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  • Other Sources  (267)
  • SPACECRAFT PROPULSION AND POWER  (267)
  • 2010-2014
  • 1995-1999
  • 1985-1989  (267)
  • 1987  (267)
  • 1
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    The 1987 advanced space design projects (1987)
    In:  CASI
    Details
    Publication Date: 2004-12-04
    Description: The topics addressed are: (1) phobos power plant; (2) fusion power/propulsion system; (3) surface power from an orbiting spacecraft; (4) RTG replacement; (5) MHD-thermoelectric burst reactor; (6) TAU Voyage power/propulsion device; (7) ESCAPE to ODYSSEY.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: USRA, Agenda of the Third Annual Summer Conference, NASA(USRA University Advanced Design Program; p 33
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  • 2
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    Opening up to the future in space with nuclear power (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The relationship between the exploration of space and the availability of abundant power supplies is discussed. It is proposed that nuclear power will be needed to satisfy the power demands of manufacturing facilities in LEO, and power demands for the year 2000 are projected to be 300 KW(e). The capabilities and development of the Space Station are described; the use of nuclear power for the Station and various reactor location configurations are studied. The power requirements that will be necessary for the development of lunar resource bases and the exploration of Mars and other planets are considered; the advantages of nuclear power are examined.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 3
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    Performance of high-area-ratio nozzle for a small rocket thruster (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 3; 329-333
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  • 4
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    Advanced propulsion activities in the USA (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An evaluation is made of technology development prospects for launch vehicle, orbit transfer vehicle, satellite, and planetary exploration spacecraft propulsion systems being contemplated by NASA and its research contractors. Attention is given to such electric propulsion systems as arcjet, pulsed plasma, ion, and resistojet thrusters, as well as to solar thermal heat exchanger powerplants, beamed energy propulsion systems, and ultra-advanced nuclear fission and fusion propulsion concepts.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 16; 357-366
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  • 5
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    NASA Growth Space Station missions and candidate nuclear/solar power systems (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A brief summary is presented of a NASA study contract and in-house investigation on Growth Space Station missions and appropriate nuclear and solar space electric power systems. By the year 2000 some 300 kWe will be needed for missions and housekeeping power for a 12 to 18 person Station crew. Several Space Station configurations employing nuclear reactor power systems are discussed, including shielding requirements and power transmission schemes. Advantages of reactor power include a greatly simplified Station orientation procedure, greatly reduced occultation of views of the earth and deep space, near elimination of energy storage requirements, and significantly reduced station-keeping propellant mass due to very low drag of the reactor power system. The in-house studies of viable alternative Growth Space Station power systems showed that at 300 kWe a rigid silicon solar cell array with NiCd batteries had the highest specific mass at 275 kg/kWe, with solar Stirling the lowest at 40 kg/kWe. However, when 10 year propellant mass requirements are factored in, the 300 kWe nuclear Stirling exhibits the lowest total mass.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 6
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    Space Station propulsion system technology (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Two propulsion systems have been selected for the Space Station: O/H rockets for high thrust applications and the multipropellant resistojets for low thrust needs. These thruster systems integrate very well with the fluid systems on the station. Both thrusters will utilize waste fluids as their source of propellant. The O/H rocket will be fueled by electrolyzed water and the resistojets will use stored waste gases from the environmental control system and the various laboratories. This paper presents the results of experimental efforts with O/H and resistojet thrusters to determine their performance and life capability.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Acta Astronautica (ISSN 0094-5765); 15; 673-683
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  • 7
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    Oxidation-resistant reflective surfaces for solar dynamic power generation in near earth orbit (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Reflective surfaces for Space Station power generation systems are required to withstand the atomic oxygen-dominated environment of near earth orbit. Thin films of platinum and rhodium, which are corrosion resistant reflective metals, have been deposited by ion beam sputter deposition onto various substrate materials. Solar reflectances were then measured as a function of time of exposure to a RF-generated air plasma.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Vacuum Science and Technology A (ISSN 0734-2101); 5; 2737-274
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  • 8
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    Probabilistic structural analysis methods for space propulsion system components (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The development of a three-dimensional inelastic analysis methodology for the Space Shuttle main engine (SSME) structural components is described. The methodology is composed of: (1) composite load spectra, (2) probabilistic structural analysis methods, (3) the probabilistic finite element theory, and (4) probabilistic structural analysis. The methodology has led to significant technical progress in several important aspects of probabilistic structural analysis. The program and accomplishments to date are summarized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Probabilistic Engineering Mechanics (ISSN 0266-8920); 2; 100-110
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  • 9
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    Some aspects of space propulsion with extraterrestrial resources (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Extraterrestrial resources for space processing of chemicals, in general, and propellants, in particular, are explored quantitatively. It is seen that, for several candidate space mission scenarios, space processing of both space resources and earth-carried resources can make decisive differences in the mission success for a given payload. To fix ideas and demonstrate trends, the specific case of water splitting to extract oxygen, discard (or use without storage) the resulting hydrogen, and burn earth-carried noncryogenic liquid fuel(s) in a simple rocket motor, designed for periodic thrusting, is treated in some detail. Experimental hardware is assembled and demonstrated to perform adequately, besides showing compactness of the space-packaged 'capsule' module that is self-contained. Building upon previous studies, the concept of in situ propellant production (ISPP) is reexamined in light of more recent energy and materials technologies. Missions to comets and Mars Sample Return are mentioned as candidate scenarios. The mission duration, reliability-repairability of hardware, resource availability in low earth orbit (LEO), and the thrust requirements are considered in turn. It is seen that space storage of hydrogen for extended durations (5-10 years) involves problems that require detailed studies, besides involving many presently unanswered issues. A study of the energy option in LEO and in deep space is developed in simple terms. The different solar, radioisotope, and nuclear power sources are mentioned. Storage and handling of raw and processed chemicals are considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 236-244
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  • 10
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    Manned spacecraft electrical power systems (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A brief history of the development of electrical power systems from the earliest manned space flights illustrates a natural trend toward a growth of electrical power requirements and operational lifetimes with each succeeding space program. A review of the design philosophy and development experience associated with the Space Shuttle Orbiter electrical power system is presented, beginning with the state of technology at the conclusion of the Apollo Program. A discussion of prototype, verification, and qualification hardware is included, and several design improvements following the first Orbiter flight are described. The problems encountered, the scientific and engineering approaches used to meet the technological challenges, and the results obtained are stressed. Major technology barriers and their solutions are discussed, and a brief Orbiter flight experience summary of early Space Shuttle missions is included. A description of projected Space Station power requirements and candidate system concepts which could satisfy these anticipated needs is presented. Significant challenges different from Space Shuttle, innovative concepts and ideas, and station growth considerations are discussed. The Phase B Advanced Development hardware program is summarized and a status of Phase B preliminary tradeoff studies is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE, Proceedings (ISSN 0018-9219); 75; 277-307
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  • 11
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    Analysis of mid-tropospheric Space Shuttle exhausted aluminum oxide particles (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Aluminum oxide particles from the exhaust of the Space Shuttle were collected immediately after the launch of the SEPEX mission and during the descent over the altitude interval of 7.6-4.6 km. The SEM examination revealed that the particles were spherical and ranged in diameter from about 0.1 micron to 10 microns. Results from the energy dispersive analysis (by an X-ray method) and of the particle chemistry (by electron spectroscopy) confirmed that the particles were predominantly composed of aluminum and oxygen. The particle size distribution of the Al2O3 was bimodal, with one observed peak centered near 2.0 microns; the other distribution mode centered at a diameter of less than 0.3 micron, but could not be accurately located. A mass median diameter was slightly less than 2 microns. Evaluation of ice nucleation activity revealed only a small fraction (about 1 ppm) of active ice nuclei among the Al2O3 particulates.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Atmospheric Environment (ISSN 0004-6981); 21; 5, 19
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  • 12
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    Space shuttle main engine vibration data base (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: In order to evaluate Space Shuttle Main Engine (SSME) vibration data without having to constantly replay analog tapes, the SSME Vibration Data Base was developed. This data base contains data that have been digitized at a high sample rate for the entire test duration. It provides quick and efficient recall capabilities for numerious computation and display routines. The data base components are described as well as some of the compution and display features.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: The 58th Shock and Vibration Symposium, Volume 1; p 353-359
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  • 13
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    High frequency data acquisition system for space shuttle main engine testing (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The high frequency data acquisition system developed for the Space Shuttle Main Engine (SSME) single engine test facility at the National Space Technology Laboratories is discussed. The real time system will provide engineering data for a complete set of SSME instrumentation (approx. 100 measurements) within 4 hours following engine cutoff, a decrease of over 48 hours from the previous analog tape based system.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: The 58th Shock and Vibration Symposium, Volume 1; p 349-352
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  • 14
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    Particle sizing in rocket motor studies utilizing hologram image processing (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A technique of obtaining particle size information from holograms of combustion products is described. The holograms are obtained with a pulsed ruby laser through windows in a combustion chamber. The reconstruction is done with a krypton laser with the real image being viewed through a microscope. The particle size information is measured with a Quantimet 720 image processing system which can discriminate various features and perform measurements of the portions of interest in the image. Various problems that arise in the technique are discussed, especially those that are a consequence of the speckle due to the diffuse illumination used in the recording process.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Ames Research Center, Automated Reduction of Data from Images and Holograms; p 589-606
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  • 15
