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Sample records for kepler space mission

  1. Kepler Mission

    NASA Technical Reports Server (NTRS)

    Borucki, William J.; DeVincenzi, D. (Technical Monitor)

    2002-01-01

    The first step in discovering, the extent of life in our galaxy is to determine the number of terrestrial planets in the habitable zone (HZ). The Kepler Mission is a 0.95 m aperture photometer scheduled to be launched in 2006. It is designed to continuously monitor the brightness of 100,000 solar-like stars to detect the transits of Earth-size and larger planets. The depth and repetition time of transits provide the size of the planet relative to the star and its orbital period. When combined with ground-based spectroscopy of these stars to fix the stellar parameters, the true planet radius and orbit scale, hence the relation to the HZ are determined. These spectra are also used to discover the relationships between the characteristics of planets and the stars they orbit. In particular, the association of planet size and occurrence frequency with stellar mass and metallicity will be investigated. Based on the results of the current Doppler - velocity discoveries, over a thousand giant planets will be found. Information on the albedos and densities of those giants showing transits will be obtained. At the end of the four year mission, hundreds of terrestrial planets should be discovered in and near the HZ of their stars if such planets are common. A null result would imply that terrestrial planets in the HZ occur in less than 1% of the stars and that life might be quite rare.

  2. Hubble Space Telescope Parallel Observations Supporting the Kepler Mission

    NASA Astrophysics Data System (ADS)

    Caldwell, J.; Borucki, W.

    1999-09-01

    Kepler will detect Earth-like planets by monitoring 100,000 stars over four years for planetary transits. The required photometric precision is one part in 100.000. It is expected that if such ``Earths" are common, about 200 will be detected. In order to achieve the necessary precision, Kepler will be intentionally unfocussed, spreading the light of a single star over an area of 25 pixels. This will minimize the effect of space-craft jitter on photon counting. However, it will also allow the possibility of confusion with background objects which may be in the line of sight to a Kepler target. The greatest concern is that there may be a distant eclipsing binary star which could introduce a photometric signature that is similar to a planetary transit. For the brightest stars in Kepler's intended magnitude range, which is 9 to 14 mv, this will not be serious, because the profiles are different: eclipses have a ``V" shape, transits are flat-bottomed, and Kepler will differentiate the two. However, in this magnitude range, the number of stars per magnitude doubles at each fainter magnitude. More than half of Kepler's discoveries will be in the magnitude which is the faintest in which the precision of the photometry will be able to reveal a transit. That is, most of the discoveries will be low signal to noise events, in which the reality of a small decrease in the light from the region of the target star is certain, but the details of the decrease are not. Hubble Space Telescope images indicate there will be, on average, 0.5 background objects in the magnitude range that could be a problem for Kepler in the 25 pixel blur region of Kepler's optics. Approximately half of the stars will be binaries. The probability that a binary will be eclipsing is the same as that a planetary orbit will be transitting. In order to reduce the chance of a misidentification, various strategies can be used. Rather than integrating the signal over the 25 pixels and returning only the sum, the

  3. Lessons Learned from the Kepler Mission and Space Telescope Management

    NASA Technical Reports Server (NTRS)

    Fanson, James

    2010-01-01

    This paper presents lessons learned over the course of several space telescope mission and instrument developments spanning two decades. These projects involved astronomical telescopes developed by the National Aeronautics and Space Administration (NASA) and were designed to further our understanding of the Universe. It is hoped that the lessons drawn from these experiences may be of use to future mission developers.

  4. Kepler's Third Law and NASA's Kepler Mission

    NASA Astrophysics Data System (ADS)

    Gould, Alan; Komatsu, Toshi; DeVore, Edna; Harman, Pamela; Koch, David

    2015-04-01

    NASA's Kepler Mission (Fig. 1) has been wildly successful in discovering exoplanets. This paper summarizes the mission goals, briefly explains the transit method of finding exoplanets and design of the mission, provides some key findings, and describes useful education materials available at the Kepler website.

  5. Kepler's Third Law and NASA's "Kepler Mission"

    ERIC Educational Resources Information Center

    Gould, Alan; Komatsu, Toshi; DeVore, Edna; Harman, Pamela; Koch, David

    2015-01-01

    NASA's "Kepler Mission" has been wildly successful in discovering exoplanets. This paper summarizes the mission goals, briefly explains the transit method of finding exoplanets and design of the mission, provides some key findings, and describes useful education materials available at the "Kepler" website.

  6. AUTOMATED CLASSIFICATION OF VARIABLE STARS IN THE ASTEROSEISMOLOGY PROGRAM OF THE KEPLER SPACE MISSION

    SciTech Connect

    Blomme, J.; Debosscher, J.; De Ridder, J.; Aerts, C.; Gilliland, R. L.; Christensen-Dalsgaard, J.; Kjeldsen, H.; Brown, T. M.; Borucki, W. J.; Koch, D.; Jenkins, J. M.; Stello, D.; Derekas, A.; Stevens, I. R.; Suran, M. D.

    2010-04-20

    We present the first results of the application of supervised classification methods to the Kepler Q1 long-cadence light curves of a subsample of 2288 stars measured in the asteroseismology program of the mission. The methods, originally developed in the framework of the CoRoT and Gaia space missions, are capable of identifying the most common types of stellar variability in a reliable way. Many new variables have been discovered, among which a large fraction are eclipsing/ellipsoidal binaries unknown prior to launch. A comparison is made between our classification from the Kepler data and the pre-launch class based on data from the ground, showing that the latter needs significant improvement. The noise properties of the Kepler data are compared to those of the exoplanet program of the CoRoT satellite. We find that Kepler improves on CoRoT by a factor of 2-2.3 in point-to-point scatter.

  7. Kepler Mission: Current Status

    NASA Astrophysics Data System (ADS)

    Borucki, William J.; Koch, D. G.; Lissauer, J. J.; Bryson, S.; Natalie, B.; Caldwell, D. A.; DeVore, E.; Jenkins, J. M.; Christensen-Dalsgaard, J.; Cochran, W. D.; Dunham, E. W.; Gautier, T. N.; Geary, J. C.; Latham, D. W.; Sasselov, D.; Gilliland, R. L.; Gould, A.; Howell, S. B.; Monet, D. G.

    2007-12-01

    Kepler is a Discovery-class mission designed to determine the frequency of Earth-size planets in and near the habitable zone of solar-like stars. The instrument consists of a high precision photometer with Schmidt-type optics and a focal plane containing 95 million pixels to monitor over 100,000 stars to search for patterns of transits generated by planets as small as Mars. The recent reduction in the mission duration is discussed with regard to the impact on the expected science product and null statistics. Both terrestrial and giant planets discoveries will be followed up with ground-based Doppler-velocity observations to determine mass and density. The first meeting of Kepler Asteroseismic Science Consortium was held in Paris to organize an international team to analyze the Kepler data to determine the characteristics of the brighter target stars including their size and age. Stellar size determinations accurate to a few percent are expected. These will allow very accurate planet sizes to be determined from the depth of the transit signals. NASA HQ received thirty six proposals for the Participating Scientist Program and chose several new members to join the Science Team. Both the 0.95 m Schmidt corrector and 1.4 m aperture primary mirror have been completed and delivered for integration into the photometer. The focal plane with forty-two science CCD detectors and their processing electronics has been assembled and tested. The spacecraft assembly has begun with the mounting of the reaction control system, reaction wheels, attitude determination & control system, and power systems. Both the photometer and spacecraft are nearing final assembly with all subsystems having passed their environmental and performance testing. The photometer to spacecraft integration will begin this spring. The Mission is on schedule for a launch in February 2009. The Kepler Mission is funded by the NASA Astrophysics Division, Science Mission Directorate.

  8. Kepler Mission Development Challenges and Early Results

    NASA Technical Reports Server (NTRS)

    Fanson, J.

    2011-01-01

    Kepler is NASA`s first mission capable of detecting Earth-size planets orbiting in the habitable zone of stars other than the sun. Kepler comprises a space telescope designed to continuously monitor the brightnesses of more than 100,000 target stars, and a ground segment to analyze the measured stellar light curves and detect the signatures of orbiting planets. In order to detect Earth-size planets orbiting Sun-like stars Kepler was designed to provide unprecedented photometric sensitivity and stability. This paper addresses some of the technical challenges encountered during the development of the Kepler mission and the measures taken to overcome them. Early scientific results are summarized.

  9. Kepler Mission Development Challenges and Early Results

    NASA Technical Reports Server (NTRS)

    Fanson, J.; Duren, R.; Frerking, M.

    2011-01-01

    Kepler is NASA s first mission capable of detecting Earth-size planets orbiting in the habitable zone of stars other than the Sun. Kepler comprises a space telescope designed to continuously monitor the brightnesses of more than 100,000 target stars, and a ground segment to analyze the measured stellar light curves and detect the signatures of orbiting planets. In order to detect Earth-size planets orbiting Sun-like stars Kepler was designed to provide unprecedented photometric sensitivity and stability. This paper addresses some of the technical challenges encountered during the development of the Kepler mission and the measures taken to overcome them. Early scientific results are summarized.

  10. Kepler Mission Design

    NASA Technical Reports Server (NTRS)

    Koch, David; Borucki, William; Lissauer, J.; Mayer, David; Voss, Janice; Basri, Gibor; Gould, Alan; Brown, Timothy; Cockran, William; Caldwell, Douglas

    2005-01-01

    The Kepler Mission is in the development phase with launch planned for 2007. The mission goal first off is to reliably detect a significant number of Earth-size planets in the habitable zone of solar-like stars. The mission design allows for exploring the diversity of planetary sizes, orbital periods, stellar spectral types, etc. In this paper we describe the technical approach taken for the mission design; describing the flight and ground system, the detection methodology, the photometer design and capabilities, and the way the data are taken and processed. (For Stellar Classification program. Finally the detection capability in terms of planet size and orbit are presented as a function of mission duration and stellar type.

  11. KEPLER Mission: development and overview.

    PubMed

    Borucki, William J

    2016-03-01

    The Kepler Mission is a space observatory launched in 2009 by NASA to monitor 170,000 stars over a period of four years to determine the frequency of Earth-size and larger planets in and near the habitable zone of Sun-like stars, the size and orbital distributions of these planets, and the types of stars they orbit. Kepler is the tenth in the series of NASA Discovery Program missions that are competitively-selected, PI-directed, medium-cost missions. The Mission concept and various instrument prototypes were developed at the Ames Research Center over a period of 18 years starting in 1983. The development of techniques to do the 10 ppm photometry required for Mission success took years of experimentation, several workshops, and the exploration of many 'blind alleys' before the construction of the flight instrument. Beginning in 1992 at the start of the NASA Discovery Program, the Kepler Mission concept was proposed five times before its acceptance for mission development in 2001. During that period, the concept evolved from a photometer in an L2 orbit that monitored 6000 stars in a 50 sq deg field-of-view (FOV) to one that was in a heliocentric orbit that simultaneously monitored 170,000 stars with a 105 sq deg FOV. Analysis of the data to date has detected over 4600 planetary candidates which include several hundred Earth-size planetary candidates, over a thousand confirmed planets, and Earth-size planets in the habitable zone (HZ). These discoveries provide the information required for estimates of the frequency of planets in our galaxy. The Mission results show that most stars have planets, many of these planets are similar in size to the Earth, and that systems with several planets are common. Although planets in the HZ are common, many are substantially larger than Earth.

  12. Planet Detection: The Kepler Mission

    NASA Astrophysics Data System (ADS)

    Jenkins, Jon M.; Smith, Jeffrey C.; Tenenbaum, Peter; Twicken, Joseph D.; Van Cleve, Jeffrey

    2012-03-01

    and another 1100 pixels containing virtual smear measurements used to remove artifacts caused by the lack of a shutter and a finite 0.51-s readout time; and 1070 trailing black measurements that monitor the bias voltage presented at the input of the analog-to-digital converter so that the zero point can be restored to the digitized data during processing [24]. There are a total of up to 6,092,680 pixels containing the stellar and collateral data collected for each LC, with 48 LCs/day. While only 512 SC targets are defined at any given time, there are 30 SC intervals for each LC interval, and an average of 85 pixels are allocated for each SC target star. Smear and black-level measurements are collected for each SC target, but only for the rows and columns occupied by SC stellar target pixels. Approximately 21% of the pixel data returned by Kepler are SC data. The total data rate for both LC and SC data is 1.3 GB/day when the data are expanded to 4 bytes/pixel from the compressed bit stream. Raw pixel data are downlinked at monthly intervals through National Aeronautics and Space Administration's (NASA's) Deep Space Network (DSN) and routed through the ground system to the Kepler Science Operations Center (SOC) at NASA Ames Research Center. The SOC performs a number of critical functions for the mission, including management of the target definitions which specify the pixels needed for each stellar target and the compression tables that allow a ˜5:1 compression of the science data onboard the SSR (from 23 bits/pixel to 4.6 bits/pixel), but its two major tasks are to: 1. Process raw pixel data to produce archival science data products, including calibrated pixels, measurements of the location or centroid of each star in each frame, flux time series representing the brightness of each star in each data frame, and systematic error-corrected flux time series that have instrumental artifacts removed. 2. Search each target-star light curve to identify transit-like features

  13. NASA's Kepler Mission Announces Latest Discoveries

    NASA Video Gallery

    Scientists from NASA's Kepler mission have been busy recently. The team has announced the discovery of Kepler-22b, its first confirmed planet in the habitable zone of its solar system, 600 light ye...

  14. Comparison of the Kepler and Eddington Missions

    NASA Technical Reports Server (NTRS)

    Borucki, William J.; DeVincenzi, D. (Technical Monitor)

    2002-01-01

    The Kepler and Eddington missions are spaceborne photometric missions with similar apertures. Both are capable of finding Earth-size extrasolar planets and both can detect p-mode oscillations in stars. The Kepler mission is optimized to find Earth-size planets in the habitability zone of Solar-like stars and does astroseismology only as incidental science. The Eddington mission appears to be optimized for astroseismology. The Kepler design provides a very large field of view, a low measurement cadence, a heliocentric orbit, and a long mission duration. The demand for a large field-of-view results in a Schmidt design with a massive corrector. However, the use of the corrector allows a 105 square degree FOV and thereby provides 15 times the number of stars at a given magnitude than does the optical design used in Eddington. Because Kepler stares at a single FOV throughout the mission, it does much less astroseismology than Eddington. Other comparisons are also discussed.

  15. The Kepler Project: Mission Update

    NASA Technical Reports Server (NTRS)

    Borucki, William J.; Koch, David G.

    2009-01-01

    Kepler is a Discovery-class mission designed to determine the frequency of Earth-size planets in and near the habitable zone of solar-like stars. The instrument consists of a 0.95 m aperture photometer designed to obtain high precision photometric measurement of > 100,000 stars to search for patterns of transits. The focal plane of the Schmidt-telescope contains 42 CCDs with at total of 95 mega pixels that cover 116 square degrees of sky. The photometer was launched into an Earth-trailing heliocentric orbit on March 6, 2009, finished its commissioning on May 12, and is now in the science operations mode. During the commissioning of the Kepler photometer, data were obtained at a 30 minute cadence for 53,000 stars for 9.7 days. Although the data have not yet been corrected for the presence of systematic errors and artifacts, the data show the presence of hundreds of eclipsing binary stars and variable stars of amazing variety. To provide some estimate of the capability of the photometer, a quick analysis of the photometric precision was made. Analysis of the commissioning data also show transits, occultations and light emitted from the known exoplanet HAT-P7b. The data show a smooth rise and fall of light: from the planet as it orbits its star, punctuated by a drop of 130 +/- 11 ppm in flux when the planet passes behind its star. We interpret this as the phase variation of the dayside thermal emission plus reflected light from the planet as it orbits its star and is occulted. The depth of the occultation is similar in amplitude to that expected from a transiting Earth-size planet and demonstrates that the Mission has the precision necessary to detect such planets.

  16. Kepler Mission Website: Portal to the International Year of Astronomy

    NASA Astrophysics Data System (ADS)

    Harman, Pamela; DeVore, E.; Gould, A.; Koch, D.

    2008-05-01

    The 400th anniversary of Galileo's telescope is an opportunity to turn the public's eyes skyward and to the universe beyond the solar system. The Kepler Mission, launching in 2009, the International Year of Astronomy (IYA) will is specifically designed to survey our region of the Milky Way galaxy to detect and characterize hundreds of Earth-size and smaller planets in or near the habitable zone, using the transit method of detection. The habitable zone encompasses the distances from a star where liquid water can exist on a planet's surface. Results from this mission will allow us to place our solar system within the continuum of planetary systems in the Galaxy. The Kepler Mission is a NASA Discovery Program Mission. The Kepler Mission website http://www.kepler.arc.nasa.gov/ offers classroom activity lesson plans Detecting Planet Transits, The Human Orrery, and Morning Star and Evening Star. The activities are suitable for the informal science education realm. The spacecraft paper model and LEGO model orrerey can be used in the classroom by teachers or at home by families. The mission simulation and animation, as well as lessons and models highlight the science concepts critical to employing the transit method of detection, Kepler's Laws. The Send Your Name to Space on Kepler Spacecraft provides a certificate of participation for all individuals that submit there name to be listed on a DVD placed on the spacecraft. This poster will provide details on each of the items described.

  17. Kepler Mission: A Technical Overview

    NASA Technical Reports Server (NTRS)

    Borucki, W. J.

    2003-01-01

    The Kepler Mission is a Discovery-class mission designed to continuously monitor the brightness of 100,000 solar-like stars to detect the transits of Earth-size and larger planets. It is a wide field of view photometer Schmidt-type telescope with an array of 42 CCDs. It has a 0.95 m aperture and 1.4 m primary and is designed to attain a photometric precision of 2 parts in 10(exp 5) for 12th magnitude solar-like stars for a 6 hr transit duration. It will continuously observe 100,000 main-sequence stars from 9th to 14th magnitude in the Cygnus constellation for a period of four years with a cadence of 4/hour. An additional 250 stars can be monitored at a cadence of l/minute to do astro-seismology of stars brighter than 11.5 mv. The photometer is scheduled to be launched into heliocentric orbit in 2007. A ground-based program to classify all 225,000 stars in the FOV and to do a detailed examination of a subset of the stars that show planetary companions is also planned.

  18. Celebrating 400 Years of Astronomia Nova: Johannes Kepler, the Kepler Mission, and the International Year of Astronomy

    NASA Astrophysics Data System (ADS)

    Devore, E. K.; Koch, D.; Gould, A.; Harman, P. K.

    2008-12-01

    The International Year of Astronomy 2009 is an occasion to celebrate astronomy around the world. In addition to honoring Galileo and the invention of the astronomical telescope, 2009 is the 400th anniversary year of Kepler's publication of the Astronomia Nova containing his first two laws of planetary motion. In recognition of Kepler's accomplishment, the first NASA mission capable of detecting Earth-size and smaller planets in the habitable zone of stars has been named after Johannes Kepler. The Kepler Mission launches in the spring of 2009 and will search for evidence of extrasolar planets as they transit--pass in front of--their parent stars. Using Kepler's Laws, scientists will interpret the Mission data to characterize the planets that are discovered. The Kepler Mission is conducting several Educational and Public Outreach (E/PO) activities leading up to and during IYA. Among these are the Name In Space project which offers participants the opportunity to send their name into space along with a statement about the importance of searching for extrasolar Earths. The Kepler Star Wheel (planisphere) shows both the Kepler field of view and naked eye stars with known planetary systems. A series of StarDate programs will be broadcast in English and Spanish. Inquiry-based classroom lessons suitable for middle and high school science classes are available for download at the website, and on the Kepler Mission poster. The Kepler Mission poster will be distributed to middle and high school science teachers through the National Science Teacher's Association and other science teacher organizations. Copies will be available at AGU. The Kepler EPO team is presenting pre-launch teacher workshops at several locations around the US. Details about the workshop, and event timeline will be presented. For further information on the Kepler Mission, its E/PO program, and online resources, please visit: http://Kepler.NASA.gov.

  19. Celebrating 400 Years of Astronomia Nova: Johannes Kepler, the Kepler Mission, and the International Year of Astronomy

    NASA Astrophysics Data System (ADS)

    DeVore, Edna; Koch, D.; Gould, A.; Harman, P.

    2009-01-01

    The International Year of Astronomy 2009 is an occasion to celebrate astronomy around the world. In addition to honoring Galileo and the invention of the astronomical telescope, 2009 is the 400th anniversary year of Kepler's publication of the Astronomia Nova containing his first two laws of planetary motion. In recognition of Kepler's accomplishment, the first NASA mission capable of detecting Earth-size and smaller planets in the habitable zone of stars has been named after Johannes Kepler. The Kepler Mission launches in the spring of 2009 and will search for evidence of extrasolar planets as they transit--pass in front of--their parent stars. Using Kepler's Laws, scientists will interpret the Mission data to characterize the planets that are discovered. The Kepler Mission is conducting several Educational and Public Outreach (E/PO) activities leading up to and during IYA. Among these are the "Name In Space” project which offers participants the opportunity to send their name into space along with a statement about the importance of searching for extrasolar Earths. The "Kepler Star Wheel” (planisphere) shows both the Kepler field of view and naked eye stars with known planetary systems. A series of StarDate programs will be broadcast in English and Spanish. Inquiry-based classroom lessons suitable for middle and high school science classes are available for download at the website, and on the Kepler Mission poster. The Kepler Mission poster will be distributed to middle and high school science teachers through the National Science Teacher's Association and other science teacher organizations. Copies will be available at AAS. The Kepler EPO team is presenting pre-launch teacher workshops at several locations around the US. Details about the workshop, and event timeline will be presented. For further information on the Kepler Mission, its E/PO program, and online resources, please visit: http://kepler.nasa.gov. Funded by NASA's Science Mission Directorate.

  20. Exploring exoplanet populations with NASA's Kepler Mission.

    PubMed

    Batalha, Natalie M

    2014-09-02

    The Kepler Mission is exploring the diversity of planets and planetary systems. Its legacy will be a catalog of discoveries sufficient for computing planet occurrence rates as a function of size, orbital period, star type, and insolation flux. The mission has made significant progress toward achieving that goal. Over 3,500 transiting exoplanets have been identified from the analysis of the first 3 y of data, 100 planets of which are in the habitable zone. The catalog has a high reliability rate (85-90% averaged over the period/radius plane), which is improving as follow-up observations continue. Dynamical (e.g., velocimetry and transit timing) and statistical methods have confirmed and characterized hundreds of planets over a large range of sizes and compositions for both single- and multiple-star systems. Population studies suggest that planets abound in our galaxy and that small planets are particularly frequent. Here, I report on the progress Kepler has made measuring the prevalence of exoplanets orbiting within one astronomical unit of their host stars in support of the National Aeronautics and Space Administration's long-term goal of finding habitable environments beyond the solar system.

  1. Management and Systems Engineering of the Kepler Mission

    NASA Technical Reports Server (NTRS)

    Fanson, James; Livesay, Leslie; Frerking, Margaret; Cooke, Brian

    2010-01-01

    Kepler is the National Aeronautics and Space Administration's (NASA's) first mission capable of detecting Earth-size planets orbiting in the habitable zones around stars other than the sun. Selected for implementation in 2001 and launched in 2009, Kepler seeks to determine whether Earth-like planets are common or rare in the galaxy. The investigation requires a large, space-based photometer capable of simultaneously measuring the brightnesses of 100,000 stars at part-per-million level of precision. This paper traces the development of the mission from the perspective of project management and systems engineering and describes various methodologies and tools that were found to be effective. The experience of the Kepler development is used to illuminate lessons that can be applied to future missions.

  2. Take off with NASA's Kepler Mission!: The Search for Other "Earths"

    ERIC Educational Resources Information Center

    Koch, David; DeVore, Edna K.; Gould, Alan; Harman, Pamela

    2009-01-01

    Humans have long wondered about life in the universe. Are we alone? Is Earth unique? What is it that makes our planet a habitable one, and are there others like Earth? NASA's Kepler Mission seeks the answers to these questions. Kepler is a space-based, specially designed 0.95 m aperture telescope. Launching in 2009, Kepler is NASA's first mission…

  3. Kepler Mission: A Search for Habitable Planets

    NASA Technical Reports Server (NTRS)

    Koch, David; Fonda, Mark (Technical Monitor)

    2002-01-01

    The Kepler Mission was selected by NASA as one of the next two Discovery Missions. The mission design is based on the search for Earth-size planets in the habitable zone of solar-like stars, but does not preclude the discovery of larger or smaller planets in other orbits of non-solar-like stars. An overview of the mission, the scientific goals and the anticipated results will be presented.

  4. Kepler Mission Development Challenges and Early Results

    NASA Technical Reports Server (NTRS)

    Fanson, James; Frerking, Margaret; Duren, Riley

    2011-01-01

    Kepler is NASA s first mission capable of detecting Earthsize planets orbiting in Habitable Zone of Sun-like stars. Objective is to measure how frequently planets of various sizes and orbits form around stars in the Milky Way. Kepler detects planets by measuring drop in brightness of star due to "transit" of a planet Earth-size planet transiting Sunlike star causes drop in brightness of only 84 parts per million

  5. Kepler as a Binary Star Mission

    NASA Astrophysics Data System (ADS)

    di Stefano, Rosanne

    2010-12-01

    The Kepler observatory was designed to discover transits by Earth-like planets orbiting Sun-like stars. Its first major discoveries, however, are hot objects in close orbits around main-sequence stars. These are likely to be white-dwarf remnants of stars that have transferred mass to the present-day main sequence stars. These particular main-sequence stars are among the Kepler targets because they are bright. The question is: how many of the other Kepler target stars are also orbited by white dwarfs? We have shown that several hundred white dwarfs are likely to transit the Kepler target stars during the mission. In some cases, the signature will be dominated by gravitational lensing, producing distinctive ``antitransits''. Neutron stars and black holes may also be discovered this way. The lensing signature provides a measurement of the gravitational mass of the compact object. Through the discovery of both transits and antitransits caused by white dwarfs, Kepler will discover and study binaries that have already experienced a phase of mass transfer or a common envelope phase. Thus, Kepler will become a premier tool for the study of interacting binaries. During the next phase of interaction, some of the Kepler binaries may become nuclear-burning white dwarfs, and may be candidates for Type Ia supernovae or accretion-induced collapse.

  6. Eclipsing Binaries from the Kepler Mission

    NASA Technical Reports Server (NTRS)

    Koch, David; Borucki, William; Lissauer, J.; Basri, Gibor; Brown, Timothy; Caldwell, Douglas; Cochran, William; Jenkins, Jon; Dunham, Edward; Gautier, Nick

    2005-01-01

    The Kepler Mission is a photometric space mission that will continuously observe a single 100 sq deg field of view (FOV) of greater than 100,000 stars in the Cygnus-Lyra region for 4 or more years with a precision of 14 ppm (R=12). The primary goal of the mission is to detect Earth-size planets in the habitable zone of solar-like stars. In the process, many eclipsing binaries (EB) will also be detected. Prior to launch, the stellar characteristics will have been detennined for all the stars in the FOV with R<16. As part of the verification process, stars with transits <5% will need to have follow-up radial velocity observations performed to determine the component masses and thereby separate transits caused by stellar companions from those caused by planets. The result will be a rich database on EBs. The community will have access to the archive for uses such as for EB modeling of the high-precision light curves. A guest observer program is also planned for objects not already on the target list.

  7. KEPLER MISSION STELLAR AND INSTRUMENT NOISE PROPERTIES

    SciTech Connect

    Gilliland, Ronald L.; Chaplin, William J.; Elsworth, Yvonne P.; Miglio, Andrea; Dunham, Edward W.; Argabright, Vic S.; Borucki, William J.; Bryson, Stephen T.; Koch, David G.; Walkowicz, Lucianne M.; Basri, Gibor; Buzasi, Derek L.; Caldwell, Douglas A.; Jenkins, Jon M.; Van Cleve, Jeffrey; Welsh, William F.

    2011-11-01

    Kepler mission results are rapidly contributing to fundamentally new discoveries in both the exoplanet and asteroseismology fields. The data returned from Kepler are unique in terms of the number of stars observed, precision of photometry for time series observations, and the temporal extent of high duty cycle observations. As the first mission to provide extensive time series measurements on thousands of stars over months to years at a level hitherto possible only for the Sun, the results from Kepler will vastly increase our knowledge of stellar variability for quiet solar-type stars. Here, we report on the stellar noise inferred on the timescale of a few hours of most interest for detection of exoplanets via transits. By design the data from moderately bright Kepler stars are expected to have roughly comparable levels of noise intrinsic to the stars and arising from a combination of fundamental limitations such as Poisson statistics and any instrument noise. The noise levels attained by Kepler on-orbit exceed by some 50% the target levels for solar-type, quiet stars. We provide a decomposition of observed noise for an ensemble of 12th magnitude stars arising from fundamental terms (Poisson and readout noise), added noise due to the instrument and that intrinsic to the stars. The largest factor in the modestly higher than anticipated noise follows from intrinsic stellar noise. We show that using stellar parameters from galactic stellar synthesis models, and projections to stellar rotation, activity, and hence noise levels reproduce the primary intrinsic stellar noise features.

  8. Kepler Mission Discovers Trove of Extrasolar Planet Candidates

    NASA Astrophysics Data System (ADS)

    Showstack, Randy

    2011-02-01

    NASA's Kepler discovery mission is collecting more than just pennies from heaven. Results from the first 4 months of science operations of the Kepler space telescope, announced on 2 February, include the discovery of 1235 candidate planets orbiting 997 stars in a small portion of the Milky Way galaxy examined by the telescope. Follow-up observations likely could confirm about 80% of the candidates as actual planets rather than false positives, according to researchers. This new trove of possible exoplanets could greatly expand the number of known planets outside of our solar system.

  9. Data Processing and Archiving Software for the Kepler Mission

    NASA Astrophysics Data System (ADS)

    Swam, M. S.; Swade, D.; Sontag, C.; Heller-Boyer, C.; Gaffney, N.; Kidwell, R.

    2007-10-01

    The Kepler Mission, a NASA Discovery mission scheduled for launch in 2008 November, will survey a 105 deg^2 field of view in the Cygnus-Lyra region of the Milky Way galaxy to detect and characterize hundreds of Earth-size planets in or near the habitable zone. The Kepler Data Management Center at the Space Telescope Science Institute (STScI) will provide the data processing and archiving functions for the mission. Data processing consists of converting spacecraft telemetry into FITS data products, populating header keywords, and basic calibration of the data. The archive will save the original telemetry and science data products in several different forms to serve the principal investigator, guest observers, and the astronomical community at large. Extensive re-use of proven, multi-mission data processing and archive systems developed at STScI for the Hubble Space Telescope project will greatly reduce the development effort for the Kepler mission, and should result in fewer operational problems. This paper will discuss the software architecture and re-use plans for these systems.

  10. Kepler & K2: One spacecraft, Two Missions

    NASA Astrophysics Data System (ADS)

    Batalha, Natalie

    2015-12-01

    This year, we mark twenty years of exploring the diversity of planets and planetary systems orbiting main sequence stars. Exoplanet discoveries spill into the thousands, and the sensitivity boundaries continue to expand. NASA's Kepler Mission unveiled a galaxy replete with small planets and revealed populations that don't exist in our own solar system. The mission has yielded a sample sufficient for computing planet occurrence rates as a function of size, orbital period, and host star properties. We've learned that every late-type star has at least one planet on average, that terrestrial-sized planets are more common than larger planets within 1 AU, and that the nearest, potentially habitable earth-sized planet is likely within 5pc. After four years of continuous observations, the Kepler prime mission ended in May 2013 with the loss of a second reaction wheel. Thanks to innovative engineering, the spacecraft gained a second lease on life and emerged as the ecliptic surveyor, K2. In many regards, K2 is a distinctly new mission, not only by pointing at new areas of the sky but also by focusing on community-driven goals that diversify the science yield. For exoplanets, this means targeting bright and low mass stars -- the populations harboring planets amenable to dynamical and atmospheric characterization. To date, the mission has executed 7 observing campaigns lasting ~80 days each and has achieved a 6-hour photometric precision of 30 ppm. A couple dozen planets have been confirmed, including two nearby (< 50 pc) systems on the watch-list for future JWST campaigns. While Kepler prime is setting the stage for the direct imaging missions of the future, K2 is easing us into an era of atmospheric characterization -- one spacecraft, two missions, and a bright future for exoplanet science.

  11. Latest Results from the Kepler Mission

    NASA Astrophysics Data System (ADS)

    Borucki, William J.; Kepler Mission Team

    2012-10-01

    As the Kepler Mission completes the end of its third year of science observations, calibrated time series data of increasing length are becoming available that make possible the detection of planetary candidates smaller than Earth and candidates with orbital periods nearing one year. Further, the greater capability and sophistication of the pipeline analyses improve the completeness of the results and provide better estimates of the parameter distributions. The most recent data release on 28 July 2012 (Quarters 6 through 9) adds an additional ¾ year of observations so that most planetary candidates with orbital periods as long as 273 days now show at least 3 transits. Data for an additional year (i.e., Quarters 10 through 13) are scheduled to be released on 28 October 2012. A first look at the size, period, and semi-major axis distributions of these data will be presented. Summaries of the planets confirmed, candidates that are being actively analyzed, and the methods being used to verify and confirm planets will be discussed. The Extended Kepler Mission operations begin on 1 October 2012 and many changes in mission focus and operations, data release, and science community participation are being implemented and will be outlined. Funding for this Discovery mission is provided by NASA's Science Mission Directorate.

  12. Variable Stars with the Kepler Space Telescope

    NASA Astrophysics Data System (ADS)

    Molnár, L.; Szabó, R.; Plachy, E.

    2016-12-01

    The Kepler space telescope has revolutionized our knowledge about exoplanets and stars and is continuing to do so in the K2 mission. The exquisite photometric precision, together with the long, uninterrupted observations opened up a new way to investigate the structure and evolution of stars. Asteroseismology, the study of stellar oscillations, allowed us to investigate solar-like stars, and to peer into the insides of red giants and massive stars. But many discoveries have been made about classical variable stars, too, ranging from pulsators like Cepheids and RR Lyraes to eclipsing binary stars and cataclysmic variables, and even supernovae. In this review, which is far from an exhaustive summary of all results obtained with Kepler, we collected some of the most interesting discoveries, and ponder on the role for amateur observers in this golden era of stellar astrophysics.

  13. Planet Hunters in the Kepler Extended Mission

    NASA Astrophysics Data System (ADS)

    Schwamb, Megan E.; Lintott, C. J.; Fischer, D.; Brewer, J. M.; Giguere, M. J.; Lynn, S.; Parrish, M.; Schawinski, K.; Simpson, R.; Smith, A. M.; Orosz, J. A.; Carter, J. A.; Howard, A.; Torres, G.; Crepp, J. R.; Keel, W. C.; Welsh, W. F.; Kaib, N. A.; Terrell, D.; Gagliano, R.; Jek, K. J.

    2013-01-01

    Planet Hunters (http://www.planethunters.org), part of the Zooniverse's (http://www.zooniverse.org) collection of online citizen science projects, uses the World Wide Web to enlist the general public to identify transits in the Kepler light curves. Volunteers are asked to draw boxes to mark the locations of visible transits, with multiple independent classifiers reviewing a randomly selected ~30-day light curve segment from one of Kepler's ~160,000 target stars. Since December 2010, more than 170,000 members of the general public have participated in Planet Hunters contributing over 13 million classifications. With the start of the Kepler extended mission, Planet Hunters has entered a new phase. We will detail the upgrades and new features added to the project, highlighting in particular our search for circumbinary planets (planets orbiting both stars in binary) in the the extended mission Quarterly data releases. We will also report on our latest planet candidates, including the characterization of our first confirmed planet candidate, a circumbinary planet in a four star system. Acknowledgements: MES is supported by a National Science Foundation Astronomy and Astrophysics Postdoctoral Fellowship under award AST-1003258 and in part by an American Philosophical Society Franklin Grant.

  14. Testing the asymptotic relation for period spacings from mixed modes of red giants observed with the Kepler mission

    NASA Astrophysics Data System (ADS)

    Buysschaert, B.; Beck, P. G.; Corsaro, E.; Christensen-Dalsgaard, J.; Aerts, C.; Arentoft, T.; Kjeldsen, H.; García, R. A.; Silva Aguirre, V.; Degroote, P.

    2016-04-01

    Context. Dipole mixed pulsation modes of consecutive radial order have been detected for thousands of low-mass red-giant stars with the NASA space telescope Kepler. These modes have the potential to reveal information on the physics of the deep stellar interior. Aims: Different methods have been proposed to derive an observed value for the gravity-mode period spacing, the most prominent one relying on a relation derived from asymptotic pulsation theory applied to the gravity-mode character of the mixed modes. Our aim is to compare results based on this asymptotic relation with those derived from an empirical approach for three pulsating red-giant stars. Methods: We developed a data-driven method to perform frequency extraction and mode identification. Next, we used the identified dipole mixed modes to determine the gravity-mode period spacing by means of an empirical method and by means of the asymptotic relation. In our methodology we consider the phase offset, ɛg, of the asymptotic relation as a free parameter. Results: Using the frequencies of the identified dipole mixed modes for each star in the sample, we derived a value for the gravity-mode period spacing using the two different methods. These values differ by less than 5%. The average precision we achieved for the period spacing derived from the asymptotic relation is better than 1%, while that of our data-driven approach is 3%. Conclusions: Good agreement is found between values for the period spacing derived from the asymptotic relation and from the empirical method. The achieved uncertainties are small, but do not support the ultra-high precision claimed in the literature. The precision from our data-driven method is mostly affected by the differing number of observed dipole mixed modes. For the asymptotic relation, the phase offset, ɛg, remains ill defined, but enables a more robust analysis of both the asymptotic period spacing and the dimensionless coupling factor. However, its estimation might

  15. Scientific Issues Addressed by the Kepler Mission

    NASA Technical Reports Server (NTRS)

    Bourcki, W. J.; Koch, D. G.; Lissauer, J. J.; Jenkins, J. M.; DeVincenzi, Donald L. (Technical Monitor)

    1998-01-01

    The Kepler Mission uses a wide field-of-view telescope to photometrically monitor 100,000 main-sequence stars for evidence of planetary transits. Because of the large number of stars monitored and because the mission is designed with a precision (0.002%) sufficient to readily recognize Earth-size planets transiting solar-like stars, several hundred Earth-size planets should be found. Based on the the Dopper velocity observations that find 2% of the main-sequence stars have Jupiter-size planets in short-period orbits, the Kepler mission is also expected to detect about 2000 giant planets. Several questions about the association of planet types and stellar characteristics can be investigated. For example; Are small planets found when Jupiter-mass planets are also present in inner orbits? What is the frequency of small planets compared to Jupiter-mass planets? What is the frequency and distribution of planets intermediate in size and mass to that of Earth and Jupiter? What correlations exist between planet size, distribution, and frequency with the characteristics of the stars they orbit? A comparison between model predictions and observation should be a useful step in evolving better models of planetary system formation and help put the formation of our Solar System in perspective.

  16. The Kepler Mission and Early Results

    NASA Astrophysics Data System (ADS)

    Koch, David; Borucki, William; Jenkins, Jon; Basri, Gibor; Batalha, Natalie M.; Brown, Timothy M.; Caldwell, Douglas; Christensen-Dalsgaard, Jørgen; Cochran, William D.; Devore, Edna; Dunham, Edward W.; Gautier, Thomas N., III; Geary, John C.; Gilliland, Ronald L.; Gould, Alan; Jenkins, Jon; Latham, David W.; Lissauer, Jack J.; Marcy, Geoffrey; Monet, David; Sasselov, Dimitar; Boss, Alan; Caldwell, John; Dupree, Andrea K.; Howell, Steve B.; Kjeldsen, Hans; Meibom, Søren; Morrison, David; Tarter, Jill; Bryson, Stephen T.; Dotson, Jessie L.; Haas, Michael R.; Kolodziejczak, Jeffrey; Rowe, Jason F.; van Cleve, Jeffrey E.; Buzasi, Derek; Charbonneau, David; Doyle, Lau-Rance; Ford, Eric; Fortney, Jonathan; Holman, Matthew; Seager, Sara; Steffen, Jason; Welsh, William

    Kepler is a Discovery-class mission designed to determine the frequency of Earth-size planets in and near the habitable zone of solar-like stars. The instrument consists of a 0.95 m aperture photometer designed to obtain high-precision photometric measurement for more than 3.5 years of more than 100,000 stars to search for patterns of transits of exoplanets. The focal plane of the Schmidt telescope contains 42 CCDs with a total of 95 megapixels that cover 115 square degrees of sky. The single star field will be viewed for the entire duration of the mission. The photometer was launched into an Earth-trailing heliocentric orbit on March 6, 2009, finished its commissioning on May 12, and is now in the science operations mode. The bases for a number of the design choices are described. Although the data have not yet been fully corrected for the presence of systematic errors and artifacts, the data show the presence of thousands of eclipsing binaries and variable stars of amazing variety. The character of stellar variability allows us to distinguish dwarf stars from giants. Astrometric stability at the sub-millipixel level of the photocenters of stars allows us in many cases to distinguish transit candidates from background eclipsing binaries. Analysis of the early data shows transits, occultations and even visible light emission from the hot exoplanet HAT-P-7b. The latest results on exoplanet detections from Kepler will be presented. Funding for this mission is provided by NASA's Science Mission Directorate.

  17. The Kepler Mission and Eclipsing Binaries

    NASA Technical Reports Server (NTRS)

    Koch, David; Borucki, William; Lissauer, J.; Basri, Gibor; Brown, Timothy; Caldwell, Douglas; Cochran, William; Jenkins, Jon; Dunham, Edward; Gautier, Nick

    2006-01-01

    The Kepler Mission is a photometric mission with a precision of 14 ppm (at R=12) that is designed to continuously observe a single field of view (FOV) of greater 100 sq deg in the Cygnus-Lyra region for four or more years. The primary goal of the mission is to monitor greater than 100,000 stars for transits of Earth-size and smaller planets in the habitable zone of solar-like stars. In the process, many eclipsing binaries (EB) will also be detected and light curves produced. To enhance and optimize the mission results, the stellar characteristics for all the stars in the FOV with R less than 16 will have been determined prior to launch. As part of the verification process, stars with transit candidates will have radial velocity follow-up observations performed to determine the component masses and thereby separate eclipses caused by stellar companions from transits caused by planets. The result will be a rich database on EBs. The community will have access to the archive for further analysis, such as, for EB modeling of the high-precision light curves. A guest observer program is also planned to allow for photometric observations of objects not on the target list but within the FOV, since only the pixels of interest from those stars monitored will be transmitted to the ground.

  18. NASA's Kepler Mission Discovers Multiple Planets Orbiting Twin Suns

    NASA Video Gallery

    NASA's Kepler mission has discovered the first transiting circumbinary system -- multiple planets orbiting two suns -- 4,900 light-years from Earth, in the constellation Cygnus, proving that more t...

  19. Kepler Mission to Detect Earth-like Planets

    NASA Technical Reports Server (NTRS)

    Kondo, Yoji

    2002-01-01

    Kepler Mission to detect Earth-like planets in our Milky Way galaxy was approved by NASA in December 2001 for a 4-5 year mission. The launch is planned in about 5 years. The Kepler observatory will be placed in an Earth-trailing orbit. The unique feature of the Kepler Mission is its ability to detect Earth-like planets orbiting around solar-type stars at a distance similar to that of Earth (from our Sun); such an orbit could provide an environment suitable for supporting life as we know it. The Kepler observatory accomplishes this feat by looking for the transits of planetary object in front of their suns; Kepler has a photometric precision of 10E-5 (0.00001) to achieve such detections. Other ongoing planetary detection programs (based mostly on a technique that looks for the shifting of spectral lines of the primary star due to its planetary companions' motions around it) have detected massive planets (with masses in the range of Jupiter); such massive planets are not considered suitable for supporting life. If our current theories for the formation of planetary systems are valid, we expect to detect about 50 Earth-like planets during Kepler's 4-year mission (assuming a random distribution of the planetary orbital inclinations with respect to the line of sight from Kepler). The number of detection will increase about 640 planets if the planets to be detected are Jupiter-sized.

  20. Kepler Mission to Detect Earth-like Planets

    NASA Technical Reports Server (NTRS)

    Kondo, Yoji

    2003-01-01

    Kepler Mission to detect Earth-like planets in our Milky Way galaxy was approved by NASA in December 2001 for a 4-5 year mission. The launch is planned in about 5 years. The Kepler observatory will be placed in an Earth-trailing orbit. The unique feature of the Kepler Mission is its ability to detect Earth-like planets orbiting around solar-type stars at a distance similar to that of Earth (from our Sun); such an orbit could provide an environment suitable for supporting life as we know it. The Kepler observatory accomplishes this feat by looking for the transits of planetary object in front of their suns; Kepler has a photometric precision of 10E-5 (0.00001) to achieve such detections. Other ongoing planetary detection programs (based mostly on a technique that looks for the shifting of spectral lines of the primary star due to its planetary companions' motions around it) have detected massive planets (with masses in the range of Jupiter); such massive planets are not considered suitable for supporting life. If our current theories for the formation of planetary systems are valid, we expect to detect about 50 Earth-like planets during Kepler's 4-year mission (assuming a random distribution of the planetary orbital inclinations with respect to the line of sight from Kepler). The number of detection will increase about 640 planets if the planets to be detected are Jupiter-sized.

  1. Exoplanet Science from NASA’s Kepler Mission

    SciTech Connect

    Steffen, Jason

    2012-09-12

    NASA's exoplanet mission is the world's premier instrument for the discovery and study of planets orbiting distant stars. As the nominal mission comes to a close, Kepler has discovered nearly 2500 planet candidates, confirmed dozens of multi-planet systems, provided important insights into the orbital architectures of planetary systems, identified specific systems that challenge theories of planet formation and dynamical evolution, has revolutionized our understanding of stellar interiors, and is gearing to measure the frequency of Earth-like planets in the habitable zones of Sun-like stars in its extended mission phase. I present the most recent results from the Kepler mission.

  2. The search for ZZ Ceti stars in the original Kepler mission

    NASA Astrophysics Data System (ADS)

    Greiss, S.; Hermes, J. J.; Gänsicke, B. T.; Steeghs, D. T. H.; Bell, Keaton J.; Raddi, R.; Tremblay, P.-E.; Breedt, E.; Ramsay, G.; Koester, D.; Carter, P. J.; Vanderbosch, Z.; Winget, D. E.; Winget, K. I.

    2016-04-01

    We report the discovery of 42 white dwarfs in the original Kepler mission field, including nine new confirmed pulsating hydrogen-atmosphere white dwarfs (ZZ Ceti stars). Guided by the Kepler-Isaac Newton Telescope Survey, we selected white dwarf candidates on the basis of their U - g, g - r, and r - Hα photometric colours. We followed up these candidates with high-signal-to-noise optical spectroscopy from the 4.2-m William Herschel Telescope. Using ground-based, time series photometry, we put our sample of new spectroscopically characterized white dwarfs in the context of the empirical ZZ Ceti instability strip. Prior to our search, only two pulsating white dwarfs had been observed by Kepler. Ultimately, four of our new ZZ Cetis were observed from space. These rich data sets are helping initiate a rapid advancement in the asteroseismic investigation of pulsating white dwarfs, which continues with the extended Kepler mission, K2.

  3. Exploring exoplanet populations with NASA’s Kepler Mission

    PubMed Central

    Batalha, Natalie M.

    2014-01-01

    The Kepler Mission is exploring the diversity of planets and planetary systems. Its legacy will be a catalog of discoveries sufficient for computing planet occurrence rates as a function of size, orbital period, star type, and insolation flux. The mission has made significant progress toward achieving that goal. Over 3,500 transiting exoplanets have been identified from the analysis of the first 3 y of data, 100 planets of which are in the habitable zone. The catalog has a high reliability rate (85–90% averaged over the period/radius plane), which is improving as follow-up observations continue. Dynamical (e.g., velocimetry and transit timing) and statistical methods have confirmed and characterized hundreds of planets over a large range of sizes and compositions for both single- and multiple-star systems. Population studies suggest that planets abound in our galaxy and that small planets are particularly frequent. Here, I report on the progress Kepler has made measuring the prevalence of exoplanets orbiting within one astronomical unit of their host stars in support of the National Aeronautics and Space Administration’s long-term goal of finding habitable environments beyond the solar system. PMID:25049406

  4. Kepler Planet Detection Mission: Introduction and First Results

    NASA Technical Reports Server (NTRS)

    Borucki, William; Koch, David; Basri, Gibor; Batalha, Natalie; Brown, Timothy; Lissauer, Jack J.; Morrison, David; Rowe, Jason; Bryson, Stephen T.; Dotson, Jessie; Haas,Michael; Gautier, Thomas N.

    2010-01-01

    The Kepler Mission is designed to determine the frequency of Earth-size and rocky planets in and near the habitable zone (HZ) of solar-like stars. The HZ is defined to be the region of space where a rocky planet could maintain liquid water on its surface. Kepler is the 10th competitively-selected Discovery Mission and was launched on March 6, 2009. Since completing its commissioning, Kepler has observed over 156,000 stars simultaneously and near continuously to search for planets that periodically pass in front of their host star (transit). The photometric precision is approximately 23 ppm for 50% of the 12th magnitude dwarf stars for an integration period of 6.5 hours. During the first 3 months of operation the photometer detected transit-like signatures from more than 200 stars. Careful examination shows that many of these events are false-positives such as small stars orbiting large stars or blends of target stars with eclipsing binary stars. Ground-based follow-up observations confirm the discovery of five new exoplanets with sizes between 0.37 andl.6 Jupiter radii (R(sub J)) and orbital periods ranging from 3.2 to 4.9 days. Ground-based observations with the Keck 1, Hobby-Ebberly, Hale, WIYN, MMT, Tillinghast, Shane, and Nordic Optical Telescopes are used to vet the planetary candidates and measure the masses of the putative planets. Observations of occultations and phase variations of hot, short-period planets such as HT-P-7b provide a probe of atmospheric properties. Asteroseismic analysis already shows the presence of p-mode oscillations in several stars. Such observations will be used to measure the mean stellar density and infer the stellar size and age. For stars too dim to permit asteroseismology, observations of the centroid motion of target stars will be used to measure the parallax and be combined with photometric measurements to estimate stellar sizes. Four open clusters are being observed to determine stellar rotation rates as a function of age and

  5. Kepler planet-detection mission: introduction and first results.

    PubMed

    Borucki, William J; Koch, David; Basri, Gibor; Batalha, Natalie; Brown, Timothy; Caldwell, Douglas; Caldwell, John; Christensen-Dalsgaard, Jørgen; Cochran, William D; DeVore, Edna; Dunham, Edward W; Dupree, Andrea K; Gautier, Thomas N; Geary, John C; Gilliland, Ronald; Gould, Alan; Howell, Steve B; Jenkins, Jon M; Kondo, Yoji; Latham, David W; Marcy, Geoffrey W; Meibom, Søren; Kjeldsen, Hans; Lissauer, Jack J; Monet, David G; Morrison, David; Sasselov, Dimitar; Tarter, Jill; Boss, Alan; Brownlee, Don; Owen, Toby; Buzasi, Derek; Charbonneau, David; Doyle, Laurance; Fortney, Jonathan; Ford, Eric B; Holman, Matthew J; Seager, Sara; Steffen, Jason H; Welsh, William F; Rowe, Jason; Anderson, Howard; Buchhave, Lars; Ciardi, David; Walkowicz, Lucianne; Sherry, William; Horch, Elliott; Isaacson, Howard; Everett, Mark E; Fischer, Debra; Torres, Guillermo; Johnson, John Asher; Endl, Michael; MacQueen, Phillip; Bryson, Stephen T; Dotson, Jessie; Haas, Michael; Kolodziejczak, Jeffrey; Van Cleve, Jeffrey; Chandrasekaran, Hema; Twicken, Joseph D; Quintana, Elisa V; Clarke, Bruce D; Allen, Christopher; Li, Jie; Wu, Haley; Tenenbaum, Peter; Verner, Ekaterina; Bruhweiler, Frederick; Barnes, Jason; Prsa, Andrej

    2010-02-19

    The Kepler mission was designed to determine the frequency of Earth-sized planets in and near the habitable zone of Sun-like stars. The habitable zone is the region where planetary temperatures are suitable for water to exist on a planet's surface. During the first 6 weeks of observations, Kepler monitored 156,000 stars, and five new exoplanets with sizes between 0.37 and 1.6 Jupiter radii and orbital periods from 3.2 to 4.9 days were discovered. The density of the Neptune-sized Kepler-4b is similar to that of Neptune and GJ 436b, even though the irradiation level is 800,000 times higher. Kepler-7b is one of the lowest-density planets (approximately 0.17 gram per cubic centimeter) yet detected. Kepler-5b, -6b, and -8b confirm the existence of planets with densities lower than those predicted for gas giant planets.

  6. Kepler Planet-Detection Mission: Introduction and First Results

    SciTech Connect

    Borucki, William J.; Koch, David; Basri, Gibor; Batalha, Natalie; Brown, Timothy; Caldwell, Douglas; Caldwell, John; Christensen-Dalsgaard, Jorgen; Cochran, William D.; DeVore, Edna; Dunham, Edward W.; /Lowell Observ. /Harvard-Smithsonian Ctr. Astrophys.

    2010-01-01

    The Kepler mission was designed to determine the frequency of Earth-sized planets in and near the habitable zone of Sun-like stars. The habitable zone is the region where planetary temperatures are suitable for water to exist on a planet's surface. During the first 6 weeks of observations, Kepler monitored 156,000 stars, and five new exoplanets with sizes between 0.37 and 1.6 Jupiter radii and orbital periods from 3.2 to 4.9 days were discovered. The density of the Neptune-sized Kepler-4b is similar to that of Neptune and GJ 436b, even though the irradiation level is 800,000 times higher. Kepler-7b is one of the lowest-density planets ({approx}0.17 gram per cubic centimeter) yet detected. Kepler-5b, -6b, and -8b confirm the existence of planets with densities lower than those predicted for gas giant planets.

  7. Kepler

    NASA Technical Reports Server (NTRS)

    Howell, Steve B.

    2011-01-01

    The NASA Kepler mission recently announced over 1200 exoplanet candidates. While some are common Hot Jupiters, a large number are Neptune size and smaller, transit depths suggest sizes down to the radius of Earth. The Kepler project has a fairly high confidence that most of these candidates are real exoplanets. Many analysis steps and lessons learned from Kepler light curves are used during the vetting process. This talk will cover some new results in the areas of stellar variability, solar systems with multiple planets, and how transit-like signatures are vetted for false positives, especially those indicative of small planets.

  8. Spacing of Kepler Planets: Sculpting by Dynamical Instability

    NASA Astrophysics Data System (ADS)

    Pu, Bonan; Wu, Yanqin

    2015-07-01

    We study the orbital architecture of multi-planet systems detected by the Kepler transit mission using N-body simulations, focusing on the orbital spacing between adjacent planets in systems showing four or more transiting planets. We find that the observed spacings are tightly clustered around 12 mutual Hill radii, when transit geometry and sensitivity limits are accounted for. In comparison, dynamical integrations reveal that the minimum spacing required for systems of similar masses to survive dynamical instability for as long as 1 billion yr is ∼10 if all orbits are circular and coplanar and ∼12 if planetary orbits have eccentricities of ∼0.02 (a value suggested by studies of planet transit-time variations). This apparent coincidence, between the observed spacing and the theoretical stability threshold, leads us to propose that typical planetary systems were formed with even tighter spacing, but most, except for the widest ones, have undergone dynamical instability, and are pared down to a more anemic version of their former selves, with fewer planets and larger spacings. So while the high-multiple systems (five or more transiting planets) are primordial systems that remain stable, the single or double planetary systems, abundantly discovered by the Kepler mission, may be the descendants of more closely packed high-multiple systems. If this hypothesis is correct, we infer that the formation environment of Kepler systems should be more dissipative than that of the terrestrial planets.

  9. The Kepler Mission and the International Year of Astronomy

    NASA Astrophysics Data System (ADS)

    Harman, Pamela; DeVore, E.; Gould, A.; Koch, D.

    2008-05-01

    Johannes Kepler was one of Galileo's contemporaries, publishing New Astronomy defining his first two laws, nearly 400 years ago, in 1609. It is a fitting tribute that the Kepler Mission launches in 2009. Kepler continued his studies of motion and made observations of satellites of Jupiter, and published his third law. We now recognize Kepler's laws as 1. Planets move in elliptical; 2. The planets move such that the line between the Sun and the Planet sweeps out equal areas in equal time no matter where in the orbit; and 3. The square of the period of the orbit of a planet is proportional to the mean distance from the Sun cubed. Kepler's laws were deduced empirically from the motions of the planet Mars in the early 17th century, before Newton deduced the law of gravity and his laws of motion. The Kepler Mission, a NASA Discovery mission, is specifically designed to survey our region of the Milky Way galaxy to detect and characterize hundreds of Earth-size and smaller planets in or near the habitable zone. The habitable zone encompasses the distances from a star where liquid water can exist on a planet's surface. Results from this mission will allow us to place our solar system within the continuum of planetary systems in the Galaxy. The Mission Education and Public Outreach (EPO) Program has developed a Night Sky Network (NSN) outreach kit, Shadows and Silhouettes. This NSN kit is used by amateur astronomers at school and public observing events to illustrate a transit, and explain eclipses.

  10. The Kepler Mission: Search for Habitable Planets

    NASA Technical Reports Server (NTRS)

    Borucki, William; Likins, B.; DeVincenzi, Donald L. (Technical Monitor)

    1998-01-01

    Detecting extrasolar terrestrial planets orbiting main-sequence stars is of great interest and importance. Current ground-based methods are only capable of detecting objects about the size or mass of Jupiter or larger. The difficulties encountered with direct imaging of Earth-size planets from space are expected to be resolved in the next twenty years. Spacebased photometry of planetary transits is currently the only viable method for detection of terrestrial planets (30-600 times less massive than Jupiter). This method searches the extended solar neighborhood, providing a statistically large sample and the detailed characteristics of each individual case. A robust concept has been developed and proposed as a Discovery-class mission. Its capabilities and strengths are presented.

  11. DISCOVERY OF A ZZ CETI IN THE KEPLER MISSION FIELD

    SciTech Connect

    Hermes, J. J.; Winget, D. E.; Mullally, Fergal; Howell, Steve B.; Oestensen, R. H.; Bloemen, S.; Williams, Kurtis A.; Telting, John; Southworth, John; Everett, Mark

    2011-11-01

    We report the discovery of the first identified pulsating DA white dwarf, WD J1916+3938 (Kepler ID 4552982), in the field of the Kepler mission. This ZZ Ceti star was first identified through ground-based, time-series photometry, and follow-up spectroscopy confirms that it is a hydrogen-atmosphere white dwarf with T {sub eff} = 11,129 {+-} 115 K and log g = 8.34 {+-} 0.06, placing it within the empirical ZZ Ceti instability strip. The object shows up to 0.5% amplitude variability at several periods between 800 and 1450 s. Extended Kepler observations of WD J1916+3938 could yield the best light curve, to date, of any pulsating white dwarf, allowing us to directly study the interior of an evolved object representative of the fate of the majority of stars in our Galaxy.

  12. The Kepler Mission on Two Reaction Wheels is K2

    NASA Astrophysics Data System (ADS)

    Haas, Michael R.; Barclay, T.; Batalha, N. M.; Bryson, S.; Caldwell, D. A.; Campbell, J.; Coughlin, J.; Howell, S. B.; Jenkins, J. M.; Klaus, T. C.; Mullally, F.; Sanderfer, D. T.; Sobeck, C. K.; Still, M. D.; Troeltzsch, J.; Twicken, J. D.

    2014-01-01

    Although data collection for the original Kepler mission is complete, a repurposed Kepler has the potential to discover many hundreds of new, small exoplanets around low-mass stars located in or near the ecliptic plane. This repurposing of the Kepler spacecraft, dubbed “K2,” seeks to maximize photometric performance using its two operational reaction wheels by observing in the ecliptic plane where solar torques can be carefully balanced to minimize boresight roll. The K2 mission shows great promise and, once approved, will observe many different fields during a sequence of two- to three-month campaigns over the next few years. Like the original Kepler mission, K2 has many challenges, but is anticipated to be well worth the climb scientifically. K2 can observe many thousands of new sources during each campaign and hundreds of thousands of new sources over its lifetime. In addition to its continued search for exoplanets, the K2 mission will provide access to a wide variety of scientifically interesting targets that include young and variable stars, open clusters of differing ages, star-forming regions, supernovae, white dwarfs, microlensing events, solar system objects, AGNs, normal galaxies, and the Galactic Center. Performance testing began in September, 2013, and has continued throughout the fall and early winter. The results of the first ecliptic-plane tests are described and used to predict photometric performance. A trade study reveals the likely number of targets, cadence durations, initial fields of view, and planned observing strategies. K2 is an exciting new mission that addresses a wide variety of scientific questions with expanded opportunities for community participation.

  13. Spitzer Space Telescope mission design

    NASA Technical Reports Server (NTRS)

    Kwok, Johnny H.; Garcia, Mark D.; Bonfiglio, Eugene; Long, Stacia M.

    2004-01-01

    This paper gives a description of the mission design, launch, orbit, and navigation results for the Spitzer space telescope mission. The Spitzer telescope was launched by the Delta II Heavy launch vehicle into a heliocentric Earth trailing orbit. This orbit is flown for the first time and will be used by several future astronomical missions such as Kepler, SIM, and LISA. This paper describes the launch strategy for a winter versus a summer launch and how it affects communications. It also describes how the solar orbit affects the design and operations of the Observatory. It describes the actual launch timeline, launch vehicle flight performance, and the long term behavior of the as flown orbit. It also provides the orbit knowledge from in-flight navigation data.

  14. On the abundance of extraterrestrial life after the Kepler mission

    NASA Astrophysics Data System (ADS)

    Wandel, Amri

    2015-07-01

    The data recently accumulated by the Kepler mission have demonstrated that small planets are quite common and that a significant fraction of all stars may have an Earth-like planet within their habitable zone. These results are combined with a Drake-equation formalism to derive the space density of biotic planets as a function of the relatively modest uncertainty in the astronomical data and of the (yet unknown) probability for the evolution of biotic life, F b. I suggest that F b may be estimated by future spectral observations of exoplanet biomarkers. If F b is in the range 0.001-1, then a biotic planet may be expected within 10-100 light years from Earth. Extending the biotic results to advanced life I derive expressions for the distance to putative civilizations in terms of two additional Drake parameters - the probability for evolution of a civilization, F c, and its average longevity. For instance, assuming optimistic probability values (F b~F c~1) and a broadcasting longevity of a few thousand years, the likely distance to the nearest civilizations detectable by searching for intelligent electromagnetic signals is of the order of a few thousand light years. The probability of detecting intelligent signals with present and future radio telescopes is calculated as a function of the Drake parameters. Finally, I describe how the detection of intelligent signals would constrain the Drake parameters.

  15. Kepler Mission: Detecting Earth-sized Planets in Habitable Zones

    NASA Technical Reports Server (NTRS)

    Kondo, Yoji; Fisher, Richard R. (Technical Monitor)

    2001-01-01

    The Kepler Mission, which is presently in Phase A, is being proposed for launch in 5 years for a 4-year mission to determine the frequency of Earth-sized or larger planets in habitable zones in our galaxy. Kepler will be placed in an Earth-trailing orbit to provide stable physical environments for the sensitive scientific instruments. The satellite is equipped with a photometric system with the precision of 10E-5, which should be sufficient for detecting the transits of Earth-sized or larger planets in front of dwarf stars similar to the Sun. Approximately 100,000 or more sun-like stars brighter than the 14th apparently magnitude will be monitored continuously for 4 years in a preselected region of the sky, which is about 100 square degrees in size. In addition, Kepler will have a participating scientist program that will enable research in intrinsic variable stars, interacting binaries including cataclysmic stars and X-ray binaries, and a large number of solar analogs in our galaxy. Several ten thousand additional stars may be investigated in the guest observer program open to the whole world.

  16. The Kepler Mission: A Photometric Search for Earthlike Planets

    NASA Technical Reports Server (NTRS)

    Lissauer, Jack J.; Borucki, William; Koch, David; Young, Richard E. (Technical Monitor)

    1998-01-01

    If Earth lies in or near the orbital plane of an extrasolar planet, that planet passes in front of the disk of its star once each orbit as viewed from Earth. Precise photometry can reveal such transits, which can be distinguished from rotationally-modulated starspots and intrinsic stellar variability by their periodicity, square-well shapes and relative spectral neutrality. Transit observations would provide the size and orbital period of the detected planet. Although geometrical considerations limit the fraction of planets detectable by this technique, many stars can be surveyed within the field of view of one telescope, so transit photometry is quite efficient. Scintillation in and variability of Earth's atmosphere limit photometric precision to roughly one-thousandth of a magnitude, allowing detection of transits by Jupiter-sized planets but not by Earth-sized planets from the ground. The COROT spacecraft will be able to detect Uranus-sized planets orbiting near stars. The Kepler Mission, which is being proposed to NASA's Discovery Program this year, will have a photometer with a larger aperture (1 meter) than will COROT, so it will be able to detect transits by planets as small as Earth. Moreover, the Kepler mission will examine the same star field for four years, allowing confirmation of planets with orbital periods of a year. If the Sun's planetary system is typical for single stars, Kepler should detect approximately 480 terrestrial planets. Assuming the statistics from radial velocity surveys are typical, Kepler should also detect transits of 150 inner giant planets and reflected light variations of 1400 giant planets with orbital periods of less than one week.

