Launch summary for 1980

NASA Technical Reports Server (NTRS)

Vostreys, R. W.

1981-01-01

Sounding rockets, artificial Earth satellites, and space probes launched betweeen January 1 and December 31, 1980 are listed. Data tabulated for the rocket launchings show launching site, instruments carried, date of launch, agency rocket identification, sponsoring country, experiment discipline, peak altitude, and the experimenter or institution responsible. Tables for satellites and space probes show COSPAR designation, spacecraft name, country, launch date, epoch date, orbit type, apoapsis, periapsis and inclination period. The functions and responsibilities of the World Data Center and the areas of scientific interest at the seven subcenters are defined. An alphabetical listing of experimenters using the sounding rockets is also provided.

Large Field of View PIV Measurements of Air Entrainment by SLS SMAT Water Sound Suppression System

NASA Astrophysics Data System (ADS)

Stegmeir, Matthew; Pothos, Stamatios; Bissell, Dan

2015-11-01

Water-based sound suppressions systems have been used to reduce the acoustic impact of space vehicle launches. Water flows at a high rate during launch in order to suppress Engine Generated Acoustics and other potentially damaging sources of noise. For the Space Shuttle, peak flow rates exceeded 900,000 gallons per minute. Such large water flow rates have the potential to induce substantial entrainment of the surrounding air, affecting the launch conditions and generating airflow around the launch vehicle. Validation testing is necessary to quantify this impact for future space launch systems. In this study, PIV measurements were performed to map the flow field above the SMAT sub-scale launch vehicle scaled launch stand. Air entrainment effects generated by a water-based sound suppression system were studied. Mean and fluctuating fluid velocities were mapped up to 1m above the test stand deck and compared to simulation results. Measurements performed with NASA MSFC.

GPS Sounding Rocket Developments

NASA Technical Reports Server (NTRS)

Bull, Barton

1999-01-01

Sounding rockets are suborbital launch vehicles capable of carrying scientific payloads several hundred miles in altitude. These missions return a variety of scientific data including; chemical makeup and physical processes taking place In the atmosphere, natural radiation surrounding the Earth, data on the Sun, stars, galaxies and many other phenomena. In addition, sounding rockets provide a reasonably economical means of conducting engineering tests for instruments and devices used on satellites and other spacecraft prior to their use in more expensive activities. The NASA Sounding Rocket Program is managed by personnel from Goddard Space Flight Center Wallops Flight Facility (GSFC/WFF) in Virginia. Typically around thirty of these rockets are launched each year, either from established ranges at Wallops Island, Virginia, Poker Flat Research Range, Alaska; White Sands Missile Range, New Mexico or from Canada, Norway and Sweden. Many times launches are conducted from temporary launch ranges in remote parts of the world requi6ng considerable expense to transport and operate tracking radars. An inverse differential GPS system has been developed for Sounding Rocket. This paper addresses the NASA Wallops Island history of GPS Sounding Rocket experience since 1994 and the development of a high accurate and useful system.

Acoustic Test Results of Melamine Foam with Application to Payload Fairing Acoustic Attenuation Systems

NASA Technical Reports Server (NTRS)

Hughes, William O.; McNelis, Anne M.

2014-01-01

A spacecraft at launch is subjected to a harsh acoustic and vibration environment resulting from the passage of acoustic energy, created during the liftoff of a launch vehicle, through the vehicle's payload fairing. In order to ensure the mission success of the spacecraft it is often necessary to reduce the resulting internal acoustic sound pressure levels through the usage of acoustic attenuation systems. Melamine foam, lining the interior walls of the payload fairing, is often utilized as the main component of such a system. In order to better understand the acoustic properties of melamine foam, with the goal of developing improved acoustic attenuation systems, NASA has recently performed panel level testing on numerous configurations of melamine foam acoustic treatments at the Riverbank Acoustical Laboratory. Parameters assessed included the foam's thickness and density, as well as the effects of a top outer cover sheet material and mass barriers embedded within the foam. This testing followed the ASTM C423 standard for absorption and the ASTM E90 standard for transmission loss. The acoustic test data obtained and subsequent conclusions are the subjects of this paper.

Oceanographic Measurements Program Review.

DTIC Science & Technology

1982-03-01

prototype Advanced Microstructure Profiler (AMP) was completed and the unit was operationally tested in local waters (Lake Washington and Puget Sound ...Expendables ....... ............. ..21 A.W. Green The Developent of an Air-Launched ................ 25 Expendable Sound Velocimeter (AXSV); R. Bixby...8217., ,? , .’,*, ;; .,’...; "’ . :" .* " . .. ". ;’ - ~ ~ ~ ~ ’ V’ 7T W, V a .. -- THE DEVELOPMENT OF AN AIR-LAUNCHED EXPENDABLE SOUND VELOCIMETER (AXSV) Richard Bixby

Efficacy of passive acoustic screening: implications for the design of imager and MR-suite.

PubMed

Moelker, Adriaan; Vogel, Mika W; Pattynama, Peter M T

2003-02-01

To investigate the efficacy of passive acoustic screening in the magnetic resonance (MR) environment by reducing direct and indirect MR-related acoustic noise, both from the patient's and health worker's perspective. Direct acoustic noise refers to sound originating from the inner and outer shrouds of the MR imager, and indirect noise to acoustic reflections from the walls of the MR suite. Sound measurements were obtained inside the magnet bore (patient position) and at the entrance of the MR imager (health worker position). Inner and outer shrouds and walls were lined with thick layers of sound insulation to eliminate the direct and indirect acoustic pathways. Sound pressure levels (SPLs) and octave band frequencies were acquired during various MR imaging sequences at 1.5 T. Inside the magnet bore, direct acoustic noise radiating from the inner shroud was most relevant, with substantial reductions of up to 18.8 dB when using passive screening of the magnetic bore. At the magnet bore entrance, blocking acoustic noise from the outer shroud and reflections showed significant reductions of 4.5 and 2.8 dB, respectively, and 9.4 dB when simultaneously applied. Inner shroud coverage contributed minimally to the overall SPL reduction. Maximum noise reduction by passive acoustic screening can be achieved by reducing direct sound conduction through the inner and outer shrouds. Additional measures to optimize the acoustic properties of the MR suite have only little effect. Copyright 2003 Wiley-Liss, Inc.

Static length changes of cochlear outer hair cells can tune low-frequency hearing

PubMed Central

Ciganović, Nikola; Warren, Rebecca L.; Keçeli, Batu; Jacob, Stefan

2018-01-01

The cochlea not only transduces sound-induced vibration into neural spikes, it also amplifies weak sound to boost its detection. Actuators of this active process are sensory outer hair cells in the organ of Corti, whereas the inner hair cells transduce the resulting motion into electric signals that propagate via the auditory nerve to the brain. However, how the outer hair cells modulate the stimulus to the inner hair cells remains unclear. Here, we combine theoretical modeling and experimental measurements near the cochlear apex to study the way in which length changes of the outer hair cells deform the organ of Corti. We develop a geometry-based kinematic model of the apical organ of Corti that reproduces salient, yet counter-intuitive features of the organ’s motion. Our analysis further uncovers a mechanism by which a static length change of the outer hair cells can sensitively tune the signal transmitted to the sensory inner hair cells. When the outer hair cells are in an elongated state, stimulation of inner hair cells is largely inhibited, whereas outer hair cell contraction leads to a substantial enhancement of sound-evoked motion near the hair bundles. This novel mechanism for regulating the sensitivity of the hearing organ applies to the low frequencies that are most important for the perception of speech and music. We suggest that the proposed mechanism might underlie frequency discrimination at low auditory frequencies, as well as our ability to selectively attend auditory signals in noisy surroundings. PMID:29351276

Launch summary for 1978

NASA Technical Reports Server (NTRS)

Vostreys, R. W.

1978-01-01

Sounding rocket, satellite, and space probe launchings are presented. Time, date, and location of the launches are provided. The sponsoring countries and the institutions responsible for the launch are listed.

Sound generated by instability waves of supersonic flows. I Two-dimensional mixing layers. II - Axisymmetric jets

NASA Technical Reports Server (NTRS)

Tam, C. K. W.; Burton, D. E.

1984-01-01

An investigation is conducted of the phenomenon of sound generation by spatially growing instability waves in high-speed flows. It is pointed out that this process of noise generation is most effective when the flow is supersonic relative to the ambient speed of sound. The inner and outer asymptotic expansions corresponding to an excited instability wave in a two-dimensional mixing layer and its associated acoustic fields are constructed in terms of the inner and outer spatial variables. In matching the solutions, the intermediate matching principle of Van Dyke and Cole is followed. The validity of the theory is tested by applying it to an axisymmetric supersonic jet and comparing the calculated results with experimental measurements. Very favorable agreements are found both in the calculated instability-wave amplitude distribution (the inner solution) and the near pressure field level contours (the outer solution) in each case.

Single-unit labeling of medial olivocochlear neurons: the cochlear frequency map for efferent axons.

PubMed

Brown, M Christian

2014-06-01

Medial olivocochlear (MOC) neurons are efferent neurons that project axons from the brain to the cochlea. Their action on outer hair cells reduces the gain of the "cochlear amplifier," which shifts the dynamic range of hearing and reduces the effects of noise masking. The MOC effects in one ear can be elicited by sound in that ipsilateral ear or by sound in the contralateral ear. To study how MOC neurons project onto the cochlea to mediate these effects, single-unit labeling in guinea pigs was used to study the mapping of MOC neurons for neurons responsive to ipsilateral sound vs. those responsive to contralateral sound. MOC neurons were sharply tuned to sound frequency with a well-defined characteristic frequency (CF). However, their labeled termination spans in the organ of Corti ranged from narrow to broad, innervating between 14 and 69 outer hair cells per axon in a "patchy" pattern. For units responsive to ipsilateral sound, the midpoint of innervation was mapped according to CF in a relationship generally similar to, but with more variability than, that of auditory-nerve fibers. Thus, based on CF mappings, most of the MOC terminations miss outer hair cells involved in the cochlear amplifier for their CF, which are located more basally. Compared with ipsilaterally responsive neurons, contralaterally responsive neurons had an apical offset in termination and a larger span of innervation (an average of 10.41% cochlear distance), suggesting that when contralateral sound activates the MOC reflex, the actions are different than those for ipsilateral sound. Copyright © 2014 the American Physiological Society.

Single-unit labeling of medial olivocochlear neurons: the cochlear frequency map for efferent axons

PubMed Central

2014-01-01

Medial olivocochlear (MOC) neurons are efferent neurons that project axons from the brain to the cochlea. Their action on outer hair cells reduces the gain of the “cochlear amplifier,” which shifts the dynamic range of hearing and reduces the effects of noise masking. The MOC effects in one ear can be elicited by sound in that ipsilateral ear or by sound in the contralateral ear. To study how MOC neurons project onto the cochlea to mediate these effects, single-unit labeling in guinea pigs was used to study the mapping of MOC neurons for neurons responsive to ipsilateral sound vs. those responsive to contralateral sound. MOC neurons were sharply tuned to sound frequency with a well-defined characteristic frequency (CF). However, their labeled termination spans in the organ of Corti ranged from narrow to broad, innervating between 14 and 69 outer hair cells per axon in a “patchy” pattern. For units responsive to ipsilateral sound, the midpoint of innervation was mapped according to CF in a relationship generally similar to, but with more variability than, that of auditory-nerve fibers. Thus, based on CF mappings, most of the MOC terminations miss outer hair cells involved in the cochlear amplifier for their CF, which are located more basally. Compared with ipsilaterally responsive neurons, contralaterally responsive neurons had an apical offset in termination and a larger span of innervation (an average of 10.41% cochlear distance), suggesting that when contralateral sound activates the MOC reflex, the actions are different than those for ipsilateral sound. PMID:24598524

Freezing Fog Formation in a Supercooled Boundary Layer: Solving the Winter Fog Forecasting Challenge for Elmendorf Air Force Base, Alaska

DTIC Science & Technology

2007-03-01

from PANC launched at 00Z on 28 Nov 2005. From UWSP, 2007. ............................................................................ 34 Figure 17...Upper-air sounding from PANC launched at 12Z on 28 Nov 2005. From UWSP, 2007...sounding from PANC launched at 00Z (top) and 12Z (bottom) on 4 Dec 2005. From UWSP, 2007...................................... 47 Figure 29. Sea-level

Sounding rockets in Antarctica

NASA Technical Reports Server (NTRS)

Alford, G. C.; Cooper, G. W.; Peterson, N. E.

1982-01-01

Sounding rockets are versatile tools for scientists studying the atmospheric region which is located above balloon altitudes but below orbital satellite altitudes. Three NASA Nike-Tomahawk sounding rockets were launched from Siple Station in Antarctica in an upper atmosphere physics experiment in the austral summer of 1980-81. The 110 kg payloads were carried to 200 km apogee altitudes in a coordinated project with Arcas rocket payloads and instrumented balloons. This Siple Station Expedition demonstrated the feasibility of launching large, near 1,000 kg, rocket systems from research stations in Antarctica. The remoteness of research stations in Antarctica and the severe environment are major considerations in planning rocket launching expeditions.

Collaborative Sounding Rocket launch in Alaska and Development of Hybrid Rockets

NASA Astrophysics Data System (ADS)

Ono, Tomohisa; Tsutsumi, Akimasa; Ito, Toshiyuki; Kan, Yuji; Tohyama, Fumio; Nakashino, Kyouichi; Hawkins, Joseph

Tokai University student rocket project (TSRP) was established in 1995 for a purpose of the space science and engineering hands-on education, consisting of two space programs; the one is sounding rocket experiment collaboration with University of Alaska Fairbanks and the other is development and launch of small hybrid rockets. In January of 2000 and March 2002, two collaborative sounding rockets were successfully launched at Poker Flat Research Range in Alaska. In 2001, the first Tokai hybrid rocket was successfully launched at Alaska. After that, 11 hybrid rockets were launched to the level of 180-1,000 m high at Hokkaido and Akita in Japan. Currently, Tokai students design and build all parts of the rockets. In addition, they are running the organization and development of the project under the tight budget control. This program has proven to be very effective in providing students with practical, real-engineering design experience and this program also allows students to participate in all phases of a sounding rocket mission. Also students learn scientific, engineering subjects, public affairs and system management through experiences of cooperative teamwork. In this report, we summarize the TSRP's hybrid rocket program and discuss the effectiveness of the program in terms of educational aspects.

Acoustic properties of a short-finned pilot whale head with insight into temperature influence on tissues' sound velocity.

PubMed

Dong, Jianchen; Song, Zhongchang; Li, Songhai; Gong, Zining; Li, Kuan; Zhang, Peijun; Zhang, Yu; Zhang, Meng

2017-10-01

Acoustic properties of odontocete head tissues, including sound velocity, density, and acoustic impedance, are important parameters to understand dynamics of its echolocation. In this paper, acoustic properties of head tissues from a freshly dead short-finned pilot whale (Globicephala macrorhynchus) were reconstructed using computed tomography (CT) and ultrasound. The animal's forehead soft tissues were cut into 188 ordered samples. Sound velocity, density, and acoustic impedance of each sample were either directly measured or calculated by formula, and Hounsfield Unit values (HUs) were obtained from CT scanning. According to relationships between HUs and sound velocity, HUs and density, as well as HUs and acoustic impedance, distributions of acoustic properties in the head were reconstructed. The inner core in the melon with low-sound velocity and low-density is an evidence for its potential function of sound focusing. The increase in acoustic impedance of forehead tissues from inner core to outer layer may be important for the acoustic impedance matching between the outer layer tissue and seawater. In addition, temperature dependence of sound velocity in soft tissues was also examined. The results provide a guide to the simulation of the sound emission of the short-finned pilot whale.

Peaceful Use of Outer Space: principles of Japanese Policies on Utilization and Activities in Outer space

NASA Astrophysics Data System (ADS)

Kosuge, Toshio

2002-01-01

" P e aceful use of outer space of outer space.....Principles of exploitation of outer space was passed in the Japanese Diet. It clearly mentioned that any activity of launching space object into outer space and developing launching rocket should be exclusively for peaceful purpose. NASDA was also established based upon the same principles of the public law. Japanese interpretation of Space Treaty and other related international agreements has been more strict on peaceful use of outer space, like non-military use rather than non-aggressive, because of influence of Japanese Constitution. Treaty and other agreements is analyzed through rapid development of its space activities, technologies and international cooperation with other space powers. Through more than thirty years experiences in space activities in public and private sectors, Japanese domestic laws and policies have not been changed in relation with basic principles. and laws relating to space activities in order to develop new space law and more international cooperation for space utilization rather than military use in new century.

Electrically evoked reticular lamina and basilar membrane vibrations in mice with alpha tectorin C1509G mutation

NASA Astrophysics Data System (ADS)

Ren, Tianying; He, Wenxuan

2015-12-01

Mechanical coupling between the tectorial membrane and the hair bundles of outer hair cells is crucial for stimulating mechanoelectrical transduction channels, which convert sound-induced vibrations into electrical signal, and for transmitting outer hair cell-generated force back to the basilar membrane to boost hearing sensitivity. It has been demonstrated that the detached tectorial membrane in mice with C1509G alpha tectorin mutation caused hearing loss, but enhanced electrically evoked otoacoustic emissions. To understand how the mutated cochlea emits sounds, the reticular lamina and basilar membrane vibrations were measured in the electrically stimulated cochlea in this study. The results showed that the electrically evoked basilar membrane vibration decreased dramatically while the reticular lamina vibration and otoacoustic emissions exhibited no significant change in C1509G mutation mice. This result indicates that a functional cochlear amplifier and a normal basilar membrane vibration are not required for the outer hair cell-generated sound to exit the cochlea.

Aerocoat 7 Replacement Coatings

NASA Technical Reports Server (NTRS)

2008-01-01

Kennedy Space Center has used Aerocoat 7 (AR-7) to protect stainless-steel flex hoses at Launch Complex (LC-39) and hydraulic lines of the Mobile Launcher Platform (MLP) because it provides excellent corrosion protection in low-temperature applications. The Sovereign Company produced AR-7 exclusively for NASA but discontinued production because the coating released high levels of volatile organic compounds (VOCs) and had a significant environmental impact. The purpose of this project was to select and evaluate potential replacement coatings for AR-7 that would be more environmentally sound. The physical and mechanical properties of commercially available coatings were investigated through the Internet. The ideal coating would be fluid enough to penetrate the outer mesh of a stainless-steel flex hose and coat the inner hose, and flexible enough to withstand the movement of the hose, as well as the expansion and contraction of its metal caused by changes in temperature.

Call sign intelligibility improvement using a spatial auditory display

NASA Technical Reports Server (NTRS)

Begault, Durand R.

1994-01-01

A spatial auditory display was designed for separating the multiple communication channels usually heard over one ear to different virtual auditory positions. The single 19 foot rack mount device utilizes digital filtering algorithms to separate up to four communication channels. The filters use four different binaural transfer functions, synthesized from actual outer ear measurements, to impose localization cues on the incoming sound. Hardware design features include 'fail-safe' operation in the case of power loss, and microphone/headset interfaces to the mobile launch communication system in use at KSC. An experiment designed to verify the intelligibility advantage of the display used 130 different call signs taken from the communications protocol used at NASA KSC. A 6 to 7 dB intelligibility advantage was found when multiple channels were spatially displayed, compared to monaural listening. The findings suggest that the use of a spatial auditory display could enhance both occupational and operational safety and efficiency of NASA operations.

Liquid Iron Alloys with Hydrogen at Outer Core Conditions by First Principles

NASA Astrophysics Data System (ADS)

Umemoto, K.; Hirose, K.

2015-12-01

Since the density of the outer core deduced from seismic data is about 10% lower than that of pure iron at core pressures and temperatures (P-T), it is widely believed that the outer core includes one or more light elements. Although intensive experimental and theoretical studies have been performed so far, the light element in the core has not yet been identified. Comparison of the density and sound velocity of liquid iron alloys with observations, such as the PREM, is a promising way to determine the species and quantity of light alloying component(s) in the outer core. Here we report the results of a first-principles molecular dynamics study on liquid iron alloyed with hydrogen, one of candidates of the light elements. Hydrogen had been much less studied than other candidates. However, hydrogen has been known to reduce the melting temperature of Fe-H solid [1]. Furthermore, very recently, Nomura et al. argued that the outer core may include 24 at.% H in order to be molten under relatively low temperature (< 3600 K) [2]. Since then hydrogen has attracted strong interests. We clarify the effects of hydrogen on density and sound velocity of liquid iron alloys under outer core P-T conditions. It is shown that ~1 wt% hydrogen can reproduce PREM density and sound velocity simultaneously very well. In addition, we show the presence of hydrogen rather reduces Gruneisen parameters. It indicates that, if hydrogen exists in the outer core, temperature profile of the outer core could be changed considerably from one estimated so far. [1] Sakamaki, K., E. Takahashi, Y. Nakajima, Y. Nishihara, K. Funakoshi, T. Suzuki, and Y. Fukai, Phys. Earth Planet. Inter., 174, 192-201 (2009). [2] Nomura, R., K. Hirose, K. Uesugi, Y. Ohishi, A. Tsuchiyama, A. Miyake, and Y. Ueno, Science 31, 522-525 (2014).

Ear Deformations Give Bats a Physical Mechanism for Fast Adaptation of Ultrasonic Beam Patterns

NASA Astrophysics Data System (ADS)

Gao, Li; Balakrishnan, Sreenath; He, Weikai; Yan, Zhen; Müller, Rolf

2011-11-01

A large number of mammals, including humans, have intricate outer ear shapes that diffract incoming sound in a direction- and frequency-specific manner. Through this physical process, the outer ear shapes encode sound-source information into the sensory signals from each ear. Our results show that horseshoe bats could dynamically control these diffraction processes through fast nonrigid ear deformations. The bats’ ear shapes can alter between extreme configurations in about 100 ms and thereby change their acoustic properties in ways that would suit different acoustic sensing tasks.

Trajectory and System Analysis For Outer-Planet Solar-Electric Propulsion Missions

NASA Technical Reports Server (NTRS)

Cupples, Michael; Woo, Byoungsam; Coverstone, Victoria L.; Hartmann, John W.

2004-01-01

Outer-planet mission and systems analyses are performed using three next generation solar-electric ion thruster models. The impact of variations in thruster model, flight time, launch vehicle, propulsion and power systems characteristics is investigated. All presented trajectories have a single Venus gravity assist and maximize the delivered mass to Saturn or Neptune. The effect of revolution ratio - the ratio of Venusian orbital period to the flight time between launch and flyby dates - is also discussed.

Automated design of gravity-assist trajectories to Mars and the outer planets

NASA Technical Reports Server (NTRS)

Longuski, James M.; Williams, Steve N.

1991-01-01

In this paper, a new approach to planetary mission design is described which automates the search for gravity-assist trajectories. This method finds all conic solutions given a range of launch dates, a range of launch energies and a set of target planets. The new design tool is applied to the problems of finding multiple encounter trajectories to the outer planets and Venus gravity-assist trajectories to Mars. The last four-planet grand tour opportunity (until the year 2153) is identified. It requires an earth launch in 1996 and encounters Jupiter, Uranus, Neptune, and Pluto. Venus gravity-assist trajectories to Mars for the 30 year period 1995-2024 are examined. It is shown that in many cases these trajectories require less launch energy to reach Mars than direct ballistic trajectories.

Numerical Comparison of Active Acoustic and Structural Noise Control in a Stiffened Double Wall Cylinder

NASA Technical Reports Server (NTRS)

Grosveld, Ferdinand W.

1996-01-01

The active acoustic and structural noise control characteristics of a double wall cylinder with and without ring stiffeners were numerically evaluated. An exterior monopole was assumed to acoustically excite the outside of the double wall cylinder at an acoustic cavity resonance frequency. Structural modal vibration properties of the inner and outer shells were analyzed by post-processing the results from a finite element analysis. A boundary element approach was used to calculate the acoustic cavity response and the coupled structural-acoustic interaction. In the frequency region of interest, below 500 Hz, all structural resonant modes were found to be acoustically slow and the nonresonant modal response to be dominant. Active sound transmission control was achieved by control forces applied to the inner or outer shell, or acoustic control monopoles placed just outside the inner or outer shell. A least mean square technique was used to minimize the interior sound pressures at the nodes of a data recovery mesh. Results showed that single acoustic control monopoles placed just outside the inner or outer shells resulted in better sound transmission control than six distributed point forces applied to either one of the shells. Adding stiffeners to the double wall structure constrained the modal vibrations of the shells, making the double wall stiffer with associated higher modal frequencies. Active noise control obtained for the stiffened double wall configurations was less than for the unstiffened cylinder. In all cases, the acoustic control monopoles controlled the sound transmission into the interior better than the structural control forces.

The NASA Sounding Rocket Program and space sciences.

PubMed

Gurkin, L W

1992-10-01

High altitude suborbital rockets (sounding rockets) have been extensively used for space science research in the post-World War II period; the NASA Sounding Rocket Program has been on-going since the inception of the Agency and supports all space science disciplines. In recent years, sounding rockets have been utilized to provide a low gravity environment for materials processing research, particularly in the commercial sector. Sounding rockets offer unique features as a low gravity flight platform. Quick response and low cost combine to provide more frequent spaceflight opportunities. Suborbital spacecraft design practice has achieved a high level of sophistication which optimizes the limited available flight times. High data-rate telemetry, real-time ground up-link command and down-link video data are routinely used in sounding rocket payloads. Standard, off-the-shelf, active control systems are available which limit payload body rates such that the gravitational environment remains less than 10(-4) g during the control period. Operational launch vehicles are available which can provide up to 7 minutes of experiment time for experiment weights up to 270 kg. Standard payload recovery systems allow soft impact retrieval of payloads. When launched from White Sands Missile Range, New Mexico, payloads can be retrieved and returned to the launch site within hours.

The NASA Sounding Rocket Program and space sciences

NASA Technical Reports Server (NTRS)

Gurkin, L. W.

1992-01-01

High altitude suborbital rockets (sounding rockets) have been extensively used for space science research in the post-World War II period; the NASA Sounding Rocket Program has been on-going since the inception of the Agency and supports all space science disciplines. In recent years, sounding rockets have been utilized to provide a low gravity environment for materials processing research, particularly in the commercial sector. Sounding rockets offer unique features as a low gravity flight platform. Quick response and low cost combine to provide more frequent spaceflight opportunities. Suborbital spacecraft design practice has achieved a high level of sophistication which optimizes the limited available flight times. High data-rate telemetry, real-time ground up-link command and down-link video data are routinely used in sounding rocket payloads. Standard, off-the-shelf, active control systems are available which limit payload body rates such that the gravitational environment remains less than 10(-4) g during the control period. Operational launch vehicles are available which can provide up to 7 minutes of experiment time for experiment weights up to 270 kg. Standard payload recovery systems allow soft impact retrieval of payloads. When launched from White Sands Missile Range, New Mexico, payloads can be retrieved and returned to the launch site within hours.

The Adaptable, Deployable Entry and Placement Technology (ADEPT)

NASA Technical Reports Server (NTRS)

Wercinski, Paul

2017-01-01

The initial system-level development of the nano-ADEPT architecture will culminate in the launch of a 0.7 meter deployed diameter ADEPT sounding rocket flight experiment named, SR-1. Launch is planned for August 2017. The test will utilize the NASA Flight Opportunities Program sounding rocket platform provided by UP Aerospace to launch SR-1 to an apogee over 100 km and achieve re-entry conditions with a peak velocity near Mach 3. The SR-1 flight experiment will demonstrate most of the primary end-to-end mission stages including: launch in a stowed configuration, separation and deployment in exo-atmospheric conditions, and passive ballistic re-entry of a 70-degree half-angle faceted cone geometry.

Linear models for sound from supersonic reacting mixing layers

NASA Astrophysics Data System (ADS)

Chary, P. Shivakanth; Samanta, Arnab

2016-12-01

We perform a linearized reduced-order modeling of the aeroacoustic sound sources in supersonic reacting mixing layers to explore their sensitivities to some of the flow parameters in radiating sound. Specifically, we investigate the role of outer modes as the effective flow compressibility is raised, when some of these are expected to dominate over the traditional Kelvin-Helmholtz (K-H) -type central mode. Although the outer modes are known to be of lesser importance in the near-field mixing, how these radiate to the far-field is uncertain, on which we focus. On keeping the flow compressibility fixed, the outer modes are realized via biasing the respective mean densities of the fast (oxidizer) or slow (fuel) side. Here the mean flows are laminar solutions of two-dimensional compressible boundary layers with an imposed composite (turbulent) spreading rate, which we show to significantly alter the growth of instability waves by saturating them earlier, similar to in nonlinear calculations, achieved here via solving the linear parabolized stability equations. As the flow parameters are varied, instability of the slow modes is shown to be more sensitive to heat release, potentially exceeding equivalent central modes, as these modes yield relatively compact sound sources with lesser spreading of the mixing layer, when compared to the corresponding fast modes. In contrast, the radiated sound seems to be relatively unaffected when the mixture equivalence ratio is varied, except for a lean mixture which is shown to yield a pronounced effect on the slow mode radiation by reducing its modal growth.

14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...

14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...

14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...

14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...

14 CFR 431.35 - Acceptable reusable launch vehicle mission risk.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Acceptable reusable launch vehicle mission risk. 431.35 Section 431.35 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... launch flight through orbital insertion of an RLV or vehicle stage or flight to outer space, whichever is...

Hearing with an atympanic ear: good vibration and poor sound-pressure detection in the royal python, Python regius.

PubMed

Christensen, Christian Bech; Christensen-Dalsgaard, Jakob; Brandt, Christian; Madsen, Peter Teglberg

2012-01-15

Snakes lack both an outer ear and a tympanic middle ear, which in most tetrapods provide impedance matching between the air and inner ear fluids and hence improve pressure hearing in air. Snakes would therefore be expected to have very poor pressure hearing and generally be insensitive to airborne sound, whereas the connection of the middle ear bone to the jaw bones in snakes should confer acute sensitivity to substrate vibrations. Some studies have nevertheless claimed that snakes are quite sensitive to both vibration and sound pressure. Here we test the two hypotheses that: (1) snakes are sensitive to sound pressure and (2) snakes are sensitive to vibrations, but cannot hear the sound pressure per se. Vibration and sound-pressure sensitivities were quantified by measuring brainstem evoked potentials in 11 royal pythons, Python regius. Vibrograms and audiograms showed greatest sensitivity at low frequencies of 80-160 Hz, with sensitivities of -54 dB re. 1 m s(-2) and 78 dB re. 20 μPa, respectively. To investigate whether pythons detect sound pressure or sound-induced head vibrations, we measured the sound-induced head vibrations in three dimensions when snakes were exposed to sound pressure at threshold levels. In general, head vibrations induced by threshold-level sound pressure were equal to or greater than those induced by threshold-level vibrations, and therefore sound-pressure sensitivity can be explained by sound-induced head vibration. From this we conclude that pythons, and possibly all snakes, lost effective pressure hearing with the complete reduction of a functional outer and middle ear, but have an acute vibration sensitivity that may be used for communication and detection of predators and prey.

Space Shuttle Crawler Transporter Sound Attenuation Study

NASA Technical Reports Server (NTRS)

Margasahayam, Ravi N.; MacDonald, Rod; Faszer, Clifford

2004-01-01

The crawler transporter (CT) is the world's largest tracked vehicle known, weighing 6 million pounds with a length of 131 feet and a width of 113 feet. The Kennedy Space Center (KSC) has two CTs that were designed and built for the Apollo program in the 1960's, maintained and retrofitted for use in the Space Shuttle program. As a key element of the Space Shuttle ground systems, the crawler transports the entire 12-million-pound stack comprising the orbiter, the mobile launch platform (MLP), the external tank (ET), and the solid rocket boosters (SRB) from the Vehicle Assembly Building (VAB) to the launch pad. This rollout, constituting a 3.5-5.0-mile journey at a top speed of 0.9 miles-per-hour, requires over 8 hours to reach either Launch Complex 39A or B. This activity is only a prelude to the spectacle of sound and fury of the Space Shuttle launch to orbit in less than 10 minutes and traveling at orbital velocities of Mach 24. This paper summarizes preliminary results from the Crawler Transporter Sound Attenuation Study, encompassing test and engineering analysis of significant sound sources to measure and record full frequency spectrum and intensity of the various noise sources and to analyze the conditions of vibration. Additionally, data such as ventilation criteria, plus operational procedures were considered to provide a comprehensive noise suppression design for implementation. To date, sound attenuation study and results on Crawler 2 have shown significant noise reductions ranging from 5 to 24 dBA.

Signal Processing, Pattern Formation and Adaptation in Neural Oscillators

DTIC Science & Technology

2016-11-29

nonlinear oscillations of outer hair cells. We obtained analytical forms for auditory tuning curves of both unidirectionally and bidirectionally coupled...oscillations of outer hair cells in the cochlea, mode-locking of chopper cells to sound in the cochlear nucleus, and entrainment of cortical...oscillations of outer hair cells (e.g., Fredrickson-Hemsing, Ji, Bruinsma, & Bozovic, 2012), mode-locking of choppers in the cochlear nucleus (e.g., Laudanski

Sounding Rocket Launches Successfully from Alaska

NASA Image and Video Library

2015-01-28

A NASA Oriole IV sounding rocket with the Aural Spatial Structures Probe leaves the launch pad on Jan. 28, 2015, from the Poker Flat Research Range in Alaska. Credit: NASA/Lee Wingfield More info: On count day number 15, the Aural Spatial Structures Probe, or ASSP, was successfully launched on a NASA Oriole IV sounding rocket at 5:41 a.m. EST on Jan. 28, 2015, from the Poker Flat Research Range in Alaska. Preliminary data show that all aspects of the payload worked as designed and the principal investigator Charles Swenson at Utah State University described the mission as a “raging success.” “This is likely the most complicated mission the sounding rocket program has ever undertaken and it was not easy by any stretch," said John Hickman, operations manager of the NASA sounding rocket program office at the Wallops Flight Facility, Virginia. "It was technically challenging every step of the way.” “The payload deployed all six sub-payloads in formation as planned and all appeared to function as planned. Quite an amazing feat to maneuver and align the main payload, maintain the proper attitude while deploying all six 7.3-pound sub payloads at about 40 meters per second," said Hickman. Read more: www.nasa.gov/content/assp-sounding-rocket-launches-succes... NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Vandenberg Air Force Base Upper Level Wind Launch Weather Constraints

NASA Technical Reports Server (NTRS)

Shafer, Jaclyn A.; Wheeler, Mark M.

2012-01-01

The 30th Operational Support Squadron Weather Flight (30 OSSWF) provides comprehensive weather services to the space program at Vandenberg Air Force Base (VAFB) in California. One of their responsibilities is to monitor upper-level winds to ensure safe launch operations of the Minuteman III ballistic missile. The 30 OSSWF tasked the Applied Meteorology Unit (AMU) to analyze VAFB sounding data with the goal of determining the probability of violating (PoV) their upper-level thresholds for wind speed and shear constraints specific to this launch vehicle, and to develop a tool that will calculate the PoV of each constraint on the day of launch. In order to calculate the probability of exceeding each constraint, the AMU collected and analyzed historical data from VAFB. The historical sounding data were retrieved from the National Oceanic and Atmospheric Administration Earth System Research Laboratory archive for the years 1994-2011 and then stratified into four sub-seasons: January-March, April-June, July-September, and October-December. The maximum wind speed and 1000-ft shear values for each sounding in each subseason were determined. To accurately calculate the PoV, the AMU determined the theoretical distributions that best fit the maximum wind speed and maximum shear datasets. Ultimately it was discovered that the maximum wind speeds follow a Gaussian distribution while the maximum shear values follow a lognormal distribution. These results were applied when calculating the averages and standard deviations needed for the historical and real-time PoV calculations. In addition to the requirements outlined in the original task plan, the AMU also included forecast sounding data from the Rapid Refresh model. This information provides further insight for the launch weather officers (LWOs) when determining if a wind constraint violation will occur over the next few hours on day of launch. The interactive graphical user interface (GUI) for this project was developed in Microsoft Excel using Visual Basic for Applications. The GUI displays the critical sounding data easily and quickly for the LWOs on day of launch. This tool will replace the existing one used by the 30 OSSWF, assist the LWOs in determining the probability of exceeding specific wind threshold values, and help to improve the overall upper winds forecast for the launch customer.

Low launch-energy trajectories to the outer solar system via Venus and earth gravity-assist flybys

NASA Technical Reports Server (NTRS)

Diehl, Roger; Belbruno, Edward; Bender, David; Myers, Mark; Stetson, Douglas

1988-01-01

Recent cancellation of the program to develop a Centaur upper stage for use in the Space Transportation System (STS) has motivated considerable interest in trajectory modes with low launch-energy requirements to the outer solar system. Flyby encounters of the inner planets, especially Venus and earth, may be used to enable missions to Jupiter, Saturn, and a restricted class of comets. An examination of mission opportunities to these targets is presented through the end of this century using gravity-assist trajectories.

Determining the Probability of Violating Upper-Level Wind Constraints for the Launch of Minuteman III Ballistic Missiles at Vandenberg Air Force Base

NASA Technical Reports Server (NTRS)

Shafer, Jaclyn A.; Brock, Tyler M.

2012-01-01

The 30th Operational Support Squadron Weather Flight (30 OSSWF) provides comprehensive weather services to the space program at Vandenberg Air Force Base (VAFB) in California. One of their responsibilities is to monitor upper-level winds to ensure safe launch operations of the Minuteman Ill ballistic missile. The 30 OSSWF tasked the Applied Meteorology Unit (AMU) to analyze VAFB sounding data with the goal of determining the probability of violating (PoV) their upper-level thresholds for wind speed and shear constraints specific to this launch vehicle, and to develop a tool that will calculate the PoV of each constraint on the day of launch. In order to calculate the probability of exceeding each constraint, the AMU collected and analyzed historical data from VAFB. The historical sounding data were retrieved from the National Oceanic and Atmospheric Administration Earth System Research Laboratory archive for the years 1994-2011 and then stratified into four sub-seasons: January-March, April-June, July-September, and October-December. The AMU determined the theoretical distributions that best fit the maximum wind speed and maximum wind shear datasets and applied this information when calculating the averages and standard deviations needed for the historical and real-time PoV calculations. In addition, the AMU included forecast sounding data from the Rapid Refresh model. This information provides further insight for the launch weather officers (LWOs) when determining if a wind constraint violation will occur over the next few hours on the day of launch. The AMU developed an interactive graphical user interface (GUI) in Microsoft Excel using Visual Basic for Applications. The GUI displays the critical sounding data easily and quickly for LWOs on day of launch. This tool will replace the existing one used by the 30 OSSWF, assist the LWOs in determining the probability of exceeding specific wind threshold values, and help to improve the overall upper winds forecast for the launch customer. This presentation will describe how the AMU calculated the historical and real-time PoV values for the specific upper-level wind launch constraints and outline the development of the interactive GUI display.

Proposal to National Aeronautics and Space Administration for continuation of a grazing incidence imaging telescope for X-ray astronomy using sounding rockets

NASA Technical Reports Server (NTRS)

Murray, B.

1976-01-01

The construction of a high resolution imaging telescope experiment payload suitable for launch on an Astrobee F sounding rocket was proposed. Also integration, launch, and subsequent data analysis effort were included. The payload utilizes major component subassemblies from the HEAO-B satellite program which were nonflight development units for that program. These were the X ray mirror and high resolution imager brassboard detector. The properties of the mirror and detector were discussed. The availability of these items for a sounding rocket experiment were explored with the HEAO-B project office.

The National Aeronautics and Space Administration (NASA)/Goddard Space Flight Center (GSFC) sounding-rocket program

NASA Technical Reports Server (NTRS)

Guidotti, J. G.

1976-01-01

An overall introduction to the NASA sounding rocket program as managed by the Goddard Space Flight Center is presented. The various sounding rockets, auxiliary systems (telemetry, guidance, etc.), launch sites, and services which NASA can provide are briefly described.

78 FR 40196 - National Environmental Policy Act; Sounding Rockets Program; Poker Flat Research Range

Federal Register 2010, 2011, 2012, 2013, 2014

2013-07-03

...; Sounding Rockets Program; Poker Flat Research Range AGENCY: National Aeronautics and Space Administration... Sounding Rockets Program (SRP) at Poker Flat Research Range (PFRR), Alaska. SUMMARY: Pursuant to the... government agencies, and educational institutions have conducted suborbital rocket launches from the PFRR...

14 CFR 415.15 - Rights not conferred by launch license.

Code of Federal Regulations, 2012 CFR

2012-01-01

... facilities, airspace, or outer space. ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Rights not conferred by launch license. 415.15 Section 415.15 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

14 CFR 415.15 - Rights not conferred by launch license.

Code of Federal Regulations, 2014 CFR

2014-01-01

... facilities, airspace, or outer space. ... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Rights not conferred by launch license. 415.15 Section 415.15 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

14 CFR 415.15 - Rights not conferred by launch license.

Code of Federal Regulations, 2011 CFR

2011-01-01

... facilities, airspace, or outer space. ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Rights not conferred by launch license. 415.15 Section 415.15 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

14 CFR 415.15 - Rights not conferred by launch license.

Code of Federal Regulations, 2010 CFR

2010-01-01

... facilities, airspace, or outer space. ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Rights not conferred by launch license. 415.15 Section 415.15 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

14 CFR 415.15 - Rights not conferred by launch license.

Code of Federal Regulations, 2013 CFR

2013-01-01

... facilities, airspace, or outer space. ... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Rights not conferred by launch license. 415.15 Section 415.15 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

Sliding Mode Control of the X-33 Vehicle in Launch Mode

NASA Technical Reports Server (NTRS)

Shtessel, Yuri; Jackson, Mark; Hall, Charles; Krupp, Don; Hendrix, N. Douglas

1998-01-01

The "nested" structure of the control system for the X33 vehicle in launch mode is developed. Employing backstopping concepts, the outer loop (guidance) and the Inner loop (rates) continuous sliding mode controllers are designed. Simulations of the 3-DOF model of the X33 launch vehicle showed an accurate, robust, de-coupled tracking performance.

Northeastern Quadrant of the Caloris Basin

NASA Image and Video Library

2000-01-14

This image, from NASA Mariner 10 spacecraft which launched in 1974, is of the northeastern quadrant of the Caloris basin and shows the smooth hills and domes between the inner and outer scarps and the well-developed radial system east of the outer scarp

Determining the Probability of Violating Upper-Level Wind Constraints for the Launch of Minuteman Ill Ballistic Missiles At Vandenberg Air Force Base

NASA Technical Reports Server (NTRS)

Shafer, Jaclyn A.; Brock, Tyler M.

2013-01-01

The 30th Operational Support Squadron Weather Flight (30 OSSWF) provides comprehensive weather services to the space program at Vandenberg Air Force Base (VAFB) in California. One of their responsibilities is to monitor upper-level winds to ensure safe launch operations of the Minuteman Ill ballistic missile. The 30 OSSWF requested the Applied Meteorology Unit (AMU) analyze VAFB sounding data to determine the probability of violating (PoV) upper-level thresholds for wind speed and shear constraints specific to this launch vehicle, and to develop a graphical user interface (GUI) that will calculate the PoV of each constraint on the day of launch. The AMU suggested also including forecast sounding data from the Rapid Refresh (RAP) model. This would provide further insight for the launch weather officers (LWOs) when determining if a wind constraint violation will occur over the next few hours, and help to improve the overall upper winds forecast on launch day.

Snapshot recordings provide a first description of the acoustic signatures of deeper habitats adjacent to coral reefs of Moorea.