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    Probabilistic structural analysis to evaluate the structural durability of SSME critical components (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: NASA Lewis Research Center is currently developing probabilistic structural analysis methods for select Space Shuttle Main Engine (SSME) structural components. Briefly, the deterministic, three-dimensional, inelastic analysis methodology developed under the Hot Section Technology (HOST) and R and T Base Programs is being augmented to accommodate the complex probabilistic loading spectra, the thermoviscoplastic material behavior, and the material degradation associated with the environment of space propulsion system structural components representative of the SSME such as turbine blades, transfer ducts, and liquid-oxygen posts. The development of probabilistic structural analysis methodology consists of the following program elements: (1) composite load spectra; (2) probabilistic structural analysis methods; (3) probabilistic finite element theory - new variational principles; and (4) probabilistic structural analysis application. In addition, the program includes deterministic analysis elements: (1) development of structural tailoring computer codes (SSME/STAEBL); (2) development of dynamic creep buckling/ratcheting theory; (3) evaluation of the dynamic characteristics of single-crystal SSME blades; (4) development of SSME blade damper technology; and (5) development of integrated boundary elements for hotfluid structure interaction.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 117-119
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  • 16
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    Propulsion estimation techniques (1987)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: A brief overview of statistical tools needed to perform post flight/test reconstruction of state variables is given. Linear regression, recursive linear regression, and the exact connection between the Kalman filter and linear regression are discussed. The regression connection is expected to serve as an aid in the application of a recently developed analytical method of flight reconstruction to single engine test firing data.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center, Research Reports: 1987 NASA(ASEE Summer Faculty Fellowship Program; 14 p
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  • 17
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    Equilibrium retention in the nozzle of oxygen hydrogen propulsion systems (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Arguments are presented for the retention of vibrational equilibrium of species in the nozzle of the Space Shuttle Main Engine which are especially applicable to water and the hydroxyl radical. It is shown that the reaction OH + HH yields HOH + H maintains equilibrium as well. This is used to relate OH to H, the temperature, and the oxidizer-to-fuel ratio.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Marshall Space Flight Center, Research Reports: 1987 NASA(ASEE Summer Faculty Fellowship Program; 26 p
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  • 18
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    Development of an integrated BEM (Boundary Element Mesh) for hot fluid-structure interaction (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A boundary integral representation for a coupled approach to fluid flow and solid deformation problems associated with the design of hot-section components such as those in the Space Shuttle Main Engine is discussed. The formulation is based on the fundamental analytical solution of the Navier-Stokes equation for fluid velocity in an infinite domain. This fundamental solution was obtained by decomposing a Navier-Stokes equation into vorticity and dilation transport equations. A boundary integral involving convolutions in time was then constructed in which the convective terms appear in the volume integral.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 219-222
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  • 19
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    SSME blade damper technology (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Before 1975 turbine blade damper designs were based on experience and very simple mathematical models. Failure of the dampers to perform as expected showed the need to gain a better understanding of the physical mechanism of friction dampers. Over the last 10 years research on friction dampers for aeronautical propulsion systems has resulted in methods to optimize damper designs. The first-stage turbine blades on the Space Shuttle Main Engine (SSME) high-pressure oxygen pump have experienced cracking problems due to excessive vibration. A solution is to incorporate a well-designed friction dampers to attenuate blade vibration. The subject study, a cooperative effort between NASA Lewis and Carnegie-Mellon University, represents an application of recently developed friction damper technology to the SSME high-pressure oxygen turbopump. The major emphasis was the contractor's design known as the two-piece damper. Damping occurs at the frictional interface between the top half of the damper and the underside of the platforms of the adjacent blades. The lower half of the damper is an air seal to retard airflow in the volume between blade necks.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 215-217
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  • 20
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    Structural tailoring using the SSME/STAEBL code (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Space Shuttle Main Engine/Structural Tailoring of Engine Blades (SSME/STAEBL) was developed by systematically modifying and enhancing the STAEBL code developed by Pratt and Whitney under contract to NASA Lewis Research Center. STAEBL was designed for application to gas turbine blade design. Typical design variables include blade thickness distribution and root chord. Typical constraints include resonance margins, root stress, and root to chord ratios. In this program, the blade is loaded by centrifugal forces only. Additions and modifications of STAEBL included in SSME/STAEBL include (1) thermal stress analysis; (2) gas dynamic (pressure) loads; (3) temperature dependent material and thermal properties; (4) forced vibrations; (5) tip displacement constraints; (6) single crystal material analysis; (7) blade cross section stacking offsets; and (8) direct time integration algorithm for transient dynamic response. Capabilities are also included which permit data transfer from finite element models and stand-alone analysis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 201-205
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  • 21
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    Probabilistic load model development and validation for composite load spectra for select space propulsion engines (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A major task of the program to develop an expert system to predict the loads on selected components of a generic space propulsion engine is the design development and application of a probabilitic loads model. This model is being developed in order to account for the random nature of the loads and assess the variable load ranges' effect on the engine performance. A probabilistic model has been developed. The model is based primarily on simulation methods, but also has a Gaussian algebra method (if all variables are near normal), a fast probability integrator routine (for the calculation of low probability events), and a separate, stand alone program for performing barrier crossing calculations. Each of these probabilistic methods has been verified with theoretical calculations using assumed distributional forms.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 189-199
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  • 22
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    Quantifying uncertainties in the structural response of SSME blades (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: To quantify the uncertainties associated with the geometry and material properties of a Space Shuttle Main Engine (SSME) turbopump blade, a computer code known as STAEBL was used. A finite element model of the blade used 80 triangular shell elements with 55 nodes and five degrees of freedom per node. The whole study was simulated on the computer and no real experiments were conducted. The structural response has been evaluated in terms of three variables which are natural frequencies, root (maximum) stress, and blade tip displacements. The results of the study indicate that only the geometric uncertainties have significant effects on the response. Uncertainties in material properties have insignificant effects.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 167-173
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  • 23
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    Probabilistic SSME blades structural response under random pulse loading (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The purpose is to develop models of random impacts on a Space Shuttle Main Engine (SSME) turbopump blade and to predict the probabilistic structural response of the blade to these impacts. The random loading is caused by the impact of debris. The probabilistic structural response is characterized by distribution functions for stress and displacements as functions of the loading parameters which determine the random pulse model. These parameters include pulse arrival, amplitude, and location. The analysis can be extended to predict level crossing rates. This requires knowledge of the joint distribution of the response and its derivative. The model of random impacts chosen allows the pulse arrivals, pulse amplitudes, and pulse locations to be random. Specifically, the pulse arrivals are assumed to be governed by a Poisson process, which is characterized by a mean arrival rate. The pulse intensity is modelled as a normally distributed random variable with a zero mean chosen independently at each arrival. The standard deviation of the distribution is a measure of pulse intensity. Several different models were used for the pulse locations. For example, three points near the blade tip were chosen at which pulses were allowed to arrive with equal probability. Again, the locations were chosen independently at each arrival. The structural response was analyzed both by direct Monte Carlo simulation and by a semi-analytical method.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 161-166
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  • 24
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    Advanced probabilistic method of development (1987)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: Advanced structural reliability methods are utilized on the Probabilistic Structural Analysis Methods (PSAM) project to provide a tool for analysis and design of space propulsion system hardware. The role of the effort at the University of Arizona is to provide reliability technology support to this project. PSAM computer programs will provide a design tool for analyzing uncertainty associated with thermal and mechanical loading, material behavior, geometry, and the analysis methods used. Specifically, reliability methods are employed to perform sensitivity analyses, to establish the distribution of a critical response variable (e.g., stress, deflection), to perform reliability assessment, and ultimately to produce a design which will minimize cost and/or weight. Uncertainties in the design factors of space propulsion hardware are described by probability models constructed using statistical analysis of data. Statistical methods are employed to produce a probability model, i.e., a statistical synthesis or summary of each design variable in a format suitable for reliability analysis and ultimately, design decisions.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 145-149
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  • 25
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    Liquid Engine Jet Atomization Workshop report (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The workshop was oriented to disclose information and unsettled problems to understand the fundamental physical mechanism of the droplet formation process. Based on presentation and discussion of results, recommendations were made which should lead to associated future activities. To accomplish this task, existing observations and experiments, contributing to the basic knowledge, providing data for analytical concept verification, and forming a basis for empirical correlations were solicited. Advanced analytical modeling methods or results from specific studies were requested as well as the experience and advice from injector designers. All effort is directed to advance current analytical techniques, simulating the flow behavior downstream of the injection elements in a liquid rocket combustion chamber. Such a tool can be used to optimize injector designs with respect to short length weight savings, wall material protection, or large heat energy transport to a regenerative cooling fluid, while simultaneously achieving the maximum specific impulse in performance. The liquid atomization process also forms a sound basis for combustion instability analysis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 351-353
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  • 26
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    A detailed description of the uncertainty analysis for high area ratio rocket nozzle tests at the NASA Lewis Research Center (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A preliminary uncertainty analysis was performed for the High Area Ratio Rocket Nozzle test program which took place at the altitude test capsule of the Rocket Engine Test Facility at the NASA Lewis Research Center. Results from the study establish the uncertainty of measured and calculated parameters required for the calculation of rocket engine specific impulse. A generalized description of the uncertainty methodology used is provided. Specific equations and a detailed description of the analysis is presented. Verification of the uncertainty analysis model was performed by comparison with results from the experimental program's data reduction code. Final results include an uncertainty for specific impulse of 1.30 percent. The largest contributors to this uncertainty were calibration errors from the test capsule pressure and thrust measurement devices.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 291-318
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  • 27