  17. Space physics missions handbook

    NASA Technical Reports Server (NTRS)

    Cooper, Robert A. (Compiler); Burks, David H. (Compiler); Hayne, Julie A. (Editor)

    1991-01-01

    The purpose of this handbook is to provide background data on current, approved, and planned missions, including a summary of the recommended candidate future missions. Topics include the space physics mission plan, operational spacecraft, and details of such approved missions as the Tethered Satellite System, the Solar and Heliospheric Observatory, and the Atmospheric Laboratory for Applications and Science.

  18. Kepler Mission to Detect Earth-like Planes

    NASA Technical Reports Server (NTRS)

    Kondo, Yoji

    2005-01-01

    Kepler Mission has been approved and funded for launch into an Earth-trailing orbit in 2007. The satellite observatory is designed to detect Earth-like planets in the Cygnus region of the sky (one hundred square degrees). If all goes as planned, we expect to detect some 60 Earth-like planets, plus a greater number of larger planets. None of the planets that have been discovered so far are not Earth-like; they are mostly Jupiter-sized, large planets.

  19. RADIUS DETERMINATION OF SOLAR-TYPE STARS USING ASTEROSEISMOLOGY: WHAT TO EXPECT FROM THE KEPLER MISSION

    SciTech Connect

    Stello, Dennis; Bruntt, Hans; Bedding, Timothy R.; Chaplin, William J.; Elsworth, Yvonne; Creevey, Orlagh L.; Jimenez-Reyes, Sebastian J.; Garcia-Hernandez, Antonio; Moya, Andres; Suarez, Juan-Carlos; Monteiro, Mario J. P. F. G.; Sousa, Sergio G.; Quirion, Pierre-Olivier; Arentoft, Torben; Christensen-Dalsgaard, Joergen; Appourchaux, Thierry; Ballot, Jerome; Fletcher, Stephen T.; Garcia, Rafael A.

    2009-08-01

    For distant stars, as observed by the NASA Kepler satellite, parallax information is currently of fairly low quality and is not complete. This limits the precision with which the absolute sizes of the stars and their potential transiting planets can be determined by traditional methods. Asteroseismology will be used to aid the radius determination of stars observed during NASA's Kepler mission. We report on the recent asteroFLAG hare-and-hounds Exercise no. 2, where a group of 'hares' simulated data of F-K main-sequence stars that a group of 'hounds' sought to analyze, aimed at determining the stellar radii. We investigated stars in the range 9 < V < 15, both with and without parallaxes. We further test different uncertainties in T {sub eff}, and compare results with and without using asteroseismic constraints. Based on the asteroseismic large frequency spacing, obtained from simulations of 4 yr time series data from the Kepler mission, we demonstrate that the stellar radii can be correctly and precisely determined, when combined with traditional stellar parameters from the Kepler Input Catalogue. The radii found by the various methods used by each independent hound generally agree with the true values of the artificial stars to within 3%, when the large frequency spacing is used. This is 5-10 times better than the results where seismology is not applied. These results give strong confidence that radius estimation can be performed to better than 3% for solar-like stars using automatic pipeline reduction. Even when the stellar distance and luminosity are unknown we can obtain the same level of agreement. Given the uncertainties used for this exercise we find that the input log g and parallax do not help to constrain the radius, and that T {sub eff} and metallicity are the only parameters we need in addition to the large frequency spacing. It is the uncertainty in the metallicity that dominates the uncertainty in the radius.

  20. Radius Determination of Solar-type Stars Using Asteroseismology: What to Expect from the Kepler Mission

    NASA Astrophysics Data System (ADS)

    Stello, Dennis; Chaplin, William J.; Bruntt, Hans; Creevey, Orlagh L.; García-Hernández, Antonio; Monteiro, Mario J. P. F. G.; Moya, Andrés; Quirion, Pierre-Olivier; Sousa, Sergio G.; Suárez, Juan-Carlos; Appourchaux, Thierry; Arentoft, Torben; Ballot, Jerome; Bedding, Timothy R.; Christensen-Dalsgaard, Jørgen; Elsworth, Yvonne; Fletcher, Stephen T.; García, Rafael A.; Houdek, Günter; Jiménez-Reyes, Sebastian J.; Kjeldsen, Hans; New, Roger; Régulo, Clara; Salabert, David; Toutain, Thierry

    2009-08-01

    For distant stars, as observed by the NASA Kepler satellite, parallax information is currently of fairly low quality and is not complete. This limits the precision with which the absolute sizes of the stars and their potential transiting planets can be determined by traditional methods. Asteroseismology will be used to aid the radius determination of stars observed during NASA's Kepler mission. We report on the recent asteroFLAG hare-and-hounds Exercise#2, where a group of "hares" simulated data of F-K main-sequence stars that a group of "hounds" sought to analyze, aimed at determining the stellar radii. We investigated stars in the range 9 < V < 15, both with and without parallaxes. We further test different uncertainties in T eff, and compare results with and without using asteroseismic constraints. Based on the asteroseismic large frequency spacing, obtained from simulations of 4 yr time series data from the Kepler mission, we demonstrate that the stellar radii can be correctly and precisely determined, when combined with traditional stellar parameters from the Kepler Input Catalogue. The radii found by the various methods used by each independent hound generally agree with the true values of the artificial stars to within 3%, when the large frequency spacing is used. This is 5-10 times better than the results where seismology is not applied. These results give strong confidence that radius estimation can be performed to better than 3% for solar-like stars using automatic pipeline reduction. Even when the stellar distance and luminosity are unknown we can obtain the same level of agreement. Given the uncertainties used for this exercise we find that the input log g and parallax do not help to constrain the radius, and that T eff and metallicity are the only parameters we need in addition to the large frequency spacing. It is the uncertainty in the metallicity that dominates the uncertainty in the radius.

  1. KEPLER MISSION STELLAR AND INSTRUMENT NOISE PROPERTIES REVISITED

    SciTech Connect

    Gilliland, Ronald L.; Ramsey, Lawrence W.; Chaplin, William J.; Jenkins, Jon M.; Smith, Jeffrey C.

    2015-10-15

    An earlier study of the Kepler Mission noise properties on timescales of primary relevance to detection of exoplanet transits found that higher than expected noise followed, to a large extent, from the stars rather than instrument or data analysis performance. The earlier study over the first six quarters of Kepler data is extended to the full four years ultimately comprising the mission. Efforts to improve the pipeline data analysis have been successful in reducing noise levels modestly as evidenced by smaller values derived from the current data products. The new analyses of noise properties on transit timescales show significant changes in the component attributed to instrument and data analysis, with essentially no change in the inferred stellar noise. We also extend the analyses to timescales of several days, instead of several hours to better sample stellar noise that follows from magnetic activity. On the longer timescale there is a shift in stellar noise for solar-type stars to smaller values in comparison to solar values.

  2. KEPLER MISSION DESIGN, REALIZED PHOTOMETRIC PERFORMANCE, AND EARLY SCIENCE

    SciTech Connect

    Koch, David G.; Borucki, William J.; Lissauer, Jack J.; Basri, Gibor; Marcy, Geoffrey; Batalha, Natalie M.; Brown, Timothy M.; Caldwell, Douglas; DeVore, Edna; Jenkins, Jon; Christensen-Dalsgaard, Joergen; Cochran, William D.; Dunham, Edward W.; Gautier, Thomas N.; Gilliland, Ronald L.; Gould, Alan; Kondo, Yoji; Monet, David

    2010-04-20

    The Kepler Mission, launched on 2009 March 6, was designed with the explicit capability to detect Earth-size planets in the habitable zone of solar-like stars using the transit photometry method. Results from just 43 days of data along with ground-based follow-up observations have identified five new transiting planets with measurements of their masses, radii, and orbital periods. Many aspects of stellar astrophysics also benefit from the unique, precise, extended, and nearly continuous data set for a large number and variety of stars. Early results for classical variables and eclipsing stars show great promise. To fully understand the methodology, processes, and eventually the results from the mission, we present the underlying rationale that ultimately led to the flight and ground system designs used to achieve the exquisite photometric performance. As an example of the initial photometric results, we present variability measurements that can be used to distinguish dwarf stars from red giants.

  3. Classical variables in the era of space photometric missions

    NASA Astrophysics Data System (ADS)

    Molnár, L.; Plachy, E.; Szabó, R.; Benkő, J. M.

    2015-09-01

    The space photometric missions like CoRoT and Kepler transformed our view of pulsating stars, including the well-known RR Lyrae and Cepheid classes. The K2, TESS and PLATO missions will expand these investigations to larger sample sizes and to specific stellar populations.

  4. Confirmation and Characterization of Kepler Mission Exoplanets: The Era of Rock and Ice Exoplanets

    NASA Astrophysics Data System (ADS)

    Charbonneau, David; Borucki, William; Brown, Timothy; Deming, Drake; Ford, Eric; Fortney, Jonathan; Gilliland, Ronald; Knutson, Heather; Latham, David; Seager, Sara

    2008-12-01

    In the past 4 years, the combination of ground-based transit surveys and the remarkable stability of the Spitzer Space Telescope permitted the direct investigation of the atmospheres of one specific class of exoplanet, namely the Hot Jupiters. The power of the NASA Kepler Mission will be to discover dozens of transiting exoplanets that are not detectable from the ground either due to the shallow transit depth or the low transit frequency resulting from their longer orbital periods. Kepler will find large numbers of transiting hot Neptunes and hot SuperEarth exoplanets, as well as cooler Jupiters, each of which are nonetheless amenable to direct study of their infrared emission. We propose to use Spitzer to observe Kepler-detected exoplanets and candidates to pursue two goals. First, we will measure the two-color planetary emission for 20 representative members of these previously inaccessible cexoplanets. Such observations will permit the first opportunity to directly test theoretical models of exoplanetary atmospheres of varying compositions (notably SuperEarths and Neptunes) and under differing levels of irradiation (cooler Jovian companions). The same data will permit an estimate of the orbital eccentricities, thus providing a test of models of the orbital migration, and tidal dissipation for these various types of exoplanets. Second, we will use Spitzer to follow up Kepler-identified candidate terrestrial exoplanets to prove that these signals are indeed planetary in origin. By gathering single color time series spanning times of primary transit, we will exclude a significant source of astrophysical false positives (resulting from blends of triple stars systems containing an eclipsing binary) that will precisely mimic an exoplanetary signature in the Kepler data. These infrared data will provide a crucial step in confirming the planetary nature of many of the most exciting candidates, namely the planets with the smallest radii that are likely rocky in

  5. Kepler Planet Detection Mission: Introduction and First Results

    NASA Astrophysics Data System (ADS)

    Borucki, William J.; Koch, D.; Basri, G.; Batalha, N. M.; Brown, T.; Caldwell, D. A.; Caldwell, J.; Christensen-Dalsgaard, J.; Cochran, W.; DeVore, E.; Dunham, E.; Dupree, A.; Gautier, T.; Geary, J.; Gilliland, R.; Gould, A.; Howell, S.; Jenkins, J.; Kjeldsen, H.; Kondo, Y.; Latham, D.; Lissauer, J.; Marcy, G.; Meibom, S.; Monet, D.; Morrison, D.; Sasselov, D.; Tarter, J.

    2010-01-01

    The Kepler Mission is designed to determine the frequency of Earth-size and terrestrial size planets in and near the HZ of solar-like stars. It was competitively selected as Discovery Mission #10 and launched on March 6, 2009. Since completion of commissioning, it has continuously observed over 145,000 main sequence stars. The photometric precision reaches 20 ppm for 12th magnitude stars on the least noisy detectors in 6.5 hours. During the first month of operation, the photometer detected transit-like signatures from over 100 stars. Careful examination of these events shows many of them to be false-positives such as background eclipsing binaries. However ground-based follow up observations confirm the discovery of exoplanets with sizes ranging from 0.6 Rj to1.5Rj and orbital periods ranging from 3 to 9 days. Observations at Keck, Hobby-Eberly, Harlan-Smith, WIYN, MMT, Tillighast, Shane, and Nordic Optic telescopes are vetting many of the candidates and measuring their masses. Discovery of the HAT-P7b occultation will be used to derive atmospheric properties and demonstrates the precision necessary to detect Earth-size planets. Asteroseismic analyses of several stars show the presence of p-mode oscillations that can be used to determine stellar size and age. This effort is being organized by the Kepler Asteroseismic Science Consortium at Aarhus University in Denmark. Stellar parallaxes are determined from the centroid motion of the stellar images and will be combined with photometric measurements to get the sizes of stars too dim for asteroseismic measurement. Four open clusters are being observed to determine rotation rates with stellar age and spectral type. Many types of stellar variability are observed with unprecedented precision and over long continuous time periods. Examples of many of these discoveries are presented. Funding by the Exoplanet Exploration Program of the NASA Astrophysics Division is gratefully acknowledged.

  6. SPECTROSCOPY OF FAINT KEPLER MISSION EXOPLANET CANDIDATE HOST STARS

    SciTech Connect

    Everett, Mark E.; Silva, David R.; Howell, Steve B.; Szkody, Paula

    2013-07-10

    Stellar properties are measured for a large set of Kepler mission exoplanet candidate host stars. Most of these stars are fainter than 14th magnitude, in contrast to other spectroscopic follow-up studies. This sample includes many high-priority Earth-sized candidate planets. A set of model spectra are fitted to R {approx} 3000 optical spectra of 268 stars to improve estimates of T{sub eff}, log (g), and [Fe/H] for the dwarfs in the range 4750 {<=} T{sub eff} {<=} 7200 K. These stellar properties are used to find new stellar radii and, in turn, new radius estimates for the candidate planets. The result of improved stellar characteristics is a more accurate representation of this Kepler exoplanet sample and identification of promising candidates for more detailed study. This stellar sample, particularly among stars with T{sub eff} {approx}> 5200 K, includes a greater number of relatively evolved stars with larger radii than assumed by the mission on the basis of multi-color broadband photometry. About 26% of the modeled stars require radii to be revised upward by a factor of 1.35 or greater, and modeling of 87% of the stars suggest some increase in radius. The sample presented here also exhibits a change in the incidence of planets larger than 3-4 R{sub Circled-Plus} as a function of metallicity. Once [Fe/H] increases to {>=} - 0.05, large planets suddenly appear in the sample while smaller planets are found orbiting stars with a wider range of metallicity. The modeled stellar spectra, as well as an additional 84 stars of mostly lower effective temperatures, are made available to the community.

  7. A Bewildering and Dynamic Picture of Exoplanetary Systems Identified by the Kepler Mission (Invited)

    NASA Astrophysics Data System (ADS)

    Jenkins, J. M.

    2013-12-01

    notion of the habitable zone for single stars and static planetary system configurations. This talk will provide an overview of the science results from the Kepler Mission and the work ahead to derive the frequency of Earth-size planets in the habitable zone of solar-like stars from the treasure trove of Kepler data. NASA's quest for exoplanets continues with the Transiting Exoplanet Survey Satellite (TESS) mission, slated for launch in May 2017 by NASA's Explorer Program. TESS will conduct an all- sky transit survey to identify the 1000 best small exoplanets in the solar neighborhood for follow up observations and characterization. TESS's targets will include all F, G, K dwarfs from +4 to +12 magnitude and all M dwarfs known within ~200 light-years. 500,000 target stars will be observed over two years with ~500 square degrees observed continuously for a year in each hemisphere in the James Webb Space Telescopes continuously viewable zones. Since the typical TESS target star is 5 magnitudes brighter than that of Kepler and 10 times closer, TESS discoveries will afford significant opportunities to measure the masses of the exoplanets and to characterize their atmospheres with JWST, ELTs and other exoplanet explorers. TESS' discoveries will raise new questions regarding habitability that will be open to investigation through active efforts to characterize their atmospheres and search for biomarkers. Funding for this mission is provided by NASA's Science Mission Directorate.

  8. Confirmation and Characterization of Kepler Mission Exoplanets: The Era of Rock and Ice Exoplanets

    NASA Astrophysics Data System (ADS)

    Knutson, Heather; Charbonneau, D.

    2009-05-01

    In the past 4 years, the combination of ground-based transit surveys and the remarkable stability of the Spitzer Space Telescope permitted the direct investigation of the atmospheres of one specific class of exoplanet, namely the Hot Jupiters. The NASA Kepler mission (scheduled for launch early this year) will have the ability to discover dozens of transiting exoplanets that are not currently detectable from the ground, including large numbers of transiting hot Neptune and hot Super-Earth exoplanets, as well as cooler Jupiters. Our Exploration Science program will measure the two-color planetary emission for 20 representative members of these previously inaccessible exoplanets, providing the first opportunity to directly test theoretical models of exoplanetary atmospheres of varying compositions (notably Super-Earths and Neptunes) and under differing levels of irradiation (cooler Jovian companions). The same data will permit an estimate of the orbital eccentricities, thus providing a test of models of the orbital migration and tidal dissipation for these various types of exoplanets. We will also use Spitzer to follow up Kepler-identified candidate terrestrial exoplanets to prove that these signals are indeed planetary in origin. By gathering single color time series spanning times of primary transit, we will exclude a significant source of astrophysical false positives (resulting from blends of triple star systems containing an eclipsing binary) that can precisely mimic an exoplanetary signature in the Kepler data. These infrared data will provide a crucial confirmation of the planetary nature of the most exciting terrestrial-planet candidates.

  9. VizieR Online Data Catalog: Kepler Mission. VII. Eclipsing binaries in DR3 (Kirk+, 2016)

    NASA Astrophysics Data System (ADS)

    Kirk, B.; Conroy, K.; Prsa, A.; Abdul-Masih, M.; Kochoska, A.; Matijevic, G.; Hambleton, K.; Barclay, T.; Bloemen, S.; Boyajian, T.; Doyle, L. R.; Fulton, B. J.; Hoekstra, A. J.; Jek, K.; Kane, S. R.; Kostov, V.; Latham, D.; Mazeh, T.; Orosz, J. A.; Pepper, J.; Quarles, B.; Ragozzine, D.; Shporer, A.; Southworth, J.; Stassun, K.; Thompson, S. E.; Welsh, W. F.; Agol, E.; Derekas, A.; Devor, J.; Fischer, D.; Green, G.; Gropp, J.; Jacobs, T.; Johnston, C.; Lacourse, D. M.; Saetre, K.; Schwengeler, H.; Toczyski, J.; Werner, G.; Garrett, M.; Gore, J.; Martinez, A. O.; Spitzer, I.; Stevick, J.; Thomadis, P. C.; Vrijmoet, E. H.; Yenawine, M.; Batalha, N.; Borucki, W.

    2016-07-01

    The Kepler Eclipsing Binary Catalog lists the stellar parameters from the Kepler Input Catalog (KIC) augmented by: primary and secondary eclipse depth, eclipse width, separation of eclipse, ephemeris, morphological classification parameter, and principal parameters determined by geometric analysis of the phased light curve. The previous release of the Catalog (Paper II; Slawson et al. 2011, cat. J/AJ/142/160) contained 2165 objects, through the second Kepler data release (Q0-Q2). In this release, 2878 objects are identified and analyzed from the entire data set of the primary Kepler mission (Q0-Q17). The online version of the Catalog is currently maintained at http://keplerEBs.villanova.edu/. A static version of the online Catalog associated with this paper is maintained at MAST https://archive.stsci.edu/kepler/eclipsing_binaries.html. (10 data files).

  10. Planetary and Stellar Data Products Expected From The Kepler Mission

    NASA Technical Reports Server (NTRS)

    Borucki, W. J.; Koch, David G.; Basri, Gibor; Cochran, William; Dunham, Edward W.; Gilliland, Ronald; Jenkins, Jon M.; Caldwell, Douglas; Kondo, Yoji; Latham, David; DeVincenzi, Donald (Technical Monitor)

    2002-01-01

    The Kepler Mission is a Discovery-class mission scheduled to be launched in the 2006-2007 time frame. It is a wide field of view photometer with a 95 m aperture designed to attain a photometric precision of 2 parts in 10^5 for the 12th magnitude stars. It will continually observe 100,000 main-sequence stars from 9th to 14th magnitude for a period of four years with a cadence of 4/hour. This database should be unique in its photometric precision, cadence, and duration of observations. Several hundred terrestrial-size planets will be detected if they are common around solar-like stars. Based on the current results of Doppler-velocity searches, over a thousand giant planets will also be found. A guest investigator program is planned that would provide the opportunity to observe thousands of other objects in the 105 square degree FOV. Such objects could include stars with micro-variability, other intrinsic variables, cataclysmic variables, eclipsing binaries (including x-ray binaries), and possibly AGN. A ground-based program to classify all 225,000 stars in the FOV and to do a detailed examination of a subset of the stars that show planetary companions is planned. Doppler-velocity observations will be made to find the presence of giant planets not seen in transit. The data will be rapidly released to the community for follow up observations and for changes to the guest investigator program.

  11. Validating and Characterizing Transiting Exoplanets from Space with EPOXI, Kepler, and Warm Spitzer

    NASA Astrophysics Data System (ADS)

    Ballard, Sarah

    2012-01-01

    My thesis work comprises analyses of transiting exoplanets with observations from three space-based instruments. The Extrasolar Planet Observation and Characterization (EPOCh) component of the EPOXI mission repurposed the Deep Impact Spacecraft to gather photometry of six known transiting exoplanet systems. I systematically searched the EPOXI light curves for additional transiting planets, and identified one such candidate in the exoplanet system GJ 436. I gathered Warm Spitzer light curves of GJ 436 during a predicted transit of this putative planet: while I ruled out the presence of the hypothesized planet, I developed a novel reduction technique for Warm Spitzer observations and demonstrated the sensitivity of that instrument to sub-Earth-sized transiting planets. I next applied these techniques to a sample of super-Earth-sized planetary candidates identified by the Kepler mission. In the absence of radial velocity confirmation (challenging for such low-mass planets), it is nonetheless possible to make a statistical argument for the planetary nature of the candidate, if the combined likelihood of all false positive scenarios is sufficiently smaller than the planet scenario. An authentic planet will exhibit an achromatic transit depth, as measured in the optical with Kepler and near-infrared with Warm Spitzer. The eclipse from a stellar blend, in contrast, would likely vary with wavelength. I presented the discovery of the Kepler-19 system, applying Warm Spitzer observations toward validation of the transiting 2.2 REarth planet, Kepler-19b. I identified systematic variations in the transit times of Kepler-19b, which led to the first robust detection of a non-transiting planet using the transit timing variation method: Kepler-19c. Support for EPOXI was provided by NASA's Discovery Program via Agreement NNX08AB64A. This work is based on observations made with the Spitzer Space Telescope. Support for Spitzer observations is provided by NASA through an award issued

  12. Kepler: NASA's First Mission Capable of Finding Earth-Size Planets

    NASA Technical Reports Server (NTRS)

    Borucki, William J.

    2009-01-01

    Kepler, a NASA Discovery mission, is a spaceborne telescope designed to search a nearby region of our galaxy for Earth-size planets orbiting in the habitable zone of stars like our sun. The habitable zone is that region around a start where the temperature permits water to be liquid on the surface of a planet. Liquid water is considered essential forth existence of life. Mission Phases: Six mission phases have been defined to describe the different periods of activity during Kepler's mission. These are: launch; commissioning; early science operations, science operations: and decommissioning

  13. Low Cost Mission Operations Workshop. [Space Missions

    NASA Technical Reports Server (NTRS)

    1994-01-01

    The presentations given at the Low Cost (Space) Mission Operations (LCMO) Workshop are outlined. The LCMO concepts are covered in four introductory sections: Definition of Mission Operations (OPS); Mission Operations (MOS) Elements; The Operations Concept; and Mission Operations for Two Classes of Missions (operationally simple and complex). Individual presentations cover the following topics: Science Data Processing and Analysis; Mis sion Design, Planning, and Sequencing; Data Transport and Delivery, and Mission Coordination and Engineering Analysis. A list of panelists who participated in the conference is included along with a listing of the contact persons for obtaining more information concerning LCMO at JPL. The presentation of this document is in outline and graphic form.

  14. Kepler

    NASA Astrophysics Data System (ADS)

    Wilson, C.; Murdin, P.

    2000-11-01

    Johannes Kepler (1571-1630) was arguably the most innovative astronomical theorist in the millennium and a half from Claudius PTOLEMY's Almagest (c. AD 150) to Isaac NEWTON's Principia (1687). Before Kepler, planetary and lunar theory had consisted in combining circular motions, either strictly uniform or angularly uniform about an off-center `equant' point, so as to `save the appearances'. T...

  15. Hubble Space Telescope High-Resolution Imaging of Kepler Small and Cool Exoplanet Host Stars

    NASA Astrophysics Data System (ADS)

    Gilliland, Ronald L.; Cartier, Kimberly M. S.; Adams, Elisabeth R.; Ciardi, David R.; Kalas, Paul; Wright, Jason T.

    2015-01-01

    High-resolution imaging is an important tool for follow-up study of exoplanet candidates found via transit detection with the Kepler mission. We discuss here Hubble Space Telescope imaging with the WFC3 of 23 stars that host particularly interesting Kepler planet candidates based on their small size and cool equilibrium temperature estimates. Results include detections, exclusion of background stars that could be a source of false positives for the transits, and detection of physically associated companions in a number of cases providing dilution measures necessary for planet parameter refinement. For six Kepler objects of interest, we find that there is ambiguity regarding which star hosts the transiting planet(s), with potentially strong implications for planetary characteristics. Our sample is evenly distributed in G, K, and M spectral types. Albeit with a small sample size, we find that physically associated binaries are more common than expected at each spectral type, reaching a factor of 10 frequency excess in M. We document the program detection sensitivities, detections, and deliverables to the Kepler follow-up program archive. Based on observations with the NASA/ESA Hubble Space Telescope, obtained at the Space Telescope Science Institute, operated by AURA, Inc., under NASA contract NAS 5-26555.

  16. Spitzer Observations of Exoplanets Discovered with the Kepler K2 Mission

    NASA Astrophysics Data System (ADS)

    Beichman, Charles; Livingston, John; Werner, Michael; Gorjian, Varoujan; Krick, Jessica; Deck, Katherine; Knutson, Heather; Wong, Ian; Petigura, Erik; Christiansen, Jessie; Ciardi, David; Greene, Thomas P.; Schlieder, Joshua E.; Line, Mike; Crossfield, Ian; Howard, Andrew; Sinukoff, Evan

    2016-05-01

    We have used the Spitzer Space Telescope to observe two transiting planetary systems orbiting low-mass stars discovered in the Kepler K2 mission. The system K2-3 (EPIC 201367065) hosts three planets, while K2-26 (EPIC 202083828) hosts a single planet. Observations of all four objects in these two systems confirm and refine the orbital and physical parameters of the planets. The refined orbital information and more precise planet radii possible with Spitzer will be critical for future observations of these and other K2 targets. For K2-3b we find marginally significant evidence for a transit timing variation between the K2 and Spitzer epochs.

  17. The Kepler Mission: A Transit-Photometry Mission to Discover Terrestrial Planets

    NASA Astrophysics Data System (ADS)

    Borucki, William J.; Koch, David; Basri, Gibor; Brown, Timothy; Caldwell, Douglas; Devore, Edna; Dunham, Edward; Gautier, Thomas; Geary, John; Gilliland, Ronald; Gould, Alan; Howell, Steve; Jenkins, Jon

    The Kepler Mission is a NASA Discovery-class mission designed to continuously monitor the brightness of 100,000 main sequence stars to detect the transit of Earth-size and larger planets. It is a wide field of view photometer with a Schmidt-type telescope and an array of 42 CCDs covering the 100 sq. degree field-of-view (FOV). It has a 0.95 m aperture and a 1.4 m primary and is designed to attain a photometric precision of 20 parts per million (ppm) for 12th magnitude solar-like stars for a 6.5-hour transit duration. It will continuously observe 100,000 main sequence stars from 9th to 15th magnitude in the Cygnus constellation for a period of four years with a cadence of 4 measurements per hour. Kepler is Discovery Mission #10 and is on schedule for launch in 2007 into heliocentric orbit. A ground-based program to classify all 450,000 stars brighter than 15th magnitude in the FOV and to conduct a detailed examination of a subset of the stars that show planetary companions is also planned. Hundreds of Earth-size planets should be detected if they are common around solarlike stars. Ground-based spectrometric observations of those stars with planetary companions will be made to determine the dependences of the frequency and size of terrestrial planets on stellar characteristics such as type and metallicity. A null result would imply that terrestrial planets are rare.

  18. The Kepler Mission: A Search for Terrestrial Planets - Development Status

    NASA Technical Reports Server (NTRS)

    Koch, David; Borucki, W.; Mayer, D.; Caldwell, D.; Jenkens, J.; Dunham, E.; Geary, J.; Bachtell, E.; Deininger, W.; Philbrick, R.

    2003-01-01

    We have embarked on a mission to detect terrestrial planets. The space mission has been optimized to search for earth-size planets (0.5 to 10 earth masses) in the habitable zone (HZ) of solar-like stars. Given this design, the mission will necessarily be capable of not only detecting Earth analogs, but a wide range of planetary types and characteristics ranging from Mercury-size objects with orbital periods of days to gas-giants in decade long orbits that have undeniable signatures even with only one transit detected. The mission is designed to survey the full range of spectral-type dwarf stars. The approach is to detect the periodic signal of transiting planets. Three or more transits of a star exceeding a combined threshold of eight sigma with a statistically consistent period, brightness change and duration provide a rigorous method of detection. From the relative brightness change the planet size can be calculated. From the period the orbital size can be calculated and its location relative to the HZ determined. Presented here are: the mission goals, the top level system design requirements derived from these goals that drive the flight system design, a number of the trades that have lead to the mission concept, expected photometric performance dependence on stellar brightness and spectral type based on the system 'noise tree' analysis. Updated estimates are presented of the numbers of detectable planets versus size, orbit, stellar spectral type and distances based on a planet frequency hypothesis. The current project schedule and organization are given.

  19. An Introduction to Exoplanets and the Kepler Mission

    NASA Technical Reports Server (NTRS)

    Lissauer, Jack

    2014-01-01

    A quarter century ago, the only planets known to humanity were the familiar objects that orbit our Sun. But improved observational techniques allowed astronomers to begin detecting planets around other stars in the 1990s. The first extrasolar planets (often referred to as exoplanets) to be discovered were quite exotic and unfamiliar objects. Most were giant objects that are hundreds of times as massive as the Earth and orbit so close to their star that they are hotter than pizza ovens. But as observational capabilities improved, smaller and cooler planets were found. The most capable planet-hunting tool developed to date is NASA's Kepler telescope, which was launched in 2009. Kepler has found that planets similar in size to our Earth are quite abundant within our galaxy. Results of Kepler's research will be summarized and placed into context within the new and growing discipline of exoplanet studies.

  20. Hubble space telescope high-resolution imaging of Kepler small and cool exoplanet host stars

    SciTech Connect

    Gilliland, Ronald L.; Cartier, Kimberly M. S.; Wright, Jason T.; Adams, Elisabeth R.; Ciardi, David R.

    2015-01-01

    High-resolution imaging is an important tool for follow-up study of exoplanet candidates found via transit detection with the Kepler mission. We discuss here Hubble Space Telescope imaging with the WFC3 of 23 stars that host particularly interesting Kepler planet candidates based on their small size and cool equilibrium temperature estimates. Results include detections, exclusion of background stars that could be a source of false positives for the transits, and detection of physically associated companions in a number of cases providing dilution measures necessary for planet parameter refinement. For six Kepler objects of interest, we find that there is ambiguity regarding which star hosts the transiting planet(s), with potentially strong implications for planetary characteristics. Our sample is evenly distributed in G, K, and M spectral types. Albeit with a small sample size, we find that physically associated binaries are more common than expected at each spectral type, reaching a factor of 10 frequency excess in M. We document the program detection sensitivities, detections, and deliverables to the Kepler follow-up program archive.

  1. The Space Interferometry Mission

    NASA Technical Reports Server (NTRS)

    Unwin, Stephen C.

    1998-01-01

    The Space Interferometry Mission (SIM) is the next major space mission in NASA's Origins program after SIRTF. The SIM architecture uses three Michelson interferometers in low-earth orbit to provide 4 microarcsecond precision absolute astrometric measurements on approx. 40,000 stars. SIM will also provide synthesis imaging in the visible waveband to a resolution of 10 milliarcsecond, and interferometric nulling to a depth of 10(exp -4). A near-IR (1-2 micron) capability is being considered. Many key technologies will be demonstrated by SIM that will be carried over directly or can be readily scaled to future Origins missions such as TPF. The SIM spacecraft will carry a triple Michelson interferometer with baselines in the 10 meter range. Two interferometers act as high precision trackers, providing attitude information at all time, while the third one conducts the science observations. Ultra-accurate laser metrology and active systems monitor the systematic errors and to control the instrument vibrations in order to reach the 4 microarcsecond level on wide-angle measurements. SIM will produce a wealth of new astronomical data. With an absolute positional precision of 4 microarcsecond, SIM will improve on the best currently available measures (the Hipparcos catalog) by 2 or 3 orders of magnitude, providing parallaxes accurate to 10% and transverse velocities to 0.2 km/s anywhere in the Galaxy, to stars as faint as 20th magnitude. With the addition of radial velocities, knowledge of the 6-dimension phase space for objects of interest will allow us to attack a wide array of previously inaccessible problems such as: search for planets down to few earth masses; calibration of stellar luminosities and by means of standard candles, calibration of the cosmic distance scale; detecting perturbations due to spiral arms, disk warps and central bar in our galaxy; probe of the gravitational potential of the Galaxy, several kiloparsecs out of the galactic plane; synthesis imaging

  2. VizieR Online Data Catalog: Kepler Mission. II. Eclipsing binaries in DR2 (Slawson+, 2011)

    NASA Astrophysics Data System (ADS)

    Slawson, R. W.; Prsa, A.; Welsh, W. F.; Orosz, J. A.; Rucker, M.; Batalha, N.; Doyle, L. R.; Engle, S. G.; Conroy, K.; Coughlin, J.; Gregg, T. A.; Fetherolf, T.; Short, D. R.; Windmiller, G.; Fabrycky, D. C.; Howell, S. B.; Jenkins, J. M.; Uddin, K.; Mullally, F.; Seader, S. E.; Thompson, S. E.; Sanderfer, D. T.; Borucki, W.; Koch, D.

    2013-03-01

    The Kepler Mission (launched in 2009 March) provides nearly continuous monitoring of ~156000 objects with unprecedented photometric precision. Coincident with the first data release, we presented a catalog of 1879 eclipsing binary systems identified within the 115deg2 Kepler field of view (FOV). Here, we provide an updated catalog from paper I (Prsa et al. 2011, Cat. J/AJ/141/83) augmented with the second Kepler data release which increases the baseline nearly fourfold to 125 days. Three hundred and eighty-six new systems have been added, ephemerides and principal parameters have been recomputed. We have removed 42 previously cataloged systems that are now clearly recognized as short-period pulsating variables and another 58 blended systems where we have determined that the Kepler target object is not itself the eclipsing binary. A number of interesting objects are identified. We present several exemplary cases: four eclipsing binaries that exhibit extra (tertiary) eclipse events; and eight systems that show clear eclipse timing variations indicative of the presence of additional bodies bound in the system. We have updated the period and galactic latitude distribution diagrams. With these changes, the total number of identified eclipsing binary systems in the Kepler FOV has increased to 2165, 1.4% of the Kepler target stars. (4 data files).

  3. SPECKLE CAMERA OBSERVATIONS FOR THE NASA KEPLER MISSION FOLLOW-UP PROGRAM

    SciTech Connect

    Howell, Steve B.; Everett, Mark E.; Sherry, William; Horch, Elliott; Ciardi, David R.

    2011-07-15

    We present the first results from a speckle imaging survey of stars classified as candidate exoplanet host stars discovered by the Kepler mission. We use speckle imaging to search for faint companions or closely aligned background stars that could contribute flux to the Kepler light curves of their brighter neighbors. Background stars are expected to contribute significantly to the pool of false positive candidate transiting exoplanets discovered by the Kepler mission, especially in the case that the faint neighbors are eclipsing binary stars. Here, we describe our Kepler follow-up observing program, the speckle imaging camera used, our data reduction, and astrometric and photometric performance. Kepler stars range from R = 8 to 16 and our observations attempt to provide background non-detection limits 5-6 mag fainter and binary separations of {approx}0.05-2.0 arcsec. We present data describing the relative brightness, separation, and position angles for secondary sources, as well as relative plate limits for non-detection of faint nearby stars around each of 156 target stars. Faint neighbors were found near 10 of the stars.

  4. Space missions to comets

    NASA Technical Reports Server (NTRS)

    Neugebauer, M. (Editor); Yeomans, D. K. (Editor); Brandt, J. C. (Editor); Hobbs, R. W. (Editor)

    1979-01-01

    The broad impact of a cometary mission is assessed with particular emphasis on scientific interest in a fly-by mission to Halley's comet and a rendezvous with Tempel 2. Scientific results, speculations, and future plans are discussed.

  5. Ensemble asteroseismology of solar-type stars with the NASA Kepler mission.

    PubMed

    Chaplin, W J; Kjeldsen, H; Christensen-Dalsgaard, J; Basu, S; Miglio, A; Appourchaux, T; Bedding, T R; Elsworth, Y; García, R A; Gilliland, R L; Girardi, L; Houdek, G; Karoff, C; Kawaler, S D; Metcalfe, T S; Molenda-Żakowicz, J; Monteiro, M J P F G; Thompson, M J; Verner, G A; Ballot, J; Bonanno, A; Brandão, I M; Broomhall, A-M; Bruntt, H; Campante, T L; Corsaro, E; Creevey, O L; Doğan, G; Esch, L; Gai, N; Gaulme, P; Hale, S J; Handberg, R; Hekker, S; Huber, D; Jiménez, A; Mathur, S; Mazumdar, A; Mosser, B; New, R; Pinsonneault, M H; Pricopi, D; Quirion, P-O; Régulo, C; Salabert, D; Serenelli, A M; Silva Aguirre, V; Sousa, S G; Stello, D; Stevens, I R; Suran, M D; Uytterhoeven, K; White, T R; Borucki, W J; Brown, T M; Jenkins, J M; Kinemuchi, K; Van Cleve, J; Klaus, T C

    2011-04-08

    In addition to its search for extrasolar planets, the NASA Kepler mission provides exquisite data on stellar oscillations. We report the detections of oscillations in 500 solar-type stars in the Kepler field of view, an ensemble that is large enough to allow statistical studies of intrinsic stellar properties (such as mass, radius, and age) and to test theories of stellar evolution. We find that the distribution of observed masses of these stars shows intriguing differences to predictions from models of synthetic stellar populations in the Galaxy.

  6. Kepler Mission: A Mission to Find Earth-size Planets in the Habitable Zone

    NASA Technical Reports Server (NTRS)

    Borucki, W. J.

    2003-01-01

    The Kepler Mission is a Discovery-class mission designed to continuously monitor the brightness of 100,000 solar-like stars to detect the transits of Earth-size and larger planets. It is a wide field of view photometer Schmidt-type telescope with an array of 42 CCDs. It has a 0.95 m aperture and 1.4 m primary and is designed to attain a photometric precision of 2 parts in 10(exp 5) for 12th magnitude solar-like stars for a 6 hr transit duration. It will continuously observe 100,000 main-sequence stars from 9th to 14th magnitude in the Cygnus constellation for a period of four years with a cadence of 4/hour. An additional 250 stars can be monitored at a cadence of l/minute to do astro-seismology of stars brighter than 11.5 mv. The photometer is scheduled to be launched into heliocentric orbit in 2007. When combined with ground-based spectrometric observations of these stars, the positions of the planets relative to the habitable zone can be found. The spectra of the stars are also used to determine the relationships between the characteristics of terrestrial planets and the characteristics of the stars they orbit. In particular, the association of planet size and occurrence frequency with stellar mass and metallicity will be investigated. Based on the results of the current Doppler-velocity discoveries, over a thousand giant planets will also be found. Information on the albedos and densities of those giants showing transits will be obtained. At the end of the four year mission, hundreds of Earth-size planets should be discovered in and near the HZ of their stars if such planets are common. A null result would imply that terrestrial planets in the HZ are very rare and that life might also be quite rare.

  7. The Space Technology 8 mission

    NASA Technical Reports Server (NTRS)

    Franklin, Stephen F.; Ku, Jentung; Spence, Brian; McEachen, Mike; White, Steve; Samson, John; Some, Rafael; Zsoldos, Jennifer

    2006-01-01

    the Space Technology 8 (ST8) mission is the latest in NASA's New Millenium Program technology demonstration missions. ST8 includes a spacecraft bus built by industry, flying four new technology payloads in low Earth orbit. This paper will describe each payload, along with a brief description of the mission and spacecraft.

  8. ATV Engineering Support Team Safety Console Preparation for the Johannes Kepler Mission

    NASA Astrophysics Data System (ADS)

    Chase, R.; Oliefka, L.

    2010-09-01

    This paper describes the improvements to be implemented in the Safety console position of the Engineering Support Team(EST) at the Automated Transfer Vehicle(ATV) Control Centre(ATV-CC) for the upcoming ATV Johannes Kepler mission. The ATV missions to the International Space Station are monitored and controlled from the ATV-CC in Toulouse, France. The commanding of ATV is performed by the Vehicle Engineering Team(VET) in the main control room under authority of the Flight Director. The EST performs a monitoring function in a room beside the main control room. One of the EST positions is the Safety console, which is staffed by safety engineers from ESA and the industrial prime contractor, Astrium. The function of the Safety console is to check whether the hazard controls are available throughout the mission as required by the Hazard Reports approved by the ISS Safety Review Panel. Safety console preparation activities were limited prior to the first ATV mission due to schedule constraints, and the safety engineers involved have been working to improve the readiness for ATV 2. The following steps have been taken or are in process, and will be described in this paper: • review of the implementation of Operations Control Agreement Documents(OCADs) that record the way operational hazard controls are performed to meet the needs of the Hazard Reports(typically in Flight Rules and Crew Procedures), • crosscheck of operational control needs and implementations with respect to ATV's first flight observations and post flight evaluations, with a view to identifying additional, obsolete or revised operational hazard controls, • participation in the Flight Rule review and update process carried out between missions, • participation in the assessment of anomalies observed during the first ATV mission, to ensure that any impacts are addressed in the ATV 2 safety documentation, • preparation of a Safety console handbook to provide lists of important safety aspects to be

  9. Towards Automatic Classification of Exoplanet-Transit-Like Signals: A Case Study on Kepler Mission Data

    NASA Astrophysics Data System (ADS)

    Valizadegan, Hamed; Martin, Rodney; McCauliff, Sean D.; Jenkins, Jon Michael; Catanzarite, Joseph; Oza, Nikunj C.

    2015-08-01

    Building new catalogues of planetary candidates, astrophysical false alarms, and non-transiting phenomena is a challenging task that currently requires a reviewing team of astrophysicists and astronomers. These scientists need to examine more than 100 diagnostic metrics and associated graphics for each candidate exoplanet-transit-like signal to classify it into one of the three classes. Considering that the NASA Explorer Program's TESS mission and ESA's PLATO mission survey even a larger area of space, the classification of their transit-like signals is more time-consuming for human agents and a bottleneck to successfully construct the new catalogues in a timely manner. This encourages building automatic classification tools that can quickly and reliably classify the new signal data from these missions. The standard tool for building automatic classification systems is the supervised machine learning that requires a large set of highly accurate labeled examples in order to build an effective classifier. This requirement cannot be easily met for classifying transit-like signals because not only are existing labeled signals very limited, but also the current labels may not be reliable (because the labeling process is a subjective task). Our experiments with using different supervised classifiers to categorize transit-like signals verifies that the labeled signals are not rich enough to provide the classifier with enough power to generalize well beyond the observed cases (e.g. to unseen or test signals). That motivated us to utilize a new category of learning techniques, so-called semi-supervised learning, that combines the label information from the costly labeled signals, and distribution information from the cheaply available unlabeled signals in order to construct more effective classifiers. Our study on the Kepler Mission data shows that semi-supervised learning can significantly improve the result of multiple base classifiers (e.g. Support Vector Machines, Ada

  10. Kepler Planet-Detection Mission: Introduction and First Results

    DTIC Science & Technology

    2010-02-19

    Sun-like stars. The habitable zone is the region where planetary temperatures are suitable for water to exist on a planet?s surface. During the first 6... planetary temperatures are suitable for water to exist on a planet’s surface. During the first 6 weeks of observations, Kepler monitored 156,000 stars...inward migration of a giant planet is expected to remove inner, smaller planets by scattering them into the star or out of the planetary system, a second

  11. Validating the First Habitable-Zone Planet Candidates Identified by the NASA Kepler Mission

    NASA Astrophysics Data System (ADS)

    Charbonneau, David; Desert, Jean-Michel; Fressin, Francois; Ballard, Sarah; Borucki, William; Latham, David; Gilliland, Ronald; Seager, Sara; Knutson, Heather; Fortney, Jonathan; Brown, Timothy; Ford, Eric; Deming, Drake; Torres, Guillermo

    2011-05-01

    At the beginning of Cycle 8, the NASA Kepler Mission will have completed two years of science observations, the minimum baseline sufficient to identify candidate transiting exoplanets orbiting within the habitable-zones of Sun-like stars. The principal task that lies ahead is to reject from this sample the false positives (blends of eclipsing binaries that precisely mimic the signal of a transiting exoplanet), and to confirm the planetary nature of the remaining candidates. For planets more massive than Neptune, the direct confirmation of their planetary status can be accomplished by radial-velocity measurements. However, such planets possess primordial envelopes of hydrogen and helium that make them unsuitable to life as we know it. The most exciting candidates -- and the ones that Kepler is specifically tasked with finding -- are super-Earth and Earth-sized planets orbiting within their stellar habitable zones. Kepler has just begun to identify such planet candidates, and it will identify many more as its baseline increases throughout the coming year. While the Kepler team has developed powerful tools to weed out the impostors, Spitzer possesses the unique ability to provide the final validation of these candidates as planets, namely by measuring the depth of the transit at infrared wavelengths. By combining the infrared and optical measurements of the transit depth with models of hypothetical stellar blends, we can definitively test the stellar-blend hypothesis. We propose to observe the transits of 20 candidate habitable-zone super-Earths to be identified by the Kepler Mission. The results from this Exploration Science Program will be twofold: First, we will definitively validate the first potentially habitable planets ever identified. Second, we will determine the rate of occurrence of impostors. This rate of false positives can then be applied to the much larger sample of candidates identified by Kepler, to deduce the true rate of planetary companions.

  12. Results of CCD Transit Photometry Testing for the Kepler Mission

    NASA Astrophysics Data System (ADS)

    Koch, D.; Witteborn, F.; Dunham, E.; Jenkins, J.; Borucki, W.; Webster, L.

    1999-12-01

    Transit signals produced by Earth-size planets in orbit around solar-like stars are of the order of 8e-5 and have durations from 4 to 16 hours for planets in or near the habitable zone. A mission to search for habitable planets has been proposed (Koch, et al., 1998). At the heart of the mission is an array of CCDs used to continuously measure the relative brightness variations of 100,000 dwarf stars for transits. A testbed facility has been constructed to determine the effects of various induced noise sources on the capability of a CCD photometer to maintain an instrument relative precision of better than 1e-5. The photometry facility includes: a simulated star field with an approximate solar spectrum, fast optics to simulate the space borne telescope, a thinned back-illuminated CCD similar to those to be used on the spacecraft operating at 1 Mpix/sec read rate, and shutterless operation. The test facility is thermally and mechanically isolated. Each source of noise is introduced in a controlled fashion and evaluated. Pointing noise or changing thermal conditions in the spacecraft can cause star-image motion at the milli-pixel level. These motions are imposed by piezo-electric devices that move the photometer relative to the star field. Transit signals as small as Earth-size transits of solar-like stars are generated and measured. This is accomplished by electrical self-heating and expansion of fine wires placed across many of the star apertures. The small decrease in stellar brightness is used to demonstrate that Earth-size planets can be detected under realistic noise conditions and at the shot-noise-limited level. The effects of imposing several noise sources are shown and the resulting detectability of planets is presented. This work is supported in part by the NASA Discovery program and NASA Ames. Koch, D., Borucki, W., Webster, L., Dunham, E., Jenkins, J., Marriott, J. and Reitsema, H. SPIE Conf. on Space Telescopes and Instruments V, 3356, 599-607 (1998)

  13. Kepler Mission: a mission to find Earth-size planets in the habitable zone

    NASA Astrophysics Data System (ADS)

    Borucki, William J.; Koch, David; Basri, Gibor; Brown, Timothy; Caldwell, Douglas; Devore, Edna; Dunham, Edward; Gautier, Thomas; Geary, John; Gilliland, Ronald; Gould, Alan; Howell, Steve; Jenkins, Jon

    2003-10-01

    The Kepler Mission is a NASA Discovery-class mission designed to continuously monitor the brightness of 100,000 main sequence stars to detect the transit of Earth-size and larger planets. It is a wide field of view photometer with a Schmidt-type telescope and an array of 42 CCDs covering the 100 sq. degree field-of-view (FOV). It has a 0.95 m aperture and a 1.4 m primary and is designed to attain a photometric precision of 20 parts per million (ppm) for 12th magnitude solar-like stars for a 6.5-hour transit duration. It will continuously observe 100,000 main sequence stars from 9th to 15th magnitude in the Cygnus constellation for a period of four years with a cadence of 4 measurements per hour. The photometer is scheduled to be launched in 2007 into heliocentric orbit. A ground-based program to classify all 450,000 stars brighter than 15th magnitude in the FOV and to conduct a detailed examination of a subset of the stars that show planetary companions is also planned. Hundreds of Earth-size planets should be detected if they are common around solar-like stars. Ground-based spectrometric observations of those stars with planetary companions will be made to determine the dependences of the frequency and size of terrestrial planets on stellar characteristics such as type and metallicity. A null result would imply that terrestrial planets are rare.

  14. Space Shuttle mission extension capability

    NASA Technical Reports Server (NTRS)

    Fraser, W. M., Jr.

    1984-01-01

    Space Shuttle missions are currently limited to 11 days, primarily due to depletion of the power reactants (hydrogen and oxygen). A power system Mission Extension Kit (MEK) is described which could provide the capability to stay on orbit 10 additional days. These extra days would benefit Space Station construction and missions such as materials processing, earth and celestial observation, and life science studies (Spacelab). Other constraints to longer missions which may dictate minor Orbiter modifications will be discussed. The power system MEK is particularly desirable because of its existing flight qualified hardware which can be delivered within 3 to 4 years.

  15. Advanced automation for space missions

    NASA Technical Reports Server (NTRS)

    Freitas, R. A., Jr.; Healy, T. J.; Long, J. E.

    1982-01-01

    A NASA/ASEE Summer Study conducted at the University of Santa Clara in 1980 examined the feasibility of using advanced artificial intelligence and automation technologies in future NASA space missions. Four candidate applications missions were considered: (1) An intelligent earth-sensing information system, (2) an autonomous space exploration system, (3) an automated space manufacturing facility, and (4) a self-replicating, growing lunar factory. The study assessed the various artificial intelligence and machine technologies which must be developed if such sophisticated missions are to become feasible by century's end.

  16. Systems engingeering for the Kepler Mission : a search for terrestrial planets

    NASA Technical Reports Server (NTRS)

    Duren, Riley M.; Dragon, Karen; Gunter, Steve Z.; Gautier, Nick; Koch, Dave; Harvey, Adam; Enos, Alan; Borucki, Bill; Sobeck, Charlie; Mayer, Dave; Jenkins, Jon; Thompson, Rick; Bachtell, Eric; Peters, Dan

    2004-01-01

    The Kepler mission will launch in 2007 and determine the distribution of earth-size planets (0.5 to 10 earth masses) in the habitable zones (HZs) of solar-like stars. The mission will monitor > 100,000 dwarf stars simultaneously for at least 4 years. Precision differential photometry will be used to detect the periodic signals of transiting planets. Kepler will also support asteroseismology by measuring the pressure-mode (p-mode) oscillations of selected stars. Key mission elements include a spacecraft bus and 0.95 meter, wide-field, CCD-based photometer injected into an earth-trailing heliocentric orbit by a 3-stage Delta II launch vehicle as well as a distributed Ground Segment and Follow-up Observing Program. The project is currently preparing for Preliminary Design Review (October 2004) and is proceeding with detailed design and procurement of long-lead components. In order to meet the unprecedented photometric precision requirement and to ensure a statistically significant result, the Kepler mission involves technical challenges in the areas of photometric noise and systematic error reduction, stability, and false-positive rejection. Programmatic and logistical challenges include the collaborative design, modeling, integration, test, and operation of a geographically and functionally distributed project. A very rigorous systems engineering program has evolved to address these challenges. This paper provides an overview of the Kepler systems engineering program, including some examples of our processes and techniques in areas such as requirements synthesis, validation & verification, system robustness design, and end-to-end performance modeling.

  17. Spitzer Space Telescope Spectroscopy of the Kepler Supernova Remnant

    NASA Technical Reports Server (NTRS)

    Roellig, T. L.; Onaka, T.

    2004-01-01

    The Infrared Spectrograph on the Spitzer Space Telescope was used for observations of the Kepler supernova remnant, with all four instrument modules targeted on the bright infrared knot located at 17h30m35.80s,-21d28m54.0s (J2000). The low spectral resolution modules data show a dust continuum spectrum consistent with dust grains heated by high-energy electrons, while the high resolution modules data show atomic emission line ratios consistent with excitation by a high velocity shock of greater than 100 kilometers per second and electron densities of approximately 1,000 per centimeter. The abundance ratios for the six detected elements show signs of heavy-element enhancement. This work is based on observations made with the Spitzer Space Telescope, which is operated by the Jet Propulsion Laboratory, California Institute of Technology. Support for this work was provided by NASA's Office of Space Science.

  18. Space Shuttle Missions Summary

    NASA Technical Reports Server (NTRS)

    Bennett, Floyd V.; Legler, Robert D.

    2011-01-01

    This document has been produced and updated over a 21-year period. It is intended to be a handy reference document, basically one page per flight, and care has been exercised to make it as error-free as possible. This document is basically "as flown" data and has been compiled from many sources including flight logs, flight rules, flight anomaly logs, mod flight descent summary, post flight analysis of mps propellants, FDRD, FRD, SODB, and the MER shuttle flight data and inflight anomaly list. Orbit distance traveled is taken from the PAO mission statistics.

  19. VizieR Online Data Catalog: Kepler Mission. VIII. 285 false positives (Abdul-Masih+, 2016)

    NASA Astrophysics Data System (ADS)

    Abdul-Masih, M.; Prsa, A.; Conroy, K.; Bloemen, S.; Boyajian, T.; Doyle, L. R.; Johnston, C.; Kostov, V.; Latham, D. W.; Matijevic, G.; Shporer, A.; Southworth, J.

    2016-08-01

    The Kepler mission was launched in 2009 and provided photometric data for ~200000 objects in the 105deg2 contained in the Kepler field of view (FOV; Batalha et al. 2013, Cat. J/ApJS/204/24). Each of the 95 million Kepler pixels cover 3.98*3.98'' and are designed to maximize the number of resolvable stars with magnitudes brighter than 15. There are approximately 500000 objects in the Kepler FOV that are brighter than V=16; however, only ~200000 were assigned as targets for observation, leaving many bright objects in the field unobserved. Since the main goal of Kepler is to find Earth-sized planets in the habitable zone of Sun-like stars, the targets that were chosen for observation were those with the highest potential for terrestrial planet detection. Thus, many objects in the Kepler FOV have not been observed. Due to the proximity of some of these unobserved objects to the identified targets, the possibility of contaminated signals arises. Of the observed targets, 2772 eclipsing binaries have been found and cataloged in the Kepler Eclipsing Binary Catalog (http://keplerebs.villanova.edu/; see also Kirk et al. 2016, Cat. J/AJ/151/68). A false positive is a case where the signal from a binary object in close proximity to a target contaminates the aperture pixels, causing the target light curve to show a binary signal. This means that the incorrect object is being identified as the source of the binary signal. Once the source of the binary signal is identified, a new light curve can be extracted. The re-extraction process is comprised of several automated steps and results in three new light curves generated for the true source of the binary signal for each quarter of available data. These light curves are generated by optimizing the signal-to-noise ratio (S/N light curve), percent eclipse depth (PED light curve), and flux eclipse depth (FED light curve). Before re-extracting the new light curves, we obtain the S/N, the PED, and the FED for the original false

  20. DETECTION OF POTENTIAL TRANSIT SIGNALS IN THE FIRST 12 QUARTERS OF KEPLER MISSION DATA

    SciTech Connect

    Tenenbaum, Peter; Jenkins, Jon M.; Seader, Shawn; Burke, Christopher J.; Christiansen, Jessie L.; Rowe, Jason F.; Caldwell, Douglas A.; Clarke, Bruce D.; Li, Jie; Quintana, Elisa V.; Smith, Jeffrey C.; Thompson, Susan E.; Twicken, Joseph D.; Girouard, Forrest R. [Orbital Sciences Corporation and others

    2013-05-01

    We present the results of a search for potential transit signals in the first three years of photometry data acquired by the Kepler mission. The targets of the search include 112,321 targets that were observed over the full interval and an additional 79,992 targets that were observed for a subset of the full interval. From this set of targets we find a total of 11,087 targets that contain at least one signal that meets the Kepler detection criteria: periodicity of the signal, an acceptable signal-to-noise ratio, and three tests that reject false positives. Each target containing at least one detected signal is then searched repeatedly for additional signals, which represent multi-planet systems of transiting planets. When targets with multiple detections are considered, a total of 18,406 potential transiting planet signals are found in the Kepler mission data set. The detected signals are dominated by events with relatively low signal-to-noise ratios and by events with relatively short periods. The distribution of estimated transit depths appears to peak in the range between 20 and 30 parts per million, with a few detections down to fewer than 10 parts per million. The detections exhibit signal-to-noise ratios from 7.1{sigma}, which is the lower cutoff for detections, to over 10,000{sigma}, and periods ranging from 0.5 days, which is the shortest period searched, to 525 days, which is the upper limit of achievable periods given the length of the data set and the requirement that all detections include at least three transits. The detected signals are compared to a set of known transit events in the Kepler field of view, many of which were identified by alternative methods; the comparison shows that the current search recovery rate for targets with known transit events is 98.3%.

  1. Kepler-15b: A Hot Jupiter Enriched in Heavy Elements and the First Kepler Mission Planet Confirmed with the Hobby-Eberly Telescope

    NASA Astrophysics Data System (ADS)

    Endl, Michael; MacQueen, Phillip J.; Cochran, William D.; Brugamyer, Erik J.; Buchhave, Lars A.; Rowe, Jason; Lucas, Phillip; Isaacson, Howard; Bryson, Steve; Howell, Steve B.; Fortney, Jonathan J.; Hansen, Terese; Borucki, William J.; Caldwell, Douglas; Christiansen, Jessie L.; Ciardi, David R.; Demory, Brice-Olivier; Everett, Mark; Ford, Eric B.; Haas, Michael R.; Holman, Matthew J.; Horch, Elliott; Jenkins, Jon M.; Koch, David J.; Lissauer, Jack J.; Machalek, Pavel; Still, Martin; Welsh, William F.; Sanderfer, Dwight T.; Seader, Shawn E.; Smith, Jeffrey C.; Thompson, Susan E.; Twicken, Joseph D.

    2011-11-01

    We report the discovery of Kepler-15b (KOI-128), a new transiting exoplanet detected by NASA's Kepler mission. The transit signal with a period of 4.94 days was detected in the quarter 1 (Q1) Kepler photometry. For the first time, we have used the High Resolution Spectrograph (HRS) at the Hobby-Eberly Telescope (HET) to determine the mass of a Kepler planet via precise radial velocity (RV) measurements. The 24 HET/HRS RVs and 6 additional measurements from the Fibre-fed Échelle Spectrograph spectrograph at the Nordic Optical Telescope reveal a Doppler signal with the same period and phase as the transit ephemeris. We used one HET/HRS spectrum of Kepler-15 taken without the iodine cell to determine accurate stellar parameters. The host star is a metal-rich ([Fe/H] = 0.36 ± 0.07) G-type main-sequence star with T eff = 5515 ± 124 K. The semi-amplitude K of the RV orbit is 78.7+8.5 -9.5 m s-1, which yields a planet mass of 0.66 ± 0.1 M Jup. The planet has a radius of 0.96 ± 0.06 R Jup and a mean bulk density of 0.9 ± 0.2 g cm-3. The radius of Kepler-15b is smaller than the majority of transiting planets with similar mass and irradiation level. This suggests that the planet is more enriched in heavy elements than most other transiting giant planets. For Kepler-15b we estimate a heavy element mass of 30-40 M ⊕. Based on observations obtained with the Hobby-Eberly Telescope, which is a joint project of the University of Texas at Austin, the Pennsylvania State University, Stanford University, Ludwig-Maximilians-Universität München, and Georg-August-Universität Göttingen.

  2. KEPLER-15b: A HOT JUPITER ENRICHED IN HEAVY ELEMENTS AND THE FIRST KEPLER MISSION PLANET CONFIRMED WITH THE HOBBY-EBERLY TELESCOPE

    SciTech Connect

    Endl, Michael; MacQueen, Phillip J.; Cochran, William D.; Brugamyer, Erik J.; Buchhave, Lars A.; Rowe, Jason; Lucas, Phillip; Isaacson, Howard; Bryson, Steve; Howell, Steve B.; Borucki, William J.; Caldwell, Douglas; Christiansen, Jessie L.; Haas, Michael R.; Fortney, Jonathan J.; Hansen, Terese; Ciardi, David R.; Everett, Mark; Ford, Eric B.; and others

    2011-11-01

    We report the discovery of Kepler-15b (KOI-128), a new transiting exoplanet detected by NASA's Kepler mission. The transit signal with a period of 4.94 days was detected in the quarter 1 (Q1) Kepler photometry. For the first time, we have used the High Resolution Spectrograph (HRS) at the Hobby-Eberly Telescope (HET) to determine the mass of a Kepler planet via precise radial velocity (RV) measurements. The 24 HET/HRS RVs and 6 additional measurements from the Fibre-fed Echelle Spectrograph spectrograph at the Nordic Optical Telescope reveal a Doppler signal with the same period and phase as the transit ephemeris. We used one HET/HRS spectrum of Kepler-15 taken without the iodine cell to determine accurate stellar parameters. The host star is a metal-rich ([Fe/H] = 0.36 {+-} 0.07) G-type main-sequence star with T{sub eff} = 5515 {+-} 124 K. The semi-amplitude K of the RV orbit is 78.7{sup +8.5}{sub -9.5} m s{sup -1}, which yields a planet mass of 0.66 {+-} 0.1 M{sub Jup}. The planet has a radius of 0.96 {+-} 0.06 R{sub Jup} and a mean bulk density of 0.9 {+-} 0.2 g cm{sup -3}. The radius of Kepler-15b is smaller than the majority of transiting planets with similar mass and irradiation level. This suggests that the planet is more enriched in heavy elements than most other transiting giant planets. For Kepler-15b we estimate a heavy element mass of 30-40 M{sub Circled-Plus }.

  3. Target Characterization and Follow-Up Observations in Support of the Kepler Mission

    NASA Technical Reports Server (NTRS)

    Latham, David W.

    2003-01-01

    A variety of experiments were carried out to investigate the number and characteristics of the stars to be included in the Kepler Input Catalog. One result of this work was the proposal that the 2MASS Catalog of astrometry and photometry in the infrared be used as the primary source for the initial selection of candidate target stars, because this would naturally decrease the number of unsuitable hot blue stars and would also increase the number of desirable solar-type dwarf stars. Another advantage of the 2MASS catalogue is that the stellar positions have more than adequate astrometric accuracy for the Kepler target selection. The original plan reported in the Concept Study Report was to use the parallaxes and multi-band photometry from the FAME mission to provide the information needed for reliable separation of giants and dwarfs. As a result of NASA's withdrawal of support for FAME an alternate approach was needed. In November 2002 we proposed to the Kepler Science Team that a ground-based multi-band photometric survey could help alleviate the loss of the FAME data. The Science Team supported this proposal strongly, and we undertook a survey of possible facilities for such a survey. We concluded that the SAO's 4Shooter CCD camera on the 1.2-m telescope at the Whipple Observatory on Mount Hopkins, Arizona, showed promise for this work.

  4. Kepler Mission Design, Realized Photometric Performance, and Early Science

    DTIC Science & Technology

    2010-04-20

    designed with the explicit capability to detect Earth- size planets in the habitable zone of solar-like stars using the transit photometry method...that can be used to distinguish dwarf stars from red giants. Key words: instrumentation: photometers – planetary systems – space vehicles: instruments...characteristics. The method of choice is transit photometry (Pont et al. 2009), which provides the orbital period and size of the planet relative to its

  5. HD 24355 observed by the Kepler K2 mission: a rapidly oscillating Ap star pulsating in a distorted quadrupole mode

    NASA Astrophysics Data System (ADS)

    Holdsworth, Daniel L.; Kurtz, Donald W.; Smalley, Barry; Saio, Hideyuki; Handler, Gerald; Murphy, Simon J.; Lehmann, Holger

    2016-10-01

    We present an analysis of the first Kepler K2 mission observations of a rapidly oscillating Ap (roAp) star, HD 24355 (V = 9.65). The star was discovered in SuperWASP broad-band photometry with a frequency of 224.31 d-1 (2596.18 μHz; P = 6.4 min) and an amplitude of 1.51 mmag, with later spectroscopic analysis of low-resolution spectra showing HD 24355 to be an A5 Vp SrEu star. The high-precision K2 data allow us to identify 13 rotationally split sidelobes to the main pulsation frequency of HD 24355. This number of sidelobes combined with an unusual rotational phase variation show this star to be the most distorted quadrupole roAp pulsator yet observed. In modelling this star, we are able to reproduce well the amplitude modulation of the pulsation, and find a close match to the unusual phase variations. We show this star to have a pulsation frequency higher than the critical cut-off frequency. This is currently the only roAp star observed with the Kepler spacecraft in short cadence mode that has a photometric amplitude detectable from the ground, thus allowing comparison between the mmag amplitude ground-based targets and the μmag spaced-based discoveries. No further pulsation modes are identified in the K2 data, showing this star to be a single-mode pulsator.