PubMed

Bertucci, Frédéric; Parmentier, Eric; Berthe, Cécile; Besson, Marc; Hawkins, Anthony D; Aubin, Thierry; Lecchini, David

2017-01-01

Acoustic recording has been recognized as a valuable tool for non-intrusive monitoring of the marine environment, complementing traditional visual surveys. Acoustic surveys conducted on coral ecosystems have so far been restricted to barrier reefs and to shallow depths (10-30 m). Since they may provide refuge for coral reef organisms, the monitoring of outer reef slopes and describing of the soundscapes of deeper environment could provide insights into the characteristics of different biotopes of coral ecosystems. In this study, the acoustic features of four different habitats, with different topographies and substrates, located at different depths from 10 to 100 m, were recorded during day-time on the outer reef slope of the north Coast of Moorea Island (French Polynesia). Barrier reefs appeared to be the noisiest habitats whereas the average sound levels at other habitats decreased with their distance from the reef and with increasing depth. However, sound levels were higher than expected by propagation models, supporting that these habitats possess their own sound sources. While reef sounds are known to attract marine larvae, sounds from deeper habitats may then also have a non-negligible attractive potential, coming into play before the reef itself.

77 FR 61642 - National Environmental Policy Act; Sounding Rockets Program; Poker Flat Research Range

Federal Register 2010, 2011, 2012, 2013, 2014

2012-10-10

...; Sounding Rockets Program; Poker Flat Research Range AGENCY: National Aeronautics and Space Administration... Sounding Rockets Program (SRP) at Poker Flat Research Range (PFRR), Alaska. SUMMARY: Pursuant to the... educational institutions have conducted suborbital rocket launches from the PFRR. While the PFRR is owned and...

Design of Sounding Rocket Payloads.

DTIC Science & Technology

1981-07-01

AD-AlB 271 NORTHEASTERN UNIV BOSTON MASS ELECTRONICS RESEARCH LAB F/6 19/7 DESIGN OF SOUNDING ROCKET PAYLOADS. (U) JUL Al R L MORIN, L .J O’CONNOR...Morin Lawrence J. O’Connor NORTHEASTERN UNIVERSITY Electronics Research Laboratory D T I Boston, Massachusetts 02115 ELECTE S DEC 9 19813 FINAL REPORT... Research Range on 21 February 1978. The payload was re-assembled, checked and mated to the launch vehicle on 27 February. Launch -8- criteria were

Experimental constraints on light elements in the Earth’s outer core

PubMed Central

Zhang, Youjun; Sekine, Toshimori; He, Hongliang; Yu, Yin; Liu, Fusheng; Zhang, Mingjian

2016-01-01

Earth’s outer core is liquid and dominantly composed of iron and nickel (~5–10 wt%). Its density, however, is ~8% lower than that of liquid iron, and requires the presence of a significant amount of light element(s). A good way to specify the light element(s) is a direct comparison of density and sound velocity measurements between seismological data and those of possible candidate compositions at the core conditions. We report the sound velocity measurements of a model core composition in the Fe-Ni-Si system at the outer core conditions by shock-wave experiments. Combining with the previous studies, we found that the best estimate for the outer core’s light elements is ~6 wt% Si, ~2 wt% S, and possible ~1–2.5 wt% O. This composition satisfies the requirements imposed by seismology, geochemistry, and some models of the early core formation. This finding may help us to further constrain the thermal structure of the Earth and the models of Earth’s core formation. PMID:26932596

77 FR 59611 - Environmental Impacts Statements; Notice of Availability

Federal Register 2010, 2011, 2012, 2013, 2014

2012-09-28

...: Sandy Hurlocker 505-753-7331. EIS No. 20120308, Draft EIS (Tiering), NASA, AK, Sounding Rocket Program (SRP) at Poker Flat Research Range (PFRR), Continuing Sounding Rocket Launches, Alaska, Comment Period...

50 CFR 217.75 - Requirements for monitoring and reporting.

Code of Federal Regulations, 2014 CFR

2014-10-01

... camera system designed to detect pinniped responses to rocket launches for at least the first five..., whenever a new class of rocket is flown from the Kodiak Launch Complex, a real-time sound pressure and...) Assess the cumulative impacts on pinnipeds and other marine mammals from multiple rocket launches. ...

50 CFR 217.75 - Requirements for monitoring and reporting.

Code of Federal Regulations, 2011 CFR

2011-10-01

... camera system designed to detect pinniped responses to rocket launches for at least the first five..., whenever a new class of rocket is flown from the Kodiak Launch Complex, a real-time sound pressure and...) Assess the cumulative impacts on pinnipeds and other marine mammals from multiple rocket launches. ...

Mission operations for unmanned nuclear electric propulsion outer planet exploration with a thermionic reactor spacecraft.

NASA Technical Reports Server (NTRS)

Spera, R. J.; Prickett, W. Z.; Garate, J. A.; Firth, W. L.

1971-01-01

Mission operations are presented for comet rendezvous and outer planet exploration NEP spacecraft employing in-core thermionic reactors for electric power generation. The selected reference missions are the Comet Halley rendezvous and a Jupiter orbiter at 5.9 planet radii, the orbit of the moon Io. The characteristics of the baseline multi-mission NEP spacecraft are presented and its performance in other outer planet missions, such as Saturn and Uranus orbiters and a Neptune flyby, are discussed. Candidate mission operations are defined from spacecraft assembly to mission completion. Pre-launch operations are identified. Shuttle launch and subsequent injection to earth escape by the Centaur D-1T are discussed, as well as power plant startup and the heliocentric mission phases. The sequence and type of operations are basically identical for all missions investigated.

An Overview of Research Activity at the Launch Systems Testbed

NASA Technical Reports Server (NTRS)

Vu, Bruce; Kandula, Max

2003-01-01

This paper summarizes the acoustic testing and analysis activities at the Launch System Testbed (LST) of Kennedy Space Center (KSC). A major goal is to develop passive methods of mitigation of sound from rocket exhaust jets with ducted systems devoid of traditional water injection. Current testing efforts are concerned with the launch-induced vibroacoustic behavior of scaled exhaust jets. Numerical simulations are also developed to study the sound propagation from supersonic jets in free air and through enclosed ducts. Scaling laws accounting for the effects of important parameters such as jet Mach number, jet velocity, and jet temperature on the far-field noise are investigated in order to deduce full-scale environment from small-scale tests.

NASA's Space Launch System: An Evolving Capability for Exploration

NASA Technical Reports Server (NTRS)

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

2015-01-01

Designed to enable human space exploration missions, including eventually 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. The vehicle will be able to deliver greater mass to orbit than any contemporary launch vehicle. 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.

National Report on the NASA Sounding Rocket and Balloon Programs

NASA Technical Reports Server (NTRS)

Eberspeaker, Philip; Fairbrother, Debora

2013-01-01

The U. S. National Aeronautics and Space Administration (NASA) Sounding Rockets and Balloon Programs conduct a total of 30 to 40 missions per year in support of the NASA scientific community and other users. The NASA Sounding Rockets Program supports the science community by integrating their experiments into the sounding rocket payloads, and providing both the rocket vehicle and launch operations services. Activities since 2011 have included two flights from Andoya Rocket Range, more than eight flights from White Sands Missile Range, approximately sixteen flights from Wallops Flight Facility, two flights from Poker Flat Research Range, and four flights from Kwajalein Atoll. Other activities included the final developmental flight of the Terrier-Improved Malemute launch vehicle, a test flight of the Talos-Terrier-Oriole launch vehicle, and a host of smaller activities to improve program support capabilities. Several operational missions have utilized the new Terrier-Malemute vehicle. The NASA Sounding Rockets Program is currently engaged in the development of a new sustainer motor known as the Peregrine. The Peregrine development effort will involve one static firing and three flight tests with a target completion data of August 2014. The NASA Balloon Program supported numerous scientific and developmental missions since its last report. The program conducted flights from the U.S., Sweden, Australia, and Antarctica utilizing standard and experimental vehicles. Of particular note are the successful test flights of the Wallops Arc Second Pointer (WASP), the successful demonstration of a medium-size Super Pressure Balloon (SPB), and most recently, three simultaneous missions aloft over Antarctica. NASA continues its successful incremental design qualification program and will support a science mission aboard WASP in late 2013 and a science mission aboard the SPB in early 2015. NASA has also embarked on an intra-agency collaboration to launch a rocket from a balloon to conduct supersonic decelerator tests. An overview of NASA's Sounding Rockets and Balloon Operations, Technology Development and Science support activities will be presented.

Scale Model Experiments on Sound Propagation From a Mach 2.5 Cold Nitrogen Jet Flowing Through a Rigid-Walled Duct With a J-Deflector

NASA Technical Reports Server (NTRS)

Kandula, Max; Vu, Bruce

2003-01-01

The Launch Systems Testbed (LST) represents the evolution of vibroacoustics research and development work performed at NASA John F. Kennedy Space Center (KSC) over the last 15 years. The LST is located at the Launch Equipment Test Facility (LETF) in the KSC industrial complex. The LETF is operated by Sierra Lobo, Inc., as a member of University-Affiliated Technology Development Contract (USTDC) to KSC Spaceport and Engineering and Technology Directorate (YA), with ASRC Aerospace Corporation as a the prime contractor. Trajectory Simulation Mechanism (TSM) is a major component of the LST, developed specifically to simulate nonstationary acoustic loads on launch pad structures, vehicles, and payloads. TSM enhances the capabilities within LST for simulating launch environments of future vehicles. The scaled launch environments will be used to predict the full-scale launch environment via an appropriate scaling procedure. Air Force Research Laboratory (AFRL) has tasked NASA KSC to perform a basic technology test program in support of developing a low-cost clean pad (incorporating passive mitigation techniques) for future launch vehicles. The overall goal of the program is to develop innovative launch exhaust management systems, which effectively reduce launch acoustic environment with innovative duct designs, while eliminating traditional sound suppression water systems. Passive techniques, such as nontraditional duct geometries, resonators, and diffusers, etc., will be investigated. The overall goals are to advance innovative concepts for a clean pad while developing ideas to reduce transmitted sound via investigation and modeling of jet exhaust acoustic and flow field characteristics. The series of tests outlined in this report represent baseline tests and are geared towards defining the acoustic load environment on the TSM pad for open and closed duct configurations. This report summarizes the cold jet acoustic testing for Mach 2.5 supersonic nitrogen jet issuing from a nozzle with 1-inch exit diameter. Acoustic data, including spectral sound power and Overall Sound Pressure Level (OASPL), are obtained both for a free jet and with the jet flowing through a rigid-walled duct with a J-deflector. The relative performance of closed duct and open duct is evaluated. The results show that the closed duct is superior to the partially open duct, and results in about 3-decibel (dB) noise reduction (near the duct axis) relative to the free jet. The location of the nozzle exit plane (NEP) relative to the duct inlet plane (DIP) has a significant effect on the acoustic field. The results suggest that the location of NEP at 10 inches above the DIP results in reduced acoustic loads relative to 5 inches above the duct inlet and 1 inch into the duct inlet.

KSC-07pd1288

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- Many former astronauts gathered at the opening of the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

KSC-07pd1285

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- NASA, Kennedy Space Center and State of Florida dignitaries helped launch the opening of the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. Speaking to attendees is Center Director Bill Parsons. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

Earth Science

NASA Image and Video Library

1995-12-02

The Solar Heliospheric Observatory (SOHO) is launched atop an ATLAS-IIAS expendable launch vehicle. Liftoff from launch complex 36B at Cape Canaveral Air Station marked the 10th Atlas launch from the Eastern range for 1995. SOHO is a cooperative effort involving NASA and the European Space Agency (ESA) within the framework of the International Solar-Terrestrial Physics Program. During its 2-year mission, the SOHO spacecraft gathered data on the internal structure of the Sun, its extensive outer atmosphere and the origin of the solar wind.

Snapshot recordings provide a first description of the acoustic signatures of deeper habitats adjacent to coral reefs of Moorea

PubMed Central

Parmentier, Eric; Berthe, Cécile; Besson, Marc; Hawkins, Anthony D.; Aubin, Thierry; Lecchini, David

2017-01-01

Acoustic recording has been recognized as a valuable tool for non-intrusive monitoring of the marine environment, complementing traditional visual surveys. Acoustic surveys conducted on coral ecosystems have so far been restricted to barrier reefs and to shallow depths (10–30 m). Since they may provide refuge for coral reef organisms, the monitoring of outer reef slopes and describing of the soundscapes of deeper environment could provide insights into the characteristics of different biotopes of coral ecosystems. In this study, the acoustic features of four different habitats, with different topographies and substrates, located at different depths from 10 to 100 m, were recorded during day-time on the outer reef slope of the north Coast of Moorea Island (French Polynesia). Barrier reefs appeared to be the noisiest habitats whereas the average sound levels at other habitats decreased with their distance from the reef and with increasing depth. However, sound levels were higher than expected by propagation models, supporting that these habitats possess their own sound sources. While reef sounds are known to attract marine larvae, sounds from deeper habitats may then also have a non-negligible attractive potential, coming into play before the reef itself. PMID:29158970

41. March 18, 1939 Oakland, California Launching party with sponsor ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

41. March 18, 1939 Oakland, California Launching party with sponsor Miss Harriet Biota Mason (holding flowers) at the Moore Dry Dock Company. - U.S. Coast Guard Cutter FIR, Puget Sound Area, Seattle, King County, WA

Project Centaur. [for earth dayside magnetic cleft investigation

NASA Technical Reports Server (NTRS)

Brence, W. A.; Hardin, J. W.; Crook, E. D.; Roberts, H.

1982-01-01

The National Aeronautics and Space Administration (NASA) and the Canada Centre for Space Science, National Research Council of Canada (NRCC), conducted a cooperative sounding rocket campaign in the Canadian Arctic during November/December 1981. The objective of the campaign was to investigate the earth's dayside magnetic cleft region. The project was named CENTAUR for Cleft Energetics Transport and Ultraviolet Radiation. Remote launch support facilities were established at Cape Parry, NWT, Canada (70 deg 10 min N latitude, 124 deg 40 min W longitude). The cleft region is accessible from this location when launched poleward during reasonably quiet magnetic activity. Five large sounding rockets were launched (3 NASA, 2 NRCC). About 30 scientific experiments were launched, and an extensive array of ground based experiments was established at Cape Parry and at Sachs Harbour, Banks Island, 130 miles poleward. This paper discusses the unique organization, planning, facilities, instrumentation, and operation required to support the campaign, and looks briefly at the results.

Austrian National Space Law

NASA Astrophysics Data System (ADS)

Steinkogler, Cordula

2017-08-01

The Austrian Outer Space Act, which entered into force in December 2011; and the Austrian Outer Space Regulation, which has been in force since February 2015, form the legal framework for Austrian national space activities. The elaboration of national space legislation became necessary to ensure compliance with Austria's obligations as State Party to the five United Nations Space Treaties when the first two Austrian satellites were launched in 2012 and Austria became a launching state on its own. The legislation comprehensively regulates legal aspects related to space activities, such as authorization, supervision, and termination of space activities; registration and transfer of space objects; recourse of the government against the operator; as well as implementation of the law and sanctions for its infringement. One of the main purposes of the law is to ensure the authorization of national space activities. The Outer Space Act sets forth the main conditions for authorization, which inter alia refer to the expertise of the operator; requirements for orbital positions and frequency assignments; space debris mitigation, insurance requirements, and the safeguard of public order; public health; national security as well as Austrian foreign policy interests; and international law obligations. The Austrian Outer Space Regulation complements these provisions by specifying the documents the operator must submit as evidence of the fulfillment of the authorization conditions, which include the results of safety tests, emergency plans, and information on the collection and use of Earth observation data. Particular importance is attached to the mitigation of space debris. Operators are required to take measures in accordance with international space debris mitigation guidelines for the avoidance of operational debris, the prevention of on-orbit break-ups and collisions, and the removal of space objects from Earth orbit after the end of the mission. Another specificity of the Austrian space legislation is the possibility of an exemption from the insurance requirement or a reduction of the insurance sum, if the space activity is in the public interest. This allows support to space activities that serve science, research, and education. Moreover, the law also provides for the establishment of a national registry for objects launched into outer space by the competent Austrian Ministry. The first two Austrian satellites have been entered into this registry after their launch in 2012. The third Austrian satellite, launched in June 2017, will be the first satellite authorized under the Austrian space legislation.

Potential advantages of solar electric propulsion for outer planet orbiters.

NASA Technical Reports Server (NTRS)

Sauer, C. G.; Atkins, K. L.

1972-01-01

Past studies of solar electric propulsion for outer planet orbiters have generally emphasized the advantages of flight time reduction and payload increases. However, several subtle advantages exist, which may become important in an environment of increasingly difficult requirements as ways to extend current technology are sought. These advantages accrue primarily because of the inherent capability, unique to electric propulsion, to efficiently shape a trajectory while enroute. Stressed in this paper are: the ability to meet orbital constraints due to assumed radiation belts, science flexibility in a dual launch program, increased numbers of observational passes, and the lengthening of launch periods. These are examined for years representative of relatively easy and difficult ballistic missions. The results indicate that an early investment in solar electric technology will provide a strong performance foundation for a long range outer planet exploration program which evolves from current spacecraft technology.

[The acoustics of the open mastoid cavity (so-called "radical cavity") and its modification by surgical measures. II. Clinical studies].

PubMed

Hartwein, J

1992-09-01

The acoustic resonance of a severely altered outer ear channel (radical mastoid cavity) is investigated in a series of 18 patients who underwent revision surgery by means of in-situ measurements of the sound-pressure-level near the tympanic membrane. While the average volume of the open cavity differs from the normal ear channel for the factor 2.5, the size of the external meatus is--in average--only 20% larger. This leads to an average frequency in patients with open cavity of 1939 Hz, more than 1000 Hz less than in a series (n = 20) of normal ears (average resonance frequency: 2942 Hz). The altered acoustic behaviour of the open cavity leads to partial extensive discrepancies of the resonance-caused sound-pressure augmentation in the frequencies of 3 and 4 kHz, which are important for speech perception. The average difference is more than 10 dB (SPL). Proved surgical techniques of cavity obliteration and meatoplasty can lead to a nearly normalized acoustic behaviour of the outer ear in a statistic significant way. Due to these surgical procedures, an average postoperative resonance frequency of 2421 Hz could be reached in our patients. Especially, the resonance-caused sound-pressure augmentation in 3-4 kHz could nearly be equalized to such of a normal outer ear. Differences in the acoustic behaviour of the outer ear as can be found between patients with an open mastoid cavity and normal ears can almost be eliminated surgically.(ABSTRACT TRUNCATED AT 250 WORDS)

Effects of Gravity-Assist Timing on Outer-Planet Missions Using Solar-Electric Propulsion

NASA Technical Reports Server (NTRS)

Woo, Byoungsam; Coverstone, Victoria L.; Cupples, Michael

2004-01-01

Missions to the outer planets for spacecraft with a solar-electric propulsion system (SEPS) and that utilize a single Venus gravity assist are investigated. The trajectories maximize the delivered mass to the target planet for a range of flight times. A comparison of the trajectory characteristics (delivered mass, launch energy and onboard propulsive energy) is made for various Venus gravity assist opportunities. Methods to estimate the delivered mass to the outer planets are developed.

The Law of Neutrality in Outer Space

DTIC Science & Technology

2008-09-01

the prospect of potential downward competitive price pressures -- its successful launch of an Italian astronomy satellite into low Earth orbit at a...For example, following its successful launch of Italy’s astronomy satellite, India launched an 16Israeli spy satellite into a low Earth polar orbit...and ARABSAT have not. What are the respective rights and duties of these corporations and organizations (to include their member States) during

Taiwan Space Programs

NASA Astrophysics Data System (ADS)

Liu, Jann-Yenq

Taiwan space programs consist of FORMOSAT-1, -2, and -3, sounding rockets, and international cooperation. FORMOSAT-1, a low-earth-orbit (LEO) scientific experimental satellite, was launched on January 26, 1999. It circulates with an altitude of 600 km and 35 degree inclination around the Earth every 97 minutes, transmitting collected data to Taiwan's receiving stations approximately six times a day. The major mission of FORMOSAT-1 includes three scientific experiments for measuring the effects of ionospheric plasma and electrodynamics, taking the ocean color image and conducting Ka-band communication experiment. The FORMOSAT- 1 mission was ended by June 15, 2004. FORMOSAT-2, launched on May 21, 2004 onto the Sun-synchronous orbit located at 891 km above ground. The main mission of FORMOSAT-2 is to conduct remote sensing imaging over Taiwan and on terrestrial and oceanic regions of the entire earth. The images captured by FORMOSAT-2 during daytime can be used for land distribution, natural resources research, environmental protection, disaster prevention and rescue work etc. When the satellite travels to the eclipsed zone, it observes natural phenomena of lighting in the upper atmosphere. FORMOSAT-3 is an international collaboration project between Taiwan and the US to develop advanced technology for the real-time monitoring of the global climate. This project is also named Constellation Observing System for Meteorology, Ionosphere and Climate, or FORMOSAT-3/COSMIC for short. Six micro-satellites were launched on 15 April 2007 and eventually placed into six different orbits at 700 800 kilometer above the earth ground. These satellites orbit around the earth to form a LEO constellation that receives signals transmitted by the 24 US GPS satellites. The satellite observation covers the entire global atmosphere and ionosphere, providing over 2,500 global sounding data per day. These data distribute uniformly over the earth's atmosphere. The global climate information collection and analysis can be completed in three hours while the sounding data is updated every 90 minutes for updating weather forecast. In addition, this system can also be used as the long-term climate change research, interactive ionosphere monitoring, global space weather forecast, and earth gravity research. From 1997 to 2003, there are three launches of sounding rockets. To compliment the second phase of Taiwan's national space technology long-term development plan, the sounding rocket space exploration project was established. The timeframe of the second phase sounding rocket project is 15 years, from January 2004 to December 2018, and 10 15 sounding rockets will be launched during this time period. In this paper, the current status and results of the programs are presented in detail.

50 CFR 217.75 - Requirements for monitoring and reporting.

Code of Federal Regulations, 2013 CFR

2013-10-01

..., during, and 2 hours after launch; (2) Ensure a remote camera system will be in place and operating in a..., whenever a new class of rocket is flown from the Kodiak Launch Complex, a real-time sound pressure and... camera system designed to detect pinniped responses to rocket launches for at least the first five...

50 CFR 217.75 - Requirements for monitoring and reporting.

Code of Federal Regulations, 2012 CFR

2012-10-01

..., during, and 2 hours after launch; (2) Ensure a remote camera system will be in place and operating in a..., whenever a new class of rocket is flown from the Kodiak Launch Complex, a real-time sound pressure and... camera system designed to detect pinniped responses to rocket launches for at least the first five...

The Advanced Technology Microwave Sounder (ATMS): First Year On-Orbit

NASA Technical Reports Server (NTRS)

Kim, Edward J.

2012-01-01

The Advanced Technology Microwave Sounder (ATMS) is a new satellite microwave sounding sensor designed to provide operational weather agencies with atmospheric temperature and moisture profile information for global weather forecasting and climate applications. A TMS will continue the microwave sounding capabilities first provided by its predecessors, the Microwave Sounding Unit (MSU) and Advanced Microwave Sounding Unit (AMSU). The first flight unit was launched a year ago in October, 2011 aboard the Suomi-National Polar-Orbiting Partnership (S-NPP) satellite, part of the new Joint Polar-Orbiting Satellite System (JPSS). Microwave soundings by themselves are the highest-impact input data used by Numerical Weather Prediction models; and A TMS, when combined with the Cross-track Infrared Sounder (CrIS), forms the Cross-track Infrared and Microwave Sounding Suite (CrIMSS). The microwave soundings help meet sounding requirements under cloudy sky conditions and provide key profile information near the surface. ATMS was designed & built by Aerojet Corporation in Azusa, California, (now Northrop Grumman Electronic Systems). It has 22 channels spanning 23-183 GHz, closely following the channel set of the MSU, AMSU-AI/2, AMSU-B, Microwave Humidity Sounder (MHS), and Humidity Sounder for Brazil (HSB). It continues their cross-track scanning geometry, but for the first time, provides Nyquist sample spacing. All this is accomplished with approximately V. the volume, Y, the mass, and Y, the power of the three AMSUs. A description will be given of its performance from its first year of operation as determined by post-launch calibration activities. These activities include radiometric calibration using the on-board warm targets and cold space views, and geolocation determination. Example imagery and zooms of specific weather events will be shown. The second ATMS flight model is currently under construction and planned for launch on the "Jl" satellite of the JPSS program in approximately 2016. Additional units are expected on the J2 and 13 satellites, as well as potentially on future European METOP satellites.

Hair cell transduction, tuning and synaptic transmission in the mammalian cochlea

PubMed Central

Fettiplace, Robert

2017-01-01

Sound pressure fluctuations striking the ear are conveyed to the cochlea, where they vibrate the basilar membrane on which sit hair cells, the mechanoreceptors of the inner ear. Recordings of hair cell electrical responses have shown that they transduce sound via sub-micrometer deflections of their hair bundles, which are arrays of interconnected stereocilia containing the mechanoelectrical transducer (MET) channels. MET channels are activated by tension in extracellular tip links bridging adjacent stereocilia, and they can respond within microseconds to nanometer displacements of the bundle, facilitated by multiple processes of Ca2+-dependent adaptation. Studies of mouse mutants have produced much detail about the molecular organization of the stereocilia, the tip links and their attachment sites, and the MET channels localized to the lower ends of each tip link. The mammalian cochlea contains two categories of hair cells. Inner hair cells relay acoustic information via multiple ribbon synapses that transmit rapidly without rundown. Outer hair cells are important for amplifying sound-evoked vibrations. The amplification mechanism primarily involves contractions of the outer hair cells, which are driven by changes in membrane potential and mediated by prestin, a motor protein in the outer hair cell lateral membrane. Different sound frequencies are separated along the cochlea, with each hair cell being tuned to a narrow frequency range; amplification sharpens the frequency resolution and augments sensitivity 100-fold around the cell’s characteristic frequency. Genetic mutations and environmental factors such as acoustic overstimulation cause hearing loss through irreversible damage to the hair cells or degeneration of inner hair cell synapses. PMID:28915323

[Conversion of sound into auditory nerve action potentials].

PubMed

Encke, J; Kreh, J; Völk, F; Hemmert, W

2016-11-01

Outer hair cells play a major role in the hearing process: they amplify the motion of the basilar membrane up to a 1000-fold and at the same time sharpen the excitation patterns. These patterns are converted by inner hair cells into action potentials of the auditory nerve. Outer hair cells are delicate structures and easily damaged, e. g., by overexposure to noise. Hearing aids can amplify the amplitude of the excitation patterns, but they cannot restore their degraded frequency selectivity. Noise overexposure also leads to delayed degeneration of auditory nerve fibers, particularly those with low a spontaneous rate, which are important for the coding of sound in noise. However, this loss cannot be diagnosed by pure-tone audiometry.

Probe design

NASA Technical Reports Server (NTRS)

Cowan, W.

1974-01-01

Outer planetary probe designs consider mission characteristics, structural configuration, delivery mode, scientific payload, environmental extremes, mass properties, and the launch vehicle and spacecraft interface.

Severe storms observing satellite (STORMSAT)

NASA Technical Reports Server (NTRS)

1976-01-01

The primary payload for this satellite is the Advanced Atmospheric Sounding and Imaging Radiometer which will perform precise infrared temperature sounding and visible/infrared imaging from geostationary orbit. A secondary payload instrument which may be utilized on STORMSAT is the Microwave Atmospheric Sounding Radiometer which provides an independent set of temperature and humidity sounding in cloudy, meteorologically active regions. The study provides satellite designs and identifies mission-unique subsystems using the Multimission Modular Spacecraft using a Shuttle/Interim Upper Stage launch vehicle.

An Overview of the NASA Sounding Rocket and Balloon Programs

NASA Technical Reports Server (NTRS)

Eberspeaker, Philip J.; Smith, Ira S.

2003-01-01

The U.S. National Aeronautics and Space Administration (NASA) Sounding Rockets and Balloon Programs conduct a total of 50 to 60 missions per year in support of the NASA scientific community. These missions support investigations sponsored by NASA's Offices of Space Science, Life and Microgravity Sciences & Applications, and Earth Science. The Goddard Space Flight Center has management and implementation responsibility for these programs. The NASA Sounding Rockets Program provides the science community with payload development support, environmental testing, launch vehicles, and launch operations from fixed and mobile launch ranges. Sounding rockets continue to provide a cost-effective way to make in situ observations from 50 to 1500 km in the near-earth environment and to uniquely cover the altitude regime between 50 km and 130 km above the Earth's surface. New technology efforts include GPS payload event triggering, tailored trajectories, new vehicle configuration development to expand current capabilities, and the feasibility assessment of an ultra high altitude sounding rocket vehicle. The NASA Balloon Program continues to make advancements and developments in its capabilities for support of the scientific ballooning community. The Long Duration Balloon (LDB) is capable of providing flight durations in excess of two weeks and has had many successful flights since its development. The NASA Balloon Program is currently engaged in the development of the Ultra Long Duration Balloon (ULDB), which will be capable of providing flight times up to 100-days. Additional development efforts are focusing on ultra high altitude balloons, station keeping techniques and planetary balloon technologies.

KSC-07pd1289

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- Many former astronauts gather at the opening of the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. In front are John Young (left) and Bob Crippen. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

Optimizing the Launch of a Projectile to Hit a Target

NASA Astrophysics Data System (ADS)

Mungan, Carl E.

2017-12-01

Some teenagers are exploring the outer perimeter of a castle. They notice a spy hole in its wall, across the moat a horizontal distance x and vertically up the wall a distance y. They decide to throw pebbles at the hole. One girl wants to use physics to throw with the minimum speed necessary to hit the hole. What is the required launch speed v and launch angle θ above the horizontal?

14 CFR 420.41 - License to operate a launch site-general.

Code of Federal Regulations, 2010 CFR

2010-01-01

... does it confer any proprietary, property, or exclusive right in the use of airspace or outer space. ... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false License to operate a launch site-general. 420.41 Section 420.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

14 CFR 420.41 - License to operate a launch site-general.

Code of Federal Regulations, 2011 CFR

2011-01-01

... does it confer any proprietary, property, or exclusive right in the use of airspace or outer space. ... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false License to operate a launch site-general. 420.41 Section 420.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

14 CFR 420.41 - License to operate a launch site-general.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false License to operate a launch site-general. 420.41 Section 420.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... regulations; nor does it confer any proprietary, property, or exclusive right in the use of airspace or outer...

14 CFR 420.41 - License to operate a launch site-general.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false License to operate a launch site-general. 420.41 Section 420.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... regulations; nor does it confer any proprietary, property, or exclusive right in the use of airspace or outer...

14 CFR 420.41 - License to operate a launch site-general.

Code of Federal Regulations, 2012 CFR

2012-01-01

... does it confer any proprietary, property, or exclusive right in the use of airspace or outer space. ... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false License to operate a launch site-general. 420.41 Section 420.41 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION...

76 FR 19122 - Record of Decision (ROD) for Authorizing the Use of Outer Continental Shelf (OCS) Sand Resources...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-04-06

... Aeronautics and Space Administration's Wallops Flight Facility Shoreline Restoration and Infrastructure... authorize the use of OCS sand resources in National Aeronautics and Space Administration's (NASA's) Wallops... infrastructure on the WFF (such as rocket launch pads, runways, and launch control centers) valued at over $1...

Small Upper Stage Basic Program Final Report

DTIC Science & Technology

1991-08-27

design of the SUS. During storage, the SUS shall3 be required to withstand environments as specified in 3.2.5.1. Environmental protection shall be...accomplish this goal, a launch vehicle survey was conducted to establish the current LV capability and environments with respect to small satellites...4 Launch Vehicle Shock Environment ...................................................................... 2-4 2-5 Launch Vehicle Sound Pressure

Sounding Rocket Launches Successfully from Alaska

NASA Image and Video Library

2015-01-28

Caption: Time lapse photo of the NASA Oriole IV sounding rocket with Aural Spatial Structures Probe as an aurora dances over Alaska. All four stages of the rocket are visible in this image. Credit: NASA/Jamie Adkins More info: On count day number 15, the Aural Spatial Structures Probe, or ASSP, was successfully launched on a NASA Oriole IV sounding rocket at 5:41 a.m. EST on Jan. 28, 2015, from the Poker Flat Research Range in Alaska. Preliminary data show that all aspects of the payload worked as designed and the principal investigator Charles Swenson at Utah State University described the mission as a “raging success.” “This is likely the most complicated mission the sounding rocket program has ever undertaken and it was not easy by any stretch," said John Hickman, operations manager of the NASA sounding rocket program office at the Wallops Flight Facility, Virginia. "It was technically challenging every step of the way.” “The payload deployed all six sub-payloads in formation as planned and all appeared to function as planned. Quite an amazing feat to maneuver and align the main payload, maintain the proper attitude while deploying all six 7.3-pound sub payloads at about 40 meters per second," said Hickman. Read more: www.nasa.gov/content/assp-sounding-rocket-launches-succes... NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Hair cell counts in a rat model of sound damage: Effects of tissue preparation & identification of regions of hair cell loss.

PubMed

Neal, Christopher; Kennon-McGill, Stefanie; Freemyer, Andrea; Shum, Axel; Staecker, Hinrich; Durham, Dianne

2015-10-01

Exposure to intense sound can damage or kill cochlear hair cells (HC). This loss of input typically manifests as noise induced hearing loss, but it can also be involved in the initiation of other auditory disorders such as tinnitus or hyperacusis. In this study we quantify changes in HC number following exposure to one of four sound damage paradigms. We exposed adult, anesthetized Long-Evans rats to a unilateral 16 kHz pure tone that varied in intensity (114 dB or 118 dB) and duration (1, 2, or 4 h) and sacrificed animals 2-4 weeks later. We compared two different methods of tissue preparation, plastic embedding/sectioning and whole mount dissection, for quantifying hair cell loss as a function of frequency. We found that the two methods of tissue preparation produced largely comparable cochleograms, with whole mount dissections allowing a more rapid evaluation of hair cell number. Both inner and outer hair cell loss was observed throughout the length of the cochlea irrespective of sound damage paradigm. Inner HC loss was either equal to or greater than outer HC loss. Increasing the duration of sound exposures resulted in more severe HC loss, which included all HC lesions observed in an analogous shorter duration exposure. Copyright © 2015 Elsevier B.V. All rights reserved.

Sound Transmission through Two Concentric Cylindrical Sandwich Shells

NASA Technical Reports Server (NTRS)

Tang, Yvette Y.; Silcox, Richard J.; Robinson, Jay H.

1996-01-01

This paper solves the problem of sound transmission through a system of two infinite concentric cylindrical sandwich shells. The shells are surrounded by external and internal fluid media and there is fluid (air) in the annular space between them. An oblique plane sound wave is incident upon the surface of the outer shell. A uniform flow is moving with a constant velocity in the external fluid medium. Classical thin shell theory is applied to the inner shell and first-order shear deformation theory is applied to the outer shell. A closed form for transmission loss is derived based on modal analysis. Investigations have been made for the impedance of both shells and the transmission loss through the shells from the exterior into the interior. Results are compared for double sandwich shells and single sandwich shells. This study shows that: (1) the impedance of the inner shell is much smaller than that of the outer shell so that the transmission loss is almost the same in both the annular space and the interior cavity of the shells; (2) the two concentric sandwich shells can produce an appreciable increase of transmission loss over single sandwich shells especially in the high frequency range; and (3) design guidelines may be derived with respect to the noise reduction requirement and the pressure in the annular space at a mid-frequency range.

KSC-07pd1294

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- Former astronauts take their seats in the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. In the front row are (left to right) John Young, Rick Searfoss, Charles Bolden and Norm Thagard. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

(abstract) A Low-Cost Mission to 2060 Chiron Based on the Pluto Fast Flyby

NASA Technical Reports Server (NTRS)

Stern, S. A.; Salvo, C. G.; Wallace, R. A.; Weinstein, S. S.; Weissman, P. R.

1994-01-01

The Pluto Fast Flyby-based mission to Chiron described in this paper is a low cost, scientifically rewarding, focused mission in the outer solar system. The proposed mission will make a flyby of 2060 Chiron, an active 'comet' with over 10(sup 4) times the mass of Halley, and an eccentric, Saturn-crossing orbit which ranges from 8.5 to 19 AU. This mission concept achieves the flyby 4.2 years after launch on a direct trajectory from Earth, is independent of Jupiter launch windows, and fits within Discovery cost guidelines. This mission offers the scientific opportunity to examine a class of object left unsampled by the trail-blazing Mariners, Pioneers, Voyagers, and missions to Halley. Spacecraft reconnaissance of Chiron addresses unique objectives relating to cometary science, other small bodies, the structure of quasi-bound atmospheres on modest-sized bodies, and the origin of primitive bodies and the giant planets. Owing to Chiron's large size (180

GREECE Mission Launching Into Aurora

NASA Image and Video Library

2014-03-04

Caption: A NASA-funded sounding rocket launches into an aurora in the early morning of March 3, 2014, over Venetie, Alaska. The GREECE mission studies how certain structures – classic curls like swirls of cream in coffee -- form in the aurora. Credit: NASA/Christopher Perry More info: On March 3, 2014, at 6:09 a.m. EST, a NASA-funded sounding rocket launched straight into an aurora over Venetie, Alaska. The Ground-to-Rocket Electrodynamics – Electron Correlative Experiment, or GREECE, sounding rocket mission, which launched from Poker Flat Research Range in Poker Flat, Alaska, will study classic curls in the aurora in the night sky. The GREECE instruments travel on a sounding rocket that launches for a ten-minute ride right through the heart of the aurora reaching its zenith over the native village of Venetie, Alaska. To study the curl structures, GREECE consists of two parts: ground-based imagers located in Venetie to track the aurora from the ground and the rocket to take measurements from the middle of the aurora itself. At their simplest, auroras are caused when particles from the sun funnel over to Earth's night side, generate electric currents, and trigger a shower of particles that strike oxygen and nitrogen some 60 to 200 miles up in Earth's atmosphere, releasing a flash of light. But the details are always more complicated, of course. Researchers wish to understand the aurora, and movement of plasma in general, at much smaller scales including such things as how different structures are formed there. This is a piece of information, which in turn, helps paint a picture of the sun-Earth connection and how energy and particles from the sun interact with Earth's own magnetic system, the magnetosphere. GREECE is a collaborative effort between SWRI, which developed particle instruments and the ground-based imaging, and the University of California, Berkeley, measuring the electric and magnetic fields. The launch is supported by a sounding rocket team from NASA’s Wallops Flight Facility, Wallops Island, Va. The Poker Flat Research Range is operated by the University of Alaska, Fairbanks. “The conditions were optimal,” said Marilia Samara, principal investigator for the mission at Southwest Research Institute in San Antonio, Texas. “We can’t wait to dig into the data.” For more information on the GREECE mission visit: www.nasa.gov/content/goddard/nasa-funded-sounding-rocket- .NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

KSC-07pd1287

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- NASA, Kennedy Space Center and State of Florida dignitaries helped launch the opening of the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. Walking through the crowd is former astronaut Roy Bridges, who also is a former center director of KSC. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

NASA's Space Launch System: Progress Toward the Proving Ground

NASA Technical Reports Server (NTRS)

Jackman, Angie

2017-01-01

Space Launch System will be able to offer payload accommodations with five times more volume than any contemporary launch vehicle. center dot Payload fairings of up to 10-meter diameter are planned. Space Launch System will offer an initial capability of greater than 70 metric tons to low Earth orbit; current U.S. launch vehicle maximum is 28 t. center dot Evolved version of SLS will offer greatest-ever capability of greater than 130 t to LEO. SLS offers reduced transit times to the outer solar system by half or greater. center dot Higher characteristic energy (C3) also enables larger payloads to destination.

Nuclear Thermal Rocket (NTR) Propulsion and Power Systems for Outer Planetary Exploration Missions

NASA Technical Reports Server (NTRS)

Borowski, S. K.; Cataldo, R. L.

2001-01-01

The high specific impulse (I (sub sp)) and engine thrust generated using liquid hydrogen (LH2)-cooled Nuclear Thermal Rocket (NTR) propulsion makes them attractive for upper stage applications for difficult robotic science missions to the outer planets. Besides high (I (sub sp)) and thrust, NTR engines can also be designed for "bimodal" operation allowing substantial amounts of electrical power (10's of kWe ) to be generated for onboard spacecraft systems and high data rate communications with Earth during the course of the mission. Two possible options for using the NTR are examined here. A high performance injection stage utilizing a single 15 klbf thrust engine can inject large payloads to the outer planets using a 20 t-class launch vehicle when operated in an "expendable mode". A smaller bimodal NTR stage generating approx. 1 klbf of thrust and 20 to 40 kWe for electric propulsion can deliver approx. 100 kg using lower cost launch vehicles. Additional information is contained in the original extended abstract.

KSC-07pd1292

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- A crowd of visitors to Kennedy Space Center's Visitor Complex eagerly wait to experience the newest attraction, the Shuttle Launch Experience. The attraction was officially open to the public following a ribbon breaking attended by NASA, Kennedy Space Center and State of Florida dignitaries. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

KSC-07pd1293

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- Former astronauts take their seats in the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. In the front row are (from left) Bob Crippen, John Young, Rick Searfoss, Charles Bolden and Norm Thagard. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

A Space Based Internet Protocol System for Launch Vehicle Tracking and Control

NASA Technical Reports Server (NTRS)

Bull, Barton; Grant, Charles; Morgan, Dwayne; Streich, Ron; Bauer, Frank (Technical Monitor)

2001-01-01

Personnel from the Goddard Space Flight Center Wallops Flight Facility (GSFC/WFF) in Virginia are responsible for the overall management of the NASA Sounding Rocket and Scientific Balloon Programs. Payloads are generally in support of NASA's Space Science Enterprise's missions and return a variety of scientific data as well as providing a reasonably economical means of conducting engineering tests for instruments and devices used on satellites and other spacecraft. Sounding rockets used by NASA can carry payloads of various weights to altitudes from 50 km to more than 1,300 km. Scientific balloons can carry a payload weighing as much as 3,630 Kg to an altitude of 42 km. Launch activities for both are conducted not only from established ranges, but also from remote locations worldwide requiring mobile tracking and command equipment to be transported and set up at considerable expense. The advent of low earth orbit (LEO) commercial communications satellites provides an opportunity to dramatically reduce tracking and control costs of these launch vehicles and Unpiloted Aerial Vehicles (UAVs) by reducing or eliminating this ground infrastructure. Additionally, since data transmission is by packetized Internet Protocol (IP), data can be received and commands initiated from practically any location. A low cost Commercial Off The Shelf (COTS) system is currently under development for sounding rockets that also has application to UAVs and scientific balloons. Due to relatively low data rate (9600 baud) currently available, the system will first be used to provide GPS data for tracking and vehicle recovery. Range safety requirements for launch vehicles usually stipulate at least two independent tracking sources. Most sounding rockets flown by NASA now carry GP receivers that output position data via the payload telemetry system to the ground station. The Flight Modem can be configured as a completely separate link thereby eliminating the requirement for tracking radar. The system architecture that integrates antennas, GPS receiver, commercial satellite packet data modem, and a single board computer with custom software is described along with the technical challenges and the plan for their resolution. These include antenna development, high Doppler rates, reliability, environmental ruggedness, hand over between satellites, and data security. An aggressive test plan is included which, in addition to environmental testing, measures bit error rate, latency and antenna patterns. Actual launches on a sounding rocket and various aircraft flights have taken place. Flight tests are planned for the near future on aircraft, long duration balloons and sounding rockets. These results, as well as the current status of the project, are reported.

