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  • Other Sources  (1,316)
  • SPACECRAFT PROPULSION AND POWER  (1,316)
  • 1985-1989  (1,316)
  • 1950-1954
  • 1
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    The liquid rocket booster and its potential for the STS (1989)
    In:  CASI
    Details
    Publication Date: 2006-06-11
    Description: Results of the liquid rocket booster study initiated by NASA to define an alternative to solid rocket boosters, are presented. The prime study contractors, Martin Marietta Corporation and General Dynamics, have identified liquid rocket booster configurations that can increase shuttle performance to 70 klb. These boosters will provide improved reliability, hold down, verification prior to vehicle release, engine-out and abort capabilities. Phasing of these boosters into Space Transportation System (STS) operations without adversely affecting flight rate is described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, Progress in Space Transportation; p 405-41
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  • 2
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    Space shuttle solid rocket booster redesign and testing (1989)
    In:  CASI
    Details
    Publication Date: 2006-06-11
    Description: The redesigned solid rocket motor of the Space Shuttle is described. Improvements over the model that led to the loss of the Space Shuttle Challenger are outlined. Scale and full-size tests carried out to verify the quality of the redesign are described. A unique feature of the test program is the introduction of deliberate flaws into some test articles. Post-flight evaluation of the redesigned boosters show excellent results.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, Progress in Space Transportation; p 173-18
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  • 3
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    Superfluid Helium On-Orbit Transfer (SHOOT) operations (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The in-flight tests and the operational sequences of the Superfluid Helium On-Orbit Transfer (SHOOT) experiment are outlined. These tests include the transfer of superfluid helium at a variety of rates, the transfer into cold and warm receivers, the operation of an extravehicular activity coupling, and tests of a liquid acquisition device. A variety of different types of instrumentation will be required for these tests. These include pressure sensors and liquid flow meters that must operate in liquid helium, accurate thermometry, two types of quantity gauges, and liquid-vapor sensors.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Cryogenics (ISSN 0011-2275); 29; 493-497
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  • 4
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    Electromagnetic emission experiences using electric propulsion systems (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 534-547
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  • 5
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    Probabilistic structural analysis methods for improving Space Shuttle engine reliability (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Probabilistic structural analysis methods are particularly useful in the design and analysis of critical structural components and systems that operate in very severe and uncertain environments. These methods have recently found application in space propulsion systems to improve the structural reliability of Space Shuttle Main Engine (SSME) components. A computer program, NESSUS, based on a deterministic finite-element program and a method of probabilistic analysis (fast probability integration) provides probabilistic structural analysis for selected SSME components. While computationally efficient, it considers both correlated and nonnormal random variables as well as an implicit functional relationship between independent and dependent variables. The program is used to determine the response of a nickel-based superalloy SSME turbopump blade. Results include blade tip displacement statistics due to the variability in blade thickness, modulus of elasticity, Poisson's ratio or density. Modulus of elasticity significantly contributed to blade tip variability while Poisson's ratio did not. Thus, a rational method for choosing parameters to be modeled as random is provided.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 426-430
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  • 6
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    Performance characterizations of an engineering model multipropellant resistojet (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 197-203
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  • 7
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    Computer-controlled xenon ion engine operation (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 42-48
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  • 8
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    Assessment of impingement effects in the isentropic core of a small satellite control thruster plume (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Two computational techniques commonly employed in the calculation of rocket and thruster expansion plumes are assessed. These are the method of characteristics (MOC), which is derived from the continuum Euler equations, and the direct simulation Monte Carlo (DSMC) method, which adopts a discrete particle approach. These techniques vary both in the computational expense and in the accuracy and detail of the solutions that they provide, depending upon the regime of application. The assessment is made with reference to the plume expanding from a small monopropellant hydrazine thruster and concentrates on the isentropic core of the jet for the flow regime lying between the continuum and free molecular limits. It is found that the more numerically intensive DSMC method offers the better correspondence to the available experimental data. In addition, large differences in typical impingement effects such as drag force and heat transfer are found at the free molecular limit of the plume expansion for the two predictive techniques. It is concluded that accurate estimation of impingement potential may only be achieved through application of the discrete particle method.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Institution of Mechanical Engineers, Proceedings, Part G - Journal of Aerospace Engineering (ISSN 0954-4100); 203; G2, 1
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  • 9
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    Electric propulsion for constellation deployment and spacecraft maneuvering (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 26; 352-357
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  • 10
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    Rocket plume spectrometry: A system permitting engine condition monitoring, as applied to the technology test bed engine (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The appearance of visible objects in the exhaust plume of space shuttle main engines (SSME) during test firings is discussed. A program was undertaken to attempt to identify anomalous material resulting from wear, normal or excessive, of internal parts, allowing time monitoring of engine condition or detection of failure precursors. Measurements were taken during test firings at Stennis Space Center and at the Santa Suzanna facility in California. The results indicated that a system having high spectral resolution, a fast time response, and a wide spectral range was required to meet all requirements, thus two special systems have been designed and built. One is the Optical Plume Anomaly Detector (OPAD). The other instrument, which is described in this report, is the superspectrometer, an optical multichannel analyzer having 8,192 channels covering the spectral band 250 to 1,000 nm.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center, Structural Integrity and Durability of Reusable Space Propulsion Systems; p 127-135
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  • 11
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    Thin-film sensors for space propulsion technology: Fabrication and preparation for testing (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The goal of this work is to develop and test thin-film thermocouples for Space Shuttle Main Engine (SSME) components. Thin-film thermocouples have been developed for aircraft gas turbine engines and are in use for temperature measurement on turbine blades up to 1800 F. Established aircraft engine gas turbine technology is currently being adapted to turbine engine blade materials and the environment encountered in the SSME, especially severe thermal shock from cryogenic fuel to combustion temperatures. Initial results using coupons of MAR M-246 (+Hf) and PWA 1480 have been followed by fabrication of thin-film thermocouples on SSME turbine blades. Current efforts are focused on preparing for testing in the Turbine Blade Tester at the NASA Marshall Space Flight Center (MSFC). Future work will include testing of thin-film thermocouples on SSME blades of single crystal PWA 1480 at MSFC.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 123-126
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  • 12
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    Advanced APS Impacts on Vehicle Payloads (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Advanced auxiliary propulsion system (APS) technology has the potential to both, increase the payload capability of earth-to-orbit (ETO) vehicles by reducing APS propellant mass, and simplify ground operations and logistics by reducing the number of fluids on the vehicle and eliminating toxic, corrosive propellants. The impact of integrated cryogenic APS on vehicle payloads is addressed. In this system, launch propulsion system residuals are scavenged from integral launch propulsion tanks for use in the APS. Sufficient propellant is preloaded into the APS to return to earth with margin and noncomplete scavenging assumed. No propellant conditioning is required by the APS, but ambient heat soak is accommodated. High temperature rocket materials enable the use of the unconditioned hydrogen/oxygen in the APS and are estimated to give APS rockets specific impulse of up to about 444 sec. The payload benefits are quantified and compared with an uprated monomethyl hydrazine/nitrogen tetroxide system in a conservative fashion, by assuming a 25.5 percent weight growth for the hydrogen/oxygen system and a 0 percent weight growth for the uprated system. The combination and scavenging and high performance gives payload impacts which are highly mission specific. A payload benefit of 861 kg (1898 lbm) was estimated for a Space Station Freedom rendezvous mission and 2099 kg (4626 lbm) for a sortie mission, with payload impacts varying with the amount of launch propulsion residual propellants. Missions without liquid propellant scavenging were estimated to have payload penalties, however, operational benefits were still possible.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 209-218
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  • 13
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    Effect of Propellant Flowrate and Purity on Carbon Deposition in LO2/Methane Gas Generators (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The generation and deposition of carbon was studied in the Carbon Deposition Program using subscale hardware with LO2/Liquid Natural Gas (LNG) and LO2/Methane propellants at low mixture ratios. The purpose of the testing was to evaluate the effect of methane purity and full scale injection density on carbon deposition. The LO2/LNG gas generator/preburner testing was performed at mixture ratios between 0.24 and 0.58 and chamber pressures from 5.8 to 9.4 MPa (840 to 1370 psia). A total of seven 200 second duration tests were performed. The LNG testing occurred at low injection densities, similar to the previous LO2/RP-1, LO2/propane, and LO2/methane testing performed on the carbon deposition program. The current LO2/methane test series occurred at an injection density factor of approximately 10 times higher than the previous testing. The high injection density LO2/methane testing was performed at mixture ratios between from 0.23 to 0.81 and chamber pressures from 6.4 to 15.2 MPa (925 to 2210 psia). A total of nine high injection density tests were performed. The testing performed demonstrated that low purity methane (LNG) did not produce any detectable change in carbon deposition when compared to pure methane. In addition, the C* performance and the combustion gas temperatures measured were similar to those obtained for pure methane. Similar results were obtained testing pure methane at higher propellant injection densities with coarse injector elements.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 131-144
