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  • Other Sources  (453)
  • SPACECRAFT PROPULSION AND POWER  (453)
  • 2010-2014
  • 1995-1999
  • 1985-1989  (453)
  • 1987  (267)
  • 1985  (186)
  • 1
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    The 1987 advanced space design projects (1987)
    In:  CASI
    Details
    Publication Date: 2004-12-04
    Description: The topics addressed are: (1) phobos power plant; (2) fusion power/propulsion system; (3) surface power from an orbiting spacecraft; (4) RTG replacement; (5) MHD-thermoelectric burst reactor; (6) TAU Voyage power/propulsion device; (7) ESCAPE to ODYSSEY.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: USRA, Agenda of the Third Annual Summer Conference, NASA(USRA University Advanced Design Program; p 33
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  • 2
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    Particle size, number, composition and velocity from solid rocket motors (1985)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The damage potentials to the space shuttle orbiter caused by the high velocity particles contained in the exhaust plume of an upper stage is discussed. In particular, the particle size distribution and composition, the velocity of the particles and the expected contribution from shuttle launched upper stages are addressed. Particle size estimates based on historical data are compapred with those derived from upper stage motor performance testing. The particle velocities as determined by the best available plume computational technique are presented. The shuttle is scheduled to launch approximately 135 upper-stages over its lifetime looking at the currently scheduled flights and averaging over a yearly basis yields the contribution of particulates from the uper-stages. On the average, 91,645 llbs of Al2O3 will be ejected on each launch. The analysis to determine how much of this 91,645 lbs will remain in orbit or the decay rate is yet to be accomplished.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Orbital Debris; p 170-176
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  • 3
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    Opening up to the future in space with nuclear power (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The relationship between the exploration of space and the availability of abundant power supplies is discussed. It is proposed that nuclear power will be needed to satisfy the power demands of manufacturing facilities in LEO, and power demands for the year 2000 are projected to be 300 KW(e). The capabilities and development of the Space Station are described; the use of nuclear power for the Station and various reactor location configurations are studied. The power requirements that will be necessary for the development of lunar resource bases and the exploration of Mars and other planets are considered; the advantages of nuclear power are examined.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 4
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    SSME failure detection (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: During ground testing of the Space Shuttle Main Engine (SSME), there have been twenty-six major incidents resulting in substantial hardware damage and loss. Historical characteristics, advances in detection technology, and advances in computing technology led to plans for study of an advanced real time SSME test stand failure detection system which would reduce damage and preserve evidence when a failure with major incident potential occurs. This detection system will speed recognition of dangerous engine operation, and quicken the shutdown decision. The scope of this study, SSME characteristics, SSME test history, the problem definition, and some technical issues will be addressed herein.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 5
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    Performance of high-area-ratio nozzle for a small rocket thruster (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 3; 329-333
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  • 6
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    Advanced propulsion activities in the USA (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An evaluation is made of technology development prospects for launch vehicle, orbit transfer vehicle, satellite, and planetary exploration spacecraft propulsion systems being contemplated by NASA and its research contractors. Attention is given to such electric propulsion systems as arcjet, pulsed plasma, ion, and resistojet thrusters, as well as to solar thermal heat exchanger powerplants, beamed energy propulsion systems, and ultra-advanced nuclear fission and fusion propulsion concepts.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 16; 357-366
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  • 7
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    NASA Growth Space Station missions and candidate nuclear/solar power systems (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A brief summary is presented of a NASA study contract and in-house investigation on Growth Space Station missions and appropriate nuclear and solar space electric power systems. By the year 2000 some 300 kWe will be needed for missions and housekeeping power for a 12 to 18 person Station crew. Several Space Station configurations employing nuclear reactor power systems are discussed, including shielding requirements and power transmission schemes. Advantages of reactor power include a greatly simplified Station orientation procedure, greatly reduced occultation of views of the earth and deep space, near elimination of energy storage requirements, and significantly reduced station-keeping propellant mass due to very low drag of the reactor power system. The in-house studies of viable alternative Growth Space Station power systems showed that at 300 kWe a rigid silicon solar cell array with NiCd batteries had the highest specific mass at 275 kg/kWe, with solar Stirling the lowest at 40 kg/kWe. However, when 10 year propellant mass requirements are factored in, the 300 kWe nuclear Stirling exhibits the lowest total mass.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 8
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    Space Station Power System issues (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A number of attractive options are available for the Space Station Power System. These include a photovoltaic system or solar dynamic system for power generation, batteries or fuel cells for energy storage and ac or dc for power management and distribution. These options are being explored during the present preliminary design and definition phase of the Space Station Program. Final selections are presently targeted for January 1986.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 9
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    Protection of solar array blankets from attack by low earth orbital atomic oxygen (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The ram impact of low earth orbital atomic oxygen causes oxidation of spacecraft materials including polymers such as polyimides. The rate of oxidation is sufficiently high to potentially compromise the long term durability of Kapton solar array blankets. Ion beam sputter deposited atomic oxygen protective coatings of aluminum oxide, silicon dioxide, and codeposited silicon dioxide with small amounts of polytetrafluoroethylene were evaluated both in RF plasma asher tests and in low earth orbit. Deposition techniques, mechanical properties, and atomic oxygen protection performance are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 10
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    High temperature, high intensity solar array (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The solar array for the Venus Radar Mapper mission will operate in the high temperature, high intensity conditions of a low Venus orbit environment. To fulfill the performance requirements in this environment at minimum cost and mass while maximizing power density and packing factor on the panel surface, several features were introduced into the design. These features included the use of optical surface reflectors (OSR's) to reduce the operating temperature; new adhesives for conductive bonding of OSR's to avoid electrostatic discharges; custom-designed large area cells and novel shunt diode circuit and panel power harness configurations.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 11
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    Application of expert systems in the Common Module electrical power system (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Each Common Module (CM) of the Space Station must be capable of handling a 50 kW electricity supply, 25 kW for transmission and 25 kW for consumption. The power must be handled and managed by on-board systems, a necessity that dovetails with the objectives of Public Law 98-371, which mandates that the Space Station push the state of the art of automation and AI. Expert systems will be needed to handle the large data flow for the power system and to ensure that the system degrades gracefully. Features of the first expert systems expected for the power system, i.e., a dynamic load planner/scheduler and energy storage subsystem management, fault diagnosis/analysis, health status/trend analysis, and orbital replacement advisor expert systems, are described. Finally, growth Space Station expert systems applications are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 12
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    Nuclear powerplants for lunar bases (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Attention is given to the goals and preliminary determinations of the SP-100 program, whose objective is the design of space and lunar base nuclear powerplants capable of generating 100-1000 kW(e) for two years, with potential growth to 7 years. Current program studies are focusing on design concepts and the development status evaluation of critical technology. The dimensions of an SP-100 powerplant must allow transportation aboard the Space Shuttle. Reactor, heat conversion cycle, heat transfer medium, and thermal rejection system alternatives are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 13
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    Space Station propulsion system technology (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Two propulsion systems have been selected for the Space Station: O/H rockets for high thrust applications and the multipropellant resistojets for low thrust needs. These thruster systems integrate very well with the fluid systems on the station. Both thrusters will utilize waste fluids as their source of propellant. The O/H rocket will be fueled by electrolyzed water and the resistojets will use stored waste gases from the environmental control system and the various laboratories. This paper presents the results of experimental efforts with O/H and resistojet thrusters to determine their performance and life capability.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 15; 673-683
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  • 14
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    Oxidation-resistant reflective surfaces for solar dynamic power generation in near earth orbit (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Reflective surfaces for Space Station power generation systems are required to withstand the atomic oxygen-dominated environment of near earth orbit. Thin films of platinum and rhodium, which are corrosion resistant reflective metals, have been deposited by ion beam sputter deposition onto various substrate materials. Solar reflectances were then measured as a function of time of exposure to a RF-generated air plasma.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Vacuum Science and Technology A (ISSN 0734-2101); 5; 2737-274
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  • 15
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    Probabilistic structural analysis methods for space propulsion system components (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The development of a three-dimensional inelastic analysis methodology for the Space Shuttle main engine (SSME) structural components is described. The methodology is composed of: (1) composite load spectra, (2) probabilistic structural analysis methods, (3) the probabilistic finite element theory, and (4) probabilistic structural analysis. The methodology has led to significant technical progress in several important aspects of probabilistic structural analysis. The program and accomplishments to date are summarized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Probabilistic Engineering Mechanics (ISSN 0266-8920); 2; 100-110