  6. White Label Space GLXP Mission

    NASA Astrophysics Data System (ADS)

    Barton, A.

    2012-09-01

    This poster presents a lunar surface mission concept and corresponding financing approach developed by the White Label Space team, an official competitor in the Google Lunar X PRIZE. The White Label Space team's origins were in the European Space Agency's ESTEC facility in the Netherlands. Accordingly the team's technical headquarters are located just outside ESTEC in the Space Business Park. The team has active partners in Europe, Japan and Australia. The team's goal is to provide a unique publicity opportunity for global brands to land on the moon and win the prestigious Google Lunar X PRIZE. The poster presents the main steps to achieve this goal, the cost estimates for the mission, describes the benefits to the potential sponsors and supporters, and details the progress achieved to date.

  7. Space Mission : Y3K

    NASA Astrophysics Data System (ADS)

    2001-01-01

    ESA and the APME are hosting a contest for 10 - 15 year olds in nine European countries (Austria, Belgium, France, Germany, Italy, the Netherlands, Spain, Sweden and the United Kingdom). The contest is based on an interactive CD ROM, called Space Mission: Y3K, which explores space technology and shows some concrete uses of that technology in enhancing the quality of life on Earth. The CD ROM invites kids to join animated character Space Ranger Pete on an action-packed, colourful journey through space. Space Ranger Pete begins on Earth: the user navigates around a 'locker room' to learn about synthetic materials used in rocket boosters, heat shields, space suits and helmets, and how these materials have now become indispensable to everyday life. From Earth he flies into space and the user follows him from the control room in the spacecraft to a planet, satellites and finally to the International Space Station. Along the way, the user jots down clues that he or she discovers in this exploration, designing an imaginary space community and putting together a submission for the contest. The lucky winners will spend a weekend training as "junior astronauts" at the European Space Centre in Belgium (20-22 April 2001). They will be put through their astronaut paces, learning the art of space walking, running their own space mission, piloting a space capsule and re-entering the Earth's atmosphere. The competition features in various youth media channels across Europe. In the UK, popular BBC Saturday morning TV show, Live & Kicking, will be launching the competition and will invite viewers to submit their space community designs to win a weekend at ESC. In Germany, high circulation children's magazine Geolino will feature the competition in the January issue and on their internet site. And youth magazine ZoZitDat will feature the competition in the Netherlands throughout February. Space Mission: Y3K is part of an on-going partnership between the ESA's Technology Transfer

  8. VizieR Online Data Catalog: Minima of 41 binaries from entire Kepler mission (Gies+, 2015)

    NASA Astrophysics Data System (ADS)

    Gies, D. R.; Matson, R. A.; Guo, Z.; Lester, K. V.; Orosz, J. A.; Peters, G. J.

    2016-06-01

    We embarked on a search for eclipse timing variations among a subset of 41 eclipsing binaries that were identified prior to the start of Kepler observations (see our first paper, Gies et al. 2012, cat. J/AJ/143/137). Our first paper documented the eclipse times in observations made over quarters Q0-Q9 (2009.3-2011.5). Now with the Kepler mission complete with observations through Q17 (ending 2013.4), we present here the eclipse timings for our sample of 41 binaries over the entire duration of the mission. The associated times given in our first paper were based upon UTC (Coordinated Universal Time) while the current set uses TDB (Barycentric Dynamical Time), and here we report the times in reduced Barycentric Julian Date (BJD-2400000 days). We used the Simple Aperture Photometry (SAP) flux except in the case of KIC04678873. The list of targets appears in Table1. The eclipse timing measurements were made in almost the same way as described in our first paper. Our measurements appear in Table2. (2 data files).

  9. Defining Space Mission Architects for the Smaller Missions

    NASA Technical Reports Server (NTRS)

    Anderson, C.

    1999-01-01

    The definition of the Space Mission Architect (SMA) must be clear in both technical and human terms if we expect to train and/or to find people needed to architect the numbers of smaller missions expected in the future.

  10. Detecting non-uniform period spacings in the Kepler photometry of γ Doradus stars: methodology and case studies

    NASA Astrophysics Data System (ADS)

    Van Reeth, T.; Tkachenko, A.; Aerts, C.; Pápics, P. I.; Degroote, P.; Debosscher, J.; Zwintz, K.; Bloemen, S.; De Smedt, K.; Hrudkova, M.; Raskin, G.; Van Winckel, H.

    2015-02-01

    Context. The analysis of stellar oscillations is one of the most reliable ways to probe stellar interiors. Recent space missions such as Kepler have provided us with an opportunity to study these oscillations with unprecedented detail. For many multi-periodic pulsators such as γ Doradus stars, this led to the detection of dozens to hundreds of oscillation frequencies that could not be found from ground-based observations. Aims: We aim to detect non-uniform period spacings in the Fourier spectra of a sample of γ Doradus stars observed by Kepler. Such detection is complicated by both the large number of significant frequencies in the space photometry and by overlapping non-equidistant rotationally split multiplets. Methods: Guided by theoretical properties of gravity-mode oscillation of γ Doradus stars, we developed a period-spacing detection method and applied it to Kepler observations of a few stars, after having tested the performance from simulations. Results: The application of the technique resulted in the clear detection of non-uniform period spacing series for three out of the five treated Kepler targets. Disadvantages of the technique are also discussed, and include the disability to distinguish between different values of the spherical degree and azimuthal order of the oscillation modes without additional theoretical modelling. Conclusions: Despite the shortcomings, the method is shown to allow solid detections of period spacings for γ Doradus stars, which will allow future asteroseismic analyses of these stars. Based on data gathered with the NASA Discovery mission Kepler and the HERMES spectrograph, which is installed at the Mercator Telescope, operated on the island of La Palma by the Flemish Community at the Spanish Observatorio del Roque de los Muchachos of the Instituto de Astrofísica de Canarias, and supported by the Fund for Scientific Research of Flanders (FWO), Belgium, the Research Council of KU Leuven, Belgium, the Fonds National de la

  11. Space Shuttle mission: STS-67

    NASA Astrophysics Data System (ADS)

    1995-03-01

    The Space Shuttle Endeavor, scheduled to launch March 2, 1995 from NASA's Kennedy Space Center, will conduct NASA's longest Shuttle flight prior to date. The mission, designated STS-67, has a number of experiments and payloads, which the crew, commanded by Stephen S. Oswald, will have to oversee. This NASA press kit for the mission contains a general background (general press release, media services information, quick-look facts page, shuttle abort modes, summary timeline, payload and vehicle weights, orbital summary, and crew responsibilities); cargo bay payloads and activities (Astro 2, Get Away Special Experiments); in-cabin payloads (Commercial Minimum Descent Altitude Instrumentation Technology Associates Experiments, protein crystal growth experiments, Middeck Active Control Experiment, and Shuttle Amateur Radio Experiment); and the STS-67 crew biographies. The payloads and experiments are described and summarized to give an overview of the goals, objectives, apparatuses, procedures, sponsoring parties, and the assigned crew members to carry out the tasks.

  12. Space Shuttle mission: STS-67

    NASA Technical Reports Server (NTRS)

    1995-01-01

    The Space Shuttle Endeavor, scheduled to launch March 2, 1995 from NASA's Kennedy Space Center, will conduct NASA's longest Shuttle flight prior to date. The mission, designated STS-67, has a number of experiments and payloads, which the crew, commanded by Stephen S. Oswald, will have to oversee. This NASA press kit for the mission contains a general background (general press release, media services information, quick-look facts page, shuttle abort modes, summary timeline, payload and vehicle weights, orbital summary, and crew responsibilities); cargo bay payloads and activities (Astro 2, Get Away Special Experiments); in-cabin payloads (Commercial Minimum Descent Altitude Instrumentation Technology Associates Experiments, protein crystal growth experiments, Middeck Active Control Experiment, and Shuttle Amateur Radio Experiment); and the STS-67 crew biographies. The payloads and experiments are described and summarized to give an overview of the goals, objectives, apparatuses, procedures, sponsoring parties, and the assigned crew members to carry out the tasks.

  13. System Engineering Challenges of Future Space Missions

    NASA Technical Reports Server (NTRS)

    Hyde, Tristam Tupper

    2005-01-01

    A viewgraph presentation on the system engineering challenges that face NASA's future space missions is shown. The topics include: 1) Future Space Missions; 2) Trends; and 3) Developing System Engineers.

  14. Compaction of Space Mission Wastes

    NASA Technical Reports Server (NTRS)

    Fisher, John; Pisharody, Suresh; Wignarajah, K.

    2004-01-01

    The current solid waste management system employed on the International Space Station (ISS) consists of compaction, storage, and disposal. Wastes such plastic food packaging and trash are compacted manually and wrapped in duct tape footballs by the astronauts. Much of the waste is simply loaded either into the empty Russian Progress vehicle for destruction on reentry or into Shuttle for return to Earth. This manual method is wasteful of crew time and does not transition well to far term missions. Different wastes onboard spacecraft vary considerably in their characteristics and in the appropriate method of management. In advanced life support systems for far term missions, recovery of resources such as water from the wastes becomes important. However waste such as plastic food packaging, which constitutes a large fraction of solid waste (roughly 21% on ISS, more on long duration missions), contains minimal recoverable resource. The appropriate management of plastic waste is waste stabilization and volume minimization rather than resource recovery. This paper describes work that has begun at Ames Research Center on development of a heat melt compactor that can be used on near term and future missions, that can minimize crew interaction, and that can handle wastes with a significant plastic composition. The heat melt compactor takes advantage of the low melting point of plastics to compact plastic materials using a combination of heat and pressure. The US Navy has demonstrated successful development of a similar unit for shipboard application. Ames is building upon the basic approach demonstrated by the Navy to develop an advanced heat melt type compactor for space mission type wastes.

  15. DETECTION OF POTENTIAL TRANSIT SIGNALS IN THE FIRST THREE QUARTERS OF Kepler MISSION DATA

    SciTech Connect

    Tenenbaum, Peter; Christiansen, Jessie L.; Jenkins, Jon M.; Rowe, Jason F.; Seader, Shawn; Caldwell, Douglas A.; Clarke, Bruce D.; Li, Jie; Quintana, Elisa V.; Smith, Jeffrey C.; Stumpe, Martin C.; Thompson, Susan E.; Twicken, Joseph D.; Van Cleve, Jeffrey; Girouard, Forrest R.; Klaus, Todd C. [Orbital Sciences Corporation and others

    2012-03-01

    We present the results of a search for potential transit signals in the first three quarters of photometry data acquired by the Kepler mission. The targets of the search include 151,722 stars which were observed over the full interval and an additional 19,132 stars which were observed for only one or two quarters. From this set of targets we find a total of 5392 detections which meet the Kepler detection criteria: those criteria are periodicity of signal, an acceptable signal-to-noise ratio, and a composition test which rejects spurious detections which contain non-physical combinations of events. The detected signals are dominated by events with relatively low signal-to-noise ratio and by events with relatively short periods. The distribution of estimated transit depths appears to peak in the range between 40 and 100 parts per million, with a few detections down to fewer than 10 parts per million. The detections exhibit signal-to-noise ratios from 7.1{sigma}, which is the lower cutoff for detections, to over 10,000{sigma}, and periods ranging from 0.5 days, which is the lower cutoff used in the procedure, to 109 days, which is the upper limit of achievable periods given the length of the data set and the criteria used for detections. The detected signals are compared to a set of known transit events in the Kepler field of view which were derived by a different method using a longer data interval; the comparison shows that the current search correctly identified 88.1% of the known events. A tabulation of the detected transit signals, examples which illustrate the analysis and detection process, a discussion of future plans and open, potentially fruitful, areas of further research are included.

  16. Generating an optimal target list for a space mission dedicated to transit spectroscopy

    NASA Astrophysics Data System (ADS)

    Zingales, Tiziano

    2016-10-01

    Nowadays several space missions and ground-based surveys discovered more than 3000 exoplanets. The characterization of their atmospheres is necessary to understand how were they formed, how do they evolve, how are they affected by starlight, stellar winds and other fundamental questions. ARIEL and Twinkle are two dedicated space mission for the study of exoplanetary atmospheres. ARIEL is one the three candidates for the next ESA medium class mission expected to be launched in 2026. Twinkle, proposed to be launched in 2019, is a small, low-cost mission. In order to draft the target lists of the two missions, it is important to look for the best targets that can be observed with the instrumentationassembled on the two satellites. The final lists have to take into account both the number of already known exoplanets and the number of existing exoplanets still not discovered (thanks to the Kepler space mission we can estimate the occurrence rate of exoplanets around the stars, Fressin et al, 2013). Future space missions (GAIA, Cheops, PLATO, Kepler II and TESS) and ground-based surveys will deliver many new exoplanets in the next decade. For this reason a trustworthy target list of exoplanets for a space mission planned to be launched in 2026 (or 2019) needs to take intoaccount a more complete list than the currently available.

  17. The Spitzer Space Telescope Mission

    NASA Technical Reports Server (NTRS)

    Werner, M. W.

    2005-01-01

    The Spitzer Space Telescope, NASA's Great Observatory for infrared astronomy, was launched 2003 August 25 and is returning excellent scientific data from its Earth-trailing solar orbit. Spitzer combines the intrinsic sensitivity achievable with a cryogenic telescope in space with the great imaging and spectroscopic power of modern detector arrays to provide the user community with huge gains in capability for exploration of the cosmos in the infrared. The observatory systems are largely performing as expected, and the projected cryogenic lifetime is about five years. Spitzer is thus both a scientific and a technical precursor to the infrared astronomy missions of the future. This very brief paper refers interested readers to several sets of recent publications which describe both the scientific and the technical features of Spitzer in detail. Note that, until 2003 December, Spitzer was known as the Space Infrared Telescope Facility (SIRTF).

  18. DETECTION OF POTENTIAL TRANSIT SIGNALS IN 16 QUARTERS OF KEPLER MISSION DATA

    SciTech Connect

    Tenenbaum, Peter; Jenkins, Jon M.; Seader, Shawn; Burke, Christopher J.; Christiansen, Jessie L.; Rowe, Jason F.; Caldwell, Douglas A.; Clarke, Bruce D.; Coughlin, Jeffrey L.; Li, Jie; Quintana, Elisa V.; Smith, Jeffrey C.; Thompson, Susan E.; Twicken, Joseph D.; Campbell, Jennifer R.; Girouard, Forrest R. [Orbital Sciences Corporation and others

    2014-03-01

    We present the results of a search for potential transit signals in 4 yr of photometry data acquired by the Kepler mission. The targets of the search include 111,800 stars which were observed for the entire interval and 85,522 stars which were observed for a subset of the interval. We found that 9743 targets contained at least one signal consistent with the signature of a transiting or eclipsing object where the criteria for detection are periodicity of the detected transits, adequate signal-to-noise ratio, and acceptance by a number of tests which reject false positive detections. When targets that had produced a signal were searched repeatedly, an additional 6542 signals were detected on 3223 target stars, for a total of 16,285 potential detections. Comparison of the set of detected signals with a set of known and vetted transit events in the Kepler field of view shows that the recovery rate for these signals is 96.9%. The ensemble properties of the detected signals are reviewed.

  19. Kepler Orrery

    NASA Video Gallery

    Animation showing all the multiple-planet systems discovered by Kepler as of 2/2/2011; orbits go through the entire mission (3.5 years). Hot colors to cool colors (Red to yellow to green to cyan to...

  20. Precise time series photometry for the Kepler-2.0 mission

    NASA Astrophysics Data System (ADS)

    Aigrain, S.; Hodgkin, S. T.; Irwin, M. J.; Lewis, J. R.; Roberts, S. J.

    2015-03-01

    The recently approved NASA K2 mission has the potential to multiply by an order of magnitude the number of short-period transiting planets found by Kepler around bright and low-mass stars, and to revolutionize our understanding of stellar variability in open clusters. However, the data processing is made more challenging by the reduced pointing accuracy of the satellite, which has only two functioning reaction wheels. We present a new method to extract precise light curves from K2 data, combining list-driven, soft-edged aperture photometry with a star-by-star correction of systematic effects associated with the drift in the roll angle of the satellite about its boresight. The systematics are modelled simultaneously with the stars' intrinsic variability using a semiparametric Gaussian process model. We test this method on a week of data collected during an engineering test in 2014 January, perform checks to verify that our method does not alter intrinsic variability signals, and compute the precision as a function of magnitude on long-cadence (30 min) and planetary transit (2.5 h) time-scales. In both cases, we reach photometric precisions close to the precision reached during the nominal Kepler mission for stars fainter than 12th magnitude, and between 40 and 80 parts per million for brighter stars. These results confirm the bright prospects for planet detection and characterization, asteroseismology and stellar variability studies with K2. Finally, we perform a basic transit search on the light curves, detecting two bona fide transit-like events, seven detached eclipsing binaries and 13 classical variables.

  1. Challenges of Space Mission Interoperability

    NASA Technical Reports Server (NTRS)

    Martin, Warren L.; Hooke, Adrian J.

    2007-01-01

    This viewgraph presentation reviews some of the international challenges to space mission interoperability. Interoperability is the technical capability of two or more systems or components to exchange information and to use the information that has been exchanged. One of the challenges that is addressed is the problem of spectrum bandwidth, and interference. The key to interoperability is the standardization of space communications services and protocols. Various levels of international cross support are reviewed: harmony, cooperation cross support and confederation cross support. The various international bodies charged with implementing cross support are reviewed. The goal of the Interagency Operations Advisory Group (IOAG) is to achieve plug-and-play operations where all that is required is for each of the systems to use an agreed communications medium, after which the systems configure each other for the purpose of exchanging information and subsequently effect such exchange automatically.

  2. Horizon Missions Technology Study. [for space exploration

    NASA Technical Reports Server (NTRS)

    Anderson, John L.

    1992-01-01

    The purpose of the HMT Study was to develop and demonstrate a systematic methodology for identifying and evaluating innovative technology concepts offering revolutionary, breadkthrough-type capabilities for advanced space missions and for assessing their potential mission impact. The methodology is based on identifying the new functional, operational and technology capabilities needed by hypothetical 'Horizon' space missions that have performance requirements that cannot be met, even by extrapolating known space technologies. Nineteen Horizon Missions were selected to represent a collective vision of advanced space missions of the mid-21st century. The missions typically would occur beyond the lifetime of current or planned space assets. The HM methodology and supporting data base may be used for advanced technology planning, advanced mission planning and multidisciplinary studies and analyses.

  3. Detection of Potential Transit Signals in 17 Quarters of Kepler Mission Data

    NASA Astrophysics Data System (ADS)

    Seader, Shawn; Jenkins, Jon M.; Tenenbaum, Peter; Twicken, Joseph D.; Smith, Jeffrey C.; Morris, Rob; Catanzarite, Joseph; Clarke, Bruce D.; Li, Jie; Cote, Miles T.; Burke, Christopher J.; McCauliff, Sean; Girouard, Forrest R.; Campbell, Jennifer R.; Kamal Uddin, Akm; Zamudio, Khadeejah A.; Sabale, Anima; Henze, Christopher E.; Thompson, Susan E.; Klaus, Todd C.

    2015-03-01

    We present the results of a search for potential transit signals in the full 17-quarter data set collected during Kepler's primary mission that ended on 2013 May 11, due to the on board failure of a second reaction wheel needed to maintain high precision, fixed, pointing. The search includes a total of 198,646 targets, of which 112,001 were observed in every quarter and 86,645 were observed in a subset of the 17 quarters. For the first time, this multi-quarter search is performed on data that have been fully and uniformly reprocessed through the newly released version of the Data Processing Pipeline. We find a total of 12,669 targets that contain at least one signal that meets our detection criteria: periodicity of the signal, a minimum of three transit events, an acceptable signal-to-noise ratio, and four consistency tests that suppress many false positives. Each target containing at least one transit-like pulse sequence is searched repeatedly for other signals that meet the detection criteria, indicating a multiple planet system. This multiple planet search adds an additional 7698 transit-like signatures for a total of 20,367. Comparison of this set of detected signals with a set of known and vetted transiting planet signatures in the Kepler field of view shows that the recovery rate of the search is 90.3%. We review ensemble properties of the detected signals and present various metrics useful in validating these potential planetary signals. We highlight previously undetected transit-like signatures, including several that may represent small objects in the habitable zone of their host stars.

  4. SOPHIE velocimetry of Kepler transit candidates

    NASA Astrophysics Data System (ADS)

    Santerne, A.; Moutou, C.; Bouchy, F.; Hébrard, G.; Deleuil, M.; Díaz, R. F.; Bonomo, A. S.; Almenara, J.-M.

    2011-10-01

    As CoRoT, the Kepler space mission found a large amount of planetary transit candidates for which radial velocity follow-up is necessary in order to establish the planetary nature and then, to characterize the mass of the transiting companion. We are following up some interesting Kepler candidates with the SOPHIE spectrograph mounted at the 1.93-m telescope in Observatoire de Haute Provence (France). More than one year after the first Kepler release, we will present the strategy used to select the most promising Kepler candidates, within reach of a detection with SOPHIE, using the experience of more than 4 years of CoRoT, SWASP and HAT radial velocity follow-up. We will also highlight the results of the first year of observations that led to the discovery of several new transiting exoplanets and help the understanding of the false positive rate of the Kepler mission.

  5. The Kepler Mission: A wide-field transit search for terrestrial planets [review article

    NASA Astrophysics Data System (ADS)

    Basri, Gibor; Borucki, William J.; Koch, David

    2005-11-01

    The Kepler Mission is a NASA Discovery mission which will continuously monitor the brightness of at least 100,000 main sequence stars, to detect the transits of terrestrial and larger planets. It is scheduled to be launched in 2007 into an Earth-trailing heliocentric orbit. It is a wide-field photometer with a Schmidt-type telescope and array of 42 CCDs covering the 100 square degree field-of-view. It has a 1-m aperture which enables a differential photometric precision of 2 parts in 100,000 for 12th magnitude solar-like stars over a 6.5-hour transit duration. It will continuously observe dwarf stars from 8th to 15th magnitude in the Cygnus constellation, for a period of four years, with a cadence of 4 measurements per hour. Hundreds of terrestrial planets should be detected if they are common around solar-type stars. Ground-based spectrometry of stars with planetary candidates will help eliminate false-positives, and determine stellar characteristics such as mass and metallicity. A null result would imply that terrestrial planets are rare.

  6. Second Epoch Hubble Space Telescope Imaging of Kepler's Supernova Remnant

    NASA Astrophysics Data System (ADS)

    Sankrit, Ravi; Blair, William P.; Borkowski, Kazimierz J.; Long, Knox S.; Patnaude, Daniel; Raymond, John C.; Reynolds, Stephen P.; Williams, Brian J.

    2015-01-01

    We have obtained new HST/WFC3 images of Kepler's supernova remnant in H-alpha (F656N) and [N II] (F658N) emission line filters. The bright radiative shocks in dense clumps are detected in both filters, while non-radiative shocks are seen as faint filaments only in the H-alpha image. Most of these Balmer filaments lie around the periphery of the remnant where the blast wave encounters partially neutral interstellar gas. We compare the new images with HST/ACS images taken nearly 10 years previously, and find that these filaments tracing the forward shock have moved 0.6"-0.9" between the two epochs. Assuming a distance of 4 kpc to the remnant, these proper motions correspond to shock velocities of 1160-1740 km/s, which are consistent with the published values, 1550-2000 km/s (e.g. Blair et al. 1991, ApJ 366, 484). We also find a few Balmer filaments with highly non-radial proper motions. In one particularly interesting case in the projected interior of the remnant, SE of the center, the shock appears to have wrapped around a sharp density enhancement and moved about 0.3" in the period between the observations.The images allow us to study the evolution of the shock around an ejecta knot, which is punching through the remnant boundary in the northwest. The forward shock, visible as an arcuate Balmer filament, has moved about 1". At the trailing edges, the system of radiative knots formed by Rayleigh-Taylor instabilities have undergone significant changes - some knots have disappeared, new ones have appeared, and many have changed in brightness. Elsewhere in the remnant we find changes in the relative intensities of many small, bright knots over the 10 year baseline, indicating the short radiative lifetimes of these features.This work has been supported in part by grant HST-GO-12885 to the Universities Space Research Association.

  7. Space Mission Human Reliability Analysis (HRA) Project

    NASA Technical Reports Server (NTRS)

    Boyer, Roger

    2014-01-01

    The purpose of the Space Mission Human Reliability Analysis (HRA) Project is to extend current ground-based HRA risk prediction techniques to a long-duration, space-based tool. Ground-based HRA methodology has been shown to be a reasonable tool for short-duration space missions, such as Space Shuttle and lunar fly-bys. However, longer-duration deep-space missions, such as asteroid and Mars missions, will require the crew to be in space for as long as 400 to 900 day missions with periods of extended autonomy and self-sufficiency. Current indications show higher risk due to fatigue, physiological effects due to extended low gravity environments, and others, may impact HRA predictions. For this project, Safety & Mission Assurance (S&MA) will work with Human Health & Performance (HH&P) to establish what is currently used to assess human reliabiilty for human space programs, identify human performance factors that may be sensitive to long duration space flight, collect available historical data, and update current tools to account for performance shaping factors believed to be important to such missions. This effort will also contribute data to the Human Performance Data Repository and influence the Space Human Factors Engineering research risks and gaps (part of the HRP Program). An accurate risk predictor mitigates Loss of Crew (LOC) and Loss of Mission (LOM).The end result will be an updated HRA model that can effectively predict risk on long-duration missions.

  8. Space Station Live: Robotic Refueling Mission

    NASA Video Gallery

    NASA Public Affairs Officer Dan Huot speaks with Robert Pickle, Robotic Refueling Mission ROBO lead, about the International Space Station demonstration of the tools, technologies and techniques to...

  9. NASA Missions Enabled by Space Nuclear Systems

    NASA Technical Reports Server (NTRS)

    Scott, John H.; Schmidt, George R.

    2009-01-01

    This viewgraph presentation reviews NASA Space Missions that are enabled by Space Nuclear Systems. The topics include: 1) Space Nuclear System Applications; 2) Trade Space for Electric Power Systems; 3) Power Generation Specific Energy Trade Space; 4) Radioisotope Power Generation; 5) Radioisotope Missions; 6) Fission Power Generation; 7) Solar Powered Lunar Outpost; 8) Fission Powered Lunar Outpost; 9) Fission Electric Power Generation; and 10) Fission Nuclear Thermal Propulsion.

  10. STS-38 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Camp, David W.; Germany, D. M.; Nicholson, Leonard S.

    1991-01-01

    The STS-38 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-seventh flight of the Space Shuttle and the seventh flight of the Orbiter vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-40/LWT-33), three Space Shuttle main engines (SSME's) (serial numbers 2019, 2022, 2027), and two Solid Rocket Boosters (SRB's), designated as BI-039. The STS-38 mission was a classified Department of Defense mission, and as much, the classified portions of the mission are not presented in this report. The sequence of events for this mission is shown. The significant problems that occurred in the Space Shuttle Orbiter subsystem during the mission are summarized and the official problem tracking list is presented. In addition, each Space Shuttle Orbiter problem is cited in the subsystem discussion.

  11. Spaceport operations for deep space missions

    NASA Technical Reports Server (NTRS)

    Holt, Alan C.

    1990-01-01

    Space Station Freedom is designed with the capability to cost-effectively evolve into a transportation node which can support manned lunar and Mars missions. To extend a permanent human presence to the outer planets (moon outposts) and to nearby star systems, additional orbiting space infrastructure and great advances in propulsion system and other technologies will be required. To identify primary operations and management requirements for these deep space missions, an interstellar design concept was developed and analyzed. The assembly, test, servicing, logistics resupply, and increment management techniques anticipated for lunar and Mars missions appear to provide a pattern which can be extended in an analogous manner to deep space missions. A long range, space infrastructure development plan (encompassing deep space missions) coupled with energetic, breakthrough level propulsion research should be initiated now to assist in making the best budget and schedule decisions.

  12. NASA mission planning for space nuclear power

    NASA Technical Reports Server (NTRS)

    Bennett, Gary L.; Schnyer, A. D.

    1991-01-01

    An evaluation is conducted of those aspects of the Space Exploration Initiative which stand to gain from the use of nuclear powerplants. Low-power, less than 10 kW(e) missions in question encompass the Comet Rendezvous Asteroid Flyby, the Cassini mission to Saturn, the Mars Network mission, a solar probe, the Mars Rover Sample Return mission, the Rosetta comet nucleus sample return mission, and an outer planets orbiter/probe. Reactor power yielding 10-100 kW(e) can be used by advanced rovers and initial lunar and Martian outposts, as well as Jovian and Saturnian grand tours and sample-return missions.

  13. Detection of Potential Transit Signals in 17 Quarters of Kepler Data: Results of the Final Kepler Mission Transiting Planet Search (DR25)

    NASA Astrophysics Data System (ADS)

    Twicken, Joseph D.; Jenkins, Jon M.; Seader, Shawn E.; Tenenbaum, Peter; Smith, Jeffrey C.; Brownston, Lee S.; Burke, Christopher J.; Catanzarite, Joseph H.; Clarke, Bruce D.; Cote, Miles T.; Girouard, Forrest R.; Klaus, Todd C.; Li, Jie; McCauliff, Sean D.; Morris, Robert L.; Wohler, Bill; Campbell, Jennifer R.; Kamal Uddin, Akm; Zamudio, Khadeejah A.; Sabale, Anima; Bryson, Steven T.; Caldwell, Douglas A.; Christiansen, Jessie L.; Coughlin, Jeffrey L.; Haas, Michael R.; Henze, Christopher E.; Sanderfer, Dwight T.; Thompson, Susan E.

    2016-12-01

    We present results of the final Kepler Data Processing Pipeline search for transiting planet signals in the full 17-quarter primary mission data set. The search includes a total of 198,709 stellar targets, of which 112,046 were observed in all 17 quarters and 86,663 in fewer than 17 quarters. We report on 17,230 targets for which at least one transit signature is identified that meets the specified detection criteria: periodicity, minimum of three observed transit events, detection statistic (i.e., signal-to-noise ratio) in excess of the search threshold, and passing grade on three statistical transit consistency tests. Light curves for which a transit signal is identified are iteratively searched for additional signatures after a limb-darkened transiting planet model is fitted to the data and transit events are removed. The search for additional planets adds 16,802 transit signals for a total of 34,032; this far exceeds the number of transit signatures identified in prior pipeline runs. There was a strategic emphasis on completeness over reliability for the final Kepler transit search. A comparison of the transit signals against a set of 3402 well-established, high-quality Kepler Objects of Interest yields a recovery rate of 99.8%. The high recovery rate must be weighed against a large number of false-alarm detections. We examine characteristics of the planet population implied by the transiting planet model fits with an emphasis on detections that would represent small planets orbiting in the habitable zone of their host stars.

  14. ROTATION PERIODS AND AGES OF SOLAR ANALOGS AND SOLAR TWINS REVEALED BY THE KEPLER MISSION

    SciTech Connect

    Do Nascimento Jr, J.-D.; Meibom, S.; García, R. A.; Salabert, D.; Ceillier, T.; Anthony, F.; Da Costa, J. S.; Castro, M.; Barnes, S. A.

    2014-08-01

    A new sample of solar analogs and twin candidates has been constructed and studied, paying particular attention to their light curves from NASA's Kepler mission. This Letter aims to assess their evolutionary status, derive their rotation and ages, and identify those which are solar analogs or solar twin candidates. We separate out the subgiants that compose a large fraction of the asteroseismic sample, and which show an increase in the average rotation period as the stars ascend the subgiant branch. The rotation periods of the dwarfs, ranging from 6 to 30 days and averaging 19 days, allow us to assess their individual evolutionary states on the main sequence and to derive their ages using gyrochronology. These ages are found to be in agreement with a correlation coefficient of r = 0.79 with independent asteroseismic ages, where available. As a result of this investigation, we are able to identify 34 stars as solar analogs and 22 of them as solar twin candidates.

  15. Space missions in the Arab countries

    NASA Astrophysics Data System (ADS)

    Mosalam Shaltout, M. A.

    Since about twenty years ago, artificial satellites for the Arab countries, were manufactured and released by developed countries for TV and communication purposes such as Arabsat, Nilesat, and Soryia. But with the starting of the 21st century, there are few space missions developed by Arab Countries in Cooperation with International Partners, in Alger, Saudi Arabia, and Egypt. Where: 1. The National Administration of Space Science and Technology in Alger developed two Experimental Space Missions released at November 2002 (AlgerSat-1), and November 2003 (AlgerSat-2). The program is still continuous for developing more space missions with High Technology for different purposes. 2. Space Research Institute in King Abd-Alaziz city for science and Technology, Riyadh, Saudi Arabia developed three space missions in collaboration with international partners, where the three missions are released for different purposes. 3. The National Authority for Remote Sensing and Space Sciences (NARSS) in Cairo-Egypt developed in cooperation with Ukraine a mission Egyptsat-1, by total price 30 million US, for the purpose of studding the desert geology and Environment. It will be released at October 2004. The program will be continued for developing more space mission by high technology. This paper describe in detail Arabian three programs for the three Arabian countries (Alger, Saudi Arabia, and Egypt), and will discuss on what we can expect for the future, focussing on international cooperation in the field of space science and technology.

  16. Target Charaterization and Follow-Up Observations in Support of the Kepler Mission

    NASA Technical Reports Server (NTRS)

    Latham, David W.

    2004-01-01

    This report covers work carried out at the Smithsonian Astrophysical Observatory during the period 1 December 2003 to 30 November 2004 to support efforts to prepare the Kepler Input Catalog. The Catalog will be used to select the targets observed for planetary transits by Kepler.

  17. STS-36 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Mechelay, Joseph E.; Germany, D. M.; Nicholson, Leonard S.

    1990-01-01

    The STS-36 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-fourth flight of the Space Shuttle and the sixth flight of the OV-104 Orbiter vehicle, Atlantis. In addition to the Atlantis vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-33/LWT-26), three Space Shuttle main engines (SSME's) (serial numbers 2019, 2030, and 2029), and two Solid Rocket Boosters (SRB's) (designated as BI-036). The STS-36 mission was a classified Department of Defense mission, and as such, the classified portions of the mission are not discussed. The unclassified sequence of events for this mission is shown in tabular form. Summarized are the significant problems that occurred in the Orbiter subsystems during the mission. The official problem tracking list is presented. In addition, each of the Orbiter problems is cited in the subsystem discussion.

  18. Space Interferometry Mission: Measuring the Universe

    NASA Technical Reports Server (NTRS)

    Marr, James; Dallas, Saterios; Laskin, Robert; Unwin, Stephen; Yu, Jeffrey

    1991-01-01

    The Space Interferometry Mission (SIM) will be the NASA Origins Program's first space based long baseline interferometric observatory. SIM will use a 10 m Michelson stellar interferometer to provide 4 microarcsecond precision absolute position measurements of stars down to 20th magnitude over its 5 yr. mission lifetime. SIM will also provide technology demonstrations of synthesis imaging and interferometric nulling. This paper describes the what, why and how of the SIM mission, including an overall mission and system description, science objectives, general description of how SIM makes its measurements, description of the design concepts now under consideration, operations concept, and supporting technology program.

  19. Low Cost Missions Operations on NASA Deep Space Missions

    NASA Astrophysics Data System (ADS)

    Barnes, R. J.; Kusnierkiewicz, D. J.; Bowman, A.; Harvey, R.; Ossing, D.; Eichstedt, J.

    2014-12-01

    The ability to lower mission operations costs on any long duration mission depends on a number of factors; the opportunities for science, the flight trajectory, and the cruise phase environment, among others. Many deep space missions employ long cruises to their final destination with minimal science activities along the way; others may perform science observations on a near-continuous basis. This paper discusses approaches employed by two NASA missions implemented by the Johns Hopkins University Applied Physics Laboratory (JHU/APL) to minimize mission operations costs without compromising mission success: the New Horizons mission to Pluto, and the Solar Terrestrial Relations Observatories (STEREO). The New Horizons spacecraft launched in January 2006 for an encounter with the Pluto system.The spacecraft trajectory required no deterministic on-board delta-V, and so the mission ops team then settled in for the rest of its 9.5-year cruise. The spacecraft has spent much of its cruise phase in a "hibernation" mode, which has enabled the spacecraft to be maintained with a small operations team, and minimized the contact time required from the NASA Deep Space Network. The STEREO mission is comprised of two three-axis stabilized sun-staring spacecraft in heliocentric orbit at a distance of 1 AU from the sun. The spacecraft were launched in October 2006. The STEREO instruments operate in a "decoupled" mode from the spacecraft, and from each other. Since STEREO operations are largely routine, unattended ground station contact operations were implemented early in the mission. Commands flow from the MOC to be uplinked, and the data recorded on-board is downlinked and relayed back to the MOC. Tools run in the MOC to assess the health and performance of ground system components. Alerts are generated and personnel are notified of any problems. Spacecraft telemetry is similarly monitored and alarmed, thus ensuring safe, reliable, low cost operations.

  20. Advanced automation for space missions: Technical summary

    NASA Technical Reports Server (NTRS)

    1980-01-01

    Several representative missions which would require extensive applications of machine intelligence were identified and analyzed. The technologies which must be developed to accomplish these types of missions are discussed. These technologies include man-machine communication, space manufacturing, teleoperators, and robot systems.

  1. STS-81 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1997-01-01

    STS-81 was the fifth of nine planned missions to dock with the Russian Mir Space Station and the fourth crewmember transfer mission. The double Spacehab module was carried for the second time, and it housed experiments that were performed by the crew and logistics equipment that was transferred to the Mir.

  2. Eighteenth Space Simulation Conference: Space Mission Success Through Testing

    NASA Technical Reports Server (NTRS)

    Stecher, Joseph L., III (Compiler)

    1994-01-01

    The Institute of Environmental Sciences' Eighteenth Space Simulation Conference, 'Space Mission Success Through Testing' provided participants with a forum to acquire and exchange information on the state-of-the-art in space simulation, test technology, atomic oxygen, program/system testing, dynamics testing, contamination, and materials. The papers presented at this conference and the resulting discussions carried out the conference theme 'Space Mission Success Through Testing.'

  3. Cloud Computing Techniques for Space Mission Design

    NASA Technical Reports Server (NTRS)

    Arrieta, Juan; Senent, Juan

    2014-01-01

    The overarching objective of space mission design is to tackle complex problems producing better results, and faster. In developing the methods and tools to fulfill this objective, the user interacts with the different layers of a computing system.

  4. The Deep Space Atomic Clock Mission

    NASA Technical Reports Server (NTRS)

    Ely, Todd A.; Koch, Timothy; Kuang, Da; Lee, Karen; Murphy, David; Prestage, John; Tjoelker, Robert; Seubert, Jill

    2012-01-01

    The Deep Space Atomic Clock (DSAC) mission will demonstrate the space flight performance of a small, low-mass, high-stability mercury-ion atomic clock with long term stability and accuracy on par with that of the Deep Space Network. The timing stability introduced by DSAC allows for a 1-Way radiometric tracking paradigm for deep space navigation, with benefits including increased tracking via utilization of the DSN's Multiple Spacecraft Per Aperture (MSPA) capability and full ground station-spacecraft view periods, more accurate radio occultation signals, decreased single-frequency measurement noise, and the possibility for fully autonomous on-board navigation. Specific examples of navigation and radio science benefits to deep space missions are highlighted through simulations of Mars orbiter and Europa flyby missions. Additionally, this paper provides an overview of the mercury-ion trap technology behind DSAC, details of and options for the upcoming 2015/2016 space demonstration, and expected on-orbit clock performance.

  5. Space Launch System Mission Flexibility Assessment

    NASA Technical Reports Server (NTRS)

    Monk, Timothy; Holladay, Jon; Sanders, Terry; Hampton, Bryan

    2012-01-01

    The Space Launch System (SLS) is envisioned as a heavy lift vehicle that will provide the foundation for future beyond low Earth orbit (LEO) missions. While multiple assessments have been performed to determine the optimal configuration for the SLS, this effort was undertaken to evaluate the flexibility of various concepts for the range of missions that may be required of this system. These mission scenarios include single launch crew and/or cargo delivery to LEO, single launch cargo delivery missions to LEO in support of multi-launch mission campaigns, and single launch beyond LEO missions. Specifically, we assessed options for the single launch beyond LEO mission scenario using a variety of in-space stages and vehicle staging criteria. This was performed to determine the most flexible (and perhaps optimal) method of designing this particular type of mission. A specific mission opportunity to the Jovian system was further assessed to determine potential solutions that may meet currently envisioned mission objectives. This application sought to significantly reduce mission cost by allowing for a direct, faster transfer from Earth to Jupiter and to determine the order-of-magnitude mass margin that would be made available from utilization of the SLS. In general, smaller, existing stages provided comparable performance to larger, new stage developments when the mission scenario allowed for optimal LEO dropoff orbits (e.g. highly elliptical staging orbits). Initial results using this method with early SLS configurations and existing Upper Stages showed the potential of capturing Lunar flyby missions as well as providing significant mass delivery to a Jupiter transfer orbit.

  6. Use of IPsec by Manned Space Missions

    NASA Technical Reports Server (NTRS)

    Pajevski, Michael J.

    2009-01-01

    NASA's Constellation Program is developing its next generation manned space systems for missions to the International Space Station (ISS) and the Moon. The Program is embarking on a path towards standards based Internet Protocol (IP) networking for space systems communication. The IP based communications will be paired with industry standard security mechanisms such as Internet Protocol Security (IPsec) to ensure the integrity of information exchanges and prevent unauthorized release of sensitive information in-transit. IPsec has been tested in simulations on the ground and on at least one Earth orbiting satellite, but the technology is still unproven in manned space mission situations and significant obstacles remain.

  7. The Trojans' Odyssey space mission

    NASA Astrophysics Data System (ADS)

    Lamy, P.; Vernazza, P.; Groussin, O.; Poncy, J.; Martinot, V.; Hinglais, E.; Bell, J.; Cruikshank, D.; Helbert, J.; Marzari, F.; Morbidelli, A.; Rosenblatt, P.

    2011-10-01

    In our present understanding of the Solar System, small bodies (asteroids, Jupiter Trojans, comets and TNOs) are the most direct remnants of the original building blocks that formed the planets. Jupiter Trojan and Hilda asteroids are small primitive bodies located beyond the "snow line", around respectively the L4 and L5 Lagrange points of Jupiter at 5.2 AU (Trojans) and in the 2:3 mean-motion resonance with Jupiter near 3.9 AU (Hildas). They are at the crux of several outstanding and still conflicting issues regarding the formation and evolution of the Solar System. They hold the potential to unlock the answers to fundamental questions about planetary migration, the late heavy bombardment, the formation of the Jovian system, the origin and evolution of trans-neptunian objects, and the delivery of water and organics to the inner planets. The proposed Trojans' Odyssey mission is envisioned as a reconnaissance, multiple flyby mission aimed at visiting several objects, typically five Trojans and one Hilda. It will attempt exploring both large and small objects and sampling those with any known differences in photometric properties. The orbital strategy consists in a direct trajectory to one of the Trojan swarms. By carefully choosing the aphelion of the orbit (typically 5.3 AU), the trajectory will offer a long arc in the swarm thus maximizing the number of flybys. Initial gravity assists from Venus and Earth will help reducing the cruise to 7 years as well as the ?V needed for injection thus offering enough capacity to navigate among Trojans. This solution further opens the unique possibility to flyby a Hilda asteroid when leaving the Trojan swarm. During the cruise phase, a Main Belt Asteroid could be targeted if requiring a modest ?V. The specific science objectives of the mission will be best achieved with a payload that will perform high-resolution panchromatic and multispectral imaging, thermal-infrared imaging/ radiometry, near- and mid-infrared spectroscopy

  8. MDP: Reliable File Transfer for Space Missions

    NASA Technical Reports Server (NTRS)

    Rash, James; Criscuolo, Ed; Hogie, Keith; Parise, Ron; Hennessy, Joseph F. (Technical Monitor)

    2002-01-01

    This paper presents work being done at NASA/GSFC (Goddard Space Flight Center) by the Operating Missions as Nodes on the Internet (OMNI) project to demonstrate the application of the Multicast Dissemination Protocol (MDP) to space missions to reliably transfer files. This work builds on previous work by the OMNI project to apply Internet communication technologies to space communication. The goal of this effort is to provide an inexpensive, reliable, standard, and interoperable mechanism for transferring files in the space communication environment. Limited bandwidth, noise, delay, intermittent connectivity, link asymmetry, and one-way links are all possible issues for space missions. Although these are link-layer issues, they can have a profound effect on the performance of transport and application level protocols. MDP, a UDP (User Datagram Protocol)-based reliable file transfer protocol, was designed for multicast environments which have to address these same issues, and it has done so successfully. Developed by the Naval Research Lab in the mid 1990s, MDP is now in daily use by both the US Post Office and the DoD (Department of Defense). This paper describes the use of MDP to provide automated end-to-end data flow for space missions. It examines the results of a parametric study of MDP in a simulated space link environment and discusses the results in terms of their implications for space missions. Lessons learned are addressed, which suggest minor enhancements to the MDP user interface to add specific features for space mission requirements, such as dynamic control of data rate, and a checkpoint/resume capability. These are features that are provided for in the protocol, but are not implemented in the sample MDP application that was provided. A brief look is also taken at the status of standardization. A version of MDP known as NORM (Nack Oriented Reliable Multicast) is in the process of becoming an IETF (Internet Engineering Task Force) standard.

  9. In Brief: Proposed European space missions

    NASA Astrophysics Data System (ADS)

    Showstack, Randy

    2007-10-01

    New candidates for possible future scientific missions were selected by the European Space Agency's Space Science Advisory Committee at its 17-18 October meeting. Among the eight candidates are four solar system missions. The Laplace mission would perform coordinated observations of Europa, the Jovian satellites, Jupiter's magnetosphere, and its atmosphere and interior. Tandem is a mission that would explore two Saturn satellites-Titan and Enceladus-in situ and from orbit to investigate their origins, interiors, and evolution as well as their astrobiological potential. Cross-Scale, with 12 spacecraft, would make simultaneous measurements of plasma on different scales at shocks, reconnection sites, and turbulent regions in near-Earth space. Marco Polo would characterize a near-Earth object at multiple scales and return with a sample. Among other missions, Plato, a photometry mission, would detect and characterize transiting exoplanets, while Spica, a next-generation infrared observatory, would address planetary formation questions. Ultimately, two missions will be proposed for implementation, with launches planned for 2017 and 2018.

  10. MDP: Reliable File Transfer for Space Missions

    NASA Technical Reports Server (NTRS)

    Rash, James; Criscuolo, Ed; Hogie, Keith; Parise, Ron; Hennessy, Joseph F. (Technical Monitor)

    2002-01-01

    This paper presents work being done at NASA/GSFC by the Operating Missions as Nodes on the Internet (OMNI) project to demonstrate the application of the Multicast Dissemination Protocol (MDP) to space missions to reliably transfer files. This work builds on previous work by the OMNI project to apply Internet communication technologies to space communication. The goal of this effort is to provide an inexpensive, reliable, standard, and interoperable mechanism for transferring files in the space communication environment. Limited bandwidth, noise, delay, intermittent connectivity, link asymmetry, and one-way links are all possible issues for space missions. Although these are link-layer issues, they can have a profound effect on the performance of transport and application level protocols. MDP, a UDP-based reliable file transfer protocol, was designed for multicast environments which have to address these same issues, and it has done so successfully. Developed by the Naval Research Lab in the mid 1990's, MDP is now in daily use by both the US Post Office and the DoD. This paper describes the use of MDP to provide automated end-to-end data flow for space missions. It examines the results of a parametric study of MDP in a simulated space link environment and discusses the results in terms of their implications for space missions. Lessons learned are addressed, which suggest minor enhancements to the MDP user interface to add specific features for space mission requirements, such as dynamic control of data rate, and a checkpoint/resume capability. These are features that are provided for in the protocol, but are not implemented in the sample MDP application that was provided. A brief look is also taken at the status of standardization. A version of MDP known as NORM (Neck Oriented Reliable Multicast) is in the process of becoming an IETF standard.

  11. STS-80 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1997-01-01

    The STS-80 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the eightieth flight of the Space Shuttle Program, the fifty-fifth flight since the return-to-flight, and the twenty-first flight of the Orbiter Columbia (OV-102).

  12. Blast-Off on Mission: SPACE

    NASA Technical Reports Server (NTRS)

    2003-01-01

    Part of NASA's mission is to inspire the next generation of explorers. NASA often reaches children - the inventors of tomorrow - through teachers, reporters, exhibit designers, and other third-party entities. Therefore, when Walt Disney Imagineering, the creative force behind the planning, design, and construction of Disney parks and resorts around the world, approached NASA with the desire to put realism into its Mission: SPACE project, the Agency was happy to offer its insight.

  13. Sustainable and Autonomic Space Exploration Missions

    NASA Technical Reports Server (NTRS)

    Hinchey, Michael G.; Sterritt, Roy; Rouff, Christopher; Rash, James L.; Truszkowski, Walter

    2006-01-01

    Visions for future space exploration have long term science missions in sight, resulting in the need for sustainable missions. Survivability is a critical property of sustainable systems and may be addressed through autonomicity, an emerging paradigm for self-management of future computer-based systems based on inspiration from the human autonomic nervous system. This paper examines some of the ongoing research efforts to realize these survivable systems visions, with specific emphasis on developments in Autonomic Policies.

  14. Training Concept for Long Duration Space Mission

    NASA Technical Reports Server (NTRS)

    O'Keefe, William

    2008-01-01

    There has been papers about maintenance and psychological training for Long Duration Space Mission (LDSM). There are papers on the technology needed for LDSMs. Few are looking at how groundbased pre-mission training and on-board in-transit training must be melded into one training concept that leverages this technology. Even more importantly, fewer are looking at how we can certify crews pre-mission. This certification must ensure, before the crew launches, that they can handle any problem using on-board assets without a large ground support team.

  15. Mars mission effects on Space Station evolution

    NASA Technical Reports Server (NTRS)

    Askins, Barbara S.; Cook, Stephen G.

    1989-01-01

    The permanently manned Space Station scheduled to be operational in low earth by the mid 1990's, will provide accommodations for science, applications, technology, and commercial users, and will develop enabling capabilities for future missions. A major aspect of the baseline Space Station design is that provisions for evolution to greater capabilities are included in the systems and subsystems designs. User requirements are the basis for conceptual evolution modes or infrastructure to support the paths. Four such modes are discussed in support of a Human to Mars mission, along with some of the near term actions protecting the future of supporting Mars missions on the Space Station. The evolution modes include crew and payload transfer, storage, checkout, assembly, maintenance, repair, and fueling.

  16. Advanced power sources for space missions

    NASA Technical Reports Server (NTRS)

    Gavin, Joseph G., Jr.; Burkes, Tommy R.; English, Robert E.; Grant, Nicholas J.; Kulcinski, Gerald L.; Mullin, Jerome P.; Peddicord, K. Lee; Purvis, Carolyn K.; Sarjeant, W. James; Vandevender, J. Pace

    1989-01-01

    Approaches to satisfying the power requirements of space-based Strategic Defense Initiative (SDI) missions are studied. The power requirements for non-SDI military space missions and for civil space missions of the National Aeronautics and Space Administration (NASA) are also considered. The more demanding SDI power requirements appear to encompass many, if not all, of the power requirements for those missions. Study results indicate that practical fulfillment of SDI requirements will necessitate substantial advances in the state of the art of power technology. SDI goals include the capability to operate space-based beam weapons, sometimes referred to as directed-energy weapons. Such weapons pose unprecedented power requirements, both during preparation for battle and during battle conditions. The power regimes for these two sets of applications are referred to as alert mode and burst mode, respectively. Alert-mode power requirements are presently stated to range from about 100 kW to a few megawatts for cumulative durations of about a year or more. Burst-mode power requirements are roughly estimated to range from tens to hundreds of megawatts for durations of a few hundred to a few thousand seconds. There are two likely energy sources, chemical and nuclear, for powering SDI directed-energy weapons during the alert and burst modes. The choice between chemical and nuclear space power systems depends in large part on the total duration during which power must be provided. Complete study findings, conclusions, and eight recommendations are reported.

  17. STS-31 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Camp, David W.; Germany, D. M.; Nicholson, Leonard S.

    1990-01-01

    The STS-31 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-fifth flight of the Space Shuttle and the tenth flight of the Orbiter Vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-34/LWT-27), three Space Shuttle main engines (SSME's) (serial numbers 2011, 2031, and 2107), and two Solid Rocket Booster (SRB) (designated as BI-037). The primary objective of the mission was to place the Hubble Space Telescope (HST) into a 330 nmi. circular orbit having an inclination of 28.45 degrees. The secondary objectives were to perform all operations necessary to support the requirements of the Protein Crystal Growth (PCG), Investigations into Polymer Membrane Processing (IPMP), Radiation Monitoring Equipment (RME), Ascent Particle Monitor (APM), IMAX Cargo Bay Camera (ICBC), Air Force Maui Optical Site Calibration Test (AMOS), IMAX Crew Compartment Camera, and Ion Arc payloads. In addition, 12 development test objectives (DTO's) and 10 detailed supplementary objectives (DSO's) were assigned to the flight. The sequence of events for this mission is shown. The significant problems that occurred in the Space Shuttle Orbiter subsystems during the mission are summarized, and the official problem tracking list is presented. In addition, each of the Space Shuttle Orbiter problems is cited in the subsystem discussion.

  18. Recent Applications of Space Weather Research to NASA Space Missions

    NASA Technical Reports Server (NTRS)

    Willis, Emily M.; Howard, James W., Jr.; Miller, J. Scott; Minow, Joseph I.; NeergardParker, L.; Suggs, Robert M.

    2013-01-01

    Marshall Space Flight Center s Space Environments Team is committed to applying the latest research in space weather to NASA programs. We analyze data from an extensive set of space weather satellites in order to define the space environments for some of NASA s highest profile programs. Our goal is to ensure that spacecraft are designed to be successful in all environments encountered during their missions. We also collaborate with universities, industry, and other federal agencies to provide analysis of anomalies and operational impacts to current missions. This presentation is a summary of some of our most recent applications of space weather data, including the definition of the space environments for the initial phases of the Space Launch System (SLS), acquisition of International Space Station (ISS) frame potential variations during geomagnetic storms, and Nascap-2K charging analyses.

  19. STS-61 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1994-01-01

    The STS-61 Space Shuttle Program Mission Report summarizes the Hubble Space Telescope (HST) servicing mission as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the fifty-ninth flight of the Space Shuttle Program and fifth flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-60; three SSME's which were designated as serial numbers 2019, 2033, and 2017 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-063. The RSRM's that were installed in each SRB were designated as 360L023A (lightweight) for the left SRB, and 360L023B (lightweight) for the right SRB. This STS-61 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objective of the STS-61 mission was to perform the first on-orbit servicing of the Hubble Space Telescope. The servicing tasks included the installation of new solar arrays, replacement of the Wide Field/Planetary Camera I (WF/PC I) with WF/PC II, replacement of the High Speed Photometer (HSP) with the Corrective Optics Space Telescope Axial Replacement (COSTAR), replacement of rate sensing units (RSU's) and electronic control units (ECU's), installation of new magnetic sensing systems and fuse plugs, and the repair of the Goddard High Resolution Spectrometer (GHRS). Secondary objectives were to perform the requirements of the IMAX Cargo Bay Camera (ICBC), the IMAX Camera, and the Air Force Maui Optical Site (AMOS) Calibration Test.

  20. Probing Seismic Solar Analogues Through Observations With The NASA Kepler Space Telescope and Hermes High-Resolution Spectrograph

    NASA Astrophysics Data System (ADS)

    Beck, P. G.; Salabert, D.; Garcia, R. A.; do Nascimento, J., Jr.; Duarte, T. S. S.; Mathis, S.; Regulo, C.; Ballot, J.; Egeland, R.; Castro, M.; Pérez-Herńandez, F.,; Creevey, O.; Tkachenko, A.; van Reeth, T.; Bigot, L.; Corsaro, E.; Metcalfe, T.; Mathur, S.; Palle, P. L.; Allende Prieto, C.; Montes, D.; Johnston, C.; Andersen, M. F.; van Winckel, H.

    2016-11-01

    Stars similar to the Sun, known as solar analogues, provide an excellent opportunity to study the preceding and following evolutionary phases of our host star. The unprecedented quality of photometric data collected by the Kepler NASA mission allows us to characterise solar-like stars through asteroseismology and study diagnostics of stellar evolution, such as variation of magnetic activity, rotation and the surface lithium abundance. In this project, presented in a series of papers by Salabert et al (2016ab) and Beck et al. (2016ab), we investigate the link between stellar activity, rotation, lithium abundance and oscillations in a group of 18 solar-analogue stars through space photometry, obtained with the NASA Kepler space telescope and from currently 50+ hours of ground-based, high-resolution spectroscopy with the Hermes instrument. In these proceedings, we first discuss the selection of the stars in the sample, observations and calibrations and then summarise the main results of the project. By investigating the chromospheric and photospheric activity of the solar analogues in this sample, it was shown that for a large fraction of these stars the measured activity levels are compatible to levels of the 11-year solar activity cycle 23. A clear correlation between the lithium abundance and surface rotation was found for rotation periods shorter than the solar value. Comparing the lithium abundance measured in the solar analogues to evolutionary models with the Toulouse-Geneva Evolutionary Code (TGEC), we found that the solar models calibrated to the Sun also correctly describe the set of solar/stellar analogs showing that they share the same internal mixing physics. Finally, the star KIC3241581 and KIC10644353 are discussed in more detail.

  1. Life sciences space missions. Overview

    NASA Technical Reports Server (NTRS)

    Sulzman, F. M.

    1996-01-01

    It has been known for many years that weightlessness induces changes in numerous physiological systems: the cardiovascular system declines in both aerobic capacity and orthostatic tolerance; there is a reduction in fluid and electrolyte balance, hematocrit, and certain immune parameters; bone and muscle mass and strength are reduced; various neurological responses include space motion sickness and posture and gate alterations. These responses are caused by the hypokinesia of weightlessness, the cephalic fluid shift, the unloading of the vestibular system, stress, and the altered temporal environment.

  2. The limit passage of space curvature in problems of celestial mechanics with the generalized Kepler and Hooke potentials

    NASA Astrophysics Data System (ADS)

    Vozmishcheva, Tatiana

    2016-09-01

    The connection between the problems of celestial mechanics: the Kepler problem, the two-center problem and the two body problem in spaces of constant curvature with the generalized Kepler and Hooke potentials is investigated. The limit passage in the two-center and two body problems in the Lobachevsky space and on a sphere is carried out as λto0 (λ is the curvature of the corresponding space) for the two potentials. The potentials and metrics in spaces under study are written in the gnomonic coordinates. It is shown that as the curvature radius tends to infinity, the generalized gravitational and elastic potentials transform to the Kepler and Hooke forms in the Euclidean space.

  3. STS-41 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Camp, David W.; Germany, D. M.; Nicholson, Leonard S.

    1990-01-01

    The STS-41 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities on this thirty-sixth flight of the Space Shuttle and the eleventh flight of the Orbiter vehicle, Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-39/LWT-32), three Space Shuttle main engines (SSME's) (serial numbers 2011, 2031, and 2107), and two Solid Rocket Boosters (SRB's), designated as BI-040. The primary objective of the STS-41 mission was to successfully deploy the Ulysses/inertial upper stage (IUS)/payload assist module (PAM-S) spacecraft. The secondary objectives were to perform all operations necessary to support the requirements of the Shuttle Backscatter Ultraviolet (SSBUV) Spectrometer, Solid Surface Combustion Experiment (SSCE), Space Life Sciences Training Program Chromosome and Plant Cell Division in Space (CHROMEX), Voice Command System (VCS), Physiological Systems Experiment (PSE), Radiation Monitoring Experiment - 3 (RME-3), Investigations into Polymer Membrane Processing (IPMP), Air Force Maui Optical Calibration Test (AMOS), and Intelsat Solar Array Coupon (ISAC) payloads. The sequence of events for this mission is shown in tabular form. Summarized are the significant problems that occurred in the Orbiter subsystems during the mission. The official problem tracking list is presented. In addition, each Orbiter problem is cited in the subsystem discussion.

  4. Artificial Neural Network Solutions to Eclipsing Binary Lightcurves from the Kepler Space Telescope Database

    NASA Astrophysics Data System (ADS)

    Hause, Connor; Prsa, Andrej; Matijevic, Gal; Guinan, Edward F.

    2017-01-01

    Fully automated methods of data analysis are necessary for surpassing the human bottleneck in astrophysical data processing and maximizing scientific results from the great volume of observations to be taken over the next few decades. Prsa et al. (2008, ApJ, 687:542) addressed this issue by introducing an artificial neural network (ANN) which estimates the principal parameters of detached eclipsing binary (EB) stars. Parameters obtained by the process can be passed on to advanced modeling engines to produce a qualified EB database. The ANN was originally developed and trained for the OGLE EBs. Our project focuses on retraining this ANN for EBs from NASA’s Kepler Space Telescope database and serves as an extension to the eclipsing binaries via artificial intelligence (EBAI) project. The Kepler photometry is much more precise than photometry available from OGLE and other previous ground-based studies.. For our training set, we generated theoretical lightcurves via a Monte Carlo based Python script utilizing PHOEBE which samples EB parameter values according to prior distribution functions. Novel to our analysis is the use of chi-squared statistical tests which serve to qualify the overlap between the calculated exemplars and observed data. This enables the trained ANN to more accurately parameterize each EB. We describe our training process, present principal parameter estimates of Kepler EBs obtained by the ANNs, and discuss ongoing endeavors to refine those solutions. This research was supported by the National Science Foundation grant #1517474 which we gratefully acknowledge.

  5. STS-43 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1991-01-01

    The STS-43 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-second flight of the Space Shuttle Program and the ninth flight of the Orbiter Vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-47 (LWT-40); three Space Shuttle main engines (SSME's) (serial numbers 2024, 2012, and 2028 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-045. The primary objective of the STS-43 mission was to successfully deploy the Tracking and Data Relay Satellite-E/Inertial Upper Stage (TDRS-E/IUS) satellite and to perform all operations necessary to support the requirements of the Shuttle Solar Backscatter Ultraviolet (SSBUV) payload and the Space Station Heat Pipe Advanced Radiator Element (SHARE-2).

  6. New ideas for affordable space missions

    PubMed

    Eller, E; Roussel-Dupre, D; Weiss, R; Bruegman, O

    1996-04-01

    In September 1995, NASA-Goddard held a workshop on low-cost access to space for science missions. The workshop provided briefings on balloons, sounding rockets, Shuttle payloads, and low-cost free-flyer concepts, to provide options of getting experiments into space. This report is the result of a panel session organized with the aim of generating new ideas beyond those presented in the workshop. In addition to the authors, Orlando Figueroa and Paul Ondrus of NASA-Goddard and Richard Zwirnbaum of Computer Sciences Corp. participated in the discussions. The ideas presented do not necessarily reflect the current thinking of NASA managers. Although the panel discussion was focused on the kinds of science missions usually funded by NASA, most of the ideas that were generated are relevant to military and commercial missions as well.

  7. Benefits of slush hydrogen for space missions

    NASA Technical Reports Server (NTRS)

    Friedlander, Alan; Zubrin, Robert; Hardy, Terry L.

    1991-01-01

    A study was performed to quantify the benefits of using slush hydrogen instead of normal boiling point liquid hydrogen as a fuel for several space missions. Vehicles considered in the study included the Space Shuttle/Shuttle-C, LEO to GEO transfer vehicles, Lunar and Mars transfer vehicles, and cryogenic depots in low Earth orbit. The advantages of using slush hydrogen were expressed in terms of initial mass differences at a constant payload, payload differences at a constant tank volume, and increases in fuel storage time for cryogenic depots. Both chemical oxygen/hydrogen and hydrogen nuclear thermal rocket propulsion were considered in the study. The results indicated that slush hydrogen offers the potential for significant decreases in initial mass and increases in payload for most missions studied. These advantages increase as the mission difficulty, or energy, increases.

  8. STS-59 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1994-01-01

    The STS-59 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-second flight of the Space Shuttle Program and sixth flight of the Orbiter vehicle Endeavor (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-63; three SSME's which were designated as serial numbers 2028, 2033, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-065. The RSRM's that were installed in each SRB were designated as 360W037A (welterweight) for the left SRB, and 360H037B (heavyweight) for the right SRB. This STS-59 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objective of the STS-59 mission was to successfully perform the operations of the Space Radar Laboratory-1 (SRL-1). The secondary objectives of this flight were to perform the operations of the Space Tissue Loss-A (STL-A) and STL-B payloads, the Visual Function Tester-4 (VFT-4) payload, the Shuttle Amateur Radio Experiment-2 (SAREX-2) experiment, the Consortium for Materials Development in Space Complex Autonomous Payload-4 (CONCAP-4), and the three Get-Away Special (GAS) payloads.