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  • 14
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    Vacuum microelectronics for beam power and rectennas (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Vacuum Microelectronic devices can be described as vacuum transistors or micro-miniature vacuum tubes, as one chooses. The fundamental reason behind this new technology is the very large current densities available from field emitters, namely as high as 10(8) A/sq cm. Array current densities as high as 1000 A/sq cm have been measured. Total electron transit times from source to drain for 1 micron feature size devices have been predicted to be about 150fs. This very short transit time implies the possibility of submillimeter wave transmitters and rectennas in devices which can operate with reasonably high voltages and which are small in size and are lightweight. In addition, they are expected to be extremely radiation hard and very temperature insensitive. That is, they are expected to have radiation hardness characteristics similar to vacuum tubes, and both the high temperature and low temperature limits should be determined by the package. That is, there should be no practical intrinsic temperature or carrier freezeout problems for devices based on metals or composites. But the technology is difficult to implement at the present time because it is based on 300 to 500 angstrom radius field emitters which must be relatively uniform. There is also the need to understand the non-equilibrium transport physics in the near-surface regions of the field emitters.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 107-125
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  • 15
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    Pyro thruster for performing rocket booster attachment, disconnect, and jettison functions (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The concept of a pyro thruster, combining an automatic structural attachment with quick disconnect and thrusting capability, is described. The purpose of the invention is to simplify booster installation, disengagement, and jettison functions for the U.S. Air Force Advanced Launch Systems (ALS) program.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Marshall Space Flight Center, The 23rd Aerospace Mechanisms Symposium; p 157-167
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  • 16
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    Performance of Large Area Xenon Ion Thrusters for Orbit Transfer Missions (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Studies have indicated that xenon ion propulsion systems can enable the use of smaller earth-launch vehicles for satellite placement which results in significant cost savings. These analyses have assumed the availability of advanced, high power ion thrusters-operating at about 10 kW or higher. A program was initiated to explore the viability of operating 50 cm diameter ion thrusters at this power level. Operation with several discharge chamber and ion extraction grid set combinations was demonstrated and data were obtained at power levels to 16 kW. Fifty cm diameter thrusters using state of the art 30 cm diameter grids or advanced technology 50 cm diameter grids allow discharge power and beam current densities commensurate with long life at power levels up to 10 kW. In addition, 50 cm diameter thrusters are shown to have potential for growth in thrust and power levels beyond 10 kW.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 267-276
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  • 17
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    Power from space for use on earth: An emerging global option (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The concept of the Earth as a closed ecological system is addressed from the point of view of the availability and use of energy from space and its potential influence on the economies of both developed and developing countries. The results of past studies of the solar power satellite (SPS) are reviewed, and the current international activities exploring various aspects of an SPS are mentioned. The functions of an SPS, including collection of solar energy in orbit, conversion to an intermediate form of energy, transmission of energy from orbit to Earth, and conversion to useful energy in the most appropriate form are discussed. Directions for future developments are addressed including a suggested planning framework. Salient aspects of SPS technologies are presented, and the potential benefits of the uses of lunar materials for the SPS construction are outlined. Scenarios within the context of international participation in a global SPS system are presented. The conclusion is drawn that an SPS system is one of the few promising, globally applicable power generation options that has the potential to meet energy demands in the 21st Century and to achieve the inevitable transition to inexhaustible and renewable energy sources.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 57-68
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  • 18
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    Laser propulsion to earth orbit. Has its time come? (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Recent developments in high energy lasers, adaptive optics, and atmospheric transmission bring laser propulsion much closer to realization. Proposed here is a reference vehicle for study which consists of payload and solid propellant (e.g. ice). A suitable laser pulse is proposed for using a Laser Supported Detonation wave to produce thrust efficiently. It seems likely that a minimum system (10 Mw CO2 laser and 10 m dia. mirror) could be constructed for about $150 M. This minimum system could launch payloads of about 13 kg to a 400 km orbit every 10 minutes. The annual launch capability would be about 683 tons times the duty factor. Laser propulsion would be an order of magnitude cheaper than chemical rockets if the duty factor was 20 percent (10,000 launches/yr). Launches beyond that would be even cheaper. The chief problem which needs to be addressed before these possibilities could be realized is the design of a propellant to turn laser energy into thrust efficiently and to withstand the launch environment.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 41-56
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  • 19
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    Power beaming options (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Some large scale power beaming applications are proposed for the purpose of stimulating research. The first proposal is for a combination of large phased arrays on the ground near power stations and passive reflectors in geostationary orbit. The systems would beam excess electrical power in microwave form to areas in need of electrical power. Another proposal is to build solar arrays in deserts and beam the energy around the world. Another proposal is to use lasers to beam energy from earth to orbiting spacecraft.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 21-40
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  • 20
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    Office of exploration overview (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The NASA Office of Exploration case studies for FY89 are reviewed with regard to study ground rules and constraints. Three study scenarios are presented: lunar evolution, Mars evolution, and Mars expedition with emphasis on the key mission objectives.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 3-18
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  • 21
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    Involute composite design evaluation using global design sensitivity derivatives (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An optimization capability for involute structures has been developed. Its key feature is the use of global material geometry variables which are so chosen that all combinations of design variables within a set of lower and upper bounds correspond to manufacturable designs. A further advantage of global variables is that their number does not increase with increasing mesh density. The accuracy of the sensitivity derivatives has been verified both through finite difference tests and through the successful use of the derivatives by an optimizer. The state of the art in composite design today is still marked by point design algorithms linked together using ad hoc methods not directly related to a manufacturing procedure. The global design sensitivity approach presented here for involutes can be applied to filament wound shells and other composite constructions using material form features peculiar to each construction. The present involute optimization technology is being applied to the Space Shuttle SRM nozzle boot ring redesigns by PDA Engineering.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Recent Advances in Multidisciplinary Analysis and Optimization, Part 2; p 991-1008
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  • 22
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    Development of parallel algorithms for electrical power management in space applications (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The application of parallel techniques for electrical power system analysis is discussed. The Newton-Raphson method of load flow analysis was used along with the decomposition-coordination technique to perform load flow analysis. The decomposition-coordination technique enables tasks to be performed in parallel by partitioning the electrical power system into independent local problems. Each independent local problem represents a portion of the total electrical power system on which a loan flow analysis can be performed. The load flow analysis is performed on these partitioned elements by using the Newton-Raphson load flow method. These independent local problems will produce results for voltage and power which can then be passed to the coordinator portion of the solution procedure. The coordinator problem uses the results of the local problems to determine if any correction is needed on the local problems. The coordinator problem is also solved by an iterative method much like the local problem. The iterative method for the coordination problem will also be the Newton-Raphson method. Therefore, each iteration at the coordination level will result in new values for the local problems. The local problems will have to be solved again along with the coordinator problem until some convergence conditions are met.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lyndon B.; NASA, Lyndon B. John
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  • 23
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    On-orbit results of the LIPS 3/InP homojunction solar cell experiment (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The flight performance of the NASA indium phosphide homojunction cell module on the LIPS 3 satellite is presented. The experimental objectivewas to measure the InP cell performance in the natural radiation environment in a circular 1100 km altitude orbit inclined 60 degrees. Flight data for the first year is close to expected values. No degradation in the short-circuit current is seen. Details of cell structure and flight module design are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, European Space Power, Volume 2; p 759-764
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  • 24