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  • 16
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    Some aspects of space propulsion with extraterrestrial resources (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Extraterrestrial resources for space processing of chemicals, in general, and propellants, in particular, are explored quantitatively. It is seen that, for several candidate space mission scenarios, space processing of both space resources and earth-carried resources can make decisive differences in the mission success for a given payload. To fix ideas and demonstrate trends, the specific case of water splitting to extract oxygen, discard (or use without storage) the resulting hydrogen, and burn earth-carried noncryogenic liquid fuel(s) in a simple rocket motor, designed for periodic thrusting, is treated in some detail. Experimental hardware is assembled and demonstrated to perform adequately, besides showing compactness of the space-packaged 'capsule' module that is self-contained. Building upon previous studies, the concept of in situ propellant production (ISPP) is reexamined in light of more recent energy and materials technologies. Missions to comets and Mars Sample Return are mentioned as candidate scenarios. The mission duration, reliability-repairability of hardware, resource availability in low earth orbit (LEO), and the thrust requirements are considered in turn. It is seen that space storage of hydrogen for extended durations (5-10 years) involves problems that require detailed studies, besides involving many presently unanswered issues. A study of the energy option in LEO and in deep space is developed in simple terms. The different solar, radioisotope, and nuclear power sources are mentioned. Storage and handling of raw and processed chemicals are considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 236-244
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  • 17
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    Manned spacecraft electrical power systems (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A brief history of the development of electrical power systems from the earliest manned space flights illustrates a natural trend toward a growth of electrical power requirements and operational lifetimes with each succeeding space program. A review of the design philosophy and development experience associated with the Space Shuttle Orbiter electrical power system is presented, beginning with the state of technology at the conclusion of the Apollo Program. A discussion of prototype, verification, and qualification hardware is included, and several design improvements following the first Orbiter flight are described. The problems encountered, the scientific and engineering approaches used to meet the technological challenges, and the results obtained are stressed. Major technology barriers and their solutions are discussed, and a brief Orbiter flight experience summary of early Space Shuttle missions is included. A description of projected Space Station power requirements and candidate system concepts which could satisfy these anticipated needs is presented. Significant challenges different from Space Shuttle, innovative concepts and ideas, and station growth considerations are discussed. The Phase B Advanced Development hardware program is summarized and a status of Phase B preliminary tradeoff studies is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE, Proceedings (ISSN 0018-9219); 75; 277-307
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  • 18
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    Solar thermal propulsion for planetary spacecraft (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Previous studies have shown that many desirable planetary exploration missions require large injection delta-V. Solar Thermal Rocket (STR) propulsion, under study for orbit-raising applications may enhance or enable such high-energy missions. The required technology of thermal control for liquid hydrogen propellant is available for the required storage duration. Self-deploying, inflatable solar concentrators are under study. The mass penalty for passive cryogenic thermal control, liquid hydrogen tanks and solar concentrators does not compromise the specific impulse advantage afforded by the STR as compared to chemical propulsion systems. An STR injection module is characterized and performance is evaluated by comparison to electric propulsion options for the Saturn Orbiter Titan Probe (SOTP) and Uranus Flyby Uranus Probe (UFUP) missions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 445-456
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  • 19
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    Space station advanced propulsion and fluid management program (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: In preparation for the development of a manned space station program of advanced technology and development to make new advanced propulsion options available for the initial space station in the 1990's is described. This paper reviews the objectives of the advanced technology and development program in propulsion, describes its origin and how it relates to the forthcoming development program. The advanced propulsion and fluid management systems to be investigated in the program are discussed along with the rationale for their selection. Finally, the systems test program is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 413-421
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  • 20
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    The O sub 2/H sub 2 propulsion module for planetary spacecraft injection energy augmentation (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A propulsion module to augment the Centaur G-Prime and the Aerobraked OTV (AOTV) injection energy (C sub 3) was studied. The characteristics and performance of a variety of Earth-storable and cryogenic propulsion systems are presented. A pump-fed, cryogenic O2/H2 propulsion system enables the elimination of a three-year delta V Earth gravity assist (delta VEGA) maneuver for several planetary missions currently under consideration by the NASA. This trip time reduction can significantly reduce mission support costs, reduce spacecraft (S/C) life requirements and potentially increase the probability of mission success. This study also shows that an O2/H2 propulsion module, developed for Centaur C sub 3 augmentation can be used with a space-based AOTV in the return mode, allowing the reuse of the high-value AOTV while still delivering the required high-injection energy for direct planetary missions. The propulsion module performance was estimated for a space shuttle delivery capability to LEO of 65,000 lb sub m and 75,000 lb sub m. The required minimum thrust level to minimize gravity losses was also determined. For several currently planned NASA planetary missions, the Centaur G-Prime injection energy is augmented by a delta VEGA maneuver. For these missions, direct injection by the Centaur cannot provide a shorter trip time than the delta VEGA injection trip time.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 435-443
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  • 21
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    Advanced research and technology program for advanced high pressure oxygen-hydrogen rocket propulsion (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A research and technology program for advanced high pressure, oxygen-hydrogen rocket propulsion technology is presently being pursued by the National Aeronautics and Space Administration (NASA) to establish the basic discipline technologies, develop the analytical tools, and establish the data base necessary for an orderly evolution of the staged combustion reusable rocket engine. The need for the program is based on the premise that the USA will depend on the Shuttle and its derivative versions as its principal Earth-to-orbit transportation system for the next 20 to 30 yr. The program is focused in three principal areas of enhancement: (1) life extension, (2) performance, and (3) operations and diagnosis. Within the technological disciplines the efforts include: rotordynamics, structural dynamics, fluid and gas dynamics, materials fatigue/fracture/life, turbomachinery fluid mechanics, ignition/combustion processes, manufacturing/producibility/nondestructive evaluation methods and materials development/evaluation. An overview of the Advanced High Pressure Oxygen-Hydrogen Rocket Propulsion Technology Program Structure and Working Groups objectives are presented with highlights of several significant achievements.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 247-256
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  • 22
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    Simplified design and life prediction of rocket thrust chambers (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 181-187
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  • 23
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    Analysis of mid-tropospheric Space Shuttle exhausted aluminum oxide particles (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Aluminum oxide particles from the exhaust of the Space Shuttle were collected immediately after the launch of the SEPEX mission and during the descent over the altitude interval of 7.6-4.6 km. The SEM examination revealed that the particles were spherical and ranged in diameter from about 0.1 micron to 10 microns. Results from the energy dispersive analysis (by an X-ray method) and of the particle chemistry (by electron spectroscopy) confirmed that the particles were predominantly composed of aluminum and oxygen. The particle size distribution of the Al2O3 was bimodal, with one observed peak centered near 2.0 microns; the other distribution mode centered at a diameter of less than 0.3 micron, but could not be accurately located. A mass median diameter was slightly less than 2 microns. Evaluation of ice nucleation activity revealed only a small fraction (about 1 ppm) of active ice nuclei among the Al2O3 particulates.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Atmospheric Environment (ISSN 0004-6981); 21; 5, 19
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  • 24
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    Microwave electric propulsion for orbit transfer applications (1985)
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    Publication Date: 2011-08-19
    Description: A Microwave Electric Propulsion (MEP) concept is developed for an unmanned Orbit Transfer Vehicle (OTV). The concept is based on the use of beamed microwave power and on an extrapolation of ion thruster technology. Beamed microwave power transmission is discussed in terms of its relationship to spacecraft propulsion. Characteristics of an MEP OTV are determined and performance is evaluated by comparison to a variety of alternative propulsion systems for the completion of a ten-year mission model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 509-518
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  • 25
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    Thermal arcjet technology for space propulsion (1985)
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    Publication Date: 2011-08-19
    Description: Advanced space propulsion systems are required to meet projected Air Force needs through the year 2000. Most of these missions require a large, on-orbit impulse capability. High specific impulse (I sub sp) electric engines can provide this impulse while consuming relatively little propellant. An arcjet engine system, which operates in the range of 800 to 2000 s I sub sp, is a promising candidate to meet these projected Air Force mission needs. This electric propulsion system is ideally suited to missions currently under consideration, such as the Space-based Radar and other space platforms, because sufficient power is already installed for other functions on the spacecraft. Also, arcjet systems are attractive for NASA near-term, low-cost Mariner Mark II missions to Saturn and Uranus. Development of arcjet engines was an Air Force and NASA-sponsored activity that proceeded vigorously from its inception during the late 1950's up to the mid-1960's when the programs were terminated. This paper describes thermal arcjet technology as it was developed over two decades ago and points to the direction this technology development should proceed in the future. In particular, operation with storable propellants such as ammonia and hydrazine are considered. The performance, applicability and advantages of these systems in terms of increased payload and/or decreased trip times are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 485-494
