Sample records for fully stacked shuttle
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Shuttle Boosters stacked in the VAB
2007-01-04
Workers continue stacking the solid rocket boosters in highbay 1 inside Kennedy Space Center's Vehicle Assembly Building. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007.
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Shuttle Boosters stacked in the VAB
2007-01-04
Workers continue stacking the twin solid rocket boosters in highbay 1 inside Kennedy Space Center's Vehicle Assembly Building. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007.
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Shuttle Boosters stacked in the VAB
2007-01-04
Lighting inside Kennedy Space Center's Vehicle Assembly Building seems to bathe the highbay 1 area in a golden hue as workers continue stacking the twin solid rocket boosters. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007.
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1978-09-01
This photograph shows stacking of the left side of the solid rocket booster (SRB) segments in the Dynamic Test Stand at the east test area of the Marshall Space Flight Center (MSFC). Staging shown here are the aft skirt, aft segment, and aft center segment. The SRB was attached to the external tank (ET) and then the orbiter later for the Mated Vertical Ground Vibration Test (MVGVT), that resumed in October 1978. The stacking of a complete Shuttle in the Dynamic Test Stand allowed test engineers to perform ground vibration testing on the Shuttle in its liftoff configuration. The purpose of the MVGVT is to verify that the Space Shuttle would perform as predicted during launch. The platforms inside the Dynamic Test Stand were modified to accommodate two SRB's to which the ET was attached.
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1978-09-01
Workmen in the Dynamic Test Stand lowered the nose cone into place to complete stacking of the left side of the solid rocket booster (SRB) in the Dynamic Test Stand at the east test area of the Marshall Space Flight Center (MSFC). The SRB would be attached to the external tank (ET) and then the orbiter later for the Mated Vertical Ground Vibration Test (MVGVT), that resumed in October 1978. The stacking of a complete Shuttle in the Dynamic Test Stand allowed test engineers to perform ground vibration testing on the Shuttle in its liftoff configuration. The purpose of the MVGVT was to verify that the Space Shuttle would perform as predicted during launch. The platforms inside the Dynamic Test Stand were modified to accommodate two SRB'S to which the ET was attached.
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Proton Exchange Membrane (PEM) fuel Cell for Space Shuttle
NASA Technical Reports Server (NTRS)
Hoffman, William C., III; Vasquez, Arturo; Lazaroff, Scott M.; Downey, Michael G.
1999-01-01
Development of a PEM fuel cell powerplant (PFCP) for use in the Space Shuttle offers multiple benefits to NASA. A PFCP with a longer design life than is delivered currently from the alkaline fuel will reduce Space Shuttle Program maintenance costs. A PFCP compatible with zero-gravity can be adapted for future NASA transportation and exploration programs. Also, the commercial PEM fuel cell industry ensures a competitive environment for select powerplant components. Conceptual designs of the Space Shuttle PFCP have resulted in identification of key technical areas requiring resolution prior to development of a flight system. Those technical areas include characterization of PEM fuel cell stack durability under operational conditions and water management both within and external to the stack. Resolution of the above issues is necessary to adequately control development, production, and maintenance costs for a PFCP.
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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
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Research and Development of Fully Automatic Alien Smoke Stack and Packaging System
NASA Astrophysics Data System (ADS)
Yang, Xudong; Ge, Qingkuan; Peng, Tao; Zuo, Ping; Dong, Weifu
2017-12-01
The problem of low efficiency of manual sorting packaging for the current tobacco distribution center, which developed a set of safe efficient and automatic type of alien smoke stack and packaging system. The functions of fully automatic alien smoke stack and packaging system adopt PLC control technology, servo control technology, robot technology, image recognition technology and human-computer interaction technology. The characteristics, principles, control process and key technology of the system are discussed in detail. Through the installation and commissioning fully automatic alien smoke stack and packaging system has a good performance and has completed the requirements for shaped cigarette.
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Atlantis is lowered to external stack in the VAB
NASA Technical Reports Server (NTRS)
2001-01-01
KENNEDY SPACE CENTER, Fla. -- In Vehicle Assembly Building high bay 1, the orbiter Atlantis is being lowered into position for mating to its external tank/solid rocket booster stack. Space Shuttle Atlantis is scheduled to launch on mission STS-104 in early July.
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NASA Technical Reports Server (NTRS)
Zhu, Ji-Xiang; Chaikin, P. M.; Li, Min; Russel, W. B.; Ottewill, R. H.; Rogers, R.; Meyer, W. V.
1998-01-01
Classical hard spheres have long served as a paradigm for our understanding of the structure of liquids, crystals, and glasses and the transitions between these phases. Ground-based experiments have demonstrated that suspensions of uniform polymer colloids are near-ideal physical realizations of hard spheres. However, gravity appears to play a significant and unexpected role in the formation and structure of these colloidal crystals. In the microgravity environment of the Space Shuttle, crystals grow purely via random stacking of hexagonal close-packed planes, lacking any of the face-centered cubic (FCC) component evident in crystals grown in 1 g beyond melting and allowed some time to settle. Gravity also masks 33-539 the natural growth instabilities of the hard sphere crystals which exhibit striking dendritic arms when grown in microgravity. Finally, high volume fraction "glass" samples which fail to crystallize after more than a year in 1 g begin nucleation after several days and fully crystallize in less than 2 weeks on the Space Shuttle.
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Characterization of the Space Shuttle Ascent Debris using CFD Methods
NASA Technical Reports Server (NTRS)
Murman, Scott M.; Aftosmis, Michael J.; Rogers, Stuart E.
2005-01-01
After video analysis of space shuttle flight STS-107's ascent showed that an object shed from the bipod-ramp region impacted the left wing, a transport analysis was initiated to determine a credible flight path and impact velocity for the piece of debris. This debris transport analysis was performed both during orbit, and after the subsequent re-entry accident. The analysis provided an accurate prediction of the velocity a large piece of foam bipod ramp would have as it impacted the wing leading edge. This prediction was corroborated by video analysis and fully-coupled CFD/six degree of freedom (DOF) simulations. While the prediction of impact velocity was accurate enough to predict critical damage in this case, one of the recommendations of the Columbia Accident Investigation Board (CAIB) for return-to-flight (RTF) was to analyze the complete debris environment experienced by the shuttle stack on ascent. This includes categorizing all possible debris sources, their probable geometric and aerodynamic characteristics, and their potential for damage. This paper is chiefly concerned with predicting the aerodynamic characteristics of a variety of potential debris sources (insulating foam and cork, nose-cone ablator, ice, ...) for the shuttle ascent configuration using CFD methods. These aerodynamic characteristics are used in the debris transport analysis to predict flight path, impact velocity and angle, and provide statistical variation to perform risk analyses where appropriate. The debris aerodynamic characteristics are difficult to determine using traditional methods, such as static or dynamic test data, due to the scaling requirements of simulating a typical debris event. The use of CFD methods has been a critical element for building confidence in the accuracy of the debris transport code by bridging the gap between existing aerodynamic data and the dynamics of full-scale, in-flight events.
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2010-09-20
NEW ORLEANS -- The Space Shuttle Program's last external fuel tank, ET-122, is loaded onto the Pegasus Barge at NASA's Michoud Assembly Facility in New Orleans. The tank will travel 900 miles to NASA's Kennedy Space Center in Florida where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2011-05-20
CAPE CANAVERAL, Fla. -- NASA's Gravity Recovery and Interior Laboratory, or GRAIL, spacecraft is offloaded from an Air Force C-17 cargo plane on the Shuttle Landing Facility at Kennedy Space Center in Florida. The spacecraft traveled from the Lockheed Martin plant in Denver, Colo., and will undergo further processing in the Astrotech payload processing facility in Titusville, Fla. The United Launch Alliance Delta II rocket that will carry GRAIL into lunar orbit already is fully stacked at NASA's Space Launch Complex 17B and launch is scheduled for Sept. 8. The GRAIL mission is a part of NASA's Discovery Program. GRAIL will fly twin spacecraft in tandem orbits around the moon for several months to measure its gravity field. The mission also will answer longstanding questions about Earth's moon and provide scientists a better understanding of how Earth and other rocky planets in the solar system formed. For more information, visit http://science.nasa.gov/missions/grail/. Photo credit: NASA/Dimitri Gerondidakis
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2011-05-20
CAPE CANAVERAL, Fla. -- NASA's Gravity Recovery and Interior Laboratory, or GRAIL, spacecraft is offloaded from an Air Force C-17 cargo plane on the Shuttle Landing Facility at Kennedy Space Center in Florida. The spacecraft traveled from the Lockheed Martin plant in Denver, Colo., and will undergo further processing in the Astrotech payload processing facility in Titusville, Fla. The United Launch Alliance Delta II rocket that will carry GRAIL into lunar orbit already is fully stacked at NASA's Space Launch Complex 17B and launch is scheduled for Sept. 8. The GRAIL mission is a part of NASA's Discovery Program. GRAIL will fly twin spacecraft in tandem orbits around the moon for several months to measure its gravity field. The mission also will answer longstanding questions about Earth's moon and provide scientists a better understanding of how Earth and other rocky planets in the solar system formed. For more information, visit http://science.nasa.gov/missions/grail/. Photo credit: NASA/Dimitri Gerondidakis
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2011-05-20
CAPE CANAVERAL, Fla. -- NASA's Gravity Recovery and Interior Laboratory, or GRAIL, spacecraft will be offloaded from an Air Force C-17 cargo plane on the Shuttle Landing Facility at Kennedy Space Center in Florida. The spacecraft traveled from the Lockheed Martin plant in Denver, Colo., and will undergo further processing in the Astrotech payload processing facility in Titusville, Fla. The United Launch Alliance Delta II rocket that will carry GRAIL into lunar orbit already is fully stacked at NASA's Space Launch Complex 17B and launch is scheduled for Sept. 8. The GRAIL mission is a part of NASA's Discovery Program. GRAIL will fly twin spacecraft in tandem orbits around the moon for several months to measure its gravity field. The mission also will answer longstanding questions about Earth's moon and provide scientists a better understanding of how Earth and other rocky planets in the solar system formed. For more information, visit http://science.nasa.gov/missions/grail/. Photo credit: NASA/Dimitri Gerondidakis
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2011-05-20
CAPE CANAVERAL, Fla. -- NASA's Gravity Recovery and Interior Laboratory, or GRAIL, spacecraft will be offloaded from an Air Force C-17 cargo plane on the Shuttle Landing Facility at Kennedy Space Center in Florida. The spacecraft traveled from the Lockheed Martin plant in Denver, Colo., and will undergo further processing in the Astrotech payload processing facility in Titusville, Fla. The United Launch Alliance Delta II rocket that will carry GRAIL into lunar orbit already is fully stacked at NASA's Space Launch Complex 17B and launch is scheduled for Sept. 8. The GRAIL mission is a part of NASA's Discovery Program. GRAIL will fly twin spacecraft in tandem orbits around the moon for several months to measure its gravity field. The mission also will answer longstanding questions about Earth's moon and provide scientists a better understanding of how Earth and other rocky planets in the solar system formed. For more information, visit http://science.nasa.gov/missions/grail/. Photo credit: NASA/Dimitri Gerondidakis
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2011-05-20
CAPE CANAVERAL, Fla. -- NASA's Gravity Recovery and Interior Laboratory, or GRAIL, spacecraft will be offloaded from an Air Force C-17 cargo plane on the Shuttle Landing Facility at Kennedy Space Center in Florida. The spacecraft traveled from the Lockheed Martin plant in Denver, Colo., and will undergo further processing in the Astrotech payload processing facility in Titusville, Fla. The United Launch Alliance Delta II rocket that will carry GRAIL into lunar orbit already is fully stacked at NASA's Space Launch Complex 17B and launch is scheduled for Sept. 8. The GRAIL mission is a part of NASA's Discovery Program. GRAIL will fly twin spacecraft in tandem orbits around the moon for several months to measure its gravity field. The mission also will answer longstanding questions about Earth's moon and provide scientists a better understanding of how Earth and other rocky planets in the solar system formed. For more information, visit http://science.nasa.gov/missions/grail/. Photo credit: NASA/Dimitri Gerondidakis
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2011-05-20
CAPE CANAVERAL, Fla. -- NASA's Gravity Recovery and Interior Laboratory, or GRAIL, spacecraft is offloaded from an Air Force C-17 cargo plane on the Shuttle Landing Facility at Kennedy Space Center in Florida. The spacecraft traveled from the Lockheed Martin plant in Denver, Colo., and will undergo further processing in the Astrotech payload processing facility in Titusville, Fla. The United Launch Alliance Delta II rocket that will carry GRAIL into lunar orbit already is fully stacked at NASA's Space Launch Complex 17B and launch is scheduled for Sept. 8. The GRAIL mission is a part of NASA's Discovery Program. GRAIL will fly twin spacecraft in tandem orbits around the moon for several months to measure its gravity field. The mission also will answer longstanding questions about Earth's moon and provide scientists a better understanding of how Earth and other rocky planets in the solar system formed. For more information, visit http://science.nasa.gov/missions/grail/. Photo credit: NASA/Dimitri Gerondidakis
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2011-05-20
CAPE CANAVERAL, Fla. -- NASA's Gravity Recovery and Interior Laboratory, or GRAIL, spacecraft is offloaded from an Air Force C-17 cargo plane on the Shuttle Landing Facility at Kennedy Space Center in Florida. The spacecraft traveled from the Lockheed Martin plant in Denver, Colo., and will undergo further processing in the Astrotech payload processing facility in Titusville, Fla. The United Launch Alliance Delta II rocket that will carry GRAIL into lunar orbit already is fully stacked at NASA's Space Launch Complex 17B and launch is scheduled for Sept. 8. The GRAIL mission is a part of NASA's Discovery Program. GRAIL will fly twin spacecraft in tandem orbits around the moon for several months to measure its gravity field. The mission also will answer longstanding questions about Earth's moon and provide scientists a better understanding of how Earth and other rocky planets in the solar system formed. For more information, visit http://science.nasa.gov/missions/grail/. Photo credit: NASA/Dimitri Gerondidakis
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NASA Technical Reports Server (NTRS)
1973-01-01
A fuel cell technology program was established to advance the state-of-the-art of hydrogen-oxygen fuel cells using low temperature, potassium hydroxide electrolyte technology as the base. Program tasks are described consisting of baseline cell design and stack testing, hydrogen pump design and testing, and DM-2 powerplant testing and technology extension efforts. A baseline cell configuration capable of a minimum of 2000 hours of life was defined. A 6-cell prototype stack, incorporating most of the scheme cell features, was tested for a total of 10,497 hours. A 6-cell stack incorporating all of the design features was tested. The DM-2 powerplant with a 34 cell stack, an accessory section packaged in the basic configuration anticipated for the space shuttle powerplant and a powerplant control unit, was defined, assembled, and tested. Cells were used in the stack and a drag-type hydrogen pump was installed in the accessory section. A test program was established, in conjunction with NASA/JSC, based on space shuttle orbiter mission. A 2000-hour minimum endurance test and a 5000-hour goal were set and the test started on August 8, 1972. The 2000-hour milestone was completed on November 3, 1972. On 13 March 1973, at the end of the thirty-first simulated seven-day mission and 5072 load hours, the test was concluded, all goals having been met. At this time, the DM-2 was in excellent condition and capable of additional endurance.
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2010-09-20
NEW ORLEANS -- Workers escort the Space Shuttle Program's last external fuel tank, ET-122, to the Pegasus Barge at NASA's Michoud Assembly Facility in New Orleans. The tank will travel 900 miles aboard the Pegasus Barge to NASA's Kennedy Space Center in Florida where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2010-12-29
CAPE CANAVERAL, Fla. -- Inside the intertank of space shuttle Discovery's external fuel tank, a technician holds the film used to project computed radiography scans. The shuttle stack, consisting of the shuttle, external tank and solid rocket boosters, was moved from Launch Pad 39A to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida so technicians could examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank and re-apply foam insulation. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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Operating Deflection Shapes for the Space Shuttle Partial Stack Rollout
NASA Technical Reports Server (NTRS)
Buehrle, Ralph D.; Kappus, Kathy
2005-01-01
In November of 2003 a rollout test was performed to gain a better understanding of the dynamic environment for the Space Shuttle during transportation from the Vehicle Assembly Building to the launch pad. This was part of a study evaluating the methodology for including the rollout dynamic loads in the Space Shuttle fatigue life predictions. The rollout test was conducted with a partial stack consisting of the Crawler Transporter, Mobile Launch Platform, and the Solid Rocket Boosters with an interconnecting crossbeam. Instrumentation included over 100 accelerometers. Data was recorded for steady state speeds, start-ups and stops, and ambient wind excitations with the vehicle at idle. This paper will describe the operating deflection shape analysis performed using the measured acceleration response data. The response data for the steady state speed runs were dominated by harmonics of the forcing frequencies, which were proportional to the vehicle speed. Assuming a broadband excitation for the wind, analyses of the data sets with the vehicle at idle were used to estimate the natural frequencies and corresponding mode shapes. Comparisons of the measured modal properties with numerical predictions are presented.
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2008-02-12
KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building, space shuttle Endeavour is lowered into high bay 1 toward the external tank and solid rocket boosters already stacked on the mobile launcher platform. The stacking is in preparation for launch on the STS-123 mission, targeted for March 11. The mission will deliver the first section of the Japan Aerospace Exploration Agency's Kibo laboratory and the Canadian Space Agency's two-armed robotic system, Dextre. Photo credit: NASA/Dimitri Gerondidakis
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1977-11-18
This photograph shows Solid Rocket Booster segments undergoing stacking operations in Marshall Space Flight Center's Building 4707. The Solid Rocket Boosters were designed in-house at the Marshall Center with the Thiokol Corporation as the prime contractor.
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NASA Technical Reports Server (NTRS)
Helms, W. Jason; Pohlkamp, Kara M.
2011-01-01
The Space Shuttle does not dock at an exact 90 degrees to the International Space Station (ISS) x-body axis. This offset from 90 degrees, along with error sources within their respective attitude knowledge, causes the two vehicles to never completely agree on their attitude, even though they operate as a single, mated stack while docked. The docking offset can be measured in flight when both vehicles have good attitude reference and is a critical component in calculations to transfer attitude reference from one vehicle to another. This paper will describe how the docking offset and attitude reference errors between both vehicles are measured and how this information would be used to recover Shuttle attitude reference from ISS in the event of multiple failures. During STS-117, ISS on-board Guidance, Navigation and Control (GNC) computers began having problems and after several continuous restarts, the systems failed. The failure took the ability for ISS to maintain attitude knowledge. This paper will also demonstrate how with knowledge of the docking offset, the contingency procedure to recover Shuttle attitude reference from ISS was reversed in order to provide ISS an attitude reference from Shuttle. Finally, this paper will show how knowledge of the docking offset can be used to speed up attitude control handovers from Shuttle to ISS momentum management. By taking into account the docking offset, Shuttle can be commanded to hold a more precise attitude which better agrees with the ISS commanded attitude such that start up transients with the ISS momentum management controllers are reduced. By reducing start-up transients, attitude control can be transferred from Shuttle to ISS without the use of ISS thrusters saving precious on-board propellant, crew time and minimizing loads placed upon the mated stack.
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Waelès, Philip; Fournel-Marotte, Karine; Coutrot, Frédéric
2017-08-25
This paper reports on the synthesis of a tri-stable [2]rotaxane molecular shuttle, in which the motion of the macrocycle is triggered by either selective protonation/deprotonation or specific carbamoylation/decarbamoylation of an alkylbenzylamine. The threaded axle is surrounded by a dibenzo[24]crown[8] (DB24C8) macrocycle and contains three sites of different binding affinities towards the macrocycle. An N-methyltriazolium moiety acts as a molecular station that has weak affinity for the DB24C8 macrocycle and is located in the centre of the molecular axle. Two other molecular stations, arylammonium and alkylbenzylammonium moieties, sit on either side of the triazolium moiety along the molecular axle and have stronger affinities for the DB24C8 macrocycle. These two ammonium moieties are covalently linked to two different stopper groups at each extremity of the thread: a tert-butylphenyl group and a substituted DB24C8 unit. Owing to steric hindrance, the former does not allow any π-π stacking interactions with the encircling DB24C8 macrocycle, whereas the latter residue does; therefore, this allows the discrimination of the two ammonium stations by the surrounding DB24C8 macrocycle in the fully protonated state. In the deprotonated state, the contrasting reactivity of the amine functional groups, as either a base or a nucleophile, allows for selective reactions that trigger the controlled shuttling of the macrocycle around the three molecular stations. © 2017 Wiley-VCH Verlag GmbH & Co. KGaA, Weinheim.
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Space Shuttle Orbiter Atlantis Liquid Oxygen Prevalve Detent Roller Cracking Investigation
NASA Technical Reports Server (NTRS)
Holleman, Elizabeth; Eddleman, David; Richard, James; Jacobs, Rebecca
2008-01-01
During routine inspections of the Space Shuttle's Main Propulsion System (MPS) Liquid Oxygen (LO2) pre-valve, the mechanism provided to maintain the valve in the open position was found cracked. The mechanism is a Vespel roller held against the valve visor by a stack of Belleville springs. The roller has been found cracked 3 times. All three instances were in the same valve in the same location. There are 6 pre-valves on each orbiter, and only one has exhibited this problem. Every-flight inspections were instituted and the rollers were found to be cracked after only one flight. Engineers at Marshall Space Flight Center, Johnson Space Center and Kennedy Space Center worked together to determine a solution. There were several possible contributors to the failure: a mis-aligned visor, an out of specification edge with a sharp radius, an out of specification tolerance stack up of a Belleville spring stack that caused un-predicted loads on the Vespel SP-21 roller, and a dimple machined into the side of the roller to indicate LO2 compatibility that created a stress riser. The detent assembly was removed and replaced with parts that were on the low-side of the tolerance stack up to eliminate the potential for high loads on the detent roller. After one flight, the roller was inspected and showed fewer signs of wear and no cracks.
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Space Shuttle Orbiter Atlantis Liquid Oxygen Pre-Valve Detent Roller Cracking Investigation
NASA Technical Reports Server (NTRS)
Holleman, Elizabeth; Eddleman, David; Jacobs, Rebecca; Richard, James
2008-01-01
During routine inspections of the Space Shuttle s Main Propulsion System Liquid Oxygen (LO2) pre-valve, the mechanism provided to maintain the valve in the open position was found cracked. The mechanism is a Vespel roller held against the valve visor by a stack of Belleville springs. The roller has been found cracked 3 times. All three instances were in the same valve in the same location. There are 6 pre-valves on each orbiter, and only one has exhibited this problem. Every-flight inspections were instituted and the rollers were found to be cracked after only one flight. Engineers at Marshall Space Flight Center, Johnson Space Center, and Kennedy Space Center worked together to determine a solution. There were several possible contributors to the failure: a misaligned visor, an out-of-specification edge with a sharp radius, an out-of-specification tolerance stack up of a Belleville spring stack that caused un-predicted loads on the Vespel SP-21 roller, and a dimple machined into the side of the roller to indicate LO2 compatibility that created a stress riser. The detent assembly was removed and replaced with parts that were on the low side of the tolerance stack up to eliminate the potential for high loads on the detent roller. After one flight, the roller was inspected and showed fewer signs of wear and no cracks.
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Protonmotive force: development of electrostatic drivers for synthetic molecular motors.
Crowley, James D; Steele, Ian M; Bosnich, Brice
2006-12-04
Ferrocene has been investigated as a platform for developing protonmotive electrostatic drivers for molecular motors. When two 3-pyridine groups are substituted to the (rapidly rotating) cyclopentadienyl (Cp) rings of ferrocene, one on each Cp, it is shown that the (Cp) eclipsed, pi-stacked rotameric conformation is preferred both in solution and in the solid state. Upon quaternization of both of the pyridines substituents, either by protonation or by alkylation, it is shown that the preferred rotameric conformation is one where the pyridinium groups are rotated away from the fully pi-stacked conformation. Electrostatic calculations indicate that the rotation is caused by the electrostatic repulsion between the charges. Consistently, when the pi-stacking energy is increased pi-stacked population increases, and conversely when the electrostatic repulsion is increased pi-stacked population is decreased. This work serves to provide an approximate estimate of the amount of torque that the electrostatically driven ferrocene platform can generate when incorporated into a molecular motor. The overall conclusion is that the electrostatic interaction energy between dicationic ferrocene dipyridyl systems is similar to the pi-stacking interaction energy and, consequently, at least tricationic systems are required to fully uncouple the pi-stacked pyridine substituents.
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2010-09-20
NEW ORLEANS -- Workers at NASA's Michoud Assembly Facility in New Orleans prepare the Space Shuttle Program's last external fuel tank, ET-122, for transportation to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea secured aboard the Pegasus Barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-21
NEW ORLEANS -- At NASA's Michoud Assembly Facility in New Orleans the Space Shuttle Program's last external fuel tank, ET-122, is ready for transportation to NASA's Kennedy Space Center in Florida. Secured aboard the Pegasus Barge the tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-28
CAPE CANAVERAL, Fla. -- The Space Shuttle Program's last external fuel tank, ET-122, moves from the Turn Basin to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Once inside the Vehicle Assembly Building, it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-22
LOUISIANA -- In Gulfport, La., workers connect the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, to Freedom Star, NASA's solid rocket booster retrieval ship. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-28
CAPE CANAVERAL, Fla. -- The Space Shuttle Program's last external fuel tank, ET-122, moves from the Turn Basin to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Once inside the Vehicle Assembly Building, it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-21
NEW ORLEANS -- A tug boat is pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-28
CAPE CANAVERAL, Fla. -- The Space Shuttle Program's last external fuel tank, ET-122, enters the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans to Kennedy's Turn Basin aboard the Pegasus Barge. The tank eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-20
NEW ORLEANS -- Workers escort the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans onto the Pegasus Barge. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-28
CAPE CANAVERAL, Fla. -- The Space Shuttle Program's last external fuel tank, ET-122, moves from the Turn Basin to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Once inside the Vehicle Assembly Building, it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-21
NEW ORLEANS -- A tug boat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-20
NEW ORLEANS -- Workers escort the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans for transportation to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea secured aboard the Pegasus Barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-28
CAPE CANAVERAL, Fla. -- The Space Shuttle Program's last external fuel tank, ET-122, has been moved inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans to Kennedy's Turn Basin aboard the Pegasus Barge. The tank eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-28
CAPE CANAVERAL, Fla. -- The Space Shuttle Program's last external fuel tank, ET-122, moves into the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans to Kennedy's Turn Basin aboard the Pegasus Barge. The tank eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2007-07-03
KENNEDY SPACE CENTER, FLA. -- The main engines on the orbiter Endeavour (upper right) are seen as Endeavour is lowered into high bay 1 of the Vehicle Assembly Building for stacking with the external tank (seen at left) and solid rocket boosters on the mobile launcher platform. Endeavour will be launched on mission STS-118, its first flight in more than four years. The shuttle has undergone extensive modifications, including the addition of safety upgrades already added to shuttles Discovery and Atlantis. Endeavour also features new hardware, such as the Station-to-Shuttle Power Transfer System that will allow the docked shuttle to draw electrical power from the station and extend its visits to the orbiting lab. Endeavour is targeted for launch on Aug. 7. Photo credit: NASA/Troy Cryder
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2000-06-01
KENNEDY SPACE CENTER, FLA. -- A crawler-transporter with mobile launcher platform on top tests the buried portion of the Apollo-era crawlerway leading to the Vehicle Assembly Building (VAB) high bay 2 on the southwest side. The road was restored as part of KSC’s Safe Haven project. High bay 2 provides a third stacking area. The primary goal of the Safe Haven construction project was to strengthen readiness for hurricane season by expanding the VAB’s storage capacity. The new area, in high bay 2, will allow NASA to preassemble stacks and still have room in the VAB to pull a Shuttle back from the pad if severe weather threatens. Potential rollouts of the Space Shuttle to the launch pad from high bay 2 will involve making a turn around the north side of the VAB in contrast to the straight rollouts from high bays 1 and 3, on the east side of the VAB facing the launch pads
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2000-06-01
KENNEDY SPACE CENTER, FLA. -- A crawler-transporter with mobile launcher platform on top tests the buried portion of the Apollo-era crawlerway leading to the Vehicle Assembly Building (VAB) high bay 2 on the southwest side. The road was restored as part of KSC’s Safe Haven project. High bay 2 provides a third stacking area. The primary goal of the Safe Haven construction project was to strengthen readiness for hurricane season by expanding the VAB’s storage capacity. The new area, in high bay 2, will allow NASA to preassemble stacks and still have room in the VAB to pull a Shuttle back from the pad if severe weather threatens. Potential rollouts of the Space Shuttle to the launch pad from high bay 2 will involve making a turn around the north side of the VAB in contrast to the straight rollouts from high bays 1 and 3, on the east side of the VAB facing the launch pads
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Space Shuttle Transportation (Roll-Out) Loads Diagnostics
NASA Technical Reports Server (NTRS)
Elliott, Kenny B.; Buehrle, Ralph D.; James, George H.; Richart, Jene A.
2005-01-01
The Space Transportation System (STS) consists of three primary components; an Orbiter Vehicle, an External Fuel Tank, and two Solid Rocket Boosters. The Orbiter Vehicle and Solid Rocket Boosters are reusable components, and as such, they are susceptible to durability issues. Recently, the fatigue load spectra for these components have been updated to include load histories acquired during the rollout phase of the STS processing for flight. Using traditional program life assessment techniques, the incorporation of these "rollout" loads produced unacceptable life estimates for certain Orbiter structural members. As a result, the Space Shuttle System Engineering and Integration Office has initiated a program to re-assess the method used for developing the "rollout" loads and performing the life assessments. In the fall of 2003 a set of tests were preformed to provide information to either validate existing load spectra estimation techniques or generate new load spectra estimation methods. Acceleration and strain data were collected from two rollouts of a partial-stack configuration of the Space Shuttle. The partial stack configuration consists of two Solid Rocket Boosters tied together at the upper External Tank attachment locations mounted on the Mobile Launch Platform carried by a Crawler Transporter (CT). In the current analysis, the data collected from this test is examined for consistency in speed, surface condition effects, and the characterization of the forcing function. It is observed that the speed of the CT is relatively stable. The dynamic response acceleration of the partial-stack is slightly sensitive to the surface condition of the road used for transport, and the dynamic response acceleration of the partial-stack generally increases as the transport speed increases. However, the speed sensitivity is dependent on the measurement location. Finally, the character of the forcing function is narrow-banded with the primary drivers being harmonics of two CT speed dependent excitations. One source is an excitation due to the CT treads striking the road surface, and the second is unknown.
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2007-09-05
KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the top of external tank No. 120 is seen as the tank is lowered between the solid rocket boosters for mating on the mobile launcher platform. The external tank-SRB stack is being prepared for the orbiter Discovery, which will be mated to the stack in the VAB in two weeks. Space Shuttle Discovery is targeted to launch Oct. 23 on mission STS-120 to the International Space Station. Photo credit: NASA/George Shelton
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Space Shuttle Upgrades: Long Life Alkaline Fuel Cell
NASA Technical Reports Server (NTRS)
McCurdy, Kerri
2004-01-01
NASA has utilized the alkaline fuel cell technology to provide electrical power for manned launch vehicles such as Gemini, Apollo, and the Space Shuttle. The current Shuttle alkaline fuel cells are procured from UTC Fuel Cells, a United Technologies Company. The alkaline fuel cells are very reliable but the operating life is limited to 2600 hours due to voltage degradation of the individual cells. The main limiting factor in the life of the cells is corrosion of the cell's fiberglass/epoxy frame by the aqueous potassium hydroxide electrolyte. To reduce operating costs, the orbiter program office approved the Long Life Alkaline Fuel Cell (LLAFC) program as a shuttle upgrade in 1999 to increase the operating life of the fuel cell powerplant to 5000 hours. The LLAFC program incorporates improving the cell by extending the length of the corrosion path, which reduces the cell frame corrosion. UTCFC performed analysis to understand the fundamental mechanisms that drive the cell frame corrosion. The analysis indicated that the corrosion path started along the bond line between the cathode and the cell frame. Analysis also showed that the oxygen available at the cathode, the catalyst on the electrode, and the electrode substrate all supported or intensified the corrosion. The new cell design essentially doubled the corrosion path to mitigate the problem. A 10-cell stack was tested for 5000 hours during the development phase of this program to verify improved cell performance. A complete 96-cell stack was then tested for 5000 hours during the full manned-space qualification phase of this program. Additional upgrades to the powerplant under this program are: replacing the aluminum body in the pressure regulator with stainless steel to reduce corrosion, improving stack insulator plate with improved resistance to stress failure and improved temperature capability, and replacing separator plate elastomer seals with a more durable material and improved seal retention.
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2010-09-27
CAPE CANAVERAL, Fla. -- A tugboat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, toward the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. In the background, space shuttle Discovery is on Launch Pad 39A awaiting liftoff on the STS-133 mission to the International Space Station. Next, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-27
CAPE CANAVERAL, Fla. -- The Pegasus Barge, carrying the Space Shuttle Program's last external fuel tank, ET-122, nears NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- A tugboat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jim Grossmann
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, to the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, to the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-27
CAPE CANAVERAL, Fla. -- The Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, arrives at the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. Next, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-22
GULFPORT, La. -- At Gulfport, La., Michael Nicholas, captain M/V Freedom Star, guides NASA's solid rocket booster retrieval ship out of port pulling the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- NASA's Pegasus barge, carrying the Space Shuttle Program's last external fuel tank, ET-122, arrives at the Turn Basin of NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. Next, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2010-09-25
CAPE CANAVERAL, Fla. -- This sunrise view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-20
NEW ORLEANS -- To commemorate the history of the Space Shuttle Program's last external fuel tank, its intertank door is emblazoned with an ET-122 insignia. The external tank will travel 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans to NASA's Kennedy Space Center in Florida secured aboard the Pegasus Barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, toward the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb., 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-26
CAPE CANAVERAL, Fla. -- Deckhands on Freedom Star, one of NASA's solid rocket booster retrieval ships, keep the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- The Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, arrives at the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. Next, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-20
NEW ORLEANS -- Workers watch the progress of the Space Shuttle Program's last external fuel tank, ET-122, at NASA's Michoud Assembly Facility in New Orleans, as it is being loaded onto the Pegasus Barge. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, to the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, toward the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-21
NEW ORLEANS -- At NASA's Michoud Assembly Facility in New Orleans a tug boat is prepared to escort the Space Shuttle Program's last external fuel tank, ET-122, for transportation to NASA's Kennedy Space Center in Florida. Secured aboard the Pegasus Barge the tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-20
NEW ORLEANS -- Workers check the progress of the Space Shuttle Program's last external fuel tank, ET-122, at NASA's Michoud Assembly Facility in New Orleans as it is being loaded onto the Pegasus Barge. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, the Pegasus Barge, carrying the Space Shuttle Program's last external fuel tank, ET-122, arrives at the Turn Basin. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-26
CAPE CANAVERAL, Fla. -- This view is from the deck of Freedom Star, one of NASA's solid rocket booster retrieval ships, as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-22
CAPE CANAVERAL, Fla. -- This view from Freedom Star, one NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is transported to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-26
CAPE CANAVERAL, Fla. -- This view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-26
CAPE CANAVERAL, Fla. -- Deckhands on Freedom Star, one of NASA's solid rocket booster retrieval ships, keep the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-22
CAPE CANAVERAL, Fla. -- This view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is transported to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea, offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- A tugboat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, toward the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. Next, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-28
CAPE CANAVERAL, Fla. -- This overhead view shows the Space Shuttle Program's last external fuel tank, ET-122, as it is being transported to the Vehicle Assembly Building (VAB) at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea, carried in the Pegasus Barge, from NASA's Michoud Assembly Facility in New Orleans. Once inside the VAB, it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station targeted to launch Feb. 2011. STS-134 currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kevin O'Connell
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, toward the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb., 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-25
CAPE CANAVERAL, Fla. -- This view from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-26
CAPE CANAVERAL, Fla. -- A deckhand on Freedom Star, one of NASA's solid rocket booster retrieval ships, keeps the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, toward the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb., 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-27
CAPE CANAVERAL, Fla. -- A tug boat pulls the Space Shuttle Program's last external fuel tank, ET-122, toward the Turn Basin at NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. Next, the tank will be offloaded and moved to Kennedy's Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-26
CAPE CANAVERAL, Fla. -- Deckhands on Freedom Star, one of NASA's solid rocket booster retrieval ships, keep the ship in good repair as it pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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1978-09-01
This photograph shows the left side of the solid rocket booster (SRB) segment as it awaits being mated to the nose cone and forward skirt in the Dynamic Test Stand at the east test area of the Marshall Space Flight Center (MSFC). The SRB would be attached to the external tank (ET) and then the orbiter later for the Mated Vertical Ground Vibration Test (MVGVT), that resumed in October 1978. The stacking of a complete Shuttle in the Dynamic Test Stand allowed test engineers to perform ground vibration testing on the Shuttle in its liftoff configuration. The purpose of the MVGVT was to verify that the Space Shuttle would perform as predicted during launch. The platforms inside the Dynamic Test Stand were modified to accommodate two SRB's to which the ET was attached.
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2010-09-20
NEW ORLEANS -- Workers monitor the progress of the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans as it is being loaded onto the Pegasus Barge. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-20
NEW ORLEANS -- Workers monitor the progress of the Space Shuttle Program's last external fuel tank, ET-122, at NASA's Michoud Assembly Facility in New Orleans as it is being loaded onto the Pegasus BargeThe tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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Ares I-X Flight Test Vehicle: Stack 5 Modal Test
NASA Technical Reports Server (NTRS)
Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Danel R.
2010-01-01
Ares I-X was the first flight test vehicle used in the development of NASA's Ares I crew launch vehicle. The Ares I-X used 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. Three modal tests were defined to verify the dynamic finite element model of the Ares I-X flight test vehicle. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report focuses on the first modal test that was performed on the top section of the vehicle referred to as Stack 5, which consisted of the spacecraft adapter, service module, crew module and launch abort system simulators. This report describes the test requirements, constraints, pre-test analysis, test operations and data analysis for the Ares I-X Stack 5 modal test.
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Ares I-X Flight Test Vehicle:Stack 1 Modal Test
NASA Technical Reports Server (NTRS)
Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Daniel R.
2010-01-01
Ares I-X was the first flight test vehicle used in the development of NASA s Ares I crew launch vehicle. The Ares I-X used 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. Three modal tests were defined to verify the dynamic finite element model of the Ares I-X flight test vehicle. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report focuses on the second modal test that was performed on the middle section of the vehicle referred to as Stack 1, which consisted of the subassembly from the 5th segment simulator through the interstage. This report describes the test requirements, constraints, pre-test analysis, test operations and data analysis for the Ares I-X Stack 1 modal test.
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The STS-93 external tank and booster stack sits at the Mobile Launcher Platform park site
NASA Technical Reports Server (NTRS)
1999-01-01
The STS-93 stack of solid rocket boosters and external tank sits at the Mobile Launcher Platform park site waiting for lightning shield wires to be installed on the Vehicle Assembly Building (VAB) in the background. The stack is being temporarily stored outside the VAB while Space Shuttle Discovery undergoes repair to hail damage in High Bay 1. Discovery was rolled back from Pad 39B to the VAB for repairs because access to all of the damaged areas was not possible at the pad. The STS-93 stack will be moved under the wires at the VAB for protection until Discovery returns to the pad, later this week. The scheduled date for launch of mission STS-96 is no earlier than May 27. STS-93 is targeted for launch on July 22, carrying the Chandra X-ray Observatory.
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2010-09-27
CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-27
CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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2010-09-27
CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, ushers the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-27
CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- NASA's Pegasus barge moves through the bridge at Port Canaveral, Fla. The barge is carrying the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2010-09-22
CAPE CANAVERAL, Fla. -- This view at dusk from the stern of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is transported to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, ushers the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-22
GULFPORT, La. -- This view from the captain's deck of Freedom Star, one of NASA's solid rocket booster retrieval ships, shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, as it is escorted from Gulfport, La., to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- NASA's Pegasus barge is pulled toward NASA's Kennedy Space Center in Florida by a tug boat. The barge is carrying the Space Shuttle Program's last external fuel tank, ET-122 and traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Kim Shiflett
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2010-09-27
CAPE CANAVERAL, Fla. -- Freedom Star, one of NASA's solid rocket booster retrieval ships, pulls the Space Shuttle Program's last external fuel tank, ET-122, toward NASA's Kennedy Space Center in Florida. The tank traveled 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. After reaching the Turn Basin at Kennedy, the tank will be offloaded and moved to the Vehicle Assembly Building where it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Jack Pfaller
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Estimating the Cost of NASA's Space Launch Initiative: How SLI Cost Stack Up Against the Shuttle
NASA Technical Reports Server (NTRS)
Hamaker, Joseph H.; Roth, Axel (Technical Monitor)
2002-01-01
NASA is planning to replace the Space Shuttle with a new completely reusable Second Generation Launch System by approximately 2012. Numerous contracted and NASA in-house Space Transportation Architecture Studies and various technology maturation activities are proceeding and have resulted in scores of competing architecture configurations being proposed. Life cycle cost is a key discriminator between all these various concepts. However, the one obvious analogy for costing purposes remains the current Shuttle system. Are there credible reasons to believe that a second generation reusable launch system can be accomplished at less cost than the Shuttle? The need for a credible answer to this question is critical. This paper reviews the cost estimating approaches being used by the contractors and the government estimators to address this issue and explores the rationale behind the numbers.