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    Modal survey of the space shuttle solid rocket motor using multiple input methods (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The ability to accurately characterize propellant in a finite element model is a concern of engineers tasked with studying the dynamic response of the Space Shuttle Solid Rocket Motor (SRM). THe uncertainties arising from propellant characterization through specimem testing led to the decision to perform a model survey and model correlation of a single segment of the Shuttle SRM. Multiple input methods were used to excite and define case/propellant modes of both an inert segment and, later, a live propellant segment. These tests were successful at defining highly damped, flexible modes, several pairs of which occured with frequency spacing of less than two percent.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-Marshall Space Flight Center, The 58th Shock and Vibration Symposium, Volume 1; p 155-167
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  • 28
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    Space station power system (1987)
    In:  CASI
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    Publication Date: 2013-08-31
    Description: The major requirements and guidelines that affect the space station configuration and power system are explained. The evolution of the space station power system from the NASA program development-feasibility phase through the current preliminary design phase is described. Several early station concepts are described and linked to the present concept. Trade study selections of photovoltaic system technologies are described in detail. A summary of present solar dynamic and power management and distribution systems is also given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Photovoltaic Research and Technology 1986. High Efficiency, Space Environment and Array Technology; p 321-332
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  • 29
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    Spacecraft 2000: The challenge of the future (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Considerable opportunity exists to improve the systems, subsystems, components, etc., included in the space station bus, the non-payload portion of the spacecraft. The steps followed to date, the challenges being faced by industry, and the progress toward establishing a new NASA initiative which will identify the technologies required to build spacecraft of the 21st century and which will implement the technology development/validation programs necessary are described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Photovoltaic Research and Technology 1986. High Efficiency, Space Environment and Array Technology; p 333-341
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    Space station electrical power system (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this paper is to describe the design of the Space Station Electrical Power System. This includes the Photovoltaic and Solar Dynamic Power Modules as well as the Power Management and Distribution System (PMAD). In addition, two programmatic options for developing the Electrical Power System will be presented. One approach is defined as the Enhanced Configuration and represents the results of the Phase B studies conducted by the NASA Lewis Research Center over the last two years. Another option, the Phased Program, represents a more measured approach to reaching about the same capability as the Enhanced Configuration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100140 , E-3692 , NAS 1.15:100140 , IAF-87-234
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    Recent developments in indium phosphide space solar cell research (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent developments and progress in indium phosphide solar cell research for space application are reviewed. Indium phosphide homojunction cells were fabricated in both the n+p and p+n configurations with total area efficiencies of 17.9 and 15.9% (air mass 0 and 25 C) respectively. Organometallic chemical vapor deposition, liquid phase epitaxy, ion implantation and diffusion techniques were employed in InP cell fabrication. A theoretical model of a radiation tolerant, high efficiency homojunction cell was developed. A realistically attainable AMO efficiency of 20.5% was calculated using this model with emitter and base doping of 6 x 10 to the 17th power and 5 x 10 the the 16th power/cu cm respectively. Cells of both configurations were irradiated with 1 MeV electrons and 37 MeV protons. For both proton and electron irradiation, the n+p cells are more radiation resistant at higher fluences than the p+n cells. The first flight module of four InP cells was assembled for the Living Plume Shield III satellite.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100139 , E-3690 , NAS 1.15:100139 , AIAA PAPER 87-9053
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  • 32
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    Water-propellant resistojets for man-tended platforms (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The selection of a propulsion system for a man-tended platform has been influenced by the planned use of resistojets for drag make-up on the manned space station. For that application a resistojet has been designed that is capable of operation with a wide variety of propellants, including water. The reasons for the selection of water as the propellant and the performance of water as a propellant are discussed. The man-tended platform and its mission requirements are described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100110 , E-3649 , NAS 1.15:100110 , IAF-87-259
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  • 33
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    Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced Earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus liquid hydrogen addition, and the addition of an aluminum/liquid hydrogen slurry on the theoretical performance of a PBAN solid propellant rocket. The space shuttle solid rocket booster was used as a reference point. All three quasi-hybrid systems theoretically offer higher specific impulse when compared with the space shuttle solid rocket boosters. However, based on operational and safety considerations, the quasi-hybrid rocket is not a practical choice for near-term Earth-to-orbit booster applications. Safety and technology issues pertinent to quasi-hybrid rocket systems are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-2751 , E-3554 , NAS 1.60:2751 , AIAA PAPER 87-2082
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  • 34
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    Composite load spectra for select space propulsion structural components (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of this program is to develop generic load models to simulate the composite load spectra (CLS) that are induced in space propulsion system components representative of the space shuttle main engines (SSME). These models are being developed through describing individual component loads with an appropriate mix of deterministic and state-of-the-art probabilistic models that are related to key generic variables. Combinations of the individual loads are used to synthesize the composite loads spectra. A second approach for developing the composite loads spectra load model simulation, the option portion of the contract will develop coupled models which combine the individual load models. Statistically varying coefficients of the physical models will be used to obtain the composite load spectra.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 175-187
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  • 35
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    Probabilistic Structural Analysis Methods (PSAM) for select space propulsion system structural components (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective is the development of several modular structural analysis packages capable of predicting the probabilistic response distribution for key structural variables such as maximum stress, natural frequencies, transient response, etc. The structural analysis packages are to include stochastic modeling of loads, material properties, geometry (tolerances), and boundary conditions. The solution is to be in terms of the cumulative probability of exceedance distribution (CDF) and confidence bounds. Two methods of probability modeling are to be included as well as three types of structural models - probabilistic finite-element method (PFEM); probabilistic approximate analysis methods (PAAM); and probabilistic boundary element methods (PBEM). The purpose in doing probabilistic structural analysis is to provide the designer with a more realistic ability to assess the importance of uncertainty in the response of a high performance structure. Probabilistic Structural Analysis Method (PSAM) tools will estimate structural safety and reliability, while providing the engineer with information on the confidence that should be given to the predicted behavior. Perhaps most critically, the PSAM results will directly provide information on the sensitivity of the design response to those variables which are seen to be uncertain.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Structural Integrity and Durability of Reusable Space Propulsion Systems; p 121-125
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  • 36
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    Langmuir probe surveys of an arcjet exhaust (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Electrostatic (Langmuir) probes of both spherical and cylindrical geometry have been used to obtain electron number density and temperature in the exhaust of a laboratory arcjet. The arcjet thruster operated on nitrogen and hydrogen mixtures to simulate fully decomposed hydrazine in a vacuum environment with background pressures less than 0.05 Pa. The exhaust appears to be only slightly ionized (less than 1 percent) with local plasma potentials near facility ground. The current-voltage characteristics of the probes indicate a Maxwellian temperature distribution. Plume data are presented as a function of arcjet operating conditions and also position in the exhaust.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89924 , E-3623 , NAS 1.15:89924 , AIAA PAPER 87-1950
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  • 37
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    Structural Integrity and Durability of Reusable Space Propulsion Systems (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A two-day conference on the structural integrity and durability of reusable space propulsion systems was held on May 12 and 13, 1987, at the NASA Lewis research Center. Aerothermodynamic loads; instrumentation; fatigue, fracture, and constitutive modeling; and structural dynamics were discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CP-2471 , E-3512 , NAS 1.55:2471
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  • 38
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    Vectorizable algorithms for adaptive schemes for rapid analysis of SSME flows (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An initial study into vectorizable algorithms for use in adaptive schemes for various types of boundary value problems is described. The focus is on two key aspects of adaptive computational methods which are crucial in the use of such methods (for complex flow simulations such as those in the Space Shuttle Main Engine): the adaptive scheme itself and the applicability of element-by-element matrix computations in a vectorizable format for rapid calculations in adaptive mesh procedures.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179082 , NAS 1.26:179082 , TR-87-03
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  • 39
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    EMC and power quality standards for 20-kHz power distribution (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Space Station Power Distribution System has been baselined as a sinusoidal single phase, 440 VRMS system. This system has certain unique characteristics directly affecting its application. In particular, existing systematic description and control documents were modified to reflect the high operating frequency. This paper will discuss amendments made on Mil STD 704 (Electrical Power Characteristics), and Mil STD 461-B (Electromagnetic Emission and Susceptibility Requirements for the Control of Electromagnetic Interference). In some cases these amendments reflect changes of several orders of magnitude. Implications and impacts of these changes are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89925 , E-3626 , NAS 1.15:89925 , AIAA PAPER 87-9355
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  • 40
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    Space station electric power system requirements and design (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An overview of the conceptual definition and design of the space station Electric Power System (EPS) is given. Responsibilities for the design and development of the EPS are defined. The EPS requirements are listed and discussed, including average and peak power requirements, contingency requirements, and fault tolerance. The most significant Phase B trade study results are summarized, and the design selections and rationale are given. Finally, the power management and distribution system architecture is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89889 , E-3577 , NAS 1.15:89889 , AIAA PAPER 87-9003
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  • 41
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    Coaxial tube array space transmission line characterization (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The coaxial tube array tether/transmission line used to connect an SP-100 nuclear power system to the space station was characterized over the range of reactor-to-platform separation distances of 1 to 10 km. Characterization was done with respect to array performance, physical dimensions and masses. Using a fixed design procedure, a family of designs was generated for the same power level (300 kWe), power loss (1.5 percent), and meteoroid survival probability (99.5 percent over 10 yr). To differentiate between vacuum insulated and gas insulated lines, two different maximum values of the E field were considered: 20 kV/cm (appropriate to vacuum insulation) and 50 kV/cm (compressed SF6). Core conductor, tube, bumper, standoff, spacer and bumper support dimensions, and masses were also calculated. The results of the characterization show mainly how transmission line size and mass scale with reactor-to-platform separation distance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89864 , E-3531 , NAS 1.15:89864