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  • 26
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    Vacuum chamber pressure effects on thrust measurements (1985)
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    Publication Date: 2011-08-19
    Description: Tests were conducted to investigate the effect of vacuum facility pressure on the performance of small thruster nozzles. Thrust measurements of two converging-diverging nozzles with an area ratio of 140 and an orifice plate flowing unheated nitrogen and hydrogen were taken over a wide range of vacuum facility pressures and nozzle throat Reynolds numbers. In the Reynolds number range of 2200 to 12,000 there was no discernable viscous effect on thrust below an ambient to total pressure ratio of 1000. In nearly all cases, flow separation occurred at a pressure ratio of about 1000. This was the upper limit for obtaining an accurate thrust measurement for a conical nozzle with an area ratio of 140.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 469-474
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  • 27
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    Compatibility experiments of facilities, materials, and propellants for electrothermal thrusters (1985)
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    Publication Date: 2011-08-19
    Description: Experiments were performed to determine the compatibility of materials and propellants for electro-thermal thrusters. Candidate propellants for resistojet propulsion include carbon dioxide, methane, hydrogen, ammonia, and hydrazine. The materials being examined are grain stabilized platinum for resistojets for space station and rhenium for high performance resistojets for satellites. Heater mass loss and deterioration of materials were evaluated. A coiled tube of platinum, with yttria dispersed throughout the base material to inhibit grain growth, was tested in carbon dioxide at 1300 C for 2000 hr. Post-test examination indicated the platinum-yttria heater would last over 100,000 hr with less than 10 percent mass loss. Short-term compatibility tests were conducted to test the integrity of the platinum-yttria in hydrogen, methane, carbon dioxide/methane mixtures and ammonia environments. In each of these 100 hr tests, the platinum-yttria mass change indicated a minimum coil life of 100,000 hr. Facility related effects were investigated in materials tests using rhenium heated to high temperatures. Vacuum facility water reduction was monitored using a mass spectrometer. In vacuum environments obtained using only diffusion pumping and those obtained with the assistance of cryogenic equipment there were mass gains in the rhenium heaters. These mass gains were the result of the high amount of oxygen and water contained in the gas. Propellant purity and preferred test facility environments are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 475-484
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  • 28
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    The design and application of nickel-cadmium batteries in space (1985)
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    Publication Date: 2011-08-19
    Description: This paper describes the considerations given to selection of 20 and 50 A h nickel-cadmium cells and batteries for NASA/Goddard's Solar Max and Landsat D missions. Results of cell and battery manufacturer testing and improvements in design required by NASA standard specifications are shown. Operation of three batteries in parallel using a single voltage limit/current taper charge control system is described along with suggestions for optimizing life and uniformity. The results of three years of in-orbit operation is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Power Sources (ISSN 0378-7753); 15; 119-140
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  • 29
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    Electric power - Photovoltaic or solar dynamic? (1985)
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    Details
    Publication Date: 2011-08-19
    Description: The design of the power system for supplying the Space Station with insolation-generated electricity is the main Phase B task at NASA-Lewis Center. The advantages and limitations of two types of power systems, the photovoltaic arrays (PV) and the solar dynamic system (SD), are discussed from the points of view of cost, overall systems integration, and growth. Subsystems of each of these options are described, and a sketch of a projected SD system is shown. The PV technology is well developed and proven, but its low efficiency calls for solar arrays of large areas, which affect station dynamics, control, and drag compensation. The SD systems would be less costly to operate than VP, and are more efficient, needing less deployed area. The major drawback of the SD is its infancy. The conservative and forgiving designs for some of its components must still be created and tested, and the development risks assessed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Aerospace America (ISSN 0740-722X); 23; 60-62
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    Computation of the Shuttle solid booster nozzle start-up transient flow (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 1; 321-328
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  • 31
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    A fracture mechanics study of the turbine wheel in the Space Shuttle auxiliary power unit (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The experimental and analytical efforts performed for fracture control of the Space Shuttle auxiliary power unit (APU) wheel are described and a summary of fracture mechanics concepts relevant to safe-life analysis of fatigue loaded parts is given. An environmental crack growth test program is conducted by NASA on candidate wheel materials exposed to decomposed hydrazine which is found to be no more severe in causing crack growth than an environment of high-temperature air. Details of the crack growth testing and the safe-life analysis are presented. The results show that special nondestructive examination is needed for the APU wheel to meet the required mission life for either the maximum design or expected speed-range operations.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Theoretical and Applied Fracture Mechanics (ISSN 0167-8442); 3; 71-84
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  • 32
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    Power supplies for primary electric propulsion missions (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 1; 163-171
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  • 33
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    Airborne measurements of Space Shuttle exhaust constituents (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA Journal (ISSN 0001-1452); 23; 283-287
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  • 34
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    Space shuttle main engine vibration data base (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: In order to evaluate Space Shuttle Main Engine (SSME) vibration data without having to constantly replay analog tapes, the SSME Vibration Data Base was developed. This data base contains data that have been digitized at a high sample rate for the entire test duration. It provides quick and efficient recall capabilities for numerious computation and display routines. The data base components are described as well as some of the compution and display features.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: The 58th Shock and Vibration Symposium, Volume 1; p 353-359
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  • 35
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    Space station power management and distribution (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The power system architecture is presented by a series of schematics which illustrate the power management and distribution (PMAD) system at the component level, including converters, controllers, switchgear, rotary power transfer devices, power and data cables, remote power controllers, and load converters. Power distribution options, reference power management, and control strategy are also outlined. A summary of advanced development status and plans and an overview of system test plans are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Photovoltaic Research and Technology 1985; p 279-285
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  • 36
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    Manufacturing and producibility technology (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Activities of the manufacturing/producibility working group within the Advanced High-Pressure O2/H2 Technology Program are summarized. The objectives of the M/P working group are: to develop and evaluate process and manufacturing techniques for advanced propulsion hardware design and selected materials; and to optimize the producibility of (SSME) components and assemblies by improved performance, increased life, greater reliability, and/or reduced cost. The technologies being developed include: plasma arc, laser, and inertia welding; combustion chamber and turbine blade coatings; coating processes; high performance alloy electroforming; and process control technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Advan. High Pressure O2(H2 Technol.; p 44-48
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  • 37
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    Fuel and oxidizer turbine loss analysis (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The turbine losses for the fuel and oxidizer turbines at the FPL condition were assessed by a quasi-3D loss analysis method. This loss analysis method uses two flow codes - MERIDL and TSONIC - to calculate the flow velocities along the blade surfaces and endwalls. The velocities are then used as input to the boundary layer code - BLAYER - to calculate the friction losses due to incidence, secondary flow, and tip clearance. The loss analysis for the fuel turbine indicated an overall two-stage efficiency of about 90%. The largest loss was due to rotor tip clearance. The loss analysis for the oxidizer turbine is nearly completed. Results for the first stage of the two-stage design indicates an efficiency of about 80%, with high losses due to rotor incidence and blade and endwall friction.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.; p 560-570
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  • 38
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    Housing flexibility effects on rotor stability (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Preliminary rotordynamic evaluations are performed with a housing stiffness assumption that is typically determined only after the hardware is built. In addressing rotor stability, a rigid housing assumption was shown to predict an instability at a lower spin speed than a comparable flexible housing analysis. This rigid housing assumption therefore provides a conservative estimate of the stability threshold speed. A flexible housing appears to act as an energy absorber and dissipated some of the destabilizing force. The fact that a flexible housing is usually asymmetric and considerably heavier than the rotor was related to this apparent increase in rotor stability. Rigid housing analysis is proposed as a valuable screening criteria and may save time and money in construction of elaborate housing finite element models for linear stability analyses.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.; p 482-507
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  • 39
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    Solid Rocket Motor Case (SRMC) dynamic sensitivity to changes in composite properties (1985)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Traditional composite lamination theory was used to compute the constitutive matrices using a potential range of lamina properties. Sensitivity of vibrational frequencies was examined for variations in constituent materials and geometric properties. The material component interactions examined were the lamina longitudinal and transverse Young's modulus, the lamina Poisson's ratio, and the shear modulus. Fiber and resin properties were related to the frequency response through lamina properties. Geometric properties examined are void ratio and helical wind angle. Capabilities and applications of the SPAR and NASTRAN computer codes are examined for laminated cylindrical shells.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ. Res. Rept.: 1984 NASA/ASEE Summer Faculty Fellowship Program (NASA-CR; 20p
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  • 40