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2000-01-09
JSC2003-E-15407 (9 Jan. 1990) --- A 35mm still camera located in the umbilical well of the Space Shuttle Columbia took this photograph of the external fuel tank (ET) after it was dropped from the launch stack as the shuttle headed for Earth-orbit on Jan. 9, 1990 for the STS-32 mission. Several large divots are visible near the forward ET/orbiter bipod and smaller divots are visible on the H2 tank acreage. The vertical streak and the horizontal bands were the results of repairs done prior to launch.
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NASA Technical Reports Server (NTRS)
1972-01-01
A fuel cell technology program was established to advance the state-of-the art of hydrogen oxygen fuel cells using low temperature, potassium hydroxide electrolyte technology as the base. Cell and component testing confirmed that low temperature, potassium hydroxide electrolyte technology is compatible with the requirements of the space shuttle Phase B contractors. Testing of the DM-1 powerplant demonstrated all of the important requirements of the shuttle except operating life. Testing also identified DM-1 powerplant life limiting mechanisms; hydrogen pump gear wear and pressurization of the cell stack over its design limits.
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NASA Technical Reports Server (NTRS)
Willams, M. C.
1985-01-01
Assuring personnel and equipment are fully protected during the Space Shuttle launch and landing operations has been a primary concern of NASA and its associated contractors since the inception of the program. A key factor in support of this policy has been the area access safety training requirements for badging of employees assigned to work on Space Shuttle Launch and Facilities. This requirement was targeted for possible cost savings and the transition of physical on-site walkdowns to the use of television tapes has realized program cost savings while continuing to fully satisfy the area access safety training requirements.
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A 3D network of helicates fully assembled by pi-stacking interactions.
Vázquez, Miguel; Taglietti, Angelo; Gatteschi, Dante; Sorace, Lorenzo; Sangregorio, Claudio; González, Ana M; Maneiro, Marcelino; Pedrido, Rosa M; Bermejo, Manuel R
2003-08-07
The neutral dinuclear dihelicate [Cu2(L)2] x 2CH3CN (1) forms a unique 3D network in the solid state due to pi-stacking interactions, which are responsible for intermolecular antiferromagnetic coupling between Cu(II) ions.
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2013-08-09
CAPE CANAVERAL, Fla. – As seen on Google Maps, Firing Room 4 inside the Launch Control Center at NASA's Kennedy Space Center was one of the four control rooms used by NASA and contractor launch teams to oversee a space shuttle countdown. This firing room was the most advanced of the control rooms used for shuttle missions and was the primary firing room for the shuttle's final series of launches before retirement. It is furnished in a more contemporary style with wood cabinets and other features, although it retains many of the computer systems the shuttle counted on to operate safely. Specialized operators worked at consoles tailored to keep track of the status of shuttle systems while the spacecraft was processed in the Orbiter Processing Facility, being stacked inside the Vehicle Assembly Building and standing at the launch pad before liftoff. The firing rooms, including 3, were also used during NASA's Apollo Program. Google precisely mapped the space center and some of its historical facilities for the company's map page. The work allows Internet users to see inside buildings at Kennedy as they were used during the space shuttle era. Photo credit: Google/Wendy Wang
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Study of structural active cooling and heat sink systems for space shuttle
NASA Technical Reports Server (NTRS)
1972-01-01
This technology investigation was conducted to evaluate the feasibility of a number of thermal protection systems (TPS) concepts which are alternate candidates to the space shuttle baseline TPS. Four independent tasks were performed. Task 1 consisted of an in-depth evaluation of active structural cooling of the space shuttle orbiter. In Task 2, heat sink concepts for the booster were studied to identify and postulate solutions for design problems unique to heat sink TPS. Task 3 consisted of a feasibility demonstration test of a phase change material (PCM) incorporated into a reusable surface insulation (RSI) thermal protection system for the shuttle orbiter. In Task 4 the feasibility of heat pipes for stagnation region cooling was studied for the booster and the orbiter. Designs were developed for the orbiter leading edge and used in trade studies of leading edge concepts. At the time this program was initiated, a 2-stage fully reusable shuttle system was envisioned; therefore, the majority of the tasks were focused on the fully reusable system environments. Subsequently, a number of alternate shuttle system approaches, with potential for reduced shuttle system development funding requirements, were proposed. Where practicable, appropriate shifts in emphasis and task scoping were made to reflect these changes.
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Concepts for the evolution of the Space Station Program
NASA Technical Reports Server (NTRS)
Michaud, Roger B.; Miller, Ladonna J.; Primeaux, Gary R.
1986-01-01
An evaluation is made of innovative but pragmatic waste management, interior and exterior orbital module construction, Space Shuttle docking, orbital repair operation, and EVA techniques applicable to the NASA Space Station program over the course of its evolution. Accounts are given of the Space Shuttle's middeck extender module, an on-orbit module assembly technique employing 'Pringles' stack-transportable conformal panels, a flexible Shuttle/Space Station docking tunnel, an 'expandable dome' for transfer of objects into the Space Station, and a Space Station dual-hatch system. For EVA operations, pressurized bubbles with articulating manipulator arms and EVA hard suits incorporating maneuvering, life support and propulsion capabilities, as well as an EVA gas propulsion system, are proposed. A Space Station ultrasound cleaning system is also discussed.
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2010-09-20
NEW ORLEANS -- Associate Administrator for Space Operations Bill Gerstenmaier and Manny Zulueta, Lockheed Martin vice president and site executive at NASA's Michoud Assembly Facility in New Orleans, discuss the progress of the Space Shuttle Program's last external fuel tank, ET-122, as it is being transported from the facility to the Pegasus Barge. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida, secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-28
CAPE CANAVERAL, Fla. -- To commemorate the history of the Space Shuttle Program's last external fuel tank, its intertank door is emblazoned with an ET-122 insignia. The tank is in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida after traveling 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. It eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was completed in 2002, modified during Return to Flight operations in 2003 and 2004, damaged during Hurricane Katrina in 2005, and then restored to flight configuration by Lockheed Martin Space Systems Company employees in 2008 at NASA's Marshall Space Flight Center in Alabama. Photo credit: NASA/Jack Pfaller
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2010-09-28
CAPE CANAVERAL, Fla. -- This panoramic image shows the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, through the Port Canaveral locks on its way to the Turn Basin at NASA's Kennedy Space Center in Florida. Once docked, the tank will be offloaded from the barge and transported to the Vehicle Assembly Building (VAB). The tank traveled 900 miles by sea, carried in the barge, from NASA's Michoud Assembly Facility in New Orleans. Once inside the VAB, it eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station targeted to launch Feb. 2011. STS-134 currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. Photo credit: NASA/Frankie Martin
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2010-09-20
NEW ORLEANS -- Associate Administrator for Space Operations Bill Gerstenmaier and Manny Zulueta, Lockheed Martin vice president and site executive at NASA's Michoud Assembly Facility in New Orleans, watch the progress of the Space Shuttle Program's last external fuel tank, ET-122, as it is being transported from the facility to the Pegasus Barge. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-22
LOUISIANA -- A tug boat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans toward a dock in Gulfport, La. The barge will meet up with Freedom Star, NASA's solid rocket booster retrieval ship, which will escort it to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-20
NEW ORLEANS -- At NASA's Michoud Assembly Facility in New Orleans, Associate Administrator for Space Operations Bill Gerstenmaier and a Michoud employee discuss the progress of the Space Shuttle Program's last external fuel tank, ET-122, as it is being transported from the facility to the Pegasus Barge. The tank will travel 900 miles by sea to NASA's Kennedy Space Center in Florida secured aboard the barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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2010-09-28
CAPE CANAVERAL, Fla. -- To commemorate the history of the Space Shuttle Program's last external fuel tank, its intertank door is emblazoned with an ET-122 insignia. The tank is in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida after traveling 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans aboard the Pegasus Barge. It eventually will be attached to space shuttle Endeavour for the STS-134 mission to the International Space Station. STS-134, targeted to launch in Feb. 2011, currently is scheduled to be the last mission in the shuttle program. The tank, which is the largest element of the space shuttle stack, was completed in 2002, modified during Return to Flight operations in 2003 and 2004, damaged during Hurricane Katrina in 2005, and then restored to flight configuration by Lockheed Martin Space Systems Company employees in 2008 at NASA's Marshall Space Flight Center in Alabama. Photo credit: NASA/Jack Pfaller
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2010-09-22
LOUISIANA -- A tug boat pulls the Pegasus Barge carrying the Space Shuttle Program's last external fuel tank, ET-122, from NASA's Michoud Assembly Facility in New Orleans toward Gulfport, La. The barge will meet up with Freedom Star, NASA's solid rocket booster retrieval ship, which will escort it to NASA's Kennedy Space Center in Florida. The tank will travel 900 miles by sea before being offloaded and moved to Kennedy's Vehicle Assembly Building. There it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett
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NASA Astrophysics Data System (ADS)
Chagarov, Evgueni A.; Kavrik, Mahmut S.; Fang, Ziwei; Tsai, Wilman; Kummel, Andrew C.
2018-06-01
Comprehensive Density-Functional Theory (DFT) Molecular Dynamics (MD) simulations were performed to investigate interfaces between a-HfO2 and SiGe or Ge semiconductors with fully-stoichiometric a-SiO2 or sub-oxide SiO interlayers. The electronic structure of the selected stacks was calculated with a HSE06 hybrid functional. Simulations were performed before and after hydrogen passivation of residual interlayer defects. For the SiGe substrate with Ge termination prior to H passivation, the stacks with a-SiO suboxide interlayer (a-HfO2/a-SiO/SiGe) demonstrate superior electronic properties and wider band-gaps than the stacks with fully coordinated a-SiO2 interlayers (a-HfO2/a-SiO2/SiGe). After H passivation, most of the a-HfO2/a-SiO2/SiGe defects are passivated. To investigate effect of random placement of Si and Ge atoms additional simulations with a randomized SiGe slab were performed demonstrating improvement of electronic structure. For Ge substrates, before H passivation, the stacks with a SiO suboxide interlayer (a-HfO2/a-SiO/Ge) also demonstrate wider band-gaps than the stacks with fully coordinated a-SiO2 interlayers (a-HfO2/a-SiO2/Ge). However, even for a-HfO2/a-SiO/Ge, the Fermi level is shifted close to the conduction band edge (CBM) consistent with Fermi level pinning. Again, after H passivation, most of the a-HfO2/a-SiO2/Ge defects are passivated. The stacks with fully coordinated a-SiO2 interlayers have much stronger deformation and irregularity in the semiconductor (SiGe or Ge) upper layers leading to multiple under-coordinated atoms which create band-edge states and decrease the band-gap prior to H passivation.
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DOT National Transportation Integrated Search
2013-08-01
As a means of controlling mercury (Hg) stack emissions at cement kiln operations, some facilities have proposed or have instituted a practice known as dust shuttling, where baghouse filter dust (BFD) is routed to be blended with the final cement prod...
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Investigations of Shuttle Main Landing Gear Door Environmental Seals
NASA Technical Reports Server (NTRS)
Finkbeiner, Joshua; Dunlap, Pat; Steinetz, Bruce; DeMango, Jeff; Newswander, Daniel
2005-01-01
The environmental seals for the main landing gear doors of the Shuttle Orbiters were raised by the Columbia Accident Investigation Board as a potential safety concern. Inspections of seals installed on the Shuttle Discovery revealed that they were permanently deformed and no longer met certified seal compression requirements. Replacement of the seals led to the inability to fully close the main landing gear doors. Johnson Space Center requested that Glenn Research Center conduct tests on the main landing gear door environmental seals to assist in installing the seals in a manner to allow the main landing gear doors to fully close. Further testing was conducted to fill out the seal performance database. Results from the testing indicated that the method of bonding the seals was important in reducing seal loads on the main landing gear doors. Also, the replacement seals installed in Shuttle Discovery were found to have leakage performance sufficient to meet the certification requirements.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In a Vehicle Assembly Building (VAB) high bay, workers monitor the movement of a Solid Rocket Booster (SRB) aft center segment as it is lowered toward an aft segment already secured to a Mobile Launch Platform. These segments are part of the right SRB for the Space Shuttle Return to Flight mission, STS-114. Two SRBs are stacked on a Mobile Launch Platform for each Shuttle flight and later joined by an External Tank. The twin 149-foot tall, 12-foot diameter SRBs provide the main propulsion system during launch. They operate in parallel with the Space Shuttle main engines for the first two minutes of flight and jettison away from the orbiter with help from the Booster Separation Motors, about 26.3 nautical miles above the Earths surface.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In a Vehicle Assembly Building (VAB) high bay, workers check the alignment of a Solid Rocket Booster (SRB) aft center segment as it is lowered toward an aft segment already secured to a Mobile Launch Platform. These segments are part of the right SRB for the Space Shuttle Return to Flight mission, STS-114. Two SRBs are stacked on a Mobile Launch Platform for each Shuttle flight and later joined by an External Tank. The twin 149-foot tall, 12-foot diameter SRBs provide the main propulsion system during launch. They operate in parallel with the Space Shuttle main engines for the first two minutes of flight and jettison away from the orbiter with help from the Booster Separation Motors, about 26.3 nautical miles above the Earths surface.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In a Vehicle Assembly Building (VAB) high bay, workers check the alignment of a Solid Rocket Booster (SRB) aft center segment which has been lowered onto an aft segment already secured to a Mobile Launch Platform. These segments are part of the right SRB for the Space Shuttle Return to Flight mission, STS-114. Two SRBs are stacked on a Mobile Launch Platform for each Shuttle flight and later joined by an External Tank. The twin 149-foot tall, 12-foot diameter SRBs provide the main propulsion system during launch. They operate in parallel with the Space Shuttle main engines for the first two minutes of flight and jettison away from the orbiter with help from the Booster Separation Motors, about 26.3 nautical miles above the Earths surface.
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Flight Results of the Chandra X-ray Observatory Inertial Upper Stage Space Mission
NASA Technical Reports Server (NTRS)
Tillotson, R.; Walter, R.
2000-01-01
Under contract to NASA, a specially configured version of the Boeing developed Inertial Upper Stage (IUS) booster was provided by Boeing to deliver NASA's 1.5 billion dollar Chandra X-Ray Observatory satellite into a highly elliptical transfer orbit from a Shuttle provided circular park orbit. Subsequently, the final orbit of the Chandra satellite was to be achieved using the Chandra Integral Propulsion System (IPS) through a series of IPS burns. On 23 July 1999 the Shuttle Columbia (STS-93) was launched with the IUS/Chandra stack in the Shuttle payload bay. Unfortunately, the Shuttle Orbiter was unexpectantly inserted into an off-nominal park orbit due to a Shuttle propulsion anomaly occurring during ascent. Following the IUS/Chandra on-orbit deployment from the Shuttle, at seven hours from liftoff, the flight proven IUS GN&C system successfully injected Chandra into the targeted transfer orbit, in spite of the off-nominal park orbit. This paper describes the IUS GN&C system, discusses the specific IUS GN&C mission data load development, analyses and testing for the Chandra mission, and concludes with a summary of flight results for the IUS part of the Chandra mission.
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A review of polymer electrolyte membrane fuel cell stack testing
NASA Astrophysics Data System (ADS)
Miller, M.; Bazylak, A.
This paper presents an overview of polymer electrolyte membrane fuel cell (PEMFC) stack testing. Stack testing is critical for evaluating and demonstrating the viability and durability required for commercial applications. Single cell performance cannot be employed alone to fully derive the expected performance of PEMFC stacks, due to the non-uniformity in potential, temperature, and reactant and product flow distributions observed in stacks. In this paper, we provide a comprehensive review of the state-of-the art in PEMFC testing. We discuss the main topics of investigation, including single cell vs. stack-level performance, cell voltage uniformity, influence of operating conditions, durability and degradation, dynamic operation, and stack demonstrations. We also present opportunities for future work, including the need to verify the impact of stack size and cell voltage uniformity on performance, determine operating conditions for achieving a balance between electrical efficiency and flooding/dry-out, meet lifetime requirements through endurance testing, and develop a stronger understanding of degradation.
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2000-06-29
Inside the Vehicle Assembly Building, the forward section of a solid rocket booster (SRB) sits on top of the rest of the stack for mating. The forward section of each booster, from nose cap to forward skirt contains avionics, a sequencer, forward separation motors, a nose cone separation system, drogue and main parachutes, a recovery beacon, a recovery light, a parachute camera on selected flights and a range safety system. Each SRB weighs approximately 1.3 million pounds at launch. The SRB is part of the stack for Space Shuttle Discovery and the STS-92 mission, scheduled for launch Oct. 5, from Launch Pad 39A, on the fifth flight to the International Space Station
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2000-06-29
Inside the Vehicle Assembly Building, the forward section of a solid rocket booster (SRB) sits on top of the rest of the stack for mating. The forward section of each booster, from nose cap to forward skirt contains avionics, a sequencer, forward separation motors, a nose cone separation system, drogue and main parachutes, a recovery beacon, a recovery light, a parachute camera on selected flights and a range safety system. Each SRB weighs approximately 1.3 million pounds at launch. The SRB is part of the stack for Space Shuttle Discovery and the STS-92 mission, scheduled for launch Oct. 5, from Launch Pad 39A, on the fifth flight to the International Space Station
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2013-08-09
CAPE CANAVERAL, Fla. – As seen on Google Maps, Firing Room 3 inside the Launch Control Center at NASA's Kennedy Space Center was one of the four control rooms used by NASA and contractor launch teams to oversee a space shuttle countdown. This firing room is furnished in the classic style with the same metal computer cabinets and some of the same monitors in place when the first shuttle mission launched April 12, 1981. Specialized operators worked at consoles tailored to keep track of the status of shuttle systems while the spacecraft was processed in the Orbiter Processing Facility, being stacked inside the Vehicle Assembly Building and standing at the launch pad before liftoff. The firing rooms, including 3, were also used during NASA's Apollo Program. Google precisely mapped the space center and some of its historical facilities for the company's map page. The work allows Internet users to see inside buildings at Kennedy as they were used during the space shuttle era. Photo credit: Google/Wendy Wang
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2010-08-12
CAPE CANAVERAL, Fla. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a technician is applying HD calcium grease to the field joint along the base of the left forward center solid rocket booster segment to inhibit rust and corrosion from occurring in the area. The booster along with its twin will be stacked on the mobile launcher platform along with an external fuel tank awaiting the arrival of space shuttle Endeavour for its flight to the International Space Station. As the final planned mission of the Space Shuttle Program, Endeavour and its crew will deliver the Alpha Magnetic Spectrometer, as well as critical spare components to the station on the STS-134 mission targeted for launch Feb. 26, 2011. For more information visit, http://www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Kim Shiflett
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) is removed from space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers examine the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers examine the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove the ground umbilical carrier plate (GUCP) from space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2008-09-04
CAPE CANAVERAL, Fla. – Space shuttle Atlantis approaches the top of Launch Pad 39A after rolling from the Vehicle Assembly Building at NASA's Kennedy Space Center. The shuttle stack, with solid rocket boosters and external fuel tank attached to Atlantis, rest on the mobile launcher platform. Movement is provided by the crawler-transporter underneath. First motion occurred at 9:19 a.m. EDT. The Sept. 2 rollout date was postponed due to Tropical Storm Hanna’s shift to a northern track. Atlantis is scheduled to launch on the STS-125 mission to service NASA’s Hubble Space Telescope. Launch is targeted for Oct. 8. Photo credit: NASA/Jack Pfaller
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2008-09-04
CAPE CANAVERAL, Fla. – Space shuttle Atlantis passes through the gate and approaches the top of Launch Pad 39A after rolling from the Vehicle Assembly Building at NASA's Kennedy Space Center. The shuttle stack, with solid rocket boosters and external fuel tank attached to Atlantis, rest on the mobile launcher platform. Movement is provided by the crawler-transporter underneath. First motion occurred at 9:19 a.m. EDT. The Sept. 2 rollout date was postponed due to Tropical Storm Hanna’s shift to a northern track. Atlantis is scheduled to launch on the STS-125 mission to service NASA’s Hubble Space Telescope. Launch is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett
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Putting the Power of Configuration in the Hands of the Users
NASA Technical Reports Server (NTRS)
Al-Shihabi, Mary-Jo; Brown, Mark; Rigolini, Marianne
2011-01-01
Goal was to reduce the overall cost of human space flight while maintaining the most demanding standards for safety and mission success. In support of this goal, a project team was chartered to replace 18 legacy Space Shuttle nonconformance processes and systems with one fully integrated system Problem Reporting and Corrective Action (PRACA) processes provide a closed-loop system for the identification, disposition, resolution, closure, and reporting of all Space Shuttle hardware/software problems PRACA processes are integrated throughout the Space Shuttle organizational processes and are critical to assuring a safe and successful program Primary Project Objectives Develop a fully integrated system that provides an automated workflow with electronic signatures Support multiple NASA programs and contracts with a single "system" architecture Define standard processes, implement best practices, and minimize process variations
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NASA Astrophysics Data System (ADS)
Stelter, Michael; Reinert, Andreas; Mai, Björn Erik; Kuznecov, Mihail
A solid oxide fuel cell (SOFC) stack module is presented that is designed for operation on diesel reformate in an auxiliary power unit (APU). The stack was designed using a top-down approach, based on a specification of an APU system that is installed on board of vehicles. The stack design is planar, modular and scalable with stamped sheet metal interconnectors. It features thin membrane electrode assemblies (MEAs), such as electrolyte supported cells (ESC) and operates at elevated temperatures around 800 °C. The stack has a low pressure drop in both the anode and the cathode to facilitate a simple system layout. An overview of the technical targets met so far is given. A stack power density of 0.2 kW l -1 has been demonstrated in a fully integrated, thermally self-sustaining APU prototype running with diesel and without an external water supply.
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Operational Lessons Learned from the Ares I-X Flight Test
NASA Technical Reports Server (NTRS)
Davis, Stephan R.
2010-01-01
The Ares I-X flight test, launched in 2009, is the first test of the Ares I crew launch vehicle. This development flight test evaluated the flight dynamics, roll control, and separation events, but also provided early insights into logistical, stacking, launch, and recovery operations for Ares I. Operational lessons will be especially important for NASA as the agency makes the transition from the Space Shuttle to the Constellation Program, which is designed to be less labor-intensive. The mission team itself comprised only 700 individuals over the life of the project compared to the thousands involved in Shuttle and Apollo missions; while missions to and beyond low-Earth orbit obviously will require additional personnel, this lean approach will serve as a model for future Constellation missions. To prepare for Ares I-X, vehicle stacking and launch infrastructure had to be modified at Kennedy Space Center's Vehicle Assembly Building (VAB) as well as Launch Complex (LC) 39B. In the VAB, several platforms and other structures designed for the Shuttle s configuration had to be removed to accommodate the in-line, much taller Ares I-X. Vehicle preparation activities resulted in delays, but also in lessons learned for ground operations personnel, including hardware deliveries, cable routing, transferred work and custodial paperwork. Ares I-X also proved to be a resource challenge, as individuals and ground service equipment (GSE) supporting the mission also were required for Shuttle or Atlas V operations at LC 40/41 at Cape Canaveral Air Force Station. At LC 39B, several Shuttle-specific access arms were removed and others were added to accommodate the in-line Ares vehicle. Ground command, control, and communication (GC3) hardware was incorporated into the Mobile Launcher Platform (MLP). The lightning protection system at LC 39B was replaced by a trio of 600-foot-tall towers connected by a catenary wire to account for the much greater height of the vehicle. Like Shuttle, Ares I-X will be stacked on a MLP and rolled out to the pad on a Saturn-era crawler-transporter. While Ares I-X was only held in place by the four hold-down posts on its aft skirt during rollout, a new vehicle stabilization system (VSS) attached to the vertical service structure kept the vehicle from undue swaying prior to launch at the pad, LC 39B. Following the launch, the flight test vehicle first stage was recovered with the aid of new parachutes resized to accommodate the five-segment-long first stage, which had a much greater length and mass than the Shuttle s reusable solid rocket boosters. After splashdown, recovery divers exercised extra care when handling the first stage to ensure that the flight data recorders in the fifth segment simulator were not damaged by exposure to sea water. The data recovered from the Ares I-X flight test will be very valuable in verifying the predicted environments and models used to design the vehicle. Lessons learned from Ares I-X will be shared with the Ares Projects through written and verbal reports and through integration of mission team members into the Project workforce.
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1970-01-01
In 1970, NASA initiated Phase A contracts to study alternate Space Shuttle designs in addition to the two-stage fully-reusable Space Shuttle system already under development. A number of alternate systems were developed to ensure the development of the optimum earth-to-orbit system, including the Stage-and-a-half Chemical Interorbital Shuttle, shown here. The concept would utilize a reusable marned spacecraft with an onboard propulsion system attached to an expendable fuel tank to provide supplementary propellants.
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 Mission Specialist Nicole Stott prepares to depart NASA's Kennedy Space Center in Florida in a T-38 training jet. Stott and her five crewmates will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 crew members depart NASA's Kennedy Space Center in Florida in a T-38 training jet. The six-member crew will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 Commander Steve Lindsey prepares to depart NASA's Kennedy Space Center in Florida in a T-38 training jet. Lindsey and his five crewmates will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 crew members depart NASA's Kennedy Space Center in Florida in a T-38 training jet. The six-member crew will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 Commander Steve Lindsey, left, and Mission Specialist Nicole Stott prepare to depart NASA's Kennedy Space Center in Florida in a T-38 training jet. The six-member crew will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 Pilot Eric Boe prepares to depart NASA's Kennedy Space Center in Florida in a T-38 training jet. Boe and his five crewmates will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 crew prepares to depart NASA's Kennedy Space Center in Florida in T-38 training jets. Mission Specialist Michael Barratt, left, Pilot Eric Boe and Mission Specialist Nicole Stott and their three crewmates will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 Pilot Eric Boe prepares to depart NASA's Kennedy Space Center in Florida in a T-38 training jet. Boe and his five crewmates will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2010-11-05
CAPE CANAVERAL, Fla. -- Space shuttle Discovery's STS-133 Mission Specialist Tim Kopra prepares to depart NASA's Kennedy Space Center in Florida in a T-38 training jet. Kopra and his five crewmates will wait until at least Nov. 30 to launch to the International Space Station because a leak was detected at the Ground Umbilical Carrier Plate (GUCP) while Discovery's external fuel tank was being loaded for launch on Nov. 5. The GUCP is an attachment point between the external tank and a pipe that carries gaseous hydrogen safely away from the shuttle to the flare stack, where it is burned off. Engineers and managers also will evaluate a crack in the foam on the external tank. During the 11-day mission, STS-133 will deliver the Permanent Multipurpose Module, packed with supplies and critical spare parts, as well as Robonaut 2, to the orbiting laboratory. Discovery, which will fly its 39th mission, is scheduled to be retired following STS-133. This will be the 133rd Space Shuttle Program mission and the 35th shuttle voyage to the space station. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Kim Shiflett
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2013-08-09
CAPE CANAVERAL, Fla. – As seen on Google Maps, the view from the top of the Fixed Service Structure at Launch Complex 39A at NASA's Kennedy Space Center. The FSS, as the structure is known, is 285 feet high and overlooks the Rotating Service Structure that was rolled into place when a space shuttle was at the pad. The path taken by NASA's massive crawler-transporters that carried the shuttle stack 3 miles from Vehicle Assembly Building are also visible leading up to the launch pad. In the distance are seen the launch pads and support structures at Cape Canaveral Air Force Station for the Atlas V, Delta IV and Falcon 9 rockets. Google precisely mapped the space center and some of its historical facilities for the company's map page. The work allows Internet users to see inside buildings at Kennedy as they were used during the space shuttle era. Photo credit: Google/Wendy Wang
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NASA Technical Reports Server (NTRS)
Thorpe, Douglas G.
1991-01-01
An operation and schedule enhancement is shown that replaces the four-body cluster (Space Shuttle Orbiter (SSO), external tank, and two solid rocket boosters) with a simpler two-body cluster (SSO and liquid rocket booster/external tank). At staging velocity, the booster unit (liquid-fueled booster engines and vehicle support structure) is jettisoned while the remaining SSO and supertank continues on to orbit. The simpler two-bodied cluster reduces the processing and stack time until SSO mate from 57 days (for the solid rocket booster) to 20 days (for the liquid rocket booster). The areas in which liquid booster systems are superior to solid rocket boosters are discussed. Alternative and future generation vehicles are reviewed to reveal greater performance and operations enhancements with more modifications to the current methods of propulsion design philosophy, e.g., combined cycle engines, and concentric propellant tanks.
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1998-09-21
KENNEDY SPACE CENTER, FLA. -- Looking eastward, the Vehicle Assembly Building (VAB) in the Launch Complex 39 area can be seen with its new coat of paint, along with newly painted American flag and NASA logo. The improved look was finished in time to honor NASA's 40th anniversary on Oct. 1. In order to do the job, workers were suspended on platforms from the top of the 525-foot-high VAB. One of the world's largest buildings by volume, the VAB is the last stop for the Shuttle before rollout to the launch pad. Integration and stacking of the complete Space Shuttle vehicle (orbiter, two solid rocket boosters and the external tank) takes place in High Bays 1 or 3. Stretching from the side of the VAB, on the right, is the crawlerway, used to transport the Space Shuttle to the launch pad. Beyond the VAB is Banana Creek
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2010-08-12
CAPE CANAVERAL, Fla. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, an inspection is being performed on the bare metal parts of the "tang" end of the segment. The tang mates with the "clevis" and creates a field joint where each segment is put together. Grease has been coated on the bare steel to inhibit rust and corrosion. The booster along with its twin will be stacked on the mobile launcher platform along with an external fuel tank awaiting the arrival of space shuttle Endeavour for its flight to the International Space Station. As the final planned mission of the Space Shuttle Program, Endeavour and its crew will deliver the Alpha Magnetic Spectrometer, as well as critical spare components to the station on the STS-134 mission targeted for launch Feb. 26, 2011. For more information visit, http://www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts134/index.html. Photo credit: NASA/Kim Shiflett
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2007-01-05
KENNEDY SPACE CENTER, FLA. -- Lighting inside Kennedy Space Center's Vehicle Assembly Building seems to bathe the highbay 1 area in a golden hue as workers continue stacking the twin solid rocket boosters. The solid rocket boosters are being prepared for NASA's next Space Shuttle launch, mission STS-117. The mission is scheduled to launch aboard Atlantis no earlier than March 16, 2007. Photo credit: NASA/George Shelton
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View of the ISS stack as seen during the fly-around by the STS-96 crew
2017-04-20
S96-E-5218 (3 June 1999) --- Partially silhouetted over clouds and a wide expanse of ocean waters, the unmanned International Space Station (ISS) moves away from the Space Shuttle Discovery. An electronic still camera (ESC) was aimed through aft flight deck windows to capture the image at 23:01:00 GMT, June 3, 1999.
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Atlantis is lifted from its transporter in the VAB
NASA Technical Reports Server (NTRS)
2001-01-01
KENNEDY SPACE CENTER, Fla. -- In the transfer aisle of the Vehicle Assembly Building, the orbiter Atlantis is suspended vertically via overhead cranes. The orbiter will be rotated and lifted into high bay 1 where it will be stacked with its external tank and solid rocket boosters. Space Shuttle Atlantis is scheduled to launch on mission STS-104 in early July.
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Atlantis is lifted from its transporter in the VAB
NASA Technical Reports Server (NTRS)
2001-01-01
KENNEDY SPACE CENTER, Fla. -- This closeup shows the workers, standing on lifts, who are checking the bolts on the apparatus holding the orbiter Atlantis. The orbiter will be rotated and lifted into high bay 1 where it will be stacked with its external tank and solid rocket boosters. Space Shuttle Atlantis is scheduled to launch on mission STS-104 in early July.
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ESTIMATION OF THE SPACE SHUTTLE ROLLOUT FORCING FUNCTION
NASA Technical Reports Server (NTRS)
James, George H., III; Carne, Thomas; Elliott, Kenny; Wilson, Bruce
2005-01-01
The Space Shuttle Vehicle is assembled in the Vertical Assembly Building (VAB) at Kennedy Space Flight Center in Florida. The Vehicle is stacked on a Mobile Launch Platform (MLP) that weighs eight million pounds. A Crawler Transporter (CT) then carries the MLP and the stacked vehicle (12 million pounds total weight) to the launch complex located 5 miles away. This operation is performed at 0.9 mph resulting in a 4.5-hour transport. A recent test was performed to monitor the dynamic environment that was produced during rollout. It was found that the rollout is a harmonic-rich dynamic environment that was previously not understood. This paper will describe work that has been performed to estimate the forcing function that is produced in the transportation process. The rollout analysis team has determined that there are two families of harmonics of the drive train, which excite the system as a function of CT speed. There are also excitation sources, which are random or narrow-band in frequency and are not a function of CT speed. This presentation will discuss the application of the Sum of Weighted Accelerations Technique (SWAT) to further refine this understanding by estimating the forces and moments at the center-of-mass.
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to remove the ground umbilical carrier plate (GUCP) from space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove the seal from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers install a cap over the hole in space shuttle Discovery's external fuel tank where the ground umbilical carrier plate (GUCP) was removed. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers begin to remove the ground umbilical carrier plate (GUCP) from space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) is ready to be examined. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers examine the seal from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers begin to remove the seal from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers move the ground umbilical carrier plate (GUCP) to a location where it can be examined. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers install a cap over the hole in space shuttle Discovery's external fuel tank where the ground umbilical carrier plate (GUCP) was removed. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to remove the ground umbilical carrier plate (GUCP) from space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers examine the seal from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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2009-03-11
CAPE CANAVERAL, Fla. – Seen in the photo is the hydrogen vent line attached to the Ground Umbilical Carrier Plate on space shuttle Discovery's external fuel tank. The shuttle is on Launch Pad 39A at NASA's Kennedy Space Center in Florida. A leak of hydrogen at the location during tanking caused the STS-119 mission to be scrubbed at 2:36 p.m. March 11. The vent line is at the intertank and is the overboard vent to the pad and the flare stack where the vented hydrogen is burned off. Mission management teams believe they have sufficient understanding of the repair plan to continue toward a March 15 launch at 7:43 p.m. EDT. Photo courtesy of United Space Alliance
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2012-02-03
CAPE CANAVERAL, Fla. -- In Orbiter Processing Facility-2 at NASA’s Kennedy Space Center in Florida, one of space shuttle Endeavour’s payload bay doors has been fully opened so that an antenna can be retracted. Space Shuttle Program transition and retirement work continues on Discovery and Endeavour in the orbiter processing facilities, while shuttle Atlantis is in temporary storage in high bay 4 of the Vehicle Assembly Building. Endeavour is being prepared for display at the California Science Center in Los Angeles. Photo credit: NASA/Kim Shiflett
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2012-02-03
CAPE CANAVERAL, Fla. - In Orbiter Processing Facility-2 at NASA’s Kennedy Space Center in Florida, one of space shuttle Endeavour’s payload bay doors has been fully opened so that an antenna can be retracted. Space Shuttle Program transition and retirement work continues on Discovery and Endeavour in the orbiter processing facilities, while shuttle Atlantis is in temporary storage in high bay 4 of the Vehicle Assembly Building. Endeavour is being prepared for display at the California Science Center in Los Angeles. Photo credit: NASA/Kim Shiflett
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2012-02-03
CAPE CANAVERAL, Fla. – In Orbiter Processing Facility-2 at NASA’s Kennedy Space Center in Florida, one of space shuttle Endeavour’s payload bay doors has been fully opened so that an antenna can be retracted. Space Shuttle Program transition and retirement work continues on Discovery and Endeavour in the orbiter processing facilities, while shuttle Atlantis is in temporary storage in high bay 4 of the Vehicle Assembly Building. Endeavour is being prepared for display at the California Science Center in Los Angeles. Photo credit: NASA/Kim Shiflett
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2012-02-03
CAPE CANAVERAL, Fla. -- In Orbiter Processing Facility-2 at NASA’s Kennedy Space Center in Florida, one of space shuttle Endeavour’s payload bay doors has been fully opened so that an antenna can be retracted. Space Shuttle Program transition and retirement work continues on Discovery and Endeavour in the orbiter processing facilities, while shuttle Atlantis is in temporary storage in high bay 4 of the Vehicle Assembly Building. Endeavour is being prepared for display at the California Science Center in Los Angeles. Photo credit: NASA/Kim Shiflett
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2012-02-03
CAPE CANAVERAL, Fla. -- In Orbiter Processing Facility-2 at NASA’s Kennedy Space Center in Florida, one of space shuttle Endeavour’s payload bay doors has been fully opened so that an antenna can be retracted. Space Shuttle Program transition and retirement work continues on Discovery and Endeavour in the orbiter processing facilities, while shuttle Atlantis is in temporary storage in high bay 4 of the Vehicle Assembly Building. Endeavour is being prepared for display at the California Science Center in Los Angeles. Photo credit: NASA/Kim Shiflett
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2012-02-03
CAPE CANAVERAL, Fla. -- In Orbiter Processing Facility-2 at NASA’s Kennedy Space Center in Florida, one of space shuttle Endeavour’s payload bay doors has been fully opened and an antenna has been retracted. Space Shuttle Program transition and retirement work continues on Discovery and Endeavour in the orbiter processing facilities, while shuttle Atlantis is in temporary storage in high bay 4 of the Vehicle Assembly Building. Endeavour is being prepared for display at the California Science Center in Los Angeles. Photo credit: NASA/Kim Shiflett
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Space Shuttle Orbital Drag Parachute Design
NASA Technical Reports Server (NTRS)
Meyerson, Robert E.
2001-01-01
The drag parachute system was added to the Space Shuttle Orbiter's landing deceleration subsystem beginning with flight STS-49 in May 1992. The addition of this subsystem to an existing space vehicle required a detailed set of ground tests and analyses. The aerodynamic design and performance testing of the system consisted of wind tunnel tests, numerical simulations, pilot-in-the-loop simulations, and full-scale testing. This analysis and design resulted in a fully qualified system that is deployed on every flight of the Space Shuttle.
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A view toward future launch vehicles - A civil perspective
NASA Technical Reports Server (NTRS)
Darwin, Charles R.; Austin, Gene; Varnado, Lee; Eudy, Glenn
1989-01-01
Prospective NASA launch vehicle development efforts, which in addition to follow-on developments of the Space Shuttle encompass the Shuttle-C cargo version, various possible Advanced Launch System (ALS) configurations, and various Heavy Lift Launch System (HLLS) design options. Fully and partially reusable manned vehicle alternatives are also under consideration. In addition to improving on the current Space Shuttle's reliability and flexibility, ALS and HLLV development efforts are expected to concentrate on the reduction of operating costs for the given payload-launch capability.
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1999-09-20
The Butler Building at Kennedy Space Center is nearly demolished, with the help of the crane in the background. The building, which is near the Orbiter Processing Facility (right), is being demolished in order to extend the crawlerway leading to the high bay of the Vehicle Assembly Building (VAB), part of KSC's Safe Haven project. The goal of Safe Haven is to strengthen readiness for Florida's hurricane season by expanding the VAB's storage capacity. Construction includes outfitting the VAB with a third stacking area, in high bay 2, that will allow NASA to preassemble stacks and still have room in the VAB to pull a Shuttle back from the pad into the safety of the VAB if severe weather threatens. The VAB can withstand winds up to 125 mph
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1999-09-20
The walls of the Butler Building at Kennedy Space Center come tumbling down, with the help of the crane in the background. The building, which is near the Orbiter Processing Facility, is being demolished in order to extend the crawlerway leading to the high bay of the Vehicle Assembly Building (VAB), part of KSC's Safe Haven project. The goal of Safe Haven is to strengthen readiness for Florida's hurricane season by expanding the VAB's storage capacity. Construction includes outfitting the VAB with a third stacking area, in high bay 2, that will allow NASA to preassemble stacks and still have room in the VAB to pull a Shuttle back from the pad into the safety of the VAB if severe weather threatens. The VAB can withstand winds up to 125 mph
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Wideband analytical equivalent circuit for one-dimensional periodic stacked arrays.