  9. Helios mission support. [Deep Space Network

    NASA Technical Reports Server (NTRS)

    Goodwin, P. S.; Rockwell, G. M.

    1978-01-01

    Activities of the Deep Space Network Operations organization in support of the Helios Project from 15 October 1977 through 15 December 1977 are described. Topics covered include: (1) Mark 3 data subsystem testing at the conjoint Deep Space Stations (DSS) 42/43 (Canberra, Australia); (2) MDS implementation at DSS 61/63 (Madrid, Spain); (3) Radio Science update, and (4) other mission-related activities.

  10. Euclid Space Mission: building the sky survey

    NASA Astrophysics Data System (ADS)

    Tereno, I.; Carvalho, C. S.; Dinis, J.; Scaramella, R.; Amiaux, J.; Burigana, C.; Cuillandre, J. C.; da Silva, A.; Derosa, A.; Maiorano, E.; Maris, M.; Oliveira, D.; Franzetti, P.; Garilli, B.; Gomez-Alvarez, P.; Meneghetti, M.; Wachter, S.; Wachter

    2014-05-01

    The Euclid space mission proposes to survey 15000 square degrees of the extragalactic sky during 6 years, with a step-and-stare technique. The scheduling of observation sequences is driven by the primary scientific objectives, spacecraft constraints, calibration requirements and physical properties of the sky. We present the current reference implementation of the Euclid survey and on-going work on survey optimization.

  11. A Probabilistic Mass-Radius Relationship for Sub-Neptune-Sized Planets: Implications for Missions Post-Kepler

    NASA Astrophysics Data System (ADS)

    Wolfgang, Angie; Rogers, Leslie; Ford, Eric B.; Laughlin, Gregory P.

    2016-01-01

    The Kepler Mission has discovered thousands of planets with radii between 1 and 4 R_Earth, paving the way for the first statistical studies of the dynamics, formation, and evolution of planets in a size range where there are no Solar System analogs. Masses are an important physical property for these theoretical studies, and yet the vast majority of Kepler planet candidates do not have theirs measured. Therefore, a key practical concern is how to most accurately map a measured sub-Neptune radius to a mass estimate given the existing observations. This issue is also highly relevant to devising the most efficient follow-up programs of future transiting exoplanet detection missions such as TESS. Here we present a probabilistic mass-radius relationship (M-R relation) evaluated within a hierarchical Bayesian framework, which both accounts for the anticipated intrinsic dispersion in these planets' compositions and quantifies the uncertainties on the M-R relation parameters. Assuming that the M-R relation can be described as a power law with a dispersion that is constant and normally distributed, we find that M/M_Earth = 2.7 (R/R_Earth)^1.3 and a scatter in mass of 1.9 M_Earth is the "best-fit" probabilistic M-R relation for the sample of RV-measured transiting sub-Neptunes (R_pl < 4 R_Earth; Wolfgang, Rogers, & Ford, in review). The probabilistic nature of this M-R relation has several advantages: not only does its use automatically account for a significant source of uncertainty in the comparison between planet formation theory and observation, but it can predict the yield of future transit missions' follow-up programs under the observed range of planet compositions at a given radius. We demonstrate the latter with TESS as a case study, building on Sullivan et al. 2015 to provide the RV semi-amplitude distribution predicted by this more general M-R relation and a more detailed treatment of the underlying planet population as derived from Kepler. The uncertainties in the

  12. A Probabilistic Mass-Radius Relationship for Sub-Neptune-Sized Planets: Implications for Missions Post-Kepler

    NASA Astrophysics Data System (ADS)

    Wolfgang, Angie; Rogers, Leslie A.; Ford, Eric B.; Laughlin, Gregory

    2015-12-01

    The Kepler Mission has discovered thousands of planets with radii between 1 and 4 R_Earth, paving the way for the first statistical studies of the dynamics, formation, and evolution of planets in a size range where there are no Solar System analogs. Masses are an important physical property for these theoretical studies, and yet the vast majority of Kepler planet candidates do not have theirs measured. Therefore, a key practical concern is how to most accurately map a measured sub-Neptune radius to a mass estimate given the existing observations. This issue is also highly relevant to devising the most efficient follow-up programs of future transiting exoplanet detection missions such as TESS. Here we present a probabilistic mass-radius relationship (M-R relation) evaluated within a hierarchical Bayesian framework, which both accounts for the anticipated intrinsic dispersion in these planets' compositions and quantifies the uncertainties on the M-R relation parameters. Assuming that the M-R relation can be described as a power law with a dispersion that is constant and normally distributed, we find that M/M_Earth = 2.7 (R/R_Earth)^1.3 and a scatter in mass of 1.9 M_Earth is the "best-fit" probabilistic M-R relation for the sample of RV-measured transiting sub-Neptunes (R_pl < 4 R_Earth; Wolfgang, Rogers, & Ford, in review). The probabilistic nature of this M-R relation has several advantages: not only does its use automatically account for a significant source of uncertainty in the comparison between planet formation theory and observation, but it can predict the yield of future transit missions' follow-up programs under the observed range of planet compositions at a given radius. We demonstrate the latter with TESS as a case study, building on Sullivan et al. 2015 to provide the RV semi-amplitude distribution predicted by this more general M-R relation and a more detailed treatment of the underlying planet population as derived from Kepler. The uncertainties in the

  13. STS-62 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1994-01-01

    The STS-62 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSHE) systems performance during the sixty-first flight of the Space Shuttle Program and sixteenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-62; three SSME's which were designated as serial numbers 2031, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-064. The RSRM's that were installed in each SRB were designated as 360L036A (lightweight) for the left SRB, and 36OWO36B (welterweight) for the right SRB. This STS-62 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-62 mission were to perform the operations of the United States Microgravity Payload-2 (USMP-2) and the Office of Aeronautics and Space Technology-2 (OAST-2) payload. The secondary objectives of this flight were to perform the operations of the Dexterous End Effector (DEE), the Shuttle Solar Backscatter Ultraviolet/A (SSBUV/A), the Limited Duration Space Environment Candidate Material Exposure (LDCE), the Advanced Protein Crystal Growth (APCG), the Physiological Systems Experiments (PSE), the Commercial Protein Crystal Growth (CPCG), the Commercial Generic Bioprocessing Apparatus (CGBA), the Middeck Zero-Gravity Dynamics Experiment (MODE), the Bioreactor Demonstration System (BDS), the Air Force Maui Optical Site Calibration Test (AMOS), and the Auroral Photography Experiment (APE-B).

  14. ISS Update: Communication Delays During Deep Space Missions

    NASA Video Gallery

    NASA Public Affairs Officer Brandi Dean talks with Jeremy Frank, Autonomous Mission Operations Test Principal Investigator, about how communication delays will affect future deep space missions and...

  15. Reusable space tug concept and mission

    NASA Astrophysics Data System (ADS)

    Cresto Aleina, Sara; Viola, Nicole; Stesina, Fabrizio; Viscio, Maria Antonietta; Ferraris, Simona

    2016-11-01

    The paper deals with the conceptual design of a space tug to be used in support to Earth satellites transfer manoeuvres. Usually Earth satellites are released in a non-definitive low orbit, depending on the adopted launcher, and they need to be equipped with an adequate propulsion system able to perform the transfer to their final operational location. In order to reduce the mass at launch of the satellite system, an element pre-deployed on orbit, i.e. the space tug, can be exploited to perform the transfer manoeuvres; this allows simplifying the propulsion requirements for the satellite, with a consequent decrease of mass and volume, in favour of larger payloads. The space tug here presented is conceived to be used for the transfer of a few satellites from low to high orbits, and vice versa, if needed. To support these manoeuvres, dedicated refuelling operations are envisaged. The paper starts from on overview of the mission scenario, the concept of operations and the related architecture elements. Then it focuses on the detailed definition of the space tug, from the requirements' assessment up to the budgets' development, through an iterative and recursive design process. The overall mission scenario has been derived from a set of trade-off analyses that have been performed to choose the mission architecture and operations that better satisfy stakeholder expectations: the most important features of these analyses and their results are described within the paper. Eventually, in the last part of the work main conclusions are drawn on the selected mission scenario and space tug and further utilizations of this innovative system in the frame of future space exploration are discussed. Specifically, an enhanced version of the space tug that has been described in the paper could be used to support on orbit assembly of large spacecraft for distant and long exploration missions. The Space Tug development is an activity carried on in the frame of the SAPERE project (Space

  16. STS-77 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1996-01-01

    The STS-77 Space Shuttle Program Mission Report summarizes the Payload activities as well as the: Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle Main Engine (SSME) systems performance during the seventy-seventh flight of the Space Shuttle Program, the fifty-second flight since the return-to-flight, and the eleventh flight of the Orbiter Endeavour (OV-105). STS-77 was also the last flight of OV-105 prior to the vehicle being placed in the Orbiter Maintenance Down Period (OMDP). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-78; three SSME's that were designated as serial numbers 2037, 2040, and 2038 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-080. The RSRM's, designated RSRM-47, were installed in each SRB and the individual RSRM's were designated as 360TO47A for the left SRB, and 360TO47B for the right SRB. The STS-77 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume VII, Appendix E. The requirement stated in that document is that each organizational element supporting the Program will report the results of their hardware (and software) evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of this flight were to successfully perform the operations necessary to fulfill the requirements of Spacehab-4, the SPARTAN 207/inflatable Antenna Experiment (IAE), and the Technology Experiments Advancing Missions in Space (TEAMS) payload. Secondary objectives of this flight were to perform the experiments of the Aquatic Research Facility (ARF), Brilliant Eyes Ten-Kelvin Sorption Cryocooler Experiment (BETSCE), Biological Research in Canisters (BRIC), Get-Away-Special (GAS), and GAS Bridge Assembly (GBA). The STS-77 mission was planned as a 9-day flight plus 1 day, plus 2 contingency days, which were available for

  17. STS-57 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1993-01-01

    The STS-57 Space Shuttle Program Mission Report provides a summary of the Payloads, as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the fifty-sixth flight of the Space Shuttle Program and fourth flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET (ET-58); three SSME's which were designated as serial numbers 2019, 2034, and 2017 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-059. The lightweight RSRM's that were installed in each SRB were designated as 360L032A for the left SRB and 360W032B for the right SRB. The STS-57 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement, as documented in NSTS 07700, Volume 8, Appendix E. That document states that each major organizational element supporting the Program will report the results of their hardware evaluation and mission performance plus identify all related in-flight anomalies.

  18. The Kepler Follow-up Observation Program

    NASA Astrophysics Data System (ADS)

    Gautier, Thomas N., III; Borucki, W. J.; Caldwell, D. A.; Koch, D. G.

    2007-07-01

    The Kepler mission will use a space based, 95 cm Schmidt telescope to survey >100,000 late type dwarf stars for transiting Earth-sized planets over a period of 4 years. Up to 2000 such planets might be detected along with a hundred or more transiting giant planets. About 1000 false positive planet detections, due mainly to eclipsing binary stars, are also expected. A ground based follow-up program is planned to observe all of the planet candidates found by Kepler to weed out these false positives and produce a final catalog with a reliability greater than 95%. In addition, follow-up observations will, where possible, measure the mass of confirmed planets and look for any non-transiting giant planets. The Kepler Project is Funded by the National Aeronautics and Space Administration as a Discovery Mission.

  19. A moderate space mission for optical interferometry

    NASA Technical Reports Server (NTRS)

    Gershman, R.; Rayman, M. D.; Shao, M.

    1991-01-01

    The Orbiting Stellar Interferometer (OSI) is a proposed space-based observatory which will open exciting new vistas in astronomy and address fundamental scientific questions by making extremely accurate (3 - 30 microarcsecond) astrometric measurements of the positions of stars, quasars, and other astronomical objects as faint as magnitude 20. In addition, it will be able to image objects with a resolution of 5 milliarcseconds. As the first optical interferometer in space, OSI will provide major advances in astrophysics while demonstrating a powerful concept applicable to major space-based observations of the future. The Jet Propulsion Laboratory has developed a preliminary design of OSI to establish its feasibility and to estimate performance that can be achieved in a mission of moderate scale. In this first publication of the results of the first year of study, the science objectives are presented, and the design of the mission, instrument, and spacecraft are discussed.

  20. Decoder synchronization for deep space missions

    NASA Technical Reports Server (NTRS)

    Statman, J. I.; Cheung, K.-M.; Chauvin, T. H.; Rabkin, J.; Belongie, M. L.

    1994-01-01

    The Consultative Committee for Space Data Standards (CCSDS) recommends that space communication links employ a concatenated, error-correcting, channel-coding system in which the inner code is a convolutional (7,1/2) code and the outer code is a (255,223) Reed-Solomon code. The traditional implementation is to perform the node synchronization for the Viterbi decoder and the frame synchronization for the Reed-Solomon decoder as separate, sequential operations. This article discusses a unified synchronization technique that is required for deep space missions that have data rates and signal-to-noise ratios (SNR's) that are extremely low. This technique combines frame synchronization in the bit and symbol domains and traditional accumulated-metric growth techniques to establish a joint frame and node synchronization. A variation on this technique is used for the Galileo spacecraft on its Jupiter-bound mission.

  1. STS-58 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1994-01-01

    The STS-58 Space Shuttle Program Mission Report provides a summary of the payload activities as well as the orbiter, external tank (ET), solid rocket booster (SRB) and redesigned solid rocket motor (RSRM), and the space shuttle main engine (SSME) subsystems performance during the fifty-eighth mission of the space shuttle program and fifteenth flight of the orbiter vehicle Columbia (OV-102). In addition to the orbiter, the flight vehicle consisted of an ET (ET-57); three SSME's, which were designated as serial numbers 2024, 2109, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-061. The lightweight RSRM's that were installed in each SRB were designated as 360L034A for the left SRB and 360W034B for the right SRB.

  2. Psychological considerations in future space missions

    NASA Technical Reports Server (NTRS)

    Helmreich, R. L.; Wilhelm, J. A.; Runge, T. E.

    1980-01-01

    Issues affecting human psychological adjustments to long space missions are discussed. Noting that the Shuttle flight crewmembers will not have extensive flight qualification requirements, the effects of a more heterogeneous crew mixture than in early space flights is considered to create possibilities of social conflicts. Routine space flight will decrease the novelty of a formerly unique experience, and the necessity of providing personal space or other mechanisms for coping with crowded, permanently occupied space habitats is stressed. Women are noted to display more permeable personal space requirements. The desirability of planning leisure activities is reviewed, and psychological test results for female and male characteristics are cited to show that individuals with high scores in both traditionally male and female attributes are most capable of effective goal-oriented behavior and interpersonal relationships. Finally, it is shown that competitiveness is negatively correlated with the success of collaborative work and the social climate of an environment.

  3. Internet Data Delivery for Future Space Missions

    NASA Technical Reports Server (NTRS)

    Rash, James; Hogie, Keith; Casasanta, Ralph; Hennessy, Joseph F. (Technical Monitor)

    2002-01-01

    This paper presents work being done at NASA/GSFC (Goddard Space Flight Center) on applying standard Internet applications and protocols to meet the technology challenge of future satellite missions. Internet protocols (IP) can provide seamless dynamic communication among heterogeneous instruments, spacecraft, ground stations, and constellations of spacecraft. A primary component of this work is to design and demonstrate automated end-to-end transport of files in a dynamic space environment using off-the-shelf, low-cost, commodity-level standard applications and protocols. These functions and capabilities will become increasingly significant in the years to come as both Earth and space science missions fly more sensors and the present labor-intensive, mission-specific techniques for processing and routing data become prohibitively expensive. This paper describes how an IP-based communication architecture can support existing operations concepts and how it will enable some new and complex communication and science concepts. The authors identify specific end-to-end file transfers all the way from instruments to control centers and scientists, and then describe how each data flow can be supported using standard Internet protocols and applications. The scenarios include normal data downlink and command uplink as well as recovery scenarios for both onboard and ground failures. The scenarios are based on an Earth orbiting spacecraft with data rates and downlink capabilities from 300 Kbps to 4 Mbps. Many examples are based on designs currently being investigated for the Global Precipitation Measurement (GPM) mission.

  4. World Space Observatory Ultraviolet mission: status 2016

    NASA Astrophysics Data System (ADS)

    Sachkov, Mikhail; Shustov, Boris; Gómez de Castro, Ana Inés.

    2016-07-01

    The WSO-UV (World Space Observatory - Ultraviolet) project is intended to built and operate an international space observatory designed for observations in the UV (115 - 310 nm) range, where some of the most important astrophysical processes can be efficiently studied. It is the solution to the problem of future access to UV spectroscopy. Dedicated to spectroscopic and imaging observations of the ultraviolet sky, the World Space Observatory - Ultraviolet mission is a Russian-Spanish collaboration with potential Mexican minor contribution. This paper provides a summary on the project, its status and the major outcomes since the last SPIE meeting.

  5. Advanced automation in space shuttle mission control

    NASA Technical Reports Server (NTRS)

    Heindel, Troy A.; Rasmussen, Arthur N.; Mcfarland, Robert Z.

    1991-01-01

    The Real Time Data System (RTDS) Project was undertaken in 1987 to introduce new concepts and technologies for advanced automation into the Mission Control Center environment at NASA's Johnson Space Center. The project's emphasis is on producing advanced near-operational prototype systems that are developed using a rapid, interactive method and are used by flight controllers during actual Shuttle missions. In most cases the prototype applications have been of such quality and utility that they have been converted to production status. A key ingredient has been an integrated team of software engineers and flight controllers working together to quickly evolve the demonstration systems.

  6. National Space Transportation Systems Program mission report

    NASA Technical Reports Server (NTRS)

    Collins, M. A., Jr.; Aldrich, A. D.; Lunney, G. S.

    1984-01-01

    The STS 41-C National Space Transportation Systems Program Mission Report contains a summary of the major activities and accomplishments of the eleventh Shuttle flight and fifth flight of the OV-099 vehicle, Challenger. Also summarized are the significant problems that occurred during STS 41-C, and a problem tracking list that is a complete list of all problems that occurred during the flight. The major objectives of flight STS 41-C were to successfully deploy the LDEF (long duration exposure facility) and retrieve, repair and redeploy the SMM (Solar Maximum Mission) spacecraft, and perform functions of IMAX and Cinema 360 cameras.

  7. STS-71, Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Frike, Robert W., Jr.

    1995-01-01

    The STS-71 Space Shuttle Program Mission Report summarizes the Payload activities and provides detailed data on the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance. STS-71 is the 100th United States manned space flight, the sixty-ninth Space Shuttle flight, the forty-fourth flight since the return-to-flight, the fourteenth flight of the OV-104 Orbiter vehicle Atlantis, and the first joint United States (U.S.)-Russian docking mission since 1975. In addition to the OV-104 Orbiter vehicle, the flight vehicle consisted of an ET that was designated ET-70; three SSMEs that were designated 2028, 2034, and 2032 in positions 1, 2, and 3, respectively; and two SRBs that were designated Bl-072. The RSRMs that were an integral part of the SRBs were designated 360L045A for the left SRB and 360W045B for the right SRB. The STS-71 mission was planned as a 1 0-day plus 1-day-extension mission plus 2 additional days for contingency operations and weather avoidance. The primary objectives of this flight were to rendezvous and dock with the Mir Space Station and perform on-orbit joint U.S.-Russian life sciences investigations, logistical resupply of the Mir Space Station, return of the United States astronaut flying on the Mir, the replacement of the Mir-18 crew with the two-cosmonaut Mir-19 crew, and the return of the Mir-18 crew to Earth. The secondary objectives were to perform the requirements of the IMAX Camera and the Shuttle Amateur Radio experiment-2 (SAREX-2).

  8. Assured Mission Support Space Architecture (AMSSA) study

    NASA Technical Reports Server (NTRS)

    Hamon, Rob

    1993-01-01

    The assured mission support space architecture (AMSSA) study was conducted with the overall goal of developing a long-term requirements-driven integrated space architecture to provide responsive and sustained space support to the combatant commands. Although derivation of an architecture was the focus of the study, there are three significant products from the effort. The first is a philosophy that defines the necessary attributes for the development and operation of space systems to ensure an integrated, interoperable architecture that, by design, provides a high degree of combat utility. The second is the architecture itself; based on an interoperable system-of-systems strategy, it reflects a long-range goal for space that will evolve as user requirements adapt to a changing world environment. The third product is the framework of a process that, when fully developed, will provide essential information to key decision makers for space systems acquisition in order to achieve the AMSSA goal. It is a categorical imperative that military space planners develop space systems that will act as true force multipliers. AMSSA provides the philosophy, process, and architecture that, when integrated with the DOD requirements and acquisition procedures, can yield an assured mission support capability from space to the combatant commanders. An important feature of the AMSSA initiative is the participation by every organization that has a role or interest in space systems development and operation. With continued community involvement, the concept of the AMSSA will become a reality. In summary, AMSSA offers a better way to think about space (philosophy) that can lead to the effective utilization of limited resources (process) with an infrastructure designed to meet the future space needs (architecture) of our combat forces.

  9. A Kepler Mission, A Search for Habitable Planets: Concept, Capabilities and Strengths

    NASA Technical Reports Server (NTRS)

    Koch, David; Borucki, William; Lissauer, Jack; Dunham, Edward; Jenkins, Jon; DeVincenzi, D. (Technical Monitor)

    1998-01-01

    The detection of extrasolar terrestrial planets orbiting main-sequence stars is of great interest and importance. Current ground-based methods are only capable of detecting objects about the size or mass of Jupiter or larger. The technological challenges of direct imaging of Earth-size planets from space are expected to be resolved over the next twenty years. Spacebased photometry of planetary transits is currently the only viable method for detection of terrestrial planets (30-600 times less massive than Jupiter). The method searches the extended solar neighborhood, providing a statistically large sample and the detailed characteristics of each individual case. A robust concept has been developed and proposed as a Discovery-class mission. The concept, its capabilities and strengths are presented.

  10. STS-78 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1996-01-01

    The STS-78 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the seventy-eighth flight of the Space Shuttle Program, the fifty-third flight since the return-to-flight, and the twentieth flight of the Orbiter Columbia (OV-102). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-79; three SSME's that were designated as serial numbers 2041, 2039, and 2036 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-081. The RSRM's, designated RSRM-55, were installed in each SRB and the individual RSRM's were designated as 360L055A for the left SRB, and 360L055B for the right SRB. The STS-78 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 7, Appendix E. The requirement stated in that document is that each organizational element supporting the Program will report the results of their hardware (and software) evaluation and mission performance plus identify all related in-flight anomalies. The primary objective of this flight was to successfully perform the planned operations of the Life and Microgravity Spacelab experiments. The secondary objectives of this flight were to complete the operations of the Orbital Acceleration Research Experiment (OARE), Biological Research in Canister Unit-Block II (BRIC), and the Shuttle Amateur Radio Experiment II-Configuration C (SAREX-II). The STS-78 mission was planned as a 16-day, plus one day flight plus two contingency days, which were available for weather avoidance or Orbiter contingency operations. The sequence of events for the STS-78 mission is shown in Table 1, and the Space Shuttle Vehicle Management Office Problem Tracking List is shown in Table 2. The Government Furnished Equipment/Flight Crew Equipment

  11. Internet Data Delivery for Future Space Missions

    NASA Technical Reports Server (NTRS)

    Rash, James; Casasanta, Ralph; Hogie, Keith; Hennessy, Joseph F. (Technical Monitor)

    2002-01-01

    Ongoing work at National Aeronautics and Space Administration Goddard Space Flight Center (NASA/GSFC), seeks to apply standard Internet applications and protocols to meet the technology challenge of future satellite missions. Internet protocols and technologies are under study as a future means to provide seamless dynamic communication among heterogeneous instruments, spacecraft, ground stations, constellations of spacecraft, and science investigators. The primary objective is to design and demonstrate in the laboratory the automated end-to-end transport of files in a simulated dynamic space environment using off-the-shelf, low-cost, commodity-level standard applications and protocols. The demonstrated functions and capabilities will become increasingly significant in the years to come as both earth and space science missions fly more sensors and as the need increases for more network-oriented mission operations. Another element of increasing significance will be the increased cost effectiveness of designing, building, integrating, and operating instruments and spacecraft that will come to the fore as more missions take up the approach of using commodity-level standard communications technologies. This paper describes how an IP (Internet Protocol)-based communication architecture can support all existing operations concepts and how it will enable some new and complex communication and science concepts. The authors identify specific end-to-end data flows from the instruments to the control centers and scientists, and then describe how each data flow can be supported using standard Internet protocols and applications. The scenarios include normal data downlink and command uplink as well as recovery scenarios for both onboard and ground failures. The scenarios are based on an Earth orbiting spacecraft with downlink data rates from 300 Kbps to 4 Mbps. Included examples are based on designs currently being investigated for potential use by the Global Precipitation

  12. Planetary mission applications for space storable propulsion

    NASA Technical Reports Server (NTRS)

    Chase, R. L.; Cork, M. J.; Young, D. L.

    1974-01-01

    This paper presents the results of a study to compare space-storable with earth-storable spacecraft propulsion systems, space-storable with solid kick stages, and several space-storable development options on the basis of benefits received for cost expenditures required. The results show that, for a launch vehicle with performance less than that of Shuttle/Centaur, space-storable spacecraft propulsion offers an incremental benefit/cost ratio between 1.0 and 5.5 when compared to earth-storable systems for three of the four missions considered. In the case of VOIR 83, positive benefits were apparent only for a specific launch vehicle-spacecraft propulsion combination. A space-storable propulsion system operating at thrust of 600 lbf, 355 units of specific impulse, and with blowdown pressurization, represents the best choice for the JO 81 mission on a Titan/Centaur if only spacecraft propulsion modifications are considered. For still higher performance, a new solid-propellant kick stage with space-storable spacecraft propulsion is preferred over a system which uses space-storable propellants for both the kick stage and the spacecraft system.

  13. OBSERVATIONS OF INTENSITY FLUCTUATIONS ATTRIBUTED TO GRANULATION AND FACULAE ON SUN-LIKE STARS FROM THE KEPLER MISSION

    SciTech Connect

    Karoff, C.; Campante, T. L.; Ballot, J.; Kallinger, T.; Gruberbauer, M.; Garcia, R. A.

    2013-04-10

    Sun-like stars show intensity fluctuations on a number of timescales due to various physical phenomena on their surfaces. These phenomena can convincingly be studied in the frequency spectra of these stars-while the strongest signatures usually originate from spots, granulation, and p-mode oscillations, it has also been suggested that the frequency spectrum of the Sun contains a signature of faculae. We have analyzed three stars observed for 13 months in short cadence (58.84 s sampling) by the Kepler mission. The frequency spectra of all three stars, as for the Sun, contain signatures that we can attribute to granulation, faculae, and p-mode oscillations. The temporal variability of the signatures attributed to granulation, faculae, and p-mode oscillations was analyzed and the analysis indicates a periodic variability in the granulation and faculae signatures-comparable to what is seen in the Sun.

  14. Project trades model for complex space missions

    NASA Technical Reports Server (NTRS)

    Girerd, Andre R.; Shishko, Roberto

    2003-01-01

    A Project Trades Model (PTM) is a collection of tools/simulations linked together to rapidly perform integrated system trade studies of performance, cost, risk, and mission effectiveness. An operating PTM captures the interactions between various targeted systems and subsystems through an exchange of computed variables of the constituent models. Selection and implementation of the order, method of interaction, model type, and envisioned operation of the ensemble of tools rpresents the key system engineering challenge of the approach. This paper describes an approach to building a PTM and using it to perform top-level system trades for a complex space mission. In particular, the PTM discussed here is for a future Mars mission involving a large rover.

  15. Manned Mars missions using propellant from space

    SciTech Connect

    Zuppero, A.C.; Olson, T.S. ); Redd, L.R. )

    1993-01-10

    .A recent discovery (8/14/92) of a near-earth object containing materials potentially useful for space activities could perhaps change the entire way humans access and operate in space. A near-Earth object ([number sign]4015, 1979 VA, comet Wilson-Harrington) contains water ice that could be used for space propulsion. In addition, this type of object may contain structural and lifesustaining materials (complex hydrocarbons, ammonia and/or bound nitrogen compounds) for space structures, manned planetary bases, or planetary surface terraforming. The retrieval and utilization of rocket propellant from near-Earth objects, for manned Mars missions in particular, has been investigated and the benefits of this scenario to over performing a Mars mission with terrestrial propellants have been documented. The results show water extracted from these objects and retrieved to Earth orbit for use in going to Mars may actually enable manned Mars exploration by reducing the number of Heavy Lift Launch Vehicle (HLLV) flights or eliminating the need for HLLV's altogether. The mission can perhaps be supported with existing launch vehicles and not required heavy lift capability. Also, the development of a nuclear thermal rocket for this alternate approach may be simplified substantially by reducing the operating temperature required.

  16. Space Shuttle Mission Sequence-Illustration

    NASA Technical Reports Server (NTRS)

    1975-01-01

    This diagram illustrates the Space Shuttle mission sequence. The Space Shuttle was approved as a national program in 1972 and developed through the 1970s. Part spacecraft and part aircraft, the Space Shuttle orbiter, the brain and the heart of the Space Transportation System (STS), required several technological advances, including thousands of insulating tiles able to stand the heat of reentry over the course of many missions, as well as sophisticated engines that could be used again and again without being thrown away. The airplane-like orbiter has three main engines, that burn liquid hydrogen and oxygen stored in the large external tank, the single largest structure in the Shuttle. Attached to the tank are two solid rocket boosters that provide the vehecile with most of the thrust needed for liftoff. Two minutes into the flight, the spent solids drop into the ocean to be recovered and refurbished for reuse, while the orbiter engines continue burning until approximately 8 minutes into the flight. After the mission is completed, the orbiter lands on a runway like an airplane.

  17. Systems Architecture for Fully Autonomous Space Missions

    NASA Technical Reports Server (NTRS)

    Esper, Jamie; Schnurr, R.; VanSteenberg, M.; Brumfield, Mark (Technical Monitor)

    2002-01-01

    The NASA Goddard Space Flight Center is working to develop a revolutionary new system architecture concept in support of fully autonomous missions. As part of GSFC's contribution to the New Millenium Program (NMP) Space Technology 7 Autonomy and on-Board Processing (ST7-A) Concept Definition Study, the system incorporates the latest commercial Internet and software development ideas and extends them into NASA ground and space segment architectures. The unique challenges facing the exploration of remote and inaccessible locales and the need to incorporate corresponding autonomy technologies within reasonable cost necessitate the re-thinking of traditional mission architectures. A measure of the resiliency of this architecture in its application to a broad range of future autonomy missions will depend on its effectiveness in leveraging from commercial tools developed for the personal computer and Internet markets. Specialized test stations and supporting software come to past as spacecraft take advantage of the extensive tools and research investments of billion-dollar commercial ventures. The projected improvements of the Internet and supporting infrastructure go hand-in-hand with market pressures that provide continuity in research. By taking advantage of consumer-oriented methods and processes, space-flight missions will continue to leverage on investments tailored to provide better services at reduced cost. The application of ground and space segment architectures each based on Local Area Networks (LAN), the use of personal computer-based operating systems, and the execution of activities and operations through a Wide Area Network (Internet) enable a revolution in spacecraft mission formulation, implementation, and flight operations. Hardware and software design, development, integration, test, and flight operations are all tied-in closely to a common thread that enables the smooth transitioning between program phases. The application of commercial software

  18. STS-60 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1994-01-01

    The STS-60 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixtieth flight of the Space Shuttle Program and eighteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET designated at ET-61 (Block 10); three SSME's which were designated as serial numbers 2012, 2034, and 2032 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-062. The RSRM's that were installed in each SRB were designated as 360L035A (lightweight) for the left SRB, and 360Q035B (quarterweight) for the right SRB. This STS-60 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume VIII, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-60 mission were to deploy and retrieve the Wake Shield Facility-1 (WSF-1), and to activate the Spacehab-2 payload and perform on-orbit experiments. Secondary objectives of this flight were to activate and command the Capillary Pumped Loop/Orbital Debris Radar Calibration Spheres/Breman Satellite Experiment/Getaway Special (GAS) Bridge Assembly (CAPL/ODERACS/BREMSAT/GBA) payload, the Auroral Photography Experiment-B (APE-B), and the Shuttle Amateur Radio Experiment-II (SAREX-II).

  19. Animation: Kepler-11 and Six Orbiting Planets

    NASA Video Gallery

    NASA's Kepler space telescope watches a star, Kepler-11. The star appears to blink in a pattern. It dims like clockwork as six "hands" of differing size orbit around it at different rates. Kepler-1...

  20. Digital communication constraints in prior space missions

    NASA Technical Reports Server (NTRS)

    Yassine, Nathan K.

    2004-01-01

    Digital communication is crucial for space endeavors. Jt transmits scientific and command data between earth stations and the spacecraft crew. It facilitates communications between astronauts, and provides live coverage during all phases of the mission. Digital communications provide ground stations and spacecraft crew precise data on the spacecraft position throughout the entire mission. Lessons learned from prior space missions are valuable for our new lunar and Mars missions set by our president s speech. These data will save our agency time and money, and set course our current developing technologies. Limitations on digital communications equipment pertaining mass, volume, data rate, frequency, antenna type and size, modulation, format, and power in the passed space missions are of particular interest. This activity is in support of ongoing communication architectural studies pertaining to robotic and human lunar exploration. The design capabilities and functionalities will depend on the space and power allocated for digital communication equipment. My contribution will be gathering these data, write a report, and present it to Communications Technology Division Staff. Antenna design is very carefully studied for each mission scenario. Currently, Phased array antennas are being developed for the lunar mission. Phased array antennas use little power, and electronically steer a beam instead of DC motors. There are 615 patches in the phased array antenna. These patches have to be modified to have high yield. 50 patches were created for testing. My part is to assist in the characterization of these patch antennas, and determine whether or not certain modifications to quartz micro-strip patch radiators result in a significant yield to warrant proceeding with repairs to the prototype 19 GHz ferroelectric reflect-array antenna. This work requires learning how to calibrate an automatic network, and mounting and testing antennas in coaxial fixtures. The purpose of this

  1. Antimatter Driven Sail for Deep Space Missions

    NASA Astrophysics Data System (ADS)

    Howe, Steven D.; Jackson, Gerald P.

    2005-02-01

    The concept of the Antimatter Driven Sail (ADS) has been examined in three major areas: Mission Architecture, Subsystem Technologies, and a Technology Roadmap. The Mission Architecture effort has focused on developing an integrated systems model to evaluate the performance of the entire spacecraft for a mission. The Subsystem Technologies investigation examined 1) the fundamental reactions between the antiprotons and the sail material and the subsequent momentum transfer, 2) a concept for storing antihydrogen at high densities, and 3) an entirely new concept for electrical power production. The new electrical-power concept may have applicability to nearer-term space missions as a power supply if the availability of antiprotons becomes common. In developing the Technology Roadmap, we examined the potential 1) for using recent developments in antiproton storage and antihydrogen formation to create a path to ultra-high density antihydrogen storage, and 2) for increasing production of antiprotons by modifying the existing Fermilab facility. Our system analysis indicates that a 10 kg instrument pay load could be sent to 250 AU in 10 years using 30 milligrams of antihydrogen. This amount of antimatter is clearly within the production potential of the US within the next 40 years using currently accepted accelerator technologies. Major aspects of the architecture remain to be investigated but the first-cut assessment of the mission profile, the subsystem technologies, and the technology development path have all been identified. The antimatter driven sail may in-fact allow humanity to consider sending probes to the stars.

  2. Viking mission support. [Deep Space Network activities

    NASA Technical Reports Server (NTRS)

    Johnston, D. W. H.

    1977-01-01

    Statistics listing the Deep Space Network tracking and command support and the discrepancy report status for 1 January through 28 February 1977 are presented in tables. The initial Viking extended mission period of normal DSN support, following the nonstandard operations during the solar conjunction period is included. Operational testing subsequent to the MK III data system installations at DSS 12, 44, and 62 during this period are also discussed.

  3. Internet Technology for Future Space Missions

    NASA Technical Reports Server (NTRS)

    Hennessy, Joseph F. (Technical Monitor); Rash, James; Casasanta, Ralph; Hogie, Keith

    2002-01-01

    Ongoing work at National Aeronautics and Space Administration Goddard Space Flight Center (NASA/GSFC), seeks to apply standard Internet applications and protocols to meet the technology challenge of future satellite missions. Internet protocols and technologies are under study as a future means to provide seamless dynamic communication among heterogeneous instruments, spacecraft, ground stations, constellations of spacecraft, and science investigators. The primary objective is to design and demonstrate in the laboratory the automated end-to-end transport of files in a simulated dynamic space environment using off-the-shelf, low-cost, commodity-level standard applications and protocols. The demonstrated functions and capabilities will become increasingly significant in the years to come as both earth and space science missions fly more sensors and the present labor-intensive, mission-specific techniques for processing and routing data become prohibitively. This paper describes how an IP-based communication architecture can support all existing operations concepts and how it will enable some new and complex communication and science concepts. The authors identify specific end-to-end data flows from the instruments to the control centers and scientists, and then describe how each data flow can be supported using standard Internet protocols and applications. The scenarios include normal data downlink and command uplink as well as recovery scenarios for both onboard and ground failures. The scenarios are based on an Earth orbiting spacecraft with downlink data rates from 300 Kbps to 4 Mbps. Included examples are based on designs currently being investigated for potential use by the Global Precipitation Measurement (GPM) mission.

  4. Developing Fault Models for Space Mission Software

    NASA Technical Reports Server (NTRS)

    Nikora, Allen P.; Munson, John C.

    2003-01-01

    A viewgraph presentation on the development of fault models for space mission software is shown. The topics include: 1) Goal: Improve Understanding of Technology Fault Generation Process; 2) Required Measurement; 3) Measuring Structural Evolution; 4) Module Attributes; 5) Principal Components of Raw Metrics; 6) The Measurement Process; 7) View of Structural Evolution at the System and Module Level; 8) Identifying and Counting Faults; 9) Fault Enumeration; 10) Modeling Fault Content; 11) Modeling Results; 12) Current and Future Work; and 13) Discussion and Conclusions.

  5. High performance techniques for space mission scheduling

    NASA Technical Reports Server (NTRS)

    Smith, Stephen F.

    1994-01-01

    In this paper, we summarize current research at Carnegie Mellon University aimed at development of high performance techniques and tools for space mission scheduling. Similar to prior research in opportunistic scheduling, our approach assumes the use of dynamic analysis of problem constraints as a basis for heuristic focusing of problem solving search. This methodology, however, is grounded in representational assumptions more akin to those adopted in recent temporal planning research, and in a problem solving framework which similarly emphasizes constraint posting in an explicitly maintained solution constraint network. These more general representational assumptions are necessitated by the predominance of state-dependent constraints in space mission planning domains, and the consequent need to integrate resource allocation and plan synthesis processes. First, we review the space mission problems we have considered to date and indicate the results obtained in these application domains. Next, we summarize recent work in constraint posting scheduling procedures, which offer the promise of better future solutions to this class of problems.

  6. STS-35 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Camp, David W.; Germany, D. M.; Nicholson, Leonard S.

    1991-01-01

    The STS-35 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities during this thirty-eighth flight of the Space Shuttle and the tenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of an External Tank (ET) (designated as ET-35/LWT-28), three Space Shuttle main engines (SSME's) (serial numbers 2024, 2012, and 2028 in positions 1, 2, and 3, respectively), and two Solid Rocket Boosters (SRB's) designated as BI-038. The primary objectives of this flight were to successfully perform the planned operations of the Ultraviolet Astronomy (Astro-1) payload and the Broad-Band X-Ray Telescope (BBXRT) payload in a 190-nmi. circular orbit which had an inclination of 28.45 degrees. The sequence of events for this mission is shown in tablular form. Summarized are the significant problems that occurred in the Orbiter subsystems during the mission. The official problem tracking list is presented. In addition, each Orbiter subsystem problem is cited in the applicable subsystem discussion.

  7. Modular Power Standard for Space Explorations Missions

    NASA Technical Reports Server (NTRS)

    Oeftering, Richard C.; Gardner, Brent G.

    2016-01-01

    Future human space exploration will most likely be composed of assemblies of multiple modular spacecraft elements with interconnected electrical power systems. An electrical system composed of a standardized set modular building blocks provides significant development, integration, and operational cost advantages. The modular approach can also provide the flexibility to configure power systems to meet the mission needs. A primary goal of the Advanced Exploration Systems (AES) Modular Power System (AMPS) project is to establish a Modular Power Standard that is needed to realize these benefits. This paper is intended to give the space exploration community a "first look" at the evolving Modular Power Standard and invite their comments and technical contributions.

  8. Space platform reference mission studies overview

    NASA Technical Reports Server (NTRS)

    Harrison, J. K.

    1981-01-01

    The design requirements for three major space platform systems are identified. The three were the Science and Applications Space Platform (SASP), the Geostationary Platform (GSP), and the Satellite Power System (SPS). Because the SASP and GSP were assumed to require no advanced technology for their development an advanced version of each was selected on which to base the design requirements. The SPS represented the opposite development state hence a nearer term test article was selected on which to base the requirements. The development period for these missions is estimated.

  9. On the Astron UV space mission data

    NASA Astrophysics Data System (ADS)

    Kilpio, E. Yu.; Mironov, A. V.; Malkov, O. Yu.

    The Soviet UV space mission Astron, launched in 1983, had been operational for eight years as the largest ultraviolet space telescope during its lifetime. Astron provided a lot of observational material for various types of astrophysical objects, but unfortunately these data were not widely available and, as a result, unduly forgotten. Here we present some results of our comparison of the Astron data to the modern UV stellar data, such as the NGSL spectral library, discuss the precision and accuracy achieved with Astron, and make some conclusions on potential application areas of these data.

  10. STS-79 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1996-01-01

    STS-79 was the fourth of nine planned missions to the Russian Mir Space Station. This report summarizes the activities such as rendezvous and docking and spaceborne experiment operations. The report also discusses the Orbiter, External Tank (ET), Solid Rocket Boosters (SRB), Reusable Solid Rocket Motor (RSRM) and the space shuttle main engine (SSME) systems performance during the flight. The primary objectives of this flight were to rendezvous and dock with the Mir Space Station and exchange a Mir Astronaut. A double Spacehab module carried science experiments and hardware, risk mitigation experiments (RME's) and Russian logistics in support of program requirements. Additionally, phase 1 program science experiments were carried in the middeck. Spacehab-05 operations were performed. The secondary objectives of the flight were to perform the operations necessary for the Shuttle Amateur Radio Experiment-2 (SAREX-2). Also, as a payload of opportunity, the requirements of Midcourse Space Experiment (MSX) were completed.

  11. STS-39 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1991-01-01

    The STS-39 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the fortieth flight of the Space Shuttle and the twelfth flight of the Orbiter Vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of the following: an External Tank (ET) (designated as ET-46 (LWT-39); three Space Shuttle main engines (SSME's) (serial numbers 2026, 2030, and 2029 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-043. The primary objective of this flight was to successfully perform the planned operations of the Infrared Background Signature Survey (IBSS), Air Force Payload (AFP)-675, Space Test Payload (STP)-1, and the Multipurpose Experiment Canister (MPEC) payloads.

  12. Space Missions Trade Space Generation and Assessment Using JPL Rapid Mission Architecture (RMA) Team Approach

    NASA Technical Reports Server (NTRS)

    Moeller, Robert C.; Borden, Chester; Spilker, Thomas; Smythe, William; Lock, Robert

    2011-01-01

    The JPL Rapid Mission Architecture (RMA) capability is a novel collaborative team-based approach to generate new mission architectures, explore broad trade space options, and conduct architecture-level analyses. RMA studies address feasibility and identify best candidates to proceed to further detailed design studies. Development of RMA first began at JPL in 2007 and has evolved to address the need for rapid, effective early mission architectural development and trade space exploration as a precursor to traditional point design evaluations. The RMA approach integrates a small team of architecture-level experts (typically 6-10 people) to generate and explore a wide-ranging trade space of mission architectures driven by the mission science (or technology) objectives. Group brainstorming and trade space analyses are conducted at a higher level of assessment across multiple mission architectures and systems to enable rapid assessment of a set of diverse, innovative concepts. This paper describes the overall JPL RMA team, process, and high-level approach. Some illustrative results from previous JPL RMA studies are discussed.

  13. Exo-C: A Space Mission for Direct Imaging and Spectroscopy of Extrasolar Planetary Systems

    NASA Technical Reports Server (NTRS)

    Stapelfeldt, Karl; Belikov, Ruslan; Marley, Mark; Bryden, Geoff; Serabyn, Eugene; Trauger, John; Cahoy, Kerri; Chakrabarti, Supriya; McElwain, Michael; Meadows, Victoria; Dekens, Frank; Warfield, Keith; Brenner, Michael; Brugarolas, Paul; Effinger, Robert T.; Heeg, Casey; Birsch, Brian; Kissel, Andrew; Kirst, John E.; Lang, Jared; Nissen, Joel; Oseas, Jeffrey M.; Pong, Chris; Sunada, Eric

    2015-01-01

    Exo-C is NASAs first community study of a modest aperture space telescope designed for high contrast observations of exoplanetary systems. The mission will be capable of taking optical spectra of nearby exoplanets in reflected light, discovering previously undetected planets, and imaging structure in a large sample of circumstellar disks. It will obtain unique science results on planets down to super-Earth sizes and serve as a technology pathfinder toward an eventual flagship-class mission to find and characterize habitable Earth-like exoplanets. We present the mission/payload design and highlight steps to reduce mission cost/risk relative to previous mission concepts. Key elements are an unobscured telescope aperture, an internal coronagraph with deformable mirrors for precise wavefront control, and an orbit and observatory design chosen for high thermal stability. Exo-C has a similar telescope aperture, orbit, lifetime, and spacecraft bus requirements to the highly successful Kepler mission (which is our cost reference). The needed technology development is on-course for a possible mission start in 2017. This paper summarizes the study final report completed in January 2015. During 2015 NASA will make a decision on its potential development.

  14. The Deep Space 1 and Space Technology 4/Champollion Missions

    NASA Technical Reports Server (NTRS)

    Weissman, Paul R.

    2000-01-01

    NASA's New Millennium Program (NMP) is designed to develop, test, and flight validate new, advanced technologies for planetary and Earth exploration missions, using a series of low cost spacecraft. Two of NMP's current missions include encounters with comets and asteroids. The Deep Space 1 mission was launched on October 24, 1998 and will fly by asteroid 1992 KD on July 29, 1999, and possibly Comet Wilson-Harrington and/or Comet Borrelly in 2001. The Space Technology 4/Champollion mission will be launched in April, 2003 and will rendezvous with, orbit and land on periodic Comet Tempel 1 in 2006. ST-4/Champollion is a joint project with CNES, the French space agency. The DS-1 mission is going well since launch and has already validated several major technologies, including solar electric propulsion (SEP), solar concentrator arrays, a small deep space transponder, and autonomous navigation. The spacecraft carries two scientific instruments: MICAS, a combined visible camera and UV and IR spectrometers, and PEPE, an ion and electron spectrometer. Testing of the science instruments is ongoing. Following the asteroid encounter in July, 1999, DS-1 will go on to encounters with one or both comets if NASA approves funding for an extended mission. The ST-4/Champollion mission will use an advanced, multi-engine SEP system to effect a rendezvous with Comet P/Tempel 1 in February, 2006, after a flight time of 2.8 years. After orbiting the comet for several months in order to map its surface and determine its gravity field, ST-4/Champollion will descend to the comet's surface and will anchor itself with a 3-meter long harpoon. Scientific experiments include narrow and wide angle cameras for orbital mapping, panoramic and near-field cameras for landing site mapping, a gas chromatograph/mass spectrometer, a combined microscope and infrared spectrometer, and physical properties probes. Cometary samples will be obtained from depths up to 1.4 meters. The spacecraft is solar powered

  15. New Space at Airbus Defence & Space to facilitate science missions

    NASA Astrophysics Data System (ADS)

    Boithias, Helene; Benchetrit, Thierry

    2016-10-01

    In addition to Airbus legacy activities, where Airbus satellites usually enable challenging science missions such as Venus Express, Mars Express, Rosetta with an historic landing on a comet, Bepi Colombo mission to Mercury and JUICE to orbit around Jupiter moon Ganymede, Swarm studying the Earth magnetic field, Goce to measure the Earth gravitational field and Cryosat to monitor the Earth polar ice, Airbus is now developing a new approach to facilitate next generation missions.After more than 25 years of collaboration with the scientists on space missions, Airbus has demonstrated its capacity to implement highly demanding missions implying a deep understanding of the science mission requirements and their intrinsic constraints such as- a very fierce competition between the scientific communities,- the pursuit of high maturity for the science instrument in order to be selected,- the very strict institutional budget limiting the number of operational missions.As a matter of fact, the combination of these constraints may lead to the cancellation of valuable missions.Based on that and inspired by the New Space trend, Airbus is developing an highly accessible concept called HYPE.The objective of HYPE is to make access to Space much more simple, affordable and efficient.With a standardized approach, the scientist books only the capacities he needs among the resources available on-board, as the HYPE satellites can host a large range of payloads from 1kg up to 60kg.At prices significantly more affordable than those of comparable dedicated satellite, HYPE is by far a very cost-efficient way of bringing science missions to life.After the launch, the scientist enjoys a plug-and-play access to two-way communications with his instrument through a secure high-speed portal available online 24/7.Everything else is taken care of by Airbus: launch services and the associated risk, reliable power supply, setting up and operating the communication channels, respect of space law

  16. Training for long duration space missions

    NASA Technical Reports Server (NTRS)

    Goldberg, Joseph H.

    1987-01-01

    The successful completion of an extended duration manned mission to Mars will require renewed research effort in the areas of crew training and skill retention techniques. The current estimate of inflight transit time is about nine months each way, with a six month surface visit, an order of magnitude beyond previous U.S. space missions. Concerns arise when considering the level of skill retention required for highly critical, one time operations such as an emergency procedure or a Mars orbit injection. The factors responsible for the level of complex skill retention are reviewed, optimal ways of refreshing degraded skills are suggested, and a conceptual crew training design for a Mars mission is outlined. Currently proposed crew activities during a Mars mission were reviewed to identify the spectrum of skills which must be retained over a long time period. Skill retention literature was reviewed to identify those factors which must be considered in deciding when and which tasks need retraining. Task, training, and retention interval factors were identified. These factors were then interpreted in light of the current state of spaceflight and adaptive training systems.

  17. STS-44 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1992-01-01

    The STS-44 Space Shuttle Program Mission Report is a summary of the vehicle subsystem operations during the forty-fourth flight of the Space Shuttle Program and the tenth flight of the Orbiter vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-53 (LWT-46); three Space Shuttle main engines (SSME's) (serial numbers 2015, 2030, and 2029 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-047. The lightweight redesigned Solid Rocket Motors (RSRM's) installed in each one of the SRB's were designated as 360L019A for the left SRB and 360W019B for the right SRB. The primary objective of the STS-44 mission was to successfully deploy the Department of Defense (DOD) Defense Support Program (DSP) satellite/inertial upper stage (IUS) into a 195 nmi. earth orbit at an inclination of 28.45 deg. Secondary objectives of this flight were to perform all operations necessary to support the requirements of the following: Terra Scout, Military Man in Space (M88-1), Air Force Maui Optical System Calibration Test (AMOS), Cosmic Radiation Effects and Activation Monitor (CREAM), Shuttle Activation Monitor (SAM), Radiation Monitoring Equipment-3 (RME-3), Visual Function Tester-1 (VFT-1), and the Interim Operational Contamination Monitor (IOCM) secondary payloads/experiments.

  18. Target Analysis for the Twinkle Space Mission

    NASA Astrophysics Data System (ADS)

    Rice, Malena; Tinetti, Giovanna; Zingales, Tiziano; Twinkle Consortium

    2016-10-01

    Twinkle is a dedicated exoplanet space mission planned for launch in 2019 to observe and characterize the atmospheres of planets around F, G, K, and M type stars. By obtaining high-resolution near-infrared transit spectra (0.5 - 4.5 microns), Twinkle will identify molecules of interest within planetary atmospheres. Twinkle will provide critical data for the characterization of individual exoplanets, leading to an improved understanding of planetary systems as a whole. In this study, we provide an analysis of potential targets for the Twinkle space mission, and we find that the spacecraft will be capable of observing a wide range of planet types, including Earths, Super Earths, Sub Neptunes, Large Neptunes, and Hot Jupiters. We discuss the population distribution of observable targets in terms of planet temperature and radius, host star temperature, and observation time necessary to achieve the desired signal-to-noise ratios. We also include sample Twinkle spectra from a simulated data set, as well as an example retrieval using the TauRex program to retrieve molecules in these simulated spectra. We conclude with a discussion of these results and their implications for the Twinkle mission.

  19. A mission planning concept and mission planning system for future manned space missions

    NASA Technical Reports Server (NTRS)

    Wickler, Martin

    1994-01-01

    The international character of future manned space missions will compel the involvement of several international space agencies in mission planning tasks. Additionally, the community of users requires a higher degree of freedom for experiment planning. Both of these problems can be solved by a decentralized mission planning concept using the so-called 'envelope method,' by which resources are allocated to users by distributing resource profiles ('envelopes') which define resource availabilities at specified times. The users are essentially free to plan their activities independently of each other, provided that they stay within their envelopes. The new developments were aimed at refining the existing vague envelope concept into a practical method for decentralized planning. Selected critical functions were exercised by planning an example, founded on experience acquired by the MSCC during the Spacelab missions D-1 and D-2. The main activity regarding future mission planning tasks was to improve the existing MSCC mission planning system, using new techniques. An electronic interface was developed to collect all formalized user inputs more effectively, along with an 'envelope generator' for generation and manipulation of the resource envelopes. The existing scheduler and its data base were successfully replaced by an artificial intelligence scheduler. This scheduler is not only capable of handling resource envelopes, but also uses a new technology based on neuronal networks. Therefore, it is very well suited to solve the future scheduling problems more efficiently. This prototype mission planning system was used to gain new practical experience with decentralized mission planning, using the envelope method. In future steps, software tools will be optimized, and all data management planning activities will be embedded into the scheduler.

  20. STS-49: Space shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1992-01-01

    The STS-49 Space Shuttle Program Mission Report contains a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and Space Shuttle main engine (SSME) subsystem performance during the forty-seventh flight of the Space Shuttle Program and the first flight of the Orbiter vehicle Endeavor (OV-105). In addition to the Endeavor vehicle, the flight vehicle consisted of an ET designated as ET-43 (LWT-36); three SSME's which were serial numbers 2030, 2015, and 2017 in positions 1, 2, and 3, respectively; and two SRB's designated as BI-050. The lightweight RSRM's installed in each SRB were designated as 360L022A for the left RSRM and 360L022B for the right RSRM.

  1. STS-48 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1991-01-01

    The STS-48 Space Shuttle Program Mission Report is a summary of the vehicle subsystem operations during the forty-third flight of the Space Shuttle Program and the thirteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-42 (LUT-35); three Space Shuttle main engines (SSME's) (serial numbers 2019, 2031, and 2107 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-046. The lightweight redesigned Solid Rocket Motors (RSRM's) installed in each one of the SRB's were designated as 360L018A for the left SRB and 360L018B for the right SRB. The primary objective of the flight was to successfully deploy the Upper Atmospheric Research Satellite (UARS) payload.

  2. STS-51 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1993-01-01

    The STS-51 Space Shuttle Program Mission Report summarizes the payloads as well as the orbiter, external tank (ET), solid rocket booster (SRB), redesigned solid rocket motor (RSRM), and the space shuttle main engine (SSME) systems performance during the fifty-seventh flight of the space shuttle program and seventeenth flight of the orbiter vehicle Discovery (OV-103). In addition to the orbiter, the flight vehicle consisted of an ET designated as ET-59; three SSME's, which were designated as serial numbers 2031, 2034, and 2029 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-060. The lightweight RSRM's that were installed in each SRB were designated as 360W033A for the left SRB and 360L033B for the right SRB.

  3. STS-56 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1993-01-01

    The STS-56 Space Shuttle Program Mission Report provides a summary of the Payloads, as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the fifty-fourth flight of the Space Shuttle Program and sixteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET (ET-54); three SSME's, which were designated as serial numbers 2024, 2033, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-058. The lightweight RSRM's that were installed in each SRB were designated as 360L031A for the left SRB and 360L031B for the right SRB.

  4. STS-40 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1991-01-01

    The STS-40 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-first flight of the Space Shuttle and the eleventh flight of the Orbiter Vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of an External Tank (ET) designated as ET-41 (LWT-34), three Space Shuttle main engines (SSME's) (serial numbers 2015, 2022, and 2027 in positions 1, 2, and 3, respectively), and two Solid Rocket Boosters (SRB's) designated as BI-044. The primary objective of the STS-40 flight was to successfully perform the planned operations of the Spacelab Life Sciences-1 (SLS-1) payload. The secondary objectives of this flight were to perform the operations required by the Getaway Special (GAS) payloads and the Middeck O-Gravity Dynamics Experiment (MODE) payload.

  5. Automation of Hubble Space Telescope Mission Operations

    NASA Technical Reports Server (NTRS)

    Burley, Richard; Goulet, Gregory; Slater, Mark; Huey, William; Bassford, Lynn; Dunham, Larry

    2012-01-01

    On June 13, 2011, after more than 21 years, 115 thousand orbits, and nearly 1 million exposures taken, the operation of the Hubble Space Telescope successfully transitioned from 24x7x365 staffing to 815 staffing. This required the automation of routine mission operations including telemetry and forward link acquisition, data dumping and solid-state recorder management, stored command loading, and health and safety monitoring of both the observatory and the HST Ground System. These changes were driven by budget reductions, and required ground system and onboard spacecraft enhancements across the entire operations spectrum, from planning and scheduling systems to payload flight software. Changes in personnel and staffing were required in order to adapt to the new roles and responsibilities required in the new automated operations era. This paper will provide a high level overview of the obstacles to automating nominal HST mission operations, both technical and cultural, and how those obstacles were overcome.

  6. NASA's Spitzer Space Telescope's Operational Mission Experience

    NASA Technical Reports Server (NTRS)

    Wilson, Robert K.; Scott, Charles P.

    2006-01-01

    New Generation of Detector Arrays(100 to 10,000 Gain in Capability over Previous Infrared Space Missions). IRAC: 256 x 256 pixel arrays operating at 3.6 microns, 4.5 microns, 5.8 microns, 8.0 microns. MIPS: Photometer with 3 sets of arrays operating at 24 microns, 70 microns and 160 microns. 128 x 128; 32 x 32 and 2 x 20 arrays. Spectrometer with 50-100 micron capabilities. IRS: 4 Array (128x128 pixel) Spectrograph, 4 -40 microns. Warm Launch Architecture: All other Infrared Missions launched with both the telescope and scientific instrument payload within the cryostat or Dewar. Passive cooling used to cool outer shell to approx.40 K. Cryogenic Boil-off then cools telescope to required 5.5K. Earth Trailing Heliocentric Orbit: Increased observing efficiency, simplification of observation planning, removes earth as heat source.

  7. Granulation in Red Giants: Observations by the Kepler Mission and Three-dimensional Convection Simulations

    NASA Astrophysics Data System (ADS)

    Mathur, S.; Hekker, S.; Trampedach, R.; Ballot, J.; Kallinger, T.; Buzasi, D.; García, R. A.; Huber, D.; Jiménez, A.; Mosser, B.; Bedding, T. R.; Elsworth, Y.; Régulo, C.; Stello, D.; Chaplin, W. J.; De Ridder, J.; Hale, S. J.; Kinemuchi, K.; Kjeldsen, H.; Mullally, F.; Thompson, S. E.

    2011-11-01

    The granulation pattern that we observe on the surface of the Sun is due to hot plasma rising to the photosphere where it cools down and descends back into the interior at the edges of granules. This is the visible manifestation of convection taking place in the outer part of the solar convection zone. Because red giants have deeper convection zones than the Sun, we cannot a priori assume that their granulation is a scaled version of solar granulation. Until now, neither observations nor one-dimensional analytical convection models could put constraints on granulation in red giants. With asteroseismology, this study can now be performed. We analyze ~1000 red giants that have been observed by Kepler during 13 months. We fit the power spectra with Harvey-like profiles to retrieve the characteristics of the granulation (timescale τgran and power P gran). We search for a correlation between these parameters and the global acoustic-mode parameter (the position of maximum power, νmax) as well as with stellar parameters (mass, radius, surface gravity (log g), and effective temperature (T eff)). We show that τeffvpropν-0.89 max and P granvpropν-1.90 max, which is consistent with the theoretical predictions. We find that the granulation timescales of stars that belong to the red clump have similar values while the timescales of stars in the red giant branch are spread in a wider range. Finally, we show that realistic three-dimensional simulations of the surface convection in stars, spanning the (T eff, log g) range of our sample of red giants, match the Kepler observations well in terms of trends.

  8. GRANULATION IN RED GIANTS: OBSERVATIONS BY THE KEPLER MISSION AND THREE-DIMENSIONAL CONVECTION SIMULATIONS

    SciTech Connect

    Mathur, S.; Hekker, S.; Trampedach, R.; Ballot, J.; Kallinger, T.; Buzasi, D.; Garcia, R. A.; Jimenez, A.; Regulo, C.; Mosser, B.; Elsworth, Y.; Chaplin, W. J.; Hale, S. J.; De Ridder, J.; Kinemuchi, K.; Mullally, F.

    2011-11-10

    The granulation pattern that we observe on the surface of the Sun is due to hot plasma rising to the photosphere where it cools down and descends back into the interior at the edges of granules. This is the visible manifestation of convection taking place in the outer part of the solar convection zone. Because red giants have deeper convection zones than the Sun, we cannot a priori assume that their granulation is a scaled version of solar granulation. Until now, neither observations nor one-dimensional analytical convection models could put constraints on granulation in red giants. With asteroseismology, this study can now be performed. We analyze {approx}1000 red giants that have been observed by Kepler during 13 months. We fit the power spectra with Harvey-like profiles to retrieve the characteristics of the granulation (timescale {tau}{sub gran} and power P{sub gran}). We search for a correlation between these parameters and the global acoustic-mode parameter (the position of maximum power, {nu}{sub max}) as well as with stellar parameters (mass, radius, surface gravity (log g), and effective temperature (T{sub eff})). We show that {tau}{sub eff}{proportional_to}{nu}{sup -0.89}{sub max} and P{sub gran}{proportional_to}{nu}{sup -1.90}{sub max}, which is consistent with the theoretical predictions. We find that the granulation timescales of stars that belong to the red clump have similar values while the timescales of stars in the red giant branch are spread in a wider range. Finally, we show that realistic three-dimensional simulations of the surface convection in stars, spanning the (T{sub eff}, log g) range of our sample of red giants, match the Kepler observations well in terms of trends.

  9. A Distant Mirror: Solar Oscillations Observed on Neptune by the Kepler K2 Mission

    NASA Astrophysics Data System (ADS)

    Gaulme, P.; Rowe, J. F.; Bedding, T. R.; Benomar, O.; Corsaro, E.; Davies, G. R.; Hale, S. J.; Howe, R.; Garcia, R. A.; Huber, D.; Jiménez, A.; Mathur, S.; Mosser, B.; Appourchaux, T.; Boumier, P.; Jackiewicz, J.; Leibacher, J.; Schmider, F.-X.; Hammel, H. B.; Lissauer, J. J.; Marley, M. S.; Simon, A. A.; Chaplin, W. J.; Elsworth, Y.; Guzik, J. A.; Murphy, N.; Silva Aguirre, V.

    2016-12-01

    Starting in 2014 December, Kepler K 2 observed Neptune continuously for 49 days at a 1 minute cadence. The goals consisted of studying its atmospheric dynamics, detecting its global acoustic oscillations, and those of the Sun, which we report on here. We present the first indirect detection of solar oscillations in intensity measurements. Beyond the remarkable technical performance, it indicates how Kepler would see a star like the Sun. The result from the global asteroseismic approach, which consists of measuring the oscillation frequency at maximum amplitude ν max and the mean frequency separation between mode overtones Δν, is surprising as the ν max measured from Neptune photometry is larger than the accepted value. Compared to the usual reference ν max,⊙ = 3100 μHz, the asteroseismic scaling relations therefore make the solar mass and radius appear larger by 13.8 ± 5.8% and 4.3 ± 1.9%, respectively. The higher ν max is caused by a combination of the value of ν max,⊙, being larger at the time of observations than the usual reference from SOHO/VIRGO/SPM data (3160 ± 10 μHz), and the noise level of the K 2 time series, being 10 times larger than VIRGO’s. The peak-bagging method provides more consistent results: despite a low signal-to-noise ratio (S/N), we model 10 overtones for degrees ℓ = 0, 1, 2. We compare the K 2 data with simultaneous SOHO/VIRGO/SPM photometry and BiSON velocity measurements. The individual frequencies, widths, and amplitudes mostly match those from VIRGO and BiSON within 1σ, except for the few peaks with the lowest S/N.