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    An investigation of space shuttle main engine shutdown chugging instability (1985)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The Space Shuttle Main Engines experience a low frequency pressure pulsation in both the fuel and oxidizer preburners during shutdown. The pressure pulsations (chugging) occur during the helium purge of oxidizer from the preburner manifolds. Possible causes and triggering mechanisms are considered as details of the chugging process are presented and discussed. A simple chugging model capable of predicting pressure excursion amplitudes and frequencies is proposed and preliminary results presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Alabama Univ. Res. Rept.: 1984 NASA/ASEE Summer Faculty Fellowship Program (NASA-CR; 36p
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  • 41
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    Thermal design of the space shuttle solid rocket booster (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The thermal protection systems (TPS) to meet the quick turnaround and low cost required for reuse of the solid rocket booster (SRB) hardware. The TPS development considered the ease of application, changing ascent/reentry environments, and the problem of cleaning the residual insulation upon recovery. A sprayable ablator TPS material was developed. The challenges involved in design and development of this thermal system are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center Space Shuttle Tech. Conf., Pt. 2; p 1030-1040
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  • 42
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    Debris control design achievements of the booster separation motors (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The stringent debris control requirements imposed on the design of the Space Shuttle booster separation motor are described along with the verification program implemented to ensure compliance with debris control objectives. The principal areas emphasized in the design and development of the Booster Separation Motor (BSM) relative to debris control were the propellant formulation and nozzle closures which protect the motors from aerodynamic heating and moisture. A description of the motor design requirements, the propellant formulation and verification program, and the nozzle closures design and verification are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center Space Shuttle Tech. Conf., Pt. 2; p 628-638
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  • 43
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    Solid rocket motor certification to meet space shuttle requirements from challenge to achievement (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Three solid rocket motor (SRM) design requirements for the Space Shuttle were discussed. No existing solid rocket motor experience was available for the requirement for a thrust-time trace, twenty uses for the principle hardware, and a moveable nozzle with an 8 deg. omnivaxial vectoring capability. The solutions to these problems are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center Space Shuttle Tech. Conf., Pt. 2; p 618-627
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  • 44
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    Space shuttle main engine: Interactive design challenges (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The operating requirements established by NASA for the SSME were considerably more demanding than those for earlier rocket engines used in the military launch vehicles or Apollo program. The SSME, in order to achieve the high performance, low weight, long life, reusable objectives, embodied technical demands far in excess of its predecessor rocket engines. The requirements dictated the use of high combustion pressure and the staged combustion cycle which maximizes performance through total use of all propellants in the main combustion process. This approach presented a myriad of technical challenges for maximization of performance within attainable state of the art capabilities for operating pressures, operating temperatures and rotating machinery efficiencies. Controlling uniformity of the high pressure turbomachinery turbine temperature environment was a key challenge for thrust level and life capability demanding innovative engineering. New approaches in the design of the components were necessary to accommodate the multiple use, minimum maintenance objectives. Included were the use of line replaceable units to facilitate field maintenance automatic checkout and internal inspection capabilities.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center Space Shuttle Tech. Conf., Pt. 2; p 600-617
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  • 45
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    Space shuttle main engine hardware simulation (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Huntsville Simulation Laboratory (HSL) provides a simulation facility to test and verify the space shuttle main engine (SSME) avionics and software system using a maximum complement of flight type hardware. The HSL permits evaluations and analyses of the SSME avionics hardware, software, control system, and mathematical models. The laboratory has performed a wide spectrum of tests and verified operational procedures to ensure system component compatibility under all operating conditions. It is a test bed for integration of hardware/software/hydraulics. The HSL is and has been an invaluable tool in the design and development of the SSME.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center Space Shuttle Tech. Conf., Pt. 1; p 54-63
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  • 46
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    Redistribution of the inlet temperature profile through the SSME fuel turbine (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A three-dimensional Euler code was used to predict radial inlet temperature profile redistribution through the two-stage fuel turbopump turbine. The calculation was made at the FPL condition using a turbine inlet radial temperature profile. This same calculation was made earlier on single-stage turbine. There was a redistribution of the temperature profile such that the hotter gas that originated at the midspan region at the turbine inlet was shifted to the hub and tip regions on the blade pressure surface at the rotor exit. For the SSME fuel turbine, however, there was no redistribution of the inlet temperature profile. No strong secondary flow patterns were identified. It is indicated that this trend is attributed to the high solidity SSME blading.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.; p 571-578
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  • 47
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    Numerical analysis of flow non-uniformity in the hot gas manifold of the Space Shuttle main engine (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Three-dimensional viscous flow in a conceptual hot gas manifold (HGM) for the Space Shuttle Main Engine High Pressure Fuel Turbopump (SSME HPFTP) was numerically analyzed. A finite difference scheme was used to solve the Navier-Stokes equations. The exact geometry of the SSME HGM was modeled using boundary fitted curvilinear coordinates and the General Interpolants Method (GIM) code. Slight compressibility of the subsonic flow was modeled using a linearized equation of state with artificial compressibility. A time relaxation method was used to obtain a steady state solution. The feasibility and potential usefulness of computational methods in assisting the design of SSME components which involves the flow of fluids within complex geometrical shapes is demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.; p 548-559
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  • 48
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    SSME Turbopump Turbine Computations (1985)
    In:  CASI
    Details
    Publication Date: 2014-08-30
    Description: A two-dimensional viscous code was developed to be used in the prediction of the flow in the SSME high-pressure turbopump blade passages. The rotor viscous code (RVC) employs a four-step Runge-Kutta scheme to solve the two-dimensional, thin-layer Navier-Stokes equations. The Baldwin-Lomax eddy-viscosity model is used for these turbulent flow calculations. A viable method was developed to use the relative exit conditions from an upstream blade row as the inlet conditions to the next blade row. The blade loading diagrams are compared with the meridional values obtained from an in-house quasithree-dimensional inviscid code. Periodic boundary conditions are imposed on a body-fitted C-grid computed by using the GRAPE GRids about Airfoils using Poisson's Equation (GRAPE) code. Total pressure, total temperature, and flow angle are specified at the inlet. The upstream-running Riemann invariant is extrapolated from the interior. Static pressure is specified at the exit such that mass flow is conserved from blade row to blade row, and the conservative variables are extrapolated from the interior. For viscous flows the noslip condition is imposed at the wall. The normal momentum equation gives the pressure at the wall. The density at the wall is obtained from the wall total temperature.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 15-26
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  • 49
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    SSME Fuel Preburner Two-dimensional Analysis (1985)
    In:  CASI
    Details
    Publication Date: 2014-08-27
    Description: The durability of the SSME turbine is strongly affected by the temperature profile leaving the preburner. A reacting flow computer model to predict the turbine inlet temperature profile was used. Calculations were made by using a reacting flow code, to assess the sensitivity of the turbine inlet temperature profile to variations in the flow entering the SSME preburner.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 7-14
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  • 50
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    Overview of Aerothermodynamic Loads Definition Study (1985)
    In:  CASI
    Details
    Publication Date: 2014-08-30
    Description: The Aerothermodynamic Loads Definition were studied to develop methods to more accurately predict the operating environment in the space shuttle main engine (SSME) components. Development of steady and time-dependent, three-dimensional viscous computer codes and experimental verification and engine diagnostic testing are considered. The steady, nonsteady, and transient operating loads are defined to accurately predict powerhead life. Improvements in the structural durability of the SSME turbine drive systems depends on the knowledge of the aerothermodynamic behavior of the flow through the preburner, turbine, turnaround duct, gas manifold, and injector post regions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Struct. Integrity and Durability of Reusable Space Propulsion Systems; p 3-5
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  • 51
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    High frequency data acquisition system for space shuttle main engine testing (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The high frequency data acquisition system developed for the Space Shuttle Main Engine (SSME) single engine test facility at the National Space Technology Laboratories is discussed. The real time system will provide engineering data for a complete set of SSME instrumentation (approx. 100 measurements) within 4 hours following engine cutoff, a decrease of over 48 hours from the previous analog tape based system.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: The 58th Shock and Vibration Symposium, Volume 1; p 349-352
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  • 52
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    Particle sizing in rocket motor studies utilizing hologram image processing (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A technique of obtaining particle size information from holograms of combustion products is described. The holograms are obtained with a pulsed ruby laser through windows in a combustion chamber. The reconstruction is done with a krypton laser with the real image being viewed through a microscope. The particle size information is measured with a Quantimet 720 image processing system which can discriminate various features and perform measurements of the portions of interest in the image. Various problems that arise in the technique are discussed, especially those that are a consequence of the speckle due to the diffuse illumination used in the recording process.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Ames Research Center, Automated Reduction of Data from Images and Holograms; p 589-606