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  • 42
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    Effect of an oxygen plasma on uncoated thin aluminum reflecting films (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thin aluminum films were considered for use as a reflective surface for solar collectors on orbiting solar dynamic power systems. A matter of concern is the durability of such reflective coatings against oxidative attack by highly reactive neutral atomic oxygen, which is the predominate chemical specie in low Earth orbit. Research to date was aimed at evaluating the protective merit of thin dielectric coatings over the aluminum or other reflective metals. However, an uncoated aluminum reflector may self-protect by virtue of the oxide formed from its exposed surface, which constitutes a physical barrier to further oxidation. This possibility was investigated, and an attempt was made to characterize the effects of atomic oxygen on thin Al films using photomicrographs, scanning electron microscopy, spectrophotometry, Auger analysis, and mass measurements. Data collected in a parallel effort is discussed for its comparative value. The results of the investigation of uncoated aluminum supported the self-protection hypothesis, and importantly, it was found that long term specular reflectance for uncoated aluminum exceeded that of Al and Ag reflectors with dielectric coatings.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89882 , E-3564 , NAS 1.15:89882
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  • 43
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    Arcjet starting reliability: A multistart test on hydrogen/nitrogen mixtures (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An arcjet starting reliability test was performed to investigate one feasibility issue in the use of arcjets onboard a satellite for north-south stationkeeping. A 1 kW arcjet was run on hydrogen/nitrogen gas mixtures simulating decomposed hydrazine. A pulse width modulated power supply with an integral high voltage starting pulser was used for arc ignition and steady-state operation. The test was performed in four phases in order to determine if starting characteristics changed as a result of long term thruster operation. More than 300 successful starts were accumulated over an operating time of 18 hrs. Overall results indicate that there is a link between starting characteristics and long term thruster operation; however, the large number of starts had no effect on steady-state performance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89867 , E-3538 , NAS 1.15:89867 , AIAA PAPER 87-1061
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  • 44
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    Experimental study of low Reynolds number nozzles (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High-performance electrothermal thrusters operate in a low nozzle-throat Reynolds number regime. Under these conditions, the flow boundary layer occupies a large volume inside the nozzle, contributing to large viscous losses. Four nozzles (conical, bell, trumpet, and modified trumpet) and a sharp-edged orifice were evaluated over a Reynolds number range of 500 to 9000 with unheated nitrogen and hydrogen. The nozzles showed significant decreases in specific impulse efficiency with decreasing Reynolds number. At Reynolds numbers less than 1000, all four nozzles were probably filled with a large boundary layer. The discharge coefficient decreased with Reynolds number in the same manner as the specific impulse efficiency. The bell and modified trumpet nozzles had discharge coefficients 4 to 8 percent higher than those of the cone or trumpet nozzles. The Two-Dimensional Kinetics (TDK) nozzle analysis computer program was used to predict nozzle performance. The results were then compared to the experimental results in order to determine the accuracy of the program within this flow regime.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89858 , E-3526 , NAS 1.15:89858 , AIAA PAPER 87-0992
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  • 45
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    Arcjet component conditions through a multistart test (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low power, dc arcjet thruster was tested for starting reliability using hydrogen-nitrogen mixtures simulating the decomposition products of hydrazine. More than 300 starts were accumulated in phases with extended burn-in periods interlaced. A high degree of flow stabilization was built into the arcjet and the power supply incorporated both rapid current regulation and a high voltage, pulsed starting circuit. A nominal current level of 10 A was maintained throughout the test. Photomicrographs of the cathode tip showed a rapid recession to a steady-state operating geometry. A target of 300 starts was selected, as this represents significantly more than anticipated (150 to 240), in missions of 10 yr or less duration. Weighings showed no apparent mass loss. Some anode erosion was observed, particularly at the entrance to the constrictor. This was attributed to the brief period during startup the arc mode attachment point spends in the high pressure region upstream of the nozzle. Based on the results obtained, startup does not appear to be performance or life limiting for the number of starts typical of operational satellite applications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89857 , E-3525 , NAS 1.15:89857 , AIAA PAPER 87-1060
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  • 46
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    Experimental thrust performance of a high-area-ratio rocket nozzle (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the thrust performance attainable from high-area-ratio rocket nozzles. A modified Rao-contoured nozzle with an expansion area of 1030 was test fired with hydrogen-oxygen propellants at altitude conditions. The nozzle was also tested as a truncated nozzle, at an expansion area ratio of 428. Thrust coefficient and thrust coefficient efficiency values are presented for each configuration at various propellant mixture ratios (oxygen/fuel). Several procedural techniques were developed permitting improved measurement of nozzle performance. The more significant of these were correcting the thrust for the aneroid effects, determining the effective chamber pressure, and referencing differential pressure transducers to a vacuum reference tank.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-2720 , E-3236-1 , NAS 1.60:2720
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  • 47
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    Solar array flight experiment/dynamic augmentation experiment (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the objectives, design, testing, and data analyses of the Solar Array Flight Experiment/Dynamic Augmentation Experiment (SAFE/DAE) that was tested aboard Shuttle in September 1984. The SAFE was a lightweight, flat-fold array that employed a thin polyimide film (Kapton) as a substrate for the solar cells. Extension/retraction, dynamics, electrical and thermal tests, were performed. Of particular interest is the dynamic behavior of such a large lightweight structure in space. Three techniques for measuring and analyzing this behavior were employed. The methodology for performing these tests, gathering data, and data analyses are presented. The report shows that the SAFE solar array technology is ready for application and that new methods are available to assess the dynamics of large structures in space.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-2690 , NAS 1.60:2690
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  • 48
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    Comparison of two procedures for predicting rocket engine nozzle performance (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two nozzle performance prediction procedures which are based on the standardized JANNAF methodology are presented and compared for four rocket engine nozzles. The first procedure required operator intercedence to transfer data between the individual performance programs. The second procedure is more automated in that all necessary programs are collected into a single computer code, thereby eliminating the need for data reformatting. Results from both procedures show similar trends but quantitative differences. Agreement was best in the predictions of specific impulse and local skin friction coefficient. Other compared quantities include characteristic velocity, thrust coefficient, thrust decrement, boundary layer displacement thickness, momentum thickness, and heat loss rate to the wall. Effects of wall temperature profile used as an input to the programs was investigated by running three wall temperature profiles. It was found that this change greatly affected the boundary layer displacement thickness and heat loss to the wall. The other quantities, however, were not drastically affected by the wall temperature profile change.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89814 , E-3458 , NAS 1.15:89814
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  • 49
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    Conceptual design and integration of a space station resistojet propulsion assembly (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The resistojet propulsion module is designed as a simple, long life, low risk system offering operational flexibility to the space station program. It can dispose of a wide variety of typical space station waste fluids by using them as propellants for orbital maintenance. A high temperature mode offers relatively high specific impulse with long life while a low temperature mode can propulsively dispose of mixtures that contain oxygen or hydrocarbons without reducing thruster life or generating particulates in the plume. A low duty cycle and a plume that is confined to a small aft region minimizes the impacts on the users. Simple interfaces with other space station systems facilitate integration. It is concluded that there are no major obstacles and many advantages to developing, installing, and operating a resistojet propulsion module aboard the Initial Operational Capability (IOC) space station.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89847 , E-3483 , NAS 1.15:89847
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    Ignition overpressure study from solid rocket motor firings (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective was to investigate, through experimental means, the basic mechanisms influencing ignition overpressure and to determine ways to suppress ignition overpressure. Ignition overpressure was studied using solid rocket motors with geometry scaled at 1 percent of the Shuttle's Solid Rocket Boosters. Both water injection and aerosol foam were examined as a mean of reducing ignition overpressure. The results of the water injection tests indicate that a relatively small amount of water is sufficient to provide significant suppression. Of the flow rates tested, the lower water injection flow rates provided the best reduction of the ignition overpressure wave. Also, the test results show there is an optimum water flow rate range that provides the best suppression, and as this range is exceeded the effectiveness of water to reduce ignition overpressure is decreased. Aerosol foam provided very little reduction of ignition overpressure, but only small volumes of foam were used and further testing is necessary to determine its total effectiveness as a means of suppression.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-86587 , NAS 1.15:86587
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    High- and low-thrust propulsion systems for the space station (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of the Advanced Development program was to investigate propulsion options for the space station. Two options were investigated in detail: a high-thrust system consisting of 25 to 50 lbf gaseous oxygen/hydrogen rockets, and a low-thrust system of 0.1 lbf multipropellant resistojets. An effort is also being conducted to determine the life capability of hydrazine-fueled thrusters. During the course of this program, studies clearly identified the benefits of utilizing waste water and other fluids as propellant sources. The results of the H/O thruster test programs are presented and the plan to determine the life of hydrazine thrusters is discussed. The background required to establish a long-life resistojet is presented and the first design model is shown in detail.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-88877 , E-3285 , NAS 1.15:88877
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  • 52
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    Low Reynolds Number Nozzle Flow Study (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental study of low Reynolds number nozzle flow was performed. A brief comparison was made between some of the experimental performance data and performance predicted by a viscous flow code. The performance of 15, 20, and 25 deg conical nozzles, bell nozzles, and trumpet nozzles was evaluated with unheated nitrogen and hydrogen. The numerical analysis was applied to the conical nozzles only, using an existing viscous flow code that was based on a slender-channel approximation. Although the trumpet and 25 deg conical nozzles had slightly better performance at lower Reynolds numbers, it is unclear which nozzle is superior as all fell within the experimental error band. The numerical rssults were found to agree with experimental results for nitrogen and for some of the hydrogen data. Some code modification is recommended to improve confidence in the performance prediction.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100130 , E-3679 , NAS 1.15:100130