SLS Overview and Progress

NASA Technical Reports Server (NTRS)

Honeycutt, John

2017-01-01

Space Launch System will be able to offer payload accommodations with five times more volume than any contemporary launch vehicle Payload fairings of up to 10-meter diameter are being studied Space Launch System will offer an initial capability of greater than 70 metric tons to low Earth orbit; current U.S. launch vehicle maximum is 28 t Evolved version of SLS will offer Mars-enabling capability of greater than 130 metric tons to LEO SLS offers reduced transit times to the outer solar system by half or greater Higher characteristic energy (C3) also enables larger payloads to destination

Outer Planet Exploration with Advanced Radioisotope Electric Propulsion

NASA Technical Reports Server (NTRS)

Oleson, Steven; Gefert, Leon; Patterson, Michael; Schreiber, Jeffrey; Benson, Scott; McAdams, Jim; Ostdiek, Paul

2002-01-01

In response to a request by the NASA Deep Space Exploration Technology Program, NASA Glenn Research Center conducted a study to identify advanced technology options to perform a Pluto/Kuiper mission without depending on a 2004 Jupiter Gravity Assist, but still arriving before 2020. A concept using a direct trajectory with small, sub-kilowatt ion thrusters and Stirling radioisotope power systems was shown to allow the same or smaller launch vehicle class as the chemical 2004 baseline and allow a launch slip and still flyby in the 2014 to 2020 timeframe. With this promising result the study was expanded to use a radioisotope power source for small electrically propelled orbiter spacecraft for outer planet targets such as Uranus, Neptune, and Pluto.

The Advanced Technology Microwave Sounder (ATMS): A New Operational Sensor Series

NASA Technical Reports Server (NTRS)

Kim, Edward; Lyu, Cheng-H Joseph; Leslie, R. Vince; Baker, Neal; Mo, Tsan; Sun, Ninghai; Bi, Li; Anderson, Mike; Landrum, Mike; DeAmici, Giovanni;

Beyond Electric Propulsion: Non-Propulsive Benefits of Nuclear Power for the Exploration of the Outer Solar System

NASA Astrophysics Data System (ADS)

Zubrin, Robert M.

1994-07-01

In the past, most studies dealing with the benefits of space nuclear electric power systems for solar system exploration have focused on the potential of nuclear electric propulsion (NEP) to enhance missions by increasing delivered payload, decreasing LEO mass, or reducing trip time. While important, such mission enhancements have failed to go to the heart of the concerns of the scientific community supporting interplanetary exploration. To put the matter succinctly, scientists don't buy delivered payload - they buy data returned. With nuclear power we can increase both the quantity of data returned, by enormously increasing data communication rates, and the quality of data by enabling a host of active sensing techniques otherwise impossible. These non-propulsive mission enhancement capabilities of space nuclear power have been known in principle for many years, but they have not been adequately documented. As a result, support for the development of space nuclear power by the interplanetary exploration community has been much less forceful than it might otherwise be. In this paper we shall present mission designs that take full advantage of the potential mission enhancements offered by space nuclear power systems in the 10 to 100 kWe range, not just for propulsion, but to radically improve, enrich, and expand the science return itself. Missions considered include orbiter missions to each of the outer planets. It will be shown that be using hybrid trajectories combining chemical propulsion with NEP and (in certain cases) gravity assists, that it is possible, using a Titan IV-Centaur launch vehicle, for high-powered spacecraft to be placed in orbit around each of the outer planets with electric propulsion burn times of less than 4 years. Such hybrid trajectories therefore make the outer solar-system available to near-term nuclear electric power systems. Once in orbit, the spacecraft will utilize multi-kilowatt communication systems, similar to those now employed by the U.S. military, to increase data return far beyond that possible utilizing the 40 W rf traveling wave tube antennas that are the current NASA standard. This higher data rate will make possible very high resolution multi-spectral imaging (with high resolutions both spatially and spectrally), a form of science hitherto impossible in the outer solar system. Large numbers of such images could be returned, allowing the creation of motion pictures of atmospheric phenomenon on a small scale and greatly increasing the probability of capturing transient phenomena such as lighting or volcanic activity. The multi-kilowatt power sources on the spacecraft also enables active sensing, including radar, which could be used to do topographic and subsurface studies of clouded bodies such as Titan, ground penetrating sounding of Pluto, the major planet's moons, and planetoids, and topside sounding of the electrically conductive atmospheres of Jupiter, Saturn, Uranus and Neptune to produce profiles of fluid density, conductivity, and horizontal and vertical velocity as a function of depth and global location. Radio science investigations of planetary atmospheres and ring systems would be greatly enhanced by increased transmitter power. The scientific benefits of utilizing such techniques are discussed, and a comparison is made with the quantity and quality of science that a low-powered spacecraft employing RTGs could return. It is concluded that the non-propulsive benefits of nuclear power for spacecraft exploring the outer solar system are enormous, and taken together with the well documented mission enhancements enabled by electric propulsion fully justify the expenditures needed to bring a space qualified nuclear electric power source into being.

KSC-07pd1286

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- NASA, Kennedy Space Center and State of Florida dignitaries helped launch the opening of the newest attraction at Kennedy Space Center's Visitor Complex the Shuttle Launch Experience. Former astronauts John Young (left) and Bob Crippen (right) share their impressions with the audience. Seated on stage are Lt. Governor of Florida Jeff Kottkamp and Center Director Bill Parsons. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

Radioisotope Electric Propulsion for Fast Outer Planetary Orbiters

NASA Technical Reports Server (NTRS)

Oleson, Steven; Benson, Scott; Gefert, Leon; Patterson, Michael; Schreiber, Jeffrey

2002-01-01

Recent interest in outer planetary targets by the Office of Space Science has spurred the search for technology options to enable relatively quick missions to outer planetary targets. Several options are being explored including solar electric propelled stages combined with aerocapture at the target and nuclear electric propulsion. Another option uses radioisotope powered electric thrusters to reach the outer planets. Past work looked at using this technology to provide faster flybys. A better use for this technology is for outer planet orbiters. Combined with medium class launch vehicles and a new direct trajectory these small, sub-kilowatt ion thrusters and Stirling radioisotope generators were found to allow missions as fast as 5 to 12 years for objects from Saturn to Pluto, respectively. Key to the development is light spacecraft and science payload technologies.

Atmosphere Explorer set for launch

NASA Technical Reports Server (NTRS)

1975-01-01

The Atmosphere Explorer-D (Explorer-54) is described which will explore in detail an area of the earth's outer atmosphere where important energy transfer, atomic and molecular processes, and chemical reactions occur that are critical to the heat balance of the atmosphere. Data are presented on the mission facts, launch vehicle operations, AE-D/Delta flight events, spacecraft description, scientific instruments, tracking, and data acquisition.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the second Mars Exploration Rover, Opportunity, is poised for launch after rollback of the Mobile Service Tower. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rover’s prime mission is planned to last three months on Mars.

NASA Image and Video Library

2003-07-07

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the second Mars Exploration Rover, Opportunity, is poised for launch after rollback of the Mobile Service Tower. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rover’s prime mission is planned to last three months on Mars.

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the rover "Opportunity" for the second Mars Exploration Rover mission launches at 11:18:15 p.m. EDT. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rover’s prime mission is planned to last three months on Mars.

NASA Image and Video Library

2003-07-07

KENNEDY SPACE CENTER, FLA. - On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the rover "Opportunity" for the second Mars Exploration Rover mission launches at 11:18:15 p.m. EDT. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rover’s prime mission is planned to last three months on Mars.

Structural parameter effect of porous material on sound absorption performance of double-resonance material

NASA Astrophysics Data System (ADS)

Fan, C.; Tian, Y.; Wang, Z. Q.; Nie, J. K.; Wang, G. K.; Liu, X. S.

2017-06-01

In view of the noise feature and service environment of urban power substations, this paper explores the idea of compound impedance, fills some porous sound-absorption material in the first resonance cavity of the double-resonance sound-absorption material, and designs a new-type of composite acoustic board. We conduct some acoustic characterizations according to the standard test of impedance tube, and research on the influence of assembly order, the thickness and area density of the filling material, and back cavity on material sound-absorption performance. The results show that the new-type of acoustic board consisting of aluminum fibrous material as inner structure, micro-porous board as outer structure, and polyester-filled space between them, has good sound-absorption performance for low frequency and full frequency noise. When the thickness, area density of filling material and thickness of back cavity increase, the sound absorption coefficient curve peak will move toward low frequency.

46 CFR 199.640 - Alternatives for cargo vessels in a specified service.

Code of Federal Regulations, 2012 CFR

2012-10-01

...; coastwise; Great Lakes; lakes, bays, and sounds; and rivers service may comply with alternative requirements... Coastwise Great Lakes Lakes, bays, and sounds Rivers 199.60(c): Distress signals 199.640(b) 1 199.640(b) 1... capacity sufficient to accommodate the total number of people on board. The lifefloat launching arrangement...

46 CFR 199.640 - Alternatives for cargo vessels in a specified service.

Code of Federal Regulations, 2011 CFR

2011-10-01

...; coastwise; Great Lakes; lakes, bays, and sounds; and rivers service may comply with alternative requirements... Coastwise Great Lakes Lakes, bays, and sounds Rivers 199.60(c): Distress signals 199.640(b) 1 199.640(b) 1... capacity sufficient to accommodate the total number of people on board. The lifefloat launching arrangement...

46 CFR 199.640 - Alternatives for cargo vessels in a specified service.

Code of Federal Regulations, 2010 CFR

2010-10-01

...; coastwise; Great Lakes; lakes, bays, and sounds; and rivers service may comply with alternative requirements... Coastwise Great Lakes Lakes, bays, and sounds Rivers 199.60(c): Distress signals 199.640(b) 1 199.640(b) 1... capacity sufficient to accommodate the total number of people on board. The lifefloat launching arrangement...

46 CFR 199.640 - Alternatives for cargo vessels in a specified service.

Code of Federal Regulations, 2014 CFR

2014-10-01

...; coastwise; Great Lakes; lakes, bays, and sounds; and rivers service may comply with alternative requirements... Coastwise Great Lakes Lakes, bays, and sounds Rivers 199.60(c): Distress signals 199.640(b) 1 199.640(b) 1... capacity sufficient to accommodate the total number of people on board. The lifefloat launching arrangement...

46 CFR 199.640 - Alternatives for cargo vessels in a specified service.

Code of Federal Regulations, 2013 CFR

2013-10-01

...; coastwise; Great Lakes; lakes, bays, and sounds; and rivers service may comply with alternative requirements... Coastwise Great Lakes Lakes, bays, and sounds Rivers 199.60(c): Distress signals 199.640(b) 1 199.640(b) 1... capacity sufficient to accommodate the total number of people on board. The lifefloat launching arrangement...

Results of the measurement of the vertical profile of ozone up to a height of 70 km by means of the MR-12 and M-100 sounding rockets

NASA Technical Reports Server (NTRS)

Brezgin, N. I.; Kuznetsov, G. I.; Chizhov, A. F.; Shtyrkov, O. V.

1979-01-01

The photometers used and methods of calculation of the vertical ozone concentration profile are described. The results obtained in several series of MR-12 and M-100 sounding rocket launchings are presented and discussed.

Rocket noise - A review

NASA Astrophysics Data System (ADS)

McInerny, S. A.

1990-10-01

This paper reviews what is known about far-field rocket noise from the controlled studies of the late 1950s and 1960s and from launch data. The peak dimensionless frequency, the dependence of overall sound power on exhaust parameters, and the directivity of the overall sound power of rockets are compared to those of subsonic jets and turbo-jets. The location of the dominant sound source in the rocket exhaust plume and the mean flow velocity in this region are discussed and shown to provide a qualitative explanation for the low peak Strouhal number, fD(e)/V(e), and large angle of maximum directivity. Lastly, two empirical prediction methods are compared with data from launches of a Titan family vehicle (two, solid rocket motors of 5.7 x 10 to the 6th N thrust each) and the Saturn V (five, liquid oxygen/rocket propellant engines of 6.7 x 10 to the 6th N thrust, each). The agreement is favorable. In contrast, these methods appear to overpredict the far-field sound pressure levels generated by the Space Shuttle.

A telescopic cinema sound camera for observing high altitude aerospace vehicles

NASA Astrophysics Data System (ADS)

Slater, Dan

2014-09-01

Rockets and other high altitude aerospace vehicles produce interesting visual and aural phenomena that can be remotely observed from long distances. This paper describes a compact, passive and covert remote sensing system that can produce high resolution sound movies at >100 km viewing distances. The telescopic high resolution camera is capable of resolving and quantifying space launch vehicle dynamics including plume formation, staging events and payload fairing jettison. Flight vehicles produce sounds and vibrations that modulate the local electromagnetic environment. These audio frequency modulations can be remotely sensed by passive optical and radio wave detectors. Acousto-optic sensing methods were primarily used but an experimental radioacoustic sensor using passive micro-Doppler radar techniques was also tested. The synchronized combination of high resolution flight vehicle imagery with the associated vehicle sounds produces a cinema like experience that that is useful in both an aerospace engineering and a Hollywood film production context. Examples of visual, aural and radar observations of the first SpaceX Falcon 9 v1.1 rocket launch are shown and discussed.

Bulgarian singer Dyana presents PA Director Dickinson with her new CD on STS-90 launch day

NASA Technical Reports Server (NTRS)

1998-01-01

David Dickinson, the acting director of the National Aeronautics and Space Administration (NASA) Public Affairs Office at Kennedy Space Center, accepts a copy of Bulgarian singer Dyana Dafova's latest compact disc (CD) from her on behalf of NASA. The 525-foot tall Vehicle Assembly Building, where Space Shuttle orbiters are mated to their external tank/solid rocket booster stacks, looms in the background. Dyana is touring the United States to promote her CD, entitled 'Sounds of the Earth,' and was an invited guest of NASA for the launch of Columbia on STS-90, the Neurolab mission, earlier in the day. Columbia lifted off from Launch Pad 39B at 2:19 p.m. EDT. Dyana characterized the music on her CD as a new sound, incorporating jazz and new age classics, sung in a newly created language comprised of Bulgarian, English, Sanskrit, Aramski and Hebrew.

MUSIC Successfully Launched from NASA Wallops

NASA Image and Video Library

2017-12-08

The Multiple User Suborbital Instrument Carrier or MUSIC payload was successfully launched at 9:50 a.m. today on a Terrier-Improved Malemute suborbital sounding rocket from NASA’s Wallops Flight Facility. The payload flew to approximately 115 miles apogee and preliminary analysis shows good data was received. Payload recovery is in progress. The next launch from Wallops is between 7 and 10 a.m. EST, Monday, March 7. Three space technology payloads will be carried on a Terrier-Improved Orion suborbital sounding rocket. Credit: NASA/Wallops/Allison Stancil NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

KSC-00pp1300

NASA Image and Video Library

2000-09-12

KENNEDY SPACE CENTER, Fla. -- While the morning sun paints the sky pale gold, the structures on Launch Pad 39A are silhouetted in brown. Space Shuttle Discovery can be seen on the other side of the Fixed Service Structure; the Rotating Service Structure at right is still open. At left is the 300,000-gallon water tank that is part of the sound suppression system during launches. Discovery will launch on mission STS-92 Oct. 5, 2000

KSC00pp1300

NASA Image and Video Library

2000-09-12

KENNEDY SPACE CENTER, Fla. -- While the morning sun paints the sky pale gold, the structures on Launch Pad 39A are silhouetted in brown. Space Shuttle Discovery can be seen on the other side of the Fixed Service Structure; the Rotating Service Structure at right is still open. At left is the 300,000-gallon water tank that is part of the sound suppression system during launches. Discovery will launch on mission STS-92 Oct. 5, 2000

Characterizing the 3-D atmosphere with NUCAPS sounding products from multiple platforms

NASA Astrophysics Data System (ADS)

Barnet, C. D.; Smith, N.; Gambacorta, A.; Wheeler, A. A.; Sjoberg, W.; Goldberg, M.

2017-12-01

The JPSS Proving Ground and Risk Reduction (PGRR) Program launched the Sounding Initiative in 2014 to develop operational applications that use 3-D satellite soundings. These are near global daily swaths of vertical atmospheric profiles of temperature, moisture and trace gas species. When high vertical resolution satellite soundings first became available, their assimilation into user applications was slow: forecasters familiar with 2-D satellite imagery or 1-D radiosondes did not have the technical capability nor product knowledge to readily ingest satellite soundings. Similarly, the satellite sounding developer community lacked wherewithal to understand the many challenges forecasters face in their real time decision-making. It took the PGRR Sounding Initiative to bring these two communities together and develop novel applications that now depend on NUCAPS soundings. NUCAPS - the NOAA Unique Combined Atmospheric Processing System - is platform agnostic and generates satellite soundings from measurements made by infrared and microwave sounder pairs on the MetOp (IASI/AMSU) and Suomi NPP (CrIS/ATMS) polar-orbiting platforms. We highlight here three new applications developed under the PGRR Sounding Initiative. They are, (i) aviation: NUCAPS identifies cold air "blobs" that causes jet fuel to freeze, (ii) severe weather: NUCAPS identifies areas of convective initiation, and (iii) air quality: NUCAPS identifies stratospheric intrusions and tracks long-range transport of biomass burning plumes. The value of NUCAPS being platform agnostic will become apparent with the JPSS-1 launch. NUCAPS soundings from Suomi NPP and JPSS-1, being 50 min apart, could capture fast-changing weather events and together with NUCAPS soundings from the two MetOp platforms ( 4 hours earlier in the day than JPSS) could characterize diurnal cycles. In this paper, we will summarize key accomplishments and assess whether NUCAPS maintains enough continuity in its sounding products from multiple platforms to sufficiently characterize atmospheric evolution at localized scales. With this we will address one of the primary data requirements that emerged in the Sounding Initiative, namely the need for a time sequence of satellite sounding products.

Atmospheric Soundings from AIRS/AMSU/HSB

NASA Technical Reports Server (NTRS)

Susskind, Joel; Atlas, Robert

2004-01-01

AIRS was launched on EOS Aqua on May 4, 2002, together with AMSU A and HSB, to form a next generation polar orbiting infrared and microwave atmospheric sounding system. The primary products of AIRS/AMSU/HSB are twice daily global fields of atmospheric temperature-humidity profiles, ozone profiles, sea/land surface skin temperature, and cloud related parameters including OLR. The sounding goals of AIRS are to produce 1 km tropospheric layer mean temperatures with an rms error of lK, and 1 km tropospheric layer precipitable water with an rms error of 20%, in cases with up to 80% effective cloud cover. Pre-launch simulation studies indicated that these results should be achievable. Minor modifications have been made to the pre-launch retrieval algorithm as alluded to in this paper. Sample fields of parameters retrieved from AIRS/AMSU/HSB data are presented and temperature profiles are validated as a function of retrieved effective fractional cloud cover. As in simulation, the degradation of retrieval accuracy with increasing cloud cover is small. Select fields are also compared to those contained in the ECMWF analysis, done without the benefit of AIRS data, to demonstrate information that AIRS can add to that already contained in the ECMWF analysis. Assimilation of AIRS temperature soundings in up to 80% cloud cover for the month of January 2003 into the GSFC FVSSI data assimilation system resulted in improved 5 day forecasts globally, both with regard to anomaly correlation coefficients and the prediction of location and intensity of cyclones.

Launch Environment Water Flow Simulations Using Smoothed Particle Hydrodynamics

NASA Technical Reports Server (NTRS)

Vu, Bruce T.; Berg, Jared J.; Harris, Michael F.; Crespo, Alejandro C.

2015-01-01

This paper describes the use of Smoothed Particle Hydrodynamics (SPH) to simulate the water flow from the rainbird nozzle system used in the sound suppression system during pad abort and nominal launch. The simulations help determine if water from rainbird nozzles will impinge on the rocket nozzles and other sensitive ground support elements.

Improved Soundings and Error Estimates using AIRS/AMSU Data

NASA Technical Reports Server (NTRS)

Susskind, Joel

2006-01-01

AIRS was launched on EOS Aqua on May 4, 2002, together with AMSU A and HSB, to form a next generation polar orbiting infrared and microwave atmospheric sounding system. The primary products of AIRS/AMSU are twice daily global fields of atmospheric temperature-humidity profiles, ozone profiles, sea/land surface skin temperature, and cloud related parameters including OLR. The sounding goals of AIRS are to produce 1 km tropospheric layer mean temperatures with an rms error of 1 K, and layer precipitable water with an rms error of 20 percent, in cases with up to 80 percent effective cloud cover. The basic theory used to analyze AIRS/AMSU/HSB data in the presence of clouds, called the at-launch algorithm, and a post-launch algorithm which differed only in the minor details from the at-launch algorithm, have been described previously. The post-launch algorithm, referred to as AIRS Version 4.0, has been used by the Goddard DAAC to analyze and distribute AIRS retrieval products. In this paper we show progress made toward the AIRS Version 5.0 algorithm which will be used by the Goddard DAAC starting late in 2006. A new methodology has been developed to provide accurate case by case error estimates for retrieved geophysical parameters and for the channel by channel cloud cleared radiances used to derive the geophysical parameters from the AIRS/AMSU observations. These error estimates are in turn used for quality control of the derived geophysical parameters and clear column radiances. Improvements made to the retrieval algorithm since Version 4.0 are described as well as results comparing Version 5.0 retrieval accuracy and spatial coverage with those obtained using Version 4.0.

Finite element modelling of sound transmission from outer to inner ear.

PubMed

Areias, Bruno; Santos, Carla; Natal Jorge, Renato M; Gentil, Fernanda; Parente, Marco Pl

2016-11-01

The ear is one of the most complex organs in the human body. Sound is a sequence of pressure waves, which propagates through a compressible media such as air. The pinna concentrates the sound waves into the external auditory meatus. In this canal, the sound is conducted to the tympanic membrane. The tympanic membrane transforms the pressure variations into mechanical displacements, which are then transmitted to the ossicles. The vibration of the stapes footplate creates pressure waves in the fluid inside the cochlea; these pressure waves stimulate the hair cells, generating electrical signals which are sent to the brain through the cochlear nerve, where they are decoded. In this work, a three-dimensional finite element model of the human ear is developed. The model incorporates the tympanic membrane, ossicular bones, part of temporal bone (external auditory meatus and tympanic cavity), middle ear ligaments and tendons, cochlear fluid, skin, ear cartilage, jaw and the air in external auditory meatus and tympanic cavity. Using the finite element method, the magnitude and the phase angle of the umbo and stapes footplate displacement are calculated. Two slightly different models are used: one model takes into consideration the presence of air in the external auditory meatus while the other does not. The middle ear sound transfer function is determined for a stimulus of 60 dB SPL, applied to the outer surface of the air in the external auditory meatus. The obtained results are compared with previously published data in the literature. This study highlights the importance of external auditory meatus in the sound transmission. The pressure gain is calculated for the external auditory meatus.

PVDF-Based Piezoelectric Microphone for Sound Detection Inside the Cochlea: Toward Totally Implantable Cochlear Implants.

PubMed

Park, Steve; Guan, Xiying; Kim, Youngwan; Creighton, Francis Pete X; Wei, Eric; Kymissis, Ioannis John; Nakajima, Hideko Heidi; Olson, Elizabeth S

2018-01-01

We report the fabrication and characterization of a prototype polyvinylidene fluoride polymer-based implantable microphone for detecting sound inside gerbil and human cochleae. With the current configuration and amplification, the signal-to-noise ratios were sufficiently high for normally occurring sound pressures and frequencies (ear canal pressures >50-60 dB SPL and 0.1-10 kHz), though 10 to 20 dB poorer than for some hearing aid microphones. These results demonstrate the feasibility of the prototype devices as implantable microphones for the development of totally implantable cochlear implants. For patients, this will improve sound reception by utilizing the outer ear and will improve the use of cochlear implants.

PVDF-Based Piezoelectric Microphone for Sound Detection Inside the Cochlea: Toward Totally Implantable Cochlear Implants

PubMed Central

Guan, Xiying; Kim, Youngwan; Creighton, Francis (Pete) X.; Wei, Eric; Kymissis, Ioannis(John); Nakajima, Hideko Heidi; Olson, Elizabeth S.

2018-01-01

We report the fabrication and characterization of a prototype polyvinylidene fluoride polymer-based implantable microphone for detecting sound inside gerbil and human cochleae. With the current configuration and amplification, the signal-to-noise ratios were sufficiently high for normally occurring sound pressures and frequencies (ear canal pressures >50–60 dB SPL and 0.1–10 kHz), though 10 to 20 dB poorer than for some hearing aid microphones. These results demonstrate the feasibility of the prototype devices as implantable microphones for the development of totally implantable cochlear implants. For patients, this will improve sound reception by utilizing the outer ear and will improve the use of cochlear implants. PMID:29732950

Enhanced Soundings for Local Coupling Studies: 2015 ARM Climate Research Facility Field Campaign

DOE Office of Scientific and Technical Information (OSTI.GOV)

Ferguson, CR; Santanello, JA; Gentine, P

2015-11-01

Matching observed diurnal cycles is a fundamental yet extremely complex test for models. High temporal resolution measurements of surface turbulent heat fluxes and boundary layer properties are required to evaluate the daytime evolution of the boundary layer and its sensitivity to land-atmosphere coupling. To address this need, (12) one-day intensive observing periods (IOP) with enhanced radiosonding will be carried out at the ARM Southern Great Plains (SGP) Central Facility (CF) during summer 2015. Each IOP will comprise a single launch to correspond with the nighttime overpass of the A-Train of satellites (~0830 UTC) and hourly launches during daytime beginning frommore » 1130 UTC and ending at 2130 UTC. At 3-hourly intervals (i.e., 1140 UTC, 1440 UTC, 1740 UTC, and 2040 UTC) a duplicate second radiosonde will be launched 10 minutes subsequent to launch of the on-hour radiosonde for the purpose of assessing horizontal atmospheric variability. In summary, each IOP will have a 14-sounding supplement to the 6-hourly operational sounding schedule at the ARM-SGP CF. The IOP days will be decided before sunset on the preceding day, according to the judgment of the PI’s and taking into consideration daily weather forecasts and the operability of complimentary ARM-SGP CF instrumentation. An overarching goal of the project is to address how ARM could better observe land-atmosphere coupling to support the evaluation and refinement of coupled weather and climate models.« less

GPS Sounding Rocket Developments

NASA Technical Reports Server (NTRS)

Bull, Barton

1999-01-01

Sounding rockets are suborbital launch vehicles capable of carrying scientific payloads several hundred miles in altitude. These missions return a variety of scientific data including; chemical makeup and physical processes taking place in the atmosphere, natural radiation surrounding the Earth, data on the Sun, stars, galaxies and many other phenomena. In addition, sounding rockets provide a reasonably economical means of conducting engineering tests for instruments and devices used on satellites and other spacecraft prior to their use in more expensive activities. This paper addresses the NASA Wallops Island history of GPS Sounding Rocket experience since 1994 and the development of highly accurate and useful system.

Creating a AIRS/AMSU and CrIS/ATMS continuity sounding product

NASA Astrophysics Data System (ADS)

Barnet, C. D.; Gambacorta, A.; Smith, N.; Wheeler, A. A.

2017-12-01

The AIRS/AMSU (Atmospheric Infrared Sounder; Advanced Microwave Sounding Unit) onboard the EOS/Aqua was launched in 2002. CrIS/ATMS (CrossTrack Infrared Sounder; Advanced Technology Microwave Sounder) onboard Suomi NPP was launched in 2011 and will also be launched on the Joint Polar Sounding System (JPSS) series of satellites beginning in 2017. Suomi NPP and EOS/Aqua now have more than five years of overlap. Demonstrating data continuity between these two platforms has become a priority especially since EOS/Aqua is well past its design lifetime. Additionally, with JPSS, this record of soundings will be extended into future decades and will enable critically important scientific research on large scale (long term) atmospheric processes. The AIRS/AMSU and CrIS/ATMS have many differences in instrument design, spatial sampling, spectral coverage and resolution. Instruments also degrade with time. It is only with careful, deliberate and transparent error characterization and propagation that systematic effects can be accounted for, and preferably minimized, in retrieved sounding products. We have developed the Community Long-term Infrared Microwave Coupled Product System (CLIMCAPS) to achieve a seamless record of satellite soundings. A CLIMCAPS sounding is comprised of a set of parameters that characterizes the full atmospheric state and includes profiles of temperature, moisture, cloud and surface products, and trace gas species (O3, CH4, CO, SO2, HNO3, N2O and CO2). The trace gases are by-products necessary to remove biases in temperature and moisture retrievals; however, they can also be readily ingested into science applications. The information content of an IR sounder such as AIRS and CrIS is a function of lapse rate, the quantity of absorbers such as clouds, moisture and trace gases, as well as the instrument's sensitivity. Information content can vary vertically, spatially, and temporally. CLIMCAPS uses the NASA Modern-Era Retrospective Analysis for Research (MERRA) as an a-priori to stabilize the solution in low information content domains. We will demonstrate the unique properties of the CLIMCAPS algorithm that enables continuity and error characterization with the Aqua/NPP data record.

KSC-07pd1284

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- NASA, Kennedy Space Center and State of Florida dignitaries helped launch the opening of the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. At the dais is Dan LeBlanc, chief operating officer of the KSC Visitor Complex. Seated on stage are (from left) Lt. Governor of Florida Jeff Kottkamp, Center Director Bill Parsons, and former astronauts John Young and Bob Crippen. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

50 CFR 216.234 - Mitigation, monitoring and reporting.

Code of Federal Regulations, 2010 CFR

2010-10-01

... sound level monitor mounted upon the Ugak Island haulout and set to highlight sounds greater than 70 dBA... northern side of the island and their reactions to launch noise will be made as soon as practicable. A... to flush as a result of the overflight and estimate a number. (f) The holder of the Letter of...

Determination of the center of brightness of the lunar crescent. [through use of a sounding rocket payload

NASA Technical Reports Server (NTRS)

Rose, C.

1975-01-01

The operational characteristics of the lunar sensor which was used to point the sounding rocket are discussed briefly. The associated mathematical model of the system is developed and the computer programs which were written to implement the model are described. Data pertinent to the two launches is presented.

Project Hermes 'Use of Smartphones for Receiving Telemetry and Commanding a Satellite'

NASA Technical Reports Server (NTRS)

Maharaja, Rishabh (Principal Investigator)

2016-01-01

TCPIP protocols can be applied for satellite command, control, and data transfer. Project Hermes was an experiment set-up to test the use of the TCPIP protocol for communicating with a space bound payload. The idea was successfully demonstrated on high altitude balloon flights and on a sub-orbital sounding rocket launched from NASAs Wallops Flight Facility. TCPIP protocols can be applied for satellite command, control, and data transfer. Project Hermes was an experiment set-up to test the use of the TCPIP protocol for communicating with a space bound payload. The idea was successfully demonstrated on high altitude balloon flights and on a sub-orbital sounding rocket launched from NASAs Wallops Flight Facility.

Deep electromagnetic sounding of the moon with Lunokhod 2 data

NASA Technical Reports Server (NTRS)

Vanyan, L. L.; Yegorov, I. V.; Faynberg, E. B.

1977-01-01

Results of electromagnetic sounding distinguished an outer high resistance shell about 200 km thick in the moon's structure. A preliminary petrological interpretation of the moon's layers indicated their origin as a consequence of differentiation of the initial peridotite material. Upon melting, 20% to 40% of the material melts and is removed to form a high resistance basaltic shell underlain by a layer of spinal peridotites enriched in divalent iron oxides and having a reduced resistance.

The Space Launch System and Missions to the Outer Solar System

NASA Astrophysics Data System (ADS)

Klaus, Kurt K.; Post, Kevin

2015-11-01

Introduction: America’s heavy lift launch vehicle, the Space Launch System, enables a variety of planetary science missions. The SLS can be used for most, if not all, of the National Research Council’s Planetary Science Decadal Survey missions to the outer planets. The SLS performance enables larger payloads and faster travel times with reduced operational complexity.Europa Clipper: Our analysis shows that a launch on the SLS would shorten the Clipper mission travel time by more than four years over earlier mission concept studies.Jupiter Trojan Tour and Rendezvous: Our mission concept replaces Advanced Stirling Radioisotope Generators (ASRGs) in the original design with solar arrays. The SLS capability offers many more target opportunities.Comet Surface Sample Return: Although in our mission concept, the SLS launches later than the NRC mission study (November 2022 instead of the original launch date of January 2021), it reduces the total mission time, including sample return, by two years.Saturn Apmospheric Entry Probe: Though Saturn arrivial time remains the same in our concept as the arrival date in the NRC study (2034), launching on the SLS shortens the mission travel time by three years with a direct ballistic trajectory.Uranus Orbiter with Probes: The SLS shortens travel time for an Uranus mission by four years with a Jupiter swing-by trajectory. It removes the need for a solar electric propulsion (SEP) stage used in the NRC mission concept study.Other SLS Science Mission Candidates: Two other mission concepts we are investigating that may be of interest to this community are the Advanced Technology Large Aperature Space Telescope (ATLAST) and the Interstellar Explorer also referred to as the Interstellar Probe.Summary: The first launch of the SLS is scheduled for 2018 followed by the first human launch in 2021. The SLS in its evolving configurations will enable a broad range of exploration missions which will serve to recapture the enthusiasm and commitment that permeated the planetary exploration community during the early years of robotic exploration.

15 CFR 744.3 - Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch...

Code of Federal Regulations, 2010 CFR

2010-01-01

... 15 Commerce and Foreign Trade 2 2010-01-01 2010-01-01 false Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch vehicles and sounding rockets) and Unmanned Air...: END-USER AND END-USE BASED § 744.3 Restrictions on Certain Rocket Systems (including ballistic missile...

15 CFR 744.3 - Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch...

Code of Federal Regulations, 2011 CFR

2011-01-01

... 15 Commerce and Foreign Trade 2 2011-01-01 2011-01-01 false Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch vehicles and sounding rockets) and Unmanned Air...: END-USER AND END-USE BASED § 744.3 Restrictions on Certain Rocket Systems (including ballistic missile...

15 CFR 744.3 - Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch...

Code of Federal Regulations, 2013 CFR

2013-01-01

... 15 Commerce and Foreign Trade 2 2013-01-01 2013-01-01 false Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch vehicles and sounding rockets) and Unmanned Air...: END-USER AND END-USE BASED § 744.3 Restrictions on Certain Rocket Systems (including ballistic missile...

15 CFR 744.3 - Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch...

Code of Federal Regulations, 2014 CFR

2014-01-01

... 15 Commerce and Foreign Trade 2 2014-01-01 2014-01-01 false Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch vehicles and sounding rockets) and Unmanned Air...: END-USER AND END-USE BASED § 744.3 Restrictions on Certain Rocket Systems (including ballistic missile...

15 CFR 744.3 - Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch...

Code of Federal Regulations, 2012 CFR

2012-01-01

... 15 Commerce and Foreign Trade 2 2012-01-01 2012-01-01 false Restrictions on Certain Rocket Systems (including ballistic missile systems and space launch vehicles and sounding rockets) and Unmanned Air...: END-USER AND END-USE BASED § 744.3 Restrictions on Certain Rocket Systems (including ballistic missile...

KSC-2009-2537

NASA Image and Video Library

2009-04-06

CAPE CANAVERAL, Fla. – The sound suppression system is tested on the mobile launcher platform on Launch Pad 39B at NASA's Kennedy Space Center in Florida. Pad 39B will be the site of the first Ares vehicle launch, including the Ares I-X flight test that is targeted for summer 2009. The mobile launcher platform was handed over to the Constellation Program and modified for the Ares I-X flight test. It is being tested before being moved to the Vehicle Assembly Building for assembly of the Ares I-X rocket. A sound suppression water system is in¬stalled on the pads to protect against damage by acoustical energy and rocket exhaust reflected from the flame trench and mobile launcher plat¬form during a launch. The sound suppression system includes an elevated 290-foot-high water tank with a capacity of 300,000 gallons. The water releases just prior to the ignition of the rocket and flows through 7-foot-diameter pipes for about 20 seconds. A torrent of water will flow onto the mobile launcher platform from six large quench nozzles, or “rainbirds,” mounted on its surface. The rainbirds are 12 feet high. The two in the center are 42 inches in diameter; the other four have a 30-inch diameter. Photo credit: NASA/Jim Grossmann

KSC-2009-2538

NASA Image and Video Library

2009-04-06

CAPE CANAVERAL, Fla. – The sound suppression system is tested on the mobile launcher platform on Launch Pad 39B at NASA's Kennedy Space Center in Florida. Pad 39B will be the site of the first Ares vehicle launch, including the Ares I-X flight test that is targeted for summer 2009. The mobile launcher platform was handed over to the Constellation Program and modified for the Ares I-X flight test. It is being tested before being moved to the Vehicle Assembly Building for assembly of the Ares I-X rocket. A sound suppression water system is in¬stalled on the pads to protect against damage by acoustical energy and rocket exhaust reflected from the flame trench and mobile launcher plat¬form during a launch. The sound suppression system includes an elevated 290-foot-high water tank with a capacity of 300,000 gallons. The water releases just prior to the ignition of the rocket and flows through 7-foot-diameter pipes for about 20 seconds. A torrent of water will flow onto the mobile launcher platform from six large quench nozzles, or “rainbirds,” mounted on its surface. The rainbirds are 12 feet high. The two in the center are 42 inches in diameter; the other four have a 30-inch diameter. Photo credit: NASA/Jim Grossmann

Small Space Launch: Origins & Challenges

NASA Astrophysics Data System (ADS)

Freeman, T.; Delarosa, J.

2010-09-01

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. 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 an old, unresponsive and relatively expensive set of launchers in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. 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. On 1 Aug 06, Air Force Space Command activated the Space Development & Test Wing (SDTW) to perform development, test and evaluation of Air Force space systems and to execute advanced space deployment and demonstration projects to exploit new concepts and technologies, and rapidly migrate capabilities to the warfighter. The SDTW charged the Launch Test Squadron (LTS) with the mission to develop the capability of small space launch, supporting government research and development space launches and missile defense target missions, with operationally responsive spacelift for Low-Earth-Orbit Space Situational Awareness assets as a future mission. This new mission created new challenges for LTS. The LTS mission tenets of developing space launches and missile defense target vehicles were an evolution from the squadrons previous mission of providing sounding rockets under the Rocket Sounding Launch Program (RSLP). The new mission tenets include shortened operational response periods criteria for the warfighter, while reducing the life-cycle development, production and launch costs of space launch systems. This presentation will focus on the technical challenges in transforming and integrating space launch vehicles and space craft vehicles for small space launch missions.

The Pioneer Missions

NASA Technical Reports Server (NTRS)

Lasher, Larry E.; Hogan, Robert (Technical Monitor)

1999-01-01

This article describes the major achievements of the Pioneer Missions and gives information about mission objectives, spacecraft, and launches of the Pioneers. Pioneer was the United States' longest running space program. The Pioneer Missions began forty years ago. Pioneer 1 was launched shortly after Sputnik startled the world in 1957 as Earth's first artificial satellite at the start of the space age. The Pioneer Missions can be broken down into four distinct groups: Pioneer (PN's) 1 through 5, which comprise the first group - the "First Pioneers" - were launched from 1958 through 1960. These Pioneers made the first thrusts into space toward the Moon and into interplanetary orbit. The next group - the "Interplanetary Pioneers" - consists of PN's 6 through 9, with the initial launch being in 1965 (through 1968); this group explored inward and outward from Earth's orbit and travel in a heliocentric orbit around the Sun just as the Earth. The Pioneer group consisting of 10 and 11 - the "Outer Solar System Pioneers" - blazed a trail through the asteroid belt and was the first to explore Jupiter, Saturn and the outer Solar System and is seeking the borders of the heliosphere and will ultimately journey to the distant stars. The final group of Pioneer 12 and 13 the "Planetary Pioneers" - traveled to Earth's mysterious twin, Venus, to study this planet.

KSC00pp0540

NASA Image and Video Library

2000-04-21

The GOES-L satellite arrives on pad 36A, Cape Canaveral Air Force Station. The Atlas IIA rocket is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC-00pp0540

NASA Image and Video Library

2000-04-21

The GOES-L satellite arrives on pad 36A, Cape Canaveral Air Force Station. The Atlas IIA rocket is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

NPP After Launch: Characterizing ATMS Performance

NASA Technical Reports Server (NTRS)

Lambrigtsen, Bjorn

2011-01-01

The NPOESS Preparatory Project (NPP) mission is scheduled to launch in the fall of 2011. Although several teams from the government and the instrument contractor will be assessing and characterizing the performance of the Advanced Technology Microwave Sounder (ATMS) and the Cross-track Infrared Sounder (CrIS) sounding suite, the NASA NPP Science Team will be paying particular attention to the aspects of these sensors that affect their utility for atmospheric and climate research. In this talk we discuss relevant aspects of ATMS and our post launch analysis approach.

Boby-Vortex Interaction, Sound Generation and Destructive Interference

NASA Technical Reports Server (NTRS)

Kao, Hsiao C.

2000-01-01

It is generally recognized that interaction of vortices with downstream blades is a major source of noise production. To analyze this problem numerically, a two-dimensional model of inviscid flow together with the method of matched asymptotic expansions is proposed. The method of matched asymptotic expansions is used to match the inner region of incompressible flow to the outer region of compressible flow. Because of incompressibility, relatively simple numerical methods are available to treat multiple vortices and multiple bodies of arbitrary shape. Disturbances from vortices and bodies propagate outward as sound waves. Due to their interactions, either constructive or destructive interference may result. When it is destructive, the combined sound intensity can be reduced, sometimes substantially. In addition, an analytical solution to sound generation by the cascade-vonex interaction is given.

JPL-20140817-LDSDf-0001-Flying Saucer Test Flight

NASA Image and Video Library

2014-08-17

Ian Clark, Low Density Supersonic Decelerator (LDSD) Principal Investigator, narrates balloon launch, rocket firing and parachute testing on June 28, 2014. The LDSD is a concept for slowing a spacecraft entering Mars' atmosphere at supersonic speeds. For this test, the goal was to slow the test vehicle from four times the speed of sound to 2.5 times the speed of sound.

KSC-07pd1291

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- NASA, Kennedy Space Center and State of Florida dignitaries helped launch the opening of the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. Breaking the ribbon are (left to right) Dan LeBlanc, chief operating officer of the KSC Visitor Complex; Lt. Governor of Florida Jeff Kottkamp; former astronauts John Young and Bob Crippen; Center Director Bill Parsons; KSC Director of External Relations Lisa Malone; and former astronaut Buzz Aldrin. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

Magnetorotational instability in decretion disks of critically rotating stars and the outer structure of Be and Be/X-ray disks

NASA Astrophysics Data System (ADS)

Krtička, J.; Kurfürst, P.; Krtičková, I.

2015-01-01

Context. Evolutionary models of fast-rotating stars show that the stellar rotational velocity may approach the critical speed. Critically rotating stars cannot spin up more, therefore they lose their excess angular momentum through an equatorial outflowing disk. The radial extension of such disks is unknown, partly because we lack information about the radial variations of the viscosity. Aims: We study the magnetorotational instability, which is considered to be the origin of anomalous viscosity in outflowing disks. Methods: We used analytic calculations to study the stability of outflowing disks submerged in the magnetic field. Results: The magnetorotational instability develops close to the star if the plasma parameter is large enough. At large radii the instability disappears in the region where the disk orbital velocity is roughly equal to the sound speed. Conclusions: The magnetorotational instability is a plausible source of anomalous viscosity in outflowing disks. This is also true in the region where the disk radial velocity approaches the sound speed. The disk sonic radius can therefore be roughly considered as an effective outer disk radius, although disk material may escape from the star to the insterstellar medium. The radial profile of the angular momentum-loss rate already flattens there, consequently, the disk mass-loss rate can be calculated with the sonic radius as the effective disk outer radius. We discuss a possible observation determination of the outer disk radius by using Be and Be/X-ray binaries.