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  • 53
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    Probabilistic structural analysis to evaluate the structural durability of SSME critical components (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: NASA Lewis Research Center is currently developing probabilistic structural analysis methods for select Space Shuttle Main Engine (SSME) structural components. Briefly, the deterministic, three-dimensional, inelastic analysis methodology developed under the Hot Section Technology (HOST) and R and T Base Programs is being augmented to accommodate the complex probabilistic loading spectra, the thermoviscoplastic material behavior, and the material degradation associated with the environment of space propulsion system structural components representative of the SSME such as turbine blades, transfer ducts, and liquid-oxygen posts. The development of probabilistic structural analysis methodology consists of the following program elements: (1) composite load spectra; (2) probabilistic structural analysis methods; (3) probabilistic finite element theory - new variational principles; and (4) probabilistic structural analysis application. In addition, the program includes deterministic analysis elements: (1) development of structural tailoring computer codes (SSME/STAEBL); (2) development of dynamic creep buckling/ratcheting theory; (3) evaluation of the dynamic characteristics of single-crystal SSME blades; (4) development of SSME blade damper technology; and (5) development of integrated boundary elements for hotfluid structure interaction.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 117-119
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  • 54
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    Propulsion estimation techniques (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A brief overview of statistical tools needed to perform post flight/test reconstruction of state variables is given. Linear regression, recursive linear regression, and the exact connection between the Kalman filter and linear regression are discussed. The regression connection is expected to serve as an aid in the application of a recently developed analytical method of flight reconstruction to single engine test firing data.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center, Research Reports: 1987 NASA(ASEE Summer Faculty Fellowship Program; 14 p
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  • 55
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    Equilibrium retention in the nozzle of oxygen hydrogen propulsion systems (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Arguments are presented for the retention of vibrational equilibrium of species in the nozzle of the Space Shuttle Main Engine which are especially applicable to water and the hydroxyl radical. It is shown that the reaction OH + HH yields HOH + H maintains equilibrium as well. This is used to relate OH to H, the temperature, and the oxidizer-to-fuel ratio.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center, Research Reports: 1987 NASA(ASEE Summer Faculty Fellowship Program; 26 p
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  • 56
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    Development of an integrated BEM (Boundary Element Mesh) for hot fluid-structure interaction (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A boundary integral representation for a coupled approach to fluid flow and solid deformation problems associated with the design of hot-section components such as those in the Space Shuttle Main Engine is discussed. The formulation is based on the fundamental analytical solution of the Navier-Stokes equation for fluid velocity in an infinite domain. This fundamental solution was obtained by decomposing a Navier-Stokes equation into vorticity and dilation transport equations. A boundary integral involving convolutions in time was then constructed in which the convective terms appear in the volume integral.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 219-222
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  • 57
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    SSME blade damper technology (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Before 1975 turbine blade damper designs were based on experience and very simple mathematical models. Failure of the dampers to perform as expected showed the need to gain a better understanding of the physical mechanism of friction dampers. Over the last 10 years research on friction dampers for aeronautical propulsion systems has resulted in methods to optimize damper designs. The first-stage turbine blades on the Space Shuttle Main Engine (SSME) high-pressure oxygen pump have experienced cracking problems due to excessive vibration. A solution is to incorporate a well-designed friction dampers to attenuate blade vibration. The subject study, a cooperative effort between NASA Lewis and Carnegie-Mellon University, represents an application of recently developed friction damper technology to the SSME high-pressure oxygen turbopump. The major emphasis was the contractor's design known as the two-piece damper. Damping occurs at the frictional interface between the top half of the damper and the underside of the platforms of the adjacent blades. The lower half of the damper is an air seal to retard airflow in the volume between blade necks.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 215-217
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  • 58
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    Structural tailoring using the SSME/STAEBL code (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Space Shuttle Main Engine/Structural Tailoring of Engine Blades (SSME/STAEBL) was developed by systematically modifying and enhancing the STAEBL code developed by Pratt and Whitney under contract to NASA Lewis Research Center. STAEBL was designed for application to gas turbine blade design. Typical design variables include blade thickness distribution and root chord. Typical constraints include resonance margins, root stress, and root to chord ratios. In this program, the blade is loaded by centrifugal forces only. Additions and modifications of STAEBL included in SSME/STAEBL include (1) thermal stress analysis; (2) gas dynamic (pressure) loads; (3) temperature dependent material and thermal properties; (4) forced vibrations; (5) tip displacement constraints; (6) single crystal material analysis; (7) blade cross section stacking offsets; and (8) direct time integration algorithm for transient dynamic response. Capabilities are also included which permit data transfer from finite element models and stand-alone analysis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 201-205
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  • 59
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    Probabilistic load model development and validation for composite load spectra for select space propulsion engines (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A major task of the program to develop an expert system to predict the loads on selected components of a generic space propulsion engine is the design development and application of a probabilitic loads model. This model is being developed in order to account for the random nature of the loads and assess the variable load ranges' effect on the engine performance. A probabilistic model has been developed. The model is based primarily on simulation methods, but also has a Gaussian algebra method (if all variables are near normal), a fast probability integrator routine (for the calculation of low probability events), and a separate, stand alone program for performing barrier crossing calculations. Each of these probabilistic methods has been verified with theoretical calculations using assumed distributional forms.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 189-199
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    Quantifying uncertainties in the structural response of SSME blades (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: To quantify the uncertainties associated with the geometry and material properties of a Space Shuttle Main Engine (SSME) turbopump blade, a computer code known as STAEBL was used. A finite element model of the blade used 80 triangular shell elements with 55 nodes and five degrees of freedom per node. The whole study was simulated on the computer and no real experiments were conducted. The structural response has been evaluated in terms of three variables which are natural frequencies, root (maximum) stress, and blade tip displacements. The results of the study indicate that only the geometric uncertainties have significant effects on the response. Uncertainties in material properties have insignificant effects.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 167-173
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    Probabilistic SSME blades structural response under random pulse loading (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The purpose is to develop models of random impacts on a Space Shuttle Main Engine (SSME) turbopump blade and to predict the probabilistic structural response of the blade to these impacts. The random loading is caused by the impact of debris. The probabilistic structural response is characterized by distribution functions for stress and displacements as functions of the loading parameters which determine the random pulse model. These parameters include pulse arrival, amplitude, and location. The analysis can be extended to predict level crossing rates. This requires knowledge of the joint distribution of the response and its derivative. The model of random impacts chosen allows the pulse arrivals, pulse amplitudes, and pulse locations to be random. Specifically, the pulse arrivals are assumed to be governed by a Poisson process, which is characterized by a mean arrival rate. The pulse intensity is modelled as a normally distributed random variable with a zero mean chosen independently at each arrival. The standard deviation of the distribution is a measure of pulse intensity. Several different models were used for the pulse locations. For example, three points near the blade tip were chosen at which pulses were allowed to arrive with equal probability. Again, the locations were chosen independently at each arrival. The structural response was analyzed both by direct Monte Carlo simulation and by a semi-analytical method.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 161-166
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    Advanced probabilistic method of development (1987)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Advanced structural reliability methods are utilized on the Probabilistic Structural Analysis Methods (PSAM) project to provide a tool for analysis and design of space propulsion system hardware. The role of the effort at the University of Arizona is to provide reliability technology support to this project. PSAM computer programs will provide a design tool for analyzing uncertainty associated with thermal and mechanical loading, material behavior, geometry, and the analysis methods used. Specifically, reliability methods are employed to perform sensitivity analyses, to establish the distribution of a critical response variable (e.g., stress, deflection), to perform reliability assessment, and ultimately to produce a design which will minimize cost and/or weight. Uncertainties in the design factors of space propulsion hardware are described by probability models constructed using statistical analysis of data. Statistical methods are employed to produce a probability model, i.e., a statistical synthesis or summary of each design variable in a format suitable for reliability analysis and ultimately, design decisions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 145-149
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    Liquid metal cooled reactors for space power applications (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The technology basis for evaluation of liquid metal cooled space reactors is summarized. Requirements for space nuclear power which are relevant to selection of the reactor subsystem are then reviewed. The attributes of liquid metal cooled reactors are considered in relation to these requirements in the areas of liquid metal properties, neutron spectrum characteristics, and fuel form. Key features of typical reactor designs are illustrated. It is concluded that liquid metal cooled fast spectrum reactors provide a high confidence, flexible option for meeting requirements for SP-100 and beyond.