Molero, Carlos; Rodríguez-Berral, Raúl; Mesa, Francisco; Medina, Francisco; Yakovlev, Alexander B
2016-01-01
A wideband equivalent circuit is proposed for the accurate analysis of scattering from a set of stacked slit gratings illuminated by a plane wave with transverse magnetic or electric polarization that impinges normally or obliquely along one of the principal planes of the structure. The slit gratings are printed on dielectric slabs of arbitrary thickness, including the case of closely spaced gratings that interact by higher-order modes. A Π-circuit topology is obtained for a pair of coupled arrays, with fully analytical expressions for all the circuit elements. This equivalent Π circuit is employed as the basis to derive the equivalent circuit of finite stacks with any given number of gratings. Analytical expressions for the Brillouin diagram and the Bloch impedance are also obtained for infinite periodic stacks.
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Rendezvous and Proximity Operations of the Space Shuttle
NASA Technical Reports Server (NTRS)
Goodman, John L.
2005-01-01
Space Shuttle rendezvous missions present unique challenges that were not fully recognized when the Shuttle was designed. Rendezvous targets could be passive (i.e., no lights or transponders), and not designed to facilitate Shuttle rendezvous, proximity operations, and retrieval. Shuttle reaction control system jet plume impingement on target spacecraft presented induced dynamics, structural loading, and contamination concerns. These issues, along with limited reaction control system propellant in the Shuttle nose, drove a change from the legacy Gemini/Apollo coelliptic profile to a stable orbit profile, and the development of new proximity operations techniques. Multiple scientific and on-orbit servicing missions, and crew exchange, assembly and replenishment flights to Mir and to the International Space Station drove further profile and piloting technique changes. These changes included new proximity operations, relative navigation sensors, and new computer generated piloting cues. However, the Shuttle's baseline rendezvous navigation system has not required modification to place the Shuttle at the proximity operations initiation point for all rendezvous missions flown.
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers will focus their attention on the ground umbilical carrier plate (GUCP), which is on space shuttle Discovery's orange external fuel tank at the end of the access arm. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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2010-11-30
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) of space shuttle Discovery's external fuel tank has been repaired. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston
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2010-11-30
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) of space shuttle Discovery's external fuel tank has been repaired. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers are focusing their attention on the ground umbilical carrier plate (GUCP), which is on space shuttle Discovery's orange external fuel tank at the end of the access arm. A hydrogen gas leak at that location during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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NASA PEMFC Development Background and History
NASA Technical Reports Server (NTRS)
Hoberecht, Mark
2011-01-01
NASA has been developing proton-exchange-membrane (PEM) fuel cell power systems for the past decade, as an upgraded technology to the alkaline fuel cells which presently provide power for the Shuttle Orbiter. All fuel cell power systems consist of one or more fuel cell stacks in combination with appropriate balance-of-plant hardware. Traditional PEM fuel cells are characterized as flow-through, in which recirculating reactant streams remove product water from the fuel cell stack. NASA recently embarked on the development of non-flow-through fuel cell systems, in which reactants are dead-ended into the fuel cell stack and product water is removed by internal wicks. This simplifies the fuel cell power system by eliminating the need for pumps to provide reactant circulation, and mechanical water separators to remove the product water from the recirculating reactant streams. By eliminating these mechanical components, the resulting fuel cell power system has lower mass, volume, and parasitic power requirements, along with higher reliability and longer life. Four vendors have designed and fabricated non-flow-through fuel cell stacks under NASA funding. One of these vendors is considered the "baseline" vendor, and the remaining three vendors are competing for the "alternate" role. Each has undergone testing of their stack hardware integrated with a NASA balance-of-plant. Future Exploration applications for this hardware include primary fuel cells for a Lunar Lander and regenerative fuel cells for Surface Systems.
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2000-11-21
KENNEDY SPACE CENTER, FLA. -- A newly arrived external tank is transported from the turn basin to the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission
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2000-11-21
KENNEDY SPACE CENTER, FLA. -- A newly arrived external tank heads from the turn basin toward the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission
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2000-11-21
KENNEDY SPACE CENTER, FLA. -- A newly arrived external tank heads from the turn basin toward the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission
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Atlantis is lifted from its transporter in the VAB
NASA Technical Reports Server (NTRS)
2001-01-01
KENNEDY SPACE CENTER, Fla. -- In the Vehicle Assembly Building, the orbiter Atlantis is being lifted from a transporter after rolling over from Orbiter Processing Facility bay 3. The orbiter will be raised to a vertical position, rotated and lifted into high bay 1, and stacked with its external tank and solid rocket boosters. Space Shuttle Atlantis is scheduled to launch on mission STS-104 in early July.
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Rendezvous and Proximity Operations of the Space Shuttle
NASA Technical Reports Server (NTRS)
Goodman, John L.
2005-01-01
Space Shuttle rendezous missions presented unique challenges that were not fully recognized when the Shuttle was designed. Rendezvous targets could be passive (i.e., no lights or transponders), and not designed to facilitate Shuttle rendezvous, proximity operations and retrieval. Shuttle reaction control system jet plume impingement on target spacecraft presented induced dynamics, structural loading and contamination concerns. These issues, along with limited forward reaction control system propellant, drove a change from the Gemimi/Apollo coelliptic profile heritage to a stable orbit profile, and the development of new proximity operations techniques. Multiple scientific and on-orbit servicing missions and crew exchange, assembly and replinishment flights to Mir and to the International Space Station drove further profile and piloting technique changes, including new relative navigation sensors and new computer generated piloting cues.
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Space shuttle phase B wind tunnel model and test information. Volume 2: Orbiter configuration
NASA Technical Reports Server (NTRS)
Glynn, J. L.; Poucher, D. E.
1988-01-01
Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a data base and are available for applying to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Data Base is structured by vehicle component and configuration type. Basic components include the booster, the orbiter, and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retro-glide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks, and double delta wings. Launch configuration types include booster and orbiter components in various stacked and tandem combinations.
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2009-10-06
CAPE CANAVERAL, Fla. – Workers supervise the move of space shuttle Atlantis from its hangar, Orbiter Processing Facility 1, to the Vehicle Assembly Building at NASA’s Kennedy Space Center in Florida. The rollover began about 7 a.m. EDT and was complete at 8:25 a.m. when Atlantis was towed into the VAB's transfer aisle. Next, Atlantis will be lifted over a transom and lowered into the VAB's high bay 1, where it will be attached to its external fuel tank and solid rocket boosters. Rollout of the 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 during a 10-minute launch window on Nov. 12. 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
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Space shuttle phase B wind tunnel model and test information. Volume 3: Launch configuration
NASA Technical Reports Server (NTRS)
Glynn, J. L.; Poucher, D. E.
1988-01-01
Archived wind tunnel data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel data acquired in the Phase B development have been compiled into a data base and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include booster, orbiter and launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbital configuration types include straight and delta wings, lifting body, drop tanks and double delta wings. This is Volume 3 (Part 2) of the report -- Launch Configuration -- which includes booster and orbiter components in various stacked and tandem combinations.
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NASA Technical Reports Server (NTRS)
Griffin, Timothy P.; Naylor, Guy R.; Haskell, William D.; Breznik, Greg S.; Mizell, Carolyn A.; Helms, William R.; Voska, N. (Technical Monitor)
2002-01-01
An on-line gas monitoring system was developed to replace the older systems used to monitor for cryogenic leaks on the Space Shuttles before launch. The system uses a mass spectrometer to monitor multiple locations in the process, which allows the system to monitor all gas constituents of interest in a nearly simultaneous manner. The system is fully redundant and meets all requirements for ground support equipment (GSE). This includes ruggedness to withstand launch on the Mobile Launcher Platform (MLP), ease of operation, and minimal operator intervention. The system can be fully automated so that an operator is notified when an unusual situation or fault is detected. User inputs are through personal computer using mouse and keyboard commands. The graphical user for detecting cryogenic leaks, many other gas constituents could be monitored using the Hazardous Gas Detection System (HGDS) 2000.
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Design concept definition study for an improved shuttle waste collection subsystem
NASA Technical Reports Server (NTRS)
1984-01-01
A no-risk approach for developing an Improved Waste Collection Subsystem (WCS) for the shuttle orbiter is described. The GE Improved WCS Concept builds on the experience of 14 Shuttle missions with over 400 man-days of service. This concept employs the methods of the existing flight-proven mature design, augmenting them to eliminate foreseen difficulties and to fully comply with the design requirements. The GE Improved WCS Concept includes separate storage for used wipes. Compaction of the wipes provides a solution to the capacity problem, fully satisfying the 210 man-day storage requirement. The added feature of in-flight serviceable storage space for the wipes creates a variable capacity feature which affords redundancy in the event of wipes compaction system failure. Addition of features permitting in-flight servicing of the feces storage tank creates a variable capacity WCS with easier post-flight servicing to support rapid turnaround of the Shuttle orbiter. When these features are combined with a vacuum pump to evacuate wipes and fecal storage tanks through replaceable odor/bacteria filters to the cabin, the GE Improved WCS satisfies the known requirements for Space Station use, including no venting to space.
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NASA Technical Reports Server (NTRS)
Griffin, Timothy P.; Naylor, Guy R.; Haskell, William D.; Breznik, Greg S.; Mizell, Carolyn A.; Helms, William R.; Steinrock, T. (Technical Monitor)
2001-01-01
An on-line gas monitoring system was developed to replace the older systems used to monitor for cryogenic leaks on the Space Shuttles before launch. The system uses a mass spectrometer to monitor multiple locations in the process, which allows the system to monitor all gas constituents of interest in a nearly simultaneous manner. The system is fully redundant and meets all requirements for ground support equipment (GSE). This includes ruggedness to withstand launch on the Mobile Launcher Platform (MLP), ease of operation, and minimal operator intervention. The system can be fully automated so that an operator is notified when an unusual situation or fault is detected. User inputs are through personal computer using mouse and keyboard commands. The graphical user interface is very intuitive and easy to operate. The system has successfully supported four launches to date. It is currently being permanently installed as the primary system monitoring the Space Shuttles during ground processing and launch operations. Time and cost savings will be substantial over the current systems when it is fully implemented in the field. Tests were performed to demonstrate the performance of the system. Low limits-of-detection coupled with small drift make the system a major enhancement over the current systems. Though this system is currently optimized for detecting cryogenic leaks, many other gas constituents could be monitored using the Hazardous Gas Detection System (HGDS) 2000.
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CFD Applications in Support of the Space Shuttle Risk Assessment
NASA Technical Reports Server (NTRS)
Baum, Joseph D.; Mestreau, Eric; Luo, Hong; Sharov, Dmitri; Fragola, Joseph; Loehner, Rainald; Cook, Steve (Technical Monitor)
2000-01-01
The paper describes a numerical study of a potential accident scenario of the space shuttle, operating at the same flight conditions as flight 51L, the Challenger accident. The interest in performing this simulation is derived by evidence that indicates that the event itself did not exert large enough blast loading on the shuttle to break it apart. Rather, the quasi-steady aerodynamic loading on the damaged, unbalance vehicle caused the break-up. Despite the enormous explosive potential of the shuttle total fuel load (both liquid and solid), the post accident explosives working group estimated the maximum energy involvement to be equivalent to about five hundreds of pounds of TNT. This understanding motivated the simulation described here. To err on the conservative side, we modeled the event as an explosion, and used the maximum energy estimate. We modeled the transient detonation of a 500 lbs spherical charge of TNT, placed at the main engine, and the resulting blast wave propagation about the complete stack. Tracking of peak pressures and impulses at hundreds of locations on the vehicle surface indicate that the blast load was insufficient to break the vehicle, hence demonstrating likely crew survivability through such an event.
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NASA Technical Reports Server (NTRS)
Margasahayam, Ravi N.; Meyer, Karl A.; Nerolich, Shaun M.; Burton, Roy C.; Gosselin, Armand M.
2004-01-01
The Crawler Transporter (CT), designed and built for the Apollo Program in the 1960's and surpassing its initial operational life, has become an integral part of the Space Shuttle Program (SSP). The CT transports the Space Shuttle Vehicle (SSV) stack, atop the Mobile Launch Platform (MLP), from the Vehicle Assembly Building (VAB) to the launch pad. This support structure provides hydraulic jacking, leveling and load equalization for the 12 million pound stack on its 3.5-5.0 mile rollout to the launch pad. Major elements of the SSV, consisting of the orbiter, solid rocket boosters (SRB) and external tank (ET) have required fatigue analyses as part of the mission life certification. Compared to rollout vibration, the SSV sees relatively high vibration loads during launch, ascent, descent and landing phases of the mission. Although preliminary measured SRB vibration levels during rollout were of low amplitude and frequency, the duration of the rollout phase is typically high, from 5-6 hours. As part of an expanded mission life assessment, additional certification effort was initiated to define fatigue load spectra for rollout. This study addresses the CT vibration analyses in support of the rollout fatigue study. Structural models developed for modal and vibration analyses were used to identify unique CT, CT/MLP and CT/MLP/SRB vibration characteristics for comparison to instrumented rollout tests. Whereas the main structural and vibration characteristics of the SSV are well defined, minimum analytical and vibration test data on the Crawler Transporter were available. Unique vibration characteristics of the CT are attributable to the drive mechanism, hydraulic jacking system, structural framing and the CT-to-MLP support pad restraints. Initial tests performed on the CT/MLP/SRB configuration showed reasonable correlation with predicted mode shapes and frequencies.
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EVA view of the Zenith (-ZA/FGB Plane III) side of the Functional Cargo Block (FGB).
1998-12-12
STS088-353-006 (4 -15 Dec. 1998) --- Astronaut James H. Newman, mission specialist, holds onto a handrail on Zarya while conducting a space walk at the top of the Unity-Zarya stack in the cargo bay of the Earth-orbiting Space Shuttle Endeavour. The open payload doors and part of the cargo bay, including the Ku-band antenna, are seen in upper left.
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2002-04-24
KENNEDY SPACE CENTER, FLA. -- A tug boat tows a newly arrived external tank in the Banana River to its offloading site. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. From there it will be transported to the Vehicle Assembly Building where the tank will await stacking for a future Shuttle mission
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker begins to remove the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP) on space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for the STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to remove the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP) on space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for the STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP) on space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for the STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker prepares to remove the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-11
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers examine one of the ground umbilical carrier plate's (GUCP) quick disconnects. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP) on space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for the STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers begin to remove the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove one of the ground umbilical carrier plate's (GUCP) quick disconnects. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jack Pfaller
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP) on space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for the STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect has been removed from the external fuel tank. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP) on space shuttle Discovery's external fuel tank. A hydrogen gas leak at that location during tanking for the STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2008-09-04
CAPE CANAVERAL, Fla. – Space shuttle Atlantis has passed the bend in the crawlerway taking it to Launch Pad 39A, above left, at NASA's Kennedy Space Center. The crawlerway is flanked by the Banana River at right and Banana Creek at left. The Atlantic Ocean stretches across the horizon. The shuttle stack, with solid rocket boosters and external fuel tank attached to Atlantis, rest on the mobile launcher platform. Movement is provided by the crawler-transporter underneath. First motion occurred at 9:19 a.m. EDT. The Sept. 2 rollout date was postponed due to Tropical Storm Hanna’s shift to a northern track. Atlantis is scheduled to launch on the STS-125 mission to service NASA’s Hubble Space Telescope. Launch is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Wheeler, Douglas; Ulsh, Michael
The results of two Manufacturing Readiness Assessments of PEM fuel cell stacks and material handling equipment (MHE) and backup power (BUP) PEM fuel cell systems are given. Design modifications of fuel cell systems were made because the initial, 2008 designs did not fully meet the operational requirements of the markets. This situation indicates the 2008 risk elements were overstated.For 2010 BUP and MHE fuel cell systems, manufacturers had not reached the Low Rate Initial Production (LRIP) defined in the 2008 MRA Report at 1,000 units per year per manufacturer.For fuel cell stacks, LRIP was demonstrated by more than one manufacturer.Themore » federal tax incentive program has compensated for the initial high cost of fuel cell systems.The Balance-of-Plant (BOP) has not evolved as rapidly as the PEM fuel cell stack manufacturing readiness.The BOP in 2014 is as costly as the fuel cell stack for MHE applications.« less
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Effect of stacking faults on the magnetocrystalline anisotropy of hcp Co: a first-principles study.
Aas, C J; Szunyogh, L; Evans, R F L; Chantrell, R W
2013-07-24
In terms of the fully relativistic screened Korringa-Kohn-Rostoker method we investigate the effect of stacking faults on the magnetic properties of hexagonal close-packed (hcp) cobalt. In particular, we consider the formation energy and the effect on the magnetocrystalline anisotropy energy (MAE) of four different stacking faults in hcp cobalt-an intrinsic growth fault, an intrinsic deformation fault, an extrinsic fault and a twin-like fault. We find that the intrinsic growth fault has the lowest formation energy, in good agreement with previous first-principles calculations. With the exception of the intrinsic deformation fault which has a positive impact on the MAE, we find that the presence of a stacking fault generally reduces the MAE of bulk Co. Finally, we consider a pair of intrinsic growth faults and find that their effect on the MAE is not additive, but synergic.
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Electrochemical Detection in Stacked Paper Networks.
Liu, Xiyuan; Lillehoj, Peter B
2015-08-01
Paper-based electrochemical biosensors are a promising technology that enables rapid, quantitative measurements on an inexpensive platform. However, the control of liquids in paper networks is generally limited to a single sample delivery step. Here, we propose a simple method to automate the loading and delivery of liquid samples to sensing electrodes on paper networks by stacking multiple layers of paper. Using these stacked paper devices (SPDs), we demonstrate a unique strategy to fully immerse planar electrodes by aqueous liquids via capillary flow. Amperometric measurements of xanthine oxidase revealed that electrochemical sensors on four-layer SPDs generated detection signals up to 75% higher compared with those on single-layer paper devices. Furthermore, measurements could be performed with minimal user involvement and completed within 30 min. Due to its simplicity, enhanced automation, and capability for quantitative measurements, stacked paper electrochemical biosensors can be useful tools for point-of-care testing in resource-limited settings. © 2015 Society for Laboratory Automation and Screening.
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Radiation Tolerant Intelligent Memory Stack (RTIMS)
NASA Technical Reports Server (NTRS)
Ng, Tak-kwong; Herath, Jeffrey A.
2006-01-01
The Radiation Tolerant Intelligent Memory Stack (RTIMS), suitable for both geostationary and low earth orbit missions, has been developed. The memory module is fully functional and undergoing environmental and radiation characterization. A self-contained flight-like module is expected to be completed in 2006. RTIMS provides reconfigurable circuitry and 2 gigabits of error corrected or 1 gigabit of triple redundant digital memory in a small package. RTIMS utilizes circuit stacking of heterogeneous components and radiation shielding technologies. A reprogrammable field programmable gate array (FPGA), six synchronous dynamic random access memories, linear regulator, and the radiation mitigation circuitries are stacked into a module of 42.7mm x 42.7mm x 13.00mm. Triple module redundancy, current limiting, configuration scrubbing, and single event function interrupt detection are employed to mitigate radiation effects. The mitigation techniques significantly simplify system design. RTIMS is well suited for deployment in real-time data processing, reconfigurable computing, and memory intensive applications.
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The Advantages of Non-Flow-Through Fuel Cell Power Systems for Aerospace Applications
NASA Technical Reports Server (NTRS)
Hoberecht, Mark; Burke, Kenneth; Jakupca, Ian
2011-01-01
NASA has been developing proton-exchange-membrane (PEM) fuel cell power systems for the past decade, as an upgraded technology to the alkaline fuel cells which presently provide power for the Shuttle Orbiter. All fuel cell power systems consist of one or more fuel cell stacks in combination with appropriate balance-of-plant hardware. Traditional PEM fuel cells are characterized as flow-through, in which recirculating reactant streams remove product water from the fuel cell stack. NASA recently embarked on the development of non-flow-through fuel cell systems, in which reactants are dead-ended into the fuel cell stack and product water is removed by internal wicks. This simplifies the fuel cell power system by eliminating the need for pumps to provide reactant circulation, and mechanical water separators to remove the product water from the recirculating reactant streams. By eliminating these mechanical components, the resulting fuel cell power system has lower mass, volume, and parasitic power requirements, along with higher reliability and longer life. These improved non-flow-through fuel cell power systems therefore offer significant advantages for many aerospace applications.
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NASA Technical Reports Server (NTRS)
Dinetta, L. C.; Hannon, M. H.; Cummings, J. R.; Mcneeley, J. B.; Barnett, Allen M.
1990-01-01
Free-standing, transparent, tunable bandgap AlxGa1-xAs top solar cells have been fabricated for mechanical attachment in a four terminal tandem stack solar cell. Evaluation of the device results has demonstrated 1.80 eV top solar cells with efficiencies of 18 percent (100 X, and AM0) which would yield stack efficiencies of 31 percent (100 X, AM0) with a silicon bottom cell. When fully developed, the AlxGa1-xAs/Si mechanically-stacked two-junction solar cell concentrator system can provide efficiencies of 36 percent (AM0, 100 X). AlxGa1-xAs top solar cells with bandgaps from 1.66 eV to 2.08 eV have been fabricated. Liquid phase epitaxy (LPE) growth techniques have been used and LPE has been found to yield superior AlxGa1-xAs material when compared to molecular beam epitaxy and metal-organic chemical vapor deposition. It is projected that stack assembly technology will be readily applicable to any mechanically stacked multijunction (MSMJ) system. Development of a wide bandgap top solar cell is the only feasible method for obtaining stack efficiencies greater than 40 percent at AM0. System efficiencies of greater than 40 percent can be realized when the AlGaAs top solar cell is used in a three solar cell mechanical stack.
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Method and apparatus for adding electrolyte to a fuel cell stack
DOE Office of Scientific and Technical Information (OSTI.GOV)
Congdon, J.V.; English, J.G.
1986-06-24
A process is described for adding electrolyte to a fuel cell stack, the stack comprising sheet-like elements defining a plurality of fuel cell units disposed one atop the other in abutting relationship, the units defining a substantially flat, vertically extending face, each unit including a cell comprising a pair of sheet-like spaced apart gas porous electrodes with a porous matrix layer sandwiched therebetween for retaining electrolyte during cell operation, each unit also including a sheet-like substantially non-porous separator, the separator being sandwiched between the cells of adjacent units. The improvement described here consists of: extending at least one of themore » sheet-like elements of each of a plurality of the fuel cell units outwardly from the stack face to define horizontal tabs disposed one above the other; depositing dilute electrolyte directly from electrolyte supply means upon substantially the full length, parallel to the stack face, of at least the uppermost tab, the tabs being constructed and arranged such that at least a portion of the deposited electrolyte cascades from tab to tab and down the face of the stack, the deposited electrolyte being absorbed by capillary action into the elements of the stack, the step of depositing continuing until all of the electrodes and matrix layers of the stack are fully saturated with the dilute electrolyte; and thereafter evaporating liquid from the saturated elements under controlled conditions of humidity and temperature until the stack has a desired electrolyte volume and electrolyte concentration therein.« less
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Analysis and Test of a Proton Exchange Membrane Fuel Cell Power System for Space Power Applications
NASA Technical Reports Server (NTRS)
Vasquez, Arturo; Varanauski, Donald; Clark, Robert, Jr.
2000-01-01
An effort is underway to develop a prototype Proton Exchange Membrane (PEM) Fuel Cell breadboard system for fuhlre space applications. This prototype will be used to develop a comprehensive design basis for a space-rated PEM fuel cell powerplant. The prototype system includes reactant pressure regulators, ejector-based reactant pumps, a 4-kW fuel cell stack and cooling system, and a passive, membranebased oxygen / water separator. A computer model is being developed concurrently to analytically predict fluid flow in the oxidant reactant system. Fuel cells have historically played an important role in human-rated spacecraft. The Gemini and Apollo spacecraft used fuel cells for vehicle electrical power. The Space Shuttle currently uses three Alkaline Fuel Cell Powerplants (AFCP) to generate all of the vehicle's 15-20kW electrical power. Engineers at the Johnson Space Center have leveraged off the development effort ongoing in the commercial arena to develop PEM fuel cel ls for terrestrial uses. The prototype design originated from efforts to develop a PEM fuel cell replacement for the current Space Shuttle AFCP' s. In order to improve on the life and an already excellent hi storical record of reliability and safety, three subsystems were focused on. These were the fuel cell stack itself, the reactant circulation devices, and reactant / product water separator. PEM fuel cell stack performance is already demonstrating the potential for greater than four times the useful life of the current Shuttle's AFCP. Reactant pumping for product water removal has historically been accomplished with mechanical pumps. Ejectors offer an effective means of reactant pumping as well as the potential for weight reduction, control simplification, and long life. Centrifugal water separation is used on the current AFCP. A passive, membrane-based water separator offers compatibility with the micro-gravity environment of space, and the potential for control simplification, elimination of moving parts in an oxygen environment, and long life. The prototype system has been assembled from components that have previously been tested and evaluated at the component level. Preliminary data obtained from tests performed with the prototype system, as well as other published data, has been used to validate the analytical component models. These components have been incorporated into an integrated oxidant fluid system model. Results obtained from both the performance tests and the analytical model are presented.
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Ensuring Safe Exploration: Ares Launch Vehicle Integrated Vehicle Ground Vibration Testing
NASA Technical Reports Server (NTRS)
Tuma, M. L.; Chenevert, D. J.
2009-01-01
Ground vibration testing has been an integral tool for developing new launch vehicles throughout the space age. Several launch vehicles have been lost due to problems that would have been detected by early vibration testing, including Ariane 5, Delta III, and Falcon 1. NASA will leverage experience and testing hardware developed during the Saturn and Shuttle programs to perform ground vibration testing (GVT) on the Ares I crew launch vehicle and Ares V cargo launch vehicle stacks. NASA performed dynamic vehicle testing (DVT) for Saturn and mated vehicle ground vibration testing (MVGVT) for Shuttle at the Dynamic Test Stand (Test Stand 4550) at Marshall Space Flight Center (MSFC) in Huntsville, Alabama, and is now modifying that facility to support Ares I integrated vehicle ground vibration testing (IVGVT) beginning in 2012. The Ares IVGVT schedule shows most of its work being completed between 2010 and 2014. Integrated 2nd Stage Ares IVGVT will begin in 2012 and IVGVT of the entire Ares launch stack will begin in 2013. The IVGVT data is needed for the human-rated Orion launch vehicle's Design Certification Review (DCR) in early 2015. During the Apollo program, GVT detected several serious design concerns, which NASA was able to address before Saturn V flew, eliminating costly failures and potential losses of mission or crew. During the late 1970s, Test Stand 4550 was modified to support the four-body structure of the Space Shuttle. Vibration testing confirmed that the vehicle's mode shapes and frequencies were better than analytical models suggested, however, the testing also identified challenges with the rate gyro assemblies, which could have created flight instability and possibly resulted in loss of the vehicle. Today, NASA has begun modifying Test Stand 4550 to accommodate Ares I, including removing platforms needed for Shuttle testing and upgrading the dynamic test facilities to characterize the mode shapes and resonant frequencies of the vehicle. The IVGVT team expects to collect important information about the new launch vehicles, greatly increasing astronaut safety as NASA prepares to explore the Moon and beyond.
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Solid polymer membrane program
NASA Technical Reports Server (NTRS)
1971-01-01
The results are presented for a solid polymer electrolyte fuel cell development program. Failure mechanism was identified and resolution of the mechanism experienced in small stack testing was demonstrated. The effect included laboratory analysis and evaluation of a matrix of configurations and operational variables for effects on the degree of hydrogen fluoride released from the cell and on the degree of blistering/delamination occurring in the reactant inlet areas of the cell and to correlate these conditions with cell life capabilities. The laboratory evaluation tests were run at conditions intended to accelerate the degradation of the solid polymer electrolyte in order to obtain relative evaluations as quick as possible. Evaluation of the resolutions for the identified failure mechanism in space shuttle configuration cell assemblies was achieved with the fabrication and life testing of two small stack buildups of four cell assemblies and eight cells each.
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A History of Space Shuttle Main Engine (SSME) Redline Limits Management
NASA Technical Reports Server (NTRS)
Arnold, Thomas M.
2011-01-01
The Space Shuttle Main Engine (SSME) has several "redlines", which are operational limits designated to preclude a catastrophic shutdown of the SSME. The Space Shuttle Orbiter utilizes a combination of hardware and software to enable or disable the automated redline shutdown capability. The Space Shuttle is launched with the automated SSME redline limits enabled, but there are many scenarios which may result in the manual disabling of the software by the onboard crew. The operational philosophy for manually enabling and disabling the redline limits software has evolved continuously throughout the history of the Space Shuttle Program, due to events such as SSME hardware changes and updates to Space Shuttle contingency abort software. In this paper, the evolution of SSME redline limits management will be fully reviewed, including the operational scenarios which call for manual intervention, and the events that triggered changes to the philosophy. Following this review, improvements to the management of redline limits for future spacecraft will be proposed.
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2002-07-25
KENNEDY SPACE CENTER, FLA. -- In Vehicle Assembly Building (VAB) high bay 4, installation of a Payload Bay Door Drying Enclosure is in progress. The enclosure will keep moisture from being absorbed into the graphite epoxy used on the payload bay doors of the Shuttle orbiters with the assistance of mini-Portable Purge Units (PPUs). Once in operation, the enclosure will allow NASA the option to store an orbiter in the VAB bay up to 180 days in a "standby-to-stack" mode.
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2002-07-25
KENNEDY SPACE CENTER, FLA. -- In Vehicle Assembly Building (VAB) high bay 4, installation of a Payload Bay Door Drying Enclosure is in progress. The enclosure will keep moisture from being absorbed into the graphite epoxy used on the payload bay doors of the Shuttle orbiters with the assistance of mini-Portable Purge Units (PPUs). Once in operation, the enclosure will allow NASA the option to store an orbiter in the VAB bay up to 180 days in a "standby-to-stack" mode.
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2002-07-26
KENNEDY SPACE CENTER, FLA. -- -- In Vehicle Assembly Building (VAB) high bay 4, installation of a Payload Bay Door Drying Enclosure is in progress. The enclosure will keep moisture from being absorbed into the graphite epoxy used on the payload bay doors of the Shuttle orbiters with the assistance of mini-Portable Purge Units (PPUs). Once in operation, the enclosure will allow NASA the option to store an orbiter in the VAB bay up to 180 days in a "standby-to-stack" mode.
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An external tank is moved from a barge in the turn basin to the VAB
NASA Technical Reports Server (NTRS)
2000-01-01
A newly arrived external tank is transported from the turn basin to the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission.
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An external tank is moved from a barge in the turn basin to the VAB
NASA Technical Reports Server (NTRS)
2000-01-01
A newly arrived external tank heads from the turn basin toward the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission.
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is towed into the Orbiter Processing Facility. Atlantis was removed from its external fuel tank and solid rocket boosters stack in the Vehicle Assembly Building after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Dimitri Gerondidakis
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is towed into the Orbiter Processing Facility. Atlantis was removed from its external fuel tank and solid rocket boosters stack in the Vehicle Assembly Building after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Tim Jacobs
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Tubular gage for a liquid-metal-cooled fast breeder reactor
Hutter, Ernest; Tuma, Leroy A.
1977-06-14
Spring-loaded plungers are arranged about a housing for insertion into a polygonal tube, one plunger for each side of the tube. Each plunger has a locking cam and sliding wedge mechanism which can overcome the spring force associated with the plunger and lock it in any position. The wedges are operated by a rod moveable axially in the housing. Several housings with their associated plungers can be stacked. The stack is lowered into the polygonal tube with all of the plungers locked in a fully inward position. When the stack is in the tube, each wedge is moved to release its locking cam, allowing each of the plungers to spring outward against an inner side of the tube. Each housing will thus gage the internal dimensions of the tube at its elevation. The plungers are locked in position, the entire stack is rotated to bring the plungers into the corners described by the intersections of the flat sides, and the stack is removed from the tube whereupon the dimensions across opposite locked plungers may be read by a micrometer.
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Integrated Evaluation of Reliability and Power Consumption of Wireless Sensor Networks.
Dâmaso, Antônio; Rosa, Nelson; Maciel, Paulo
2017-11-05
Power consumption is a primary interest in Wireless Sensor Networks (WSNs), and a large number of strategies have been proposed to evaluate it. However, those approaches usually neither consider reliability issues nor the power consumption of applications executing in the network. A central concern is the lack of consolidated solutions that enable us to evaluate the power consumption of applications and the network stack also considering their reliabilities. To solve this problem, we introduce a fully automatic solution to design power consumption aware WSN applications and communication protocols. The solution presented in this paper comprises a methodology to evaluate the power consumption based on the integration of formal models, a set of power consumption and reliability models, a sensitivity analysis strategy to select WSN configurations and a toolbox named EDEN to fully support the proposed methodology. This solution allows accurately estimating the power consumption of WSN applications and the network stack in an automated way.
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Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration
NASA Technical Reports Server (NTRS)
Glynn, J. L.; Poucher, D. E.
1988-01-01
Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter, and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 2) of the report -- Booster Configuration.
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Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration
NASA Technical Reports Server (NTRS)
Glynn, J. L.; Poucher, D. E.
1988-01-01
Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks, and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 1) of the report -- Booster Configuration.
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Space shuttle phase B wind tunnel model and test information. Volume 3: Launch configuration
NASA Technical Reports Server (NTRS)
Glynn, J. L.; Poucher, D. E.
1988-01-01
Archived wind tunnel test data are available for flyback booster or other alternate recoverable configuration as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle, including contractor data for an extensive variety of configurations with an array of wing and body planforms. The test data have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration. Basic components include booster, orbiter, and launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configurations include straight and delta wings, lifting body, drop tanks and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. The digital database consists of 220 files containing basic tunnel data. Database structure is documented in a series of reports which include configuration sketches for the various planforms tested. This is Volume 3 -- launch configurations.
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2004-08-03
KENNEDY SPACE CENTER, FLA. - In the Space Shuttle Main Engine (SSME) Processing Facility, Boeing-Rocketdyne crane operator Joe Ferrante (left) lowers SSME 2058, the first SSME fully assembled at KSC, onto an engine stand with the assistance of other technicians on his team. The engine is being moved from its vertical work stand into a horizontal position in preparation for shipment to NASA’s Stennis Space Center in Mississippi to undergo a hot fire acceptance test. It is the first of five engines to be fully assembled on site to reach the desired number of 15 engines ready for launch at any given time in the Space Shuttle program. A Space Shuttle has three reusable main engines. Each is 14 feet long, weighs about 7,800 pounds, is seven-and-a-half feet in diameter at the end of its nozzle, and generates almost 400,000 pounds of thrust. Historically, SSMEs were assembled in Canoga Park, Calif., with post-flight inspections performed at KSC. Both functions were consolidated in February 2002. The Rocketdyne Propulsion and Power division of The Boeing Co. manufactures the engines for NASA.
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2004-08-03
KENNEDY SPACE CENTER, FLA. - In the Space Shuttle Main Engine (SSME) Processing Facility, Boeing-Rocketdyne crane operator Joe Ferrante (second from right) lifts SSME 2058, the first SSME fully assembled at KSC, with the assistance of other technicians on his team. The engine is being lifted from its vertical work stand into a horizontal position in preparation for shipment to NASA’s Stennis Space Center in Mississippi to undergo a hot fire acceptance test. It is the first of five engines to be fully assembled on site to reach the desired number of 15 engines ready for launch at any given time in the Space Shuttle program. A Space Shuttle has three reusable main engines. Each is 14 feet long, weighs about 7,800 pounds, is seven-and-a-half feet in diameter at the end of its nozzle, and generates almost 400,000 pounds of thrust. Historically, SSMEs were assembled in Canoga Park, Calif., with post-flight inspections performed at KSC. Both functions were consolidated in February 2002. The Rocketdyne Propulsion and Power division of The Boeing Co. manufactures the engines for NASA.
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NASA Technical Reports Server (NTRS)
2004-01-01
KENNEDY SPACE CENTER, FLA. In the Space Shuttle Main Engine (SSME) Processing Facility, Boeing-Rocketdyne quality inspector Nick Grimm (center) monitors the work of technicians on his team as they lower SSME 2058, the first SSME fully assembled at KSC, onto an engine stand. The engine is being placed into a horizontal position in preparation for shipment to NASAs Stennis Space Center in Mississippi to undergo a hot fire acceptance test. It is the first of five engines to be fully assembled on site to reach the desired number of 15 engines ready for launch at any given time in the Space Shuttle program. A Space Shuttle has three reusable main engines. Each is 14 feet long, weighs about 7,800 pounds, is seven-and-a-half feet in diameter at the end of its nozzle, and generates almost 400,000 pounds of thrust. Historically, SSMEs were assembled in Canoga Park, Calif., with post-flight inspections performed at KSC. Both functions were consolidated in February 2002. The Rocketdyne Propulsion and Power division of The Boeing Co. manufactures the engines for NASA.
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2004-08-03
KENNEDY SPACE CENTER, FLA. - In the Space Shuttle Main Engine (SSME) Processing Facility, Boeing-Rocketdyne quality inspector Nick Grimm (center) monitors the work of technicians on his team as they lower SSME 2058, the first SSME fully assembled at KSC, onto an engine stand. The engine is being placed into a horizontal position in preparation for shipment to NASA’s Stennis Space Center in Mississippi to undergo a hot fire acceptance test. It is the first of five engines to be fully assembled on site to reach the desired number of 15 engines ready for launch at any given time in the Space Shuttle program. A Space Shuttle has three reusable main engines. Each is 14 feet long, weighs about 7,800 pounds, is seven-and-a-half feet in diameter at the end of its nozzle, and generates almost 400,000 pounds of thrust. Historically, SSMEs were assembled in Canoga Park, Calif., with post-flight inspections performed at KSC. Both functions were consolidated in February 2002. The Rocketdyne Propulsion and Power division of The Boeing Co. manufactures the engines for NASA.
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers take photos of the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect, which has been removed from the external fuel tank. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers take photos of the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect, which has been removed from the external fuel tank. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove the vent line attached to the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- As the sun rises over Launch Pad 39A at NASA's Kennedy Space Center in Florida, preparations to remove the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect are under way. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-10
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers take photos of the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect, which has been removed from the external fuel tank. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the vent line is detached from the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the vent line is detached from the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the tip-top of the bright-orange external fuel tank is where workers will prepare to begin removing the quick disconnect from the ground umbilical carrier plate (GUCP). A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is targeted for no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the vent line is detached from the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-10
CAPE CANAVERAL, Fla. -- As the sun begins to rise over Launch Pad 39A at NASA's Kennedy Space Center in Florida, preparations to remove the ground umbilical carrier plate's (GUCP) 7-inch quick disconnect are under way. A hydrogen gas leak at that location on the external fuel tank during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Troy Cryder
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1987-07-01
A forward segment is being lowered into the Transient Pressure Test Article (TPTA) test stand at the Marshall Space Flight Center (MSFC) east test area. The TPTA test stand, 14-feet wide, 27-feet long, and 33-feet high, was built in 1987 to provide data to verify the sealing capability of the redesign solid rocket motor (SRM) field and nozzle joints. The test facility applies pressure, temperature, and external loads to a short stack of solid rocket motor hardware. The simulated SRM ignition pressure and temperature transients are achieved by firing a small amount of specially configured solid propellant. The pressure transient is synchronized with external programmable dynamic loads that simulate lift off loads at the external tank attach points. Approximately one million pounds of dead weight on top of the test article simulates the weight of the other Shuttle elements.
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1987-07-01
A forward segment is being lowered into the Transient Pressure Test Article (TPTA) test stand at thw Marshall Space Flight Center (MSFC) east test area. The TPTA test stand, 14-feet wide, 27-feet long, and 33-feet high, was built in 1987 to provide data to verify the sealing capability of the redesign solid rocket motor (SRM) field and nozzle joints. The test facility applies pressure, temperature, and external loads to a short stack of solid rocket motor hardware. The simulated SRM ignition pressure and temperature transients are achieved by firing a small amount of specially configured solid propellant. The pressure transient is synchronized with external programmable dynamic loads that simulate lift off loads at the external tank attach points. Approximately one million pounds of dead weight on top of the test article simulates the weight of the other Shuttle elements.
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2002-09-10
KENNEDY SPACE CENTER, FLA. -- After an early morning rollout, Space Shuttle Atlantis sits on the launch pad. Visible near the tail are the tail service masts that support the fluid, gas and electrical requirements of the orbiter's liquid oxygen and liquid hydrogen aft T-0 umbilicals. After being stacked with its solid rocket boosters and external tank, Atlantis began its rollout to Launch Pad 39B at 2:27 a.m. EDT in preparation for launch to the International Space Station. The Shuttle arrived at the Pad and was hard down at 9:38 a.m. Launch is scheduled no earlier than Oct. 2 for mission STS-112, the 15th assembly flight to the International Space Station. Atlantis will carry the S1 Integrated Truss Structure, which will be attached to the central truss segment, the S0 truss, during the mission.