KSC-04PD-1063

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04PD-1077

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- A crimson and gold sunrise over the Central Florida coast begins illuminating Launch Pad 39A, where a water sound suppression test is to take place. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiters three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04PD-1064

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04PD-1075

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Water recedes from the Mobile Launcher Platform (MLP) on Launch Pad 39A after the water sound suppression test. Workers and the media (left) were on hand to witness the rare event. This test was conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04PD-1062

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1063

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1065

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1075

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- Water recedes from the Mobile Launcher Platform (MLP) on Launch Pad 39A after the water sound suppression test. Workers and the media (left) were on hand to witness the rare event. This test was conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1064

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1077

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- A crimson and gold sunrise over the Central Florida coast begins illuminating Launch Pad 39A, where a water sound suppression test is to take place. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter’s three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1062

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

30 CFR 250.298 - How long will MMS take to evaluate and make a decision on the CID?

Code of Federal Regulations, 2010 CFR

2010-07-01

... THE INTERIOR OFFSHORE OIL AND GAS AND SULPHUR OPERATIONS IN THE OUTER CONTINENTAL SHELF Plans and... CID request based on your commitment to develop economically producible reservoirs according to sound...

NASA Successfully Conducts Wallops Rocket Launch with Technology Experiments

NASA Image and Video Library

2015-07-07

NASA successfully launched a NASA Black Brant IX suborbital sounding rocket carrying two space technology demonstration projects at 6:15 a.m. today. The rocket carried the SOAREX-8 Exo-Brake Flight Test from NASA’s Ames Research Center in California and the Radial Core Heat Spreader from NASA’s Glenn Research Center in Ohio. Preliminary analysis shows that data was received on both projects. The payload flew to an altitude of 206 miles and impacted in the Atlantic Ocean approximately 10 minutes after launch. The payload will not be recovered. The flight was conducted through NASA’s Space Technology Mission Directorate. The next launch from NASA’s Wallops Flight Facility is a Terrier-Improved Malemute suborbital sounding rocket early in the morning on August 11 carrying the RockSat-X university student payload. For more information on NASA’s Wallops Flight Facility, visit: www.nasa.gov/wallops NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

KSC-04pd1066

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. Because of the unusual event, media and workers watch from nearby vantage points on the Fixed Service Structure (left). This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released for launch just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

Recent sounding rocket highlights and a concept for melding sounding rocket and space shuttle activities

NASA Technical Reports Server (NTRS)

Lane, J. H.; Mayo, E. E.

1980-01-01

Highlights include launching guided vehicles into the African Solar Eclipse, initiation of development of a Three-Stage Black Brant to explore the dayside polar cusp, large payload Aries Flights at White Sands Missile Range, and an active program with the Orion vehicle family using surplus motors. Sounding rocket philosophy and experience is being applied to the shuttle in a Get Away Special and Experiments of Opportunity Payloads Programs. In addition, an orbit selection and targeting software system to support shuttle pallet mounted experiments is under development.

Safety Practices Followed in ISRO Launch Complex- An Overview

NASA Astrophysics Data System (ADS)

Krishnamurty, V.; Srivastava, V. K.; Ramesh, M.

2005-12-01

The spaceport of India, Satish Dhawan Space Centre (SDSC) SHAR of Indian Space Research Organisation (ISRO), is located at Sriharikota, a spindle shaped island on the east coast of southern India.SDSC SHAR has a unique combination of facilities, such as a solid propellant production plant, a rocket motor static test facility, launch complexes for different types of rockets, telemetry, telecommand, tracking, data acquisition and processing facilities and other support services.The Solid Propellant Space Booster Plant (SPROB) located at SDSC SHAR produces composite solid propellant for rocket motors of ISRO. The main ingredients of the propellant produced here are ammonium perchlorate (oxidizer), fine aluminium powder (fuel) and hydroxyl terminated polybutadiene (binder).SDSC SHAR has facilities for testing solid rocket motors, both at ambient conditions and at simulated high altitude conditions. Other test facilities for the environmental testing of rocket motors and their subsystems include Vibration, Shock, Constant Acceleration and Thermal / Humidity.SDSC SHAR has the necessary infrastructure for launching satellites into low earth orbit, polar orbit and geo-stationary transfer orbit. The launch complexes provide complete support for vehicle assembly, fuelling with both earth storable and cryogenic propellants, checkout and launch operations. Apart from these, it has facilities for launching sounding rockets for studying the Earth's upper atmosphere and for controlled reentry and recovery of ISRO's space capsule reentry missions.Safety plays a major role at SDSC SHAR right from the mission / facility design phase to post launch operations. This paper presents briefly the infrastructure available at SDSC SHAR of ISRO for launching sounding rockets, satellite launch vehicles, controlled reentry missions and the built in safety systems. The range safety methodology followed as a part of the real time mission monitoring is presented. The built in safety systems provided onboard the launch vehicle are automatic shut off the propulsion system based on real time mission performance and a passivation system incorporated in the orbit insertion stage are highlighted.

Registration of Space Objects

NASA Astrophysics Data System (ADS)

Schmidt-Tedd, Bernhard

2017-07-01

Space objects are subject to registration in order to allocate "jurisdiction and control" over those objects in the sovereign-free environment of outer space. This approach is similar to the registration of ships in view of the high sea and for aircrafts with respect to the international airspace. Registration is one of the basic principles of space law, starting with UN General Assembly Resolution 1721 B (XVI) of December 20, 1961, followed by Resolution 1962 (XVIII) of December 13, 1963, then formulated in Article VIII of the Outer Space Treaty of 1967 and as specified in the Registration Convention of 1975. Registration of space objects can be seen today as a principle of customary international law, relevant for each spacefaring state. Registration is divided into a national and an international level. The State Party establishes a national registry for its space objects, and those registrations have to be communicated via diplomatic channel to the UN Register of space objects. This UN Register is handled by the UN Office for Outer Space Affairs (UNOOSA) and is an open source of information for space objects worldwide. Registration is linked to the so-called launching state of the relevant space object. There might be more than one launching state for the specific launch event, but only one state actor can register a specific space object. The state of registry gains "jurisdiction and control" over the space object and therefore no double registration is permissible. Based on the established UN Space Law, registration practice was subject to some adaptions due to technical developments and legal challenges. After the privatization of the major international satellite organizations, a number of non-registrations had to be faced. The state actors reacted with the UN Registration Practice Resolution of 2007 as elaborated in the Legal Subcommittee of UNCOPUOS, the Committee for the Peaceful Use of Outer Space. In this context an UNOOSA Registration Information Submission Form had been developed. Today the complexity of launch activities and the concepts of mega-constellations lead to new challenges to the registration system. The Registration Practice Resolution already recommends that in cases of joint launches, each space object should be registered separately. Registration of space objects is a legal instrument in the context of state responsibility; it is not an instrument of traffic management. The orbit information of the registration system is indicative for identification purposes but not real-time positioning information. Such traffic management information follows different rules.

DOE Office of Scientific and Technical Information (OSTI.GOV)

M. P. Jensen; Toto, T.

Standard Atmospheric Radiation Measurement (ARM) Climate Research Facility sounding files provide atmospheric state data in one dimension of increasing time and height per sonde launch. Many applications require a quick estimate of the atmospheric state at higher time resolution. The INTERPOLATEDSONDE (i.e., Interpolated Sounding) Value-Added Product (VAP) transforms sounding data into continuous daily files on a fixed time-height grid, at 1-minute time resolution, on 332 levels, from the surface up to a limit of approximately 40 km. The grid extends that high so the full height of soundings can be captured; however, most soundings terminate at an altitude between 25more » and 30 km, above which no data is provided. Between soundings, the VAP linearly interpolates atmospheric state variables in time for each height level. In addition, INTERPOLATEDSONDE provides relative humidity scaled to microwave radiometer (MWR) observations.« less

Maximizing the science return of interplanetary missions using nuclear electric power

NASA Astrophysics Data System (ADS)

Zubrin, Robert M.

1995-01-01

In the past, most studies dealing with the benefits of space nuclear electric power systems for solar system exploration have focused on the potential of nuclear electric propulsion (NEP) to enhance missions by increasing delivered payload, decreasing LEO mass, or reducing trip time. While important, such mission enhancements have failed to go to the heart of the concerns of the scientific community supporting interplanetary exploration. To put the matter succintly, scientists don't buy delivered payload—they buy data returned. With nuclear power we can increase both the quantity of data returned, by enormously increasing data communication rates, and the quality of data by enabling a host of active sensing techniques otherwise impossible. These non-propulsive mission enhancement capabilities of space nuclear power have been known in principle for many years, but they have not been adequately documented. As a result, support for the development of space nuclear power by the interplanetary exploration community has been much less forceful than it might otherwise be. In this paper we shall present mission designs that take full advantage of the potential mission enhancements offered by space nuclear power systems in the 15 to 30 kWe range, not just for propulsion, but to radically improve, enrich, and expand the science return itself. Missions considered include orbiter missions to each of the outer planets. It will be shown that by using hybrid trajectories combining chemical propulsion with NEP and (in certain cases) gravity assists, that it is possible, using Proton, Tatan III or Titan IV-Centaur launch vehicles, for high-powered spacecraft to be placed in orbit around each of the outer planets with electric propulsion burn times of less than 4 years. Such hybrid trajectories therefore make the outer solar-system available to near-term nuclear electric power systems. Once in orbit, the spacecraft will utilize multi-kilowatt communication systems, similar to those now employed by the U.S. military, to increse data return far beyond that possible utilizing the 40 W rf traveling wave tube antennas that are the current NASA stadard. This higher data rate will make possible very high resolution multi-space imaging (with high resolutions both spatially and spectrally), a form of science hitherto impossible in the outer solar system. Larger numbers of such images could be returned, allowing the creation of motion pictures of atmospheric phenomenon on a small scale and greatly increasing the probability of capturing transient phenomena such as lighting or volcanic activity. The multi-kilowatt power sources on the spaecraft also enables active sensing, including radar, which could be used to do topographic and subsurface studies of clouded bodies such as Titan, ground pentrating sounding of Pluto, the major planet's moons, and planetoids, and topside sounding of the electrically conductive atmospheres of Jupiter, Saturn, Uranus and Neptune to produce profiles of fluid density, conductivity, and horizontal and vertical velocity as a function of depth and global location. Radio science investigations of planetary atmospheres and ring systems would be greatly enhanced by increased transmitter power. The scientific benefits of utilizing such techniques are discussed, and a comparison is made with the quantity and quality of science that a low-powered spacecraft employing RTGs could return. It is concluded that the non-propulsive benefits of nuclear power for spacecraft exploring the outer solar system are enormous, and taken together with the well documented mission enhancements enabled by electric propulsion fully justify the expanditures needed to bring a space qualified nuclear electric power source into being.

Improved Determination of Surface and Atmospheric Temperatures Using Only Shortwave AIRS Channels: The AIRS Version 6 Retrieval Algorithm

NASA Technical Reports Server (NTRS)

Susskind, Joel; Blaisdell, John; Iredell, Lena

2010-01-01

AIRS was launched on EOS Aqua on May 4, 2002 together with ASMU-A and HSB to form a next generation polar orbiting infrared and microwave atmosphere sounding system (Pagano et al 2003). The theoretical approach used to analyze AIRS/AMSU/HSB data in the presence of clouds in the AIRS Science Team Version 3 at-launch algorithm, and that used in the Version 4 post-launch algorithm, have been published previously. Significant theoretical and practical improvements have been made in the analysis of AIRS/AMSU data since the Version 4 algorithm. Most of these have already been incorporated in the AIRS Science Team Version 5 algorithm (Susskind et al 2010), now being used operationally at the Goddard DISC. The AIRS Version 5 retrieval algorithm contains three significant improvements over Version 4. Improved physics in Version 5 allowed for use of AIRS clear column radiances (R(sub i)) in the entire 4.3 micron CO2 absorption band in the retrieval of temperature profiles T(p) during both day and night. Tropospheric sounding 15 micron CO2 observations were used primarily in the generation of clear column radiances (R(sub i)) for all channels. This new approach allowed for the generation of accurate Quality Controlled values of R(sub i) and T(p) under more stressing cloud conditions. Secondly, Version 5 contained a new methodology to provide accurate case-by-case error estimates for retrieved geophysical parameters and for channel-by-channel clear column radiances. Thresholds of these error estimates are used in a new approach for Quality Control. Finally, Version 5 contained for the first time an approach to provide AIRS soundings in partially cloudy conditions that does not require use of any microwave data. This new AIRS Only sounding methodology was developed as a backup to AIRS Version 5 should the AMSU-A instrument fail. Susskind et al 2010 shows that Version 5 AIRS Only sounding are only slightly degraded from the AIRS/AMSU soundings, even at large fractional cloud cover.

KSC-00pp0412

NASA Image and Video Library

2000-03-27

Workers at Cape Canaveral Air Force Station prepare to erect the first stage of an Atlas II/Centaur rocket in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0417

NASA Image and Video Library

2000-03-27

The first stage of an Atlas II/Centaur rocket stands erect in the launch gantry on pad 36A, Cape Canaveral Air Force Station. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0416

NASA Image and Video Library

2000-03-27

At Cape Canaveral Air Force Station, the first stage of an Atlas II/Centaur rocket is nearing erection in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0415

NASA Image and Video Library

2000-03-27

At Cape Canaveral Air Force Station, the first stage of an Atlas II/Centaur rocket is slowly raised in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0417

NASA Image and Video Library

2000-03-27

The first stage of an Atlas II/Centaur rocket stands erect in the launch gantry on pad 36A, Cape Canaveral Air Force Station. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0541

NASA Image and Video Library

2000-04-21

The GOES-L satellite is lifted up the gantry on pad 36A, Cape Canaveral Air Force Station. the Atlas IIA is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC-00pp0416

NASA Image and Video Library

2000-03-27

At Cape Canaveral Air Force Station, the first stage of an Atlas II/Centaur rocket is nearing erection in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0414

NASA Image and Video Library

2000-03-27

At Cape Canaveral Air Force Station, the first stage of an Atlas II/Centaur rocket begins erection in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0412

NASA Image and Video Library

2000-03-27

Workers at Cape Canaveral Air Force Station prepare to erect the first stage of an Atlas II/Centaur rocket in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0541

NASA Image and Video Library

2000-04-21

The GOES-L satellite is lifted up the gantry on pad 36A, Cape Canaveral Air Force Station. the Atlas IIA is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC-00pp0543

NASA Image and Video Library

2000-04-23

The GOES-L satellite is about midway in its journey up the gantry on pad 36A, Cape Canaveral Air Force Station. The Atlas IIA rocket is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC00pp0415

NASA Image and Video Library

2000-03-27

At Cape Canaveral Air Force Station, the first stage of an Atlas II/Centaur rocket is slowly raised in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0414

NASA Image and Video Library

2000-03-27

At Cape Canaveral Air Force Station, the first stage of an Atlas II/Centaur rocket begins erection in the launch gantry on pad 36A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0543

NASA Image and Video Library

2000-04-23

The GOES-L satellite is about midway in its journey up the gantry on pad 36A, Cape Canaveral Air Force Station. The Atlas IIA rocket is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

Low-frequency sound affects active micromechanics in the human inner ear

PubMed Central

Kugler, Kathrin; Wiegrebe, Lutz; Grothe, Benedikt; Kössl, Manfred; Gürkov, Robert; Krause, Eike; Drexl, Markus

2014-01-01

Noise-induced hearing loss is one of the most common auditory pathologies, resulting from overstimulation of the human cochlea, an exquisitely sensitive micromechanical device. At very low frequencies (less than 250 Hz), however, the sensitivity of human hearing, and therefore the perceived loudness is poor. The perceived loudness is mediated by the inner hair cells of the cochlea which are driven very inadequately at low frequencies. To assess the impact of low-frequency (LF) sound, we exploited a by-product of the active amplification of sound outer hair cells (OHCs) perform, so-called spontaneous otoacoustic emissions. These are faint sounds produced by the inner ear that can be used to detect changes of cochlear physiology. We show that a short exposure to perceptually unobtrusive, LF sounds significantly affects OHCs: a 90 s, 80 dB(A) LF sound induced slow, concordant and positively correlated frequency and level oscillations of spontaneous otoacoustic emissions that lasted for about 2 min after LF sound offset. LF sounds, contrary to their unobtrusive perception, strongly stimulate the human cochlea and affect amplification processes in the most sensitive and important frequency range of human hearing. PMID:26064536

KSC-2009-2539

NASA Image and Video Library

2009-04-06

CAPE CANAVERAL, Fla. – Water cascades over the side of the mobile launcher platform on Launch Pad 39B at NASA's Kennedy Space Center in Florida. The sound suppression system is being tested on the platform. Pad 39B will be the site of the first Ares vehicle launch, including the Ares I-X flight test that is targeted for summer 2009. The mobile launcher platform was handed over to the Constellation Program and modified for the Ares I-X flight test. It is being tested before being moved to the Vehicle Assembly Building for assembly of the Ares I-X rocket. A sound suppression water system is in¬stalled on the pads to protect against damage by acoustical energy and rocket exhaust reflected from the flame trench and mobile launcher plat¬form during a launch. The sound suppression system includes an elevated 290-foot-high water tank with a capacity of 300,000 gallons. The water releases just prior to the ignition of the rocket and flows through 7-foot-diameter pipes for about 20 seconds. A torrent of water will flow onto the mobile launcher platform from six large quench nozzles, or “rainbirds,” mounted on its surface. The rainbirds are 12 feet high. The two in the center are 42 inches in diameter; the other four have a 30-inch diameter. Photo credit: NASA/Dimitri Gerondidakis

Water Flow Test at Launch Complex 39B

NASA Image and Video Library

2017-12-20

Water flowed during a test at Launch Complex 39B at NASA’s Kennedy Space Center in Florida. About 450,000 gallons of water flowed at high speed from a holding tank through new and modified piping and valves, the flame trench, flame deflector nozzles and mobile launcher interface risers during a wet flow test at Launch Complex 39B. At peak flow, the water reached about 100 feet in the air above the pad surface. The test was a milestone to confirm and baseline the performance of the Ignition Overpressure/Sound Suppression system. During launch of NASA's Space Launch System rocket and Orion spacecraft, the high-speed water flow will help protect the vehicle from the extreme acoustic and temperature environment during ignition and liftoff.

KSC-07pd1290

NASA Image and Video Library

2007-05-25

KENNEDY SPACE CENTER, FLA. -- NASA, Kennedy Space Center and State of Florida dignitaries helped launch the opening of the newest attraction at Kennedy Space Center's Visitor Complex, the Shuttle Launch Experience. Holding the ribbon for the breaking are (left to right) Dan LeBlanc, chief operating officer of the KSC Visitor Complex; Lt. Governor of Florida Jeff Kottkamp; former astronauts John Young and Bob Crippen; Center Director Bill Parsons; KSC Director of External Relations Lisa Malone; and former astronaut Buzz Aldrin. The attraction includes a simulated launch with the sights, sounds and sensations of launching into space. Find out more about the Visitor Complex and the Shuttle Launch Experience at http://www.kennedyspacecenter.com/visitKSC/attractions/index.asp. Photo credit: NASA/George Shelton

DARTFire Sees Microgravity Fires in a New Light--Large Data Base of Images Obtained

NASA Technical Reports Server (NTRS)

Olson, Sandra L.; Hegde, Uday; Altenkirch, Robert A.; Bhatacharjee, Subrata

1999-01-01

The recently completed DARTFire sounding rocket microgravity combustion experiment launched a new era in the imaging of flames in microgravity. DARTFire stands for "Diffusive and Radiative Transport in Fires," which perfectly describes the two primary variables--diffusive flow and radiation effects--that were studied in the four launches of this program (June 1996 to September 1997). During each launch, two experiments, which were conducted simultaneously during the 6 min of microgravity, obtained results as the rocket briefly exited the Earth s atmosphere.

75 FR 80773 - Takes of Marine Mammals Incidental to Specified Activities; Taking Marine Mammals Incidental to...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-12-23

... Delta II, which is being withdrawn from service. The U.S. Air Force reports that sound pressures of the Delta II were slightly less than those from the Taurus I (Castor 120) as measured from the same point... conducted after one Delta IV launch in 2006. During this launch the digital audio tape (DAT) recorder was...

Feasibility of a low-cost sounding rockoon platform

NASA Astrophysics Data System (ADS)

Okninski, Adam; Raurell, Daniel Sors; Mitre, Alberto Rodriguez

2016-10-01

This paper presents the results of analyses and simulations for the design of a small sounding platform, dedicated to conducting scientific atmospheric research and capable of reaching the von Kármán line by means of a rocket launched from it. While recent private initiatives have opted for the air launch concept to send small payloads to Low Earth Orbit, several historical projects considered the use of balloons as the first stage of orbital and suborbital platforms, known as rockoons. Both of these approaches enable the minimization of drag losses. This paper addresses the issue of utilizing stratospheric balloons as launch platforms to conduct sub-orbital rocket flights. Research and simulations have been conducted to demonstrate these capabilities and feasibility. A small sounding solid propulsion rocket using commercially-off-the-shelf hardware is proposed. Its configuration and design are analyzed with special attention given to the propulsion system and its possible mission-orientated optimization. The cost effectiveness of this approach is discussed. Performance calculation outcomes are shown. Additionally, sensitivity study results for different design parameters are given. Minimum mass rocket configurations for various payload requirements are presented. The ultimate aim is to enhance low-cost experimentation maintaining high mobility of the system and simplicity of operations. An easier and more affordable access to a space-like environment can be achieved with this system, thus allowing for widespread outreach of space science and technology knowledge. This project is based on earlier experience of the authors in LEEM Association of the Technical University of Madrid and the Polish Small Sounding Rocket Program developed at the Institute of Aviation and Warsaw University of Technology in Poland.

Sound velocity of Fe-S liquids at high pressure: Implications for the Moon's molten outer core

DOE Office of Scientific and Technical Information (OSTI.GOV)

Jing, Zhicheng; Wang, Yanbin; Kono, Yoshio

2014-07-21

Sound velocities of Fe and Fe–S liquids were determined by combining the ultrasonic measurements and synchrotron X-ray techniques under high pressure–temperature conditions from 1 to 8 GPa and 1573 K to 1973 K. Four different liquid compositions were studied including Fe, Fe–10 wt% S, Fe–20 wt% S, and Fe–27 wt% S. Our data show that the velocity of Fe-rich liquids increases upon compression and decreases with increasing sulfur content, whereas temperature has negligible effect on the velocity of Fe–S liquids. The sound velocity data were combined with ambient-pressure densities to fit the Murnaghan equation of state (EOS). Compared to themore » lunar seismic model, our velocity data constrain the sulfur content at 4±3 wt%, indicating a significantly denser (6.5±0.5 g/cm 3) and hotter (1870-70+100 K) outer core than previously estimated. A new lunar structure model incorporating available geophysical observations points to a smaller core radius. Our model suggests a top–down solidification scenario for the evolution of the lunar core. Such “iron snow” process may have been an important mechanism for the growth of the inner core.« less

CANSAT: Design of a Small Autonomous Sounding Rocket Payload

NASA Technical Reports Server (NTRS)

Berman, Joshua; Duda, Michael; Garnand-Royo, Jeff; Jones, Alexa; Pickering, Todd; Tutko, Samuel

2009-01-01

CanSat is an international student design-build-launch competition organized by the American Astronautical Society (AAS) and American Institute of Aeronautics and Astronautics (AIAA). The competition is also sponsored by the Naval Research Laboratory (NRL), the National Aeronautics and Space Administration (NASA), AGI, Orbital Sciences Corporation, Praxis Incorporated, and SolidWorks. Specifically, the 2009 Virginia Tech CanSat Team is funded by BAE Systems, Incorporated of Manassas, Virginia. The objective of the 2009 CanSat competition is to complete remote sensing missions by designing a small autonomous sounding rocket payload. The payload designed will follow and perform to a specific set of mission requirements for the 2009 competition. The competition encompasses a complete life-cycle of one year which includes all phases of design, integration, testing, reviews, and launch.

Infrared Imagery of Solid Rocket Exhaust Plumes

NASA Technical Reports Server (NTRS)

Moran, Robert P.; Houston, Janice D.

2011-01-01

The Ares I Scale Model Acoustic Test program consisted of a series of 18 solid rocket motor static firings, simulating the liftoff conditions of the Ares I five-segment Reusable Solid Rocket Motor Vehicle. Primary test objectives included acquiring acoustic and pressure data which will be used to validate analytical models for the prediction of Ares 1 liftoff acoustics and ignition overpressure environments. The test article consisted of a 5% scale Ares I vehicle and launch tower mounted on the Mobile Launch Pad. The testing also incorporated several Water Sound Suppression Systems. Infrared imagery was employed during the solid rocket testing to support the validation or improvement of analytical models, and identify corollaries between rocket plume size or shape and the accompanying measured level of noise suppression obtained by water sound suppression systems.

A Real Time Differential GPS Tracking System for NASA Sounding Rockets

NASA Technical Reports Server (NTRS)

Bull, Barton; Bauer, Frank (Technical Monitor)

2000-01-01

Sounding rockets are suborbital launch vehicles capable of carrying scientific payloads to several hundred miles in altitude. These missions return a variety of scientific data including: chemical makeup and physical processes taking place in the atmosphere, natural radiation surrounding the Earth, data on the Sun, stars, galaxies and many other phenomena. In addition, sounding rockets provide a reasonably economical means of conducting engineering tests for instruments and devices to be used on satellites and other spacecraft prior to their use in these more expensive missions. Typically around thirty of these rockets are launched each year, from established ranges at Wallops Island, Virginia; Poker Flat Research Range, Alaska; White Sands Missile Range, New Mexico and from a number of ranges outside the United States. Many times launches are conducted from temporary launch ranges in remote parts of the world requiring considerable expense to transport and operate tracking radars. In order to support these missions, an inverse differential GPS system has been developed. The flight system consists of a small, inexpensive receiver, a preamplifier and a wrap-around antenna. A rugged, compact, portable ground station extracts GPS data from the raw payload telemetry stream, performs a real time differential solution and graphically displays the rocket's path relative to a predicted trajectory plot. In addition to generating a real time navigation solution, the system has been used for payload recovery, timing, data timetagging, precise tracking of multiple payloads and slaving of optical tracking systems for over the horizon acquisition. This paper discusses, in detail, the flight and ground hardware, as well as data processing and operational aspects of the system, and provides evidence of the system accuracy.

NASA EVEX Experiment Launches from the Marshall Islands

NASA Image and Video Library

2017-12-08

Red and white vapor clouds filled the skies over the Marshall Islands as part of NASA’s Equatorial Vortex Experiment (EVEX). The red cloud was formed by the release of lithium vapor and the white tracer clouds were formed by the release of trimethyl aluminum (TMA). These clouds allowed scientists on the ground from various locations in the Marshall Islands to observe the neutral winds in the ionosphere. Credit: NASA/Jon Grant --- The Equatorial Vortex Experiment (EVEX) was successfully conducted during the early morning hours (eastern time) May 7 from Roi Namur, Republic of the Marshall Islands. A NASA Terrier-Oriole sounding rocket was launched at 3:39 a.m. EDT and was followed by a launch of Terrier-Improved Malemute sounding rocket 90 seconds later. Preliminary indications are that both rockets released their vapor clouds of lithium or trimethyl aluminum, which were observed from various locations in the area, and all science instruments on the rockets worked as planned. More information on EVEX can be found at www.nasa.gov/mission_pages/sounding-rockets/news/evex.html These were the second and third rockets of four planned for launch during this year’s campaign in the Marshall Islands. The first and fourth rockets are supporting the Metal Oxide Space Cloud experiment (MOSC), which is studying radio frequency propagation. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Safe and Sound: An Educational Leader's Guide to Evidence-Based Social and Emotional Learning (SEL) Programs. Illinois Edition

ERIC Educational Resources Information Center

Collaborative for Academic, Social, and Emotional Learning (NJ1), 2005

2005-01-01

Based on a three-year study funded by the Office of Safe and Drug-Free Schools (OSDFS) in the U.S. Department of Education, "Safe and Sound" is a comprehensive and inclusive guide for social and emotional learning (SEL) programming. The guide provides a road map for schools and districts that are launching or adding social, emotional,…

33 CFR 334.770 - Gulf of Mexico and St. Andrew Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor...

Code of Federal Regulations, 2010 CFR

2010-07-01

... 33 Navigation and Navigable Waters 3 2010-07-01 2010-07-01 false Gulf of Mexico and St. Andrew... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.770 Gulf of Mexico and St....; restricted area. (a) The area. The waters of the Gulf of Mexico and St. Andrew Sound within an area described...

33 CFR 334.770 - Gulf of Mexico and St. Andrew Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor...

Code of Federal Regulations, 2014 CFR

2014-07-01

... 33 Navigation and Navigable Waters 3 2014-07-01 2014-07-01 false Gulf of Mexico and St. Andrew... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.770 Gulf of Mexico and St....; restricted area. (a) The area. The waters of the Gulf of Mexico and St. Andrew Sound within an area described...

33 CFR 334.770 - Gulf of Mexico and St. Andrew Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor...

Code of Federal Regulations, 2013 CFR

2013-07-01

... 33 Navigation and Navigable Waters 3 2013-07-01 2013-07-01 false Gulf of Mexico and St. Andrew... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.770 Gulf of Mexico and St....; restricted area. (a) The area. The waters of the Gulf of Mexico and St. Andrew Sound within an area described...

33 CFR 334.770 - Gulf of Mexico and St. Andrew Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor...

Code of Federal Regulations, 2012 CFR

2012-07-01

... 33 Navigation and Navigable Waters 3 2012-07-01 2012-07-01 false Gulf of Mexico and St. Andrew... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.770 Gulf of Mexico and St....; restricted area. (a) The area. The waters of the Gulf of Mexico and St. Andrew Sound within an area described...

33 CFR 334.770 - Gulf of Mexico and St. Andrew Sound, south of East Bay, Fla., Tyndall Drone Launch Corridor...

Code of Federal Regulations, 2011 CFR

2011-07-01

... 33 Navigation and Navigable Waters 3 2011-07-01 2011-07-01 false Gulf of Mexico and St. Andrew... ARMY, DEPARTMENT OF DEFENSE DANGER ZONE AND RESTRICTED AREA REGULATIONS § 334.770 Gulf of Mexico and St....; restricted area. (a) The area. The waters of the Gulf of Mexico and St. Andrew Sound within an area described...

Acoustic property reconstruction of a neonate Yangtze finless porpoise's (Neophocaena asiaeorientalis) head based on CT imaging.

PubMed

Wei, Chong; Wang, Zhitao; Song, Zhongchang; Wang, Kexiong; Wang, Ding; Au, Whitlow W L; Zhang, Yu

2015-01-01

The reconstruction of the acoustic properties of a neonate finless porpoise's head was performed using X-ray computed tomography (CT). The head of the deceased neonate porpoise was also segmented across the body axis and cut into slices. The averaged sound velocity and density were measured, and the Hounsfield units (HU) of the corresponding slices were obtained from computed tomography scanning. A regression analysis was employed to show the linear relationships between the Hounsfield unit and both sound velocity and density of samples. Furthermore, the CT imaging data were used to compare the HU value, sound velocity, density and acoustic characteristic impedance of the main tissues in the porpoise's head. The results showed that the linear relationships between HU and both sound velocity and density were qualitatively consistent with previous studies on Indo-pacific humpback dolphins and Cuvier's beaked whales. However, there was no significant increase of the sound velocity and acoustic impedance from the inner core to the outer layer in this neonate finless porpoise's melon.

Bioburden release of Ariane 5 Fairing Acoustic Protection Panels

NASA Astrophysics Data System (ADS)

Stieglmeier, Michaela; Rohr, Thomas; Schmeitzky, Olivier; Rumler, Peter; Kminek, Gerhard

The ESA-NASA ExoMars mission will be subject to strict Planetary Protection constrictions. The original ExoMars mission concept was based on an Ariane 5 launch system. Like all launch systems, the Ariane 5 fairing is lined with acoustic protection panels. These panels consist of an outer polyester/cotton fabric and an inner open celled foam. During launch the panels will be exposed to vibrations and a decrease in pressure. A release of possible external and/ or embedded microbes would cause a contamination of the satellite. Planetary Protection requirements for ExoMars imply the determination of the bioburden release from the Ariane 5 Fairing Acoustic Protection Panels (FAP-panels). Thus a study at ESTEC was performed comparing the bioburden release of a sterilized and non-sterilized panel by simulating a launch environment. Panels were mounted in test jigs above a sterile ground plate. Sterile stainless steel witness plates for the determination of bioburden release were mounted on the latter. The launch environment was simulated in two different tests. In a vacuum chamber the panels were exposed to a depressurization event. For the simulation of the vibrations the jigs were mounted in the Large European Acoustic Facility (LEAF) at ESTEC. After each test witness plates were demounted under sterile conditions and analyzed for microbial growth by incubating them in agar. Furthermore pieces of the outer fabric as well as the inner foam were taken and examined for embedded microbes. In total the amount of embedded microbes was very low and there was no significant difference between the sterilized and non-sterilized panel concerning the released bioburden. Thus sterilization of the Ariane 5 FAP-panels seems not necessary to comply with Planetary Protection constraints. Although the ExoMars project will use a different launch system in the new mission concept, the data acquired during these tests can be used for future scientific satellites launched with Ariane 5.

Acoustics Research of Propulsion Systems

NASA Technical Reports Server (NTRS)

Gao, Ximing; Houston, Janice D.

2014-01-01

The liftoff phase induces some of the highest acoustic loading over a broad frequency for a launch vehicle. These external acoustic environments are used in the prediction of the internal vibration responses of the vehicle and components. Thus, predicting these liftoff acoustic environments is critical to the design requirements of any launch vehicle but there are challenges. Present liftoff vehicle acoustic environment prediction methods utilize stationary data from previously conducted hold-down tests; i.e. static firings conducted in the 1960's, to generate 1/3 octave band Sound Pressure Level (SPL) spectra. These data sets are used to predict the liftoff acoustic environments for launch vehicles. To facilitate the accuracy and quality of acoustic loading, predictions at liftoff for future launch vehicles such as the Space Launch System (SLS), non-stationary flight data from the Ares I-X were processed in PC-Signal in two forms which included a simulated hold-down phase and the entire launch phase. In conjunction, the Prediction of Acoustic Vehicle Environments (PAVE) program was developed in MATLAB to allow for efficient predictions of sound pressure levels (SPLs) as a function of station number along the vehicle using semiempirical methods. This consisted, initially, of generating the Dimensionless Spectrum Function (DSF) and Dimensionless Source Location (DSL) curves from the Ares I-X flight data. These are then used in the MATLAB program to generate the 1/3 octave band SPL spectra. Concluding results show major differences in SPLs between the hold-down test data and the processed Ares IX flight data making the Ares I-X flight data more practical for future vehicle acoustic environment predictions.

NASA launches student experiments from Wallops

NASA Image and Video Library

2015-08-12

NASA launched a Terrier-Improved Malemute suborbital sounding rocket carrying the RockSat-X payload with university and community college student experiments at 6:04 a.m. EDT Wednesday, Aug. 12, from NASA’s Wallops Flight Facilityin Virginia. More than 60 students and instructors from across the continental United States, Hawaii and Puerto Rico were on hand to witness the launch of their experiments. The payload flew to an altitude of about 97 miles and descended via parachute into the Atlantic Ocean off the coast of Wallops. Payload recovery operations began after lift-off. Developed by students from seven higher education programs, the experiments flew through the RockSat-X program in conjunction with the Colorado Space Grant Consortium. Participating institutions in this flight are the University of Colorado, Boulder; Northwest Nazarene University, Nampa, Idaho; the University of Puerto Rico; the University of Nebraska, Lincoln; Virginia Tech University, Blacksburg; Capitol Technology University, Laurel, Maryland; and University of Hawai'i Community Colleges at the Honolulu, Kapi'olani, Kaua'i, and Windward campuses. The next launch scheduled from Wallops is a NASA Black Brant IX suborbital sounding rocket carrying several technology development instruments. The launch is scheduled between 7 and 7:41 p.m. Sept. 29. The backup launch days are Sept. 30 through Oct. 12. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Compendium of meteorological data for the Titan 3C (AF-777) launch in May 1975

NASA Technical Reports Server (NTRS)

Stephens, J. B.; Adelfang, S. I.; Goldford, A. I.

1976-01-01

Meteorological data for the 26-hour period prior to launch are recorded. Data were collected in support of the NASA rocket exhaust effluent prediction and monitoring program. Soundings were made approximately every 2 hours from T-14 hours to T-O; therefore, high temporal resolution is provided. All supporting data, such as synoptic charts and wind tower data, are also included.

KSC-2009-1623

NASA Image and Video Library

2009-02-06

VANDENBERG AIR FORCE BASE, Calif. -- The United Launch Alliance Delta II rocket carrying NASA's NOAA-N Prime satellite lifts off Space Launch Complex 2 at Vandenberg Air Force Base in California at 2:22 a.m. PST Feb. 6, 2009. The countdown and launch were managed by Kennedy Space Center’s Launch Services Program. Built for NASA by Lockheed Martin, the satellite will improve weather forecasting and monitor the world for environmental events, as well as for distress signals for the Search and Rescue Satellite-Aided Tracking System. NOAA-N Prime is the fifth and last in the National Oceanic and Atmospheric Administration’s current series of five polar-orbiting satellites with improved imaging and sounding capabilities. Photo credit: NASA/Carleton Bailie, VAFB-ULA

KSC-00pp0413

NASA Image and Video Library

2000-03-27

Workers at Cape Canaveral Air Force Station prepare to erect the first stage of an Atlas II/Centaur rocket in the launch gantry on pad 36A. Shown are the rocket thrusters. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0426

NASA Image and Video Library

2000-03-29

At launch pad 36-A, Cape Canaveral Air Force Station, cables help guide the second stage of an Atlas II/Centaur rocket as it is lifted up the gantry (behind it) for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0424

NASA Image and Video Library

2000-03-29

At launch pad 36-A, Cape Canaveral Air Force Station, workers check over the second stage of an Atlas II/Centaur rocket before it is lifted up the gantry (behind it) for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0413

NASA Image and Video Library

2000-03-27

Workers at Cape Canaveral Air Force Station prepare to erect the first stage of an Atlas II/Centaur rocket in the launch gantry on pad 36A. Shown are the rocket thrusters. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the NASA/Lockheed Martin GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0544

NASA Image and Video Library

2000-04-23

The GOES-L satellite approaches the end of its journey up the gantry on pad 36A, Cape Canaveral Air Force Station, for mating with the Atlas IIA/Centaur rocket. The Atlas IIA is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC00pp0424

NASA Image and Video Library

2000-03-29

At launch pad 36-A, Cape Canaveral Air Force Station, workers check over the second stage of an Atlas II/Centaur rocket before it is lifted up the gantry (behind it) for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0542

NASA Image and Video Library

2000-04-21

The GOES-L satellite is ready for mating with the lower stages of the Atlas IIA rocket on pad 36A, Cape Canaveral Air Force Station. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC-00pp0425

NASA Image and Video Library

2000-03-29

At launch pad 36-A, Cape Canaveral Air Force Station, the second stage of an Atlas II/Centaur rocket is lifted up the gantry (behind it) for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0425

NASA Image and Video Library

2000-03-29

At launch pad 36-A, Cape Canaveral Air Force Station, the second stage of an Atlas II/Centaur rocket is lifted up the gantry (behind it) for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0544

NASA Image and Video Library

2000-04-23

The GOES-L satellite approaches the end of its journey up the gantry on pad 36A, Cape Canaveral Air Force Station, for mating with the Atlas IIA/Centaur rocket. The Atlas IIA is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC00pp0542

NASA Image and Video Library

2000-04-21

The GOES-L satellite is ready for mating with the lower stages of the Atlas IIA rocket on pad 36A, Cape Canaveral Air Force Station. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

Wet Flow Test at Launch Complex 39B

NASA Image and Video Library

2017-12-20

About 450,000 gallons of water flowed at high speed from a holding tank through new and modified piping and valves, the flame trench, flame deflector nozzles and mobile launcher interface risers during a wet flow test at Launch Pad 39B at NASA's Kennedy Space Center in Florida. At peak flow, the water reached about 100 feet in the air above the pad surface. The test was a milestone to confirm and baseline the performance of the Ignition Overpressure/Sound Suppression system. During launch of NASA's Space Launch System rocket and Orion spacecraft, the high-speed water flow will help protect the vehicle from the extreme acoustic and temperature environment during ignition and liftoff.

NASA Successfully Launches Suborbital Rocket from Wallops with Student Experiments

NASA Image and Video Library

2015-06-25

NASA successfully launched a NASA Terrier-Improved Orion suborbital sounding rocket carrying student experiments with the RockOn/RockSat-C programs at 6 a.m., today More than 200 middle school and university students and instructors participating in Rocket Week at Wallops were on hand to witness the launch. Through RockOn and RockSat-C students are learning and applying skills required to develop experiments for suborbital rocket flight. In addition, middle school educators through the Wallops Rocket Academy for Teachers (WRATS) are learning about applying rocketry basics in their curriculum. The payload flew to an altitude of 71.4 miles and descended by parachute into the Atlantic Ocean off the coast of Wallops. Payload recovery is in progress. The next launch from NASA’s Wallops Flight Facility is a Black Brant IX suborbital sounding rocket currently scheduled between 6 and 10 a.m., July 7. For more information on NASA’s Wallops Flight Facility, visit: www.nasa.gov/wallops NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Student experimenters successfully launch suborbital rocket from NASA Wallops

NASA Image and Video Library

2015-06-25

NASA successfully launched a NASA Terrier-Improved Orion suborbital sounding rocket carrying student experiments with the RockOn/RockSat-C programs at 6 a.m., today. More than 200 middle school and university students and instructors participating in Rocket Week at Wallops were on hand to witness the launch. Through RockOn and RockSat-C students are learning and applying skills required to develop experiments for suborbital rocket flight. In addition, middle school educators through the Wallops Rocket Academy for Teachers (WRATS) are learning about applying rocketry basics in their curriculum. The payload flew to an altitude of 71.4 miles and descended by parachute into the Atlantic Ocean off the coast of Wallops. Payload recovery is in progress. The next launch from NASA’s Wallops Flight Facility is a Black Brant IX suborbital sounding rocket currently scheduled between 6 and 10 a.m., July 7. Credits: NASA Wallops Optics Lab NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Introduction to the Special Issue on Sounding Rockets and Instrumentation

NASA Astrophysics Data System (ADS)

Christe, Steven; Zeiger, Ben; Pfaff, Rob; Garcia, Michael

2016-03-01

Rocket technology, originally developed for military applications, has provided a low-cost observing platform to carry critical and rapid-response scientific investigations for over 70 years. Even with the development of launch vehicles that could put satellites into orbit, high altitude sounding rockets have remained relevant. In addition to science observations, sounding rockets provide a unique technology test platform and a valuable training ground for scientists and engineers. Most importantly, sounding rockets remain the only way to explore the tenuous regions of the Earth’s atmosphere (the upper stratosphere, mesosphere, and lower ionosphere/thermosphere) above balloon altitudes (˜40km) and below satellite orbits (˜160km). They can lift remote sensing telescope payloads with masses up to 400kg to altitudes of 350km providing observing times of up to 6min above the blocking influence of Earth’s atmosphere. Though a number of sounding rocket research programs exist around the world, this article focuses on the NASA Sounding Rocket Program, and particularly on the astrophysical and solar sounding rocket payloads.