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    The advanced photovoltaic solar array program (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The background and development status of an ultralightweight flexible-blanket flatpack, fold-out solar array is presented. It is scheduled for prototype demonstration in late 1989. The Advanced Photovoltaic Solar Array (APSA) design represents a critical intermediate milestone of the goal of 300 W/kg at beginning-of-life (BOL) with specific performance characteristics of 130 W/kg (BOL) and 100 W/kg at end-of-life (EOL) for a 10-year geosynchronous geostationary earth orbit 10-kW (BOL) space power system. The APSA wing design is scalable over a power range of 2 to 15 kW and is suitable for a full range of missions including Low Earth Orbit (LEO), orbital transfer from LEO to geostationary earth orbit and interplanetary flight.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, European Space Power, Volume 2; p 775-781
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  • 25
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    High power millimeter wave source development program (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: High power millimeter wave sources for fusion program; ECH source development program strategy; and 1 MW, 140 GHz gyrotron experiment design philosophy are briefly outlined. This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 153-157
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  • 26
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    Solar-pumped laser for free space power transmission (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Laser power transmission; laser systems; space-borne and available lasers; 2-D and 1 MW laser diode array systems; technical issues; iodine solar pumped laser system; and laser power transmission applications are presented. This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 137-152
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  • 27
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    The 10-100 kW submillimeter gyrotron (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: High frequency high harmonic gyrotrons; cyclotron autoresonance maser (CARM); CARM amplifier schematics; MIT electron gun; and baseline design for the 140 GHz CARM amplifier are briefly reviewed. This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 127-136
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  • 28
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    Free electron lasers driven by linear induction accelerators: High power radiation sources (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The technology of Free Electron Lasers (FELs) and linear induction accelerators (LIAs) is addressed by outlining the following topics: fundamentals of FELs; basic concepts of linear induction accelerators; the Electron Laser Facility (a microwave FEL); PALADIN (an infrared FEL); magnetic switching; IMP; and future directions (relativistic klystrons). This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 67-96
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  • 29
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    Operation of a step tunable megawatt gyrotron (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An electron cyclotron resonance maser; gyrotron fundamental oscillator; advantages of gyrotrons; a schematic of the experiment; gyrotron design theory; 1 MW design parameters; compact ignition tokamak; and a gyrotron with quasi-optical output coupler are briefly presented. This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 115-125
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  • 30
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    Large space systems antenna technology (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Program objectives; approach; surface characterization of large scale antennas; adaptive feed-multimode horn and array configuration; and technology benefits of CSEI program are outlined. This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 37-49
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    Millimeter wavelength rectenna development (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Rectennas were studied with the intent of converting the Earth's (black body) radiation into dc power for satellites in earth orbit. Power densities; metal-oxide-metal diodes; antenna design configurations; fluid patterns; substrate mounted antennas; and directions for future work are outlined. This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 19-35
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  • 32
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    Inflatable antennas for microwave pwoer transmission (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Operational phase of the inflatable radiator; inflatable space structures; advantages; inflated thin-film satellites; antenna configuration; 3 meter diameter test paraboloid (HAIR program); and weight breakdown for the 100 meter diameter reflector are outlined. This presentation is represented by viewgraphs only.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Lewis Research Center, Free-Space Power Transmission; p 51-65
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  • 33
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    Transient Pressure Test Article Test Program (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Transient Pressure Test Article (TPTA) test program is being conducted at a new test facility located in the East Test Area at the National Aeronautics and Space Administration's (NASA's) Marshall Space Flight Center (MSFC) in Huntsville, Alabama. This facility, along with the special test equipment (STE) required for facility support, was constructed specifically to test and verify the sealing capability of the Redesigned Solid Rocket Motor (RSRM) field, igniter, and nozzle joints. The test article consists of full scale RSRM hardware loaded with inert propellant and assembled in a short stack configuration. The TPTA is pressurized by igniting a propellant cartridge capable of inducing a pressure rise rate which stimulates the ignition transient that occurs during launch. Dynamic loads are applied during the pressure cycle to simulate external tank attach (ETA) strut loads present on the ETA ring. Sealing ability of the redesigned joints is evaluated under joint movement conditions produced by these combined loads since joint sealing ability depends on seal resilience velocity being greater than gap opening velocity. Also, maximum flight dynamic loads are applied to the test article which is either pressurized to 600 psia using gaseous nitrogen (GN2) or applied to the test article as the pressure decays inside the test article on the down cycle after the ignition transient cycle. This new test facility is examined with respect to its capabilities. In addition, both the topic of test effectiveness versus space vehicle flight performance and new aerospace test techniques, as well as a comparison between the old SRM design and the RSRM are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 35-43
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    A Perspective on the Use of Storable Propellants for Future Space Vehicle Propulsion (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Propulsion system configurations for future NASA and DOD space initiatives are driven by the continually emerging new mission requirements. These initiatives cover an extremely wide range of mission scenarios, from unmanned planetary programs, to manned lunar and planetary programs, to earth-oriented (Mission to Planet Earth) programs, and they are in addition to existing and future requirements for near-earth missions such as to geosynchronous earth orbit (GEO). Increasing space transportation costs, and anticipated high costs associated with space-basing of future vehicles, necessitate consideration of cost-effective and easily maintainable configurations which maximize the use of existing technologies and assets, and use budgetary resources effectively. System design considerations associated with the use of storable propellants to fill these needs are presented. Comparisons in areas such as complexity, performance, flexibility, maintainability, and technology status are made for earth and space storable propellants, including nitrogen tetroxide/monomethylhydrazine and LOX/monomethylhydrazine.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 219-228
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  • 35
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    Applicability of the beamed power concept to lunar rovers, construction, mining, explorers and other mobile equipment (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Some of the technical issues dealing with the feasibility of high power (10 Kw to 100 Kw) mobile manned equipment for settlement, exploration and exploitation of Lunar resources are addressed. Short range mining/construction equipment, a moderate range (50 Km) exploration vehicle, and an unlimited range explorer are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 343-356
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  • 36
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    Microwave beam power (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Information on microwave beam power is given in viewgraph form. Information is given on orbit transfer proulsion applications, costs of delivering 100 kWe of usable power, and costs of delivering a 1 kg payload into orbit.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 397-403
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    Power for the moon: Is microwave power beaming an option? (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Microwave power beaming options for powering lunar bases are presented in viewgraph form. Information is given on power dependent system masses, a solar source beam power system, a nuclear source beam power system, a three satellite beam power system, antenna configurations, and antenna design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 329-342
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  • 38
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    Arcjet Cathode Phenomena (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Cathode tips made from a number of different materials were tested in a modular arcjet thruster in order to examine cathode phenomena. Periodic disassembly and examination, along with the data collected during testing, indicated that all of the tungsten-based materials behaved similarly despite the fact that in one of these samples the percentage of thorium oxide was doubled and another was 25 percent rhenium. The mass loss rate from a 2 percent thoriated rhenium cathode was found to be an order of magnitude greater than that observed using 2 percent thoriated tungsten. Detailed analysis of one of these cathode tips showed that the molten crater contained pure tungsten to a depth of about 150 microns. Problems with thermal stress cracking were encountered in the testing of a hafnium carbide tip. Post test analysis showed that the active area of the tip had chemically reacted with the propellant. A 100 hour continuous test was run at about 1 kW. Post test analysis revealed no dendrite formation, such as observed in a 30 kW arcjet lifetest, near the cathode crater. The cathodes from both this test and a previously run 1000 hour cycled test displayed nearly identical arc craters. Data and calculations indicate that the mass losses observed in testing can be explained by evaporation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 349-366
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    Arcjet Nozzle Design Impacts (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The effect of nozzle configuration on the operating characteristics of a low power dc arcjet thruster was determined. A conical nozzle with a 30 deg converging angle, a 20 deg diverging angle, and an area ratio of 225 served as the baseline case. Variations on the geometry included bell-shaped contours both up and downstream, and a downstream trumpet-shaped contour. The nozzles were operated over a range of specific power near that anticipated for on-orbit operation. Mass flow rate, thrust, current, and voltage were monitored to provide accurate comparisons between nozzles. The upstream contour was found to have minimal effect on arcjet operation. It was determined that the contour of the divergent section of the nozzle, that serves as the anode, was very important in determining the location of arc attachment, and thus had a significant impact on arcjet performance. The conical nozzle was judged to have the optimal current/voltage characteristics and produced the best performance of the nozzles tested.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 367-380