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    Tethered nuclear power for the space station (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A nuclear space power system the SP-100 is being developed for future missions where large amounts of electrical power will be required. Although it is primarily intended for unmanned spacecraft, it can be adapted to a manned space platform by tethering it above the station through an electrical transmission line which isolates the reactor far away from the inhabited platform and conveys its power back to where it is needed. The transmission line, used in conjunction with an instrument rate shield, attenuates reactor radiation in the vicinity of the space station to less than one-one hundredth of the natural background which is already there. This combination of shielding and distance attenuation is less than one-tenth the mass of boom-mounted or onboard man-rated shields that are required when the reactor is mounted nearby. This paper describes how connection is made to the platform (configuration, operational requirements) and introduces a new element the coaxial transmission tube which enables efficient transmission of electrical power through long tethers in space. Design methodology for transmission tubes and tube arrays is discussed. An example conceptual design is presented that shows SP-100 at three power levels 100 kWe, 300 kWe, and 1000 kWe connected to space station via a 2 km HVDC transmission line/tether. Power system performance, mass, and radiation hazard are estimated with impacts on space station architecture and operation.
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    Direct solar heating for Space Station application (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Early investigations have shown that a large percentage of the power generated on the Space Station will be needed in the form of high-temperature thermal energy. The most efficient method of satisfying this requirement is through direct utilization of available solar energy. A system concept for the direct use of solar energy on the Space Station, including its benefits to customers, technologists, and designers of the station, is described. After a brief discussion of energy requirements and some possible applications, results of selective tradeoff studies are discussed, showing area reduction benefits and some possible configurations for the practical use of direct solar heating. Following this is a description of system elements and required technologies. Finally, an assessment of available contributive technologies is presented, and a Space Shuttle Orbiter flight experiment is proposed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 66
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    Design tradeoffs for a Space Station solar-Brayton power system (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Mass, area, and station-keeping propellant needs have been estimated for a typical system. And, although important criteria such as cost, Shuttle packaging, and erection/deployment schemes were not considered, the documented trends should aid in many of the design choices to be made. Effects on system characteristics were examined for: three heat storage salts with melting temperatures from 743 to 1121 K; parabolic and Cassegrainian mirrors; module power levels of 20 and 40 kW; and, alternate pumped-loop, tube-and-fin radiator configurations, with and without micrometeoroid armoring.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    Thermionic reactors for space nuclear power (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Thermionic reactor designs for a variety of space power applications spanning the range from 5 kWe to 3 MWe are described. In all of these reactors, nuclear heat is converted directly to electrical energy in thermionic fuel elements (TFEs). A circulating reactor coolant carries heat from the core of TFEs directly to a heat rejection radiator system. The recent design of a thermionic reactor to meet the SP-100 requirements is emphasized. Design studies of reactors at other power levels show that the same TFE can be used over a broad range in power, and that design modifications can extend the range to many megawatts. The design of the SP-100 TFE is similar to that of TFEs operated successfully in test reactors, but with design improvements to extend the operating lifetime to seven years.
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    Reactor power system deployment and startup (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: This paper addresses issues that should receive further examination in the near-term as concept selection for development of a U.S. space reactor power system is approached. The issues include: the economics, practicality and system reliability associated with transfer of nuclear spacecraft from low earth shuttle orbits to operational orbits, via chemical propulsion versus nuclear electric propulsion; possible astronaut supervised reactor and nuclear electric propulsion startup in low altitude Shuttle orbit; potential deployment methods for nuclear powered spacecraft from Shuttle; the general public safety of low altitude startup and nuclear safe and disposal orbits; the question of preferred reactor power level; and the question of frozen versus molten alkali metal coolant during launch and deployment. These issues must be considered now because they impact the SP-100 concept selection, power level selection, weight and size limits, use of deployable radiators, reliability requirements, and economics, as well as the degree of need for and the urgency of developing space reactor power systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    Autonomously managed high power systems (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The need for autonomous power management capabilities will increase as the power levels of spacecraft increase into the multi-100 kW range. The quantity of labor intensive ground and crew support consumed by the 9 kW Skylab cannot be afforded in support of a 75-300 kW Space Station or high power earth orbital and interplanetary spacecraft. Marshall Space Flight Center is managing a program to develop necessary technologies for high power system autonomous management. To date a reference electrical power system and automation approaches have been defined. A test facility for evaluation and verification of management algorithms and hardware has been designed with the first of the three power channel capability nearing completion.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    Space Station power system issues (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Issues governing the selection of power systems for long-term manned Space Stations intended solely for earth orbital missions are covered briefly, drawing on trade study results from both in-house and contracted studies that have been conducted over nearly two decades. An involvement, from the Program Development Office at MSFC, with current Space Station concepts began in late 1982 with the NASA-wide Systems Definition Working Group and continued throughout 1984 in support of various planning activities. The premise for this discussion is that, within the confines of the current Space Station concept, there is good reason to consider photovoltaic power systems to be a venerable technology option for both the initial 75 kW and 300 kW (or much greater) growth stations. The issue of large physical size required by photovoltaic power systems is presented considering mass, atmospheric drag, launch packaging and power transmission voltage as being possible practicality limitations. The validity of searching for a cross-over point necessitating the introduction of solar thermal or nuclear power system options as enabling technologies is considered with reference to programs ranging from the 4.8 kW Skylab to the 9.5 gW Space Power Satellite.
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    The Rockwell SR-100G reactor turboelectric space power system (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: During FY 1982 and 1983, Rockwell International performed system and subsystem studies for space reactor power systems. These studies drew on the expertise gained from the design and flight of the SNAP-10A space nuclear reactor system. These studies, performed for the SP-100 Program, culminated in the selection of a reactor-turboelectric (gas Brayton) system for the SP-100 application; this system is called the SR-100G. This paper describes the features of the system and provides references where more detailed information can be obtained.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    Reactor power system/spacecraft integration (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The new national initiative in space reactor technology evaluation and development is strongly tied to mission applications and to spacecraft and space transportation system (STS) compatibility. This paper discusses the power system integration interfaces with potential using spacecraft and the STS, and the impact of these requirements on the design. The integration areas of interest are mechanical, thermal, electrical, attitude control, and mission environments. The mission environments include space vacuum, solar input, heat sink, space radiation, weapons effects, and reactor power system radiation environments. The natural, reactor, and weapons effects radiation must be evaluated and combined to define the design requirements for spacecraft electronic equipment.
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    Thermal energy storage for a space solar dynamic power system (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: In the past, NASA has employed solar photovoltaic devices for long-duration missions. Thus, the Skylab system has operated with a silicon photovoltaic array and a nickel-cadmium electrochemical system energy storage system. Difficulties regarding the employment of such a system for the larger power requirements of the Space Station are related to a low orbit system efficiency and the large weight of the battery. For this reason the employment of a solar dynamic power system (SDPS) has been considered. The primary components of an SDPS include a concentrating mirror, a heat receiver, a thermal energy storage (TES) system, a thermodynamic heat engine, an alternator, and a heat rejection system. The heat-engine types under consideration are a Brayton cycle engine, an organic Rankine cycle engine, and a free-piston/linear-alternator Stirling cycle engine. Attention is given to a system description, TES integration concepts, and a TES technology assessment.