Effect of flow on the acoustic performance of extended reaction lined ducts

NASA Technical Reports Server (NTRS)

Hersh, A. S.; Walker, B.

1983-01-01

A model is developed for the effects of uniform and boundary-layer mean flow on the attenuation and propagation of harmonically excited sound waves in an extended reaction lined cylindrical duct. A duct geometry consisting of an annular outer region of bulk material surrounding an inner cylinder of air is utilized. A numerical solution is obtained for the coupled wave equations governing the motion of the sound in both the inner and annular regions. It is found that the numerically predicted attenuation and propagations constants are in excellent agreement with measured values using Kevlar as the liner material for plane-wave mode (O,O) excitation over a wide range of mean flows and sound frequency. The boundary-layer effects are determined to be unimportant, at least for plane-wave sound. In addition, numerical studies indicate small differences between the use of either the radial velocity or the radial displacement boundary conditions.

Eocene evolution of whale hearing.

PubMed

Nummela, Sirpa; Thewissen, J G M; Bajpai, Sunil; Hussain, S Taseer; Kumar, Kishor

2004-08-12

The origin of whales (order Cetacea) is one of the best-documented examples of macroevolutionary change in vertebrates. As the earliest whales became obligately marine, all of their organ systems adapted to the new environment. The fossil record indicates that this evolutionary transition took less than 15 million years, and that different organ systems followed different evolutionary trajectories. Here we document the evolutionary changes that took place in the sound transmission mechanism of the outer and middle ear in early whales. Sound transmission mechanisms change early on in whale evolution and pass through a stage (in pakicetids) in which hearing in both air and water is unsophisticated. This intermediate stage is soon abandoned and is replaced (in remingtonocetids and protocetids) by a sound transmission mechanism similar to that in modern toothed whales. The mechanism of these fossil whales lacks sophistication, and still retains some of the key elements that land mammals use to hear airborne sound.

Mission building blocks for outer solar system exploration.

NASA Technical Reports Server (NTRS)

Herman, D.; Tarver, P.; Moore, J.

1973-01-01

Description of the technological building blocks required for exploring the outer planets with maximum scientific yields under stringent resource constraints. Two generic spacecraft types are considered: the Mariner and the Pioneer. Following a discussion of the outer planet mission constraints, the evolutionary development of spacecraft, probes, and propulsion building blocks is presented. Then, program genealogies are shown for Pioneer and Mariner missions and advanced propulsion systems to illustrate the soundness of a program based on spacecraft modification rather than on the development of new spacecraft for each mission. It is argued that, for minimum costs, technological advancement should occur in an evolutionary manner from mission to mission. While this strategy is likely to result in compromises on specific missions, the realization of the overall objectives calls for an advance commitment to the entire mission series.

Delta II Heavy launch of "Opportunity" MER-B Rover

NASA Image and Video Library

2003-07-07

On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the rover "Opportunity" for the second Mars Exploration Rover mission launches at 11:18:15 p.m. EDT. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rover’s prime mission is planned to last three months on Mars.

NASA Launches Rocket Into Active Auroras

NASA Image and Video Library

2017-12-08

A test rocket is launched the night of Feb. 17 from the Poker Flat Research Range in Alaska. Test rockets are launched as part of the countdown to test out the radar tracking systems. NASA is launching five sounding rockets from the Poker Range into active auroras to explore the Earth's magnetic environment and its impact on Earth’s upper atmosphere and ionosphere. The launch window for the four remaining rockets runs through March 3. Credit: NASA/Terry Zaperach NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

KSC-04PD-1072

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- From vantage points on the Fixed Service Structure (bottom right and left) on Launch Pad 39A, workers and the media look down upon the Mobile Launcher Platform (MLP) at the start of a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04PD-1074

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Water is released onto the Mobile Launcher Platform (MLP) on Launch Pad 39A at the start of a water sound suppression test. Workers and the media (left) are on hand to witness the rare event. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04PD-1073

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Water is released onto the Mobile Launcher Platform (MLP) on Launch Pad 39A at the start of a water sound suppression test. Workers and the media (left) are on hand to witness the rare event. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04PD-1076

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Some water remains on the surface of the Mobile Launcher Platform (MLP) on Launch Pad 39A after a water sound suppression test. Workers and the media (left) were on hand to witness the rare event. This test was conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1073

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- Water is released onto the Mobile Launcher Platform (MLP) on Launch Pad 39A at the start of a water sound suppression test. Workers and the media (left) are on hand to witness the rare event. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1071

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- From vantage points on the Fixed Service Structure (left) on Launch Pad 39A, workers and the media look down upon the Mobile Launcher Platform (MLP) waiting for the start of a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1074

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- Water is released onto the Mobile Launcher Platform (MLP) on Launch Pad 39A at the start of a water sound suppression test. Workers and the media (left) are on hand to witness the rare event. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1076

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- Some water remains on the surface of the Mobile Launcher Platform (MLP) on Launch Pad 39A after a water sound suppression test. Workers and the media (left) were on hand to witness the rare event. This test was conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1070

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- From vantage points on the Fixed Service Structure (left) on Launch Pad 39A, workers and the media look down upon the Mobile Launcher Platform (MLP) waiting for the start of a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1072

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- From vantage points on the Fixed Service Structure (bottom right and left) on Launch Pad 39A, workers and the media look down upon the Mobile Launcher Platform (MLP) at the start of a water sound suppression test. This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

Research in extreme ultraviolet and far ultraviolet astronomy

NASA Technical Reports Server (NTRS)

Bowyer, C. S.

1985-01-01

The Far Ultraviolet imager (FUVI) was flown on the Aries class sounding rocket 24.015, producing outstanding results. The diffuse extreme ultraviolet (EUV) background spectrometer which is under construction is described. It will be launched on the Black Brant sounding rocket flight number 27.086. Ongoing design studies of a high resolution spectrometer are discussed. This instrument incorporates a one meter normal incidence mirror and will be suitable for an advanced Spartan mission.

Interpolated Sounding and Gridded Sounding Value-Added Products

DOE Office of Scientific and Technical Information (OSTI.GOV)

Toto, T.; Jensen, M.

Standard Atmospheric Radiation Measurement (ARM) Climate Research Facility sounding files provide atmospheric state data in one dimension of increasing time and height per sonde launch. Many applications require a quick estimate of the atmospheric state at higher time resolution. The INTERPOLATEDSONDE (i.e., Interpolated Sounding) Value-Added Product (VAP) transforms sounding data into continuous daily files on a fixed time-height grid, at 1-minute time resolution, on 332 levels, from the surface up to a limit of approximately 40 km. The grid extends that high so the full height of soundings can be captured; however, most soundings terminate at an altitude between 25more » and 30 km, above which no data is provided. Between soundings, the VAP linearly interpolates atmospheric state variables in time for each height level. In addition, INTERPOLATEDSONDE provides relative humidity scaled to microwave radiometer (MWR) observations.The INTERPOLATEDSONDE VAP, a continuous time-height grid of relative humidity-corrected sounding data, is intended to provide input to higher-order products, such as the Merged Soundings (MERGESONDE; Troyan 2012) VAP, which extends INTERPOLATEDSONDE by incorporating model data. The INTERPOLATEDSONDE VAP also is used to correct gaseous attenuation of radar reflectivity in products such as the KAZRCOR VAP.« less

High-Temperature, Bellows Hybrid Seal

NASA Technical Reports Server (NTRS)

Steinetz, Bruce M. (Inventor); Sirocky, Paul J. (Inventor)

1994-01-01

A high-temperature hybrid seal is constructed of multiple elements to meet the many demands placed on the seal. The primary elements are: a central high-temperature bellows, a braided ceramic sheath covering the bellows, an outer abrasion resistant sheath covering the ceramic sheath, and a structurally-sound seal-end termination.

The Genesis of an Impulsive Coronal Mass Ejection Observed at Ultra-High Cadence by AIA on SDO

DTIC Science & Technology

2010-04-01

Most CMEmodels agree that the final ejected structure is a magnetic fluxrope which may correspond to the cavity observed in 3-part CMEs in the outer ...signals the launch of an EUV wave around the bubble (movie1.mpg) but the wave analysis will be reported elsewhere. The outer rim of the bubble becomes...the upper section of the flux-rope and not to its legs. 2RHESSI was observing the Crab Nebula during our event. – 6 – SXR rise profile arises from the

Factors Influencing Solar Electric Propulsion Vehicle Payload Delivery for Outer Planet Missions

NASA Technical Reports Server (NTRS)

Cupples, Michael; Green, Shaun; Coverstone, Victoria

2003-01-01

Systems analyses were performed for missions utilizing solar electric propulsion systems to deliver payloads to outer-planet destinations. A range of mission and systems factors and their affect on the delivery capability of the solar electric propulsion system was examined. The effect of varying the destination, the trip time, the launch vehicle, and gravity-assist boundary conditions was investigated. In addition, the affects of selecting propulsion system and power systems characteristics (including primary array power variation, number of thrusters, thruster throttling mode, and thruster Isp) on delivered payload was examined.

Current results from AlRS/AMSU/HSB

NASA Technical Reports Server (NTRS)

Susskind, Joel; Atlas, Robert; Barnet, Christopher; Blaisdell, Jon; Iredell, Lena; Bri, Genia; Jusem, Juan Carlos; Keita, Fricky; Kouvaris, Louis; Molnar, Gyula

2004-01-01

AIRS was launched on EOS Aqua on May 4,2002, together with AMSU A and HSB, to form a next generation polar orbiting infrared and microwave atmospheric sounding system. The primary products of AIRS/AMSU/HSB are twice daily global fields of atmospheric temperature-humidity profiles, ozone profiles, sea/land surface skin temperature, and cloud related parameters including OLR. The sounding goals of AIRS are to produce 1 km tropospheric layer mean temperatures with an rms error of 1K, and layer precipitable water with an rms error of 20%, in cases with up to 80% effective cloud cover. Pre-launch simulation studies indicated that these results should be achievable. Minor modifications have been made to the pre-launch retrieval algorithm as alluded to in this paper. Sample fields of parameters retrieved from AIRS/AMSU/HSB data are presented and temperature profiles are validated as a function of retrieved fractional cloud cover. As in simulation, the degradation of retrieval accuracy with increasing cloud cover is small. Select fields are also compared to those contained in the ECMWF analysis, done without the benefit of AIRS data, to demonstrate information that AIRS can add to that already contained in the ECMWF analysis. Assimilation of AIRS temperature soundings in up to 80% cloud cover for the month of January 2003 into the GSFC FVSSI data assimilation system resulted in improved 5 day forecasts globally, both with regard to anomaly correction coefficients and the prediction of location and intensity of cyclones.

Influence of microgravity on root-cap regeneration and the structure of columella cells in Zea mays

NASA Technical Reports Server (NTRS)

Moore, R.; McClelen, C. E.; Fondren, W. M.; Wang, C. L.

1987-01-01

We launched imbibed seeds and seedlings of Zea mays into outer space aboard the space shuttle Columbia to determine the influence of microgravity on 1) root-cap regeneration, and 2) the distribution of amyloplasts and endoplasmic reticulum (ER) in the putative statocytes (i.e., columella cells) of roots. Decapped roots grown on Earth completely regenerated their caps within 4.8 days after decapping, while those grown in microgravity did not regenerate caps. In Earth-grown seedlings, the ER was localized primarily along the periphery of columella cells, and amyloplasts sedimented in response to gravity to the lower sides of the cells. Seeds germinated on Earth and subsequently launched into outer space had a distribution of ER in columella cells similar to that of Earth-grown controls, but amyloplasts were distributed throughout the cells. Seeds germinated in outer space were characterized by the presence of spherical and ellipsoidal masses of ER and randomly distributed amyloplasts in their columella cells. These results indicate that 1) gravity is necessary for regeneration of the root cap, 2) columella cells can maintain their characteristic distribution of ER in microgravity only if they are exposed previously to gravity, and 3) gravity is necessary to distribute the ER in columella cells of this cultivar of Z. mays.

Si-depleted outer core inferred from sound velocity measurements of liquid Fe-Si alloys

NASA Astrophysics Data System (ADS)

Nakajima, Y.; Imada, S.; Hirose, K.; Kuwayama, Y.; Sinmyo, R.; Tateno, S.; Ozawa, H.; Tsutsui, S.; Uchiyama, H.; Baron, A. Q. R.

2016-12-01

Recent core formation models [1,2] suggested that a large amount of Si could have been incorporated into the core forming metals in the early stage of the Earth. These studies gave estimates for the Si content in the core, from 2 to 9 wt.%. In order to constrain the Si content of the outer core, we have determined the sound wave velocity of liquid Fe-Si alloys under high pressures and high temperatures. Starting materials of Fe-Si alloys with 6.5 and 9 wt.% Si were melted in a laser-heated diamond-anvil cell. The longitudinal acoustic phonon excitation of a liquid metal was measured up to 52 GPa and 3200 K by using high resolution inelastic X-ray scattering spectroscopy at beamline BL35XU [3] of the SPring-8 synchrotron facility. Our results show that silicon significantly increases the P-wave velocity of liquid Fe. Seismological observation shows that the P-wave velocity in the outer core is 3-4% faster than in pure iron. Comparing the present results with seismological observations, the silicon content of the outer core should be limited to be <2 wt.%, significantly lower than previous estimates based on the element partitioning between core forming mental and silicate magma ocean during core formation processes. This indicates that the present-day core is depleted in Si relative to the ancient core just after core formation, which agrees with the recent proposal [4] that the Si content in the outer core has been diminished by SiO2 crystallization through the core cooling history. [1] Rubie et al. (2011) Earth Planet. Sci. Lett. 301, 31-42. [2] Siebert et al. (2013) Science 339, 1194-1197. [3] Baron et al. (2000) J. Phys. Chem. Solids 61, 461-465 [4] Hirose et al. (2015) Abstract presented at AGU Fall Meeting 2015.

Performance enhancement of existing two-stage sounding rocket vehicles through the use of tandem booster systems

NASA Technical Reports Server (NTRS)

Flores, C. C.; Gurkin, L. W.

1982-01-01

The three-stage Taurus-Nike-Tomahawk launch vehicle is being considered for performance enhancement of the existing Taurus-Tomahawk flight system. In addition, performance enhancement of other existing two-stage launch vehicles is being considered through the use of tandem booster systems. Aeroballistic characteristics of the proposed Taurus-Nike-Tomahawk vehicle are presented, as are overall performance capabilities of other potential three-stage flight systems.

KSC-08pd2288

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment (MULE) carrier arrives at NASA's Kennedy Space Center for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

In-line quincke tube muffler

NASA Astrophysics Data System (ADS)

Patrick, William P.; Bryant, Rebecca S.; Greenwald, Larry E.

2002-05-01

A unique low-pressure-drop muffler is described which has been designed to attenuate low frequency tonal noise in ducts. Flow through the muffler is divided into two noncommunicating paths in the cylindrical configuration which was designed, built, and tested. Half of the flow is ducted through a straight central annulus and the other half is ducted through a partitioned outer annulus which directs the flow in a spiral flow pattern around the inner annulus. Thus the outer flow has a longer path length and the sound within the outer annulus is phase-delayed relative to the inner flow causing destructive interference between the inner and outer waves with resulting strong attenuation at the tuned frequencies. A procedure will be described for designing a muffler (with flow) to produce high attenuation at the fundamental noise tone and all harmonics (up to the first cross mode). Results will be presented which show that the muffler achieved over 20 dB attenuation for the first five harmonics of the incident noise in a flowing duct.

Aftereffects of Intense Low-Frequency Sound on Spontaneous Otoacoustic Emissions: Effect of Frequency and Level.

PubMed

Jeanson, Lena; Wiegrebe, Lutz; Gürkov, Robert; Krause, Eike; Drexl, Markus

2017-02-01

The presentation of intense, low-frequency (LF) sound to the human ear can cause very slow, sinusoidal oscillations of cochlear sensitivity after LF sound offset, coined the "Bounce" phenomenon. Changes in level and frequency of spontaneous otoacoustic emissions (SOAEs) are a sensitive measure of the Bounce. Here, we investigated the effect of LF sound level and frequency on the Bounce. Specifically, the level of SOAEs was tracked for minutes before and after a 90-s LF sound exposure. Trials were carried out with several LF sound levels (93 to 108 dB SPL corresponding to 47 to 75 phons at a fixed frequency of 30 Hz) and different LF sound frequencies (30, 60, 120, 240 and 480 Hz at a fixed loudness level of 80 phons). At an LF sound frequency of 30 Hz, a minimal sound level of 102 dB SPL (64 phons) was sufficient to elicit a significant Bounce. In some subjects, however, 93 dB SPL (47 phons), the lowest level used, was sufficient to elicit the Bounce phenomenon and actual thresholds could have been even lower. Measurements with different LF sound frequencies showed a mild reduction of the Bounce phenomenon with increasing LF sound frequency. This indicates that the strength of the Bounce not only is a simple function of the spectral separation between SOAE and LF sound frequency but also depends on absolute LF sound frequency, possibly related to the magnitude of the AC component of the outer hair cell receptor potential.

ATK Launch Vehicle (ALV-X1) Liftoff Acoustic Environments: Prediction vs. Measurement

NASA Technical Reports Server (NTRS)

Houston, Janice; Counter, Douglas; Kenny, Jeremy; Murphy, John

2009-01-01

The ATK Launch Vehicle (ALV-X1) provided an opportunity to measure liftoff acoustic noise data. NASA Marshall Space Flight Center (MSFC) engineers were interested in the ALV-X1 launch because the First Stage motor and launch pad conditions, including a relativity short deflector ducting, provide a potential analogue to future Ares I launches. This paper presents the measured liftoff acoustics on the vehicle and tower. Those measured results are compared to predictions based upon the method described in NASA SP-8072 "Acoustic Loads Generated by the Propulsion System" and the Vehicle Acoustic Environment Prediction Program (VAEPP) which was developed by MSFC acoustics engineers. One-third octave band sound pressure levels will be presented. This data is useful for the ALV-X1 in validating the pre-launch environments and loads predictions. Additionally, the ALV-X1 liftoff data can be scaled to define liftoff environments for the NASA Constellation program Ares vehicles. Vehicle liftoff noise is caused by the supersonic jet flow interaction with surrounding atmosphere or more simply, jet noise. As the vehicle's First Stage motor is ignited, an acoustic noise field is generated by the exhaust. This noise field persists due to the supersonic jet noise and reflections from the launch pad and tower, then changes as the vehicle begins to liftoff from the launch pad. Depending on launch pad and adjacent tower configurations, the liftoff noise is generally very high near the nozzle exit and decreases rapidly away from the nozzle. The liftoff acoustic time range of interest is typically 0 to 20 seconds after ignition. The exhaust plume thermo-fluid mechanics generates sound at approx.10 Hz to 20 kHz. Liftoff acoustic noise is usually the most severe dynamic environment for a launch vehicle or payload in the mid to high frequency range (approx.50 to 2000 Hz). This noise environment can induce high-level vibrations along the external surfaces of the vehicle and surrounding launch facility structures. The acoustic pressure fluctuations will induce severe vibrations in relatively large lightweight structures. Consequently, there is the potential for failure of the structure or attached electrical components. Due to these potential failures, the liftoff acoustic noise is one of the noise source inputs used to determine the vibro-acoustic qualification environment for a launch vehicle and its components.

STS-65 Columbia, OV-102, clears launch tower after liftoff from KSC LC 39A

NASA Technical Reports Server (NTRS)

1994-01-01

Columbia, Orbiter Vehicle (OV) 102, heads skyward after clearing the fixed service structure (FSS) tower at Kennedy Space Center (KSC) Launch Complex (LC) Pad 39A. Florida plant life appears in the foreground. The exhaust cloud produced by OV-102's solid rocket boosters (SRBs) covers the launch pad area with the exception of the sound suppression water system tower. OV-102's starboard side and the right SRB are visible from this angle. Launch occurred at 12:43 pm Eastern Daylight Time (EDT). Once in Earth orbit, STS-65's six NASA astronauts and a Japanese Payload Specialist aboard OV-102 will begin two weeks of experimentation in support of the second International Microgravity Laboratory (IML-2).

KSC00pp0545

NASA Image and Video Library

2000-04-23

The GOES-L satellite, after being lifted up to the top of the gantry on pad 36A, Cape Canaveral Air Force Station, is ready for mating with the Atlas IIA/Centaur rocket. Atlas IIA is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

KSC-00pp0545

NASA Image and Video Library

2000-04-23

The GOES-L satellite, after being lifted up to the top of the gantry on pad 36A, Cape Canaveral Air Force Station, is ready for mating with the Atlas IIA/Centaur rocket. Atlas IIA is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing. Launch is scheduled for May 3

Water Deluge Test at Launch Complex 39B

NASA Image and Video Library

2018-05-24

About 450,000 gallons of water flow at high speed from a holding tank through new and modified piping and valves, the flame trench, flame deflector nozzles and mobile launcher interface risers during a wet flow test on May 24, 2018, at Launch Pad 39B at NASA's Kennedy Space Center in Florida. At peak flow, the water reached about 100 feet in the air above the pad surface. The test was performed by Exploration Ground Systems to confirm the performance of the Ignition Overpressure/Sound Suppression system. During launch of NASA's Space Launch System rocket and Orion spacecraft, the high-speed water flow will help protect the vehicle from the extreme acoustic and temperature environment during ignition and liftoff.

ADDJUST - An automated system for steering Centaur launch vehicles in measured winds

NASA Technical Reports Server (NTRS)

Swanson, D. C.

1977-01-01

ADDJUST (Automatic Determination and Dissemination of Just-Updated Steering Terms) is an automated computer and communication system designed to provide Atlas/Centaur and Titan/Centaur launch vehicles with booster-phase steering data on launch day. Wind soundings are first obtained, from which a smoothed wind velocity vs altitude relationship is established. Design for conditions at the end of the boost phase with initial pitch and yaw maneuvers, followed by zero total angle of attack through the filtered wind establishes the required vehicle attitude as a function of altitude. Polynomial coefficients for pitch and yaw attitude vs altitude are determined and are transmitted for validation and loading into the Centaur airborne computer. The system has enabled 14 consecutive launches without a flight wind delay.

STS-65 Columbia, OV-102, clears launch tower after liftoff from KSC LC 39A

NASA Image and Video Library

1994-07-08

Columbia, Orbiter Vehicle (OV) 102, heads skyward after clearing the fixed service structure (FSS) tower at Kennedy Space Center (KSC) Launch Complex (LC) Pad 39A. Florida plant life appears in the foreground. The exhaust cloud produced by OV-102's solid rocket boosters (SRBs) covers the launch pad area with the exception of the sound suppression water system tower. OV-102's starboard side and the right SRB are visible from this angle. Launch occurred at 12:43 pm Eastern Daylight Time (EDT). Once in Earth orbit, STS-65's six NASA astronauts and a Japanese Payload Specialist aboard OV-102 will begin two weeks of experimentation in support of the second International Microgravity Laboratory (IML-2).

COBE video news

NASA Astrophysics Data System (ADS)

1989-10-01

This videotape was produced for hand-out to both local and national broadcast media as a prelude to the launch of the Cosmic Background Explorer. The tape consists of short clips with multi-channel sound to facilitate news media editing.

Voyager Special Cargo: The Golden Record

NASA Image and Video Library

2011-04-29

This image highlights the special cargo onboard NASA Voyager spacecraft: the Golden Record. Each of the two Voyager spacecraft launched in 1977 carry a 12-inch gold-plated phonograph record with images and sounds from Earth.

Indian space transportation programme: Near term outlook and issues for commercialisation

NASA Astrophysics Data System (ADS)

Nagendra, Narayan Prasad

2015-05-01

The Indian space transportation programme has grown from strength to strength with the launching of sounding rockets in the 60's to the development of heavy lift vehicles for telecommunication satellites in the present decade. With the growing market confidence in Indian Space Research Organisation's ability to reliably deliver payloads to low Earth orbit with its Polar Satellite Launch Vehicle, there is an inherent opportunity for India to cater to the commercial market. The present work assesses the current launch capacity of India in retrospect of international launches and provides India's outlook for the space transportation in the current decade. Launch capacity correlation with the requirements within the Indian space programme as well as the current space transportation infrastructure have been considered to identify bottlenecks in catering to the current national requirements alongside securing a greater market share in the international launch market. The state of commercialisation of launch vehicle development has been presented to provide an overview of policy and organisational issues for commercialisation of space transportation in India.

The Extended Duration Sounding Rocket (EDSR): Low Cost Science and Technology Missions

NASA Astrophysics Data System (ADS)

Cruddace, R. G.; Chakrabarti, S.; Cash, W.; Eberspeaker, P.; Figer, D.; Figueroa, O.; Harris, W.; Kowalski, M.; Maddox, R.; Martin, C.; McCammon, D.; Nordsieck, K.; Polidan, R.; Sanders, W.; Wilkinson, E.; Asrat

2011-12-01

The 50-year old NASA sounding rocket (SR) program has been successful in launching scientific payloads into space frequently and at low cost with a 85% success rate. In 2008 the NASA Astrophysics Sounding Rocket Assessment Team (ASRAT), set up to review the future course of the SR program, made four major recommendations, one of which now called Extended Duration Sounding Rocket (EDSR). ASRAT recommended a system capable of launching science payloads (up to 420 kg) into low Earth orbit frequently (1/yr) at low cost, with a mission duration of approximately 30 days. Payload selection would be based on meritorious high-value science that can be performed by migrating sub-orbital payloads to orbit. Establishment of this capability is a essential for NASA as it strives to advance technical readiness and lower costs for risk averse Explorers and flagship missions in its pursuit of a balanced and sustainable program and achieve big science goals within a limited fiscal environment. The development of a new generation of small, low-cost launch vehicles (SLV), primarily the SpaceX Falcon 1 and the Orbital Sciences Minotaur I has made this concept conceivable. The NASA Wallops Flight Facility (WFF)conducted a detailed engineering concept study, aimed at defining the technical characteristics of all phases of a mission, from design, procurement, assembly, test, integration and mission operations. The work was led by Dr. Raymond Cruddace, a veteran of the SR program and the prime mover of the EDSR concept. The team investigated details such as, the "FAA licensed contract" for launch service procurement, with WFF and NASA SMD being responsible for mission assurance which results in a factor of two cost savings over the current approach. These and other creative solutions resulted in a proof-of-concept Class D mission design that could have a sustained launch rate of at least 1/yr, a mission duration of up to about 3 months, and a total cost of $25-30 million for each mission. The payload includes a pointing system with arc second precision, a command and data system which can be configured to meet the unique requirements of a particular mission, and a solar cell-battery power system. Anticipating the tremendous need of access to space, Cruddace and his team included a capability of inclusion of a number of smaller secondary instruments, ranging in size from CubeSats to instruments weighing up to 100 lb. These secondary payloads could be ejected as needed by P-PODs. In this talk, we will summarize EDSR, a legacy of Ray Cruddace.

Determination of equivalent sound speed profiles for ray tracing in near-ground sound propagation.

PubMed

Prospathopoulos, John M; Voutsinas, Spyros G

2007-09-01

The determination of appropriate sound speed profiles in the modeling of near-ground propagation using a ray tracing method is investigated using a ray tracing model which is capable of performing axisymmetric calculations of the sound field around an isolated source. Eigenrays are traced using an iterative procedure which integrates the trajectory equations for each ray launched from the source at a specific direction. The calculation of sound energy losses is made by introducing appropriate coefficients to the equations representing the effect of ground and atmospheric absorption and the interaction with the atmospheric turbulence. The model is validated against analytical and numerical predictions of other methodologies for simple cases, as well as against measurements for nonrefractive atmospheric environments. A systematic investigation for near-ground propagation in downward and upward refractive atmosphere is made using experimental data. Guidelines for the suitable simulation of the wind velocity profile are derived by correlating predictions with measurements.

ARES I Aerodynamic Testing at the NASA Langley Unitary Plan Wind Tunnel

NASA Technical Reports Server (NTRS)

Erickson, Gary E.; Wilcox, Floyd J.

2011-01-01

Small-scale force and moment and pressure models based on the outer mold lines of the Ares I design analysis cycle crew launch vehicle were tested in the NASA Langley Research Center Unitary Plan Wind Tunnel from May 2006 to September 2009. The test objectives were to establish supersonic ascent aerodynamic databases and to obtain force and moment, surface pressure, and longitudinal line-load distributions for comparison to computational predictions. Test data were obtained at low through high supersonic Mach numbers for ranges of the Reynolds number, angle of attack, and roll angle. This paper focuses on (1) the sensitivity of the supersonic aerodynamic characteristics to selected protuberances, outer mold line changes, and wind tunnel boundary layer transition techniques, (2) comparisons of experimental data to computational predictions, and (3) data reproducibility. The experimental data obtained in the Unitary Plan Wind Tunnel captured the effects of evolutionary changes to the Ares I crew launch vehicle, exhibited good agreement with predictions, and displayed satisfactory within-test and tunnel-to-tunnel data reproducibility.

Magnetour: Surfing planetary systems on electromagnetic and multi-body gravity fields

NASA Astrophysics Data System (ADS)

Lantoine, Gregory; Russell, Ryan P.; Anderson, Rodney L.; Garrett, Henry B.

2017-09-01

A comprehensive tour of the complex outer planet systems is a central goal in space science. However, orbiting multiple moons of the same planet would be extremely prohibitive using traditional propulsion and power technologies. In this paper, a new mission concept, named Magnetour, is presented to facilitate the exploration of outer planet systems and address both power and propulsion challenges. This approach would enable a single spacecraft to orbit and travel between multiple moons of an outer planet, without significant propellant or onboard power source. To achieve this free-lunch 'Grand Tour', Magnetour exploits the unexplored combination of magnetic and multi-body gravitational fields of planetary systems, with a unique focus on using a bare electrodynamic tether for power and propulsion. Preliminary results indicate that the Magnetour concept is sound and is potentially highly promising at Jupiter.

Nuclear thermal rockets using indigenous extraterrestrial propellants

NASA Technical Reports Server (NTRS)

Zubrin, Robert M.

1990-01-01

A preliminary examination of a concept for a Mars and outer solar system exploratory vehicle is presented. Propulsion is provided by utilizing a nuclear thermal reactor to heat a propellant volatile indigenous to the destination world to form a high thrust rocket exhaust. Candidate propellants, whose performance, materials compatibility, and ease of acquisition are examined and include carbon dioxide, water, methane, nitrogen, carbon monoxide, and argon. Ballistics and winged supersonic configurations are discussed. It is shown that the use of this method of propulsion potentially offers high payoff to a manned Mars mission. This is accomplished by sharply reducing the initial mission mass required in low earth orbit, and by providing Mars explorers with greatly enhanced mobility in traveling about the planet through the use of a vehicle that can refuel itself each time it lands. Thus, the nuclear landing craft is utilized in combination with a hydrogen-fueled nuclear-thermal interplanetary launch. By utilizing such a system in the outer solar system, a low level aerial reconnaissance of Titan combined with a multiple sample return from nearly every satellite of Saturn can be accomplished in a single launch of a Titan 4 or the Space Transportation System (STS). Similarly a multiple sample return from Callisto, Ganymede, and Europa can also be accomplished in one launch of a Titan 4 or the STS.

Sound Transmission through Cylindrical Shell Structures Excited by Boundary Layer Pressure Fluctuations

NASA Technical Reports Server (NTRS)

Tang, Yvette Y.; Silcox, Richard J.; Robinson, Jay H.

1996-01-01

This paper examines sound transmission into two concentric cylindrical sandwich shells subject to turbulent flow on the exterior surface of the outer shell. The interior of the shells is filled with fluid medium and there is an airgap between the shells in the annular space. The description of the pressure field is based on the cross-spectral density formulation of Corcos, Maestrello, and Efimtsov models of the turbulent boundary layer. The classical thin shell theory and the first-order shear deformation theory are applied for the inner and outer shells, respectively. Modal expansion and the Galerkin approach are used to obtain closed-form solutions for the shell displacements and the radiation and transmission pressures in the cavities including both the annular space and the interior. The average spectral density of the structural responses and the transmitted interior pressures are expressed explicitly in terms of the summation of the cross-spectral density of generalized force induced by the boundary layer turbulence. The effects of acoustic and hydrodynamic coincidences on the spectral density are observed. Numerical examples are presented to illustrate the method for both subsonic and supersonic flows.

Earth Science

NASA Image and Video Library

1995-12-01

The reflection of the Atlas IIAS expendable launch vehicle with the Solar Heliospheric Observatory (SOHO) inside its payload fairing can be seen on the surface of a retention pond at Launch Pad 36B on Cape Canaveral Air Station just hours before liftoff. SOHO is a cooperative effort involving NASA and the European Space Agency (ESA) within the framework of the International Solar-Terrestrial Physics Program. During its 2-year mission, the SOHO spacecraft will gather data on the internal structure of the Sun, its extensive outer atmosphere and the origin of the solar wind.

Multi-Objective Hybrid Optimal Control for Multiple-Flyby Interplanetary Mission Design Using Chemical Propulsion

NASA Technical Reports Server (NTRS)

Englander, Jacob; Vavrina, Matthew

2015-01-01

The customer (scientist or project manager) most often does not want just one point solution to the mission design problem Instead, an exploration of a multi-objective trade space is required. For a typical main-belt asteroid mission the customer might wish to see the trade-space of: Launch date vs. Flight time vs. Deliverable mass, while varying the destination asteroid, planetary flybys, launch year, etcetera. To address this question we use a multi-objective discrete outer-loop which defines many single objective real-valued inner-loop problems.

Nimbus-F to carry advanced weather instruments

NASA Technical Reports Server (NTRS)

1975-01-01

Meteorological research instruments launched aboard NASA's Nimbus-F spacecraft are briefly described along with the Nimbus satellite program initiated to develop an observatory system capable of meeting the research and development needs of the nation's atmospheric and earth sciences program. The following aspects of the mission are described: spacecraft design, launch operations, sequence of orbital events, and operations control and tracking. The Global Atmospheric Research program is discussed in terms of the Nimbus-F experiments and atmospheric sounding instruments.

Vacuum-isolation vessel and method for measurement of thermal noise in microphones

NASA Technical Reports Server (NTRS)

Zuckerwar, Allan J. (Inventor); Ngo, Kim Chi T. (Inventor)

1992-01-01

The vacuum isolation vessel and method in accordance with the present invention are used to accurately measure thermal noise in microphones. The apparatus and method could be used in a microphone calibration facility or any facility used for testing microphones. Thermal noise is measured to determine the minimum detectable sound pressure by the microphone. Conventional isolation apparatus and methods have been unable to provide an acoustically quiet and substantially vibration free environment for accurately measuring thermal noise. In the present invention, an isolation vessel assembly comprises a vacuum sealed outer vessel, a vacuum sealed inner vessel, and an interior suspension assembly coupled between the outer and inner vessels for suspending the inner vessel within the outer vessel. A noise measurement system records thermal noise data from the isolation vessel assembly. A vacuum system creates a vacuum between an internal surface of the outer vessel and an external surface of the inner vessel. The present invention thus provides an acoustically quiet environment due to the vacuum created between the inner and outer vessels and a substantially vibration free environment due to the suspension assembly suspending the inner vessel within the outer vessel. The thermal noise in the microphone, effectively isolated according to the invention, can be accurately measured.

Optical power splitter and polarization splitter

NASA Technical Reports Server (NTRS)

Bogert, Gail A. (Inventor)

1988-01-01

A 3.times.3 optical guiding arrangement is disclosed for providing both power splitting between a pair of output guides in the 3.times.3 guide structure and polarization splitting (into the TE and TM modes) between the central guide and the pair of outer guides. In accordance with the present invention, the mutual coupling length L and separation distance d between adjacent guides are chosen to provide the desired polarization splitting and total intensity (power) in the outer guides. For example, an input signal of intensity I comprising both the TE and TM modes may be launched in the center guide and with correct choices for L and d, will result in output signals of I.sub.TM /2 each of the outer pair of guides and I.sub.TE from the central guide.

76 FR 16311 - Takes of Marine Mammals Incidental to Specified Activities; Taking Marine Mammals Incidental to...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-23

... sound for various biological functions including, but not limited to: (1) Social interactions; (2... launch: (1) Combustion noise; (2) jet noise from interaction of combustion exhaust gases with the...

Supersonic Retropropulsion Flight Test Concepts

NASA Technical Reports Server (NTRS)

Post, Ethan A.; Dupzyk, Ian C.; Korzun, Ashley M.; Dyakonov, Artem A.; Tanimoto, Rebekah L.; Edquist, Karl T.

2011-01-01

NASA's Exploration Technology Development and Demonstration Program has proposed plans for a series of three sub-scale flight tests at Earth for supersonic retropropulsion, a candidate decelerator technology for future, high-mass Mars missions. The first flight test in this series is intended to be a proof-of-concept test, demonstrating successful initiation and operation of supersonic retropropulsion at conditions that replicate the relevant physics of the aerodynamic-propulsive interactions expected in flight. Five sub-scale flight test article concepts, each designed for launch on sounding rockets, have been developed in consideration of this proof-of-concept flight test. Commercial, off-the-shelf components are utilized as much as possible in each concept. The design merits of the concepts are compared along with their predicted performance for a baseline trajectory. The results of a packaging study and performance-based trade studies indicate that a sounding rocket is a viable launch platform for this proof-of-concept test of supersonic retropropulsion.

KSC-98pc633

NASA Image and Video Library

1998-04-17

KENNEDY SPACE CENTER, FLA. -- David Dickinson, the acting director of the National Aeronautics and Space Administration (NASA) Public Affairs Office at Kennedy Space Center, accepts a copy of Bulgarian singer Dyana Dafova's latest compact disc (CD) from her on behalf of NASA. The 525-foot tall Vehicle Assembly Building, where Space Shuttle orbiters are mated to their external tank/solid rocket booster stacks, looms in the background. Dyana is touring the United States to promote her CD, entitled "Sounds of the Earth," and was an invited guest of NASA for the launch of Columbia on STS-90, the Neurolab mission, earlier in the day. Columbia lifted off from Launch Pad 39B at 2:19 p.m. EDT. Dyana characterized the music on her CD as a new sound, incorporating jazz and new age classics, sung in a newly created language comprised of Bulgarian, English, Sanskrit, Aramski and Hebrew

Sounding rocket/ground-based observation campaign to study Medium-Scale Traveling Ionospheric Disturbances (MSTID)

NASA Astrophysics Data System (ADS)

Yamamoto, Mamoru; Otsuka, Yuichi; Abe, Takumi; Yokoyama, Tatsuhiro; Bernhardt, Paul; Watanabe, Shigeto; Yamamoto, Masa-yuki; Larsen, Miguel; Saito, Akinori; Pfaff, Robert; Ishisaka, Keigo

2012-07-01

An observation campaign is under preparation. It is to launch sounding rockets S-520-27 and S-310-42 from Uchinoura Space Center of JAXA, while ground-based instruments measure waves in the ionosphere. The main purpose of the study is to reveal seeding mechanism of Medium-Scale Traveling Ionospheric Disturbances (MSTID). The MSTID is enhanced in the summer nighttime of the mid-latitude ionosphere. The MSTID is not only a simple reflection of atmospheric waves to the ionosphere, but includes complicated processes including the electromagnetic coupling of the F- and E-regions, and inter-hemisphere coupling of the ionosphere. We will measure ionospheric parameters such as electron density and electric fields together with neutral winds in the E- and F-regions. TMA and Lithium release experiment will be conducted with S-310-42 and S-520-27 rockets, respectively. The observation campaign is planned in summer 2012 or 2013. In the presentation we will overview characteristics of MSTID, and show plan and current status of the project. We also touch results from the sounding rocket S-520-26 that was launched on January 12, 2012. We will show results of the rocket-ground dual-band beacon experiment.

Performance analysis of an IMU-augmented GNSS tracking system on board the MAIUS-1 sounding rocket

NASA Astrophysics Data System (ADS)

Braun, Benjamin; Grillenberger, Andreas; Markgraf, Markus

2018-05-01

Satellite navigation receivers are adequate tracking sensors for range safety of both orbital launch vehicles and suborbital sounding rockets. Due to high accuracy and its low system complexity, satellite navigation is seen as well-suited supplement or replacement of conventional tracking systems like radar. Having the well-known shortcomings of satellite navigation like deliberate or unintentional interferences in mind, it is proposed to augment the satellite navigation receiver by an inertial measurement unit (IMU) to enhance continuity and availability of localization. The augmented receiver is thus enabled to output at least an inertial position solution in case of signal outages. In a previous study, it was shown by means of simulation using the example of Ariane 5 that the performance of a low-grade microelectromechanical IMU is sufficient to bridge expected outages of some ten seconds, and still meeting the range safety requirements in effect. In this publication, these theoretical findings shall be substantiated by real flight data that were recorded on MAIUS-1, a sounding rocket launched from Esrange, Sweden, in early 2017. The analysis reveals that the chosen representative of a microelectromechanical IMU is suitable to bridge outages of up to thirty seconds.

KSC00pp0421

NASA Image and Video Library

2000-03-29

The second stage of an Atlas II/Centaur rocket arrives on pad 36-A, Cape Canaveral Air Force Station, for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0421

NASA Image and Video Library

2000-03-29

The second stage of an Atlas II/Centaur rocket arrives on pad 36-A, Cape Canaveral Air Force Station, for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

30 CFR 250.918 - What are the CVA's primary duties during the installation phase?

Code of Federal Regulations, 2010 CFR

2010-07-01

... INTERIOR OFFSHORE OIL AND GAS AND SULPHUR OPERATIONS IN THE OUTER CONTINENTAL SHELF Platforms and..., and review the towing records; (iii) Launching and uprighting operations; (iv) Submergence operations..., and when the independent monitoring activities were conducted; (2) Describe the CVA's activities...

The Science Detectives.

ERIC Educational Resources Information Center

Search for Extraterrestrial Intelligence Inst., Mountain View, CA.

The possibility of life on other planets holds enormous fascination for people of all ages. This interdisciplinary learning kit uses that theme to launch scientific learning in young students. Through a series of hands-on activities, it directs participants to solve an outer space mystery thereby acquiring and developing scientific knowledge and…

Development of Modeling Capabilities for Launch Pad Acoustics and Ignition Transient Environment Prediction

NASA Technical Reports Server (NTRS)

West, Jeff; Strutzenberg, Louise L.; Putnam, Gabriel C.; Liever, Peter A.; Williams, Brandon R.

2012-01-01

This paper presents development efforts to establish modeling capabilities for launch vehicle liftoff acoustics and ignition transient environment predictions. Peak acoustic loads experienced by the launch vehicle occur during liftoff with strong interaction between the vehicle and the launch facility. Acoustic prediction engineering tools based on empirical models are of limited value in efforts to proactively design and optimize launch vehicles and launch facility configurations for liftoff acoustics. Modeling approaches are needed that capture the important details of the plume flow environment including the ignition transient, identify the noise generation sources, and allow assessment of the effects of launch pad geometric details and acoustic mitigation measures such as water injection. This paper presents a status of the CFD tools developed by the MSFC Fluid Dynamics Branch featuring advanced multi-physics modeling capabilities developed towards this goal. Validation and application examples are presented along with an overview of application in the prediction of liftoff environments and the design of targeted mitigation measures such as launch pad configuration and sound suppression water placement.

Simulation of tsunamis from great earthquakes on the cascadia subduction zone.