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    Test Facility and Preliminary Performance of a 100 kW Class MPD Thruster (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A 260 kW magnetoplasmadynamic (MPD) thruster test facility was assembled and used to characterize thrusters at power levels up to 130 kW using argon and helium propellants. Sensitivities of discharge characteristics to arc current, mass flow rate, and applied magnetic field were investigated. A thermal efficiency correlation developed by others for low power MPD thrusters defined parametric guidelines to minimize electrode losses in MPD thrusters. Argon and helium results suggest that a parameter defined as the product of arc voltage and the square root of the mass flow rate must exceed 0.7 V/kg(sup 1/2)/sec(sup 1/2) in order to obtain thermal efficiencies in excess of 60 percent.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 325-338
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  • 41
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    Electric Propulsion Options for 10 kW Class Earth-Space Missions (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Five and 10 kW ion and arcjet propulsion system options for a near-term space demonstration experiment were evaluated. Analyses were conducted to determine first-order propulsion system performance and system component mass estimates. Overall mission performance of the electric propulsion systems was quantified in terms of the maximum thrusting time, total impulse, and velocity increment capability available when integrated onto a generic spacecraft under fixed mission model assumptions. Maximum available thrusting times for the ion-propelled spacecraft options, launched on a DELTA 2 6920 vehicle, range from approximately 8,600 hours for a 4-engine 10 kW system to more than 29,600 hours for a single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 1.2x10 (exp 7) to 2.1x10 (exp 7) N-s, and 3550 to 6200 m/s, respectively. Maximum available thrusting times for the arcjet propelled spacecraft launched on the DELTA 2 6920 vehicle range from approximately 528 hours for the 6-engine 10 kW hydrazine system to 2328 hours for the single-engine 5 kW system. Maximum total impulse values and maximum delta-v's range from 2.2x10 (exp 6) to 3.6x10 (exp 6) N-s, and approximately 662 to 1072 m/s, respectively.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 1989 JANNAF Propulsion Meeting, Volume 1; p 239-265
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    Low-earth-orbit to low-lunar-orbit laser freighter (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The objective of this mission study was to compare laser propulsion to chemical LOX/H2 and nuclear electric propulsion for the specific mission of delivering a 144-metric ton lunar base from low-Earth-orbit to low-lunar-orbit. The basis of comparison was total mass in low-Earth-orbit needed to accomplish this mission. The Office of Exploration approach to establishing the lunar base was to use two vehicles: a nuclear electric propulsion (NEP) vehicle to deliver cargo and a chemical vehicle to deliver humans. The NEP vehicle was reactor driven with a vehicle dry mass of 125 metric tons. The Office of Exploration study did not use chemical propulsion for cargo, but in the present study it was used for cargo for comparison to laser propulsion. This mission study assumes a high-power laser, either nuclear or solar electric-driven diode laser, is in orbit around Earth, beaming power to a laser propulsion vehicle. Laser power is only used for the LEO escape burn; other much lower-power burns are done with LOX/H2.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Second Beamed Space-Power Workshop; p 363-364
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    History and status of beamed power technology and applications at 2.45 Gigahertz (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Various applications of beamed power technology are discussed. An experimental microwave powered helicopter, rectenna technology, the use of the Solar Power Satellite to beam energy to Earth via microwaves, the use of cyclotron resonance devices, microwave powered airships, and electric propulsion are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center, Second Beamed Space-Power Workshop; p 171-185
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  • 44
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    Structural tailoring of Space Shuttle Main Engine turbopump blades SSME/STAEBL (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 421-425
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    Langmuir probe measurements of an arcjet exhaust (1989)
    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); 5; 287-294
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  • 46
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    Spacecraft and mission design for the SP-100 flight experiment (1989)
    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); 26; 109-115
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    Space Station Freedom resistojet system study (1989)
    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); 5; 694-702
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  • 48
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    Regenerative fuel cell systems for project pathfinder (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The objectives of a surface power program, an element of the exploration thrust of the Pathfinder project, and plans for meeting them are outlined. Technological assessment and tradeoff studies of fuel cell and electrolyzer technologies suitable for use in a regenerative fuel cell are described. The viability of proton exchange membranes (PEM) in meeting the system requirements is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, European Space Power, Volume 1; p 217-219
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    Advanced space power PEM fuel cell systems (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: A model showing mass and heat transfer in proton exchange membrane (PEM) single cells is presented. For space applications, stack operation requiring combined water and thermal management is needed. Advanced hardware designs able to combine these two techniques are available. Test results are shown for membrane materials which can operate with sufficiently fast diffusive water transport to sustain current densities of 300 ma per square centimeter. Higher power density levels are predicted to require active water removal.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, European Space Power, Volume 1; p 211-216
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    Challenges for future space power systems (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Forecasts of space power needs are presented. The needs fall into three broad categories: survival, self-sufficiency, and industrialization. The cost of delivering payloads to orbital locations and from Low Earth Orbit (LEO) to Mars are determined. Future launch cost reductions are predicted. From these projections the performances necessary for future solar and nuclear space power options are identified. The availability of plentiful cost effective electric power and of low cost access to space are identified as crucial factors in the future extension of human presence in space.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, European Space Power, Volume 1; p 133-136
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  • 51
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    Toward an electrical power utility for space exploration (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Future electrical power requirements for space exploration are discussed. Megawatts of power with enough reliability for multi-year missions and with enough flexibility to adapt to needs unanticipated at design time are some of the criteria which space power systems must be able to meet. The reasons for considering the power management and distribution in the various systems, from a total mission perspective rather than simply extrapolating current spacecraft design practice, are discussed. A utility approach to electric power integrating requirements from a broad selection of current development programs, with studies in which both space and terrestrial technologies are conceptually applied to exploration mission scenarios, is described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA, European Space Power, Volume 1; p 19-22
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  • 52
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    Design of a direct nuclear propulsion system for a resupply mission to Phobos (1989)
    In:  CASI
    Details
    Publication Date: 2017-03-17
    Description: For a long-term mission in space, a propulsion system with a high specific impulse and low mass must be designed. The system must also be safe in terms of human lives and must be cost efficient to a degree. The main focus is to design a direct nuclear propulsion system for a resupply mission to Phobos from an orbiting Earth space station and return. The design considered is an annular, packed particle bed nuclear reactor with hydrogen used as the reflector, moderator, coolant, and propellant. The use of hydrogen in all these areas helps reduce the total mass, since the amount of hydrogen required is only that needed for propulsion. The mass of hydrogen required for propulsion is reduced by using a direct nuclear propulsion system with a high specific impulse relative to a hydrogen oxygen system. Certain calculations were not looked at in great detail. This included the aerospace details of the mission. Most of the numbers for this section were found in tables and taken to be correct without extensive calculations. The main objective of the project was to study the thermohydraulic and neutronic aspects of the reactor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: USRA, NASA(USRA University Advanced Design Program Fifth Annual Summer Conference; p 195-200
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  • 53
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    Flight motor set 360T004 (STS-30R). Volume 1: System overview (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The fourth NASA space shuttle flight incorporating redesigned solid rocket motors began on 4 May 1989. The flight motors were designated 360Q004A (left-hand) and 360H004B (right-hand); the mission was designated STS-30R. Overall engine performance was excellent. The low sample rate data that was available showed exceptional propulsion performance. All ballistic and mass property parameters closely matched the predicted values and were well within the required contract end item specification levels that could be assessed. No strain, vibration, or aft skirt heating environments could be addressed due to developmental flight instrumentation deletion. Infrared readings from the shuttle thermal imager were considered very good when compared with ground environment instrumentation readings taken during both the aborted and the actual countdowns. However, hand-held infrared gun reading/ground environment instrumentation comparisons were considered poor during both countdowns, with the exception of the T - 3 hour timeframe during the actual launch. Postflight inspection again verified superior performance of the insulation, phenolics, metal parts, and seals. All combustion gas was contained by the insulation in the field and case-to-nozzle joints. Inadequate parachute performance on the left-hand booster caused high splashdown loads, which resulted in a displaced nozzle and factory joint weatherseal unbond anomalies. Recommendations were made concerning improved thermal modeling and instruments. The rationale for these recommendations, the dispositions of all anomalies, and complete result details are given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-184187 , NAS 1.26:184187 , TWR-17543-1-VOL-1 , PUBL-90089