  10. STS-72 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1996-01-01

    The STS-72 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the seventy-fourth flight of the Space Shuttle Program, the forty-ninth flight since the return-to-flight, and the tenth flight of the Orbiter Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-75; three Block I SSME's that were designated as serial numbers 2028, 2039, and 2036 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-077. The RSRM's, designated RSRM-52, were installed in each SRB and the individual RSRM's were designated as 36OW052A for the left SRB, and 36OW052B for the right SRB. Appendix A lists the sources of data, both formal and informal, that were used to prepare this report. The primary objectives of this flight were to retrieve the Japanese Space Flyer Unit (JSFU) and deploy and retrieve the Office of Aeronautics and Space Technology-Flyer (OAST-Flyer). Secondary objectives were to perform the operations of the Shuttle Solar Backscatter Ultraviolet (SSBUV/A) experiment, Shuttle Laser Altimeter (SLA)/get-Away Special (GAS) payload, Physiological and Anatomical Rodent Experiment/National Institutes of Health-Cells (STL/NIH-C) experiment, Protein Crystal Growth-Single Locker Thermal Enclosure System (PCG-STES) experiment, Commercial Protein Crystal Growth (CPCG) payload and perform two extravehicular activities (EVA's) to demonstrate International Space Station Alpha (ISSA) assembly techniques). Appendix B provides the definition of acronyms and abbreviations used throughout the report. All times during the flight are given in Greenwich mean time (GMT) and mission elapsed time (MET).

  11. Kepler Field of View

    NASA Video Gallery

    The Kepler mission will be looking continuously at over 100,000 stars in one region of the sky, in the Cygnus and Lyra constellations. The field of view is extremely large for an astronomical teles...

  12. STS-42 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1992-01-01

    The STS-42 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-fifth flight of the Space Shuttle Program and the fourteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-52 (LWT-45); three Space Shuttle main engines (SSME's), which were serial numbers 2026, 2022, and 2027 in positions 1, 2, and 3, respectively; and two Solid Rocket Boosters (SRB's) designated as BI-048. The lightweight redesigned Solid Rocket Motors (RSRM's) installed in each one of the SRB's were designated as 360L020A for the left SRM and 360Q020B for the right SRM. The primary objective of the STS-42 mission was to complete the objectives of the first International Microgravity Laboratory (IML-1). Secondary objectives were to perform all operations necessary to support the requirements of the following: Gelation of Sols: Applied Microgravity Research (GOSAMR); Student Experiment 81-09 (Convection in Zero Gravity); Student Experiment 83-02 (Capillary Rise of Liquid Through Granular Porous Media); the Investigation into Polymer Membrane Processing (IPMP); the Radiation Monitoring Equipment-3 (RME-3); and Get-Away Special (GAS) payloads carried on the GAS Beam Assembly.

  13. STS-75 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1996-01-01

    The STS-75 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the seventy-fifth flight of the Space Shuttle Program, the fiftieth flight since the return-to-flight, and the nineteenth flight of the Orbiter Columbia (OV-102). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-76; three SSME's that were designated as serial numbers 2029, 2034, and 2017 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-078. The RSRM's, designated RSRM-53, were installed in each SRB and the individual RSRMs were designated as 36OW53A for the left SRB, and 36OW053B for the right SRB. The primary objectives of this flight were to perform the operations necessary to fulfill the requirements of the Tethered Satellite System-1 R (TSS-1R), and the United States Microgravity Payload-3 (USMP-3). The secondary objectives were to complete the operations of the Orbital Acceleration Research Experiment (OARE), and to meet the requirements of the Middeck Glovebox (MGBX) facility and the Commercial Protein Crystal Growth (CPCG) experiment. Appendix A provides the definition of acronyms and abbreviations used thorughout the report. All times during the flight are given in Greenwich mean time (GMT) and mission elapsed time (MET).

  14. Emergency Communications for NASA's Deep Space Missions

    NASA Technical Reports Server (NTRS)

    Shambayati, Shervin; Lee, Charles H.; Morabito, David D.; Cesarone, Robert J.; Abraham, Douglas S.

    2011-01-01

    The ability to communicate with spacecraft during emergencies is a vital service that NASA's Deep Space Network (DSN) provides to all deep space missions. Emergency communications is characterized by low data rates(typically is approximately10 bps) with the spacecraft using either a low-gain antenna (LGA, including omnidirectional antennas) or,in some cases, a medium-gain antenna (MGA). Because of the use of LGAs/MGAs for emergency communications, the transmitted power requirements both on the spacecraft andon the ground are substantially greater than those required for normal operations on the high-gain antenna (HGA) despite the lower data rates. In this paper, we look at currentand future emergency communications capabilities available to NASA's deep-space missions and discuss their limitations in the context of emergency mode operations requirements.These discussions include the use of the DSN 70-m diameter antennas, the use of the 34-m diameter antennas either alone or arrayed both for the uplink (Earth-to-spacecraft) and the downlink (spacecraft-to-Earth), upgrades to the ground transmitters, and spacecraft power requirements both with unitygain (0 dB) LGAs and with antennas with directivity (>0 dB gain, either LGA or MGA, depending on the gain). Also discussed are the requirements for forward-error-correctingcodes for both the uplink and the downlink. In additional, we introduce a methodology for proper selection of a directionalLGA/MGA for emergency communications.

  15. Positive psychological effects of space missions

    NASA Astrophysics Data System (ADS)

    Ritsher, Jennifer Boyd; Ihle, Eva C.; Kanas, Nick

    2005-07-01

    Being in space is a powerful experience that can have an enduring, positive impact on the psychological well-being of astronauts and cosmonauts. We sought to examine the frequency, intensity and distribution of such salutogenic experiences among persons who have flown in space, using a questionnaire we developed based on the scientific literature and first person accounts. All participants reported positive effects of being in space, but the degree of change varied widely, and some experiences were particularly common. Three of our five predicted attitude behavior relationships were supported by the data. Response patterns did not vary according to demographics or time in space. Cluster analysis yielded two groups of participants. One group was generally more reactive and also placed a higher priority on perceptions of space than did the other group. We conclude that positive experiences are common among space travelers and seem to cluster into meaningful patterns that may be consequential for Mars missions. We consider the possible selection, training, and monitoring issues raised by our findings.

  16. Positive psychological effects of space missions.

    PubMed

    Ritsher, Jennifer Boyd; Ihle, Eva C; Kanas, Nick

    2005-01-01

    Being in space is a powerful experience that can have an enduring, positive impact on the psychological well-being of astronauts and cosmonauts. We sought to examine the frequency, intensity and distribution of such salutogenic experiences among persons who have flown in space, using a questionnaire we developed based on the scientific literature and first person accounts. All participants reported positive effects of being in space, but the degree of change varied widely, and some experiences were particularly common. Three of our five predicted attitude-behavior relationships were supported by the data. Response patterns did not vary according to demographics or time in space. Cluster analysis yielded two groups of participants. One group was generally more reactive and also placed a higher priority on perceptions of space than did the other group. We conclude that positive experiences are common among space travelers and seem to cluster into meaningful patterns that may be consequential for Mars missions. We consider the possible selection, training, and monitoring issues raised by our findings.

  17. Irreducible Tests for Space Mission Sequencing Software

    NASA Technical Reports Server (NTRS)

    Ferguson, Lisa

    2012-01-01

    As missions extend further into space, the modeling and simulation of their every action and instruction becomes critical. The greater the distance between Earth and the spacecraft, the smaller the window for communication becomes. Therefore, through modeling and simulating the planned operations, the most efficient sequence of commands can be sent to the spacecraft. The Space Mission Sequencing Software is being developed as the next generation of sequencing software to ensure the most efficient communication to interplanetary and deep space mission spacecraft. Aside from efficiency, the software also checks to make sure that communication during a specified time is even possible, meaning that there is not a planet or moon preventing reception of a signal from Earth or that two opposing commands are being given simultaneously. In this way, the software not only models the proposed instructions to the spacecraft, but also validates the commands as well.To ensure that all spacecraft communications are sequenced properly, a timeline is used to structure the data. The created timelines are immutable and once data is as-signed to a timeline, it shall never be deleted nor renamed. This is to prevent the need for storing and filing the timelines for use by other programs. Several types of timelines can be created to accommodate different types of communications (activities, measurements, commands, states, events). Each of these timeline types requires specific parameters and all have options for additional parameters if needed. With so many combinations of parameters available, the robustness and stability of the software is a necessity. Therefore a baseline must be established to ensure the full functionality of the software and it is here where the irreducible tests come into use.

  18. STS-76 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1996-01-01

    The STS-76 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the seventy-sixth flight of the Space Shuttle Program, the fifty-first flight since the return-to-flight, and the sixteenth flight of the Orbiter Atlantis (OV-104). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-77; three SSME's that were designated as serial numbers 2035, 2109, and 2019 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-079. The RSRM's, designated RSRM-46, were installed in each SRB and the individual RSRM's were designated as 360TO46A for the left SRB, and 360TO46B for the right SRB. The primary objectives of this flight were to rendezvous and dock with the Mir Space Station and transfer one U.S. Astronaut to the Mir. A single Spacehab module carried science equipment and hardware, Risk Mitigation Experiments (RME's), and Russian Logistics in support of the Phase 1 Program requirements. In addition, the European Space Agency (ESA) Biorack operations were performed. Appendix A lists the sources of data, both formal and informal, that were used to prepare this report. Appendix B provides the definition of acronyms and abbreviations used throughout the report. All times during the flight are given in Greenwich mean time (GMT) and mission elapsed time (MET).

  19. STS-46 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1992-01-01

    The STS-46 Space Shuttle Program Mission Report contains a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the forty-ninth flight of the Space Shuttle Program, and the twelfth flight of the Orbiter vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an ET, designated ET-48 (LWT-41); three SSME's, which were serial numbers 2032, 2033, and 2027 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-052. The lightweight/redesigned SRM's that were installed in each SRB were designated 360W025A for the left RSRM and 360L025B for the right RSRM. The primary objective of this flight was to successfully deploy the European Retrievable Carrier (EURECA) payload and perform the operations of the Tethered Satellite System-1 (TSS-1) and the Evaluation of Oxygen Interaction with Material 3/Thermal Energy Management Processes 2A-3 (EOIM-3/TEMP 2A-3). The secondary objectives of this flight were to perform the operations of the IMAX Cargo Bay Camera (ICBC), Consortium for Material Development in Space Complex Autonomous Payload-2 and 3 (CONCAP-2 and CONCAP-3), Limited Duration Space Environment Candidate Materials Exposure (LDCE), Pituitary Growth Hormone Cell Function (PHCF), and Ultraviolet Plume Instrumentation (UVPI). In addition to summarizing subsystem performance, this report also discusses each Orbiter, ET, SSME, SRB, and RSRM in-flight anomaly in the applicable section of the report. Also included in the discussion is a reference to the assigned tracking number as published on the Problem Tracking List. All times are given in Greenwich mean time (G.m.t.) as well as mission elapsed time (MET).

  20. STS-46 Space Shuttle mission report

    NASA Astrophysics Data System (ADS)

    Fricke, Robert W.

    1992-10-01

    The STS-46 Space Shuttle Program Mission Report contains a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the forty-ninth flight of the Space Shuttle Program, and the twelfth flight of the Orbiter vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an ET, designated ET-48 (LWT-41); three SSME's, which were serial numbers 2032, 2033, and 2027 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-052. The lightweight/redesigned SRM's that were installed in each SRB were designated 360W025A for the left RSRM and 360L025B for the right RSRM. The primary objective of this flight was to successfully deploy the European Retrievable Carrier (EURECA) payload and perform the operations of the Tethered Satellite System-1 (TSS-1) and the Evaluation of Oxygen Interaction with Material 3/Thermal Energy Management Processes 2A-3 (EOIM-3/TEMP 2A-3). The secondary objectives of this flight were to perform the operations of the IMAX Cargo Bay Camera (ICBC), Consortium for Material Development in Space Complex Autonomous Payload-2 and 3 (CONCAP-2 and CONCAP-3), Limited Duration Space Environment Candidate Materials Exposure (LDCE), Pituitary Growth Hormone Cell Function (PHCF), and Ultraviolet Plume Instrumentation (UVPI). In addition to summarizing subsystem performance, this report also discusses each Orbiter, ET, SSME, SRB, and RSRM in-flight anomaly in the applicable section of the report. Also included in the discussion is a reference to the assigned tracking number as published on the Problem Tracking List. All times are given in Greenwich mean time (G.m.t.) as well as mission elapsed time (MET).

  1. Hubble Space Telescope First Servicing Mission Prelaunch Mission Operation Report

    NASA Technical Reports Server (NTRS)

    1993-01-01

    The Hubble Space Telescope (HST) is a high-performance astronomical telescope system designed to operate in low-Earth orbit. It is approximately 43 feet long, with a diameter of 10 feet at the forward end and 14 feet at the aft end. Weight at launch was approximately 25,000 pounds. In principle, it is no different than the reflecting telescopes in ground-based astronomical observatories. Like ground-based telescopes, the HST was designed as a general-purpose instrument, capable of using a wide variety of scientific instruments at its focal plane. This multi-purpose characteristic allows the HST to be used as a national facility, capable of supporting the astronomical needs of an international user community. The telescope s planned useful operational lifetime is 15 years, during which it will make observations in the ultraviolet, visible, and infrared portions of the spectrum. The extended operational life of the HST is possible by using the capabilities of the Space Transportation System to periodically visit the HST on-orbit to replace failed or degraded components, install instruments with improved capabilities, re-boost the HST to higher altitudes compensating for gravitational effects, and to bring the HST back to Earth when the mission is terminated. The largest ground-based observatories, such as the 200-inch aperture Hale telescope at Palomar Mountain, California, can recognize detail in individual galaxies several billion light years away. However, like all earthbound devices, the Hale telescope is limited because of the blurring effect of the Earth s atmosphere. Further, the wavelength region observable from the Earth s surface is limited by the atmosphere to the visible part of the spectrum. The very important ultraviolet portion of the spectrum is lost. The HST uses a 2.4-meter reflective optics system designed to capture data over a wavelength region that reaches far into the ultraviolet and infrared portions of the spectrum.

  2. Space missions orbits around small worlds

    NASA Astrophysics Data System (ADS)

    Cardoso dos Santos, Josué; dos Santos Carvalho, Jean Paulo; Vilhena de Moraes, Rodolpho; Bertachini de Almeida Prado, Antônio Fernando

    2015-08-01

    Space missions under study to visit icy moons and small worlds in our solar system will requires orbits with low-altitude and high inclinations. These orbits provides a better coverage to map the surface and to analyse the gravitational and magnetic fields. In this context, obtain these orbits has become important in planning of these missions. Celestial bodies like Haumea, Europa, Ganymede, Callisto, Enceladus, Titan and Triton are among the objects under study study to receive missions in a near future. In order to obtain low-altitude and high inclined orbits for future exploration of these bodies, this work aims to present an analytical study to describe and evaluate gravitational disturbances over a spacecraft's orbit around a minor body. An analytical model for the third-body perturbation is presented. Perturbations due to the non-sphericity of the minor body are considered. The effects on spacecraft's orbital elements are analyzed to provide the the more useful and desired orbits. The dynamic of these orbits is explored by numerical simulations. The results present good accordance with the literature.

  3. Spreadsheets for Analyzing and Optimizing Space Missions

    NASA Technical Reports Server (NTRS)

    Some, Raphael R.; Agrawal, Anil K.; Czikmantory, Akos J.; Weisbin, Charles R.; Hua, Hook; Neff, Jon M.; Cowdin, Mark A.; Lewis, Brian S.; Iroz, Juana; Ross, Rick

    2009-01-01

    XCALIBR (XML Capability Analysis LIBRary) is a set of Extensible Markup Language (XML) database and spreadsheet- based analysis software tools designed to assist in technology-return-on-investment analysis and optimization of technology portfolios pertaining to outer-space missions. XCALIBR is also being examined for use in planning, tracking, and documentation of projects. An XCALIBR database contains information on mission requirements and technological capabilities, which are related by use of an XML taxonomy. XCALIBR incorporates a standardized interface for exporting data and analysis templates to an Excel spreadsheet. Unique features of XCALIBR include the following: It is inherently hierarchical by virtue of its XML basis. The XML taxonomy codifies a comprehensive data structure and data dictionary that includes performance metrics for spacecraft, sensors, and spacecraft systems other than sensors. The taxonomy contains >700 nodes representing all levels, from system through subsystem to individual parts. All entries are searchable and machine readable. There is an intuitive Web-based user interface. The software automatically matches technologies to mission requirements. The software automatically generates, and makes the required entries in, an Excel return-on-investment analysis software tool. The results of an analysis are presented in both tabular and graphical displays.

  4. STS-68 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1995-01-01

    The STS-68 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-fifth flight of the Space Shuttle Program and the seventh flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-65; three SSMEs that were designated as serial numbers 2028, 2033, and 2026 in positions 1, 2, and 3, respectively; and two SRBs that were designated BI-067. The RSRMs that were installed in each SRB were designated as 360W040A for the left SRB and 360W040B for the right SRB. The primary objective of this flight was to successfully perform the operations of the Space Radar Laboratory-2 (SRL-2). The secondary objectives of the flight were to perform the operations of the Chromosome and Plant Cell Division in Space (CHROMEX), the Commercial Protein Crystal Growth (CPCG), the Biological Research in Canisters (BRIC), the Cosmic Radiation Effects and Activation Monitor (CREAM), the Military Application of Ship Tracks (MAST), and five Get-Away Special (GAS) payloads.

  5. STS-47 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1992-01-01

    The STS-47 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the fiftieth Space Shuttle Program flight and the second flight of the Orbiter Vehicle Endeavour (OV-105). In addition to the Endeavour vehicle, the flight vehicle consisted of the following: an ET which was designated ET-45 (LWT-38); three SSME's which were serial numbers 2026, 2022, and 2029 and were located in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-053. The lightweight/redesigned RSRM that was installed in the left SRB was designated 360L026A, and the RSRM that was installed in the right SRB was 360W026B. The primary objective of the STS-47 flight was to successfully perform the planned operations of the Spacelab-J (SL-J) payload (containing 43 experiments--of which 34 were provided by the Japanese National Space Development Agency (NASDA)). The secondary objectives of this flight were to perform the operations of the Israeli Space Agency Investigation About Hornets (ISAIAH) payload, the Solid Surface Combustion Experiment (SSCE), the Shuttle Amateur Radio Experiment-2 (SAREX-2), and the Get-Away Special (GAS) payloads. The Ultraviolet Plume Instrument (UVPI) was flown as a payload of opportunity.

  6. STS-47 Space Shuttle mission report

    NASA Astrophysics Data System (ADS)

    Fricke, Robert W., Jr.

    1992-10-01

    The STS-47 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the fiftieth Space Shuttle Program flight and the second flight of the Orbiter Vehicle Endeavour (OV-105). In addition to the Endeavour vehicle, the flight vehicle consisted of the following: an ET which was designated ET-45 (LWT-38); three SSME's which were serial numbers 2026, 2022, and 2029 and were located in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-053. The lightweight/redesigned RSRM that was installed in the left SRB was designated 360L026A, and the RSRM that was installed in the right SRB was 360W026B. The primary objective of the STS-47 flight was to successfully perform the planned operations of the Spacelab-J (SL-J) payload (containing 43 experiments--of which 34 were provided by the Japanese National Space Development Agency (NASDA)). The secondary objectives of this flight were to perform the operations of the Israeli Space Agency Investigation About Hornets (ISAIAH) payload, the Solid Surface Combustion Experiment (SSCE), the Shuttle Amateur Radio Experiment-2 (SAREX-2), and the Get-Away Special (GAS) payloads. The Ultraviolet Plume Instrument (UVPI) was flown as a payload of opportunity.

  7. STS-45 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1992-01-01

    The STS-45 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-sixth flight of the Space Shuttle Program and the eleventh flight of the Orbiter Vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an External Tank (ET) designated as ET-44 (LWT-37); three Space Shuttle main engines (SSME's), which were serial numbers 2024, 2012, and 2028 in positions 1, 2, and 3, respectively; and two Solid Rocket Boosters (SRB's) designated as BI-049. The lightweight redesigned Solid Rocket Motors (RSRM's) installed in each of the SRB's were designated as 360L021A for the left SRM and 360W021B for the right SRM. The primary objective of this mission was to successfully perform the planned operations of the Atmospheric Laboratory for Applications and Science-1 (ATLAS-1) and the Shuttle Solar Backscatter Ultraviolet Instrument (SSBUV) payloads. The secondary objectives were to successfully perform all operations necessary to support the requirements of the following: the Space Tissue Loss-01 (STL-01) experiment; the Radiation Monitoring Equipment-3 (RME-3) experiment; the Visual Function Tester-2 (VFT-2) experiment; the Cloud Logic to Optimize use of Defense System (CLOUDS-1A) experiment; the Shuttle Amateur Radio Experiment 2 (SAREX-2) Configuration B; the Investigation into Polymer Membranes Processing experiment; and the Get-Away Special (GAS) payload G-229. The Ultraviolet Plume Instrument (UVPI) was a payload of opportunity that required no special maneuvers. In addition to the primary and secondary objectives, the crew was tasked to perform as many as 10 Development Test Objectives (DTO'S) and 14 Detailed Supplementary Objectives (DSO's).

  8. STS-69 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1995-01-01

    The STS-69 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the seventy-first flight of the Space Shuttle Program, the forty-sixth flight since the return-to-flight, and the ninth flight of the Orbiter Endeavour(OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-72; three SSME's that were designated as serial numbers 2035, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-074. The RSRMS, designated RSRM-44, were installed in each SRB and the individual RSRM's were designated as 36OL048A for the left SRB, and 36OW048B for the right SRB. The primary objectives of this flight were to perform the operations necessary to fulfill the requirments of Wake Shield Facility (WSF) and SPARTAN-201. The secondary objectives were to perform the operation of the International Extreme Ultraviolet Hitchhiker (IEH-1), the Capillary Pumped Loop-2/GAS Bridge Assembly (CAPL-2/GBA), Thermal Energy Storage (TES), Auroral Photography Experiment-B (APE-B) and the Extravehicular Activity (EVA) Development Flight Test 02 (EDFT-02), the Biological Research in Canister (BRIC) payload, the Commercial Generic Bioprocessing Apparatus (CGBA) payload, the Electrolysis Performance Improvement Concept Study (EPICS) payload, the Space Tissue Loss, National Institute of Health-Cells (STL/NIH-CS) payload, and the Commercial Middeck Instrumentation Technology Associates Experiment (CMIX). Appendix A lists the sources of data, both formal and informal, that were used to prepare this report. Appendix B provides the definition of acronyms and abbreviations used throughout the report. All times during the flight are given in Greenwich mean time (GMT) and mission elapsed time (MET).

  9. STS-54 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1993-01-01

    The STS-54 Space Shuttle Program Mission Report is a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle Main Engine (SSME) subsystems performance during this fifty-third flight of the Space Shuttle Program, and the third flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET, which was designated ET-51; three SSME's, which were serial numbers 2019, 2033, and 2018 in positions 1, 2, and 3, respectively; and two retrievable and reusable SRB's which were designated BI-056. The lightweight RSRM's that were installed in each SRB were designated 360L029A for the left SRB, and 360L029B for the right SRB. The primary objectives of this flight were to perform the operations to deploy the Tracking and Data Relay Satellite-F/Inertial Upper Stage payload and to fulfill the requirements of the Diffuse X-Ray Spectrometer (DXS) payload. The secondary objective was to fly the Chromosome and Plant Cell Division in Space (CHROMEX), Commercial Generic Bioprocessing Apparatus (CGBA), Physiological and Anatomical Rodent Experiment (PARE), and the Solid Surface Combustion Experiment (SSCE). In addition to presenting a summary of subsystem performance, this report also discusses each Orbiter, ET, SSME, SRB, and RSRM in-flight anomaly in the applicable section of the report. The official tracking number for each in-flight anomaly, assigned by the cognizant project, is also shown. All times are given in Greenwich mean time (G.m.t.) and mission elapsed time (MET).

  10. STS-74 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1996-01-01

    The STS-74 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the seventy-third flight of the Space Shuttle Program, the forty-eighth flight since the return-to-flight, and the fifteenth flight of the Orbiter Atlantis (OV-104). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-74; three Phase 11 SSME's that were designated as serial numbers 2012, 2026, and 2032 in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-076. The RSRM's, designated RSRM-51, were installed in each SRB and the individual RSRM's were designated as 360TO51 A for the left SRB, and 360TO51 B for the right SRB. The primary objectives of this flight were to rendezvous and dock with the Mir Space Station and perform life sciences investigations. The Russian Docking Module (DM) was berthed onto the Orbiter Docking System (ODS) using the Remote Manipulator System (RMS), and the Orbiter docked to the Mir with the DM. When separating from the Mir, the Orbiter undocked, leaving the DM attached to the Mir. The two solar arrays, mounted on the DM, were delivered for future Russian installation to the Mir. The secondary objectives of the flight were to perform the operations necessary to fulfill the requirements of the GLO experiment (GLO-4)/Photogrammetric Appendage Structural Dynamics Experiment Payload (PASDE) (GPP), the IMAX Cargo Bay Camera (ICBC), and the Shuttle Amateur Radio Experiment-2 (SAREX-2). Appendix A lists the sources of data, both formal and informal, that were used to prepare this report. Appendix B provides the definition of acronyms and abbreviations used throughout the report. All times during the flight are given in Greenwich mean time (GMT)) and mission elapsed time (MET).

  11. The Kepler Follow-up Observation Program

    NASA Astrophysics Data System (ADS)

    Gautier, T. N.; Borucki, W. J.; Caldwell, D. A.; Koch, D. G.

    2007-07-01

    The Kepler mission will use a space based, 95-cm Schmidt telescope to survey 100,000 late type dwarf stars for transiting Earth-sized planets over a period of 4 years. Up to ˜ 2000 such planets might be detected along with a hundred or more transiting giant planets. About 1,000 false positive planet detections, due mainly to eclipsing binary stars, will also be found. A ground based follow-up program is planned to observe all of the planet candidates found by Kepler to weed out these false positives and produce a final catalog with a reliability greater than 95%.

  12. Space Missions and Information Technology: Some Thoughts and Highlights

    NASA Technical Reports Server (NTRS)

    Doyle, Richard J.

    2006-01-01

    A viewgraph presentation about information technology and its role in space missions is shown. The topics include: 1) Where is the IT on Space Missions? 2) Winners of the NASA Software of the Year Award; 3) Space Networking Roadmap; and 4) 10 (7) -Year Vision for IT in Space.

  13. Space Interferometry Mission starlight and metrology subsystems

    NASA Astrophysics Data System (ADS)

    Ames, Lawrence L.; Barrett, Stephanie D.; Calhoon, Stuart J.; Kvamme, Eric T.; Mason, James E.; Oseas, Jeffrey M.; Pryor, Mark; Schaechter, David B.; Stubbs, David M.

    2003-02-01

    The Space Interferometry Mission (SIM), planned for launch in 2009, will measure the positions of celestial objects to an unprecedented accuracy of 4.0 microarcseconds. In order to achieve this accuracy, which represents an improvement of almost two orders of magnitude over previous astrometric measurements, a ten-meter baseline interferometer will be flown in space. NASA challenges JPL and its industrial partners, Lockheed Martin and TRW, to develop an affordable mission. This challenge will be met using a combination of existing designs and new technology. Performance and affordability must be balanced with a cost-conscious Systems Engineering approach to design and implementation trades. This paper focuses on the Lockheed Martin-led Starlight (STL) and Metrology (MET) subsystems within the main instrument of SIM. Starlight is collected by 35cm diameter telescopes to form fringes on detectors. To achieve the stated accuracy, the position of these white-light fringes must be measured to 10-9 of a wavelength of visible light. The STL Subsystem consists of siderostats, telescopes, fast steering mirrors, roof mirrors, optical delay lines and beam combiners. The MET Subsystem is used to measure very precisely the locations of the siderostats with respect to one another as well as to measure the distance traveled by starlight from the siderostat mirrors and reference corner cubes through the system to a point very close to the detectors inside the beam combiners. The MET subsystem consists of beam launchers, double and triple corner cubes, and a laser distribution system.

  14. Radiation protection guidelines for space missions

    NASA Technical Reports Server (NTRS)

    Fry, R. J.; Nachtwey, D. S.

    1988-01-01

    The current radiation protection guidelines of the National Aeronautics and Space Administration (NASA) were recommended in 1970. The career limit was set at 4.0 Sv (400 rem). Using the same approach as in 1970 but current risk estimates, a considerably lower career limit would obtain today. Also, there is now much more information about the radiation environments that will be experienced in different missions. Furthermore, since 1970 women have joined the ranks of the astronauts. For these and other reasons, it was considered necessary to re-examine the radiation protection guidelines. This task has been undertaken by the National Council on Radiation Protection and Measurements Scientific Committee 75. Within the magnetosphere, the radiation environment varies with altitude and inclination of the orbit. In outer space missions, galactic cosmic rays, with the small but important heavy-ion component, determine the radiation environment. The new recommendations for career dose limits, based on lifetime excess risk of cancer mortality, take into account age at first exposure and sex. The career limits range from 1.0 Sv (100 rem) for a 24-y-old female up to 4.0 Sv (400 rem) for a 55-y-old male, compared with the previous single limit of 4.0 Sv (400 rem). The career limit for the lens of the eye has been reduced from 6.0 Sv (600 rem) to 4.0 Sv (400 rem).

  15. Operationally Responsive Space Launch for Space Situational Awareness Missions

    NASA Astrophysics Data System (ADS)

    Freeman, T.

    The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft and in the development of constellations of spacecraft. This position is founded upon continued government investment in research and development in space technology, which is clearly reflected in the Space Situational Awareness capabilities and the longevity of these missions. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by unresponsive and relatively expensive launchers in the Expandable, Expendable Launch Vehicles (EELV). The EELV systems require an average of six to eight months from positioning on the launch table until liftoff. Access to space requires maintaining a robust space transportation capability, founded on a rigorous industrial and technology base. To assure access to space, the United States directed Air Force Space Command to develop the capability for operationally responsive access to space and use of space to support national security, including the ability to provide critical space capabilities in the event of a failure of launch or on-orbit capabilities. Under the Air Force Policy Directive, the Air Force will establish, organize, employ, and sustain space forces necessary to execute the mission and functions assigned including rapid response to the National Command Authorities and the conduct of military operations across the spectrum of conflict. Air Force Space Command executes the majority of spacelift operations for DoD satellites and other government and commercial agencies. The

  16. LHS 6343 C: A TRANSITING FIELD BROWN DWARF DISCOVERED BY THE KEPLER MISSION

    SciTech Connect

    Johnson, John Asher; Crepp, Justin R.; Morton, Timothy D.; Apps, Kevin; Gazak, J. Zachary; Crossfield, Ian J.; Howard, Andrew W.; Marcy, Geoff W.; Chubak, Carly; Isaacson, Howard

    2011-04-01

    We report the discovery of a brown dwarf that transits one member of the M+M binary system LHS 6343 AB every 12.71 days. The transits were discovered using photometric data from the Kepler public data release. The LHS 6343 stellar system was previously identified as a single high proper motion M dwarf. We use adaptive optics imaging to resolve the system into two low-mass stars with masses 0.370 {+-} 0.009 M{sub sun} and 0.30 {+-} 0.01 M{sub sun}, respectively, and a projected separation of 0.''55. High-resolution spectroscopy shows that the more massive component undergoes Doppler variations consistent with Keplerian motion, with a period equal to the transit period and an amplitude consistent with a companion mass of M{sub C} = 62.7 {+-} 2.4 M{sub Jup}. Based on our analysis of the transit light curve, we estimate the radius of the companion to be R{sub C} = 0.833 {+-} 0.021 R{sub Jup}, which is consistent with theoretical predictions of the radius of a >1 Gyr brown dwarf.

  17. Automated Design of Multiphase Space Missions Using Hybrid Optimal Control

    ERIC Educational Resources Information Center

    Chilan, Christian Miguel

    2009-01-01

    A modern space mission is assembled from multiple phases or events such as impulsive maneuvers, coast arcs, thrust arcs and planetary flybys. Traditionally, a mission planner would resort to intuition and experience to develop a sequence of events for the multiphase mission and to find the space trajectory that minimizes propellant use by solving…

  18. Kepler Mission: a Discovery-Class Mission Designed to Determine the Frequency of Earth-Size and Larger Planets Around Solar-Like Stars

    NASA Technical Reports Server (NTRS)

    Borucki, William; Koch, David; Lissauer, Jack; Basri, Gibor; Caldwell, John; Cochran, William; Dunham, Edward W.; Gilliland, Ronald; Caldwell, Douglas; Kondo, Yoji; DeVincenzi, Donald (Technical Monitor)

    2002-01-01

    The first step in discovering the extent of life in our galaxy is to determine the number of terrestrial planets in the habitable zone (HZ). The Kepler Mission is designed around a 0.95 in aperture Schmidt-type telescope with an array of 42 CCDs designed to continuously monitor the brightness of 100,000 solar-like stars to detect the transits of Earth-size and larger planets. The photometer is scheduled to be launched into heliocentric orbit in 2007. Measurements of the depth and repetition time of transits provide the size of the planet relative to the star and its orbital period. When combined with ground-based spectroscopy of these stars to fix the stellar parameters, the true planet radius and orbit scale, hence the position relative to the HZ are determined. These spectra are also used to discover the relationships between the characteristics of planets and the stars they orbit. In particular, the association of planet size and occurrence frequency with stellar mass and metallicity will be investigated. At the end of the four year mission, hundreds of terrestrial planets should be discovered in and near the HZ of their stars if such planets are common. Extending the mission to six years doubles the expected number of Earth-size planets in the HZ. A null result would imply that terrestrial planets in the HZ occur in less than 1% of the stars and that life might be quite rare. Based on the results of the current Doppler-velocity discoveries, detection of a thousand giant planets is expected. Information on their albedos and densities of those giants showing transits will be obtained.

  19. The Kepler Mission: A Mission to Determine the Frequency of Inner Planets Near the Habitable Zone of a Wide Range of Stars

    NASA Technical Reports Server (NTRS)

    Borucki, W. J.; Koch, D. G.; Dunham, E. W.; Jenkins, J. M.

    1997-01-01

    The surprising discovery of giant planets in inner orbits around solar-like stars has brought into question our understanding of the development and evolution of planetary systems, including our solar system. To make further progress, it is critical to detect and obtain data on the frequency and characteristics of Earth-class planets. The Kepler Mission is designed to be a quick, low-cost approach to accomplish that objective. Transits by Earth-class planets produce a fractional change. in stellar brightness of 5 x 10(exp -5) to 40 x 10(exp -5) lasting for 4 to 16 hours. From the period and depth of the transits, the orbit and size of the planets can be calculated. The proposed instrument is a one-meter aperture photometer with a 12 deg. field-of-view (FOV). To obtain the required precision and to avoid interruptions caused by day-night and seasonal cycles, the photometer will be launched into a heliocentric orbit. It will continuously and simultaneously monitor the flux from 80,000 dwarf stars brighter than 14th magnitude in the Cygnus constellation. The mission tests the hypothesis that the formation of most stars produces Earth-class planets in inner orbits. Based on this assumption and the recent observations that 2% of the stars have giant planets in inner orbits, several types of results are expected from the mission: 1. From transits of Earth-class planets, about 480 planet detections and 60 cases where two or more planets are found in the same system. 2. From transits of giant planets, about 160 detections of inner-orbit planets and 24 detections of outer-orbit planets. 3. From the phase modulation of the reflected light from giant planets, about 1400 planet detections with periods less than a week, albedos for 160 of these giant planets, and densities for seven planets.

  20. The Kepler Mission: A Mission to Determine the Frequency of Inner Planets Neat the Habitable Zone of a Wide Range of Stars

    NASA Technical Reports Server (NTRS)

    Borucki, W. J.; Koch, D. G.; Dunham, E. W.; Jenkins, J. M.; Young, Richard E. (Technical Monitor)

    1997-01-01

    The surprising discovery of giant planets in inner orbits around solar-like stars has brought into question our understanding of the development and evolution of planetary systems, including our solar system. To make further progress, it is critical to detect and obtain data on the frequency and characteristics of Earth-class planets. The Kepler Mission is designed to be a quick, low-cost approach to accomplish that objective. Transits by Earth-class planets produce a fractional change in stellar brightness of 5 x 10(exp -5) to 40 x 10(exp -5) lasting for 4 to 16 hours, From the period and depth of the transits, the orbit and size of the planets can be calculated. The proposed instrument is a one-meter aperture photometer with a 12 deg field-of-view (FOV). To obtain the required precision and to avoid interruptions caused by day-night and seasonal cycles, the photometer will be launched into a heliocentric orbit. It will continuously and simultaneously monitor the flux from 80,000 dwarf stars brighter than 14th magnitude in the Cygnus constellation. The mission tests the hypothesis that the formation of most stars produces Earth-class planets in inner orbits. Based on this assumption and the recent observations that 2% of the stars have giant planets in inner orbits, several types of results are expected from the mission: 1. From transits of Earth-class planets, about 480 planet detections and 60 cases where two or more planets are found in the same system. 2. From transits of giant planets, about 160 detections of inner-orbit planets and 24 detections of outer-orbit planets. 3. From the phase modulation of the reflected light from giant planets, about 1400 planet detections with periods less than a week, albedos for 160 of these giant planets, and densities for seven planets.

  1. Mission planning for the Lidar in Space Technology Experiment

    NASA Technical Reports Server (NTRS)

    Redifer, Matthew E.

    1995-01-01

    Developing a mission planning system for a Space Shuttle mission is a complex procedure. Several months of preparation are required to develop a plan that optimizes science return during the short operations time frame. Further complicating the scenario is the necessity to schedule around crew activities and other payloads which share Orbiter resources. SpaceTec, Inc. developed the mission planning system for the Lidar In Space Technology Experiment, or LITE, which flew on Space Shuttle mission STS-64 in September of 1994. SpaceTec used a combination of off-th-shelf and in-house developed software to analyze various mission scenarios both premission and real-time during the flight. From this analysis, SpaceTec developed a comprehensive mission plan that met the mission objectives.

  2. STS-64 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1995-01-01

    The STS-64 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-fourth flight of the Space Shuttle Program and the nineteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-66; three SSMEs that were designated as serial numbers 2031, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-068. The RSRM's that were installed in each SRB were designated as 360L041 A for the left SRB, and 360L041 B for the right SRB. The primary objective of this flight was to successfully perform the planned operations of the Lidar In-Space Technology Experiment (LITE), and to deploy the Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN) -201 payload. The secondary objectives were to perform the planned activities of the Robot Operated Materials Processing System (ROMPS), the Shuttle Amateur Radio Experiment - 2 (SAREX-2), the Solid Surface Combustion Experiment (SSCE), the Biological Research in Canisters (BRIC) experiment, the Radiation Monitoring Equipment-3 (RME-3) payload, the Military Application of Ship Tracks (MAST) experiment, and the Air Force Maui Optical Site Calibration Test (AMOS) payload.

  3. Radiation shielding for future space exploration missions

    NASA Astrophysics Data System (ADS)

    DeWitt, Joel Michael

    Scope and Method of Study. The risk to space crew health and safety posed by exposure to space radiation is regarded as a significant obstacle to future human space exploration. To countermand this risk, engineers and designers in today's aerospace community will require detailed knowledge of a broad range of possible materials suitable for the construction of future spacecraft or planetary surface habitats that provide adequate protection from a harmful space radiation environment. This knowledge base can be supplied by developing an experimental method that provides quantitative information about a candidate material's space radiation shielding efficacy with the understanding that (1) shielding is currently the only practical countermeasure to mitigate the effects of space radiation on human interplanetary missions, (2) any mass of a spacecraft or planetary surface habitat necessarily alters the incident flux of ionizing radiation on it, and (3) the delivery of mass into LEO and beyond is expensive and therefore may benefit from the possible use of novel multifunctional materials that could in principle reduce cost as well as ionizing radiation exposure. The developed method has an experimental component using CR-39 PNTD and Al2O3:C OSLD that exposes candidate space radiation shielding materials of varying composition and depth to a representative sample of the GCR spectrum that includes 1 GeV 1H and 1 GeV/n 16O, 28Si, and 56Fe heavy ion beams at the BNL NSRL. The computer modeling component of the method used the Monte Carlo radiation transport code FLUKA to account for secondary neutrons that were not easily measured in the laboratory. Findings and Conclusions. This study developed a method that quantifies the efficacy of a candidate space radiation shielding material relative to the standard of polyethylene using a combination of experimental and computer modeling techniques. The study used established radiation dosimetry techniques to present an empirical

  4. Definition of technology development missions for early space stations. Large space structures, phase 2, midterm review

    NASA Technical Reports Server (NTRS)

    1984-01-01

    The large space structures technology development missions to be performed on an early manned space station was studied and defined and the resources needed and the design implications to an early space station to carry out these large space structures technology development missions were determined. Emphasis is being placed on more detail in mission designs and space station resource requirements.

  5. Space-time dynamics estimation from space mission tracking data

    NASA Astrophysics Data System (ADS)

    Dirkx, D.; Noomen, R.; Visser, P. N. A. M.; Gurvits, L. I.; Vermeersen, L. L. A.

    2016-03-01

    Aims: Many physical parameters that can be estimated from space mission tracking data influence both the translational dynamics and proper time rates of observers. These different proper time rates cause a variability of the time transfer observable beyond that caused by their translational (and rotational) dynamics. With the near-future implementation of transponder laser ranging, these effects will become increasingly important, and will require a re-evaluation of the common data analysis practice of using a priori time ephemerides, which is the goal of this paper. Methods: We develop a framework for the simultaneous estimation of the initial translational state and the initial proper time of an observer, with the goal of facilitating robust tracking data analysis from next-generation space missions carrying highly accurate clocks and tracking equipment. Using our approach, the influence of physical parameters on both translational and time dynamics are considered at the same level in the analysis, and mutual correlations between the signatures of the two are automatically identified. We perform a covariance analysis using our proposed method with simulated laser data from Earth-based stations to both a Mars and Mercury lander. Results: Using four years of tracking data for the Mars lander simulations, we find a difference between our results using the simultaneous space-time dynamics estimation and the classical analysis technique (with an a priori time ephemeris) of around 0.1% in formal errors and correlation coefficients. For a Mercury lander this rises to around 1% for a one-month mission and 10% for a four-year mission. By means of Monte Carlo simulations, we find that using an a priori time ephemeris of representative accuracy will result in estimation errors that are orders of magnitude above the formal error when processing highly accurate laser time transfer data.

  6. KEPLER SCIENCE OPERATIONS

    SciTech Connect

    Haas, Michael R.; Bryson, Steve T.; Dotson, Jessie L.; Koch, David G.; Smith, Marcie; Sobeck, Charles K.; Batalha, Natalie M.; Stober, Jeremy

    2010-04-20

    Kepler's mission design includes a comprehensive plan for commissioning and science operations. The commissioning phase completed all critical tasks and accomplished all mission objectives within a week of the pre-launch plan. Since the start of science data collection, the nominal timeline has been interrupted by two safe-mode events, several losses of fine point, and some small pointing adjustments. The most important anomalies are understood and mitigated, so Kepler's technical performance has improved significantly over this period, and the prognosis for mission success is excellent. The Kepler data archive is established and hosting data for the science team, guest observers, and the public. The first data to become publicly available include the monthly full-frame images and the light curves for targets that are dropped from the exoplanet program or released after publication. Data are placed in the archive on a quarterly basis; the Kepler Results Catalog will be released annually starting in 2011.

  7. Kepler Discovers Its First Rocky Planet

    NASA Video Gallery

    NASA's Kepler mission confirmed the discovery of its first rocky planet, named Kepler-10b. Measuring 1.4 times the size of Earth, it is the smallest planet ever discovered outside our solar system....

  8. STS-53 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1993-01-01

    The STS-53 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle Main Engine (SSME) subsystems performance during the fifty-second flight of the Space Shuttle Program, and the fifteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET, which was designated as ET-49/LWT-42; three SSME's, which were serial numbers 2024, 2012, and 2017 in positions 1, 2, and 3, respectively; and two SRB's, which were designated BI-055. The lightweight RSRM's that were installed in each SRB were designated 360L028A for the left SRB, and 360L028B for the right SRB. The primary objective of this flight was to successfully deploy the Department of Defense 1 (DOD-1) payload. The secondary objectives of this flight were to perform the operations required by the Glow Experiment/Cryogenic Heat Pipe Experiment Payload (GCP); the Hand-Held, Earth-Oriented, Real-Time, Cooperative, User-Friendly, Location-Targeting and Environmental System (HERCULES); the Space Tissue Loss (STL); the Battlefield Laser Acquisition Sensor Test (BLAST); the Radiation Monitoring Equipment-III (RME-III); the Microcapsules in Space-1 (MIS-1); the Visual Function Tester-2 (VFT-2); the Cosmic Radiation Effects and Activation Monitor (CREAM); the Clouds Logic to Optimize Use of Defense Systems-1A (CLOUDS-1A); the Fluids Acquisition and Resupply Experiment (FARE); and the Orbital Debris Radar Calibration Spheres (ODERACS). In addition to presenting a summary of subsystem performance, this report also discusses each Orbiter, ET, SSME, SRB, and RSRM in-flight anomaly in the applicable section of the report. Listed in the discussion of each anomaly is the officially assigned tracking number as published by each Project Office in their respective Problem Tracking List. All times given in this report are in Greenwich mean time (G.m.t.) as

  9. Atmospheric constraint statistics for the Space Shuttle mission planning

    NASA Technical Reports Server (NTRS)

    Smith, O. E.; Batts, G. W.; Willett, J. A.

    1982-01-01

    The procedures used to establish statistics of atmospheric constraints of interest to the Space Shuttle mission planning are presented. The statistics considered are for the frequency of occurrence, runs, and time conditional probabilities of several atmospheric constrants for each of the Space Shuttle mission phases. The mission phases considered are (1) prelaunch, (2) launch, (3) return to launch site, (4) abort once around landing, and (5) end of mission landing.

  10. Space Shuttle Mission STS-61: Hubble Space Telescope servicing mission-01

    NASA Technical Reports Server (NTRS)

    1993-01-01

    This press kit for the December 1993 flight of Endeavour on Space Shuttle Mission STS-61 includes a general release, cargo bay payloads and activities, in-cabin payloads, and STS-61 crew biographies. This flight will see the first in a series of planned visits to the orbiting Hubble Space Telescope (HST). The first HST servicing mission has three primary objectives: restoring the planned scientific capabilities, restoring reliability of HST systems and validating the HST on-orbit servicing concept. These objectives will be accomplished in a variety of tasks performed by the astronauts in Endeavour's cargo bay. The primary servicing task list is topped by the replacement of the spacecraft's solar arrays. The spherical aberration of the primary mirror will be compensated by the installation of the Wide Field/Planetary Camera-II and the Corrective Optics Space Telescope Axial Replacement. New gyroscopes will also be installed along with fuse plugs and electronic units.

  11. Nuclear Electric Propulsion for Outer Space Missions

    NASA Technical Reports Server (NTRS)

    Barret, Chris

    2003-01-01

    Today we know of 66 moons in our very own Solar System, and many of these have atmospheres and oceans. In addition, the Hubble (optical) Space Telescope has helped us to discover a total of 100 extra-solar planets, i.e., planets going around other suns, including several solar systems. The Chandra (X-ray) Space Telescope has helped us to discover 33 Black Holes. There are some extremely fascinating things out there in our Universe to explore. In order to travel greater distances into our Universe, and to reach planetary bodies in our Solar System in much less time, new and innovative space propulsion systems must be developed. To this end NASA has created the Prometheus Program. When one considers space missions to the outer edges of our Solar System and far beyond, our Sun cannot be relied on to produce the required spacecraft (s/c) power. Solar energy diminishes as the square of the distance from the Sun. At Mars it is only 43% of that at Earth. At Jupiter, it falls off to only 3.6% of Earth's. By the time we get out to Pluto, solar energy is only .066% what it is on Earth. Therefore, beyond the orbit of Mars, it is not practical to depend on solar power for a s/c. However, the farther out we go the more power we need to heat the s/c and to transmit data back to Earth over the long distances. On Earth, knowledge is power. In the outer Solar System, power is knowledge. It is important that the public be made aware of the tremendous space benefits offered by Nuclear Electric Propulsion (NEP) and the minimal risk it poses to our environment. This paper presents an overview of the reasons for NEP systems, along with their basic components including the reactor, power conversion units (both static and dynamic), electric thrusters, and the launch safety of the NEP system.

  12. STS-37 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1991-01-01

    The STS-37 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem activities during this thirty-ninth flight of the Space Shuttle and the eighth flight of the Orbiter Vehicle Atlantis (OV-104). In addition to the Atlantis vehicle, the flight vehicle consisted of the following: an External Tank (ET) (designated as ET-37/LWT-30); three Space Shuttle main engines (SSME's) (serial numbers 2019, 2031, and 2107 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-042. The primary objective of this flight was to successfully deploy the Gamma Ray Observatory (GRO) payload. The secondary objectives were to successfully perform all operations necessary to support the requirements of the Protein Crystal Growth (PCG) Block 2 version, Radiation Monitoring Experiment-3 (RME-3), Ascent Particle Monitor (APM), Shuttle Amateur Radio Experiment-2 (SAREX-2), Air Force Maui Optical Site Calibration Test (AMOS), Bioserve Instrumentation Technology Associates Materials Dispersion Apparatus (BIMDA), and the Crew and Equipment Transfer Aids (CETA) payloads.

  13. STS-50 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W.

    1992-01-01

    The STS-50 Space Shuttle Program Mission Report contains a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the forty-eighth flight of the Space Shuttle Program, and the twelfth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of the following: an ET which was designated ET-50 (LUT-43); three SSME's which were serial numbers 2019, 2031, and 2011 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-051. The lightweight/redesigned RSRM's installed in each SRB were designated 360L024A for the left RSRM and 360M024B for the right RSRM. The primary objective of the STS-50 flight was to successfully perform the planned operations of the United States Microgravity Laboratory (USML-1) payload. The secondary objectives of this flight were to perform the operations required by the Investigations into Polymer Membrane Processing (IPMP), and the Shuttle Amateur Radio Experiment 2 (SAREX-2) payloads. An additional secondary objective was to meet the requirements of the Ultraviolet Plume Instrument (UVPI), which was flown as a payload of opportunity.

  14. STS-65 Space Shuttle mission report

    NASA Astrophysics Data System (ADS)

    Fricke, Robert W., Jr.

    1994-09-01

    The STS-65 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-third flight of the Space Shuttle Program and the seventeenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbits the flight vehicle consisted of an ET that was designated ET-64; three SSME's that were designated as serial numbers 2019, 2030, and 2017 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-066. The RSRM's that were installed in each SRB were designated as 360P039A for the left SRB, and 360W039 for the right SRB. The primary objective of this flight was to complete the operation of the second International Microgravity Laboratory (IML-2). The secondary objectives of this flight were to complete the operations of the Commercial Protein Crystal Growth (CPCG), Orbital Acceleration Research Experiment (OARE), and the Shuttle Amateur Radio Experiment (SAREX) II payloads. Additional secondary objectives were to meet the requirements of the Air Force Maui Optical Site (AMOS) and the Military Application Ship Tracks (MAST) payloads, which were manifested as payloads of opportunity.

  15. STS-73 Space Shuttle Mission Report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1995-01-01

    The STS-73 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the seventy-second flight of the Space Shuttle Program, the forty-seventh flight since the return-to-flight, and the eighteenth flight of the Orbiter Columbia (OV-102). STS-73 was also the first flight of OV-102 following the vehicle's return from the Orbiter Maintenance Down Period (OMDP). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-73; three SSME's that were designated as serial numbers 2037 (Block 1), 2031 (PH-1), and 2038 (Block 1) in positions 1, 2, and 3, respectively; and two SRB's that were designated BI-075. The RSRM's, designated RSRM-50, were installed in each SRB and the individual RSRM's were designated as 36OL050A for the left SRB, and 36OW050B for the right SRB. The primary objective of this flight was to successfully perform the planned operations of the United States Microgravity Laboratory (USML)-2 payload.

  16. STS-65 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1994-01-01

    The STS-65 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-third flight of the Space Shuttle Program and the seventeenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbits the flight vehicle consisted of an ET that was designated ET-64; three SSME's that were designated as serial numbers 2019, 2030, and 2017 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-066. The RSRM's that were installed in each SRB were designated as 360P039A for the left SRB, and 360W039 for the right SRB. The primary objective of this flight was to complete the operation of the second International Microgravity Laboratory (IML-2). The secondary objectives of this flight were to complete the operations of the Commercial Protein Crystal Growth (CPCG), Orbital Acceleration Research Experiment (OARE), and the Shuttle Amateur Radio Experiment (SAREX) II payloads. Additional secondary objectives were to meet the requirements of the Air Force Maui Optical Site (AMOS) and the Military Application Ship Tracks (MAST) payloads, which were manifested as payloads of opportunity.

  17. STS-52 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1992-01-01

    The STS-52 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the fifty-first flight of the Space Shuttle Program, and the thirteenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbiter, the flight vehicle consisted of the following: an ET (designated as ET-55/LWT-48); three SSME's, which were serial numbers 2030, 2015, and 2034 in positions 1, 2, and 3, respectively; and two SRB's, which were designated BI-054. The lightweight RSRM's that were installed in each SRB were designated 360L027A for the left SRB and 360Q027B for the right SRB. The primary objectives of this flight were to successfully deploy the Laser Geodynamic Satellite (LAGEOS-2) and to perform operations of the United States Microgravity Payload-1 (USMP-1). The secondary objectives of this flight were to perform the operations of the Attitude Sensor Package (ASP), the Canadian Experiments-2 (CANEX-2), the Crystals by Vapor Transport Experiment (CVTE), the Heat Pipe Performance Experiment (HPP), the Commercial Materials Dispersion Apparatus Instrumentation Technology Associates Experiments (CMIX), the Physiological System Experiment (PSE), the Commercial Protein Crystal Growth (CPCG-Block 2), the Shuttle Plume Impingement Experiment (SPIE), and the Tank Pressure Control Experiment (TPCE) payloads.

  18. Radiation protection guidelines for space missions

    NASA Technical Reports Server (NTRS)

    Fry, R. J. M.; Nachtwey, D. S.

    1986-01-01

    NASA's current radiation protection guidelines date from 1970, when the career limit was set at 400 rem. Today, using the same approach, but with the current risk estimates, a considerably lower career limit would obtain. Also, there is considerably more information about the radiation environments to be experienced in different missions than previously. Since 1970 women have joined the ranks. For these and other reasons it was necessary to reexamine the radiation protection guidelines. This task was undertaken by the National Council on Radiation Protection and Measurements Scientific Committee 75 (NCRP SC 75). Below the magnetosphere the radiation environment varies with altitude and orbit inclination. In outer space missions galactic cosmic rays, with the small but important heavy ion component, determine the radiation environment. The new recommendations for career dose limits, based on lifetime excess risk of cancer mortality, take into account age at first exposure and sex. The career limits range from 100 rem (4.0Sv) for a 24 year old female to 400 rem for a 55 year old male compared to the previous single limit of 400 rem (4.0 Sv). The career limit for the lens of the eye was reduced from 600 to 400 rem (6.0 to 4.0 Sv.)

  19. Polarization Effects Aboard the Space Interferometry Mission

    NASA Technical Reports Server (NTRS)

    Levin, Jason; Young, Martin; Dubovitsky, Serge; Dorsky, Leonard

    2006-01-01

    For precision displacement measurements, laser metrology is currently one of the most accurate measurements. Often, the measurement is located some distance away from the laser source, and as a result, stringent requirements are placed on the laser delivery system with respect to the state of polarization. Such is the case with the fiber distribution assembly (FDA) that is slated to fly aboard the Space Interferometry Mission (SIM) next decade. This system utilizes a concatenated array of couplers, polarizers and lengthy runs of polarization-maintaining (PM) fiber to distribute linearly-polarized light from a single laser to fourteen different optical metrology measurement points throughout the spacecraft. Optical power fluctuations at the point of measurement can be traced back to the polarization extinction ration (PER) of the concatenated components, in conjunction with the rate of change in phase difference of the light along the slow and fast axes of the PM fiber.

  20. Using Spitzer to Estimate the Kepler False Positive Rate and to Validate Kepler Candidates.

    NASA Astrophysics Data System (ADS)

    Desert, Jean-Michel; Charbonneau, D.; Fressin, F.; Torres, G.

    2012-01-01

    I present the results from an ongoing large campaign with the Spitzer Space Telescope to gather near-infrared photometric measurements of Kepler Objects of Interest (KOI). Our goals are (1) to validate the planetary status of these Kepler candidates, (2) to estimate observationally the false positive rate, and (3) to study the atmospheres of confirmed planets through measurements of their secondary eclipses. Our target list spans of wide range of candidate sizes and periods orbiting various spectral type stars. The Spitzer observations provide constraints on the possibility of astrophysical false positives resulting from stellar blends, including eclipsing binaries and hierarchical triples. The number of possible blends per star is estimated using stellar population synthesis models and observational probes of the KOI close environments from direct imaging (e.g. Adaptive Optics, Speckle images, Kepler centroids). Combining all the above information with the shape of the transit lightcurves from the Kepler photometry, we compute odd ratios for the 34 candidates we observed in order to determine their false positive probability. Our results suggest that the Kepler false positive rate in this subset of candidates is low. I finally present a new list of Kepler candidates that we were able to validate using this method. This work is based on observations made with the Spitzer, which is operated by JPL/Caltech, under a contract with NASA. Support was provided by NASA through an award issued by JPL/Caltech. Kepler was selected as the 10th mission of the Discovery Program. Funding for this mission is provided by NASA, Science Mission Directorate.

  1. A university-based distributed satellite mission control network for operating professional space missions

    NASA Astrophysics Data System (ADS)

    Kitts, Christopher; Rasay, Mike

    2016-03-01

    For more than a decade, Santa Clara University's Robotic Systems Laboratory has operated a unique, distributed, internet-based command and control network for providing professional satellite mission control services for a variety of government and industry space missions. The system has been developed and is operated by students who become critical members of the mission teams throughout the development, test, and on-orbit phases of these missions. The mission control system also supports research in satellite control technology and hands-on student aerospace education. This system serves as a benchmark for its comprehensive nature, its student-centric nature, its ability to support NASA and industry space missions, and its longevity in providing a consistent level of professional services. This paper highlights the unique features of this program, reviews the network's design and the supported spacecraft missions, and describes the critical programmatic features of the program that support the control of professional space missions.

  2. Space Mission Utility and Requirements for a Heat Melt Compactor

    NASA Technical Reports Server (NTRS)

    Fisher, John W.; Lee, Jeffrey M.

    2016-01-01

    Management of waste on long-duration space missions is both a problem and an opportunity. Uncontained or unprocessed waste is a crew health hazard and a habitat storage problem. A Heat Melt Compactor (HMC) such as NASA has been developing is capable of processing space mission trash and converting it to useful products. The HMC is intended to process space mission trash to achieve a number of objectives including: volume reduction, biological safening and stabilization, water recovery, radiation shielding, and planetary protection. This paper explores the utility of the HMC to future space missions and how this translates into HMC system requirements.

  3. National Space Transportation Systems Program mission report

    NASA Technical Reports Server (NTRS)

    Collins, M. A., Jr.; Aldrich, A. D.; Lunney, G. S.

    1984-01-01

    The 515-41B National Space Transportation Systems Program Mission Report contains a summary of the major activities and accomplishments of the sixth operational Shuttle flight and fourth flight of the OV-099 vehicle, Challenger. Since this flight was the first to land at Kennedy Space Center, the vehicle was towed directly to the OPF (Orbiter Processing Facility) where preparations for flight STS-41C, scheduled for early April 1984, began immediately. The significant problems that occurred during STS-41B are summarized and a problem tracking list that is a complete list of all problems that occurred during the flight is given. None of the problems will affect the STS 41C flight. The major objectives of flight STS-41B were to successfully deploy the Westar satellite and the Indonesian Communications Satellite-B2 (PALAPA-B2); to evaluate the MMU (Manned Maneuvering Unit) support for EVA (Extravehicular Activities); to exercise the MFR (Manipulator Foot Restraint); to demonstrate a closed loop rendezvous; and to operate the M.R (Monodisperse Latex Reactor), the ACES (Acoustic Containerless Experiment System) and the IEF (Isoelectric Focusing) in cabin experiments; and to obtain photographs with the Cinema 360 Cameras.

  4. STS-67 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1995-01-01

    The STS-67 Space Shuttle Program Mission Report provides the results of the orbiter vehicle performance evaluation during this sixty-eighth flight of the Shuttle Program, the forty-third flight since the return to flight, and the eighth flight of the Orbiter vehicle Endeavour (OV-105). In addition, the report summarizes the payload activities and the performance of the External Tank (ET), Solid Rocket Booster (SRB), Reusable Solid Rocket Motor (RSRM), and the Space Shuttle Main Engines (SSME). The serial numbers of the other elements of the flight vehicle were ET-69 for the ET; 2012, 2033, and 2031 for SSME's 1, 2, and 3, respectively; and Bl-071 for the SRB's. The left-hand RSRM was designated 360W043A, and the right-hand RSRM was designated 360L043B. The primary objective of this flight was to successfully perform the operations of the ultraviolet astronomy (ASTRO-2) payload. Secondary objectives of this flight were to complete the operations of the Protein Crystal Growth - Thermal Enclosure System (PCG-TES), the Protein Crystal Growth - Single Locker Thermal Enclosure System (PCG-STES), the Commercial Materials Dispersion Apparatus ITA Experiments (CMIX), the Shuttle Amateur Radio Experiment-2 (SAREX-2), the Middeck Active Control Experiment (MACE), and two Get-Away Special (GAS) payloads.

  5. STS-66 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1995-01-01

    The primary objective of this flight was to accomplish complementary science objectives by operating the Atmospheric Laboratory for Applications and Science-3 (ATLAS-3) and the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite (CRISTA-SPAS). The secondary objectives of this flight were to perform the operations of the Shuttle Solar Backscatter Ultraviolet/A (SSBUV/A) payload, the Experiment of the Sun Complementing the Atlas Payload and Education-II (ESCAPE-II) payload, the Physiological and Anatomical Rodent Experiment/National Institutes of Health Rodents (PARE/NIH-R) payload, the Protein Crystal Growth-Thermal Enclosure System (PCG-TES) payload, the Protein Crystal Growth-Single Locker Thermal Enclosure System (PCG-STES), the Space Tissue/National Institutes of Health Cells STL/N -A payload, the Space Acceleration Measurement Systems (SAMS) Experiment, and Heat Pipe Performance Experiment (HPPE) payload. The 11-day plus 2 contingency day STS-66 mission was flown as planned, with no contingency days used for weather avoidance or Orbiter contingency operations. Appendix A lists the sources of data from which this report was prepared, and Appendix B defines all acronyms and abbreviations used in the report.

  6. Infrared Space Astrometry Missions ˜ JASMINE Missions ˜

    NASA Astrophysics Data System (ADS)

    Gouda, N.

    2012-08-01

    "JASMINE" is an abbreviation of Japan Astrometry Satellite Mission for Infrared Exploration. Three satellites are planned as a series of JASMINE missions, as a step-by-step approach, to overcome technical issues and promote scientific results. These are Nano-JASMINE, Small-JASMINE and (medium-sized) JASMINE. JASMINE missions provide the positions and proper motions of celestial objects. Nano-JASMINE uses a very small nano-satellite and is scheduled to be launched in 2013. Nano-JASMINE will operate in zw-band (˜ 0.8μm) to perform an all sky survey with an accuracy of 3 milli-arcseconds for position and parallaxes. Small-JASMINE will observe towards a region around the Galactic center and other small regions, which include interesting scientific targets, with accuracies of 10 to 50 μ-arcseconds in an infrared Hw-band (˜ 1.7 μm). The target launch date is around 2017. (Medium-sized) JASMINE is an extended mission of Small-JASMINE, which will observe towards almost the whole region of the Galactic bulge with accuracies of ˜ 10 μ arcseconds in Kw-band (˜ 2.0μ m). The target launch date is the first half of the 2020s.

  7. Second Epoch Hubble Space Telescope Observations of Kepler's Supernova Remnant: The Proper Motions of Balmer Filaments

    NASA Astrophysics Data System (ADS)

    Sankrit, Ravi; Raymond, John C.; Blair, William P.; Long, Knox S.; Williams, Brian J.; Borkowski, Kazimierz J.; Patnaude, Daniel J.; Reynolds, Stephen P.

    2016-01-01

    We report on the proper motions of Balmer-dominated filaments in Kepler’s supernova remnant using high resolution images obtained with the Hubble Space Telescope at two epochs separated by about 10 years. We use the improved proper motion measurements and revised values of shock velocities to derive a distance to Kepler of {5.1}-0.7+0.8 kpc. The main shock around the northern rim of the remnant has a typical speed of 1690 km s-1 and is encountering material with densities of about 8 cm-3. We find evidence for the variation of shock properties over small spatial scales, including differences in the driving pressures as the shock wraps around a curved cloud surface. We find that the Balmer filaments ahead of the ejecta knot on the northwest boundary of the remnant are becoming fainter and more diffuse. We also find that the Balmer filaments associated with circumstellar material in the interior regions of the remnant are due to shocks with significantly lower velocities and that the brightness variations among these filaments trace the density distribution of the material, which may have a disk-like geometry. Based on observations made with the Hubble Space Telescope.

  8. Deep space 1 mission and observation of comet Borrellly

    USGS Publications Warehouse

    Lee, M.; Weidner, R.J.; Soderblom, L.A.

    2002-01-01

    The NASA's new millennium program (NMP) focuses on testing high-risk, advanced technologies in space with low-cost flights. The objective of the NMP technology validation missions is to enable future science missions. The NMP missions are technology-driven, with the principal requirements coming from the needs of the advanced technologies that form the 'payload'.

  9. Heuristics Applied in the Development of Advanced Space Mission Concepts

    NASA Technical Reports Server (NTRS)

    Nilsen, Erik N.