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STS-28 Columbia, OV-102, ET/SRB mating preparations at KSC VAB
1989-07-03
S89-39624 (3 July 1989) --- Following rollover from the Orbiter Processing Facility, the orbiter Columbia is prepared for mating with the ET/SRB stack in the Vehicle Assembly Building transfer aisle as work continues toward an early August launch of Space Shuttle Mission STS-28. STS-28 is a Department of Defense dedicated mission. Crew members for the mission are: Commander Brewster H. Shaw, Pilot Richard N. Richards, and Mission Specialists Mark N. Brown, James C. Adamson, and David C. Leestma.
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A theoretical/experimental program to develop active optical pollution sensors, part 2
NASA Technical Reports Server (NTRS)
Poultney, S. K.
1975-01-01
Progress is reported on experimental investigations of Lidar and the application of Lidar to environmental and atmospheric science. Specifically the following programs are considered: calibration and application of the LaRC 48-inch Lidar; efficient and certain detection of SO2 and other gases in the calibration tank using the Raman Stack Monitor Lidar; the potential of Lidar remote sensing from the space shuttle; and the planning and mounting of efforts to realize the promise of backscatter differential absorption Lidar.
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is towed from the Vehicle Assembly Building to the Orbiter Processing Facility at NASA's Kennedy Space Center in Florida. Atlantis was removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Tim Jacobs
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Supersonic/Hypersonic Correlations for In-Cavity Transition and Heating Augmentation
NASA Technical Reports Server (NTRS)
Everhart, Joel L.
2011-01-01
Laminar-entry cavity heating data with a non-laminar boundary layer exit flow have been retrieved from the database developed at Mach 6 and 10 in air on large flat plate models for the Space Shuttle Return-To-Flight Program. Building on previously published fully laminar and fully turbulent analysis methods, new descriptive correlations of the in-cavity floor-averaged heating and endwall maximum heating have been developed for transitional-to-turbulent exit flow. These new local-cavity correlations provide the expected flow and geometry conditions for transition onset; they provide the incremental heating augmentation induced by transitional flow; and, they provide the transitional-to-turbulent exit cavity length. Furthermore, they provide an upper application limit for the previously developed fully-laminar heating correlations. An example is provided that demonstrates simplicity of application. Heating augmentation factors of 12 and 3 above the fully laminar values are shown to exist on the cavity floor and endwall, respectively, if the flow exits in fully tripped-to-turbulent boundary layer state. Cavity floor heating data in geometries installed on the windward surface of 0.075-scale Shuttle wind tunnel models have also been retrieved from the boundary layer transition database developed for the Return-To-Flight Program. These data were independently acquired at Mach 6 and Mach 10 in air, and at Mach 6 in CF4. The correlation parameters for the floor-averaged heating have been developed and they offer an exceptionally positive comparison to previously developed laminar-cavity heating correlations. Non-laminar increments have been extracted from the Shuttle data and they fall on the newly developed transitional in-cavity correlations, and they are bounded by the 95% correlation prediction limits. Because the ratio of specific heats changes along the re-entry trajectory, turning angle into a cavity and boundary layer flow properties may be affected, raising concerns regarding the application validity of the heating augmentation predictions.
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Zou, Xiao; Xu, Jingping; Huang, Hao; Zhu, Ziqang; Wang, Hongjiu; Li, Borui; Liao, Lei; Fang, Guojia
2018-06-15
Top-gated and bottom-gated transistors with multilayer MoS 2 channel fully encapsulated by stacked Al 2 O 3 /HfO 2 (9 nm/6 nm) were fabricated and comparatively studied. Excellent electrical properties are demonstrated for the TG transistors with high on-off current ratio of 10 8 , high field-effect mobility of 10 2 cm 2 V -1 s -1 , and low subthreshold swing of 93 mV dec -1 . Also, enhanced reliability has been achieved for the TG transistors with threshold voltage shift of 10 -3 -10 -2 V MV -1 cm -1 after 6 MV cm -1 gate-biased stressing. All improvement for the TG device can be ascribed to the formed device structure and dielectric environment. Degradation of the performance for the BG transistors should be attributed to reduced gate capacitance density and deteriorated interface properties related to vdW gap with a thickness about 0.4 nm. So, the TG transistor with MoS 2 channel fully encapsulated by stacked Al 2 O 3 /HfO 2 is a promising way to fabricate high-performance ML MoS 2 field-effect transistors for practical electron device applications.
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NASA Astrophysics Data System (ADS)
Zou, Xiao; Xu, Jingping; Huang, Hao; Zhu, Ziqang; Wang, Hongjiu; Li, Borui; Liao, Lei; Fang, Guojia
2018-06-01
Top-gated and bottom-gated transistors with multilayer MoS2 channel fully encapsulated by stacked Al2O3/HfO2 (9 nm/6 nm) were fabricated and comparatively studied. Excellent electrical properties are demonstrated for the TG transistors with high on–off current ratio of 108, high field-effect mobility of 102 cm2 V‑1 s‑1, and low subthreshold swing of 93 mV dec–1. Also, enhanced reliability has been achieved for the TG transistors with threshold voltage shift of 10‑3–10‑2 V MV–1 cm–1 after 6 MV cm‑1 gate-biased stressing. All improvement for the TG device can be ascribed to the formed device structure and dielectric environment. Degradation of the performance for the BG transistors should be attributed to reduced gate capacitance density and deteriorated interface properties related to vdW gap with a thickness about 0.4 nm. So, the TG transistor with MoS2 channel fully encapsulated by stacked Al2O3/HfO2 is a promising way to fabricate high-performance ML MoS2 field-effect transistors for practical electron device applications.
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NASA Astrophysics Data System (ADS)
Kalaycıoğlu, Barış; Husnu Dirikolu, M.
2010-09-01
In this study, a Type III composite pressure vessel (ISO 11439:2000) loaded with high internal pressure is investigated in terms of the effect of the orientation of the element coordinate system while simulating the continuous variation of the fibre angle, the effect of symmetric and non-symmetric composite wall stacking sequences, and lastly, a stacking sequence evaluation for reducing the cylindrical section-end cap transition region stress concentration. The research was performed using an Ansys® model with 2.9 l volume, 6061 T6 aluminium liner/Kevlar® 49-Epoxy vessel material, and a service internal pressure loading of 22 MPa. The results show that symmetric stacking sequences give higher burst pressures by up to 15%. Stacking sequence evaluations provided a further 7% pressure-carrying capacity as well as reduced stress concentration in the transition region. Finally, the Type III vessel under consideration provides a 45% lighter construction as compared with an all metal (Type I) vessel.
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CdSe quantum dot sensitized solar cells. Shuttling electrons through stacked carbon nanocups.
Farrow, Blake; Kamat, Prashant V
2009-08-12
The charge separation between excited CdSe semiconductor quantum dots and stacked-cup carbon nanotubes (SCCNTs) has been successfully tapped to generate photocurrent in a quantum dot sensitized solar cell (QDSC). By employing an electrophoretic deposition technique we have cast SCCNT-CdSe composite films on optically transparent electrodes (OTEs). The quenching of CdSe emission, as well as transient absorption measurements, confirms ultrafast electron transfer to SCCNTs. The rate constant for electron transfer increases from 9.51 x 10(9) s(-1) to 7.04 x 10(10) s(-1) as we decrease the size of CdSe nanoparticles from 4.5 to 3 nm. The ability of SCCNTs to collect and transport electrons from excited CdSe has been established from photocurrent measurements. The morphological and excited state properties of SCCNT-CdSe composites demonstrate their usefulness in energy conversion devices.
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NASA Technical Reports Server (NTRS)
Leestma, David
2013-01-01
David Leestma was EV-1 for the STS-41G extravehicular activity (EVA) with Kathy Sullivan (first American female spacewalker). They conducted an EVA to fully demonstrate the feasibility of refueling satellites from the Space Shuttle, and performed the first contingency EVA task involving the Ku-band antenna. STS-41G was the fourth Space Shuttle mission to perform an EVA, and Leestma related his experiences with training, the spacesuit, and EVA tasks that were conducted on October 11, 1984 during this mission.
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NASA Technical Reports Server (NTRS)
Griffin, T. P.; Naylor, G. R.; Haskell, W. D.; Breznik, G. S.; Mizell, C. A.; Steinrock, Todd (Technical Monitor)
2001-01-01
This paper presents an on-line mass spectrometer designed to monitor for cryogenic leaks on the Space Shuttle. The topics include: 1) Hazardous Gas Detection Lab; 2) LASRE Test Support; 3) Background; 4) Location of Systems; 5) Sample Lines for Gas Detection; 6) Problems with Current Systems; 7) Requirements for New System (Nitrogen and Helium Background); and 8) HGDS 2000. This paper is in viewgraph form.
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Lactate: link between glycolytic and oxidative metabolism.
Brooks, George A
2007-01-01
Once thought to be the consequence of oxygen lack in contracting skeletal muscle, the glycolytic product lactate is formed and utilised continuously under fully aerobic conditions. 'Cell-cell' and 'intracellular lactate shuttle' concepts describe the roles of lactate in delivery of oxidative and gluconeogenic substrates as well as in cell signalling. Examples of cell-cell shuttles include lactate exchanges (i) between white-glycolytic and red-oxidative fibres within a working muscle bed; (ii) between working skeletal muscle and heart; and (iii) between tissues of net lactate release and gluconeogenesis. Lactate shuttles exist in diverse tissues including in the brain, where a shuttle between astrocytes and neurons is linked to glutamatergic signalling. Because lactate, the product of glycogenolysis and glycolysis, is disposed of by oxidative metabolism, lactate shuttling unites the two major processes of cellular energy transduction. Lactate disposal is mainly through oxidation, especially during exercise when oxidation accounts for 70-75% of removal and gluconeogenesis the remainder. Lactate flux occurs down proton and concentration gradients that are established by the mitochondrial lactate oxidation complex. Marathon running is a power activity requiring high glycolytic and oxidative fluxes; such activities require lactate shuttling. Knowledge of the lactate shuttle is yet to be imparted to the sport.
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Study of Alternate Space Shuttle Concepts. Volume 2. Part 1: Concept Analysis and Definition
NASA Technical Reports Server (NTRS)
1971-01-01
Three different space shuttle systems have been defined and analyzed. The first is a stage-and-one-half system optimized to meet program requirements. The second is a two-stage, fully reusable system also designed to meet program requirements. The third is a convertible system which operates initially as a stage-and-one-half system and is subsequently converted to a two-stage, fully reusable system by reconfiguration of the orbiter vehicle and development of a booster vehicle. The design and performance of this third system must necessarily be compromised somewhat to facilitate the conversion. For each system, the applicable requirements, ground rules, and assumptions are defined. The characteristics of each system are listed and a detailed description and analysis of the system are presented. Finally, a cost analysis for the system is given.
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers begin to remove the vent line attached to the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker begins to remove the vent line attached to the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers begin to remove the vent line attached to the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers begin to remove the vent line attached to the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-09
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers begin to remove the vent line attached to the ground umbilical carrier plate (GUCP) on the bright-orange external fuel tank. Next, the GUCP's 7-inch quick disconnect will be removed. A hydrogen gas leak at that location during tanking for space shuttle Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP will be examined to determine the cause of the hydrogen leak and then repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Discovery's next launch attempt is no earlier than Nov. 30 at 4:02 a.m. EST. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin
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2010-11-30
CAPE CANAVERAL, Fla. -- On Launch Pad 39A at NASA's Kennedy Space Center in Florida, the ground umbilical carrier plate (GUCP) and cracks on space shuttle Discovery's external fuel have been repaired. A hydrogen gas leak at the GUCP during tanking for Discovery's STS-133 mission to the International Space Station caused the launch attempt to be scrubbed Nov. 5. The GUCP is the overboard vent to the pad and the flame stack where the excess hydrogen is burned off. Also during initial loading operations, the foam cracked on two of the tank's 108 stringers, which are the composite aluminum ribs located vertically on the intertank area. Discovery's next launch attempt is no earlier than Dec. 17 at 8:51 p.m. EST. Until then, engineers will continue to analyze data from the GUCP and stringer crack repairs. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston
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Managing computer-controlled operations
NASA Technical Reports Server (NTRS)
Plowden, J. B.
1985-01-01
A detailed discussion of Launch Processing System Ground Software Production is presented to establish the interrelationships of firing room resource utilization, configuration control, system build operations, and Shuttle data bank management. The production of a test configuration identifier is traced from requirement generation to program development. The challenge of the operational era is to implement fully automated utilities to interface with a resident system build requirements document to eliminate all manual intervention in the system build operations. Automatic update/processing of Shuttle data tapes will enhance operations during multi-flow processing.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Stange, H., E-mail: helena.stange@helmholtz-berlin.de; Brunken, S.; Hempel, H.
While presence of Na is essential for the performance of high-efficiency Cu(In,Ga)Se{sub 2} thin film solar cells, the reasons why addition of Na by post-deposition treatment is superior to pre-deposition Na supply—particularly at low growth temperatures—are not yet fully understood. Here, we show by X-ray diffraction and electron microscopy that Na impedes annihilation of stacking faults during the Cu-poor/Cu-rich transition of low temperature 3-stage co-evaporation and prevents Cu homogeneity on a microscopic level. Lower charge carrier mobilities are found by optical pump terahertz probe spectroscopy for samples with remaining high stacking fault density, indicating a detrimental effect on electronic propertiesmore » if Na is present during growth.« less
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2004-08-03
KENNEDY SPACE CENTER, FLA. - In the Space Shuttle Main Engine (SSME) Processing Facility, Boeing-Rocketdyne technicians prepare to move SSME 2058, the first SSME fully assembled at KSC. Move conductor Bob Brackett (on ladder) supervises the placement of a sling around the engine with the assistance of crane operator Joe Ferrante (center) and a technician. The engine will be lifted from its vertical work stand into a horizontal position in preparation for shipment to NASA’s Stennis Space Center in Mississippi to undergo a hot fire acceptance test. It is the first of five engines to be fully assembled on site to reach the desired number of 15 engines ready for launch at any given time in the Space Shuttle program. A Space Shuttle has three reusable main engines. Each is 14 feet long, weighs about 7,800 pounds, is seven-and-a-half feet in diameter at the end of its nozzle, and generates almost 400,000 pounds of thrust. Historically, SSMEs were assembled in Canoga Park, Calif., with post-flight inspections performed at KSC. Both functions were consolidated in February 2002. The Rocketdyne Propulsion and Power division of The Boeing Co. manufactures the engines for NASA.
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Integrated Evaluation of Reliability and Power Consumption of Wireless Sensor Networks
Dâmaso, Antônio; Maciel, Paulo
2017-01-01
Power consumption is a primary interest in Wireless Sensor Networks (WSNs), and a large number of strategies have been proposed to evaluate it. However, those approaches usually neither consider reliability issues nor the power consumption of applications executing in the network. A central concern is the lack of consolidated solutions that enable us to evaluate the power consumption of applications and the network stack also considering their reliabilities. To solve this problem, we introduce a fully automatic solution to design power consumption aware WSN applications and communication protocols. The solution presented in this paper comprises a methodology to evaluate the power consumption based on the integration of formal models, a set of power consumption and reliability models, a sensitivity analysis strategy to select WSN configurations and a toolbox named EDEN to fully support the proposed methodology. This solution allows accurately estimating the power consumption of WSN applications and the network stack in an automated way. PMID:29113078
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NASA Technical Reports Server (NTRS)
Friend, Robert B.
1998-01-01
In the modeling of spacecraft dynamics it is important to accurately characterize the environment in which the vehicle operates, including the environments induced by the vehicle itself. On the Space Shuttle these induced environmental factors include reaction control system plume. Knowledge of these environments is necessary for performance of control systems and loads analyses, estimation of disturbances due to thruster firings, and accurate state vector propagation. During the STS-71 mission, while the Orbiter was performing attitude control for the mated Orbiter/Mir stack, it was noted that the autopilot was limit cycling at a rate higher than expected from pre-flight simulations. Investigations during the mission resulted in the conjecture that an unmodelled plume impingement force was acting upon the orbiter elevons. The in-flight investigations were not successful in determining the actual magnitude of the impingement, resulting in several sequential post-flight investigations. Efforts performed to better quantify the vernier reaction control system induced plume impingement environment of the Space Shuttle orbiter are described in this paper, and background detailing circumstances which required the more detailed knowledge of the RCS self impingement forces, as well as a description of the resulting investigations and their results is presented. The investigations described in this paper applied microgravity acceleration data from two shuttle borne microgravity experiments, SAMS and OARE, to the solution of this particular problem. This solution, now used by shuttle analysts and mission planners, results in more accurate propellant consumption and attitude limit cycle estimates in preflight analyses, which are critical for pending International Space Station missions.
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1999-05-16
KENNEDY SPACE CENTER, FLA. -- A crawler transporter moves Space Shuttle Discovery, with its external tank and solid rocket boosters, from Pad 39B back to the Vehicle Assembly Building (VAB) at left to repair damage to the external tank's foam insulation caused by hail. The external tank-solid rocket booster stack for mission STS-93, which was moved out of High Bay 1 to make room for Discovery, can be seen in the background between Discovery and the VAB. The necessary repair work could not be performed at the pad due to limited access to the damaged areas. The work is expected to take two to three days, allowing Discovery to roll back to Pad 39B by midweek for launch of mission STS-96, the 94th launch in the Space Shuttle Program. This is only the 13th time since 1981 that a Shuttle has had to roll back from the pad. Liftoff will occur no earlier than May 27. STS-96 is a logistics and resupply mission for the International Space Station, carrying such payloads as a Russian crane, the Strela; a U.S.-built crane; the Spacehab Oceaneering Space System Box (SHOSS), a logistics items carrier; and STARSHINE, a student-shared experiment
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1999-05-16
KENNEDY SPACE CENTER, FLA. -- On a beautiful Florida morning, a crawler transporter moves Space Shuttle Discovery (right, nearly hidden behind its external tank and solid rocket boosters) from Pad 39B back to the Vehicle Assembly Building (VAB) at left to repair damage to the external tank's foam insulation caused by hail. The external tank-solid rocket booster stack for mission STS-93 was moved out of High Bay 1, which awaits Discovery's arrival with its door open. The necessary repair work could not be performed at the pad due to limited access to the damaged areas. The work is expected to take two to three days, allowing Discovery to roll back to Pad 39B by midweek for launch of mission STS-96, the 94th launch in the Space Shuttle Program. This is only the 13th time since 1981 that a Shuttle has had to roll back from the pad. Liftoff will occur no earlier than May 27. STS-96 is a logistics and resupply mission for the International Space Station, carrying such payloads as a Russian crane, the Strela; a U.S.-built crane; the Spacehab Oceaneering Space System Box (SHOSS), a logistics items carrier; and STARSHINE, a student-shared experiment
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1999-05-16
KENNEDY SPACE CENTER, FLA. -- A crawler transporter moves Space Shuttle Discovery, hidden by its external tank and solid rocket boosters, from Pad 39B back to the Vehicle Assembly Building (VAB) for repair of damage to the external tank foam insulation caused by hail. The external tank/solid rocket booster stack for mission STS-93 was moved out of High Bay 1 to make room for Discovery and can be seen on the horizon between Discovery and the VAB. The necessary repair work could not be performed at the pad due to limited access to the damaged areas. The work is expected to take two to three days, allowing Discovery to roll back to Pad 39B by midweek for launch of mission STS-96, the 94th launch in the Space Shuttle Program. This is only the 13th time since 1981 that a Shuttle has had to roll back from the pad. Liftoff will occur no earlier than May 27. STS-96 is a logistics and resupply mission for the International Space Station, carrying such payloads as a Russian crane, the Strela; a U.S.-built crane; the Spacehab Oceaneering Space System Box (SHOSS), a logistics items carrier; and STARSHINE, a student-shared experiment
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Fuel cell technology program contract summary report
NASA Technical Reports Server (NTRS)
1972-01-01
A fuel cell technology program which was established to advance the state-of-the-art of hydrogen-oxygen fuel cells using the P and WA PC8B technology as the base is reported. The major tasks of this program consisted of (1) fuel cell system studies of a space shuttle powerplant conceptual design (designated engineering model -1, EM-1) supported by liaison with the space shuttle prime contractors; (2) component and subsystem technology advancement and; (3) a demonstrator powerplant test. Fuel cell system studies, with the EM-1 as the focal point of design activities, included determination of voltage regulation, specific reactant consumption, weight, voltage level and performance characteristics. These studies provided the basis for coordination activities with the space shuttle vehicle prime contractor. Interface information, on-board checkout and in-flight monitoring requirements, and development cost data were also provided as part of this activity. Even though the two vehicles primes had different voltage requirements (115 volts in one case and 28 volts in the other), it was concluded that either option could be provided in the fuel cell power system by the electrical hook-up of the cells in the stack.
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NASA Astrophysics Data System (ADS)
Kumar, Manoranjan; Topham, Benjamin J.; Yu, RuiHui; Ha, Quoc Binh Dang; Soos, Zoltán G.
2011-06-01
The molar spin susceptibilities χ(T) of Na-tetracyanoquinodimethane (TCNQ), K-TCNQ, and Rb-TCNQ(II) are fit quantitatively to 450 K in terms of half-filled bands of three one-dimensional Hubbard models with extended interactions using exact results for finite systems. All three models have bond order wave (BOW) and charge density wave (CDW) phases with boundary V = Vc(U) for nearest-neighbor interaction V and on-site repulsion U. At high T, all three salts have regular stacks of TCNQ^- anion radicals. The χ(T) fits place Na and K in the CDW phase and Rb(II) in the BOW phase with V ≈ Vc. The Na and K salts have dimerized stacks at T < Td while Rb(II) has regular stacks at 100 K. The χ(T) analysis extends to dimerized stacks and to dimerization fluctuations in Rb(II). The three models yield consistent values of U, V, and transfer integrals t for closely related TCNQ^- stacks. Model parameters based on χ(T) are smaller than those from optical data that in turn are considerably reduced by electronic polarization from quantum chemical calculation of U, V, and t of adjacent TCNQ^- ions. The χ(T) analysis shows that fully relaxed states have reduced model parameters compared to optical or vibration spectra of dimerized or regular TCNQ^- stacks.
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First-principles studies of electric field effects on the electronic structure of trilayer graphene
NASA Astrophysics Data System (ADS)
Wang, Yun-Peng; Li, Xiang-Guo; Fry, James N.; Cheng, Hai-Ping
2016-10-01
A gate electric field is a powerful way to manipulate the physical properties of nanojunctions made of two-dimensional crystals. To simulate field effects on the electronic structure of trilayer graphene, we used density functional theory in combination with the effective screening medium method, which enables us to understand the field-dependent layer-layer interactions and the fundamental physics underlying band gap variations and the resulting band modifications. Two different graphene stacking orders, Bernal (or ABC) and rhombohedral (or ABA), were considered. In addition to confirming the experimentally observed band gap opening in ABC-stacked and the band overlap in ABA-stacked trilayer systems, our results reveal rich physics in these fascinating systems, where layer-layer couplings are present but some characteristics features of single-layer graphene are partially preserved. For ABC stacking, the electric-field-induced band gap size can be tuned by charge doping, while for ABA band the tunable quantity is the band overlap. Our calculations show that the electronic structures of the two stacking orders respond very differently to charge doping. We find that in the ABA stacking hole doping can reopen a band gap in the band-overlapping region, a phenomenon distinctly different from electron doping. The physical origins of the observed behaviors were fully analyzed, and we conclude that the dual-gate configuration greatly enhances the tunability of the trilayer systems.
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Development of deployable structures for large space platform systems, part 1
NASA Technical Reports Server (NTRS)
Cox, R. L.; Nelson, R. A.
1982-01-01
Eight deployable platform design objectives were established: autodeploy/retract; fully integrated utilities; configuration variability; versatile payload and subsystem interfaces; structural and packing efficiency; 1986 technology readiness; minimum EVA/RMS; and Shuttle operational compatibility.
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International Space Station (ISS)
1995-04-17
International Cooperation Phase III: A Space Shuttle docked to the International Space Station (ISS) in this computer generated representation of the ISS in its completed and fully operational state with elements from the U.S., Europe, Canada, Japan, and Russia.
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Void-Free Lid for Food Packaging
NASA Technical Reports Server (NTRS)
Watson, C. D.; Farris, W. P.
1986-01-01
Flexible cover eliminates air pockets in sealed container. Universal food-package lid formed from flexible plastic. Partially folded, lid unfolded by depressing center portion. Height of flat portion of lid above flange thereby reduced. Pressure of food against central oval depression pops it out, forming dome that provides finger grip for mixing contents with water or opening lid. Therefore food stays fresh, allows compact stacking of partially filled containers, and resists crushing. Originally developed for packaging dehydrated food for use in human consumption on Space Shuttle missions. Other uses include home canning and commercial food packaging.
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2008-11-11
CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is lifted by a sling. Atlantis is being taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is towed out of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Atlantis was removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. It is returning to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Tim Jacobs
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is towed out of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Atlantis was removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. It is returning to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Dimitri Gerondidakis
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2008-11-11
CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is lifted by a sling. Atlantis is being taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is towed out of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Atlantis was removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. It is returning to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Dimitri Gerondidakis
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is towed out of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Atlantis was removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. It is returning to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Dimitri Gerondidakis
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Characterization of Space Shuttle Ascent Debris Aerodynamics Using CFD Methods
NASA Technical Reports Server (NTRS)
Murman, Scott M.; Aftosmis, Michael J.; Rogers, Stuart E.
2005-01-01
An automated Computational Fluid Dynamics process for determining the aerodynamic Characteristics of debris shedding from the Space Shuttle Launch Vehicle during ascent is presented. This process uses Cartesian fully-coupled, six-degree-of-freedom simulations of isolated debris pieces in a Monte Carlo fashion to produce models for the drag and crossrange behavior over a range of debris shapes and shedding scenarios. A validation of the Cartesian methods against ballistic range data for insulating foam debris shapes at flight conditions, as well as validation of the resulting models, are both contained. These models are integrated with the existing shuttle debris transport analysis software to provide an accurate and efficient engineering tool for analyzing debris sources and their potential for damage.
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Tuan, Chia-Chi; James, Nathan Pataki; Lin, Ziyin; Chen, Yun; Liu, Yan; Moon, Kyoung-Sik; Li, Zhuo; Wong, C P
2017-03-15
As microelectronics are trending toward smaller packages and integrated circuit (IC) stacks nowadays, underfill, the polymer composite filled in between the IC chip and the substrate, becomes increasingly important for interconnection reliability. However, traditional underfills cannot meet the requirements for low-profile and fine pitch in high density IC stacking packages. Post-applied underfills have difficulties in flowing into the small gaps between the chip and the substrate, while pre-applied underfills face filler entrapment at bond pads. In this report, we present a self-patterning underfilling technology that uses selective wetting of underfill on Cu bond pads and Si 3 N 4 passivation via surface energy engineering. This novel process, fully compatible with the conventional underfilling process, eliminates the issue of filler entrapment in typical pre-applied underfilling process, enabling high density and fine pitch IC die bonding.
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Redox flow cell energy storage systems
NASA Technical Reports Server (NTRS)
Thaller, L. H.
1979-01-01
The redox flow cell energy storage system being developed by NASA for use in remote power systems and distributed storage installations for electric utilities is presented. The system under consideration is an electrochemical storage device which utilizes the oxidation and reduction of two fully soluble redox couples (acidified chloride solutions of chromium and iron) as active electrode materials separated by a highly selective ion exchange membrane. The reactants are contained in large storage tanks and pumped through a stack of redox flow cells where the electrochemical reactions take place at porous carbon felt electrodes. Redox equipment has allowed the incorporation of state of charge readout, stack voltage control and system capacity maintenance (rebalance) devices to regulate cells in a stack jointly. A 200 W, 12 V system with a capacity of about 400 Wh has been constructed, and a 2 kW, 10kWh system is planned.
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49 CFR 178.707 - Standards for composite IBCs.
Code of Federal Regulations, 2013 CFR
2013-10-01
... designed to bear the entire stacking load. The inner receptacle and outer packaging form an integral... outer packaging. (2) A composite IBC with a fully enclosing outer packaging must be designed to permit assessment of the integrity of the inner container following the leakproofness and hydraulic tests. The outer...
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Communication and Mental Health: Psychiatric Forerunners.
ERIC Educational Resources Information Center
Brooks, Deems M.
The connections between human communication and mental health were first noted 50 to 60 years ago by such early psychiatrists as Alfred Adler, Harry Stack Sullivan, and Karen Horney. They were concerned with understanding those communication processes and skills that make for effective, fully functioning human beings. Adler emphasized faulty…
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First Integrated Flight Simulation For STS 114
2004-10-13
JSC2004-E-45138 (13 October 2004) --- Astronaut Stephen N. Frick monitors communications at the spacecraft communicator (CAPCOM) console in the Shuttle Flight Control Room (WFCR) in Johnson Space Centers (JSC) Mission Control Center (MCC) with the STS-114 crewmembers during a fully-integrated simulation on October 13. The seven member crew was in a JSC-based simulator during the sims. The dress rehearsal of Discovery's rendezvous and docking with the International Space Station (ISS) was the first flight-specific training for the Space Shuttle's return to flight.
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Analysis of launch site processing effectiveness for the Space Shuttle 26R payload
NASA Technical Reports Server (NTRS)
Flores, Carlos A.; Heuser, Robert E.; Pepper, Richard E., Jr.; Smith, Anthony M.
1991-01-01
A trend analysis study has been performed on problem reports recorded during the Space Shuttle 26R payload's processing cycle at NASA-Kennedy, using the defect-flow analysis (DFA) methodology; DFA gives attention to the characteristics of the problem-report 'population' as a whole. It is established that the problem reports contain data which distract from pressing problems, and that fully 60 percent of such reports were caused during processing at NASA-Kennedy. The second major cause of problem reports was design defects.
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Lightweight Long Life Heat Exchanger
NASA Technical Reports Server (NTRS)
Moore, E. K.
1976-01-01
A shuttle orbiter flight configuration aluminum heat exchanger was designed, fabricated, and tested. The heat exchanger utilized aluminum clad titanium composite parting sheets for protection against parting sheet pin hole corrosion. The heat exchanger, which is fully interchangeable with the shuttle condensing heat exchanger, includes slurpers (a means for removing condensed water from the downstream face of the heat exchanger), and both the core air passes and slurpers were hydrophilic coated to enhance wettability. The test program included performance tests which demonstrated the adequacy of the design and confirmed the predicted weight savings.
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Space Shuttle Crawler Transporter Sound Attenuation Study
NASA Technical Reports Server (NTRS)
Margasahayam, Ravi N.; MacDonald, Rod; Faszer, Clifford
2004-01-01
The crawler transporter (CT) is the world's largest tracked vehicle known, weighing 6 million pounds with a length of 131 feet and a width of 113 feet. The Kennedy Space Center (KSC) has two CTs that were designed and built for the Apollo program in the 1960's, maintained and retrofitted for use in the Space Shuttle program. As a key element of the Space Shuttle ground systems, the crawler transports the entire 12-million-pound stack comprising the orbiter, the mobile launch platform (MLP), the external tank (ET), and the solid rocket boosters (SRB) from the Vehicle Assembly Building (VAB) to the launch pad. This rollout, constituting a 3.5-5.0-mile journey at a top speed of 0.9 miles-per-hour, requires over 8 hours to reach either Launch Complex 39A or B. This activity is only a prelude to the spectacle of sound and fury of the Space Shuttle launch to orbit in less than 10 minutes and traveling at orbital velocities of Mach 24. This paper summarizes preliminary results from the Crawler Transporter Sound Attenuation Study, encompassing test and engineering analysis of significant sound sources to measure and record full frequency spectrum and intensity of the various noise sources and to analyze the conditions of vibration. Additionally, data such as ventilation criteria, plus operational procedures were considered to provide a comprehensive noise suppression design for implementation. To date, sound attenuation study and results on Crawler 2 have shown significant noise reductions ranging from 5 to 24 dBA.
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Space Shuttle 2 Advanced Space Transportation System. Volume 1: Executive Summary
NASA Technical Reports Server (NTRS)
Adinaro, James N.; Benefield, Philip A.; Johnson, Shelby D.; Knight, Lisa K.
1989-01-01
An investigation into the feasibility of establishing a second generation space transportation system is summarized. Incorporating successful systems from the Space Shuttle and technological advances made since its conception, the second generation shuttle was designed to be a lower-cost, reliable system which would guarantee access to space well into the next century. A fully reusable, all-liquid propellant booster/orbiter combination using parallel burn was selected as the base configuration. Vehicle characteristics were determined from NASA ground rules and optimization evaluations. The launch profile was constructed from particulars of the vehicle design and known orbital requirements. A stability and control analysis was performed for the landing phase of the orbiter's flight. Finally, a preliminary safety analysis was performed to indicate possible failure modes and consequences.
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Transition Induced by Fence Geometrics on Shuttle Orbiter at Mach 10
NASA Technical Reports Server (NTRS)
Everhart, Joel L.
2010-01-01
Fence-induced transition data simulating a raised gap filler have been acquired on the wing lower surface of a Shuttle Orbiter model in the Langley 31-Inch Mach 10 Tunnel to compare with the Shuttle Boundary Layer Transition Flight and HYTHIRM Experiments, and to provide additional correlation data for the Boundary Layer Transition Tool. In a qualitative assessment, the data exhibit the expected response to all parameter variations; however, it is unclear whether fully effective tripping at the fence was ever realized at any test condition with the present model hardware. A preliminary, qualitative comparison of the ground-based transition measurements with those obtained from the STS-128 HYTHIRM imagery at Mach 15 reveal similar transition-wake response characteristics in terms of the spreading and the path along the vehicle surface.
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Perpendicular magnetic anisotropy in CoXPd100-X alloys for magnetic tunnel junctions
NASA Astrophysics Data System (ADS)
Clark, B. D.; Natarajarathinam, A.; Tadisina, Z. R.; Chen, P. J.; Shull, R. D.; Gupta, S.
2017-08-01
CoFeB/MgO-based perpendicular magnetic tunnel junctions (p-MTJ's) with high anisotropy and low damping are critical for spin-torque transfer random access memory (STT-RAM). Most schemes of making the pinned CoFeB fully perpendicular require ferrimagnets with high damping constants, a high temperature-grown L10 alloy, or an overly complex multilayered synthetic antiferromagnet (SyAF). We report a compositional study of perpendicular CoxPd alloy-pinned Co20Fe60B20/MgO based MTJ stacks, grown at moderate temperatures in a planetary deposition system. The perpendicular anisotropy of the CoxPd alloy films can be tuned based on the layer thickness and composition. The films were characterized by alternating gradient magnetometry (AGM), energy-dispersive X-rays (EDX), and X-ray diffraction (XRD). Current-in-plane tunneling (CIPT) measurements have also been performed on the compositionally varied CoxPd MTJ stacks. The CoxPd alloy becomes fully perpendicular at approximately x = 30% (atomic fraction) Co. Full-film MTJ stacks of Si/SiO2/MgO (13)/CoXPd100-x (50)/Ta (0.3)/CoFeB (1)/MgO (1.6)/CoFeB (1)/Ta (5)/Ru (10), with the numbers enclosed in parentheses being the layer thicknesses in nm, were sputtered onto thermally oxidized silicon substrates and in-situ lamp annealed at 400 °C for 5 min. CIPT measurements indicate that the highest TMR is observed for the CoPd composition with the highest perpendicular magnetic anisotropy.
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Space Shuttle Solid Rocket Booster Debris Assessment
NASA Technical Reports Server (NTRS)
Kendall, Kristin; Kanner, Howard; Yu, Weiping
2006-01-01
The Space Shuttle Columbia Accident revealed a fundamental problem of the Space Shuttle Program regarding debris. Prior to the tragedy, the Space Shuttle requirement stated that no debris should be liberated that would jeopardize the flight crew and/or mission success. When the accident investigation determined that a large piece of foam debris was the primary cause of the loss of the shuttle and crew, it became apparent that the risk and scope of - damage that could be caused by certain types of debris, especially - ice and foam, were not fully understood. There was no clear understanding of the materials that could become debris, the path the debris might take during flight, the structures the debris might impact or the damage the impact might cause. In addition to supporting the primary NASA and USA goal of returning the Space Shuttle to flight by understanding the SRB debris environment and capability to withstand that environment, the SRB debris assessment project was divided into four primary tasks that were required to be completed to support the RTF goal. These tasks were (1) debris environment definition, (2) impact testing, (3) model correlation and (4) hardware evaluation. Additionally, the project aligned with USA's corporate goals of safety, customer satisfaction, professional development and fiscal accountability.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Lee, Jinhong; Song, Jongchan; Lee, Hongkyung
Formation of soluble polysulfide (PS), which is a key feature of lithium sulfur (Li–S) batteries, provides a fast redox kinetic based on a liquid–solid mechanism; however, it imposes the critical problem of PS shuttle. Here, we address the dilemma by exploiting a solvent-swollen polymeric single-ion conductor (SPSIC) as the electrolyte medium of the Li–S battery. The SPSIC consisting of a polymeric single-ion conductor and lithium salt-free organic solvents provides Li ion hopping by forming a nanoscale conducting channel and suppresses PS shuttle according to the Donnan exclusion principle when being employed for Li–S batteries. The organic solvents at the interfacemore » of the sulfur/carbon composite and SPSIC eliminate the poor interfacial contact and function as a soluble PS reservoir for maintaining the liquid–solid mechanism. Furthermore, the quasi-solid-state SPSIC allows the fabrication of a bipolar-type stack, which promises the realization of a high-voltage and energy-dense Li–S battery.« less
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Objectives and Progress on Integrated Vehicle Ground Vibration Testing for the Ares Launch Vehicles
NASA Technical Reports Server (NTRS)
Tuma, Margaret L.; Asloms. Brice R.
2009-01-01
As NASA begins design and development of the Ares launch vehicles to replace the Space Shuttle and explore beyond low Earth orbit, Integrated Vehicle Ground Vibration Testing (IVGVT) will be a vital component of ensuring that those vehicles can perform the missions assigned to them. A ground vibration test (GVT) is intended to measure by test the fundamental dynamic characteristics of launch vehicles during various phases of flight. During the series of tests, properties such as natural frequencies, mode shapes, and transfer functions are measured directly. This data is then used to calibrate loads and control systems analysis models for verifying analyses of the launch vehicle. The Ares Flight & Integrated Test Office (FITO) will be conducting IVGVT for the Ares I crew launch vehicle at Marshall Space Flight Center (MSFC) from 2011 to 2012 using the venerable Test Stand (TS) 4550, which supported similar tests for the Saturn V and Space Shuttle vehicle stacks.
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Cold Flow Plume Entrainment Test Final Report NTF Test Number 2456
NASA Technical Reports Server (NTRS)
Ruf, Joseph H.; McDaniels, David; Mishtawy, Jason; Ramachandran, Narayanan; Hammad, Khaled J.
2005-01-01
As part of the Space Shuttle Return to Flight (RTF) program, Marshall Space Flight Center (MSFC) performed computational fluid dynamics (CFD) analysis to define the velocity flowfields around the Shuttle stack at liftoff. These CFD predicted velocity flowfields were used in debris transport analysis (DTA). High speed flows such as plumes induce or 'entrain' mass from the surrounding environment. Previous work had shown that CFD analysis over-predicts plume induced flows. Therefore, the DTA would tend to 1) predict more debris impacts, and 2) the debris velocity (and kinetic energy) of those impacts would be too high. At a November, 2004 peer-review it was recommended that the Liftoff DTA team quantify the uncertainty in the DTA caused by the CFD's over prediction of plume induced flow. To do so, the Liftoff DTA team needed benchmark quality data for plume induced flow to quantify the CFD accuracy and its effect on the DTA. MSFC's Nozzle Test Facility (NTF) conducted the "Nozzle Induced Flows test, P#2456" to obtain experimental data for plume induced flows for nozzle flow exhausting into q quiescent freestream. Planning for the test began in December, 2004 and the experimental data was obtained in February and March of 2005. The funding for this test was provided by MSFC's Space Shuttle Propulsion Systems Integration and Engineering office.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Essig, Stephanie; Geisz, John F.; Steiner, Myles A.