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    Hybrid Propulsion Technology Program, phase 1. Volume 1: Executive summary (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The study program was contracted to evaluate concepts of hybrid propulsion, select the most optimum, and prepare a conceptual design package. Further, this study required preparation of a technology definition package to identify hybrid propulsion enabling technologies and planning to acquire that technology in Phase 2 and demonstrate that technology in Phase 3. Researchers evaluated two design philosophies for Hybrid Rocket Booster (HRB) selection. The first is an ASRM modified hybrid wherein as many components/designs as possible were used from the present Advanced Solid Rocket Motor (ASRM) design. The second was an entirely new hybrid optimized booster using ASRM criteria as a point of departure, i.e., diameter, thrust time curve, launch facilities, and external tank attach points. Researchers selected the new design based on the logic of optimizing a hybrid booster to provide NASA with a next generation vehicle in lieu of an interim advancement over the ASRM. The enabling technologies for hybrid propulsion are applicable to either and vehicle design may be selected at a downstream point (Phase 3) at NASA's discretion. The completion of these studies resulted in ranking the various concepts of boosters from the RSRM to a turbopump fed (TF) hybrid. The scoring resulting from the Figure of Merit (FOM) scoring system clearly shows a natural growth path where the turbopump fed solid liquid staged combustion hybrid provides maximized payload and the highest safety, reliability, and low life cycle costing.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183950 , NAS 1.26:183950
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    Hybrid Propulsion Technology Program, phase 1. Volume 2: Technical discussion (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Information on hybrid propulsion system concepts is given largely in the form of outlines, charts and graphs. Included are the concept definition, trade study data generation, concept evaluation and selection, conceptual design definition, and technology definition.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183951 , NAS 1.26:183951
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    Low thrust propulsion literature survey (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A literature search was performed to investigate the area of low thrust propulsion. In an effort to evaluate this technology, a number of articles, obtained through the use of the NASA-RECON database, were collected and categorized. The study indicates that although much was done, particularly in the 1960's and 1970's, more can be done in the area of practical navigation and guidance. It is suggested that the older studies be reinvestigated to see what potential there exists for future low thrust applications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-190179 , NAS 1.26:190179
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    Advanced NSTS propulsion system verification study (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The merits of propulsion system development testing are discussed. The existing data base of technical reports and specialists is utilized in this investigation. The study encompassed a review of all available test reports of propulsion system development testing for the Saturn stages, the Titan stages, and the Space Shuttle main propulsion system. The knowledge on propulsion system development and system testing available from specialists and managers was also 'tapped' for inclusion.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-184306 , NAS 1.26:184306
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    Probabilistic structural analysis methods of hot engine structures (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Development of probabilistic structural analysis methods for hot engine structures is a major activity at Lewis Research Center. Recent activities have focused on extending the methods to include the combined uncertainties in several factors on structural response. This paper briefly describes recent progress on composite load spectra models, probabilistic finite element structural analysis, and probabilistic strength degradation modeling. Progress is described in terms of fundamental concepts, computer code development, and representative numerical results.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ASME PAPER 89-GT-122
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    Power considerations for an early manned Mars mission utilizing the Space Station (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Power requirements and candidate electrical power sources were examined for the supporting space infrastructure for an early (2004) manned Mars mission. This two-year mission (60-day stay time) assumed a single six crew piloted vehicle with a Mars lander for four of the crew. The transportation vehicle was assumed to be a hydrogen/oxygen propulsion design with or without large aerobrakes and assembled and checked out on the LEO Space Station. The long transit time necessitated artificial gravity of the crew by rotating the crew compartments. This rotation complicates power source selection. Candidate power sources were examined for the Lander, Mars Orbiter, supporting Space Station, co-orbiting Propellant Storage Depot, and, alternatively, a co-orbiting Propellant Generation (water electrolysis) Depot. Candidates considered were photovoltaics with regenerative fuel cells or batteries, solar dynamics, isotope dynamics, and nuclear power.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AAS PAPER 87-223
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    Response of gravity level fluctuations on the Gravity Probe-B spacecraft propellant system (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Time-dependent computations have been performed to investigate the dynamical behaviors of fluid under a microgravity environment. A computer algorithm is introduced which can be used to simulate the fluid behavior in that environment, in particular the excitation of sloshing waves due to different gravity environments and rotation speeds. A suggestion on the proper handling and managing of cryogenic fluid propellant to be used in the Gravity Probe-B spacecraft propulsion is made.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 89-411
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    Space Station Freedom power management and distribution system design (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The design is described of the Space Station Freedom Power Management and Distribution (PMAD) System. In addition, the significant trade studies which were conducted are described, which led to the current PMAD system configuration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 89-078
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    The SP-100 space reactor as a power source for Mars exploration missions (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper argues that many of the power requirements of complex, relatively long-duration space missions such as the exploration of Mars may best be met through the use of power systems which use nuclear reactors as a thermal energy source. The development of such a power system, the SP-100, and its application in Mars mission scenarios is described. The missions addressed include a freighter mission and a mission involving exploration of the Martian surface.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AAS PAPER 87-224
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    Space Propulsion Hazards Analysis Manual (SPHAM), volume 2 (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Space Propulsion Hazards Analysis Manual (SPHAM) contains an exhaustive bibliography, hazardous properties information on selected space propulsion commodities, and system descriptions of various launch vehicles, upper stages, and spacecrafts.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: CPIA-PUBL-494-VOL-2 , NASA-CR-190872 , AD-A219608 , NAS 1.26:190872
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    Accuracy analysis of the space shuttle solid rocket motor profile measuring device (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Profile Measuring Device (PMD) was developed at the George C. Marshall Space Flight Center following the loss of the Space Shuttle Challenger. It is a rotating gauge used to measure the absolute diameters of mating features of redesigned Solid Rocket Motor field joints. Diameter tolerance of these features are typically + or - 0.005 inches and it is required that the PMD absolute measurement uncertainty be within this tolerance. In this analysis, the absolute accuracy of these measurements were found to be + or - 0.00375 inches, worst case, with a potential accuracy of + or - 0.0021 inches achievable by improved temperature control.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-101131 , NAS 1.15:101131 , PB90-148362 , NISTIR-89/4171
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    Dual-fuel, dual-mode rocket engine (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The invention relates to a dual fuel, dual mode rocket engine designed to improve the performance of earth-to-orbit vehicles. For any vehicle that operates from the earth's surface to earth orbit, it is advantageous to use two different fuels during its ascent. A high density impulse fuel, such as kerosene, is most efficient during the first half of the trajectory. A high specific impulse fuel, such as hydrogen, is most efficient during the second half of the trajectory. The invention allows both fuels to be used with a single rocket engine. It does so by adding a minimum number of state-of-the-art components to baseline single made rocket engines, and is therefore relatively easy to develop for near term applications. The novelty of this invention resides in the mixing of fuels before exhaust nozzle cooling. This allows all of the engine fuel to cool the exhaust nozzle, and allows the ratio of fuels used throughout the flight depend solely on performance requirements, not cooling requirements.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    An assessment of liquid propulsion in the United States (1989)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: The paper examines the status of liquid propulsion capability and technology in the U.S. today versus where it needs to be to satisfy proposed near and long term goals. Attention is given to four areas of liquid propulsion: earth-to-orbit propulsion, orbital transfer propulsion, on-orbit and planetary propulsion, and advanced propulsion. Recommendations on improving the state of liquid propulsion in the U.S. are presented.
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    Power from the Space Shuttle (1989)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: The use of the Space Shuttle to provide avionics and electrical power accommodations to a large dedicated payload and/or to multiple smaller payloads throughout the flight is studied. The payload equipment can be mounted in the Shuttle Orbiter aft flight deck and middeck portions of the crew cabins and in the Orbiter cargo bay. The Orbiter provides avionics services to the following major payload classes: the single-section payload, the small payload, the middeck payload, and the Get-Away Special payload.
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    Wave combustors for trans-atmospheric vehicles (1989)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: A performance analysis is given of a conceptual transatmospheric vehicle (TAV). The TAV is powered by a an oblique detonation wave engine (ODWE). The ODWE is an airbreathing hypersonic propulsion system which utilizes shock and detonation waves to enhance fuel-air mixing and combustion in supersonic flow. In this wave combustor concept, an oblique shock wave in the combustor can act as a flameholder by increasing the pressure and temperature of the air-fuel mixture, thereby decreasing the ignition delay. If the oblique shock is sufficiently strong, then the combustion front and the shock wave can couple into a detonation wave. In this case, combustion occurs almost instantaneously in a thin zone behind the wave front. The result is a shorter lighter engine compared to the scramjet. The ODWE-powered hypersonic vehicle performance is compared to that of a scramjet-powered vehicle. Among the results outlined, it is found that the ODWE trades a better engine performance above Mach 15 for a lower performance below Mach 15. The overall higher performance of the ODWE results in a 51,000-lb weight savings and a higher payload weight fraction of approximately 12 percent.