    1998-01-01

    Advanced mission studies are the first step in determining the feasibility of a given space exploration concept. A space scientist develops a science goal in the exploration of space. This may be a new observation method, a new instrument or a mission concept to explore a solar system body. In order to determine the feasibility of a deep space mission, a concept study is convened to determine the technology needs and estimated cost of performing that mission. Heuristics are one method of defining viable mission and systems architectures that can be assessed for technology readiness and cost. Developing a viable architecture depends to a large extent upon extending the existing body of knowledge, and applying it in new and novel ways. These heuristics have evolved over time to include methods for estimating technical complexity, technology development, cost modeling and mission risk in the unique context of deep space missions. This paper examines the processes involved in performing these advanced concepts studies, and analyzes the application of heuristics in the development of an advanced in-situ planetary mission. The Venus Surface Sample Return mission study provides a context for the examination of the heuristics applied in the development of the mission and systems architecture. This study is illustrative of the effort involved in the initial assessment of an advance mission concept, and the knowledge and tools that are applied.

  10. A Multi-resolution, Multi-epoch Low Radio Frequency Survey of the Kepler K2 Mission Campaign 1 Field

    NASA Astrophysics Data System (ADS)

    Tingay, S. J.; Hancock, P. J.; Wayth, R. B.; Intema, H.; Jagannathan, P.; Mooley, K.

    2016-10-01

    We present the first dedicated radio continuum survey of a Kepler K2 mission field, Field 1, covering the North Galactic Cap. The survey is wide field, contemporaneous, multi-epoch, and multi-resolution in nature and was conducted at low radio frequencies between 140 and 200 MHz. The multi-epoch and ultra wide field (but relatively low resolution) part of the survey was provided by 15 nights of observation using the Murchison Widefield Array (MWA) over a period of approximately a month, contemporaneous with K2 observations of the field. The multi-resolution aspect of the survey was provided by the low resolution (4‧) MWA imaging, complemented by non-contemporaneous but much higher resolution (20″) observations using the Giant Metrewave Radio Telescope (GMRT). The survey is, therefore, sensitive to the details of radio structures across a wide range of angular scales. Consistent with other recent low radio frequency surveys, no significant radio transients or variables were detected in the survey. The resulting source catalogs consist of 1085 and 1468 detections in the two MWA observation bands (centered at 154 and 185 MHz, respectively) and 7445 detections in the GMRT observation band (centered at 148 MHz), over 314 square degrees. The survey is presented as a significant resource for multi-wavelength investigations of the more than 21,000 target objects in the K2 field. We briefly examine our survey data against K2 target lists for dwarf star types (stellar types M and L) that have been known to produce radio flares.

  11. Space transfer concepts and analysis for exploration missions

    NASA Technical Reports Server (NTRS)

    1991-01-01

    A broad scoped and systematic study was made of space transfer concepts for human Lunar and Mars missions. Relevant space transportation studies were initiated to lead to further detailed activities in the following study period.

  12. STS-1: the first space shuttle mission, April 12, 1981

    NASA Video Gallery

    Space shuttle Columbia launched on the first space shuttle mission on April 12, 1981, a two-day demonstration of the first reusable, piloted spacecraft's ability to go into orbit and return safely ...

  13. An Evolvable Space Telescope for NASA’s Next UVOIR Flagship Mission

    NASA Astrophysics Data System (ADS)

    Lillie, Charles F.; Breckinridge, James B.; MacEwen, Howard A.; Polidan, Ronald S.; Flannery, Martin; Dailey, Dean

    2015-01-01

    NASA has sponsored several studies to develop conceptual designs for the next UVOIR Flagship mission, including an Advanced Technology Large Space Telescope (ATLAST). These studies concluded that a space observatory launched in ~2030 will require a telescope aperture of 8 to 16 meters to address the most compelling astrophysical questions raised by missions such as HST, Kepler, TESS, JWST and WFIRST as well as the large ground based telescopes that will coming on-line in the next decade. This telescope will be designed to search for the bio-signatures of life in the universe as well as to study the physics of star formation and to unravel the complex interactions between dark matter, galaxies and the intergalactic medium.Unfortunately, telescopes with this aperture will have a long development time with peak funding requirements that will absorb most NASA's Astrophysics budget for many years. To minimize this impact on NASA's budget and to drastically shorten the time between program start and 'first light' for this UVOIR space observatory we have been developing conceptual designs for an Evolvable Space Telescope (EST) that would be assembled on-orbit in three stages, beginning with the launch of a 2 mirror 4 x 12 meter telescope with 2 instruments 5 to 7 years after program start, and then adding mirror segments and instruments ay ~ 5 year intervals to obtain a 12-m filled aperture, and then a 20-m filled aperture telescope. We describe our approach in this presentation.

  14. Quasar Astrophysics with the Space Interferometry Mission

    NASA Technical Reports Server (NTRS)

    Unwin, Stephen; Wehrle, Ann; Meier, David; Jones, Dayton; Piner, Glenn

    2007-01-01

    Optical astrometry of quasars and active galaxies can provide key information on the spatial distribution and variability of emission in compact nuclei. The Space Interferometry Mission (SIM PlanetQuest) will have the sensitivity to measure a significant number of quasar positions at the microarcsecond level. SIM will be very sensitive to astrometric shifts for objects as faint as V = 19. A variety of AGN phenomena are expected to be visible to SIM on these scales, including time and spectral dependence in position offsets between accretion disk and jet emission. These represent unique data on the spatial distribution and time dependence of quasar emission. It will also probe the use of quasar nuclei as fundamental astrometric references. Comparisons between the time-dependent optical photocenter position and VLBI radio images will provide further insight into the jet emission mechanism. Observations will be tailored to each specific target and science question. SIM will be able to distinguish spatially between jet and accretion disk emission; and it can observe the cores of galaxies potentially harboring binary supermassive black holes resulting from mergers.

  15. The Space Time Asymmetry Research Mission

    NASA Astrophysics Data System (ADS)

    Scargle, Jeffrey; Goebel, John; Buchman, Sasha; Byer, Robert; Sun, Ke-Xun; Lipa, John; Chu-Thielbar, Lisa; Hall, John

    We will use precision molecular iodine stabilized Nd:YAG laser interferometers to search for small deviations from Lorentz Invariance, a cornerstone of relativity and particle physics, and thus our understanding of the Universe. A Lorentz violation would have profound implications for cosmology and particle physics. An improved null result will constrain theories attempting to unite particle physics and gravity. Science Objectives: Measure the absolute anisotropy of the velocity of light to 10-18 (100-fold improvement) Derive the Michelson-Morley coefficient to 10-12 (100-fold improvement) Derive the Kennedy-Thorndyke coefficient to 7x10-10 (400-fold improvement) Derive the coefficients of Lorentz violation in the Standard Model Extension, in the range 7x10-18 to 10-14 (50 to 500-fold improvement) Thermal control, stabilization and uniformitization are great concerns, so new technology has been devised that keeps these parameters within strict specified limits. Thereby STAR is able to operate effectively in all possible orbits. The spacecraft is based on a bus development by NASA Ames Research Center. STAR is designed to fly as a secondary payload on a Delta IV launch vehicle with an ESPA ring into an 850 km circular orbit. It will have a one-year mission and is capable of even longer duration. Other orbit options are possible depending on the launch opportunities available. The STAR project is a partnership between Stanford University, NASA Ames Research Center and NASA Goddard Space Flight Center.

  16. Deep Space Mission Applications for NEXT: NASA's Evolutionary Xenon Thruster

    NASA Technical Reports Server (NTRS)

    Oh, David; Benson, Scott; Witzberger, Kevin; Cupples, Michael

    2004-01-01

    NASA's Evolutionary Xenon Thruster (NEXT) is designed to address a need for advanced ion propulsion systems on certain future NASA deep space missions. This paper surveys seven potential missions that have been identified as being able to take advantage of the unique capabilities of NEXT. Two conceptual missions to Titan and Neptune are analyzed, and it is shown that ion thrusters could decrease launch mass and shorten trip time, to Titan compared to chemical propulsion. A potential Mars Sample return mission is described, and compassion made between a chemical mission and a NEXT based mission. Four possible near term applications to New Frontiers and Discovery class missions are described, and comparisons are made to chemical systems or existing NSTAR ion propulsion system performance. The results show that NEXT has potential performance and cost benefits for missions in the Discovery, New Frontiers, and larger mission classes.

  17. Space transfer concepts and analysis for exploration missions

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Covered here is the second phase of a broad scoped and systematic study of space transfer concepts for human lunar and Mars missions. The study addressed issues that were raised during Phase 1, developed generic Mars missions profile analysis data, and conducted preliminary analysis of the Mars in-space transportation requirements and implementation from the Stafford Committee Synthesis Report.

  18. An integrated medical system for long-duration space missions.

    NASA Technical Reports Server (NTRS)

    Pool, S. L.; Belasco, N.

    1972-01-01

    A description is given of the Integrated Medical and Behavioral Laboratory Measurement System (IMBLMS) being developed for onboard medical support of the crew and for medical research during space missions. The system is suitable for use during early extended space flights and for accommodating measurement and diagnostic apparatus as well as treatment and surgical facilities developed for later missions.

  19. Spacebuoy: A University Nanosat Space Weather Mission (III)

    DTIC Science & Technology

    2013-10-11

    SPACEBUOY A UNIVERSITY NANOSAT SPACE WEATHER MISSION (III) DAVID KLUMPAR MONTANA STATE UNIVERSITY 10/11/2013 Final Report DISTRIBUTION A...2011 - 4/14/2013 SPACEBUOY A UNIVERSITY NANOSAT SPACE WEATHER MISSION (III) FA9550-11-1-0045 David Klumpar Montana State University 307 Montana ...David Klumpar 406-994-6169 Montana State University University Nanosat-7 FCR Presentation January 10, 2013 Albuquerque, NM 1 2 Mission

  20. Mars rover/sample return mission requirements affecting space station

    NASA Technical Reports Server (NTRS)

    1988-01-01

    The possible interfaces between the Space Station and the Mars Rover/Sample Return (MRSR) mission are defined. In order to constrain the scope of the report a series of seven design reference missions divided into three major types were assumed. These missions were defined to span the probable range of Space Station-MRSR interactions. The options were reduced, the MRSR sample handling requirements and baseline assumptions about the MRSR hardware and the key design features and requirements of the Space Station are summarized. Only the aspects of the design reference missions necessary to define the interfaces, hooks and scars, and other provisions on the Space Station are considered. An analysis of each of the three major design reference missions, is reported, presenting conceptual designs of key hardware to be mounted on the Space Station, a definition of weights, interfaces, and required hooks and scars.

  1. Achieving Supportability on Exploration Missions with In-Space Servicing

    NASA Technical Reports Server (NTRS)

    Bacon, Charles; Pellegrino, Joseph F.; McGuire, Jill; Henry, Ross; DeWeese, Keith; Reed, Benjamin; Aranyos, Thomas

    2015-01-01

    One of the long-term exploration goals of NASA is manned missions to Mars and other deep space robotic exploration. These missions would include sending astronauts along with scientific equipment to the surface of Mars for extended stay and returning the crew, science data and surface sample to Earth. In order to achieve this goal, multiple precursor missions are required that would launch the crew, crew habitats, return vehicles and destination systems into space. Some of these payloads would then rendezvous in space for the trip to Mars, while others would be sent directly to the Martian surface. To support such an ambitious mission architecture, NASA must reduce cost, simplify logistics, reuse and/or repurpose flight hardware, and minimize resources needed for refurbishment. In-space servicing is a means to achieving these goals. By designing a mission architecture that utilizes the concept of in-space servicing (robotic and manned), maximum supportability can be achieved.

  2. Achieving Supportability on Exploration Missions with In-Space Servicing

    NASA Technical Reports Server (NTRS)

    Bacon, Charles; McGuire, Jill; Pellegrino, Joseph; Strube, Matthew; Aranyos, Thomas; Reed, Benjamin

    2015-01-01

    One of the long-term exploration goals of NASA is manned missions to Mars and other deep space robotic exploration. These missions would include sending astronauts along with scientific equipment to the surface of Mars for extended stay and returning the crew, science data and surface samples, and equipment to Earth. In order to achieve this goal, multiple precursor missions are required that would launch the crew, crew habitats, return vehicles and destination systems into space. Some of these payloads would then rendezvous in space for the trip to Mars, while others would be sent directly to the Martian surface. To support such an ambitious mission architecture, NASA must reduce cost, simplify logistics, reuse and/or repurpose flight hardware, and minimize resources needed for refurbishment. In space servicing is a means to achieving these goals. By designing a mission architecture that relies on the concept of in space servicing (robotic and manned), maximum supportability can be achieved.

  3. Pioneers 10 and 11 deep space missions

    NASA Technical Reports Server (NTRS)

    Dyal, Palmer

    1990-01-01

    Pioneers 10 and 11 were launched from Earth, 2 March 1972, and 5 April 1973, respectively. The Pioneers were the first spacecraft to explore the asteroid belt and the first to encounter the giant planets, Jupiter and Saturn. The Pioneer 10 spacecraft is now the most distant man-made object in our solar system and is farther from the Sun than all nine planets. It is 47 AU from the Sun and is moving in a direction opposite to that of the Sun's motion through the galaxy. Pioneer 11 is 28 AU from the Sun and is traveling in the direction opposite of Pioneer 10, in the same direction as the Sun moves in the galaxy. These two Pioneer spacecraft provided the first large-scale, in-situ measurements of the gas and dust surrounding a star, the Sun. Since launch, the Pioneers have measured large-scale properties of the heliosphere during more than one complete 11-year solar sunspot cycle, and have measured the properties of the expanding solar atmosphere, the transport of cosmic rays into the heliosphere, and the high-energy trapped radiation belts and magnetic fields associated with the planets Jupiter and Saturn. Accurate Doppler tracking of these spin-stabilized spacecraft was used to search for differential gravitational forces from a possible trans-Neptunian planet and to search for gravitational radiation. Future objectives of the Pioneer 10 and 11 missions are to continue measuring the large-scale properties of the heliosphere and to search for its boundary with interstellar space.

  4. Deciphering Kepler's Planetary Systems

    NASA Astrophysics Data System (ADS)

    Lithwick, Yoram

    The theory for how planetary systems form and achieve their final configuration remains highly uncertain. Until now, theories could only be tested against a single system -- the solar system. The Kepler mission, with its abundance of planetary systems, will likely prove to be a Rosetta stone. However, much remains to be deciphered. To help realize the potential of the Kepler mission, we propose to pursue the complementary tasks of characterizing the properties of the Kepler systems and developing theories to explain these properties: 1) Characterizing Kepler systems. We will characterize these planets using the transit-time-variation (TTV) signatures obtained by the mission. We have recently derived a simple expression for the TTV, and used it to derive the masses and eccentricities of a couple dozen Kepler planets. We will extend that work by applying it to many more planets, and by deriving higher-order TTV effects that will allow us to obtain more accurate measurements by breaking degeneracies. We will also use the TTV signals, as well as other observables, to infer the intrinsic orbital architecture of Kepler planets. This will form the basis for the following study. 2) Assembling Kepler systems. Informed by our above analysis, we will try to uncover how the Kepler planets were assembled onto their current orbits. Our recent work on the resonant repulsion mechanism suggests that the final assembly was shaped by a dissipative process, and we will explore that mechanism further. We will also run simulations to test the conjecture that planetesimals were the dissipative agent responsible for final assembly -- just as they are thought to be responsible for the assembly of the planets in the outer solar system

  5. Cross support overview and operations concept for future space missions

    NASA Technical Reports Server (NTRS)

    Stallings, William; Kaufeler, Jean-Francois

    1994-01-01

    Ground networks must respond to the requirements of future missions, which include smaller sizes, tighter budgets, increased numbers, and shorter development schedules. The Consultative Committee for Space Data Systems (CCSDS) is meeting these challenges by developing a general cross support concept, reference model, and service specifications for Space Link Extension services for space missions involving cross support among Space Agencies. This paper identifies and bounds the problem, describes the need to extend Space Link services, gives an overview of the operations concept, and introduces complimentary CCSDS work on standardizing Space Link Extension services.

  6. Spots and the activity of M dwarfs from observations with the Kepler Space Telescope

    NASA Astrophysics Data System (ADS)

    Dmitrienko, E. S.; Savanov, I. S.

    2017-02-01

    A method for estimating the spottedness parameter S (the spotted area as a fraction of the surface of an active star) proposed earlier is applied to an analysis of activity in 1570 M dwarf stars. The analysis is based on observational material obtained with the Kepler Space Telescope, as well as data on the fluxes of the studied objects in the near and far ultraviolet (NUV and FUV) based on data from the GALEX space telescope. The variations of S with the ages of the stars are studied (four groups with different ages are distinguished), as well as variations of S with their rotational periods. A diagram characterizing the relationship between S and the Rossby number Ro resembles the classical dependence of the X-ray luminosities of active stars on Ro, and a saturation regime is attained at the same value, Ro = 0.13. Moreover, objects with ages of more than 100 million years do not form a single sequence (and stars older than 900 million years possess surface spottednesses of order 1%). The S-Ro dependence obtained could expand possibilities for analyzing the dependence of the X-ray luminosities of active stars on their Rossby numbers, and could also be applied to refine parameters characterizing the action of dynamo mechanisms, such as the dynamo number N D . A comparison of the GALEX NUV and FUV brightness estimates with the activity parameters of the stars suggests that younger, more rapidly rotating active stars are brighter in the NUV, and that the FUV flux grows and the difference of the FUV and NUV brightnesses decreases with increasing spottedness S.

  7. Fusion energy for space missions in the 21st Century

    NASA Technical Reports Server (NTRS)

    Schulze, Norman R.

    1991-01-01

    Future space missions were hypothesized and analyzed and the energy source for their accomplishment investigated. The mission included manned Mars, scientific outposts to and robotic sample return missions from the outer planets and asteroids, as well as fly-by and rendezvous mission with the Oort Cloud and the nearest star, Alpha Centauri. Space system parametric requirements and operational features were established. The energy means for accomplishing the High Energy Space Mission were investigated. Potential energy options which could provide the propulsion and electric power system and operational requirements were reviewed and evaluated. Fusion energy was considered to be the preferred option and was analyzed in depth. Candidate fusion fuels were evaluated based upon the energy output and neutron flux. Reactors exhibiting a highly efficient use of magnetic fields for space use while at the same time offering efficient coupling to an exhaust propellant or to a direct energy convertor for efficient electrical production were examined. Near term approaches were identified.

  8. Fusion energy for space missions in the 21st Century

    SciTech Connect

    Schulze, N.R.

    1991-08-01

    Future space missions were hypothesized and analyzed and the energy source for their accomplishment investigated. The mission included manned Mars, scientific outposts to and robotic sample return missions from the outer planets and asteroids, as well as fly-by and rendezvous mission with the Oort Cloud and the nearest star, Alpha Centauri. Space system parametric requirements and operational features were established. The energy means for accomplishing the High Energy Space Mission were investigated. Potential energy options which could provide the propulsion and electric power system and operational requirements were reviewed and evaluated. Fusion energy was considered to be the preferred option and was analyzed in depth. Candidate fusion fuels were evaluated based upon the energy output and neutron flux. Reactors exhibiting a highly efficient use of magnetic fields for space use while at the same time offering efficient coupling to an exhaust propellant or to a direct energy convertor for efficient electrical production were examined. Near term approaches were identified.

  9. Descent guidance and mission planning for space shuttle

    NASA Technical Reports Server (NTRS)

    Joosten, B. K.

    1985-01-01

    The Space Shuttle descent mission planning, mission design, deorbit targeting, and entry guidance have necessarily become interrelated because of the nature of the Orbiter's design and mission requirements. The desired descent trajectory has been formulated in a drag acceleration/relative velocity state space since nearly all of the vehicle's highly constraining flight limitations can be uniquely represented in this plane. Constraints and flight requirements that affect the descent are described. The guidance logic which allows the Orbiter to follow the designed trajectory, the impacts of contingency aborts and flightcrew interaction are discussed. The mission planning and guidance techniques remain essentially unchanged through the Shuttle flight test program and subsequent operational flights.

  10. Reducing Mission Costs by Leveraging Previous Investments in Space

    NASA Technical Reports Server (NTRS)

    Miller, Ron; Adams, W. James

    1999-01-01

    The Rapid Spacecraft Development Office (RSDO) at NASA's Goddard Space Flight Center has been charged with the responsibility to reduce mission cost by allowing access to previous developments on government and commercial space missions. RSDO accomplishes this responsibility by implementing two revolutionary contract vehicles, the Rapid Spacecraft Acquisition (RSA) and Quick Ride. This paper will describe the concept behind these contracts, the current capabilities available to missions, analysis of pricing trends to date using the RSDO processes, and future plans to increase flexibility and capabilities available to mission planners.

  11. Radiological risk analysis of potential SP-100 space mission scenarios

    SciTech Connect

    Bartram, B.W.; Weitzberg, A.

    1988-08-19

    This report presents a radiological risk analysis of three representative space mission scenarios utilizing a fission reactor. The mission profiles considered are: a high-altitude mission, launched by a TITAN IV launch vehicle, boosted by chemical upper stages into its operational orbit, a interplanetary nuclear electric propulsion (NEP) mission, started directly from a shuttle parking orbit, a low-altitude mission, launched by the Shuttle and boosted by a chemical stage to its operational orbit, with subsequent disposal boost after operation. 21 refs., 12 figs., 7 tabs.

  12. Validating Kepler Planet Candidates

    NASA Astrophysics Data System (ADS)

    Lissauer, Jack J.; Torres, G.; Marcy, G.; Brown, T.; Gilliland, R.; Gautier, T. N.; Isaacson, H.; Dupree, A.; Kepler Science Team

    2011-01-01

    The Kepler Science Team has identified more than 700 transit-like signatures in the first 43 days of data returned from the spacecraft (Borucki et al. 2010, arXiv1006.2799B). However, only 7 of these candidates have been confirmed as planets as of late September 2010. The number of true planets in this sample is clearly far larger than 7, but the sample is also 'contaminated' with false-positives, including many from eclipsing binary stars. Separating the wheat from the chaff requires a careful study of individual candidates using both Kepler photometry and spectroscopic and imaging data from the ground. Techniques that the Science Team is developing to address these issues, which include detailed analysis of the photometric data and follow-up observations with ground-based telescopes, will be presented. Kepler was selected as the 10th mission of the Discovery Program. Funding for this mission is provided by NASA, Science Mission Directorate.

  13. Space water electrolysis: Space Station through advance missions

    NASA Technical Reports Server (NTRS)

    Davenport, Ronald J.; Schubert, Franz H.; Grigger, David J.

    1991-01-01

    Static Feed Electrolyzer (SFE) technology can satisfy the need for oxygen (O2) and Hydrogen (H2) in the Space Station Freedom and future advanced missions. The efficiency with which the SFE technology can be used to generate O2 and H2 is one of its major advantages. In fact, the SFE is baselined for the Oxygen Generation Assembly within the Space Station Freedom's Environmental Control and Life Support System (ECLSS). In the conventional SFE process an alkaline electrolyte is contained within the matrix and is sandwiched between two porous electrodes. The electrodes and matrix make up a unitized cell core. The electrolyte provides the necessary path for the transport of water and ions between the electrodes, and forms a barrier to the diffusion of O2 and H2. A hydrophobic, microporous membrane permits water vapor to diffuse from the feed water to the cell core. This membrane separates the liquid feed water from the product H2, and, therefore, avoids direct contact of the electrodes by the feed water. The feed water is also circulated through an external heat exchanger to control the temperature of the cell.

  14. Space water electrolysis: Space Station through advance missions

    NASA Astrophysics Data System (ADS)

    Davenport, Ronald J.; Schubert, Franz H.; Grigger, David J.

    1991-09-01

    Static Feed Electrolyzer (SFE) technology can satisfy the need for oxygen (O2) and Hydrogen (H2) in the Space Station Freedom and future advanced missions. The efficiency with which the SFE technology can be used to generate O2 and H2 is one of its major advantages. In fact, the SFE is baselined for the Oxygen Generation Assembly within the Space Station Freedom's Environmental Control and Life Support System (ECLSS). In the conventional SFE process an alkaline electrolyte is contained within the matrix and is sandwiched between two porous electrodes. The electrodes and matrix make up a unitized cell core. The electrolyte provides the necessary path for the transport of water and ions between the electrodes, and forms a barrier to the diffusion of O2 and H2. A hydrophobic, microporous membrane permits water vapor to diffuse from the feed water to the cell core. This membrane separates the liquid feed water from the product H2, and, therefore, avoids direct contact of the electrodes by the feed water. The feed water is also circulated through an external heat exchanger to control the temperature of the cell.

  15. Active Refrigeration for Space Astrophysics Missions

    NASA Technical Reports Server (NTRS)

    Wade, L.

    1994-01-01

    The use of cryogen dewars limits mission lifetime, increases sensor mass, and increases program engineering and launch costs on spacebased low-background, precision-pointing instruments, telescopes and interferometers.

  16. Analysis of selected deep space missions

    NASA Technical Reports Server (NTRS)

    West, W. S.; Holman, M. L.; Bilsky, H. W.

    1971-01-01

    Task 1 of the NEW MOONS (NASA Evaluation With Models of Optimized Nuclear Spacecraft) study is discussed. Included is an introduction to considerations of launch vehicles, spacecraft, spacecraft subsystems, and scientific objectives associated with precursory unmanned missions to Jupiter and thence out of the ecliptic plane, as well as other missions to Jupiter and other outer planets. Necessity for nuclear power systems is indicated. Trajectories are developed using patched conic and n-body computer techniques.

  17. Deep space network: Mission support requirements

    NASA Technical Reports Server (NTRS)

    1991-01-01

    The purpose is to provide NASA and Jet Propulsion Laboratory management with a concise summary of information concerning the forecasting of the necessary support and requirements for missions described here, including the Earth Radiation Budget Experiment, the Cosmic Background Explorer, the Comet Rendezvous Asteroid Flyby, the Cassini, and the Dynamics Explorer-1. A brief description of various missions along with specific support requirements for each are given.

  18. Deep Space 2: The Mars Microprobe Mission

    NASA Astrophysics Data System (ADS)

    Smrekar, Suzanne; Catling, David; Lorenz, Ralph; Magalhães, Julio; Moersch, Jeffrey; Morgan, Paul; Murray, Bruce; Presley-Holloway, Marsha; Yen, Albert; Zent, Aaron; Blaney, Diana

    The Mars Microprobe Mission will be the second of the New Millennium Program's technology development missions to planetary bodies. The mission consists of two penetrators that weigh 2.4 kg each and are being carried as a piggyback payload on the Mars Polar Lander cruise ring. The spacecraft arrive at Mars on December 3, 1999. The two identical penetrators will impact the surface at ~190 m/s and penetrate up to 0.6 m. They will land within 1 to 10 km of each other and ~50 km from the Polar Lander on the south polar layered terrain. The primary objective of the mission is to demonstrate technologies that will enable future science missions and, in particular, network science missions. A secondary goal is to acquire science data. A subsurface evolved water experiment and a thermal conductivity experiment will estimate the water content and thermal properties of the regolith. The atmospheric density, pressure, and temperature will be derived using descent deceleration data. Impact accelerometer data will be used to determine the depth of penetration, the hardness of the regolith, and the presence or absence of 10 cm scale layers.

  19. Kepler Education and Public Outreach: Engaging Students and the Public in the Discovery of Other Worlds

    NASA Astrophysics Data System (ADS)

    Harman, P.; DeVore, E. K.; Gould, A.; Koch, D.

    2003-12-01

    Are we alone? Are there other worlds like our own? Astronomers are discovering Saturn-size planets, but can smaller planets-new Earths-be found? These are powerful and exciting questions that motivate student learning and public interest in the Kepler search for planets. The Kepler Mission Education and Public Outreach (EPO) program capitalizes on the excitement of discovering Earth-size planets in the habitable zone, stimulating student learning and public interest in astronomy and physics. Kepler is a NASA Discovery mission, selected in December 2001, with launch and the search for extra-solar Earths commencing in 2007. This poster describes the breadth of the Kepler EPO programs, projects and activities. Uniquely, the Kepler Mission plans a technology transfer program that will engage college and university undergraduates directly in ground-based observations of extra-solar giant planets discovered by Kepler. Our goal is to engage underserved students and institutions by providing Kepler data, training, technology and support for observers. Doppler spectroscopy will be used to determine their orbits and predict future transits. Ground-based telescopes operated by students as well as amateur astronomers can be used for these observations even well after the end of the mission. As a space-based research mission, Kepler is being developed and will be operated by a team led by William Borucki, PI, at NASA Ames Research Center. The additional team members include Ball Aerospace, Jet Propulsion Laboratories, Lawrence Hall of Science at UC Berkeley, SETI Institute, Smithsonian Center for Astrophysics, and Space Telescope Science Institute. In addition, scientists from several US, and one Canadian university are participating in the Kepler Mission. The EPO planning engages these scientists to insure the quality as well as the creativity and best application of Kepler results for education and outreach. The Kepler EPO team is led by Alan Gould of the Lawrence Hall of

  20. Space transfer concepts and analyses for exploration missions, phase 3

    NASA Technical Reports Server (NTRS)

    Woodcock, Gordon R.

    1993-01-01

    This report covers the third phase of a broad-scoped and systematic study of space transfer concepts for human lunar and Mars missions. The study addressed issues that were raised during Phase 2, developed generic Mars missions profile analysis data, and conducted preliminary analysis of the Mars in-space transportation requirements and implementation from Stafford Committee Synthesis Report. The major effort of the study was the development of the first Lunar Outpost (FLO) baseline which evolved from the Space Station Freedom Hab Module. Modifications for the First Lunar Outpost were made to meet mission requirements and technology advancements.

  1. Magnetic Materials Suitable for Fission Power Conversion in Space Missions

    NASA Technical Reports Server (NTRS)

    Bowman, Cheryl L.

    2012-01-01

    Terrestrial fission reactors use combinations of shielding and distance to protect power conversion components from elevated temperature and radiation. Space mission systems are necessarily compact and must minimize shielding and distance to enhance system level efficiencies. Technology development efforts to support fission power generation scenarios for future space missions include studying the radiation tolerance of component materials. The fundamental principles of material magnetism are reviewed and used to interpret existing material radiation effects data for expected fission power conversion components for target space missions. Suitable materials for the Fission Power System (FPS) Project are available and guidelines are presented for bounding the elevated temperature/radiation tolerance envelope for candidate magnetic materials.

  2. Liftoff of Space Shuttle Endeavour on mission STS-97

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Space Shuttle Endeavour rockets off Launch Pad 39B in a perfect, on-time launch. Liftoff of Endeavour occurred at 10:06:01 p.m. EST on mission STS-97. Endeavour and its five-member crew will deliver U.S. solar arrays to the International Space Station and be the first Shuttle crew to visit the Station'''s first resident crew. The 11-day mission includes three spacewalks. This marks the 101st mission in Space Shuttle history and the 25th night launch. Endeavour is expected to land Dec. 11 at 6:19 p.m. EST.

  3. Space-Based Gravitational-Wave Observatory Mission Concept

    NASA Astrophysics Data System (ADS)

    Livas, Jeffrey C.

    2014-08-01

    Space-based Gravitational-wave Observatories (SGOs) will enable the systematic study of the frequency band from 0.0001 - 1 Hz of gravitational waves, where a rich array of astrophysical sources is expected. ESA has selected “The Gravitational Universe” as the science theme for the L3 mission opportunity with a nominal launch date in 2034. This will be at a minimum 15 years after ground-based detectors and pulsar timing arrays announce their first detections and at least 18 years after the LISA Pathfinder Mission will have demonstrated key technologies in a dedicated space mission. It is therefore important to develop mission concepts that can take advantage of the momentum in the field and the investment in both technology development and a precision measurement community on a more near-term timescale than the L3 opportunity. This talk will discuss a mission concept based on the LISA baseline that resulted from a recent mission architecture study.

  4. The phase smearing effect in the light curves of contact binaries observed by the Kepler mission and the determination of the parameters of 17 contact systems

    NASA Astrophysics Data System (ADS)

    Zola, S.; Baran, A.; Debski, B.; Jableka, D.

    2017-04-01

    The Kepler mission observations, taken in the long cadence mode, have a time resolution of about 30 min. In this paper, we investigate how the long cadence binning influences the shapes of the light curves of eclipsing binaries. A simulated light curve of a contact binary exhibiting a flat-bottom secondary minimum was applied for this purpose. We found that the binning caused a change in the variation amplitude and the shape of the minima. We modelled the simulated light curves corresponding to periods between 0.2 and 2 d using a code that does not account for binning and we derived the parameters. It turned out that only when the binary period is close to or longer than about 1.5 d are the solutions derived with such a code accurate. Rigorous modelling of systems with shorter periods requires the use of codes that do account for phase smearing due to long exposure times. We selected a sample of contact binaries observed by the Kepler mission, exhibiting a flat-bottom secondary minimum and showing no intrinsic activity. We solved the light curves of the sample with the most recent (2015) version of the Wilson-Devinney code and we derived the system parameters. The best models that we derived indicate that most of the systems in our sample have a deep contact configuration and that 13 out of 17 required the addition of a third light for good fits. Our results suggest that 13 systems could have tertiary companions.

  5. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    KENNEDY SPACE CENTER, Fla. -- It'''s tail bathed in light, Space Shuttle Atlantis roars into space on mission STS-98. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle'''s robotic arm. Three spacewalks are required to complete the planned construction work during the 11-day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA'''s Space Shuttle program. The planned landing is at KSC Feb. 18 about 1:00 p.m. EST.

  6. Overview of RICOR tactical cryogenic refrigerators for space missions

    NASA Astrophysics Data System (ADS)

    Riabzev, Sergey; Filis, Avishai; Livni, Dorit; Regev, Itai; Segal, Victor; Gover, Dan

    2016-05-01

    Cryogenic refrigerators represent a significant enabling technology for Earth and Space science enterprises. Many of the space instruments require cryogenic refrigeration to enable the use of advanced detectors to explore a wide range of phenomena from space. RICOR refrigerators involved in various space missions are overviewed in this paper, starting in 1994 with "Clementine" Moon mission, till the latest ExoMars mission launched in 2016. RICOR tactical rotary refrigerators have been incorporated in many space instruments, after passing qualification, life time, thermal management testing and flight acceptance. The tactical to space customization framework includes an extensive characterization and qualification test program to validate reliability, the design of thermal interfacing with a detector, vibration export control, efficient heat dissipation in a vacuum environment, robustness, mounting design, compliance with outgassing requirements and strict performance screening. Current RICOR development is focused on dedicated ultra-long-life, highly reliable, space cryogenic refrigerator based on a Pulse Tube design

  7. Handbook for Using IP Protocols for Space Missions

    NASA Technical Reports Server (NTRS)

    Hogie, Keith; Criscuolo, Ed; Parise, Ron

    2004-01-01

    This presentation will provide a summary of a handbook developed at GSFC last year that contains concepts and guidelines for using Internet protocols for space missions. It will include topics on: Lessons learned from current Space IP mission. General architectural issues related to use of IP in space. Operational scenarios for common space data transfer applications. Security issues. A general review of protocols applicable for use with IP in space. The presentation will also pose questions on what sort of information would be useful in future versions of the document.

  8. Studying RR Lyrae Stars with Kepler/K2 (Abstract)

    NASA Astrophysics Data System (ADS)

    Kuehn, C.

    2016-12-01

    (Abstract only) While RR Lyrae stars have long been studied from the ground, the high photometric precision, high cadence, and long observing times offered by the Kepler Space Telescope have yielded exciting discoveries that are revolutionizing our understanding of these stars. In its new K2 mission, Kepler is observing an even larger sample of RR Lyrae stars, promising to provide new insights into them and our Milky Way. In this talk I will present some of the most exciting new discoveries about RR Lyrae stars from the K2 mission with a special focus on what we are learning about the RR Lyrae in the globular cluster M4, our first chance to observe a single population of RR Lyrae with Kepler.

  9. Excluding False Positive Detections in Kepler Data

    NASA Astrophysics Data System (ADS)

    Caldwell, John J.; Ouvarova, T.; Borucki, W. J.

    2006-09-01

    The NASA Kepler Mission, scheduled for launch in 2008, will search for Earth-size planets orbiting Sun-like stars in or near habitable zones. A high precision photometer will search for planetary transits of parent stars. For a system similar to the Earth-Sun, the decrease in light during a central transit will be one part in 10,000 of the total stellar brightness out of transit. This poster discusses the effort to address a significant concern: the possibility of false positive detections of extra-solar Earth analogs. The concern arises because about 50 per cent of star systems are double or multiple. Further, because the photometer design is constrained by the requirement for high sensitivity to changes of low light levels, the optical resolution is not high compared to other space or terrestrial telescopes. If a relatively nearby Kepler target star happens to contain, within the Kepler PSF, an eclipsing binary system that is reduced in brightness by a factor of 10,000, say because it is 100 times farther away, the photometric profile of an eclipse could mimic a planetary transit. We have therefore developed a program to use archival data from the Hubble Space Telescope to quantify the number density of faint stars in the Kepler field that are in the brightness range that could cause confusion. Since the beginning of the project, the location of the Kepler field itself has been changed to optimize observing efficiency. The work originally included HST/WFPC2 data, and has now been expanded to ACS data as well. We present here a summary of completed and continuing work on faint background systems in the new Kepler field.

  10. Space station needs, attributes, and architectural options: Mission requirements

    NASA Technical Reports Server (NTRS)

    Riel, F. D.

    1983-01-01

    Space station missions and their requirements are discussed. Analyses of the following four mission categories are summarized: (1) commercial, (2) technology, (3) operation, and (4) science and applications. The requirements determined by the study dictate a very strong need for a manned space station to satisfy the majority of the missions. The station is best located at a 28.5-deg inclination and initially (1992 era) requires a crew of four (three for mission payloads) and a mission power of 25 kW. A space platform in a polar orbit is needed to augment the station capability; it initially would be a 15-kW system, located in a sun-synchronous orbit.

  11. Official portrait space shuttle mission 41-D crew

    NASA Technical Reports Server (NTRS)

    1984-01-01

    Official portrait of the space shuttle mission 41-D crew. Seated are (left to right): Richard M. (Mike) Mullane and Steven A. Hawley, mission specialists; Henry W. Hartsfield, Jr., crew commander; Michael L. Coats, pilot. Standing are Charles D. Walker, pilot and Judith A. Resnik, mission specialist. Behind them is a model of the early sailing vessel Discovery and a model of the shuttle Discovery.

  12. Collaboration support system for "Phobos-Soil" space mission.

    NASA Astrophysics Data System (ADS)

    Nazarov, V.; Nazirov, R.; Zakharov, A.

    2009-04-01

    Rapid development of communication facilities leads growth of interactions done via electronic means. However we can see some paradox in this segment in last times: Extending of communication facilities increases collaboration chaos. And it is very sensitive for space missions in general and scientific space mission particularly because effective decision of this task provides successful realization of the missions and promises increasing the ratio of functional characteristic and cost of mission at all. Resolving of this problem may be found by using respective modern technologies and methods which widely used in different branches and not in the space researches only. Such approaches as Social Networking, Web 2.0 and Enterprise 2.0 look most prospective in this context. The primary goal of the "Phobos-Soil" mission is an investigation of the Phobos which is the Martian moon and particularly its regolith, internal structure, peculiarities of the orbital and proper motion, as well as a number of different scientific measurements and experiments for investigation of the Martian environment. A lot of investigators involved in the mission. Effective collaboration system is key facility for information support of the mission therefore. Further to main goal: communication between users of the system, modern approaches allows using such capabilities as self-organizing community, user generated content, centralized and federative control of the system. Also it may have one unique possibility - knowledge management which is very important for space mission realization. Therefore collaboration support system for "Phobos-Soil" mission designed on the base of multilayer model which includes such levels as Communications, Announcement and Information, Data sharing and Knowledge management. The collaboration support system for "Phobos-Soil" mission will be used as prototype for prospective Russian scientific space missions and the presentation describes its architecture

  13. An integrated mission planning approach for the space exploration initiative

    SciTech Connect

    Coomes, E.P.; Dagle, J.E.; Bamberger, J.A.; Noffsinger, K.E.

    1992-01-01

    A fully integrated energy-based approach to mission planning is needed if the Space Exploration Initiative (SEI) is to succeed. Such an approach would reduce the number of new systems and technologies requiring development. The resultant horizontal commonality of systems and hardware would reduce the direct economic impact of SEI and provide an economic benefit by greatly enhancing our international technical competitiveness through technology spin-offs and through the resulting early return on investment. Integrated planning and close interagency cooperation must occur if the SEI is to achieve its goal of expanding the human presence into the solar system and be an affordable endeavor. An energy-based mission planning approach gives each mission planner the needed power, yet preserves the individuality of mission requirements and objectives while reducing the concessions mission planners must make. This approach may even expand the mission options available and enhance mission activities.

  14. An integrated mission planning approach for the Space Exploration Initiative

    SciTech Connect

    Coomes, E.P.; Dagle, J.E.; Bamberger, J.A.; Noffsinger, K.E.

    1992-08-01

    This report discusses a fully integrated energy-based approach to mission planning which is needed if the Space Exploration Initiative (SEI) is to succeed. Such an approach would reduce the number of new systems and technologies requiring development. The resultant horizontal commonality of systems and hardware would reduce the direct economic impact of SEI and provide an economic benefit by greatly enhancing our international technical competitiveness through technology spin-offs and through the resulting early return on investment. Integrated planning and close interagency cooperation must occur if the SEI is to achieve its goal of expanding the human presence into the solar system and be an affordable endeavor. An energy-based mission planning approach gives each mission planner the needed power, yet preserves the individuality of mission requirements and objectives while reducing the concessions mission planners must make. This approach may even expand the mission options available and enhance mission activities.

  15. Space Station needs, attributes and architectural options. Volume 2, book 1, part 1: Mission requirements

    NASA Technical Reports Server (NTRS)

    1983-01-01

    The baseline mission model used to develop the space station mission-related requirements is described as well as the 90 civil missions that were evaluated, (including the 62 missions that formed the baseline model). Mission-related requirements for the space station baseline are defined and related to space station architectural development. Mission-related sensitivity analyses are discussed.

  16. Small planetary missions for the Space Shuttle

    NASA Technical Reports Server (NTRS)

    Staehle, R. L.

    1979-01-01

    The paper deals with the concept of a small planetary mission that might be described as one which: (1) focuses on a narrow set of discovery-oriented objectives, (2) utilizes largely existing and proven subsystem capabilities, (3) does not tax future launch vehicle capabilities, and (4) is flexible in terms of mission timing such that it can be easily integrated with launch vehicle schedules. Three small planetary mission concepts are presented: a tour of earth-sun Lagrange regions in search of asteroids which might be gravitationally trapped, a network of spacecraft to search beyond Pluto for a tenth planet; and a probe which could be targeted for infrequent long period 'comets of opportunity' or for a multitude of shorter period comets.

  17. SPECTROSCOPY OF NEW AND POORLY KNOWN CATACLYSMIC VARIABLES IN THE KEPLER FIELD

    SciTech Connect

    Howell, Steve B.; Still, Martin; Everett, Mark E.; Seebode, Sally A.; Szkody, Paula; Wood, Matt; Ramsay, Gavin; Cannizzo, John

    2013-04-15

    The NASA Kepler mission has been in science operation since 2009 May and is providing high precision, high cadence light curves of over 150,000 targets. Prior to launch, nine cataclysmic variables were known to lie within Kepler's field of view. We present spectroscopy for seven systems, four of which were newly discovered since launch. All of the stars presented herein have been observed by, or are currently being observed by, the Kepler space telescope. Three historic systems and one new candidate could not be detected at their sky position and two candidates are called into question as to their true identity.

  18. Reducing the Risk of Human Space Missions with INTEGRITY

    NASA Technical Reports Server (NTRS)

    Jones, Harry W.; Dillon-Merill, Robin L.; Tri, Terry O.; Henninger, Donald L.

    2003-01-01

    The INTEGRITY Program will design and operate a test bed facility to help prepare for future beyond-LEO missions. The purpose of INTEGRITY is to enable future missions by developing, testing, and demonstrating advanced human space systems. INTEGRITY will also implement and validate advanced management techniques including risk analysis and mitigation. One important way INTEGRITY will help enable future missions is by reducing their risk. A risk analysis of human space missions is important in defining the steps that INTEGRITY should take to mitigate risk. This paper describes how a Probabilistic Risk Assessment (PRA) of human space missions will help support the planning and development of INTEGRITY to maximize its benefits to future missions. PRA is a systematic methodology to decompose the system into subsystems and components, to quantify the failure risk as a function of the design elements and their corresponding probability of failure. PRA provides a quantitative estimate of the probability of failure of the system, including an assessment and display of the degree of uncertainty surrounding the probability. PRA provides a basis for understanding the impacts of decisions that affect safety, reliability, performance, and cost. Risks with both high probability and high impact are identified as top priority. The PRA of human missions beyond Earth orbit will help indicate how the risk of future human space missions can be reduced by integrating and testing systems in INTEGRITY.

  19. Space Station polar orbiting platform - Mission analysis and planning

    NASA Technical Reports Server (NTRS)

    Miller, P. A.

    1986-01-01

    The Space Station Polar Orbiting Platform will be a serviceable spacecraft supporting a range of missions. The planning and analysis of these missions is investigated. The subjects of STS compatibility, rendezvous strategy, and requisite launch windows are addressed. General, as well as, two specific cases are detailed with respect to their incremental velocity requirements.

  20. National Space Transportation Systems Program mission report

    NASA Technical Reports Server (NTRS)

    Collins, M. A., Jr.; Aldrich, A. D.; Lunney, G. S.

    1984-01-01

    The major activities and accomplishments of this first Spacelab mission using Orbiter vehicle 102. The significant configuration differences incorporated prior to STS-9 include the first use of the 3 substack fuel cells, the use of 5 cryo tanks sets and the addition of a galley and crew sleep stations. These differences combined with the Spacelab payload resulted in the heaviest landing weight yet flown. The problems that occurred are cited and a problem tracking list of all significant anomalies tht occurred during the mission is included. Scientific results of experiments conducted are highlighted.

  1. Expert systems and advanced automation for space missions operations

    NASA Astrophysics Data System (ADS)

    Durrani, Sajjad H.; Perkins, Dorothy C.; Carlton, P. Douglas

    1990-10-01

    Increased complexity of space missions during the 1980s led to the introduction of expert systems and advanced automation techniques in mission operations. This paper describes several technologies in operational use or under development at the National Aeronautics and Space Administration's Goddard Space Flight Center. Several expert systems are described that diagnose faults, analyze spacecraft operations and onboard subsystem performance (in conjunction with neural networks), and perform data quality and data accounting functions. The design of customized user interfaces is discussed, with examples of their application to space missions. Displays, which allow mission operators to see the spacecraft position, orientation, and configuration under a variety of operating conditions, are described. Automated systems for scheduling are discussed, and a testbed that allows tests and demonstrations of the associated architectures, interface protocols, and operations concepts is described. Lessons learned are summarized.

  2. Mission Operations Directorate - Success Legacy of the Space Shuttle Program

    NASA Technical Reports Server (NTRS)

    Azbell, James A.

    2011-01-01

    In support of the Space Shuttle Program, as well as NASA s other human space flight programs, the Mission Operations Directorate (MOD) at the Johnson Space Center has become the world leader in human spaceflight operations. From the earliest programs - Mercury, Gemini, Apollo - through Skylab, Shuttle, ISS, and our Exploration initiatives, MOD and its predecessors have pioneered ops concepts and emphasized a history of mission leadership which has added value, maximized mission success, and built on continual improvement of the capabilities to become more efficient and effective. MOD s focus on building and contributing value with diverse teams has been key to their successes both with the US space industry and the broader international community. Since their beginning, MOD has consistently demonstrated their ability to evolve and respond to an ever changing environment, effectively prepare for the expected and successfully respond to the unexpected, and develop leaders, expertise, and a culture that has led to mission and Program success.

  3. Mission Operations Directorate - Success Legacy of the Space Shuttle Program

    NASA Technical Reports Server (NTRS)

    Azbell, Jim

    2010-01-01

    In support of the Space Shuttle Program, as well as NASA's other human space flight programs, the Mission Operations Directorate (MOD) at the Johnson Space Center has become the world leader in human spaceflight operations. From the earliest programs - Mercury, Gemini, Apollo - through Skylab, Shuttle, ISS, and our Exploration initiatives, MOD and its predecessors have pioneered ops concepts and emphasized a history of mission leadership which has added value, maximized mission success, and built on continual improvement of the capabilities to become more efficient and effective. MOD's focus on building and contributing value with diverse teams has been key to their successes both with the US space industry and the broader international community. Since their beginning, MOD has consistently demonstrated their ability to evolve and respond to an ever changing environment, effectively prepare for the expected and successfully respond to the unexpected, and develop leaders, expertise, and a culture that has led to mission and Program success.

  4. Kepler's Orbit

    NASA Video Gallery

    Kepler does not orbit the Earth, rather it orbits the Sun in concert with the Earth, slowly drifting away from Earth. Every 61 Earth years, Kepler and Earth will pass by each other. Throughout the ...

  5. Buzz Lightyear's Space Station Mission Logs

    NASA Video Gallery

    The world's most famous space ranger returned to Earth in September 2009 after more than a year in orbit, and now he's sharing his adventures. Learn more about the International Space Station with ...

  6. Flight Opportunities: Space Technology Mission Directorate

    NASA Technical Reports Server (NTRS)

    Van Dijk, Alexander

    2016-01-01

    Flight Opportunities enables maturation of new space technologies by funding access to commercially available space-relevant test environments. The program also supports capability development in the commercial suborbital and orbital small satellite launcher markets.

  7. KEPLER Mission Status

    DTIC Science & Technology

    2007-01-01

    stars. The instrument consists of a 0.95-m aperture photometer capable of doing high precision photometry of more than 100,000 late-type main sequence... parameters and to choose appropriate targets. The association of planet size and occurrence frequency with stellar mass and metallicity will be...into the star or out of the planetary system. It is also possible that the stars not showing the presence of giant planets are devoid of all planets

  8. The Extreme Universe Space Observatory Super Pressure Balloon Mission

    NASA Astrophysics Data System (ADS)

    Wiencke, Lawrence; Olinto, Angela; Adams, Jim; JEM-EUSO Collaboration

    2017-01-01

    The Extreme Universe Space Observatory on a super pressure balloon (EUSO-SPB) mission will make the first fluorescence observations of high energy cosmic ray extensive air showers by looking down on the atmosphere from near space. A long duration flight of at least 50 nights launched from Wanaka NZ is planned for 2017. We describe completed instrument, and the planned mission. We acknowledge the support of NASA through grants NNX13AH53G and NNX13AH55G.

  9. Distribution of Cost Growth in Robotic Space Science Missions

    NASA Technical Reports Server (NTRS)

    Swan, Christopher

    2007-01-01

    Cost growth characterization is a critical factor for effective cost risk analysis and project planning. This study analyzed low level budget changes in Jet Propulsion Laboratory-managed space science missions, which occurred during the development of the project. The data was then curve fit, according to cost distribution categories, to provide a reference set of distribution parameters with sufficient granularity to effectively model cost growth in robotic space science missions.

  10. Advanced Power Sources for Space Missions

    DTIC Science & Technology

    1989-01-01

    baseload operation of the space platform, including communication, station-keeping, and surveillance systems. A typical household consumes energy at the...RESEARCH CENTER, CLEVELAND, OHIO June 25,1987 NASA space power need» and programs SDI space power architecture studies SDI nonnuclear baseload

  11. Deep Space Habitat Concept of Operations for Transit Mission Phases

    NASA Technical Reports Server (NTRS)

    Hoffman, Stephen J.

    2011-01-01

    The National Aeronautics and Space Administration (NASA) has begun evaluating various mission and system components of possible implementations of what the U.S. Human Spaceflight Plans Committee (also known as the Augustine Committee) has named the flexible path (Anon., 2009). As human spaceflight missions expand further into deep space, the duration of these missions increases to the point where a dedicated crew habitat element appears necessary. There are several destinations included in this flexible path a near Earth asteroid (NEA) mission, a Phobos/Deimos (Ph/D) mission, and a Mars surface exploration mission that all include at least a portion of the total mission in which the crew spends significant periods of time (measured in months) in the deep space environment and are thus candidates for a dedicated habitat element. As one facet of a number of studies being conducted by the Human Spaceflight Architecture Team (HAT) a workshop was conducted to consider how best to define and quantify habitable volume for these future deep space missions. One conclusion reached during this workshop was the need for a description of the scope and scale of these missions and the intended uses of a habitat element. A group was set up to prepare a concept of operations document to address this need. This document describes a concept of operations for a habitat element used for these deep space missions. Although it may eventually be determined that there is significant overlap with this concept of operations and that of a habitat destined for use on planetary surfaces, such as the Moon and Mars, no such presumption is made in this document.

  12. Kepler's Planetary Systems in Motion

    NASA Video Gallery

    The animation shows an overhead view of the orbital position of the planets in systems with multiple transiting planets discovered by NASA's Kepler mission as of Jan. 2012. All the colored planets ...

  13. Discovery of Kepler-16b

    NASA Video Gallery

    NASA’s Kepler mission has turned fiction into fact. A world with a double sunset that was first imagined in "Star Wars" over 30 years ago in a galaxy far, far away has become scientific reality. ...

  14. Artificial intelligence techniques for scheduling Space Shuttle missions

    NASA Technical Reports Server (NTRS)

    Henke, Andrea L.; Stottler, Richard H.

    1994-01-01

    Planning and scheduling of NASA Space Shuttle missions is a complex, labor-intensive process requiring the expertise of experienced mission planners. We have developed a planning and scheduling system using combinations of artificial intelligence knowledge representations and planning techniques to capture mission planning knowledge and automate the multi-mission planning process. Our integrated object oriented and rule-based approach reduces planning time by orders of magnitude and provides planners with the flexibility to easily modify planning knowledge and constraints without requiring programming expertise.

  15. Mission planning parameters for the Space Shuttle large format camera

    NASA Technical Reports Server (NTRS)

    Wood, G. A.

    1979-01-01

    The paper discusses the impact of various Space Shuttle mission parameters on the efficient and meaningful utilization of the large format camera (LFC) as a photographic acquisition system. Some of the LFC's vital statistics and its mounting within the Orbiter payload are described. LFC characteristics and mounting dictate certain mission parameters. The controlling parameters are orbit inclinations, launch time of year, launch time of day, orbital altitude, mission duration, overlap selection, film capacity, and climatological prediction. A mission case is evaluated relative to controlling parameters and geographical area(s) of interest.

  16. Space Shuttle Discovery lifts off successfully on mission STS-95

    NASA Technical Reports Server (NTRS)

    1998-01-01

    Space Shuttle Discovery soars above billowing clouds of steam and smoke into clear blue skies as it lifts off from Launch Pad 39B at 2:19 p.m. EST Oct. 29 on mission STS-95. The crew members are Mission Commander Curtis L. Brown Jr.; Pilot Steven W. Lindsey; Payload Specialist Chiaki Mukai, (M.D., Ph.D.), with the National Space Development Agency of Japan (NASDA); Mission Specialist Scott E. Parazynski; Mission Specialist Stephen K. Robinson; Mission Specialist Pedro Duque of Spain, representing the European Space Agency (ESA); and Payload Specialist John H. Glenn Jr., a senator from Ohio and one of the original Mercury 7 astronauts. Glenn is making his second voyage into space after 36 years. The STS-95 mission includes research payloads such as the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbital Systems Test Platform, the International Extreme Ultraviolet Hitchhiker, as well as the SPACEHAB single module with experiments on space flight and the aging process. Discovery is expected to return to KSC at 11:49 a.m. EST on Nov. 7.

  17. Atmosphere composition monitor for space station and advanced missions application

    SciTech Connect

    Wynveen, R.A.; Powell, F.T.

    1987-01-01

    Long-term human occupation of extraterrestrial locations may soon become a reality. The National Aeronautics and Space Administration (NASA) has recently completed the definition and preliminary design of the low earth orbit (LEO) space station. They are now currently moving into the detailed design and fabrication phase of this space station and are also beginning to analyze the requirements of several future missions that have been identified. These missions include, for example, Lunar and Mars sorties, outposts, bases, and settlements. A requirement of both the LEO space station and future missions are environmental control and life support systems (ECLSS), which provide a comfortable environment for humans to live and work. The ECLSS consists of several major systems, including atmosphere revitalization system (ARS), atmosphere pressure and composition control system, temperature and humidity control system, water reclamation system, and waste management system. Each of these major systems is broken down into subsystems, assemblies, units, and instruments. Many requirements and design drivers are different for the ECLSS of the LEO space station and the identified advanced missions (e.g., longer mission duration). This paper discusses one of the ARS assemblies, the atmosphere composition monitor assembly (ACMA), being developed for the LEO space station and addresses differences that will exist for the ACMA of future missions.

  18. Vision for Micro Technology Space Missions. Chapter 2

    NASA Technical Reports Server (NTRS)

    Dennehy, Neil

    2005-01-01

    It is exciting to contemplate the various space mission applications that Micro Electro Mechanical Systems (MEMS) technology could enable in the next 10-20 years. The primary objective of this chapter is to both stimulate ideas for MEMS technology infusion on future NASA space missions and to spur adoption of the MEMS technology in the minds of mission designers. This chapter is also intended to inform non-space oriented MEMS technologists, researchers and decision makers about the rich potential application set that future NASA Science and Exploration missions will provide. The motivation for this chapter is therefore to lead the reader down a path to identify and it is exciting to contemplate the various space mission applications that Micro Electro Mechanical Systems (MEMS) technology could enable in the next 10-20 years. The primary objective of this chapter is to both stimulate ideas for MEMS technology infusion on future NASA space missions and to spur adoption of the MEMS technology in the minds of mission designers. This chapter is also intended to inform non-space oriented MEMS technologists, researchers and decision makers about the rich potential application set that future NASA Science and Exploration missions will provide. The motivation for this chapter is therefore to lead the reader down a path to identify and consider potential long-term, perhaps disruptive or revolutionary, impacts that MEMS technology may have for future civilian space applications. A general discussion of the potential for MEMS in space applications is followed by a brief showcasing of a few selected examples of recent MEMS technology developments for future space missions. Using these recent developments as a point of departure, a vision is then presented of several areas where MEMS technology might eventually be exploited in future Science and Exploration mission applications. Lastly, as a stimulus for future research and development, this chapter summarizes a set of barriers

  19. Bounding the Spacecraft Atmosphere Design Space for Future Exploration Missions

    NASA Technical Reports Server (NTRS)

    Lange, Kevin E.; Perka, Alan T.; Duffield, Bruce E.; Jeng, Frank F.

    2005-01-01

    The selection of spacecraft and space suit atmospheres for future human space exploration missions will play an important, if not critical, role in the ultimate safety, productivity, and cost of such missions. Internal atmosphere pressure and composition (particularly oxygen concentration) influence many aspects of spacecraft and space suit design, operation, and technology development. Optimal atmosphere solutions must be determined by iterative process involving research, design, development, testing, and systems analysis. A necessary first step in this process is the establishment of working bounds on the atmosphere design space.

  20. Logistics Needs for Potential Deep Space Mission Scenarios Post Asteroid Crewed Mission

    NASA Technical Reports Server (NTRS)

    Lopez, Pedro, Jr.

    2015-01-01

    A deep-space mission has been proposed to identify and redirect an asteroid to a distant retrograde orbit around the moon, and explore it by sending a crew using the Space Launch System and the Orion spacecraft. The Asteroid Redirect Crewed Mission (ARCM), which represents the third segment of the Asteroid Redirect Mission (ARM), could be performed on EM-3 or EM-4 depending on asteroid return date. Recent NASA studies have raised questions on how we could progress from current Human Space Flight (HSF) efforts to longer term human exploration of Mars. This paper will describe the benefits of execution of the ARM as the initial stepping stone towards Mars exploration, and how the capabilities required to send humans to Mars could be built upon those developed for the asteroid mission. A series of potential interim missions aimed at developing such capabilities will be described, and the feasibility of such mission manifest will be discussed. Options for the asteroid crewed mission will also be addressed, including crew size and mission duration.

  1. Attracting Students to Space Science Fields: Mission to Mars

    NASA Astrophysics Data System (ADS)

    Congdon, Donald R.; Lovegrove, William P.; Samec, Ronald G.

    Attracting high school students to space science is one of the main goals of Bob Jones University's annual Mission to Mars (MTM). MTM develops interest in space exploration through a highly realistic simulated trip to Mars. Students study and learn to appreciate the challenges of space travel including propulsion life support medicine planetary astronomy psychology robotics and communication. Broken into teams (Management Spacecraft Design Communications Life Support Navigation Robotics and Science) they address the problems specific to each aspect of the mission. Teams also learn to interact and recognize that a successful mission requires cooperation. Coordinated by the Management Team the students build a spacecraft and associated apparatus connect computers and communications equipment train astronauts on the mission simulator and program a Pathfinder-type robot. On the big day the astronauts enter the spacecraft as Mission Control gets ready to support them through the expected and unexpected of their mission. Aided by teamwork the astronauts must land on Mars perform their scientific mission on a simulated surface of mars and return home. We see the success of MTM not only in successful missions but in the students who come back year after year for another MTM.

  2. Space-Based Gravitational-wave Mission Concept Studies

    NASA Technical Reports Server (NTRS)

    Livas, Jeffrey C.

    2012-01-01

    The LISA Mission Concept has been under study for over two decades as a spacebased gravitational-wave detector capable of observing astrophysical sources in the 0.0001 to 1 Hz band. The concept has consistently received strong recommendations from various review panels based on the expected science, most recently from the US Astr02010 Decadal Review. Budget constraints have led both the US and European Space agencies to search for lower cost options. We report results from the US effort to explore the tradeoffs between mission cost and science return, and in particular a family of mission concepts referred to as SGO (Space-based Gravitational-wave Observatory).

  3. Space mission scenario development and performance analysis tool

    NASA Technical Reports Server (NTRS)

    Kordon, Mark; Baker, John; Gilbert, John; Hanks, David

    2004-01-01

    This paper discusses a new and innovative approach for a rapid spacecraft multi-disciplinary performance analysis using a tool called the Mission Scenario Development Workbench (MSDW). To meet the needs of new classes of space missions, analysis tools with proven models were developed and integrated into a framework to enable rapid trades and analyses between spacecraft designs and operational scenarios during the formulation phase of a mission. Generally speaking, spacecraft resources are highly constrained on deep space missions and this approach makes it possible to maximize the use of existing resources to attain the best possible science return. This approach also has the potential benefit of reducing the risk of costly design changes made later in the design cycle necessary to meet the mission requirements by understanding system design sensitivities early and adding appropriate margins. This paper will describe the approach used by the Mars Science Laboratory Project to accomplish this result.

  4. Social and cultural issues during Shuttle/Mir space missions.

    PubMed

    Kanas, N; Salnitskiy, V; Grund, E M; Gushin, V; Weiss, D S; Kozerenko, O; Sled, A; Marmar, C R

    2000-01-01

    A number of interpersonal issues relevant to manned space missions have been identified from the literature. These include crew tension, cohesion, leadership, language and cultural factors, and displacement. Ground-based studies by others and us have clarified some of the parameters of these issues and have indicated ways in which they could be studied during actual space missions. In this paper, we summarize some of our findings related to social and cultural issues from a NASA-funded study conducted during several Shuttle/Mir space missions. We used standardized mood and group climate measures that were completed on a weekly basis by American and Russian crew and mission control subjects who participated in these missions. Our results indicated that American subjects reported more dissatisfaction with their interpersonal environment than their Russian counterparts, especially American astronauts. Mission control personnel were more dysphoric than crewmembers, but both groups were significantly less dysphoric than other work groups on Earth. Countermeasures based on our findings are discussed which can be applied to future multicultural space missions.

  5. Social and cultural issues during Shuttle/Mir space missions

    NASA Technical Reports Server (NTRS)

    Kanas, N.; Salnitskiy, V.; Grund, E. M.; Gushin, V.; Weiss, D. S.; Kozerenko, O.; Sled, A.; Marmar, C. R.

    2000-01-01

    A number of interpersonal issues relevant to manned space missions have been identified from the literature. These include crew tension, cohesion, leadership, language and cultural factors, and displacement. Ground-based studies by others and us have clarified some of the parameters of these issues and have indicated ways in which they could be studied during actual space missions. In this paper, we summarize some of our findings related to social and cultural issues from a NASA-funded study conducted during several Shuttle/Mir space missions. We used standardized mood and group climate measures that were completed on a weekly basis by American and Russian crew and mission control subjects who participated in these missions. Our results indicated that American subjects reported more dissatisfaction with their interpersonal environment than their Russian counterparts, especially American astronauts. Mission control personnel were more dysphoric than crewmembers, but both groups were significantly less dysphoric than other work groups on Earth. Countermeasures based on our findings are discussed which can be applied to future multicultural space missions. Published by Elsevier Science Ltd.

  6. Space radiation incident on SATS missions

    NASA Technical Reports Server (NTRS)

    Stassinopoulos, E. G.

    1973-01-01

    A special orbital radiation study was conducted in order to evaluate mission encountered energetic particle fluxes. This information is to be supplied to the project subsystem engineers for their guidance in designing flight hardware to withstand the expected radiation levels. Flux calculations were performed for a set of 20 nominal trajectories placed at several altitudes and inclinations. Temporal variations in the ambient electron environment were considered and partially accounted for. Magnetic field calculations were performed with a current field model, extrapolated to the tentative SATS launch epoch with linear time terms. Orbital flux integrations ware performed with the latest proton and electron environment models, using new computational methods. The results are presented in graphical and tabular form. Estimates of energetic solar proton fluxes are given for a one year mission at selected integral energies ranging from 10 to 100 Mev, calculated for a year of maximum solar activity during the next solar cycle.