Dual-junction solar cells consisting of rear-heterojunction GaInP top cells and back-junction, back-contacted crystalline Si bottom cells were fabricated and characterized. Our calculations show that theoretical efficiencies up to 38.9% can be achieved with Si-based tandem devices. In our experiments, the two subcells were fabricated separately and stacked with an index matching fluid. In contrast to conventional mechanically stacked solar cells, that contain two metal grids at the interface, our concept includes a fully back contacted bottom cell which reduces the shadow losses in the device. A 1-sun AM1.5g cumulative efficiency of (26.2 +/- 0.6)% has been achieved with this novelmore » GaInP/Si 4-terminal tandem solar cell.« less
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2000-06-18
At Launch Pad 36A, Cape Canaveral Air Force Station, workers (at left) oversee the lifting of the nose fairing covering the Tracking and Data Relay Satellite (TDRS-H). Once at the top, the fairing will be mated with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2000-06-18
The nose fairing covering the Tracking and Data Relay Satellite (TDRS-H) is close to the top of the launch tower at Launch Pad 36A, Cape Canaveral Air Force Station. It is being lifted to mate with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2000-06-18
At Launch Pad 36A, Cape Canaveral Air Force Station, workers (at left) oversee the lifting of the nose fairing covering the Tracking and Data Relay Satellite (TDRS-H). Once at the top, the fairing will be mated with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2000-06-18
The nose fairing covering the Tracking and Data Relay Satellite (TDRS-H) is close to the top of the launch tower at Launch Pad 36A, Cape Canaveral Air Force Station. It is being lifted to mate with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2008-11-11
CAPE CANAVERAL, Fla. – In the transfer aisle of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, the sling is removed from space shuttle Atlantis before its return to the Orbiter Processing Facility. Atlantis was removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Tim Jacobs
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2008-11-11
CAPE CANAVERAL, Fla. – In In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is lowered by a sling toward the transfer aisle floor. Atlantis has been taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – This close-up shows space shuttle Atlantis being lowered onto its wheels in the transfer aisle of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Atlantis has been removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Troy Cryder
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2008-11-11
CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis hangs suspended above the transfer aisle floor. Atlantis has been taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is lowered by a sling toward the transfer aisle floor. Atlantis has been taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – In the transfer aisle of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis has been lowered to a horizontal position. Atlantis has been taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – Space shuttle Atlantis is lowered onto its wheels in the transfer aisle of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Atlantis has been removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Troy Cryder
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2008-11-11
CAPE CANAVERAL, Fla. – In the transfer aisle of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is lowered to a horizontal position. Atlantis has been taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – This close-up shows space shuttle Atlantis being lowered onto its wheels in the transfer aisle of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida. Atlantis has been removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Troy Cryder
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Xiao, Senbo; Xiao, Shijun; Gräter, Frauke
2013-06-14
Stacking of β-sheets results in a protein super secondary structure with remarkable mechanical properties. β-Stacks are the determinants of a silk fiber's resilience and are also the building blocks of amyloid fibrils. While both silk and amyloid-type crystals are known to feature a high resistance against rupture, their structural and mechanical similarities and particularities are yet to be fully understood. Here, we systematically compare the rupture force and stiffness of amyloid and spider silk poly-alanine β-stacks of comparable sizes using Molecular Dynamics simulations. We identify the direction of force application as the primary determinant of the rupture strength; β-sheets in silk are orientated along the fiber axis, i.e. the pulling direction, and consequently require high forces in the several nanoNewton range for shearing β-strands apart, while β-sheets in amyloid are oriented vertically to the fiber, allowing a zipper-like rupture at sub-nanoNewton forces. A secondary factor rendering amyloid β-stacks softer and weaker than their spider silk counterparts is the sub-optimal side-chain packing between β-sheets due to the sequence variations of amyloid-forming proteins as opposed to the perfectly packed poly-alanine β-sheets of silk. Taken together, amyloid fibers can reach the stiffness of silk fibers in spite of their softer and weaker β-sheet arrangement as they are missing a softening amorphous matrix.
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NASA Technical Reports Server (NTRS)
Corso, G. J.
1986-01-01
The use of a tethered subsatellite employed downward into the earth's upper atmosphere to an altitude of about 110 km above the earth would eliminate the orbital contamination problem while at the same time affording a measure of atmospheric braking to reduce the velocities of many particles to where they may be captured intact or nearly so with properly designed collectors. The same technique could also be used to monitor the flux of all types of man-made orbital debris out to a distance of more than a hundred kilometers in any direction from the space station. In this way the build up of any debris belt orbiting earth could be determined. The actual collecting elements used for both purposes could be of several different materials and designs so as to optimize the collection of different types of particles with different densities. Stacks of foils, films, plastics, and foams, as well as simple capture cells would be mounted in clusters around the outside of a tethered satellite and protected by iris covers until the tethered had been fully deployed. If the orientation history of the satellite were known the direction of the incoming material could be infered. A chief advantage in deploying such tethered collectors from the Space Station instead of from the shuttle is the ability to maintain deployment of the tether for days instead of hours resulting in much greater yields of intact particles and impact debris.
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Evolution of the Ariane 5 concept
NASA Astrophysics Data System (ADS)
Bouchet, J.
Cost reduction of the post Ariane 5 family of launch vehicles is discussed. Recovery at sea of the first stage is proposed. Apart from economic advantages over land recovery or the development of a fully recoverable (shuttle type) system, sea recovery is practical for aborted missions.
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Waste collection subsystem study
NASA Technical Reports Server (NTRS)
1984-01-01
Practical ways were explored of improving waste compaction and of providing rapid turnaround between flights at essentially no cost for the space shuttle waste collection subsystem commode. Because of the possible application of a fully developed shuttle commode to the space station, means of providing waste treatment without overboard venting were also considered. Three basic schemes for compaction and rapid turnaround, each fully capable of meeting the objectives, were explored in sufficient depth to bring out the characteristic advantages and disadvantages of each. Tradeoff comparisons were very close between leading contenders and efforts were made to refine the design concepts sufficiently to justify a selection. The concept selected makes use of a sealed canister containing wastes that have been forcibly compacted, which is removable in flight. No selection was made between three superior non-venting treatment methods owing to the need for experimental evaluations of the processes involved. A system requirements definition document has been prepared to define the task for a test embodiment of the selected concept.
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One Idea for a Next Generation Shuttle
NASA Technical Reports Server (NTRS)
MacConochie, Ian O.; Cerro, Jeffrey A.
2004-01-01
In this configuration, the current Shuttle External Tank serves as core structure for a fully reusable second stage. This stage is equipped with wings, vertical fin, landing gear, and thermal protection. The stage is geometrically identical to (but smaller than) a single stage that has been tested hyper-sonically, super-sonically, and sub-sonically in the NASA Langley Research Center wind tunnels. The three LOX/LH engines that currently serve as main propulsion for the Shuttle Orbiter, serve as main propulsion on the new stage. The new stage is unmanned but is equipped with the avionics needed for automatic maneuvering on orbit and for landing on a runway. Three rails are installed along the top surface of the vehicle for attachment of various payloads. Pay- loads might include third stages with satellites attached, personnel pods, propellants, or other items.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Zhang, H. L.; Han, Y. F., E-mail: yfhan@sjtu.edu.cn, E-mail: bdsun@sjtu.edu.cn; Zhou, W.
2015-01-26
Atomic ordering in Al melts induced by liquid/substrate interface with Ti solute was investigated by ab initio molecular dynamics simulations and in-situ synchrotron X-ray diffraction. It is predicted that deformed nanoscale ordering Al layers with a rhombohedral-centered hexagonal structure (R3{sup ¯}m space group) instead of the intrinsic fcc structure (Fm3{sup ¯}m space group) form on substrate at temperature above Al liquids. With Al atoms stacking away from the interface, the ordering structure reaches a critical thickness, which inhibits the consecutive stacking of Al atoms on substrates. The locally stacking reconstruction induced by Ti atom relieves the accumulated elastic strain energymore » in ordered Al layers, facilitating fully heterogeneous nucleation on substrate beyond the deformed ordering Al layer around the melting point. The roles of liquid/substrate interface with Ti solute in the physical behavior of heterogeneous nucleation on substrate were discussed.« less
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Redox flow cell energy storage systems
NASA Technical Reports Server (NTRS)
Thaller, L. H.
1979-01-01
NASA-Redox systems are electrochemical storage devices that use two fully soluble Redox couples, anode and cathode fluids, as active electrode materials separated by a highly selective ion exchange membrane. The reactants are contained in large storage tanks and pumped through a stack of Redox flow cells where the electrochemical reactions (reduction and oxidation) take place at porous carbon felt electrodes. A string or stack of these power producing cells is connected in series in a bipolar manner. Redox energy storage systems promise to be inexpensive and possess many features that provide for flexible design, long life, high reliability and minimal operation and maintenance costs. These features include independent sizing of power and storage capacity requirements and inclusion within the cell stack of a cell that monitors the state of charge of the system as a whole, and a rebalance cell which permits continuous correction to be made for minor side reactions that would tend to result in the anode fluid and cathode fluids becoming electrochemically out of balance. These system features are described and discussed.
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STS-66 landing at Edwards Air Force Base
NASA Technical Reports Server (NTRS)
1994-01-01
The drag chute is fully deployed as the Space Shuttle Atlantis heads toward a stop at Edwards Air Force Base in southern California, ending a successful 10 day, 22 hour and 34 minute space mission. Landing occured at 7:34 a.m. (PST), November 14, 1994.
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BLIMPK/Streamline Surface Catalytic Heating Predictions on the Space Shuttle Orbiter
NASA Technical Reports Server (NTRS)
Marichalar, Jeremiah J.; Rochelle, William C.; Kirk, Benjamin S.; Campbell, Charles H.
2006-01-01
This paper describes the results of an analysis of localized catalytic heating effects to the U.S. Space Shuttle Orbiter Thermal Protection System (TPS). The analysis applies to the High-temperature Reusable Surface Insulation (HRSI) on the lower fuselage and wing acreage, as well as the critical Reinforced Carbon-Carbon on the nose cap, chin panel and the wing leading edge. The object of the analysis was to use a modified two-layer approach to predict the catalytic heating effects on the Orbiter windward HRSI tile acreage, nose cap, and wing leading edge assuming localized highly catalytic or fully catalytic surfaces. The method incorporated the Boundary Layer Integral Matrix Procedure Kinetic (BLIMPK) code with streamline inputs from viscous Navier-Stokes solutions to produce heating rates for localized fully catalytic and highly catalytic surfaces as well as for nominal partially catalytic surfaces (either Reinforced Carbon-Carbon or Reaction Cured Glass) with temperature-dependent recombination coefficients. The highly catalytic heating results showed very good correlation with Orbiter Experiments STS-2, -3, and -5 centerline and STS-5 wing flight data for the HRSI tiles. Recommended catalytic heating factors were generated for use in future Shuttle missions in the event of quick-time analysis of damaged or repaired TPS areas during atmospheric reentry. The catalytic factors are presented along the streamlines as well as a function of stagnation enthalpy so they can be used for arbitrary trajectories.
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Constellation's First Flight Test: Ares I-X
NASA Technical Reports Server (NTRS)
Davis, Stephan R.; Askins, Bruce R.
2010-01-01
On October 28, 2009, NASA launched Ares I-X, the first flight test of the Constellation Program that will send human beings to the Moon and beyond. This successful test is the culmination of a three-and-a-half-year, multi-center effort to design, build, and fly the first demonstration vehicle of the Ares I crew launch vehicle, the successor vehicle to the Space Shuttle. The suborbital mission was designed to evaluate the atmospheric flight characteristics of a vehicle dynamically similar to Ares I; perform a first stage separation and evaluate its effects; characterize and control roll torque; stack, fly, and recover a solid-motor first stage testing the Ares I parachutes; characterize ground, flight, and reentry environments; and develop and execute new ground hardware and procedures. Built from existing flight and new simulator hardware, Ares I-X integrated a Shuttle-heritage four-segment solid rocket booster for first stage propulsion, a spacer segment to simulate a five-segment booster, Peacekeeper axial engines for roll control, and Atlas V avionics, as well as simulators for the upper stage, crew module, and launch abort system. The mission leveraged existing logistical and ground support equipment while also developing new ones to accommodate the first in-line rocket for flying astronauts since the Saturn IB last flew from Kennedy Space Center (KSC) in 1975. This paper will describe the development and integration of the various vehicle and ground elements, from conception to stacking in KSC s Vehicle Assembly Building; hardware performance prior to, during, and after the launch; and preliminary lessons and data gathered from the flight. While the Constellation Program is currently under review, Ares I-X has and will continue to provide vital lessons for NASA personnel in taking a vehicle concept from design to flight.
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Property Morphology Correlations of Organic Semiconductor Nanowires
NASA Astrophysics Data System (ADS)
McFarland, Frederick Marshall
Chemically doped and non-doped P3HT nanoaggregates are studied to establish a comprehensive understanding of the interplay between their morphology and various optoelectronic properties. One-dimensional nanoaggregates of P3HT are chosen as the model systems here due to their high surface/volume ratio and suitability for microscopic investigations. Atomic force microscopy (AFM) and kelvin probe force microscopy (KPFM) are used to correlate property/morphology characteristics of non-doped P3HT nanowhiskers. Topographical measurements indicate that individually folded P3HT motifs stack via interfacial interactions to form nanowhiskers in solution. Further aging leads to multi-layered nanowhiskers with greater stability and less instances of ?-? sliding of interfacial edge-on oriented motifs. KPFM measurements show higher surface potentials on portions of nanowhiskers containing local defects and stacking faults due to overlapping, and nanowhiskers that are at least triple-layered. Simultaneous UV-Vis and AFM characterizations compare the aggregation rates and morphologies of doped and non-doped P3HT nanowhiskers. Allowing fully solubilized P3HT to age without doping may produce high aspect ratio nanowhiskers containing disordered segments protruding out from the edges of the nanowhiskers. These protruding segments could also serve as "tie-molecules" between adjacent nanowhiskers. Doping fully solubilized P3HT will lead to substantially higher rates of P3HT aggregation. Doped nanowhiskers also display different morphologies. They pack tighter, are smoother, and are thicker and higher versus non-doped nanowhiskers, indicating a different aggregation mechanism. Stopped flow-kinetics was employed to investigate the reactivity of two distinctively different morphological forms of P3HT towards dopants. Fully solubilized P3HT undergoes a slow doping mechanism whereas pre-aggregated P3HT undergoes a fast doping mechanism. Pseudo-single reactant rate fittings indicate that both mechanisms appear to be 1st order in P3HT, whereby pre-aggregated P3HT mixtures will produce more doped products per P3HT monomer unit than fully solubilized P3HT. This study highlights the impact of conjugated polymer's morphology on their doping efficiency. Density functional theory was used to investigate the charge transfer (CT) states between oligothiophene and F4-TCNQ. CT of several unreported complexes that feature two oligomers stacked in a sandwich or layered configuration is investigated. Our preliminary results suggest that these new complexes can generate substantially more charge per F4-TCNQ than previously reported.
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A Fully Coupled Multi-Rigid-Body Fuel Slosh Dynamics Model Applied to the Triana Stack
NASA Technical Reports Server (NTRS)
London, K. W.
2001-01-01
A somewhat general multibody model is presented that accounts for energy dissipation associated with fuel slosh and which unifies some of the existing more specialized representations. This model is used to predict the mutation growth time constant for the Triana Spacecraft, or Stack, consisting of the Triana Observatory mated with the Gyroscopic Upper Stage of GUS (includes the solid rocket motor, SRM, booster). At the nominal spin rate of 60 rpm and with 145 kg of hydrazine propellant on board, a time constant of 116 s is predicted for worst case sloshing of a spherical slug model compared to 1,681 s (nominal), 1,043 s (worst case) for sloshing of a three degree of freedom pendulum model.
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Magnetospheric Multiscale (MMS)
2014-05-09
MMS Stacked – View of the fully stacked MMS prior to being bagged for vibration tests. Learn more about MMS at www.nasa.gov/mms Credit NASA/Chris Gunn The Magnetospheric Multiscale, or MMS, will study how the sun and the Earth's magnetic fields connect and disconnect, an explosive process that can accelerate particles through space to nearly the speed of light. This process is called magnetic reconnection and can occur throughout all space. 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
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STS-67 landing at Edwards Air Force Base
NASA Technical Reports Server (NTRS)
1995-01-01
The drag chute is fully deployed in this view of the Space Shuttle Endeavour as it completes a mission of almost 17 days duration in space on runway 22 at Edwards Air Force Base in southern California. Landing occurred at 1:46 p.m. (EST), March 18, 1995.
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NASA Technical Reports Server (NTRS)
Fehrman, A. L.; Masek, R. V.
1972-01-01
Quantitative estimates of the uncertainty in predicting aerodynamic heating rates for a fully reusable space shuttle system are developed and the impact of these uncertainties on Thermal Protection System (TPS) weight are discussed. The study approach consisted of statistical evaluations of the scatter of heating data on shuttle configurations about state-of-the-art heating prediction methods to define the uncertainty in these heating predictions. The uncertainties were then applied as heating rate increments to the nominal predicted heating rate to define the uncertainty in TPS weight. Separate evaluations were made for the booster and orbiter, for trajectories which included boost through reentry and touchdown. For purposes of analysis, the vehicle configuration is divided into areas in which a given prediction method is expected to apply, and separate uncertainty factors and corresponding uncertainty in TPS weight derived for each area.
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STS-65 Columbia, OV-102, with drag chute deployed lands at KSC SLF
NASA Technical Reports Server (NTRS)
1994-01-01
The Space Shuttle Columbia, Orbiter Vehicle (OV) 102, its drag chute fully deployed, completes a record duration mission as it lands on Runway 33 at the Kennedy Space Center (KSC) Shuttle Landing Facility (SLF). A helicopter flying overhead observes as OV-102's nose landing gear (NLG) and main landing gear (MLG) roll along the runway. Landing occurred at 6:38 am (Eastern Daylight Time (EDT)). STS-65 mission duration was 14 days 17 hours and 56 minutes. Onboard were six NASA astronauts and a Japanese payload specialist who conducted experiments in support of the International Microgravity Laboratory 2 (IML-2) during the mission.
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Rationale for windshield glass system specification requirements for shuttle orbiter
NASA Technical Reports Server (NTRS)
Hayashida, K.; King, G. L.; Tesinsiky, J.; Wittenburg, D. R.
1972-01-01
A preliminary procurement specification for the space shuttle orbiter windshield pane, and some of the design considerations and rationale leading to its development are presented. The windshield designer is given the necessary methods and procedures for assuring glass pane structural integrity by proof test. These methods and procedures are fully developed for annealed and thermally tempered aluminosilicate, borosilicate, and soda lime glass and for annealed fused silica. Application of the method to chemically tempered glass is considered. Other considerations are vision requirements, protection against bird impact, hail, frost, rain, and meteoroids. The functional requirements of the windshield system during landing, ferrying, boost, space flight, and entry are included.
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NASA Technical Reports Server (NTRS)
Ingels, F.; Schoggen, W. O.
1981-01-01
Several methods for increasing bit transition densities in a data stream are summarized, discussed in detail, and compared against constraints imposed by the 2 MHz data link of the space shuttle high rate multiplexer unit. These methods include use of alternate pulse code modulation waveforms, data stream modification by insertion, alternate bit inversion, differential encoding, error encoding, and use of bit scramblers. The psuedo-random cover sequence generator was chosen for application to the 2 MHz data link of the space shuttle high rate multiplexer unit. This method is fully analyzed and a design implementation proposed.
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Haddad, Raoudha; Mattei, Jean-Gabriel; Thery, Jessica; Auger, Aurélien
2015-06-28
Glucose oxidase (GOx) is immobilized on ZnO nanoparticle-modified electrodes. The immobilized glucose oxidase shows efficient mediated electron transfer with ZnO nanoparticles to which the ferrocenyl moiety is π-stacked into a supramolecular architecture. The constructed ZnO-Fc/CNT modified electrode exhibits high ferrocene surface coverage, preventing any leakage of the π-stacked ferrocene from the newly described ZnO hybrid nanoparticles. The use of the new architecture of ZnO supported electron mediators to shuttle electrons from the redox centre of the enzyme to the surface of the working electrode can effectively bring about successful glucose oxidation. These modified electrodes evaluated as a highly efficient architecture provide a catalytic current for glucose oxidation and are integrated in a specially designed glucose/air fuel cell prototype using a conventional platinum-carbon (Pt/C) cathode at physiological pH (7.0). The obtained architecture leads to a peak power density of 53 μW cm(-2) at 300 mV for the Nafion® based biofuel cell under "air breathing" conditions at room temperature.
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Liu, Jiao; Tian, Ji; Li, Jin; Azietaku, John Teye; Zhang, Bo-Li; Gao, Xiu-Mei; Chang, Yan-Xu
2016-07-01
An in-capillary 2, 2-diphenyl-1-picrylhydrazyl (DPPH)-CE-the DAD (in-capillary DPPH-CE-DAD) combined with reversed-electrode polarity stacking mode has been developed to screen and quantify the active antioxidant components of Cuscuta chinensis Lam. The operation parameters were optimized with regard to the pH and concentration of buffer solution, SDS, β-CDs, organic modifier, as well as separation voltage and temperature. Six antioxidants including chlorogenic acid, p-coumaric acid, rutin, hyperin, isoquercitrin, and astragalin were screened and the total antioxidant activity of the complex matrix was successfully evaluated based on the decreased peak area of DPPH by the established DPPH-CE-DAD method. Sensitivity was enhanced under reversed-electrode polarity stacking mode and 10- to 31-fold of magnitude improvement in detection sensitivity for each analyte was attained. The results demonstrated that the newly established in-capillary DPPH-CE-DAD method combined with reversed-electrode polarity stacking mode could integrate sample concentration, the oxidizing reaction, separation, and detection into one capillary to fully automate the system. It was considered a suitable technique for the separation, screening, and determination of trace antioxidants in natural products. © 2016 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.
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2000-06-18
An overhead crane is positioned on the nose fairing covering the Tracking and Data Relay Satellite (TDRS-H) in order to lift it up the tower at Launch Pad 36A, Cape Canaveral Air Force Station. It will be mated with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2000-06-18
An overhead crane is positioned on the nose fairing covering the Tracking and Data Relay Satellite (TDRS-H) in order to lift it up the tower at Launch Pad 36A, Cape Canaveral Air Force Station. It will be mated with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2000-06-18
The nose fairing covering the Tracking and Data Relay Satellite (TDRS-H) nears the top of the launch tower at Launch Pad 36A, Cape Canaveral Air Force Station. It will be mated with the Atlas IIA/Centaur rocket, which is already stacked (barely visible behind the framework on lower left), for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2000-06-18
The nose fairing covering the Tracking and Data Relay Satellite (TDRS-H) nears the top of the launch tower at Launch Pad 36A, Cape Canaveral Air Force Station. It will be mated with the Atlas IIA/Centaur rocket, which is already stacked (barely visible behind the framework on lower left), for launch on June 29. The satellite will augment the TDRS system’s existing Sand Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communication with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low earth orbit
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2009-06-24
CAPE CANAVERAL, Fla. – The afternoon sun casts shadows on space shuttle Endeavour's external fuel tank as workers remove the seal from the Ground Umbilical Carrier Plate, or GUCP, on the tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, work continues on removing the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2008-11-11
CAPE CANAVERAL, Fla. – In the transfer aisle of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis has been lowered to a horizontal position and its wheels lowered. Atlantis has been removed from its external fuel tank and solid rocket boosters stack after the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Troy Cryder
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2008-11-11
CAPE CANAVERAL, Fla. – As it hangs suspended in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is being fitted with an apparatus that will help lower it to a horizontal position. Atlantis has been taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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2008-11-11
CAPE CANAVERAL, Fla. – As it hangs suspended in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is being fitted with an apparatus that will help lower it to a horizontal position. Atlantis has been taken off its external fuel tank and solid rocket boosters stack after of the delay of its STS-125 mission to NASA's Hubble Space Telescope. Atlantis will be returned to the Orbiter Processing Facility. Atlantis' targeted launch on Oct. 14 was delayed when a system that transfers science data from the orbiting observatory to Earth malfunctioned on Sept. 27. The new target launch date is under review. Photo credit: NASA/Jim Grossmann
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Shuttle Return-to-Flight IH-108 Aerothermal Test at CUBRC - Flow Field Calibration and CFD
NASA Technical Reports Server (NTRS)
Lau, Kei Y.; Holden, Michael
2010-01-01
This paper discusses one specific aspect of the Shuttle Retrun-To-Flight IH-108 Aerothermal Test at CUBRC, the test flow field calibration. It showed the versatility of the CUBRC LENS II wind tunnel for an aerothermal test with unique and demanding requirements. CFD analyses were used effectively to extend the test range at the low end of the Mach range. It demonstrated how ground test facility and CFD synergy can be utilitzed iteratively to enhance the confidence in the fedility of both tools. It addressed the lingering concerns of the aerothermal community on use of inpulse facility and CFD analysis. At the conclusion of the test program, members from the NASA Marshall (MSFC), CUBRC and USA (United Space Alliance) Consultants (The Grey Beards) were asked to independently verify the flight scaling data generated by Boeing for flight certification of the re-designed external tank (ET) components. The blind test comparison showed very good results. A more comprehensive discussion of the topics in this paper can be found in Chapter 6 of Reference [1]. The overall aspect of the test program has been discussed in an AIAA paper by Tim Wadhams [2]. The Shuttle Ascent Stack performance and related issues discussed in the Report [1] are not included in this paper. No ITAR data is included in this paper.
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2009-10-28
CAPE CANAVERAL, Fla. - About the length of eight school buses stacked end to end, the Constellation Program's 327-foot-tall Ares I-X test rocket races off Launch Complex 39B at NASA's Kennedy Space Center in Florida. The rocket produces 2.96 million pounds of thrust at liftoff and reaches a speed of 100 mph in eight seconds. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo courtesy of Scott Andrews
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An investigation of the needs and the design of an orbiting space station with growth capabilities
NASA Technical Reports Server (NTRS)
Dossey, J. R.; Trotti, G.
1977-01-01
An architectural approach to the evolutionary growth of an orbiting space station from a small manned satellite to a fully independent, self-sustainable space colony facility is presented. Social and environmental factors, ease of transportation via the space shuttle, and structural design are considered.
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Liquid flyback booster pre-phase: A study assessment
NASA Technical Reports Server (NTRS)
Peterson, W.; Ankney, W.; Bell, J.; Berning, M.; Bryant, L.; Bufkin, A.; Cain, L.; Caram, J.; Cockrell, B.; Curry, D.
1994-01-01
The concept of a flyback booster has been around since early in the shuttle program. The original two-stage shuttle concepts used a manned flyback booster. These boosters were eliminated from the program for funding and size reasons. The current shuttle uses two Redesigned Solid Rocket Motors (RSRM's), which are recovered and refurbished after each flight; this is one of the major cost factors of the program. Replacement options have been studied over the past ten years. The conclusion reached by the most recent study is that the liquid flyback booster (LFBB) is the only competitive option from a life-cycle cost perspective. The purpose of this study was to assess the feasibility and practicality of LFBB's. The study provides an expansion of the recommendations made during the aforementioned study. The primary benefits are the potential for enhanced reusability and a reduction of recurring costs. The potential savings in vehicle turnaround could offset the up-front costs. Development of LFBB's requires a commitment to the shuttle program for 20 to 30 years. LFBB's also offer enhanced safety and abort capabilities. Currently, any failure of an RSRM can be considered catastrophic, since there are no intact abort capabilities during the burn of the RSRM's. The performance goal of the LFBB's was to lift a fully loaded orbiter under optimal conditions, so as not to be the limiting factor of the performance capability of the shuttle. In addition, a final benefit is the availability of growth paths for applications other than shuttle.
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Liquid Flyback Booster Pre-Phase A Study Assessment. Volume 1
NASA Technical Reports Server (NTRS)
Peterson, W.; Ankney, W.; Bell, J.; Berning, M.; Bryant, L.; Bufkin, A.; Cain, L.; Caram, J.; Cockrell, B.; Curry, D.;
1994-01-01
Mw concept of a flyback booster has been around since early in the Shuttle program. The original two-stage Shuttle concepts used a manned flyback booster. These boosters were eliminated from the program for funding and size reasons. The current Shuttle uses two Redesigned Solid Rocket Motors (RSRMs), which are recovered and refurbished after each flight; this is one of the major cost factors of the program. Replacement options have been studied over the past ten years. The conclusion reached by the most recent study is that the liquid flyback booster (LFBB) is the only competitive option from a life-cycle cost perspective. The purpose of this study was to assess the feasibility and practicality of LFBBs. The study provides an expansion of the recommendations made during the during the aforementioned study. The primary benefits are the potential for enhanced reusability and a reuction of recurring costs. The potential savings in vehicle turnaround could offset the up-front costs. Development of LFBBs requires a commitment to the Shuttle program for 20 to 30 years. LFBBs also offer enhanced safety and abort capabilities. Currently, any failure of an RSRM can be considered catastrophic since them we no intact abort capabilities during the burn of the RSRMS. The performance goal of the LFBBs was to lift a fully loaded Orbiter under optimal conditions, so as not to be the limiting factor of the performance capability of the Shuttle. In addition, a final benefit is the availability of growth paths for applications other than the Shuttle.
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Columbia Accident Investigation Board. Volume One
NASA Technical Reports Server (NTRS)
2003-01-01
The Columbia Accident Investigation Board's independent investigation into the February 1, 2003, loss of the Space Shuttle Columbia and its seven-member crew lasted nearly seven months. A staff of more than 120, along with some 400 NASA engineers, supported the Board's 13 members. Investigators examined more than 30,000 documents, conducted more than 200 formal interviews, heard testimony from dozens of expert witnesses, and reviewed more than 3,000 inputs from the general public. In addition, more than 25,000 searchers combed vast stretches of the Western United States to retrieve the spacecraft's debris. In the process, Columbia's tragedy was compounded when two debris searchers with the U.S. Forest Service perished in a helicopter accident. This report concludes with recommendations, some of which are specifically identified and prefaced as 'before return to flight.' These recommendations are largely related to the physical cause of the accident, and include preventing the loss of foam, improved imaging of the Space Shuttle stack from liftoff through separation of the External Tank, and on-orbit inspection and repair of the Thermal Protection System. The remaining recommendations, for the most part, stem from the Board's findings on organizational cause factors. While they are not 'before return to flight' recommendations, they can be viewed as 'continuing to fly' recommendations, as they capture the Board's thinking on what changes are necessary to operate the Shuttle and future spacecraft safely in the mid- to long-term. These recommendations reflect both the Board's strong support for return to flight at the earliest date consistent with the overriding objective of safety, and the Board's conviction that operation of the Space Shuttle, and all human space-flight, is a developmental activity with high inherent risks.
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Aeroelastic Response and Protection of Space Shuttle External Tank Cable Trays
NASA Technical Reports Server (NTRS)
Edwards, John W.; Keller, Donald F.; Schuster, David M.; Piatak, David J.; Rausch, Russ D.; Bartels, Robert E.; Ivanco, Thomas G.; Cole, Stanley R.; Spain, Charles V.
2005-01-01
Sections of the Space Shuttle External Tank Liquid Oxygen (LO2) and Liquid Hydrogen (LH2) cable trays are shielded from potentially damaging airloads with foam Protuberance Aerodynamic Load (PAL) Ramps. Flight standard design LO2 and LH2 cable tray sections were tested with and without PAL Ramp models in the United States Air Force Arnold Engineering Development Center s (AEDC) 16T transonic wind tunnel to obtain experimental data on the aeroelastic stability and response characteristics of the trays and as part of the larger effort to determine whether the PAL ramps can be safely modified or removed. Computational Fluid Dynamic simulations of the full-stack shuttle launch configuration were used to investigate the flow characeristics around and under the cable trays without the protective PAL ramps and to define maximum crossflow Mach numbers and dynamic pressures experienced during launch. These crossflow conditions were used to establish wind tunnel test conditions which also included conservative margins. For all of the conditions and configurations tested, no aeroelastic instabilities or unacceptable dynamic response levels were encountered and no visible structural damage was experienced by any of the tested cable tray sections. Based upon this aeroelastic characterization test, three potentially acceptable alternatives are available for the LO2 cable tray PAL Ramps: Mini-Ramps, Tray Fences, or No Ramps. All configurations were tested to maximum conditions, except the LH2 trays at -15 deg. crossflow angle. This exception is the only caveat preventing the proposal of acceptable alternative configurations for the LH2 trays as well. Structural assessment of all tray loads and tray response measurements from launches following the Shuttle Return To Flight with the existing PAL Ramps will determine the acceptability of these PAL Ramp alternatives.
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Design and realization of a 300 W fuel cell generator on an electric bicycle
NASA Astrophysics Data System (ADS)
Cardinali, Luciano; Santomassimo, Saverio; Stefanoni, Marco
At ENEA Casaccia Research Center (Rome, Italy) a 300 W NUVERA fuel cell stack has been utilized for the construction of a range extender generator on a commercial electric bicycle. The generator is fully automated with a programmable logic controller (PLC) safely operating start-up, shut-down and emergencies; a volumetric compressor supplies air to the cathode, a dc/dc converter transfers energy from the stack to the battery. All ancillary equipment are commercial; only the cell voltage sensors have been developed in order to obtain miniaturized and low consumption components. With this generator the bicycle nominal range of 25 km (utilizing only the Ni-Mh battery) is extended to over 120 km, by installing a 200 bar, 5 l bottle of hydrogen.
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``Carbon Credits'' for Resource-Bounded Computations Using Amortised Analysis
NASA Astrophysics Data System (ADS)
Jost, Steffen; Loidl, Hans-Wolfgang; Hammond, Kevin; Scaife, Norman; Hofmann, Martin
Bounding resource usage is important for a number of areas, notably real-time embedded systems and safety-critical systems. In this paper, we present a fully automatic static type-based analysis for inferring upper bounds on resource usage for programs involving general algebraic datatypes and full recursion. Our method can easily be used to bound any countable resource, without needing to revisit proofs. We apply the analysis to the important metrics of worst-case execution time, stack- and heap-space usage. Our results from several realistic embedded control applications demonstrate good matches between our inferred bounds and measured worst-case costs for heap and stack usage. For time usage we infer good bounds for one application. Where we obtain less tight bounds, this is due to the use of software floating-point libraries.
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1996-09-26
STS079-S-021 (26 Sept. 1996) --- The drag chute on the space shuttle Atlantis is fully deployed as the orbiter rolls down Runway 15 at the Shuttle Landing Facility (SLF) at the Kennedy Space Center (KSC), bringing an end to the successful ten-day mission. Landing occurred at 8:13:15 a.m. (EDT), Sept. 26, 1996. The touchdown marked the end of 188 days in space for astronaut Shannon W. Lucid, following her in-space exchange with astronaut John E. Blaha, who is now aboard Russia's Mir Space Station. Returning along with Lucid were her STS-79 crew mates - astronauts William F. Readdy, commander; Terrence W. Wilcutt, pilot; and Thomas D. Akers, Jerome (Jay) Apt and Carl E. Walz, mission specialists.
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Gap heating with pressure gradients. [for Shuttle Orbiter thermal protection system tiles
NASA Technical Reports Server (NTRS)
Scott, C. D.; Maraia, R. J.
1979-01-01
The heating rate distribution and temperature response on the gap walls of insulating tiles is analyzed to determine significant phenomena and parameters in flows where there is an external surface pressure gradient. Convective heating due to gap flow, modeled as fully developed pipe flow, is coupled with a two-dimensional thermal model of the tiles that includes conduction and radiative heat transfer. To account for geometry and important environmental parameters, scale factors are obtained by curve-fitting measured temperatures to analytical solutions. These scale factors are then used to predict the time-dependent gap heat flux and temperature response of tile gaps on the Space Shuttle Orbiter during entry.
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NASA Technical Reports Server (NTRS)
Baer, J. W.; Black, W. E.
1974-01-01
The thermal protection system (TPS), designed for incorporation with space shuttle orbiter systems, consists of one primary heat shield thermally and structurally isolated from the test fixture by eight peripheral guard panels, all encompassing an area of approximately 12 sq ft. TPS components include tee-stiffened Cb 752/R-512E heat shields, bi-metallic support posts, panel retainers, and high temperature insulation blankets. The vehicle primary structure was simulated by a titanium skin, frames, and stiffeners. Test procedures, manufacturing processes, and methods of analysis are fully documented. For Vol. 1, see N72-30948; for Vol. 2, see N74-15660.
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Space power distribution system technology. Volume 1: Reference EPS design
NASA Technical Reports Server (NTRS)
Decker, D. K.; Cannady, M. D.; Cassinelli, J. E.; Farber, B. F.; Lurie, C.; Fleck, G. W.; Lepisto, J. W.; Massner, A.; Ritterman, P. F.
1983-01-01
The multihundred kilowatt electrical power aspects of a mannable space platform in low Earth orbit is analyzed from a cost and technology viewpoint. At the projected orbital altitudes, Shuttle launch and servicing are technically and economically viable. Power generation is specified as photovoltaic consistent with projected planning. The cost models and trades are based upon a zero interest rate (the government taxes concurrently as required), constant dollars (1980), and costs derived in the first half of 1980. Space platform utilization of up to 30 years is evaluated to fully understand the impact of resupply and replacement as satellite missions are extended. Such lifetimes are potentially realizable with Shuttle servicing capability and are economically desirable.
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Hubble Servicing Challenges Drive Innovation of Shuttle Rendezvous Techniques
NASA Technical Reports Server (NTRS)
Goodman, John L.; Walker, Stephen R.
2009-01-01
Hubble Space Telescope (HST) servicing, performed by Space Shuttle crews, has contributed to what is arguably one of the most successful astronomy missions ever flown. Both nominal and contingency proximity operations techniques were developed to enable successful servicing, while lowering the risk of damage to HST systems, and improve crew safety. Influencing the development of these techniques were the challenges presented by plume impingement and HST performance anomalies. The design of both the HST and the Space Shuttle was completed before the potential of HST contamination and structural damage by shuttle RCS jet plume impingement was fully understood. Relative navigation during proximity operations has been challenging, as HST was not equipped with relative navigation aids. Since HST reached orbit in 1990, proximity operations design for servicing missions has evolved as insight into plume contamination and dynamic pressure has improved and new relative navigation tools have become available. Servicing missions have provided NASA with opportunities to gain insight into servicing mission design and development of nominal and contingency procedures. The HST servicing experiences and lessons learned are applicable to other programs that perform on-orbit servicing and rendezvous, both human and robotic.
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A Near-Term, High-Confidence Heavy Lift Launch Vehicle
NASA Technical Reports Server (NTRS)
Rothschild, William J.; Talay, Theodore A.
2009-01-01
The use of well understood, legacy elements of the Space Shuttle system could yield a near-term, high-confidence Heavy Lift Launch Vehicle that offers significant performance, reliability, schedule, risk, cost, and work force transition benefits. A side-mount Shuttle-Derived Vehicle (SDV) concept has been defined that has major improvements over previous Shuttle-C concepts. This SDV is shown to carry crew plus large logistics payloads to the ISS, support an operationally efficient and cost effective program of lunar exploration, and offer the potential to support commercial launch operations. This paper provides the latest data and estimates on the configurations, performance, concept of operations, reliability and safety, development schedule, risks, costs, and work force transition opportunities for this optimized side-mount SDV concept. The results presented in this paper have been based on established models and fully validated analysis tools used by the Space Shuttle Program, and are consistent with similar analysis tools commonly used throughout the aerospace industry. While these results serve as a factual basis for comparisons with other launch system architectures, no such comparisons are presented in this paper. The authors welcome comparisons between this optimized SDV and other Heavy Lift Launch Vehicle concepts.
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STS-9 payload specialists and backup in training session
NASA Technical Reports Server (NTRS)
1983-01-01
Two Spacelab 1 payload specialists and a backup for that flight prepare for a training session in the JSC mockup and integration laboratory. Fully decked out in the Shuttle constant wear garments (foreground) are Ulf Merbold, left, and Byron K. Licktenberg, prime crewmembers on the STS-9 team. In civilian clothes is payload specialist backup Michael L. Lampton.
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NASA Astrophysics Data System (ADS)
Koshelev, Alexei
2013-03-01
Stacks of intrinsic Josephson-junctions are realized in mesas fabricated out of layered superconducting single crystals, such as Bi2Sr2CaCu2O8 (BSCCO). Synchronization of phase oscillations in different junctions can be facilitated by the coupling to the internal cavity mode leading to powerful and coherent electromagnetic radiation in the terahertz frequency range. An important characteristic of this radiation is the shape of the emission line. A finite line width appears due to different noise sources leading to phase diffusion. We investigated the intrinsic line shape caused by the thermal noise for a mesa fabricated on the top of a BSCCO single crystal. In the ideal case of fully synchronized stack the finite line width is coming from two main contributions, the quasiparticle-current noise inside the mesa and the fluctuating radiation in the base crystal. We compute both contributions and conclude that for realistic mesa's parameters the second mechanism typically dominates. The role of the cavity quality factor in the emission line spectrum is clarified. Analytical results were verified by numerical simulations. In real mesa structures part of the stack may not be synchronized and chaotic dynamics of unsynchronized junctions may determine the real line width. Work supported by UChicago Argonne, LLC, under contract No. DE-AC02-06CH11357.
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Variable density randomized stack of spirals (VDR-SoS) for compressive sensing MRI.