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    Space station propulsion system technology (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two propulsion systems have been selected for the space station: O/H rockets for high thrust applications and the multipropellant resistojets for low thrust needs. These thruster systems integrate very well with the fluid systems on the station. Both thrusters will utilize waste fluids as their source of propellant. The O/H rocket will be fueled by electrolyzed water and the resistojets will use stored waste gases from the environmental control system and the various laboratories. This paper presents the results of experimental efforts with O/H and resistojet thrusters to determine their performance and life capability.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100108 , E-3648 , NAS 1.15:100108
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    Technology for satellite power conversion (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Components were examined that will be needed for high frequency rectenna devices. The majority of the effort was spent on measuring the directivity and efficiency of the half-wave dipole antenna. It is felt that the antenna and diode should be roughly optimized before they are combined into a rectenna structure. An integrated low pass filter had to be added to the antenna structure in order to facilitate the field pattern measurements. A calculation was also made of the power density of the Earth's radiant energy as seen by satellites in Earth orbit. Finally, the feasibility of using a Metal-Oxide-Metal (MOM) diode for rectification of the received power was assessed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-181057 , A-3244 , NAS 1.26:181057
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    The NASA/USAF arcjet research and technology program (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Direct current arcjets have the potential to provide specific impulses greater than 500 sec with storable propellants, and greater than 1000 sec with hydrogen. This level of performance can provide significant benefits for such applications as orbit transfer, station keeping, orbit change, and maneuvering. The simplicity of the arcjet system and its elements of commonality with state-of-the-art resistojet systems offer a relatively low risk transition to these enhanced levels of performance for low power (0.5 to 1.5 kW) station keeping applications. Arcjets at power levels of 10 to 30 kW are potentially applicable to orbit transfer missions. Furthermore, with the anticipated development of space nuclear power systems, arcjets at greater than 100 kW may become attractive. This paper describes the ongoing NASA/USAF program and describes major recent accomplishments.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100112 , E-3656 , NAS 1.15:100112 , AIAA PAPER 87-1946
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    In-situ analysis of hydrazine decomposition products (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A gas analyzer utilizing a nondispersive infrared (NDIR) detection system was used to monitor the ammonia and water vapor content of the products of a previously unused hydrazine gas generator. This provided an in-situ measurement of the generator's efficiency difficult to obtain by other means. The analyzer was easily installed in both the calibration and hydrazine systems, required no maintenance other than periodic zero adjustments, and performed well for extended periods in the operating range tested. The catalyst bed operated smoothly and repeatably during the 28 hr of testing. No major transients were observed on startup or during steady state operation. The amount of ammonia in the output stream of the gas generator was found to be a strong function of temperature at catalyst bed temperatures below 450 C. At temperatures above this, the efficiency remained nearly constant. On startup the gas generator efficiency was found to decrease with time until a steady state value was attained. Elevated catalyst bed temperatures in the periods before steady state operation was found to be responsible for this phenomenon.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89916 , E-3609 , NAS 1.15:89916 , AIAA PAPER 87-2122
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    Potential propellant storage and feed systems for space station resistojet propulsion options (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The resistojet system has been defined as part of the baseline propulsion system for the initial Operating Capability Space Station. The resistojet propulsion module will perform a reboost function using a wide variety of fluids as propellants. There are many optional propellants and propellant combinations for use in the resistojet including (but not limited to): hydrazine, hydrogen, oxygen, nitrogen, water, carbon dioxide, and methane. Many different types of propulsion systems have flown or have been conceptualized that may have application for use with resistojets. This paper describes and compares representative examples of these systems that may provide a basis for space station resistojet system design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179457 , E-3366 , NAS 1.26:179457
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    The survivability of large space-borne reflectors under atomic oxygen and micrometeoroid impact (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Solar dynamic power system mirrors for use on space station and other spacecraft flown in low Earth orbit (LEO) are exposed to the harshness of the LEO environment. Both atomic oxygen and micrometeoroids/space debris can degrade the performance of such mirrors. Protective coatings will be required to protect oxidizable reflecting media, such as silver and aluminum, from atomic oxygen attack. Several protective coating materials have been identified as good candidates for use in this application. The durability of these coating/mirror systems after pinhole defects have been inflicted during their fabrication and deployment or through micrometeoroid/space debris impact once on-orbit is of concern. Studies of the effect of an oxygen plasma environment on protected mirror surfaces with intentionally induced pinhole defects have been conducted at NASA Lewis and are reviewed. It has been found that oxidation of the reflective layer and/or the substrate in areas adjacent to a pinhole defect, but not directly exposed by the pinhole, can occur.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-88914 , E-3338 , NAS 1.15:88914
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    A detailed description of the uncertainty analysis for High Area Ratio Rocket Nozzle tests at the NASA Lewis Research Center (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A preliminary uncertainty analysis has been performed for the High Area Ratio Rocket Nozzle test program which took place at the altitude test capsule of the Rocket Engine Test Facility at the NASA Lewis Research Center. Results from the study establish the uncertainty of measured and calculated parameters required for the calculation of rocket engine specific impulse. A generalized description of the uncertainty methodology used is provided. Specific equations and a detailed description of the analysis are presented. Verification of the uncertainty analysis model was performed by comparison with results from the experimental program's data reduction code. Final results include an uncertainty for specific impulse of 1.30 percent. The largest contributors to this uncertainty were calibration errors from the test capsule pressure and thrust measurement devices.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100203 , E-3799 , NAS 1.15:100203
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  • 60
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    Control considerations for high frequency, resonant, power processing equipment used in large systems (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Addressed is a class of resonant power processing equipment designed to be used in an integrated high frequency (20 KHz domain), utility power system for large, multi-user spacecraft and other aerospace vehicles. It describes a hardware approach, which has been the basis for parametric and physical data used to justify the selection of high frequency ac as the PMAD baseline for the space station. This paper is part of a larger effort undertaken by NASA and General Dynamics to be sure that all potential space station contractors and other aerospace power system designers understand and can comfortably use this technology, which is now widely used in the commercial sector. In this paper, we will examine control requirements, stability, and operational modes; and their hardware impacts from an integrated system point of view. The current space station PMAD system will provide the overall requirements model to develop an understanding of the performance of this type of system with regard to: (1) regulation; (2) power bus stability and voltage control; (3) source impedance; (4) transient response; (5) power factor effects, and (6) limits and overloads.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89926 , E-3629 , NAS 1.15:89926 , AIAA PAPER 87-9353
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    Space station WP-04 power system. Volume 2: Study results (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of the phase B study contract for the definition of the space station Electric Power System (EPS) are presented in detail along with backup information and supporting data. Systems analysis and trades, preliminary design, advanced development, customer accommodations, operations planning, product assurance, and design and development phase planning are addressed. The station design is a hybrid approach which provides user power of 25 kWe from the photovoltaic subsystem and 50 kWe from the solar dynamic subsystem. The electric power is distributed to users as a utility service; single phase at a frequency of 20 kHz and voltage of 440VAC. The solar array NiH2 batteries of the photovoltaic subsystem are based on commonality to those used on the co-orbiting and solar platforms.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179587-VOL-2 , NAS 1.26:179587-VOL-2 , FSR-DR-15-VOL-2
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  • 62
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    Space station WP-04 power system. Volume 1: Executive summary (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Major study activities and results of the phase B study contract for the preliminary design of the space station Electrical Power System (EPS) are summarized. The areas addressed include the general system design, man-tended option, automation and robotics, evolutionary growth, software development environment, advanced development, customer accommodations, operations planning, product assurance, and design and development phase planning. The EPS consists of a combination photovoltaic and solar dynamic power generation subsystem and a power management and distribution (PMAD) subsystem. System trade studies and costing activities are also summarized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179587-VOL-1 , NAS 1.26:179587-VOL-1 , FSR-DR-15-VOL-1
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  • 63
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    Low power arcjet thruster pulse ignition (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the pulse ignition characteristics of a 1 kW class arcjet using an inductive energy storage pulse generator with a pulse width modulated power converter identified several thruster and pulse generator parameters that influence breakdown voltage including pulse generator rate of voltage rise. This work was conducted with an arcjet tested on hydrogen-nitrogen gas mixtures to simulate fully decomposed hydrazine. Over all ranges of thruster and pulser parameters investigated, the mean breakdown voltages varied from 1.4 to 2.7 kV. Ignition tests at elevated thruster temperatures under certain conditions revealed occasional breakdowns to thruster voltages higher than the power converter output voltage. These post breakdown discharges sometimes failed to transition to the lower voltage arc discharge mode and the thruster would not ignite. Under the same conditions, a transition to the arc mode would occur for a subsequent pulse and the thruster would ignite. An automated 11 600 cycle starting and transition to steady state test demonstrated ignition on the first pulse and required application of a second pulse only two times to initiate breakdown.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100123 , E-3645 , NAS 1.15:100123
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  • 64
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    Low power DC arcjet operation with hydrogen/nitrogen/ammonia mixtures (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of gas composition and ambient pressure on arcjet operation was determined. Arcjet operation in different facilities was also compared to determine the validity of tests in small facilities. Volt-ampere characteristics were determined for an arcjet using hydrogen/nitrogen mixtures (simulating both ammonia and hydrazine), hydrogen/nitrogen/ammonia mixtures, and pure ammonia as propellants at various flow rates. The arcjet had a typical performance of 450 sec specific impulse at 1 kW with hydrogen/nitrogen mixures. It was determined that the amount of ammonia present in the gas stream had a significant effect on the arcjet volt-ampere characteristics. Also, hydrogen/nitrogen mixtures simulating ammonia gave arc characteristics approximately the same as those of pure ammonia. Finally, no differences in arc volt-ampere characteristics were seen between low and high ambient pressure operation in the same facility. A 3 to 5 V difference was seen when different facilities were compared, but this difference was probably due to differences in the voltage drops across the current connections, and not due to arcjet operational differences in the two facilities.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89876 , E-3553 , NAS 1.15:89876 , AIAA PAPER 87-1948
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    Electromagnetic emission experiences using electric propulsion systems: A survey (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As electric propulsion systems become ready to integrate with spacecraft systems, the impact of propulsion system radiated emissions are of significant interest. Radiated emissions from electromagnetic, electrostatic, and electrothermal systems have been characterized and results synopsized from the literature describing 21 space flight programs. Electromagnetic radiated emission results from ground tests and flight experiences are presented with particular attention paid to the performance of spacecraft subsystems and payloads during thruster operations. The impacts to transmission of radio frequency signals through plasma plumes are also reviewed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100120 , E-3618 , NAS 1.15:100120 , AIAA PAPER 87-2028