  7. Design Reference Missions for Deep-Space Optical Communication

    NASA Astrophysics Data System (ADS)

    Breidenthal, J.; Abraham, D.

    2016-05-01

    We examined the potential, but uncertain, NASA mission portfolio out to a time horizon of 20 years, to identify mission concepts that potentially could benefit from optical communication, considering their communications needs, the environments in which they would operate, and their notional size, weight, and power constraints. A set of 12 design reference missions was selected to represent the full range of potential missions. These design reference missions span the space of potential customer requirements, and encompass the wide range of applications that an optical ground segment might eventually be called upon to serve. The design reference missions encompass a range of orbit types, terminal sizes, and positions in the solar system that reveal the chief system performance variables of an optical ground segment, and may be used to enable assessments of the ability of alternative systems to meet various types of customer needs.

  8. Manned orbital systems concepts study. Book 3: Configurations for extended duration missions. [mission planning and project planning for space missions

    NASA Technical Reports Server (NTRS)

    1975-01-01

    Mission planning, systems analysis, and design concepts for the Space Shuttle/Spacelab system for extended manned operations are described. Topics discussed are: (1) payloads, (2) spacecraft docking, (3) structural design criteria, (4) life support systems, (5) power supplies, and (6) the role of man in long duration orbital operations. Also discussed are the assembling of large structures in space. Engineering drawings are included.

  9. Detection of Solar-like Oscillations, Observational Constraints, and Stellar Models for θ Cyg, the Brightest Star Observed By the Kepler Mission

    NASA Astrophysics Data System (ADS)

    Guzik, J. A.; Houdek, G.; Chaplin, W. J.; Smalley, B.; Kurtz, D. W.; Gilliland, R. L.; Mullally, F.; Rowe, J. F.; Bryson, S. T.; Still, M. D.; Antoci, V.; Appourchaux, T.; Basu, S.; Bedding, T. R.; Benomar, O.; Garcia, R. A.; Huber, D.; Kjeldsen, H.; Latham, D. W.; Metcalfe, T. S.; Pápics, P. I.; White, T. R.; Aerts, C.; Ballot, J.; Boyajian, T. S.; Briquet, M.; Bruntt, H.; Buchhave, L. A.; Campante, T. L.; Catanzaro, G.; Christensen-Dalsgaard, J.; Davies, G. R.; Doğan, G.; Dragomir, D.; Doyle, A. P.; Elsworth, Y.; Frasca, A.; Gaulme, P.; Gruberbauer, M.; Handberg, R.; Hekker, S.; Karoff, C.; Lehmann, H.; Mathias, P.; Mathur, S.; Miglio, A.; Molenda-Żakowicz, J.; Mosser, B.; Murphy, S. J.; Régulo, C.; Ripepi, V.; Salabert, D.; Sousa, S. G.; Stello, D.; Uytterhoeven, K.

    2016-11-01

    θ Cygni is an F3 spectral type magnitude V = 4.48 main-sequence star that was the brightest star observed by the original Kepler spacecraft mission. Short-cadence (58.8 s) photometric data using a custom aperture were first obtained during Quarter 6 (2010 June-September) and subsequently in Quarters 8 and 12-17. We present analyses of solar-like oscillations based on Q6 and Q8 data, identifying angular degree l = 0, 1, and 2 modes with frequencies of 1000-2700 μHz, a large frequency separation of 83.9 ± 0.4 μHz, and maximum oscillation amplitude at frequency ν max = 1829 ± 54 μHz. We also present analyses of new ground-based spectroscopic observations, which, combined with interferometric angular diameter measurements, give T eff = 6697 ± 78 K, radius 1.49 ± 0.03 R ⊙, [Fe/H] = -0.02 ± 0.06 dex, and log g = 4.23 ± 0.03. We calculate stellar models matching these constraints using the Yale Rotating Evolution Code and the Asteroseismic Modeling Portal. The best-fit models have masses of 1.35-1.39 M ⊙ and ages of 1.0-1.6 Gyr. θ Cyg’s T eff and log g place it cooler than the red edge of the γ Doradus instability region established from pre-Kepler ground-based observations, but just at the red edge derived from pulsation modeling. The pulsation models show γ Dor gravity modes driven by the convective blocking mechanism, with frequencies of 1-3 cycles per day (11 to 33 μHz). However, gravity modes were not seen in Kepler data; one signal at 1.776 cycles per day (20.56 μHz) may be attributable to a faint, possibly background, binary.

  10. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    As Space Shuttle Atlantis blasts off from Launch Pad 39A on mission STS-98, it lights up the nearby water. Billows of smoke and steam fill Launch Pad 39A. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle's robotic arm. Three spacewalks are required to complete the planned construction work during the 11- day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA's Space Shuttle program. The planned landing is at KSC Feb. 18 about 1 p.m. EST.

  11. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    As Space Shuttle Atlantis lifts off from Launch Pad 39A on mission STS-98, clouds of smoke and steam appear to surround it. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle's robotic arm. Three spacewalks are required to complete the planned construction work during the 11-day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA's Space Shuttle program. The planned landing is at KSC Feb. 18 about 1 p.m. EST.

  12. Potential anesthesia protocols for space exploration missions.

    PubMed

    Komorowski, Matthieu; Watkins, Sharmila D; Lebuffe, Gilles; Clark, Jonathan B

    2013-03-01

    In spaceflight beyond low Earth's orbit, medical conditions requiring surgery are of a high level of concern because of their potential impact on crew health and mission success. Whereas surgical techniques have been thoroughly studied in spaceflight analogues, the research focusing on anesthesia is limited. To provide safe anesthesia during an exploration mission will be a highly challenging task. The research objective is thus to describe specific anesthesia procedures enabling treatment of pre-identified surgical conditions. Among the medical conditions considered by the NASA Human Research Program Exploration Medical Capability element, those potentially necessitating anesthesia techniques have been identified. The most appropriate procedure for each condition is thoroughly discussed. The substantial cost of training time necessary to implement regional anesthesia is pointed out. Within general anesthetics, ketamine combines the unique advantages of preservation of cardiovascular stability, the protective airway reflexes, and spontaneous ventilation. Ketamine side effects have for decades tempered enthusiasm for its use, but recent developments in mitigation means broadened its indications. The extensive experience gathered in remote environments, with minimal equipment and occasionally by insufficiently trained care providers, confirms its high degree of safety. Two ketamine-based anesthesia protocols are described with their corresponding indications. They have been designed taking into account the physiological changes occurring in microgravity and the specific constraints of exploration missions. This investigation could not only improve surgical care during long-duration spaceflights, but may find a number of terrestrial applications in isolated or austere environments.

  13. Space Station Mission Planning System (MPS) development study. Volume 2

    NASA Technical Reports Server (NTRS)

    Klus, W. J.

    1987-01-01

    The process and existing software used for Spacelab payload mission planning were studied. A complete baseline definition of the Spacelab payload mission planning process was established, along with a definition of existing software capabilities for potential extrapolation to the Space Station. This information was used as a basis for defining system requirements to support Space Station mission planning. The Space Station mission planning concept was reviewed for the purpose of identifying areas where artificial intelligence concepts might offer substantially improved capability. Three specific artificial intelligence concepts were to be investigated for applicability: natural language interfaces; expert systems; and automatic programming. The advantages and disadvantages of interfacing an artificial intelligence language with existing FORTRAN programs or of converting totally to a new programming language were identified.

  14. Manned Space-Flight Experiments: Gemini V Mission

    NASA Technical Reports Server (NTRS)

    1966-01-01

    This compilation of papers constitutes an interim report on the results of experiments conducted during the Gemini V manned space flight. The results of experiments conducted on Gemini III and IV manned space flights have been published previously in a similar interim report, "Manned Space Flight Experiments Symposium, Gemini Missions III and IV," which is available upon request from MSC Experiments Program Office, Houston, Texas (Code EX, Attention of R. Kinard). The Gemini V mission provided the greatest opportunity to date for conducting experiments; the increased mission duration of eight days provided this added capability. The total mission experiment complement was seventeen. Five experiments were designed to obtain basic scientific knowledge, five were medical, and seven were technological and engineering in nature. Six of the experiments had flown previously on Gemini IV, and eleven were new. The results of the experiments, including real-time modification to preflight plans made necessary by abnormal spacecraft system operation, are presented.

  15. Analysis of Space Coherent LIDAR Wind Mission

    NASA Technical Reports Server (NTRS)

    Spiers, Gary D.

    1997-01-01

    An evaluation of the performance of a coherent Doppler lidar proposed by a team comprising the NASA Marshall Space Flight Center, Lockheed Martin Space Company, University of Wisconsin and Los Alamos National Laboratory to NASA's Earth System Science Pathfinder (ESSP) program was performed. The design went through several iterations and only the performance of the final design is summarized here.

  16. STS-55 Space Shuttle mission report

    NASA Technical Reports Server (NTRS)

    Fricke, Robert W., Jr.

    1993-01-01

    A summary of the Space Shuttle Payloads, Orbiter, External Tank, Solid Rocket Booster, Redesigned Solid Rocket Motor, and the Main Engine subsystems performance during the 55th flight of the Space Shuttle Program and the 14th flight of Columbia is presented.

  17. Logistics Needs for Potential Deep Space Mission Scenarios Post Asteroid Redirect Crewed Mission

    NASA Technical Reports Server (NTRS)

    Lopez, Pedro, Jr.; Shultz, Eric; Mattfeld, Bryan; Stromgren, Chel; Goodliff, Kandyce

    2015-01-01

    The Asteroid Redirect Mission (ARM) is currently being explored as the next step towards deep space human exploration, with the ultimate goal of reaching Mars. NASA is currently investigating a number of potential human exploration missions, which will progressively increase the distance and duration that humans spend away from Earth. Missions include extended human exploration in cis-lunar space which, as conceived, would involve durations of around 60 days, and human missions to Mars, which are anticipated to be as long as 1000 days. The amount of logistics required to keep the crew alive and healthy for these missions is significant. It is therefore important that the design and planning for these missions include accurate estimates of logistics requirements. This paper provides a description of a process and calculations used to estimate mass and volume requirements for crew logistics, including consumables, such as food, personal items, gasses, and liquids. Determination of logistics requirements is based on crew size, mission duration, and the degree of closure of the environmental control life support system (ECLSS). Details are provided on the consumption rates for different types of logistics and how those rates were established. Results for potential mission scenarios are presented, including a breakdown of mass and volume drivers. Opportunities for mass and volume reduction are identified, along with potential threats that could possibly increase requirements.

  18. Primary electric propulsion for future space missions

    NASA Technical Reports Server (NTRS)

    Byers, D. C.; Terdan, F. F.; Myers, I. T.

    1979-01-01

    A general methodology is presented which allows prediction of the overall characteristics of thrust systems employing electron-bombardment ion thrusters. Elements of the thrust system are defined and their characteristics presented in a parametric fashion. Two system approaches are evaluated where power management and control elements and thruster characteristics were substantially different. For an assumed system approach, the methodology presented predicts overall system properties, such as input power and mass, when major mission and thrust system parameters, such as trip time and specific impulse, are assumed.

  19. Reliable Multicore Processors for NASA Space Missions

    NASA Technical Reports Server (NTRS)

    Villalpando, Carlos; Rennels, David; Some, Raphael; Cabanas-Holmen, Manuel

    2011-01-01

    The current trend in commercial processors of moving to many cores (30 to100 and beyond) on a single die poses both an opportunity and a challenge for space based processing. 1 2 The opportunity is to leverage this trend for space application and thus provide an order of magnitude increase in onboard processing capability. The challenge is to provide the requisite reliability in an extremely challenging environment. In this paper, we will discuss the requirements for reliable space based multicore computing and approaches being explored to deliver this capability within NASA's extremely tight power, mass, and cost constraints.

  20. Game Changing: NASA's Space Launch System and Science Mission Design

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.

    2013-01-01

    NASA s Marshall Space Flight Center (MSFC) is directing efforts to build the Space Launch System (SLS), a heavy-lift rocket that will carry the Orion Multi-Purpose Crew Vehicle (MPCV) and other important payloads far beyond Earth orbit (BEO). Its evolvable architecture will allow NASA to begin with Moon fly-bys and then go on to transport humans or robots to distant places such as asteroids and Mars. Designed to simplify spacecraft complexity, the SLS rocket will provide improved mass margins and radiation mitigation, and reduced mission durations. These capabilities offer attractive advantages for ambitious missions such as a Mars sample return, by reducing infrastructure requirements, cost, and schedule. For example, if an evolved expendable launch vehicle (EELV) were used for a proposed mission to investigate the Saturn system, a complicated trajectory would be required - with several gravity-assist planetary fly-bys - to achieve the necessary outbound velocity. The SLS rocket, using significantly higher C3 energies, can more quickly and effectively take the mission directly to its destination, reducing trip time and cost. As this paper will report, the SLS rocket will launch payloads of unprecedented mass and volume, such as "monolithic" telescopes and in-space infrastructure. Thanks to its ability to co-manifest large payloads, it also can accomplish complex missions in fewer launches. Future analyses will include reviews of alternate mission concepts and detailed evaluations of SLS figures of merit, helping the new rocket revolutionize science mission planning and design for years to come.

  1. Preliminary analysis of space mission applications for electromagnetic launchers

    NASA Technical Reports Server (NTRS)

    Miller, L. A.; Rice, E. E.; Earhart, R. W.; Conlon, R. J.

    1984-01-01

    The technical and economic feasibility of using electromagnetically launched EML payloads propelled from the Earth's surface to LEO, GEO, lunar orbit, or to interplanetary space was assessed. Analyses of the designs of rail accelerators and coaxial magnetic accelerators show that each is capable of launching to space payloads of 800 KG or more. A hybrid launcher in which EML is used for the first 2 KM/sec followed by chemical rocket stages was also tested. A cost estimates study shows that one to two EML launches per day are needed to break even, compared to a four-stage rocket. Development models are discussed for: (1) Earth orbital missions; (2) lunar base supply mission; (3) solar system escape mission; (4) Earth escape missions; (5) suborbital missions; (6) electromagnetic boost missions; and (7) space-based missions. Safety factors, environmental impacts, and EML systems analysis are discussed. Alternate systems examined include electrothermal thrustors, an EML rocket gun; an EML theta gun, and Soviet electromagnetic accelerators.

  2. An Open Specification for Space Project Mission Operations Control Architectures

    NASA Technical Reports Server (NTRS)

    Hooke, A.; Heuser, W. R.

    1995-01-01

    An 'open specification' for Space Project Mission Operations Control Architectures is under development in the Spacecraft Control Working Group of the American Institute for Aeronautics and Astro- nautics. This architecture identifies 5 basic elements incorporated in the design of similar operations systems: Data, System Management, Control Interface, Decision Support Engine, & Space Messaging Service.

  3. Mission Peculiar Equipment Support Structure: A platform for space construction

    NASA Technical Reports Server (NTRS)

    Hill, Robert

    1987-01-01

    The Space Shuttle requires carriers to support payloads in the cargo bay. As a result, the Mission Peculiar Equipment Support Structure (MPESS) was designed to carry partial payloads aboard the shuttle. The efforts to customize the MPESS for the Experimental Assembly of Structure in EVA (EASE) and Assembly Concept for Construction of Erectable Space Structure (ACCESS) experiments are summarized.

  4. Precision Laser Development for Gravitational Wave Space Mission

    NASA Technical Reports Server (NTRS)

    Numata, Kenji; Camp, Jordan

    2011-01-01

    Optical fiber and semiconductor laser technologies have evolved dramatically over the last decade due to the increased demands from optical communications. We are developing a laser (master oscillator) and optical amplifier based on those technologies for interferometric space missions, such as the gravitational-wave mission LISA, and GRACE follow-on, by fully utilizing the mature wave-guided optics technologies. In space, where a simple and reliable system is preferred, the wave-guided components are advantageous over bulk, crystal-based, free-space laser, such as NPRO (Non-planar Ring Oscillator) and bulk-crystal amplifier, which are widely used for sensitive laser applications on the ground.

  5. Liftoff of Space Shuttle Endeavour on mission STS-97

    NASA Technical Reports Server (NTRS)

    2000-01-01

    Twin columns of flame spew from the solid rocket boosters lifting Space Shuttle Endeavour out of the smoke and steam and into the night sky. Liftoff occurred on time at 10:06:01 p.m. EST. The Shuttle and its five-member crew will deliver U.S. solar arrays to the International Space Station and be the first Shuttle crew to visit the Station'''s first resident crew. The 11-day mission includes three spacewalks. This marks the 101st mission in Space Shuttle history and the 25th night launch. Endeavour is expected to land at KSC Dec. 11 at 6:19 p.m. EST.

  6. Open source IPSEC software in manned and unmanned space missions

    NASA Astrophysics Data System (ADS)

    Edwards, Jacob

    Network security is a major topic of research because cyber attackers pose a threat to national security. Securing ground-space communications for NASA missions is important because attackers could endanger mission success and human lives. This thesis describes how an open source IPsec software package was used to create a secure and reliable channel for ground-space communications. A cost efficient, reproducible hardware testbed was also created to simulate ground-space communications. The testbed enables simulation of low-bandwidth and high latency communications links to experiment how the open source IPsec software reacts to these network constraints. Test cases were built that allowed for validation of the testbed and the open source IPsec software. The test cases also simulate using an IPsec connection from mission control ground routers to points of interest in outer space. Tested open source IPsec software did not meet all the requirements. Software changes were suggested to meet requirements.

  7. The International Space Station Photographed During the STS-112 Mission

    NASA Technical Reports Server (NTRS)

    2002-01-01

    This image of the International Space Station (ISS) was photographed by one of the crewmembers of the STS-112 mission following separation from the Space Shuttle Orbiter Atlantis as the orbiter pulled away from the ISS. The newly added S1 truss is visible in the center frame. The primary payloads of this mission, International Space Station Assembly Mission 9A, were the Integrated Truss Assembly S-1 (S-One), the Starboard Side Thermal Radiator Truss,and the Crew Equipment Translation Aid (CETA) cart to the ISS. The S1 truss provides structural support for the orbiting research facility's radiator panels, which use ammonia to cool the Station's complex power system. The S1 truss was attached to the S0 (S Zero) truss, which was launched on April 8, 2002 aboard the STS-110, and flows 637 pounds of anhydrous ammonia through three heat rejection radiators. The truss is 45-feet long, 15-feet wide, 10-feet tall, and weighs approximately 32,000 pounds. The CETA cart was attached to the Mobil Transporter and will be used by assembly crews on later missions. Manufactured by the Boeing Company in Huntington Beach, California, the truss primary structure was transferred to the Marshall Space Flight Center in February 1999 for hardware installations and manufacturing acceptance testing. The launch of the STS-112 mission occurred on October 7, 2002, and its 11-day mission ended on October 18, 2002.

  8. The International Space Station Photographed During STS-112 Mission

    NASA Technical Reports Server (NTRS)

    2002-01-01

    This image of the International Space Station (ISS) was photographed by one of the crewmembers of the STS-112 mission following separation from the Space Shuttle Orbiter Atlantis as the orbiter pulled away from the ISS. The primary payloads of this mission, International Space Station Assembly Mission 9A, were the Integrated Truss Assembly S1 (S-One), the Starboard Side Thermal Radiator Truss, and the Crew Equipment Translation Aid (CETA) cart to the ISS. The S1 truss provides structural support for the orbiting research facility's radiator panels, which use ammonia to cool the Station's complex power system. The S1 truss was attached to the S0 (S Zero) truss, which was launched on April 8, 2002 aboard the STS-110, and flows 637 pounds of anhydrous ammonia through three heat-rejection radiators. The truss is 45-feet long, 15-feet wide, 10-feet tall, and weighs approximately 32,000 pounds. The CETA cart was attached to the Mobil Transporter and will be used by assembly crews on later missions. Manufactured by the Boeing Company in Huntington Beach, California, the truss primary structure was transferred to the Marshall Space Flight Center in February 1999 for hardware installations and manufacturing acceptance testing. The launch of the STS-112 mission occurred on October 7, 2002, and its 11-day mission ended on October 18, 2002.

  9. Definition of technology development missions for early space stations: Large space structures

    NASA Technical Reports Server (NTRS)

    1983-01-01

    The testbed role of an early (1990-95) manned space station in large space structures technology development is defined and conceptual designs for large space structures development missions to be conducted at the space station are developed. Emphasis is placed on defining requirements and benefits of development testing on a space station in concert with ground and shuttle tests.

  10. Potential large missions enabled by NASA's space launch system

    NASA Astrophysics Data System (ADS)

    Stahl, H. Philip; Hopkins, Randall C.; Schnell, Andrew; Smith, David A.; Jackman, Angela; Warfield, Keith R.

    2016-07-01

    Large space telescope missions have always been limited by their launch vehicle's mass and volume capacities. The Hubble Space Telescope (HST) was specifically designed to fit inside the Space Shuttle and the James Webb Space Telescope (JWST) is specifically designed to fit inside an Ariane 5. Astrophysicists desire even larger space telescopes. NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. NASA's "Planning for the 2020 Decadal Survey" calls for a Habitable Exoplanet Imaging (HabEx) and a LUVOIR as well as Far-IR and an X-Ray Surveyor missions. Packaging larger space telescopes into existing launch vehicles is a significant engineering complexity challenge that drives cost and risk. NASA's planned Space Launch System (SLS), with its 8 or 10-m diameter fairings and ability to deliver 35 to 45-mt of payload to Sun-Earth-Lagrange-2, mitigates this challenge by fundamentally changing the design paradigm for large space telescopes. This paper reviews the mass and volume capacities of the planned SLS, discusses potential implications of these capacities for designing large space telescope missions, and gives three specific mission concept implementation examples: a 4-m monolithic off-axis telescope, an 8-m monolithic on-axis telescope and a 12-m segmented on-axis telescope.

  11. Potential Large Decadal Missions Enabled by Nasas Space Launch System

    NASA Technical Reports Server (NTRS)

    Stahl, H. Philip; Hopkins, Randall C.; Schnell, Andrew; Smith, David Alan; Jackman, Angela; Warfield, Keith R.

    2016-01-01

    Large space telescope missions have always been limited by their launch vehicle's mass and volume capacities. The Hubble Space Telescope (HST) was specifically designed to fit inside the Space Shuttle and the James Webb Space Telescope (JWST) is specifically designed to fit inside an Ariane 5. Astrophysicists desire even larger space telescopes. NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. NASA's "Planning for the 2020 Decadal Survey" calls for a Habitable Exoplanet Imaging (HabEx) and a LUVOIR as well as Far-IR and an X-Ray Surveyor missions. Packaging larger space telescopes into existing launch vehicles is a significant engineering complexity challenge that drives cost and risk. NASA's planned Space Launch System (SLS), with its 8 or 10-m diameter fairings and ability to deliver 35 to 45-mt of payload to Sun-Earth-Lagrange-2, mitigates this challenge by fundamentally changing the design paradigm for large space telescopes. This paper reviews the mass and volume capacities of the planned SLS, discusses potential implications of these capacities for designing large space telescope missions, and gives three specific mission concept implementation examples: a 4-m monolithic off-axis telescope, an 8-m monolithic on-axis telescope and a 12-m segmented on-axis telescope.

  12. Designing astrophysics missions for NASA's Space Launch System

    NASA Astrophysics Data System (ADS)

    Stahl, H. Philip; Hopkins, Randall C.; Schnell, Andrew; Smith, David Alan; Jackman, Angela; Warfield, Keith R.

    2016-10-01

    Large space telescope missions have always been limited by their launch vehicle's mass and volume capacities. The Hubble Space Telescope was specifically designed to fit inside the Space Shuttle and the James Webb Space Telescope was specifically designed to fit inside an Ariane 5. Astrophysicists desire even larger space telescopes. NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultrahigh-contrast spectroscopy and coronagraphy. Association of Universities for Research in Astronomy's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. NASA's "Planning for the 2020 Decadal Survey" calls for a Habitable Exoplanet Imaging (HabEx) and an LUVOIR as well as Far-IR and an X-ray Surveyor missions. Packaging larger space telescopes into existing launch vehicles is a significant engineering complexity challenge that drives cost and risk. NASA's planned Space Launch System (SLS), with its 8- or 10-m diameter fairings and ability to deliver 35 to 45 mt of payload to Sun-Earth-Lagrange-2, mitigates this challenge by fundamentally changing the design paradigm for large space telescopes. This paper introduces the mass and volume capacities of the planned SLS, provides a simple mass allocation recipe for designing large space telescope missions to this capacity, and gives three specific mission concept implementation examples: a 4-m monolithic off-axis telescope, an 8-m monolithic on-axis telescope, and a 12-m segmented on-axis telescope.

  13. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    KENNEDY SPACE CENTER, Fla. -- Trailing a column of flame-bright smoke, Space Shuttle Atlantis clears the lightning rod on Launch Pad 39A as it climbs into the early evening sky. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle'''s robotic arm. Three spacewalks are required to complete the planned construction work during the 11-day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA'''s Space Shuttle program. The planned landing is at KSC Feb. 18 about 1:00 p.m. EST.

  14. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    KENNEDY SPACE CENTER, Fla. -- Space Shuttle Atlantis leaps up from the flames and smoke behind it as it lifts off from Launch Pad 39A into the early evening sky. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle'''s robotic arm. Three spacewalks are required to complete the planned construction work during the 11-day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA'''s Space Shuttle program. The planned landing is at KSC Feb. 18 about 1:00 p.m. EST.

  15. TAMU: A New Space Mission Operations Paradigm

    NASA Technical Reports Server (NTRS)

    Meshkat, Leila; Ruszkowski, James; Haensly, Jean; Pennington, Granvil A.; Hogle, Charles

    2011-01-01

    The Transferable, Adaptable, Modular and Upgradeable (TAMU) Flight Production Process (FPP) is a model-centric System of System (SoS) framework which cuts across multiple organizations and their associated facilities, that are, in the most general case, in geographically diverse locations, to develop the architecture and associated workflow processes for a broad range of mission operations. Further, TAMU FPP envisions the simulation, automatic execution and re-planning of orchestrated workflow processes as they become operational. This paper provides the vision for the TAMU FPP paradigm. This includes a complete, coherent technique, process and tool set that result in an infrastructure that can be used for full lifecycle design and decision making during any flight production process. A flight production process is the process of developing all products that are necessary for flight.

  16. Achieving Supportability on Exploration Missions with In-Space Servicing

    NASA Technical Reports Server (NTRS)

    Bacon, Charles; Pellegrino, Joseph; McGuire, Jill; Henry, Ross; DeWeese, Keith; Reed, Benjamin; Aranyos, Thomas

    2015-01-01

    One of the long-term exploration goals of NASA is manned missions to Mars and other deep space robotic exploration. These missions would include sending astronauts along with scientific equipment to the surface of Mars for extended stay and returning the crew, science data and surface samples, and equipment to Earth. In order to achieve this goal, multiple precursor missions are required that would launch the crew, crew habitats, return vehicles and destination systems into space. Some of these payloads would then rendezvous in space for the trip to Mars, while others would be sent directly to the Martian surface. To support such an ambitious mission architecture, NASA must reduce cost, simplify logistics, re-use and or re-purpose flight hardware, and minimize resources needed for refurbishment. In-space servicing is a means to achieving these goals. By designing a mission architecture that relies on the concept of in-space servicing (robotic and manned), maximum supportability can be achieved.

  17. Development of a figure-of-merit for space missions

    NASA Technical Reports Server (NTRS)

    Preiss, Bruce; Pan, Thomas; Ramohalli, Kumar

    1991-01-01

    The concept of a quantitative figure-of-merit (FOM) to evaluate different and competing options for space missions is further developed. Over six hundred individual factors are considered. These range from mission orbital mechanics to in-situ resource utilization (ISRU/ISMU) plants. The program utilizes a commercial software package for synthesis and visual display; the details are completely developed in-house. Historical FOM's are derived for successful space missions such as the Surveyor, Voyager, Apollo, etc. A cost FOM is also mentioned. The bulk of this work is devoted to one specific example of Mars Sample Return (MSR). The program is flexible enough to accommodate a variety of evolving technologies. Initial results show that the FOM for sample return is a function of the mass returned to LEO, and that missions utilizing ISRU/ISMU are far more cost effective than those that rely on all earth-transported resources.

  18. Voice loops as coordination aids in space shuttle mission control.

    PubMed

    Patterson, E S; Watts-Perotti, J; Woods, D D

    1999-01-01

    Voice loops, an auditory groupware technology, are essential coordination support tools for experienced practitioners in domains such as air traffic management, aircraft carrier operations and space shuttle mission control. They support synchronous communication on multiple channels among groups of people who are spatially distributed. In this paper, we suggest reasons for why the voice loop system is a successful medium for supporting coordination in space shuttle mission control based on over 130 hours of direct observation. Voice loops allow practitioners to listen in on relevant communications without disrupting their own activities or the activities of others. In addition, the voice loop system is structured around the mission control organization, and therefore directly supports the demands of the domain. By understanding how voice loops meet the particular demands of the mission control environment, insight can be gained for the design of groupware tools to support cooperative activity in other event-driven domains.

  19. Voice loops as coordination aids in space shuttle mission control

    NASA Technical Reports Server (NTRS)

    Patterson, E. S.; Watts-Perotti, J.; Woods, D. D.

    1999-01-01

    Voice loops, an auditory groupware technology, are essential coordination support tools for experienced practitioners in domains such as air traffic management, aircraft carrier operations and space shuttle mission control. They support synchronous communication on multiple channels among groups of people who are spatially distributed. In this paper, we suggest reasons for why the voice loop system is a successful medium for supporting coordination in space shuttle mission control based on over 130 hours of direct observation. Voice loops allow practitioners to listen in on relevant communications without disrupting their own activities or the activities of others. In addition, the voice loop system is structured around the mission control organization, and therefore directly supports the demands of the domain. By understanding how voice loops meet the particular demands of the mission control environment, insight can be gained for the design of groupware tools to support cooperative activity in other event-driven domains.

  20. The Challenge of Configuring Model-Based Space Mission Planners

    NASA Technical Reports Server (NTRS)

    Frank, Jeremy D.; Clement, Bradley J.; Chachere, John M.; Smith, Tristan B.; Swanson, Keith J.

    2011-01-01

    Mission planning is central to space mission operations, and has benefited from advances in model-based planning software. Constraints arise from many sources, including simulators and engineering specification documents, and ensuring that constraints are correctly represented in the planner is a challenge. As mission constraints evolve, planning domain modelers need help with modeling constraints efficiently using the available source data, catching errors quickly, and correcting the model. This paper describes the current state of the practice in designing model-based mission planning tools, the challenges facing model developers, and a proposed Interactive Model Development Environment (IMDE) to configure mission planning systems. We describe current and future technology developments that can be integrated into an IMDE.

  1. First Multi-Planet System Discovered by Kepler

    NASA Video Gallery

    NASA's Kepler Mission has discovered the first confirmed planetary system with more than one planet transiting the same star. The announcement of the discovery of the two planets, Kepler 9b and 9c,...

  2. Heritage Systems Engineering Lessons from NASA Deep Space Missions

    NASA Technical Reports Server (NTRS)

    Barley, Bryan; Newhouse, Marilyn; Clardy, Dennon

    2010-01-01

    In the design and development of complex spacecraft missions, project teams frequently assume the use of advanced technology systems or heritage systems to enable a mission or reduce the overall mission risk and cost. As projects proceed through the development life cycle, increasingly detailed knowledge of the advanced and heritage systems within the spacecraft and mission environment identifies unanticipated technical issues. Resolving these issues often results in cost overruns and schedule impacts. The National Aeronautics and Space Administration (NASA) Discovery & New Frontiers (D&NF) Program Office at Marshall Space Flight Center (MSFC) recently studied cost overruns and schedule delays for 5 missions. The goal was to identify the underlying causes for the overruns and delays, and to develop practical mitigations to assist the D&NF projects in identifying potential risks and controlling the associated impacts to proposed mission costs and schedules. The study found that optimistic hardware/software inheritance and technology readiness assumptions caused cost and schedule growth for all five missions studied. The cost and schedule growth was not found to be the result of technical hurdles requiring significant technology development. The projects institutional inheritance and technology readiness processes appear to adequately assess technology viability and prevent technical issues from impacting the final mission success. However, the processes do not appear to identify critical issues early enough in the design cycle to ensure project schedules and estimated costs address the inherent risks. In general, the overruns were traceable to: an inadequate understanding of the heritage system s behavior within the proposed spacecraft design and mission environment; an insufficient level of development experience with the heritage system; or an inadequate scoping of the systemwide impacts necessary to implement an advanced technology for space flight applications

  3. A multinational Mars mission for the International Space University

    NASA Technical Reports Server (NTRS)

    Mendell, Wendell W.

    1992-01-01

    The International Space University's 1991 design project activity has yielded a report on the organization and implementation of a multinational program for manned exploration of Mars; the organization encompasses a political as well as a technical component. This International Manned Mission employs an artificial-gravity spacecraft with nuclear-electric propulsion for interplanetary transfer. An unmanned cargo mission precedes the piloted flights to increase the mass deliverable to Mars, as well as to serve as a testbed for interplanetary vehicle design.

  4. Planning for Crew Exercise for Deep Space Mission Scenarios

    NASA Technical Reports Server (NTRS)

    Moore, E. Cherice; Ryder, Jeff

    2015-01-01

    Exercise which is necessary for maintaining crew health on-orbit and preparing the crew for return to 1G can be challenging to incorporate into spaceflight vehicles. Deep space missions will require further understanding of the physiological response to microgravity, understanding appropriate mitigations, and designing the exercise systems to effectively provide mitigations, and integrating effectively into vehicle design with a focus to support planned mission scenarios. Recognizing and addressing the constraints and challenges can facilitate improved vehicle design and exercise system incorporation.

  5. Risks of radiation cataracts from interplanetary space missions.

    PubMed

    Lett, J T; Lee, A C; Cox, A B

    1994-11-01

    Recognition of the human risks from radiation exposure during manned missions in deep space has been fostered by international co-operation; interagency collaboration is facilitating their evaluation. Further co-operation can lead, perhaps by the end of this decade, to an evaluation of one of the three major risks, namely radiation cataractogenesis, sufficient for use in the planning of the manned mission to Mars.

  6. Radiation effects on microelectronics and future space missions

    NASA Technical Reports Server (NTRS)

    Patterson, Jeffrey D.

    2003-01-01

    This paper briefly reviews the three basic radiation effect mechanisms, and how they interrupt the functionality of currently available non-volatile memory technologies. This paper also presents a very general overview of the radiation environments expected in future space exploration missions. Unfortunately, these environments will be very harsh, from a radiation standpoint, and thus a significant effort is required to develop non-volatile technologies that will meet future mission requirements.

  7. Fiber optic rotation sensor for long lifetime space missions

    NASA Technical Reports Server (NTRS)

    Dorsky, L.; Bartman, R.; Lehman, D.; Salomon, P.; Freier, L.; Laznicka, O.; Magee, R.; Murphy, J.

    1992-01-01

    The present F-O rotation sensors (FORS) are all-solid state devices for measuring rotations and rotation rates in inertial space that may reach the 0.003 deg/hr (1-sigma) accuracies required for NASA's Saturn-orbiting Cassini mission. Attention is presently given to the mission, inertial reference unit, and FORS instrument optoelectronic component requirements envisioned for such spacecraft applications.

  8. Helios mission support. [Deep Space Network

    NASA Technical Reports Server (NTRS)

    Goodwin, P. S.; Burke, E. S.; Rockwell, G. M.

    1977-01-01

    Deep Space Network coverage of Helios-1 and Helios-2 from Feb. 1 through Apr. 15, 1977 is presented in tabular form. Mark III data system (MDS) performance and station modifications for MDS configuration are discussed. Cross support for Helios operations by DSN and STDN is described and their downlink performances compared.

  9. Planning for Crew Exercise for Future Deep Space Mission Scenarios

    NASA Technical Reports Server (NTRS)

    Moore, Cherice; Ryder, Jeff

    2015-01-01

    Providing the necessary exercise capability to protect crew health for deep space missions will bring new sets of engineering and research challenges. Exercise has been found to be a necessary mitigation for maintaining crew health on-orbit and preparing the crew for return to earth's gravity. Health and exercise data from Apollo, Space Lab, Shuttle, and International Space Station missions have provided insight into crew deconditioning and the types of activities that can minimize the impacts of microgravity on the physiological systems. The hardware systems required to implement exercise can be challenging to incorporate into spaceflight vehicles. Exercise system design requires encompassing the hardware required to provide mission specific anthropometrical movement ranges, desired loads, and frequencies of desired movements as well as the supporting control and monitoring systems, crew and vehicle interfaces, and vibration isolation and stabilization subsystems. The number of crew and operational constraints also contribute to defining the what exercise systems will be needed. All of these features require flight vehicle mass and volume integrated with multiple vehicle systems. The International Space Station exercise hardware requires over 1,800 kg of equipment and over 24 m3 of volume for hardware and crew operational space. Improvements towards providing equivalent or better capabilities with a smaller vehicle impact will facilitate future deep space missions. Deep space missions will require more understanding of the physiological responses to microgravity, understanding appropriate mitigations, designing the exercise systems to provide needed mitigations, and integrating effectively into vehicle design with a focus to support planned mission scenarios. Recognizing and addressing the constraints and challenges can facilitate improved vehicle design and exercise system incorporation.

  10. Reconfigurable Computing Concepts for Space Missions: Universal Modular Spares

    NASA Technical Reports Server (NTRS)

    Patrick, M. Clinton

    2007-01-01

    Computing hardware for control, data collection, and other purposes will prove many times over crucial resources in NASA's upcoming space missions. Ability to provide these resources within mission payload requirements, with the hardiness to operate for extended periods under potentially harsh conditions in off-World environments, is daunting enough without considering the possibility of doing so with conventional electronics. This paper examines some ideas and options, and proposes some initial approaches, for logical design of reconfigurable computing resources offering true modularity, universal compatibility, and unprecedented flexibility to service all forms and needs of mission infrastructure.

  11. Nano-Satellite Secondary Spacecraft on Deep Space Missions

    NASA Technical Reports Server (NTRS)

    Klesh, Andrew T.; Castillo-Rogez, Julie C.

    2012-01-01

    NanoSat technology has opened Earth orbit to extremely low-cost science missions through a common interface that provides greater launch accessibility. They have also been used on interplanetary missions, but these missions have used one-off components and architectures so that the return on investment has been limited. A natural question is the role that CubeSat-derived NanoSats could play to increase the science return of deep space missions. We do not consider single instrument nano-satellites as likely to complete entire Discovery-class missions alone,but believe that nano-satellites could augment larger missions to significantly increase science return. The key advantages offered by these mini-spacecrafts over previous planetary probes is the common availability of advanced subsystems that open the door to a large variety of science experiments, including new guidance, navigation and control capabilities. In this paper, multiple NanoSat science applications are investigated, primarily for high risk/high return science areas. We also address the significant challenges and questions that remain as obstacles to the use of nano-satellites in deep space missions. Finally, we provide some thoughts on a development roadmap toward interplanetary usage of NanoSpacecraft.

  12. Impact of lunar and planetary missions on the space station

    NASA Technical Reports Server (NTRS)

    1984-01-01

    The impacts upon the growth space station of several advanced planetary missions and a populated lunar base are examined. Planetary missions examined include sample returns from Mars, the Comet Kopff, the main belt asteroid Ceres, a Mercury orbiter, and a saturn orbiter with multiple Titan probes. A manned lunar base build-up scenario is defined, encompassing preliminary lunar surveys, ten years of construction, and establishment of a permanent 18 person facility with the capability to produce oxygen propellant. The spacecraft mass departing from the space station, mission Delta V requirements, and scheduled departure date for each payload outbound from low Earth orbit are determined for both the planetary missions and for the lunar base build-up. Large aerobraked orbital transfer vehicles (OTV's) are used. Two 42 metric ton propellant capacity OTV's are required for each the the 68 lunar sorties of the base build-up scenario. The two most difficult planetary missions (Kopff and Ceres) also require two of these OTV's. An expendable lunar lander and ascent stage and a reusable lunar lander which uses lunar produced oxygen are sized to deliver 18 metric tons to the lunar surface. For the lunar base, the Space Station must hangar at least two non-pressurized OTV's, store 100 metric tons of cryogens, and support an average of 14 OTV launch, return, and refurbishment cycles per year. Planetary sample return missions require a dedicated quarantine module.

  13. Impact of ηEarth on the Capabilities of Affordable Space Missions to Detect Biosignatures on Extrasolar Planets

    NASA Astrophysics Data System (ADS)

    Léger, Alain; Defrère, Denis; Malbet, Fabien; Labadie, Lucas; Absil, Olivier

    2015-08-01

    We present an analytic model to estimate the capabilities of space missions dedicated to the search for biosignatures in the atmosphere of rocky planets located in the habitable zone of nearby stars. Relations between performance and mission parameters, such as mirror diameter, distance to targets, and radius of planets, are obtained. Two types of instruments are considered: coronagraphs observing in the visible, and nulling interferometers in the thermal infrared. Missions considered are: single-pupil coronagraphs with a 2.4 m primary mirror, and formation-flying interferometers with 4 × 0.75 m collecting mirrors. The numbers of accessible planets are calculated as a function of ηEarth. When Kepler gives its final estimation for ηEarth, the model will permit a precise assessment of the potential of each instrument. Based on current estimations, ηEarth = 10% around FGK stars and 50% around M stars, the coronagraph could study in spectroscopy only ∼1.5 relevant planets, and the interferometer ∼14.0. These numbers are obtained under the major hypothesis that the exozodiacal light around the target stars is low enough for each instrument. In both cases, a prior detection of planets is assumed and a target list established. For the long-term future, building both types of spectroscopic instruments, and using them on the same targets, will be the optimal solution because they provide complementary information. But as a first affordable space mission, the interferometer looks the more promising in terms of biosignature harvest.

  14. Space missions to the exoplanets: Will they ever be possible

    NASA Astrophysics Data System (ADS)

    Genta, Giancarlo

    There is no doubt that the discovery of exoplanets has made interstellar space mission much more interesting than they were in the past. The possible discovery of a terrestrial type plane at a reasonable distance will give a strong impulse in this direction. However, there are doubts that such long range space mission will ever become feasible at all and, in case they will be, it is impossible to forecast a timeframe for them. At present, precursor interstellar missions are planned, but they fall way short from yielding interesting information about exoplanets, except perhaps in the case of missions to the focal line of the Sun’s gravitational lens, whose usefulness in this context is still to be demonstrated. They are anyway an essential step in the roadmap toward interstellar missions. Often the difficulties linked with interstellar missions are considered as related with the huge quantity of energy required for reaching the target star system within a reasonable timeframe. While this may well be a showstopper, it is not the only problem to be solved to make them possible. Two other issues are those linked with the probe’s autonomy and the telecommunications required to transmit large quantities of information at those distances. Missions to the exoplanets may be subdivided in the following categories: 1) robotic missions to the destination system, including flybys; 2) robotic missions including landing on an exoplanet; 3) robotic sample return missions; 4) human missions. The main problem to be solved for missions of type 1 is linked with propulsion and with energy availability, while autonomy (artificial intelligence) and telecommunication problems are more or less manageable with predictable technologies. Missions of type 2 are more demanding for what propulsion is concerned, but above all require a much larger artificial intelligence and also will generate a large amount of data, whose transmission back to Earth may become a problem. The suggestion of

  15. Space Mission Concept Development Using Concept Maturity Levels

    NASA Technical Reports Server (NTRS)

    Wessen, Randii R.; Borden, Chester; Ziemer, John; Kwok, Johnny

    2013-01-01

    Over the past five years, pre-project formulation experts at the Jet Propulsion Laboratory (JPL) has developed and implemented a method for measuring and communicating the maturity of space mission concepts. Mission concept development teams use this method, and associated tools, prior to concepts entering their Formulation Phases (Phase A/B). The organizing structure is Concept Maturity Level (CML), which is a classification system for characterizing the various levels of a concept's maturity. The key strength of CMLs is the ability to evolve mission concepts guided by an incremental set of assessment needs. The CML definitions have been expanded into a matrix form to identify the breadth and depth of analysis needed for a concept to reach a specific level of maturity. This matrix enables improved assessment and communication by addressing the fundamental dimensions (e.g., science objectives, mission design, technical risk, project organization, cost, export compliance, etc.) associated with mission concept evolution. JPL's collaborative engineering, dedicated concept development, and proposal teams all use these and other CML-appropriate design tools to advance their mission concept designs. This paper focuses on mission concept's early Pre-Phase A represented by CMLs 1- 4. The scope was limited due to the fact that CMLs 5 and 6 are already well defined based on the requirements documented in specific Announcement of Opportunities (AO) and Concept Study Report (CSR) guidelines, respectively, for competitive missions; and by NASA's Procedural Requirements NPR 7120.5E document for Projects in their Formulation Phase.

  16. Spacecraft and mission design for the SpaceNuclear PowerSystem Reference Mission

    NASA Technical Reports Server (NTRS)

    Deininger, William D.; Vondra, Robert J.

    1987-01-01

    The design and performance of a spacecraft employing arcjet nuclear electric propulsion, suitable for use in the Space Nuclear Power System Reference Mission, are outlined. The vehicle design is based on a 92 kW ammonia arcjet system operating at an I(sp) of 1050 s and an efficiency of 45 percent. The arcjet/gimbal system, power processing unit, and propellant feed-system are described. A 100 kW(e) space nuclear power system is assumed and the spacecraft mass is baselined at 5250 kg excluding the propellant, propellent feed system, and integrated chemical boost engine. A radiation/arcjet efflux diagnostics package is included in the performance analysis. Three mission scenarios are described and are capable of demonstrating the full capability of the space nuclear power source. The missions considered include power system deployment to possible SDI platform orbits and a spacecraft storage mission to an orbit of three times geosynchronous (GEO) with return to GEO corresponding to Delta V's between 7400 m/s, and 7900 m/s. This spacecraft meets the Reference Mission constraint of low developmental risk and is scaleable to power levels projected for future space platforms.

  17. NASA'S Space Launch System: Opening Opportunities for Mission Design

    NASA Technical Reports Server (NTRS)

    Robinson, Kimberly F.; Hefner, Keith; Hitt, David

    2015-01-01

    Designed to meet the stringent requirements of human exploration missions into deep space and to Mars, NASA's Space Launch System (SLS) vehicle represents a unique new launch capability opening new opportunities for mission design. While SLS's super-heavy launch vehicle predecessor, the Saturn V, was used for only two types of missions - launching Apollo spacecraft to the moon and lofting the Skylab space station into Earth orbit - NASA is working to identify new ways to use SLS to enable new missions or mission profiles. In its initial Block 1 configuration, capable of launching 70 metric tons (t) to low Earth orbit (LEO), SLS is capable of not only propelling the Orion crew vehicle into cislunar space, but also delivering small satellites to deep space destinations. With a 5-meter (m) fairing consistent with contemporary Evolved Expendable Launch Vehicles (EELVs), the Block 1 configuration can also deliver science payloads to high-characteristic-energy (C3) trajectories to the outer solar system. With the addition of an upper stage, the Block 1B configuration of SLS will be able to deliver 105 t to LEO and enable more ambitious human missions into the proving ground of space. This configuration offers opportunities for launching co-manifested payloads with the Orion crew vehicle, and a new class of secondary payloads, larger than today's cubesats. The evolved configurations of SLS, including both Block 1B and the 130 t Block 2, also offer the capability to carry 8.4- or 10-m payload fairings, larger than any contemporary launch vehicle. With unmatched mass-lift capability, payload volume, and C3, SLS not only enables spacecraft or mission designs currently impossible with contemporary EELVs, it also offers enhancing benefits, such as reduced risk and operational costs associated with shorter transit time to destination and reduced risk and complexity associated with launching large systems either monolithically or in fewer components. As this paper will

  18. Hubble Space Telescope observations of the Kepler-field cluster NGC 6819 - I. The bottom of the white dwarf cooling sequence

    NASA Astrophysics Data System (ADS)

    Bedin, L. R.; Salaris, M.; Anderson, J.; Cassisi, S.; Milone, A. P.; Piotto, G.; King, I. R.; Bergeron, P.

    2015-04-01

    We use Hubble Space Telescope (HST) to reach the end of the white dwarf (WD) cooling sequence (CS) in the solar-metallicity open cluster NGC 6819. Our photometry and completeness tests show a sharp drop in the number of WDs along the CS at magnitudes fainter than mF606W = 26.050 ± 0.075. This implies an age of 2.25 ± 0.20 Gyr, consistent with the age of 2.25 ± 0.30 Gyr obtained from fits to the main-sequence turn-off. The use of different WD cooling models and initial-final-mass relations have a minor impact the WD age estimate, at the level of ˜0.1 Gyr. As an important by-product of this investigation we also release, in electronic format, both the catalogue of all the detected sources and the atlases of the region (in two filters). Indeed, this patch of sky studied by HST (of size ˜70 arcmin2) is entirely within the main Kepler-mission field, so the high-resolution images and deep catalogues will be particularly useful.

  19. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    Like 10,000 fireworks going off at once, Space Shuttle Atlantis roars into the moonlit sky while clouds of steam and smoke cascade behind. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle's robotic arm. Three spacewalks are required to complete the planned construction work during the 11-day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA's Space Shuttle program. The planned landing is at KSC Feb. 18 about 1:39 p.m. EST.

  20. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    Space Shuttle Atlantis roars into the moonlit sky while clouds of steam and smoke cascade behind. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle's robotic arm. Three spacewalks are required to complete the planned construction work during the 11- day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA's Space Shuttle program. The planned landing is at KSC Feb. 18 about 1:39 p.m. EST.

  1. Liftoff of Space Shuttle Atlantis on mission STS-98

    NASA Technical Reports Server (NTRS)

    2001-01-01

    Clouds of smoke and steam roll out from the launch pad as Space Shuttle Atlantis roars into the moonlit sky. Liftoff occurred at 6:13:02 p.m. EST. Along with a crew of five, Atlantis is carrying the U.S. Laboratory Destiny, a key module in the growth of the Space Station. Destiny will be attached to the Unity node on the Space Station using the Shuttle's robotic arm. Three spacewalks are required to complete the planned construction work during the 11-day mission. This mission marks the seventh Shuttle flight to the Space Station, the 23rd flight of Atlantis and the 102nd flight overall in NASA's Space Shuttle program. The planned landing is at KSC Feb. 18 about 1:39 p.m. EST.

  2. Habitability issues in long duration undersea and space missions

    NASA Technical Reports Server (NTRS)

    Parker, J. F., Jr.; Every, M. G.

    1972-01-01

    The report reviews a number of studies in the area of habitability. Emphasis was placed on extracting from these studies that information most relevant to any long-term mission in confinement. It is concluded that, whereas the basic laws of habitability are known, there is much yet to be learned concerning development of social structures in small groups in relative isolation, planning for necessary hygiene needs, development of proper work spaces, and construction of internal and external communications systems. With respect to testing for habitability and the documentation of habitability principles, the space program was found to be considerably more advanced than was the program for undersea missions.

  3. Electromagnetically launched micro spacecraft for space science missions

    NASA Technical Reports Server (NTRS)

    Jones, Ross M.

    1988-01-01

    This paper presents the concept of using very small spacecraft launched by an electromagnetic launcher located in low earth orbit to perform space science missions. This paper includes a discussion of flight time versus distance performance, potential missions, electromagnetic launchers, micro spacecraft concepts, high G technology and a conceptual launcher design. It is suggested that the present is an especially good time to investigate the subject concept due to the current launch vehicle crisis for space science, and due to the large amounts of resources that the SDIO is spending on the development of the technology for electromagnetic launchers and projectiles.

  4. Space salvage - A report on Shuttle mission STS 51-A

    NASA Technical Reports Server (NTRS)

    Hauck, F. H.; Gardner, D. A.

    1985-01-01

    The success of the Space Shuttle Orbiter and Manned Maneuvering Unit (MMU) in the rendezvous and capture of the Westar and Palapa satellites was largely attributable to the availability and fidelity of numerous simulators, which facilitated real time development and verification of satellite rescue procedures and hardware. This complex Space Shuttle mission, STS 51-A, was developed and executed in only 8 months; by contrast, the Solar Maximum repair mission was developed over a period of three years. Attention is presently given to Orbiter sensors, satellite night stationkeeping, satellite stabilization tasks, MMU tasks, and preparatory simulations.

  5. Space Mission Operations Ground Systems Integration Customer Service

    NASA Technical Reports Server (NTRS)

    Roth, Karl

    2014-01-01

    The facility, which is now the Huntsville Operations Support Center (HOSC) at Marshall Space Flight Center in Huntsville, AL, has provided continuous space mission and related services for the space industry since 1961, from Mercury Redstone through the International Space Station (ISS). Throughout the long history of the facility and mission support teams, the HOSC has developed a stellar customer support and service process. In this era, of cost cutting, and providing more capability and results with fewer resources, space missions are looking for the most efficient way to accomplish their objectives. One of the first services provided by the facility was fax transmission of documents to, then, Cape Canaveral in Florida. The headline in the Marshall Star, the newspaper for the newly formed Marshall Space Flight Center, read "Exact copies of Documents sent to Cape in 4 minutes." The customer was Dr. Wernher von Braun. Currently at the HOSC we are supporting, or have recently supported, missions ranging from simple ISS payloads requiring little more than "bentpipe" telemetry access, to a low cost free-flyer Fast, Affordable, Science and Technology Satellite (FASTSAT), to a full service ISS payload Alpha Magnetic Spectrometer 2 (AMS2) supporting 24/7 operations at three operations centers around the world with an investment of over 2 billion dollars. The HOSC has more need and desire than ever to provide fast and efficient customer service to support these missions. Here we will outline how our customer-centric service approach reduces the cost of providing services, makes it faster and easier than ever for new customers to get started with HOSC services, and show what the future holds for our space mission operations customers. We will discuss our philosophy concerning our responsibility and accessibility to a mission customer as well as how we deal with the following issues: initial contact with a customer, reducing customer cost, changing regulations and security

  6. Radiation protection guidelines for space missions

    SciTech Connect

    Fry, R.J.M.

    1987-01-01

    The original recommendations for radiation protection guidelines were made by the National Academy of Sciences in 1970. Since that time the US crews have become more diverse in their makeup and much has been learned about both radiation-induced cancer and other late effects. While far from adequate there is now some understanding of the risks that high-Z and -energy (HZE) particles pose. For these reasons it was time to reconsider the radiation protection guidelines for space workers. This task was undertaken recently by National Council on Radiation Protection (NCRP). 42 refs., 2 figs., 9 tabs.

  7. Micro-Flying Robotics in Space Missions

    NASA Technical Reports Server (NTRS)

    Bardina, Jorge; Thirumalainambi, Rajkumar

    2005-01-01

    The Columbia Accident Investigation Board issued a major recommendation to NASA. Prior to return to flight, NASA should develop and implement a comprehensive inspection plan to determine the structural integrity of all Reinforced Carbon-Carbon (RCC) system components. This inspection plan should take advantage of advanced non-destructive inspection technology. This paper describes a non-intrusive technology with a micro-flying robot to continuously monitor inside a space vehicle for any stress related fissures, cracks and foreign material embedded in walls, tubes etc.

  8. Johannes Kepler

    NASA Astrophysics Data System (ADS)

    Bialas, Volker

    Johannes Kepler (1571 - 1630) gilt zurecht als einer der bedeutendsten Mathematiker und Astronomen der frühen Neuzeit, doch wurde das Philosophische in seinem Werk bislang kaum in angemessener Weise gewürdigt. Volker Bialas legt eine fundierte und anregende Einführung in Leben, Werk und Weltanschauung Keplers vor und setzt dabei durch die Akzentuierung des philosophisch-ganzheitlichen Denkens bewußt einen Kontrapunkt zum herkömmlichen Kepler-Bild.

  9. Photometric analysis in the Kepler Science Operations Center pipeline

    NASA Astrophysics Data System (ADS)

    Twicken, Joseph D.; Clarke, Bruce D.; Bryson, Stephen T.; Tenenbaum, Peter; Wu, Hayley; Jenkins, Jon M.; Girouard, Forrest; Klaus, Todd C.

    2010-07-01

    We describe the Photometric Analysis (PA) software component and its context in the Kepler Science Operations Center (SOC) Science Processing Pipeline. The primary tasks of this module are to compute the photometric flux and photocenters (centroids) for over 160,000 long cadence (~thirty minute) and 512 short cadence (~one minute) stellar targets from the calibrated pixels in their respective apertures. We discuss science algorithms for long and short cadence PA: cosmic ray cleaning; background estimation and removal; aperture photometry; and flux-weighted centroiding. We discuss the end-to-end propagation of uncertainties for the science algorithms. Finally, we present examples of photometric apertures, raw flux light curves, and centroid time series from Kepler flight data. PA light curves, centroid time series, and barycentric timestamp corrections are exported to the Multi-mission Archive at Space Telescope [Science Institute] (MAST) and are made available to the general public in accordance with the NASA/Kepler data release policy.

  10. THE KEPLER CLUSTER STUDY: STELLAR ROTATION IN NGC 6811

    SciTech Connect

    Meibom, Soeren; Latham, David W.; Dupree, Andrea K.; Furesz, Gabor; Szentgyorgyi, Andrew H.; Buchhave, Lars A.; Barnes, Sydney A.; Batalha, Natalie; Borucki, William J.; Koch, David G.; Jenkins, Jon; Van Cleve, Jeffrey; Haas, Michael R.; Bryson, Stephen T.; Basri, Gibor; Walkowicz, Lucianne M.; Janes, Kenneth A.; Clarke, Bruce D.; Twicken, Joseph D.; Quintana, Elisa V.

    2011-05-20

    We present rotation periods for 71 single dwarf members of the open cluster NGC 6811 determined using photometry from NASA's Kepler mission. The results are the first from The Kepler Cluster Study, which combines Kepler's photometry with ground-based spectroscopy for cluster membership and binarity. The rotation periods delineate a tight sequence in the NGC 6811 color-period diagram from {approx}1 day at mid-F to {approx}11 days at early-K spectral type. This result extends to 1 Gyr similar prior results in the {approx}600 Myr Hyades and Praesepe clusters, suggesting that rotation periods for cool dwarf stars delineate a well-defined surface in the three-dimensional space of color (mass), rotation, and age. It implies that reliable ages can be derived for field dwarf stars with measured colors and rotation periods, and it promises to enable further understanding of various aspects of stellar rotation and activity for cool stars.

  11. Photometric Analysis in the Kepler Science Operations Center Pipeline

    NASA Technical Reports Server (NTRS)

    Twicken, Joseph D.; Clarke, Bruce D.; Bryson, Stephen T.; Tenenbaum, Peter; Wu, Hayley; Jenkins, Jon M.; Girouard, Forrest; Klaus, Todd C.

    2010-01-01

    We describe the Photometric Analysis (PA) software component and its context in the Kepler Science Operations Center (SOC) pipeline. The primary tasks of this module are to compute the photometric flux and photocenters (centroids) for over 160,000 long cadence (thirty minute) and 512 short cadence (one minute) stellar targets from the calibrated pixels in their respective apertures. We discuss the science algorithms for long and short cadence PA: cosmic ray cleaning; background estimation and removal; aperture photometry; and flux-weighted centroiding. We discuss the end-to-end propagation of uncertainties for the science algorithms. Finally, we present examples of photometric apertures, raw flux light curves, and centroid time series from Kepler flight data. PA light curves, centroid time series, and barycentric timestamp corrections are exported to the Multi-mission Archive at Space Telescope [Science Institute] (MAST) and are made available to the general public in accordance with the NASA/Kepler data release policy.

  12. Exploration Life Support Critical Questions for Future Human Space Missions

    NASA Technical Reports Server (NTRS)

    Kwert, Michael K.; Barta, Daniel J.; McQuillan, Jeff

    2010-01-01

    Exploration Life Support (ELS) is a current project under NASA's Exploration Systems Mission Directorate. The ELS Project plans, coordinates and implements the development of advanced life support technologies for human exploration missions in space. Recent work has focused on closed loop atmosphere and water systems for long duration missions, including habitats and pressurized rovers. But, what are the critical questions facing life support system developers for these and other future human missions? This paper explores those questions and how progress in the development of ELS technologies can help answer them. The ELS Project includes the following Elements: Atmosphere Revitalization Systems, Water Recovery Systems, Waste Management Systems, Habitation Engineering, Systems Integration, Modeling and Analysis, and Validation and Testing, which includes the Sub-Elements Flight Experiments and Integrated Testing. Systems engineering analysis by ELS seeks to optimize overall mission architectures by considering all the internal and external interfaces of the life support system and the potential for reduction or reuse of commodities. In particular, various sources and sinks of water and oxygen are considered along with the implications on loop closure and the resulting launch mass requirements. Systems analysis will be validated through the data gathered from integrated testing, which will demonstrate the interfaces of a closed loop life support system. By applying a systematic process for defining, sorting and answering critical life support questions, the ELS project is preparing for a variety of future human space missions

  13. Next Generation Simulation Framework for Robotic and Human Space Missions

    NASA Technical Reports Server (NTRS)

    Cameron, Jonathan M.; Balaram, J.; Jain, Abhinandan; Kuo, Calvin; Lim, Christopher; Myint, Steven

    2012-01-01

    The Dartslab team at NASA's Jet Propulsion Laboratory (JPL) has a long history of developing physics-based simulations based on the Darts/Dshell simulation framework that have been used to simulate many planetary robotic missions, such as the Cassini spacecraft and the rovers that are currently driving on Mars. Recent collaboration efforts between the Dartslab team at JPL and the Mission Operations Directorate (MOD) at NASA Johnson Space Center (JSC) have led to significant enhancements to the Dartslab DSENDS (Dynamics Simulator for Entry, Descent and Surface landing) software framework. The new version of DSENDS is now being used for new planetary mission simulations at JPL. JSC is using DSENDS as the foundation for a suite of software known as COMPASS (Core Operations, Mission Planning, and Analysis Spacecraft Simulation) that is the basis for their new human space mission simulations and analysis. In this paper, we will describe the collaborative process with the JPL Dartslab and the JSC MOD team that resulted in the redesign and enhancement of the DSENDS software. We will outline the improvements in DSENDS that simplify creation of new high-fidelity robotic/spacecraft simulations. We will illustrate how DSENDS simulations are assembled and show results from several mission simulations.

  14. Psychological Selection of NASA Astronauts for International Space Station Missions

    NASA Technical Reports Server (NTRS)

    VanderArk, Steve; Curtis, Kelly D.

    1999-01-01

    During the relatively short-duration Space Shuffle missions, a psychological support program for the astronauts has not been required. Such missions primarily require providing occasional communication with family members by means of audio, video or e-mail, and some diversions such as CD players. During the NASA-Mir Program, conducted from March 1995 through June 1998, mission duration increased to 4-6 months. As a result of these changes it was necessary for NASA to establish an operational Human Behavior and Performance Group (HBPG) to develop and implement a comprehensive program of psychological support. The Mir experience provided the opportunity to develop and implement a psychological support program for long-duration space missions. Many factors influence the support program, including individual preferences, mission duration, and environmental factors such as habitable and personal areas. Lessons learned from the Mir experience are being applied to improve the ISS psychological support program plan. This presentation will address which includes various preflight, in-flight, and post-flight support activities and tools that NASA's HBPG will provide to astronauts and their families for ISS missions.

  15. Modeling and Simulation for Multi-Missions Space Exploration Vehicle

    NASA Technical Reports Server (NTRS)

    Chang, Max

    2011-01-01

    Asteroids and Near-Earth Objects [NEOs] are of great interest for future space missions. The Multi-Mission Space Exploration Vehicle [MMSEV] is being considered for future Near Earth Object missions and requires detailed planning and study of its Guidance, Navigation, and Control [GNC]. A possible mission of the MMSEV to a NEO would be to navigate the spacecraft to a stationary orbit with respect to the rotating asteroid and proceed to anchor into the surface of the asteroid with robotic arms. The Dynamics and Real-Time Simulation [DARTS] laboratory develops reusable models and simulations for the design and analysis of missions. In this paper, the development of guidance and anchoring models are presented together with their role in achieving mission objectives and relationships to other parts of the simulation. One important aspect of guidance is in developing methods to represent the evolution of kinematic frames related to the tasks to be achieved by the spacecraft and its robot arms. In this paper, we compare various types of mathematical interpolation methods for position and quaternion frames. Subsequent work will be on analyzing the spacecraft guidance system with different movements of the arms. With the analyzed data, the guidance system can be adjusted to minimize the errors in performing precision maneuvers.

  16. Psychological Selection of NASA Astronauts for International Space Station Missions

    NASA Technical Reports Server (NTRS)

    Galarza, Laura

    1999-01-01

    During the upcoming manned International Space Station (ISS) missions, astronauts will encounter the unique conditions of living and working with a multicultural crew in a confined and isolated space environment. The environmental, social, and mission-related challenges of these missions will require crewmembers to emphasize effective teamwork, leadership, group living and self-management to maintain the morale and productivity of the crew. The need for crew members to possess and display skills and behaviors needed for successful adaptability to ISS missions led us to upgrade the tools and procedures we use for astronaut selection. The upgraded tools include personality and biographical data measures. Content and construct-related validation techniques were used to link upgraded selection tools to critical skills needed for ISS missions. The results of these validation efforts showed that various personality and biographical data variables are related to expert and interview ratings of critical ISS skills. Upgraded and planned selection tools better address the critical skills, demands, and working conditions of ISS missions and facilitate the selection of astronauts who will more easily cope and adapt to ISS flights.