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    Preliminary base heating environments for a generalized ALS LO2/LH2 launch vehicle, appendix 1 and 2 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A secondary objective of contract NAS8-39141 is to provide base heating assessments, as required, to support Advanced Launch System (ALS) preliminary launch vehicle and propulsion system design studies. The ALS propulsion systems integration working group meeting (No. 3) recently completed in San Diego, California, focused attention on the need for base heating environment determination to provide preliminary requirements for LO2/LH2 propulsion systems currently being considered for ALS. We were requested to provide these environments for a range of possible propellant mixture and nozzle area ratios. Base heating environments can only be determined as a function of altitude when the engine operating conditions and vehicle base region geometry (engine arrangement) are known. If time dependent environments are needed to assess thermal loads, a trajectory must also be provided. These parameters are not fixed at this time since the ALS configurations and propulsion operating conditions are varied and continue to be studied by Phase B contractors. Therefore, for this study, a generalized LO2/LH2 system was selected along with a vehicle configuration consisting of a seven-engine booster and a three-engine core. MSFC provided guidance for the selection. We also selected a limited number of body points on the booster and core vehicles and engines for the environment estimates. Environments at these locations are representative of maximum heating conditions in the base region and are provided as a function of altitude only. Guidelines and assumptions for this assessment, methodology for determining the environments, and preliminary results are provided in this technical note. Refinements in the environments will be provided as the ALS design matures.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-192456 , NAS 1.26:192456 , RTN-218-01-APP-1-2 , RL-TR-91-61-ATT-9.1-APP-1-2
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    Space Shuttle Main Engine (SSME) Testing at Stennis Space Center (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Different views of Space Shuttle Main Engine test firings on all three test stands including closeup of engine, day, and night firings are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-109310 , NONP-NASA-VT-93-185327
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    Advanced Solid Rocket Motor (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This video tape describes the redesign and construction of the Advanced Solid Rocket Motor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: MSFC-14565 , NASA-TM-109658 , NONP-NASA-VT-93-190456
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  • 72
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    Fluid system design for a superfluid helium space tanker (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The design of a superfluid helium space tanker is described, which has the characteristics of minimum boil-off, low-g venting and maintenance of the superfluid state, transfer operations that include a pumping method, the additional fluid conditioning required during transfer, and a liquid acquisition system for transfer in a weightless environment. A concept for loading and ground conditioning of He, that simplifies launch operations and maximizes the quantity available at launch is presented. Configuration diagrams are included.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-0586
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    The effect of adaptive grid on hypersonic nozzle flow calculations (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Adaptive grid has been applied to the numerical study of generic hypersonic nozzles for the NASP vehicle to evaluate the effect of adaptive grid on solution accuracy. Several cases are calculated with and without adaptive grids; the numerical results are compared with experimental data wherever available, and with numerical results from other researchers. The present work shows that in most situations, especially when free shear layers and shocks exist in the flowfield, adaptive grid is essential in improving solution accuracy.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-0006
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    Modeling of impulsive propellant reorientation (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The impulsive propellant reorientation process is modeled using the Energy Calculations for Liquid Propellants in a Space Environment (ECLIPSE) code. A brief description of the process and the computational model is presented. Code validation is documented via comparison to experimentally derived data for small scale tanks. Predictions of reorientation performance are presented for two tanks designed for use in flight experiments and for a proposed full scale OTV tank. A new dimensionless parameter is developed to correlate reorientation performance in geometrically similar tanks. Its success is demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-0628
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    Verification of spatial and temporal pressure distributions in segmented solid rocket motors (1989)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A wide variety of analytical tools are in use today to predict the history and spatial distributions of pressure in the combustion chambers of solid rocket motors (SRMs). Experimental and analytical methods are presented here that allow the verification of many of these predictions. These methods are applied to the redesigned space shuttle booster (RSRM). Girth strain-gage data is compared to the predictions of various one-dimensional quasisteady analyses in order to verify the axial drop in motor static pressure during ignition transients as well as quasisteady motor operation. The results of previous modeling of radial flows in the bore, slots, and around grain overhangs are supported by approximate analytical and empirical techniques presented here. The predictions of circumferential flows induced by inhibitor asymmetries, nozzle vectoring, and propellant slump are compared to each other and to subscale cold air and water tunnel measurements to ascertain their validity.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-0298
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    Flight Set 360L002 (STS-27) field joint protection system, volume 7 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains the pre-launch functioning data of the Field Joint Protection System (JPS) used on STS-27. Also included is the post flight condition of the JPS components following the launch and recovery of the two redesigned solid rocket motors (RSRM) boosters. The JPS components are: (1) field joint heaters; (2) field joint sensors; (3) field joint moisture seal; (4) moisture seal Kevlar retaining straps; (5) field joint external insulation; (6) vent valve; (7) power cables; and (8) igniter heater.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183745-VOL-7 , NAS 1.26:183745-VOL-7 , TWR-17541-VOL-7 , ECS-SS-01010 , DR-3-5 , WBS-4B601
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    Igniter heater EMI transient test (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Testing to evaluate Redesigned Solid Rocket Motor igniter heater electromagnetic interference (EMI) effects on the Safe and Arm (S and A) device was completed. It was suspected that EMI generated by the igniter heater and it's associated electromechanical relay could cause a premature firing of the NASA Standard Initiators (NSIs) inside the S and A. The maximum voltage induced into the NSI fire lines was 1/4 of the NASA specified no-fire limit of one volt (SKB 26100066). As a result, the igniter heaters are not expected to have any adverse EMI effects on the NSIs. The results did show, however, that power switching causes occasional high transients within the igniter heater power cable. These transients could affect the sensitive equipment inside the forward skirt. It is therefore recommended that the electromechanical igniter heater relays be replaced with zero crossing solid state relays. If the solid state relays are installed, it is also recommended that they be tested for EMI transient effects.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183743 , NAS 1.26:183743 , TWR-18915
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    Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 3B: High pressure fuel turbo-pump preburner pump bearing assembly analysis (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The analysis performed on the High Pressure Oxidizer Turbopump (HPOTP) preburner pump bearing assembly located on the Space Shuttle Main Engine (SSME) is summarized. An ANSYS finite element model for the inlet assembly was built and executed. Thermal and static analyses were performed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183666 , NAS 1.26:183666 , LMSC-HEC-TR-F268584-VOL-3B
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    Investigation of the transient fuel preburner manifold and combustor (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computational fluid dynamics (CFD) model with finite rate reactions, FDNS, was developed to study the start transient of the Space Shuttle Main Engine (SSME) fuel preburner (FPB). FDNS is a time accurate, pressure based CFD code. An upwind scheme was employed for spatial discretization. The upwind scheme was based on second and fourth order central differencing with adaptive artificial dissipation. A state of the art two-equation k-epsilon (T) turbulence model was employed for the turbulence calculation. A Pade' Rational Solution (PARASOL) chemistry algorithm was coupled with the point implicit procedure. FDNS was benchmarked with three well documented experiments: a confined swirling coaxial jet, a non-reactive ramjet dump combustor, and a reactive ramjet dump combustor. Excellent comparisons were obtained for the benchmark cases. The code was then used to study the start transient of an axisymmetric SSME fuel preburner. Predicted transient operation of the preburner agrees well with experiment. Furthermore, it was also found that an appreciable amount of unburned oxygen entered the turbine stages.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183715 , NAS 1.26:183715 , SECA-89-10
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    Space station propulsion test bed (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A test bed was fabricated to demonstrate hydrogen/oxygen propulsion technology readiness for the intital operating configuration (IOC) space station application. The test bed propulsion module and computer control system were delivered in December 1985, but activation was delayed until mid-1986 while the propulsion system baseline for the station was reexamined. A new baseline was selected with hydrogen/oxygen thruster modules supplied with gas produced by electrolysis of waste water from the space shuttle and space station. As a result, an electrolysis module was designed, fabricated, and added to the test bed to provide an end-to-end simulation of the baseline system. Subsequent testing of the test bed propulsion and electrolysis modules provided an end-to-end demonstration of the complete space station propulsion system, including thruster hot firings using the oxygen and hydrogen generated from electrolysis of water. Complete autonomous control and operation of all test bed components by the microprocessor control system designed and delivered during the program was demonstrated. The technical readiness of the system is now firmly established.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183615 , NAS 1.26:183615 , RI/RD89-104