PubMed

Ng, M K; Leblond, P H; Murty, T S

1990-11-30

Large earthquakes occur episodically in the Cascadia subduction zone. A numerical model has been used to simulate and assess the hazards of a tsunami generated by a hypothetical earthquake of magnitude 8.5 associated with rupture of the northern sections of the subduction zone. Wave amplitudes on the outer coast are closely related to the magnitude of sea-bottom displacement (5.0 meters). Some amplification, up to a factor of 3, may occur in some coastal embayments. Wave amplitudes in the protected waters of Puget Sound and the Strait of Georgia are predicted to be only about one fifth of those estmated on the outer coast.

Soyuz over Kitty Hawk

NASA Image and Video Library

2003-04-24

ISS006-E-50419 (2003) --- This digital still camera image of Cape Hatteras and Cape Lookout, North Carolina, with a Soyuz vehicle docked to the orbital outpost in the foreground was taken by Expedition 6 crewmember Don Pettit during his 5 1/2 month stay on the International Space Station (ISS). The largest inland body of water is Pamlico Sound. Kitty Hawk, on North Carolina's Outer Banks is also visible. On Dec. 17, 2003, the world celebrates a century of human flight with the anniversary of the Wright Brothers' first flight at Kitty Hawk. The brothers used the Outer Banks' prevailing winds and a 90-foot hill (Kill Devil Hill) to successfully demonstrate powered flight.

Rocket and laboratory studies in aeronomy and astronomy

NASA Technical Reports Server (NTRS)

Feldman, P. D.

1983-01-01

Data extracted from semi-annual status reports presented include: a list of all sounding rocket launches performed under NASA sponsorship; a list of Ph.D. and M.A. degrees awarded to students who worked in these programs; a summary bibliography of all publications through 1983; the most recent list of the publications from the IUE program; a summary of instrument development supported by the Johns Hopkins sounding rocket program; and a list of faculty and post-doctoral research associates whose work was supported by this grant.

KSC-04pd1067

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are being released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. Because of the unusual event, media and workers watch from nearby vantage points on the Fixed Service Structure (left). This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1069

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are being released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. Because of the unusual event, media and workers watch from nearby vantage points on the Fixed Service Structure (left). This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

KSC-04pd1068

NASA Image and Video Library

2004-05-07

KENNEDY SPACE CENTER, FLA. -- For the fourth time in Space Shuttle Program history, 350,000 gallons of water are being released on a Mobile Launcher Platform (MLP) at Launch Pad 39A during a water sound suppression test. Because of the unusual event, media and workers watch from nearby vantage points on the Fixed Service Structure (left). This test is being conducted following the replacement of the six main system valves, which had been in place since the beginning of the Shuttle Program and had reached the end of their service life. Also, the hydraulic portion of the valve actuators has been redesigned and simplified to reduce maintenance costs. The sound suppression water system is installed on the launch pads to protect the orbiter and its payloads from damage by acoustical energy reflected from the MLP during launch. The system includes an elevated water tank with a capacity of 300,000 gallons. The tank is 290 feet high and stands on the northeast side of the Pad. The water is released just before the ignition of the orbiter's three main engines and twin solid rocket boosters, and flows through parallel 7-foot-diameter pipes to the Pad area.

Planetary/DOD entry technology flight experiments. Volume 2: Planetary entry flight experiments

NASA Technical Reports Server (NTRS)

Christensen, H. E.; Krieger, R. J.; Mcneilly, W. R.; Vetter, H. C.

1976-01-01

The technical feasibility of launching a high speed, earth entry vehicle from the space shuttle to advance technology for the exploration of the outer planets' atmospheres was established. Disciplines of thermodynamics, orbital mechanics, aerodynamics propulsion, structures, design, electronics and system integration focused on the goal of producing outer planet environments on a probe shaped vehicle during an earth entry. Major aspects of analysis and vehicle design studied include: planetary environments, earth entry environment capability, mission maneuvers, capabilities of shuttle upper stages, a comparison of earth entry planetary environments, experiment design and vehicle design.

Science Preparations for the Orbiting Carbon Observatory - 2 (OCO-2) Launch

NASA Astrophysics Data System (ADS)

Gunson, M. R.; Crisp, D.; Eldering, A.

2013-12-01

The Orbiting Carbon Observatory-2 (OCO-2) is the first NASA satellite designed to collect the measurements needed measure atmospheric CO2 with the precision, resolution, and coverage needed to identify and quantify atmospheric sources and sinks on regional scales over the globe. OCO-2 is currently scheduled to launch from Vandenberg Air Force Base at 3 AM 1 July 2014. After a series of maneuvers, OCO-2 will be inserted at the head of the 705-km Afternoon Constellation (A-Train), about 6 minutes ahead of the GCOM-W1 satellite. OCO-2 will fly along a ground track that is displaced 217.3 km to the east of the World Reference System-2 (WRS-2) track followed by the NASA Aqua platform, such that it overflies the ground footprints of the CloudSat radar and the CALIPSO lidar. The OCO-2 spacecraft carries a single instrument that incorporates three, high-resolution, imaging spectrometers designed to measure the absorption of reflected sunlight by CO2 and O2. This instrument will collect about 1,000,000 soundings over the sunlit hemisphere each day. Rigorous instrument characterization has been completed to verify that it will meet requirements for sensitivity, with a high signal to noise ratio, large dynamic range, over a small sounding footprint (< 3 km2) that will enable OCO-2 to determine CO2 concentrations at regional scales with better that 1 ppm uncertainty. These capabilities have been incorporated into the main data processing and retrieval software for testing. This paper will describe pre-launch plans for testing both based on simulations and with the continuing data stream from the Japanese GOSAT instrument. We describe post-launch plans to further down-select the 1,000,000 soundings to those for immediate processing, user help in data quality assessment, and the schedule for data release to the science community.

The Orbiting Carbon Observatory - 2 (OCO-2) Mission and Preparation for 2014 Launch

NASA Astrophysics Data System (ADS)

Eldering, Annmarie; Gunson, Michael; Crisp, David

2014-05-01

The Orbiting Carbon Observatory-2 (OCO-2) is the first NASA satellite designed to collect the measurements needed measure atmospheric CO2 with the precision, resolution, and coverage needed to identify and quantify atmospheric sources and sinks on regional scales over the globe. OCO-2 is currently scheduled to launch from Vandenberg Air Force Base at 3 AM 1 July 2014. After a series of maneuvers, OCO-2 will be inserted at the head of the 705-km Afternoon Constellation (A-Train), about 6 minutes ahead of the GCOM-W1 satellite. OCO-2 will fly along a ground track that is displaced 217.3 km to the east of the World Reference System-2 (WRS-2) track followed by the NASA Aqua platform, such that it overflies the ground footprints of the CloudSat radar and the CALIPSO lidar. The OCO-2 spacecraft carries a single instrument that incorporates three, high-resolution, imaging spectrometers designed to measure the absorption of reflected sunlight by CO2 and O2. This instrument will collect about 1,000,000 soundings over the sunlit hemisphere each day. Rigorous instrument characterization has been completed to verify that it will meet requirements for sensitivity, with a high signal to noise ratio, large dynamic range, over a small sounding footprint (< 3 km2) that will enable OCO-2 to determine CO2 concentrations at regional scales with better that 1 ppm uncertainty. These capabilities have been incorporated into the main data processing and retrieval software for testing. This paper will describe pre-launch plans for testing both based on simulations and with the continuing data stream from the Japanese GOSAT instrument. We describe post-launch plans to further down-select the 1,000,000 soundings to those for immediate processing, user help in data quality assessment, and the schedule for data release to the science community.

Accuracy of Geophysical Parameters Derived from AIRS/AMSU as a Function of Fractional Cloud Cover

NASA Technical Reports Server (NTRS)

Susskind, Joel; Barnet, Chris; Blaisdell, John; Iredell, Lena; Keita, Fricky; Kouvaris, Lou; Molnar, Gyula; Chahine, Moustafa

2006-01-01

AIRS was launched on EOS Aqua on May 4,2002, together with AMSU A and HSB, to form a next generation polar orbiting infrared and microwave atmospheric sounding system. The primary products of AIRS/AMSU are twice daily global fields of atmospheric temperature-humidity profiles, ozone profiles, sea/land surface skin temperature, and cloud related parameters including OLR. The sounding goals of AIRS are to produce 1 km tropospheric layer mean temperatures with an rms error of lK, and layer precipitable water with an rms error of 20 percent, in cases with up to 80 percent effective cloud cover. The basic theory used to analyze Atmospheric InfraRed Sounder/Advanced Microwave Sounding Unit/Humidity Sounder Brazil (AIRS/AMSU/HSB) data in the presence of clouds, called the at-launch algorithm, was described previously. Pre-launch simulation studies using this algorithm indicated that these results should be achievable. Some modifications have been made to the at-launch retrieval algorithm as described in this paper. Sample fields of parameters retrieved from AIRS/AMSU/HSB data are presented and validated as a function of retrieved fractional cloud cover. As in simulation, the degradation of retrieval accuracy with increasing cloud cover is small and the RMS accuracy of lower tropospheric temperature retrieved with 80 percent cloud cover is about 0.5 K poorer than for clear cases. HSB failed in February 2003, and consequently HSB channel radiances are not used in the results shown in this paper. The AIRS/AMSU retrieval algorithm described in this paper, called Version 4, become operational at the Goddard DAAC (Distributed Active Archive Center) in April 2003 and is being used to analyze near-real time AIRS/AMSU data. Historical AIRS/AMSU data, going backwards from March 2005 through September 2002, is also being analyzed by the DAAC using the Version 4 algorithm.

Pre-Launch Characterization of the Advanced Technology Microwave Sounder (ATMS) on the Joint Polar Satellite System-1 Satellite (JPSS-1)

NASA Astrophysics Data System (ADS)

Kim, Edward; Leslie, Vince; Lyu, Joseph; Smith, Craig; McCormick, Lisa; Anderson, Kent

2016-04-01

The Advanced Technology Microwave Sounder (ATMS) is the newest generation of microwave sounder in the international fleet of polar-orbiting weather satellites, replacing the Advanced Microwave Sounding Unit (AMSU) which first entered service in 1998. The first ATMS was launched aboard the Suomi NPP (S-NPP) satellite in late 2011. The second ATMS is manifested on the Joint Polar Satellite System-1 Satellite (JPSS-1). ATMS provides 22 channels of temperature and humidity sounding observations over a frequency range from 23 to 183 GHz. These microwave soundings provide the highest impact data ingested by operational Numerical Weather Prediction (NWP) models, and are the most critical of the polar-orbiting satellite observations, particularly because microwave sensing can penetrate clouds. This paper will present performance characterizations from pre-launch calibration measurements of the JPSS-1 ATMS just completed in December, 2015. The measurements were conducted in a thermal vacuum chamber with blackbody targets simulating cold space, ambient, and a variable Earth scene. They represent the best opportunity for calibration characterization of the instrument since the environment can be carefully controlled. We will present characterizations of the sensitivity (NEDT), accuracy, nonlinearity, noise spectral characteristics, gain stability, repeatability, and inter-channel correlation. An estimate of expected "striping" will be presented, and a discussion of reflector emissivity effects will also be provided. Comparisons will be made with the S-NPP flight unit. Finally, we will describe planned on-orbit characterizations - such as pitch and roll maneuvers - that will further improve both the measurement quality and the understanding of various error contributions.

Shuttle launched flight tests - Supporting technology for planetary entry missions

NASA Technical Reports Server (NTRS)

Vetter, H. C.; Mcneilly, W. R.; Siemers, P. M., III; Nachtsheim, P. R.

1975-01-01

The feasibility of conducting Space Shuttle-launched earth entry flight tests to enhance the technology base for second generation planetary entry missions is examined. Outer planet entry environments are reviewed, translated into earth entry requirements and used to establish entry test system design and cost characteristics. Entry speeds up to those needed to simulate radiative heating levels of more than 30 kW/sq cm are shown to be possible. A standardized recoverable test bed concept is described that is capable of accommodating a wide range of entry technology experiments. The economic advantage of shared Shuttle launches are shown to be achievable through a test system configured to the volume constraints of a single Spacelab pallet using existing propulsion components.

Absolute measurement of the Hugoniot and sound velocity of liquid copper at multimegabar pressures

DOE PAGES

McCoy, Chad August; Knudson, Marcus David; Root, Seth

2017-11-13

Measurement of the Hugoniot and sound velocity provides information on the bulk modulus and Grüneisen parameter of a material at extreme conditions. The capability to launch multilayered (copper/aluminum) flyer plates at velocities in excess of 20 km/s with the Sandia Z accelerator has enabled high-precision sound-velocity measurements at previously inaccessible pressures. For these experiments, the sound velocity of the copper flyer must be accurately known in the multi-Mbar regime. Here we describe the development of copper as an absolutely calibrated sound-velocity standard for high-precision measurements at pressures in excess of 400 GPa. Using multilayered flyer plates, we performed absolute measurementsmore » of the Hugoniot and sound velocity of copper for pressures from 500 to 1200 GPa. These measurements enabled the determination of the Grüneisen parameter for dense liquid copper, clearly showing a density dependence above the melt transition. As a result, combined with earlier data at lower pressures, these results constrain the sound velocity as a function of pressure, enabling the use of copper as a Hugoniot and sound-velocity standard for pressures up to 1200 GPa.« less

Absolute measurement of the Hugoniot and sound velocity of liquid copper at multimegabar pressures

DOE Office of Scientific and Technical Information (OSTI.GOV)

McCoy, Chad August; Knudson, Marcus David; Root, Seth

Measurement of the Hugoniot and sound velocity provides information on the bulk modulus and Grüneisen parameter of a material at extreme conditions. The capability to launch multilayered (copper/aluminum) flyer plates at velocities in excess of 20 km/s with the Sandia Z accelerator has enabled high-precision sound-velocity measurements at previously inaccessible pressures. For these experiments, the sound velocity of the copper flyer must be accurately known in the multi-Mbar regime. Here we describe the development of copper as an absolutely calibrated sound-velocity standard for high-precision measurements at pressures in excess of 400 GPa. Using multilayered flyer plates, we performed absolute measurementsmore » of the Hugoniot and sound velocity of copper for pressures from 500 to 1200 GPa. These measurements enabled the determination of the Grüneisen parameter for dense liquid copper, clearly showing a density dependence above the melt transition. As a result, combined with earlier data at lower pressures, these results constrain the sound velocity as a function of pressure, enabling the use of copper as a Hugoniot and sound-velocity standard for pressures up to 1200 GPa.« less

Evaluation of Transient Pin-Stress Requirements for Spacecraft Launching in Lightning Environments. Pain Free Analysis to Alleviate Those Pin Stress Headaches

NASA Technical Reports Server (NTRS)

Edwards, Paul; Terseck, Alex; Trout, Dawn

2016-01-01

Spacecraft are generally protected from direct lightning attachment by encapsulation within the payload fairing of a launch vehicle and the ground structures that exist at the launch site. Regardless of where lightning strikes, potentially damaging indirect effects prevail from the coupling of electromagnetic fields into a loop created by outer shield of the payload umbilical. The energy coupled into individual spacecraft circuits is dependent on the umbilical current drive, the cable transfer impedance and the source/ load circuitry, and the reference potential used. Lightning induced transient susceptibility of the spacecraft avionics needs to be fully understood in order to define realistic re-test criteria in the event of a lightning occurrence during the launch campaign. Use of standards such as RTCA/DO-160 & SAE 5412 has some applicability but do not represent the indirect environment adequately. This paper evaluates the launch pad environments, the measurement data available, and computer simulations to provide pain-free analysis to alleviate the transient pin-stress headaches for spacecraft launching in Lightning environments.

The law applicable to the use of space for commercial activities

NASA Technical Reports Server (NTRS)

Hosenball, S. N.

1983-01-01

The general principles of space law that have an impact on commercial space activities are discussed. The Outer Space Treaty guaranteed the right of private enterprise in space, with jurisdiction over the participating parties residing in the country of origin. The liability for damages caused to a third party is also assigned to the country of origin. Government consent is necessary in the U.S. before a private firm is permitted to launch an object into space, with the relevant statute sections being part of the Arms Export Control Act; launches are legally treated as exports. FAA regulations define the safe area and flight conditions that must be satisfied for a private launch, although NASA, in the 1958 act which formed the agency, potentialy has the power to regulate space launch activities. The DoD must be notified of any launches in order to notify the U.S.S.R., filings must be made with the Bureau of Alcohol, Tobacco, and Firearms, and fees must be paid to the IRS. It is presently U.S. government policy to encourage and facilitate private sector development of commercial launch services.

Research in X-ray Astronomy

NASA Technical Reports Server (NTRS)

1997-01-01

This research grant supported an active sounding rocket program at Penn State University over a period of over 10 years. During this period, the grant supported at least 8 graduate students in Astronomy & Astrophysics for at least a portion of their research. During the same period, our group was involved in seven sounding rocket flights, launched from White Sands, New Mexico, and from Woomera, Australia. Most of these rocket flights, and most of the work supported by this grant, involved the use of X-ray CCD cameras. The first X-ray CCD camera ever flown in space was our sounding rocket observation of SN1987A (flight 36.030 in 1987). Subsequent flights utilized improved CCD detectors, culminating in the'state-of-the-art EEV detector developed for our CUBIC mission, which was flown on 36.093 last May. Data from the last three flights, which observed the diffuse X-ray background with CCDS, include detection of the OVII He(alpha) line in the high latitude diffuse background and detection of the Mg XI He(alpha) line in the North Polar Spur. These results have been reported at meetings of the American Astronomical Society and the SPIE. The analysis of flights 36.092 and 36.106 is part of Jeff Mendenhall's PhD thesis and will be published in the Astrophysical Journal next year. The 36.093 data are currently being analyzed by PhD student Laura Cawley. From 1990 to 1996 this grant supported our development and launch of the CUBIC instrument on the SAC-B satellite, which was designed to measure the spectrum of the soft X-ray diffuse background with moderate energy resolution and high S/N ratio. Unfortunately, this mission terminated shortly after launch due to a failure of the Pegasus XL launch vehicle. This work resulted in publication of 4 papers in the SPIE Proceedings and four others in refereed journals, in addition to several other conference proceedings and contributed papers. In addition to the CCD flights described above, this grant has supported preliminary development of a new sounding rocket payload utilizing a replicated Ni mirror that is being developed at PSU in collaboration with MSFC. Initial testing of the coating technology has produced promising results.

30 CFR 250.918 - What are the CVA's primary duties during the installation phase?

Code of Federal Regulations, 2014 CFR

2014-07-01

..., DEPARTMENT OF THE INTERIOR OFFSHORE OIL AND GAS AND SULPHUR OPERATIONS IN THE OUTER CONTINENTAL SHELF... location, and review the towing records; (iii) Launching and uprighting operations; (iv) Submergence..., and when the independent monitoring activities were conducted; (2) Describe the CVA's activities...

30 CFR 250.918 - What are the CVA's primary duties during the installation phase?

Code of Federal Regulations, 2011 CFR

2011-07-01

..., AND ENFORCEMENT, DEPARTMENT OF THE INTERIOR OFFSHORE OIL AND GAS AND SULPHUR OPERATIONS IN THE OUTER... specified location, and review the towing records; (iii) Launching and uprighting operations; (iv..., and when the independent monitoring activities were conducted; (2) Describe the CVA's activities...

30 CFR 250.918 - What are the CVA's primary duties during the installation phase?

Code of Federal Regulations, 2012 CFR

2012-07-01

..., DEPARTMENT OF THE INTERIOR OFFSHORE OIL AND GAS AND SULPHUR OPERATIONS IN THE OUTER CONTINENTAL SHELF... location, and review the towing records; (iii) Launching and uprighting operations; (iv) Submergence..., and when the independent monitoring activities were conducted; (2) Describe the CVA's activities...

30 CFR 250.918 - What are the CVA's primary duties during the installation phase?

Code of Federal Regulations, 2013 CFR

2013-07-01

..., DEPARTMENT OF THE INTERIOR OFFSHORE OIL AND GAS AND SULPHUR OPERATIONS IN THE OUTER CONTINENTAL SHELF... location, and review the towing records; (iii) Launching and uprighting operations; (iv) Submergence..., and when the independent monitoring activities were conducted; (2) Describe the CVA's activities...

Saturn Apollo Program

NASA Image and Video Library

1964-03-03

Two technicians apply insulation to the outer surface of the S-II second stage booster for the Saturn V moon rocket. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A view from underneath one of the vertical support posts for NASA's Space Launch System rocket. Two after skirt electrical umbilicals (ASEUs) and the first of the vertical support post were transported by flatbed truck from the Launch Equipment Test Facility to the Mobile Launcher Yard as NASA's Kennedy Space Center in Florida. The ASEUs and the VSP underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

Construction workers assist as a crane is used to lower a vertical support post for NASA's Space Launch System (SLS) onto a platform at the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. Two ASEUs and the first of the vertical support posts underwent a series of tests at the Launch Equipment Test Facility to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

KSC-03PD-2086

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the rover 'Opportunity' for the second Mars Exploration Rover mission is poised for launch after rollback of the Mobile Service Tower. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rovers prime mission is planned to last three months on Mars.

Delta II Heavy MER-B Prelaunch

NASA Image and Video Library

2003-07-07

On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the rover "Opportunity" for the second Mars Exploration Rover mission is poised for launch after rollback of the Mobile Service Tower. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rover’s prime mission is planned to last three months on Mars.

KSC-03PD-2091

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the rover 'Opportunity' for the second Mars Exploration Rover mission launches at 11:18:15 p.m. EDT. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rovers prime mission is planned to last three months on Mars.

KSC-03PD-2090

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. On Launch Complex 17-B, Cape Canaveral Air Force Station, the Delta II Heavy launch vehicle carrying the rover 'Opportunity' for the second Mars Exploration Rover mission launches at 11:18:15 p.m. EDT. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rovers prime mission is planned to last three months on Mars.

Delta II Heavy MER-B - MST Rollback

NASA Image and Video Library

2003-07-07

The Mobile Service Tower is ready to be rolled back at Launch Complex 17-B, Cape Canaveral Air Force Station, to launch the Delta II Heavy launch vehicle carrying the rover "Opportunity" on the second Mars Exploration Rover mission. Opportunity will reach Mars on Jan. 25, 2004. Together the two MER rovers, Spirit (launched June 10) and Opportunity, seek to determine the history of climate and water at two sites on Mars where conditions may once have been favorable to life. The rovers are identical. They will navigate themselves around obstacles as they drive across the Martian surface, traveling up to about 130 feet each Martian day. Each rover carries five scientific instruments including a panoramic camera and microscope, plus a rock abrasion tool that will grind away the outer surfaces of rocks to expose their interiors for examination. Each rover’s prime mission is planned to last three months on Mars.

KSC01pp0784

NASA Image and Video Library

2001-04-11

At the KSC Shuttle Landing Facility, the GOES-M satellite is offloaded from the yawning mouth of the C-5 aircraft. It will be transferred to Astrotech in Titusville, Fla., for final testing. The GOES-M (Geostationary Operational Environmental Satellite, I-M Series) provides weather imagery and quantitative sounding data used to support weather forecasting, severe storm tracking, and meteorological research. The satellite is scheduled to be launched on an Atlas-IIA booster, with a Centaur upper stage, July 12 from Launch Pad 36-A, Cape Canaveral Air Force Station

KSC01pp0785

NASA Image and Video Library

2001-04-11

At the KSC Shuttle Landing Facility, the GOES-M satellite, encased in a container, begins its trek to Astrotech in Titusville, Fla., where it will undergo final testing. The GOES-M (Geostationary Operational Environmental Satellite, I-M Series) provides weather imagery and quantitative sounding data used to support weather forecasting, severe storm tracking, and meteorological research. The satellite is scheduled to be launched on an Atlas-IIA booster, with a Centaur upper stage, July 12 from Launch Pad 36-A, Cape Canaveral Air Force Station

Atmospheric soundings during the Washita 1992 campaign

NASA Technical Reports Server (NTRS)

Brutsaert, W.

1992-01-01

During the period June 9 through June 18, 1992, an intensive radiosounding program was conducted to measure atmospheric profiles of the wind velocity, the temperature and the specific humidity. The launch site was located near site MS000 in the northeastern part of the catchment of the Little Washita River; this location was selected in order to ensure that the measured profiles would reflect the catchment's surface features for the prevailing southwesterly winds during this time of the year. The launch times of the rawinsondes are shown.

Understanding Effects of Traumatic Insults on Brain Structure and Function

DTIC Science & Technology

2016-08-01

42 Fig. 33 The supersonic shock wave at the various distances from its launch. The liposome is located at 117.4 nm. The...For instance, although the pressure front of a shock wave travels at supersonic speeds (the speed of sound in water is 1,497 m/s), the shock wave... supersonic shock wave at the various distances from its launch. The liposome is located at 117.4 nm. The Mach number is 1.49. b) The pressure profile at t

Saturn Apollo Program

NASA Image and Video Library

1965-01-01

Workers at the Marshall Space Flight Center's (MSFC) Dynamic Test Stand install S-IB-200D, a dynamic test version of the Saturn IB launch vehicle's first stage, on January 11, 1965. MSFC Test Laboratory persornel assembled a complete Saturn IB to test the launch vehicle's structural soundness. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine the larger boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

Introduction to AIRS and CrIS

NASA Technical Reports Server (NTRS)

Susskind, Joel

2004-01-01

"Introduction to AIRS and CrIS" is a chapter in a book dealing with various aspects of remote sensing. AIRS and CrIS are both high spectral resolution IR sounding instruments, which were recently launched (AIRS) or will soon be launched (CrIS). The chapter explains the general principles of infra-red remote sensing, and explains the significance and information content of high spectral resolution IR measurements. The chapter shows results obtained using AIRS observations, and explains why similar quality results should be obtainable from CrIS data.

KSC-2014-4382

NASA Image and Video Library

2014-11-04

CAPE CANAVERAL, Fla. – The Orion spacecraft sits inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida. The Ogive panels have been installed around the launch abort system. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The spacecraft is being readied for its move to Space Launch Complex 37 at Cape Canaveral Air Force Station for its flight test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2014-4379

NASA Image and Video Library

2014-11-04

CAPE CANAVERAL, Fla. – The Orion spacecraft sits inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida. The Ogive panels have been installed around the launch abort system. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The spacecraft is being readied for its move to Space Launch Complex 37 at Cape Canaveral Air Force Station for its flight test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2014-4380

NASA Image and Video Library

2014-11-04

CAPE CANAVERAL, Fla. – The Orion spacecraft sits inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida. The Ogive panels have been installed around the launch abort system. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The spacecraft is being readied for its move to Space Launch Complex 37 at Cape Canaveral Air Force Station for its flight test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2014-4384

NASA Image and Video Library

2014-11-04

CAPE CANAVERAL, Fla. – The Orion spacecraft sits inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida. The Ogive panels have been installed around the launch abort system. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The spacecraft is being readied for its move to Space Launch Complex 37 at Cape Canaveral Air Force Station for its flight test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2014-4381

NASA Image and Video Library

2014-11-04

CAPE CANAVERAL, Fla. – The Orion spacecraft sits inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida. The Ogive panels have been installed around the launch abort system. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The spacecraft is being readied for its move to Space Launch Complex 37 at Cape Canaveral Air Force Station for its flight test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2014-4385

NASA Image and Video Library

2014-11-04

CAPE CANAVERAL, Fla. – The Orion spacecraft sits inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida. The Ogive panels have been installed around the launch abort system. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The spacecraft is being readied for its move to Space Launch Complex 37 at Cape Canaveral Air Force Station for its flight test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2014-4249

NASA Image and Video Library

2014-10-12

CAPE CANAVERAL, Fla. – Installation of four Ogive panels on Orion's Launch Abort System continues inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Daniel Casper

KSC-2014-4383

NASA Image and Video Library

2014-11-04

CAPE CANAVERAL, Fla. – The Orion spacecraft sits inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida. The Ogive panels have been installed around the launch abort system. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The spacecraft is being readied for its move to Space Launch Complex 37 at Cape Canaveral Air Force Station for its flight test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

Reacting to nuclear power systems in space: American public protests over outer planetary probes since the 1980s

NASA Astrophysics Data System (ADS)

Launius, Roger D.

2014-03-01

The United States has pioneered the use of nuclear power systems for outer planetary space probes since the 1970s. These systems have enabled the Viking landings to reach the surface of Mars and both Pioneers 10 and 11 and Voyagers 1 and 2 to travel to the limits of the solar system. Although the American public has long been concerned about safety of these systems, in the 1980s a reaction to nuclear accidents - especially the Soviet Cosmos 954 spacecraft destruction and the Three Mile Island nuclear power plant accidents - heightened awareness about the hazards of nuclear power and every spacecraft launch since that time has been contested by opponents of nuclear energy. This has led to a debate over the appropriateness of the use of nuclear power systems for spacecraft. It has also refocused attention on the need for strict systems of control and rigorous checks and balances to assure safety. This essay describes the history of space radioisotope power systems, the struggles to ensure safe operations, and the political confrontation over whether or not to allow the launch the Galileo and Cassini space probes to the outer planets. Effectively, these efforts have led to the successful flights of 12 deep space planetary probes, two-thirds of them operated since the accidents of Cosmos 954, Three Mile Island, and Chernobyl.

30 CFR 250.1165 - What must I do for enhanced recovery operations?

Code of Federal Regulations, 2011 CFR

2011-07-01

... reservoirs where these operations would result in an increase in ultimate recovery of oil or gas under sound... 30 Mineral Resources 2 2011-07-01 2011-07-01 false What must I do for enhanced recovery operations... ENFORCEMENT, DEPARTMENT OF THE INTERIOR OFFSHORE OIL AND GAS AND SULPHUR OPERATIONS IN THE OUTER CONTINENTAL...

KSC-00pp0422

NASA Image and Video Library

2000-03-29

The second stage of an Atlas II/Centaur rocket is raised to a vertical position in front of the gantry on pad 36-A, Cape Canaveral Air Force Station, for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0422

NASA Image and Video Library

2000-03-29

The second stage of an Atlas II/Centaur rocket is raised to a vertical position in front of the gantry on pad 36-A, Cape Canaveral Air Force Station, for mating with the first stage. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC00pp0423

NASA Image and Video Library

2000-03-29

Workers at Cape Canaveral Air Force Station watch as the second stage of an Atlas II/Centaur rocket is raised to a vertical position in front of the gantry on pad 36-A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

KSC-00pp0423

NASA Image and Video Library

2000-03-29

Workers at Cape Canaveral Air Force Station watch as the second stage of an Atlas II/Centaur rocket is raised to a vertical position in front of the gantry on pad 36-A. Atlas II is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. The rocket is the launch vehicle for the GOES-L satellite, part of the NOAA National Weather Service system in weather imagery and atmospheric sounding information. The primary objective of the GOES-L is to provide a full capability satellite in an on-orbit storage condition, to assure NOAA continuity in services from a two-satellite constellation. Launch services are being provided by the 45th Space Wing

Water Deluge Test at Pad 39B

NASA Image and Video Library

2018-05-24

About 450,000 gallons of water flow at high speed from a holding tank through new and modified piping and valves, the flame trench, flame deflector nozzles and mobile launcher interface risers during a wet flow test on May 24, 2018, at Launch Pad 39B at NASA's Kennedy Space Center in Florida. At peak flow, the water reached about 100 feet in the air above the pad surface. The test was performed by Exploration Ground Systems to confirm the performance of the Ignition Overpressure/Sound Suppression system. During launch of NASA's Space Launch System rocket and Orion spacecraft, the high-speed water flow will help protect the vehicle from the extreme acoustic and temperature environment during ignition and liftoff.

KSC-99pp0493

NASA Image and Video Library

1999-05-04

At Astrotech, Titusville, Fla., the fully encapsulated GOES-L weather satellite is ready for transfer to Launch Pad 36A, Cape Canaveral Air Station. The fourth of a new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration (NOAA), GOES-L is a three-axis inertially stabilized spacecraft that will provide pictures and perform atmospheric sounding at the same time. After it is launched, the satellite will undergo checkout and then provide backup capabilities for the existing, aging operational satellites. Once in orbit, the satellite will become GOES-11, joining GOES-8, GOES-9 and GOES-10 in space. The GOES is scheduled for launch aboard a Lockheed Martin Atlas II rocket later in May

KSC-99pp0488

NASA Image and Video Library

1999-05-04

At Astrotech, Titusville, Fla., the GOES-L weather satellite sits on a workstand, ready to be encapsulated for its transfer to Launch Pad 36A, Cape Canaveral Air Station. GOES is scheduled for launch aboard a Lockheed Martin Atlas II rocket later in May. The fourth of a new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration (NOAA), GOES-L is a three-axis inertially stabilized spacecraft that will provide pictures and perform atmospheric sounding at the same time. After it is launched, the satellite will undergo checkout and then provide backup capabilities for the existing, aging operational satellites. Once in orbit, the satellite will become GOES-11, joining GOES-8, GOES-9 and GOES-10 in space

Optical and Acoustic Sensor-Based 3D Ball Motion Estimation for Ball Sport Simulators †.

PubMed

Seo, Sang-Woo; Kim, Myunggyu; Kim, Yejin

2018-04-25

Estimation of the motion of ball-shaped objects is essential for the operation of ball sport simulators. In this paper, we propose an estimation system for 3D ball motion, including speed and angle of projection, by using acoustic vector and infrared (IR) scanning sensors. Our system is comprised of three steps to estimate a ball motion: sound-based ball firing detection, sound source localization, and IR scanning for motion analysis. First, an impulsive sound classification based on the mel-frequency cepstrum and feed-forward neural network is introduced to detect the ball launch sound. An impulsive sound source localization using a 2D microelectromechanical system (MEMS) microphones and delay-and-sum beamforming is presented to estimate the firing position. The time and position of a ball in 3D space is determined from a high-speed infrared scanning method. Our experimental results demonstrate that the estimation of ball motion based on sound allows a wider activity area than similar camera-based methods. Thus, it can be practically applied to various simulations in sports such as soccer and baseball.

Extraterrestrial sound for planetaria: A pedagogical study.

PubMed

Leighton, T G; Banda, N; Berges, B; Joseph, P F; White, P R

2016-08-01

The purpose of this project was to supply an acoustical simulation device to a local planetarium for use in live shows aimed at engaging and inspiring children in science and engineering. The device plays audio simulations of estimates of the sounds produced by natural phenomena to accompany audio-visual presentations and live shows about Venus, Mars, and Titan. Amongst the simulated noise are the sounds of thunder, wind, and cryo-volcanoes. The device can also modify the speech of the presenter (or audience member) in accordance with the underlying physics to reproduce those vocalizations as if they had been produced on the world under discussion. Given that no time series recordings exist of sounds from other worlds, these sounds had to be simulated. The goal was to ensure that the audio simulations were delivered in time for a planetarium's launch show to enable the requested outreach to children. The exercise has also allowed an explanation of the science and engineering behind the creation of the sounds. This has been achieved for young children, and also for older students and undergraduates, who could then debate the limitations of that method.

Solar system 'fast mission' trajectories using aerogravity assist

NASA Technical Reports Server (NTRS)

Randolph, James E.; Mcronald, Angus D.

1992-01-01

Initial analyses of the aerogravity assist (AGA) delivery technique to solar system targets (and beyond) has been encouraging. Mission opportunities are introduced that do not exist with typical gravity assist trajectories and current launch capabilities. The technique has the most payoff for high-energy missions such as outer planet orbiters and flybys. The goal of this technique is to reduce the flight duration significantly and to eliminate propulsion for orbit insertion. The paper will discuss detailed analyses and parametric studies that consider launch opportunities for missions to the sun, Saturn, Uranus, Neptune, and Pluto using AGA at Venus and Mars.

Volume measurement of cryogenic deuterium pellets by Bayesian analysis of single shadowgraphy images

NASA Astrophysics Data System (ADS)

Szepesi, T.; Kálvin, S.; Kocsis, G.; Lang, P. T.; Wittmann, C.

2008-03-01

In situ commissioning of the Blower-gun injector for launching cryogenic deuterium pellets at ASDEX Upgrade tokamak was performed. This injector is designed for high repetitive launch of small pellets for edge localised modes pacing experiments. During the investigation the final injection geometry was simulated with pellets passing to the torus through a 5.5m long guiding tube. For investigation of pellet quality at launch and after tube passage laser flash camera shadowgraphy diagnostic units before and after the tube were installed. As indicator of pellet quality we adopted the pellet mass represented by the volume of the main remaining pellet fragment. Since only two-dimensional (2D) shadow images were obtained, a reconstruction of the full three-dimensional pellet body had to be performed. For this the image was first converted into a 1-bit version prescribing an exact 2D contour. From this contour the expected value of the volume was calculated by Bayesian analysis taking into account the likely cylindrical shape of the pellet. Under appropriate injection conditions sound pellets with more than half of their nominal mass are detected after acceleration; the passage causes in average an additional loss of about 40% to the launched mass. Analyzing pellets arriving at tube exit allowed for deriving the injector's optimized operational conditions. For these more than 90% of the pellets were arriving with sound quality when operating in the frequency range 5-50Hz.

Non-auditory health effects among air force crew chiefs exposed to high level sound.

PubMed

Jensen, Anker; Lund, Søren Peter; Lücke, Thorsten Høgh; Clausen, Ole Voldum; Svendsen, Jørgen Torp

2009-01-01

The possibility of non-auditory health effects in connection with occupational exposure to high level sound is supposed by some researchers, but is still debated. Crew chiefs on airfields are exposed to high-level aircraft sound when working close to aircraft with running engines. We compared their health status with a similar control group who were not subject to this specific sound exposure. Health records of 42 crew chiefs were compared to health records of 42 aircraft mechanics and 17 former crew chiefs. The specific sound exposure of crew chiefs was assessed. The number of reported disease cases was generally small, but generally slightly higher among mechanics than among crew chiefs. Diseases of the ear were more frequent among crew chiefs (not significant). Former crew chiefs reported fewer diseases of the ear and more airways infections (both significant). The sound exposure during launch was up to 144 dB (peak) and 124 dB (L(eq) ), but for limited time. The study did not reveal a higher disease frequency in general among crew chiefs. However, it did reveal a tendency to ear diseases, possibly due to their exposure to high-level sound.

Constraints on the Properties of the Moon's Outer Core from High-Pressure Sound Velocity Measurements on Fe-S Liquids

NASA Astrophysics Data System (ADS)

Jing, Z.; Wang, Y.; Kono, Y.; Yu, T.; Sakamaki, T.; Park, C.; Rivers, M. L.; Sutton, S. R.; Shen, G.

2013-12-01

Geophysical observations based on lunar seismology and laser ranging strongly suggest that the Moon's iron core is partially molten. Similar to Earth and other terrestrial planets, light elements, such as sulfur, silicon, carbon, and oxygen, are likely present in the lunar core. Determining the light element concentration in the outer core is of vital importance to the understanding of the structure, dynamics, and chemical evolution of the Moon, as well as the enigmatic history of the lunar dynamo. Among the candidate elements, sulfur is the preferred major light element in the lunar outer due to its high abundance in the parent bodies of iron meteorites, its high solubility in liquid Fe at the lunar core pressure (~5 GPa), and its strong effects on reducing the density, velocity, and freezing temperature of the core. In this study, we conducted in-situ sound velocity measurements on liquid samples of four different compositions, including pure Fe, Fe-10wt%S, Fe-20wt%S, and Fe-27wt%S, at pressure and temperature conditions up to 8 GPa and 1973 K (encompassing the entire lunar depth range), using the Kawai-type multi-anvil device at the GSECARS beamline 13-ID-D and the Paris-Edinburgh cell at HPCAT beamline 16-BM-B. Our results show that the velocity of Fe-rich liquids increases upon compression, decreases with increasing sulfur content, and is nearly independent of temperature. Compared to the seismic velocity of the outer core, our velocity data constrain the sulfur content at 4×2 wt%, indicating a significantly denser (6.4×0.4 g/cm3) and hotter (1860×60 K) outer core than previously estimated. A new lunar structure model incorporating available geophysical observations points to a smaller core radius. Our model also suggests a top-down solidification scenario for the evolution of the lunar core. Such an 'iron snow' process may have been an important mechanism for the growth of the inner core.

New Cosmic Horizons: Space Astronomy from the V2 to the Hubble Space Telescope

NASA Astrophysics Data System (ADS)

Leverington, David

2001-02-01

Preface; 1. The sounding rocket era; 2. The start of the space race; 3. Initial exploration of the Solar System; 4. Lunar exploration; 5. Mars and Venus; early results; 6. Mars and Venus; the middle period; 7. Venus, Mars and cometary spacecraft post-1980; 8. Early missions to the outer planets; 9. The Voyager missions to the outer planets; 10. The Sun; 11. Early spacecraft observations of non-solar system sources; 12. A period of rapid growth; 13. The high energy astronomy observatory programme; 14. IUE, IRAS and Exosat - spacecraft for the early 1980s; 15. Hiatus; 16. Business as usual; 17. The Hubble Space Telescope.

Rockets Launched from NASA’s Wallops Flight Facility

NASA Image and Video Library

2015-02-24

NASA’s Wallops Flight Facility supported the successful launch of three Terrier-Oriole suborbital rockets for the Department of Defense between 2:30 and 2:31 a.m. today, Feb. 24, from NASA’s launch range on the Eastern Shore of Virginia. The next launch from the Wallops Flight Facility is a NASA Terrier-Improved Malemute suborbital sounding rocket between 6 and 9 a.m. on March 27. The rocket will be carrying the Rocksat-X payload carrying university student developed experiments. Credit: NASA/Alison Stancil NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

KSC-08pd2291

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment (MULE) carrier arrives at the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

Planetary quarantine. Space research and technology

NASA Technical Reports Server (NTRS)

1973-01-01

The impact of satisfying satellite quarantine constraints on outer planet missions and spacecraft design are studied by considering the effects of planetary radiation belts, solar wind radiation, and space vacuum on microorganism survival. Post launch recontamination studies evaluate the effects of mission environments on particle distributions on spacecraft surfaces and effective cleaning and decontamination techniques.

A Space Based Internet Protocol System for Sub-Orbital Tracking and Control

NASA Technical Reports Server (NTRS)

Bull, Barton; Grant, Charles; Morgan, Dwayne; Streich, Ron; Bauer, Frank (Technical Monitor)

2001-01-01

Personnel from the Goddard Space Flight Center Wallops Flight Facility (GSFC/WFF) in Virginia are responsible for the overall management of the NASA Sounding Rocket Program. Payloads are generally in support of NASA's Space Science Enterprise's missions and return a variety of scientific data as well as providing a reasonably economical means of conducting engineering tests for instruments and devices used on satellites and other spacecraft. The fifteen types of sounding rockets used by NASA can carry payloads of various weights to altitudes from 50 km to more than 1,300 km. Launch activities are conducted not only from established missile ranges, but also from remote locations worldwide requiring mobile tracking and command equipment to be transported and set up at considerable expense. The advent of low earth orbit (LEO) commercial communications satellites provides an opportunity to dramatically reduce tracking and control costs of launch vehicles and Unpiloted Aerial Vehicles (UAVs) by reducing or eliminating this ground infrastructure. Additionally, since data transmission is by packetized Internet Protocol (IP), data can be received and commands initiated from practically any location. A low cost Commercial Off The Shelf (COTS) system is currently under development for sounding rockets which also has application to UAVs and scientific balloons. Due to relatively low data rate (9600 baud) currently available, the system will first be used to provide GPS data for tracking and vehicle recovery. Range safety requirements for launch vehicles usually stipulate at least two independent tracking sources. Most sounding rockets flown by NASA now carry GPS receivers that output position data via the payload telemetry system to the ground station. The Flight Modem can be configured as a completely separate link thereby eliminating requirement for tracking radar. The system architecture which integrates antennas, GPS receiver, commercial satellite packet data modem, and a single board computer with custom software is described along with the technical challenges and the plan for their resolution. These include antenna development, high Doppler rates, reliability, environmental ruggedness, hand over between satellites and data security. An aggressive test plan is included which in addition to environmental testing measures bit error rate, latency and antenna patterns. Actual flight tests are planned for the near future on aircraft, long duration balloons and sounding rockets and these results as well as the current status of the project are reported.