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    Impact of thermal energy storage properties on solar dynamic space power conversion system mass (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 16 parameter solar concentrator/heat receiver mass model is used in conjunction with Stirling and Brayton Power Conversion System (PCS) performance and mass computer codes to determine the effect of thermal energy storage (TES) material property changes on overall PCS mass as a function of steady state electrical power output. Included in the PCS mass model are component masses as a function of thermal power for: concentrator, heat receiver, heat exchangers (source unless integral with heat receiver, heat sink, regenerator), heat engine units with optional parallel redundancy, power conditioning and control (PC and C), PC and C radiator, main radiator, and structure. Critical TES properties are: melting temperature, heat of fusion, density of the liquid phase, and the ratio of solid-to-liquid density. Preliminary results indicate that even though overalll system efficiency increases with TES melting temperature up to 1400 K for concentrator surface accuracies of 1 mrad or better, reductions in the overall system mass beyond that achievable with lithium fluoride (LiF) can be accomplished only if the heat of fusion is at least 800 kJ/kg and the liquid density is comparable to that of LiF (1880 kg/cu m.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89909 , E-3601 , NAS 1.15:89909 , AIAA PAPER 87-9442
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    Studies and analyses of the space shuttle main engine: High-pressure oxidizer turbopump failure information propagation model (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The high-pressure oxidizer turbopump (HPOTP) failure information propagation model (FIPM) is presented. The text includes a brief discussion of the FIPM methodology and the various elements which comprise a model. Specific details of the HPOTP FIPM are described. Listings of all the HPOTP data records are included as appendices.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179079 , NAS 1.26:179079 , BCD-SSME-TR-87-1
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  • 68
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    Space station resistojet system requirements and interface definition study (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preliminary resistojet design requirements were established based on initial technical requirements imposed by the results of NASA and Rocketdyne studies. The requirements are directed toward long life, simplicity, flexibility, and commonality with other space station components. The resistojet assembly is comprised of eight resistojets, fluid components downstream of the waste fluid storage system, a power controller, structure, and shielding. It consists of two identical subassemblies, one of which is redundant. Each subassembly consists of four 500-W resistojets, series redundant latch values, a power controller, a water vaporizer, two pressure regulators, filters, check valves, disconnects, fluid tubing, and electrical cables. All components are packaged at the end of the stinger aft of the JEM and Columbus modules. Different flow and power control methods were studied. A constant inlet pressure and a two-power setting controller were tentatively selected based on simplicity and reasonably high specific impulse for the range of waste gas compositions that are anticipated. The constant pressure is supplied by pressure regulators. The two set point power control includes individual power supplies to each resistojet heater and water vaporizer. An embedded data processor, a multiplexer-demultiplexer, and a network interface unit that are standard space station components are included in the power controller. The total dry weight of the resistojet assembly is approximately 172 lb. The total cost for design, development, test, evaluation, qualification, and flight hardware is estimated to be $16 million.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179581 , NAS 1.26:179581 , RI/RD87-109
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    Statistical analysis of 59 inspected SSME HPFTP turbine blades (uncracked and cracked) (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The numerical results of statistical analysis of the test data of Space Shuttle Main Engine high pressure fuel turbopump second-stage turbine blades, including some with cracks are presented. Several statistical methods use the test data to determine the application of differences in frequency variations between the uncracked and cracked blades.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-86584 , NAS 1.15:86584
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  • 70
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    Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 1030:1 carbon steel, heat-sink nozzle was tested. The test conditions included a nominal chamber pressure of 2413 kN/sq m and a mixture ratio range of 2.78 to 5.49. The propellants were gaseous oxygen and gaseous hydrogen. Outer wall temperature measurements were used to calculate the inner wall temperature and the heat flux and heat rate to the nozzle at specified axial locations. The experimental heat fluxes were compared to those predicted by the Two-Dimensional Kinetics (TDK) computer model analysis program. When laminar boundary layer flow was assumed in the analysis, the predicted values were within 15% of the experimental values for the area ratios of 20 to 975. However, when turbulent boundary layer conditions were assumed, the predicted values were approximately 120% higher than the experimental values. A study was performed to determine if the conditions within the nozzle could sustain a laminar boundary layer. Using the flow properties predicted by TDK, the momentum-thickness Reynolds number was calculated, and the point of transition to turbulent flow was predicted. The predicted transition point was within 0.5 inches of the nozzle throat. Calculations of the acceleration parameter were then made to determine if the flow conditions could produce relaminarization of the boundary layer. It was determined that if the boundary layer flow was inclined to transition to turbulent, the acceleration conditions within the nozzle would tend to suppress turbulence and keep the flow laminar-like.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-2726 , E-3558 , NAS 1.60:2726 , AIAA PAPER 87-2070
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    Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m2 (350 psia) (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The joint Army. Navy, NASA. Air Force (JANNAF) rocket engine peformnace prediction procedure is based on the use of various reference computer programs. One of the reference programs for nozzle analysis is the Two-Dimensional Kinetics (TDK) Program. The purpose of this report is to calibrate the JANNAF procedure incorporated into the December l984 version of the TDK program for the high-area-ratio rocket engine regime. The calibration was accomplished by modeling the performance of a 1030:1 rocket nozzle tested at NASA Lewis Research Center. A detailed description of the experimental test conditions and TDK input parameters is given. The results show that the computer code predicts delivered vacuum specific impulse to within 0.12 to 1.9 percent of the experimental data. Vacuum thrust coefficient predictions were within + or - 1.3 percent of experimental results. Predictions of wall static pressure were within approximately + or - 5 percent of the measured values. An experimental value for inviscid thrust was obtained for the nozzle extension between area ratios of 427.5 and 1030 by using an integration of the measured wall static pressures. Subtracting the measured thrust gain produced by the nozzle between area ratios of 427.5 and 1030 from the inviscid thrust gain yielded experimental drag decrements of 10.85 and 27.00 N (2.44 and 6.07 lb) for mixture ratios of 3.04 and 4.29, respectively. These values correspond to 0.45 and 1.11 percent of the total vacuum thrust. At a mixture ratio of 4.29, the TDK predicted drag decrement was 16.59 N (3.73 lb), or 0.71 percent of the predicted total vacuum thrust.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-2725 , E-3523 , NAS 1.60:2725 , AIAA PAPER 87-2069
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    Development of an advanced photovoltaic concentrator system for space applications (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent studies indicate that significant increases in system performance (increased efficiency and reduced system mass) are possible for high power space based systems by incorporating technological developments with photovoltaic power systems. The Advanced Photovoltaic Concentrator Program is an effort to take advantage of recent advancements in refractive optical elements. By using a domed Fresnel lens concentrator and a prismatic cell cover, to eliminate metallization losses, dramatic reductions in the required area and mass over current space photovoltaic systems are possible. The advanced concentrator concept also has significant advantages when compared to solar dynamic Organic Rankine Cycle power systems in Low Earth Orbit applications where energy storage is required. The program is currently involved in the selection of a material for the optical element that will survive the space environment and a demonstration of the system performance of the panel design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100101 , E-3637 , NAS 1.15:100101 , AIAA PAPER 87-9034
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  • 73
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    Nuclear powered Mars cargo transport mission utilizing advanced ion propulsion (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Nuclear-powered ion propulsion technology was combined with detailed trajectory analysis to determine propulsion system and trajectory options for an unmanned cargo mission to Mars in support of manned Mars missions. A total of 96 mission scenarios were identified by combining two power levels, two propellants, four values of specific impulse per propellant, three starting altitudes, and two starting velocities. Sixty of these scenarios were selected for a detailed trajectory analysis; a complete propulsion system study was then conducted for 20 of these trajectories. Trip times ranged from 344 days for a xenon propulsion system operating at 300 kW total power and starting from lunar orbit with escape velocity, to 770 days for an argon propulsion system operating at 300 kW total power and starting from nuclear start orbit with circular velocity. Trip times for the 3 MW cases studied ranged from 356 to 413 days. Payload masses ranged from 5700 to 12,300 kg for the 300 kW power level, and from 72,200 to 81,500 kg for the 3 MW power level.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100109 , E-3641 , NAS 1.15:100109 , AIAA PAPER 87-1903
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    An evaluation of metallized propellants based on vehicle performance (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analytical study was conducted to determine the improvements in vehicle performance possible by burning metals with conventional liquid bipropellants. These metallized propellants theoretically offer higher specific impulse, increased propellant density and improved vehicle performance compared with conventional liquid bipropellants. Metals considered were beryllium, lithium, aluminum and iron. Liquid bipropellants were H2/O2, N2H4/N2O4, RP-1/O2 and H2/F2. A mission with a delta V = 4267.2 m/sec (14,000 ft/sec) and vehicle with propellant volume fixed at 56.63 cu m (2000 cu ft) and dry mass fixed at 2761.6 kg (6000 lb) was used, roughly representing the transfer of a chemically propelled upper-stage vehicle from a low-Earth orbit to a geosynchronous orbit. The results of thermochemical calculations and mission analysis calculations for bipropellants metallized with beryllium, lithium, aluminum and iron are presented. Technology issues pertinent to metallized propellants are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100104 , E-3639 , NAS 1.15:100104 , AIAA PAPER 87-1773
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    An analytical and experimental investigation of resistojet plumes (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a part of the electrothermal propulsion plume research program at the NASA Lewis Research Center, efforts have been initiated to analytically and experimentally investigate the plumes of resistojet thrusters. The method of G.A. Simons for the prediction of rocket exhaust plumes is developed for the resistojet. Modifications are made to the source flow equations to account for the increased effects of the relatively large nozzle boundary layer. Additionally, preliminary mass flux measurements of a laboratory resistojet using CO2 propellant at 298 K have been obtained with a cryogenically cooled quartz crystal microbalance (QCM). There is qualitative agreement between analysis and experiment, at least in terms of the overall number density shape functions in the forward flux region.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-88852 , E-3243 , NAS 1.15:88852
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    Electric propulsion options for the SP-100 reference mission (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Analyses were performed to characterize and compare electric propulsion systems for use on a space flight demonstration of the SP-100 nuclear power system. The component masses of resistojet, arcjet, and ion thruster systems were calculated using consistent assumptions and the maximum total impulse, velocity increment, and thrusting time were determined, subject to the constraint of the lift capability of a single Space Shuttle launch. From the study it was found that for most systems the propulsion system dry mass was less than 20 percent of the available mass for the propulsion system. The maximum velocity increment was found to be up to 2890 m/sec for resistojet, 3760 m/sec for arcjet, and 23 000 m/sec for ion thruster systems. The maximum thruster time was found to be 19, 47, and 853 days for resistojet, arcjet, and ion thruster systems, respectively.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-88918 , E-3343 , NAS 1.15:88918