Valvano, Giuseppe; Martini, Nicola; Landini, Luigi; Santarelli, Maria Filomena
2016-07-01
To develop a 3D sampling strategy based on a stack of variable density spirals for compressive sensing MRI. A random sampling pattern was obtained by rotating each spiral by a random angle and by delaying for few time steps the gradient waveforms of the different interleaves. A three-dimensional (3D) variable sampling density was obtained by designing different variable density spirals for each slice encoding. The proposed approach was tested with phantom simulations up to a five-fold undersampling factor. Fully sampled 3D dataset of a human knee, and of a human brain, were obtained from a healthy volunteer. The proposed approach was tested with off-line reconstructions of the knee dataset up to a four-fold acceleration and compared with other noncoherent trajectories. The proposed approach outperformed the standard stack of spirals for various undersampling factors. The level of coherence and the reconstruction quality of the proposed approach were similar to those of other trajectories that, however, require 3D gridding for the reconstruction. The variable density randomized stack of spirals (VDR-SoS) is an easily implementable trajectory that could represent a valid sampling strategy for 3D compressive sensing MRI. It guarantees low levels of coherence without requiring 3D gridding. Magn Reson Med 76:59-69, 2016. © 2015 Wiley Periodicals, Inc. © 2015 Wiley Periodicals, Inc.
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NASA Astrophysics Data System (ADS)
Ruiu, Tiziana; Dreizler, Andreas M.; Mitzel, Jens; Gülzow, Erich
2016-01-01
Nowadays, the operating temperature of polymer electrolyte membrane fuel cell stacks is typically limited to 80 °C due to water management issues of membrane materials. In the present work, short-term operation at elevated temperatures up to 120 °C and long-term steady-state operation under automotive relevant conditions at 80 °C are examined using a 30-cell stack developed at DLR. The high temperature behavior is investigated by using temperature cycles between 90 and 120 °C without adjustment of the gases dew points, to simulate a short-period temperature increase, possibly caused by an extended power demand and/or limited heat removal. This galvanostatic test demonstrates a fully reversible performance decrease of 21 ± 1% during each thermal cycle. The irreversible degradation rate is about a factor of 6 higher compared to the one determined by the long-term test. The 1200-h test at 80 °C demonstrates linear stack voltage decay with acceptable degradation rate, apart from a malfunction of the air compressor, which results in increased catalyst degradation effects on individual cells. This interpretation is based on an end-of-life characterization, aimed to investigate catalyst, electrode and membrane degradation, by determining hydrogen crossover rates, high frequency resistances, electrochemically active surface areas and catalyst particle sizes.
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2000-06-18
KENNEDY SPACE CENTER, FLA. -- In a view taken near the top of the launch tower at Launch Pad 36A, Cape Canaveral Air Force Station, the nose fairing with the Tracking and Data Relay Satellite (TDRS-H) inside is hoisted up the tower by the overhead crane (left). The fairing will be mated with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system's existing S- and Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communications with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low-earth orbit.
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2000-06-18
KENNEDY SPACE CENTER, FLA. -- In a view taken near the top of the launch tower at Launch Pad 36A, Cape Canaveral Air Force Station, the nose fairing with the Tracking and Data Relay Satellite (TDRS-H) inside is hoisted up the tower by the overhead crane (left). The fairing will be mated with the Atlas IIA/Centaur rocket, which is already stacked, for launch on June 29. The satellite will augment the TDRS system's existing S- and Ku-band frequencies by adding Ka-band capability. TDRS will serve as the sole means of continuous, high-data-rate communications with the Space Shuttle, with the International Space Station upon its completion, and with dozens of unmanned scientific satellites in low-earth orbit.
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2014-03-04
CAPE CANAVERAL, Fla. – Astronaut candidates Tyler "Nick" Hague, Josh Cassada, Christina Hamock, Jessica Meir, STS-41G astronaut Jon McBride, astronaut candidates Nicole Mann, Anne McClain, Andrew Morgan and Victor Glover pose in front of the Space Shuttle Atlantis exhibit and its full-scale external tank and solid rocket booster stack at the Kennedy Space Center Visitor Complex in Florida. The astronaut class of 2013 was selected by NASA after an extensive year-and-a-half search. The new group will help the agency push the boundaries of exploration and travel to new destinations in the solar system. To learn more about the astronaut class of 2013, visit: http://www.nasa.gov/astronauts/2013astroclass.html Photo credit: NASA/Daniel Casper
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker examines the location of the quick disconnect on the Ground Umbilical Carrier Plate, or GUCP, being removed from space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker has removed the seal from the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to remove the 7-inch quick disconnect on the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove the 7-inch quick disconnect on the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove the 7-inch quick disconnect on the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove the 7-inch quick disconnect on the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker has removed the seal from the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker removes the seal from the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers remove the 7-inch quick disconnect from the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, a worker has removed the 7-inch quick disconnect from the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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2009-06-24
CAPE CANAVERAL, Fla. – On Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers prepare to remove the seal from the Ground Umbilical Carrier Plate, or GUCP, on space shuttle Endeavour's external fuel tank. A hydrogen leak at the location during tanking for the STS-127 mission caused the launch attempts to be scrubbed on June 13 and June 17. The GUCP will be examined to determine the cause of the hydrogen leak and repaired. The GUCP is the overboard vent to the pad and the flame stack where the vented hydrogen is burned off. Endeavour's next launch attempt is targeted for July 11 at 7:39 p.m. EDT. Photo credit: NASA/Jack Pfaller
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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
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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
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Interaction of FeS 2 and Sulfur in Li-S Battery System
Sun, Ke; Cama, Christina A.; DeMayo, Rachel A.; ...
2016-09-09
Many transition metal sulfides are electronically conductive, electrochemically active and reversible in reactions with lithium. However, the application of transition metal sulfides as sulfur cathode additives in lithium-sulfur (Li-S) batteries has not been fully explored. In this study, Pyrite (FeS 2) is studied as a capacity contributing conductive additive in sulfur cathode for Li-S batteries. Electrochemically discharging the S-FeS 2 composite electrodes to 1.0 V activates the FeS 2 component, contributing to the improved Li-S cell discharge energy density. However, direct activation of the FeS 2 component in a fresh S-FeS 2 cell results in a significant shuttling effect inmore » the subsequent charging process, preventing further cell cycling. The slight FeS 2 solubility in electrolyte and its activation alone in S-FeS 2 cells are not the root causes of the severe shuttling effect. The observed severe shuttling effect is strongly correlated to the 1st charging of the activated S-FeS 2 electrode that promotes iron dissolution in electrolyte and the deposition of electronically conductive FeS on the anode SEI. Pre-cycling of the S-FeS 2 cell prior to the FeS 2 activation or the use of LiNO 3 electrolyte additive help to prevent the severe shuttling effect and allow the cell to cycle between 2.6 V to 1.0 V with an extra capacity contribution from the FeS2 components. However, a more effective method of anode pre-passivation is still needed to fully protect the lithium surface from FeS deposition and allow the S-FeS 2 electrode to maintain high energy density over extended cycles. A mechanism explaining the observed phenomena based on the experimental data is proposed and discussed« less
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Harnessing Vehicle Automation for Public Mobility -- An Overview of Ongoing Efforts
DOE Office of Scientific and Technical Information (OSTI.GOV)
Young, Stanley E.
This presentation takes a look at the efforts to harness automated vehicle technology for public transport. The European CityMobil2 is the leading demonstration project in which automated shuttles were, or are planned to be, demonstrated in several cities and regions. The presentation provides a brief overview of the demonstrations at Oristano, Italy (July 2014), LaRochelle, France (Dec 2014), Lausanne, Switzerland (Apr 2015), Vantaa, Finland (July 2015), and Trikala, Greece (Sept 2015). In addition to technology exposition, the objectives included generating a legal framework for operation in each location and gaging the reaction of the public to unmanned shuttles, both ofmore » which were successfully achieved. Several such demonstrations are planned throughout the world, including efforts in North America in conjunction with the GoMentum Station in California. These early demonstration with low-speed automated shuttles provide a glimpse of the possible with a fully automated fleet of driverless vehicle providing a public transit service.« less
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Light-erasable embedded charge-trapping memory based on MoS2 for system-on-panel applications
NASA Astrophysics Data System (ADS)
He, Long-Fei; Zhu, Hao; Xu, Jing; Liu, Hao; Nie, Xin-Ran; Chen, Lin; Sun, Qing-Qing; Xia, Yang; Wei Zhang, David
2017-11-01
The continuous scaling and challenges in device integrations in modern portable electronic products have aroused many scientific interests, and a great deal of effort has been made in seeking solutions towards a more microminiaturized package assembled with smaller and more powerful components. In this study, an embedded light-erasable charge-trapping memory with a high-k dielectric stack (Al2O3/HfO2/Al2O3) and an atomically thin MoS2 channel has been fabricated and fully characterized. The memory exhibits a sufficient memory window, fast programming and erasing (P/E) speed, and high On/Off current ratio up to 107. Less than 25% memory window degradation is observed after projected 10-year retention, and the device functions perfectly after 8000 P/E operation cycles. Furthermore, the programmed device can be fully erased by incident light without electrical assistance. Such excellent memory performance originates from the intrinsic properties of two-dimensional (2D) MoS2 and the engineered back-gate dielectric stack. Our integration of 2D semiconductors in the infrastructure of light-erasable charge-trapping memory is very promising for future system-on-panel applications like storage of metadata and flexible imaging arrays.
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NASA Astrophysics Data System (ADS)
Kestur, Ramesh; Farooq, Shariq; Abdal, Rameen; Mehraj, Emad; Narasipura, Omkar; Mudigere, Meenavathi
2018-01-01
Road extraction in imagery acquired by low altitude remote sensing (LARS) carried out using an unmanned aerial vehicle (UAV) is presented. LARS is carried out using a fixed wing UAV with a high spatial resolution vision spectrum (RGB) camera as the payload. Deep learning techniques, particularly fully convolutional network (FCN), are adopted to extract roads by dense semantic segmentation. The proposed model, UFCN (U-shaped FCN) is an FCN architecture, which is comprised of a stack of convolutions followed by corresponding stack of mirrored deconvolutions with the usage of skip connections in between for preserving the local information. The limited dataset (76 images and their ground truths) is subjected to real-time data augmentation during training phase to increase the size effectively. Classification performance is evaluated using precision, recall, accuracy, F1 score, and brier score parameters. The performance is compared with support vector machine (SVM) classifier, a one-dimensional convolutional neural network (1D-CNN) model, and a standard two-dimensional CNN (2D-CNN). The UFCN model outperforms the SVM, 1D-CNN, and 2D-CNN models across all the performance parameters. Further, the prediction time of the proposed UFCN model is comparable with SVM, 1D-CNN, and 2D-CNN models.
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2007-09-30
STS123-S-001 (Oct. 2007) --- STS-123 continues assembly of the International Space Station (ISS). The primary mission objectives include rotating an expedition crew member and installing both the first component of the Japanese Experimental Module (the Experimental Logistics Module - Pressurized Section (ELM-PS)) and the Canadian Special Purpose Dexterous Manipulator (SPDM). In addition, STS-123 will deliver various spare ISS components and leave behind the sensor boom used for inspecting the shuttle's thermal protection system. A follow-on mission to ISS will utilize and then return home with this sensor boom. A total of four spacewalks are planned to accomplish these tasks. The mission will also require the use of both the shuttle and ISS robotic arms. STS-123 will utilize the Station-Shuttle Power Transfer System to extend the docked portion of the mission to eleven days, with a total planned duration of 15 days. The crew patch depicts the space shuttle in orbit with the crew names trailing behind. STS-123's major additions to ISS (the ELM-PS installation with the shuttle robotic arm and the fully constructed SPDM) are both illustrated. The ISS is shown in the configuration that the STS-123 crew will encounter when they arrive. The NASA insignia design for space shuttle flights is reserved for use by the astronauts and for other official use as the NASA Administrator may authorize. Public availability has been approved only in the forms of illustrations by the various news media. When and if there is any change in this policy, which is not anticipated, the change will be publicly announced. Photo credit: NASA
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2007-10-01
JOHNSON SPACE CENTER, HOUSTON -- STS123-S-001-- STS-123 continues assembly of the International Space Station (ISS). The primary mission objectives include rotating an expedition crew member and installing both the first component of the Japanese Experimental Module (the Experimental Logistics Module - Pressurized Section [ELM-PS]) and the Canadian Special Purpose Dexterous Manipulator (SPDM). In addition, STS-123 will deliver various spare ISS components and leave behind the sensor boom used for inspecting the shuttle's thermal protection system. A follow-on mission to ISS will utilize and then return home with this sensor boom. A total of four spacewalks are planned to accomplish these tasks. The mission will also require the use of both the shuttle and ISS robotic arms. STS-123 will utilize the Station-Shuttle Power Transfer System to extend the docked portion of the mission to 11 days, with a total planned duration of 15 days. The crew patch depicts the space shuttle in orbit with the crew names trailing behind. STS-123's major additions to ISS (the ELM-PS installation with the shuttle robotic arm and the fully constructed SPDM) are both illustrated. The ISS is shown in the configuration that the STS-123 crew will encounter when they arrive. The NASA insignia design for shuttle flights is reserved for use by the astronauts and for other official use as the NASA Administrator may authorize. Public availability has been approved only in the form of illustrations by the various news media. When and if there is any change in this policy, which is not anticipated, it will be publicly announced.
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Ares I-X Flight Test Vehicle Modal Test
NASA Technical Reports Server (NTRS)
Buehrle, Ralph D.; Templeton, Justin D.; Reaves, Mercedes C.; Horta, Lucas G.; Gaspar, James L.; Bartolotta, Paul A.; Parks, Russel A.; Lazor, Daniel R.
2010-01-01
The first test flight of NASA's Ares I crew launch vehicle, called Ares I-X, was launched on October 28, 2009. Ares I-X used 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 was not practical within project constraints, modal tests for several configurations during vehicle stacking were defined to calibrate the FEM. Test configurations included two partial stacks and the full Ares I-X flight test vehicle on the Mobile Launcher Platform. This report describes the test requirements, constraints, pre-test analysis, test execution and results for the Ares I-X flight test vehicle modal test on the Mobile Launcher Platform. Initial comparisons between pre-test predictions and test data are also presented.
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Stack Characterization in CryoSat Level1b SAR/SARin Baseline C
NASA Astrophysics Data System (ADS)
Scagliola, Michele; Fornari, Marco; Di Giacinto, Andrea; Bouffard, Jerome; Féménias, Pierre; Parrinello, Tommaso
2015-04-01
CryoSat was launched on the 8th April 2010 and is the first European ice mission dedicated to the monitoring of precise changes in the thickness of polar ice sheets and floating sea ice. CryoSat is the first altimetry mission operating in SAR mode and it carries an innovative radar altimeter called the Synthetic Aperture Interferometric Altimeter (SIRAL), that transmits pulses at a high pulse repetition frequency thus making the received echoes phase coherent and suitable for azimuth processing. The current CryoSat IPF (Instrument Processing Facility), Baseline B, was released in operation in February 2012. After more than 2 years of development, the release in operations of the Baseline C is expected in the first half of 2015. It is worth recalling here that the CryoSat SAR/SARin IPF1 generates 20Hz waveforms in correspondence of an approximately equally spaced set of ground locations on the Earth surface, i.e. surface samples, and that a surface sample gathers a collection of single-look echoes coming from the processed bursts during the time of visibility. Thus, for a given surface sample, the stack can be defined as the collection of all the single-look echoes pointing to the current surface sample, after applying all the necessary range corrections. The L1B product contains the power average of all the single-look echoes in the stack: the multi-looked L1B waveform. This reduces the data volume, while removing some information contained in the single looks, useful for characterizing the surface and modelling the L1B waveform. To recover such information, a set of parameters has been added to the L1B product: the stack characterization or beam behaviour parameters. The stack characterization, already included in previous Baselines, has been reviewed and expanded in Baseline C. This poster describes all the stack characterization parameters, detailing what they represent and how they have been computed. In details, such parameters can be summarized in: - Stack statistical parameters, such as skewness and kurtosis - Look angle (i.e. the angle at which the surfaces sample is seen with respect to the nadir direction of the satellite) and Doppler angle (i.e. the angle at which the surfaces sample is seen with respect to the normal to the velocity vector) for the first and the last single-look echoes in the stack. - Number of single-looks averaged in the stack (in Baseline C a stack-weighting has been applied that reduces the number of looks). With the correct use of these parameters, users will be able to retrieve some of the 'lost' information contained within the stack and fully exploit the L1B product.
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Space shuttle electrical power generation and reactant supply system
NASA Technical Reports Server (NTRS)
Simon, W. E.
1985-01-01
The design philosophy and development experience of fuel cell power generation and cryogenic reactant supply systems are reviewed, beginning with the state of technology at the conclusion of the Apollo Program. Technology advancements span a period of 10 years from initial definition phase to the most recent space transportation system (STS) flights. The development program encompassed prototype, verification, and qualification hardware, as well as post-STS-1 design improvements. Focus is on the problems encountered, the scientific and engineering approaches employed to meet the technological challenges, and the results obtained. Major technology barriers are discussed, and the evolving technology development paths are traced from their conceptual beginnings to the fully man-rated systems which are now an integral part of the shuttle vehicle.
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Controlled tether extends satellite's orbital range
NASA Astrophysics Data System (ADS)
Wigotsky, V.
1984-06-01
A low orbit satellite tethered to the Space Shuttle Orbiter's cargo bay would be able to conduct upper atmosphere experiments without fear of orbit deterioration. NASA has in light of this initiated a Tethered Satellite System program aimed at the 1987 deployment of a 1,100-lb, 5 ft-diameter satellite to a distance of 6-12 miles from the Space Shuttle on a Kevlar tether. The distance of the fully developed system will be 62 miles, representing an altitude of 80 miles above the earth. Tether diameters under consideration are in the 0.065-0.1 inch range. The satellite control system will consist of a reel drive, a deployment boom, and a boom-mounted tether control, in order to vary tether tension during gravity gradient changes.
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Comparison of ACCENT 2000 Shuttle Plume Data with SIMPLE Model Predictions
NASA Astrophysics Data System (ADS)
Swaminathan, P. K.; Taylor, J. C.; Ross, M. N.; Zittel, P. F.; Lloyd, S. A.
2001-12-01
The JHU/APL Stratospheric IMpact of PLume Effluents (SIMPLE)model was employed to analyze the trace species in situ composition data collected during the ACCENT 2000 intercepts of the space shuttle Space Transportation Launch System (STS) rocket plume as a function of time and radial location within the cold plume. The SIMPLE model is initialized using predictions for species depositions calculated using an afterburning model based on standard TDK/SPP nozzle and SPF plume flowfield codes with an expanded chemical kinetic scheme. The time dependent ambient stratospheric chemistry is fully coupled to the plume species evolution whose transport is based on empirically derived diffusion. Model/data comparisons are encouraging through capturing observed local ozone recovery times as well as overall morphology of chlorine chemistry.
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Reusable space systems (Eugen Saenger Lecture, 1987)
NASA Technical Reports Server (NTRS)
Fletcher, J. C.
1988-01-01
The history and current status of reusable launch vehicle (RLV) development are surveyed, with emphases on the contributions of Eugen Saenger and ongoing NASA projects. Topics addressed include the capabilities and achievements of the Space Shuttle, the need to maintain a fleet with both ELVs and RLVs to meet different mission requirements, the X-30 testbed aircraft for the National Aerospace Plane program, current design concepts for Shuttle II (a 1000-ton fully reusable two-stage rocket-powered spacecraft capable of carrying 11,000 kg to Space Station orbit), proposals for dual-fuel-propulsion SSTO RLVs, and the Space Station Orbital Maneuvering Vehicle and Orbital Transfer Vehicle. The importance of RLVs and of international cooperation in establishing the LEO infrastructure needed for planetary exploration missions is stressed.
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NASA Technical Reports Server (NTRS)
Kromis, Phillip A.
2010-01-01
This viewgraph presentation describes the modeling and simulation of the Ares Upper Stage Transportation, lifting, stacking, and mating operations within the Vehicle Assembly Building (VAB) at Kennedy Space Center (KSC). An aerial view of KSC Launch Shuttle Complex, two views of the Delmia process control layout, and an upper stage move subroutine and breakdown are shown. An overhead image of the VAB and the turning basin along with the Pegasus barge at the turning basin are also shown. This viewgraph presentation also shows the actual design and the removal of the mid-section spring tensioners, the removal of the AFT rear and forward tensioners tie downs, and removing the AFT hold down post and mount. US leaving the Pegasus Barge, the upper stage arriving at transfer aisle, upper stage receiving/inspection in transfer aisle, and an overhead view of upper stage receiving/inspection in transfer aisle are depicted. Five views of the actual connection of the cabling to the upper stage aft lifting hardware are shown. The upper stage transporter forward connector, two views of the rotation horizontal to vertical, the disconnection of the rear bolt ring cabling, the lowering of the upper stage to the inspection stand, disconnection of the rear bolt ring from the upper stage, the lifting of the upper stage and inspection of AFT fange, and the transfer of upper stage in an integrated stack are shown. Six views of the mating of the upper stage to the first stage are depicted. The preparation, inspection, and removal of the forward dome are shown. The upper stage mated on the integrated stack and crawler is also shown. This presentation concludes with A Rapid Upper Limb Assessment (RULA) utilizing male and female models for assessing risk factors to the upper extremities of human beings in an actual physical environment.
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NASA Technical Reports Server (NTRS)
Burkardt, Leo A.
1992-01-01
A recent study has confirmed the feasibility of a near term, fully reusable, horizontal takeoff and landing two-stage-to-orbit (TSTO) launch vehicle concept. The vehicle stages at Mach 6.5. The first stage is powered by a turboramjet propulsion system with the turbojets being fueled by JP and the ramjet by LH2. The second stage is powered by a space shuttle main engine (SSME) rocket engine. For about the same gross weight as growth versions of the 747, the vehicle can place 10,000 lbm. in low polar orbit or 16,000 lbm. to Space Station Freedom.
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NASA Technical Reports Server (NTRS)
Otte, Neil E.; Lyles, Garry; Reuter, James L.; Davis, Daniel J.
2008-01-01
Fielding an integrated launch vehicle system entails many challenges, not the least of which is the fact that it has been over 30 years since the United States has developed a human-rated vehicle - the venerable Space Shuttle. Over time, whole generations of rocket scientists have passed through the aerospace community without the opportunity to perform such exacting, demanding, and rewarding work. However, with almost 50 years of experience leading the design, development, and end-to-end systems engineering and integration of complex launch vehicles, the National Aeronautics and Space Administration's (NASA's) Marshall Space Flight Center offers the in-house talent - both junior- and senior-level personnel - to shape a new national asset to meet the requirements for safe, reliable, and affordable space exploration solutions. The technical personnel are housed primarily in Marshall's Engineering Directorate and are matrixed into the programs and projects that reside at the rocket center. Fortunately, many Apollo-era and Shuttle engineers, as well as those who gained valuable hands-on experience in the 1990s by conducting technology demonstrator projects such as the Delta-Clipper Experimental Advanced, X-33, X-34, and X-37, as well as the short-lived Orbital Space Plane, work closely with industry partners to advance the nation's strategic capability for human access to space. The Ares Projects Office, resident at Marshall, is managing the design and development of America's new space fleet, including the Ares I, which will loft the Orion crew capsule for its first test flight in the 2013 timeframe, as well as the heavy-lift Ares V, which will round out the capability to leave low-Earth orbit once again, when it delivers the Altair lunar lander to orbit late next decade. This paper provides information about the approach to integrating the Ares I stack and designing the upper stage in house, using unique facilities and an expert workforce to revitalize the nation's space exploration resources.
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Xu, Shuozhi; Xiong, Liming; Chen, Youping; ...
2017-04-26
Dislocation/stacking fault interactions play an important role in the plastic deformation of metallic nanocrystals and polycrystals. These interactions have been explored in atomistic models, which are limited in scale length by high computational cost. In contrast, multiscale material modeling approaches have the potential to simulate the same systems at a fraction of the computational cost. In this paper, we validate the concurrent atomistic-continuum (CAC) method on the interactions between a lattice screw dislocation and a stacking fault (SF) in three face-centered cubic metallic materials—Ni, Al, and Ag. Two types of SFs are considered: intrinsic SF (ISF) and extrinsic SF (ESF).more » For the three materials at different strain levels, two screw dislocation/ISF interaction modes (annihilation of the ISF and transmission of the dislocation across the ISF) and three screw dislocation/ESF interaction modes (transformation of the ESF into a three-layer twin, transformation of the ESF into an ISF, and transmission of the dislocation across the ESF) are identified. Here, our results show that CAC is capable of accurately predicting the dislocation/SF interaction modes with greatly reduced DOFs compared to fully-resolved atomistic simulations.« less
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Xu, Shuozhi; Xiong, Liming; Chen, Youping
Dislocation/stacking fault interactions play an important role in the plastic deformation of metallic nanocrystals and polycrystals. These interactions have been explored in atomistic models, which are limited in scale length by high computational cost. In contrast, multiscale material modeling approaches have the potential to simulate the same systems at a fraction of the computational cost. In this paper, we validate the concurrent atomistic-continuum (CAC) method on the interactions between a lattice screw dislocation and a stacking fault (SF) in three face-centered cubic metallic materials—Ni, Al, and Ag. Two types of SFs are considered: intrinsic SF (ISF) and extrinsic SF (ESF).more » For the three materials at different strain levels, two screw dislocation/ISF interaction modes (annihilation of the ISF and transmission of the dislocation across the ISF) and three screw dislocation/ESF interaction modes (transformation of the ESF into a three-layer twin, transformation of the ESF into an ISF, and transmission of the dislocation across the ESF) are identified. Here, our results show that CAC is capable of accurately predicting the dislocation/SF interaction modes with greatly reduced DOFs compared to fully-resolved atomistic simulations.« less
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Implementation of Grid Tier 2 and Tier 3 facilities on a Distributed OpenStack Cloud
NASA Astrophysics Data System (ADS)
Limosani, Antonio; Boland, Lucien; Coddington, Paul; Crosby, Sean; Huang, Joanna; Sevior, Martin; Wilson, Ross; Zhang, Shunde
2014-06-01
The Australian Government is making a AUD 100 million investment in Compute and Storage for the academic community. The Compute facilities are provided in the form of 30,000 CPU cores located at 8 nodes around Australia in a distributed virtualized Infrastructure as a Service facility based on OpenStack. The storage will eventually consist of over 100 petabytes located at 6 nodes. All will be linked via a 100 Gb/s network. This proceeding describes the development of a fully connected WLCG Tier-2 grid site as well as a general purpose Tier-3 computing cluster based on this architecture. The facility employs an extension to Torque to enable dynamic allocations of virtual machine instances. A base Scientific Linux virtual machine (VM) image is deployed in the OpenStack cloud and automatically configured as required using Puppet. Custom scripts are used to launch multiple VMs, integrate them into the dynamic Torque cluster and to mount remote file systems. We report on our experience in developing this nation-wide ATLAS and Belle II Tier 2 and Tier 3 computing infrastructure using the national Research Cloud and storage facilities.
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NASA Glenn Research Center's Fuel Cell Stack, Ancillary and System Test and Development Laboratory
NASA Technical Reports Server (NTRS)
Loyselle, Patricia L.; Prokopius, Kevin P.; Becks, Larry A.; Burger, Thomas H.; Dick, Joseph F.; Rodriguez, George; Bremenour, Frank; Long, Zedock
2011-01-01
At the NASA Glenn Research Center, a fully operational fuel cell test and evaluation laboratory is available which is capable of evaluating fuel cell components and systems for future NASA missions. Components and subsystems of various types can be operated and monitored under a variety of conditions utilizing different reactants. This fuel cell facility can test the effectiveness of various component and system designs to meet NASA's needs.
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Höfle, Stefan; Schienle, Alexander; Bernhard, Christoph; Bruns, Michael; Lemmer, Uli; Colsmann, Alexander
2014-08-13
Fully solution processed monochromatic and white-light emitting tandem or multi-photon polymer OLEDs with an inverted device architecture have been realized by employing WO3 /PEDOT:PSS/ZnO/PEI charge carrier generation layers. The luminance of the sub-OLEDs adds up in the stacked device indicating multi-photon emission. The white OLEDs exhibit a CRI of 75. © 2014 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.
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Carey, Tian; Cacovich, Stefania; Divitini, Giorgio; Ren, Jiesheng; Mansouri, Aida; Kim, Jong M; Wang, Chaoxia; Ducati, Caterina; Sordan, Roman; Torrisi, Felice
2017-10-31
Fully printed wearable electronics based on two-dimensional (2D) material heterojunction structures also known as heterostructures, such as field-effect transistors, require robust and reproducible printed multi-layer stacks consisting of active channel, dielectric and conductive contact layers. Solution processing of graphite and other layered materials provides low-cost inks enabling printed electronic devices, for example by inkjet printing. However, the limited quality of the 2D-material inks, the complexity of the layered arrangement, and the lack of a dielectric 2D-material ink able to operate at room temperature, under strain and after several washing cycles has impeded the fabrication of electronic devices on textile with fully printed 2D heterostructures. Here we demonstrate fully inkjet-printed 2D-material active heterostructures with graphene and hexagonal-boron nitride (h-BN) inks, and use them to fabricate all inkjet-printed flexible and washable field-effect transistors on textile, reaching a field-effect mobility of ~91 cm 2 V -1 s -1 , at low voltage (<5 V). This enables fully inkjet-printed electronic circuits, such as reprogrammable volatile memory cells, complementary inverters and OR logic gates.
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DOE Office of Scientific and Technical Information (OSTI.GOV)
Hoffeditz, William L.; Katz, Michael J.; Deria, Pravas
Dye-sensitized solar cells (DSCs) are an established alternative photovoltaic technology that offers numerous potential advantages in solar energy applications. However, this technology has been limited by the availability of molecular redox couples that are both noncorrosive/nontoxic and do not diminish the performance of the device. In an effort to overcome these shortcomings, a copper-containing redox shuttle derived from 1,8-bis(2'-pyridyl)-3,6-dithiaoctane (PDTO) ligand and the common DSC additive 4-tert-butylpyridine (TBP) was investigated. Electrochemical measurements, single-crystal X-ray diffraction, and absorption and electron paramagnetic resonance spectroscopies reveal that, upon removal of one metal-centered electron, PDTO-enshrouded copper ions completely shed the tetradentate PDTO ligand andmore » replace it with four or more TBP ligands. Thus, the Cu(I) and Cu(II) forms of the electron shuttle have completely different coordination spheres and are characterized by widely differing Cu(II/I) formal potentials and reactivities for forward versus reverse electron transfer. Notably, the coordination-sphere replacement process is fully reversed upon converting Cu(II) back to Cu(I). In cells featuring an adsorbed organic dye and a nano- and mesoparticulate, TiO2-based, photoelectrode, the dual species redox shuttle system engenders performance superior to that obtained with shuttles based on the (II/I) forms of either of the coordination complexes in isolation.« less
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NASA Technical Reports Server (NTRS)
1987-01-01
The Advanced Space Design project for 1986-87 was the design of a two stage launch vehicle, representing a second generation space transportation system (STS) which will be needed to support the space station. The first stage is an unmanned winged booster which is fully reusable with a fly back capability. It has jet engines so that it can fly back to the landing site. This adds safety as well as the flexibility to choose alternate landing sites. There are two different second stages. One of the second stages is a manned advanced space shuttle called Space Shuttle II. Space Shuttle II has a payload capability of delivering 40,000 pounds to the space station in low Earth orbit (LEO), and returning 40,000 pounds to Earth. Servicing the space station makes the ability to return a heavy payload to Earth as important as being able to launch a heavy payload. The other second stage is an unmanned heavy lift cargo vehicle with ability to deliver 150,000 pounds of payload to LEO. This vehicle will not return to Earth; however, the engines and electronics can be removed and returned to Earth in the Space Shuttle II. The rest of the vehicle can then be used on orbit for storage or raw materials, supplies, and space manufactured items awaiting transport back to Earth.
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ELECTROCHEMISTRY AND ON-CELL REFORMATION MODELING FOR SOLID OXIDE FUEL CELL STACKS
DOE Office of Scientific and Technical Information (OSTI.GOV)
Recknagle, Kurtis P.; Jarboe, Daniel T.; Johnson, Kenneth I.
2007-01-16
ABSTRACT Providing adequate and efficient cooling schemes for solid-oxide-fuel-cell (SOFC) stacks continues to be a challenge coincident with the development of larger, more powerful stacks. The endothermic steam-methane reformation reaction can provide cooling and improved system efficiency when performed directly on the electrochemically active anode. Rapid kinetics of the endothermic reaction typically causes a localized temperature depression on the anode near the fuel inlet. It is desirable to extend the endothermic effect over more of the cell area and mitigate the associated differences in temperature on the cell to alleviate subsequent thermal stresses. In this study, modeling tools validated formore » the prediction of fuel use, on-cell methane reforming, and the distribution of temperature within SOFC stacks, are employed to provide direction for modifying the catalytic activity of anode materials to control the methane conversion rate. Improvements in thermal management that can be achieved through on-cell reforming is predicted and discussed. Two operating scenarios are considered: one in which the methane fuel is fully pre-reformed, and another in which a substantial percentage of the methane is reformed on-cell. For the latter, a range of catalytic activity is considered and the predicted thermal effects on the cell are presented. Simulations of the cell electrochemical and thermal performance with and without on-cell reforming, including structural analyses, show a substantial decrease in thermal stresses for an on-cell reforming case with slowed methane conversion.« less
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Energetics analysis of interstitial loops in single-phase concentrated solid-solution alloys
NASA Astrophysics Data System (ADS)
Wang, Xin-Xin; Niu, Liang-Liang; Wang, Shaoqing
2018-04-01
Systematic energetics analysis on the shape preference, relative stability and radiation-induced segregation of interstitial loops in nickel-containing single-phase concentrated solid-solution alloys have been conducted using atomistic simulations. It is shown that the perfect loops prefer rhombus shape for its low potential energy, while the Frank faulted loops favor ellipse for its low potential energy and the possible large configurational entropy. The decrease of stacking fault energy with increasing compositional complexity provides the energetic driving force for the formation of faulted loops, which, in conjunction with the kinetic factors, explains the experimental observation that the fraction of faulted loops rises with increasing compositional complexity. Notably, the kinetics is primarily responsible for the absence of faulted loops in nickel-cobalt with a very low stacking fault energy. We further demonstrate that the simultaneous nickel enrichment and iron/chromium depletion on interstitial loops can be fully accounted for by their energetics.
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Reactivating the Ni-YSZ electrode in solid oxide cells and stacks by infiltration
NASA Astrophysics Data System (ADS)
Skafte, Theis Løye; Hjelm, Johan; Blennow, Peter; Graves, Christopher
2018-02-01
The solid oxide cell (SOC) could play a vital role in energy storage when the share of intermittent electricity production is high. However, large-scale commercialization of the technology is still hindered by the limited lifetime. Here, we address this issue by examining the potential for repairing various failure and degradation mechanisms occurring in the fuel electrode, thereby extending the potential lifetime of a SOC system. We successfully infiltrated the nickel and yttria-stabilized zirconia cermet electrode in commercial cells with Gd-doped ceria after operation. By this method we fully reactivated the fuel electrode after simulated reactant starvation and after carbon formation. Furthermore, by infiltrating after 900 h of operation, the degradation of the fuel electrode was reduced by a factor of two over the course of 2300 h. Lastly, the scalability of the concept is demonstrated by reactivating an 8-cell stack based on a commercial design.
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2009-03-11
CAPE CANAVERAL, Fla. – A closeup of the 7-inch quick disconnect that will be replaced on the hydrogen vent line to the Ground Umbilical Carrier Plate of space shuttle Discovery's external fuel tank. The replacement will be made on Launch Pad 39A at NASA's Kennedy Space Center in Florida. A leak of hydrogen at the site during fueling caused the STS-119 mission to be scrubbed at 2:36 p.m. March 11. The vent line is at the intertank and is the overboard vent to the pad and the flare stack where the vented hydrogen is burned off. Mission management teams believe they have sufficient understanding of the repair plan to continue toward a March 15 launch at 7:43 p.m. EDT. Photo courtesy of United Space Alliance
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Thermal Analysis of Cryogenic Hydrogen Liquid Separator
NASA Technical Reports Server (NTRS)
Congiardo, Jared F.; Fortier, Craig R. (Editor)
2014-01-01
During launch for the new Space Launch System (SLS) liquid hydrogen is bleed through the engines during replenish, pre-press, and extended pre-press to condition the engines prior to launch. The predicted bleed flow rates are larger than for the shuttle program. A consequence of the increased flow rates is having liquif hydrogen in the vent system, which the facilities was never designed to handle. To remedy the problem a liquid separator is being designed in the system to accumulated the liquid propellant and protect the facility flare stack (which can only handle gas). The attached document is a presentation of the current thermalfluid analysis performed for the separator and will be presented at the Thermal and Fluid Analysis Workshop (NASA workshop) next week in Cleveland, Ohio.
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Extracting 5m Shorelines From Multi-Temporal Images
NASA Astrophysics Data System (ADS)
Kapadia, A.; Jordahl, K. A.; Kington, J. D., IV
2016-12-01
Planet operates the largest Earth observing constellation of satellites, collecting imagery at an unprecedented temporal resolution. While daily cadence is expected in early 2017, Planet has already imaged the majority of landmass several dozen times over the past year. The current dataset provides enough value to build and test algorithms to automatically extract information. Here we demonstrate the extraction of shorelines across California using image stacks. The method implemented uses as input an uncalibrated RGB data product and limited NIR combined with the National Land Cover Database 2011 (NLCD2011) and Shuttle Radar Topography Mission (SRTM) to extract shorelines at 5 meter resolution. In the near future these methods along with daily cadence of imagery will allow for temporal monitoring of shorelines on a global scale.
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2007-10-11
KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the frustum is lifted from a transporter to be moved onto a stand. The solid rocket booster segment will be added to the stack for space shuttle Atlantis, launch vehicle for mission STS-122 targeted for a December launch. Atlantis will be carrying the Columbus Laboratory, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Jack Pfaller
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2007-10-11
KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the frustum is lifted from a transporter to be moved onto a stand. The solid rocket booster segment will be added to the stack for space shuttle Atlantis, launch vehicle for mission STS-122 targeted for a December launch. Atlantis will be carrying the Columbus Laboratory, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Jack Pfaller
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Space Shuttle Reusable Solid Rocket Motor
NASA Technical Reports Server (NTRS)
Moore, Dennis; Phelps, Jack; Perkins, Fred
2010-01-01
RSRM is a highly reliable human-rated Solid Rocket Motor: a) Largest diameter SRM to achieve flight status; b) Only human-rated SRM. RSRM reliability achieved by: a)Applying special attention to Process Control, Testing, and Postflight; b) Communicating often; c) Identifying and addressing issues in a disciplined approach; d) Identifying and fully dispositioning "out-of-family" conditions; e) Addressing minority opinions; and f) Learning our lessons.
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Space science experimentation automation and support
NASA Technical Reports Server (NTRS)
Frainier, Richard J.; Groleau, Nicolas; Shapiro, Jeff C.
1994-01-01
This paper outlines recent work done at the NASA Ames Artificial Intelligence Research Laboratory on automation and support of science experiments on the US Space Shuttle in low earth orbit. Three approaches to increasing the science return of these experiments using emerging automation technologies are described: remote control (telescience), science advisors for astronaut operators, and fully autonomous experiments. The capabilities and limitations of these approaches are reviewed.
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Survey of Advanced Booster Options for Potential Shuttle Derivative Vehicles
NASA Technical Reports Server (NTRS)
Sackheim, Robert L.; Ryan, Richard; Threet, Ed; Kennedy, James W. (Technical Monitor)
2001-01-01
A never-ending major goal for the Space Shuttle program is to continually improve flight safety, as long as this launch system remains in operational service. One of the options to improve system safety and to enhance vehicle performance as well, that has been seriously studied over the past several decades, is to replace the existing strap-on four segment solid rocket boosters (SRB's) with more capable units. A number of booster upgrade options have been studied in some detail, ranging from five segment solids through hybrids and a wide variety of liquid strap-ons (both pressure and pump fed with various propellants); all the way to a completely reusable liquid fly back booster (complete with air breathing engines for controlled landing and return). All of these possibilities appear to offer improvements in varying degrees; and each has their strengths and weaknesses from both programmatic and technical points of view. The most beneficial booster upgrade/design, if the shuttle program were to continue long enough to justify the required investment, would be an approach that greatly increased both vehicle and crew safety. This would be accomplished by increasing the minimum range/minimum altitude envelope that would readily allow abort to orbit (ATO), possibly even to zero/zero, and possibly reduce or eliminate the Return to Launch Site (RTLS) and even the Trans Atlantic Landing (TAL) abort mode requirements. This paper will briefly survey and discuss all of the various booster'upgrade options studied previously, and compare their relative attributes. The survey will explicitly discuss, in summary comparative form, options that include: five segment solids; several hybrid possibilities; pressure and/or pump-fed liquids using either LO2/kerosene, H2O/kerosene and LO2/J2, any of which could be either fully expendable, partly or fully reusable; and finally a fully reusable liquid fly back booster system, with a number of propellant and propulsion system options. Performance and configuration comparison illustrations and tables will be included to provide a comprehensive survey for the paper.