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    Qualification Motor no. 8 (QM-8), volume 1 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: All inspection and instrumentation data indicate that the QM-8 static test firing conducted 20 January 1989 was successful. Ambient temperature at T-0 was 28 F. With two flights successfully accomplished, this final test in the redesigned solid rocket motor (RSRM) program certified that the design meets motor performance requirements under extreme cold conditions. This test was a prerequisite to the third flight. The entire test article was cold conditioned at 20 to 25 F for approximately 31 days to assure a maximum propellant mean bulk temperature (PMBT) of 40 F, making it the lowest PMBT in the history of the program. This extreme condition also presented the opportunity to certify critical components at low temperatures. Certification of field joint and igniter heaters, adhesive bondline integrity, flex bearing performance, flight instrumentation performance, RSRM seal performance, and LSC and nozzle plug performance was accomplished. Prior to motor ignition, the field joints were maintained between 75 to 130 F, the igniter-to-case joint was maintained between 75 to 123 F, and the case-to-nozzle joint was maintained between 75 to 120 F. QM-8 was tested with induced side loads to simulate the strut loads experienced during ignition and maximum aerodynamic loading conditions. The ability of the safe and arm device to change position from safe-to-arm and arm-to-safe was certified. Ballistics performance was certified at the lower limits. Values were within specification requirements. Nozzle performance was nominal with typical erosion. The use of Fiberite carbon-cloth phenolic was certified. The water deluge system, CO2 quench, and other test equipment performed as planned during all required test operations.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183650 , NAS 1.26:183650 , TWR-17591-VOL-1 , PUBL-89605-VOL-1
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    Orbit transfer rocket engine technology program: Oxygen materials compatibility testing (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Particle impact and frictional heating tests of metals in high pressure oxygen, are conducted in support of the design of an advanced rocket engine oxygen turbopump. Materials having a wide range of thermodynamic properties including heat of combustion and thermal diffusivity were compared in their resistance to ignition and sustained burning. Copper, nickel and their alloys were found superior to iron based and stainless steel alloys. Some materials became more difficult to ignite as oxygen pressure was increased from 7 to 21 MPa (1000 to 3000 psia).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-182195 , NAS 1.26:182195 , REPT-CC0134
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    Combined microwave science and propulsion (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The combined use of high-power active science instruments and high-power electric propulsion is investigated with a view to new science opportunities and measurements on future planetary missions. An example of a comet rendezvous mission that could benefit from this combination is discussed. It was found that, with electric propulsion, the launch mass of the comet spacecraft could be reduced by 61-68 percent over the chemical propulsion baseline mission. This high-power spacecraft is also capable of delivering a significant high-power radar science payload to the comet.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-0513
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    Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 1: Aft Skirt analysis (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Using the ANSYS finite element program, a global model of the aft skirt and a detailed nonlinear model of the failure region was made. The analysis confirmed the area of failure in both STA-2B and STA-3 tests as the forging heat affected zone (HAZ) at the aft ring centerline. The highest hoop strain in the HAZ occurs in this area. However, the analysis does not predict failure as defined by ultimate elongation of the material equal to 3.5 percent total strain. The analysis correlates well with the strain gage data from both the Wyle influence test of the original design aft sjirt and the STA-3 test of the redesigned aft skirt. it is suggested that the sensitivity of the failure area material strength and stress/strain state to material properties and therefore to small manufacturing or processing variables is the most likely cause of failure below the expected material ultimate properties.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183663 , NAS 1.26:183663 , LMSC-HEC-TR-F268584-VOL-1
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    Performance estimates for the Space Station power system Brayton Cycle compressor and turbine (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The methods which have been used by the NASA Lewis Research Center for predicting Brayton Cycle compressor and turbine performance for different gases and flow rates are described. These methods were developed by NASA Lewis during the early days of Brayton cycle component development and they can now be applied to the task of predicting the performance of the Closed Brayton Cycle (CBC) Space Station Freedom power system. Computer programs are given for performing these calculations and data from previous NASA Lewis Brayton Compressor and Turbine tests is used to make accurate estimates of the compressor and turbine performance for the CBC power system. Results of these calculations are also given. In general, calculations confirm that the CBC Brayton Cycle contractor has made realistic compressor and turbine performance estimates.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-182263 , E-4657 , NAS 1.26:182263
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    Flow fields of low pressure vent exhausts (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flow field produced by low pressure gas vents are described based on experimental data obtained from tests in a large vacuum chamber. The gas density, pressure, and flux at any location in the flow field are calculated based on the vent plume description and the knowledge of the flow rate and velocity of the venting gas. The same parameters and the column densities along a specified line of sight traversing the plume are also obtained and shown by a computer-generated graphical representation. The fields obtained with a radially scanning Pitot probe within the exhausting gas are described by a power of the cosine function, the mass rate and the distance from the exit port. The field measurements were made for gas at pressures ranging from 2 to 50 torr venting from pipe fittings with diameters of 3/16 inch to 1-1/2 inches I.D. (4.76 mm to 38.1 mm). The N(2) mass flow rates ranged from 2E-4 to 3.7E-1 g/s.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100738 , NAS 1.15:100738 , REPT-89B00151
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    Field joint protection system rain qualification test report (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report documents the procedures, performance, and results obtained from the Field Joint Protection System (FJPS) rain test. This test was performed to validate that the flight configuration FJPS prevents the accumulation of moisture in the redesigned solid rocket motor (RSRM) field joints when subjected to simulated prelaunch natural rain environments. The FJPS test article was exposed to rain simulation for approximately 50 minutes. During the test, water entered through the open upper end of the systems tunnel and was funneled down between the tunnel and case. A sealant void at the moisture seal butt splice allowed this water to flow underneath the FJPS. The most likely cause of voids was improper bondline preparation, particularly on the moisture seal surface. In total, water penetrated underneath approximately 60 percent of the FJPS circumference. Because the test article was substantially different from flight configuration (no systems tunnel closeout), results of this test will not affect current flight motors. Due to the omission of systems tunnel covers and systems tunnel floor plate closeout, the test assembly was not representative of flight hardware and resulted in a gross overtest. It is therefore recommended that the test be declared void. It is also recommended that the test be repeated with a complete closeout of the systems tunnel, sealed systems tunnel ends, and improved adhesive bondline preparation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183702 , NAS 1.26:183702 , TWR-18076 , WBS-4B102-10-03 , ECS-SS-1323
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    Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 7: High pressure fuel turbo-pump third stage impeller analysis (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This volume summarizes the analysis used to assess the structural life of the Space Shuttle Main Engine (SSME) High Pressure Fuel Turbo-Pump (HPFTP) Third Stage Impeller. This analysis was performed in three phases, all using the DIAL finite element code. The first phase was a static stress analysis to determine the mean (non-varying) stress and static margin of safety for the part. The loads involved were steady state pressure and centrifugal force due to spinning. The second phase of the analysis was a modal survey to determine the vibrational modes and natural frequencies of the impeller. The third phase was a dynamic response analysis to determine the alternating component of the stress due to time varying pressure impulses at the outlet (diffuser) side of the impeller. The results of the three phases of the analysis show that the Third Stage Impeller operates very near the upper limits of its capability at full power level (FPL) loading. The static loading alone creates stresses in some areas of the shroud which exceed the yield point of the material. Additional cyclic loading due to the dynamic force could lead to a significant reduction in the life of this part. The cyclic stresses determined in the dynamic response phase of this study are based on an assumption regarding the magnitude of the forcing function.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183670 , NAS 1.26:183670 , LMSC-HEC-TR-F268584-VOL-7
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    Solar cell radiation handbook. Addendum 1: 1982-1988 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Solar Cell Radiation Handbook (JPL Publication 82-69) is updated. In order to maintain currency of solar cell radiation data, recent solar cell designs have been acquired, irradiated with 1 MeV electrons, and measured. The results of these radiation experiments are reported.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-185465 , JPL-PUBL-82-69-ADD-1 , NAS 1.26:185465
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  • 90
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    Advanced power system protection and incipient fault detection and protection of spaceborne power systems (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This research concentrated on the application of advanced signal processing, expert system, and digital technologies for the detection and control of low grade, incipient faults on spaceborne power systems. The researchers have considerable experience in the application of advanced digital technologies and the protection of terrestrial power systems. This experience was used in the current contracts to develop new approaches for protecting the electrical distribution system in spaceborne applications. The project was divided into three distinct areas: (1) investigate the applicability of fault detection algorithms developed for terrestrial power systems to the detection of faults in spaceborne systems; (2) investigate the digital hardware and architectures required to monitor and control spaceborne power systems with full capability to implement new detection and diagnostic algorithms; and (3) develop a real-time expert operating system for implementing diagnostic and protection algorithms. Significant progress has been made in each of the above areas. Several terrestrial fault detection algorithms were modified to better adapt to spaceborne power system environments. Several digital architectures were developed and evaluated in light of the fault detection algorithms.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-185330 , JSC10-86-8483 , NAS 1.26:185330
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  • 91