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    A feasibility assessment of installation, operation and disposal options for nuclear reactor power system concepts for a NASA growth space station (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A preliminary feasibility assessment of the integration of reactor power system concepts with a projected growth space station architecture was conducted to address a variety of installation, operational disposition, and safety issues. A previous NASA sponsored study, which showed the advantages of space station - attached concepts, served as the basis for this study. A study methodology was defined and implemented to assess compatible combinations of reactor power installation concepts, disposal destinations, and propulsion methods. Three installation concepts that met a set of integration criteria were characterized from a configuration and operational viewpoint, with end-of-life disposal mass identified. Disposal destinations that met current aerospace nuclear safety criteria were identified and characterized from an operational and energy requirements viewpoint, with delta-V energy requirement as a key parameter. Chemical propulsion methods that met current and near-term application criteria were identified and payload mass and delta-V capabilities were characterized. These capabilities were matched against concept disposal mass and destination delta-V requirements to provide the feasibility of each combination.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-89923 , E-3622 , NAS 1.15:89923
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    Analysis of closed cycle megawatt class space power systems with nuclear reactor heat sources (1987)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The analysis and integration studies of multimegawatt nuclear power conversion systems for potential SDI applications is presented. A study is summarized which considered 3 separate types of power conversion systems for steady state power generation with a duty requirement of 1 yr at full power. The systems considered are based on the following conversion cycles: direct and indirect Brayton gas turbine, direct and indirect liquid metal Rankine, and in core thermionic. A complete mass analysis was performed for each system at power levels ranging from 1 to 25 MWe for both heat pipe and liquid droplet radiator options. In the modeling of common subsystems, reactor and shield calculations were based on multiparameter correlation and an in-house analysis for the heat rejection and other subsystems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: New Mexico Univ., Transactions of the Fourth Symposium on Space Nuclear Power Systems; p 423-426
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    A fusion based plasma propulsion system (1987)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The Fusion Plasma Propulsion System scoping study was performed to investigate the possibilities of a fusion powered plasma propulsion system for space applications. Specifically, it was to be compared against existing electric propulsion concepts for a manned Mars mission. Design parameters consist of 1000 N thrust for 500 days, and the minimum mass possible. This investigation is briefly presented and conclusions drawn.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: New Mexico Univ., Transactions of the Fourth Symposium on Space Nuclear Power Systems; p 81-84
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  • 80
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    Low Thrust Space Propulsion (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An overview of low rocket engine propulsion concepts for space missions is presented. Chemical and electrical rocket engines are shown. Animation illustrates propulsion applications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-109286 , NONP-NASA-VT-93-185302
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    Space Station Electrical Power System (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The purpose of this paper is to describe the design of the Space Station Electrical Power System. This includes the Photovoltaic and Solar Dynamic Power Modules as well as the Power Management and Distribution System (PMAD). In addition, two programmatic options for developing the Electrical Power System will be presented. One approach is defined as the Enhanced Configuration and represents the results of the Phase B studies conducted by the NASA Lewis Research Center over the last two years. Another option, the Phased Program, represents a more measured approach to reaching about the same capability as the Enhanced Configuration.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 87-234
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  • 82
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    AC power system breadboard (1987)
    In:  CASI
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    Publication Date: 2019-06-28
    Description: The object of this program was to design, build, test, and deliver a high-frequency (20-kHz) Power System Breadboard which would electrically approximate a pair of dual redundant power channels of an IOC Space Station. This report describes that program, including the technical background, and discusses the results, showing that the major assumptions about the characteristics of this class of hardware (size, mass, efficiency, control, etc.) were substantially correct. This testbed equipment has been completed and delivered to LeRC, where it is operating as a part of the Space Station Power System Test Facility.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179369 , NAS 1.26:179369 , GDSS-MBB-87-001
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  • 83
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    Development of a generic combustion stability code for liquid propellant rocket engines (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The mathematical framework for a combustion stability analysis code is outlined. The goal for the code is to be general enough in problem treatment so that its validity and accuracy extend over a wide range of problem applications and that it lends the convenience for any future model improvement if necessary. An approach for modeling the combustion dynamics is devised to meet both requirements. An open-loop numerical procedure is also developed to mechanistically model various combustion processes for determining the stability parameters.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 239-257
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  • 84
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    Numerical grid generation and flow simulation in SSME thrust chamber (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The development of liquid and solid rocket engines for future space projects demands a detailed optimization process for highly efficient performance and cost reasons. Also, testing of full size engines may not be feasible when the large size requires test facilities which are cost prohibitive or if vacuum operation cannot be acquired. For such situations only scaling from small test scale measurements or accurate analytical predictions will provide the performance prior to actually flying the mission. A rigorous approach for simulating the combustion processes in liquid rocket engines by employing a direct solution of Navier-Stokes equations within the entire volume of the thrust chambers is presented. This method is illustrated in the solution of reactive flow in the Space Shuttle Main Engine (SSME) thrust chamber. The objective is to review recent improvements in the mathematical model and to present the grid generation methodology suitable for rocket thrust chamber geometries.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 259-266
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  • 85
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    A computer program for performance prediction of tripropellant rocket engines with tangential slot injection (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: For the development of a Heavy Lift Launch Vehicle (HLLV) several engines with different operating cycles and using LOX/Hydrocarbon propellants are presently being examined. Some concepts utilize hydrogen for thrust chamber wall cooling followed by a gas generator turbine drive cycle with subsequent dumping of H2/O2 combustion products into the nozzle downstream of the throat. In the Space Transportation Booster Engine (STBE) selection process the specific impulse will be one of the optimization criteria; however, the current performance prediction programs do not have the capability to include a third propellant in this process, nor to account for the effect of dumping the gas-generator product tangentially inside the nozzle. The purpose is to describe a computer program for accurately predicting the performance of such an engine. The code consists of two modules; one for the inviscid performance, and the other for the viscous loss. For the first module, the two-dimensional kinetics program (TDK) was modified to account for tripropellant chemistry, and for the effect of tangential slot injection. For the viscous loss, the Mass Addition Boundary Layer program (MABL) was modified to include the effects of the boundary layer-shear layer interaction, and tripropellant chemistry. Calculations were made for a real engine and compared with available data.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ., The 24th JANNAF Combustion Meeting, Volume 2; p 319-327
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  • 86
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    Arcjet thruster research and technology, phase 1 (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objectives of Phase 1 were to evaluate analytically and experimentally the operation, performance, and lifetime of arcjet thrusters operating between 0.5 and 3.0 kW with catalytically decomposed hydrazine (N2H4) and to begin development of the requisite power control unit (PCU) technology. Fundamental analyses were performed of the arcjet nozzle, the gas kinetic reaction effects, the thermal environment, and the arc stabilizing vortex. The VNAP2 flow code was used to analyze arcjet nozzle performance with non-uniform entrance profiles. Viscous losses become dominant beyond expansion ratios of 50:1 because of the low Reynolds numbers. A survey of vortex phenomena and analysis techniques identified viscous dissipation and vortex breakdown as two flow instabilities that could affect arcjet operation. The gas kinetics code CREK1D was used to study the gas kinetics of high temperature N2H4 decomposition products. The arc/gas energy transfer is a non-equilibrium process because of the reaction rate constants and the short gas residence times. A thermal analysis code was used to guide design work and to provide a means to back out power losses at the anode fall based on test thermocouple data. The low flow rate and large thermal masses made optimization of a regenerative heating scheme unnecessary.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-182107 , NAS 1.26:182107 , REPT-87-R-1175
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  • 87
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    Studies and analyses of the space shuttle main engine. Failure information propagation model data base and software (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The failure information propagation model (FIPM) data base was developed to store and manipulate the large amount of information anticipated for the various Space Shuttle Main Engine (SSME) FIPMs. The organization and structure of the FIPM data base is described, including a summary of the data fields and key attributes associated with each FIPM data file. The menu-driven software developed to facilitate and control the entry, modification, and listing of data base records is also discussed. The transfer of the FIPM data base and software to the NASA Marshall Space Flight Center is described. Complete listings of all of the data base definition commands and software procedures are included in the appendixes.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-183586 , NAS 1.26:183586 , BCD-SSME-TR-87-2
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  • 88
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    Orbit transfer rocket engine technology program. Phase 2: Advanced engine study (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In Phase 2 of the Advanced Engine Study, the Failure Modes and Effects Analysis (FMEA) maintenance-driven engine design, preliminary maintenance plan, and concept for space operable disconnects generated in Phase 1 were further developed. Based on the results of the vehicle contractors Orbit Transfer Vehicle (OTV) Concept Definition and System Analysis Phase A studies, minor revisions to the engine design were made. Additional refinements in the engine design were identified through further engine concept studies. These included an updated engine balance incorporating experimental heat transfer data from the Enhanced Heat Load Thrust Chamber Study and a Rao optimum nozzle contour. The preliminary maintenance plan of Phase 1 was further developed through additional studies. These included a compilation of critical component lives and life limiters and a review of the Space Shuttle Main Engine (SSME) operations and maintenance manual in order to begin outlining the overall maintenance procedures for the Orbit Transfer Vehicle Engine and identifying technology requirements for streamlining space-based operations. Phase 2 efforts also provided further definition to the advanced fluid coupling devices including the selection and preliminary design of a preferred concept and a preliminary test plan for its further development.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179602 , NAS 1.26:179602 , RI/RD-87-126
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  • 89