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Space Shuttle Main Engine - The Relentless Pursuit of Improvement
NASA Technical Reports Server (NTRS)
VanHooser, Katherine P.; Bradley, Douglas P.
2011-01-01
The Space Shuttle Main Engine (SSME) is the only reusable large liquid rocket engine ever developed. The specific impulse delivered by the staged combustion cycle, substantially higher than previous rocket engines, minimized volume and weight for the integrated vehicle. The dual pre-burner configuration permitted precise mixture ratio and thrust control while the fully redundant controller and avionics provided a very high degree of system reliability and health diagnosis. The main engine controller design was the first rocket engine application to incorporate digital processing. The engine was required to operate at a high chamber pressure to minimize engine volume and weight. Power level throttling was required to minimize structural loads on the vehicle early in flight and acceleration levels on the crew late in ascent. Fatigue capability, strength, ease of assembly and disassembly, inspectability, and materials compatibility were all major considerations in achieving a fully reusable design. During the multi-decade program the design evolved substantially using a series of block upgrades. A number of materials and manufacturing challenges were encountered throughout SSME s history. Significant development was required for the final configuration of the high pressure turbopumps. Fracture control was implemented to assess life limits of critical materials and components. Survival in the hydrogen environment required assessment of hydrogen embrittlement. Instrumentation systems were a challenge due to the harsh thermal and dynamic environments within the engine. Extensive inspection procedures were developed to assess the engine components between flights. The Space Shuttle Main Engine achieved a remarkable flight performance record. All flights were successful with only one mission requiring an ascent abort condition, which still resulted in an acceptable orbit and mission. This was achieved in large part via extensive ground testing to fully characterize performance and to establish acceptable life limits. During the program over a million seconds of accumulated test and flight time was achieved. Post flight inspection and assessment was a key part of assuring proper performance of the flight hardware. By the end of the program the predicted reliability had improved by a factor of four. These unique challenges, evolution of the design, and the resulting reliability will be discussed in this paper.
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International Space Station Configuration After P6 Truss Installation
NASA Technical Reports Server (NTRS)
2006-01-01
Photographed from the Space Shuttle Discovery upon its separation from the orbital outpost, the International Space Station (ISS) is shown sporting its new additions. A fly-around gave the crew a look at their handiwork, a new P5 spacer truss segment and a fully retracted P6 solar array wing. Earlier, the STS-116 and Expedition 14 crews concluded eight days of cooperative work onboard the shuttle and station where they accomplished the installation of the newest piece of the station and completely rewired the power grid over the course of four space walks. The station is currently the size of a typical three-bedroom house, with a surface area large enough to cover four basketball courts. The image reflects the latest configuration of the ISS as of December 19, 2006.
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Propulsion and fluid management - Station keeping will eat energy on a new scale
NASA Technical Reports Server (NTRS)
Petrash, D. A.
1983-01-01
An attempt is made to identify technologies that could be brought to a state of minimal development risk in the near term, yet offer the potential for evolutionary growth consistent with future space station propulsion requirements. Prospective auxiliary propulsion propellants will be usable by other systems, thereby offering resupply benefits and a benign rather than corrosive or toxic handling environment. NASA programs are currently underway to develop the storage and supply methods for cryogenic liquids in orbit. The recovery of unused propellants from the Space Shuttle Orbiter and External Tank are being evaluated in order to define Shuttle modifications and performance penalties. Fluid management subsystem requirements and characteristics cannot, however, be fully defined until a firm mission scenario has been established and other space station subsystems are more clearly defined.
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SLEEP - Williams wearing sleep net
1998-05-12
STS090-377-011 (17 APRIL-3 MAY 1998) --- Astronaut Dafydd R. (Dave) Williams, mission specialist representing the Canadian Space Agency (CSA), accomplishes more than one purpose when he sleeps in this bunk aboard the Earth-orbiting Space Shuttle Columbia. Conducting a Neurolab sleep experiment, Williams wears equipment which includes a sleep net (mesh cap that monitors and records brain waves); a Respiratory Inductance Plethysmograph (RIP) suit for monitoring respiration; and an activity monitor -- a device (out of view) worn on the wrist to detect and record body movement. Data on brain waves, eye movements, respiration, heart rate, and oxygen concentration are routed to a portable data recorder. The entire system has capabilities similar to a fully equipped sleep laboratory on Earth. The sleeping bag is conventional Shuttle ware and not part of the experiment.
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Redesigned Gas Mass Flow Sensors for Space Shuttle Pressure Control System and Fuel Cell System
NASA Technical Reports Server (NTRS)
1996-01-01
A program was conducted to determine if a state of the art micro-machined silicon solid state flow sensor could be used to replace the existing space shuttle orbiter flow sensors. The rather aggressive goal was to obtain a new sensor which would also be a multi-gas sensor and operate over a much wider flow range and with a higher degree of accuracy than the existing sensors. Two types of sensors were tested. The first type was a venturi throat design and the second was a bypass design. The accuracy of venturi design was found to be marginally acceptable. The bypass sensor was much better although it still did not fully reach the accuracy goal. Two main problems were identified which would require further work.
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ALT space shuttle barometric altimeter altitude analysis
NASA Technical Reports Server (NTRS)
Killen, R.
1978-01-01
The accuracy was analyzed of the barometric altimeters onboard the space shuttle orbiter. Altitude estimates from the air data systems including the operational instrumentation and the developmental flight instrumentation were obtained for each of the approach and landing test flights. By comparing the barometric altitude estimates to altitudes derived from radar tracking data filtered through a Kalman filter and fully corrected for atmospheric refraction, the errors in the barometric altitudes were shown to be 4 to 5 percent of the Kalman altitudes. By comparing the altitude determined from the true atmosphere derived from weather balloon data to the altitude determined from the U.S. Standard Atmosphere of 1962, it was determined that the assumption of the Standard Atmosphere equations contributes roughly 75 percent of the total error in the baro estimates. After correcting the barometric altitude estimates using an average summer model atmosphere computed for the average latitude of the space shuttle landing sites, the residual error in the altitude estimates was reduced to less than 373 feet. This corresponds to an error of less than 1.5 percent for altitudes above 4000 feet for all flights.
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STS-96 Discovery Night Landing with Drag chute
NASA Technical Reports Server (NTRS)
1999-01-01
With its drag chute fully deployed, Space Shuttle Discovery lands on KSC's brightly lighted Shuttle Landing Facility runway 15, completing the 9-day, 19-hour, 13-minute and 1-second long STS-96 mission. Main gear touchdown was at 2:02:43 EDT June 6 , landing on orbit 154 of the mission. Nose gear touchdown was at 2:02:59 a.m. EDT, and the wheels stopped at 2:03:39 a.m. EDT. At the controls were Commander Kent V. Rominger and Pilot Rick D. Husband. Also onboard the orbiter were Mission Specialists Ellen Ochoa (Ph.D.), Tamara E. Jernigan (Ph.D.), Daniel S. Barry (M.D., Ph.D.), Julie Payette and Valery Ivanovich Tokarev. Payette represents the Canadian Space Agency and Tokarev the Russian Space Agency. The crew returned from the second flight to the International Space Station on a logistics and resupply mission. This was the 94th flight in the Space Shuttle program and the 26th for Discovery, also marking the 47th landing at KSC, the 24th in the last 25 missions, 11th at night, and the 18th consecutive landing in Florida.
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Analysis of the Space Shuttle main engine simulation
NASA Technical Reports Server (NTRS)
Deabreu-Garcia, J. Alex; Welch, John T.
1993-01-01
This is a final report on an analysis of the Space Shuttle Main Engine Program, a digital simulator code written in Fortran. The research was undertaken in ultimate support of future design studies of a shuttle life-extending Intelligent Control System (ICS). These studies are to be conducted by NASA Lewis Space Research Center. The primary purpose of the analysis was to define the means to achieve a faster running simulation, and to determine if additional hardware would be necessary for speeding up simulations for the ICS project. In particular, the analysis was to consider the use of custom integrators based on the Matrix Stability Region Placement (MSRP) method. In addition to speed of execution, other qualities of the software were to be examined. Among these are the accuracy of computations, the useability of the simulation system, and the maintainability of the program and data files. Accuracy involves control of truncation error of the methods, and roundoff error induced by floating point operations. It also involves the requirement that the user be fully aware of the model that the simulator is implementing.
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International Cooperation in the Field of International Space Station (ISS) Payload Safety
NASA Astrophysics Data System (ADS)
Grayson, C.; Sgobba, T.; Larsen, A.; Rose, S.; Heimann, T.; Ciancone, M.; Mulhern, V.
2005-12-01
In the frame of the International Space Station (ISS) Program cooperation, in 1998 the European Space Agency (ESA) approached the National Aeronautics and Space Administration (NASA) with the unique concept of a Payload Safety Review Panel (PSRP) "franchise" based at the European Space Technology Center (ESTEC), where the panel would be capable of autonomously reviewing flight hardware for safety. This paper will recount the course of an ambitious idea as it progressed into a fully functional reality. It will show how a panel initially conceived at NASA to serve a national programme has evolved into an international safety cooperation asset. The PSRP established at NASA began reviewing ISS payloads approximately in late 1994 or early 1995 as an expansion of the pre- existing Shuttle Program PSRP. This paper briefly describes the fundamental Shuttle safety process and the establishment of the safety requirements for payloads intending to use the Space Transportation System and ISS. The paper will also offer some historical statistics about the experiments that completed the payload safety process for Shuttle and ISS. The paper then presents the background of ISS agreements and international treaties that had to be considered when establishing the ESA PSRP. The paper will expound upon the detailed franchising model, followed by an outline of the cooperation charter approved by the NASA Associate Administrator, Office of Space Flight, and ESA Director of Manned Spaceflight and Microgravity. The paper will then address the resulting ESA PSRP implementation and its success statistics to date. Additionally, the paper presents ongoing developments with the Japan Aerospace Exploration Agency (JAXA). The discussion will conclude with ideas for future developments, such to achieve a fully integrated international system of payload safety panels for ISS.
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International Cooperation in the Field of International Space Station (ISS) Payload Safety
NASA Technical Reports Server (NTRS)
Heimann, Timothy; Larsen, Axel M.; Rose, Summer; Sgobba, Tommaso
2005-01-01
In the frame of the International Space Station (ISS) Program cooperation, in 1998, the European Space Agency (ESA) approached the National Aeronautics and Space Administration (NASA) with the unique concept of a Payload Safety Review Panel (PSRP) "franchise" based at the European Space Technology Center (ESTEC), where the panel would be capable of autonomously reviewing flight hardware for safety. This paper will recount the course of an ambitious idea as it progressed into a fully functional reality. It will show how a panel initially conceived at NASA to serve a national programme has evolved into an international safety cooperation asset. The PSRP established at NASA began reviewing ISS payloads approximately in late 1994 or early 1995 as an expansion of the pre-existing Shuttle Program PSRP. This paper briefly describes the fundamental Shuttle safety process and the establishment of the safety requirements for payloads intending to use the Space Transportation System and International Space Station (ISS). The paper will also offer some historical statistics about the experiments that completed the payload safety process for Shuttle and ISS. The paper 1 then presents the background of ISS agreements and international treaties that had to be taken into account when establishing the ESA PSRP. The detailed franchising model will be expounded upon, followed by an outline of the cooperation charter approved by the NASA Associate Administrator, Office of Space Flight, and ESA Director of Manned Spaceflight and Microgravity. The resulting ESA PSRP implementation and its success statistics to date will then be addressed. Additionally the paper presents the ongoing developments with the Japan Aerospace Exploration Agency. The discussion will conclude with ideas for future developments, such to achieve a fully integrated international system of payload safety panels for ISS.
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Brooks, G A
2002-04-01
Once thought to be the consequence of oxygen lack in contracting skeletal muscle, the glycolytic product lactate is formed and utilized continuously under fully aerobic conditions. "Cell-cell" and "intracellular lactate shuttle" concepts describe the roles of lactate in the delivery of oxidative and gluconeogenic substrates, as well as in cell signalling. Examples of cell-cell shuttles include lactate exchanges between white-glycolytic and red-oxidative fibres within a working muscle bed, between working skeletal muscle and heart, and between tissues of net lactate release and gluconeogenesis. Lactate exchange between astrocytes and neurons that is linked to glutamatergic signalling in the brain is an example of a lactate shuttle supporting cell-cell signalling. Lactate uptake by mitochondria and pyruvate-lactate exchange in peroxisomes are examples of intracellular lactate shuttles. Lactate exchange between sites of production and removal is facilitated by monocarboxylate transport proteins, of which there are several isoforms, and, probably, also by scaffolding proteins. The mitochondrial lactate-pyruvate transporter appears to work in conjunction with mitochondrial lactate dehydrogenase, which permits lactate to be oxidized within actively respiring cells. Hence mitochondria function to establish the concentration and proton gradients necessary for cells with high mitochondrial densities (e.g. cardiocytes) to take up and oxidize lactate. Arteriovenous difference measurements on working cardiac and skeletal muscle beds as well as NMR spectral analyses of these tissues show that lactate is formed and oxidized within the cells of formation in vivo. Glycolysis and lactate oxidation within cells permits high flux rates and the maintenance of redox balance in the cytosol and mitochondria. Other examples of intracellular lactate shuttles include lactate uptake and oxidation in sperm mitochondria and the facilitation of beta-oxidation in peroxisomes by pyruvate-lactate exchange. An ancient origin to the utility of lactate shuttling is implied by the observation that mitochondria of Saccharomyces cerevisiae contain flavocytochrome b(2), a lactate-cytochrome c oxidoreductase that couples lactate dehydrogenation to the reduction of cytochrome c. The presence of cell-cell and intracellular lactate shuttles gives rise to the notion that glycolytic and oxidative pathways can be viewed as linked, as opposed to alternative, processes, because lactate, the product of one pathway, is the substrate for the other.
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Prediction of in-depth gap heating ratios from wing glove model test data. [space shuttle orbiter
NASA Technical Reports Server (NTRS)
1977-01-01
In-depth gap heating ratios were predicted down RSI tile sidewalls based on temperature measurements obtained from the JSC arc-jet Wing Glove model tests in order to develop gap heating ratios which resulted in the best possible fit of test data and to produce a set of engineering verification heating ratios similar in shape to one another which could be used at various body points on the Orbiter during reentry. The Rockwell TPS Multidimensional heat conduction program was used to perform 3-D thermal analyses using a 3.0 in. thick section of a curved RSI tile with 283 nodal points. Correlation with test data shows that the predicted heating ratios were significantly higher down in the gap than the zero pressure values for T/C stacks 39 and 38 on the Wing Glove model. For stack 37 (in a low pressure region), the baseline heating ratio overpredicted the temperature data. This analysis, which showed that the heating ratios were a strong function of the product of pressure and pressure gradient, will be used to compare with recent Gap/Step and Ames Double Wedge test/analysis results in the effort to identify the Orbiter gap response to high delta P flight environment.
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NASA Astrophysics Data System (ADS)
Torres-Verdin, C.
2007-05-01
This paper describes the successful implementation of a new 3D AVA stochastic inversion algorithm to quantitatively integrate pre-stack seismic amplitude data and well logs. The stochastic inversion algorithm is used to characterize flow units of a deepwater reservoir located in the central Gulf of Mexico. Conventional fluid/lithology sensitivity analysis indicates that the shale/sand interface represented by the top of the hydrocarbon-bearing turbidite deposits generates typical Class III AVA responses. On the other hand, layer- dependent Biot-Gassmann analysis shows significant sensitivity of the P-wave velocity and density to fluid substitution. Accordingly, AVA stochastic inversion, which combines the advantages of AVA analysis with those of geostatistical inversion, provided quantitative information about the lateral continuity of the turbidite reservoirs based on the interpretation of inverted acoustic properties (P-velocity, S-velocity, density), and lithotype (sand- shale) distributions. The quantitative use of rock/fluid information through AVA seismic amplitude data, coupled with the implementation of co-simulation via lithotype-dependent multidimensional joint probability distributions of acoustic/petrophysical properties, yields accurate 3D models of petrophysical properties such as porosity and permeability. Finally, by fully integrating pre-stack seismic amplitude data and well logs, the vertical resolution of inverted products is higher than that of deterministic inversions methods.
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NASA Redox cell stack shunt current, pumping power, and cell performance tradeoffs
NASA Technical Reports Server (NTRS)
Hagedorn, N.; Hoberecht, M. A.; Thaller, L. H.
1982-01-01
The NASA Redox energy storage system is under active technology development. The hardware undergoing laboratory testing is either 310 sq. cm. or 929 sq. cm. (0.33 sq. ft. or 1.0 sq. ft. per cell active area with up to 40 individual cells connected to make up a modular cell stack. This size of hardware allows rather accurate projections to be made of the shunt power/pump power tradeoffs. The modeling studies that were completed on the system concept are reviewed along with the approach of mapping the performance of Redox cells over a wide range of flow rates and depths of discharge of the Redox solutions. Methods are outlined for estimating the pumping and shunt current losses for any type of cell and stack combination. These methods are applicable to a variety of pumping options that are present with Redox systems. The results show that a fully developed Redox system has acceptable parasitic losses when using a fixed flow rate adequate to meet the worst conditions of current density and depth of discharge. These losses are reduced by about 65 percent if variable flow schedules are used. The exact value of the overall parasitics will depend on the specific system requirements of current density, voltage limits, charge, discharge time, etc.
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Structure and energetics of extended defects in ice Ih
NASA Astrophysics Data System (ADS)
Silva Junior, Domingos L.; de Koning, Maurice
2012-01-01
We consider the molecular structure and energetics of extended defects in proton-disordered hexagonal ice Ih. Using plane-wave density functional theory (DFT) calculations, we compute the energetics of stacking faults and determine the structure of the 30∘ and 90∘ partial dislocations on the basal plane. Consistent with experimental data, the formation energies of all fully reconstructed stacking faults are found to be very low. This is consistent with the idea that basal-plane glide dislocations in ice Ih are dissociated into partial dislocations separated by an area of stacking fault. For both types of partial dislocation we find a strong tendency toward core reconstruction through pairwise hydrogen-bond reformation. In the case of the 30∘ dislocation, the pairwise hydrogen-bond formation leads to a period-doubling core structure equivalent to that seen in zinc-blende semiconductor crystals. For the 90∘ partial we consider two possible core reconstructions, one in which the periodicity of the structure along the core remains unaltered and another in which it is doubled. The latter is preferred, although the energy difference between both is rather small, so that a coexistence of both reconstructions appears plausible. Our results imply that a mobility theory for dislocations on the basal plane in ice Ih should be based on the idea of reconstructed partial dislocations.
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XPS-XRF hybrid metrology enabling FDSOI process
NASA Astrophysics Data System (ADS)
Hossain, Mainul; Subramanian, Ganesh; Triyoso, Dina; Wahl, Jeremy; Mcardle, Timothy; Vaid, Alok; Bello, A. F.; Lee, Wei Ti; Klare, Mark; Kwan, Michael; Pois, Heath; Wang, Ying; Larson, Tom
2016-03-01
Planar fully-depleted silicon-on-insulator (FDSOI) technology potentially offers comparable transistor performance as FinFETs. pFET FDOSI devices are based on a silicon germanium (cSiGe) layer on top of a buried oxide (BOX). Ndoped interfacial layer (IL), high-k (HfO2) layer and the metal gate stacks are then successively built on top of the SiGe layer. In-line metrology is critical in precisely monitoring the thickness and composition of the gate stack and associated underlying layers in order to achieve desired process control. However, any single in-line metrology technique is insufficient to obtain the thickness of IL, high-k, cSiGe layers in addition to Ge% and N-dose in one single measurement. A hybrid approach is therefore needed that combines the capabilities of more than one measurement technique to extract multiple parameters in a given film stack. This paper will discuss the approaches, challenges, and results associated with the first-in-industry implementation of XPS-XRF hybrid metrology for simultaneous detection of high-k thickness, IL thickness, N-dose, cSiGe thickness and %Ge, all in one signal measurement on a FDSOI substrate in a manufacturing fab. Strong correlation to electrical data for one or more of these measured parameters will also be presented, establishing the reliability of this technique.
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NASA Astrophysics Data System (ADS)
Purohit, Ghanshyam Purshottamdas
Experimental investigations of static liquid fillets formed between small gaps of a cylindrical surface and a flat surface are carried out. The minimum volume of liquid required to form a stable fillet and the maximum liquid content the fillet can hold before becoming unstable are studied. Fillet shapes are captured in photographs obtained by a high speed image system. Experiments were conducted using water, UPA and PF 5060 on two surfaces-stand-blasted titanium and polished copper for different surface inclinations. Experimental data are generalized using appropriate non-dimensional groups. Analytical model are developed to describe the fillet curvature. Fillet curvature data are compared against model predictions and are found to be in close agreement. Bubble point experiments were carried out to measure the capillary pressure difference across the liquid-gas interface in the channels of photo-chemically etched disk stacks. Experiments were conducted using titanium stacks of five different geometrical configurations. Both well wetting liquids (IPA and PF5060) and partially wetting liquid (water) were used during experiments. Test results are found to be in close agreement with analytical predictions. Experiments were carried out to measure the frictional pressure drop across the stack as a function of liquid flow rate using two different liquids (water and IPA) and five stacks of different geometrical configurations. A channel pressure drop model is developed by treating the flow within stack channels as fully developed laminar flow between parallel plates and solving the one-dimensional Navier Stokes equation. An alternate model is developed by treating the flow in channels as flow within porous media. Expressions are developed for effective porosity and permeability for the stacks and the pressure drop is related to these parameters. Pressure drop test results are found to be in close agreement with model predictions. As a specific application of this work, a surface tension propellant management device (PMD) that uses photo-chemically etched disk stacks as capillary elements is examined. These PMDs are used in gas pressurized liquid propellant tanks to supply gas-free propellant to rocket engines in near zero-gravity environment. The experimentally validated models are integrated to perform key analyses for predicting PMD performance in zero gravity.
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2007-03-01
common FOV of each system. 64 SPECT System Our current emission tomography system uses a compact 16x20cm 2 field of view Cadmium Zinc Telluride (CZT...Brzymialkiewicz, M.P. Tornai, R.L. McKinley, J.E. Bowsher. “Evaluation of Fully 3D Emission Mammotomography with a Compact Cadmium Zinc Telluride Detector...conclusions. Stacks of breast tissue equivalent plates, each 2.0cm thick (CIRS Inc., Norfolk, VA) having either 100% glandular or 100% adipose composition
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Space shuttle orbital maneuvering engine platelet injector program
NASA Technical Reports Server (NTRS)
1975-01-01
A platelet-face injector for the fully reusable orbit maneuvering system OMS on the space shuttle was evaluated as a means of obtaining additional design margin and low cost. Performance, heat transfer, and combustion stability were evaluated over the anticipated range of OMS operating conditions. The effects of acoustic cavity configuration on combustion stability, including cavity depth, open area, inlet contour, and other parameters, were investigated using sea level bomb tests. Prototype injector and chamber behavior was evaluated for a variety of conditions; these tests examined the effects of film cooling, helium saturated propellants, chamber length, inlet conditions, and operating point, on performance, heat transfer and engine transient behavior. Helium bubble ingestion into both propellant circuits was investigated, as was chugging at low pressure operation, and hot and cold engine restart with and without a purge.
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Space shuttle electromagnetic environment experiment. Phase A: Definition study
NASA Technical Reports Server (NTRS)
Haber, F.; Showers, R. M.; Taheri, S. H.; Forrest, L. A., Jr.; Kocher, C.
1974-01-01
A program is discussed which develops a concept for measuring the electromagnetic environment on earth with equipment on board an orbiting space shuttle. Earlier work on spaceborne measuring experiments is reviewed, and emissions to be expected are estimated using, in part, previously gathered data. General relations among system parameters are presented, followed by a proposal on spatial and frequency scanning concepts. The methods proposed include a nadir looking measurement with small lateral scan and a circularly scanned measurement looking tangent to the earth's surface at the horizon. Antenna requirements are given, assuming frequency coverage from 400 MHz to 40 GHz. For the low frequency range, 400-1000 MHz, a processed, thinned array is proposed which will be more fully analyzed in the next phase of the program. Preliminary hardware and data processing requirements are presented.
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Experiment definition phase shuttle laboratory LDRL-10.6 experiment
NASA Technical Reports Server (NTRS)
1975-01-01
This report for the Experiment Definition Phase of the Shuttle Laboratory LDRL 10.6 Micrometer Experiment covers period 27 June through 26 September 1975. Activities during the fifth quarter included: (1) reevaluation of system obscuration ratio with a subsequent reduction of this ratio from 0.417 to 0.362, (2) completion of detail drawings for the 6X pre-expander, (3) completion of detail drawings for the nine mirrors that comprise pointing and tracking optomechanical subsystem, (4) continuation of detailing of mechanical portions of CMSS and modifications to accommodate new obscuration ratio, (5) qualitative operation of the optomechanical subsystem of the 10.6 um receiver achieved under experiment measurement task; receiver fully integrated and operation demonstrated over a 10 km experimental link, and (6) data collection task initiated to begin preparation of link analysis volumes.
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2009-06-14
CAPE CANAVERAL, Fla. – Seen in the photo is the 7-inch quick disconnect that will be repaired on the hydrogen vent line to the Ground Umbilical Carrier Plate on space shuttle Endeavour's external fuel tank on Launch Pad 39A at NASA's Kennedy Space Center in Florida. Teams are removing the hardware to change out seals in the internal connection points. A leak of hydrogen at the location during tanking June 12 for the STS-127 mission caused the mission to be scrubbed at 12:26 a.m. June 13. The GUCP is the overboard vent to the pad and the flare stack where the vented hydrogen is burned off. Endeavour is scheduled to launch on its STS-127 mission on June 17 at 5:40 a.m. EDT. Photo credit: NASA/Tim Jacobs
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2007-10-11
KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the frustum is ready to be lifted from a transporter to move onto a stand. The solid rocket booster segment will be added to the stack for space shuttle Atlantis, launch vehicle for mission STS-122 targeted for a December launch. Atlantis will be carrying the Columbus Laboratory, Europe’s largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Columbus, a program of ESA, is a multifunctional, pressurized laboratory that will be permanently attached to Node 2 of the space station to carry out experiments in materials science, fluid physics and biosciences, as well as to perform a number of technological applications. Photo credit: NASA/Jack Pfaller
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NASA Technical Reports Server (NTRS)
Braun, M. J.; Wheeler, R. L., III; Hendricks, R. C.
1986-01-01
The goal set forth here is to continue the work started by Braun et al. (1984-1985) and present an integrated analysis of the behavior of the two row, 20 staggered pockets, hydrostatic cryogenic bearing used by the turbopumps of the Space Shuttle main engine. The variable properties Reynolds equation is fully coupled with the two-dimensional fluid film energy equation. The three-dimensional equations of the shaft and bushing model the boundary conditions of the fluid film energy equation. The effects of shaft eccentricity, angular velocity, and inertia pressure drops at pocket edge are incorporated in the model. Their effects on the bearing fluid properties, load carrying capacity, mass flow, pressure, velocity, and temperature form the ultimate object of this paper.
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NASA Technical Reports Server (NTRS)
1987-01-01
This report describes the preliminary design specifications for an Advanced Space Transportation System consisting of a fully reusable flyback booster, an intermediate-orbit cargo vehicle, and a shuttle-type orbiter with an enlarged cargo bay. It provides a comprehensive overview of mission profile, aerodynamics, structural design, and cost analyses. These areas are related to the overall feasibility and usefullness of the proposed system.
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Requirements of IR space astronomy
NASA Technical Reports Server (NTRS)
Low, Frank J.
1989-01-01
An introduction to a series of infrared detector technology workshops is given. The establishment of goals and new requirements is addressed in a general way. The Shuttle Infrared telescope Facility (SIRIF) goals are listed. Given that the wavelength coverage is established at 2 to 750 microns and the unvignetted field of view is 7 arcmin, the field should be fully utilized at each wavelength, diffraction should be critically sampled, and each detector should be background limited.
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1, on top of the crawler-transporter, reaches the top of Launch Pad 39B at NASA's Kennedy Space Center in Florida. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1, on top of the crawler-transporter, nears the flame trench (lower left) on the top of Launch Pad 39B at NASA's Kennedy Space Center in Florida. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1 is moving to Launch Pad 39B at NASA's Kennedy Space Center in Florida via the crawler-transporter underneath. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1 nears the top of Launch Pad 39B at NASA's Kennedy Space Center in Florida via the crawler-transporter underneath. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1 is moving to Launch Pad 39B at NASA's Kennedy Space Center in Florida via the crawler-transporter underneath. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1, on top of the crawler-transporter, reaches the top of Launch Pad 39B at NASA's Kennedy Space Center in Florida. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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Design, fabrication and delivery of a miniature Cassegrainian concentrator solar array system
NASA Technical Reports Server (NTRS)
Kruer, Mark A.
1987-01-01
The optical design of the miniature Cassegrainian concentrator (MCC) element was improved for both offpoint and onpoint power capability. The cell stack design has shown no losses under the high short term thermal stresses imposed by component level test and is projected to be capable of greater than five years thermal cycle life in low Earth orbit. The structural design met all requirements for stiffness and flatness and requires adjustable inserts for fine tuning of the GFRP structure to meet flatness goals. The completed, fully populated small and large MCC panels deliverable under this contract perform electrically as expected. A solid acceptance inspection program to guarantee quality of all purchased parts, and continued manufacturing process improvements will make the MCC design a viable low cost alternative to standard flat panel technology. Minor improvements to the cell stack design of the MCC element can make significant improvements in both the performance and manufacturability of the MCC system.
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Finite Element Simulation of Solid Rocket Booster Separation Motors During Motor Firing
NASA Technical Reports Server (NTRS)
Yu. Weiping; Crane, Debora J.
2007-01-01
One of the toughest challenges facing Solid Rocket Booster (SRB) engineers is to ensure that any design changes made to the Shuttle-Derived Booster Separation Motors (BSM) for future space exploration vehicles is able to withstand the increasingly hostile motor firing environment without cracking its critical component - the graphite throat. This paper presents a critical analysis methodology and techniques for assessing effects of BSM design changes with great accuracy and precision. For current Space Shuttle operation, the motor firing occurs at SRB separation - approximately 125 seconds after Shuttle launch at an altitude of about 28 miles. The motor operation event lasts about two seconds, however, the surface temperature of the graphite throat increases approximately 3400 F in less than one second with a corresponding increase in surface pressure of approximately 2200 pounds per square inch (psi) in less than one-tenth of a second. To capture this process fully and accurately, a two-phase sequentially coupled thermal-mechanical finite element approach was developed. This method allows the time- and location-dependent pressure fields to interact with the spatial-temporal thermal fields throughout the operation. The material properties of graphite throat are orthotropic and temperature-dependent. The analysis involves preload and multiple body contacts.
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Nowicka, Urszula; Zhang, Daoning; Walker, Olivier; Krutauz, Daria; Castañeda, Carlos A.; Chaturvedi, Apurva; Chen, Tony Y.; Reis, Noa; Glickman, Michael H.; Fushman, David
2015-01-01
SUMMARY Ddi1 belongs to a family of shuttle proteins targeting polyubiquitinated substrates for proteasomal degradation. Unlike the other proteasomal shuttles, Rad23 and Dsk2, Ddi1 remains an enigma: its function is not fully understood and structural properties are poorly characterized. We determined the structure and binding properties of the ubiquitin-like (UBL) and ubiquitin-associated (UBA) domains of Ddi1 from Saccharomyces cerevisiae. We found that, while Ddi1UBA forms a characteristic UBA:ubiquitin complex, Ddi1UBL has entirely uncharacteristic binding preferences. Despite having a ubiquitin-like fold, Ddi1UBL does not interact with typical UBL-receptors but, unexpectedly, binds ubiquitin, forming a unique interface mediated by hydrophobic contacts and by salt-bridges between oppositely-charged residues of Ddi1UBL and ubiquitin. In stark contrast with ubiquitin and other UBLs, the β-sheet surface of Ddi1UBL is negatively charged and, therefore, is recognized in a completely different way. The dual functionality of Ddi1UBL, capable of binding both ubiquitin and proteasome, suggests a novel mechanism for Ddi1 as a proteasomal shuttle. PMID:25703377
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Dienel, Gerald A
2017-11-01
Glutamate-stimulated aerobic glycolysis in astrocytes coupled with lactate shuttling to neurons where it can be oxidized was proposed as a mechanism to couple excitatory neuronal activity with glucose utilization (CMR glc ) during brain activation. From the outset, this model was not viable because it did not fulfill critical stoichiometric requirements: (i) Calculated glycolytic rates and measured lactate release rates were discordant in cultured astrocytes. (ii) Lactate oxidation requires oxygen consumption, but the oxygen-glucose index (OGI, calculated as CMR O2 /CMR glc ) fell during activation in human brain, and the small rise in CMR O2 could not fully support oxidation of lactate produced by disproportionate increases in CMR glc . (iii) Labeled products of glucose metabolism are not retained in activated rat brain, indicating rapid release of a highly labeled, diffusible metabolite identified as lactate, thereby explaining the CMR glc -CMR O2 mismatch. Additional independent lines of evidence against lactate shuttling include the following: astrocytic oxidation of glutamate after its uptake can help "pay" for its uptake without stimulating glycolysis; blockade of glutamate receptors during activation in vivo prevents upregulation of metabolism and lactate release without impairing glutamate uptake; blockade of β-adrenergic receptors prevents the fall in OGI in activated human and rat brain while allowing glutamate uptake; and neurons upregulate glucose utilization in vivo and in vitro under many stimulatory conditions. Studies in immature cultured cells are not appropriate models for lactate shuttling in adult brain because of their incomplete development of metabolic capability and astrocyte-neuron interactions. Astrocyte-neuron lactate shuttling does not make large, metabolically significant contributions to energetics of brain activation. © 2017 Wiley Periodicals, Inc. © 2017 Wiley Periodicals, Inc.
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Aerospace Safety Advisory Panel
NASA Technical Reports Server (NTRS)
2002-01-01
This report presents the results of the Aerospace Safety Advisory Panel (ASAP) activities during 2002. The format of the report has been modified to capture a long-term perspective. Section II is new and highlights the Panel's view of NASA's safety progress during the year. Section III contains the pivotal safety issues facing NASA in the coming year. Section IV includes the program area findings and recommendations. The Panel has been asked by the Administrator to perform several special studies this year, and the resulting white papers appear in Appendix C. The year has been filled with significant achievements for NASA in both successful Space Shuttle operations and International Space Station (ISS) construction. Throughout the year, safety has been first and foremost in spite of many changes throughout the Agency. The relocation of the Orbiter Major Modifications (OMMs) from California to Kennedy Space Center (KSC) appears very successful. The transition of responsibilities for program management of the Space Shuttle and ISS programs from Johnson Space Center (JSC) to NASA Headquarters went smoothly. The decision to extend the life of the Space Shuttle as the primary NASA vehicle for access to space is viewed by the Panel as a prudent one. With the appropriate investments in safety improvements, in maintenance, in preserving appropriate inventories of spare parts, and in infrastructure, the Space Shuttle can provide safe and reliable support for the ISS for the foreseeable future. Indications of an aging Space Shuttle fleet occurred on more than one occasion this year. Several flaws went undetected in the early prelaunch tests and inspections. In all but one case, the problems were found prior to launch. These incidents were all handled properly and with safety as the guiding principle. Indeed, launches were postponed until the problems were fully understood and mitigating action could be taken. These incidents do, however, indicate the need to analyze the Space Shuttle certification criteria closely. Based on this analysis, NASA can determine the need to receritfy the vehicles and to incorporate more stringent inspections throughout the process to minimize launch schedule impact. A highly skilled and experience workforce will be increasingly important for safe and reliable operations as the Space Shuttle vehicles and infrastructure continue to age.
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Hollow Fiber Flight Prototype Spacesuit Water Membrane Evaporator Design and Testing
NASA Technical Reports Server (NTRS)
Bue, Grant; Vogel, Matt; Makinen, Janice; Tsioulos, Gus
2010-01-01
The spacesuit water membrane evaporator (SWME) is being developed to perform thermal control for advanced spacesuits and to take advantage of recent advances in micropore membrane technology. This results in a robust heat-rejection device that is potentially less sensitive to contamination than is the sublimator. The Membrana Celgard X50-215 microporous hollow-fiber (HoFi) membrane was selected after recent extensive testing as the most suitable candidate among commercial alternatives for continued SWME prototype development. The current design was based on a previous design that grouped the fiber layers into stacks, which were separated by small spaces and packaged into a cylindrical shape. This was developed into a full-scale prototype consisting of 14,300 tube bundled into 30 stacks, each of which is formed into a chevron shape and separated by spacers and organized into three sectors of 10 nested stacks. The new design replaced metal components with plastic ones, and has a custom built flight like backpressure valve mounted on the side of the SWME housing to reduce backpressure when fully open. The spacers that provided separation of the chevron fiber stacks were eliminated. Vacuum chamber testing showed improved heat rejection as a function of inlet water temperature and water vapor backpressure compared with the previous design. Other tests pushed the limits of tolerance to freezing and showed suitability to reject heat in a Mars pressure environment with and without a sweep gas. Tolerance to contamination by constituents expected to be found in potable water produced by distillation processes was tested in a conventional way by allowing constituents to accumulate in the coolant as evaporation occurs. For this purpose, the SWME cartridge has endured an equivalent of 30 EVAs exposure and demonstrated minimal performance decline.
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Investigation of structural factors of safety for the space shuttle
NASA Technical Reports Server (NTRS)
1972-01-01
A study was made of the factors governing the structural design of the fully reusable space shuttle booster to establish a rational approach to select optimum structural factors of safety. The study included trade studies of structural factors of safety versus booster service life, weight, cost, and reliability. Similar trade studies can be made on other vehicles using the procedures developed. The major structural components of a selected baseline booster were studied in depth, each being examined to determine the fatigue life, safe-life, and fail-safe capabilities of the baseline design. Each component was further examined to determine its reliability and safety requirements, and the change of structural weight with factors of safety. The apparent factors of safety resulting from fatigue, safe-life, proof test, and fail-safe requirements were identified. The feasibility of reduced factors of safety for design loads such as engine thrust, which are well defined, was examined.
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NASA Technical Reports Server (NTRS)
Orton, G. F.
1984-01-01
An experiment to investigate more versatile, lower cost surface tension propellant acquisition approaches for future satellite and spacecraft propellant tanks is designed to demonstrate a propellant off-load capability for a full-tank gallery surface tension device, such as that employed in the shuttle reaction control subsystem, and demonstrate a low-cost refillable trap concept that could be used in future orbit maneuver propulsion systems for multiple engine restarts. A Plexiglas test tank, movie camera and lights, auxiliary liquid accumulator, control electronics, battery pack, and associated valving and plumbing are used. The test liquid is Freon 113, dyed blue for color movie coverage. The fully loaded experiments weighs 106 pounds and is to be installed in a NASA five-cubic-foot flight canister. Vibration tests, acoustic tests, and high and low temperature tests were performed to quality the experiment for flight.
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Three-Dimensional Simulations of Electron Beams Focused by Periodic Permanent Magnets
NASA Technical Reports Server (NTRS)
Kory, Carol L.
1999-01-01
A fully three-dimensional (3D) model of an electron beam focused by a periodic permanent magnet (PPM) stack has been developed. First, the simulation code MAFIA was used to model a PPM stack using the magnetostatic solver. The exact geometry of the magnetic focusing structure was modeled; thus, no approximations were made regarding the off-axis fields. The fields from the static solver were loaded into the 3D particle-in-cell (PIC) solver of MAFIA where fully 3D behavior of the beam was simulated in the magnetic focusing field. The PIC solver computes the time-integration of electromagnetic fields simultaneously with the time integration of the equations of motion of charged particles that move under the influence of those fields. Fields caused by those moving charges are also taken into account; thus, effects like space charge and magnetic forces between particles are fully simulated. The electron beam is simulated by a number of macro-particles. These macro-particles represent a given charge Q amounting to that of several million electrons in order to conserve computational time and memory. Particle motion is unrestricted, so particle trajectories can cross paths and move in three dimensions under the influence of 3D electric and magnetic fields. Correspondingly, there is no limit on the initial current density distribution of the electron beam, nor its density distribution at any time during the simulation. Simulation results including beam current density, percent ripple and percent transmission will be presented, and the effects current, magnetic focusing strength and thermal velocities have on beam behavior will be demonstrated using 3D movies showing the evolution of beam characteristics in time and space. Unlike typical beam optics models, this 3D model allows simulation of asymmetric designs such as non- circularly symmetric electrostatic or magnetic focusing as well as the inclusion of input/output couplers.
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Inflatable Emergency Atmospheric-Entry Vehicles
NASA Technical Reports Server (NTRS)
Jones, Jack; Hall, Jeffrey; Wu, Jiunn Jeng
2004-01-01
In response to the loss of seven astronauts in the Space Shuttle Columbia disaster, large, lightweight, inflatable atmospheric- entry vehicles have been proposed as means of emergency descent and landing for persons who must abandon a spacecraft that is about to reenter the atmosphere and has been determined to be unable to land safely. Such a vehicle would act as an atmospheric decelerator at supersonic speed in the upper atmosphere, and a smaller, central astronaut pod could then separate at lower altitudes and parachute separately to Earth. Astronaut-rescue systems that have been considered previously have been massive, and the cost of designing them has exceeded the cost of fabrication of a space shuttle. In contrast, an inflatable emergency-landing vehicle according to the proposal would have a mass between 100 and 200 kg, could be stored in a volume of approximately 0.2 to 0.4 cu m, and could likely be designed and built much less expensively. When fully inflated, the escape vehicle behaves as a large balloon parachute, or ballute. Due to very low mass-per-surface area, a large radius, and a large coefficient of drag, ballutes decelerate at much higher altitudes and with much lower heating rates than the space shuttle. Although the space shuttle atmospheric reentry results in surface temperatures of about 1,600 C, ballutes can be designed for maximum temperatures below 600 C. This allows ballutes to be fabricated with lightweight ZYLON(Registered TradeMark) or polybenzoxazole (PBO), or equivalent.
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Image-Based Single Cell Profiling: High-Throughput Processing of Mother Machine Experiments
Sachs, Christian Carsten; Grünberger, Alexander; Helfrich, Stefan; Probst, Christopher; Wiechert, Wolfgang; Kohlheyer, Dietrich; Nöh, Katharina
2016-01-01
Background Microfluidic lab-on-chip technology combined with live-cell imaging has enabled the observation of single cells in their spatio-temporal context. The mother machine (MM) cultivation system is particularly attractive for the long-term investigation of rod-shaped bacteria since it facilitates continuous cultivation and observation of individual cells over many generations in a highly parallelized manner. To date, the lack of fully automated image analysis software limits the practical applicability of the MM as a phenotypic screening tool. Results We present an image analysis pipeline for the automated processing of MM time lapse image stacks. The pipeline supports all analysis steps, i.e., image registration, orientation correction, channel/cell detection, cell tracking, and result visualization. Tailored algorithms account for the specialized MM layout to enable a robust automated analysis. Image data generated in a two-day growth study (≈ 90 GB) is analyzed in ≈ 30 min with negligible differences in growth rate between automated and manual evaluation quality. The proposed methods are implemented in the software molyso (MOther machine AnaLYsis SOftware) that provides a new profiling tool to analyze unbiasedly hitherto inaccessible large-scale MM image stacks. Conclusion Presented is the software molyso, a ready-to-use open source software (BSD-licensed) for the unsupervised analysis of MM time-lapse image stacks. molyso source code and user manual are available at https://github.com/modsim/molyso. PMID:27661996
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NASA Technical Reports Server (NTRS)
Lyles, Garry; Otte, Neil E.
2008-01-01
Fielding an integrated launch vehicle system entails many challenges, not the least of which is the fact that it has been over 30 years since the United States has developed a human-rated vehicle - the venerable Space Shuttle. Over time, whole generations of rocket scientists have passed through the aerospace community without the opportunity to perform such exacting, demanding, and rewarding work. However, with almost 50 years of experience leading the design, development, and end-to-end systems engineering and integration of complex launch vehicles, NASA's Marshall Space Flight Center offers the in-house talent - both junior- and senior-level personnel - to shape a new national asset to meet the requirements for safe, reliable, and affordable space exploration solutions.' These personnel are housed primarily in Marshall's Engineering Directorate and are matrixed into the programs and projects that reside at the rocket center. Fortunately, many Apollo era and Shuttle engineers, as well as those who gained valuable hands-on experience in the 1990s by conducting technology demonstrator projects such as the Delta-Clipper Experimental Advanced, X-33, X-34, and X-37, as well as the short-lived Orbital Space Plane, work closely with industry partners to advance the nation's strategic capability for human access to space. Currently, only three spacefaring nations have this distinction, including the United States, Russia, and, more recently, China. The U.S. National Space Policy of2006 directs that NASA provide the means to travel to space, and the NASA Appropriations Act of2005 provided the initial funding to begin in earnest to replace the Shuttle after the International Space Station construction is complete in 20 IO? These and other strategic goals and objectives are documented in NASA's 2006 Strategic Plan.3 In 2005, a team of NASA aerospace experts conducted the Exploration Systems Architecture Study, which recommended a two-vehicle approach to America's next space transportation system for missions to the International Space Station in the next decade and to explore the Moon and establish an outpost around the 2020 timeframe.4 Based on this extensive study, NASA selected the Ares I crew launch vehicle configuration and the heavy-lift Ares V cargo launch vehicle (fig 1). This paper will give an overview of NASA's approach to integrating the Ares I vehicle stack using capabilities and assets that are resident in Marshall's Engineering Directorate, working in partnership with other NASA Centers and the U.S. aerospace industry. It also will provide top-level details on the progress of the in-house design of the Ares I vehicle's upper stage element.
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The Effect of Predicted Vehicle Displacement on Ground Crew Task Performance and Hardware Design
NASA Technical Reports Server (NTRS)
Atencio, Laura Ashley; Reynolds, David W.
2011-01-01
NASA continues to explore new launch vehicle concepts that will carry astronauts to low- Earth orbit to replace the soon-to-be retired Space Transportation System (STS) shuttle. A tall vertically stacked launch vehicle (> or =300 ft) is exposed to the natural environment while positioned on the launch pad. Varying directional winds and vortex shedding cause the vehicle to sway in an oscillating motion. Ground crews working high on the tower and inside the vehicle during launch preparations will be subjected to this motion while conducting critical closeout tasks such as mating fluid and electrical connectors and carrying heavy objects. NASA has not experienced performing these tasks in such environments since the Saturn V, which was serviced from a movable (but rigid) service structure; commercial launchers are likewise attended by a service structure that moves away from the vehicle for launch. There is concern that vehicle displacement may hinder ground crew operations, impact the ground system designs, and ultimately affect launch availability. The vehicle sway assessment objective is to replicate predicted frequencies and displacements of these tall vehicles, examine typical ground crew tasks, and provide insight into potential vehicle design considerations and ground crew performance guidelines. This paper outlines the methodology, configurations, and motion testing performed while conducting the vehicle displacement assessment that will be used as a Technical Memorandum for future vertically stacked vehicle designs.
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A Fully Integrated Humidity Sensor System-on-Chip Fabricated by Micro-Stamping Technology
Huang, Che-Wei; Huang, Yu-Jie; Lu, Shey-Shi; Lin, Chih-Ting
2012-01-01
A fully integrated humidity sensor chip was designed, implemented, and tested. Utilizing the micro-stamping technology, the pseudo-3D sensor system-on-chip (SSoC) architecture can be implemented by stacking sensing materials directly on the top of a CMOS-fabricated chip. The fabricated sensor system-on-chip (2.28 mm × 2.48 mm) integrated a humidity sensor, an interface circuit, a digital controller, and an On-Off Keying (OOK) wireless transceiver. With low power consumption, i.e., 750 μW without RF operation, the sensitivity of developed sensor chip was experimentally verified in the relative humidity (RH) range from 32% to 60%. The response time of the chip was also experimentally verified to be within 5 seconds from RH 36% to RH 64%. As a consequence, the implemented humidity SSoC paves the way toward the an ultra-small sensor system for various applications.
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Artist's Concept of the Atlas V-401 Rocket
2018-01-25
Interior Exploration using Seismic Investigations, Geodesy and Heat Transport, or InSight, is scheduled to launch from Vandenberg Air Force Base on California's Pacific coast between May 5 and June 8, 2018. The lander will launch to Mars aboard an Atlas V-401 launch vehicle, one of the biggest rockets available for interplanetary flight. It stands 188 feet (57.3 meters) tall, or about as tall as a 19-story building. Fully stacked, with the spacecraft, the Atlas V-401 weighs about 730,000 pounds (333,000 kilograms). That's about 14 big rigs, fully loaded with cargo! The three numbers in the 401 designation signify: 4: a payload fairing -- or nose cone -- that is about 13 feet (4 meters) in diameter 0: solid-rocket boosters supplementing the main booster 1: the upper stage, which has one engine https://photojournal.jpl.nasa.gov/catalog/PIA22231
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Development of a new generation solid rocket motor ignition computer code
NASA Technical Reports Server (NTRS)
Foster, Winfred A., Jr.; Jenkins, Rhonald M.; Ciucci, Alessandro; Johnson, Shelby D.
1994-01-01
This report presents the results of experimental and numerical investigations of the flow field in the head-end star grain slots of the Space Shuttle Solid Rocket Motor. This work provided the basis for the development of an improved solid rocket motor ignition transient code which is also described in this report. The correlation between the experimental and numerical results is excellent and provides a firm basis for the development of a fully three-dimensional solid rocket motor ignition transient computer code.
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STS-65 Earth observation of Hurricane Emilia in Eastern Pacific Ocean
1994-07-18
STS-65 Earth observation taken aboard Columbia, Orbiter Vehicle (OV) 102, shows Hurricane Emilia in the Eastern Pacific Ocean. Hurricane Emilia's wind speeds exceeded 150 knots. This high oblique view of the storm shows numerous spiral bands of thunderstorms, overshooting thunderstorm tops at the tropopause, and a well developed eye at the center of the picture. Shuttle photography provides high resolution details of these powerful and destructive systems that are not fully possible from lower-resolution, unmanned satellites.
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STS-30 Atlantis, OV-104, landing approach to runway 22 at EAFB, California
1989-05-08
STS030-S-124 (8 May 1989) --- Its landing gear fully deployed, Space Shuttle Atlantis is lined up for its approach to Runway 22 at Edwards Air Force Base in southern California. Minutes later, at 12:44:33 (PDT), the spacecraft's wheels had come to a complete stop, marking the successful conclusion for the four-day STS-30 mission. Onboard were astronauts David M. Walker, Ronald J. Grabe, Norman E. Thagard, Mary L. Cleave and Mark C. Lee.
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The Art and Science of Systems Engineering
NASA Technical Reports Server (NTRS)
Singer, Christopher E.
2009-01-01
The National Aeronautics and Space Administration (NASA) was established in 1958, and its Marshall Space Flight Center was founded in 1960, as space-related work was transferred from the Army Ballistic Missile Agency at Redstone Arsenal, where Marshall is located. With this heritage, Marshall contributes almost 50 years of systems engineering experience with human-rated launch vehicles and scientific spacecraft to fulfill NASA's mission exploration and discovery. These complex, highly specialized systems have provided vital platforms for expanding the knowledge base about Earth, the solar system, and cosmos; developing new technologies that also benefit life on Earth; and opening new frontiers for America's strategic space goals. From Mercury and Gemini, to Apollo and the Space Shuttle, Marshall's systems engineering expertise is an unsurpassed foundational competency for NASA and the nation. Current assignments comprise managing Space Shuttle Propulsion systems; developing environmental control and life support systems and coordinating science operations on the International Space Station; and a number of exploration-related responsibilities. These include managing and performing science missions, such as the Lunar Crater Observation and Sensing Satellite and the Lunar Reconnaissance Orbiter slated to launch for the Moon in April 2009, to developing the Ares I crew launch vehicle upper stage and integrating the vehicle stack in house, as well as designing the Ares V cargo launch vehicle and contributing to the development of the Altair Lunar Lander and an International Lunar Network with communications nodes and other infrastructure.
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GRAPHIC REANALYSIS OF THE TWO NINDS-TPA TRIALS CONFIRMS SUBSTANTIAL TREATMENT BENEFIT
Saver, Jeffrey L.; Gornbein, Jeffrey; Starkman, Sidney
2010-01-01
Background of Comment/Review Multiple statistical analyses of the two NINDS-TPA Trials have confirmed study findings of benefit of fibrinolytic therapy. A recent graphic analysis departed from best practices in the visual display of quantitative information by failing to take into account the skewed functional importance NIH Stroke Scale raw scores and by scaling change axes at up to twenty times the range achievable by individual patients. Methods Using the publicly available datasets of the 2 NINDS-TPA Trials, we generated a variety of figures appropriate to the characteristics of acute stroke trial data. Results A diverse array of figures all visually delineated substantial benefits of fibrinolytic therapy, including: bar charts of normalized gain and loss; stacked bar, bar, and matrix plots of clinically relevant ordinal ranks; a time series stacked line plot of continuous scale disability weights; and line plot, bubble chart, and person icon array graphs of joint outcome table analysis. The achievable change figure showed substantially greater improvement among TPA than placebo patients, median 66.7% (IQR 0–92.0) vs 50.0% (IQR −7.1 – 80.0), p=0.003. Conclusions On average, under 3 hour patients treated with TPA recovered two-thirds while placebo patients improved only half of the way towards fully normal. Graphical analyses of the two NINDS-TPA trials, when performed according to best practices, is a useful means of conveying details about patient response to therapy not fully delineated by summary statistics, and confirms a valuable treatment benefit of under 3 hour fibrinolytic therapy in acute stroke. PMID:20829518
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Business Context of Space Tourism
NASA Astrophysics Data System (ADS)
Schmitt, Harrison H.
2003-01-01
Broadly speaking, two types of potential commercial activity in space can be defined. First, there are those activities that represent an expansion and improvement on services with broad existing commercial foundations such as telecommunications. The second type of potential commercial activity in space is one that may offer a type of service with few or any existing commercial foundations such as space-based remote sensing. Space tourism clearly belongs in the first category of potential commercial activity in space. Roles in cooperation with the private sector that might be considered for NASA include 1) acceleration of the ``Professional-in Space'' initiative, 2) research and technology developments related to a) a ``Tourist Destination Module'' for the Space Station, b) an ``Extra Passengers Module'' for the payload bay of the Space Shuttle, and c) a ``Passenger-rated Expendable Launch Vehicle,'' 3) definition of criteria for qualifying candidate space tourists, and 4) initiatives to protect space tourism from unreasonable tort litigation. As baseline information for establishing fees, the cost of a possible tourist flight should be fully and objectively delineated. If it is correct that the marginal cost of each Space Shuttle flight to Earth-orbit is about $100 million and the effective Shuttle payload is about 50,000 pounds, then the marginal cost would be roughly $2,000 per pound.
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Three-Dimensional Electron Optics Model Developed for Traveling-Wave Tubes
NASA Technical Reports Server (NTRS)
Kory, Carol L.
2000-01-01
A three-dimensional traveling-wave tube (TWT) electron beam optics model including periodic permanent magnet (PPM) focusing has been developed at the NASA Glenn Research Center at Lewis Field. This accurate model allows a TWT designer to develop a focusing structure while reducing the expensive and time-consuming task of building the TWT and hot-testing it (with the electron beam). In addition, the model allows, for the first time, an investigation of the effect on TWT operation of the important azimuthally asymmetric features of the focusing stack. The TWT is a vacuum device that amplifies signals by transferring energy from an electron beam to a radiofrequency (RF) signal. A critically important component is the focusing structure, which keeps the electron beam from diverging and intercepting the RF slow wave circuit. Such an interception can result in excessive circuit heating and decreased efficiency, whereas excessive growth in the beam diameter can lead to backward wave oscillations and premature saturation, indicating a serious reduction in tube performance. The most commonly used focusing structure is the PPM stack, which consists of a sequence of cylindrical iron pole pieces and opposite-polarity magnets. Typically, two-dimensional electron optics codes are used in the design of magnetic focusing devices. In general, these codes track the beam from the gun downstream by solving equations of motion for the electron beam in static-electric and magnetic fields in an azimuthally symmetric structure. Because these two-dimensional codes cannot adequately simulate a number of important effects, the simulation code MAFIA (solution of Maxwell's equations by the Finite-Integration-Algorithm) was used at Glenn to develop a three-dimensional electron optics model. First, a PPM stack was modeled in three dimensions. Then, the fields obtained using the magnetostatic solver were loaded into a particle-in-cell solver where the fully three-dimensional behavior of the beam was simulated in the magnetic focusing field. For the first time, the effects of azimuthally asymmetric designs and critical azimuthally asymmetric characteristics of the focusing stack (such as shunts, C-magnets, or magnet misalignment) on electron beam behavior have been investigated. A cutaway portion of a simulated electron beam focused by a PPM stack is illustrated.
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Kirchhoff, H; Horstmann, S; Weis, E
2000-07-20
We investigate the role of plastoquinone (PQ) diffusion in the control of the photosynthetic electron transport. A control analysis reveals an unexpected flux control of the whole chain electron transport by photosystem (PS) II. The contribution of PSII to the flux control of whole chain electron transport was high in stacked thylakoids (control coefficient, CJ(PSII) =0.85), but decreased after destacking (CJ(PSII)=0.25). From an 'electron storage' experiment, we conclude that in stacked thylakoids only about 50 to 60% of photoreducable PQ is involved in the light-saturated linear electron transport. No redox equilibration throughout the membrane between fixed redox groups at PSII and cytochrome (cyt) bf complexes, and the diffusable carrier PQ is achieved. The data support the PQ diffusion microdomain concept by Lavergne et al. [J. Lavergne, J.-P. Bouchaud, P. Joliot, Biochim. Biophys. Acta 1101 (1992) 13-22], but we come to different conclusions about size, structure and size distribution of domains. From an analysis of cyt b6 reduction, as a function of PSII inhibition, we conclude that in stacked thylakoids about 70% of PSII is located in small domains, where only 1 to 2 PSII share a local pool of a few PQ molecules. Thirty percent of PSII is located in larger domains. No small domains were found in destacked thylakoids. We present a structural model assuming a hierarchy of specific, strong and weak interactions between PSII core, light harvesting complexes (LHC) II and cyt bf. Peripheral LHCII's may serve to connect PSII-LHCII supercomplexes to a flexible protein network, by which small closed lipid diffusion compartments are formed. Within each domain, PQ moves rapidly and shuttles electrons between PSII and cyt bf complexes in the close vicinity. At the same time, long range diffusion is slow. We conclude, that in high light, cyt bfcomplexes located in distant stromal lamellae (20 to 30%) are not involved in the linear electron transport.
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Hydrated Excess Protons Can Create Their Own Water Wires.
Peng, Yuxing; Swanson, Jessica M J; Kang, Seung-gu; Zhou, Ruhong; Voth, Gregory A
2015-07-23
Grotthuss shuttling of an excess proton charge defect through hydrogen bonded water networks has long been the focus of theoretical and experimental studies. In this work we show that there is a related process in which water molecules move ("shuttle") through a hydrated excess proton charge defect in order to wet the path ahead for subsequent proton charge migration. This process is illustrated through reactive molecular dynamics simulations of proton transport through a hydrophobic nanotube, which penetrates through a hydrophobic region. Surprisingly, before the proton enters the nanotube, it starts "shooting" water molecules into the otherwise dry space via Grotthuss shuttling, effectively creating its own water wire where none existed before. As the proton enters the nanotube (by 2-3 Å), it completes the solvation process, transitioning the nanotube to the fully wet state. By contrast, other monatomic cations (e.g., K(+)) have just the opposite effect, by blocking the wetting process and making the nanotube even drier. As the dry nanotube gradually becomes wet when the proton charge defect enters it, the free energy barrier of proton permeation through the tube via Grotthuss shuttling drops significantly. This finding suggests that an important wetting mechanism may influence proton translocation in biological systems, i.e., one in which protons "create" their own water structures (water "wires") in hydrophobic spaces (e.g., protein pores) before migrating through them. An existing water wire, e.g., one seen in an X-ray crystal structure or MD simulations without an explicit excess proton, is therefore not a requirement for protons to transport through hydrophobic spaces.
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Parametric trade studies on a Shuttle 2 launch system architecture
NASA Technical Reports Server (NTRS)
Stanley, Douglas O.; Talay, Theodore A.; Lepsch, Roger A.; Morris, W. Douglas; Naftel, J. Christopher; Cruz, Christopher I.
1991-01-01
A series of trade studies are presented on a complementary architecture of launch vehicles as a part of a study often referred to as Shuttle-2. The results of the trade studies performed on the vehicles of a reference Shuttle-2 mixed fleet architecture have provided an increased understanding of the relative importance of each of the major vehicle parameters. As a result of trades on the reference booster-orbiter configuration with a methane booster, the study showed that 60 percent of the total liftoff thrust should be on the booster and 40 percent on the orbiter. It was also found that the liftoff thrust to weight ratio (T/W) on the booster-orbiter should be 1.3. This leads to a low dry weight and still provides enough thrust to allow the design of a heavy lift architecture. As a result of another trade study, the dry weight of the reference booster-orbiter was chosen for a variety of operational considerations. Other trade studies on the booster-orbiter demonstrate that the cross feeding of propellant during boost phase is desirable and that engine-out capability from launch to orbit is worth the performance penalty. Technology assumptions made during the Shuttle-2 design were shown to be approx. equivalent to a 25 percent across the board weight reduction over the Space Shuttle technology. The vehicles of the Shuttle-2 architecture were also sized for a wide variety of payloads and missions to different orbits. Many of these same parametric trades were also performed on completely liquid hydrogen fueled fully reusable concepts. If a booster-orbiter is designed using liquid hydrogen engines on both the booster and orbiter, the total vehicle dry weight is only 3.0 percent higher than the reference dual-fuel booster-orbiter, and the gross weight is 3.8 percent less. For this booster-orbiter vehicle, a liftoff T/W of 1.3, a thrust of about 60 percent on the booster, and a Mach staging number of 3 all proved to be desirable. This modest dry weight increase for a liquid hydrogen fueled Shuttle-2 system should be more than offset by the elimination of the entire hydrocarbon engine development program and the savings in operation cost realized by the elimination of an entire fuel type.
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Empirical study of parallel LRU simulation algorithms
NASA Technical Reports Server (NTRS)
Carr, Eric; Nicol, David M.
1994-01-01
This paper reports on the performance of five parallel algorithms for simulating a fully associative cache operating under the LRU (Least-Recently-Used) replacement policy. Three of the algorithms are SIMD, and are implemented on the MasPar MP-2 architecture. Two other algorithms are parallelizations of an efficient serial algorithm on the Intel Paragon. One SIMD algorithm is quite simple, but its cost is linear in the cache size. The two other SIMD algorithm are more complex, but have costs that are independent on the cache size. Both the second and third SIMD algorithms compute all stack distances; the second SIMD algorithm is completely general, whereas the third SIMD algorithm presumes and takes advantage of bounds on the range of reference tags. Both MIMD algorithm implemented on the Paragon are general and compute all stack distances; they differ in one step that may affect their respective scalability. We assess the strengths and weaknesses of these algorithms as a function of problem size and characteristics, and compare their performance on traces derived from execution of three SPEC benchmark programs.
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Janus monolayers of transition metal dichalcogenides.
Lu, Ang-Yu; Zhu, Hanyu; Xiao, Jun; Chuu, Chih-Piao; Han, Yimo; Chiu, Ming-Hui; Cheng, Chia-Chin; Yang, Chih-Wen; Wei, Kung-Hwa; Yang, Yiming; Wang, Yuan; Sokaras, Dimosthenis; Nordlund, Dennis; Yang, Peidong; Muller, David A; Chou, Mei-Yin; Zhang, Xiang; Li, Lain-Jong
2017-08-01
Structural symmetry-breaking plays a crucial role in determining the electronic band structures of two-dimensional materials. Tremendous efforts have been devoted to breaking the in-plane symmetry of graphene with electric fields on AB-stacked bilayers or stacked van der Waals heterostructures. In contrast, transition metal dichalcogenide monolayers are semiconductors with intrinsic in-plane asymmetry, leading to direct electronic bandgaps, distinctive optical properties and great potential in optoelectronics. Apart from their in-plane inversion asymmetry, an additional degree of freedom allowing spin manipulation can be induced by breaking the out-of-plane mirror symmetry with external electric fields or, as theoretically proposed, with an asymmetric out-of-plane structural configuration. Here, we report a synthetic strategy to grow Janus monolayers of transition metal dichalcogenides breaking the out-of-plane structural symmetry. In particular, based on a MoS 2 monolayer, we fully replace the top-layer S with Se atoms. We confirm the Janus structure of MoSSe directly by means of scanning transmission electron microscopy and energy-dependent X-ray photoelectron spectroscopy, and prove the existence of vertical dipoles by second harmonic generation and piezoresponse force microscopy measurements.
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Development of a repetitive compact torus injector
NASA Astrophysics Data System (ADS)
Onchi, Takumi; McColl, David; Dreval, Mykola; Rohollahi, Akbar; Xiao, Chijin; Hirose, Akira; Zushi, Hideki
2013-10-01
A system for Repetitive Compact Torus Injection (RCTI) has been developed at the University of Saskatchewan. CTI is a promising fuelling technology to directly fuel the core region of tokamak reactors. In addition to fuelling, CTI has also the potential for (a) optimization of density profile and thus bootstrap current and (b) momentum injection. For steady-state reactor operation, RCTI is necessary. The approach to RCTI is to charge a storage capacitor bank with a large capacitance and quickly charge the CT capacitor bank through a stack of integrated-gate bipolar transistors (IGBTs). When the CT bank is fully charged, the IGBT stack will be turned off to isolate banks, and CT formation/acceleration sequence will start. After formation of each CT, the fast bank will be replenished and a new CT will be formed and accelerated. Circuits for the formation and the acceleration in University of Saskatchewan CT Injector (USCTI) have been modified. Three CT shots at 10 Hz or eight shots at 1.7 Hz have been achieved. This work has been sponsored by the CRC and NSERC, Canada.
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1 nears the top of Launch Pad 39B at NASA's Kennedy Space Center in Florida via the crawler-transporter underneath. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Seen around the service structures on the pad are the new 600-foot lightning towers and masts erected for the Ares launches. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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2009-03-25
CAPE CANAVERAL, Fla. – Mobile Launcher Platform-1 is moving to Launch Pad 39B at NASA's Kennedy Space Center in Florida via the crawler-transporter underneath. The MLP has been handed over to the Constellation Program for its future use for the Ares I-X flight test in the summer of 2009. Seen around the service structures on the pad are the new 600-foot lightning towers and masts erected for the Ares launches. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ground Control System hardware was installed in MLP-1 in December 2008. The MLP is being moved to the launch pad to check out the installed hardware with the Launch Control Center Firing Room 1 equipment, using the actual circuits that will be used when the fully stacked Ares I-X vehicle is rolled out later this year for launch. Following this testing, MLP-1 will be moved to the Vehicle Assembly Building's High Bay 3 to begin stacking, or assembling, Ares I-X. Photo credit: NASA/Kim Shiflett
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Influence of Austenite Stability on Steel Low Cycle Fatigue Response
NASA Astrophysics Data System (ADS)
Lehnhoff, G. R.; Findley, K. O.
Austenitic steels were subjected to tensile and total strain controlled, fully reversed axial low cycle fatigue (LCF) testing to determine the influence of stacking fault energy on austenite stability, or resistance to strain induced martensitic transformation during tensile and fatigue deformation. Expected differences in stacking fault energy were achieved by modifying alloys with different amounts of silicon and aluminum. Al alloying was found to promote martensite formation during both tensile and LCF loading, while Si was found to stabilize austenite. Martensite formation increases tensile work hardening rates, though Si additions also increase the work hardening rate without martensite transformation. Similarly, secondary cyclic strain hardening during LCF is attributed to strain induced martensite formation, but Si alloying resulted in less secondary cyclic strain hardening. The amount of secondary cyclic hardening scales linearly with martensite fraction and depends only on the martensite fraction achieved and not on the martensite (i.e. parent austenite) chemistry. Martensite formation was detrimental to LCF lives at all strain amplitudes tested, although the total amount of martensitic transformation during LCF did not always monotonically increase with strain amplitude nor correlate to the amount of tensile transformation.
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NASA Astrophysics Data System (ADS)
Baricco, Marcello; Bang, Mads; Fichtner, Maximilian; Hauback, Bjorn; Linder, Marc; Luetto, Carlo; Moretto, Pietro; Sgroi, Mauro
2017-02-01
The main objective of the SSH2S (Fuel Cell Coupled Solid State Hydrogen Storage Tank) project was to develop a solid state hydrogen storage tank based on complex hydrides and to fully integrate it with a High Temperature Proton Exchange Membrane (HT-PEM) fuel cell stack. A mixed lithium amide/magnesium hydride system was used as the main storage material for the tank, due to its high gravimetric storage capacity and relatively low hydrogen desorption temperature. The mixed lithium amide/magnesium hydride system was coupled with a standard intermetallic compound to take advantage of its capability to release hydrogen at ambient temperature and to ensure a fast start-up of the system. The hydrogen storage tank was designed to feed a 1 kW HT-PEM stack for 2 h to be used for an Auxiliary Power Unit (APU). A full thermal integration was possible thanks to the high operation temperature of the fuel cell and to the relative low temperature (170 °C) for hydrogen release from the mixed lithium amide/magnesium hydride system.
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Room temperature 1040fps, 1 megapixel photon-counting image sensor with 1.1um pixel pitch
NASA Astrophysics Data System (ADS)
Masoodian, S.; Ma, J.; Starkey, D.; Wang, T. J.; Yamashita, Y.; Fossum, E. R.
2017-05-01
A 1Mjot single-bit quanta image sensor (QIS) implemented in a stacked backside-illuminated (BSI) process is presented. This is the first work to report a megapixel photon-counting CMOS-type image sensor to the best of our knowledge. A QIS with 1.1μm pitch tapered-pump-gate jots is implemented with cluster-parallel readout, where each cluster of jots is associated with its own dedicated readout electronics stacked under the cluster. Power dissipation is reduced with this cluster readout because of the reduced column bus parasitic capacitance, which is important for the development of 1Gjot arrays. The QIS functions at 1040fps with binary readout and dissipates only 17.6mW, including I/O pads. The readout signal chain uses a fully differential charge-transfer amplifier (CTA) gain stage before a 1b-ADC to achieve an energy/bit FOM of 16.1pJ/b and 6.9pJ/b for the whole sensor and gain stage+ADC, respectively. Analog outputs with on-chip gain are implemented for pixel characterization purposes.
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NASA Technical Reports Server (NTRS)
Melis, Matthew E.
2007-01-01
On February 1, 2003, the Space Shuttle Columbia broke apart during reentry, resulting in loss of the vehicle and its seven crewmembers. For the next several months, an extensive investigation of the accident ensued involving a nationwide team of experts from NASA, industry, and academia, spanning dozens of technical disciplines. The Columbia Accident Investigation Board (CAIB), a group of experts assembled to conduct an investigation independent of NASA, concluded in August, 2003 that the most likely cause of the loss of Columbia and its crew was a breach in the left wing leading edge Reinforced Carbon-Carbon (RCC) thermal protection system initiated by the impact of thermal insulating foam that had separated from the orbiters external fuel tank 81 seconds into the mission's launch. During reentry, this breach allowed superheated air to penetrate behind the leading edge and erode the aluminum structure of left wing, which ultimately led to the breakup of the orbiter. The findings of the CAIB were supported by ballistic impact tests, which simulated the physics of External Tank Foam impact on the RCC wing leading edge material. These tests ranged from fundamental material characterization tests to full-scale Orbiter Wing Leading Edge tests. Following the accident investigation, NASA spent the next 18 months focused on returning the shuttle safely to flight. In order to fully evaluate all potential impact threats from the many debris sources on the Space Shuttle during ascent, NASA instituted a significant impact testing program. The results from these tests led to the validation of high-fidelity computer models, capable of predicting actual or potential Shuttle impact events, were used in the certification of STS-114, NASA s Return to Flight Mission, as safe to fly. This presentation will provide a look into the inner workings of the Space Shuttle and a behind the scenes perspective on the impact analysis and testing done for the Columbia Accident Investigation and NASA's Return to Flight programs. In addition, highlights from recent Shuttle missions are presented.
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Billing, Beant Kaur; Mayank; Agnihotri, Prabhat K; Singh, Narinder
2018-06-08
Non-covalent bonding via π-π stacking is in demand these days because it does not affect the structure of the carbon nanotube (CNT). Herein, a hybrid material was fabricated via π-π stacking between the aromatic rings of carbon nanotubes and a dihydropyrimidone-based pyrene derivative. The developed CNT@pyrene hybrid material was fully characterized using SEM, EDX, TEM, XRD, and FTIR techniques. The hybrid was developed to improve the heat transport in the hybrid solution by anion addition. The emission profile of the developed hybrid was screened against TBA salts of different anions in EtOH-H2O (10-90% v/v) solvent system to identify the anion that can interact with the hybrid. The hybrid exhibited high sensitivity and selectivity towards NO3- ions with 1.5-fold enhancement in fluorescence intensity, while other anions neither showed significant responses nor interfered in the sensor's response. The limit of NO3- ions detection was found to be 8.1 nM, calculated using the 3-sigma method. It was observed that the proposed hybrid sensor showed stable response at different pH and diverse salt concentrations. The binding mechanism was elucidated by DFT-based theoretical calculations. Real sample analysis was performed for the detection of NO3- concentrations in local water bodies with accuracy as high as 95%. Viscosity and thermal conductivity experiments were performed to measure the effect of concentration, temperature, and pH on the NO3- response.
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Wan, Xiaoqing; Zhao, Chunhui
2017-06-01
As a competitive machine learning algorithm, the stacked sparse autoencoder (SSA) has achieved outstanding popularity in exploiting high-level features for classification of hyperspectral images (HSIs). In general, in the SSA architecture, the nodes between adjacent layers are fully connected and need to be iteratively fine-tuned during the pretraining stage; however, the nodes of previous layers further away may be less likely to have a dense correlation to the given node of subsequent layers. Therefore, to reduce the classification error and increase the learning rate, this paper proposes the general framework of locally connected SSA; that is, the biologically inspired local receptive field (LRF) constrained SSA architecture is employed to simultaneously characterize the local correlations of spectral features and extract high-level feature representations of hyperspectral data. In addition, the appropriate receptive field constraint is concurrently updated by measuring the spatial distances from the neighbor nodes to the corresponding node. Finally, the efficient random forest classifier is cascaded to the last hidden layer of the SSA architecture as a benchmark classifier. Experimental results on two real HSI datasets demonstrate that the proposed hierarchical LRF constrained stacked sparse autoencoder and random forest (SSARF) provides encouraging results with respect to other contrastive methods, for instance, the improvements of overall accuracy in a range of 0.72%-10.87% for the Indian Pines dataset and 0.74%-7.90% for the Kennedy Space Center dataset; moreover, it generates lower running time compared with the result provided by similar SSARF based methodology.
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1999-10-25
The Zero Emissions (ZE) transit bus tours the KSC Visitor Complex for a test ride. In the background are a mock-up orbiter named Explorer (left) and a stack of solid rocket boosters and external tank (right), typically used on Shuttle launches. Provided by dbb fuel cell engines inc. of Vancouver, Canada, the ZE bus was brought to KSC as part of the Center's Alternative Fuel Initiatives Program. The bus uses a Proton Exchange Membrane fuel cell in which hydrogen and oxygen, from atmospheric air, react to produce electricity that powers an electric motor drive system. The by-product "exhaust" from the fuel cell is water vapor, thus zero harmful emissions. A typical diesel-powered bus emits more than a ton of harmful pollutants from its exhaust every year. The ZE bus is being used on tour routes at the KSC Visitor Complex for two days to introduce the public to the concept
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Impact of lunar and planetary missions on the space station: Preliminary STS logistics report
NASA Technical Reports Server (NTRS)
1984-01-01
Space station requirements for lunar and planetary missions are discussed. Specific reference is made to projected Ceres and Kopff missions; Titan probes; Saturn and Mercury orbiters; and a Mars sample return mission. Such requirements as base design; station function; program definition; mission scenarios; uncertainties impact; launch manifest and mission schedule; and shuttle loads are considered. It is concluded that: (1) the impact of the planetary missions on the space station is not large when compared to the lunar base; (2) a quarantine module may be desirable for sample returns; (3) the Ceres and Kopff missions require the ability to stack and checkout two-stage OTVs; and (4) two to seven manweeks of on-orbit work are required of the station crew to launch a mission and, with the exception of the quarantine module, dedicated crew will not be required.
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1988-03-21
The Marshall Space Flight Center (MSFC) successfully test fired the third in a series of Transient Pressure Test Articles (TPTA) in its east test area. The test article was a short-stack solid rocket motor 52-feet long and 12-feet in diameter. The TPTA tests were designed to evaluate the effects of temperature, pressure and external loads encountered by the SRM, primarily during ignition transients. Instrumentation on the motor recorded approximately 1,000 charnels of data to verify the structural performance, thermal response, sealing capability of the redesign field, and case-to-nozzle joints. The TPTA test stand, 14-feet wide by 26-feet long by 33-feet high, was built in 1987. The TPTA series was a joint effort among Morton Thiokol, Inc., United Space Boosters, Inc., Wyle Laboratories, and MSFC. Wyle Laboratories conducted the tests for the MSFC, which manages the redesigned SRM program for NASA.
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1998-04-17
KENNEDY SPACE CENTER, FLA. -- David Dickinson, the acting director of the National Aeronautics and Space Administration (NASA) Public Affairs Office at Kennedy Space Center, accepts a copy of Bulgarian singer Dyana Dafova's latest compact disc (CD) from her on behalf of NASA. The 525-foot tall Vehicle Assembly Building, where Space Shuttle orbiters are mated to their external tank/solid rocket booster stacks, looms in the background. Dyana is touring the United States to promote her CD, entitled "Sounds of the Earth," and was an invited guest of NASA for the launch of Columbia on STS-90, the Neurolab mission, earlier in the day. Columbia lifted off from Launch Pad 39B at 2:19 p.m. EDT. Dyana characterized the music on her CD as a new sound, incorporating jazz and new age classics, sung in a newly created language comprised of Bulgarian, English, Sanskrit, Aramski and Hebrew
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Bulgarian singer Dyana presents PA Director Dickinson with her new CD on STS-90 launch day
NASA Technical Reports Server (NTRS)
1998-01-01
David Dickinson, the acting director of the National Aeronautics and Space Administration (NASA) Public Affairs Office at Kennedy Space Center, accepts a copy of Bulgarian singer Dyana Dafova's latest compact disc (CD) from her on behalf of NASA. The 525-foot tall Vehicle Assembly Building, where Space Shuttle orbiters are mated to their external tank/solid rocket booster stacks, looms in the background. Dyana is touring the United States to promote her CD, entitled 'Sounds of the Earth,' and was an invited guest of NASA for the launch of Columbia on STS-90, the Neurolab mission, earlier in the day. Columbia lifted off from Launch Pad 39B at 2:19 p.m. EDT. Dyana characterized the music on her CD as a new sound, incorporating jazz and new age classics, sung in a newly created language comprised of Bulgarian, English, Sanskrit, Aramski and Hebrew.
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Water vapor diffusion membrane development
NASA Technical Reports Server (NTRS)
Tan, M. K.
1977-01-01
An application of the water vapor diffusion technique is examined whereby the permeated water vapor is vented to space vacuum to alleviate on-board waste storage and provide supplemental cooling. The work reported herein deals primarily with the vapor diffusion-heat rejection (VD-HR) as it applies to the Space Shuttle. A stack configuration was selected, designed and fabricated. An asymmetric cellulose acetate membrane, used in reverse osmosis application was selected and a special spacer was designed to enhance mixing and promote mass transfer. A skid-mount unit was assembled from components used in the bench unit although no attempt was made to render it flight-suitable. The operating conditions of the VD-HR were examined and defined and a 60-day continuous test was carried out. The membranes performed very well throughout the test; no membrane rupture and no unusual flux decay was observed. In addition, a tentative design for a flight-suitable VD-HR unit was made.
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Hydrogen-oxygen driven Zero Emissions bus drives around KSC Visitor Complex
NASA Technical Reports Server (NTRS)
1999-01-01
The Zero Emissions (ZE) transit bus tours the KSC Visitor Complex for a test ride. In the background are a mock-up orbiter named Explorer (left) and a stack of solid rocket boosters and external tank (right), typically used on Shuttle launches. Provided by dbb fuel cell engines inc. of Vancouver, Canada, the ZE bus was brought to KSC as part of the Center's Alternative Fuel Initiatives Program. The bus uses a Proton Exchange Membrane fuel cell in which hydrogen and oxygen, from atmospheric air, react to produce electricity that powers an electric motor drive system. The by-product 'exhaust' from the fuel cell is water vapor, thus zero harmful emissions. A typical diesel-powered bus emits more than a ton of harmful pollutants from its exhaust every year. The ZE bus is being used on tour routes at the KSC Visitor Complex for two days to introduce the public to the concept.