  17. Trade Space Assessment for Human Exploration Mission Design

    NASA Technical Reports Server (NTRS)

    Joosten, B. Kent

    2006-01-01

    Many human space exploration mission architecture assessments have been performed over the years by diverse organizations and individuals. Direct comparison of metrics among these studies is extremely difficult due to widely varying assumptions involving projected technology readiness, mission goals, acceptable risk criteria, and socio-political environments. However, constant over the years have been the physical laws of celestial dynamics and rocket propulsion systems. A finite diverse yet finite architecture trade space should exist which captures methods of human exploration - particularly of the Moon and Mars - by delineating technical trades and cataloging the physically realizable options of each. A particular architectural approach should then have a traceable path through this "trade tree". It should be pointed out that not every permutation of paths will result in a physically realizable mission approach, but cataloging options that have been examined by past studies should help guide future analysis. This effort was undertaken in two phases by multi-center NASA working groups in the spring and summer of 2004 using more than thirty years of past studies to "flesh out" the Moon-Mars human exploration trade space. The results are presented, not as a "trade tree", which would be unwieldy, but as a "menu" of potential technical options as a function of mission phases. This is envisioned as a tool to aid future mission designers by offering guidance to relevant past analyses.

  18. Pointing and Tracking Concepts for Deep Space Missions

    NASA Technical Reports Server (NTRS)

    Alexander, J. W.; Lee, S.; Chen, C.

    2000-01-01

    This paper summarizes part of a FY1998 effort on the design and development of an optical communications (Opcomm) subsystem for the Advanced Deep Space System Development (ADSSD) Project. This study was funded by the JPL X2000 program to develop an optical communications (Opcomm) subsystem for use in future planetary missions. The goal of this development effort was aimed at providing prototype hardware with the capability of performing uplink, downlink, and ranging functions from deep space distances. Such a system was envisioned to support future deep space missions in the Outer Planets/Solar Probe (OPSP) mission set such as the Pluto express and Europa orbiter by providing a significant enhancement of data return capability. A study effort was initiated to develop a flyable engineering model optical terminal to support the proposed Europa Orbiter mission - as either the prime telecom subsystem or for mission augmentation. The design concept was to extend the prototype lasercom terminal development effort currently conducted by JPL's Optical Communications Group. The subsystem would track the sun illuminated Earth at Europa and farther distances for pointing reference. During the course of the study, a number of challenging issues were found. These included thermo-mechanical distortion, straylight control, and pointing. This paper focuses on the pointing aspects required to locate and direct a laser beam from a spacecraft (S/C) near Jupiter to a receiving station on Earth.

  19. Doubled-lined eclipsing binary system KIC~2306740 with pulsating component discovered from Kepler space photometry

    NASA Astrophysics Data System (ADS)

    Yakut, Kadri

    2015-08-01

    We present a detailed study of KIC 2306740, an eccentric double-lined eclipsing binary system with a pulsating component.Archive Kepler satellite data were combined with newly obtained spectroscopic data with 4.2\\,m William Herschel Telescope(WHT). This allowed us to determine rather precise orbital and physical parameters of this long period, slightly eccentric, pulsating binary system. Duplicity effects are extracted from the light curve in order to estimate pulsation frequencies from the residuals.We modelled the detached binary system assuming non-conservative evolution models with the Cambridge STARS(TWIN) code.

  20. Microbial contamination monitoring and control during human space missions

    NASA Astrophysics Data System (ADS)

    Van Houdt, Rob; Mijnendonckx, Kristel; Leys, Natalie

    2012-01-01

    The ubiquity and resilience of microorganisms makes them unavoidable in most environments including space habitats. The impaired immune system of astronauts in flight raises the level of concern about disease risk during human space missions and additionally these biological contaminants may affect life support systems and hardware. In this review, the microbial contamination observed in manned space stations and in particular the International Space Station ISS will be discussed, demonstrating that it is a microbiologically safe working and living habitat. Microbial contamination levels were in general below the implemented quality standards, although, occasional contamination hazard reports indicate that the current prevention and monitoring strategies are the strict minimum.

  1. Nuclear electric propulsion for future NASA space science missions

    SciTech Connect

    Yen, Chen-wan L.

    1993-07-20

    This study has been made to assess the needs, potential benefits and the applicability of early (circa year 2000) Nuclear Electric Propulsion (NEP) technology in conducting NASA science missions. The study goals are: to obtain the performance characteristics of near term NEP technologies; to measure the performance potential of NEP for important OSSA missions; to compare NEP performance with that of conventional chemical propulsion; to identify key NEP system requirements; to clarify and depict the degree of importance NEP might have in advancing NASA space science goals; and to disseminate the results in a format useful to both NEP users and technology developers. This is a mission performance study and precludes investigations of multitudes of new mission operation and systems design issues attendant in a NEP flight.

  2. Multiple star systems observed with CoRoT and Kepler

    NASA Astrophysics Data System (ADS)

    Southworth, John

    2015-09-01

    The CoRoT and Kepler satellites were the first space platforms designed to perform high-precision photometry for a large number of stars. Multiple systems display a wide variety of photometric variability, making them natural benefactors of these missions. I review the work arising from CoRoT and Kepler observations of multiple systems, with particular emphasis on eclipsing binaries containing giant stars, pulsators, triple eclipses and/or low-mass stars. Many more results remain untapped in the data archives of these missions, and the future holds the promise of K2, TESS and PLATO.

  3. Distribution of Planetary Inclinations as Inferred from Kepler Observations

    NASA Astrophysics Data System (ADS)

    Ragozzine, Darin; Kepler Team

    2011-05-01

    The true mutual inclination between orbits in a planetary system is a key indicator of dominant planet formation mechanisms. It is, therefore, unfortunate that the vast majority of current exoplanet observations are only sensitive to line-of-sight inclinations, at best. Even in systems with multiple transiting planets, arguably the best observational case, the line-of-sight inclinations are a weak constraint on the mutual inclination between planetary orbits. However, the large and homogeneous observations from the Kepler Space Telescope provide a population that can be assessed statistically in order to estimate the typical mutual inclination of exoplanetary systems. Lissauer et al. 2011b use the Quarter 0-2 Kepler observations presented in Borucki et al. 2011 to show that there is a population of planetary systems with multiple, small (radii between 1.5 and 6 Earth radii), short-period planets and that the typical mutual inclination in these systems is only a few degrees. Based on these new Kepler results and other observations, I will present the current best understanding of the inclination distribution of planetary systems and prospects for future progress. Kepler was competitively selected as the tenth Discovery mission. Funding for this mission is provided by NASA's Science Mission Directorate.

  4. Collection and management of fecal wastes for space missions.

    PubMed

    Rethke, D W; Steele, J W

    1991-10-01

    An improved type of human waste collection subsystem has been developed for Space Station Freedom which is designed to meet the challenges of zero gravity collection and system performance. Fecal collection is followed by passive storage for relatively short duration missions. The benefits of utilizing components in solid wastes as part of a partial or completely closed Environmental Control and Life Support System (ECLSS) become more apparent as the duration of the mission increases. The purpose of this review is to summarize the development issues associated with the current waste management subsystem for Space Station Freedom. Also reviewed are current ideas associated with the evolutionary development of this waste management subsystem for longer duration missions.

  5. PUS Services Software Building Block Automatic Generation for Space Missions

    NASA Astrophysics Data System (ADS)

    Candia, S.; Sgaramella, F.; Mele, G.

    2008-08-01

    The Packet Utilization Standard (PUS) has been specified by the European Committee for Space Standardization (ECSS) and issued as ECSS-E-70-41A to define the application-level interface between Ground Segments and Space Segments. The ECSS-E- 70-41A complements the ECSS-E-50 and the Consultative Committee for Space Data Systems (CCSDS) recommendations for packet telemetry and telecommand. The ECSS-E-70-41A characterizes the identified PUS Services from a functional point of view and the ECSS-E-70-31 standard specifies the rules for their mission-specific tailoring. The current on-board software design for a space mission implies the production of several PUS terminals, each providing a specific tailoring of the PUS services. The associated on-board software building blocks are developed independently, leading to very different design choices and implementations even when the mission tailoring requires very similar services (from the Ground operative perspective). In this scenario, the automatic production of the PUS services building blocks for a mission would be a way to optimize the overall mission economy and improve the robusteness and reliability of the on-board software and of the Ground-Space interactions. This paper presents the Space Software Italia (SSI) activities for the development of an integrated environment to support: the PUS services tailoring activity for a specific mission. the mission-specific PUS services configuration. the generation the UML model of the software building block implementing the mission-specific PUS services and the related source code, support documentation (software requirements, software architecture, test plans/procedures, operational manuals), and the TM/TC database. The paper deals with: (a) the project objectives, (b) the tailoring, configuration, and generation process, (c) the description of the environments supporting the process phases, (d) the characterization of the meta-model used for the generation, (e) the

  6. Space transfer concepts and analyses for exploration missions

    NASA Technical Reports Server (NTRS)

    Woodcock, Gordon R.

    1992-01-01

    The current technical effort is part of the third phase of a broad-scoped and systematic study of space transfer concepts for human lunar and Mars missions. The study addressed the technical issues relating to the First Lunar Outpost (FLO) habitation vehicle with emphasis in the structure, power, life support system, and radiation environment.

  7. Mission to Jupiter. [Pioneer 10 and 11 space probes

    NASA Technical Reports Server (NTRS)

    1975-01-01

    The Pioneer 10 and Pioneer 11 space probes and their missions to Jupiter are discussed along with the experiments and investigations which will be conducted onboard. Jupiter's atmosphere, its magnetic fields, radiation belts, the spacecraft instruments, and the Jovian system will be investigated. Educational study projects are also included.

  8. Mask Design for the Space Interferometry Mission Internal Metrology

    NASA Technical Reports Server (NTRS)

    Marx, David; Zhao, Feng; Korechoff, Robert

    2005-01-01

    This slide presentation reviews the mask design used for the internal metrology of the Space Interferometry Mission (SIM). Included is information about the project, the method of measurements with SIM, the internal metrology, numerical model of internal metrology, wavefront examples, performance metrics, and mask design

  9. Probabilistic Assessment of Radiation Risk for Astronauts in Space Missions

    NASA Technical Reports Server (NTRS)

    Kim, Myung-Hee; DeAngelis, Giovanni; Cucinotta, Francis A.

    2009-01-01

    Accurate predictions of the health risks to astronauts from space radiation exposure are necessary for enabling future lunar and Mars missions. Space radiation consists of solar particle events (SPEs), comprised largely of medium energy protons, (less than 100 MeV); and galactic cosmic rays (GCR), which include protons and heavy ions of higher energies. While the expected frequency of SPEs is strongly influenced by the solar activity cycle, SPE occurrences themselves are random in nature. A solar modulation model has been developed for the temporal characterization of the GCR environment, which is represented by the deceleration potential, phi. The risk of radiation exposure from SPEs during extra-vehicular activities (EVAs) or in lightly shielded vehicles is a major concern for radiation protection, including determining the shielding and operational requirements for astronauts and hardware. To support the probabilistic risk assessment for EVAs, which would be up to 15% of crew time on lunar missions, we estimated the probability of SPE occurrence as a function of time within a solar cycle using a nonhomogeneous Poisson model to fit the historical database of measurements of protons with energy > 30 MeV, (phi)30. The resultant organ doses and dose equivalents, as well as effective whole body doses for acute and cancer risk estimations are analyzed for a conceptual habitat module and a lunar rover during defined space mission periods. This probabilistic approach to radiation risk assessment from SPE and GCR is in support of mission design and operational planning to manage radiation risks for space exploration.

  10. Technology assessment of advanced automation for space missions

    NASA Technical Reports Server (NTRS)

    1982-01-01

    Six general classes of technology requirements derived during the mission definition phase of the study were identified as having maximum importance and urgency, including autonomous world model based information systems, learning and hypothesis formation, natural language and other man-machine communication, space manufacturing, teleoperators and robot systems, and computer science and technology.

  11. Long Duration Space Missions: Human Subsystem Risks and Requirements

    NASA Technical Reports Server (NTRS)

    Kundrot, Criag E.

    2011-01-01

    This viewgraph presentation reviews the human health and performance risks associated with long duration space flight beyond low earth orbit. The contents include: 1) Human Research Program; 2) Human Subsystem Risks; 3) Human Exploration Framework Team (HEFT) Architecture Elements; 4) Potentially Unacceptable Risks -1; 5) Potentially Unacceptable Risks-2; and 6) Major Mission Drivers of Risk.

  12. Importance of Nuclear Physics to NASA's Space Missions

    NASA Technical Reports Server (NTRS)

    Tripathi, R. K.; Wilson, J. W.; Cucinotta, F. A.

    2001-01-01

    We show that nuclear physics is extremely important for accurate risk assessments for space missions. Due to paucity of experimental input radiation interaction information it is imperative to develop reliable accurate models for the interaction of radiation with matter. State-of-the-art nuclear cross sections models have been developed at the NASA Langley Research center and are discussed.

  13. Autonomous medical care for exploration class space missions.

    PubMed

    Hamilton, Douglas; Smart, Kieran; Melton, Shannon; Polk, James D; Johnson-Throop, Kathy

    2008-04-01

    The US-based health care system of the International Space Station contains several subsystems, the Health Maintenance System, Environmental Health System and the Countermeasure System. These systems are designed to provide primary, secondary and tertiary medical prevention strategies. The medical system deployed in low Earth orbit for the International Space Station is designed to support a "stabilize and transport" concept of operations. In this paradigm, an ill or injured crewmember would be rapidly evacuated to a definitive medical care facility (DMCF) on Earth, rather than being treated for a protracted period on orbit. The medical requirements of the short (7 day) and long duration (up to 6 months) exploration class missions to the moon are similar to low Earth orbit class missions but also include an additional 4 to 5 days needed to transport an ill or injured crewmember to a DMCF on Earth. Mars exploration class missions are quite different in that they will significantly delay or prevent the return of an ill or injured crewmember to a DMCF. In addition the limited mass, power and volume afforded to medical care will prevent the mission designers from manifesting the entire capability of terrestrial care. National Aeronautics and Space Administration has identified five levels of care as part of its approach to medical support of future missions including the Constellation program. To implement an effective medical risk mitigation strategy for exploration class missions, modifications to the current suite of space medical systems may be needed, including new crew medical officer training methods, treatment guidelines, diagnostic and therapeutic resources, and improved medical informatics.

  14. Earth science space missions in the 21st century

    NASA Astrophysics Data System (ADS)

    Grofic, B.

    In 2007, the National Research Council (NRC) published “ Earth Science and Applications from Space: National Imperatives for the Next Decade and Beyond, 2007” , commonly known as the “ Decadal Survey” . This report called for a balanced set of Earth Science Missions across the Earth Science research spectrum. In response, in February 2008, NASA's Earth Science Division reorganized into two program offices: The Earth Systematic Missions Program Office (ESM PO) at Goddard Space Flight Center which includes satellites making continuous measurements of the Earth's climate, and the Earth System Science Pathfinder Program Office (ESSP PO) at Langley Research Center which develops pathfinder missions through Announcements of Opportunity. In June 2010 NASA published its plan to achieve the goals of the Decadal Survey, “ Responding to the Challenge of Climate and Environmental Change: NASA's Plan for a Climate-Centric Architecture for Earth Observations and Applications from Space.” This plan includes support for the Decadal Survey missions as well as a set of “ climate continuity missions” to address the scientific need for data continuity of key climate observations. In 2011 the NRC revisited the Decadal Survey report and published “ Earth Science and Applications from Space: A Midterm Assessment of NASA's Implementation of the Decadal Survey” . This report notes that progress on the Decadal Survey plan has been slower than planned due to budget shortfalls and launch vehicle failures, and stresses that the goals of the Decadal Survey are as important as ever and must still yield a scientifically-balanced program. This paper will discuss the current status of the mission/mission study portfolios of the ESMP Program and the Earth Venture solicitations of the ESSP Program and how the Programs support the goals established and reiterated by the NRC, and will discuss the risks and challenges faced by t- e Programs as together they strive to meet these goals.

  15. Detection of Solar-Like Oscillations, Observational Constraints, and Stellar Models for θ Cyg, the Brightest Star Observed by the Kepler Mission

    DOE PAGES

    Guzik, Joyce Ann; Houdek, G.; Chaplin, W. J.; ...

    2016-10-21

    θ Cygni is an F3 spectral type magnitude V = 4.48 main-sequence star that was the brightest star observed by the original Kepler spacecraft mission. Short-cadence (58.8 s) photometric data using a custom aperture were first obtained during Quarter 6 (2010 June–September) and subsequently in Quarters 8 and 12–17. We present analyses of solar-like oscillations based on Q6 and Q8 data, identifying angular degree l = 0, 1, and 2 modes with frequencies of 1000–2700 μHz, a large frequency separation of 83.9 ± 0.4 μHz, and maximum oscillation amplitude at frequency νmax = 1829 ± 54 μHz. We also presentmore » analyses of new ground-based spectroscopic observations, which, combined with interferometric angular diameter measurements, give T eff = 6697 ± 78 K, radius 1.49 ± 0.03 R ⊙, [Fe/H] = $-$0.02 ± 0.06 dex, and log g = 4.23 ± 0.03. We calculate stellar models matching these constraints using the Yale Rotating Evolution Code and the Asteroseismic Modeling Portal. The best-fit models have masses of 1.35–1.39 M ⊙ and ages of 1.0–1.6 Gyr. θ Cyg's T eff and log g place it cooler than the red edge of the γ Doradus instability region established from pre-Kepler ground-based observations, but just at the red edge derived from pulsation modeling. Lastly, the pulsation models show γ Dor gravity modes driven by the convective blocking mechanism, with frequencies of 1–3 cycles per day (11 to 33 μHz). However, gravity modes were not seen in Kepler data; one signal at 1.776 cycles per day (20.56 μHz) may be attributable to a faint, possibly background, binary.« less

  16. Detection of Solar-Like Oscillations, Observational Constraints, and Stellar Models for θ Cyg, the Brightest Star Observed by the Kepler Mission

    SciTech Connect

    Guzik, Joyce Ann; Houdek, G.; Chaplin, W. J.; Smalley, B.; Kurtz, D. W.; Gilliland, R. L.; Mullally, F.; Rowe, J. F.; Bryson, S. T.; Still, M. D.; Antoci, V.; Appourchaux, T.; Basu, S.; Bedding, T.R.; Benomar, O.; Garcia, R.A.; Huber, D.; Kjeldsen, H.; Latham, D.; Metcalfe, T. S.; Papics, P. I.; White, T. R.; Aerts, C.; Ballot, J.; Boyajian, T.S.; Briquet, M.; Bruntt, H.; Buchhave, L.A.; Campante, T.L.; Catanzaro, G.; Christensen-Dalsgaard, J.; Davies, G.R.; Dogan, G.; Dragomir, D.; Doyle, A.P.; Elsworth, Y.; Frasca, A.; Gaulme, P.; Gruberbauer, M.; Handberg, R.; Hekker, S.; Karoff, C.; Lehmann, H.; Mathias, P.; Mathur, S.; Miglio, A.; Molenda-Zakowicz, J.; Mosser, B.; Murphy, S. J.; Regulo, C.; Ripepi, V.; Salabert, D.; Sousa, S.; Stello, D.; Uytterhoeven, K.

    2016-10-21

    θ Cygni is an F3 spectral type magnitude V = 4.48 main-sequence star that was the brightest star observed by the original Kepler spacecraft mission. Short-cadence (58.8 s) photometric data using a custom aperture were first obtained during Quarter 6 (2010 June–September) and subsequently in Quarters 8 and 12–17. We present analyses of solar-like oscillations based on Q6 and Q8 data, identifying angular degree l = 0, 1, and 2 modes with frequencies of 1000–2700 μHz, a large frequency separation of 83.9 ± 0.4 μHz, and maximum oscillation amplitude at frequency νmax = 1829 ± 54 μHz. We also present analyses of new ground-based spectroscopic observations, which, combined with interferometric angular diameter measurements, give T eff = 6697 ± 78 K, radius 1.49 ± 0.03 R , [Fe/H] = $-$0.02 ± 0.06 dex, and log g = 4.23 ± 0.03. We calculate stellar models matching these constraints using the Yale Rotating Evolution Code and the Asteroseismic Modeling Portal. The best-fit models have masses of 1.35–1.39 M and ages of 1.0–1.6 Gyr. θ Cyg's T eff and log g place it cooler than the red edge of the γ Doradus instability region established from pre-Kepler ground-based observations, but just at the red edge derived from pulsation modeling. Lastly, the pulsation models show γ Dor gravity modes driven by the convective blocking mechanism, with frequencies of 1–3 cycles per day (11 to 33 μHz). However, gravity modes were not seen in Kepler data; one signal at 1.776 cycles per day (20.56 μHz) may be attributable to a faint, possibly background, binary.

  17. Rotation Rates and other Physical Properties in a Sample of M-dwarfs from the Kepler Mission

    NASA Astrophysics Data System (ADS)

    Bachmakov, Eduard; Gouravajhala, S.; Guinan, E. F.

    2014-01-01

    M-dwarf stars are the most common stars in the universe (80%) but also form the one of the least explored spectral classes. We analyzed a photometric sample of the 500 brightest M-dwarf star long-cadence lightcurves (T<4000K, logg>4) from the Kepler MAST catalogue for rotation rates of starspots and presence of flares. We determined (differential) rotation rates for a large fraction of the sample. We present the results of our survey M-dwarf rotation rates, starspot coverage, differential rotation rates, ages derived from the Age-Activity-Rotation relationship developed by Engle and Guinan (2011) as part of the Living with a Red Dwarf Program, and flare frequencies. We wish to acknowledge support from NSF/RUI grant #AST-1009903.

  18. Definition of technology development missions for early space stations: Large space structures

    NASA Technical Reports Server (NTRS)

    Gates, R. M.; Reid, G.

    1984-01-01

    The objectives studied are the definition of the tested role of an early Space Station for the construction of large space structures. This is accomplished by defining the LSS technology development missions (TDMs) identified in phase 1. Design and operations trade studies are used to identify the best structural concepts and procedures for each TDMs. Details of the TDM designs are then developed along with their operational requirements. Space Station resources required for each mission, both human and physical, are identified. The costs and development schedules for the TDMs provide an indication of the programs needed to develop these missions.

  19. Launch and Assembly Reliability Analysis for Human Space Exploration Missions

    NASA Technical Reports Server (NTRS)

    Cates, Grant; Gelito, Justin; Stromgren, Chel; Cirillo, William; Goodliff, Kandyce

    2012-01-01

    NASA's future human space exploration strategy includes single and multi-launch missions to various destinations including cis-lunar space, near Earth objects such as asteroids, and ultimately Mars. Each campaign is being defined by Design Reference Missions (DRMs). Many of these missions are complex, requiring multiple launches and assembly of vehicles in orbit. Certain missions also have constrained departure windows to the destination. These factors raise concerns regarding the reliability of launching and assembling all required elements in time to support planned departure. This paper describes an integrated methodology for analyzing launch and assembly reliability in any single DRM or set of DRMs starting with flight hardware manufacturing and ending with final departure to the destination. A discrete event simulation is built for each DRM that includes the pertinent risk factors including, but not limited to: manufacturing completion; ground transportation; ground processing; launch countdown; ascent; rendezvous and docking, assembly, and orbital operations leading up to trans-destination-injection. Each reliability factor can be selectively activated or deactivated so that the most critical risk factors can be identified. This enables NASA to prioritize mitigation actions so as to improve mission success.

  20. Portable Diagnostics Technology Assessment for Space Missions. Part 1; General Technology Capabilities for NASA Exploration Missions

    NASA Technical Reports Server (NTRS)

    Nelson, Emily S.; Chait, Arnon

    2010-01-01

    The changes in the scope of NASA s mission in the coming decade are profound and demand nimble, yet insightful, responses. On-board clinical and environmental diagnostics must be available for both mid-term lunar and long-term Mars exploration missions in an environment marked by scarce resources. Miniaturization has become an obvious focus. Despite solid achievements in lab-based devices, broad-based, robust tools for application in the field are not yet on the market. The confluence of rapid, wide-ranging technology evolution and internal planning needs are the impetus behind this work. This report presents an analytical tool for the ongoing evaluation of promising technology platforms based on mission- and application-specific attributes. It is not meant to assess specific devices, but rather to provide objective guidelines for a rational down-select of general categories of technology platforms. In this study, we have employed our expertise in the microgravity operation of fluidic devices, laboratory diagnostics for space applications, and terrestrial research in biochip development. A rating of the current state of technology development is presented using the present tool. Two mission scenarios are also investigated: a 30-day lunar mission using proven, tested technology in 5 years; and a 2- to 3-year mission to Mars in 10 to 15 years.

  1. Liftoff of Space Shuttle Endeavour on mission STS-97

    NASA Technical Reports Server (NTRS)

    2000-01-01

    As Space Shuttle Endeavour rockets off Launch Pad 39B, spewing clouds of smoke and steam, a majestic heron soars over the nearby water and Endeavour'''s reflection. Liftoff occurred on time at 10:06:01 p.m. EST. The Shuttle and its five-member crew will deliver U.S. solar arrays to the International Space Station and be the first Shuttle crew to visit the Station'''s first resident crew. The 11-day mission includes three spacewalks. This marks the 101st mission in Space Shuttle history and the 25th night launch. Endeavour is expected to land Dec. 11 at 6:19 p.m. EST.

  2. Asynchronous Message Service for Deep Space Mission Operations

    NASA Technical Reports Server (NTRS)

    Burleigh, Scott C.

    2006-01-01

    While the CCSDS (Consultative Committee for Space Data Systems) File Delivery Protocol (CFDP) provides internationally standardized file transfer functionality that can offer significant benefits for deep space mission operations, not all spacecraft communication requirements are necessarily best met by file transfer. In particular, continuous event-driven asynchronous message exchange may also be useful for communications with, among, and aboard spacecraft. CCSDS has therefore undertaken the development of a new Asynchronous Message Service (AMS) standard, designed to provide common functionality over a wide variety of underlying transport services, ranging from shared memory message queues to CCSDS telemetry systems. The present paper discusses the design concepts of AMS, their applicability to deep space mission operations problems, and the results of preliminary performance testing obtained from exercise of a prototype implementation.

  3. Temporal Investment Strategy to Enable JPL Future Space Missions

    NASA Technical Reports Server (NTRS)

    Lincoln, William P.; Hua, Hook; Weisbin, Charles R.

    2006-01-01

    The Jet Propulsion Laboratory (JPL) formulates and conducts deep space missions for NASA (the National Aeronautics and Space Administration). The Chief Technologist of JPL has the responsibility for strategic planning of the laboratory's advanced technology program to assure that the required technological capabilities to enable future JPL deep space missions are ready as needed; as such he is responsible for the development of a Strategic Plan. As part of the planning effort, he has supported the development of a structured approach to technology prioritization based upon the work of the START (Strategic Assessment of Risk and Technology) team. A major innovation reported here is the addition of a temporal model that supports scheduling of technology development as a function of time. The JPL Strategic Technology Plan divides the required capabilities into 13 strategic themes. The results reported here represent the analysis of an initial seven.

  4. Role of Lidar Technology in Future NASA Space Missions

    NASA Technical Reports Server (NTRS)

    Amzajerdian, Farzin

    2008-01-01

    The past success of lidar instruments in space combined with potentials of laser remote sensing techniques in improving measurements traditionally performed by other instrument technologies and in enabling new measurements have expanded the role of lidar technology in future NASA missions. Compared with passive optical and active radar/microwave instruments, lidar systems produce substantially more accurate and precise data without reliance on natural light sources and with much greater spatial resolution. NASA pursues lidar technology not only as science instruments, providing atmospherics and surface topography data of Earth and other solar system bodies, but also as viable guidance and navigation sensors for space vehicles. This paper summarizes the current NASA lidar missions and describes the lidar systems being considered for deployment in space in the near future.

  5. The Virtual Space Telescope: A New Class of Science Missions

    NASA Technical Reports Server (NTRS)

    Shah, Neerav; Calhoun, Philip

    2016-01-01

    Many science investigations proposed by GSFC require two spacecraft alignment across a long distance to form a virtual space telescope. Forming a Virtual Space telescope requires advances in Guidance, Navigation, and Control (GNC) enabling the distribution of monolithic telescopes across multiple space platforms. The capability to align multiple spacecraft to an intertial target is at a low maturity state and we present a roadmap to advance the system-level capability to be flight ready in preparation of various science applications. An engineering proof of concept, called the CANYVAL-X CubeSat MIssion is presented. CANYVAL-X's advancement will decrease risk for a potential starshade mission that would fly with WFIRST.

  6. The Neurolab Spacelab Mission: Neuroscience Research in Space: Results from the STS-90, Neurolab Spacelab Mission

    NASA Technical Reports Server (NTRS)

    Buckey, Jay C., Jr. (Editor); Homick, Jerry L. (Editor)

    2003-01-01

    Neurolab (STS-90) represents a major scientific achievement that built upon the knowledge and capabilities developed during the preceding 15 successful Spacelab module missions. NASA proposed a dedicated neuroscience research flight in response to a Presidential declaration that the 1990's be the Decade of the Brain. Criteria were established for selecting research proposals in partnership with the National Institutes of Health (NM), the National Science Foundation, the Department of Defense, and a number of the International Space Agencies. The resulting Announcement of Opportunity for Neurolab in 1993 resulted in 172 proposals from scientists worldwide. After an NIH-managed peer review, NASA ultimately selected 26 proposals for flight on the Neurolab mission.

  7. Radiation environments and absorbed dose estimations on manned space missions.

    PubMed

    Curtis, S B; Atwell, W; Beever, R; Hardy, A

    1986-01-01

    In order to make an assessment of radiation risk during manned missions in space, it is necessary first to have as accurate an estimation as possible of the radiation environment within the spacecraft to which the astronauts will be exposed. Then, with this knowledge and the inclusion of body self-shielding, estimations can be made of absorbed doses for various body organs (skin, eye, blood-forming organs, etc.). A review is presented of our present knowledge of the radiation environments and absorbed doses expected for several space mission scenarios selected for our development of the new radiation protection guidelines. The scenarios selected are a 90-day mission at an altitude (450 km) and orbital inclinations (28.5 degrees, 57 degrees and 90 degrees) appropriate for NASA's Space Station, a 15-day sortie to geosynchronous orbit and a 90-day lunar mission. All scenarios chosen yielded dose equivalents between five and ten rem to the blood forming organs if no large solar particle event were encountered. Such particle events could add considerable exposure particularly to the skin and eye for all scenarios except the one at 28.5 degrees orbital inclination.

  8. Advances in Autonomous Systems for Missions of Space Exploration

    NASA Astrophysics Data System (ADS)

    Gross, A. R.; Smith, B. D.; Briggs, G. A.; Hieronymus, J.; Clancy, D. J.

    New missions of space exploration will require unprecedented levels of autonomy to successfully accomplish their objectives. Both inherent complexity and communication distances will preclude levels of human involvement common to current and previous space flight missions. With exponentially increasing capabilities of computer hardware and software, including networks and communication systems, a new balance of work is being developed between humans and machines. This new balance holds the promise of meeting the greatly increased space exploration requirements, along with dramatically reduced design, development, test, and operating costs. New information technologies, which take advantage of knowledge-based software, model-based reasoning, and high performance computer systems, will enable the development of a new generation of design and development tools, schedulers, and vehicle and system health monitoring and maintenance capabilities. Such tools will provide a degree of machine intelligence and associated autonomy that has previously been unavailable. These capabilities are critical to the future of space exploration, since the science and operational requirements specified by such missions, as well as the budgetary constraints that limit the ability to monitor and control these missions by a standing army of ground- based controllers. System autonomy capabilities have made great strides in recent years, for both ground and space flight applications. Autonomous systems have flown on advanced spacecraft, providing new levels of spacecraft capability and mission safety. Such systems operate by utilizing model-based reasoning that provides the capability to work from high-level mission goals, while deriving the detailed system commands internally, rather than having to have such commands transmitted from Earth. This enables missions of such complexity and communications distance as are not otherwise possible, as well as many more efficient and low cost

  9. [Style of communication between mission control centers and space crews].

    PubMed

    Iusupova, A K; Gushchin, V I; Shved, D M; Cheveleva, L M

    2011-01-01

    The article deals with a pilot investigation into the audio communication of cosmonauts with ground controllers. The purpose was to verify in space flight the patterns and trends revealed in model tests of intergroup communication, and to pinpoint the signature of multinational crew communication with 2 national mission control centers (MCCs). The investigation employed authors' content-analysis adapted to the scenario of long-duration mission. The investigation resulted in a phenomenon of double-loop ground-orbit communication, divergence, difference in opinion predictable from the concept formulated by G.T.Beregovoi. Also, there was a notable difference of expressions used by controllers of 2 MCCs.

  10. Wireless Network Communications Overview for Space Mission Operations

    NASA Technical Reports Server (NTRS)

    Fink, Patrick W.

    2009-01-01

    The mission of the On-Board Wireless Working Group (WWG) is to serve as a general CCSDS focus group for intra-vehicle wireless technologies. The WWG investigates and makes recommendations pursuant to standardization of applicable wireless network protocols, ensuring the interoperability of independently developed wireless communication assets. This document presents technical background information concerning uses and applicability of wireless networking technologies for space missions. Agency-relevant driving scenarios, for which wireless network communications will provide a significant return-on-investment benefiting the participating international agencies, are used to focus the scope of the enclosed technical information.

  11. Psychology and culture during long-duration space missions

    NASA Astrophysics Data System (ADS)

    Kanas, N.; Sandal, G.; Boyd, J. E.; Gushin, V. I.; Manzey, D.; North, R.; Leon, G. R.; Suedfeld, P.; Bishop, S.; Fiedler, E. R.; Inoue, N.; Johannes, B.; Kealey, D. J.; Kraft, N.; Matsuzaki, I.; Musson, D.; Palinkas, L. A.; Salnitskiy, V. P.; Sipes, W.; Stuster, J.; Wang, J.

    2009-04-01

    The objective of this paper is twofold: (a) to review the current knowledge of cultural, psychological, psychiatric, cognitive, interpersonal, and organizational issues that are relevant to the behavior and performance of astronaut crews and ground support personnel and (b) to make recommendations for future human space missions, including both transit and planetary surface operations involving the Moon or Mars. The focus will be on long-duration missions lasting at least six weeks, when important psychological and interpersonal factors begin to take their toll on crewmembers. This information is designed to provide guidelines for astronaut selection and training, in-flight monitoring and support, and post-flight recovery and re-adaptation.

  12. Space Technology 5 - A Successful Micro-Satellite Constellation Mission

    NASA Technical Reports Server (NTRS)

    Carlisle, Candace; Webb, Evan H.

    2007-01-01

    The Space Technology 5 (ST5) constellation of three micro-satellites was launched March 22, 2006. During the three-month flight demonstration phase, the ST5 team validated key technologies that will make future low-cost micro-sat constellations possible, demonstrated operability concepts for future micro-sat science constellation missions, and demonstrated the utility of a micro-satellite constellation to perform research-quality science. The ST5 mission was successfully completed in June 2006, demonstrating high-quality science and technology validation results.

  13. Space Shuttle to deploy Magellan planetary science mission

    NASA Technical Reports Server (NTRS)

    1989-01-01

    The objectives of Space Shuttle Mission STS-30 are described along with major flight activities, prelaunch and launch operations, trajectory sequence of events, and landing and post-landing operations. The primary objective of STS-30 is to successfully deploy the Magellan spacecraft into low earth orbit. Following deployment, Magellan will be propelled to its Venus trajectory by an Inertial Upper Stage booster. The objectives of the Magellan mission are to obtain radar images of more than 70 percent of Venus' surface, a near-global topographic map, and near-global gravity field data. Secondary STS-30 payloads include the Fluids Experiment Apparatus (FEA) and the Mesoscale Lightning Experiment (MLE).

  14. Automated design of multiphase space missions using hybrid optimal control

    NASA Astrophysics Data System (ADS)

    Chilan, Christian Miguel

    A modern space mission is assembled from multiple phases or events such as impulsive maneuvers, coast arcs, thrust arcs and planetary flybys. Traditionally, a mission planner would resort to intuition and experience to develop a sequence of events for the multiphase mission and to find the space trajectory that minimizes propellant use by solving the associated continuous optimal control problem. This strategy, however, will most likely yield a sub-optimal solution, as the problem is sophisticated for several reasons. For example, the number of events in the optimal mission structure is not known a priori and the system equations of motion change depending on what event is current. In this work a framework for the automated design of multiphase space missions is presented using hybrid optimal control (HOC). The method developed uses two nested loops: an outer-loop that handles the discrete dynamics and finds the optimal mission structure in terms of the categorical variables, and an inner-loop that performs the optimization of the corresponding continuous-time dynamical system and obtains the required control history. Genetic algorithms (GA) and direct transcription with nonlinear programming (NLP) are introduced as methods of solution for the outer-loop and inner-loop problems, respectively. Automation of the inner-loop, continuous optimal control problem solver, required two new technologies. The first is a method for the automated construction of the NLP problems resulting from the use of a direct solver for systems with different structures, including different numbers of categorical events. The method assembles modules, consisting of parameters and constraints appropriate to each event, sequentially according to the given mission structure. The other new technology is for a robust initial guess generator required by the inner-loop NLP problem solver. Two new methods were developed for cases including low-thrust trajectories. The first method, based on GA

  15. EVA crew workstation provisions for Skylab and Space Shuttle missions

    NASA Technical Reports Server (NTRS)

    Brown, N. E.; Saenger, E. L.

    1973-01-01

    A synopsis of scheduled extravehicular activities (EVA) for a nominal Skylab mission is presented with an overview of EV workstation equipment developed for the program. Also included are the unprogrammed extravehicular activities and supporting equipment that was quickly developed and retrofitted in a series of successful operations to salvage the crippled Skylab Cluster during the Skylab 1 Mission. Because EVA appears to be a requirement for the Space Shuttle Program, candidate EV workstations are discussed in terms of effective and economical Shuttle payload servicing and maintenance. Several such concepts, which could provide a versatile, portable EV support system, are presented.

  16. SpaceBuoy: A University Nanosat Space Weather Mission Solicitation

    DTIC Science & Technology

    2010-05-17

    with Harvard Smithsonian’s Center for Astrophysics , NASA/Ames, and other institutions. Our very active (more than 30 flights in four years) high...the Space Science and Engineering Laboratory is to educate students with the technical knowledge necessary to succeed in an aerospace career by

  17. Detectability of Oort Cloud Objects Using Kepler

    NASA Astrophysics Data System (ADS)

    Ofek, Eran O.; Nakar, Ehud

    2010-03-01

    The size distribution and total mass of objects in the Oort Cloud have important implications to the theory of planet formation, including the properties of, and the processes taking place in the early solar system. We discuss the potential of space missions, such as Kepler and CoRoT, designed to discover transiting exoplanets, to detect Oort Cloud, Kuiper Belt, and main belt objects by occultations of background stars. Relying on published dynamical estimates of the content of the Oort Cloud, we find that Kepler's main program is expected to detect between 0 and ~100 occultation events by deca-kilometer-sized Oort Cloud objects. The occultation rate depends on the mass of the Oort Cloud, the distance to its "inner edge," and the size distribution of its objects. In contrast, Kepler is unlikely to find occultations by Kuiper Belt or main belt asteroids, mainly due to the fact that it is observing a high ecliptic latitude field. Occultations by solar system objects will appear as a photometric deviation in a single measurement, implying that the information regarding the timescale and light-curve shape of each event is lost. We present statistical methods that have the potential to verify the authenticity of occultation events by solar system objects, to estimate the distance to the occulting population, and to constrain their size distribution. Our results are useful for planning of future space-based exoplanet searches in a way that will maximize the probability of detecting solar system objects, without hampering the main science goals.

  18. Estimating the Deep Space Network modification costs to prepare for future space missions by using major cost drivers

    NASA Technical Reports Server (NTRS)

    Remer, Donald S.; Sherif, Josef; Buchanan, Harry R.

    1993-01-01

    This paper develops a cost model to do long range planning cost estimates for Deep Space Network (DSN) support of future space missions. The paper focuses on the costs required to modify and/or enhance the DSN to prepare for future space missions. The model is a function of eight major mission cost drivers and estimates both the total cost and the annual costs of a similar future space mission. The model is derived from actual cost data from three space missions: Voyager (Uranus), Voyager (Neptune), and Magellan. Estimates derived from the model are tested against actual cost data for two independent missions, Viking and Mariner Jupiter/Saturn (MJS).

  19. Speckle Imaging of Kepler and CoRoT Exo-planet Transit Candidate Stars

    NASA Astrophysics Data System (ADS)

    Howell, Steve B.; Horch, Elliott; Sherry, William; Ciardi, David

    2010-08-01

    Kepler and CoRoT are complementary space missions dedicated to the detection of exoplanets. The primary science goal of CoRoT is to find Neptune-sized (>3 Earth radii) planets in intermediate orbits, while the prime science goal of Kepler is to find Earth-sized planets (<3 Earth radii) in year-long orbits. Both missions employ the photometric transit method and both spacecraft are performing well with nominal operation of the spacecraft, telescopes, electronics, and instruments. As with ground-based surveys, Kepler and CoRoT candidates need to be screened for background eclipsing binary stars which, when photometrically blended with the primary target, can mimic exo-planetary transits. The list of candidate transiting planets found by Kepler/CoRoT requires follow-up to ascertain probable or certain exo- planet detection. While Earth-sized (and Neptune-sized in long orbital periods) exo-planets can not currently (easily) be confirmed from the ground, many of the false positive eliminations steps can be performed by ground-based observations. Follow-up for Kepler exo-planet candidates is now aimed at Neptune-size and smaller planets in longer period orbits. This proposal aims to obtain high resolution speckle imaging to observe Kepler/CoRoT exo-planet transit candidates in order to eliminate the largest false positive contributor in any transit search - background eclipsing binary stars or faint companion stars.

  20. Operations Concepts for Deep-Space Missions: Challenges and Opportunities

    NASA Technical Reports Server (NTRS)

    McCann, Robert S.

    2010-01-01

    Historically, manned spacecraft missions have relied heavily on real-time communication links between crewmembers and ground control for generating crew activity schedules and working time-critical off-nominal situations. On crewed missions beyond the Earth-Moon system, speed-of-light limitations will render this ground-centered concept of operations obsolete. A new, more distributed concept of operations will have to be developed in which the crew takes on more responsibility for real-time anomaly diagnosis and resolution, activity planning and replanning, and flight operations. I will discuss the innovative information technologies, human-machine interfaces, and simulation capabilities that must be developed in order to develop, test, and validate deep-space mission operations

  1. Radiation hazards on space missions outside the magnetosphere.

    PubMed

    Letaw, J R; Silberberg, R; Tsao, C H

    1989-01-01

    Future space missions outside the magnetosphere will subject astronauts to a hostile and unfamiliar radiation environment. An annual dose equivalent to the blood-forming organs (BFOs) of approximately 0.5 Sv is expected, mostly from heavy ions in the galactic cosmic radiation. On long-duration missions, an anomalously-large solar energetic particle event may occur. Such an event can expose astronauts to up to approximately 25 Gy (skin dose) and up to approximately 2 Sv (BFO dose) with no shielding. The anticipated radiation exposure may necessitate spacecraft design concessions and some restriction of mission activities. In this paper we discuss our model calculations of radiation doses in several exo-magnetospheric environments. Specific radiation shielding strategies are discussed. A new calculation of aluminum equivalents of potential spacecraft shielding materials demonstrates the importance of low-atomic-mass species for protection from galactic cosmic radiation.

  2. Liftoff of Space Shuttle Columbia on mission STS-93

    NASA Technical Reports Server (NTRS)

    1999-01-01

    The fiery launch of Space Shuttle Columbia casts ghost-like shadows on the clouds of smoke and steam surrounding it. Liftoff occurred at 12:31 a.m. EDT. STS-93 is a five-day mission primarily to release the Chandra X-ray Observatory, which will allow scientists from around the world to study some of the most distant, powerful and dynamic objects in the universe. The crew numbers five: Commander Eileen M. Collins, Pilot Jeffrey S. Ashby, and Mission Specialists Stephen A. Hawley (Ph.D.), Catherine G. Coleman (Ph.D.) and Michel Tognini of France, with the Centre National d'Etudes Spatiales (CNES). Collins is the first woman to serve as commander of a Shuttle mission. The target landing date is July 27, 1999, at 11:20 p.m. EDT.

  3. Software Construction and Analysis Tools for Future Space Missions

    NASA Technical Reports Server (NTRS)

    Lowry, Michael R.; Clancy, Daniel (Technical Monitor)

    2002-01-01

    NASA and its international partners will increasingly depend on software-based systems to implement advanced functions for future space missions, such as Martian rovers that autonomously navigate long distances exploring geographic features formed by surface water early in the planet's history. The software-based functions for these missions will need to be robust and highly reliable, raising significant challenges in the context of recent Mars mission failures attributed to software faults. After reviewing these challenges, this paper describes tools that have been developed at NASA Ames that could contribute to meeting these challenges; 1) Program synthesis tools based on automated inference that generate documentation for manual review and annotations for automated certification. 2) Model-checking tools for concurrent object-oriented software that achieve memorability through synergy with program abstraction and static analysis tools.

  4. Space Radiation Cancer Risks and Uncertainties for Mars Missions

    NASA Technical Reports Server (NTRS)

    Cucinotta, F. A.; Schimmerling, W.; Wilson, J. W.; Peterson, L. E.; Badhwar, G. D.; Saganti, P. B.; Dicello, J. F.

    2001-01-01

    Projecting cancer risks from exposure to space radiation is highly uncertain because of the absence of data for humans and because of the limited radiobiology data available for estimating late effects from the high-energy and charge (HZE) ions present in the galactic cosmic rays (GCR). Cancer risk projections involve many biological and physical factors, each of which has a differential range of uncertainty due to the lack of data and knowledge. We discuss an uncertainty assessment within the linear-additivity model using the approach of Monte Carlo sampling from subjective error distributions that represent the lack of knowledge in each factor to quantify the overall uncertainty in risk projections. Calculations are performed using the space radiation environment and transport codes for several Mars mission scenarios. This approach leads to estimates of the uncertainties in cancer risk projections of 400-600% for a Mars mission. The uncertainties in the quality factors are dominant. Using safety standards developed for low-Earth orbit, long-term space missions (>90 days) outside the Earth's magnetic field are currently unacceptable if the confidence levels in risk projections are considered. Because GCR exposures involve multiple particle or delta-ray tracks per cellular array, our results suggest that the shape of the dose response at low dose rates may be an additional uncertainty for estimating space radiation risks.

  5. NASA'S Space Launch System Mission Capabilities for Exploration

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; Crumbly, Christopher M.; Robinson, Kimberly F.

    2015-01-01

    Designed to enable human space exploration missions, including eventual landings on Mars, NASA’s Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the lunar vicinity to high-energy transits through the outer solar system. Developed with the goals of safety, affordability and sustainability in mind, SLS is a foundational capability for NASA’s future plans for exploration, along with the Orion crew vehicle and upgraded ground systems at the agency’s Kennedy Space Center. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO), greater mass-to-orbit capability than any contemporary launch vehicle. The vehicle will then be evolved into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO, greater even than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle’s potential range of utilization. This presentation will discuss the potential opportunities this vehicle poses for the planetary sciences community, relating the vehicle’s evolution to practical implications for mission capture. As this paper will explain, SLS will be a global launch infrastructure asset, employing sustainable solutions and technological innovations to deliver capabilities for space exploration to power human and robotic systems beyond our Moon and in to

  6. NASA's Space Launch System Mission Capabilities for Exploration

    NASA Technical Reports Server (NTRS)

    Creech, Stephen D.; Crumbly, Christopher M.; Robinson, Kimberly F.

    2015-01-01

    Designed to enable human space exploration missions, including eventual landings on Mars, NASA's Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the lunar vicinity to high-energy transits through the outer solar system. Developed with the goals of safety, affordability and sustainability in mind, SLS is a foundational capability for NASA's future plans for exploration, along with the Orion crew vehicle and upgraded ground systems at the agency's Kennedy Space Center. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO), greater mass-to-orbit capability than any contemporary launch vehicle. The vehicle will then be evolved into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO, greater even than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle's potential range of utilization. This presentation will discuss the potential opportunities this vehicle poses for the planetary sciences community, relating the vehicle's evolution to practical implications for mission capture. As this paper will explain, SLS will be a global launch infrastructure asset, employing sustainable solutions and technological innovations to deliver capabilities for space exploration to power human and robotic systems beyond our Moon and in to deep space.

  7. SpaceBuoy: A University Nanosat Space Weather Mission

    DTIC Science & Technology

    2012-03-26

    the He-304 line. Our very active (more than 30 flights in four years) high altitude balloon project provides rapid turn-around flight experiences...talent. Program students have left Montana State University for jobs with NavSea, Orbital Sciences, Boeing, Tethers Unlimited, MicroSat Systems...and implementation GNC Sensors None Miniature low power magnetoresistive three axis magnetometer To qualify for space flight newly developed

  8. Informatics-based Medical Procedure Assistance during Space Missions

    PubMed Central

    Iyengar, M S; Carruth, T N; Florez-Arango, J; Dunn, K

    2008-01-01

    Currently, paper-based and/or electronic together with telecommunications links to Earth-based physicians are used to assist astronaut crews perform diagnosis and treatment of medical conditions during space travel. However, these have limitations, especially during long duration missions in which telecommunications to earth-based physicians can be delayed. We describe an experimental technology called GuideView in which clinical guidelines are presented in a structured, interactive, multi-modal format and, in each step, clinical instructions are provided simultaneously in voice, text, pictures video or animations. An example application of the system to diagnosis and treatment of space Decompression Sickness is presented. Astronauts performing space walks from the International Space Station are at risk for decompression sickness because the atmospheric pressure of the Extra-vehicular Activity space- suit is significantly less that that of the interior of the Station. PMID:19048089

  9. Space construction system analysis study: Project systems and missions descriptions

    NASA Technical Reports Server (NTRS)

    1979-01-01

    Three project systems are defined and summarized. The systems are: (1) a Solar Power Satellite (SPS) Development Flight Test Vehicle configured for fabrication and compatible with solar electric propulsion orbit transfer; (2) an Advanced Communications Platform configured for space fabrication and compatible with low thrust chemical orbit transfer propulsion; and (3) the same Platform, configured to be space erectable but still compatible with low thrust chemical orbit transfer propulsion. These project systems are intended to serve as configuration models for use in detailed analyses of space construction techniques and processes. They represent feasible concepts for real projects; real in the sense that they are realistic contenders on the list of candidate missions currently projected for the national space program. Thus, they represent reasonable configurations upon which to base early studies of alternative space construction processes.

  10. Autonomous Medical Care for Exploration Class Space Missions

    NASA Technical Reports Server (NTRS)

    Hamilton, Douglas; Smart, Kieran; Melton, Shannon; Polk, James D.; Johnson-Throop, Kathy

    2007-01-01

    The US-based health care system of the International Space Station (ISS) contains several subsystems, the Health Maintenance System, Environmental Health System and the Countermeasure System. These systems are designed to provide primary, secondary and tertiary medical prevention strategies. The medical system deployed in Low Earth Orbit (LEO) for the ISS is designed to enable a "stabilize and transport" concept of operations. In this paradigm, an ill or injured crewmember would be rapidly evacuated to a definitive medical care facility (DMCF) on Earth, rather than being treated for a protracted period on orbit. The medical requirements of the short (7 day) and long duration (up to 6 months) exploration class missions to the Moon are similar to LEO class missions with the additional 4 to 5 days needed to transport an ill or injured crewmember to a DCMF on Earth. Mars exploration class missions are quite different in that they will significantly delay or prevent the return of an ill or injured crewmember to a DMCF. In addition the limited mass, power and volume afforded to medical care will prevent the mission designers from manifesting the entire capability of terrestrial care. NASA has identified five Levels of Care as part of its approach to medical support of future missions including the Constellation program. In order to implement an effective medical risk mitigation strategy for exploration class missions, modifications to the current suite of space medical systems may be needed, including new Crew Medical Officer training methods, treatment guidelines, diagnostic and therapeutic resources, and improved medical informatics.

  11. Sleep, Circadian Rhythms, and Performance During Space Shuttle Missions

    NASA Technical Reports Server (NTRS)

    Neri, David F.; Czeisler, Charles A.; Dijk, Derk-Jan; Wyatt, James K.; Ronda, Joseph M.; Hughes, Rod J.

    2003-01-01

    Sleep and circadian rhythms may be disturbed during spaceflight, and these disturbances can affect crewmembers' performance during waking hours. The mechanisms underlying sleep and circadian rhythm disturbances in space are not well understood, and effective countermeasures are not yet available. We investigated sleep, circadian rhythms, cognitive performance, and light-dark cycles in five astronauts prior to, during, and after the 16-day STS-90 mission and the IO-day STS-95 mission. The efficacy of low-dose, alternative-night, oral melatonin administration as a countermeasure for sleep disturbances was evaluated. During these missions, scheduled rest activity cycles were 20-35 minutes shorter than 24 hours. Light levels on the middeck and in the Spacelab were very low; whereas on the flight deck (which has several windows), they were highly variable. Circadian rhythm abnormalities were observed. During the second half of the missions, the rhythm of urinary cortisol appeared to be delayed relative to the sleep-wake schedule. Performance during wakefulness was impaired. Astronauts slept only about 6.5 hours per day, and subjective sleep quality was lower in space. No beneficial effects of melatonin (0.3 mg administered prior to sleep episodes on alternate nights) were observed. A surprising finding was a marked increase in rapid eye movement (REM) sleep upon return to Earth. We conclude that these Space Shuttle missions were associated with circadian rhythm disturbances, sleep loss, decrements in neurobehavioral performance, and alterations in REM sleep homeostasis. Shorter than 24-hour rest-activity schedules and exposure to light-dark cycles inadequate for optimal circadian synchronization may have contributed to these disturbances.

  12. A Management Model for International Participation in Space Exploration Missions

    NASA Technical Reports Server (NTRS)

    George, Patrick J.; Pease, Gary M.; Tyburski, Timothy E.

    2005-01-01

    This paper proposes an engineering management model for NASA's future space exploration missions based on past experiences working with the International Partners of the International Space Station. The authors have over 25 years of combined experience working with the European Space Agency, Japan Aerospace Exploration Agency, Canadian Space Agency, Italian Space Agency, Russian Space Agency, and their respective contractors in the design, manufacturing, verification, and integration of their elements electric power system into the United States on-orbit segment. The perspective presented is one from a specific sub-system integration role and is offered so that the lessons learned from solving issues of technical and cultural nature may be taken into account during the formulation of international partnerships. Descriptions of the types of unique problems encountered relative to interactions between international partnerships are reviewed. Solutions to the problems are offered, taking into consideration the technical implications. Through the process of investigating each solution, the important and significant issues associated with working with international engineers and managers are outlined. Potential solutions are then characterized by proposing a set of specific methodologies to jointly develop spacecraft configurations that benefits all international participants, maximizes mission success and vehicle interoperability while minimizing cost.

  13. Human interactions during Shuttle/Mir space missions

    NASA Technical Reports Server (NTRS)

    Kanas, N.; Salnitskiy, V.; Grund, E. M.; Weiss, D. S.; Gushin, V.; Kozerenko, O.; Sled, A.; Marmar, C. R.

    2001-01-01

    To improve the interpersonal climate of crewmembers involved with long-duration space missions, it is important to understand the factors affecting their interactions with each other and with members of mission control. This paper will present findings from a recently completed NASA-funded study during the Shuttle/Mir program which evaluated in-group/out-group displacement of negative emotions; changes in tension, cohesion, and leader support over time; and cultural differences. In-flight data were collected from 5 astronauts, 8 cosmonauts, and 42 American and 16 Russian mission control personnel who signed informed consent. Subjects completed a weekly questionnaire that assessed their mood and perception of their work group's interpersonal climate using questions from well-known, standardized measures (Profile of Mood States, Group and Work Environment Scales) and a critical incident log. There was strong evidence for the displacement of tension and dysphoric emotions from crewmembers to mission control personnel and from mission control personnel to management. There was a perceived decrease in commander support during the 2nd half of the missions, and for American crewmembers a novelty effect was found on several subscales during the first few months on-orbit. There were a number of differences between American and Russian responses which suggested that the former were less happy with their interpersonal environment than the latter. Mission control personnel reported more tension and dysphoria than crewmembers, although both groups scored better than other work groups on Earth. Nearly all reported critical incidents came from ground subjects, with Americans and Russians showing important differences in response frequencies.

  14. Human interactions during Shuttle/Mir space missions.

    PubMed

    Kanas, N; Salnitskiy, V; Grund, E M; Weiss, D S; Gushin, V; Kozerenko, O; Sled, A; Marmar, C R

    2001-01-01

    To improve the interpersonal climate of crewmembers involved with long-duration space missions, it is important to understand the factors affecting their interactions with each other and with members of mission control. This paper will present findings from a recently completed NASA-funded study during the Shuttle/Mir program which evaluated in-group/out-group displacement of negative emotions; changes in tension, cohesion, and leader support over time; and cultural differences. In-flight data were collected from 5 astronauts, 8 cosmonauts, and 42 American and 16 Russian mission control personnel who signed informed consent. Subjects completed a weekly questionnaire that assessed their mood and perception of their work group's interpersonal climate using questions from well-known, standardized measures (Profile of Mood States, Group and Work Environment Scales) and a critical incident log. There was strong evidence for the displacement of tension and dysphoric emotions from crewmembers to mission control personnel and from mission control personnel to management. There was a perceived decrease in commander support during the 2nd half of the missions, and for American crewmembers a novelty effect was found on several subscales during the first few months on-orbit. There were a number of differences between American and Russian responses which suggested that the former were less happy with their interpersonal environment than the latter. Mission control personnel reported more tension and dysphoria than crewmembers, although both groups scored better than other work groups on Earth. Nearly all reported critical incidents came from ground subjects, with Americans and Russians showing important differences in response frequencies.

  15. Selection criteria for waste management processes in manned space missions.

    PubMed

    Doll, S; Cothran, B; McGhee, J

    1991-10-01

    Management of waste produced during manned space exploration missions will be an important function of advanced life support systems. Waste materials can be thrown away or recovered for reuse. The first approach relies totally on external supplies to replace depleted resources while the second approach regenerates resources internally. The selection of appropriate waste management processes will be based upon criteria which include mission and hardware characteristics as well as overall system considerations. Mission characteristics discussed include destination, duration, crew size, operating environment, and transportation costs. Hardware characteristics include power, mass and volume requirements as well as suitability for a given task. Overall system considerations are essential to assure optimization for the entire mission rather than for an individual system. For example, a waste management system designed for a short trip to the moon will probably not be the best one for an extended mission to Mars. The purpose of this paper is to develop a methodology to identify and compare viable waste management options for selection of an appropriate waste management system.

  16. Four NASA submillimeter-wavelength space-astrophysics missions

    NASA Technical Reports Server (NTRS)

    Mahoney, M. J.

    1991-01-01

    For several years studies have been conducted at the NASA/Jet Propulsion Laboratory on four passively-cooled submillimeter-wavelength, space observatories. Two exploratory missions were studied: a 2.5-m Submillimeter Explorer (SMME) and a more ambitious 3.7-m Submillimeter Imager and Line Survey (SMILS). Only one of these missions would actually be flown, and its goal would be to perform a high-spectral-resolution survey of several hundreds of sources at wavelengths between 100 and about 750 microns with modest angular resolution. Following either SMME or SMILS, the Large Deployable Reflector (LDR) and/or the Synthesis Array for Lunar Submillimeter Astronomy (SALSA) would be flown. LDR is a 10- to 20-m diameter telescope with greatly increased sensitivity and imaging capabilities compared to the exploratory missions. SALSA is a lunar-based array consisting of twelve 3.5-m diameter telescopes with a maximum baseline of nearly 1-km. With operating wavelengths between 30 and 500 microns, SALSA would achieve 10 milliarcsecond angular resolution, and thus could explore source structure in much greater detail than the other missions. The purpose of this paper is to present the current conceptual designs for these missions, and to discuss the most recent payload analysis.

  17. Scientific and Mission Requirements of Next-generation Space Infrared Space Telescope SPICA

    NASA Astrophysics Data System (ADS)

    Matsuhara, Hideo; Nakagawa, Takao; Ichikawa, Takashi; Takami, Michihiro; Sakon, Itsuki

    SPICA (Space Infrared Telescope for Cosmology Astrophysics) is a next-generation space tele-scope for mid-and far-infrared astronomy, based on the heritage of AKARI, Spitzer, and Her-schel, Here we introduce Mission Requirement Document (MRD), where scientific and mission requirement of SPICA are described. The MRD clarifies the objectives of the SPICA mission. These objectives are more concretely expressed by various scientific targets, and based on these targets, the mission requirements, such as required specifications of the mission instrumenta-tions, scientific operations etc. are defined. Also the success criteria, by which the evaluation of the mission achievement will be addressed, are clearly described. The mission requirements described here will give the baseline of the study of the system requirements. In the future, The MRD will also be used to confirm the development status, system performance, and operational results on orbit etc. are well in-line with the mission requirements. To summarize, the most important mission requirement of SPICA is to realize a large, mono-lithic (not segmented) 3-m class or larger mirror cooled down below 6K, in order to perform extremely deep imaging and spectroscopy at 5-210µm.

  18. Micro-Inspector Spacecraft for Space Exploration Missions

    NASA Technical Reports Server (NTRS)

    Mueller, Juergen; Alkalai, Leon; Lewis, Carol

    2005-01-01

    NASA is seeking to embark on a new set of human and robotic exploration missions back to the Moon, to Mars, and destinations beyond. Key strategic technical challenges will need to be addressed to realize this new vision for space exploration, including improvements in safety and reliability to improve robustness of space operations. Under sponsorship by NASA's Exploration Systems Mission, the Jet Propulsion Laboratory (JPL), together with its partners in government (NASA Johnson Space Center) and industry (Boeing, Vacco Industries, Ashwin-Ushas Inc.) is developing an ultra-low mass (<3.0 kg) free-flying micro-inspector spacecraft in an effort to enhance safety and reduce risk in future human and exploration missions. The micro-inspector will provide remote vehicle inspections to ensure safety and reliability, or to provide monitoring of in-space assembly. The micro-inspector spacecraft represents an inherently modular system addition that can improve safety and support multiple host vehicles in multiple applications. On human missions, it may help extend the reach of human explorers, decreasing human EVA time to reduce mission cost and risk. The micro-inspector development is the continuation of an effort begun under NASA's Office of Aerospace Technology Enabling Concepts and Technology (ECT) program. The micro-inspector uses miniaturized celestial sensors; relies on a combination of solar power and batteries (allowing for unlimited operation in the sun and up to 4 hours in the shade); utilizes a low-pressure, low-leakage liquid butane propellant system for added safety; and includes multi-functional structure for high system-level integration and miniaturization. Versions of this system to be designed and developed under the H&RT program will include additional capabilities for on-board, vision-based navigation, spacecraft inspection, and collision avoidance, and will be demonstrated in a ground-based, space-related environment. These features make the micro

  19. A space-to-space microwave wireless power transmission experiential mission using small satellites

    NASA Astrophysics Data System (ADS)

    Bergsrud, Corey; Straub, Jeremy

    2014-10-01

    A space solar microwave power transfer system (SSMPTS) may represent a paradigm shift to how space missions in Earth orbit are designed. A SSMPTS may allow a smaller receiving surface to be utilized on the receiving craft due to the higher-density power transfer (compared to direct solar flux) from a SSMPTS supplier craft; the receiving system is also more efficient and requires less mass and volume. The SSMPTS approach also increases mission lifetime, as antenna systems do not degrade nearly as quickly as solar panels. The SSMPTS supplier craft (instead) can be replaced as its solar panels degrade, a mechanism for replacing panels can be utilized or the SSMPTS can be maneuvered closer to a subset of consumer spacecraft. SSMPTS can also be utilized to supply power to spacecraft in eclipse and to supply variable amounts of power, based on current mission needs, to power the craft or augment other power systems. A minimal level of orbital demonstrations of SSP technologies have occurred. A mission is planned to demonstrate and characterize the efficacy of space-to-space microwave wireless power transfer. This paper presents an overview of this prospective mission. It then discusses the spacecraft system (comprised of an ESPA/SmallSat-class spacecraft and a 1-U CubeSat), launch options, mission operations and the process of evaluating mission outcomes.

  20. Potential civil mission applications for space nuclear power systems

    NASA Technical Reports Server (NTRS)

    Ambrus, J. H.; Beatty, R. G. G.

    1985-01-01

    It is pointed out that the energy needs of spacecraft over the last 25 years have been met by photovoltaic arrays with batteries, primary fuel cells, and radioisotope thermoelectric generators (RTG). However, it might be difficult to satisfy energy requirements for the next generation of space missions with the currently used energy sources. Applications studies have emphasized the need for a lighter, cheaper, and more compact high-energy source than the scaling up of current technologies would permit. These requirements could be satisfied by a nuclear reactor power system. The joint NASA/DOD/DOE SP-100 program is to explore and evaluate this option. Critical elements of the technology are also to be developed, taking into account space reactor systems of the 100 kW class. The present paper is concerned with some of the civil mission categories and concepts which are enabled or significantly enhanced by the performance characteristics of a nuclear reactor energy system.