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    Design of a regenerative fuel cell system for Space Station (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The NASA Space Station will employ alkaline regenerative fuel cells (RFCs) as its sole electrochemical energy storage system, in virtue of demonstrated technology readiness and a high degree of system-level design flexibility. NASA Johnson and NASA Lewis are currently engaged in the development of a 10-kW alkaline engineering model system, for 1987 delivery, which will encompass a fully autonomous 120-V system with 55 percent overall electrical efficiency and a 20,000-hr service life.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    Energy and momentum management of the Space Station using magnetically suspended composite rotors (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The research addresses the feasibility of using magnetically suspended composite rotors to jointly perform the energy and momentum management functions of an advanced manned Space Station. Recent advancements in composite materials, magnetic suspensions, and power conversion electronics have given flywheel concepts the potential to simultaneously perform these functions for large, long duration spacecraft, while offering significant weight, volume, and cost savings over conventional approaches. The Space Station flywheel concept arising out of this study consists of a composite-material rotor, a large-angle magnetic suspension (LAMS) system, an ironless armature motor/generator, and high-efficiency power conversion electronics. The LAMS design permits the application of appropriate spacecraft control torques without the use of conventional mechanical gimbals. In addition, flywheel systems have the growth potential and modularity needed to play a key role in many future system developments.
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    Current status of advanced solar array technology development (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: This paper describes the current status of the JPL high performance solar array development program. Recent progress in solar cell, blanket and structure technologies is described. Future plans for integrating this work are discussed. The impact of the Mariner Mark II mission set on the future direction taken by this development program is assessed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    Space Station Power System Advanced Development (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The objectives of the Space Station Advanced Development Program are related to the development of a set of design options and/or new capabilities to support Space Station development and operation, taking into account also a quantification of the performance and risk of key state-of-the-art technologies, and a reduction of the cost and schedule risk in Space Station development. Attention is given to the photovoltaic power system, a solar dynamic system, and aspects of power management and distribution. A major issue will be the selection of the power generation system. In view of the advantages of the solar dynamic system, it is attempted to resolve issues associated with this system.
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    Static and dynamic high power, space nuclear electric generating systems (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Space nuclear electric generating systems concepts have been assessed for their potential in satisfying future spacecraft high power (several megawatt) requirements. Conceptual designs have been prepared for reactor power systems using the most promising static (thermionic) and the most promising dynamic conversion processes. Component and system layouts, along with system mass and envelope requirements have been made. Key development problems have been identified and the impact of the conversion process selection upon thermal management and upon system and vehicle configuration is addressed.
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    Space power systems - 'Spacecraft 2000' (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The program 'Spacecraft 2000' has the objective to identify critical, high-payoff, potential spacecraft technologies, taking into account the formulation, advocation, and the management of the requisite technology development programs. This program represents a joint NASA-industry program. The technology areas addressed by 'Spacecraft 2000' are related to spacecraft power/energy storage, thermal control/thermal management, power management and distribution, autonomous operation-control, on-board system integration, spacecraft environmental interactions, secondary propulsion, communications technologies, a total system response approach, and system-subsystem technology verification. The expected benefits of a development of advanced technologies include decreased spacecraft bus system weights, decreased mission costs, increased reliability/lifetimes, and increased operational flexibility.
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  • 80
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    Effects of tripropellant engines on earth-to-orbit vehicles (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 620-625
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  • 81
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    Liquid Engine Jet Atomization Workshop report (1987)
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    Publication Date: 2011-08-19
    Description: The workshop was oriented to disclose information and unsettled problems to understand the fundamental physical mechanism of the droplet formation process. Based on presentation and discussion of results, recommendations were made which should lead to associated future activities. To accomplish this task, existing observations and experiments, contributing to the basic knowledge, providing data for analytical concept verification, and forming a basis for empirical correlations were solicited. Advanced analytical modeling methods or results from specific studies were requested as well as the experience and advice from injector designers. All effort is directed to advance current analytical techniques, simulating the flow behavior downstream of the injection elements in a liquid rocket combustion chamber. Such a tool can be used to optimize injector designs with respect to short length weight savings, wall material protection, or large heat energy transport to a regenerative cooling fluid, while simultaneously achieving the maximum specific impulse in performance. The liquid atomization process also forms a sound basis for combustion instability analysis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 351-353
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    A detailed description of the uncertainty analysis for high area ratio rocket nozzle tests at the NASA Lewis Research Center (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A preliminary uncertainty analysis was performed for the High Area Ratio Rocket Nozzle test program which took place at the altitude test capsule of the Rocket Engine Test Facility at the NASA Lewis Research Center. Results from the study establish the uncertainty of measured and calculated parameters required for the calculation of rocket engine specific impulse. A generalized description of the uncertainty methodology used is provided. Specific equations and a detailed description of the analysis is presented. Verification of the uncertainty analysis model was performed by comparison with results from the experimental program's data reduction code. Final results include an uncertainty for specific impulse of 1.30 percent. The largest contributors to this uncertainty were calibration errors from the test capsule pressure and thrust measurement devices.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 291-318
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    Cyclic structural analyses of anisotropic turbine blades for reusable space propulsion systems (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Turbine blades for reusable space propulsion systems are subjects to severe thermomechanical loading cycles that result in large inelastic strains and very short lives. These components require the use of anisotropic high temperature alloys to meet the safety and durability requirements of such systems. To assess the effects on blade life of material anisotropy, cyclic structural analyses are being performed for the first stage high pressure fuel turbopump blade (HPFTB) of the space shuttle main engine (SSME). The blade alloy is directionally solidified MAR-M 246 alloy. The analyses are based on a typical test stand engine cycle. Stress-strain histories at the airfoil critical location are computed using the MARC nonlinear finite element computer code.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 237-245
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    Oxygen/hydrocarbon combustion devices technology (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A program was conducted to investigate ignition, combustion and heat transfer characteristics of liquid oxygen and RP-1 fuel applicable to large gas generator cycle booster engines. The program was part of a broad effort intended to generate a combustion devices technology base for both RP-1 and methane fuels and both gas generator and staged combustion engine cycles. Two gas generator injector designs were tested over a chamber pressure range of 1500 to 3100 psia and a gas temperature range of 1500 to 2300 R. Both configurations were evaluated for combustion efficiency, gas temperature profile and combustion stability. Thrust chamber firings were conducted using a platelet type main injector and a water cooled calorimeter combustion chamber. Test conditions ranged from 1700 to 2200 psia chamber pressure and from 2.0 to 2.8 mixture ratio. A program goal to reduce previously measured nozzle heating rates was achieved, but at the expense of combustion efficiency.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 271-280
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  • 85
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    LOX/LH2 vane pump for auxiliary propulsion systems (1985)
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    Publication Date: 2011-08-19
    Description: Positive displacement pumps offer potential efficiency advantages over centrifugal pumps for future low thrust space missions. Low flow rate applications, such as space station auxiliary propulsion or dedicated low thrust orbiter transfer vehicles, are typical of missions where low flow and high head rise challenge centrifugal pumps. The positive displacement vane pump for pumping of LOX and LH2 is investigated. This effort has included: (1) a testing program in which pump performance was investigated for differing pump clearances and for differing pump materials while pumping LN2, LOX, and LH2; and (2) an analysis effort, in which a comprehensive pump performance analysis computer code was developed and exercised. An overview of the theoretical framework of the performance analysis computer code is presented, along with a summary of analysis results. Experimental results are presented for pump operating in liquid nitrogen. Included are data on the effects on pump performance of pump clearance, speed, and pressure rise. Pump suction performance is also presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 161-170
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    Small, two-stage, partial-admission turbine (1985)
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    Publication Date: 2011-08-19
    Description: The Rocketdyne Orbital Transfer Vehicle (OTV) cryogenic, rocket engine system, high pressure, liquid hydrogen turbopump was designed with a two-stage, partial-admission axial turbine. The turbine is basically two single-stage, partial-admission, subsonic impulse stages designed so the kinetic energy leaving the first-stage rotor is discharged directly into the second-stage nozzle at nominal operation to minimize staging losses. Very little data were available in the literature for this type of turbine design. Therefore, it was decided to test a full-size model of the turbine design using ambient-temperature gaseous nitrogen as the working fluid. The tester design features a variable orientation second-stage nozzle to determine the optimum circumferential location for highest performance. The tester also features the capability to vary the nozzle arcs of admission and incorporates quartz windows to study the flowfield upstream of the second-stage nozzle using a laser velocimeter. The test operations will probe the efficiency and flow characteristics for three arcs of admission and the effects of second-stage nozzle circumferential orientations over wide ranges of speed and pressure ratios as well as the interstage pressure distributions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 55-62