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    Flight set 360L003 instrumentation final test report, volume 9 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Post-flight instrumentation hardware and data evaluation for 360L003 is summarized. The 360L003 motors were equipped with Developmental Flight Instrumentation (DFI), Operational Flight Instrumentation (OFI), and Ground Environmental Instrumentation (GEI). The DFI was designed to measure strain, temperature, pressure, and vibration at various locations on the motor during flight. The DFI is used to validate engineering models in a flight environment. The OFI consists of six Operational Pressure Tranducers which monitor chamber pressure during flight. These pressure transducers are used in the SRB separation cue. GEI measures the motor case, igniter flange, and nozzle temperature prior to launch.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183675 , NAS 1.26:183675 , TWR-17542-VOL-9
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  • 92
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    An Evaluation of the General Dynamics 20 Khz 5 Kw Breadboard for Space Station Electrical Power at MSFC (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results and observations are discussed of tests made on the General Dynamics 20 kHz Breadboard for Space Station Electrical Power. The General Dynamics 20 kHz system only is considered, and not the issue of the use of 20 kHz ac Power for Spacecraft Applications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100367 , NAS 1.15:100367
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  • 93
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    Hybrid plume plasma rocket (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A technique for producing thrust by generating a hybrid plume plasma exhaust is disclosed. A plasma flow is generated and introduced into a nozzle which features one or more inlets positioned to direct a flow of neutral gas about the interior of the nozzle. When such a neutral gas flow is combined with the plasma flow within the nozzle, a hybrid plume is constructed including a flow of hot plasma along the center of the nozzle surrounded by a generally annular flow of neutral gas, with an annular transition region between the pure plasma and the neutral gas. The temperature of the outer gas layer is below that of the pure plasma and generally separates the pure plasma from the interior surfaces of the nozzle. The neutral gas flow both insulates the nozzle wall from the high temperatures of the plasma flow and adds to the mass flow rate of the hybrid exhaust. The rate of flow of neutral gas into the interior of the nozzle may be selectively adjusted to control the thrust and specific impulse of the device.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 94
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    Aerodynamic flight evaluation analysis and data base update (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Research was conducted to determine the feasibility of replacing the Solid Rocket Boosters on the existing Space Shuttle Launch Vehicle (SSLV) with Liquid Rocket Boosters (LRB). As a part of the LRB selection process, a series of wind tunnel tests were conducted along with aero studies to determine the effects of different LRB configurations on the SSLV. Final results were tabulated into increments and added to the existing SSLV data base. The research conducted in this study was taken from a series of wind tunnel tests conducted at Marshall's 14-inch Trisonic Wind Tunnel. The effects on the axial force (CAF), normal force (CNF), pitching moment (CMF), side force (CY), wing shear force (CSR), wing torque moment (CTR), and wing bending moment (CBR) coefficients were investigated for a number of candidate LRB configurations. The aero effects due to LRB protuberances, ET/LRB separation distance, and aft skirts were also gathered from the tests. Analysis was also conducted to investigate the base pressure and plume effects due to the new booster geometries. The test results found in Phases 1 and 2 of wind tunnel testing are discussed and compared. Preliminary LRB lateral/directional data results and trends are given. The protuberance and gap/skirt effects are discussed. The base pressure/plume effects study is discussed and results are given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183654 , NAS 1.26:183654 , LMSC-HEC-TR-F268592
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  • 95
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    Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 2: High pressure oxidizer turbo-pump turbine end bearing analysis (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The high-pressure oxidizer turbopump (HPOTP) consists of two centrifugal pumps, on a common shaft, that are directly driven by a hot-gas turbine. Pump shaft axial thrust is balanced in that the double-entry main inducer/impeller is inherently balanced and the thrusts of the preburner pump and turbine are nearly equal but opposite. Residual shaft thrust is controlled by a self-compensating, non-rubbing, balance piston. Shaft hang-up must be avoided if the balance piston is to perform properly. One potential cause of shaft hang-up is contact between the Phase 2 bearing support and axial spring cartridge of the HPOTP main pump housing. The status of the bearing support/axial spring cartridge interface is investigated under current loading conditions. An ANSYS version 4.3, three-dimensional, finite element model was generated on Lockheed's VAX 11/785 computer. A nonlinear thermal analysis was then executed on the Marshall Space Flight Center Engineering Analysis Data System (EADS). These thermal results were then applied along with the interference fit and bolt preloads to the model as load conditions for a static analysis to determine the gap status of the bearing support/axial spring cartridge interface. For possible further analysis of the local regions of HPOTP main pump housing assembly, detailed ANSYS submodels were generated using I-DEAS Geomod and Supertab (Appendix A).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183664 , NAS 1.26:183664 , LMSC-HEC-TR-F268584-VOL-2
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  • 96
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    Field joint environmental protection system vibration/pressurization qualification (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The procedures used and results obtained from vibration testing the redesigned solid rocket motor (RSRM) field joint environmental protection system (FJEPS), hereafter referred to as the joint protection system (JPS) are documented. The major purposes were to certify that the flight-designed JPS will withstand the dynamic environmental conditions of the redesigned solid rocket booster, and to certify that the cartridge check valve (vent valve) will relieve pressure build-up under the JPS during the initial 120 sec of flight. Also, an evaluation of the extruded cork insulation bonding was performed after the vibration testing.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183673 , NAS 1.26:183673 , TWR-17245 , MTI-PUBL-89343
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  • 97
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    Summary and evaluation of the Strategic Defense Initiative Space Power Architecture Study (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Space Power Architecture Study (SPAS) identified and evaluated power subsystem options for multimegawatt electric (MMWE) space based weapons and surveillance platforms for the Strategic Defense Initiative (SDI) applications. Steady state requirements of less than 1 MMWE are adequately covered by the SP-100 nuclear space power program and hence were not addressed in the SPAS. Four steady state power systems less than 1 MMWE were investigated with little difference between them on a mass basis. The majority of the burst power systems utilized H(2) from the weapons and were either closed (no effluent), open (effluent release) or steady state with storage (no effluent). Closed systems used nuclear or combustion heat source with thermionic, Rankine, turboalternator, fuel cell and battery conversion devices. Open systems included nuclear or combustion heat sources using turboalternator, magnetohydrodynamic, fuel cell or battery power conversion devices. The steady state systems with storage used the SP-100 or Star-M reactors as energy sources and flywheels, fuel cells or batteries to store energy for burst applications. As with other studies the open systems are by far the lightest, most compact and simplist (most reliable) systems. However, unlike other studies the SPAS studied potential platform operational problems caused by effluents or vibration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-102012 , E-4724 , NAS 1.15:102012
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  • 98
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    Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 6: Primary nozzle diffuser analysis (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The primary nozzle diffuser routes fuel from the main fuel valve on the Space Shuttle Main Engine (SSME) to the nozzle coolant inlet mainfold, main combustion chamber coolant inlet mainfold, chamber coolant valve, and the augmented spark igniters. The diffuser also includes the fuel system purge check valve connection. A static stress analysis was performed on the diffuser because no detailed analysis was done on this part in the past. Structural concerns were in the area of the welds because approximately 10 percent are in areas inaccessible by X-ray testing devices. Flow dynamics and thermodynamics were not included in the analysis load case. Constant internal pressure at maximum SSME power was used instead. A three-dimensional, finite element method was generated using ANSYS version 4.3A on the Lockheed VAX 11/785 computer to perform the stress computations. IDEAS Supertab on a Sun 3/60 computer was used to create the finite element model. Rocketdyne drawing number RS009156 was used for the model interpretation. The flight diffuser is denoted as -101. A description of the model, boundary conditions/load case, material properties, structural analysis/results, and a summary are included for documentation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183669 , NAS 1.26:183669 , LMSC-HEC-TR-F268584-VOL-6
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  • 99
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    Turbine rotor/stator flowfield analysis (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A numerical study of the unsteady aerodynamic and thermal environment associated with axial turbine stages is presented. Computations are performed using a modification of the ROTOR1 rotor/stator interaction code. Two different turbine states are analyzed: the first state of the United Technologies Research Center large scale rotating rig and the first state of the Space Shuttle main engine (SSME) high pressure fuel turbopump. Time-averaged blade midspan pressure and heat transfer profiles are calculated using the following different surface boundary conditions: adiabatic wall, prescribed wall temperature, and prescribed heat flux. Numerical solutions for the large scale rotating rig are compared with experimental data. Unsteady pressure envelopes are also presented for each geometry. In addition, instantaneous contours are plotted for the SSME configuration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183639 , NAS 1.26:183639 , LMSC-HEC-TR-F268519
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  • 100
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    SRB ascent aerodynamic heating design criteria reduction study, volume 2 (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data are presented for the wind tunnel interference heating factor data base, the timewise tabulated ascent design environments, and the timewise plotted environments comparing the REMTECH results to the Rockwell RI-IVBC-3 results.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183569 , NAS 1.26:183569 , RTR-090-01-VOL-2
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