Lymphocytes on sounding rocket flights.

PubMed

Cogoli-Greuter, M; Pippia, P; Sciola, L; Cogoli, A

1994-05-01

Cell-cell interactions and the formation of cell aggregates are important events in the mitogen-induced lymphocyte activation. The fact that the formation of cell aggregates is only slightly reduced in microgravity suggests that cells are moving and interacting also in space, but direct evidence was still lacking. Here we report on two experiments carried out on a flight of the sounding rocket MAXUS 1B, launched in November 1992 from the base of Esrange in Sweden. The rocket reached the altitude of 716 km and provided 12.5 min of microgravity conditions.

ADEPT SR-1 Flight Experiment

NASA Technical Reports Server (NTRS)

Wercinski, Paul F.

2017-01-01

The ADEPT architecture represents a completely new approach for entry vehicle design using a high-performance carbon fabric to serve as the primary drag surface of the mechanically deployed decelerator and to protect the payload from hypersonic aerothermal heating during entry. The initial system-level development of the nano-ADEPT architecture will culminate in the launch of a 0.7-m deployed diameter ADEPT sounding rocket flight experiment. The SR-1 sounding rocket flight experiment is a critical milestone in the technology maturation plan for ADEPT and will generate performance data on in-space deployment and aerodynamic stability.

Sounding of the Ion Energization Region: Resolving Ambiguities

NASA Technical Reports Server (NTRS)

LaBelle, James

2003-01-01

Dartmouth College provided a single-channel high-frequency wave receiver to the Sounding of the Ion Energization Region: Resolving Ambiguities (SIERRA) rocket experiment launched from Poker Flat, Alaska, in January 2002. The receiver used signals from booms, probes, preamplifiers, and differential amplifiers provided by Cornell University coinvestigators. Output was to a dedicated 5 MHz telemetry link provided by WFF, with a small amount of additional Pulse Code Modulation (PCM) telemetry required for the receiver gain information. We also performed preliminary analysis of the data. The work completed is outlined below, in chronological order.

A FPGA Implementation of the CAR-FAC Cochlear Model.

PubMed

Xu, Ying; Thakur, Chetan S; Singh, Ram K; Hamilton, Tara Julia; Wang, Runchun M; van Schaik, André

2018-01-01

This paper presents a digital implementation of the Cascade of Asymmetric Resonators with Fast-Acting Compression (CAR-FAC) cochlear model. The CAR part simulates the basilar membrane's (BM) response to sound. The FAC part models the outer hair cell (OHC), the inner hair cell (IHC), and the medial olivocochlear efferent system functions. The FAC feeds back to the CAR by moving the poles and zeros of the CAR resonators automatically. We have implemented a 70-section, 44.1 kHz sampling rate CAR-FAC system on an Altera Cyclone V Field Programmable Gate Array (FPGA) with 18% ALM utilization by using time-multiplexing and pipeline parallelizing techniques and present measurement results here. The fully digital reconfigurable CAR-FAC system is stable, scalable, easy to use, and provides an excellent input stage to more complex machine hearing tasks such as sound localization, sound segregation, speech recognition, and so on.

A FPGA Implementation of the CAR-FAC Cochlear Model

PubMed Central

Xu, Ying; Thakur, Chetan S.; Singh, Ram K.; Hamilton, Tara Julia; Wang, Runchun M.; van Schaik, André

2018-01-01

This paper presents a digital implementation of the Cascade of Asymmetric Resonators with Fast-Acting Compression (CAR-FAC) cochlear model. The CAR part simulates the basilar membrane's (BM) response to sound. The FAC part models the outer hair cell (OHC), the inner hair cell (IHC), and the medial olivocochlear efferent system functions. The FAC feeds back to the CAR by moving the poles and zeros of the CAR resonators automatically. We have implemented a 70-section, 44.1 kHz sampling rate CAR-FAC system on an Altera Cyclone V Field Programmable Gate Array (FPGA) with 18% ALM utilization by using time-multiplexing and pipeline parallelizing techniques and present measurement results here. The fully digital reconfigurable CAR-FAC system is stable, scalable, easy to use, and provides an excellent input stage to more complex machine hearing tasks such as sound localization, sound segregation, speech recognition, and so on. PMID:29692700

On the interaction of a vibrating plate with an acoustic medium

NASA Technical Reports Server (NTRS)

Mixson, J. S.; Koval, L. R.

1974-01-01

The interaction of a vibrating plate with an adjacent acoustic medium is important in problems involving the radiation of sound from panels, in problems involving the transmission of sound through walls of buildings, aircraft, or launch vehicles; and in problems involving the estimation of damping and the stress amplitude of vibration for panel-fatigue predictions. There appear to have been no systematic studies of the effects on the plate of fluid coupling for an arbitrary fluid-mass/plate-mass loading ratio. An attempt is made to determine this effect for a wide range of fluid-plate mass ratios without resorting to the usual simplifications of light or heavy fluid loading. Emphasis is with the plate motion rather than the radiation of sound.

Sound from apollo rockets in space.

PubMed

Cotten, D; Donn, W L

1971-02-12

Low-frequency sound has been recorded on at least two occasions in Bermuda with the passage of Apollo rocket vehicles 188 kilometers aloft. The signals, which are reminiscent of N-waves from sonic booms, are (i) horizontally coherent; (ii) have extremely high (supersonic) trace velocities across the tripartite arrays; (iii) have nearly identical appearance and frequencies; (iv) have essentially identical arrival times after rocket launch; and (v) are the only coherent signals recorded over many hours. These observations seem to establish that the recorded sound comes from the rockets at high elevation. Despite this high elevation, the values of surface pressure appear to be explainable on the basis of a combination of a kinetic theory approach to shock formation in rarefied atmospheres with established gas-dynamics shock theory.

Modeling of "Stripe" Wave Phenomena Seen by the CHARM II and ACES Sounding Rockets

NASA Astrophysics Data System (ADS)

Dombrowski, M. P.; Labelle, J. W.

2010-12-01

Two recent sounding-rocket missions—CHARM II and ACES—have been launched from Poker Flat Research Range, carrying the Dartmouth High-Frequency Experiment (HFE) among their primary instruments. The HFE is a receiver system which effectively yields continuous (100% duty cycle) E-field waveform measurements up to 5 MHz. The CHARM II sounding rocket was launched 9:49 UT on 15 February 2010 into a substorm, while the ACES mission consisted of two rockets, launched into quiet aurora at 9:49 and 9:50 UT on 29 January 2009. At approximately 350 km on CHARM II and the ACES High-Flyer, the HFE detected short (~2s) bursts of broadband (200-500 kHz) noise with a 'stripe' pattern of nulls imposed on it. These nulls have 10 to 20 kHz width and spacing, and many show a regular, non-linear frequency-time relation. These events are different from the 'stripes' discussed by Samara and LaBelle [2006] and Colpitts et al. [2010], because of the density of the stripes, the non-linearity, and the appearance of being an absorptive rather than emissive phenomenon. These events are similar to 'stripe' features reported by Brittain et al. [1983] in the VLF range, explained as an interference pattern between a downward-traveling whistler-mode wave and its reflection off the bottom of the ionosphere. Following their analysis method, we modeled our stripes as higher-frequency interfering whistlers reflecting off of a density gradient. This model predicts the near-hyperbolic frequency-time curves and high density of the nulls, and therefore shows promise at explaining the new observations.

Anechoic chamber in industrial plants. [construction materials and structural design

NASA Technical Reports Server (NTRS)

Halpert, E.; Juncu, O.; Lorian, R.; Marfievici, D.; Mararu, I.

1974-01-01

A light anechoic chamber for routine acoustical measurements in the machine building industry is reported. The outer housing of the chamber consists of modules cast in glass fiber reinforced polyester resin; the inner housing consists of pyramidal modules cut out of sound absorbing slates. The parameters of this anechoic chamber facilitate acoustical measurements according to ISO and CAEM recommendations.

33 CFR 110.140 - Buzzards Bay, Nantucket Sound, and adjacent waters, Mass.

Code of Federal Regulations, 2011 CFR

2011-07-01

...) New Bedford Outer Harbor—(1) Anchorage A. West of Sconticut Neck, and shoreward of a line described as...° to Sconticut Neck. (2) Anchorage B. Southeast of a line ranging 222° from the southwest corner of...; and south of a line bearing 270° from Wings Neck Light. Each vessel must obtain permission to proceed...

50 CFR Table 16 to Part 679 - Area Codes and Descriptions for Use With State of Alaska ADF&G Commercial Operator's Annual...

Code of Federal Regulations, 2011 CFR

2011-10-01

... Shrimp Outer Cook Inlet Shrimp Dungeness Crab King Crab Tanner Crab Miscellaneous Shellfish Salmon HH H H...) (K) GroundfishHerring King Crab Salmon Shrimp Dungeness Crab Tanner Crab Miscellaneous Shellfish KK K... 04.100 Prince William Sound (E) GroundfishHerring Shrimp Dungeness Crab King Crab Tanner Crab...

Strain history of ice shells of the Galilean satellites from radar detection of crystal orientation fabric

NASA Astrophysics Data System (ADS)

Barr, Amy C.; Stillman, David E.

2011-03-01

Orbital radar sounding has been suggested as a means of determining the subsurface thermal and physical structure of the outer ice I shells of the Galilean satellites. At radar frequencies, the dielectric permittivity of single- and polycrystalline water ice I is anisotropic. Crystal orientation fabric (COF), which is indicative of strain history, can be unambiguously detected by comparing the received power of dual co-polarization (linear polarization parallel and perpendicular to the orbit) radar data. Regions with crystal orientations dictated by the local strain field (“fabric”) form in terrestrial ice masses where accumulated strain and temperature are high, similar to conditions expected in a convecting outer ice I shell on Europa, Ganymede, or Callisto. We use simulations of solid-state ice shell convection to show that crystal orientation fabric can form in the warm convecting sublayer of the ice shells for plausible grain sizes. Changes in received power from parallel and perpendicular polarizations in the ice shells due to fabric could be detected if multi-polarization data is collected. With proper instrument design, radar sounding could be used to shed light on the strain history of the satellites' ice shells in addition to their present day internal structures.

Bowhead whale acoustic activity in the southeast Beaufort Sea during late summer 2008-2010.

PubMed

Charif, Russell A; Rahaman, Ashakur; Muirhead, Charles A; Pitzrick, Michael S; Warde, Ann M; Hall, James; Pyć, Cynthia; Clark, Christopher W

2013-12-01

Autonomous passive acoustic recorders were deployed to record sounds of bowhead whales (Balaena mysticetus) in the southeast Beaufort Sea for periods of 30-55 days during the late summer, open-water seasons of 2008-2010. Recordings were made in three areas licensed for hydrocarbon exploration, spanning the continental slope and adjacent outer shelf, and in a shallow inner-shelf area where bowheads have been observed congregating to feed in recent decades. Bowhead sounds were counted in samples comprising 10% of each recorded hour. In mid-August and September in all 3 years, the rate of bowhead calling at outer shelf sites exceeded that at adjacent continental slope sites by one to two orders of magnitude. Higher rates of calling occurred on the slope in late July and early August than at later dates. Calling rates varied by an order of magnitude between years in the one area that was monitored in different years. The highest rates of calling occurred on the inner shelf, offshore of the northern Tuktoyaktuk Peninsula. These trends are consistent with patterns of habitat use previously reported from aerial surveys in this and nearby areas of the Beaufort Sea and with the results of satellite tagging studies.

The George C. Marshall Space Flight Center's 14 X 14-Inch Trisonic Wind Tunnel: A Historical Perspective

NASA Technical Reports Server (NTRS)

Springer, A.

1994-01-01

A history of the National Aeronautics and Space Administration (NASA) George C. Marshall Space Flight Center's (MSFC) 14 x 14-Inch Trisonic Wind Tunnel is presented. Its early and continuing role in the United States space program is shown through highlights of the tunnel's history and the major programs tested in the tunnel over the past 40 years. The 14-Inch Tunnel has its beginning with the Army in the late 1950's under the Army Ballistic Missile Agency (ABMA). Such programs as the Redstone, Jupiter, Pershing, and early Saturn were tested in the 14-Inch Tunnel in the late 1950's. America's first launch vehicle, the Jupiter C, was designed and developed using the 14-Inch Wind Tunnel. Under NASA, the 14-Inch Wind Tunnel has made large contributions to the Saturn, Space Transportation System, and future launch vehicle programs such as Shuttle-C and the National Launch System. A technical description of the tunnel is presented for background information on the type and capabilities of the 14-Inch Wind Tunnel. The report concludes in stating: the 14-Inch Wind Tunnel as in speed of sound; transonic, at or near the speed of sound the past, will continue to play a large but unseen role in he development of America's space program.

Detection and modeling of the acoustic perturbation produced by the launch of the Space Shuttle using the Global Positioning System

NASA Astrophysics Data System (ADS)

Bowling, T. J.; Calais, E.; Dautermann, T.

2010-12-01

Rocket launches are known to produce infrasonic pressure waves that propagate into the ionosphere where coupling between electrons and neutral particles induces fluctuations in ionospheric electron density observable in GPS measurements. We have detected ionospheric perturbations following the launch of space shuttle Atlantis on 11 May 2009 using an array of continually operating GPS stations across the Southeastern coast of the United States and in the Caribbean. Detections are prominent to the south of the westward shuttle trajectory in the area of maximum coupling between the acoustic wave and Earth’s magnetic field, move at speeds consistent with the speed of sound, and show coherency between stations covering a large geographic range. We model the perturbation as an explosive source located at the point of closest approach between the shuttle path and each sub-ionospheric point. The neutral pressure wave is propagated using ray tracing, resultant changes in electron density are calculated at points of intersection between rays and satellite-to-reciever line-of-sight, and synthetic integrated electron content values are derived. Arrival times of the observed and synthesized waveforms match closely, with discrepancies related to errors in the apriori sound speed model used for ray tracing. Current work includes the estimation of source location and energy.

The Ares I-1 Flight Test--Paving the Road for the Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Davis, Stephan R.; Tinker, Michael L.; Tuma, Meg

2007-01-01

In accordance with the U.S. Vision for Space Exploration and the nation's desire to again send humans to explore beyond Earth orbit, NASA has been tasked to send human beings to the moon, Mars, and beyond. It has been 30 years since the United States last designed and built a human-rated launch vehicle. NASA is now building the Ares I crew launch vehicle, which will loft the Orion crew exploration vehicle into orbit, and the Ares V cargo launch vehicle, which will launch the Lunar Surface Access Module and Earth departure stage to rendezvous Orion for missions to the moon. NASA has marshaled unique resources from the government and private sectors to perform the technically and programmatically complex work of delivering astronauts to orbit early next decade, followed by heavy cargo late next decade. Our experiences with Saturn and the Shuttle have taught us the value of adhering to sound systems engineering, such as the "test as you fly" principle, while applying aerospace best practices and lessons learned. If we are to fly humans safely aboard a launch vehicle, we must employ a variety of methodologies to reduce the technical, schedule, and cost risks inherent in the complex business of space transportation. During the Saturn development effort, NASA conducted multiple demonstration and verification flight tests to prove technology in its operating environment before relying upon it for human spaceflight. Less testing on the integrated Shuttle system did not reduce cost or schedule. NASA plans a progressive series of demonstration (ascent), verification (orbital), and mission flight tests to supplement ground research and high-altitude subsystem testing with real-world data, factoring the results of each test into the next one. In this way, sophisticated analytical models and tools, many of which were not available during Saturn and Shuttle, will be calibrated and we will gain confidence in their predictions, as we gain hands-on experience in operating the first of two new launch vehicle systems. The Ares I-1 flight test vehicle (FTV) will incorporate a mix of flight and mockup hardware, reflecting a configuration similar in mass, weight, and shape (outer mold line or OML) to the operational vehicle. It will be powered by a four-segment reusable solid rocket booster (RSRB), which is currently in Shuttle inventory, and will be modified to include a fifth, inert segment that makes it approximately the same size and weight as the five segment RSRB, which will be available for the second flight test in 2012. The Ares I-1 vehicle configuration is shown. Each test flight has specific objectives appropriate to the design analysis cycle in progress. The Ares I-1 demonstration test, slated for April 2009, gives NASA its first opportunity to gather critical data about the flight dynamics of the integrated launch vehicle stack, understand how to control its roll during flight, and other characterize the severe stage separation environment that the upper stage will experience during future operational flights. NASA also will begin the process of modifying the launch infrastructure and fine-tuning ground and mission operational scenarios, as NASA transitions from the Shuttle to the Ares/Orion system.

Ares I-X Flight Test Vehicle Similitude to the Ares I Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Huebner, Lawrence D.; Smith, R. Marshall; Campbell, John R., Jr.; Taylor, Terry L.

2008-01-01

The Ares I-X Flight Test Vehicle is the first in a series of flight test vehicles that will take the Ares I Crew Launch Vehicle design from development to operational capability. The test flight is scheduled for April 2009, relatively early in the Ares I design process so that data obtained from the flight can impact the design of Ares I before its Critical Design Review. Because of the short time frame (relative to new launch vehicle development) before the Ares I-X flight, decisions about the flight test vehicle design had to be made in order to complete analysis and testing in time to manufacture the Ares I-X vehicle hardware elements. This paper describes the similarities and differences between the Ares I-X Flight Test Vehicle and the Ares I Crew Launch Vehicle. Areas of comparison include the outer mold line geometry, aerosciences, trajectory, structural modes, flight control architecture, separation sequence, and relevant element differences. Most of the outer mold line differences present between Ares I and Ares I-X are minor and will not have a significant effect on overall vehicle performance. The most significant impacts are related to the geometric differences in Orion Crew Exploration Vehicle at the forward end of the stack. These physical differences will cause differences in the flow physics in these areas. Even with these differences, the Ares I-X flight test is poised to meet all five primary objectives and six secondary objectives. Knowledge of what the Ares I-X flight test will provide in similitude to Ares I as well as what the test will not provide is important in the continued execution of the Ares I-X mission leading to its flight and the continued design and development of Ares I.

The Academy of Sciences stakes a claim

NASA Technical Reports Server (NTRS)

1980-01-01

The establishment of the National Committe for the International Geophysical year is described. Post-war development of the 1950's in the areas of upper atmosphere research reviewed and included: the further development of satellites; sounding rocket research; and the launching of the Sputnik Satellites.

ADEPT Sounding Rocket One (SR-1)Flight Experiment Overview

NASA Technical Reports Server (NTRS)

Wercinski, Paul; Smith, B.; Yount, B.; Cassell, A.; Kruger, C.; Brivkalns, C.; Makino, A.; Duttta, S.; Ghassemieh, S.; Wu, S.;

Examination of Cross-Scale Coupling During Auroral Events using RENU2 and ISINGLASS Sounding Rocket Data.

NASA Astrophysics Data System (ADS)

Kenward, D. R.; Lessard, M.; Lynch, K. A.; Hysell, D. L.; Hampton, D. L.; Michell, R.; Samara, M.; Varney, R. H.; Oksavik, K.; Clausen, L. B. N.; Hecht, J. H.; Clemmons, J. H.; Fritz, B.

2017-12-01

The RENU2 sounding rocket (launched from Andoya rocket range on December 13th, 2015) observed Poleward Moving Auroral Forms within the dayside cusp. The ISINGLASS rockets (launched from Poker Flat rocket range on February 22, 2017 and March 2, 2017) both observed aurora during a substorm event. Despite observing very different events, both campaigns witnessed a high degree of small scale structuring within the larger auroral boundary, including Alfvenic signatures. These observations suggest a method of coupling large-scale energy input to fine scale structures within aurorae. During RENU2, small (sub-km) scale drivers persist for long (10s of minutes) time scales and result in large scale ionospheric (thermal electron) and thermospheric response (neutral upwelling). ISINGLASS observations show small scale drivers, but with short (minute) time scales, with ionospheric response characterized by the flight's thermal electron instrument (ERPA). The comparison of the two flights provides an excellent opportunity to examine ionospheric and thermospheric response to small scale drivers over different integration times.

Sounding rocket flight report: MUMP 9 and MUMP 10

NASA Technical Reports Server (NTRS)

Grassl, H. J.

1971-01-01

The results of the launching of two Marshall-University of Michigan Probes (MUMP 9 and MUMP 10), Nike-Tomahawk sounding rocket payloads, are summarized. The MUMP 9 paylaod included an omegatron mass analyzer, a molecular fluorescence densitometer, a mini-tilty filter, and a lunar position sensor. This complement of instruments permitted the determination of the molecular nitrogen density and temperature in the altitude range from approximately 143 to 297 km over Wallops Island, Virginia, during January 1971. The MUMP 10 payload included an omegatron mass analyzer, an electron temperature probe (Spencer, Brace, and Carignan, 1962), a cryogenic densitometer, and a solar position sensor. This complement of instruments permitted the determination of the molecular nitrogen density and temperature and the charged particle density and temperature in the altitude range from approximately 145 to 290 km over Wallops Island, Virginia, during the afternoon preceding the MUMP 9 launch in January 1971. A general description of the payload kinematics, orientation analysis, and the technique for the reduction and analysis of the data is given.

Sounding rocket flight report, MUMP 9 and MUMP 10

NASA Technical Reports Server (NTRS)

Grassl, H. J.

1971-01-01

The results of the launching of two-Marshall-University of Michigan Probes (MUMP 9 and MUMP 10), Nike-Tomahawk sounding rocket payloads, are summarized. The MUMP is similar to the thermosphere probe, an ejectable instrument package for studying the variability of the earth's atmospheric parameters. The MUMP 9 payload included an omegatron mass analyzer, a molecular fluorescence densitometer, a mini-tilty filter, and a lunar position sensor. This complement of instruments permitted the determination of the molecular nitrogen density and temperature in the altitude range from approximately 143 to 297 km over Wallops Island, Virginia, during January 1971. The MUMP 10 payload included an omegatron mass analyzer, an electron temperature probe, a cryogenic densitometer, and a solar position sensor. These instruments permitted the determination of the molecular nitrogen density and temperature and the charged particle density and temperature in the altitude range from approximately 145 to 290 km over Wallops Island during the afternoon preceding the MUMP 9 launch.

Numerical Estimation of Sound Transmission Loss in Launch Vehicle Payload Fairing

NASA Astrophysics Data System (ADS)

Chandana, Pawan Kumar; Tiwari, Shashi Bhushan; Vukkadala, Kishore Nath

2017-08-01

Coupled acoustic-structural analysis of a typical launch vehicle composite payload faring is carried out, and results are validated with experimental data. Depending on the frequency range of interest, prediction of vibro-acoustic behavior of a structure is usually done using the finite element method, boundary element method or through statistical energy analysis. The present study focuses on low frequency dynamic behavior of a composite payload fairing structure using both coupled and uncoupled vibro-acoustic finite element models up to 710 Hz. A vibro-acoustic model, characterizing the interaction between the fairing structure, air cavity, and satellite, is developed. The external sound pressure levels specified for the payload fairing's acoustic test are considered as external loads for the analysis. Analysis methodology is validated by comparing the interior noise levels with those obtained from full scale Acoustic tests conducted in a reverberation chamber. The present approach has application in the design and optimization of acoustic control mechanisms at lower frequencies.

Nonlinear acoustic propagation of launch vehicle and military jet aircraft noise

NASA Astrophysics Data System (ADS)

Gee, Kent L.

2010-10-01

The noise from launch vehicles and high-performance military jet aircraft has been shown to travel nonlinearly as a result of an amplitude-dependent speed of sound. Because acoustic pressure compressions travel faster than rarefactions, the waveform steepens and shocks form. This process results in a very different (and readily audible) noise signature and spectrum than predicted by linear models. On-going efforts to characterize the nonlinearity using statistical and spectral measures are described with examples from recent static tests of solid rocket boosters and the F-22 Raptor.

Analysis of Phoenix Anomalies and IV and V Findings Applied to the GRAIL Mission

NASA Technical Reports Server (NTRS)

Larson, Steve

2012-01-01

Analysis of patterns in IV&V findings and their correlation with post-launch anomalies allowed GRAIL to make more efficient use of IV&V services . Fewer issues. . Higher fix rate. . Better communication. . Increased volume of potential issues vetted, at lower cost. . Hard to make predictions of post-launch performance based on IV&V findings . Phoenix made sound fix/use as-is decisions . Things that were fixed eliminated some problems, but hard to quantify. . Broad predictive success in one area, but inverse relationship in others.

Impact of Drift on the Vehicle Liftoff Acoustic Environments

NASA Technical Reports Server (NTRS)

Kenny, Jeremy; Giacomoni, Clothilde

2016-01-01

As a launch vehicle lifts off the pad, depending on the flyaway maneuver, it will drift away from the exhaust hole causing the plume(s) to impinge on the launch deck. This impingement on the deck creates acoustic sources and causes the noise levels on the vehicle to increase. The percentage of the plume which impinges on the deck can be calculated and related to sound pressure levels. Using this information, a delta dB can be calculated if the drift or flyaway maneuver for a specific vehicle changes during a program

KSC01pp0783

NASA Image and Video Library

2001-04-11

At the KSC Shuttle Landing Facility, a truck begins offloading the container with the GOES-M satellite from the yawning mouth of the C-5 aircraft. It will be transferred to Astrotech in Titusville, Fla., for final testing. The GOES-M (Geostationary Operational Environmental Satellite, I-M Series) provides weather imagery and quantitative sounding data used to support weather forecasting, severe storm tracking, and meteorological research. The satellite is scheduled to be launched on an Atlas-IIA booster, with a Centaur upper stage, July 12 from Launch Pad 36-A, Cape Canaveral Air Force Station

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

Marshall Space Flight Center (MSFC) workers hoist a dynamic test version of the S-IVB stage, the Saturn IB launch vehicle's second stage, into the Center's Dynamic Test Stand on January 18, 1965. MSFC Test Laboratory persornel assembled a complete Saturn IB to test the launch vehicle's structural soundness. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine the larger boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

Saturn Apollo Program

NASA Image and Video Library

1965-01-01

Marshall Space Flight Center (MSFC) workers lower S-IB-200D, a dynamic test version of the Saturn IB launch vehicle's first stage (S-IB stage), into the Center's Dynamic Test Stand on January 12, 1965. Test Laboratory persornel assembled a complete Saturn IB to test the structural soundness of the launch vehicle. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine large boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

Launch Vehicle Directorate and Centaur Rocket Model

NASA Image and Video Library

1979-05-21

The National Aeronautics and Space Administration (NASA) Lewis Research Center’s Launch Vehicle Directorate in front of a full-scale model of the Centaur second-stage rocket. The photograph was taken to mark Centaur’s fiftieth launch. NASA Lewis managed the Centaur Program since 1962. At that time, the only prior launch attempt ended in failure. Lewis improved the spacecraft and tested it extensively throughout the early 1960s. In May 1966 an Atlas-Centaur sent the Surveyor spacecraft to the moon. It was the first successful soft landing on another planet. The Launch Vehicles Division was formed in 1969 to handle the increasing number of Centaur launches. The Lewis team became experts at integrating the payload with the Centaur and calculating proper trajectories for the missions. Centaur’s first 50 missions included Orbiting Astronomical Observatories, the Mariner 6 and 7 flybys of Mars, Mariner 9 which was the first spacecraft to orbit around another planet, the Pioneer 10 and 11 missions to the outer solar system, the Mariner 10 flyby of Venus and Mercury, the Viking 1 and 2 Mars landers, Voyagers 1 and 2 missions to Jupiter, Saturn, Uranus, and Neptune, and the Pioneer 12 and 13 flights to Venus.

Velocity and bottom-stress measurements in the bottom boundary layer, outer Norton Sound, Alaska.

USGS Publications Warehouse

Cacchione, D.A.; Drake, D.E.; Wiberg, P.

1982-01-01

We have used long-term measurements of near-bottom velocities at four heights above the sea floor in Norton Sound, Alaska, to compute hourly values of shear velocity u., roughness and bottom-drag coefficient. Maximum sediment resuspension and transport, predicted for periods when the computed value of u. exceeds a critical level, occur during peak tidal currents associated with spring tides. The fortnightly variation in u. is correlated with a distinct nepheloid layer that intensifies and thickens during spring tides and diminishes and thins during neap tides. The passage of a storm near the end of the experiment caused significantly higher u. values than those found during fair weather.-from Authros

KSC-2014-4397

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida, preparations are underway to remove the window covers on Orion before the fourth and final Ogive panel is installed around the spacecraft and Launch Abort System. The Ogive panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4259

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, a crane brings the fourth and final Ogive panel closer for installation on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-4251

NASA Image and Video Library

2014-10-12

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians have installed two of the four Ogive panels on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Daniel Casper

KSC-2014-4247

NASA Image and Video Library

2014-10-11

CAPE CANAVERAL, Fla. – The first of four Ogive panels is lifted by crane for installation on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-4400

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, a window cover has been carefully removed from the Orion spacecraft before the fourth and final Ogive panel is installed around the spacecraft and Launch Abort System. The Ogive panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4256

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Technicians on work platforms monitor the progress as a crane brings the third of four Ogive panels closer for installation on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4250

NASA Image and Video Library

2014-10-12

CAPE CANAVERAL, Fla. – Technicians on work platforms continue the installation of four Ogive panels on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Daniel Casper

KSC-2014-4248

NASA Image and Video Library

2014-10-11

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians monitor the progress as a crane moves the first of four Ogive panels closer for installation on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-4255

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida, a crane brings the third of four Ogive panels closer for installation on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4258

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians attach the third of four Ogive panels on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4257

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida, technicians attach the third of four Ogive panels on Orion's Launch Abort System. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4399

NASA Image and Video Library

2014-10-13

CAPE CANAVERAL, Fla. – Inside the Launch Abort System Facility at NASA's Kennedy Space Center in Florida, a technician carefully removes the window covers on Orion before the fourth and final Ogive panel is installed around the spacecraft and Launch Abort System. The Ogive panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Ben Smegelsky

KSC-2014-4246

NASA Image and Video Library

2014-10-11

CAPE CANAVERAL, Fla. – The first of four Ogive panels is lifted by crane for installation on Orion's Launch Abort System inside the Launch Abort System Facility at NASA’s Kennedy Space Center in Florida. The panels will smooth the airflow over the conical spacecraft to limit sound and vibration, which will make for a much smoother ride for the astronauts who will ride inside Orion in the future. The work marked the final major assembly steps for the spacecraft before it is transported to Space Launch Complex 37 at Cape Canaveral Air Force Station in November. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted flight test of Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket, and in 2018 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

Exploring the outer planets

NASA Technical Reports Server (NTRS)

Parks, R. J.

1979-01-01

Initial, current and planned United States projects for the spacecraft exploration of the outer planets of the solar system are presented. Initial plans were developed in the mid-1960's for the exploration of the outer planets by utilizing the gravity-assist technique during a fortuitous alignment of the outer planets in the Grand Tour Project, however although state-of-the-art space technology could have supported the project, it was considered too expensive, therefore politically infeasible. Subsequently, the Pioneer Project was undertaken to explore the asteroid belt and the environment around Jupiter and the Voyager Project was undertaken to send two spacecraft to fly by Jupiter and utilize its gravity assist to reach Saturn. The successful Pioneer 10 and 11 missions have provided important information on the effects of the asteroid belt and the severe radiation environment around Jupiter, and Voyager 1 has collected information about Jupiter, its magnetic fields and radiation zones, and its satellites. Project Galileo is intended to be launched in January 1982 to conduct an intensive investigation of Jupiter, its satellites and immediate environment and a Saturn Orbiter dual probe mission and a Uranus orbiter are also under consideration.

KSC-08pd2516

NASA Image and Video Library

2008-05-31

CAPE CANAVERAL, Fla. – A new NASA helicopter circles space shuttle Discovery on Launch Pad 39A prior to launch on the STS-124 mission. To the left of the shuttle is the fixed service structure with the 80-foot lightning mast on top. The rotating service structure, normally closed around the shuttle, is open for liftoff. At right of the pad is the 300,000-gallon water tower that provides the water used for sound suppression on the pad during liftoff. In the background is the Atlantic Ocean. Discovery is making its 35th flight. The STS-124 mission is the 26th in the assembly of the space station. It is the second of three flights launching components to complete the Japan Aerospace Exploration Agency's Kibo laboratory.

KSC-08pd3182

NASA Image and Video Library

2008-10-14

CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the rising moon stands out alongside the rotating and fixed service structures around space shuttle Atlantis. At left is the 300,000-gallon water tower used for sound suppression during liftoffs. Atlantis’ October target launch date for the STS-125 Hubble Space Telescope servicing mission was delayed after a device on board Hubble used in the storage and transmission of science data to Earth shut down on Sept. 27. Replacing the broken device will be added to Atlantis’ servicing mission to the telescope. In the interim, Atlantis will be rolled back to the Vehicle Assembly Building until a new target launch date can be set for the mission in 2009. Photo credit: NASA/Troy Cryder

Chromospheric Lyman-alpha spectro-polarimeter (CLASP)

NASA Astrophysics Data System (ADS)

Kano, Ryouhei; Bando, Takamasa; Narukage, Noriyuki; Ishikawa, Ryoko; Tsuneta, Saku; Katsukawa, Yukio; Kubo, Masahito; Ishikawa, Shin-nosuke; Hara, Hirohisa; Shimizu, Toshifumi; Suematsu, Yoshinori; Ichimoto, Kiyoshi; Sakao, Taro; Goto, Motoshi; Kato, Yoshiaki; Imada, Shinsuke; Kobayashi, Ken; Holloway, Todd; Winebarger, Amy; Cirtain, Jonathan; De Pontieu, Bart; Casini, Roberto; Trujillo Bueno, Javier; Štepán, Jiří; Manso Sainz, Rafael; Belluzzi, Luca; Asensio Ramos, Andres; Auchère, Frédéric; Carlsson, Mats

2012-09-01

One of the biggest challenges in heliophysics is to decipher the magnetic structure of the solar chromosphere. The importance of measuring the chromospheric magnetic field is due to both the key role the chromosphere plays in energizing and structuring the outer solar atmosphere and the inability of extrapolation of photospheric fields to adequately describe this key boundary region. Over the last few years, significant progress has been made in the spectral line formation of UV lines as well as the MHD modeling of the solar atmosphere. It is found that the Hanle effect in the Lyman-alpha line (121.567 nm) is a most promising diagnostic tool for weaker magnetic fields in the chromosphere and transition region. Based on this groundbreaking research, we propose the Chromospheric Lyman-Alpha Spectro-Polarimeter (CLASP) to NASA as a sounding rocket experiment, for making the first measurement of the linear polarization produced by scattering processes and the Hanle effect in the Lyman-alpha line (121.567 nm), and making the first exploration of the magnetic field in the upper chromosphere and transition region of the Sun. The CLASP instrument consists of a Cassegrain telescope, a rotating 1/2-wave plate, a dual-beam spectrograph assembly with a grating working as a beam splitter, and an identical pair of reflective polarization analyzers each equipped with a CCD camera. We propose to launch CLASP in December 2014.

Space Technology Demo at NASA Wallops

NASA Image and Video Library

2017-12-08

A vapor cloud is seen after launch of a Black Brant IX suborbital sounding rocket, launched at 7:07 p.m., Wednesday October 7, 2015. (NASA Photo/J. Adkins) A Black Brant IX suborbital rocket was launched from NASA's Wallops Flight Facility. The launch occurred at 7:07 p.m. The primary purpose of the flight was to test the performance of the second-stage Black Brant motor. Preliminary indications are that the motor performed as planned. Preliminary data analysis of the technology experiments (vapor tracer deployments) on the payload is in progress. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

KSC-99pp1439

NASA Image and Video Library

1999-12-17

An olivaceous cormorant soars in the cloud-streaked sky near the Space Shuttle Discovery as it waits for liftoff on mission STS-103. To the left of Discovery is the Rotating Service Structure, rolled back on Dec. 16 in preparation for launch. At right is a 290-foot-high water tank with a capacity of 300,000 gallons. The tank is part of the sound suppression water system used during launch. The STS-103 mission, to service the Hubble Space Telescope, is scheduled for launch Dec. 17 at 8:47 p.m. EST from Launch Pad 39B. Mission objectives include replacing gyroscopes and an old computer, installing another solid state recorder, and replacing damaged insulation in the telescope. The mission is expected to last about 8 days and 21 hours. Discovery is expected to land at KSC Sunday, Dec. 26, at about 6:25 p.m. EST

ATK Launch Vehicle (ALV-X1) Liftoff Acoustic Environments: Prediction vs. Measurement

NASA Technical Reports Server (NTRS)

Houston, J.; Counter, Douglas; Kenny, Jeremy; Murphy, John

2010-01-01

Launched from the Mid-Atlantic Regional Spaceport (MARS) Pad 01B on August 22, 2008, the ATK Launch Vehicle (ALV-X1) provided an opportunity to measure liftoff acoustic noise data. Predicted lift-off acoustic environments were developed by both NASA MSFC and ATK engineers. ATK engineers developed predictions for use in determining vibro-acoustic loads using the method described in the monograph NASA SP-8072. The MSFC ALV-X1 lift-off acoustic prediction was made with the Vehicle Acoustic Environment Prediction Program (VAEPP). The VAEPP and SP-8072 methods predict acoustic pressures of rocket systems generally scaled to existing rocket motor data based upon designed motor or engine characteristics. The predicted acoustic pressures are sound-pressure spectra at specific positions on the vehicle. This paper presents the measured liftoff acoustics on the vehicle and tower. This data is useful for the ALV-X1 in validating the pre-launch environments and loads predictions.

27 CFR 447.21 - The U.S. Munitions Import List.

Code of Federal Regulations, 2010 CFR

2010-04-01

...—launch vehicles, guided missiles, ballistic missiles, rockets, torpedoes, bombs and mines (a) Rockets (including but not limited to meteorological and other sounding rockets), bombs, grenades, torpedoes, depth..., the following: Fuses and components for the items in this category, bomb racks and shackles, bomb...

15 CFR 742.5 - Missile technology.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Country Chart (see supplement No. 1 to part 738 of the EAR). (2) The term “missiles” is defined as rocket systems (including ballistic missile systems, space launch vehicles, and sounding rockets) and unmanned... missile and space programs of the recipient country; (iv) The nonproliferation credentials of the...

Uranus science planning. [considering Mariner Jupiter-Uranus mission

NASA Technical Reports Server (NTRS)

Moore, J.

1974-01-01

Recommendations for a 1979 Mariner Jupiter-Uranus mission are discussed with the possibility of launching the first outer planet atmospheric entry probe. Measurement categories considered for the mission include conducting imaging experiments, observations in both the IR and UV spectral range, experiments associated with magnetic fields, plasma, charged particles, and S- and X-band occultation measurements.

Two technicians apply insulation to S-II second stage

NASA Technical Reports Server (NTRS)

1964-01-01

Two technicians apply insulation to the outer surface of the S-II second stage booster for the Saturn V moon rocket. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

Payload Performance Analysis for a Reusable Two-Stage-to-Orbit Vehicle

NASA Technical Reports Server (NTRS)

Tartabini, Paul V.; Beaty, James R.; Lepsch, Roger A.; Gilbert, Michael G.

2015-01-01

This paper investigates a unique approach in the development of a reusable launch vehicle where, instead of designing the vehicle to be reusable from its inception, as was done for the Space Shuttle, an expendable two stage launch vehicle is evolved over time into a reusable launch vehicle. To accomplish this objective, each stage is made reusable by adding the systems necessary to perform functions such as thermal protection and landing, without significantly altering the primary subsystems and outer mold line of the original expendable vehicle. In addition, some of the propellant normally used for ascent is used instead for additional propulsive maneuvers after staging in order to return both stages to the launch site, keep loads within acceptable limits and perform a soft landing. This paper presents a performance analysis that was performed to investigate the feasibility of this approach by quantifying the reduction in payload capability of the original expendable launch vehicle after accounting for the mass additions, trajectory changes and increased propellant requirements necessary for reusability. Results show that it is feasible to return both stages to the launch site with a positive payload capability equal to approximately 50 percent of an equivalent expendable launch vehicle. Further discussion examines the ability to return a crew/cargo capsule to the launch site and presents technical challenges that would have to be overcome.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A flatbed truck carries a vertical support post (VSP) for NASA's Space Launch System (SLS) rocket to the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. The two aft skirt electrical umbilicals (ASEUs) and the first of the vehicle support posts underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

KSC-08pd2290

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment (MULE) carrier is driven from the Canister Rotation Facility to the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center after the shipping container was pressure cleaned. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2315

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, technicians remove the protective cover from the Multi-Use Lightweight Equipment, or MULE, carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2297

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the cover of the shipping container is lifted to reveal the Multi-Use Lightweight Equipment (MULE) carrier inside. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2316

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, a technician removes the protective cover from the Multi-Use Lightweight Equipment, or MULE, carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2312

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Multi-Use Lightweight Equipment, or MULE, carrier toward a stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2314

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, a technician begins removing the protective cover from the Multi-Use Lightweight Equipment, or MULE, carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2298

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, arcane moves the cover of the shipping container away from its cargo, the Multi-Use Lightweight Equipment (MULE) carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2289

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – At the Canister Rotation Facility at NASA's Kennedy Space Center, the shipping container with the Multi-Use Lightweight Equipment (MULE) carrier inside is pressure cleaned after its arrival. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2306

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is waiting to be moved onto another stand in the high bay in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Jack Pfaller

KSC-08pd2313

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the Multi-Use Lightweight Equipment, or MULE, carrier rests on a stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2296

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the cover of the shipping container is lifted to reveal the Multi-Use Lightweight Equipment (MULE) carrier inside. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2305

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is moved into the high bay in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Jack Pfaller

KSC-08pd2311

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Multi-Use Lightweight Equipment, or MULE, carrier toward a stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2317

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is revealed after its protective cover was removed in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2300

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the Multi-Use Lightweight Equipment (MULE) carrier awaits a move into the clean-room high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2292

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – A transporter moves the shipping container with the Multi-Use Lightweight Equipment (MULE) carrier toward the open doors of the airlock in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2304

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is being moved into the high bay in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Jack Pfaller

KSC-08pd2293

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The shipping container with the Multi-Use Lightweight Equipment (MULE) carrier inside is moved into the airlock in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-2012-6229

NASA Image and Video Library

2012-11-14

CAPE CANAVERAL, Fla. – The Orion spacecraft crew access arm, or CAA, seal prototype is being checked out at the Launch Equipment Test Facility at NASA's Kennedy Space Center in Florida. The tests will use a mockup of the vehicle Outer Mold Line and CAA white room to test the performance of the seal while simulating vehicle to CAA white room excursions. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/Jim Grossmann

KSC-2012-6225

NASA Image and Video Library

2012-11-14

CAPE CANAVERAL, Fla. – The Orion spacecraft crew access arm, or CAA, seal prototype is being checked out at the Launch Equipment Test Facility at NASA's Kennedy Space Center in Florida. The tests will use a mockup of the vehicle Outer Mold Line and CAA white room to test the performance of the seal while simulating vehicle to CAA white room excursions. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/Jim Grossmann

KSC-2012-6231

NASA Image and Video Library

2012-11-14

CAPE CANAVERAL, Fla. – The Orion spacecraft crew access arm, or CAA, seal prototype is being checked out at the Launch Equipment Test Facility at NASA's Kennedy Space Center in Florida. The tests will use a mockup of the vehicle Outer Mold Line and CAA white room to test the performance of the seal while simulating vehicle to CAA white room excursions. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/Jim Grossmann

KSC-2012-6226

NASA Image and Video Library

2012-11-14

CAPE CANAVERAL, Fla. – The Orion spacecraft crew access arm, or CAA, seal prototype is being checked out at the Launch Equipment Test Facility at NASA's Kennedy Space Center in Florida. The tests will use a mockup of the vehicle Outer Mold Line and CAA white room to test the performance of the seal while simulating vehicle to CAA white room excursions. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/Jim Grossmann

KSC-2012-6230

NASA Image and Video Library

2012-11-14

CAPE CANAVERAL, Fla. – The Orion spacecraft crew access arm, or CAA, seal prototype is being checked by technicians and engineers at the Launch Equipment Test Facility at NASAs Kennedy Space Center in Florida. The tests will use a mockup of the vehicle Outer Mold Line and CAA white room to assess the performance of the seal while simulating vehicle to CAA white room excursions. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/Jim Grossmann

KSC-2012-6228

NASA Image and Video Library

2012-11-14

CAPE CANAVERAL, Fla. – The Orion spacecraft crew access arm, or CAA, seal prototype is being checked by technicians and engineers at the Launch Equipment Test Facility at NASAs Kennedy Space Center in Florida. The tests will use a mockup of the vehicle Outer Mold Line and CAA white room to assess the performance of the seal while simulating vehicle to CAA white room excursions. Orion is the exploration spacecraft designed to carry crews to space beyond low Earth orbit. It will provide emergency abort capability, sustain the crew during the space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on a Space Launch System rocket. For more information, visit http://www.nasa.gov/orion Photo credit: NASA/Jim Grossmann

The Application of the NASA Advanced Concepts Office, Launch Vehicle Team Design Process and Tools for Modeling Small Responsive Launch Vehicles

NASA Technical Reports Server (NTRS)

Threet, Grady E.; Waters, Eric D.; Creech, Dennis M.