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    Real gas properties and Space Shuttle Main Engine fuel turbine performance prediction (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The H2/H2O mixture thermodynamic and transport properties variations for the Space Shuttle Main Engine (SSME) fuel turbine over a range of temperatures and pressures are examined. The variation of molecular viscosity, specific heat at constant pressure, and Prandtl number for the hydrogen/steam mixture are fitted using polynominal relationships for future turbine performance use. The mixture property variations are calculated using GASP and WASP computer programs. The air equivalent performance of the SSME fuel turbine is computed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ASME PAPER 87-GT-106
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  • 90
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    Solid rocket motor aft field joint flow field analysis (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An efficient Navier-Stokes analysis was successfully applied to simulate the complex flow field in the vicinity of a slot in a solid rocket motor with segment joints. The capability of the computer code to resolve the flow near solid surfaces without using a wall function assumption was demonstrated. In view of the complex nature of the flow field in the vicinity of the slot, this approach is considered essential. The results obtained from these calculations provide valuable design information, which would otherwise be extremely difficult to obtain. The results of the axisymmetric calculations indicate the presence of a region of reversed axial flow at the aft-edge of the slot and show the over-pressure in the slot to be only about 10 psi. The results of the asymmetric calculations indicate that a pressure asymmetry more than two diameters downstream of the slot has no noticeable effect on the flow field in the slot. They also indicate that the circumferential pressure differential caused in the slot due to failure of a 15 deg section of the castable inhibitor will be approximately 1 psi.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-179288 , NAS 1.26:179288 , R87-900063-F
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  • 91
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    High power ion thruster performance (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The ion thruster is one of several forms of space electric propulsion being considered for use on future SP-100 based missions. One possible major mission ground rule is the use of single Space Shuttle launch. Thus, the mass in orbit at the reactor activation altitude would be limited by the Shuttle mass constraints. When the spacecraft subsystem masses are subtracted from this available mass limit, a maximum propellant mass may be calculated. Knowing the characteristics of each type of electric thruster allow maximum values of total impulse, mission velocity increment, and thrusting time to be calculated. Because ion thrusters easily operate at high values of efficiency (60 to 70 percent) and specific impulse (3000 to 5000 sec), they can impart large values of total impulse to a spacecraft. They also can be operated with separate control of the propellant flow rate and exhaust velocity. Values are presented of demonstrated and projected performance of high power ion thrusters used in an analysis of electric propulsion for an SP-100 based mission.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: New Mexico Univ., Transactions of the Fourth Symposium on Space Nuclear Power Systems; p 173-176
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  • 92
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    Interplanetary propulsion using inertial fusion (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Inertial fusion can be used to power spacecraft within the solar system and beyond. Such spacecraft have the potential for short duration manned mission performance exceeding other technologies. A study was conducted to assess the systems aspects of inertial as applied to such missions, based on the conceptual engine design of Hyde (1983). The required systems for an entirely new spacecraft design called VISTA that is based on the use of DT fuel is described. Preliminary design details are given for the power conversion and power conditioning systems for manned missions to Mars of total duration of about 100 days.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: New Mexico Univ., Transactions of the Fourth Symposium on Space Nuclear Power Systems; p 77-80
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  • 93
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    Megawatt level electric propulsion perspectives (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For long range space missions, deliverable payload fraction is an inverse exponential function of the propellant exhaust velocity or specific impulse of the propulsion system. The exhaust velocity of chemical systems are limited by their combustion chemistry and heat transfer to a few km/s. Nuclear rockets may achieve double this range, but are still heat transfer limited and ponderous to develop. Various electric propulsion systems can achieve exhaust velocities in the 10 km/s range, at considerably lower thrust densities, but require an external electrical power source. A general overview is provided of the currently available electric propulsion systems from the perspective of their characteristics as a terminal load for space nuclear systems. A summary of the available electric propulsion options is shown and generally characterized in the power vs. exhaust velocity plot. There are 3 general classes of electric thruster devices: neutral gas heaters, plasma devices, and space charge limited electrostatic or ion thrusters.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: New Mexico Univ., Transactions of the Fourth Symposium on Space Nuclear Power Systems; p 167-171
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  • 94
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    Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus liquid hydrogen addition, and the addition of an aluminum/liquid hydrogen slurry on the theoretical performance of a PBAN solid propellant rocket. The Space Shuttle solid rocket booster was used as a reference point. All three quasi-hybrid systems theoretically offer higher specific impulse when compared with the Space Shuttle solid rocket boosters. However, based on operational and safety considerations, the quasi-hybrid rocket is not a practical choice for near-term earth-to-orbit booster applications. Safety and technology issues pertinent to quasi-hybrid rocket systems are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2082
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  • 95
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    Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A 1030:1 carbon steel, heat-sink nozzle was tested. The test conditions included a nominal chamber pressure of 2413 kN/sq m and a mixture ratio range of 2.78 to 5.49. The propellants were gaseous oxygen and gaseous hydrogen. Outer wall temperature measurements were used to calculate the inner wall temperature and the heat flux and heat rate to the nozzle at specified axial locations. The experimental heat fluxes were compared to those predicted by the Two-Dimensional Kinetics (TDK) computer model analysis program. When laminar boundary layer flow was assumed in the analysis, the predicted values were within 15 percent of the experimental values for the area ratios of 20 to 975. However, when turbulent boundary layer conditions were assumed, the predicted values were approximately 120 percent higher than the experimental values. A study was performed to determine if the conditions within the nozzle could sustain a laminar boundary layer. Using the flow properties predicted by TDK, the momentum-thickness Reynolds number was calculated, and the point of transition to turbulent flow was predicted. The predicted transition point was within 0.5 inches of the nozzle throat. Calculations of the acceleration parameter were then made to determine if the flow conditions could produce relaminarization of the boundary layer. It was determined that if the boundary layer flow was inclined to transition to turbulent, the acceleration conditions within the nozzle would tend to suppress turbulence and keep the flow laminar-like.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2070
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  • 96
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    Temperature fields due to jet induced mixing in a typical OTV tank (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Eclipse Code is being developed as a general tool for analysis of cryogenic propellant behavior in spacecraft tankage. The focus of the work being reported is on prediction of temperature fields due to introduction of a cold jet along the centerline of a typical Orbit Transfer Vehicle tank. A brief description of the formulations used for modeling heat transfer and turbulent flow is presented. Code performance is verified through comparison to experimental data for mixing in small scale tanks. An unexpected difficulty in computing long duration flows is reviewed. Preliminary results for a partially filled full scale tank are obtained by approximating the free surface by a spherical solid boundary.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2017
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  • 97
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    An evaluation of metallized propellants based on vehicle performance (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An analytical study was conducted to determine the improvements in vehicle performance possible by burning metals with conventional liquid bipropellants. These metallized propellants theoretically offer higher specific impulse, increased propellant density and improved vehicle performance compared with conventional liquid bipropellants. Metals considered were beryllium, lithium, aluminum and iron. Liquid bipropellants were H2/O2, N2H4/N2O4, RP-1/O2 and H2/F2. A mission with a delta V = 4267.2 m/sec (14,000 ft/sec) and vehicle with propellant volume fixed at 56.63 cu m (2000 cu ft) and dry mass fixed at 2761.6 kg (6000 lb) was used, roughly representing the transfer of a chemically propelled upper-stage vehicle from a low-Earth orbit to a geosynchronous orbit. The results of thermochemical calculations and mission analysis calculations for bipropellants metallized with beryllium, lithium, aluminum and iron are presented. Technology issues pertinent to metallized propellants are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-1773
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  • 98
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    Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/sq m (350 psia) (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Joint Army, Navy, NASA, Air Force (JANNAF) rocket-engine performance-prediction procedure is based on the use of various reference computer programs. One of the reference programs for nozzle analysis is the Two-Dimensional Kinetics (TDK) Program. The purpose of this report is to calibrate the JANNAF procedure that has been incorporated into the December 1984 version of the TDK program for the high-area-ratio rocket-engine regime. The calibration was accomplished by modeling the performance of a 1030:1 rocket nozzle tested at NASA Lewis. A detailed description of the test conditions and TDK input parameters is given. The reuslts indicate that the computer code predicts delivered vacuum specific impulse to within 0.12 to 1.9 percent of the experimental data. Vacuum thrust coefficient predictions were within + or - 1.3 percent of experimental results. Predictions of wall static pressure were within approximately + or - 5 percent of the measured values.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2069
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  • 99
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    Analysis of flow decay potential on Galileo (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The risks posed to the NASA's Galileo spacecraft by the oxidizer flow decay during its extended mission to Jupiter is discussed. The Galileo spacecraft will use nitrogen tetroxide (NTO)/monomethyl hydrazine bipropellant system with one large engine thrust-rated at a nominal 400 N, and 12 smaller engines each thrust-rated at a nominal 10 N. These smaller thrusters, because of their small valve inlet filters and small injector ports, are especially vulnerable to clogging by iron nitrate precipitates formed by NTO-wetted stainless steel components. To quantify the corrosion rates and solubility levels which will be seen during the Galileo mission, corrosion and solubility testing experiments were performed with simulated Galileo materials, propellants, and environments. The results show the potential benefits of propellant sieving in terms of iron and water impurity reduction.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2016
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  • 100
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    Comparison of two procedures for predicting rocket engine nozzle performance (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Two nozzle performance prediction procedures which are based on the standardized JANNAF methodology are presented and compared for four rocket engine nozzles. The first procedure required operator intercedence to transfer data between the individual performance programs. The second procedure is more automated in that all necessary programs are collected into a single computer code, thereby eliminating the need for data reformatting. Results from both procedures show similar trends but quantitative differences. Agreement was best in the predictions of specific impulse and local skin friction coefficient. Other compared quantities include characteristic velocity, thrust coefficient, thrust decrement, boundary layer displacement thickness, momentum thickness, and heat loss rate to the wall. Effects of wall temperature profile used as an input to the programs was investigated by running three wall temperature profiles. It was found that this change greatly affected the boundary layer displacement thickness and heat loss to the wall. The other quantities, however, were not drastically affected by the wall temperature profile change.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2071
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