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    Close-in characteristics of LH2/LOX reactions (1985)
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    Publication Date: 2011-08-19
    Description: In deriving shock overpressures from space vehicles employing LH2 and LOX, separate methods of analyses and prediction are recommended, as a function of the distance. Three methods of treatment are recommended. For the Far Field - where the expected shock overpressure is less than 40 psi (lambda = 5) - use the classical PYRO approach to determine TNT yield, and employ classical ordnance (Kingery) curve to obtain the overall value. For the Close-In Range, a suggested limit is 3D, or a zone from a distance of three times the tank diameter to the tank wall. Rather than estimate a specific distance from the center of explosion to the target, it is only necessary to estimate whether this could be within one, two, or three diameters away from the wall; i.e., in the 1, 2, or 3D zone. Then assess whether mixing mode is by the PYRO CBGS (spill) mode or CBM (internal mixing) mode. From the zone and mixing mode, the probability of attaining various shock overpressures is determined from the plots provided herein. For the transition zone, between 40 psi and the 3D distance, it is tentatively recommended that both of the preceding methods be used, and to be conservative, the higher resulting value be used.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 299-308
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    Alternative designs of integral tanks for advanced space transportation systems (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 425-431
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  • 89
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    Design of a nuclear electric propulsion orbital transfer vehicle (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 1; 70-76
    Format: text
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  • 90
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    Integratable propulsion systems for the Space Station (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Oxygen/hydrogen propulsion system options for space station orbit maintenance and attitude control were developed and evaluated relative to monopropellant and storable bipropellant propulsion systems. Space station propulsion requirements were analyzed with reference to such considerations as station size, altitude, power, crew size, and orbit transfer vehicle and orbital maneuvering vehicle servicing requirements. The evolutionary growth of oxygen/hydrogen bipropellant propulsion as an integral part of several interrelated space station functions, e.g., life support, power, and thermal management was considered. Propellant resupply evolves from resupply based on transport of liquid oxygen and liquid hydrogen to water. The advantages of the operation of the space station based on an oxygen/hydrogen economy are presented and discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 1; 65-69
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  • 91
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    Cost effective launch operations of the SSME (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The Space Shuttle Main Engine (SSME) represents the beginning of reusable rocket engine operations in the space transportation system (STS). Steps taken to reduce the overall cost of flight operations of the SSME by improving turnaround operations, extending the life of the engine, and improving the cost effectiveness of overhaul operations at the Canoga Park home plant are described. Ground certification testing to ensure safe launch operations is described, as well as certification extension testing that leads to a service life equivalent to 40 flights. The proven flight record of the SSME, which has demonstrated the utility of the SSME as a key component of America's space transportation system, is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 92
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    Modal survey of the space shuttle solid rocket motor using multiple input methods (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The ability to accurately characterize propellant in a finite element model is a concern of engineers tasked with studying the dynamic response of the Space Shuttle Solid Rocket Motor (SRM). THe uncertainties arising from propellant characterization through specimem testing led to the decision to perform a model survey and model correlation of a single segment of the Shuttle SRM. Multiple input methods were used to excite and define case/propellant modes of both an inert segment and, later, a live propellant segment. These tests were successful at defining highly damped, flexible modes, several pairs of which occured with frequency spacing of less than two percent.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-Marshall Space Flight Center, The 58th Shock and Vibration Symposium, Volume 1; p 155-167
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  • 93
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    Space station power system (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The major requirements and guidelines that affect the space station configuration and power system are explained. The evolution of the space station power system from the NASA program development-feasibility phase through the current preliminary design phase is described. Several early station concepts are described and linked to the present concept. Trade study selections of photovoltaic system technologies are described in detail. A summary of present solar dynamic and power management and distribution systems is also given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Photovoltaic Research and Technology 1986. High Efficiency, Space Environment and Array Technology; p 321-332
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  • 94
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    Spacecraft 2000: The challenge of the future (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Considerable opportunity exists to improve the systems, subsystems, components, etc., included in the space station bus, the non-payload portion of the spacecraft. The steps followed to date, the challenges being faced by industry, and the progress toward establishing a new NASA initiative which will identify the technologies required to build spacecraft of the 21st century and which will implement the technology development/validation programs necessary are described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Photovoltaic Research and Technology 1986. High Efficiency, Space Environment and Array Technology; p 333-341
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  • 95
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    Experimental evaluation of an advanced Space Shuttle main engine hot-gas manifold design concept (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This study, using an extensively modified, full-scale space shuttle main engine (SSME) hot-gas manifold (HGM), established a detailed aerodynamic data base to support development of an advanced, three-dimensional, fluid-dynamic analysis computer model. In addition, the advanced SSME hot-gas manifold design used in this study demonstrated improved flow environment (uniformity) in the fuel side turbine exit and transfer duct exit regions. Major modifications were incorporated in the full-scale HGM flow test article model using two large transfer ducts on the fuel turbine side of the HGM in place of the three small transfer ducts in the present design. Other model features included an increases in the flow areas downstream of the 180-degree turn and in the fishbowl regions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center Advan. High Pressure O2(H2 Technol.; p 512-547
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  • 96
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    Space station electrical power system (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this paper is to describe the design of the Space Station Electrical Power System. This includes the Photovoltaic and Solar Dynamic Power Modules as well as the Power Management and Distribution System (PMAD). In addition, two programmatic options for developing the Electrical Power System will be presented. One approach is defined as the Enhanced Configuration and represents the results of the Phase B studies conducted by the NASA Lewis Research Center over the last two years. Another option, the Phased Program, represents a more measured approach to reaching about the same capability as the Enhanced Configuration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100140 , E-3692 , NAS 1.15:100140 , IAF-87-234
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  • 97
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    Recent developments in indium phosphide space solar cell research (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent developments and progress in indium phosphide solar cell research for space application are reviewed. Indium phosphide homojunction cells were fabricated in both the n+p and p+n configurations with total area efficiencies of 17.9 and 15.9% (air mass 0 and 25 C) respectively. Organometallic chemical vapor deposition, liquid phase epitaxy, ion implantation and diffusion techniques were employed in InP cell fabrication. A theoretical model of a radiation tolerant, high efficiency homojunction cell was developed. A realistically attainable AMO efficiency of 20.5% was calculated using this model with emitter and base doping of 6 x 10 to the 17th power and 5 x 10 the the 16th power/cu cm respectively. Cells of both configurations were irradiated with 1 MeV electrons and 37 MeV protons. For both proton and electron irradiation, the n+p cells are more radiation resistant at higher fluences than the p+n cells. The first flight module of four InP cells was assembled for the Living Plume Shield III satellite.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100139 , E-3690 , NAS 1.15:100139 , AIAA PAPER 87-9053
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  • 98
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    Water-propellant resistojets for man-tended platforms (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The selection of a propulsion system for a man-tended platform has been influenced by the planned use of resistojets for drag make-up on the manned space station. For that application a resistojet has been designed that is capable of operation with a wide variety of propellants, including water. The reasons for the selection of water as the propellant and the performance of water as a propellant are discussed. The man-tended platform and its mission requirements are described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100110 , E-3649 , NAS 1.15:100110 , IAF-87-259
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  • 99
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    Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced Earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus liquid hydrogen addition, and the addition of an aluminum/liquid hydrogen slurry on the theoretical performance of a PBAN solid propellant rocket. The space shuttle solid rocket booster was used as a reference point. All three quasi-hybrid systems theoretically offer higher specific impulse when compared with the space shuttle solid rocket boosters. However, based on operational and safety considerations, the quasi-hybrid rocket is not a practical choice for near-term Earth-to-orbit booster applications. Safety and technology issues pertinent to quasi-hybrid rocket systems are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-2751 , E-3554 , NAS 1.60:2751 , AIAA PAPER 87-2082
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  • 100
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    Composite load spectra for select space propulsion structural components (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of this program is to develop generic load models to simulate the composite load spectra (CLS) that are induced in space propulsion system components representative of the space shuttle main engines (SSME). These models are being developed through describing individual component loads with an appropriate mix of deterministic and state-of-the-art probabilistic models that are related to key generic variables. Combinations of the individual loads are used to synthesize the composite loads spectra. A second approach for developing the composite loads spectra load model simulation, the option portion of the contract will develop coupled models which combine the individual load models. Statistically varying coefficients of the physical models will be used to obtain the composite load spectra.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 175-187
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