2012-01-01

The Advanced Concepts Office (ACO) Launch Vehicle Team at the NASA Marshall Space Flight Center (MSFC) is recognized throughout NASA for launch vehicle conceptual definition and pre-phase A concept design evaluation. The Launch Vehicle Team has been instrumental in defining the vehicle trade space for many of NASA s high level launch system studies from the Exploration Systems Architecture Study (ESAS) through the Augustine Report, Constellation, and now Space Launch System (SLS). The Launch Vehicle Team s approach to rapid turn-around and comparative analysis of multiple launch vehicle architectures has played a large role in narrowing the design options for future vehicle development. Recently the Launch Vehicle Team has been developing versions of their vetted tools used on large launch vehicles and repackaged the process and capability to apply to smaller more responsive launch vehicles. Along this development path the LV Team has evaluated trajectory tools and assumptions against sounding rocket trajectories and air launch systems, begun altering subsystem mass estimating relationships to handle smaller vehicle components, and as an additional development driver, have begun an in-house small launch vehicle study. With the recent interest in small responsive launch systems and the known capability and response time of the ACO LV Team, ACO s launch vehicle assessment capability can be utilized to rapidly evaluate the vast and opportune trade space that small launch vehicles currently encompass. This would provide a great benefit to the customer in order to reduce that large trade space to a select few alternatives that should best fit the customer s payload needs.

Development and Current Status of the “Cambridge” Loudness Models

PubMed Central

2014-01-01

This article reviews the evolution of a series of models of loudness developed in Cambridge, UK. The first model, applicable to stationary sounds, was based on modifications of the model developed by Zwicker, including the introduction of a filter to allow for the effects of transfer of sound through the outer and middle ear prior to the calculation of an excitation pattern, and changes in the way that the excitation pattern was calculated. Later, modifications were introduced to the assumed middle-ear transfer function and to the way that specific loudness was calculated from excitation level. These modifications led to a finite calculated loudness at absolute threshold, which made it possible to predict accurately the absolute thresholds of broadband and narrowband sounds, based on the assumption that the absolute threshold corresponds to a fixed small loudness. The model was also modified to give predictions of partial loudness—the loudness of one sound in the presence of another. This allowed predictions of masked thresholds based on the assumption that the masked threshold corresponds to a fixed small partial loudness. Versions of the model for time-varying sounds were developed, which allowed prediction of the masked threshold of any sound in a background of any other sound. More recent extensions incorporate binaural processing to account for the summation of loudness across ears. In parallel, versions of the model for predicting loudness for hearing-impaired ears have been developed and have been applied to the development of methods for fitting multichannel compression hearing aids. PMID:25315375

Accuracy of Geophysical Parameters Derived from AIRS/AMSU as a Function of Fractional Cloud Cover

NASA Technical Reports Server (NTRS)

Susskind, Joel; Barnet, Chris; Blaisdell, John; Iredell, Lena; Keita, Fricky; Kouvaris, Lou; Molnar, Gyula; Chahine, Moustafa

2005-01-01

AIRS was launched on EOS Aqua on May 4,2002, together with AMSU A and HSB, to form a next generation polar orbiting infrared and microwave atmospheric sounding system. The primary products of AIRS/AMSU are twice daily global fields of atmospheric temperature-humidity profiles, ozone profiles, sea/land surface skin temperature, and cloud related parameters including OLR. The sounding goals of AIRS are to produce 1 km tropospheric layer mean temperatures with an rms error of 1K, and layer precipitable water with an rms error of 20%, in cases with up to 80% effective cloud cover. The basic theory used to analyze AIRS/AMSU/HSB data in the presence of clouds, called the at-launch algorithm, was described previously. Pre-launch simulation studies using this algorithm indicated that these results should be achievable. Some modifications have been made to the at-launch retrieval algorithm as described in this paper. Sample fields of parameters retrieved from AIRS/AMSU/HSB data are presented and validated as a function of retrieved fractional cloud cover. As in simulation, the degradation of retrieval accuracy with increasing cloud cover is small. HSB failed in February 2005, and consequently HSB channel radiances are not used in the results shown in this paper. The AIRS/AMSU retrieval algorithm described in this paper, called Version 4, become operational at the Goddard DAAC in April 2005 and is being used to analyze near-real time AIRS/AMSU data. Historical AIRS/AMSU data, going backwards from March 2005 through September 2002, is also being analyzed by the DAAC using the Version 4 algorithm.

Operation of a swept Langmuir probe on a sounding rocket

NASA Astrophysics Data System (ADS)

Robertson, S. H.; Dickson, S.; Friedrich, M.; Sternovsky, Z.

2012-12-01

A swept cylindrical Langmuir probe was operated on two sounding rockets from ~ 60-120 km for the purpose of determining both the ambient electron density and the payload potential relative to the ambient plasma. The rockets were part of the CHAMPS (CHarge And mass of Meteoritic smoke ParticleS) rocket campaign and carried mass analyzers and various plasma probes to study charged meteoritic dust in the mesopause region. The payload potential is an important parameter for data interpretation. The rockets were launched in October of 2011 from Andøya Rocket Range, Norway. The launches were a few days apart with one taking place during the day and the other at night. The swept Langmuir probe data provided a current-voltage characteristic that had a distinct "knee" indicating the onset of electron collection; the probe voltage at this "knee" corresponds to the ambient plasma potential. The data indicate a payload potential of about -2 V to -1 V for both launches. The payload potential becomes less negative for altitudes above 80 km on the day launch due to photoemission. The probe current-voltage data are also compared with ion and electron density measurements from ion probes and Faraday rotation antennas, respectively. The data from the various instruments are in general agreement. Further consideration of the Langmuir probe performance shows that if the probe had been operated with feedback control to continuously collect electrons with a current of order 1 microamp, the probe potential would be an accurate, continuous indicator of the payload potential without the need for sweeping which could periodically alter the payload potential.

Sediment transport in Norton Sound, Alaska

USGS Publications Warehouse

Drake, D.E.; Cacchione, D.A.; Muench, R.D.; Nelson, C.H.

1980-01-01

The Yukon River, the largest single source of Bering Sea sediment, delivers >95% of its sediment load at the southwest corner of Norton Sound during the ice-free months of late May through October. During this period, surface winds in the northern Bering Sea area are generally light from the south and southwest, and surface waves are not significant. Although wind stress may cause some transport of low-density turbid surface water into the head of Norton Sound, the most significant transport of Yukon River suspended matter occurs within advective currents flowing north across the outer part of the sound. The thickest accumulations of modern Yukon silt and very fine sand occur beneath this persistent current. We monitored temporal variations in bottom currents, pressure, and suspended-matter concentrations within this major transport pathway for 80 days in the summer of 1977 using a Geological Processes Bottom Environmental (GEOPROBE) tripod system. The record reveals two distinctive periods of bottom flow and sediment transport: an initial 59 days (July 8-September 5) of fair-weather conditions, characterized by tidally dominated currents and relatively low, stable suspended-matter concentrations; and a 21-day period (September 5-September 26) during which several storms traversed the northern Bering Sea, mean suspended-matter concentrations near the bottom increased by a factor of five, and the earlier tidal dominance was overshadowed by wind-driven and oscillatory wave-generated currents. Friction velocities (u*) at the GEOPROBE site were generally subcritical during the initial fair-weather period. In contrast, the 21-day stormy period was characterized by u* values that exceeded the critical level of 1.3 cm/s more than 60% of the time. The GEPROBE data suggest that the very fine sand constituting about 50% of the sediment on the outer part of the Yukon prodelta is transported during a few late-summer and fall storms each year. A conservative estimate shows that suspended-matter transport during the storms in September 1977 was equal to four months of fair-weather transport. ?? 1980.

The neuromechanics of hearing

NASA Astrophysics Data System (ADS)

Araya, Mussie K.; Brownell, William E.

2015-12-01

Hearing requires precise detection and coding of acoustic signals by the inner ear and equally precise communication of the information through the auditory brainstem. A membrane based motor in the outer hair cell lateral wall contributes to the transformation of sound into a precise neural code. Structural, molecular and energetic similarities between the outer hair cell and auditory brainstem neurons suggest that a similar membrane based motor may contribute to signal processing in the auditory CNS. Cooperative activation of voltage gated ion channels enhances neuronal temporal processing and increases the upper frequency limit for phase locking. We explore the possibility that membrane mechanics contribute to ion channel cooperativity as a consequence of the nearly instantaneous speed of electromechanical signaling and the fact that membrane composition and mechanics modulate ion channel function.

The second filter’s second coming

DOE Office of Scientific and Technical Information (OSTI.GOV)

Ramamoorthy, Sripriya; Jacques, Steven L.; Choudhoury, Niloy

We measured sound-evoked vibrations at the stereociliary side of inner and outer hair cells and their surrounding supporting cells, using optical coherence tomography interferometry in living anesthetized guinea pigs. Our measurements demonstrate a gradient in frequency tuning among different cell types, going from a high best frequency at the inner hair cells to a lower one at the Hensen cells. This causes the locus of maximum inner hair cell activation to be shifted toward the apex of the cochlea as compared to the outer hair cells. These observations show that additional processing and filtering of acoustic signals occurs within themore » organ of Corti prior to inner hair cell excitation, thus reinstating a transformed second filter as a mechanism contributing to cochlear frequency tuning.« less

Earth Observations taken by the Expedition Seven crew

NASA Image and Video Library

2003-06-22

ISS007-E-07842 (22 June 2003) --- This image, photographed by an Expedition 7 crewmember onboard the International Space Station (ISS), features Kitty Hawk, N.C., on North Carolina’s Outer Banks. The view shows part of Pamlico Sound and the Atlantic side of the banks as well. This year the world celebrates a century of human flight with the 100th anniversary of the Wright Brothers' first flight at Kitty Hawk. The Wrights used the Outer Banks’ prevailing winds and the altitude gained by climbing a 90-foot hill (Kill Devil Hill) to successfully demonstrate powered flight. The large circle on the image is a road that wraps around Kill Devil Hill, now part of the Wright Brothers National Memorial.

The second filter's second coming

NASA Astrophysics Data System (ADS)

Ramamoorthy, Sripriya; Chen, Fangyi; Zha, Dingjun; Jacques, Steven L.; Wang, Ruikang; Choudhoury, Niloy; Nuttall, Alfred L.; Fridberger, Anders

2015-12-01

We measured sound-evoked vibrations at the stereociliary side of inner and outer hair cells and their surrounding supporting cells, using optical coherence tomography interferometry in living anesthetized guinea pigs. Our measurements demonstrate a gradient in frequency tuning among different cell types, going from a high best frequency at the inner hair cells to a lower one at the Hensen cells. This causes the locus of maximum inner hair cell activation to be shifted toward the apex of the cochlea as compared to the outer hair cells. These observations show that additional processing and filtering of acoustic signals occurs within the organ of Corti prior to inner hair cell excitation, thus reinstating a transformed second filter as a mechanism contributing to cochlear frequency tuning.

Reverse transduction measured in the living cochlea by low-coherence heterodyne interferometry.

PubMed

Ren, Tianying; He, Wenxuan; Barr-Gillespie, Peter G

2016-01-06

It is generally believed that the remarkable sensitivity and frequency selectivity of mammalian hearing depend on outer hair cell-generated force, which amplifies sound-induced vibrations inside the cochlea. This 'reverse transduction' force production has never been demonstrated experimentally, however, in the living ear. Here by directly measuring microstructure vibrations inside the cochlear partition using a custom-built interferometer, we demonstrate that electrical stimulation can evoke both fast broadband and slow sharply tuned responses of the reticular lamina, but only a slow tuned response of the basilar membrane. Our results indicate that outer hair cells can generate sufficient force to drive the reticular lamina over all audible frequencies in living cochleae. Contrary to expectations, the cellular force causes a travelling wave rather than an immediate local vibration of the basilar membrane; this travelling wave vibrates in phase with the reticular lamina at the best frequency, and results in maximal vibration at the apical ends of outer hair cells.

Status Update Report for the Peregrine 100km Sounding Rocket Project

NASA Technical Reports Server (NTRS)

Dyer, Jonny; Zilliac, Greg; Doran, Eric; Marzona, Mark Thadeus; Lohner, Kevin; Karlik, Evan; Cantwell, Brian; Karabeyoglu, Arif

2008-01-01

The Peregrine Sounding Rocket Program is a joint basic research program of NASA Ames Research Center, NASA Wallops, Stanford University and the Space Propulsion Group, Inc. (SPG). The goal is to determine the applicability of liquifying hybrid technology to a small launch system. The approach is to design, build, test and y a stable, efficient liquefying fuel hybrid rocket vehicle to an altitude of 100 km. The program was kicked o in October of 2006 and has seen considerable progress in the subsequent 18 months. Two virtually identical vehicles will be constructed and own out of the NASA Sounding Rocket Facility at Wallops Island. This paper presents the current status of the project as of June 2008. For background on the project, the reader is referred to last year's paper.

The International Safety Framework for nuclear power source applications in outer space-Useful and substantial guidance

NASA Astrophysics Data System (ADS)

Summerer, L.; Wilcox, R. E.; Bechtel, R.; Harbison, S.

2015-06-01

In 2009, the International Safety Framework for Nuclear Power Source Applications in Outer Space was adopted, following a multi-year process that involved all major space faring nations under the auspices of a partnership between the UN Committee on the Peaceful Uses of Outer Space and the International Atomic Energy Agency. The Safety Framework reflects an international consensus on best practices to achieve safety. Following the 1992 UN Principles Relevant to the Use of Nuclear Power Sources in Outer Space, it is the second attempt by the international community to draft guidance promoting the safety of applications of nuclear power sources in space missions. NPS applications in space have unique safety considerations compared with terrestrial applications. Mission launch and outer space operational requirements impose size, mass and other space environment limitations not present for many terrestrial nuclear facilities. Potential accident conditions could expose nuclear power sources to extreme physical conditions. The Safety Framework is structured to provide guidance for both the programmatic and technical aspects of safety. In addition to sections containing specific guidance for governments and for management, it contains technical guidance pertinent to the design, development and all mission phases of space NPS applications. All sections of the Safety Framework contain elements directly relevant to engineers and space mission designers for missions involving space nuclear power sources. The challenge for organisations and engineers involved in the design and development processes of space nuclear power sources and applications is to implement the guidance provided in the Safety Framework by integrating it into the existing standard space mission infrastructure of design, development and operational requirements, practices and processes. This adds complexity to the standard space mission and launch approval processes. The Safety Framework is deliberately generic to remain relevantly independent of technological progress, of national organisational setups and of space mission types. Implementing its guidance therefore leaves room for interpretation and adaptation. Relying on reported practices, we analyse the guidance particularly relevant to engineers and space mission designers.

San Marco D/L Explorer

NASA Technical Reports Server (NTRS)

1988-01-01

ti March 26, 1964, Centro Ricerche Aerospaziali (CRA) successfully launched a two-stage Nike sounding rocket from the Santa Rita launch platform off the Kenya coast, concluding Phase I. It carried basic elements of the San Marco science instrumentation and served further to flight qualify these canponents as well as provide a means of check-out of range instrumentation and equipment. The second phase culminated in the launch of the San Marco-I Spacecraft fran Wallops Island on a Scout vehicle on December 15, 1964. This launch derronstrated the readiness of the CRA launch crews for Phase III operations and qualified the basic spacecraft design. In addition it confirmed the usefulness and reliability of the drag balance device for accurate determinations of air density values and satellite attitude. phase III was completed with the launching of San Marco-11 frcm the San Marco platform off the coast of Kenya on April 26, 1967. ?he San Marco-II carried the same instrunentation as the San Marco-I, but the equatorial orbit permitted a more detailed study to be made of density variations versus altitude in the equatorial region. Ihe successful launch also served to qualify the San Marco Range as a reliable facility for future satellite launches. The successful culmination of the first San Marco endeavor paved the way for still closer collaboration in future space explorations.

The Advanced Technology Microwave Sounder (ATMS): The First 10 Months On-Orbit

NASA Technical Reports Server (NTRS)

Kim, Edward; Lyu, C-H Joseph; Blackwell, Willaim; Leslie, R. Vince; Baker, Neal; Mo, Tsan; Sun, Ninghai; Bi, Li; Anderson, Kent; Landrum, Mike;

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

Four years after its occurrence rocked the petroleum industry and revitalized the US environmental movement, the Exxon Valdez tanker oil spill off Alaska continues to stir controversy. Conflicting reports abound over whether there is long term damage to the Prince William Sound ecosystem resulting from the March 24, 1989, spill. Government scientists at recent conferences disclosed studies they contend show long term, significant damage to the sound. Exxon this month launched a counteroffensive, disclosing results of studies it funded that it claims show no credible scientific evidence of long term damage. At the same time, the company blasted as flawedmore » the government's data on assessing environmental damage to the sound and charged that test samples from the sound were mishandled. Meantime, Prince William Sound still shows lingering effects from the Exxon Valdez oil spill. But recovery has been so rapid that there is more controversy over how to use $900 million in natural resource recovery funds that Exxon paid than over how badly species are suffering. The paper describes Exxon's studies; faulty data; lingering damage; and an update on tanker safety.« less

Testing of a femtosecond pulse laser in outer space

PubMed Central

Lee, Joohyung; Lee, Keunwoo; Jang, Yoon-Soo; Jang, Heesuk; Han, Seongheum; Lee, Sang-Hyun; Kang, Kyung-In; Lim, Chul-Woo; Kim, Young-Jin; Kim, Seung-Woo

2014-01-01

We report a test operation of an Er-doped fibre femtosecond laser which was conducted for the first time in outer space. The fibre-based ultrashort pulse laser payload was designed to meet space-use requirements, undergone through ground qualification tests and finally launched into a low-earth orbit early in 2013. Test results obtained during a one-year mission lifetime confirmed stable mode-locking all the way through although the radiation induced attenuation (RIA) in the Er-doped gain fibre caused an 8.6% reduction in the output power. This successful test operation would help facilitate diverse scientific and technological applications of femtosecond lasers in space and earth atmosphere in the near future. PMID:24875665

Testing of a femtosecond pulse laser in outer space.

PubMed

Lee, Joohyung; Lee, Keunwoo; Jang, Yoon-Soo; Jang, Heesuk; Han, Seongheum; Lee, Sang-Hyun; Kang, Kyung-In; Lim, Chul-Woo; Kim, Young-Jin; Kim, Seung-Woo

2014-05-30

We report a test operation of an Er-doped fibre femtosecond laser which was conducted for the first time in outer space. The fibre-based ultrashort pulse laser payload was designed to meet space-use requirements, undergone through ground qualification tests and finally launched into a low-earth orbit early in 2013. Test results obtained during a one-year mission lifetime confirmed stable mode-locking all the way through although the radiation induced attenuation (RIA) in the Er-doped gain fibre caused an 8.6% reduction in the output power. This successful test operation would help facilitate diverse scientific and technological applications of femtosecond lasers in space and earth atmosphere in the near future.

Nano-Electric Field TechnologY (NEFTY)

NASA Technical Reports Server (NTRS)

Kintner, Paul M.

2000-01-01

The NEFTY SR&T grant was focused on the development of novel electric field boom systems for sounding rocket applications. A "yo-yo"-type boom that unwraps from a rotating and damped axel was analyzed through a simulation with Prof. Psiaki of Mechanical and Aerospace Engineering at Cornell University. The basic parameters of the analysis were evaluated and validated on a spinning platform prototyping system developed at Cornell University. The full "yo-yo"-type boom system is being developing for the SIERRA sounding rocket flight scheduled for a January 2002 launch. The principal results from this study were published.

Use of a personal computer for the real-time reception and analysis of data from a sounding rocket experiment

NASA Technical Reports Server (NTRS)

Herrick, W. D.; Penegor, G. T.; Cotton, D. M.; Kaplan, G. C.; Chakrabarti, S.

1990-01-01

In September 1988 the Earth and Planetary Atmospheres Group of the Space Sciences Laboratory of the University of California at Berkeley flew an experiment on a high-altitude sounding rocket launched from the NASA Wallops Flight Facility in Virginia. The experiment, BEARS (Berkeley EUV Airglow Rocket Spectrometer), was designed to obtain spectroscopic data on the composition and structure of the earth's upper atmosphere. Consideration is given to the objectives of the BEARS experiment; the computer interface and software; the use of remote data transmission; and calibration, integration, and flight operations.

Sounding rockets shot from the Shuttle

NASA Technical Reports Server (NTRS)

Cruddace, R.; Fritz, G.; Glaab, J.; Shrewsberry, D.

1985-01-01

The Space Shuttle-launched sounding rocket Spartan-1 will map the structure of two extended X-ray sources: the hot gas pervading the Perseus cluster of galaxies, and the central core of the Milky Way. Spartan-1 contains two large X-ray proportional counter detectors sensitive to the 1-15 A wavelength range. A new generation of instruments destined for X-ray telescope focal planes will yield high resolution imaging and spectroscopy, over observation times sometimes exceeding one day/source, in the course of a long-term Spartan research program that will encompass planetary, solar, and UV astronomy missions.

Flight Investigation of the Performance of a Two-stage Solid-propellant Nike-deacon (DAN) Meteorological Sounding Rocket

NASA Technical Reports Server (NTRS)

Heitkotter, Robert H

1956-01-01

A flight investigation of two Nike-Deacon (DAN) two-stage solid-propellant rocket vehicles indicated satisfactory performance may be expected from the DAN meteorological sounding rocket. Peak altitudes of 356,000 and 350,000 feet, respectively, were recorded for the two flight tests when both vehicles were launched from sea level at an elevation angle of 75 degrees. Performance calculations based on flight-test results show that altitudes between 358,000 feet and 487,000 feet may be attained with payloads varying between 60 pounds and 10 pounds.

Field refurbishment of recoverable sounding rocket payloads.

NASA Technical Reports Server (NTRS)

Needleman, H. C.; Tackett, C. D.

1973-01-01

Sounding rocket payload field refurbishment has been shown to be an effective means for obtaining additional scientific data with substantial time and monetary savings. In a recent campaign three successful missions were flown using two payloads. Field refurbished hardware from two previously flown and recovered payloads were field integrated to form a third payload. Although this operational method may result in compromises in the refurbished system, it allows for quick turn around when the mission requires it. This paper describes the recent success of this approach with the Dudley Observatory Nike-Apache micrometeorite collection experiments launched from Kiruna, Sweden, in October 1972.

Using Module-Based Learning Methods to Introduce Sustainable Manufacturing in Engineering Curriculum

ERIC Educational Resources Information Center

Sengupta, Debalina; Huang, Yinlun; Davidson, Cliff I.; Edgar, Thomas F.; Eden, Mario R.; El-Halwagi, Mahmoud M.

2017-01-01

Purpose: Sustainable manufacturing may be defined as the creation of manufactured products that use processes that are non-polluting, conserve energy and natural resources, and are economically sound and safe for employees, communities and consumers. Recently, there have been several industrial and governmental endeavors to launch sustainable…

50 CFR 217.65 - Requirements for monitoring and reporting.

Code of Federal Regulations, 2014 CFR

2014-10-01

... through June), conduct follow-up surveys within 2 weeks of the launch to ensure that there were no adverse... not had sound pressure level measurements made previously, and (7) Include multiple surveys each day that surveys are required that record the species, number of animals, general behavior, presence of...

World Data Center A (rockets and satellites) catalogue of data. Volume 1, part A: Sounding rockets

NASA Technical Reports Server (NTRS)

1972-01-01

A cumulative listing of all scientifically successful rockets that have been identified from various sources is presented. The listing starts with the V-2 rocket launched on 7 March 1947 and contains all rockets identified up to 31 December 1971.

Musicianship enhances ipsilateral and contralateral efferent gain control to the cochlea.

PubMed

Bidelman, Gavin M; Schneider, Amy D; Heitzmann, Victoria R; Bhagat, Shaum P

2017-02-01

Human hearing sensitivity is easily compromised with overexposure to excessively loud sounds, leading to permanent hearing damage. Consequently, finding activities and/or experiential factors that distinguish "tender" from "tough" ears (i.e., acoustic vulnerability) would be important for identifying people at higher risk for hearing damage. To regulate sound transmission and protect the inner ear against acoustic trauma, the auditory system modulates gain control to the cochlea via biological feedback of the medial olivocochlear (MOC) efferents, a neuronal pathway linking the lower brainstem and cochlear outer hair cells. We hypothesized that a salient form of auditory experience shown to have pervasive neuroplastic benefits, namely musical training, might act to fortify hearing through tonic engagement of these reflexive pathways. By measuring MOC efferent feedback via otoacoustic emissions (cochlear emitted sounds), we show that dynamic ipsilateral and contralateral cochlear gain control is enhanced in musically-trained individuals. Across all participants, MOC strength was correlated with the years of listeners' training suggested that efferent gain control is experience dependent. Our data provide new evidence that intensive listening experience(s) (e.g., musicianship) can strengthen the ipsi/contralateral MOC efferent system and sound regulation to the inner ear. Implications for reducing acoustic vulnerability to damaging sounds are discussed. Copyright © 2016 Elsevier B.V. All rights reserved.

The Properties of the Diffuse X-ray Background from the DXL sounding rocket mission (plus ROSAT, XMM-Newton and Suzaku data)

NASA Astrophysics Data System (ADS)

Galeazzi, Massimiliano

2017-08-01

Understanding the properties of the different components of the Diffuse X-ray Background (DXB) is made particularly difficult by their similar spectral signature.The University of Miami has been working on disentangling the different DXB components for many years, using a combination of proprietary and archival data from XMM-Newton, Suzaku, and Chandra, and a sounding rocket mission (DXL) specifically designed to study the properties of Local Hot Bubble (LHB) and Solar Wind Charge eXchange (SWCX) using their spatial signature. In this talk we will present:(a) Results from the DXL mission, specifically launch #2, to study the properties of the SWCX and LHB (and GH) and their contribution to the ROSAT All Sky Survey Bands(b) Results from a Suzaku key project to characterize the SWCX and build a semi-empirical model to predict the SWCX line emission for any time, any direction. A publicly available web portal for the model will go online by the end of the year(c) Results from XMM-Newton deep surveys to study the angular correlation of the Warm-Hot Intergalactic Medium (WHIM) in the direction of the Chandra Deep Field South.DXL launch #3, schedule for January 2018 and the development of the DXG sounding rocket mission to characterize the GH-CGM emission using newly developed micropore optics will also be discussed.

Sounding rocket study of auroral electron precipitation

DOE Office of Scientific and Technical Information (OSTI.GOV)

McFadden, J.P.

1985-01-01

Measurement of energetic electrons in the auroral zone have proved to be one of the most useful tools in investigating the phenomena of auroral arc formation. This dissertation presents a detailed analysis of the electron data from two sounding rocket campaigns and interprets the measurements in terms of existing auroral models. The Polar Cusp campaign consisted of a single rocket launched from Cape Parry, Canada into the afternoon auroral zone at 1:31:13 UT on January 21, 1982. The results include the measurement of a narrow, magnetic field aligned electron flux at the edge of an arc. This electron precipitation wasmore » found to have a remarkably constant 1.2 eV temperature perpendicular to the magnetic field over a 200 to 900 eV energy range. The payload also made simultaneous measurements of both energetic electrons and 3-MHz plasma waves in an auroral arc. Analysis has shown that the waves are propagating in the upper hybrid band and should be generated by a positive slope in the parallel electron distribution. A correlation was found between the 3-MHz waves and small positive slopes in the parallel electron distribution but experimental uncertainties in the electron measurement were large enough to influence the analysis. The BIDARCA campaign consisted of two sounding rockets launched from Poker Flat and Fort Yukon, Alaska at 9:09:00 UT and 9:10:40 UT on February 7, 1984.« less

Chimpanzee 'Ham' In Biopack Couch

NASA Technical Reports Server (NTRS)

1961-01-01

A three-year-old chimpanzee, named Ham, in the biopack couch for the MR-2 suborbital test flight. On January 31, 1961, a Mercury-Redstone launch from Cape Canaveral carried the chimpanzee 'Ham' over 640 kilometers down range in an arching trajectory that reached a peak of 254 kilometers above the Earth. The mission was successful and Ham performed his lever-pulling task well in response to the flashing light. NASA used chimpanzees and other primates to test the Mercury Capsule before launching the first American astronaut Alan Shepard in May 1961. The successful flight and recovery confirmed the soundness of the Mercury-Redstone systems.

KSC-99pc16

NASA Image and Video Library

1999-01-05

Loral workers at Astrotech, Titusville, Fla., deploy one of the solar panels of the GOES-L weather satellite, to be launched from Cape Canaveral Air Station (CCAS) aboard an Atlas II rocket in late March. The GOES-L is the fourth of a new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration. It is a three-axis inertially stabilized spacecraft that will provide pictures and perform atmospheric sounding at the same time. Once launched, the satellite, to be designated GOES-11, will undergo checkout and provide backup capabilities for the existing, aging GOES East weather satellite

KSC-99pc18

NASA Image and Video Library

1999-01-05

Loral workers at Astrotech, Titusville, Fla., check out the solar panels of the GOES-L weather satellite, to be launched from Cape Canaveral Air Station (CCAS) aboard an Atlas II rocket in late March. The GOES-L is the fourth of a new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration. It is a three-axis inertially stabilized spacecraft that will provide pictures and perform atmospheric sounding at the same time. Once launched, the satellite, to be designated GOES-11, will undergo checkout and provide backup capabilities for the existing, aging GOES East weather satellite

KSC-99pc17

NASA Image and Video Library

1999-01-05

Loral workers at Astrotech, Titusville, Fla., stand back as they deploy the solar panels of the GOES-L weather satellite. The satellite is to be launched from Cape Canaveral Air Station (CCAS) aboard an Atlas II rocket in late March. The GOES-L is the fourth of a new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration. It is a three-axis inertially stabilized spacecraft that will provide pictures and perform atmospheric sounding at the same time. Once launched, the satellite, to be designated GOES-11, will undergo checkout and provide backup capabilities for the existing, aging GOES East weather satellite

Mercury Project

NASA Image and Video Library

1961-01-31

A three-year-old chimpanzee, named Ham, in the biopack couch for the MR-2 suborbital test flight. On January 31, 1961, a Mercury-Redstone launch from Cape Canaveral carried the chimpanzee "Ham" over 640 kilometers down range in an arching trajectory that reached a peak of 254 kilometers above the Earth. The mission was successful and Ham performed his lever-pulling task well in response to the flashing light. NASA used chimpanzees and other primates to test the Mercury Capsule before launching the first American astronaut Alan Shepard in May 1961. The successful flight and recovery confirmed the soundness of the Mercury-Redstone systems.

Mercury Project

NASA Image and Video Library

1961-01-01

A three-year-old chimpanzee, named Ham, in the biopack couch for the MR-2 suborbital test flight. On January 31, 1961, a Mercury-Redstone launch from Cape Canaveral carried the chimpanzee "Ham" over 640 kilometers down range in an arching trajectory that reached a peak of 254 kilometers above the Earth. The mission was successful and Ham performed his lever-pulling task well in response to the flashing light. NASA used chimpanzees and other primates to test the Mercury Capsule before launching the first American astronaut Alan Shepard in May 1961. The successful flight and recovery confirmed the soundness of the Mercury-Redstone systems.

Saturn Apollo Program

NASA Image and Video Library

1965-01-01

S-IB-200D, a dynamic test version of the Saturn IB launch vehicle's first stage (S-IB), makes its way to the Marshall Space Flight Center (MSFC) East Test Area on January 4, 1965. Test Laboratory persornel assembled a complete Saturn IB to test the structural soundness of the launch vehicle in the Dynamic Test Stand. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine the larger boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

Optimizing the Launch of a Projectile to Hit a Target

ERIC Educational Resources Information Center

Mungan, Carl E.

2017-01-01

Some teenagers are exploring the outer perimeter of a castle. They notice a spy hole in its wall, across the moat a horizontal distance "x" and vertically up the wall a distance "y." They decide to throw pebbles at the hole. One girl wants to use physics to throw with the minimum speed necessary to hit the hole. What is the…

Transient Analysis of Thermal Protection System for X-33 Aircraft using MSC/NASTRAN

NASA Technical Reports Server (NTRS)

Miura, Hirokazu; Chargin, M. K.; Bowles, J.; Tam, T.; Chu, D.; Chainyk, M.; Green, Michael J. (Technical Monitor)

1997-01-01

X-33 is an advanced technology demonstrator vehicle for the Reusable Launch Vehicle (RLV) program. The thermal protection system (TPS) for the X-33 is composed of complex layers of materials to protect internal components, while withstanding severe external temperatures induced by aerodynamic heating during high speed flight. It also serves as the vehicle aeroshell in some regions using a stand-off design. MSC/NASTRAN thermal analysis capability was used to predict transient temperature distribution (within the TPS) throughout a mission, from launch through the cool-off period after landing. In this paper, a typical analysis model, representing a point on the vehicle where the liquid oxygen tank is closest to the outer mold line, is described. The maximum temperature difference between the outer mold line and the internal surface of the liquid oxygen tank can exceed 1500 F. One dimensional thermal models are used to select the materials and determine the thickness of each layer for minimum weight while insuring that all materials remain within the allowable temperature range. The purpose of working with three dimensional (3D) comprehensive models using MSC/NASTRAN is to assess the 3D radiation effects and the thermal conduction heat shorts of the support fixtures.

Exact Analytic Solution for a Ballistic Orbiting Wind

NASA Astrophysics Data System (ADS)

Wilkin, Francis P.; Hausner, Harry

2017-07-01

Much theoretical and observational work has been done on stellar winds within binary systems. We present a new solution for a ballistic wind launched from a source in a circular orbit. The solution is that of a single wind—no second wind is included in the system and the shocks that arise are those due to the orbiting wind interacting with itself. Our method emphasizes the curved streamlines in the corotating frame, where the flow is steady-state, allowing us to obtain an exact solution for the mass density at all pre-shock locations. Assuming an initially isotropic wind, fluid elements launched from the interior hemisphere of the wind will be the first to cross other streamlines, resulting in a spiral structure bounded by two shock surfaces. Streamlines from the outer wind hemisphere later intersect these shocks as well. An analytic solution is obtained for the geometry of the two shock surfaces. Although the inner and outer shock surfaces asymptotically trace Archimedean spirals, our tail solution suggests many crossings where the shocks overlap, beyond which the analytic solution cannot be continued. Our solution can be readily extended to an initially anisotropic wind.

An evaluation of Space Shuttle STS-2 payload bay acoustic data and comparison with predictions

NASA Technical Reports Server (NTRS)

Wilby, J. F.; Piersol, A. G.; Wilby, E. G.

1982-01-01

Space average sound pressure levels computed from measurements at 18 locations in the payload bay of the Space Shuttle orbiter vehicle during the STS-2 launch were compared with predicted levels obtained using the PACES computer program. The comparisons were performed over the frequency range 12.5 Hz to 1000 Hz, since the test data at higher frequencies are contaminated by instrumentation background noise. In general the PACES computer program tends to overpredict the space average sound levels in the payload bay, although the magnitude of the discrepancy is usually small. Furthermore the discrepancy depends to some extent on the manner in which the payload is modeled analytically, and the method used to determine the "measured' space average sound pressure levels. Thus the difference between predicted and measured sound levels, averaged over the 20 one third octave bands from 12.5 Hz to 1000 Hz, varies from 1 dB to 3.5 dB.

NCAR Integrated Sounding System Observations during the SOAS / SAS Field Campaign

NASA Astrophysics Data System (ADS)

Brown, W. O.; Moore, J.

2013-12-01

The National Center for Atmospheric Research (NCAR) Earth Observing Laboratory (EOL) deployed an Integrated Sounding Systems (ISS) for the SOAS (Southern Oxidant and Aerosol Study) field campaign in Alabama in the summer of 2013. The ISS was split between two sites: a former NWS site approximately 1km from the main SOAS chemistry ground site near Centerville AL, and about 20km to the south at the Alabama fish hatchery site approximately 1km from the flux tower site near Marion, AL. At the former-NWS site we launched 106 radiosonde soundings, operated a 915 MHz boundary layer radar wind profiler with RASS (Radio Acoustic Sounding System), ceilometer and various surface meteorological sensors. At the AABC site we operated a Lesosphere WIndcube 200S Doppler lidar and a Metek mini-Doppler sodar. Other NCAR facilities at the AABC site included a 45-m instrumented flux tower. This poster will present a sampling observations made by these instruments, including examples of boundary layer evolution and structure, and summarize the performance of the instrumentation.

2006 Progress Report on Acoustic and Visual Monitoring for Cetaceans along the Outer Washington Coast

DTIC Science & Technology

2007-08-01

Although Northern Resident killer whales have been extensively studied within Puget Sound and coastal British Columbia, they have been visually sighted... whales . Time series of vocalizations detected in acoustic recordings are presented for killer whales , white-sided dolphins, Risso’s dolphins...Pinniped sightings during visual surveys since August 2004. Seasonal occurrence of humpback and gray whales from visual surveys. Killer whale

Remineralization of in vitro dental caries assessed with polarization-sensitive optical coherence tomography

NASA Astrophysics Data System (ADS)

Jones, Robert S.; Darling, Cynthia L.; Featherstone, John D. B.; Fried, Daniel

2006-01-01

Polarization-sensitive optical coherence tomography (PS-OCT) is potentially useful for imaging the nonsurgical remineralization of dental enamel. This study uses an all-fiber-based PS-OCT system operating at 1310 nm to image demineralized and fluoride-enhanced remineralized artificial lesions. PS-OCT images of lesions before and after remineralization are compared with the relative mineral loss ΔZ (%vol×µm), obtained from high resolution digital microradiography (DM), and chemical composition changes by infrared spectroscopy. Severe early artificial caries show a significant increase in perpendicular-axis integrated reflectivity after remineralization. After sectioning the samples, DM demonstrates that the lesions remineralized with new mineral and the lesion surface zone show significant restoration of mineral volume. PS-OCT and DM both do not show a major change in lesion depth. For less severe artificial caries, the perpendicular-axis image resolves the scattering and depolarization of an outer growth layer after remineralization. This outer layer has a mineral volume close to that of sound enamel, and spectroscopic analysis indicates that the layer is a highly crystalline phase of apatite, without carbonate substitutions that increase the solubility of sound enamel. This study determines that PS-OCT can image the effects of fluoride-enhanced remineralization of mild and severe early artificial in vitro caries.

Fast acoustic streaming in standing waves: generation of an additional outer streaming cell.

PubMed

Reyt, Ida; Daru, Virginie; Bailliet, Hélène; Moreau, Solène; Valière, Jean-Christophe; Baltean-Carlès, Diana; Weisman, Catherine

2013-09-01

Rayleigh streaming in a cylindrical acoustic standing waveguide is studied both experimentally and numerically for nonlinear Reynolds numbers from 1 to 30 [Re(NL)=(U0/c0)(2)(R/δν)(2), with U0 the acoustic velocity amplitude at the velocity antinode, c0 the speed of sound, R the tube radius, and δν the acoustic boundary layer thickness]. Streaming velocity is measured by means of laser Doppler velocimetry in a cylindrical resonator filled with air at atmospheric pressure at high intensity sound levels. The compressible Navier-Stokes equations are solved numerically with high resolution finite difference schemes. The resonator is excited by shaking it along the axis at imposed frequency. Results of measurements and of numerical calculation are compared with results given in the literature and with each other. As expected, the axial streaming velocity measured and calculated agrees reasonably well with the slow streaming theory for small ReNL but deviates significantly from such predictions for fast streaming (ReNL>1). Both experimental and numerical results show that when ReNL is increased, the center of the outer streaming cells are pushed toward the acoustic velocity nodes until counter-rotating additional vortices are generated near the acoustic velocity antinodes.

Spacecraft Charging Issues for Launch Vehicles

NASA Technical Reports Server (NTRS)

Buhler, Janessa L.; Minow, Joseph I.; Trout, Dawn H.

2014-01-01

Spacecraft charging is well known threat to successful long term spacecraft operations and instrument reliability in orbits that spend significant time in hot electron environments. In recent years, spacecraft charging has increasingly been recognized as a potentially significant engineering issue for launch vehicles used to deploy spacecraft using (a) low Earth orbit (LEO), high inclination flight trajectories that pass through the auroral zone, (b) geostationary transfer orbits that require exposures to the hot electron environments in the Earths outer radiation belts, and (c) LEO escape trajectories using multiple phasing orbits through the Earths radiation belts while raising apogee towards a final Earth escape geometry. Charging becomes an issue when significant areas of exposed insulating materials or ungrounded conductors are used in the launch vehicle design or the payload is designed for use in a benign charging region beyond the Earths magnetosphere but must survive passage through the strong charging regimes of the Earths radiation belts. This presentation will first outline the charging risks encountered on typical launch trajectories used to deploy spacecraft into Earth orbit and Earth escape trajectories. We then describe the process used by NASAs Launch Services Program to evaluate when surface and internal charging is a potential risk to a NASA mission. Finally, we describe the options for mitigating charging risks including modification of the launch vehicle andor payload design and controlling the risk through operational launch constraints to avoid significant charging environments.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A construction worker is in view as a flatbed truck passes by carrying a vertical support post (VSP) for NASA's Space Launch System (SLS) rocket to the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. The two aft skirt electrical umbilicals (ASEUs) and the first of the vehicle support posts underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A flatbed truck carries a vertical support post (VSP) for NASA's Space Launch System (SLS) rocket to the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. In view is the mobile launcher. The two aft skirt electrical umbilicals (ASEUs) and the first of the vehicle support posts underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

KSC-08pd2307

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane is attached to the Multi-Use Lightweight Equipment, or MULE, carrier to moved the carrier to another stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller