KSC-2009-2976

NASA Image and Video Library

2009-05-06

CAPE CANAVERAL, Fla. – New windows are installed in the Launch Control Center's Firing Room 1 at NASA's Kennedy Space Center in Florida. The firing room will support the future Ares rocket launches as part of NASA's Constellation Program. Future astronauts will ride to orbit on Ares I, launched from Kennedy's Launch Pad 39B. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Jack Pfaller

Launch mission summary and sequence of events Telesat-F(anik-D1)/Delta-164

NASA Technical Reports Server (NTRS)

1982-01-01

The launch vehicle, spacecraft, and mission are summarized. Launch window information, vehicle telemetry coverage, real time data flow, telemetry coverage by station, selected trajectory information, and a brief sequence of flight events are included.

Launch mission summary: INTELSAT 5(F1) ATLAS/CENTAUR-56

NASA Technical Reports Server (NTRS)

1981-01-01

The technology and capability of the INTELSAT 5 series satellites and the Atlas-Centaur launch vehicle are described. Data relative to launch windows, flight plans, radar, and telemetry are included along with selected trajectory information and a sequence of flight events.

KSC-2009-2977

NASA Image and Video Library

2009-05-06

CAPE CANAVERAL, Fla. – A technician works at installing a new window in the Launch Control Center's Firing Room 1 at NASA's Kennedy Space Center in Florida. The firing room will support the future Ares rocket launches as part of NASA's Constellation Program. Future astronauts will ride to orbit on Ares I, launched from Kennedy's Launch Pad 39B. The Launch Control Center firing rooms face the launch pads. Photo credit: NASA/Jack Pfaller

Ascent abort capability for the HL-20

NASA Technical Reports Server (NTRS)

Naftel, J. C.; Talay, T. A.

1993-01-01

The HL-20 has been designed with the capability for rescue of the crew during all phases of powered ascent from on the launch pad until orbital injection. A launch-escape system, consisting of solid rocket motors located on the adapter between the HL-20 and the launch vehicle, provides the thrust that propels the HL-20 to a safe distance from a malfunctioning launch vehicle. After these launch-escape motors have burned out, the adapter is jettisoned and the HL-20 executes one of four abort modes. In three abort modes - return-to-launch-site, transatlantic-abort-landing, and abort-to-orbit - not only is the crew rescued, but the HL-20 is recovered intact. In the ocean-landing-by-parachute abort mode, which occurs in between the return-to-launch-site and the transatlantic-abort-landing modes, the crew is rescued, but the HL-20 would likely sustain damage from the ocean landing. This paper describes the launch-escape system and the four abort modes for an ascent on a Titan III launch vehicle.

KSC-03pd0916

NASA Image and Video Library

2003-03-29

KENNEDY SPACE CENTER, FLA. - A worker makes the final launch preparations on the rover equipment deck (RED) for the Mars Exploration Rover 2 (MER-2). Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. The rovers will be identical to each other, but will land at different regions of Mars. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

High field side launch of RF waves: A new approach to reactor actuators

NASA Astrophysics Data System (ADS)

Wallace, G. M.; Baek, S. G.; Bonoli, P. T.; Faust, I. C.; LaBombard, B. L.; Lin, Y.; Mumgaard, R. T.; Parker, R. R.; Shiraiwa, S.; Vieira, R.; Whyte, D. G.; Wukitch, S. J.

2015-12-01

Launching radio frequency (RF) waves from the high field side (HFS) of a tokamak offers significant advantages over low field side (LFS) launch with respect to both wave physics and plasma material interactions (PMI). For lower hybrid (LH) waves, the higher magnetic field opens the window between wave accessibility (n∥≡c k∥/ω >√{1 -ωpi 2/ω2+ωpe 2/ωce 2 }+ωp e/|ωc e| ) and the condition for strong electron Landau damping (n∥˜√{30 /Te } with Te in keV), allowing LH waves from the HFS to penetrate into the core of a burning plasma, while waves launched from the LFS are restricted to the periphery of the plasma. The lower n∥ of waves absorbed at higher Te yields a higher current drive efficiency as well. In the ion cyclotron range of frequencies (ICRF), HFS launch allows for direct access to the mode conversion layer where mode converted waves absorb strongly on thermal electrons and ions, thus avoiding the generation of energetic minority ion tails. The absence of turbulent heat and particle fluxes on the HFS, particularly in double null configuration, makes it the ideal location to minimize PMI damage to the antenna structure. The quiescent SOL also eliminates the need to couple LH waves across a long distance to the separatrix, as the antenna can be located close to plasma without risking damage to the structure. Improved impurity screening on the HFS will help eliminate the long-standing issues of high Z impurity accumulation with ICRF. Looking toward a fusion reactor, the HFS is the only possible location for a plasma-facing RF antenna that will survive long-term. By integrating the antenna into the blanket module it is possible to improve the tritium breeding ratio compared with an antenna occupying an equatorial port plug. Blanket modules will require remote handling of numerous cooling pipes and electrical connections, and the addition of transmission lines will not substantially increase the level of complexity. The obvious engineering challenges associated with locating antenna structures on the HFS can be overcome if HFS antennas are incorporated in the overall experimental design from the start. The Advanced Divertor and radio frequency eXperiment(ADX) will include LH and ICRF antennas located on the HFS. Compact antenna designs based on proven technologies (e.g. multi-junction and "4-way splitter" antennas) fit within the available space on the HFS of ADX. Field aligned ICRF antennas are also located on the HFS. The ADX vacuum vessel design includes dedicated space for transmission lines, pressure windows, and vacuum feedthrus for accessing the HFS wall.

14. VIEW OF MST, FACING SOUTHEAST, AND LAUNCH PAD TAKEN ...

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

14. VIEW OF MST, FACING SOUTHEAST, AND LAUNCH PAD TAKEN FROM NORTHEAST PHOTO TOWER WITH WINDOW OPEN. FEATURES LEFT TO RIGHT: SOUTH TELEVISION CAMERA TOWER, SOUTHWEST PHOTO TOWER, LAUNCHER, UMBILICAL MAST, MST, AND OXIDIZER APRON. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

Launch mission summary and terminal countdown, Delta 153 Satellite Business Systems satellite (SBS-A)

NASA Technical Reports Server (NTRS)

1980-01-01

A brief summary of the launch vehicle, spacecraft, and mission is contained. Information relative to launch windows, vehicle telemetry coverage, realtime data flow, telemetry coverage by station, selected trajectory information, and a brief sequence of flight events is also included.

Occupant-responsive optimal control of smart facade systems

NASA Astrophysics Data System (ADS)

Park, Cheol-Soo

Windows provide occupants with daylight, direct sunlight, visual contact with the outside and a feeling of openness. Windows enable the use of daylighting and offer occupants a outside view. Glazing may also cause a number of problems: undesired heat gain/loss in winter. An over-lit window can cause glare, which is another major complaint by occupants. Furthermore, cold or hot window surfaces induce asymmetric thermal radiation which can result in thermal discomfort. To reduce the potential problems of window systems, double skin facades and airflow window systems have been introduced in the 1970s. They typically contain interstitial louvers and ventilation openings. The current problem with double skin facades and airflow windows is that their operation requires adequate dynamic control to reach their expected performance. Many studies have recognized that only an optimal control enables these systems to truly act as active energy savers and indoor environment controllers. However, an adequate solution for this dynamic optimization problem has thus far not been developed. The primary objective of this study is to develop occupant responsive optimal control of smart facade systems. The control could be implemented as a smart controller that operates the motorized Venetian blind system and the opening ratio of ventilation openings. The objective of the control is to combine the benefits of large windows with low energy demands for heating and cooling, while keeping visual well-being and thermal comfort at an optimal level. The control uses a simulation model with an embedded optimization routine that allows occupant interaction via the Web. An occupant can access the smart controller from a standard browser and choose a pre-defined mode (energy saving mode, visual comfort mode, thermal comfort mode, default mode, nighttime mode) or set a preferred mode (user-override mode) by moving preference sliders on the screen. The most prominent feature of these systems is the capability of dynamically reacting to the environmental input data through real-time optimization. The proposed occupant responsive optimal control of smart facade systems could provide a breakthrough in this under-developed area and lead to a renewed interest in smart facade systems.

Launch of Space Shuttle Atlantis / STS-129 Mission

NASA Image and Video Library

2009-11-16

STS129-S-056 (16 Nov. 2009) --- Members of the space shuttle launch team watch Space Shuttle Atlantis' launch through the newly installed windows of Firing Room 4 in the Launch Control Center at NASA's Kennedy Space Center in Florida. Liftoff of Atlantis from Launch Pad 39A on its STS-129 mission to the International Space Station came at 2:28 p.m. (EST) Nov. 16, 2009.

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.

Independent Orbiter Assessment (IOA): Analysis of the purge, vent and drain subsystem

NASA Technical Reports Server (NTRS)

Bynum, M. C., III

1987-01-01

The results of the Independent Orbiter Assessment (IOA) of the Failure Modes and Effects Analysis (FMEA) and Critical Items List (CIL) are presented. The IOA approach features a top-down analysis of the hardware to determine failure modes, criticality, and potential critical items. To preserve independence, this analysis was accomplished without reliance upon the results contained within the NASA FMEA/CIL documentation. This report documents the independent analysis results corresponding to the Orbiter PV and D (Purge, Vent and Drain) Subsystem hardware. The PV and D Subsystem controls the environment of unpressurized compartments and window cavities, senses hazardous gases, and purges Orbiter/ET Disconnect. The subsystem is divided into six systems: Purge System (controls the environment of unpressurized structural compartments); Vent System (controls the pressure of unpressurized compartments); Drain System (removes water from unpressurized compartments); Hazardous Gas Detection System (HGDS) (monitors hazardous gas concentrations); Window Cavity Conditioning System (WCCS) (maintains clear windows and provides pressure control of the window cavities); and External Tank/Orbiter Disconnect Purge System (prevents cryo-pumping/icing of disconnect hardware). Each level of hardware was evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the severity of the effect for each failure mode. Four of the sixty-two failure modes analyzed were determined as single failures which could result in the loss of crew or vehicle. A possible loss of mission could result if any of twelve single failures occurred. Two of the criticality 1/1 failures are in the Window Cavity Conditioning System (WCCS) outer window cavity, where leakage and/or restricted flow will cause failure to depressurize/repressurize the window cavity. Two criticality 1/1 failures represent leakage and/or restricted flow in the Orbiter/ET disconnect purge network which prevent cryopumping/icing of disconnect hardware. Each level of hardware was evaluated and analyzed for possible failure modes and effects. Criticality was assigned based upon the severity of the effect for each failure mode.

JPL-20180406-INSIGHf-0001-InSight West Coast Launch

NASA Image and Video Library

2018-04-06

NASA's InSight mission to Mars will be the first interplanetary launch from America's West Coast. It will launch from Vandenberg Air Force Base in California. The launch window opens at 4:05 a.m. PDT and remains open for two hours. The launch period spans May 5 through June 8. Animations indicate how the launch will look to people on the ground in Santa Barbara, Los Angeles, and San Diego. A map shows the entire region in which the launch will be visible if skies are clear.

Polarization Measurements During Electron Cyclotron Heating Experiments in the DIII-D Tokamak

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

Petty, C.C.; Luce, T.C.; Austin, M.E.

The polarization of the launched electron cyclotron wave has been optimized for coupling to the X-mode by adjusting the inclination of grooved mirrors located in two consecutive mitre bends of the waveguide. The unwanted O-mode component of the launched beam can be positively identified by the difference in the power deposition profiles between X-mode and O-mode. The optimal polarization for X-mode launch is in good agreement with theoretical expectations.

Reusable Launch Vehicle Control in Multiple Time Scale Sliding Modes

NASA Technical Reports Server (NTRS)

Shtessel, Yuri

1999-01-01

A reusable launch vehicle control problem during ascent is addressed via multiple-time scaled continuous sliding mode control. The proposed sliding mode controller utilizes a two-loop structure and provides robust, de-coupled tracking of both orientation angle command profiles and angular rate command profiles in the presence of bounded external disturbances and plant uncertainties. Sliding mode control causes the angular rate and orientation angle tracking error dynamics to be constrained to linear, de-coupled, homogeneous, and vector valued differential equations with desired eigenvalues placement. The dual-time scale sliding mode controller was designed for the X-33 technology demonstration sub-orbital launch vehicle in the launch mode. 6DOF simulation results show that the designed controller provides robust, accurate, de-coupled tracking of the orientation angle command profiles in presence of external disturbances and vehicle inertia uncertainties. It creates possibility to operate the X-33 vehicle in an aircraft-like mode with reduced pre-launch adjustment of the control system.

KSC-2009-6634

NASA Image and Video Library

2009-11-30

CAPE CANAVERAL, Fla. – The Launch Control Center at NASA's Kennedy Space Center in Florida is ready to support NASA's 21st century space program. The louvered windows installed during the Apollo era have been replaced with new, hurricane-rated window systems in the four firing rooms and vestibule areas between the firing rooms. To avoid operational impacts and protect the firing rooms from the elements, the new windows were installed on the outside of the original windows, enclosing the space formerly occupied by the louvers until the new windows were leak tested. Photo credit: NASA/Jack Pfaller

KSC-2009-6631

NASA Image and Video Library

2009-11-30

CAPE CANAVERAL, Fla. – The Launch Control Center at NASA's Kennedy Space Center in Florida is ready to support NASA's 21st century space program. The louvered windows installed during the Apollo era have been replaced with new, hurricane-rated window systems in the four firing rooms and vestibule areas between the firing rooms. To avoid operational impacts and protect the firing rooms from the elements, the new windows were installed on the outside of the original windows, enclosing the space formerly occupied by the louvers until the new windows were leak tested. Photo credit: NASA/Jack Pfaller

KSC-2009-6632

NASA Image and Video Library

2009-11-30

CAPE CANAVERAL, Fla. – The Launch Control Center at NASA's Kennedy Space Center in Florida is ready to support NASA's 21st century space program. The louvered windows installed during the Apollo era have been replaced with new, hurricane-rated window systems in the four firing rooms and vestibule areas between the firing rooms. To avoid operational impacts and protect the firing rooms from the elements, the new windows were installed on the outside of the original windows, enclosing the space formerly occupied by the louvers until the new windows were leak tested. Photo credit: NASA/Jack Pfaller

KSC-2009-6633

NASA Image and Video Library

2009-11-30

CAPE CANAVERAL, Fla. – The Launch Control Center at NASA's Kennedy Space Center in Florida is ready to support NASA's 21st century space program. The louvered windows installed during the Apollo era have been replaced with new, hurricane-rated window systems in the four firing rooms and vestibule areas between the firing rooms. To avoid operational impacts and protect the firing rooms from the elements, the new windows were installed on the outside of the original windows, enclosing the space formerly occupied by the louvers until the new windows were leak tested. Photo credit: NASA/Jack Pfaller

STS-94 Mission Specialist Gernhardt in LC-39A White Room

NASA Technical Reports Server (NTRS)

1997-01-01

STS-94 Mission Specialist Michael L. Gernhardt prepares to enter the Space Shuttle Columbia at Launch Pad 39A in preparation for launch. He first flew in this capacity on STS-69. He has been a professional deep sea diver and engineer and holds a doctorate in bioengineering. Gernhardt will be in charge of the Blue shift and as flight engineer will operate and maintain the orbiter while Halsell and Still are asleep as members of the Red shift. He will also back them up on the flight deck during the ascent and re- entry phases of the mission. Gernhardt and six fellow crew members will lift off during a launch window that opens at 1:50 a.m. EDT, July 1. The launch window will open 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reach the space center.

STS-94 Payload Specialist Linteris in LC-39A White Room

NASA Technical Reports Server (NTRS)

1997-01-01

STS-94 Payload Specialist Gregory T. Linteris prepares to enter the Space Shuttle Columbia at Launch Pad 39A in preparation for launch. He holds a doctorate in mechanical and aerospace engineering. Linteris has worked at the National Institute of Standards and Technology and is the Principal Investigator on a NASA microgravity combustion experiment. As a member of the Red team, Linteris will concentrate on three combustion experiments. Two of these experiments are housed in the Combustion Module. He will also be backing up crew members on the other Microgravity Science Laboratory-1 (MSL-1) investigations. He and six fellow crew members will lift off during a launch window that opens at 1:50 a.m. EDT, July 1. The launch window will open 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reach the space center.

KSC-97PC972

NASA Image and Video Library

1997-07-01

STS-94 Payload Specialist Roger K. Crouch prepares to enter the Space Shuttle Columbia at Launch Pad 39A in preparation for launch. He is the Chief Scientist of the NASA Microgravity Space and Applications Division. He also has served as a Program Scientist for previous Spacelab microgravity missions and is an expert in semiconductor crystal growth. Since Crouch has more than 25 years of experience as a materials scientist, he will be concentrating on the five physics of materials processing experiments in the Middeck Glovebox Facility on the Blue shift. He will also share the workload with Thomas by monitoring the materials furnace experiments during this time. Crouch and six fellow crew members will lift off during a launch window that opens at 1:50 p.m. EDT, July 1. The launch window will open 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reach the space center

Astronaut Virgil Grissom shown through window of open hatch on Gemini craft

NASA Technical Reports Server (NTRS)

1965-01-01

Astronaut Virgil I. Grissom, the command pilot of the Gemini-Titan 3 three orbit mission, is shown through the window of the open hatch on Gemini spacecraft in the white room on the mornining of the launch.

KSC-03pd0980

NASA Image and Video Library

2003-04-04

KENNEDY SPACE CENTER, FLA. - Workers prepare the shrouded Mars Exploration Rover 2 (MER-2) for mating to the lander. Set to launch in Spring 2003, the MER Mission consists of two identical rovers, landing at different regions of Mars, designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

Flexible Modes Control Using Sliding Mode Observers: Application to Ares I

NASA Technical Reports Server (NTRS)

Shtessel, Yuri B.; Hall, Charles E.; Baev, Simon; Orr, Jeb S.

2010-01-01

The launch vehicle dynamics affected by bending and sloshing modes are considered. Attitude measurement data that are corrupted by flexible modes could yield instability of the vehicle dynamics. Flexible body and sloshing modes are reconstructed by sliding mode observers. The resultant estimates are used to remove the undesirable dynamics from the measurements, and the direct effects of sloshing and bending modes on the launch vehicle are compensated by means of a controller that is designed without taking the bending and sloshing modes into account. A linearized mathematical model of Ares I launch vehicle was derived based on FRACTAL, a linear model developed by NASA/MSFC. The compensated vehicle dynamics with a simple PID controller were studied for the launch vehicle model that included two bending modes, two slosh modes and actuator dynamics. A simulation study demonstrated stable and accurate performance of the flight control system with the augmented simple PID controller without the use of traditional linear bending filters.

Launch mission summary: FLTSATCOM-D Atlas/Centaur-57

NASA Technical Reports Server (NTRS)

1980-01-01

The largest and heaviest spacecraft yet to be launched into geosynchronous orbit by an Atlas Centaur launch vehicle, FLTSATCOM D is part of a versatile military satellite communication system which includes terminals at Navy land bases, and on naval aircraft, ships, and submarines. The design and capabilities of the launch vehicle are described as well as those of the satellite. Information relative to launch windows, flight plan, radar and telemetry coverage, selected trajectory information is presented. A brief sequence of flight events is included.

KSC-2009-3683

NASA Image and Video Library

2009-06-10

CAPE CANAVERAL, Fla. – A new window is lowered toward the existing Firing Room windows in the Launch Control Center at NASA's Kennedy Space Center in Florida. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Jack Pfaller

KSC-2009-3682

NASA Image and Video Library

2009-06-10

CAPE CANAVERAL, Fla. – A new window is lowered toward the existing Firing Room windows in the Launch Control Center at NASA's Kennedy Space Center in Florida. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Jack Pfaller

KSC-2009-3681

NASA Image and Video Library

2009-06-10

CAPE CANAVERAL, Fla. – Work continues on removing the louvers and replacing the windows on the Firing Room windows in the Launch Control Center at NASA's Kennedy Space Center in Florida. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Jack Pfaller

KSC-2009-3684

NASA Image and Video Library

2009-06-10

CAPE CANAVERAL, Fla. – Alongside the Launch Control Center at NASA's Kennedy Space Center in Florida, a new window is prepared to be lifted up to the existing Firing Room windows. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Jack Pfaller

KSC-2009-3685

NASA Image and Video Library

2009-06-10

CAPE CANAVERAL, Fla. – A new window is raised toward the existing Firing Room windows in the Launch Control Center at NASA's Kennedy Space Center in Florida. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Jack Pfaller

KSC-2009-3687

NASA Image and Video Library

2009-06-10

CAPE CANAVERAL, Fla. – Workers at NASA's Kennedy Space Center in Florida secure a new window on the Firing Room in the Launch Control Center. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Jack Pfaller

Mission Design for the Lunar Reconnaissance Orbiter

NASA Technical Reports Server (NTRS)

Beckman, Mark

2007-01-01

The Lunar Reconnaissance Orbiter (LRO) will be the first mission under NASA's Vision for Space Exploration. LRO will fly in a low 50 km mean altitude lunar polar orbit. LRO will utilize a direct minimum energy lunar transfer and have a launch window of three days every two weeks. The launch window is defined by lunar orbit beta angle at times of extreme lighting conditions. This paper will define the LRO launch window and the science and engineering constraints that drive it. After lunar orbit insertion, LRO will be placed into a commissioning orbit for up to 60 days. This commissioning orbit will be a low altitude quasi-frozen orbit that minimizes stationkeeping costs during commissioning phase. LRO will use a repeating stationkeeping cycle with a pair of maneuvers every lunar sidereal period. The stationkeeping algorithm will bound LRO altitude, maintain ground station contact during maneuvers, and equally distribute periselene between northern and southern hemispheres. Orbit determination for LRO will be at the 50 m level with updated lunar gravity models. This paper will address the quasi-frozen orbit design, stationkeeping algorithms and low lunar orbit determination.

STS-9 Spacelab 1 Press Kit

NASA Technical Reports Server (NTRS)

1983-01-01

Press information on the STS-9/SPACELAB 1 mission is provided. Launch preparations, launch window, flight objectives, experiments, life sciences baseline data collection, SPACELAB 1 payload operations and control crew and specialists, and tracking and data management are among the topics explained.

KSC-2009-5001

NASA Image and Video Library

2009-09-04

CAPE CANAVERAL, Fla. – This aerial view shows NASA Kennedy Space Center's Launch Control Center at left and Vehicle Assembly Building at right. The Launch Control Center recently had installed new hurricane-rated window systems in the four Firing Rooms. Photo credit: NASA/Troy Cryder

Personal exposure to fine particulate air pollution while commuting: An examination of six transport modes on an urban arterial roadway.

PubMed

Chaney, Robert A; Sloan, Chantel D; Cooper, Victoria C; Robinson, Daniel R; Hendrickson, Nathan R; McCord, Tyler A; Johnston, James D

2017-01-01

Traffic-related air pollution in urban areas contributes significantly to commuters' daily PM2.5 exposures, but varies widely depending on mode of commuting. To date, studies show conflicting results for PM2.5 exposures based on mode of commuting, and few studies compare multiple modes of transportation simultaneously along a common route, making inter-modal comparisons difficult. In this study, we examined breathing zone PM2.5 exposures for six different modes of commuting (bicycle, walking, driving with windows open and closed, bus, and light-rail train) simultaneously on a single 2.7 km (1.68 mile) arterial urban route in Salt Lake City, Utah (USA) during peak "rush hour" times. Using previously published minute ventilation rates, we estimated the inhaled dose and exposure rate for each mode of commuting. Mean PM2.5 concentrations ranged from 5.20 μg/m3 for driving with windows closed to 15.21 μg/m3 for driving with windows open. The estimated inhaled doses over the 2.7 km route were 6.83 μg for walking, 2.78 μg for cycling, 1.28 μg for light-rail train, 1.24 μg for driving with windows open, 1.23 μg for bus, and 0.32 μg for driving with windows closed. Similarly, the exposure rates were highest for cycling (18.0 μg/hr) and walking (16.8 μg/hr), and lowest for driving with windows closed (3.7 μg/hr). Our findings support previous studies showing that active commuters receive a greater PM2.5 dose and have higher rates of exposure than commuters using automobiles or public transportation. Our findings also support previous studies showing that driving with windows closed is protective against traffic-related PM2.5 exposure.

Personal exposure to fine particulate air pollution while commuting: An examination of six transport modes on an urban arterial roadway

PubMed Central

Sloan, Chantel D.; Cooper, Victoria C.; Robinson, Daniel R.; Hendrickson, Nathan R.; McCord, Tyler A.; Johnston, James D.

2017-01-01

Traffic-related air pollution in urban areas contributes significantly to commuters’ daily PM2.5 exposures, but varies widely depending on mode of commuting. To date, studies show conflicting results for PM2.5 exposures based on mode of commuting, and few studies compare multiple modes of transportation simultaneously along a common route, making inter-modal comparisons difficult. In this study, we examined breathing zone PM2.5 exposures for six different modes of commuting (bicycle, walking, driving with windows open and closed, bus, and light-rail train) simultaneously on a single 2.7 km (1.68 mile) arterial urban route in Salt Lake City, Utah (USA) during peak “rush hour” times. Using previously published minute ventilation rates, we estimated the inhaled dose and exposure rate for each mode of commuting. Mean PM2.5 concentrations ranged from 5.20 μg/m3 for driving with windows closed to 15.21 μg/m3 for driving with windows open. The estimated inhaled doses over the 2.7 km route were 6.83 μg for walking, 2.78 μg for cycling, 1.28 μg for light-rail train, 1.24 μg for driving with windows open, 1.23 μg for bus, and 0.32 μg for driving with windows closed. Similarly, the exposure rates were highest for cycling (18.0 μg/hr) and walking (16.8 μg/hr), and lowest for driving with windows closed (3.7 μg/hr). Our findings support previous studies showing that active commuters receive a greater PM2.5 dose and have higher rates of exposure than commuters using automobiles or public transportation. Our findings also support previous studies showing that driving with windows closed is protective against traffic-related PM2.5 exposure. PMID:29121096

KSC-2009-3553

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At NASA's Kennedy Space Center in Florida, new, hurricane-rated window systems for the Launch Control Center's four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts, the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers, and the old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Tim Jacobs

KSC-2009-3548

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At NASA's Kennedy Space Center in Florida, new, hurricane-rated window systems for the Launch Control Center's four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts, the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers, and the old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Tim Jacobs

KSC-2009-3550

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At NASA's Kennedy Space Center in Florida, new, hurricane-rated window systems for the Launch Control Center's four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts, the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers, and the old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Tim Jacobs

KSC-2009-3551

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At NASA's Kennedy Space Center in Florida, new, hurricane-rated window systems for the Launch Control Center's four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts, the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers, and the old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Tim Jacobs

KSC-2009-3549

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At NASA's Kennedy Space Center in Florida, new, hurricane-rated window systems for the Launch Control Center's four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts, the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers, and the old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Tim Jacobs

KSC-2009-3552

NASA Image and Video Library

2009-06-05

CAPE CANAVERAL, Fla. – At NASA's Kennedy Space Center in Florida, new, hurricane-rated window systems for the Launch Control Center's four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts, the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers, and the old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Tim Jacobs

Aerials of Orion on Launch Pad 37 from Helicopter

NASA Image and Video Library

2014-12-04

This helicopter view of the Kennedy Space Center Visitor Complex shows the thousands of vehicles parked where guests gather to see the launch of the Orion Flight Test. The liftoff was postponed because of an issue related to fill and drain valves on the Delta IV Heavy rocket that teams could not troubleshoot by the time the launch window expired.

International Ultraviolet Explorer (IUE) satellite mission analysis

NASA Technical Reports Server (NTRS)

Cook, R. A.; Griffin, J. H.

1975-01-01

The results are presented of the mission analysis performed by Computer Sciences Corporation (CSC) in support of the International Ultraviolet Explorer (IUE) satellite. The launch window is open for three separate periods (for a total time of 7 months) during the year extending from July 20, 1977, to July 20, 1978. The synchronous orbit shadow constraint limits the launch window to approximately 88 minutes per day. Apogee boost motor fuel was computed to be 455 pounds (206 kilograms) and on-station weight was 931 pounds (422 kilograms). The target orbit is elliptical synchronous, with eccentricity 0.272 and 24 hour period.

X-38 on B-52 Wing Pylon - View from Observation Window

NASA Image and Video Library

1997-11-19

A unique, close-up view of the X-38 under the wing of NASA's B-52 mothership prior to launch of the lifting-body research vehicle. The photo was taken from the observation window of the B-52 bomber as it banked in flight.

KSC-2009-3686

NASA Image and Video Library

2009-06-10

CAPE CANAVERAL, Fla. – Workers at NASA's Kennedy Space Center in Florida carefully place a new window on the Firing Room in the Launch Control Center. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 & 2 and Firing Rooms 3 & 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Jack Pfaller

KSC-2009-5806

NASA Image and Video Library

2009-10-23

CAPE CANAVERAL, Fla. – This aerial view of the Launch Control Center at NASA's Kennedy Space Center in Florida shows the installation of new windows nearing completion. New, hurricane-rated window systems for the four Firing Rooms and the vestibule areas between Firing Rooms 1 and 2 and Firing Rooms 3 and 4 are being installed. In order to avoid operational impacts the new windows are being installed on the outside of the existing windows, enclosing the space formerly occupied by the louvers. The old windows will remain in place until the new windows are completely installed and leak tested. This approach will continue to keep the firing rooms from being exposed to the elements. Photo credit: NASA/Kim Shiflett

KSC01kodi066

NASA Image and Video Library

2001-08-09

KODIAK ISLAND, Alaska -- The PICSat and Starshine 3 (back) payloads wait for their launch aboard the Athena 1 launch vehicle at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01KODI040

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Castor 120, the first stage of the Athena 1 launch vehicle, is raised off a truck at the launch pad at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi063

NASA Image and Video Library

2001-08-09

KODIAK ISLAND, Alaska -- The PCSat payload waits for its launch aboard the Athena 1 launch vehicle at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi059

NASA Image and Video Library

2001-07-31

KODIAK ISLAND, Alaska -- Technicians prepare the Starshine 3 payload for its launch aboard the Athena 1 launch vehicle at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi064

NASA Image and Video Library

2001-08-09

KODIAK ISLAND, Alaska -- Technicians prepare the PICSat payload for its launch aboard the Athena 1 launch vehicle at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01KODI055

NASA Image and Video Library

2001-05-29

KODIAK ISLAND, Alaska -- A convoy of trucks transports the stages of an Athena launch vehicle and supporting launch equipment to the pad at Kodiak Island, Alaska, as preparations to launch the Kodiak Star continue. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

8. VIEW OF SLC3W CONTROL ROOM (ROOM 105) FROM ITS ...

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

8. VIEW OF SLC-3W CONTROL ROOM (ROOM 105) FROM ITS NORTHEAST CORNER. TELEMETRY ROOM VISIBLE THROUGH WINDOWS IN SOUTH WALL. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

STS-94 Commander Halsell in LC-39A White Room

NASA Technical Reports Server (NTRS)

1997-01-01

STS-94 Mission Commander James D. Halsell, Jr., prepares to enter the Space Shuttle Columbia at Launch Pad 39A in preparation for launch. Halsell is on his fourth space flight, having served as commander of STS-83 and pilot of both STS-74 and STS-65. He is a lieutenant colonel in the Air Force and a former SR-71 Blackbird test pilot and holds masters degrees in management and space operations. Halsell will have responsibility for the success of the mission and will operate and maintain Columbia during the Red, or second shift. He will also assist with a materials science experiment and a protein crystal growth payload during the 16-day mission. Halsell and six fellow crew members will lift off during a launch window that opens at 1:50 a.m. EDT, July 1. The launch window will open 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reach the space center.

Orion Hatch Window Testing

NASA Image and Video Library

2018-04-09

Mark Nurge, Ph.D., a physicist in the Applied Physics Lab with the Exploration Research and Technology Programs at NASA's Kennedy Space Center in Florida, looks at data during the first optical quality test on a full window stack that is ready for installation in the docking hatch of NASA's Orion spacecraft. The data from the tests will help improve the requirements for manufacturing tolerances on Orion's windows and verify how the window should perform in space. Orion is being prepared for its first integrated uncrewed flight atop NASA's Space Launch System rocket on Exploration Mission-1.

Interplanetary mission design handbook. Volume 1, part 3: Earth to Jupiter ballistic mission opportunities, 1985-2005

NASA Technical Reports Server (NTRS)

Sergeyevsky, A. B.; Snyder, G. C.

1982-01-01

Graphical data necessary for the preliminary design of ballistic missions to Jupiter are provided. Contours of launch energy requirements, as well as many other launch and Jupiter arrival parameters, are presented in launch date/arrival date space for all launch opportunities from 1985 through 2005. In addition, an extensive text is included which explains mission design methods, from launch window development to Jupiter probe and orbiter arrival design, utilizing the graphical data in this volume as well as numerous equations relating various parameters.

Interplanetary mission design handbook. Volume 1, part 2: Earth to Mars ballistic mission opportunities, 1990-2005

NASA Technical Reports Server (NTRS)

Sergeyevsky, A. B.; Snyder, G. C.; Cunniff, R. A.

1983-01-01

Graphical data necessary for the preliminary design of ballistic missions to Mars are provided. Contours of launch energy requirements, as well as many other launch and Mars arrival parameters, are presented in launch date/arrival date space for all launch opportunities from 1990 through 2005. In addition, an extensive text is included which explains mission design methods, from launch window development to Mars probe and orbiter arrival design, utilizing the graphical data as well as numerous equations relating various parameters.

Interplanetary mission design handbook. Volume 1, part 1: Earth to Venus ballistic mission opportunities, 1991-2005

NASA Technical Reports Server (NTRS)

Sergeyevsky, A. B.; Yin, N. H.

1983-01-01

Graphical data necessary for the preliminary design of ballistic missions to Venus is presented. Contours of launch energy requirements, as well as many other launch and arrival parameters, are presented in launch data/arrival date space for all launch opportunities from 1991 through 2005. An extensive text is included which explains mission design methods, from launch window development to Venus probe and orbiter arrival design, utilizing the graphical data in this volume as well as numerous equations relating various parameters.

KSC01KODI057

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Technicians prepare the Athena I launch vehicle for flight at Kodiak Island, Alaska, as processing for the launch of Kodiak Star proceeds. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC-01pp1549

NASA Image and Video Library

2001-09-04

KODIAK ISLAND, Alaska -- At the Launch Service Structure, Kodiak Launch Complex (KLC), the fairing is lowered over the Kodiak Star spacecraft in preparation for launch. The first orbital launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

ARES I-X Launch

NASA Image and Video Library

2009-10-27

NASA's Ares I-X rocket is seen through the windows of Firing Room One of teh Launch Control Center (LCC) at the Kennedy Space Center as it launches from pad 39b in Cape Canaveral, Fla., Wednesday, Oct. 28, 2009. The flight test will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

Mitigation of Collision Hazard for the International Space Station (ISS) from Globally Launched Objects

NASA Astrophysics Data System (ADS)

Schultz, Eric D.; Wilde, Paul D.

2013-09-01

For the International Space Station (ISS), it can take 6 to 24 hours to reliably catalog a newly disposed upper stage and up to 33 hours to plan and execute an avoidance maneuver. This creates a gap in the existing collision risk protection for newly launched vehicles, which covers the period when these launched objects are still under propulsive control; specifically, upper stage separation plus 100 minutes for most missions. This gap results in a vulnerability of the ISS from the end of current "Launch Collision Avoidance (COLA)" protection until approximately launch plus 56 hours.In order to help mitigate this gap, conjunction analyses are being developed that identify launch times when the disposed upper stage could violate safe separation distances from the ISS. Launch window cut-out times can be determined from the analysis and implemented to protect the ISS.The COLA Gap is considered to be a risk to ISS operations and vehicle safety. Methods can be used to mitigate the risk, but the criteria and process need to be established and developed in order to reduce operational disruptions and potential risk to ISS vehicle. New requirements and analytical methods can close the current COLA gap with minimal impact to typical launch windows for Geo-Transfer Orbit (GTO) and direct injection missions. Also, strategies can be established to produce common standards in the U.S. and the world to close the current Launch COLA gap.

Rover 2 Moved to Workstand

NASA Technical Reports Server (NTRS)

2003-01-01

January 28, 2003

The Mars Exploration Rover -2 is moved to a workstand in the Payload Hazardous Servicing Facility. Set to launch in 2003, the Mars. Exploration Rover Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, 2003, and the second rover a window opening June 25, 2003.

KSC-03pd1249

NASA Image and Video Library

2003-04-25

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility help guide the Mars Exploration Rover 1 (MER-1) as it is moved to the lander base petal for installation. The MER Mission consists of two identical rovers, landing at different regions of Mars, designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening June 5, and the second rover a window opening June 25. The rovers will be launched from Cape Canaveral Air Force Station.

KSC-03pd0987

NASA Image and Video Library

2003-04-04

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility examine the Mars Exploration Rover 2 (MER-2) as it is lowered onto the base petal of the lander. Set to launch in Spring 2003, the MER Mission consists of two identical rovers. Landing at different regions of Mars, they are designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd1250

NASA Image and Video Library

2003-04-25

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility guide the Mars Exploration Rover 1 (MER-1) as it is lowered onto the lander base petal for installation. The MER Mission consists of two identical rovers, landing at different regions of Mars, designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening June 5, and the second rover a window opening June 25. The rovers will be launched from Cape Canaveral Air Force Station.

KSC-03pd0984

NASA Image and Video Library

2003-04-04

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility check the Mars Exploration Rover 2 (MER-2) before it is lifted and moved to the lander where it will be mated to the base petal. Set to launch in Spring 2003, the MER Mission consists of two identical rovers, landing at different regions of Mars, designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd1251

NASA Image and Video Library

2003-04-25

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility guide the Mars Exploration Rover 1 (MER-1) as it is lowered onto the lander base petal for installation. The MER Mission consists of two identical rovers, landing at different regions of Mars, designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening June 5, and the second rover a window opening June 25. The rovers will be launched from Cape Canaveral Air Force Station.

KSC-03pd0988

NASA Image and Video Library

2003-04-04

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility release the overhead crane used to lower the Mars Exploration Rover 2 (MER-2) onto the base petal of the lander. Set to launch in Spring 2003, the MER Mission consists of two identical rovers. Landing at different regions of Mars, they are designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

Crane Lowers Aeroshell

NASA Technical Reports Server (NTRS)

2003-01-01

January 31, 2003

In the Payload Hazardous Servicing Facility, an overhead crane lowers the Mars Exploration Rover (MER) aeroshell toward a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0771

NASA Image and Video Library

2003-03-20

KENNEDY SPACE CENTER, Fla. - The solar arrays on the Mars Exploration Rover-2 (MER-2) are fully opened during a test in the Payload Hazardous Servicing Facility. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0957

NASA Image and Video Library

2003-04-02

KENNEDY SPACE CENTER, FLA. - The Mars Exploration Rover 1 (MER-1) is seen in the foreground after the science boom was deployed. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0209

NASA Image and Video Library

2003-01-28

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, workers lift the cover from the Mars Exploration Rover -2. Set to launch in 2003, the Mars Exploration Rover Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, 2003, and the second rover a window opening June 25, 2003.

KSC-03pd0909

NASA Image and Video Library

2003-03-29

KENNEDY SPACE CENTER, FLA. - Workers gather around the Mars Exploration Rover 2 (MER-2) before flight stow of the solar panels, still extended. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. The rovers will be identical to each other, but will land at different regions of Mars. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0232

NASA Image and Video Library

2003-01-31

KENNEDY SPACE CENTER, FLA. -- In the Payload Hazardous Servicing Facility, an overhead crane lifts the Mars Exploration Rover (MER) aeroshell for transfer to a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0913

NASA Image and Video Library

2003-03-29

KENNEDY SPACE CENTER, FLA. - Workers begin closing the solar panels on the Mars Exploration Rover 2 (MER-2) for flight stow. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. The rovers will be identical to each other, but will land at different regions of Mars. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0438

NASA Image and Video Library

2003-02-04

KENNEDY SPACE CENTER, FLA. -- The aeroshell for Mars Exploration Rover 2 rests on a rotation stand in the Payload Hazardous Servicing Facility. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0230

NASA Image and Video Library

2003-01-31

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, the Mars Exploration Rover (MER) aeroshell is being prepared for transfer to a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0768

NASA Image and Video Library

2003-03-20

KENNEDY SPACE CENTER, FLA. -- The Mars Exploration Rover-2 (MER-2) is ready for solar array testing in the Payload Hazardous Servicing Facility. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0786

NASA Image and Video Library

2003-03-21

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, the Mars Exploration Rover-2 (MER-2) is tested for mobility and maneuverability. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0234

NASA Image and Video Library

2003-01-31

KENNEDY SPACE CENTER, FLA. -- In the Payload Hazardous Servicing Facility, an overhead crane lowers the Mars Exploration Rover (MER) aeroshell toward a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0457

NASA Image and Video Library

2003-02-06

KENNEDY SPACE CENTER, FLA. -- Technicians secure the aeroshell for Mars Exploration Rover 2 to a workstand in the Payload Hazardous Servicing Facility. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover, a window opening June 25, 2003.

KSC-03pd0439

NASA Image and Video Library

2003-02-04

KENNEDY SPACE CENTER, FLA. -- The aeroshell for Mars Exploration Rover 2 rests on end after rotation in the Payload Hazardous Servicing Facility. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

Mars Exploration Rover (MER) aeroshell

NASA Image and Video Library

2003-01-31

In the Payload Hazardous Servicing Facility, workers prepare the Mars Exploration Rover (MER) aeroshell for transfer to a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0212

NASA Image and Video Library

2003-01-28

KENNEDY SPACE CENTER, FLA. -- The Mars Exploration Rover -2 is moved to a workstand in the Payload Hazardous Servicing Facility. Set to launch in 2003, the Mars Exploration Rover Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, 2003, and the second rover a window opening June 25, 2003.

KSC-03pd0236

NASA Image and Video Library

2003-01-31

KENNEDY SPACE CENTER, FLA. -- Workers in the Payload Hazardous Servicing Facility help guide the Mars Exploration Rover (MER) aeroshell onto a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0235

NASA Image and Video Library

2003-01-31

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility help guide the Mars Exploration Rover (MER) aeroshell as it is lowered toward a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0210

NASA Image and Video Library

2003-01-28

KENNEDY SPACE CENTER, FLA. -- In the Payload Hazardous Servicing Facility, workers get ready to remove the plastic covering from the Mars Exploration Rover -2. Set to launch in 2003, the Mars Exploration Rover Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, 2003, and the second rover a window opening June 25, 2003.

KSC-03pd0440

NASA Image and Video Library

2003-02-04

KENNEDY SPACE CENTER, FLA. - During processing, workers in the Payload Hazardous Servicing Facility work on part of the aeroshell for Mars Exploration Rover 2. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0785

NASA Image and Video Library

2003-03-21

KENNEDY SPACE CENTER, Fla. - Workers in the Payload Hazardous Servicing Facility check different parts of the Mars Exploration Rover-2 (MER-2) after testing the rover's mobility and maneuverability. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0955

NASA Image and Video Library

2003-04-02

KENNEDY SPACE CENTER, FLA. - A worker examines the Mars Exploration Rover 1 (MER-1) after the science boom was deployed. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0911

NASA Image and Video Library

2003-03-29

KENNEDY SPACE CENTER, FLA. - A worker checks a component of the Mars Exploration Rover 2 (MER-2) before flight stow of the solar panels, still extended. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. The rovers will be identical to each other, but will land at different regions of Mars. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0886

NASA Image and Video Library

2003-03-28

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, the Mars Exploration Rover-2 (MER-2) rests on the base petal of its lander assembly. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover, a window opening June 25.

KSC-03pd0958

NASA Image and Video Library

2003-04-02

KENNEDY SPACE CENTER, FLA. - On the Mars Exploration Rover 1 (MER-1), the science boom, below the front petal, is deployed. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0910

NASA Image and Video Library

2003-03-29

KENNEDY SPACE CENTER, FLA. - Workers make additional checks of the Mars Exploration Rover 2 (MER-2) before flight stow of the solar panels, still extended. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. The rovers will be identical to each other, but will land at different regions of Mars. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0213

NASA Image and Video Library

2003-01-28

KENNEDY SPACE CENTER, FLA. - Workers in the Payload Hazardous Servicing Facility move the Mars Exploration Rover -2 to a workstand in the high bay. Set to launch in 2003, the Mars Exploration Rover Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, 2003, and the second rover a window opening June 25, 2003.

KSC-03pd0793

NASA Image and Video Library

2003-03-21

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, the Mars Exploration Rover-2 (MER-2) rolls over ramps to test its mobility and maneuverability. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0914

NASA Image and Video Library

2003-03-29

KENNEDY SPACE CENTER, FLA. - After closing the solar panels for flight stow, workers examine the Mars Exploration Rover 2 (MER-2). Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. The rovers will be identical to each other, but will land at different regions of Mars. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC01kodi058

NASA Image and Video Library

2001-07-31

KODIAK ISLAND, Alaska -- Technicians prepare the Starshine 3 payload for its launch aboard the Athena 1 launch vehicle, while the payload fairing awaits processing, at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi080

NASA Image and Video Library

2001-09-05

KODIAK ISLAND, ALASKA - The Launch Service Structure, Kodiak Launch Complex (KLC), on Kodiak Island is viewed from a distance. Kodiak Star, the first launch to take place from KLC, is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

KSC01KODI045

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Technicians inspect and secure Castor 120, the first stage of the Athena 1 launch vehicle, on the launch mount at Kodiak Island, Alaska, as processing for the launch of Kodiak Star proceeds. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi079

NASA Image and Video Library

2001-09-05

KODIAK ISLAND, ALASKA - A transporter moves the encapsulated Kodiak Star spacecraft into position in the Launch Service Structure, Kodiak Launch Complex (KLC), for final stacking for launch. The first launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

KSC-01pp1547

NASA Image and Video Library

2001-09-04

KODIAK ISLAND, Alaska -- In the Launch Service Structure, Kodiak Launch Complex (KLC), workers check the fairing that is to be placed around the Kodiak Star spacecraft in preparation for launch. The first orbital launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

KSC-01pp1548

NASA Image and Video Library

2001-09-04

KODIAK ISLAND, Alaska -- Inside the Launch Service Structure, Kodiak Launch Complex (KLC), workers watch as the fairing (background) is lifted before encapsulating the Kodiak Star spacecraft in preparation for launch. The first orbital launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

KSC01kodi076

NASA Image and Video Library

2001-09-04

KODIAK ISLAND, ALASKA - In the Launch Service Structure, Kodiak Launch Complex (KLC), the fairing is lowered over the Kodiak Star spacecraft in preparation for launch. The first launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

KSC01kodi074

NASA Image and Video Library

2001-09-04

KODIAK ISLAND, ALASKA - In the Launch Service Structure, Kodiak Launch Complex (KLC), the Kodiak Star spacecraft is ready for encapsulation in the fairing, as preparation for launch. The first launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

ARES I-X Launch

NASA Image and Video Library

2009-10-27

NASA Ares I-X Launch Director Ed Mango, left, laughs as NASA Ares I-X Assistant Launch Director Pete Nickolenko looks out the window of Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center prior to the launch of the Ares I-X rocket from pad 39b at the Kennedy Space Center in Cape Canaveral, Fla., Wednesday, Oct. 28, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

KSC01KODI046

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Technicians install Orbis 21D Equipment Section Boost Motor, the second stage of the Athena 1 launch vehicle, at Kodiak Island, Alaska, as processing for the launch of Kodiak Star proceeds. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi062

NASA Image and Video Library

2001-07-31

KODIAK ISLAND, Alaska -- Technicians prepare the Starshine 3 payload, while the payload fairing of the Athena 1 launch vehicle awaits servicing at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program

KSC01KODI043

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Castor 120, the first stage of the Athena 1 launch vehicle, is lowered into place at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01KODI039

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Trucks transporting Orbis 21D Equipment Section Boost Motor, the second stage of the Athena 1 launch vehicle, arrive at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01KODI042

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Castor 120, the first stage of the Athena 1 launch vehicle, is lifted into a vertical position at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01KODI041

NASA Image and Video Library

2001-05-31

KODIAK ISLAND, Alaska -- Technicians inspect Castor 120, the first stage of the Athena 1 launch vehicle, at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

Orion Hatch Window Testing

NASA Image and Video Library

2018-04-09

The first optical quality testing on a full window stack that is ready for installation in the docking hatch of NASA's Orion spacecraft is underway inside a laboratory in the Neil Armstrong Operations and Checkout Building at the agency's Kennedy Space Center in Florida. The test is being performed by a team from the center's Exploration Research and Technology Programs. The data from the tests will help improve the requirements for manufacturing tolerances on Orion's windows and verify how the window should perform in space. Orion is being prepared for its first integrated uncrewed flight atop NASA's Space Launch System rocket on Exploration Mission-1.

Reusable Launch Vehicle Control In Multiple Time Scale Sliding Modes

NASA Technical Reports Server (NTRS)

Shtessel, Yuri; Hall, Charles; Jackson, Mark

2000-01-01

A reusable launch vehicle control problem during ascent is addressed via multiple-time scaled continuous sliding mode control. The proposed sliding mode controller utilizes a two-loop structure and provides robust, de-coupled tracking of both orientation angle command profiles and angular rate command profiles in the presence of bounded external disturbances and plant uncertainties. Sliding mode control causes the angular rate and orientation angle tracking error dynamics to be constrained to linear, de-coupled, homogeneous, and vector valued differential equations with desired eigenvalues placement. Overall stability of a two-loop control system is addressed. An optimal control allocation algorithm is designed that allocates torque commands into end-effector deflection commands, which are executed by the actuators. The dual-time scale sliding mode controller was designed for the X-33 technology demonstration sub-orbital launch vehicle in the launch mode. Simulation results show that the designed controller provides robust, accurate, de-coupled tracking of the orientation angle command profiles in presence of external disturbances and vehicle inertia uncertainties. This is a significant advancement in performance over that achieved with linear, gain scheduled control systems currently being used for launch vehicles.

Non-numeric computation for high eccentricity orbits. [Earth satellite orbit perturbation

NASA Technical Reports Server (NTRS)

Sridharan, R.; Renard, M. L.

1975-01-01

Geocentric orbits of large eccentricity (e = 0.9 to 0.95) are significantly perturbed in cislunar space by the sun and moon. The time-history of the height of perigee, subsequent to launch, is particularly critical. The determination of 'launch windows' is mostly concerned with preventing the height of perigee from falling below its low initial value before the mission lifetime has elapsed. Between the extremes of high accuracy digital integration of the equations of motion and of using an approximate, but very fast, stability criteria method, this paper is concerned with the developement of a method of intermediate complexity using non-numeric computation. The computer is used as the theory generator to generalize Lidov's theory using six osculating elements. Symbolic integration is completely automatized and the output is a set of condensed formulae well suited for repeated applications in launch window analysis. Examples of applications are given.

Searching for O-X-B mode-conversion window with monitoring of stray microwave radiation in LHD

NASA Astrophysics Data System (ADS)

Igami, H.; Kubo, S.; Laqua, H. P.; Nagasaki, K.; Inagaki, S.; Notake, T.; Shimozuma, T.; Yoshimura, Y.; Mutoh, T.; LHD Experimental Group

2006-10-01

In the Large Helical Device, the stray microwave radiation is monitored by using so-called sniffer probes during electron cyclotron heating. In monitoring the stray radiation, we changed the microwave beam injection angle and search the O-X-B mode-conversion window to excite electron Bernstein waves (EBWs). When the microwave beam is injected toward the vicinity of the predicted O-X-B mode-conversion window, the electron temperature rises in the central part of overdense plasmas. In that case, the stray radiation level near the injection antenna becomes low. These results indicate that monitoring the stray radiation near the injection antenna is helpful in confirming the effectiveness of excitation of EBWs simply without precise analysis.

STS-47 Pilot Brown on OV-105's flight deck ten minutes after SSME cutoff

NASA Technical Reports Server (NTRS)

1992-01-01

STS-47 Pilot Curtis L. Brown, Jr, is photographed at Endeavour's, Orbiter Vehicle (OV) 105's, pilot station about ten minutes after space shuttle main engine (SSME) cutoff on launch day. Brown smiles from inside the launch and entry suit (LES) and launch and entry helmet (LEH). In the background are the flight mirror assembly silhouetted against forward window W5, control panels, and a checklist.

Lateral mode control in edge-emitting lasers with modified mirrors

NASA Astrophysics Data System (ADS)

Payusov, A.; Serin, A.; Mukhin, I.; Shernyakov, Y.; Zadiranov, Y.; Maximov, M.; Gordeev, N.

2017-11-01

We present a study on lateral mode control in edge-emitting lasers with profiled mirror reflectivity. The object was to eliminate high-order lateral modes in conventional ridge-waveguide InAs/InGaAs QD (quantum dot) lasers with the stripe width of 10 μm. We have used a FIB (focused ion beam) technique to selectively etch windows in the AR (anti-reflection) facet coatings in order to introduce extra mirror losses for the high order modes. This approach allowed us to eliminate the first-order mode lasing without deterioration of the laser parameters. We suppose that further optimisation of the laser heterostructure and window designs may lead to a pure lateral single-mode lasing in the broadened ridge waveguides.

51. VIEW OF LORAL ADS 100A COMPUTERS LOCATED CENTRALLY ON ...

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

51. VIEW OF LORAL ADS 100A COMPUTERS LOCATED CENTRALLY ON NORTH WALL OF TELEMETRY ROOM (ROOM 106). SLC-3W CONTROL ROOM IS VISIBLE IN BACKGROUND THROUGH WINDOW IN NORTH WALL. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

KSC01kodi071

NASA Image and Video Library

2001-08-08

KODIAK ISLAND, Alaska -- Technicians transport the Sapphire payload at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC-2011-1063

NASA Image and Video Library

2011-01-07

CAPE CANAVERAL, Fla. -- Workers hang artwork in the second-floor lobby of the Propellants North Administrative and Maintenance Facility at NASA's Kennedy Space Center in Florida. The artwork was produced by Greg Lee, a graphics specialist with Abacus Technology Corp., and features a silhouette of a shuttle, one of the most recognizable American icons, rolling out to Launch Complex 39. Next to the artwork are recycled firing room windows from Kennedy's Launch Control Center. Launch controllers viewed every shuttle rollout and launch through those windows before they were repurposed. The environmentally friendly facility is slated to be NASA's second Platinum-rated by the U.S. Green Building Council's (USGBC) Leadership in Environmental and Energy Design (LEED) certification system. It will be the space agency's first net-zero facility, which means it will produce enough energy onsite from renewable sources to offset what it requires to operate. The facility consists of a two-story administrative building to house managers, mechanics and technicians who fuel spacecraft at Kennedy, and a single-story shop to store cryogenic fuel transfer equipment. Photo credit: NASA/Frankie Martin

KSC-97PC957

NASA Image and Video Library

1997-07-01

STS-94 Payload Specialist Roger K. Crouch is helped into his launch/entry suit by a suit technician in the Operations and Checkout (O&C) Building after the suit has been given a pressure test. He is the Chief Scientist of the NASA Microgravity Space and Applications Division. He also has served as a Program Scientist for previous Spacelab microgravity missions and is an expert in semiconductor crystal growth. Since Crouch has more than 25 years of experience as a materials scientist, he will be concentrating on the five physics of materials processing experiments in the Middeck Glovebox Facility on the Blue shift. He will also share the workload with Thomas by monitoring the materials furnace experiments during this time. Crouch and six fellow crew members will shortly depart the O&C and head for Launch Pad 39A, where the Space Shuttle Columbia will lift off during a launch window that opens at 1:50 p.m. EDT, July 1. The launch window was opened 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reached the space center

KSC-97PC952

NASA Image and Video Library

1997-07-01

STS-94 Mission Specialist Donald A. Thomas smiles as a suit technician helps him into his launch/entry suit in the Operations and Checkout (O&C) Building. He has flown on STS-83, STS-70 and STS-65. He holds a doctorate in materials science and has been the Principal Investigator for a Space Shuttle crystal growth experiment. Because of his background in materials science, Thomas will be concentrating his efforts during the Red shift on the five experiments in this discipline in the Large Isothermal Furnace. He also will work on the ten materials science investigations in the Electromagnetic Containerless Processing Facility and four that will be measuring the effects of microgravity and motion in the orbiter on the experiments. Thomas and six fellow crew members will shortly depart the O&C and head for Launch Pad 39A, where the Space Shuttle Columbia will lift off during a launch window that opens at 1:50 p.m. EDT, July 1. The launch window was opened 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reached the space center

Launch Window Analysis for the Magnetospheric Multiscale Mission

NASA Technical Reports Server (NTRS)

Williams, Trevor W.

2012-01-01

The NASA Magnetospheric Multiscale (MMS) mission will fly four spinning spacecraft in formation in highly elliptical orbits to study the magnetosphere of the Earth. This paper describes the development of an MMS launch window tool that uses the orbitaveraged Variation of Parameter equations as the basis for a semi-analytic quantification of the dominant oblateness and lunisolar perturbation effects on the MMS orbit. This approach, coupled with a geometric interpretation of all of the MMS science and engineering constraints, allows a scan of 180(sup 2) = 32,400 different (RAAN, AOP) pairs to be carried out for a specified launch day in less than 10 s on a typical modern laptop. The resulting plot indicates the regions in (RAAN, AOP) space where each constraint is satisfied or violated: their intersection gives, in an easily interpreted graphical manner, the final solution space for the day considered. This tool, SWM76, is now used to provide launch conditions to the full fidelity (but far slower) MMS simulation code: very good agreement has been observed between the two methods.

Three Orbital Burns to Molniya Orbit Via Shuttle_Centaur G Upper Stage

NASA Technical Reports Server (NTRS)

Williams, Craig H.

2015-01-01

An unclassified analytical trajectory design, performance, and mission study was done for the 1982 to 1986 joint National Aeronautics and Space Administration (NASA)-United States Air Force (USAF) Shuttle/Centaur G upper stage development program to send performance-demanding payloads to high orbits such as Molniya using an unconventional orbit transfer. This optimized three orbital burn transfer to Molniya orbit was compared to the then-baselined two burn transfer. The results of the three dimensional trajectory optimization performed include powered phase steering data and coast phase orbital element data. Time derivatives of the orbital elements as functions of thrust components were evaluated and used to explain the optimization's solution. Vehicle performance as a function of parking orbit inclination was given. Performance and orbital element data was provided for launch windows as functions of launch time. Ground track data was given for all burns and coasts including variation within the launch window. It was found that a Centaur with fully loaded propellant tanks could be flown from a 37 deg inclination low Earth parking orbit and achieve Molniya orbit with comparable performance to the baselined transfer which started from a 57 deg inclined orbit: 9,545 versus 9,552 lb of separated spacecraft weight, respectively. There was a significant reduction in the need for propellant launch time reserve for a 1 hr window: only 78 lb for the three burn transfer versus 320 lb for the two burn transfer. Conversely, this also meant that longer launch windows over more orbital revolutions could be done for the same amount of propellant reserve. There was no practical difference in ground tracking station or airborne assets needed to secure telemetric data, even though the geometric locations of the burns varied considerably. There was a significant adverse increase in total mission elapsed time for the three versus two burn transfer (12 vs. 1-1/4 hr), but could be accommodated by modest modifications to Centaur systems. Future applications were discussed. The three burn transfer was found to be a viable, arguably preferable, alternative to the two burn transfer.

Three Orbital Burns to Molniya Orbit via Shuttle Centaur G Upper Stage

NASA Technical Reports Server (NTRS)

Williams, Craig H.

2014-01-01

An unclassified analytical trajectory design, performance, and mission study was done for the 1982-86 joint NASA-USAF Shuttle/Centaur G upper stage development program to send performance-demanding payloads to high orbits such as Molniya using an unconventional orbit transfer. This optimized three orbital burn transfer to Molniya orbit was compared to the then-baselined two burn transfer. The results of the three dimensional trajectory optimization performed include powered phase steering data and coast phase orbital element data. Time derivatives of the orbital elements as functions of thrust components were evaluated and used to explain the optimization's solution. Vehicle performance as a function of parking orbit inclination was given. Performance and orbital element data was provided for launch windows as functions of launch time. Ground track data was given for all burns and coasts including variation within the launch window. It was found that a Centaur with fully loaded propellant tanks could be flown from a 37deg inclination low Earth parking orbit and achieve Molniya orbit with comparable performance to the baselined transfer which started from a 57deg inclined orbit: 9,545 lb vs. 9,552 lb of separated spacecraft weight respectively. There was a significant reduction in the need for propellant launch time reserve for a one hour window: only 78 lb for the three burn transfer vs. 320 lb for the two burn transfer. Conversely, this also meant that longer launch windows over more orbital revolutions could be done for the same amount of propellant reserve. There was no practical difference in ground tracking station or airborne assets needed to secure telemetric data, even though the geometric locations of the burns varied considerably. There was a significant adverse increase in total mission elapsed time for the three vs. two burn transfer (12 vs. 11/4 hrs), but could be accommodated by modest modifications to Centaur systems. Future applications were discussed. The three burn transfer was found to be a viable, arguably preferable, alternative to the two burn transfer.

KSC-03pd0764

NASA Image and Video Library

2003-03-20

KENNEDY SPACE CENTER, Fla. - With cables released, this Mars Exploration Rover sits on the floor of the Payload Hazardous Servicing Facility. Processing of the rovers, cruise stage, lander and heat shield elements is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0765

NASA Image and Video Library

2003-03-20

KENNEDY SPACE CENTER, Fla. - With cables released, this Mars Exploration Rover (MER) sits on the floor of the Payload Hazardous Servicing Facility. Processing of the rovers, cruise stage, lander and heat shield elements is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0762

NASA Image and Video Library

2003-03-20

KENNEDY SPACE CENTER, Fla. - A worker in the Payload Hazardous Servicing Facility makes adjustments on one of the Mars Exploration Rovers (MER). Processing of the rovers, cruise stage, lander and heat shield elements is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0883

NASA Image and Video Library

2003-03-28

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, workers adjust the position of the Mars Exploration Rover-2 (MER-2) on the base petal of its lander assembly. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover, a window opening June 25.

KSC-03pd0784

NASA Image and Video Library

2003-03-21

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, the Mars Exploration Rover-2 (MER-2) has rotated. Atop the rover can be seen the cameras, mounted on a Pancam Mast Assembly (PMA). Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0795

NASA Image and Video Library

2003-03-21

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, workers watch as the Mars Exploration Rover-2 (MER-2) rolls over ramps to test its mobility and maneuverability. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0791

NASA Image and Video Library

2003-03-21

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, workers watch as the Mars Exploration Rover-2 (MER-2) rolls over ramps to test its mobility and maneuverability. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0790

NASA Image and Video Library

2003-03-21

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, workers watch as the Mars Exploration Rover-2 (MER-2) rolls over ramps to test its mobility and maneuverability. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25.

KSC-03pd0879

NASA Image and Video Library

2003-03-28

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, workers move the Mars Exploration Rover-2 (MER-2) into position over the base petal of its lander assembly. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover, a window opening June 25.

KSC-03pd0881

NASA Image and Video Library

2003-03-28

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, workers lower the Mars Exploration Rover-2 (MER-2) onto the base petal of its lander assembly. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover, a window opening June 25.

KSC-03pd0761

NASA Image and Video Library

2003-03-20

KENNEDY SPACE CENTER, Fla. - Workers in the Payload Hazardous Servicing Facility look over one of the Mars Exploration Rovers (MER). Processing of the rovers, cruise stage, lander and heat shield elements is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0758

NASA Image and Video Library

2003-03-20

KENNEDY SPACE CENTER, FLA. - One of the Mars Exploration Rovers (MER) sits on a stand in the Payload Hazardous Servicing Facility. Processing of the rovers, cruise stage, lander and heat shield elements is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0877

NASA Image and Video Library

2003-03-28

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, workers prepare the base petal of a lander assembly to receive the Mars Exploration Rover-2 (MER-2). Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover, a window opening June 25.

KSC-03pd0441

NASA Image and Video Library

2003-02-04

KENNEDY SPACE CENTER, FLA. - Shown are the Lander pedals for MER-1. These pedals fold up covering the Rover, which will be attached to the base pedal (not shown--empty spot in the center.) Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0211

NASA Image and Video Library

2003-01-28

KENNEDY SPACE CENTER, FLA. - After being cleaned up, the Mars Exploration Rover -2 is ready to be moved to a workstand in the Payload Hazardous Servicing Facility. Set to launch in 2003, the Mars Exploration Rover Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, 2003, and the second rover a window opening June 25, 2003.

KSC-03pd0878

NASA Image and Video Library

2003-03-28

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, workers move the Mars Exploration Rover-2 (MER-2) towards the base petal of its lander assembly. Set to launch in Spring 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day over various terrain. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover, a window opening June 25.

KSC-03pd0233

NASA Image and Video Library

2003-01-31

KENNEDY SPACE CENTER, FLA. - Suspended by an overhead crane in the Payload Hazardous Servicing Facility, the Mars Exploration Rover (MER) aeroshell is guided by workers as it moves to a rotation stand. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards (100 meters) each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC01kodi078

NASA Image and Video Library

2001-09-05

KODIAK ISLAND, ALASKA - Inside the Launch Service Structure, Kodiak Launch Complex (KLC), the final stage of the Athena I launch vehicle, with the Kodiak Star spacecraft, is maneuvered into place. The first launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

Use of DES Modeling for Determining Launch Availability for SLS

NASA Technical Reports Server (NTRS)

Watson, Michael; Staton, Eric; Cates, Grant; Finn, Ronald; Altino, Karen M.; Burns, K. Lee

2014-01-01

(1) NASA is developing a new heavy lift launch system for human and scientific exploration beyond Earth orbit comprising of the Space Launch System (SLS), Orion Multi-Purpose Crew Vehicle (MPCV), and Ground Systems Development and Operations (GSDO); (2) The desire of the system is to ensure a high confidence of successfully launching the exploration missions, especially those that require multiple launches, have a narrow Earth departure window, and high investment costs; and (3) This presentation discusses the process used by a Cross-Program team to develop the Exploration Systems Development (ESD) Launch Availability (LA) Technical Performance Measure (TPM) and allocate it to each of the Programs through the use of Discrete Event Simulations (DES).

KSC01KODI051

NASA Image and Video Library

2001-06-19

KODIAK ISLAND, Alaska -- Technicians lower the fueled Orbit Adjust Model (OAM), which navigates payloads into the correct orbit, onto Orbis 21D Equipment Section Boost Motor, the second stage of the Athena 1 launch vehicle, at the launch pad at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi075

NASA Image and Video Library

2001-09-04

KODIAK ISLAND, ALASKA - In the Launch Service Structure, Kodiak Launch Complex (KLC), the Kodiak Star spacecraft is ready for encapsulation in the fairing seen at right, above. The first launch to take place from KLC, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program. KLC is the newest commercial launch complex in the United States, ideal for launch payloads requiring low-Earth polar or sun-synchronous orbits

KSC01KODI050

NASA Image and Video Library

2001-06-19

KODIAK ISLAND, Alaska -- The fueled Orbit Adjust Model (OAM), which navigates payloads into the correct orbit, is installed onto Orbis 21D Equipment Section Boost Motor, the second stage of the Athena 1 launch vehicle, at the launch pad at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

Economical launching and accelerating control strategy for a single-shaft parallel hybrid electric bus

NASA Astrophysics Data System (ADS)

Yang, Chao; Song, Jian; Li, Liang; Li, Shengbo; Cao, Dongpu

2016-08-01

This paper presents an economical launching and accelerating mode, including four ordered phases: pure electrical driving, clutch engagement and engine start-up, engine active charging, and engine driving, which can be fit for the alternating conditions and improve the fuel economy of hybrid electric bus (HEB) during typical city-bus driving scenarios. By utilizing the fast response feature of electric motor (EM), an adaptive controller for EM is designed to realize the power demand during the pure electrical driving mode, the engine starting mode and the engine active charging mode. Concurrently, the smoothness issue induced by the sequential mode transitions is solved with a coordinated control logic for engine, EM and clutch. Simulation and experimental results show that the proposed launching and accelerating mode and its control methods are effective in improving the fuel economy and ensure the drivability during the fast transition between the operation modes of HEB.

KSC-98pc510

NASA Image and Video Library

1998-04-17

STS-90 Mission Specialist Kathryn (Kay) Hire is assisted by NASA and USA closeout crew members immediately preceding launch for the nearly 17-day Neurolab mission. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Hire and six fellow crew members will shortly enter the orbiter at KSC's Launch Pad 39B, where the Space Shuttle Columbia will lift off during a launch window that opens at 2:19 p.m. EDT, April 17

KSC-98pc514

NASA Image and Video Library

1998-04-17

STS-90 Payload Specialist Jay Buckey, M.D., is assisted by NASA and USA closeout crew members immediately preceding launch for the nearly 17-day Neurolab mission. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Buckey and six fellow crew members will shortly enter the orbiter at KSC's Launch Pad 39B, where the Space Shuttle Columbia will lift off during a launch window that opens at 2:19 p.m. EDT, April 17

STS-70 Commander Terence 'Tom' Henricks suits up

NASA Technical Reports Server (NTRS)

1995-01-01

STS-70 Commander Terence 'Tom' Henricks is donning his launch/entry suit in the Operations and Checkout Building with help from a suit technician. Henricks, who is about to make his third trip into space, and four crew members will depart shortly for Launch Pad 39B, where the Space Shuttle Discovery is undergoing final preparations for a liftoff scheduled during a two and a half hour launch window opening at 9:41 a.m. EDT.

STS-70 Mission Specialist Nancy Jane Currie suits up

NASA Technical Reports Server (NTRS)

1995-01-01

STS-70 Mission Specialist Nancy Jane Currie is donning her launch/entry suit in the Operations and Checkout Building with help from a suit technician. Currie has flown in space once before, on STS-57. Currie and four crew mates will depart shortly for Launch Pad 39B, where the Space Shuttle Discovery is undergoing final preparations for a liftoff scheduled during a two and a half hour launch window opening at 9:41 a.m. EDT.

KSC-2009-5191

NASA Image and Video Library

2009-09-23

CAPE CANAVERAL, Fla. – The mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station rolls back to reveal the United Launch Alliance Delta II rocket that will launch the Space Tracking and Surveillance System - Demonstrator into orbit. It is being launched by NASA for the Missile Defense System. The hour-long launch window opens at 8 a.m. EDT today. The STSS Demo is a space-based sensor component of a layered Ballistic Missile Defense System designed for the overall mission of detecting, tracking and discriminating ballistic missiles. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. Photo credit: NASA/Dimitri Gerondidakis

KSC01KODI035

NASA Image and Video Library

2001-05-29

KODIAK ISLAND, Alaska -- A special platform connects the barge with a ramp to allow Castor 120, the first stage of the Athena 1 launch vehicle, to safely move onto the dock at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC-2009-5193

NASA Image and Video Library

2009-09-23

CAPE CANAVERAL, Fla. – The mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station has been rolled back to reveal the United Launch Alliance Delta II rocket ready to launch the Space Tracking and Surveillance System - Demonstrator into orbit. It is being launched by NASA for the Missile Defense System. The hour-long launch window opens at 8 a.m. EDT today. The STSS Demo is a space-based sensor component of a layered Ballistic Missile Defense System designed for the overall mission of detecting, tracking and discriminating ballistic missiles. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-5192

NASA Image and Video Library

2009-09-23

CAPE CANAVERAL, Fla. – The mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station has been rolled back to reveal the United Launch Alliance Delta II rocket that will launch the Space Tracking and Surveillance System - Demonstrator into orbit. It is being launched by NASA for the Missile Defense System. The hour-long launch window opens at 8 a.m. EDT today. The STSS Demo is a space-based sensor component of a layered Ballistic Missile Defense System designed for the overall mission of detecting, tracking and discriminating ballistic missiles. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. Photo credit: NASA/Dimitri Gerondidakis

KSC01KODI036

NASA Image and Video Library

2001-05-29

KODIAK ISLAND, Alaska -- A boat moves a ramp into place that will allow Castor 120, the first stage of the Athena 1 launch vehicle, to safely move onto the dock at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KENNEDY SPACE CENTER, FLA. - The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-10

KENNEDY SPACE CENTER, FLA. - The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

Alternative Fuels Data Center: Video Download Help

Science.gov Websites

a Windows Media Video (WMV) link and select "Save Target As..." from the shortcut menu. To player on the screen. You can also expand the video to play in full-screen mode using Windows Media played in Windows Media Player. Download Windows Media Player. To watch videos on a Mac, double-click the

Noise limitations of multiplier phototubes in the radiation environment of space

NASA Technical Reports Server (NTRS)

Viehmann, W.; Eubanks, A. G.

1976-01-01

The contributions of Cerenkov emission, luminescence, secondary electron emission, and bremsstrahlung to radiation-induced data current and noise of multiplier phototubes were analyzed quantitatively. Fluorescence and Cerenkov emission in the tube window are the major contributors and can quantitatively account for dark count levels observed in orbit. Radiation-induced noise can be minimized by shielding, tube selection, and mode of operation. Optical decoupling of windows and cathode (side-window tubes) leads to further reduction of radiation-induced dark counts, as does reducing the window thickness and effective cathode area, and selection of window/cathode combinations of low fluorescence efficiency. In trapped radiation-free regions of near-earth orbits and in free space, Cerenkov emission by relativistic particles contributes predominantly to the photoelectron yield per event. Operating multiplier phototubes in the photon (pulse) counting mode will discriminate against these large pulses and substantially reduce the dark count and noise to levels determined by fluorescence.

KSC-06pd0316

NASA Image and Video Library

2006-02-18

KENNEDY SPACE CENTER, FLA. - In NASA Kennedy Space Center's Orbiter Processing Facility bay 3, United Space Alliance shuttle technicians remove the hard cover from a window on Space Shuttle Discovery to enable STS-121 crew members to inspect the window from the cockpit. Launch of Space Shuttle Discovery on mission STS-121, the second return-to-flight mission, is scheduled no earlier than May.

Geometric phase due to orbit-orbit interaction: rotating LP11 modes in a two-mode fiber

NASA Astrophysics Data System (ADS)

Pradeep Chakravarthy, T.; Naik, Dinesh N.; Viswanathan, Nirmal K.

2017-10-01

Accumulation of geometric phase due to non-coplanar propagation of higher-order modes in an optical fiber is experimentally demonstrated. Vertically-polarized LP11 fiber mode, excited in a horizontally-held, torsion-free, step-index, two-mode optical fiber, rotates due to asymmetry in the propagating k-vectors, arising due to off-centered beam location at the fiber input. Perceiving the process as due to rotation of the fiber about the off-axis launch position, the orbital Berry phase accumulation upon scanning the launch position in a closed-loop around the fiber axis manifests as rotational Doppler effect, a consequence of orbit-orbit interaction. The anticipated phase accumulation as a function of the input launch position, observed through interferometry is connected to the mode rotation angle, quantified using the autocorrelation method.

Ambitious STS-7 mission to feature first landing at Kennedy

NASA Technical Reports Server (NTRS)

Garrett, D.; Hess, M.; White, T.; Taylor, J.

1982-01-01

The STS-7 press briefing schedule, NASA select television schedule; launch preparations, countdown and liftoff; major countdown milestones; launch window; STS-7 flight sequence of events, landing timeline; STS-7 flight timeline; landing and post landing operations; flight objectives; Telesat's ANIK-C 2; PALAPA-B; STS-7 experiments; and spacecraft tracking and data network are presented.

Dynamics of Nonlinear Excitation of the High-Order Mode in a Single-Mode Step-Index Optical Fiber

NASA Astrophysics Data System (ADS)

Burdin, V.; Bourdine, A.

2018-04-01

This work is concerned with approximate model of higher-order mode nonlinear excitation in a singlemode silica optical fiber. We present some results of simulation for step-index optical fiber under femtosecond optical pulse launching, which confirm ability of relatively stable higher-order mode excitation in such singlemode optical fiber over sufficiently narrow range of launched optical power variation.

Dynamic Aberration Correction for Conformal Window of High-Speed Aircraft Using Optimized Model-Based Wavefront Sensorless Adaptive Optics.

PubMed

Dong, Bing; Li, Yan; Han, Xin-Li; Hu, Bin

2016-09-02

For high-speed aircraft, a conformal window is used to optimize the aerodynamic performance. However, the local shape of the conformal window leads to large amounts of dynamic aberrations varying with look angle. In this paper, deformable mirror (DM) and model-based wavefront sensorless adaptive optics (WSLAO) are used for dynamic aberration correction of an infrared remote sensor equipped with a conformal window and scanning mirror. In model-based WSLAO, aberration is captured using Lukosz mode, and we use the low spatial frequency content of the image spectral density as the metric function. Simulations show that aberrations induced by the conformal window are dominated by some low-order Lukosz modes. To optimize the dynamic correction, we can only correct dominant Lukosz modes and the image size can be minimized to reduce the time required to compute the metric function. In our experiment, a 37-channel DM is used to mimic the dynamic aberration of conformal window with scanning rate of 10 degrees per second. A 52-channel DM is used for correction. For a 128 × 128 image, the mean value of image sharpness during dynamic correction is 1.436 × 10(-5) in optimized correction and is 1.427 × 10(-5) in un-optimized correction. We also demonstrated that model-based WSLAO can achieve convergence two times faster than traditional stochastic parallel gradient descent (SPGD) method.

X33 Reusable Launch Vehicle Control on Sliding Modes: Concepts for a Control System Development

NASA Technical Reports Server (NTRS)

Shtessel, Yuri B.

1998-01-01

Control of the X33 reusable launch vehicle is considered. The launch control problem consists of automatic tracking of the launch trajectory which is assumed to be optimally precalculated. It requires development of a reliable, robust control algorithm that can automatically adjust to some changes in mission specifications (mass of payload, target orbit) and the operating environment (atmospheric perturbations, interconnection perturbations from the other subsystems of the vehicle, thrust deficiencies, failure scenarios). One of the effective control strategies successfully applied in nonlinear systems is the Sliding Mode Control. The main advantage of the Sliding Mode Control is that the system's state response in the sliding surface remains insensitive to certain parameter variations, nonlinearities and disturbances. Employing the time scaling concept, a new two (three)-loop structure of the control system for the X33 launch vehicle was developed. Smoothed sliding mode controllers were designed to robustly enforce the given closed-loop dynamics. Simulations of the 3-DOF model of the X33 launch vehicle with the table-look-up models for Euler angle reference profiles and disturbance torque profiles showed a very accurate, robust tracking performance.

Multi-focus image fusion based on window empirical mode decomposition

NASA Astrophysics Data System (ADS)

Qin, Xinqiang; Zheng, Jiaoyue; Hu, Gang; Wang, Jiao

2017-09-01

In order to improve multi-focus image fusion quality, a novel fusion algorithm based on window empirical mode decomposition (WEMD) is proposed. This WEMD is an improved form of bidimensional empirical mode decomposition (BEMD), due to its decomposition process using the adding window principle, effectively resolving the signal concealment problem. We used WEMD for multi-focus image fusion, and formulated different fusion rules for bidimensional intrinsic mode function (BIMF) components and the residue component. For fusion of the BIMF components, the concept of the Sum-modified-Laplacian was used and a scheme based on the visual feature contrast adopted; when choosing the residue coefficients, a pixel value based on the local visibility was selected. We carried out four groups of multi-focus image fusion experiments and compared objective evaluation criteria with other three fusion methods. The experimental results show that the proposed fusion approach is effective and performs better at fusing multi-focus images than some traditional methods.

Proper source-receiver distance to obtain surface wave group velocity profile for flaw detection inside a concrete plate-like structure

NASA Astrophysics Data System (ADS)

Cheng, Chia-Chi; Hsu, Keng-Tsang; Wang, Hong-Hua; Chiang, Chih-Hung

2018-04-01

A technique leads to rapid flaw detection for concrete plate-like structure is realized by obtaining the group velocity dispersion profile of the fundamental antisymmetric mode of the plate (A0 mode). The depth of a delaminating crack, honeycomb or depth of weak surface layer on top of the sound concrete can all be evaluated by the change of velocity in the dispersion profile of A0 mode at the wavelength about twice of the depth. The testing method involves obtaining the A0 group slowness spectrogram produced by single test with one receiver placed away from the source of impact. The image of the spectrogram is obtained by Short-Time Fourier Transfer (STFT) and enhanced by reassigned method. The choice of window length in STFT and the ratio between impactor-receiver distance and plate thickness, d/T, is essential as the dominant surface wave response may simply a non-dispersive Rayleigh wave or following the A0 or S0 (fundamental symmetric mode) modal dispersion curve. In this study, the axisymmetric finite element model of a plate subject to transient load was constructed. The nodal vertical velocity waveforms for various distances were analyzed using various STFT window lengths. The results show, for certain d/T ratio, S0 mode would be dominant when longer window is used. The best window lengths for a d/T ratio as well as the corresponding largest wavelength which follows the A0 theoretical dispersion curve or Rayleigh wave were summarized. The information allows people to determine the proper impactor-receiver distance and analyzing window to successfully detect the depth of flaws inside a plate.

Viking Mars launch set for August 11

NASA Technical Reports Server (NTRS)

Panagakos, N.

1975-01-01

The 1975-1976 Viking Mars Mission is described in detail, from launch phase through landing and communications relay phase. The mission's scientific goals are outlined and the various Martian investigations are discussed. These investigations include: geological photomapping and seismology; high-resolution, stereoscopic horizon scanning; water vapor and thermal mapping; entry science; meteorology; atmospheric composition and atmospheric density; and, search for biological products. The configurations of the Titan 3/Centaur combined launch vehicles, the Viking orbiters, and the Viking landers are described; their subsystems and performance characteristics are discussed. Preflight operations, launch window, mission control, and the deep space tracking network are also presented.

KSC01kodi072

NASA Image and Video Library

2001-08-08

KODIAK ISLAND, Alaska -- The Sapphire payload is moved into position next to the Starshine 3 payload at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi053

NASA Image and Video Library

2001-07-19

KODIAK ISLAND, Alaska -- A technician performs final testing on Starshine 3 at the Naval Research Laboratory in Washington, D.C., to prepare for the launch of the Kodiak Star at Kodiak Island, Alaska. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi054

NASA Image and Video Library

2001-07-19

KODIAK ISLAND, Alaska -- A technician performs final testing on Starshine 3 at the Naval Research Laboratory in Washington, D.C., to prepare for the launch of the Kodiak Star at Kodiak Island, Alaska. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC-98pc509

NASA Image and Video Library

1998-04-17

KENNEDY SPACE CENTER, FLA. -- STS-90 Payload Specialist James Pawelczyk, Ph.D., is assisted by NASA and United Space Alliance closeout crew members immediately preceding launch for the nearly 17-day Neurolab mission. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Pawelczyk and six fellow crew members will shortly enter the orbiter at KSC's Launch Pad 39B, where the Space Shuttle Columbia will lift off during a launch window that opens at 2:19 p.m. EDT, April 17

KSC-98pc511

NASA Image and Video Library

1998-04-17

KENNEDY SPACE CENTER, FLA. -- STS-90 Commander Richard Searfoss is assisted by NASA and USA closeout crew members immediately preceding launch for the nearly 17-day Neurolab mission. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Searfoss and his six fellow crew members will shortly enter the orbiter at KSC's Launch Pad 39B, where the Space Shuttle Columbia will lift off during a launch window that opens at 2:19 p.m. EDT, April 17

KSC-98pc512

NASA Image and Video Library

1998-04-17

KENNEDY SPACE CENTER, FLA. -- STS-90 Mission Specialist Richard Linnehan, D.V.M., is assisted by NASA and United Space Alliance closeout crew members immediately preceding launch for the nearly 17-day Neurolab mission. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Linnehan and six fellow crew members will shortly enter the orbiter at KSC's Launch Pad 39B, where the Space Shuttle Columbia will lift off during a launch window that opens at 2:19 p.m. EDT, April 17

KSC-98pc513

NASA Image and Video Library

1998-04-17

KENNEDY SPACE CENTER, FLA. -- STS-90 Pilot Scott Altman is assisted by NASA and United Space Alliance closeout crew members immediately preceding launch for the nearly 17-day Neurolab mission. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Altman and six fellow crew members will shortly enter the orbiter at KSC's Launch Pad 39B, where the Space Shuttle Columbia will lift off during a launch window that opens at 2:19 p.m. EDT, April 17

STS-77 MS Andrew Thomas suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 Mission Specialist Andrew S. W. Thomas finishes donning his launch/entry suit in the Operations and Checkout Building with assistance from a suit technician. A native of South Australia, the rookie astronaut joins a crew of five veterans on the fourth Shuttle flight of 1996. They will depart shortly for Launch Pad 39B, where the Space Shuttle Endeavour is undergoing final preparations for liftoff during a two-and-a-half hour launch window opening at 6:30 a.m. EDT, May 19.

KSC-03pd0752

NASA Image and Video Library

2003-03-17

KENNEDY SPACE CENTER, FLA. - In the Payload Hazardous Servicing Facility, workers align the Rover Equipment Deck (RED) on one of the Mars Exploration Rovers (MER) with the Warm Electronics Box (WEB). Processing of the rovers, plus cruise stage, lander and heat shield elements, is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

STS-84 Atlantis on Pad 39-A after RSS roll back

NASA Technical Reports Server (NTRS)

1997-01-01

News media representatives watch and record as the Space Shuttle Atlantis in full launch configuration is revealed after the Rotating Service Structure (RSS) is rotated back at Launch Pad 39A. Rollback of the RSS is a major preflight milestone, typically occurring during the T-11-hour hold on L-1 (the day before launch). Atlantis and its crew of seven are in final preparations for liftoff on Mission STS-84, the sixth of nine planned dockings of the Space Shuttle with the Russian Space Station Mir. Launch is scheduled at about 4:08 a.m. during an approximately 7-minute launch window. The exact liftoff time will be determined about 90 minutes prior to launch, based on the most current location of Mir.

KSC01kodi049

NASA Image and Video Library

2001-06-19

KODIAK ISLAND, Alaska -- Orbis 21D Equipment Section Boost Motor, the second stage of the Athena 1 launch vehicle, awaits the installation of the Orbit Adjust Model (OAM), which navigates the payloads into the correct orbit, at the launch pad at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

Algorithm for Determination of Orion Ascent Abort Mode Achievability

NASA Technical Reports Server (NTRS)

Tedesco, Mark B.

2011-01-01

For human spaceflight missions, a launch vehicle failure poses the challenge of returning the crew safely to earth through environments that are often much more stressful than the nominal mission. Manned spaceflight vehicles require continuous abort capability throughout the ascent trajectory to protect the crew in the event of a failure of the launch vehicle. To provide continuous abort coverage during the ascent trajectory, different types of Orion abort modes have been developed. If a launch vehicle failure occurs, the crew must be able to quickly and accurately determine the appropriate abort mode to execute. Early in the ascent, while the Launch Abort System (LAS) is attached, abort mode selection is trivial, and any failures will result in a LAS abort. For failures after LAS jettison, the Service Module (SM) effectors are employed to perform abort maneuvers. Several different SM abort mode options are available depending on the current vehicle location and energy state. During this region of flight the selection of the abort mode that maximizes the survivability of the crew becomes non-trivial. To provide the most accurate and timely information to the crew and the onboard abort decision logic, on-board algorithms have been developed to propagate the abort trajectories based on the current launch vehicle performance and to predict the current abort capability of the Orion vehicle. This paper will provide an overview of the algorithm architecture for determining abort achievability as well as the scalar integration scheme that makes the onboard computation possible. Extension of the algorithm to assessing abort coverage impacts from Orion design modifications and launch vehicle trajectory modifications is also presented.

The effect of periodic wavy profile on suppressing window multipactor under arbitrary electromagnetic mode

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

Chang, C., E-mail: chang@slac.stanford.edu; Key Laboratory of Physical Electronics and Devices of the Ministry of Education, Xi'an Jiaotong University, Xi'an, Shaanxi 710049; Liu, Y. S.

2015-01-05

The three-dimensional periodic ripple profile with each unit of rotational symmetric surface is proposed to suppress multipactor for arbitrary electromagnetic mode with any polarization. The field distribution and multipactor electron dynamics on the wavy surface are studied to illustrate the multipactor inhibition mechanism. High power microwave experiment was conducted to demonstrate the effect of wavy surface on significantly improving the window power capacity.

KSC-97pc633

NASA Image and Video Library

1997-04-08

The Lockheed Martin Atlas 1 expendable launch vehicle (AC-79) which will carry the GOES-K advanced weather satellite undergoes a critical prelaunch test with its mobile service tower pulled back. The Wet Dress Rehearsal is a major prelaunch test designed to demonstrate, in part, the launch readiness of the vehicle and launch support equipment. AC-79 will be the final launch of an Atlas 1 rocket, a derivative of the original Atlas Centaur which had its first successful launch for NASA in 1963. Future launches of Geostationary Operational Environmental Satellites (GOES) in the current series will be on Atlas II vehicles. The GOES satellites are owned and operated by the National Oceanic and Atmospheric Administration (NOAA); NASA manages the design, development and launch of the spacecraft. The launch of AC-79 with the GOES-K is targeted for April 24 during a launch window which extends from 1:50-3:09 a.m. EDT

KSC-97pc632

NASA Image and Video Library

1997-04-08

The Lockheed Martin Atlas 1 expendable launch vehicle (AC-79) which will carry the GOES-K advanced weather satellite undergoes a critical prelaunch test with its mobile service tower pulled back. The Wet Dress Rehearsal is a major prelaunch test designed to demonstrate, in part, the launch readiness of the vehicle and launch support equipment. AC-79 will be the final launch of an Atlas 1 rocket, a derivative of the original Atlas Centaur which had its first successful launch for NASA in 1963. Future launches of Geostationary Operational Environmental Satellites (GOES) in the current series will be on Atlas II vehicles. The GOES satellites are owned and operated by the National Oceanic and Atmospheric Administration (NOAA); NASA manages the design, development and launch of the spacecraft. The launch of AC-79 with the GOES-K is targeted for April 24 during a launch window which extends from 1:50-3:09 a.m. EDT

1. GENERAL VIEW OF EAST AND NORTH SIDES OF NORTH ...

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

1. GENERAL VIEW OF EAST AND NORTH SIDES OF NORTH WING; NOTE PLYWOOD COVERED WINDOWS DUE TO EXPLOSION ON LAUNCH PAD A IN MARCH 1997 WITH FIERY RAIN OF SOLID ROCKET FUEL AND PROLONGED CONCUSSION WAVES; VIEW TO SOUTHWEST. - Cape Canaveral Air Station, Launch Complex 17, Facility 36001, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

Interplanetary mission design handbook. Volume 1, part 4: Earth to Saturn ballistic mission opportunities, 1985-2005

NASA Technical Reports Server (NTRS)

Sergeyevsky, A. B.; Snyder, G. C.

1981-01-01

Graphical data necessary for the preliminary design of ballistic missions to Saturn are provided. Contours of launch energy requirements as well as many other launch and Saturn arrival parameters, are presented in launch date/arrival date space for all launch opportunities from 1985 through 2005. In addition, an extensive text is included which explains mission design methods, from launch window development to Saturn probe and orbiter arrival design, utilizing the graphical data in this volume as well as numerous equations elating various parameters. This is the first of a planned series of mission design documents which will apply to all planets and some other bodies in the solar system.

KSC01KODI037

NASA Image and Video Library

2001-05-29

KODIAK ISLAND, Alaska -- The Orbis 21D Equipment Section Boost Motor, the second stage of the Athena 1 launch vehicle, waits for the first stage, Castor 120, to be towed up the steepest part of the road, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC-2009-5194

NASA Image and Video Library

2009-09-23

CAPE CANAVERAL, Fla. – The mobile service tower on Launch Pad 17-B at Cape Canaveral Air Force Station has been rolled back as the countdown proceeds to launch of the United Launch Alliance Delta II rocket with the Space Tracking and Surveillance System - Demonstrator spacecraft aboard. It is being launched by NASA for the Missile Defense System. The hour-long launch window opens at 8 a.m. EDT today. The STSS Demo is a space-based sensor component of a layered Ballistic Missile Defense System designed for the overall mission of detecting, tracking and discriminating ballistic missiles. STSS is capable of tracking objects after boost phase and provides trajectory information to other sensors. Photo credit: NASA/Dimitri Gerondidakis

Optical fiber micro-displacement sensor using a refractive index modulation window-assisted reflection fiber taper

NASA Astrophysics Data System (ADS)

Bao, Weijia; Qiao, Xueguang; Yin, Xunli; Rong, Qiangzhou; Wang, Ruohui; Yang, Hangzhou

2017-12-01

We demonstrate a compact fiber-optic quasi-Michelson interferometer (QMI) for micro-displacement measurement. The sensor comprises a micro-structure of a reflection taper tip containing a refractive index modification (RIM) as a coupling window over the interface between core and cladding of the fiber. Femtosecond laser-based direct inscription technique is used to achieve this window inscription and to induce large refractive index change. The RIM acts as a window for the strong coupling and recoupling of core-to-cladding modes. As the core and cladding modes are reflected at the taper tip and coupled back to lead-in fiber, a well-defined interference spectrum is achieved. The spectral intensity exhibits a high micro-bending sensitivity of 4 . 94 dB / μm because of the sensitivity to bending of recoupled intensity of cladding modes. In contrast, the spectral wavelength is insensitive to bending but linearly responds to temperature. The simultaneous measurements, including power-referenced for displacement and wavelength-referenced for temperature, were achieved by selective interference dip monitoring.

Study of wavefront error and polarization of a side mounted infrared window

NASA Astrophysics Data System (ADS)

Liu, Jiaguo; Li, Lin; Hu, Xinqi; Yu, Xin

2008-03-01

The wavefront error and polarization of a side mounted infrared window made of ZnS are studied. The Infrared windows suffer from temperature gradient and stress during their launch process. Generally, the gradient in temperature changes the refractive index of the material whereas stress produces deformation and birefringence. In this paper, a thermal finite element analysis (FEA) of an IR window is presented. For this purpose, we employed an FEA program Ansys to obtain the time-varying temperature field. The deformation and stress of the window are derived from a structural FEA with the aerodynamic force and the temperature field previously obtained as being the loads. The deformation, temperature field, stress field, ray tracing and Jones Calculus are used to calculate the wavefront error and the change of polarization state.

KENNEDY SPACE CENTER, FLA. - The White Room is seen at the upper left where the astronauts enter the Space Shuttle for flight. The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-10

KENNEDY SPACE CENTER, FLA. - The White Room is seen at the upper left where the astronauts enter the Space Shuttle for flight. The Rotating Service Structure has been retracted at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

KENNEDY SPACE CENTER, FLA. - At the KSC Launch Pad 39A, two members of the payload closeout crew check equipment as the doors are just about ready to be closed. The Payload inside the bay of Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-07

KENNEDY SPACE CENTER, FLA. - At the KSC Launch Pad 39A, two members of the payload closeout crew check equipment as the doors are just about ready to be closed. The Payload inside the bay of Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope and provide a reboost to the optimum altitude.

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-07

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at KSC's Launch Pad 39A. Discovery, the orbiter for the STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

Bispectral analysis: comparison of two windowing functions

NASA Astrophysics Data System (ADS)

Silvagni, D.; Djerroud, C.; Réveillé, T.; Gravier, E.

2018-02-01

Amongst all the normalized forms of bispectrum, the bicoherence is shown to be a very useful diagnostic tool in experimental studies of nonlinear wave interactions in plasma, as it measures the fraction of wave power due to the quadratic wave coupling in a self-excited fluctuation spectrum [1, 2]. In order to avoid spectral leakage, the application of a windowing function is needed during the bicoherence computation. Spectral leakage from statistically dependent components are of crucial importance in the discrimination between coupled and uncoupled modes, as they will introduce in the bicoherence spectrum phase-coupled modes which in reality do not exist. Therefore, the windowing function plays a key role in the bicoherence estimation. In this paper, two windowing methods are compared: the multiplication of the initial signal by the Hanning function and the subtraction of the straight line which links the two extremities of the signal. The influence of these two windowing methods on both the power spectrum and the bicoherence spectrum is showed. Although both methods give precise results, the Hanning function appears to be the more suitable window.

Coupler for coupling gyrotron whispering gallery mode RF into HE11 waveguide

DOEpatents

Neilson, Jeffrey M

2015-02-24

A cylindrical waveguide with a mode converter transforms a whispering gallery mode from a gyrotron cylindrical waveguide with a helical cut launch edge to a quasi-Gaussian beam suitable for conveyance through a corrugated waveguide. This quasi-Gaussian beam is radiated away from the waveguide using a spiral cut launch edge, which is in close proximity to a first mode converting reflector. The first mode converting reflector is coupled to a second mode converting reflector which provides an output free-space HE11 mode wave suitable for direct coupling into a corrugated waveguide. The radiated beam produced at the output of the second mode converting reflector is substantially circular.

Dynamic Aberration Correction for Conformal Window of High-Speed Aircraft Using Optimized Model-Based Wavefront Sensorless Adaptive Optics

PubMed Central

Dong, Bing; Li, Yan; Han, Xin-li; Hu, Bin

2016-01-01

For high-speed aircraft, a conformal window is used to optimize the aerodynamic performance. However, the local shape of the conformal window leads to large amounts of dynamic aberrations varying with look angle. In this paper, deformable mirror (DM) and model-based wavefront sensorless adaptive optics (WSLAO) are used for dynamic aberration correction of an infrared remote sensor equipped with a conformal window and scanning mirror. In model-based WSLAO, aberration is captured using Lukosz mode, and we use the low spatial frequency content of the image spectral density as the metric function. Simulations show that aberrations induced by the conformal window are dominated by some low-order Lukosz modes. To optimize the dynamic correction, we can only correct dominant Lukosz modes and the image size can be minimized to reduce the time required to compute the metric function. In our experiment, a 37-channel DM is used to mimic the dynamic aberration of conformal window with scanning rate of 10 degrees per second. A 52-channel DM is used for correction. For a 128 × 128 image, the mean value of image sharpness during dynamic correction is 1.436 × 10−5 in optimized correction and is 1.427 × 10−5 in un-optimized correction. We also demonstrated that model-based WSLAO can achieve convergence two times faster than traditional stochastic parallel gradient descent (SPGD) method. PMID:27598161

Batch production of microchannel plate photo-multipliers

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

Frisch, Henry J.; Wetstein, Matthew; Elagin, Andrey

In-situ methods for the batch fabrication of flat-panel micro-channel plate (MCP) photomultiplier tube (PMT) detectors (MCP-PMTs), without transporting either the window or the detector assembly inside a vacuum vessel are provided. The method allows for the synthesis of a reflection-mode photocathode on the entrance to the pores of a first MCP or the synthesis of a transmission-mode photocathode on the vacuum side of a photodetector entrance window.

Mode switching in volcanic seismicity: El Hierro 2011-2013

NASA Astrophysics Data System (ADS)

Roberts, Nick S.; Bell, Andrew F.; Main, Ian G.

2016-05-01

The Gutenberg-Richter b value is commonly used in volcanic eruption forecasting to infer material or mechanical properties from earthquake distributions. Such studies typically analyze discrete time windows or phases, but the choice of such windows is subjective and can introduce significant bias. Here we minimize this sample bias by iteratively sampling catalogs with randomly chosen windows and then stack the resulting probability density functions for the estimated b>˜ value to determine a net probability density function. We examine data from the El Hierro seismic catalog during a period of unrest in 2011-2013 and demonstrate clear multimodal behavior. Individual modes are relatively stable in time, but the most probable b>˜ value intermittently switches between modes, one of which is similar to that of tectonic seismicity. Multimodality is primarily associated with intermittent activation and cessation of activity in different parts of the volcanic system rather than with respect to any systematic inferred underlying process.

The enhanced ASDEX Upgrade pellet centrifuge launcher

NASA Astrophysics Data System (ADS)

Plöckl, B.; Lang, P. T.

2013-10-01

Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system. Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.

The enhanced ASDEX Upgrade pellet centrifuge launcher.

PubMed

Plöckl, B; Lang, P T

2013-10-01

Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system. Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.

The enhanced ASDEX Upgrade pellet centrifuge launcher

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

Plöckl, B.; Lang, P. T.

2013-10-15

Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system.more » Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.« less

Trajectory options for the DART mission

NASA Astrophysics Data System (ADS)

Atchison, Justin A.; Ozimek, Martin T.; Kantsiper, Brian L.; Cheng, Andrew F.

2016-06-01

This study presents interplanetary trajectory options for the Double Asteroid Redirection Test (DART) spacecraft to reach the near Earth object, Didymos binary system, during its 2022 Earth conjunction. DART represents a component of a joint NASA-ESA mission to study near Earth object kinetic impact deflection. The DART trajectory must satisfy mission objectives for arrival timing, geometry, and lighting while minimizing launch vehicle and spacecraft propellant requirements. Chemical propulsion trajectories are feasible from two candidate launch windows in late 2020 and 2021. The 2020 trajectories are highly perturbed by Earth's orbit, requiring post-launch deep space maneuvers to retarget the Didymos system. Within these windows, opportunities exist for flybys of additional near Earth objects: Orpheus in 2021 or 2007 YJ in 2022. A second impact attempt, in the event that the first impact is unsuccessful, can be added at the expense of a shorter launch window and increased (∼3x) spacecraft ΔV . However, the second impact arrival geometry has poor lighting, high Earth ranges, and would require additional degrees of freedom for solar panel and/or antenna gimbals. A low-thrust spacecraft configuration increases the trajectory flexibility. A solar electric propulsion spacecraft could be affordably launched as a secondary spacecraft in an Earth orbit and spiral out to target the requisite interplanetary departure condition. A sample solar electric trajectory was constructed from an Earth geostationary transfer using a representative 1.5 kW thruster. The trajectory requires 9 months to depart Earth's sphere of influence, after which its interplanetary trajectory includes a flyby of Orpheus and a second Didymos impact attempt. The solar electric spacecraft implementation would impose additional bus design constraints, including large solar arrays that could pose challenges for terminal guidance. On the basis of this study, there are many feasible options for DART to meet its mission design objectives and enable this unique kinetic impact experiment.

Lunar Ascent and Rendezvous Trajectory Design

NASA Technical Reports Server (NTRS)

Sostaric, Ronald R.; Merriam, Robert S.

2008-01-01

The Lunar Lander Ascent Module (LLAM) will leave the lunar surface and actively rendezvous in lunar orbit with the Crew Exploration Vehicle (CEV). For initial LLAM vehicle sizing efforts, a nominal trajectory, along with required delta-V and a few key sensitivities, is very useful. A nominal lunar ascent and rendezvous trajectory is shown, along with rationale and discussion of the trajectory shaping. Also included are ascent delta-V sensitivities to changes in target orbit and design thrust-to-weight of the vehicle. A sample launch window for a particular launch site has been completed and is included. The launch window shows that budgeting enough delta-V for two missed launch opportunities may be reasonable. A comparison between yaw steering and on-orbit plane change maneuvers is included. The comparison shows that for large plane changes, which are potentially necessary for an anytime return from mid-latitude locations, an on-orbit maneuver is much more efficient than ascent yaw steering. For a planned return, small amounts of yaw steering may be necessary during ascent and must be accounted for in the ascent delta-V budget. The delta-V cost of ascent yaw steering is shown, along with sensitivity to launch site latitude. Some discussion of off-nominal scenarios is also included. In particular, in the case of a failed Powered Descent Initiation burn, the requirements for subsequent rendezvous with the Orion vehicle are outlined.

STS-84 Commander Charles Precourt suits up

NASA Technical Reports Server (NTRS)

1997-01-01

STS-84 Commander Charles J. Precourt adjusts the helmet of his launch and entry suit during final prelaunch preparations in the Operations and Checkout Building. This is Precourts third space flight, but his first as commander. Precourt and six other crew members will depart shortly for Launch Pad 39A, where the Space Shuttle Atlantis awaits liftoff during an approximate 7-minute launch window which opens at about 4:08 a.m. This will be the sixth docking of the Space Shuttle with the Russian Space Station Mir. The exact liftoff time will be determined about 90 minutes prior to launch, based on the most current location of Mir.

Launching lunar missions from Space Station Freedom

NASA Technical Reports Server (NTRS)

Friedlander, Alan; Young, Archie

1990-01-01

The relative orbital motion of Space Station Freedom and the moon places practical constraints on the timing of launch/return transfer trajectories. This paper describes the timing characteristics as well as the Delta-V variations over a representative cycle of launch/return opportunities. On average, the minimum-Delta-V transfer opportunities occur at intervals of 9 days. However, there is a significant nonuniform variation in this timing interval, as well as the minimum stay time at the moon, over the short cycle (51 days) and the long cycle (18.6 years). The advantage of three-impulse transfers for extending the launch window is also described.

KSC-98pc508

NASA Image and Video Library

1998-04-17

KENNEDY SPACE CENTER, FLA. -- STS-90 Mission Specialist Dafydd (Dave) Williams, M.D., with the Canadian Space Agency is assisted by NASA and United Space Alliance closeout crew members immediately preceding launch for the nearly 17-day Neurolab mission. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. Seen behind Williams also in an orange launch and re-entry suit is Mission Specialist Richard Linnehan, D.V.M. Williams and six fellow crew members will shortly enter the orbiter at KSC's Launch Pad 39B, where the Space Shuttle Columbia will lift off during a launch window that opens at 2:19 p.m. EDT, April 17

MARS GLOBAL SURVEYOR LIGHTING TEST

NASA Technical Reports Server (NTRS)

1996-01-01

In KSC's Payload Hazardous Servicing Facility (PHSF), Jet Propulsion Laboratory (JPL) workers are conducting a solar illumination test of the solar panels on the Mars Global Surveyor. The Surveyor is outfitted with two solar arrays, each featuring two panels, that provide electrical power for operating the spacecraft's electronic equipment and scientific instruments, as well as charging two nickel hydrogen batteries that provide power when the spacecraft is in the dark. For launch, the solar arrays will be folded against the side of the spacecraft. The Mars Global Surveyor is being prepared for launch aboard a Delta II expendable launch vehicle during a launch window opening Nov. 6.

KSC-06pd0903

NASA Image and Video Library

2006-05-19

KENNEDY SPACE CENTER, FLA. -- Near Launch Pad 39B, wild pigs (at right) root for food near a stand of trees while Space Shuttle Discovery rolls out to the pad. The 4.2-mile journey from the Vehicle Assembly Building began at 12:45 p.m. EDT. The rollout is an important step before launch of Discovery on mission STS-121 to the International Space Station. Discovery's launch is targeted for July 1 in a launch window that extends to July 19. During the 12-day mission, Discovery's crew will test new hardware and techniques to improve shuttle safety, as well as deliver supplies and make repairs to the station. Photo credit: NASA/Ken Thornsley

KSC-2009-5000

NASA Image and Video Library

2009-09-04

CAPE CANAVERAL, Fla. – This aerial view shows NASA Kennedy Space Center's Launch Control Center with its new hurricane-rated window systems installed in the four Firing Rooms. Photo credit: NASA/Troy Cryder

Booster Test for Space Launch System Rocket

NASA Image and Video Library

2016-06-26

The test area where the second and final qualification motor (QM-2) test for the Space Launch System’s booster is seen through the window of a camera bunker, Sunday, June 26, 2016, at Orbital ATK Propulsion Systems test facilities in Promontory, Utah. The test is scheduled for Tuesday, June 28 at 10:05 a.m. EDT (8:05 a.m. MDT). Photo Credit: (NASA/Bill Ingalls)

STS-75 Mission Commander Andrew M. Allen suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-75 Mission Commander Andrew M. Allen completes suitup activities in the Operations and Checkout Building. STS-75 will be Allen's third trip into space, his first as commander. Allen and an international crew will depart shortly for Launch Pad 39B, where the Space Shuttle Columbia awaits liftoff during a two-and- a-half-hour launch window opening at 3:18 p.m. EST.

KSC-03pd0753

NASA Image and Video Library

2003-03-17

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, workers check alignment of the Rover Equipment Deck (RED) on one of the Mars Exploration Rovers (MER) with the Warm Electronics Box (WEB). Processing of the rovers, plus cruise stage, lander and heat shield elements, is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0756

NASA Image and Video Library

2003-03-17

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, the Rover Equipment Deck (RED) on one of the Mars Exploration Rovers (MER) is integrated to the Warm Electronics Box (WEB) on the WEB cart. Processing of the rovers, plus cruise stage, lander and heat shield elements, is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

KSC-03pd0754

NASA Image and Video Library

2003-03-17

KENNEDY SPACE CENTER, Fla. - In the Payload Hazardous Servicing Facility, the Rover Equipment Deck (RED) on one of the Mars Exploration Rovers (MER) is integrated to the Warm Electronics Box (WEB) on the WEB cart. Processing of the rovers, plus cruise stage, lander and heat shield elements, is ongoing. Set to launch in 2003, the MER Mission will consist of two identical rovers designed to cover roughly 110 yards each Martian day. Each rover will carry five scientific instruments that will allow it to search for evidence of liquid water that may have been present in the planet's past. The rovers will be identical to each other, but will land at different regions of Mars. The first rover has a launch window opening May 30, and the second rover a window opening June 25, 2003.

STS-67 Payload Specialists Durrance and Parise suit up

NASA Technical Reports Server (NTRS)

1995-01-01

In the Operations and Checkout Building, STS-67 Payload Specialists Samuel T. Durrance (left) and Ronald A. Parise have finished donning their launch/entry suits and chat with astronaut Joe Tanner while waiting for the rest of the crew. The two payload specialists -- who are both making their second trip into space -- and five fellow crew members will soon depart for Launch Pad 39A, where the Space Shuttle Endeavour is being readied for liftoff during a launch window opening at 1:37 a.m. EST, March 2.

KSC-05pd2558

NASA Image and Video Library

2005-12-05

KENNEDY SPACE CENTER, FLA. - The Lockheed Martin Atlas V rocket (center) undergoes a tanking test on Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The rocket was fully fueled with liquid hydrogen, liquid oxygen and RP 1 kerosene fuel. Seen surrounding the rocket are lightning towers that support the catenary wire that provides lightning protection. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch during a 35-day window that opens Jan. 11, and fly through the Pluto system as early as summer 2015.

KSC-05pd2559

NASA Image and Video Library

2005-12-05

KENNEDY SPACE CENTER, FLA. - The Lockheed Martin Atlas V rocket (center) undergoes a tanking test on Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The rocket was fully fueled with liquid hydrogen, liquid oxygen and RP 1 kerosene fuel. Seen surrounding the rocket are lightning towers that support the catenary wire that provides lightning protection. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch during a 35-day window that opens Jan. 11, and fly through the Pluto system as early as summer 2015.

Research on Vehicle Temperature Regulation System Based on Air Convection Principle

NASA Astrophysics Data System (ADS)

Zhuge, Muzi; Li, Xiang; Liang, Caifeng

2018-03-01

The long time parking outdoors in the summer will lead to too high temperature in the car, and the harmful gas produced by the vehicle engine will stay in the confined space for a long time during the parking process, which will do great harm to the human body. If the air conditioning system is turned on before driving, the cooling rate is slow and the battery loss is large. To solve the above problems, we designed a temperature adjusting system based on the principle of air convection. We can choose the automatic mode or manual mode to achieve control of a convection window. In the automatic mode, the system will automatically detect the environmental temperature, through the sensor to complete the detection, and the signal is transmitted to the microcontroller to control the window open or close, in manual mode, the remote control of the window can be realized by Bluetooth. Therefore, the system has important practical significance to effectively regulate temperature, prolong battery life, and improve the safety and comfort of traffic vehicles.

Technicians prepare to erect the first stage of the Atlas II which will be used to launch GOES-L at

NASA Technical Reports Server (NTRS)

1999-01-01

At Launch Pad 36A on the Cape Canaveral Air Station, technicians prepare to erect the first stage of a Lockheed Martin Atlas II rocket which will be used to launch the Geostationary Operational Environmental Satellite-L (GOES-L). GOES-L is the latest in the current series of advanced geostationary weather satellites in service. Once in orbit, it will become GOES-11 and function as an on-orbit spare to be activated when one of the operational satellites needs to be replaced. Launch is scheduled for Saturday, May 15 at the opening of a launch window which extends from 2:23 to 4:41 a.m. EDT.

Launch pad lightning protection effectiveness

NASA Technical Reports Server (NTRS)

Stahmann, James R.

1991-01-01

Using the striking distance theory that lightning leaders will strike the nearest grounded point on their last jump to earth corresponding to the striking distance, the probability of striking a point on a structure in the presence of other points can be estimated. The lightning strokes are divided into deciles having an average peak current and striking distance. The striking distances are used as radii from the points to generate windows of approach through which the leader must pass to reach a designated point. The projections of the windows on a horizontal plane as they are rotated through all possible angles of approach define an area that can be multiplied by the decile stroke density to arrive at the probability of strokes with the window average striking distance. The sum of all decile probabilities gives the cumulative probability for all strokes. The techniques can be applied to NASA-Kennedy launch pad structures to estimate the lightning protection effectiveness for the crane, gaseous oxygen vent arm, and other points. Streamers from sharp points on the structure provide protection for surfaces having large radii of curvature. The effects of nearby structures can also be estimated.

Orion Hatch Window Testing

NASA Image and Video Library

2018-04-09

Inside a laboratory in the Neil Armstrong Operations and Checkout Building at NASA's Kennedy Space Center in Florida, Mark Nurge, Ph.D., at left, a physicist in the Applied Physics Lab with the center's Exploration Research and Technology Programs, and Bence Bartha, Ph.D., a specialist in non-destructive testing with URS Federal Services, are performing the first optical quality testing on a full window stack that is ready for installation in the docking hatch of NASA's Orion spacecraft. The data from the tests will help improve the requirements for manufacturing tolerances on Orion's windows and verify how the window should perform in space. Orion is being prepared for its first integrated uncrewed flight atop NASA's Space Launch System rocket on Exploration Mission-1.

Systems design study of the Pioneer Venus spacecraft. Appendices to volume 1, sections 3-6 (part 1 of 3). [design of Venus probe windows

NASA Technical Reports Server (NTRS)

1973-01-01

The design is described of the Venus probe windows, which are required to measure solar flux, infrared flux, aureole, and cloud particles. Window heating and structural materials for the probe window assemblies are discussed along with the magnetometer. The command lists for science, power and communication requirements, telemetry sign characteristics, mission profile summary, mass properties of payloads, and failure modes are presented.

Tailoring mode interference in plasmon-induced transparency metamaterials

NASA Astrophysics Data System (ADS)

Liu, Meng; Yang, Quanlong; Xu, Quan; Chen, Xieyu; Tian, Zhen; Gu, Jianqiang; Ouyang, Chunmei; Zhang, Xueqian; Han, Jiaguang; Zhang, Weili

2018-05-01

We proposed an approach to tailor the mode interference effect in plasmon-induced transparency (PIT) metamaterials. Through introducing an extra coupling mode using an asymmetric structure configuration at terahertz (THz) frequencies, the well-known single-transparency-window PIT can be switched to dual-transparency-window PIT. Proof-of-concept subwavelength structures were fabricated and experimentally characterized. The measured results are in good agreement with the simulations, and well support our theoretical analysis. The presented research delivers a novel approach toward developing subwavelength devices with varies functionalities, such as ultra-slow group velocities, longitudinal pulse compression and light storage in the THz regime, which can also be extended to other spectral regimes.

KSC-69P-631

NASA Image and Video Library

1969-07-16

CAPE CANAVERAL, Fla. – Members of the Kennedy Space Center government-industry team rise from their consoles within the Launch Control Center to watch the Apollo 11 liftoff through a window. Photo credit: NASA

A Geometric Analysis to Protect Manned Assets from Newly Launched Objects - COLA Gap Analysis

NASA Technical Reports Server (NTRS)

Hametz, Mark E.; Beaver, Brian A.

2012-01-01

A safety risk was identified for the International Space Station (ISS) by The Aerospace Corporation following the launch of GPS IIR-20 (March 24, 2009), when the spent upper stage of the launch vehicle unexpectedly crossed inside the ISS notification box shortly after launch. This event highlighted a 56-hour vulnerability period following the end of the launch Collision Avoidance (COLA) process where the ISS would be unable to react to a conjunction with a newly launched object. Current launch COLA processes screen each launched object across the launch window to determine if an object's nominal trajectory is predicted to pass within 200 km of the ISS (or any other manned/mannable object), resulting in a launch time closure. These launch COLA screens are performed from launch through separation plus I 00 minutes. Once the objects are in orbit, they are cataloged and evaluated as part of routine on-orbit conjunction assessment processes. However, as the GPS IIR-20 scenario illustrated, there is a vulnerability period in the time line between the end of launch COLA coverage and the beginning of standard on-orbit COLA assessment activities. The gap between existing launch and on-orbit COLA processes is driven by the time it takes to track and catalog a launched object, identify a conjunction, and plan and execute a collision avoidance maneuver. For the ISS, the total time required to accomplish an of these steps is 56 hours. To protect human lives, NASA/JSC has requested that an US launches take additional steps to protect the ISS during this "COLA gap" period. The uncertainty in the state of a spent upper stage can be quite large after all bums are complete and all remaining propellants are expelled to safe the stage. Simply extending the launch COLA process an additional 56 hours is not a viable option as the 3-sigma position uncertainty will far exceed the 200 km miss-distance criterion. Additionally, performing a probability of collision (Pc) analysis over this period is also not practical due to the limiting effects of these large orbit state uncertainties. An estimated upper bound for Pc for a typical spent upper stage if nominally aligned for a direct broadside collision with the ISS is only on the order of 10-6. For a smaller manned object such as a Soyuz capsule, the risk level decreases to an order of 10'8 . In comparison, the Air Force Range policy (AFI 91-217) for launch COLAs would only eliminate launch opportunities when conjunctions with objects exceed a Pc of 10'5 This paper demonstrates a conservative geometry-based methodology that may be used to determine if launch opportunities pose a threat to the ISS during the COLA gap period. The NASA Launch Services Program at Kennedy Space Center has developed this COLA gap analysis method and employed it fQr three NASA missions to identify potential ISS conjunctions and corresponding launch window closures during the 56-hour at-risk period. In the analysis, for each launch opportunity, the nominal trajectory of the spent upper stage and the orbit state of the ISS are propagated over the 56 hour period. Each time the upper stage crosses the orbit plane of the ISS, the relative radial and argument of latitude separations are calculated. A window cutout is identified if these separation differences fall within a mission-specific violation box, which is determined from the evaluation of a Monte Carlo dispersions analysis that quantifies the potential variation in the upper stage radial and argument of latitude differences. This paper details the results of these analyses and their impacts to each mission.

KSC-2009-1320

NASA Image and Video Library

2009-01-23

CAPE CANAVERAL, Fla. – In Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center in Florida, a worker inside space shuttle Endeavour checks the area where the new window will be installed. Endeavour is the designated launch vehicle for the STS-127 mission. The Japanese Experiment Module's Experiment Logistics Module-Exposed Section, or ELM-ES, is part of the payload on the mission, targeted for launch on May 15. Photo credit: NASA/Tim Jacobs

Modal noise investigation in multimode polymer waveguides

NASA Astrophysics Data System (ADS)

Beals, Joseph, IV; Bamiedakis, Nikos; Penty, Richard V.; White, Ian H.; DeGroot, Jon V., Jr.; Clapp, Terry V.

2007-11-01

In this work the recent interest in waveguides for use in short optical links has motivated a study of the modal noise dependence on launch conditions in short-reach step-index multimode polymer waveguides. Short optical links, especially those with several connection interfaces and utilising a restricted launch are likely to be subject to a modal noise power penalty. We therefore experimentally study the modal noise impact of restricted launches for a short-reach optical link employing a 50 x 50 μm polymer multimode waveguide. Lens launches resulting in small diameter input spots are investigated as are restricted launches from an 8 μm core optical fibre. For a launch spot of 10 μm diameter no impairment is observed for up to 9 dBo of mode selective loss, and for a fibre launch with a dynamic input movement of 6 μm no impairment is seen for up to 8 dBo of mode selective loss.

KSC-06pd0840

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- The payload canister passes NASA's Vehicle Assembly Building and Launch Control Center on its way to Launch Pad 39B. Inside are the payloads for mission STS-121: the multi-purpose logistics module Leonardo, with supplies and equipment for the International Space Station; the lightweight multi-purpose experiment support structure carrier; and the integrated cargo carrier, with the mobile transporter reel assembly and a spare pump module. The payload will be transferred from the canister to Space Shuttle Discovery's payload bay at the pad. Discovery is scheduled to launch on mission STS-121 from Launch Pad 39B in a window that opens July 1 and extends to July 19. Photo credit: NASA/Kim Shiflett

KSC-06pd0845

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- The payload canister passes NASA's Vehicle Assembly Building and Launch Control Center on its way to Launch Pad 39B. Inside are the payloads for mission STS-121: the multi-purpose logistics module Leonardo, with supplies and equipment for the International Space Station; the lightweight multi-purpose experiment support structure carrier; and the integrated cargo carrier, with the mobile transporter reel assembly and a spare pump module. The payload will be transferred from the canister to Space Shuttle Discovery's payload bay at the pad. Discovery is scheduled to launch on mission STS-121 from Launch Pad 39B in a window that opens July 1 and extends to July 19. Photo credit: NASA/Troy Cryder

KSC-06pd0841

NASA Image and Video Library

2006-05-17

KENNEDY SPACE CENTER, FLA. -- The payload canister passes NASA's Vehicle Assembly Building and Launch Control Center on its way to Launch Pad 39B. Inside are the payloads for mission STS-121: the multi-purpose logistics module Leonardo, with supplies and equipment for the International Space Station; the lightweight multi-purpose experiment support structure carrier; and the integrated cargo carrier, with the mobile transporter reel assembly and a spare pump module. The payload will be transferred from the canister to Space Shuttle Discovery's payload bay at the pad. Discovery is scheduled to launch on mission STS-121 from Launch Pad 39B in a window that opens July 1 and extends to July 19. Photo credit: NASA/George Shelton

KSC-06pd0820

NASA Image and Video Library

2006-05-12

KENNEDY SPACE CENTER, FLA. - The orbiter Discovery, on top of an orbiter transporter, heads toward NASA's Vehicle Assembly Building (VAB) after leaving the Orbiter Processing Facility. The rollover to the VAB marks the start of the journey to the launch pad and, ultimately, launch. Once inside the VAB, Discovery will be raised to vertical and lifted up and over into high bay 3 for stacking with its redesigned external tank and twin solid rocket boosters. The rollout of Space Shuttle Discovery to Launch Pad 39B is expected in approximately a week. Launch of Discovery on mission STS-121 is scheduled to take place in a window extending July 1 to July 19. Photo credit: NASA/Jim Grossmann

KSC-06pd0821

NASA Image and Video Library

2006-05-12

KENNEDY SPACE CENTER, FLA. - The orbiter Discovery, on top of an orbiter transporter, rolls into NASA's Vehicle Assembly Building (VAB) after leaving the Orbiter Processing Facility. The rollover to the VAB marks the start of the journey to the launch pad and, ultimately, launch. Once inside the VAB, Discovery will be raised to vertical and lifted up and over into high bay 3 for stacking with its redesigned external tank and twin solid rocket boosters. The rollout of Space Shuttle Discovery to Launch Pad 39B is expected in approximately a week. Launch of Discovery on mission STS-121 is scheduled to take place in a window extending July 1 to July 19. Photo credit: NASA/Jim Grossmann

KSC-97PC1540

NASA Image and Video Library

1997-10-12

At Launch Complex 40 on Cape Canaveral Air Station, the Mobile Service Tower has been retracted away from the Titan IVB/Centaur carrying the Cassini spacecraft, marking a major milestone in the launch countdown sequence. Retraction of the structure began about an hour later than scheduled due to minor problems with ground support equipment. The launch vehicle, Cassini spacecraft and attached Centaur stage encased in a payload fairing, altogether stand about 183 feet tall; mounted at the base of the launch vehicle are two upgraded solid rocket motors. Liftoff of Cassini on the journey to Saturn and its moon Titan is slated to occur during a window opening at 4:55 a.m. EDT, Oct. 13, and extending through 7:15 a.m

KSC-05PD-1782

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Workers in the Payload Hazardous Servicing Facility maneuver the second half of the fairing toward the Mars Reconnaissance Orbiter (right) for installation. The fairing protects the spacecraft during launch and flight through the atmosphere. Once in space, it is jettisoned. Launch of the MRO aboard an Atlas V rocket will be from Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The MRO is the next major step in Mars exploration and scheduled for launch from Cape Canaveral Air Force Station in a window opening Aug. 10. The MRO is an important next step in fulfilling NASAs vision of space exploration and ultimately sending human explorers to Mars and beyond.

KSC-05PD-1783

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Workers in the Payload Hazardous Servicing Facility stand by as the first half of the fairing (left) is moved closer to the Mars Reconnaissance Orbiter (right) for installation. The fairing protects the spacecraft during launch and flight through the atmosphere. Once in space, it is jettisoned. Launch of the MRO aboard an Atlas V rocket will be from Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The MRO is the next major step in Mars exploration and scheduled for launch from Cape Canaveral Air Force Station in a window opening Aug. 10. The MRO is an important next step in fulfilling NASAs vision of space exploration and ultimately sending human explorers to Mars and beyond.

Gyrotron whispering gallery mode coupler with a mode conversion reflector for exciting a circular symmetric uniform phase RF beam in a corrugated waveguide

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

Neilson, Jeffrey M.

A cylindrical waveguide with a mode converter transforms a whispering gallery mode from a gyrotron cylindrical waveguide with a helical cut launch edge to a quasi-Gaussian beam suitable for conveyance through a corrugated waveguide. This quasi-Gaussian beam is radiated away from the waveguide using a spiral cut launch edge, which is in close proximity to a first mode converting reflector. The first mode converting reflector is coupled to a second mode converting reflector which provides an output free-space HE11 mode wave suitable for direct coupling into a corrugated waveguide. The radiated beam produced at the output of the second modemore » converting reflector is substantially circular.« less

Unstable domains of tearing and Kelvin-Helmholtz instabilities in a rotating cylindrical plasma

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

Fan, D. M.; Wei, L.; Wang, Z. X., E-mail: zxwang@dlut.edu.cn

2014-09-15

Effects of poloidal rotation profile on tearing and Kelvin-Helmholtz (KH) instabilities in a cylindrical plasma are investigated by using a reduced magnetohydrodynamic model. Since the poloidal rotation has different effects on the tearing and KH modes in different rotation regimes, four unstable domains are numerically identified, i.e., the destabilized tearing mode domain, stabilized tearing mode domain, stable-window domain, and unstable KH mode domain. It is also found that when the rotation layer is in the outer region of the rational surface, the stabilizing role of the rotation can be enhanced so significantly that the stable window domain is enlarged. Moreover,more » Alfvén resonances can be induced by the tearing and KH modes in such rotating plasmas. Radially wide profiles of current and vorticity perturbations can be formed when multiple current sheets on different resonance positions are coupled together.« less

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

Model Analyst’s Toolkit User Guide, Version 7.1.0

DTIC Science & Technology

2015-08-01

Help > About)  Environment details ( operating system )  metronome.log file, located in your MAT 7.1.0 installation folder  Any log file that...requirements to run the Model Analyst’s Toolkit:  Windows XP operating system (or higher) with Service Pack 2 and all critical Windows updates installed...application icon on your desktop  Create a Quick Launch icon – Creates a MAT application icon on the taskbar for operating systems released

Effects of Restricted Launch Conditions for the Enhancement of Bandwidth-Distance Product of Multimode Fiber Links

NASA Technical Reports Server (NTRS)

Andrawis, Alfred S.

2000-01-01

Several techniques had been proposed to enhance multimode fiber bandwidth-distance product. Single mode-to-multimode offset launch condition technique had been experimented with at Kennedy Space Center. Significant enhancement in multimode fiber link bandwidth is achieved using this technique. It is found that close to three-fold bandwidth enhancement can be achieved compared to standard zero offset launch technique. Moreover, significant reduction in modal noise has been observed as a function of offset launch displacement. However, significant reduction in the overall signal-to-noise ratio is also observed due to signal attenuation due to mode radiation from fiber core to its cladding.

KSC-05PD-1101

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At a radar site on North Merritt Island, Fla., north of the Haulover Canal, workers are assembling the dish for the 50-foot NASA C-band radar. The radar will be used for long-term Shuttle missions to track the launches and observe possible debris coming from the Shuttle. In the background is an existing 30-foot C-band Pathfinder radar whose use was demonstrated on the Delta Messenger launch. It will be used on the upcoming two Return to Flight missions. The launch window for the first Return to Flight mission, STS-114, is July 13 to July 31..

KSC-05PD-1094

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Equipment is delivered for installation of another NASA C-band radar at a radar site on North Merritt Island, Fla. The 50-foot C-band radar will be used for long-term Shuttle missions to track the launches and observe possible debris coming from the Shuttle. In the background is an existing 30-foot C-band Pathfinder radar whose use was demonstrated on the Delta Messenger launch. It will be used on the upcoming two Return to Flight missions. The launch window for the first Return to Flight mission, STS-114, is July 13 to July 31.

KSC-05PD-0364

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Preparing for Return to Flight, workers at KSC walk the grounds around Launch Pad 39B looking for Foreign Object Debris, or FOD. The pad was recently refurbished and any possible debris left behind must be removed from the area prior to launch. Foreign objects that are alien to flight systems may cause material damage or may make the system or equipment inoperable, unsafe or less efficient. The Return to Flight mission STS-114 aboard Space Shuttle Discovery will carry supplies and equipment to the International Space Station. Discovery is scheduled for launch in a window from May 15 to June 3.

KSC-05PD-0366

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Preparing for Return to Flight, workers at KSC walk the grounds around Launch Pad 39B looking for Foreign Object Debris, or FOD. The pad was recently refurbished and any possible debris left behind must be removed from the area prior to launch. Foreign objects that are alien to flight systems may cause material damage or may make the system or equipment inoperable, unsafe or less efficient. The Return to Flight mission STS-114 aboard Space Shuttle Discovery will carry supplies and equipment to the International Space Station. Discovery is scheduled for launch in a window from May 15 to June 3.

KSC-05PD-0363

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Preparing for Return to Flight, workers at KSC walk the grounds around Launch Pad 39B looking for Foreign Object Debris, or FOD. The pad was recently refurbished and any possible debris left behind must be removed from the area prior to launch. Foreign objects that are alien to flight systems may cause material damage or may make the system or equipment inoperable, unsafe or less efficient. The Return to Flight mission STS-114 aboard Space Shuttle Discovery will carry supplies and equipment to the International Space Station. Discovery is scheduled for launch in a window from May 15 to June 3.

KSC-05PD-1095

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Equipment is delivered for installation of another NASA C-band radar at a radar site on North Merritt Island, Fla. The 50-foot C-band radar will be used for long-term Shuttle missions to track the launches and observe possible debris coming from the Shuttle. In the background is an existing 30-foot C-band Pathfinder radar whose use was demonstrated on the Delta Messenger launch. It will be used on the upcoming two Return to Flight missions. The launch window for the first Return to Flight mission, STS-114, is July 13 to July 31.

STS-131 Discovery Launch

NASA Image and Video Library

2010-04-04

NASA Administrator Charles Bolden looks out the window of Firing Room Four in the Launch Control Center during the launch of the space shuttle Discovery and the start of the STS-131 mission at NASA Kennedy Space Center in Cape Canaveral, Fla. on Monday April 5, 2010. Discovery is carrying a multi-purpose logistics module filled with science racks for the laboratories aboard the station. The mission has three planned spacewalks, with work to include replacing an ammonia tank assembly, retrieving a Japanese experiment from the station’s exterior, and switching out a rate gyro assembly on the station’s truss structure. Photo Credit: (NASA/Bill Ingalls)

KSC-05PD-1103

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At a radar site on North Merritt Island, Fla., north of the Haulover Canal, a 50-foot dish for NASAs C-band radar is being assembled. The radar will be used for long-term Shuttle missions to track the launches and observe possible debris coming from the Shuttle. At left is an existing 30-foot C-band Pathfinder radar whose use was demonstrated on the Delta Messenger launch. It will be used on the upcoming two Return to Flight missions. The launch window for the first Return to Flight mission, STS-114, is July 13 to July 31.

KSC-2011-7925

NASA Image and Video Library

2011-11-23

CAPE CANAVERAL, Fla. – At NASA Kennedy Space Center in Florida, media representatives taking the 21st Century Ground Systems tour appear to be the size of ants in this view from the top of the 355-foot-tall mobile launcher on Launch Pad 39B. Other stops on the tour include the Vehicle Assembly Building, a crawler-transporter parked on the crawlerway, and the Launch Control Center's Firing Room 1. These facilities and equipment will be used to prepare and launch NASA's new Orion spacecraft on the Space Launch System heavy-lift rocket. The tour was arranged as part of prelaunch media activities for the agency's Mars Science Laboratory (MSL) launch. Liftoff of MSL aboard a United Launch Alliance Atlas V rocket from Space Launch Complex-41 on Cape Canaveral Air Force Station is planned during a launch window which extends from 10:02 a.m. to 11:45 a.m. EST on Nov. 26. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Jim Grossmann

Polarization-Directed Surface Plasmon Polariton Launching

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

Gong, Yu; Joly, Alan G.; El-Khoury, Patrick Z.

The relative intensities of propagating surface plasmons (PSPs) simultaneously launched from opposing edges of a symmetric trench structure etched into a silver thin film may be controllably varied by tuning the linear polarization of the driving field. This is demonstrated through transient multiphoton photoemission electron microscopy measurements performed using a pair of spatially separated phase-locked femtosecond pulses. Our measurements are rationalized using finite-difference time domain simulations, which reveal that the coupling efficiency into the PSP modes is inversely proportional to the magnitude of the localized surface plasmon fields excited at the trench edges. Additional experiments on single step edges alsomore » show asymmetric PSP launching with respect to polarization, analogous to the trench results. Our combined experimental and computational results allude to the interplay between localized and propagating surface plasmon modes in the trench; strong coupling to the localized modes at the edges correlates to weak coupling to the PSP modes. Simultaneous excitation of the electric fields localized at both edges of the trench results in complex interactions between the right- and left-side PSP modes with Fabry-Perot and cylindrical modes. This results in a trench width-dependent PSP intensity ratio using otherwise identical driving fields. A systematic exploration of polarization directed PSP launching from a series of trench structures reveals an optimal PSP contrast ratio of 4.2 using a 500 nm-wide trench.« less

KSC-05PD-1240

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Resting on an orbiter transporter in the transfer aisle of the Vehicle Assembly Building, the orbiter Discovery is being prepped for a lift to vertical and remate to a new External Tank, ET-121. The new tank and Solid Rocket Boosters are waiting in high bay 3. Discovery is expected roll back to the launch pad June 13 for Return to Flight mission STS-114. The launch window extends from July 13 to July 31.

Optimization studies of the ITER low field side reflectometer.

PubMed

Diem, S J; Wilgen, J B; Bigelow, T S; Hanson, G R; Harvey, R W; Smirnov, A P

2010-10-01

Microwave reflectometry will be used on ITER to measure the electron density profile, density fluctuations due to MHD/turbulence, edge localized mode (ELM) density transients, and as an L-H transition monitor. The ITER low field side reflectometer system will measure both core and edge quantities using multiple antenna arrays spanning frequency ranges of 15-155 GHz for the O-mode system and 55-220 GHz for the X-mode system. Optimization studies using the GENRAY ray-tracing code have been done for edge and core measurements. The reflectometer launchers will utilize the HE11 mode launched from circular corrugated waveguide. The launched beams are assumed to be Gaussian with a beam waist diameter of 0.643 times the waveguide diameter. Optimum launcher size and placement are investigated by computing the antenna coupling between launchers, assuming the launched and received beams have a Gaussian beam pattern.

Low energy stage study. Volume 2: Requirements and candidate propulsion modes. [orbital launching of shuttle payloads

NASA Technical Reports Server (NTRS)

1978-01-01

A payload mission model covering 129 launches, was examined and compared against the space transportation system shuttle standard orbit inclinations and a shuttle launch site implementation schedule. Based on this examination and comparison, a set of six reference missions were defined in terms of spacecraft weight and velocity requirements to deliver the payload from a 296 km circular Shuttle standard orbit to the spacecraft's planned orbit. Payload characteristics and requirements representative of the model payloads included in the regime bounded by each of the six reference missions were determined. A set of launch cost envelopes were developed and defined based on the characteristics of existing/planned Shuttle upper stages and expendable launch systems in terms of launch cost and velocity delivered. These six reference missions were used to define the requirements for the candidate propulsion modes which were developed and screened to determine the propulsion approaches for conceptual design.

Simple and reliable light launch from a conventional single-mode fiber into a helical-core fiber through an adiabatically tapered splice.

PubMed

Kim, Hyuntai; Kim, Jongki; Jung, Yongmin; Vazquez-Zuniga, Luis Alonso; Lee, Seung Jong; Choi, Geunchang; Oh, Kyunghwan; Wang, Pu; Clarkson, W A; Jeong, Yoonchan

2012-11-05

We propose a simple and efficient light launch scheme for a helical-core fiber (HCF) by using an adiabatically tapered splice technique, through which we overcome its inherent difficulty with light launch owing to the large lateral offset and angular tilt of its core. We experimentally demonstrate single-mode excitation in the HCF in this configuration, which yields the coupling efficiency of around -5.9 dB (26%) for a ~1.1-μm light input when the splice joint is tapered down to 30 μm in diameter. To our knowledge, this is the first proof-of-principle report on the fusion-splice coupling between an HCF and a conventional single-mode fiber.

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at Pad 39A, Kennedy Space Center, Fla. Discovery, the orbiter for STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

NASA Image and Video Library

1997-02-07

KENNEDY SPACE CENTER, FLA. - The Payload is seen inside of the Bay just before the doors are closed for flight at Pad 39A, Kennedy Space Center, Fla. Discovery, the orbiter for STS-82 mission, is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) that will be installed, Fine Guidance Sensor #1 (FGS-1), and the Space Telescope Imaging Spectrograph (STIS) to be installed. The STS-82 will launch with a crew of seven at 3:54 a.m. EST, Feb. 11, 1997. The launch window is 65 minutes in duration. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope, and provide a reboost to the optimum altitude.

Demand-type gas supply system for rocket borne thin-window proportional counters

NASA Technical Reports Server (NTRS)

Acton, L. W.; Caravalho, R.; Catura, R. C.; Joki, E. G.

1977-01-01

A simple closed loop control system has been developed to maintain the gas pressure in thin-window proportional counters during rocket flights. This system permits convenient external control of detector pressure and system flushing rate. The control system is activated at launch with the sealing of a reference volume at the existing system pressure. Inflight control to plus or minus 2 torr at a working pressure of 760 torr has been achieved on six rocket flights.

Development of new S-band RF window for stable high-power operation in linear accelerator RF system

NASA Astrophysics Data System (ADS)

Joo, Youngdo; Lee, Byung-Joon; Kim, Seung-Hwan; Kong, Hyung-Sup; Hwang, Woonha; Roh, Sungjoo; Ryu, Jiwan

2017-09-01

For stable high-power operation, a new RF window is developed in the S-band linear accelerator (Linac) RF systems of the Pohang Light Source-II (PLS-II) and the Pohang Accelerator Laboratory X-ray Free-Electron Laser (PAL-XFEL). The new RF window is designed to mitigate the strength of the electric field at the ceramic disk and also at the waveguide-cavity coupling structure of the conventional RF window. By replacing the pill-box type cavity in the conventional RF window with an overmoded cavity, the electric field component perpendicular to the ceramic disk that caused most of the multipacting breakdowns in the ceramic disk was reduced by an order of magnitude. The reduced electric field at the ceramic disk eliminated the Ti-N coating process on the ceramic surface in the fabrication procedure of the new RF window, preventing the incomplete coating from spoiling the RF transmission and lowering the fabrication cost. The overmoded cavity was coupled with input and output waveguides through dual side-wall coupling irises to reduce the electric field strength at the waveguide-cavity coupling structure and the possibility of mode competitions in the overmoded cavity. A prototype of the new RF window was fabricated and fully tested with the Klystron peak input power, pulse duration and pulse repetition rate of 75 MW, 4.5 μs and 10 Hz, respectively, at the high-power test stand. The first mass-produced new RF window installed in the PLS-II Linac is running in normal operation mode. No fault is reported to date. Plans are being made to install the new RF window to all S-band accelerator RF modules of the PLS-II and PAL-XFEL Linacs. This new RF window may be applied to the output windows of S-band power sources like Klystron as wells as the waveguide windows of accelerator facilities which operate in S-band.

KSC-97pc222

NASA Image and Video Library

1997-01-24

Space Systems/LORAL employees inspect solar panels for the GOES-K weather satellite in the Astrotech facility at Titusville, Fla., as they begin final testing of the imaging system, communications and power systems of the spacecraft. The GOES-K is the third spacecraft to be launched in the new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration (NOAA). The GOES-K is built for NASA and NOAA by Space Systems/LORAL of Palo Alto, Calif. The launch of the satellite from Launch Pad 36B at Cape Canaveral Air Station on an Atlas 1 rocket (AC-79) is currently planned for Apr. 24 at the opening of a launch window which extends from 1:56 to 3:19 a.m. EDT

KSC-97pc223

NASA Image and Video Library

1997-01-24

Space Systems/LORAL employees inspect solar panels for the GOES-K weather satellite in the Astrotech facility at Titusville, Fla., as they begin final testing of the imaging system, communications and power systems of the spacecraft. The GOES-K is the third spacecraft to be launched in the new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration (NOAA). The GOES-K is built for NASA and NOAA by Space Systems/LORAL of Palo Alto, Calif. The launch of the satellite from Launch Pad 36B at Cape Canaveral Air Station on an Atlas 1 rocket (AC-79) is currently planned for Apr. 24 at the opening of a launch window which extends from 1:56 to 3:19 a.m. EDT

KSC-97pc224

NASA Image and Video Library

1997-01-24

Space Systems/LORAL employees inspect solar panels for the GOES-K weather satellite in the Astrotech facility at Titusville, Fla., as they begin final testing of the imaging system, communications and power systems of the spacecraft. The GOES-K is the third spacecraft to be launched in the new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration (NOAA). The GOES-K is built for NASA and NOAA by Space Systems/LORAL of Palo Alto, Calif. The launch of the satellite from Launch Pad 36B at Cape Canaveral Air Station on an Atlas 1 rocket (AC-79) is currently planned for Apr. 24 at the opening of a launch window which extends from 1:56 to 3:19 a.m. EDT

KSC-05PD-0855

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Mission Specialist Andrew Thomas is ready to practice driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-05PD-0854

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Pilot James Kelly is ready to practice driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-05PD-0846

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, the STS-114 Mission Specialist Wendy Lawrence is getting ready to practice driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-05PD-0848

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Mission Specialist Stephen Robinson is getting ready to practice driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

San Marco C-2 (San Marco-4) Post Launch Report No. 1

NASA Technical Reports Server (NTRS)

1974-01-01

The San Marco C-2 spacecraft, now designated San Marco-4, was successfully launched by a Scout vehicle from the San Marco Platform on 18 February 1974 at 6:05 a.m. EDT. The launch occurred 2 hours 50 minutes into the 3-hour window due co low cloud cover at the launch site. All spacecraft subsystems have been checked and are functioning normally. The protective caps for the two U.S. experiments were ejected and the Omegatron experiment activated on 19 February. The neutral mass spectrometer was activated as scheduled on 22 February after sufficient time to allow for spacecraft outgassing and to avoid the possibility of corona occurring. Both instruments are performing properly and worthwhile scientific data is being acquired.

GOES-K solar panel inspection at Astrotech

NASA Technical Reports Server (NTRS)

1997-01-01

Space Systems/LORAL employees inspect solar panels for the GOES-K weather satellite in the Astrotech facility at Titusville, Fla., as they begin final testing of the imaging system, communications and power systems of the spacecraft. The GOES-K is the third spacecraft to be launched in the new advanced series of geostationary weather satellites for the National Oceanic and Atmospheric Administration (NOAA). The GOES-K is built for NASA and NOAA by Space Systems/LORAL of Palo Alto, Calif. The launch of the satellite from Launch Pad 36B at Cape Canaveral Air Station on an Atlas 1 rocket (AC-79) is currently planned for Apr. 24 at the opening of a launch window which extends from 1:56 to 3:19 a.m. EDT.

KSC-04PD-2284

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the mobile service tower on Launch Pad 17-A, Cape Canaveral Air Force Station, Boeing technicians help guide the Swift spacecraft as it is lowered toward the Boeing Delta II launch vehicle for mating. Swift is scheduled to launch Nov. 17. The liftoff aboard a Boeing Delta II rocket is targeted at the opening of a one-hour launch window beginning at 12:09 p.m. EST. A first-of-its-kind multi-wavelength observatory dedicated to the study of gamma-ray burst (GRB) science, Swifts three instruments will work together to observe GRBs and afterglows in the gamma ray, X-ray, ultraviolet and optical wavebands. Gamma-ray bursts are distant, yet fleeting explosions that appear to signal the births of black holes.

KSC-05PD-1784

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Workers in the Payload Hazardous Servicing Facility make adjustments as they get ready to move the second half of the fairing (right) and install it with the first half around the Mars Reconnaissance Orbiter. The fairing protects the spacecraft during launch and flight through the atmosphere. Once in space, it is jettisoned. Launch of the MRO aboard an Atlas V rocket will be from Launch Complex 41 at Cape Canaveral Air Force Station in Florida. The MRO is the next major step in Mars exploration and scheduled for launch from Cape Canaveral Air Force Station in a window opening Aug. 10. The MRO is an important next step in fulfilling NASAs vision of space exploration and ultimately sending human explorers to Mars and beyond.

New electromagnetic mode in graphene.

PubMed

Mikhailov, S A; Ziegler, K

2007-07-06

A new, weakly damped, transverse electromagnetic mode is predicted in graphene. The mode frequency omega lies in the window 1.667<[see text]omega/micro < 2, where micro is the chemical potential, and can be tuned from radio waves to the infrared by changing the density of charge carriers through a gate voltage.

50-Year Window to Establish a Space Faring Civilization

NASA Technical Reports Server (NTRS)

Howe, A. Scott

2015-01-01

Humankind may only have a short window of 50 years to become a space-faring civilization, after which time the opportunity to do so may become too difficult or impractical to pursue. Current policies for space exploration and infrastructure development implicitly assume a gradualistic approach to technology, budgets, and mission execution -- the common thought has been that there will be plenty of time in humankind's future to become a space-based species, and whatever we are unable to accomplish will be borne by the generations that follow. However, considering natural events, available energy, and human tendencies, the timing to make the most effective effort to achieve multi-planet status might be now, before momentum is lost and we become distracted by Peak Oil and changing energy economies -- restarting a space program after such turmoil may be more difficult than would be practical without cheap, storable, high-energy density petroleum. "Space-faring civilization" is defined as an economically profitable space-based economy that demands the presence of humans off-world in order to sustain a high level of prosperity. An initial foothold for a space-based economy that would fit within the 50-year window might include Earth dependence on rare-earth elements or other hard-to-obtain minerals mined from moons or asteroids, or a permanent settlement on another planet. Using published sources, notional mass and energy requirements for a minimal self-sustaining Mars settlement is calculated, and the number of launch vehicles discussed. Setting the launch schedule to match that of current NASA projections, it could take more than 26 years of semi-annual launches to build up such a self-sustaining human settlement -- a cost and commitment that has not been acknowledged nor planned for. Considering the time required to establish a multi-planet species, this paper frames the required window of decision that, if not taken, could condemn the species to Earth subject to whatever natural or human-made calamities that endanger single-planet civilizations.

Investigation on Improvements in Lightning Retest Criteria for Spacecraft

NASA Technical Reports Server (NTRS)

Terseck, Alex; Trout, Dawn

2016-01-01

Spacecraft are generally protected from a direct strike by launch the vehicle and ground structures, but protocols to evaluate the impact of nearby strikes are not consistent. Often spacecraft rely on the launch vehicle constraints to trigger a retest, but launch vehicles can typically evaluate the impact of a strike within minutes while spacecraft evaluation times can be on the order of hours or even days. For launches at the Kennedy Space Center where lightning activity is among the highest in the United States, this evaluation related delay could be costly with the possibility of missing the launch window altogether. This paper evaluated available data from local lightning measurements systems and computer simulations to predict the coupled effect from various nearby strikes onto a typical payload umbilical. Recommendations are provided to reduce the typical trigger criteria and costly delays.

KSC-06pd1758

NASA Image and Video Library

2006-08-08

KENNEDY SPACE CENTER, FLA. - STS-115 Mission Specialist Daniel Burbank is ready to practice driving the M-113 armored personnel carrier. The STS-115 crew are at NASA's Kennedy Space Center for Terminal Countdown Demonstration Test activities such as the M-113 training. They will also practice emergency egress from the launch pad and take part in a simulated launch countdown. Liftoff of mission STS-115 aboard Space Shuttle Atlantis is scheduled in a window beginning Aug. 27. Photo credit: NASA/Cory Huston

KSC-06pd1752

NASA Image and Video Library

2006-08-08

KENNEDY SPACE CENTER, FLA. - STS-115 Pilot Christopher Ferguson is ready to practice driving the M-113 armored personnel carrier. The STS-115 crew are at NASA's Kennedy Space Center for Terminal Countdown Demonstration Test activities such as the M-113 training. They will also practice emergency egress from the launch pad and take part in a simulated launch countdown. Liftoff of mission STS-115 aboard Space Shuttle Atlantis is scheduled in a window beginning Aug. 27. Photo credit: NASA/Cory Huston

Overdense microwave plasma heating in the CNT stellarator

NASA Astrophysics Data System (ADS)

Hammond, K. C.; Diaz-Pacheco, R. R.; Köhn, A.; Volpe, F. A.; Wei, Y.

2018-02-01

Overdense plasmas have been attained with 2.45 GHz microwave heating in the low-field, low-aspect-ratio CNT stellarator. Densities higher than four times the ordinary (O) mode cutoff density were measured with 8 kW of power injected in the O-mode and, alternatively, with 6.5 kW in the extraordinary (X) mode. The temperature profiles peak at the plasma edge. This was ascribed to collisional damping of the X-mode at the upper hybrid resonant layer. The X-mode reaches that location by tunneling, mode-conversions or after polarization-scrambling reflections off the wall and in-vessel coils, regardless of the initial launch being in O- or X-mode. This interpretation was confirmed by full-wave numerical simulations. Also, as the CNT plasma is not completely ionized at these low microwave power levels, electron density was shown to increase with power. A dependence on magnetic field strength was also observed, for O-mode launch.

An Innovative Structural Mode Selection Methodology: Application for the X-33 Launch Vehicle Finite Element Model

NASA Technical Reports Server (NTRS)

Hidalgo, Homero, Jr.

2000-01-01

An innovative methodology for determining structural target mode selection and mode selection based on a specific criterion is presented. An effective approach to single out modes which interact with specific locations on a structure has been developed for the X-33 Launch Vehicle Finite Element Model (FEM). We presented Root-Sum-Square (RSS) displacement method computes resultant modal displacement for each mode at selected degrees of freedom (DOF) and sorts to locate modes with highest values. This method was used to determine modes, which most influenced specific locations/points on the X-33 flight vehicle such as avionics control components, aero-surface control actuators, propellant valve and engine points for use in flight control stability analysis and for flight POGO stability analysis. Additionally, the modal RSS method allows for primary or global target vehicle modes to also be identified in an accurate and efficient manner.

Launch device using endlessly single-mode PCF for ultra-wideband WDM transmission in graded-index multi-mode fiber.

PubMed

Ma, Lin; Hanzawa, Nobutomo; Tsujikawa, Kyozo; Azuma, Yuji

2012-10-22

We demonstrated ultra-wideband wavelength division multiplexing (WDM) transmission from 850 to 1550 nm in graded-index multi-mode fiber (GI-MMF) using endlessly single-mode photonic crystal fiber (ESM-PCF) as a launch device. Effective single-mode guidance is obtained in multi-mode fiber at all wavelengths by splicing cm-order length ESM-PCF to the transmission fiber. We achieved 3 × 10 Gbit/s WDM transmission in a 1 km-long 50-μm-core GI-MMF. We also realized penalty free 10 Gbit/s data transmission at a wavelength of 850 nm by optimizing the PCF structure. This method has the potential to achieve greater total transmission capacity for MMF systems by the addition of more wavelength channels.

KSC-97PC958

NASA Image and Video Library

1997-07-01

The STS-94 crew walks out of the Operations and Checkout Building and heads for the Astrovan that will transport them to Launch Pad 39A as KSC employees show their support. Waving to the crowd and leading the way are Mission Commander James D. Halsell, Jr. and Pilot Susan L. Still. Behind Still is Mission Specialist Donald A.Thomas, followed by Mission Specialist Michael L. Gernhardt , Payload Commander Janice Voss, and Payload Specialists Roger K.Crouch and Gregory T. Linteris. During the scheduled 16-day Microgravity Science Laboratory-1 (MSL-1) mission, the Spacelab module will be used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station while the flight crew conducts combustion, protein crystal growth and materials processing experiments. Also onboard is the Hitchhiker Cryogenic Flexible Diode (CRYOFD) experiment payload, which is attached to the right side of Columbia’s payload bay.The Space Shuttle Columbia is scheduled to lift off when the launch window opens at 1:50 p.m. EDT, July 1. The launch window was opened 47 minutes early to improve the opportunity to lift off before Florida summer rain showers reached the space center

Experience Gained From Launch and Early Orbit Support of the Rossi X-Ray Timing Explorer (RXTE)

NASA Technical Reports Server (NTRS)

Fink, D. R.; Chapman, K. B.; Davis, W. S.; Hashmall, J. A.; Shulman, S. E.; Underwood, S. C.; Zsoldos, J. M.; Harman, R. R.

1996-01-01

this paper reports the results to date of early mission support provided by the personnel of the Goddard Space Flight Center Flight Dynamics Division (FDD) for the Rossi X-Ray Timing Explorer (RXTE) spacecraft. For this mission, the FDD supports onboard attitude determination and ephemeris propagation by supplying ground-based orbit and attitude solutions and calibration results. The first phase of that support was to provide launch window analyses. As the launch window was determined, acquisition attitudes were calculated and calibration slews were planned. postlaunch, these slews provided the basis for ground determined calibration. Ground determined calibration results are used to improve the accuracy of onboard solutions. The FDD is applying new calibration tools designed to facilitate use of the simultaneous, high-accuracy star observations from the two RXTE star trackers for ground attitude determination and calibration. An evaluation of the performance of these tools is presented. The FDD provides updates to the onboard star catalog based on preflight analysis and analysis of flight data. The in-flight results of the mission support in each area are summarized and compared with pre-mission expectations.

Fully automatic time-window selection using machine learning for global adjoint tomography

NASA Astrophysics Data System (ADS)

Chen, Y.; Hill, J.; Lei, W.; Lefebvre, M. P.; Bozdag, E.; Komatitsch, D.; Tromp, J.

2017-12-01

Selecting time windows from seismograms such that the synthetic measurements (from simulations) and measured observations are sufficiently close is indispensable in a global adjoint tomography framework. The increasing amount of seismic data collected everyday around the world demands "intelligent" algorithms for seismic window selection. While the traditional FLEXWIN algorithm can be "automatic" to some extent, it still requires both human input and human knowledge or experience, and thus is not deemed to be fully automatic. The goal of intelligent window selection is to automatically select windows based on a learnt engine that is built upon a huge number of existing windows generated through the adjoint tomography project. We have formulated the automatic window selection problem as a classification problem. All possible misfit calculation windows are classified as either usable or unusable. Given a large number of windows with a known selection mode (select or not select), we train a neural network to predict the selection mode of an arbitrary input window. Currently, the five features we extract from the windows are its cross-correlation value, cross-correlation time lag, amplitude ratio between observed and synthetic data, window length, and minimum STA/LTA value. More features can be included in the future. We use these features to characterize each window for training a multilayer perceptron neural network (MPNN). Training the MPNN is equivalent to solve a non-linear optimization problem. We use backward propagation to derive the gradient of the loss function with respect to the weighting matrices and bias vectors and use the mini-batch stochastic gradient method to iteratively optimize the MPNN. Numerical tests show that with a careful selection of the training data and a sufficient amount of training data, we are able to train a robust neural network that is capable of detecting the waveforms in an arbitrary earthquake data with negligible detection error compared to existing selection methods (e.g. FLEXWIN). We will introduce in detail the mathematical formulation of the window-selection-oriented MPNN and show very encouraging results when applying the new algorithm to real earthquake data.

STS-76 Payload Cmdr Ronald Sega suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-76 Payload Commander Ronald M. Sega is donning his launch/entry suit in the Operations and Checkout Building with assistance from a suit technician. The third docking between the Russian Space Station Mir and the U.S. Space Shuttle marks the second trip into space for Sega, who recently served a five-month assignment in Russia as operations director for NASA activities there. Once suitup activities are completed the six-member STS-76 flight crew will depart for Launch Pad 39B, where the Space Shuttle Atlantis is undergoing final preparations for liftoff during an approximately seven-minute launch window opening around 3:13 a.m. EST, March 22.

KSC-98pc208

NASA Image and Video Library

1998-01-22

STS-89 Mission Specialist Salizhan Sharipov of the Russian Space Agency, at left, waves as he and his flight surgeon, Alexander Kulev, complete the donning of Sharipov’s launch/entry suit in the Operations and Checkout (O&C) Building. In 1994, Sharipov graduated from Moscow State University with a degree in cartography. He and six fellow crew members will soon depart the O&C and head for Launch Pad 39A, where the Space Shuttle Endeavour will lift off during a launch window that opens at 9:43 p.m. EST, Jan. 22. STS-89 is the eighth of nine planned missions to dock the Space Shuttle with Russia's Mir space station

KSC-05PD-0365

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Preparing for Return to Flight, workers at KSC walk the grounds around Launch Pad 39B looking for and picking up Foreign Object Debris, or FOD. The pad was recently refurbished and any possible debris left behind must be removed from the area prior to launch. Foreign objects that are alien to flight systems may cause material damage or may make the system or equipment inoperable, unsafe or less efficient. The Return to Flight mission STS-114 aboard Space Shuttle Discovery will carry supplies and equipment to the International Space Station. Discovery is scheduled for launch in a window from May 15 to June 3.

KSC-98pc521

NASA Image and Video Library

1998-04-21

Processing activities for STS-91 continue in KSC's Orbiter Processing Facility Bay 2. Two Get Away Special (GAS) canisters are shown after their installation into Discovery's payload bay. At left is G-090, containing three educational experiments sponsored by Utah State University, and at right is G-743, an experiment sponsored by Broward Community College in Florida to test DNA exposed to cosmic radiation in a microgravity environment. STS-91 is scheduled to launch aboard the Space Shuttle Discovery for the ninth and final docking with the Russian Space Station Mir from KSC's Launch Pad 39A on June 2 with a launch window opening around 6:04 p.m. EDT

STS-131 Discovery Launch

NASA Image and Video Library

2010-04-05

201004050001hq (5 April 2010) --- NASA Administrator Charles Bolden looks out the window of Firing Room Four in the Launch Control Center during the launch of the space shuttle Discovery and the start of the STS-131 mission at NASA Kennedy Space Center in Cape Canaveral, Fla. on April 5, 2010. Discovery is carrying a multi-purpose logistics module filled with science racks for the laboratories aboard the International Space Station. The mission has three planned spacewalks, with work to include replacing an ammonia tank assembly, retrieving a Japanese experiment from the station?s exterior, and switching out a rate gyro assembly on the station?s truss structure. Photo Credit: NASA/Bill Ingalls

KSC-05pd2542

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - Inside NASA Kennedy Space Center’s Payload Hazardous Servicing Facility, workers push the newly arrived third stage, or upper stage for the New Horizons spacecraft, into position for uncovering. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2539

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - Before dawn, the third stage, or upper stage for the New Horizons spacecraft, arrives at NASA Kennedy Space Center’s Payload Hazardous Servicing Facility. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2541

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - The third stage, or upper stage for the New Horizons spacecraft, is moved toward the open door of NASA Kennedy Space Center’s Payload Hazardous Servicing Facility. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2540

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - The third stage, or upper stage for the New Horizons spacecraft, is moved toward the open door of NASA Kennedy Space Center’s Payload Hazardous Servicing Facility. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

KSC-05pd2543

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - Inside NASA Kennedy Space Center’s Payload Hazardous Servicing Facility, workers remove the protective cover from around the newly arrived third stage, or upper stage for the New Horizons spacecraft. The third stage is a Boeing STAR 48 solid-propellant kick motor. The Atlas V is the launch vehicle for NASA’s New Horizons spacecraft, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11 and fly through the Pluto system as early as summer 2015. New Horizons will be powered by a single radioisotope thermoelectric generator (RTG), provided by the Department of Energy, which will be installed shortly before launch.

Processing activities for STS-91 continue in OPF Bay 2

NASA Technical Reports Server (NTRS)

1998-01-01

Processing activities for STS-91 continue in KSC's Orbiter Processing Facility Bay 2. Two Get Away Special (GAS) canisters are shown after their installation into Discovery's payload bay. At left is G-648, an Canadian Space Agency-sponsored study of manufactured organic thin film by the physical vapor transport method, and the can on the right contains commemorative flags to be flown during the mission. STS-91 is scheduled to launch aboard the Space Shuttle Discovery for the ninth and final docking with the Russian Space Station Mir from KSC's Launch Pad 39A on June 2 with a launch window opening around 6:04 p.m. EDT.

A Finite-Difference Time-Domain Model of Artificial Ionospheric Modification

NASA Astrophysics Data System (ADS)

Cannon, Patrick; Honary, Farideh; Borisov, Nikolay

Experiments in the artificial modification of the ionosphere via a radio frequency pump wave have observed a wide range of non-linear phenomena near the reflection height of an O-mode wave. These effects exhibit a strong aspect-angle dependence thought to be associated with the process by which, for a narrow range of off-vertical launch angles, the O-mode pump wave can propagate beyond the standard reflection height at X=1 as a Z-mode wave and excite additional plasma activity. A numerical model based on Finite-Difference Time-Domain method has been developed to simulate the interaction of the pump wave with an ionospheric plasma and investigate different non-linear processes involved in modification experiments. The effects on wave propagation due to plasma inhomogeneity and anisotropy are introduced through coupling of the Lorentz equation of motion for electrons and ions to Maxwell’s wave equations in the FDTD formulation, leading to a model that is capable of exciting a variety of plasma waves including Langmuir and upper-hybrid waves. Additionally, discretized equations describing the time-dependent evolution of the plasma fluid temperature and density are included in the FDTD update scheme. This model is used to calculate the aspect angle dependence and angular size of the radio window for which Z-mode excitation occurs, and the results compared favourably with both theoretical predictions and experimental observations. The simulation results are found to reproduce the angular dependence on electron density and temperature enhancement observed experimentally. The model is used to investigate the effect of different initial plasma density conditions on the evolution of non-linear effects, and demonstrates that the inclusion of features such as small field-aligned density perturbations can have a significant influence on wave propagation and the magnitude of temperature and density enhancements.

Window encapsulation in car industry by using the 50 {Omega} RF technology

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

Bernard, J.P.; Barboteau, M.; Collet, L.

Throughout the world car industry has been using window encapsulation for a few years now. This technology is mainly used in production lines and is called RIM for polyurethane reaction injection moulding. This technology, however brings about some problems such as: glass breaking during mould closure, high production cost, systematic rough edges. The PSA Group (Peugeot-Citroen), a pioneer in this field, in collaboration with SAIREM has launched a new innovating process for window encapsulation by using the 50 {Omega} RF technology for gelling PVC Plastisol. The study was followed by an industrial prototype. Industrial equipment was then installed at WEBASTOmore » HEULIEZ for window encapsulation of the sunshine roof for the Citroen Xantia. The authors describe the principle of window encapsulation and the different existing processes. They describe the 50 {Omega} RF technology, an industrial installation and the constraints of this technology in order to get maximum efficiency. In the conclusion they present a technical and economical analysis of the different solutions for window encapsulation. They also present the advantages of the 50 {Omega} RF technology and the new opportunities it offers.« less

Ballistic mode Mercury orbiter missions.

NASA Technical Reports Server (NTRS)

Hollenbeck, G. R.

1973-01-01

The MVM'73 Mercury flyby mission will initiate exploration of this unique planet. No firm plans for follow-on investigations have materialized due to the difficult performance requirements of the next logical step, an orbiter mission. Previous investigations of ballistic mode flight opportunities have indicated requirements for a Saturn V class launch vehicle. Consequently, most recent effort has been oriented to use of solar electric propulsion. More comprehensive study of the ballistic flight mode utilizing Venus gravity-assist has resulted in identification of timely high-performance mission opportunities compatible with programmed launch vehicles and conventional spacecraft propulsion technologies. A likely candidate for an initial orbiter mission is a 1980 opportunity which offers net orbiter spacecraft mass of about 435 kg with the Titan IIIE/Centaur launch vehicle and single stage solid propulsion for orbit insertion.

Gaussian-windowed frame based method of moments formulation of surface-integral-equation for extended apertures

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

Shlivinski, A., E-mail: amirshli@ee.bgu.ac.il; Lomakin, V., E-mail: vlomakin@eng.ucsd.edu

2016-03-01

Scattering or coupling of electromagnetic beam-field at a surface discontinuity separating two homogeneous or inhomogeneous media with different propagation characteristics is formulated using surface integral equation, which are solved by the Method of Moments with the aid of the Gabor-based Gaussian window frame set of basis and testing functions. The application of the Gaussian window frame provides (i) a mathematically exact and robust tool for spatial-spectral phase-space formulation and analysis of the problem; (ii) a system of linear equations in a transmission-line like form relating mode-like wave objects of one medium with mode-like wave objects of the second medium; (iii)more » furthermore, an appropriate setting of the frame parameters yields mode-like wave objects that blend plane wave properties (as if solving in the spectral domain) with Green's function properties (as if solving in the spatial domain); and (iv) a representation of the scattered field with Gaussian-beam propagators that may be used in many large (in terms of wavelengths) systems.« less

Center for the Built Environment: Research on Building Envelope Systems

Science.gov Websites

Studies Facade and Perimeter Zone Field Study Facades and Thermal Comfort Facade Symposium Mixed-Mode Research Adaptive Comfort Model Mixed-Mode Case Studies Operable Windows and Thermal Comfort Occupant thermal preferences in naturally ventilated as sealed buildings? Case Study Research of Mixed-Mode Office

The Multi-Attribute Task Battery II (MATB-II) Software for Human Performance and Workload Research: A User's Guide

NASA Technical Reports Server (NTRS)

Santiago-Espada, Yamira; Myer, Robert R.; Latorella, Kara A.; Comstock, James R., Jr.

2011-01-01

The Multi-Attribute Task Battery (MAT Battery). is a computer-based task designed to evaluate operator performance and workload, has been redeveloped to operate in Windows XP Service Pack 3, Windows Vista and Windows 7 operating systems.MATB-II includes essentially the same tasks as the original MAT Battery, plus new configuration options including a graphical user interface for controlling modes of operation. MATB-II can be executed either in training or testing mode, as defined by the MATB-II configuration file. The configuration file also allows set up of the default timeouts for the tasks, the flow rates of the pumps and tank levels of the Resource Management (RESMAN) task. MATB-II comes with a default event file that an experimenter can modify and adapt

In-Flight Suppression of a De-Stabilized F/A-18 Structural Mode Using the Space Launch System Adaptive Augmenting Control System

NASA Technical Reports Server (NTRS)

Wall, John; VanZwieten, Tannen; Giiligan Eric; Miller, Chris; Hanson, Curtis; Orr, Jeb

2015-01-01

Adaptive Augmenting Control (AAC) has been developed for NASA's Space Launch System (SLS) family of launch vehicles and implemented as a baseline part of its flight control system (FCS). To raise the technical readiness level of the SLS AAC algorithm, the Launch Vehicle Adaptive Control (LVAC) flight test program was conducted in which the SLS FCS prototype software was employed to control the pitch axis of Dryden's specially outfitted F/A-18, the Full Scale Advanced Systems Test Bed (FAST). This presentation focuses on a set of special test cases which demonstrate the successful mitigation of the unstable coupling of an F/A-18 airframe structural mode with the SLS FCS.

STS-75 Payload Specialist Umberto Guidoni suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-75 Payload Specialist Umberto Guidoni (right) chats with fellow crew member Mission Specialist Claude Nicollier during suitup activities in the Operations and Checkout Building. Guidoni represents the Italian Space Agency and is one of three international crew members assigned to STS-75. He and six fellow crew members will depart shortly for Launch Pad 39B, where the Space Shuttle Columbia awaits liftoff during a two-and-a-half- hour launch window opening at 3:18 p.m. EST.

KSC-06pd0764

NASA Image and Video Library

2006-04-30

KENNEDY SPACE CENTER, FLA. - On Launch Complex 37 at Cape Canaveral Air Force Station in Florida, the GOES-N spacecraft is lowered toward the second stage of the Boeing Delta IV rocket for mating. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA, providing continuous monitoring necessary for intensive data analysis. GOES-N is scheduled to be launched May 18 in an hour-long window between 6:14 and 7:14 p.m. EDT. Photo credit: NASA/Charisse Nahser

KSC-06pd1756

NASA Image and Video Library

2006-08-08

KENNEDY SPACE CENTER, FLA. - STS-115 Mission Specialist Heidemarie Stefanyshyn-Piper is ready to practice driving the M-113 armored personnel carrier. Behind her is pilot Christopher Ferguson. The STS-115 crew are at NASA's Kennedy Space Center for Terminal Countdown Demonstration Test activities such as the M-113 training. They will also practice emergency egress from the launch pad and take part in a simulated launch countdown. Liftoff of mission STS-115 aboard Space Shuttle Atlantis is scheduled in a window beginning Aug. 27. Photo credit: NASA/Cory Huston

KSC-05pd2547

NASA Image and Video Library

2005-12-01

KENNEDY SPACE CENTER, FLA. - In NASA Kennedy Space Center’s Payload Hazardous Servicing Facility, Boeing workers attach a crane to the top of the cover surrounding the third stage, or upper stage, for the New Horizons spacecraft. The third stage is a Boeing STAR 48 solid-propellant kick motor. The launch vehicle for New Horizons is the Atlas V rocket, scheduled to launch from Cape Canaveral Air Force Station, Fla., during a 35-day window that opens Jan. 11, and fly through the Pluto system as early as summer 2015.

KSC-05PD-1241

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the transfer aisle of the Vehicle Assembly Building, workers attach the 175-ton bridge crane to the orbiter Discovery, which is resting on an orbiter transporter. The crane will lift Discovery to vertical for the remate to a new External Tank, ET-121. The new tank and Solid Rocket Boosters are waiting in high bay 3. Discovery is expected roll back to the launch pad June 13 for Return to Flight mission STS-114. The launch window extends from July 13 to July 31.

KSC-05PD-1242

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the transfer aisle of the Vehicle Assembly Building, workers attach the 175-ton bridge crane to the orbiter Discovery, which is resting on an orbiter transporter. The crane will lift Discovery to vertical for the remate to a new External Tank, ET-121. The new tank and Solid Rocket Boosters are waiting in high bay 3. Discovery is expected roll back to the launch pad June 13 for Return to Flight mission STS-114. The launch window extends from July 13 to July 31.

KSC-05PD-1200

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In high bay 1 of the Vehicle Assembly Building at NASAs Kennedy Space Center, a crane is placed around the orbiter Discovery in preparation for lifting it into the transfer aisle. The orbiter is being demated from its External Tank (ET) and will be remated with another tank, ET-121. Discovery then is expected to be rolled back to the launch pad in mid-June for Return to Flight mission STS-114. The launch window extends from July 13 to July 31.

KSC-06pd2134

NASA Image and Video Library

2006-09-09

KENNEDY SPACE CENTER, FLA. - Inside the Launch Control Center, KSC officials turn from their computers to watch through the broad windows the launch of Space Shuttle Atlantis on mission STS-115. Second from left is NASA Test Director Pete Nickolenko. Mission STS-115 is the 116th space shuttle flight, the 27th flight for orbiter Atlantis, and the 19th U.S. flight to the International Space Station. sts-115 is scheduled to last 11 days with a planned landing at KSC. Photo credit: NASA/Kim Shiflett

KSC-05PD-0898

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Dozens of media are gathered at the slidewire basket landing area on Launch Pad 39B to interview and hear comments from the STS-114 crew: Mission Specialists Andrew Thomas, Wendy Lawrence and Stephen Robinson, Commander Eileen Collins, Mission Specialists Charles Camarda and Soichi Noguchi, and Pilot James Kelly. Noguchi is with the Japan Aerospace Exploration Agency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is designated the first Return to Flight mission, with a launch window extending from July 13 to July 31.

KSC-05PD-0900

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Dozens of media are gathered at the slidewire basket landing area on Launch Pad 39B to interview and hear comments from the STS-114 crew: Mission Specialists Andrew Thomas, Wendy Lawrence and Stephen Robinson, Commander Eileen Collins, Mission Specialists Charles Camarda and Soichi Noguchi, and Pilot James Kelly. Noguchi is with the Japan Aerospace Exploration Agency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is designated the first Return to Flight mission, with a launch window extending from July 13 to July 31.

KSC-05PD-0850

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Commander Eileen Collins gets ready to practice driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. Behind her is Capt. George Hoggard, who is astronaut rescue team leader. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-05PD-0849

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Mission Specialist Stephen Robinson (right) practices driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. At left is Capt. George Hoggard, who is astronaut rescue team leader. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-2011-7968

NASA Image and Video Library

2011-11-26

CAPE CANAVERAL, Fla. – At NASA Kennedy Space Center's Press Site in Florida, participants in NASA's Tweetup photograph the launch of the agency's Mars Science Laboratory (MSL) as the countdown clock ticks off the seconds. The tweeters will share their experiences with followers through the social networking site Twitter. The 197-foot-tall United Launch Alliance Atlas V rocket lifted off Space Launch Complex-41 on neighboring Cape Canaveral Air Force Station at 10:02 a.m. EST at the opening of the launch window. MSL's components include a car-sized rover, Curiosity, which has 10 science instruments designed to search for signs of life, including methane, and help determine if the gas is from a biological or geological source. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Frankie Martin

Titan 4B/Centaur/Cassini prelaunch at LC 40

NASA Technical Reports Server (NTRS)

1997-01-01

KENNEDY SPACE CENTER, FLA. -- At Launch Complex 40 on Cape Canaveral Air Station, the Mobile Service Tower has been retracted away from the Titan IVB/Centaur carrying the Cassini spacecraft, marking a major milestone in the launch countdown sequence. Retraction of the structure began about an hour later than scheduled due to minor problems with ground support equipment. The launch vehicle, Cassini spacecraft and attached Centaur stage encased in a payload fairing, altogether stand about 183 feet tall; mounted at the base of the launch vehicle are two upgraded solid rocket motors. Liftoff of Cassini on the journey to Saturn and its moon Titan is slated to occur during a window opening at 4:55 a.m. EDT, Oct. 13, and extending through 7:15 a.m.

APOLLO/SATURN (A/S) 201 - LAUNCH - CAPE

NASA Image and Video Library

1966-02-26

A/S 201 was launched from the Kennedy Space Center Launch Complex 34 at 11:12 a.m., 02/26/1966. The instrumented Apollo Command and Service Module, and, a spacecraft Lunar Excursion Module Adapter, was successfully launched on the unmanned suborbital mission by the Saturn 1B to check spacecraft launch vehicle mechanical compatibility and to test the spacecraft heat shield in a high-velocity re-entry mode. CAPE KENNEDY, FL

Realization of a compact polarization splitter-rotator on silicon.

PubMed

Dai, Daoxin; Wu, Hao

2016-05-15

A novel compact polarization splitter-rotator (PSR) is proposed and realized with silicon-on-insulator nanowires. The present PSR consists of an adiabatic taper, an asymmetric directional coupler (ADC), and a multimode interference (MMI) mode filter. The adiabatic taper enables an efficient mode conversion from the launched TM₀ mode to the TE₁ mode in a wide waveguide, which is then coupled to the TE₀ mode of a narrow waveguide through the ADC. Meanwhile, the launched TE₀ mode does not have mode conversion and outputs from the through port directly. The MMI mode filter is cascaded at the through port to filter out the residual power of the TE₁ mode so that the extinction ratio of the PSR is improved greatly. The total length of the PSR is ∼70  μm and the fabricated PSR has an extinction ratio of ∼20  dB over a broadband ranging from 1547 to 1597 nm.

Protection of Northern Chile as an ICOMOS/IAU ``Window to the Universe''

NASA Astrophysics Data System (ADS)

Smith, Malcolm G.

2015-03-01

Over the last two decades, La Serena's population has increased by about 70 percent. A site description of the AURA Observatory in Chile as a ``Window to the Universe`` is now available on the recently-launched UNESCO-IAU Astronomical Heritage Web Portal, www.astronomicalheritage.net This can serve as an example of possible material for the Chilean authorities, should they wish to propose the dark skies over much of northern Chile for protection as a World Scientific Heritage site. Some of the steps involved are discussed briefly here.

Launch window analysis in a new perspective with examples of departures from Earth to Mars

NASA Technical Reports Server (NTRS)

Thibodeau, J. R., III; Bond, V. R.

1972-01-01

Earth-departure windows are investigated for two round trip stopover missions to Mars. These are the 1981 inbound Venus swingby mission and the 1986 direct minimum-energy mission. The secular effects of planetary oblateness are used to predict the motion of the parking orbit. A procedure is developed for matching the motion of the parking orbit and the escape asymptote. Earth-departure velocity penalties, caused by orbital plane misalinement, are reduced by synchronizing the motion of the parking orbit and the escape trajectory.

Pre-launch Performance Assessment of the VIIRS Ice Surface Temperature Algorithm

NASA Astrophysics Data System (ADS)

Ip, J.; Hauss, B.

2008-12-01

The VIIRS Ice Surface Temperature (IST) environmental data product provides the surface temperature of sea-ice at VIIRS moderate resolution (750m) during both day and night. To predict the IST, the retrieval algorithm utilizes a split-window approach with Long-wave Infrared (LWIR) channels at 10.76 μm (M15) and 12.01 μm (M16) to correct for atmospheric water vapor. The split-window approach using these LWIR channels is AVHRR and MODIS heritage, where the MODIS formulation has a slightly modified functional form. The algorithm relies on the VIIRS Cloud Mask IP for identifying cloudy and ocean pixels, the VIIRS Ice Concentration IP for identifying ice pixels, and the VIIRS Aerosol Optical Thickness (AOT) IP for excluding pixels with AOT greater than 1.0. In this paper, we will report the pre-launch performance assessment of the IST retrieval. We have taken two separate approaches to perform this assessment, one based on global synthetic data and the other based on proxy data from Terra MODIS. Results of the split- window algorithm have been assessed by comparison either to synthetic "truth" or results of the MODIS retrieval. We will also show that the results of the assessment with proxy data are consistent with those obtained using the global synthetic data.

Particulates and noise exposure during bicycle, bus and car commuting: A study in three European cities.

PubMed

Okokon, Enembe O; Yli-Tuomi, Tarja; Turunen, Anu W; Taimisto, Pekka; Pennanen, Arto; Vouitsis, Ilias; Samaras, Zissis; Voogt, Marita; Keuken, Menno; Lanki, Timo

2017-04-01

In order to curb traffic-related air pollution and its impact on the physical environment, contemporary city commuters are encouraged to shift from private car use to active or public transport modes. However, personal exposures to particulate matter (PM), black carbon and noise during commuting may be substantial. Therefore, studies comparing exposures during recommended modes of transport versus car trips are needed. We measured personal exposure to various-sized particulates, soot, and noise during commuting by bicycle, bus and car in three European cities: Helsinki in Finland, Rotterdam in the Netherlands and Thessaloniki in Greece using portable monitoring devices. We monitored commonly travelled routes in these cities. The total number of one-way trips yielding data on any of the measured parameters were 84, 72, 94 and 69 for bicycle, bus, closed-window car and open-window car modes, respectively. The highest mean PM 2.5 (85µg/m 3 ), PM 10 (131µg/m 3 ), black carbon (10.9µg/m 3 ) and noise (75dBA) levels were recorded on the bus, bus (again), open-window car and bicycle modes, respectively, all in Thessaloniki, PM and soot concentrations were generally higher during biking and taking a bus than during a drive in a a car with closed windows. Ratios of bike:car PM 10 ranged from 1.1 in Thessaloniki to 2.6 in Helsinki, while bus:car ratios ranged from in 1.0 in Rotterdam to 5.6 in Thessaloniki. Higher noise levels were mostly recorded during bicycle rides. Based on our study, active- and public-transport commuters are often at risk of higher air pollution and noise exposure than private car users. This should be taken into account in urban transportation planning. Copyright © 2017 Elsevier Inc. All rights reserved.

Solar orbiter/PHI full disk telescope entrance window mechanical mount

NASA Astrophysics Data System (ADS)

Barandiaran, J.; Zuluaga, P.; Fernandez, A. B.; Vera, I.; Garranzo, D.; Nuñez, A.; Bastide, L.; Royo, M. T.; Alvarez, A.

2017-11-01

PHI is a diffraction limited, wavelength tunable, quasi-monochromatic, and polarization sensitive imager. These capabilities are needed to infer the magnetic field and line-of-sight (LOS) velocity of the region targeted by the spacecraft (spacecraft (S/C)). PHI will consist of two telescopes: The High Resolution Telescope (HRT)[1] and the Full Disk Telescope (FDT). The HRT and the FDT will view the Sun through entrance windows located in the S/C heat shield. These windows act as heat rejecting filters with a transmission band of about 30 nm width centered on the science wavelength, such that the total transmittance (integral over the filter curve weighted with solar spectrum, including white leakage plus transmission profile of the pass band) does not exceed 4% of the total energy falling onto the window [2][3]. The HREW filter has been designed by SELEX in the framework of an ESA led technology development activity under original ESTEC contract No. 20018/06/NL/CP[4], and extensions thereof. For FDT HREW SLEX will provide the windows and it coatings. The HREW consists of two parallel-plane substrate plates (window 1 & window 2)[5] made of SUPRASIL 300 with a central thickness of 9 mm and a wedge of 30 arcsec each. These two substrates are each coated on both sides with four different coatings. These coatings and the choice of SUPRASIL help to minimize the optical absorptivity in the substrate and to radiatively decouple the HREW, which is expected to run at high temperatures during perihelion passages, from the PHI instrument cavity. The temperature distribution of the HREW is driven by two main factors: the mechanical mounting of the substrates to the feedthrough, and the radiative environment within the heat-shield/feedthrough assembly. The mechanical mount must ensure the correct integration of both suprasil substrates in its correct position and minimize the loads in windows due to thermal induced deformations and launching vibration environment. All the subsystem must survive to a launching vibration environment and fulfill optical requirements in an environmental conditions according o its position in the external part of the spacecraft with a pressure of 0.0013Pa and a temperature -163°C

KSC-05PD-0620

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the waning twilight, the service structures on Launch Pad 39B (left) and the Mobile Launcher Platform carrying Space Shuttle Discovery glow with lights. The Shuttle began rollout to the pad at 2:04 p.m. EDT from the Vehicle Assembly Building at NASAs Kennedy Space Center, marking a major milestone in the Space Shuttle Programs Return to Flight. Launch of Discovery on its Return to Flight mission, STS-114, is targeted for May 15 with a launch window that extends to June 3. During its 12-day mission, Discoverys seven-person crew will test new hardware and techniques to improve Shuttle safety, as well as deliver supplies to the International Space Station.

KSC-98pc207

NASA Image and Video Library

1998-01-22

STS-89 Mission Specialist Bonnie Dunbar, Ph.D., smiles as she completes the donning of her launch/entry suit in the Operations and Checkout (O&C) Building. Dr. Dunbar completed her doctorate at the University of Houston in Texas. Her multi-disciplinary dissertation (materials science and physiology) involved evaluating the effects of simulated space flight on bone strength and fracture toughness. She and six fellow crew members will shortly depart the O&C and head for Launch Pad 39A, where the Space Shuttle Endeavour will lift off during a launch window that opens at 9:43 p.m. EST, Jan. 22. STS-89 is the eighth of nine planned missions to dock the Space Shuttle with Russia's Mir space station

KSC-2011-6208

NASA Image and Video Library

2011-08-04

CAPE CANAVERAL, Fla. -- NASA's Juno spacecraft, enclosed in its payload fairing atop a United Launch Alliance Atlas V-551 launch vehicle, is nestled between the towers of the lightning protection system at Space Launch Complex 41 on Cape Canaveral Air Force Station in Florida. In the background is the Vertical Integration Facility where the rocket was stacked. Launch is planned during a launch window which extends from 11:34 a.m. to 12:43 p.m. EDT on Aug. 5. The solar-powered spacecraft will orbit Jupiter's poles 33 times to find out more about the gas giant's origins, structure, atmosphere and magnetosphere and investigate the existence of a solid planetary core. NASA's Jet Propulsion Laboratory, Pasadena, Calif., manages the Juno mission for the principal investigator, Scott Bolton, of Southwest Research Institute in San Antonio. The Juno mission is part of the New Frontiers Program managed at NASA's Marshall Space Flight Center in Huntsville, Ala. Lockheed Martin Space Systems, Denver, built the spacecraft. Launch management for the mission is the responsibility of NASA's Launch Services Program at the Kennedy Space Center in Florida. For more information, visit www.nasa.gov/juno. Photo credit: NASA/Kim Shiflett

A Geometric Analysis to Protect Manned Assets from Newly Launched Objects - Cola Gap Analysis

NASA Technical Reports Server (NTRS)

Hametz, Mark E.; Beaver, Brian A.

2013-01-01

A safety risk was identified for the International Space Station (ISS) by The Aerospace Corporation, where the ISS would be unable to react to a conjunction with a newly launched object following the end of the launch Collision Avoidance (COLA) process. Once an object is launched, there is a finite period of time required to track, catalog, and evaluate that new object as part of standard onorbit COLA screening processes. Additionally, should a conjunction be identified, there is an additional period of time required to plan and execute a collision avoidance maneuver. While the computed prelaunch probability of collision with any object is extremely low, NASA/JSC has requested that all US launches take additional steps to protect the ISS during this "COLA gap" period. This paper details a geometric-based COLA gap analysis method developed by the NASA Launch Services Program to determine if launch window cutouts are required to mitigate this risk. Additionally, this paper presents the results of several missions where this process has been used operationally.

Opportunities to Enhance Multimode Fiber Links by Application of Overfilled Launch

NASA Astrophysics Data System (ADS)

Onlagic, Denis

2005-11-01

This paper investigates possibilities for the practical design of high-performance multimode fibers (MMFs) that can provide bandwidths in excess of 10 GHz ...km in an overfilled regime of operation. Analysis of standard MMF in an overfilled launch demonstrates that the theoretical bandwidth limitations arise from the influence of cladding on the propagation of the highest order modes. Practical MMF profile designs that overcome this problem are investigated. The standard 50-and 62.5- μm fiber profiles are redesigned first to allow for the performance in an overfilled launch with the differential mode delays (DMDs) below 0.055 and 0.250 ns/km, respectively. It is shown that such fibers can exhibit the same or better theoretical bandwidth in an overfilled launch when compared to standard fiber under restricted launch. Elimination of the need for the restricted mode launch in high-performance multimode transmission systems can improve reliability issues and can relax the range of tolerance requirements imposed on terminal equipment, optical components, and link installation. Furthermore, MMFs that can be operated in an overfilled launched are compatible with emerging vertical cavity surface emitting laser (VCSEL) wavelength division multiplexing (WDM) array technologies. A successfully controlled higher order mode DMD also allows for the reduction of MMF core size and mit Delta that can be beneficial for low-cost high-performance single-channel links. It is demonstrated that properly designed reduced core fibers can achieve theoretical DMDs in the range of 0.005-0.02 ns/km. The bend loss properties of redesigned fibers are investigated in detail, showing that the proposed modifications do not lead to significant degradation of bend loss performance. Moreover, they can be manufactured at considerably lower cost while utilizing commercially readily available low-cost VCSELs. Even where the theoretical limit is not achieved by practical fiber making, the reduced core size and mit Delta MMF can provide higher production yield, lower cost, and higher average bandwidth.

Generation of interior cavity noise due to window vibration excited by turbulent flows past a generic side-view mirror

NASA Astrophysics Data System (ADS)

Yao, Hua-Dong; Davidson, Lars

2018-03-01

We investigate the interior noise caused by turbulent flows past a generic side-view mirror. A rectangular glass window is placed downstream of the mirror. The window vibration is excited by the surface pressure fluctuations and emits the interior noise in a cuboid cavity. The turbulent flows are simulated using a compressible large eddy simulation method. The window vibration and interior noise are predicted with a finite element method. The wavenumber-frequency spectra of the surface pressure fluctuations are analyzed. The spectra are identified with some new features that cannot be explained by the Chase model for turbulent boundary layers. The spectra contain a minor hydrodynamic domain in addition to the hydrodynamic domain caused by the main convection of the turbulent boundary layer. The minor domain results from the local convection of the recirculating flow. These domains are formed in bent elliptic shapes. The spanwise expansion of the wake is found causing the bending. Based on the wavenumber-frequency relationships in the spectra, the surface pressure fluctuations are decomposed into hydrodynamic and acoustic components. The acoustic component is more efficient in the generation of the interior noise than the hydrodynamic component. However, the hydrodynamic component is still dominant at low frequencies below approximately 250 Hz since it has low transmission losses near the hydrodynamic critical frequency of the window. The structural modes of the window determine the low-frequency interior tonal noise. The combination of the mode shapes of the window and cavity greatly affects the magnitude distribution of the interior noise.

Using the full power of the cosmic microwave background to probe axion dark matter

NASA Astrophysics Data System (ADS)

Hložek, Renée; Marsh, David J. E.; Grin, Daniel

2018-05-01

The cosmic microwave background (CMB) places stringent constraints on models of dark matter (DM), and on the initial conditions of the Universe. The full Planck data set is used to test the possibility that some fraction of the DM is composed of ultralight axions (ULAs). This represents the first use of CMB lensing to test the ULA model. We find no evidence for a ULA component in the mass range 10-33 ≤ ma ≤ 10-24 eV. We put percent-level constraints on the ULA contribution to the DM, improving by up to a factor of two compared using temperature anisotropies alone. Axion DM also provides a low-energy window on to the physics of inflation through isocurvature perturbations. We perform the first systematic investigation into the parameter space of ULA isocurvature, using an accurate isocurvature transfer function at all ma values. We precisely identify a `window of co-existence' for 10-25 eV ≤ ma ≤ 10-24 eV where the data allow, simultaneously, a {˜ }10 {per cent} contribution of ULAs to the DM, and {˜ } 1 {per cent} contributions of isocurvature and tensor modes to the CMB power. ULAs in this window (and all lighter ULAs) are shown to be consistent with a large inflationary Hubble parameter, HI ˜ 1014 GeV. The window of co-existence will be fully probed by proposed CMB Stage-IV observations with increased accuracy in the high-ℓ lensing power and low-ℓ E- and B-mode polarizations. If ULAs in the window exist, this could allow for two independent measurements of HI in the CMB using isocurvature, and the tensor contribution to B modes.

A Noise Reduction Method for Dual-Mass Micro-Electromechanical Gyroscopes Based on Sample Entropy Empirical Mode Decomposition and Time-Frequency Peak Filtering

PubMed Central

Shen, Chong; Li, Jie; Zhang, Xiaoming; Shi, Yunbo; Tang, Jun; Cao, Huiliang; Liu, Jun

2016-01-01

The different noise components in a dual-mass micro-electromechanical system (MEMS) gyroscope structure is analyzed in this paper, including mechanical-thermal noise (MTN), electronic-thermal noise (ETN), flicker noise (FN) and Coriolis signal in-phase noise (IPN). The structure equivalent electronic model is established, and an improved white Gaussian noise reduction method for dual-mass MEMS gyroscopes is proposed which is based on sample entropy empirical mode decomposition (SEEMD) and time-frequency peak filtering (TFPF). There is a contradiction in TFPS, i.e., selecting a short window length may lead to good preservation of signal amplitude but bad random noise reduction, whereas selecting a long window length may lead to serious attenuation of the signal amplitude but effective random noise reduction. In order to achieve a good tradeoff between valid signal amplitude preservation and random noise reduction, SEEMD is adopted to improve TFPF. Firstly, the original signal is decomposed into intrinsic mode functions (IMFs) by EMD, and the SE of each IMF is calculated in order to classify the numerous IMFs into three different components; then short window TFPF is employed for low frequency component of IMFs, and long window TFPF is employed for high frequency component of IMFs, and the noise component of IMFs is wiped off directly; at last the final signal is obtained after reconstruction. Rotation experimental and temperature experimental are carried out to verify the proposed SEEMD-TFPF algorithm, the verification and comparison results show that the de-noising performance of SEEMD-TFPF is better than that achievable with the traditional wavelet, Kalman filter and fixed window length TFPF methods. PMID:27258276

A Noise Reduction Method for Dual-Mass Micro-Electromechanical Gyroscopes Based on Sample Entropy Empirical Mode Decomposition and Time-Frequency Peak Filtering.

PubMed

Shen, Chong; Li, Jie; Zhang, Xiaoming; Shi, Yunbo; Tang, Jun; Cao, Huiliang; Liu, Jun

2016-05-31

The different noise components in a dual-mass micro-electromechanical system (MEMS) gyroscope structure is analyzed in this paper, including mechanical-thermal noise (MTN), electronic-thermal noise (ETN), flicker noise (FN) and Coriolis signal in-phase noise (IPN). The structure equivalent electronic model is established, and an improved white Gaussian noise reduction method for dual-mass MEMS gyroscopes is proposed which is based on sample entropy empirical mode decomposition (SEEMD) and time-frequency peak filtering (TFPF). There is a contradiction in TFPS, i.e., selecting a short window length may lead to good preservation of signal amplitude but bad random noise reduction, whereas selecting a long window length may lead to serious attenuation of the signal amplitude but effective random noise reduction. In order to achieve a good tradeoff between valid signal amplitude preservation and random noise reduction, SEEMD is adopted to improve TFPF. Firstly, the original signal is decomposed into intrinsic mode functions (IMFs) by EMD, and the SE of each IMF is calculated in order to classify the numerous IMFs into three different components; then short window TFPF is employed for low frequency component of IMFs, and long window TFPF is employed for high frequency component of IMFs, and the noise component of IMFs is wiped off directly; at last the final signal is obtained after reconstruction. Rotation experimental and temperature experimental are carried out to verify the proposed SEEMD-TFPF algorithm, the verification and comparison results show that the de-noising performance of SEEMD-TFPF is better than that achievable with the traditional wavelet, Kalman filter and fixed window length TFPF methods.

Development of an expert planning system for OSSA

NASA Technical Reports Server (NTRS)

Groundwater, B.; Lembeck, M. F.; Sarsfield, L.; Diaz, Alphonso

1988-01-01

This paper presents concepts related to preliminary work for the development of an expert planning system for NASA's Office for Space Science and Applications (OSSA). The expert system will function as a planner's decision aid in preparing mission plans encompassing sets of proposed OSSA space science initiatives. These plans in turn will be checked against budgetary and technical constraints and tested for constraint violations. Appropriate advice will be generated by the system for making modifications to the plans to bring them in line with the constraints. The OSSA Planning Expert System (OPES) has been designed to function as an integral part of the OSSA mission planning process. It will be able to suggest a best plan, be able to accept and check a user-suggested strawman plan, and should provide a quick response to user request and actions. OPES will be written in the C programming language and have a transparent user interface running under Windows 386 on a Compaq 386/20 machine. The system's sorted knowledge and inference procedures will model the expertise of human planners familiar with the OSSA planning domain. Given mission priorities and budget guidelines, the system first sets the launch dates for each mission. It will check to make sure that planetary launch windows and precursor mission relationships are not violated. Additional levels of constraints will then be considered, checking such things as the availability of a suitable launch vehicle, total mission launch mass required vs. the identified launch mass capability, and the total power required by the payload at its destination vs. the actual power available. System output will be in the form of Gantt charts, spreadsheet hardcopy, and other presentation quality materials detailing the resulting OSSA mission plan.

Methodologies for Verification and Validation of Space Launch System (SLS) Structural Dynamic Models: Appendices

NASA Technical Reports Server (NTRS)

Coppolino, Robert N.

2018-01-01

Verification and validation (V&V) is a highly challenging undertaking for SLS structural dynamics models due to the magnitude and complexity of SLS subassemblies and subassemblies. Responses to challenges associated with V&V of Space Launch System (SLS) structural dynamics models are presented in Volume I of this paper. Four methodologies addressing specific requirements for V&V are discussed. (1) Residual Mode Augmentation (RMA). (2) Modified Guyan Reduction (MGR) and Harmonic Reduction (HR, introduced in 1976). (3) Mode Consolidation (MC). Finally, (4) Experimental Mode Verification (EMV). This document contains the appendices to Volume I.

Muon catalyzed fusion beam window mechanical strength testing and analysis

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

Ware, A.G.; Zabriskie, J.M.

A thin aluminum window (0.127 mm (0.005-inch) thick x 146 mm (5 3/4-inch) diameter) of 2024-T6 alloy was modeled and analyzed using the ABAQUS non-linear finite element analysis code. A group of windows was fabricated, heat-treated and subsequently tested. Testing included both ultimate burst pressure and fatigue. Fatigue testing cycles involved ''oil-canning'' behavior representing vacuum purge and reversal to pressure. Test results are compared to predictions and the mode of failure is discussed. Operational requirements, based on the above analysis and correlational testing, for the actual beam windows are discussed. 1 ref., 3 figs.

Documentation of debris impact damage to flight deck window

NASA Image and Video Library

1995-07-26

STS070-309-026 (13-22 JULY 1995) --- A close-up view of the space shuttle Discovery?s window number 6, on the forward starboard side, nearest the pilot?s station. A small impact in the window, about 1/16 inch in size, is clearly seen in the corner. Crew members told a August 11, 1995, gathering of Johnson Space Center (JSC) employees that a small piece of debris apparently struck the window during Discovery?s wing velocity vector mode. It was noticed when the astronauts awoke from their sleep period. Though watched closely during the remainder of the mission, the impact never caused a major concern.

KSC-05PD-0851

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Commander Eileen Collins takes her turn at driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. Standing behind her is Capt. George Hoggard, who is astronaut rescue team leader. On the left is KSC videographer Glen Benson. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-05PD-0853

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Mission Specialist Soichi Noguchi drives an M- 113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. Behind him at left is Capt. George Hoggard, who is astronaut rescue team leader. Noguchi is with the Japan Aerospace Exploration Agency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-97PC1542

NASA Image and Video Library

1997-10-14

At Launch Complex 40 on Cape Canaveral Air Station, the Mobile Service Tower has been retracted away from the Titan IVB/Centaur carrying the Cassini spacecraft and its attached Huygens probe. This is the second launch attempt for the Saturn-bound mission; a first try Oct. 13 was scrubbed primarily due to concerns about upper level wind conditions. Liftoff Oct. 15 is set to occur during a launch window opening at 4:43 a.m. EDT and extending until 7:03 a.m. Clearly visible in this view are the 66-foot-tall, 17-foot-wide payload fairing atop the vehicle, in which Cassini and the attached Centaur stage are encased, the two-stage liquid propellant core vehicle, and the twin 112-foot long solid rocket motor upgrades (SRMUs) straddling the core vehicle. It is the SRMUs which ignite first to begin the launch sequence

A panoramic view of the Space Station Processing Facility with Unity connecting module

NASA Technical Reports Server (NTRS)

1998-01-01

In this panoramic view of the Space Station Processing Facility (SSPF) can be seen (left to right) Unity connecting module, the Rack Insertion Device and the first Multi-Purpose Launch Module, the Leonardo. Windows at the right above Leonardo allow visitors on tour to watch the activities in the SSPF. The Unity, scheduled to be launched on STS-88 in December 1998, will be mated to the Russian-built Zarya control module which will already be in orbit. STS-88 will be the first Space Shuttle launch for the International Space Station. The Italian-built MPLM, scheduled to be launched on STS-100 on Dec. 2, 1999, will be carried in the payload bay of the Shuttle orbiter, and will provide storage and additional work space for up to two astronauts when docked to the International Space Station.

Ares I-X Launch Vehicle Modal Test Overview

NASA Technical Reports Server (NTRS)

Buehrle, Ralph D.; Bartolotta, Paul A.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Parks, Russell A.; Lazor, Daniel R.

2010-01-01

The first test flight of NASA's Ares I crew launch vehicle, called Ares I-X, is scheduled for launch in 2009. Ares IX will use a 4-segment reusable solid rocket booster from the Space Shuttle heritage with mass simulators for the 5th segment, upper stage, crew module and launch abort system. Flight test data will provide important information on ascent loads, vehicle control, separation, and first stage reentry dynamics. As part of hardware verification, a series of modal tests were designed to verify the dynamic finite element model (FEM) used in loads assessments and flight control evaluations. Based on flight control system studies, the critical modes were the first three free-free bending mode pairs. Since a test of the free-free vehicle is not practical within project constraints, modal tests for several configurations in the nominal integration flow were defined to calibrate the FEM. A traceability study by Aerospace Corporation was used to identify the critical modes for the tested configurations. Test configurations included two partial stacks and the full Ares I-X launch vehicle on the Mobile Launcher Platform. This paper provides an overview for companion papers in the Ares I-X Modal Test Session. The requirements flow down, pre-test analysis, constraints and overall test planning are described.

The Design and Realization of Radio Telescope Control Software in Windows XP System with VC++

NASA Astrophysics Data System (ADS)

Zhao, Rong-Bing; Aili, Yu; Zhang, Jin; Yu, Yun

2007-03-01

The main function of the radio telescope control software is to drive the radio telescope to track the target accurately. The design of radio telescope control software is based on Windows XP system with VC++. The functions of the software, communication mode and the user interface is introduced in this article.

STS-121: Discovery L-1 Countdown Status Briefing

NASA Technical Reports Server (NTRS)

2006-01-01

Bruce Buckingham, NASA Public Affairs, introduces Jeff Spaulding, NASA Test Director; Debbie Hahn, STS-121 Payload Manager; and Kathy Winters, Shuttle Weather Officer. Spaulding gives his opening statement on this one day prior to the launching of the Space Shuttle Discovery. He discusses the following topics: 1) Launch of the Space Shuttle Discovery; 2) Weather; 3) Load over of onboard reactants; 4) Hold time for liquid hydrogen; 5) Stowage of Mid-deck completion; 6) Check-out of onboard and ground network systems; 7) Launch windows; 8) Mission duration; 9) Extravehicular (EVA) plans; 10) Space Shuttle landing day; and 11) Scrub turn-around plans. Hahn presents and discusses a short video of the STS-121 payload flow. Kathy Winters gives her weather forecast for launch. She then presents a slide presentation on the following weather conditions for the Space Shuttle Discovery: 1) STS-121 Tanking Forecast; 2) Launch Forecast; 3) SRB Recovery; 4) CONUS Launch; 5) TAL Launch; 6) 24 Hour Delay; 7) CONUS 24 Hour; 8) TAL 24 Hour; 9) 48 Hour Launch; 10) CONUS 48 Hour; and 11) TAL 48 Hour. The briefing ends with a question and answer period from the media.

Power M-mode Doppler (PMD) for observing cerebral blood flow and tracking emboli.

PubMed

Moehring, Mark A; Spencer, Merrill P

2002-01-01

Difficulties in location of transcranial ultrasound (US) windows and blood flow in cerebral vessels, and unambiguous detection of microemboli, have limited expansion of transcranial Doppler US. We developed a new transcranial Doppler modality, power M-mode Doppler (PMD), for addressing these issues. A 2-MHz digital Doppler (Spencer Technologies TCD100M) having 33 sample gates placed with 2-mm spacing was configured to display Doppler signal power, colored red and blue for directionality, in an M-mode format. The spectrogram from a user-selected depth was displayed simultaneously. This system was then explored on healthy subjects and patients presenting with varying cerebrovascular pathology. PMD facilitated window location and alignment of the US beam to view blood flow from multiple vessels simultaneously, without sound or spectral clues. Microemboli appeared as characteristic sloping high-power tracks in the PMD image. Power M-mode Doppler is a new paradigm facilitating vessel location, diagnosis, monitoring and microembolus detection.

STS-75 Payload Commander Franklin R. Chang-Diaz suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-75 Payload Commander Franklin R. Chang-Diaz (center) chats with Johnson Space Center officials Olan Bertrand (left) and David Leestma (right) during suitup activities in the Operations and Checkout Building. Born in Costa Rica, Chang-Diaz joined NASA in 1980. He has already completed four spaceflights and logged more than 656 hours on-orbit. He and six fellow crew members will depart shortly for Launch Pad 39B, where the Space Shuttle Columbia awaits liftoff during a two-and-a-half-hour launch window opening at 3:18 p.m. EST.

STS-91 Commander Charles Precourt participates in CEIT

NASA Technical Reports Server (NTRS)

1998-01-01

STS-91 Commander Charles Precourt inspects the windows of the cockpit from inside of the orbiter Discovery during the Crew Equipment Interface Test, or CEIT, in KSC's Orbiter Processing Facility Bay 2. During CEIT, the crew have an opportunity to get a hands-on look at the payloads with which they'll be working on- orbit. The STS-91 crew are scheduled to launch aboard the Shuttle Discovery for the ninth and final docking with the Russian Space Station Mir from KSC's Launch Pad 39A on May 28 at 8:05 EDT.

KSC-97pc559

NASA Image and Video Library

1997-04-02

Yesterday, NASA decided to postpone for 24-hours the launch of Columbia on mission STS-83 due to a requirement to add additional thermal insulation to water coolant lines in the orbiter's payload bay. The water coolant lines are seen here winding their way around the window on the left. Managers determined that the lines, which cool various electronics on the orbiter, were not properly insulated and could possibly freeze during Columbia's 16-days in space. Columbia's launch is now set for 2:00 p.m. EST on Friday, April 4, 1997

New Window on the Universe.

ERIC Educational Resources Information Center

Reynolds, Ronald F.

1984-01-01

Describes the basic components of a space telescope that will be launched during a 1986 space shuttle mission. These components include a wide field/planetary camera, faint object spectroscope, high-resolution spectrograph, high-speed photometer, faint object camera, and fine guidance sensors. Data to be collected from these instruments are…

Two-dimensional numerical simulation of O-mode to Z-mode conversion in the ionosphere

NASA Astrophysics Data System (ADS)

Cannon, P. D.; Honary, F.; Borisov, N.

2016-03-01

Experiments in the illumination of the F region of the ionosphere via radio frequency waves polarized in the ordinary mode (O-mode) have revealed that the magnitude of artificial heating-induced effects depends strongly on the inclination angle of the pump beam, with a greater modification to the plasma observed when the heating beam is directed close to or along the magnetic zenith direction. Numerical simulations performed using a recently developed finite-difference time-domain (FDTD) code are used to investigate the contribution of the O-mode to Z-mode conversion process to this effect. The aspect angle dependence and angular size of the radio window for which conversion of an O-mode pump wave to the Z-mode occurs is simulated for a variety of plasma density profiles including 2-D linear gradients representative of large-scale plasma depletions, density-depleted plasma ducts, and periodic field-aligned irregularities. The angular shape of the conversion window is found to be strongly influenced by the background plasma profile. If the Z-mode wave is reflected, it can propagate back toward the O-mode reflection region leading to resonant enhancement of the electric field in this region. Simulation results presented in this paper demonstrate that this process can make a significant contribution to the magnitude of electron density depletion and temperature enhancement around the resonance height and contributes to a strong dependence of the magnitude of plasma perturbation with the direction of the pump wave.

Optimizing the performance of bandpass photon detectors for inverse photoemission: Transmission of alkaline earth fluoride window crystals

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

Thiede, Christian, E-mail: christian.thiede@uni-muenster.de; Schmidt, Anke B.; Donath, Markus

2015-08-15

Bandpass photon detectors are widely used in inverse photoemission in the isochromat mode at energies in the vacuum-ultraviolet spectral range. The energy bandpass of gas-filled counters is usually formed by the ionization threshold of the counting gas as high-pass filter and the transmission cutoff of an alkaline earth fluoride window as low-pass filter. The transmission characteristics of the window have, therefore, a crucial impact on the detector performance. We present transmission measurements in the vacuum-ultraviolet spectral range for alkaline earth fluoride window crystals in the vicinity of the transmission cutoff as a function of crystal purity, surface finish, surface contamination,more » temperature, and thickness. Our findings reveal that the transmission characteristics of the window crystal and, thus, the detector performance depend critically on these window parameters.« less

42GHz ECRH assisted Plasma Breakdown in tokamak SST-1

NASA Astrophysics Data System (ADS)

Shukla, B. K.; Pradhan, S.; Patel, Paresh; Babu, Rajan; Patel, Jatin; Patel, Harshida; Dhorajia, Pragnesh; Tanna, V.; Atrey, P. K.; Manchanda, R.; Gupta, Manoj; Joisa, Shankar; Gupta, C. N.; Danial, Raju; Singh, Prashant; Jha, R.; Bora, D.

2015-03-01

In SST-1, 42GHz ECRH system has been commissioned to carry out breakdown and heating experiments at 0.75T and 1.5T operating toroidal magnetic fields. The 42GHz ECRH system consists of high power microwave source Gyrotron capable to deliver 500kW microwave power for 500ms duration, approximately 20 meter long transmission line and a mirror based launcher. The ECRH power in fundamental O-mode & second harmonic X-mode is launched from low field side (radial port) of the tokamak. At 0.75T operation, approximately 300 kW ECH power is launched in second harmonic X-mode and successful ECRH assisted breakdown is achieved at low loop_voltage ~ 3V. The ECRH power is launched around 45ms prior to loop voltage. The hydrogen pressure in tokamak is maintained ~ 1×10-5mbar and the pre-ionized density is ~ 4×1012/cc. At 1.5T operating toroidal magnetic field, the ECH power is launched in fundamental O-mode. The ECH power at fundamental harmonic is varied from 100 kW to 250 kW and successful breakdown is achieved in all ECRH shots. In fundamental harmonic there is no delay in breakdown while at second harmonic ~ 40ms delay is observed, which is normal in case of second harmonic ECRH assisted breakdown.

Multirail electromagnetic launcher powered from a pulsed magnetohydrodynamic generator

NASA Astrophysics Data System (ADS)

Afonin, A. G.; Butov, V. G.; Panchenko, V. P.; Sinyaev, S. V.; Solonenko, V. A.; Shvetsov, G. A.; Yakushev, A. A.

2015-09-01

The operation of an electromagnetic multirail launcher of solids powered from a pulsed magnetohydrodynamic (MHD) generator is studied. The plasma flow in the channel of the pulsed MHD generator and the possibility of launching solids in a rapid-fire mode of launcher operation are considered. It is shown that this mode of launcher operation can be implemented by matching the plasma flow dynamics in the channel of the pulsed MHD generator and the launching conditions. It is also shown that powerful pulsed MHD generators can be used as a source of electrical energy for rapid-fire electromagnetic rail launchers operating in a burst mode.

KSC-2013-1384

NASA Image and Video Library

2013-02-08

VANDENBERG AIR FORCE BASE, Calif. -- Media attend a prelaunch press conference at Vandenberg Air Force Base in California to discuss NASA's readiness to launch the Landsat Data Continuity Mission LDCM. From left are George Diller of NASA Public Affairs, LDCM program executive David Jarrett from NASA Headquarters, NASA Launch Director Omar Baez from Kennedy Space Center, United Launch Alliance Program Manager for NASA Missions Vernon Thorp, LDCM Project Manager Ken Schwer from Goddard Space Flight Center, and 1st Lt. Jennifer Kelley, launch weather officer for the 30th Operations Support Squadron at Vandenberg. Launch of LDCM aboard a United Launch Alliance Atlas V rocket from Vandenberg's Space Launch Complex-3E is planned for Feb. 11 during a 48-minute launch window that opens at 10:02 a.m. PST, or 1:02 p.m. EST. LDCM is the eighth satellite in the Landsat Program series of Earth-observing missions and will continue the program’s critical role in monitoring, understanding and managing the resources needed for human sustainment, such as food, water and forests. NASA's Goddard Space Flight Center in Greenbelt, Md., is responsible for LDCM project management. Orbital Sciences Corp. built the LDCM satellite. NASA's Launch Services Program at the Kennedy Space Center in Florida provides launch management. After launch and the initial checkout phase, the U. S. Geological Survey will take operational control of LDCM, and it will be renamed Landsat 8. Photo credit: NASA/Kim Shiflett

STS-78 Mission Specialist Charles E. Brady suits up

NASA Technical Reports Server (NTRS)

1996-01-01

STS-78 Mission Specialist Charles E. Brady Jr. is donning his launch/entry suit in the Operations and Checkout Building. A spaceflight rookie, Brady was selected by NASA to join the astronaut corps in March 1992; he is a medical doctor who also is a commander in the U.S. Navy. Along with six fellow crew members, he will depart the O&C in a short while and head for Launch Pad 39B, where the Space Shuttle Columbia awaits liftoff during a two-and-a-half hour launch window opening at 10:49 a.m. EDT, June 20. STS-78 will be an extended duration flight during which extensive research will be conducted in the Life and Microgravity Spacelab (LMS) located in the payload bay.

KSC-05PD-1072

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Payload Hazardous Servicing Facility, technicians inspect the solar panels for the Mars Reconnaissance Orbiter (MRO) during an electromagnetic interference verification test. If no interference is found during the test, the Shallow Radar Antenna (SHARAD) will be installed on the spacecraft. The spacecraft is undergoing multiple mechanical assembly operations and electrical tests to verify its readiness for launch. The MRO was built by Lockheed Martin for NASAs Jet Propulsion Laboratory in California. It is the next major step in Mars exploration and scheduled for launch from Launch Complex 41 at Cape Canaveral Air Force Station in a window opening Aug. 10. The MRO is an important next step in fulfilling NASAs vision of space exploration and ultimately sending human explorers to Mars and beyond.

KSC-05PD-0633

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Space Shuttle Discovery lingers at the foot of Launch Pad 39B in the evening twilight. First motion from the Vehicle Assembly Building was at 2:04 p.m. EDT April 6, and the Shuttle was hard down on the pad at 1:16 a.m. EDT April 7. The Shuttle sits atop a Mobile Launcher Platform transported by a Crawler-Transporter underneath. Launch of Discovery on its Return to Flight mission, STS-114, is targeted for May 15 with a launch window that extends to June 3. During its 12-day mission, Discoverys seven-member crew will test new hardware and techniques to improve Shuttle safety, as well as deliver supplies to the International Space Station. Photo courtesy of Scott Andrews.

Discovery with RSS retracted

NASA Technical Reports Server (NTRS)

1997-01-01

The Rotating Service Structure has been retracted at Pad 39A. Discovery, the Space Shuttle for STS-82 Mission is ready for the launch of the second Hubble Space Telescope service mission. The payload consists of the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) Which will be installed, the Fine Guidance Sensor #1 (FGS-1) and the Space Telescope Imaging Spectrograph (STIS) which will be installed. STS-82 will launch with a crew of seven at 3:54 a.m. February 11, 1997. The launch window is 65 minutes. The Mission Commander for STS-82 is Ken Bowersox. The purpose of the mission is to upgrade the scientific capabilities, service or replace aging components on the Telescope and provide a reboost to the optimum altitude.

STS-89 M.S. Andrew Thomas suits up

NASA Technical Reports Server (NTRS)

1998-01-01

STS-89 Mission Specialist Andrew Thomas, Ph.D., gives a 'thumbs up' as he completes the donning of his launch/entry suit in the Operations and Checkout (O&C) Building. In June 1995, he was named as payload commander for STS-77 and flew his first flight in space on Endeavour in May 1996. He and six fellow crew members will soon depart the O&C and head for Launch Pad 39A, where the Space Shuttle Endeavour will lift off during a launch window that opens at 9:43 p.m. EST, Jan. 22. STS-89 is the eighth of nine planned missions to dock the Space Shuttle with Russia's Mir space station, where Dr. Thomas will succeed David Wolf, M.D.

KSC-2011-7937

NASA Image and Video Library

2011-11-25

CAPE CANAVERAL, Fla. – Rex Engelhardt, mission manager in NASA's Launch Services Program at the NASA Kennedy Space Center, speaks to a group of Tweetup participants at Kennedy's Press Site in Florida during prelaunch activities for the agency’s Mars Science Laboratory (MSL) launch. Following a series of briefings, participants will tour the center and get a close-up view of Space Launch Complex-41 on Cape Canaveral Air Force Station. The tweeters will share their experiences with followers through the social networking site Twitter. MSL's components include a car-sized rover, Curiosity, which has 10 science instruments designed to search for signs of life, including methane, and help determine if the gas is from a biological or geological source. Liftoff of MSL aboard a United Launch Alliance Atlas V rocket from pad 41 is planned during a launch window which extends from 10:02 a.m. to 11:45 a.m. EST on Nov. 26. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Jim Grossmann

KSC-05PD-1055

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. Space Shuttle launch director Michael Leinbach (right) and assistant launch director Doug Lyons support an External Tank (ET) tanking test at Launch Pad 39B from the Launch Control Center. The tanking test is designed to evaluate how the tank, orbiter, solid rocket boosters and ground systems perform under 'cryo-load,' when the tank is filled with the two ultra-low-temperature propellants. The tank filling and draining portion of the test takes about 11 hours. The test also includes a simulated countdown through the hold at T-31 seconds. The test is being conducted to troubleshoot two issues identified by a tanking test held on April 14. Data is being collected to analyze the liquid hydrogen sensors that gave intermittent readings and the liquid hydrogen pressurization relief valve that cycled more times than standard. The tanking tests are part of preparations for Space Shuttle Discovery's Return to Flight mission, STS-114, to the International Space Station. The launch window extends from July 13 through July 31.

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-2014-4400

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-2014-4399

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-98pc1792

NASA Image and Video Library

1998-12-04

KENNEDY SPACE CENTER, Fla. -- As the Space Shuttle Endeavour lifts off from Launch Pad 39A on Mission STS-88, several fish believed to be mullet (at center left) "launch" themselves out of the water from one of the waterways around the pad. Liftoff of the first U.S. mission dedicated to the assembly of the International Space Station was at 3:35:34 a.m. EST on Dec. 4. During the nearly 12-day mission, the six-member crew will mate in space the first two elements of the International Space Station the already-orbiting Zarya control module with the Unity connecting module carried by Endeavour. Crew members are Commander Robert D. Cabana, Pilot Frederick W. "Rick" Sturckow, and Mission Specialists Nancy J. Currie, Jerry L. Ross, James H. Newman and Sergei Konstantinovich Krikalev, a Russian cosmonaut. This was the second launch attempt for STS-88. The first one on Dec. 3 was scrubbed when launch controllers, following an assessment of a suspect hydraulic system, were unable to resume the countdown clock in time to launch within the remaining launch window

Particle penetration into the automotive interior. I. Influence of vehicle speed and ventilatory mode.

PubMed

Muilenberg, M L; Skellenger, W S; Burge, H A; Solomon, W R

1991-02-01

Penetration of particulate aeroallergens into the interiors of two, new, similar Chrysler Corporation passenger vehicles (having no evidence of intrinsic microbial contamination) was studied on a large circular test track during periods of high pollen and spore prevalence. Impactor collections were obtained at front and rear seat points and at the track center during periods with (1) windows and vents closed and air conditioning on, (2) windows closed, vents open, and no air conditioning, and (3) air conditioner off, front windows open, and vents closed. These conditions were examined sequentially during travel at 40, 50, 60, and 80 kph. Particle recoveries within the two, new, similar Chrysler Corporation passenger vehicles did not vary with the speed of travel, either overall or with regard to each of the three ventilatory modalities. In addition, collections at front and rear seat sampling points were comparable. Highest interior aeroallergen levels were recorded with WO, and yet, these levels averaged only half the concurrent outside concentrations at track center. Recoveries within the cars were well below recoveries obtained outside when windows were closed (both VO and AC modes). These findings suggest window ventilation as an overriding factor determining particle ingress into moving vehicles. Efforts to delineate additional determinants of exposure by direct sampling are feasible and would appear essential in formulating realistic strategies of avoidance.

Polishing techniques for MEGARA pupil elements optics

NASA Astrophysics Data System (ADS)

Izazaga, R.; Carrasco, E.; Aguirre, D.; Salas, A.; Gil de Paz, A.; Gallego, J.; Iglesias, J.; Arroyo, J. M.; Hernández, M.; López, N.; López, V.; Quechol, J. T.; Salazar, M. F.; Carballo, C.; Cruz, E.; Arriaga, J.; De la Luz, J. A.; Huepa, A.; Jaimes, G. L.; Reyes, J.

2016-07-01

MEGARA (Multi-Espectrógrafo en GTC de Alta Resolución para Astronomía) is the new integral-field and multi-object optical spectrograph for the 10.4m Gran Telescopio Canarias.. It will offer RFWHM 6,000, 12,000 and 18,700 for the low- , mid- and high-resolution, respectively in the wavelength range 3650-9700Å. .The dispersive elements are volume phase holographic (VPH) gratings, sandwiched between two flat Fused Silica windows of high optical precision in large apertures. The design, based in VPHs in combination with Ohara PBM2Y prisms allows to keep the collimator and camera angle fixed. Seventy three optical elements are being built in Mexico at INAOE and CIO. For the low resolution modes, the VPHs windows specifications in irregularity is 1 fringe in 210mm x 170mm and 0.5 fringe in 190mm x 160mm. for a window thickness of 25 mm. For the medium and high resolution modes the irregularity specification is 2 fringes in 220mm x 180mm and 1 fringe in 205mm x 160mm, for a window thickness of 20mm. In this work we present a description of the polishing techniques developed at INAOE optical workshop to fabricate the 36 Fused Silica windows and 24 PBM2Y prisms that allows us to achieve such demanding specifications. We include the processes of mounting, cutting, blocking, polishing and testing.

Pre-Launch Performance Assessment of the VIIRS Land Surface Temperature Environmental Data Record

NASA Astrophysics Data System (ADS)

Hauss, B.; Ip, J.; Agravante, H.

2009-12-01

The Visible/Infrared Imager Radiometer Suite (VIIRS) Land Surface Temperature (LST) Environmental Data Record (EDR) provides the surface temperature of land surface including coastal and inland-water pixels at VIIRS moderate resolution (750m) during both day and night. To predict the LST under optimal conditions, the retrieval algorithm utilizes a dual split-window approach with both Short-wave Infrared (SWIR) channels at 3.70 µm (M12) and 4.05 µm (M13), and Long-wave Infrared (LWIR) channels at 10.76 µm (M15) and 12.01 µm (M16) to correct for atmospheric water vapor. Under less optimal conditions, the algorithm uses a fallback split-window approach with M15 and M16 channels. By comparison, the MODIS generalized split-window algorithm only uses the LWIR bands in the retrieval of surface temperature because of the concern for both solar contamination and large emissivity variations in the SWIR bands. In this paper, we assess whether these concerns are real and whether there is an impact on the precision and accuracy of the LST retrieval. The algorithm relies on the VIIRS Cloud Mask IP for identifying cloudy and ocean pixels, the VIIRS Surface Type EDR for identifying the IGBP land cover type for the pixels, and the VIIRS Aerosol Optical Thickness (AOT) IP for excluding pixels with AOT greater than 1.0. In this paper, we will report the pre-launch performance assessment of the LST EDR based on global synthetic data and proxy data from Terra MODIS. Results of both the split-window and dual split-window algorithms will be assessed by comparison either to synthetic "truth" or results of the MODIS retrieval. We will also show that the results of the assessment with proxy data are consistent with those obtained using the global synthetic data.

KSC-07pd0420

NASA Image and Video Library

2007-02-16

KENNEDY SPACE CENTER, FLA. -- At Cape Canaveral Air Force Station, the Delta II rocket with the THEMIS spacecraft atop awaits launch on Pad 17-B. Friday's launch attempt was scrubbed due to upper-level wind violation. The launch window is 6:01 p.m. to 6:19 p.m. EST on Saturday. THEMIS, an acronym for Time History of Events and Macroscale Interactions during Substorms, consists of five identical probes that will track violent, colorful eruptions near the North Pole. This will be the largest number of scientific satellites NASA has ever launched into orbit aboard a single rocket. The THEMIS mission aims to unravel the mystery behind auroral substorms, an avalanche of magnetic energy powered by the solar wind that intensifies the northern and southern lights. The mission will investigate what causes auroras in the Earth’s atmosphere to dramatically change from slowly shimmering waves of light to wildly shifting streaks of bright color. Photo credit: NASA/Kim Shiflett

KSC-05PD-0847

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Mission Specialist Charles Camarda is getting ready to practice driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. Behind him are Mission Specialist Stephen Robinson and Capt. George Hoggard, who is astronaut rescue team leader, and, at right, Commander Eileen Collins. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-05PD-0852

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, STS-114 Mission Specialist Soichi Noguchi is ready to practice driving an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. Behind him at left is Capt. George Hoggard, who is astronaut rescue team leader. Noguchi is with the Japan Aerospace Exploration Agency.The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

Cassini Orbiter and Huygens Probe aboard the Titan IV

NASA Technical Reports Server (NTRS)

1997-01-01

At Launch Complex 40 on Cape Canaveral Air Station, the Mobile Service Tower has been retracted away from the Titan IVB/Centaur carrying the Cassini spacecraft, marking a major milestone in the launch countdown sequence. Retraction of the structure began about an hour later than scheduled due to minor problems with ground support equipment. The launch vehicle, Cassini spacecraft and attached Centaur stage encased in a payload fairing, altogether stand about 183 feet tall; mounted at the base of the launch vehicle are two upgraded solid rocket motors. Liftoff of Cassini on the journey to Saturn and its moon Titan is slated to occur during a window opening at 4:55 a.m. EDT, Oct. 13, and extending through 7:15 a.m.

The Jet Propulsion Laboratory manages the U.S. contribution to the Cassini mission for NASA's Office of Space Science.

KSC-98pc641

NASA Image and Video Library

1998-05-26

Technicians supervise the closure of Discovery's payload bay doors from the Payload Changout Room at Launch Pad 39A as preparations for the STS-91 launch continue. STS-91 is scheduled to be launched on June 2 with a launch window opening around 6:10 p.m. EDT. The mission will feature the ninth Shuttle docking with the Russian Space Station Mir, the first Mir docking for Discovery, the conclusion of Phase I of the joint U.S.-Russian International Space Station Program, and the first flight of the new Space Shuttle super lightweight external tank. The STS-91 flight crew includes Commander Charles Precourt; Pilot Dominic Gorie; and Mission Specialists Wendy B. Lawrence; Franklin Chang-Diaz, Ph.D.; Janet Kavandi, Ph.D.; and Valery Ryumin, with the Russian Space Agency. Andrew Thomas, Ph.D., will be returning to Earth with the crew after living more than four months aboard Mir

KSC-98pc640

NASA Image and Video Library

1998-05-26

Technicians supervise the closure of Discovery's payload bay doors from the Payload Changout Room at Launch Pad 39A as preparations for the STS-91 launch continue. STS-91 is scheduled to be launched on June 2 with a launch window opening around 6:10 p.m. EDT. The mission will feature the ninth Shuttle docking with the Russian Space Station Mir, the first Mir docking for Discovery, the conclusion of Phase I of the joint U.S.-Russian International Space Station Program, and the first flight of the new Space Shuttle super lightweight external tank. The STS-91 flight crew includes Commander Charles Precourt; Pilot Dominic Gorie; and Mission Specialists Wendy B. Lawrence; Franklin Chang-Diaz, Ph.D.; Janet Kavandi, Ph.D.; and Valery Ryumin, with the Russian Space Agency. Andrew Thomas, Ph.D., will be returning to Earth with the crew after living more than four months aboard Mir

Wall-ablative laser-driven in-tube accelerator

NASA Astrophysics Data System (ADS)

Sasoh, Akihiro; Suzuki, Shingo; Matsuda, Atsushi

2008-05-01

The laser-driven in-tube accelerator in which the propellant is supplied from laser-ablated gas from the tube wall was developed. Proof-of concept demonstrations of vertical launch were successfully done. The device had a 25mm X 25mm square cross-section; two opposing walls were made of polyacetal and acted as the propellant, the other two acrylic window with guide grooves to the projectile. The upper end of the launch tube was connected to a vacuum chamber of an inner volume of 0.8 m2, in which the initial pressure was set to lower than 20 Pa. With plugging the bottom end of the launch tube, a momentum coupling coefficient exceeding 2.5 mN/W was obtained. Even with the bottom end connected to the same vacuum chamber through a different duct, the projectile was vertical launched successfully, obtaining 0.14 mN/W.

KSC-05PD-0554

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At the Cape Canaveral Air Force Station Skid Strip, workers inside a Russian Antonov AH-124-100 cargo airplane roll out the booster segment for a Lockheed Martin Atlas V. The Atlas V, designated AV-007, is the launch vehicle for the Mars Reconnaissance Orbiter (MRO). The MRO is designed for a series of global mapping, regional survey and targeted observations from a near-polar, low-altitude Mars orbit. These observations will be unprecedented in terms of the spatial resolution and coverage achieved by the orbiters instruments as they observe the atmosphere and surface of Mars while probing its shallow subsurface as part of a follow the water strategy. The orbiter is undergoing environmental tests in facilities at Lockheed Martin Space Systems in Denver, Colo., and is on schedule for a launch window that begins Aug. 10. Launch will be from Launch Pad 41 at Cape Canaveral Air Force Station in Florida.

KSC-2013-4065

NASA Image and Video Library

2013-11-18

CAPE CANAVERAL, Fla. -- Dr. Jim Green, director of the Planetary Science Division at NASA Headquarters, participates in a post-launch news conference in NASA's Press Site TV auditorium following the successful launch of NASA’s Mars Atmosphere and Volatile EvolutioN, or MAVEN, spacecraft. Launch was on schedule at 1:28 p.m. EST Nov. 18 at the opening of a two-hour launch window. After a 10-month journey to the Red Planet, MAVEN will study its upper atmosphere in unprecedented detail from orbit above the planet. Built by Lockheed Martin in Littleton, Colo., MAVEN will arrive at Mars in September 2014 and will be inserted into an elliptical orbit with a high point of 3,900 miles, swooping down to as close as 93 miles above the planet's surface. For more information, visit: http://www.nasa.gov/mission_pages/maven/main/index.html. Photo credit: NASA/Kim Shiflett

Power Grab

ERIC Educational Resources Information Center

Jacobs, Paula

2009-01-01

Peter Pistorino says there is a name for the way he thinks a school district should launch an energy conservation initiative: an "envelope" approach. The term refers to looking at the outside package of a structure to check for inefficiencies: Examine the observable, external sources of energy loss such as the doors, windows, insulation,…

Independence and Choice: Western Impacts on Japanese Higher Education.

ERIC Educational Resources Information Center

Nakayama, Shigeru

1989-01-01

A brief history of the Japanese higher education system chronicles its two principal phases since the mid-nineteenth century. In the first, "window-shopping" mode, many Western models were explored and some partially adopted. In the "involvement" mode, specific Western models were adopted. The uniqueness of the Japanese…

Response measurements for two building structures excited by noise from a large horizontal axis wind turbine generator

NASA Technical Reports Server (NTRS)

Hubbard, H. H.; Shepherd, K. P.

1984-01-01

Window and wall acceleration measurements and interior noise measurements ere made for two different building structures during excitation by noise from the WTS-4 horizontal axis wind turbine generator operating in a normal power generation mode. With turbine noise input pulses resulted in acceleration pulses for the wall and window elements of the two tests buildings. Response spectra suggest that natural vibration modes of the structures are excited. Responses of a house trailer were substantially greater than those for a building of sturdier construction. Peak acceleration values correlate well with similar data for houses excited by flyover noise from commercial and military airplanes and helicopters, and sonic booms from supersonic aircraft. Interior noise spectra have peaks at frequencies corresponding to structural vibration modes and room standing waves; and the levels for particular frequencies and locations can be higher than the outside levels.

Broad bandwidth and 600 μm length photonic crystal fiber polarization filter at the communication window of 1.55 μm

NASA Astrophysics Data System (ADS)

Zhang, Zhen; Li, Shuguang; Liu, Qiang; Zhang, Shuhuan; Wang, Yujun; Wu, Junjun

2018-02-01

A broad bandwidth and 600-μm length photonic crystal fiber polarization filter at the communication window of 1.55 μm is proposed. The physical parameters are analyzed by the finite element method. In the structure, the loss is 705.81 dB/cm for y-polarized mode and 24.06 dB/cm for x-polarized mode at the wavelength of 1.55 μm; the y-polarized mode will be filtered out because of this property. The bandwidth of an extinction ratio (ER) better than -20 dB is 65 nm when the filter length is 600 μm, and the ER is -41 dB at the communication wavelength of 1.55 μm. The filter structure is simple and easy to produce, and it can be used to produce a single-polarization filter.

Ram accelerator direct space launch system - New concepts

NASA Technical Reports Server (NTRS)

Bogdanoff, David W.

1992-01-01

The ram accelerator, a chemically driven ramjet-in-tube device is a new option for direct launch of acceleration-insensitive payloads into earth orbit. The projectile is the centerbody of a ramjet and travels through a tube filled with a premixed fuel-oxidizer mixture. The tube acts as the cowl of the ramjet. A number of new concepts for a ram accelerator space launch system are presented. The velocity and acceleration capabilities of a number of ram accelerator drive modes, including several new modes, are given. Passive (fin) stabilization during atmospheric transit is investigated and found to be promising. Gasdynamic heating in-tube and during atmospheric transit is studied; the former is found to be severe, but may be alleviated by the selection of the most suitable drive modes, transpiration cooling, or a hydrogen gas core in the launch tube. To place the payload in earth orbit, scenarios using one impulse and three impulses (with an aeropass) and a new scenario involving an auxiliary vehicle are studied. The auxiliary vehicle scenario is found to be competitive regarding payload, and requires a much simpler projectile, but has the disadvantage of requiring the auxiliary vehicle.

Tailoring polarization of electromagnetically induced transparency based on non-centrosymmetric metasurfaces

NASA Astrophysics Data System (ADS)

Li, Hai-ming; Xue, Feng

2017-09-01

In this manuscript, tailoring polarization of analogy of electromagnetically induced transparency (EIT-like) based on non-centrosymmetric metasurfaces has been numerically and experimentally demonstrated. The EIT-like metamaterial is composed of a rectangle ring and two cut wires. The rectangle ring and the cut wire are chosen as the bright mode and the quasi-dark mode, respectively. Under the incident electromagnetic wave excitation, a polarization insensitive EIT-like transmission window can be observed at specific polarization angles. Within the transmission window, the phase steeply changes, which leads to the large group index. Tailoring polarization of EIT-like metamaterial with large group index at specific polarization angles may have potential application in slow light devices.

Solar power satellite system definition study. Part 2, volume 8: SPS launch vehicle ascent and entry sonic overpressure and noise effects

NASA Technical Reports Server (NTRS)

1977-01-01

Recoverable launch vehicle concepts for the Solar Power Satellite program were identified. These large launch vehicles are powered by proposed engines in the F-1 thrust level class. A description of the candidate launch vehicles and their operating mode was provided. Predictions of the sonic over pressures during ascent and entry for both types of vehicles, and prediction of launch noise levels in the vicinity of the launch site were included. An overall assessment and criteria for sonic overpressure and noise levels was examined.

Lockheed Martin Response to the OSP Challenge

NASA Technical Reports Server (NTRS)

Sullivan, Robert T.; Munkres, Randy; Megna, Thomas D.; Beckham, Joanne

2003-01-01

The Lockheed Martin Orbital Space Plane System provides crew transfer and rescue for the International Space Station more safely and affordably than current human space transportation systems. Through planned upgrades and spiral development, it is also capable of satisfying the Nation's evolving space transportation requirements and enabling the national vision for human space flight. The OSP System, formulated through rigorous requirements definition and decomposition, consists of spacecraft and launch vehicle flight elements, ground processing facilities and existing transportation, launch complex, range, mission control, weather, navigation, communication and tracking infrastructure. The concept of operations, including procurement, mission planning, launch preparation, launch and mission operations and vehicle maintenance, repair and turnaround, is structured to maximize flexibility and mission availability and minimize program life cycle cost. The approach to human rating and crew safety utilizes simplicity, performance margin, redundancy, abort modes and escape modes to mitigate credible hazards that cannot be designed out of the system.

IN2 Profile: Polyceed Electrochromic Window Technology Expected to Lower Energy Costs

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

Tenent, Rob; Achour, Maha

Through the Wells Fargo Innovation Incubator (IN²) program, Polyceed will validate their electrochromic window technology. The technology is expected to provide customers with 75% lower cost than conventional dynamic windows and offer small residences $200 a year of cost savings for energy consumption. The IN² program launched in October 2014 and is part of Wells Fargo’s 2020 Environmental Commitment to provide $100 million to environmentally-focused nonprofits and universities. The goal is to create an ecosystem that fosters and accelerates the commercialization of promising commercial buildings technologies that can provide scalable solutions to reduce the energy impact of buildings. According tomore » the Department of Energy, nearly 40 percent of energy consumption in the U.S. today comes from buildings at an estimated cost of $413 billion.« less

Printing of structures less than 0,3 μm by i-line exposure using resists TDMR-AR80 and TDMR-AR95

NASA Astrophysics Data System (ADS)

Behrendt, A.; Dow, T.; Stoeflin, K.

2007-03-01

There is increasing interest in high resolution i-line resists which allow the printing of structures smaller than 0.3μm. We have evaluated the resists TDMR-AR80 und TDMR-AR95 from TOK Company in order to check their potential concerning minimum line sizes with sufficient process window in regard to focus/exposure process latitude, with our main focus on trench structures. The Bossung Plots of dense lines and semi-dense lines were determined. The resist and etch profiles were characterised both by inline-SEM measurements and cross-sections. The influence of several stepper illumination modes and Off Axis Illumination (OAI) on the focus/exposure process window was investigated. The resists TDMR-AR80 and TDMR-AR95 enable printing of trench structures less than 0.3μm. For 0.3μm lines, our specification limit of 0.3μm +/- 10% was reached within a focus range from - 0.1 to 1.0 microns. OAI illumination mode enlarged the focus window by 20% in comparison to the standard illumination mode. Structures of 0.28μm and 0.26μm were printed with a focus window of 0.7μm which shows the high potential of this resist generation. The implementation of the resist in production provides large amounts of data which enable the calculation of parameters related to process stability (wafer to wafer and lot to lot CD-standard deviation, Cp-, Cpk-values etc.).

Evaluation of Window Failure Modes

DTIC Science & Technology

1999-12-01

U.S. Coast Guard Research and Development Center 1082 Shennecossett Road, Groton, CT 06340-6096 Report No. CG-D-08-00 EVALUATION OF WINDOW FAILURE...States Coast Guard Research & Development Center 1082 Shennecossett Road Groton, CT 06340-6096 11 I.Report No. CG-D-08-00 Technical Report...Development Center 1082 Shennecossett Road Groton,CT 06340-6096 12. Sponsoring Organization Name and Address U.S. Department of Transportation United

A procedure obtaining stiffnesses and masses of a structure from vibration modes and substructure static test data

NASA Technical Reports Server (NTRS)

Edighoffer, H. H.

1979-01-01

A component mode desynthesis procedure is developed for determining the unknown vibration characteristics of a structural component (i.e., a launch vehicle) given the vibration characteristics of a structural system composed of that component combined with a known one (i.e., a payload). At least one component static test has to be performed. These data are used in conjunction with the system measured frequencies and mode shapes to obtain the vibration characteristics of each component. The flight dynamics of an empty launch vehicle can be determined from measurements made on a vehicle/payload combination in conjunction with a static test on the payload.

Mercury orbiter transport study

NASA Technical Reports Server (NTRS)

Friedlander, A. L.; Feingold, H.

1977-01-01

A data base and comparative performance analyses of alternative flight mode options for delivering a range of payload masses to Mercury orbit are provided. Launch opportunities over the period 1980-2000 are considered. Extensive data trades are developed for the ballistic flight mode option utilizing one or more swingbys of Venus. Advanced transport options studied include solar electric propulsion and solar sailing. Results show the significant performance tradeoffs among such key parameters as trip time, payload mass, propulsion system mass, orbit size, launch year sensitivity and relative cost-effectiveness. Handbook-type presentation formats, particularly in the case of ballistic mode data, provide planetary program planners with an easily used source of reference information essential in the preliminary steps of mission selection and planning.

Trajectory Design for the Transiting Exoplanet Survey Satellite

NASA Technical Reports Server (NTRS)

Dichmann, Donald J.; Parker, Joel J. K.; Williams, Trevor W.; Mendelsohn, Chad R.

2014-01-01

The Transiting Exoplanet Survey Satellite (TESS) is a National Aeronautics and Space Administration (NASA) mission, scheduled to be launched in 2017. TESS will travel in a highly eccentric orbit around Earth, with initial perigee radius near 17 Earth radii (Re) and apogee radius near 59 Re. The orbit period is near 2:1 resonance with the Moon, with apogee nearly 90 degrees out-of-phase with the Moon, in a configuration that has been shown to be operationally stable. TESS will execute phasing loops followed by a lunar flyby, with a final maneuver to achieve 2:1 resonance with the Moon. The goals of a resonant orbit with long-term stability, short eclipses and limited oscillations of perigee present significant challenges to the trajectory design. To rapidly assess launch opportunities, we adapted the Schematics Window Methodology (SWM76) launch window analysis tool to assess the TESS mission constraints. To understand the long-term dynamics of such a resonant orbit in the Earth-Moon system we employed Dynamical Systems Theory in the Circular Restricted 3-Body Problem (CR3BP). For precise trajectory analysis we use a high-fidelity model and multiple shooting in the General Mission Analysis Tool (GMAT) to optimize the maneuver delta-V and meet mission constraints. Finally we describe how the techniques we have developed can be applied to missions with similar requirements. Keywords: resonant orbit, stability, lunar flyby, phasing loops, trajectory optimization

A High-Spin Rate Measurement Method for Projectiles Using a Magnetoresistive Sensor Based on Time-Frequency Domain Analysis.

PubMed

Shang, Jianyu; Deng, Zhihong; Fu, Mengyin; Wang, Shunting

2016-06-16

Traditional artillery guidance can significantly improve the attack accuracy and overall combat efficiency of projectiles, which makes it more adaptable to the information warfare of the future. Obviously, the accurate measurement of artillery spin rate, which has long been regarded as a daunting task, is the basis of precise guidance and control. Magnetoresistive (MR) sensors can be applied to spin rate measurement, especially in the high-spin and high-g projectile launch environment. In this paper, based on the theory of a MR sensor measuring spin rate, the mathematical relationship model between the frequency of MR sensor output and projectile spin rate was established through a fundamental derivation. By analyzing the characteristics of MR sensor output whose frequency varies with time, this paper proposed the Chirp z-Transform (CZT) time-frequency (TF) domain analysis method based on the rolling window of a Blackman window function (BCZT) which can accurately extract the projectile spin rate. To put it into practice, BCZT was applied to measure the spin rate of 155 mm artillery projectile. After extracting the spin rate, the impact that launch rotational angular velocity and aspect angle have on the extraction accuracy of the spin rate was analyzed. Simulation results show that the BCZT TF domain analysis method can effectively and accurately measure the projectile spin rate, especially in a high-spin and high-g projectile launch environment.

KSC-05PD-1086

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Complex 39B, technicians in Space Shuttle Discovery's payload bay perform a borescope inspection of the retract link assembly on the orbiter's main landing gear door. The inspection is a precautionary measure after a small crack was found in a retract link assembly on the right-hand main landing gear on orbiter Atlantis. An initial review of the closeout photos of the link assembly on Discovery did not reveal any cracks. Discovery is scheduled to return the Space Shuttle fleet to operational status on mission STS-114. This additional work does not impact the launch planning window of July 13-31.

KSC-06pd0930

NASA Image and Video Library

2006-05-24

KENNEDY SPACE CENTER, FLA. - The mobile service tower on Launch Complex 37 at Cape Canaveral Air Force Station rolls back to reveal the Boeing Delta IV rocket that will launch the GOES-N satellite into orbit. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA. A geostationary orbit is one in which a satellite remains in the same position with respect to the rotating Earth. Thus, the satellite hovers continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. GOES-N is scheduled for launch May 24 in an hour-long window between 6:11 and 7:11 p.m. EDT. Photo credit: NASA/George Shelton

KSC-06pd0928

NASA Image and Video Library

2006-05-24

KENNEDY SPACE CENTER, FLA. - Before sunrise, a Boeing Delta IV rocket stands ready to launch the GOES-N satellite at Launch Complex 37 at Cape Canaveral Air Force Station. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA. A geostationary orbit is one in which a satellite remains in the same position with respect to the rotating Earth. Thus, the satellite hovers continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. GOES-N is scheduled for launch May 24 in an hour-long window between 6:11 and 7:11 p.m. EDT. Photo credit: NASA/George Shelton

KSC-06pd0929

NASA Image and Video Library

2006-05-24

KENNEDY SPACE CENTER, FLA. - As the sun rises, a Boeing Delta IV rocket stands ready to launch the GOES-N satellite at Launch Complex 37 at Cape Canaveral Air Force Station. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA. A geostationary orbit is one in which a satellite remains in the same position with respect to the rotating Earth. Thus, the satellite hovers continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. GOES-N is scheduled for launch May 24 in an hour-long window between 6:11 and 7:11 p.m. EDT. Photo credit: NASA/George Shelton

KSC-90PC-0626

NASA Image and Video Library

1990-04-24

Through the large window panes of Firing Room 1, KSC launch team members reap the rewards of their work with a glimpse of the space shuttle Discovery soaring into the sky. Discovery was launched for the tenth time at 8:34 a.m. EDT on April 24 beginning the five-day STS-31 mission to deploy the Hubble Space Telescope. A ray of morning sunlight highlights the red and white stripes of Old Glory hanging high in the Firing Room. Launch team members overcame a last minute challenge in the STS-31 countdown when software detected a main propulsion system valve was out of position. The situation was quickly corrected and verified by the team from consoles in the Firing Room and the countdown was returned in a matter of minutes. Photo credit: NASA

KSC-90PC-0627

NASA Image and Video Library

1990-04-24

Through the large window panes of Firing Room 1, KSC launch team members reap the rewards of their work with a glimpse of the space shuttle Discovery soaring into the sky. Discovery was launched for the tenth time at 8:34 a.m. EDT on April 24 beginning the five-day STS-31 mission to deploy the Hubble Space Telescope. A ray of morning sunlight highlights the red and white stripes of Old Glory hanging high in the Firing Room. Launch team members overcame a last minute challenge in the STS-31 countdown when software detected a main propulsion system valve was out of position. The situation was quickly corrected and verified by the team from consoles in the Firing Room and the countdown was returned in a matter of minutes. Photo credit: NASA

KSC-97PC1537

NASA Image and Video Library

1997-10-10

At Launch Complex 40 on Cape Canaveral Air Station, workers are installing three Radioisotope Thermoelectric Generators (RTGs) on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13

KSC-97PC1535

NASA Image and Video Library

1997-10-10

At Launch Complex 40 on Cape Canaveral Air Station, workers are installing three Radioisotope Thermoelectric Generators (RTGs) on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13

KSC-97PC1533

NASA Image and Video Library

1997-10-10

At Launch Complex 40 on Cape Canaveral Air Station, workers are installing three Radioisotope Thermoelectric Generators (RTGs) on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13

KSC-97PC1538

NASA Image and Video Library

1997-10-10

At Launch Complex 40 on Cape Canaveral Air Station, workers are installing three Radioisotope Thermoelectric Generators (RTGs) on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13

KSC-05PD-0894

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. STS-114 Commander Eileen Collins places a mission patch on an M-113 armored personnel carrier during Terminal Countdown Demonstration Test (TCDT) activities. Looking on are Mission Specialists Andrew Thomas, Stephen Robinson and Soichi Noguchi, who is with the Japan Aerospace Exploration Agency.. The crew is at KSC for Terminal Countdown Demonstration Test (TCDT) activities. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is designated the first Return to Flight mission, with a launch window extending from July 13 to July 31.

KSC-05PD-0811

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Kennedy Space Centers Shuttle Landing Facility, Center Director Jim Kennedy talks with STS-114 Commander Eileen Collins after her arrival. She and the rest of the crew are at KSC to take part in the Terminal Countdown Demonstration Test (TCDT) over the next three days. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. This is Collins fourth space flight and second as commander. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-2013-2483

NASA Image and Video Library

2013-05-29

VANDENBERG AFB, Calif. - A mission logo decal for the launch of NASA's IRIS solar observatory aboard an Orbital Sciences Pegasus XL rocket. The decal is on the side of the Pegasus. Engineers are working inside a hangar at Vandenberg Air Force Base where IRIS, short for Interface Region Imaging Spectrograph, is being prepared for launch. Scheduled for launch from Vandenberg June 26, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun’s corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. Photo credit: NASA/Randy Beaudoin

KSC-2013-2484

NASA Image and Video Library

2013-05-29

VANDENBERG AFB, Calif. - A mission logo decal for the launch of NASA's IRIS solar observatory aboard an Orbital Sciences Pegasus XL rocket. The decal is on the side of the Pegasus. Engineers are working inside a hangar at Vandenberg Air Force Base where IRIS, short for Interface Region Imaging Spectrograph, is being prepared for launch. Scheduled for launch from Vandenberg June 26, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun’s corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. Photo credit: NASA/Randy Beaudoin

KSC-2009-5362

NASA Image and Video Library

2009-10-07

CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building's High Bay 1 at NASA’s Kennedy Space Center in Florida, workers supervise space shuttle Atlantis as it is positioned next to an external fuel tank, at left, and pair of solid rocket boosters secured to a mobile launcher platform. Next, Atlantis will be attached, completing the stacking operation. Rollout of the completed shuttle stack to Kennedy’s Launch Pad 39A, a significant milestone in launch processing activities, is planned for Oct. 13. Liftoff of Atlantis on its STS-129 mission to the International Space Station is targeted for 4:04 p.m. EST Nov. 12 during a 10-minute launch window. For information on the STS-129 mission and crew, visit http://www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts129/index.html. Photo credit: NASA/Jack Pfaller

KSC-05PD-1073

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Payload Hazardous Servicing Facility, an electromagnetic interference verification test is being conducted on the solar arrays for the Mars Reconnaissance Orbiter (MRO) and an antenna simulator (yellow horizontal rod). If no interference is found during the test, the Shallow Radar Antenna (SHARAD) will be installed on the spacecraft. The spacecraft is undergoing multiple mechanical assembly operations and electrical tests to verify its readiness for launch. The MRO was built by Lockheed Martin for NASAs Jet Propulsion Laboratory in California. It is the next major step in Mars exploration and scheduled for launch from Launch Complex 41 at Cape Canaveral Air Force Station in a window opening Aug. 10. The MRO is an important next step in fulfilling NASAs vision of space exploration and ultimately sending human explorers to Mars and beyond.

Processing activities for STS-91 continue in OPF Bay 2

NASA Technical Reports Server (NTRS)

1998-01-01

Processing activities for STS-91 continue in KSC's Orbiter Processing Facility Bay 2. The payload bay of Space Shuttle Discovery is relatively empty as installation of the Get Away Special (GAS) canisters begins. Two GAS canisters can be seen in the center of the photograph. On the left is G-648, a Canadian Space Agency-sponsored study on manufactured organic thin film by the physical vapor transport method, and on the right is a can with hundreds of commemorative flags to be flown on the mission. STS-91 is scheduled to launch aboard the Space Shuttle Discovery for the ninth and final docking with the Russian Space Station Mir from KSC's Launch Pad 39A on June 2 with a launch window opening around 6:04 p.m. EDT.

3D TRUMP - A GBI launch window tool

NASA Astrophysics Data System (ADS)

Karels, Steven N.; Hancock, John; Matchett, Gary

3D TRUMP is a novel GPS and communicatons-link software analysis tool developed for the SDIO's Ground-Based Interceptor (GBI) program. 3D TRUMP uses a computationally efficient analysis tool which provides key GPS-based performance measures for an entire GBI mission's reentry vehicle and interceptor trajectories. Algorithms and sample outputs are presented.

14. VIEW OF WEST WALL OF CLEAN ROOM (102) SHOWING ...

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

14. VIEW OF WEST WALL OF CLEAN ROOM (102) SHOWING VIEWING WINDOWS IN WEST FALSE PARTION WALL, WEST WALL OF CLEAN ROOM (102), AND ROLLS OF PLASTIC WRAP FOR COVERING CLEANED FAIRING ASSEMBLY - Vandenberg Air Force Base, Space Launch Complex 3, Vehicle Support Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

KSC-2010-5737

NASA Image and Video Library

2010-11-24

CAPE CANAVERAL, Fla. -- The finishing touches of the Propellants North Administrative and Maintenance Facility begin to take place at NASA's Kennedy Space Center in Florida. Inside the green facility is window glazing and framing from the iconic firing rooms of Kennedy's Launch Control Center (LCC). The windows are set at the same orientation and angle as they were in the LCC, looking out toward Launch Complex 39. The facility also features sustainable flooring made of polished concrete and laminated bamboo, as well as a high-efficiency roof and walls. This is the facility's two-story administrative building, which will house managers, mechanics and technicians who fuel spacecraft at Kennedy. Next door is a single-story shop that will be used to store cryogenic fuel transfer equipment. The facility is striving to qualify for the U.S. Green Building Council’s Leadership in Energy and Environmental Design (LEED) Platinum certification, which is the highest of LEED ratings. The facility, set to be complete in December 2010, was designed for NASA by Jones Edmunds and Associates. H. W. Davis Construction is the construction contractor. Photo credit: NASA/Frankie Martin

Launch Collision Probability

NASA Technical Reports Server (NTRS)

Bollenbacher, Gary; Guptill, James D.

1999-01-01

This report analyzes the probability of a launch vehicle colliding with one of the nearly 10,000 tracked objects orbiting the Earth, given that an object on a near-collision course with the launch vehicle has been identified. Knowledge of the probability of collision throughout the launch window can be used to avoid launching at times when the probability of collision is unacceptably high. The analysis in this report assumes that the positions of the orbiting objects and the launch vehicle can be predicted as a function of time and therefore that any tracked object which comes close to the launch vehicle can be identified. The analysis further assumes that the position uncertainty of the launch vehicle and the approaching space object can be described with position covariance matrices. With these and some additional simplifying assumptions, a closed-form solution is developed using two approaches. The solution shows that the probability of collision is a function of position uncertainties, the size of the two potentially colliding objects, and the nominal separation distance at the point of closest approach. ne impact of the simplifying assumptions on the accuracy of the final result is assessed and the application of the results to the Cassini mission, launched in October 1997, is described. Other factors that affect the probability of collision are also discussed. Finally, the report offers alternative approaches that can be used to evaluate the probability of collision.

XBox Input -Version 1.0

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

2012-10-03

Contains class for connecting to the Xbox 360 controller, displaying the user inputs {buttons, triggers, analog sticks), and controlling the rumble motors. Also contains classes for converting the raw Xbox 360 controller inputs into meaningful commands for the following objects: • Robot arms - Provides joint control and several tool control schemes • UGV's - Provides translational and rotational commands for "skid-steer" vehicles • Pan-tilt units - Provides several modes of control including velocity, position, and point-tracking • Head-mounted displays (HMO)- Controls the viewpoint of a HMO • Umbra frames - Controls the position andorientation of an Umbra posrot objectmore » • Umbra graphics window - Provides several modes of control for the Umbra OSG window viewpoint including free-fly, cursor-focused, and object following.« less

Combat Vehicle Command and Control System Architecture Overview

DTIC Science & Technology

1994-10-01

inserted in the software. • Interactive interface displays and controls were prepared using rapidly prototyped software and were retained at the MWTB for...being simulated "* controls , sensor displays, and out-the-window displays for the crew "* computer image generators (CIGs) for out-the-window and...black hot viewing modes. The commander may access a number of capabilities of the CITV simulation, described below, from controls located around the

The dance of molecules: new dynamical perspectives on highly excited molecular vibrations.

PubMed

Kellman, Michael E; Tyng, Vivian

2007-04-01

At low energies, molecular vibrational motion is described by the normal modes model. This model breaks down at higher energy, with strong coupling between normal modes and onset of chaotic dynamics. New anharmonic modes are born in bifurcations, or branchings of the normal modes. Knowledge of these new modes is obtained through the window of frequency-domain spectroscopy, using techniques of nonlinear classical dynamics. It may soon be possible to "watch" molecular rearrangement reactions spectroscopically. Connections are being made with reaction rate theories, condensed phase systems, and motions of electrons in quantum dots.

A multimodal logistics service network design with time windows and environmental concerns

PubMed Central

Zhang, Dezhi; He, Runzhong; Wang, Zhongwei

2017-01-01

The design of a multimodal logistics service network with customer service time windows and environmental costs is an important and challenging issue. Accordingly, this work established a model to minimize the total cost of multimodal logistics service network design with time windows and environmental concerns. The proposed model incorporates CO2 emission costs to determine the optimal transportation mode combinations and investment selections for transfer nodes, which consider transport cost, transport time, carbon emission, and logistics service time window constraints. Furthermore, genetic and heuristic algorithms are proposed to set up the abovementioned optimal model. A numerical example is provided to validate the model and the abovementioned two algorithms. Then, comparisons of the performance of the two algorithms are provided. Finally, this work investigates the effects of the logistics service time windows and CO2 emission taxes on the optimal solution. Several important management insights are obtained. PMID:28934272

A multimodal logistics service network design with time windows and environmental concerns.

PubMed

Zhang, Dezhi; He, Runzhong; Li, Shuangyan; Wang, Zhongwei

2017-01-01

The design of a multimodal logistics service network with customer service time windows and environmental costs is an important and challenging issue. Accordingly, this work established a model to minimize the total cost of multimodal logistics service network design with time windows and environmental concerns. The proposed model incorporates CO2 emission costs to determine the optimal transportation mode combinations and investment selections for transfer nodes, which consider transport cost, transport time, carbon emission, and logistics service time window constraints. Furthermore, genetic and heuristic algorithms are proposed to set up the abovementioned optimal model. A numerical example is provided to validate the model and the abovementioned two algorithms. Then, comparisons of the performance of the two algorithms are provided. Finally, this work investigates the effects of the logistics service time windows and CO2 emission taxes on the optimal solution. Several important management insights are obtained.

Launch and Assembly Reliability Analysis for Human Space Exploration Missions

NASA Technical Reports Server (NTRS)

Cates, Grant; Gelito, Justin; Stromgren, Chel; Cirillo, William; Goodliff, Kandyce

2012-01-01

NASA's future human space exploration strategy includes single and multi-launch missions to various destinations including cis-lunar space, near Earth objects such as asteroids, and ultimately Mars. Each campaign is being defined by Design Reference Missions (DRMs). Many of these missions are complex, requiring multiple launches and assembly of vehicles in orbit. Certain missions also have constrained departure windows to the destination. These factors raise concerns regarding the reliability of launching and assembling all required elements in time to support planned departure. This paper describes an integrated methodology for analyzing launch and assembly reliability in any single DRM or set of DRMs starting with flight hardware manufacturing and ending with final departure to the destination. A discrete event simulation is built for each DRM that includes the pertinent risk factors including, but not limited to: manufacturing completion; ground transportation; ground processing; launch countdown; ascent; rendezvous and docking, assembly, and orbital operations leading up to trans-destination-injection. Each reliability factor can be selectively activated or deactivated so that the most critical risk factors can be identified. This enables NASA to prioritize mitigation actions so as to improve mission success.

KSC-2014-4398

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 on a work platform 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-08pd1812

NASA Image and Video Library

2008-06-19

VANDENBERG AIR FORCE BASE, Calif. – The mobile service tower on Space Launch Complex 2 begins to roll back from the Delta II launch vehicle in preparation for launch of the Ocean Surface Topography Mission, or OSTM/Jason 2. The OSTM/Jason 2 satellite will embark on a globe-circling voyage to continue charting sea level, a vital indicator of global climate change. The mission will return a vast amount of new data that will improve weather, climate and ocean forecasts. OSTM/Jason 2's expected lifetime of at least three years will extend into the next decade the continuous record of these data started in 1992 by NASA and the French space agency Centre National d'Etudes Spatiales, or CNES, with the TOPEX/Poseidon mission. The data collection was continued by the two agencies on Jason-1 in 2001. The launch window extends from 12:46 a.m. to 12:55 a.m. PDT. The satellite will be placed in an 830-mile-high orbit at an inclination of 66 degrees after separating from the Delta II 55 minutes after liftoff. Photo credit: Photograph by Carleton Bailie for United Launch Alliance

Resonant kink-antikink scattering through quasinormal modes

NASA Astrophysics Data System (ADS)

Dorey, Patrick; Romańczukiewicz, Tomasz

2018-04-01

We investigate the role that quasinormal modes can play in kink-antikink collisions, via an example based on a deformation of the ϕ4 model. We find that narrow quasinormal modes can store energy during collision processes and later return it to the translational degrees of freedom. Quasinormal modes also decay, which leads to energy leakage, causing a closing of resonance windows and an increase of the critical velocity. We observe similar phenomena in an effective model, a small modification of the collective-coordinate approach to the ϕ4 model.

Launch Vehicle Manual Steering with Adaptive Augmenting Control In-flight Evaluations of Adverse Interactions Using a Piloted Aircraft

NASA Technical Reports Server (NTRS)

Hanson, Curt; Miller, Chris; Wall, John H.; Vanzwieten, Tannen S.; Gilligan, Eric; Orr, Jeb S.

2015-01-01

An adaptive augmenting control algorithm for the Space Launch System has been developed at the Marshall Space Flight Center as part of the launch vehicles baseline flight control system. A prototype version of the SLS flight control software was hosted on a piloted aircraft at the Armstrong Flight Research Center to demonstrate the adaptive controller on a full-scale realistic application in a relevant flight environment. Concerns regarding adverse interactions between the adaptive controller and a proposed manual steering mode were investigated by giving the pilot trajectory deviation cues and pitch rate command authority. Two NASA research pilots flew a total of twenty five constant pitch-rate trajectories using a prototype manual steering mode with and without adaptive control.

Performance Optimization of the Gasdynamic Mirror Propulsion System

NASA Technical Reports Server (NTRS)

Emrich, William J., Jr.; Kammash, Terry

1999-01-01

Nuclear fusion appears to be a most promising concept for producing extremely high specific impulse rocket engines. Engines such as these would effectively open up the solar system to human exploration and would virtually eliminate launch window restrictions. A preliminary vehicle sizing and mission study was performed based on the conceptual design of a Gasdynamic Mirror (GDM) fusion propulsion system. This study indicated that the potential specific impulse for this engine is approximately 142,000 sec. with about 22,100 N of thrust using a deuterium-tritium fuel cycle. The engine weight inclusive of the power conversion system was optimized around an allowable engine mass of 1500 Mg assuming advanced superconducting magnets and a Field Reversed Configuration (FRC) end plug at the mirrors. The vehicle habitat, lander, and structural weights are based on a NASA Mars mission study which assumes the use of nuclear thermal propulsion' Several manned missions to various planets were analyzed to determine fuel requirements and launch windows. For all fusion propulsion cases studied, the fuel weight remained a minor component of the total system weight regardless of when the missions commenced. In other words, the use of fusion propulsion virtually eliminates all mission window constraints and effectively allows unlimited manned exploration of the entire solar system. It also mitigates the need to have a large space infrastructure which would be required to support the transfer of massive amounts of fuel and supplies to lower a performing spacecraft.

R-mode constraints from neutron star equation of state

NASA Astrophysics Data System (ADS)

Papazoglou, M. C.; Moustakidis, C. C.

2016-03-01

The gravitational radiation has been proposed a long time before, as an explanation for the observed relatively low spin frequencies of young neutron stars and of accreting neutron stars in low-mass X-ray binaries as well. In the present work we studied the effects of the neutron star equation of state on the r-mode instability window of rotating neutron stars. Firstly, we employed a set of analytical solution of the Tolman-Oppenheimer-Volkoff equations with special emphasis on the Tolman VII solution. In particular, we tried to clarify the effects of the bulk neutron star properties (mass, radius, density distribution, crust size and elasticity) on the r-mode instability window. We found that the critical angular velocity \\varOmegac depends mainly on the neutron star radius. The effects of the gravitational mass and the mass distribution are almost negligible. Secondly, we studied the effect of the elasticity of the crust, via to the slippage factor S and also the effect of the nuclear equation of state, via the slope parameter L, on the instability window. We found that the crust effects are more pronounced, compared to those originated from the equation of state. Moreover, we proposed simple analytical expressions which relate the macroscopic quantity \\varOmegac to the radius, the parameter L and the factor {S}. We also investigated the possibility to measure the radius of a neutron star and the factor {S} with the help of accurate measures of \\varOmegac and the neutron star temperature. Finally, we studied the effects of the mutual friction on the instability window and discussed the results in comparison with previous similar studies.

Orion Crew Exploration Vehicle Launch Abort System Guidance and Control Analysis Overview

NASA Technical Reports Server (NTRS)

Davidson, John B.; Kim, Sungwan; Raney, David L.; Aubuchon, Vanessa V.; Sparks, Dean W.; Busan, Ronald C.; Proud, Ryan W.; Merritt, Deborah S.

2008-01-01

Aborts during the critical ascent flight phase require the design and operation of Orion Crew Exploration Vehicle (CEV) systems to escape from the Crew Launch Vehicle (CLV) and return the crew safely to the Earth. To accomplish this requirement of continuous abort coverage, CEV ascent abort modes are being designed and analyzed to accommodate the velocity, altitude, atmospheric, and vehicle configuration changes that occur during ascent. Aborts from the launch pad to early in the flight of the CLV second stage are performed using the Launch Abort System (LAS). During this type of abort, the LAS Abort Motor is used to pull the Crew Module (CM) safely away from the CLV and Service Module (SM). LAS abort guidance and control studies and design trades are being conducted so that more informed decisions can be made regarding the vehicle abort requirements, design, and operation. This paper presents an overview of the Orion CEV, an overview of the LAS ascent abort mode, and a summary of key LAS abort analysis methods and results.

KSC-2011-7935

NASA Image and Video Library

2011-11-25

CAPE CANAVERAL, Fla. – Ryan Bechtel, from the Department of Energy, speaks to a group of Tweetup participants at NASA Kennedy Space Center's Press Site in Florida during prelaunch activities for the agency’s Mars Science Laboratory (MSL) launch. Following a series of briefings, participants will tour the center and get a close-up view of Space Launch Complex-41 on Cape Canaveral Air Force Station. The tweeters will share their experiences with followers through the social networking site Twitter. MSL's components include a car-sized rover, Curiosity, which has 10 science instruments designed to search for signs of life, including methane, and help determine if the gas is from a biological or geological source. Liftoff of MSL aboard a United Launch Alliance Atlas V rocket from pad 41 is planned during a launch window which extends from 10:02 a.m. to 11:45 a.m. EST on Nov. 26. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Jim Grossmann

KSC-2011-7933

NASA Image and Video Library

2011-11-25

CAPE CANAVERAL, Fla. – Doug McCuistion, director of the Mars Exploration Program at NASA Headquarters, speaks to a group of Tweetup participants at NASA Kennedy Space Center's Press Site in Florida during prelaunch activities for the agency’s Mars Science Laboratory (MSL) launch. Following a series of briefings, participants will tour the center and get a close-up view of Space Launch Complex-41 on Cape Canaveral Air Force Station. The tweeters will share their experiences with followers through the social networking site Twitter. MSL's components include a car-sized rover, Curiosity, which has 10 science instruments designed to search for signs of life, including methane, and help determine if the gas is from a biological or geological source. Liftoff of MSL aboard a United Launch Alliance Atlas V rocket from pad 41 is planned during a launch window which extends from 10:02 a.m. to 11:45 a.m. EST on Nov. 26. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Jim Grossmann

KSC-05PD-0845

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. During Terminal Countdown Demonstration Test (TCDT) activities at NASAs Kennedy Space Center, the STS-114 crew takes part in training on an M-113, an armored personnel carrier that is used for speedy departure from the launch pad in an emergency. Seated in the M-113, left to right, are Commander Eileen Collins, Mission Specialist Stephen Robinson, Capt. George Hoggard, astronaut rescue team leader, Mission Specialists Andrew Thomas, Soichi Noguchi and Charles Camarda, and Pilot James Kelly. Noguchi is with the Japan Aerospace Exploration Agency. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

KSC-2009-1885

NASA Image and Video Library

2009-02-26

CAPE CANAVERAL, Fla. – On Launch Pad 17-B at Cape Canaveral Air Force Station in Florida, NASA's Kepler spacecraft, atop the United Launch Alliance Delta II rocket, waits for encapsulation in the fairing. The fairing is a molded structure that fits flush with the outside surface of the rocket and forms an aerodynamically smooth nose cone, protecting the spacecraft during launch and ascent. The liftoff of Kepler aboard the Delta II rocket is currently targeted for launch in a window extending 10:49 to 10:52 p.m. EST March 6 from Pad 17-B. Kepler is designed to survey more than 100,000 stars in our galaxy to determine the number of sun-like stars that have Earth-size and larger planets, including those that lie in a star's "habitable zone," a region where liquid water, and perhaps life, could exist. If these Earth-size worlds do exist around stars like our sun, Kepler is expected to be the first to find them and the first to measure how common they are. Photo credit: NASA/Jack Pfaller

Flight Data Analysis of HyShot 2

NASA Technical Reports Server (NTRS)

Hass, Neal E.; Smart, Michael K.; Paull, Alan

2005-01-01

The development of scramjet propulsion for alternative launch and payload delivery capabilities has comprised largely of ground experiments for the last 40 years. With the goal of validating the use of short duration ground test facilities, the University of Queensland, supported by a large international contingency, devised a ballistic re-entry vehicle experiment called HyShot to achieve supersonic combustion in flight above Mach 7.5. It consisted of a double wedge intake and two back-to-back constant area combustors; one supplied with hydrogen fuel at an equivalence ratio of 0.33 and the other un-fueled. Following a first launch failure on October 30th 2001, the University of Queensland conducted a successful second launch on July 30th, 2002. Post-flight data analysis of the second launch confirmed the presence of supersonic combustion during the approximately 3 second test window at altitudes between 35 and 29 km. Reasonable correlation between flight and some pre-flight shock tunnel tests was observed.

KSC-2011-7941

NASA Image and Video Library

2011-11-25

CAPE CANAVERAL, Fla. – David Blake, NASA principal investigator for the Chemistry and Mineralogy (CheMin) investigation by the Curiosity rover, demonstrates the experiment for the media in NASA Kennedy Space Center's Press Site auditorium in Florida during prelaunch activities for the agency’s Mars Science Laboratory (MSL) launch. CheMin is designed to analyze powdered rock and soil samples by identifying and quantifying their mineral content using X-ray diffraction, a first for a mission to Mars. The car-sized Martian rover, Curiosity, has 10 science instruments designed to search for signs of life, including methane, and help determine if the gas is from a biological or geological source. Liftoff of MSL aboard a United Launch Alliance Atlas V rocket from Space Launch Complex-41 on Cape Canaveral Air Force Station is planned during a launch window which extends from 10:02 a.m. to 11:45 a.m. EST on Nov. 26. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Kim Shiflett

KSC-2011-7942

NASA Image and Video Library

2011-11-25

CAPE CANAVERAL, Fla. – David Blake, NASA principal investigator for the Chemistry and Mineralogy (CheMin) investigation by the Curiosity rover, explains the experiment to the media in NASA Kennedy Space Center's Press Site auditorium in Florida during prelaunch activities for the agency’s Mars Science Laboratory (MSL) launch. CheMin is designed to analyze powdered rock and soil samples by identifying and quantifying their mineral content using X-ray diffraction, a first for a mission to Mars. The car-sized Martian rover, Curiosity, has 10 science instruments designed to search for signs of life, including methane, and help determine if the gas is from a biological or geological source. Liftoff of MSL aboard a United Launch Alliance Atlas V rocket from Space Launch Complex-41 on Cape Canaveral Air Force Station is planned during a launch window which extends from 10:02 a.m. to 11:45 a.m. EST on Nov. 26. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Kim Shiflett

STS-74 clears tower (with view of RSS)

NASA Technical Reports Server (NTRS)

1995-01-01

The STS-74 astronauts depart the Operations and Checkout Building, headed for the launch pad and a rendezvous in space. Leading the way are Commander Kenneth D. Cameron (front right) and Pilot James D. Halsell Jr. (front left). Behind them are the three mission specialists assigned to STS-74 (front to back): Chris A. Hadfield, representing the Canadian Space Agency; Jerry L. Ross, and William S. 'Bill' McArthur Jr. Awaiting them at Launch Pad 39A is the Space Shuttle Atlantis, scheduled for a second liftoff attempt lift off during a seven-minute launch window opening at about 7:30 a.m. EST, Nov. 12. During its approximately eight-day flight, Atlantis will dock with the Russian Space Station Mir and a permanent docking extension will be attached to the station, and transfer of materials to and from the mated spacecraft will be completed. A first launch attempt Nov. 11 was scrubbed due to unfavorable weather conditions at the contingency Transoceanic Abort Landing (TAL) sites.

KSC-05PD-0807

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. After arrival at NASAs Kennedy Space Center, the STS-114 crew members are greeted by KSC officials. Seen from left are Deputy Director Woodrow Whitlow Jr., Commander Eileen Collins, Mission Specialists Charles Camarda (behind Collins) and Andrew Thomas, astronaut Jerry Ross, who is chief of the Vehicle Integration Test (VIT) office, VIT Lead for STS-114 Robert Hanley, Shuttle Launch Director Mike Leinbach and Center Director Jim Kennedy. Crew members are taking part in the Terminal Countdown Demonstration Test (TCDT) over the next three days. The TCDT is held at KSC prior to each Space Shuttle flight. It provides the crew of each mission an opportunity to participate in simulated countdown activities. The test ends with a mock launch countdown culminating in a simulated main engine cutoff. The crew also spends time undergoing emergency egress training exercises at the launch pad. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends July 13 through July 31.

STS-37 Commander Nagel in commanders seat on OV-104's flight deck

NASA Technical Reports Server (NTRS)

1991-01-01

STS-37 Commander Steven R. Nagel, wearing launch and entry suit (LES), sits at commanders station on the forward flight deck of Atlantis, Orbiter Vehicle (OV) 104. Surrounding Nagel are the seat headrest, control panels, checklists, forward flight deck windows, and three drinking water containers with straws attached to forward panel F2.

KSC-05PD-1089

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, a new heater has been added to the feedline bellows to minimize the potential for ice and frost buildup. The tank has been designated to fly on Discovery for Return to Flight mission STS-114, which has a launch window extending from July 13 to July 31.

Detecting, anticipating, and predicting critical transitions in spatially extended systems.

PubMed

Kwasniok, Frank

2018-03-01

A data-driven linear framework for detecting, anticipating, and predicting incipient bifurcations in spatially extended systems based on principal oscillation pattern (POP) analysis is discussed. The dynamics are assumed to be governed by a system of linear stochastic differential equations which is estimated from the data. The principal modes of the system together with corresponding decay or growth rates and oscillation frequencies are extracted as the eigenvectors and eigenvalues of the system matrix. The method can be applied to stationary datasets to identify the least stable modes and assess the proximity to instability; it can also be applied to nonstationary datasets using a sliding window approach to track the changing eigenvalues and eigenvectors of the system. As a further step, a genuinely nonstationary POP analysis is introduced. Here, the system matrix of the linear stochastic model is time-dependent, allowing for extrapolation and prediction of instabilities beyond the learning data window. The methods are demonstrated and explored using the one-dimensional Swift-Hohenberg equation as an example, focusing on the dynamics of stochastic fluctuations around the homogeneous stable state prior to the first bifurcation. The POP-based techniques are able to extract and track the least stable eigenvalues and eigenvectors of the system; the nonstationary POP analysis successfully predicts the timing of the first instability and the unstable mode well beyond the learning data window.

Detecting, anticipating, and predicting critical transitions in spatially extended systems

NASA Astrophysics Data System (ADS)

Kwasniok, Frank

2018-03-01

A data-driven linear framework for detecting, anticipating, and predicting incipient bifurcations in spatially extended systems based on principal oscillation pattern (POP) analysis is discussed. The dynamics are assumed to be governed by a system of linear stochastic differential equations which is estimated from the data. The principal modes of the system together with corresponding decay or growth rates and oscillation frequencies are extracted as the eigenvectors and eigenvalues of the system matrix. The method can be applied to stationary datasets to identify the least stable modes and assess the proximity to instability; it can also be applied to nonstationary datasets using a sliding window approach to track the changing eigenvalues and eigenvectors of the system. As a further step, a genuinely nonstationary POP analysis is introduced. Here, the system matrix of the linear stochastic model is time-dependent, allowing for extrapolation and prediction of instabilities beyond the learning data window. The methods are demonstrated and explored using the one-dimensional Swift-Hohenberg equation as an example, focusing on the dynamics of stochastic fluctuations around the homogeneous stable state prior to the first bifurcation. The POP-based techniques are able to extract and track the least stable eigenvalues and eigenvectors of the system; the nonstationary POP analysis successfully predicts the timing of the first instability and the unstable mode well beyond the learning data window.

Use of DES Modeling for Determining Launch Availability for SLS

NASA Technical Reports Server (NTRS)

Watson, Mike; Staton, Eric; Cates, Grant; Finn, Ron; Altino, Karen; Burns, Lee

2014-01-01

The National Aeronautics and Space Administration (NASA) is developing new capabilities for human and scientific exploration beyond Earth's orbit. This effort includes the Space Shuttle derived Space Launch System (SLS), the Multi-Purpose Crew Vehicle (MPCV) "Orion", and the Ground Systems Development and Operations (GSDO). There are several requirements and Technical Performance Measures (TPMs) that have been levied by the Exploration Systems Development (ESD) upon the SLS, MPCV, and GSDO Programs including an integrated Launch Availability (LA) TPM. The LA TPM is used to drive into the SLS, Orion and GSDO designs a high confidence of successfully launching exploration missions that have narrow Earth departure windows. The LA TPM takes into consideration the reliability of the overall system (SLS, Orion and GSDO), natural environments, likelihood of a failure, and the time required to recover from an anomaly. A challenge with the LA TPM is the interrelationships between SLS, Orion, GSDO and the natural environments during launch countdown and launch delays that makes it impossible to develop an analytical solution for calculating the integrated launch probability. This paper provides an overview of how Discrete Event Simulation (DES) modeling was used to develop the LA TPM, how it was allocated down to the individual programs, and how the LA analysis is being used to inform and drive the SLS, Orion, and GSDO designs to ensure adequate launch availability for future human exploration.

Use of DES Modeling for Determining Launch Availability for SLS

NASA Technical Reports Server (NTRS)

Staton, Eric; Cates, Grant; Finn, Ronald; Altino, Karen M.; Burns, K. Lee; Watson, Michael D.

2014-01-01

The National Aeronautics and Space Administration (NASA) is developing new capabilities for human and scientific exploration beyond Earth's orbit. This effort includes the Space Shuttle derived Space Launch System (SLS), the Orion Multi-Purpose Crew Vehicle (MPCV), and the Ground Systems Development and Operations (GSDO). There are several requirements and Technical Performance Measures (TPMs) that have been levied by the Exploration Systems Development (ESD) upon the SLS, Orion, and GSDO Programs including an integrated Launch Availability (LA) TPM. The LA TPM is used to drive into the SLS, Orion and GSDO designs a high confidence of successfully launching exploration missions that have narrow Earth departure windows. The LA TPM takes into consideration the reliability of the overall system (SLS, Orion and GSDO), natural environments, likelihood of a failure, and the time required to recover from an anomaly. A challenge with the LA TPM is the interrelationships between SLS, Orion, GSDO and the natural environments during launch countdown and launch delays that makes it impossible to develop an analytical solution for calculating the integrated launch probability. This paper provides an overview of how Discrete Event Simulation (DES) modeling was used to develop the LA TPM, how it was allocated down to the individual programs, and how the LA analysis is being used to inform and drive the SLS, Orion, and GSDO designs to ensure adequate launch availability for future human exploration.

Search for the Exotic Wobbling Mode in Rhenium-171

DTIC Science & Technology

2011-05-13

USB hard drive. The decay sequences mentioned above release all of their γ rays within a nanosecond (ns). Data will be recorded when multiple ...events in which multiple detectors measured γ rays within a 120 ns window. An event in which three detectors fired within the coincidence window is...spherical nuclei; however, if the nucleus is axially deformed (non-spherical), the shell model cannot accurately describe its features . The shell model

Absolute Two-Photon Absorption Coefficients in UltraViolet Window Materials

DTIC Science & Technology

1977-12-01

fvtt* tld » II ntctHB,-y md Idtnlll’ by block number; The absolute two-photon absorption coefficiehts of u. v. transmitting materials have been...measured using well-calibrated single picosecond pulses, at the third and fourth harmonic of a mode locked Nd:YAG laser systems. Twc photon...30, 1977. Work in the area of laser induced breakdown and multiphoton absorption in ultraviolet and infrared laser window materials was carried

Operationalizing Cyberspace for Today’s Combat Air Force

DTIC Science & Technology

2010-04-01

rootkit techniques to run inside common Windows services (sometimes bundled with fake antivirus software ) or in Windows safe mode, and it can hide...has shifted to downloading other malware, with its main focus on fake alerts and rogue antivirus software . 5. TR/Dldr.Agent.JKH - Compromised U.S...patch, software update, or security breech away from failure. In short, what works AU/ACSC/SIMMONS/AY10 5 today, may not work tomorrow; this fact

KSC-01pp1560

NASA Image and Video Library

2001-09-11

KENNEDY SPACE CENTER, FLA. - At Cape Canaveral Air Force Station, Fla., the Atlas Centaur booster segment of an Atlas II rocket is offloaded. It will be mated to the first segment on Launch Pad 36-A, CCAFS, in preparation for launch of the TDRS-I spacecraft Oct. 30. The 40-minute launch window begins at 11:19 p.m. EST. The TDRS System (TDRSS) is a communication signal relay system that provides tracking and data acquisition services between low-Earth orbiting spacecraft and NASA/customer control and/or data processing facilities. The system is capable of transmitting to and receiving data from customer spacecrafts over 100 percent of their orbit (some limitations may apply depending on actual orbit). The TDRS-I provides a Ka-band service that will allow customers with extremely high data rates to be supported by TDRSS if they desire

KSC-06pd0933

NASA Image and Video Library

2006-05-24

KENNEDY SPACE CENTER, FLA. - The mobile service tower on Launch Complex 37 at Cape Canaveral Air Force Station has been removed from around a Boeing Delta IV rocket as preparations continue to launch the GOES-N satellite. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA. A geostationary orbit is one in which a satellite remains in the same position with respect to the rotating Earth. Thus, the satellite hovers continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. GOES-N is scheduled for launch May 24 in an hour-long window between 6:11 and 7:11 p.m. EDT. Photo credit: NASA/George Shelton

KSC-06pd0932

NASA Image and Video Library

2006-05-24

KENNEDY SPACE CENTER, FLA. - The mobile service tower on Launch Complex 37 at Cape Canaveral Air Force Station has been removed from around the Boeing Delta IV rocket that will launch the GOES-N satellite into orbit. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA. A geostationary orbit is one in which a satellite remains in the same position with respect to the rotating Earth. Thus, the satellite hovers continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. GOES-N is scheduled for launch May 24 in an hour-long window between 6:11 and 7:11 p.m. EDT. Photo credit: NASA/George Shelton

KSC-06pd0931

NASA Image and Video Library

2006-05-24

KENNEDY SPACE CENTER, FLA. - The mobile service tower on Launch Complex 37 at Cape Canaveral Air Force Station has been rolled back to reveal the Boeing Delta IV rocket that will launch the GOES-N satellite into orbit. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA. A geostationary orbit is one in which a satellite remains in the same position with respect to the rotating Earth. Thus, the satellite hovers continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. GOES-N is scheduled for launch May 24 in an hour-long window between 6:11 and 7:11 p.m. EDT. Photo credit: NASA/George Shelton

KSC-06pd0934

NASA Image and Video Library

2006-05-24

KENNEDY SPACE CENTER, FLA. - The mobile service tower on Launch Complex 37 at Cape Canaveral Air Force Station has been removed from around a Boeing Delta IV rocket as preparations continue to launch the GOES-N satellite. GOES-N is the latest in a series of Geostationary Operational Environmental Satellites for NOAA and NASA. A geostationary orbit is one in which a satellite remains in the same position with respect to the rotating Earth. Thus, the satellite hovers continuously over one position on the Earth's surface, appearing stationary. As a result, GOES provide a constant vigil for the atmospheric "triggers" for severe weather conditions such as tornadoes, flash floods, hail storms, and hurricanes. GOES-N is scheduled for launch May 24 in an hour-long window between 6:11 and 7:11 p.m. EDT. Photo credit: NASA/George Shelton

KSC-97PC1534

NASA Image and Video Library

1997-10-10

At Launch Complex 40 on Cape Canaveral Air Station, one of three Radioisotope Thermoelectric Generators (RTGs) is being installed on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13

KSC-97PC1532

NASA Image and Video Library

1997-10-10

KENNEDY SPACE CENTER, FLA. -- At Launch Complex 40 on Cape Canaveral Air Station, workers are installing three Radioisotope Thermoelectric Generators (RTGs) on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13

KSC-97PC1536

NASA Image and Video Library

1997-10-10

KENNEDY SPACE CENTER, FLA. -- At Launch Complex 40 on Cape Canaveral Air Station, workers are installing three Radioisotope Thermoelectric Generators (RTGs) on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13

KSC-2011-7903

NASA Image and Video Library

2011-11-25

CAPE CANAVERAL, Fla. -- On Cape Canaveral Air Force Station in Florida, lightning masts protect the 197-foot-tall United Launch Alliance Atlas V rocket as it leaves behind the safety of the Vertical Integration Facility (VIF) at Space Launch Complex-41 to take its position on the pad's surface. Atop the rocket is NASA's Mars Science Laboratory (MSL), enclosed in its payload fairing. The rocket began its move from the VIF at 8 a.m. EST. Liftoff is planned during a launch window which extends from 10:02 a.m. to 11:45 a.m. EST on Nov. 26. MSL's components include a car-sized rover, Curiosity, which has 10 science instruments designed to search for signs of life, including methane, and help determine if the gas is from a biological or geological source. For more information, visit http://www.nasa.gov/msl. Photo credit: NASA/Tony Gray

KSC-05PD-1177

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At NASAs Kennedy Space Center, Space Shuttle Discovery, resting on the Mobile Launcher Platform, rolls into high bay 1 of the Vehicle Assembly Building (VAB). The Shuttle is being rolled back from Launch Pad 39B. It will be demated from its External Tank and lifted into the transfer aisle. On or about June 7, Discovery will be attached to its new tank and Solid Rocket Boosters, which are already in the VAB. Only the 15th rollback in Space Shuttle Program history, the 4.2- mile journey allows additional modifications to be made to the External Tank prior to a safe Return to Flight. Discovery is expected to be rolled back to the launch pad in mid-June for Return to Flight mission STS-114. The launch window extends from July 13 to July 31. [Photo courtesy of Scott Andrews

Low energy trajectories to Mars via gravity assist from Venus to earth

NASA Technical Reports Server (NTRS)

Williams, S. N.; Longuski, J. M.

1991-01-01

The analytical determination of launch dates and proposed trajectories is reviewed with respect to the search for a low-energy trajectory to Mars with gravitational assist from Venus for the years 1995-2024. Both Ballistic and Venus-Earth gravity assist (VEGA) trajectories are calculated with an automated design tool by the authors (1990). The trajectories are modeled as conic sections from one gravitating body to the next, and gravity assist is considered to act impulsively. VEGA trajectories to Mars require similar launch energies for 6 years listed and have moderate arrival C3s, with the lowest C3 requirement in 2015. The flight time and arrival energies of the trajectories are found to be larger than those of ballistic trajectories, but the low-energy launch window makes them desirable for unmanned Mars missions, in particular.

Workers install the RTGs on the Cassini spacecraft at LC 40, CCAS

NASA Technical Reports Server (NTRS)

1997-01-01

At Launch Complex 40 on Cape Canaveral Air Station, workers are installing three Radioisotope Thermoelectric Generators (RTGs) on the Cassini spacecraft. RTGs are lightweight, compact spacecraft electrical power systems that have flown successfully on 23 previous U.S. missions over the past 37 years. These generators produce power by converting heat into electrical energy; the heat is provided by the natural radioactive decay of plutonium-238 dioxide, a non-weapons-grade material. RTGs enable spacecraft to operate at significant distances from the Sun where solar power systems would not be feasible. Cassini will travel two billion miles to reach Saturn and another 1.1 billion miles while in orbit around Saturn. Cassini is undergoing final preparations for liftoff on a Titan IVB/Centaur launch vehicle, with the launch window opening at 4:55 a.m. EDT, Oct. 13.

KSC-05PD-0527

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, workers mate the External Tank, at left, to the underside of Space Shuttle Discovery, at right. Each of two aft external tank umbilical plates mate with a corresponding plate on the orbiter. The plates help maintain alignment among the umbilicals. The attach fitting is aft of the nose gear wheel well. Workers next will perform an electrical and mechanical verification of the mated interfaces to verify all critical vehicle connections. A Shuttle interface test is performed using the launch processing system to verify Space Shuttle vehicle interfaces and Space Shuttle vehicle-to-ground interfaces. In approximately one week, Space Shuttle Discovery will be ready for rollout to Launch Pad 39B for Return to Flight mission STS-114. The launch window for STS-114 is May 15 to June 3.

KSC-2014-2206

NASA Image and Video Library

2014-04-18

CAPE CANAVERAL, Fla. - A blinding flash of light under the Falcon 9 rocket signals engine ignition and liftoff of the SpaceX-3 mission from Space Launch Complex 40 on Cape Canaveral Air Force Station, sending the Dragon resupply spacecraft on its way to the International Space Station. Launch was during an instantaneous window at 3:25 p.m. EDT. Dragon is making its fourth trip to the space station. The SpaceX-3 mission, carrying almost 2.5 tons of supplies, technology and science experiments, is the third of 12 flights through a $1.6 billion NASA Commercial Resupply Services contract. Dragon's cargo will support more than 150 experiments that will be conducted during the station's Expeditions 39 and 40. For more information, visit http://www.nasa.gov/mission_pages/station/structure/launch/index.html. Photo credit: NASA/Tony Gray

Tailored plasmon-induced transparency in attenuated total reflection response in a metal-insulator-metal structure.

PubMed

Matsunaga, Kouki; Hirai, Yusuke; Neo, Yoichiro; Matsumoto, Takahiro; Tomita, Makoto

2017-12-19

We demonstrated tailored plasmon-induced transparency (PIT) in a metal (Au)-insulator (SiO 2 )-metal (Ag) (MIM) structure, where the Fano interference between the MIM waveguide mode and the surface plasmon polariton (SPP) resonance mode induced a transparency window in an otherwise opaque wavenumber (k) region. A series of structures with different thicknesses of the Ag layer were prepared and the attenuated total reflection (ATR) response was examined. The height and width of the transparency window, as well as the relevant k-domain dispersion, were controlled by adjusting the Ag layer thickness. To confirm the dependency of PIT on Ag layer thickness, we performed numerical calculations to determine the electric field amplitude inside the layers. The steep k-domain dispersion in the transparency window is capable of creating a lateral beam shift known as the Goos-Hänchen shift, for optical device and sensor applications. We also discuss the Fano interference profiles in a ω - k two-dimensional domain on the basis of Akaike information criteria.

Seismic facies analysis based on self-organizing map and empirical mode decomposition

NASA Astrophysics Data System (ADS)

Du, Hao-kun; Cao, Jun-xing; Xue, Ya-juan; Wang, Xing-jian

2015-01-01

Seismic facies analysis plays an important role in seismic interpretation and reservoir model building by offering an effective way to identify the changes in geofacies inter wells. The selections of input seismic attributes and their time window have an obvious effect on the validity of classification and require iterative experimentation and prior knowledge. In general, it is sensitive to noise when waveform serves as the input data to cluster analysis, especially with a narrow window. To conquer this limitation, the Empirical Mode Decomposition (EMD) method is introduced into waveform classification based on SOM. We first de-noise the seismic data using EMD and then cluster the data using 1D grid SOM. The main advantages of this method are resolution enhancement and noise reduction. 3D seismic data from the western Sichuan basin, China, are collected for validation. The application results show that seismic facies analysis can be improved and better help the interpretation. The powerful tolerance for noise makes the proposed method to be a better seismic facies analysis tool than classical 1D grid SOM method, especially for waveform cluster with a narrow window.

Evidence of an Intermediate Phase in bulk alloy oxide glass sysem

NASA Astrophysics Data System (ADS)

Chakraborty, S.; Boolchand, P.

2011-03-01

Reversibility windows have been observed in modified oxides (alkali-silicates and -germanates) and identified with Intermediate Phases(IPs). Here we find preliminary evidence of an IP in a ternary oxide glass, (B2 O3)5 (Te O2)95-x (V2O5)x , which is composed of network formers. Bulk glasses are synthesized across the 18% x 35 % composition range, and examined in Raman scattering, modulated DSC and molar volume experiments. Glass transition temperatures Tg (x) steadily decrease with V2O5 content x, and reveal the enthalpy of relaxation at Tg to show a global minimum in the 24% x < 27 range, the reversibility window (IP). Molar volumes reveal a minimum in this window. Raman scattering reveals a Boson mode, and at least six other vibrational bands in the 100cm-1 < ν < 1700cm-1 range. Compositional trends in vibrational mode strengths and frequency are established. These results will be presented in relation to glass structure evolution with vanadia content and the underlying elastic phases. Supported by NSF grant DMR 08-53957.

KSC-2009-1529

NASA Image and Video Library

2009-02-10

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, the Ares I-X mock-up crew module displays the newly applied window decals. Ares I-X is the test flight for the Ares I. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I. The launch of full-scale Ares I-X, targeted for July 2009, will be the first in a series of unpiloted rocket launches from Kennedy. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for the astronauts. Photo credit: NASA/Tim Jacobs

KSC-2009-1528

NASA Image and Video Library

2009-02-10

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, a worker applies a window decal on the Ares I-X mock-up crew module. Ares I-X is the test flight for the Ares I. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I. The launch of full-scale Ares I-X, targeted for July 2009, will be the first in a series of unpiloted rocket launches from Kennedy. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for the astronauts. Photo credit: NASA/Tim Jacobs

KSC-2009-1527

NASA Image and Video Library

2009-02-10

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center, a worker applies a window decal on the Ares I-X mock-up crew module. Ares I-X is the test flight for the Ares I. The I-X flight will provide NASA an early opportunity to test and prove hardware, facilities and ground operations associated with Ares I. The launch of full-scale Ares I-X, targeted for July 2009, will be the first in a series of unpiloted rocket launches from Kennedy. When fully developed, the 16-foot diameter crew module will furnish living space and reentry protection for the astronauts. Photo credit: NASA/Tim Jacobs

KSC-05PD-1030

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. An overhead crane lowers the External Tank that will be used to return the Space Shuttle program to flight into high bay 3 in the Vehicle Assembly Building. The tank, ET-121, and the Solid Rocket Boosters were originally scheduled to fly with orbiter Atlantis on mission STS-121 but will now be used to launch Discovery on mission STS-114. Once secure in the high bay, a new heater will be added to the feedline bellows to minimize the potential for ice and frost buildup. STS-114 is the first Return to Flight mission to the International Space Station. The launch window extends from July 13 through July 31.

KSC-05PD-1082

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Complex 39B, a technician in Space Shuttle Discovery's payload bay studies a photo of the retract link assembly on the orbiter's main landing gear door prior to conducting a borescope inspection. The inspection is a precautionary measure after a small crack was found in a retract link assembly on the right-hand main landing gear on orbiter Atlantis. An initial review of the closeout photos of the link assembly on Discovery did not reveal any cracks. Discovery is scheduled to return the Space Shuttle fleet to operational status on mission STS-114. This additional work does not impact the launch planning window of July 13-31.

STS-29 Discovery, OV-103, crew on flight deck prepares for reentry

NASA Image and Video Library

1989-03-18

STS029-24-004 (18 March 1989) --- STS-29 crewmembers, wearing launch and entry suits (LESs) and launch and entry helmets (LEHs), review checklists on Discovery, Orbiter Vehicle (OV) 103, flight deck. Commander Michael L. Coats is seated at the forward flight deck commanders station with Mission Specialist (MS) James F. Buchli on aft flight deck strapped in mission specialist seat. OV-103 makes its return after five days in space. Note color in forward windows W1, W2, W3 caused by friction of entry through the Earth's atmosphere. Personal Egress Air Pack (PEAP) is visible on pilots seat back.

KSC-05PD-1077

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Complex 39B, technicians construct a platform in Space Shuttle Discovery's payload bay to support an upcoming borescope inspection of the retract link assembly on the orbiter's main landing gear door. The inspection is a precautionary measure after a small crack was found in a retract link assembly on the right-hand main landing gear on orbiter Atlantis. An initial review of the closeout photos of the link assembly on Discovery did not reveal any cracks. Discovery is scheduled to return the Space Shuttle fleet to operational status on mission STS-114. This additional work does not impact the launch planning window of July 13-31.

KSC-2013-2485

NASA Image and Video Library

2013-05-29

VANDENBERG AFB, Calif. - An Orbital Sciences Pegasus XL rocket undergoes launch preparations inside a hangar at Vandenberg Air Force Base for NASA's IRIS mission, short for Interface Region Imaging Spectrograph. Scheduled for launch from Vandenberg June 26, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun’s corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. Photo credit: NASA/Randy Beaudoin

KSC-2013-2486

NASA Image and Video Library

2013-05-29

VANDENBERG AFB, Calif. - An Orbital Sciences Pegasus XL rocket undergoes launch preparations inside a hangar at Vandenberg Air Force Base for NASA's IRIS mission, short for Interface Region Imaging Spectrograph. Scheduled for launch from Vandenberg June 26, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun’s corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. Photo credit: NASA/Randy Beaudoin

KSC-97pc139

NASA Image and Video Library

1997-01-12

STS-81 Mission Specialist Peter J. K. "Jeff" Wisoff prepares for the fifth ShuttleMir docking as he waits in the Operations and Checkout (O&C) Building for the operation to fit him into his launch/entry suit to be completed. He conducted a spacewalk on his on his first Shuttle mission, STS57 and holds a doctorate degree in applied physics with an emphasis on lasers and semiconductor materials. He and five crew members will shortly depart the O&C and head for Launch Pad 39B, where the Space Shuttle Atlantis will lift off during a 7-minute window that opens at 4:27 a.m. EST, January 12

KSC-97pc133

NASA Image and Video Library

1997-01-12

The STS-81 flight crew enjoys the traditional preliftoff breakfast in the crew quarters of the Operations and Checkout Building. They are (from left) Mission Specialist Marsha S. Ivins, Mission Commander Michael A. Baker; Pilot Brent W. Jett, Jr.; and Mission Specialists John M. Grunsfeld, Peter J. K. "Jeff" Wisoff; and J.M. "Jerry" Linenger. After a weather briefing, the flight crew will be fitted with their launch/entry suits and depart for Launch Pad 39B. Once there, they will take their positions in the crew cabin of the Space Shuttle Atlantis to await a liftoff during a seven-minute window that will open at 4:27 a.m. EST, January 12

KSC-05PD-1080

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Complex 39B, technicians construct a platform in Space Shuttle Discovery's payload bay to support an upcoming borescope inspection of the retract link assembly on the orbiter's main landing gear door. The inspection is a precautionary measure after a small crack was found in a retract link assembly on the right-hand main landing gear on orbiter Atlantis. An initial review of the closeout photos of the link assembly on Discovery did not reveal any cracks. Discovery is scheduled to return the Space Shuttle fleet to operational status on mission STS-114. This additional work does not impact the launch planning window of July 13-31.

KSC-97pc138

NASA Image and Video Library

1997-01-12

STS-81 Mission Commander Michael A. Baker is assisted into his launch/entry suit in the Operations and Checkout (O&C) Building. Baker is on his fourth space flight and will have responsibility for the 10-day mission, including the intricate docking and undocking maneuvers with the Russian Mir space station. He will also be in charge of two in-flight Risk Mitigation experiments and be the subject of a Human Life Sciences experiment. He and five crew members will shortly depart the O&C and head for Launch Pad 39B, where the Space Shuttle Atlantis will lift off during a 7-minute window that opens at 4:27 a.m. EST, January 12

KSC-05PD-1079

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Complex 39B, technicians construct a platform in Space Shuttle Discovery's payload bay to support an upcoming borescope inspection of the retract link assembly on the orbiter's main landing gear door. The inspection is a precautionary measure after a small crack was found in a retract link assembly on the right-hand main landing gear on orbiter Atlantis. An initial review of the closeout photos of the link assembly on Discovery did not reveal any cracks. Discovery is scheduled to return the Space Shuttle fleet to operational status on mission STS-114. This additional work does not impact the launch planning window of July 13-31.

STS-81 Mission Specialist Peter Wisoff suits up

NASA Technical Reports Server (NTRS)

1997-01-01

STS-81 Mission Specialist Peter J. K. 'Jeff' Wisoff prepares for the fifth Shuttle- Mir docking as he waits in the Operations and Checkout (O&C) Building for the operation to fit him into his launch/entry suit to be completed. He conducted a spacewalk on his on his first Shuttle mission, STS- 57 and holds a doctorate degree in applied physics with an emphasis on lasers and semiconductor materials. He and five crew members will shortly depart the O&C and head for Launch Pad 39B, where the Space Shuttle Atlantis will lift off during a 7-minute window that opens at 4:27 a.m. EST, January 12.

KSC-05PD-1085

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Complex 39B, technicians in Space Shuttle Discovery's payload bay monitor the images received during a borescope inspection of the retract link assembly on the orbiter's main landing gear door. The inspection is a precautionary measure after a small crack was found in a retract link assembly on the right-hand main landing gear on orbiter Atlantis. An initial review of the closeout photos of the link assembly on Discovery did not reveal any cracks. Discovery is scheduled to return the Space Shuttle fleet to operational status on mission STS-114. This additional work does not impact the launch planning window of July 13-31.

KSC-05PD-1084

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At Launch Complex 39B, a technician in Space Shuttle Discovery's payload bay performs a borescope inspection of the retract link assembly on the orbiter's main landing gear door. The inspection is a precautionary measure after a small crack was found in a retract link assembly on the right-hand main landing gear on orbiter Atlantis. An initial review of the closeout photos of the link assembly on Discovery did not reveal any cracks. Discovery is scheduled to return the Space Shuttle fleet to operational status on mission STS-114. This additional work does not impact the launch planning window of July 13-31.

General Dynamic (GD) Launch Waveform On-Orbit Performance Report

NASA Technical Reports Server (NTRS)

Briones, Janette C.; Shalkhauser, Mary Jo

2014-01-01

The purpose of this report is to present the results from the GD SDR on-orbit performance testing using the launch waveform over TDRSS. The tests include the evaluation of well-tested waveform modes, the operation of RF links that are expected to have high margins, the verification of forward return link operation (including full duplex), the verification of non-coherent operational models, and the verification of radio at-launch operational frequencies. This report also outlines the launch waveform tests conducted and comparisons to the results obtained from ground testing.

An unmanned probe to Pluto

NASA Technical Reports Server (NTRS)

1990-01-01

Now that Voyager II has completed its grand tour of the solar system, all the planets in the solar system, with the exception of Pluto, have been studied. Even now, missions to return to Mercury, Venus, Mars Jupiter, and Saturn are currently flying or are planned. However, a mission to explore Pluto is not, at the present time, being considered seriously. The design problem presented to the students was very general, i.e., design an unmanned mission to Pluto with a launch window constraint of the years 2000 to 2010. All other characteristics of the mission, such as mission type (flyby, orbiter, lander, penetrator), scientific objectives and payload, and the propulsion system were to be determined by the design teams. The design studies exposed several general problems to be solved. Due to the extreme distance to Pluto (and a corresponding travel time in the range of 10 to 25 years), the spacecraft had to be lighter and more robust than current spacecraft designs. In addition, advanced propulsion concepts had to be considered. These included the new generation of launch vehicles and upper stages and nuclear electric propulsion. The probe design offered an abundance of synthesis and analysis problems. These included sizing trade studies, selection of subsystem components, analysis of spacecraft dynamics, stability and control, structural design and material selection, trajectory design, and selection of scientific equipment. Since the characteristics of the mission, excluding the launch window, were to be determined by the design teams, the solutions varied widely.

A High-Spin Rate Measurement Method for Projectiles Using a Magnetoresistive Sensor Based on Time-Frequency Domain Analysis

PubMed Central

Shang, Jianyu; Deng, Zhihong; Fu, Mengyin; Wang, Shunting

2016-01-01

Traditional artillery guidance can significantly improve the attack accuracy and overall combat efficiency of projectiles, which makes it more adaptable to the information warfare of the future. Obviously, the accurate measurement of artillery spin rate, which has long been regarded as a daunting task, is the basis of precise guidance and control. Magnetoresistive (MR) sensors can be applied to spin rate measurement, especially in the high-spin and high-g projectile launch environment. In this paper, based on the theory of a MR sensor measuring spin rate, the mathematical relationship model between the frequency of MR sensor output and projectile spin rate was established through a fundamental derivation. By analyzing the characteristics of MR sensor output whose frequency varies with time, this paper proposed the Chirp z-Transform (CZT) time-frequency (TF) domain analysis method based on the rolling window of a Blackman window function (BCZT) which can accurately extract the projectile spin rate. To put it into practice, BCZT was applied to measure the spin rate of 155 mm artillery projectile. After extracting the spin rate, the impact that launch rotational angular velocity and aspect angle have on the extraction accuracy of the spin rate was analyzed. Simulation results show that the BCZT TF domain analysis method can effectively and accurately measure the projectile spin rate, especially in a high-spin and high-g projectile launch environment. PMID:27322266