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  • Other Sources  (158)
  • SPACECRAFT PROPULSION AND POWER  (158)
  • 1980-1984  (158)
  • 1950-1954
  • 1982  (158)
  • 1
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    Ground- versus spaced-based orbital transfer vehicle (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A space based orbital transfer vehicle (SBOTV) and ground based OTV's (GBOTV) are compared for debris protection, space based OTV maintenance provisions, flight performance, onorbit refueling, and launch and return operations. Debris protection has a severe impact on the SBOTV, while the penalty for the GBOTV is much less severe. A key technology issue is the protection capability of composite materials. Onorbit maintenance is critical for SBOTV. Reduction of losses during the various transfers is th maine problem with refueling a SBOTV. Zero-g propellant storage and transfer is an important technology area for SBOTV. A reusable shroud must be developed to return GBOTV's if a Shuttle derivative vehicle is used. The advantage of space basing lies in more efficient use of the launch vehicle. Since most of the mass going to LEO is OTV propellant, and the launches to deliver the SBOTV propellant are generally mass limited, substantially fewer launches are required to support the SBOTV.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 127-134
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  • 2
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    Solar array system for solar maximum mission (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The paper describes the design of the solar array system (SAS) for the Solar Maximum Mission, the unique features of the SAS, and the results of its successful in-orbit operation. It is noted that the array was unique in that: (1) major weight concessions were made to produce a dynamically stiff array; (2) it was the first array designed to be compatible with the NASA Multimission Modular Spacecraft; (3) it is the first jettisonable solar array; and (4) it represents the first use of FEP-bonded overslides on a prime power array. It is concluded that the array performed as predicted with no evidence of the FEP causing any unusual array power degradations. In addition, the deployment and telemetry systems performed as designed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 3
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    New directions in solar array development (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A broad overview is presented of current and near-term solar array technology that could be suitable for space use. Particular consideration is given to such advanced concepts as high power arrays, concentrator arrays, and ultrathin solar cell arrays. It is concluded that if such ambitious concepts as geosynchronous space platforms, orbital space stations, and alternate forms of propulsion are realized, the type of new technology described in this paper may find acceptance for space.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 4
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    Application of beam power technology to a space station (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The feasibility and performance parameters for beam microwave power supplies from a space station to nearby orbiting satellites are examined. A 5.8 GHz transmission frequency is found suitable for beaming 1-10 kW over a distance of 1-10 km. The antenna could have a 15 m diameter, a 64 kW output, provide uniform illumination, and have a retrodirective phase control system. A LEO to ground demonstration project is described, involving power levels of 0.0025 mW/sq cm and yielding 202 W at a 100 x 100 m rectenna.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 5
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    A programmable power processor for high power space applications (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A Programmable Power Processor (P3) has been developed for application in future large space power systems. The P3 is capable of operation over a wide range of input voltage (26 to 375 Vdc) and output voltage (24 to 180 Vdc). The peak output power capability is 18 kW (180 V at 100 A). The output characteristics of the P3 can be programmed to any voltage and/or current level within the limits of the processor and may be controlled as a function of internal or external parameters. Seven breadboard P3s and one 'flight-type' engineering model P3 have been built and tested both individually and in electrical power systems. The programmable feature allows the P3 to be used in a variety of applications by changing the output characteristics. Test results, including efficiency at various input/output combinations, transient response, and output impedance, are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 6
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    Synthetic battery cycling techniques (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The group of techniques that as a class are referred to as synthetic battery cycling are described with reference to spacecraft battery systems. Synthetic battery cycling makes use of the capability of computer graphics to illustrate some of the basic characteristics of operation of individual electrodes within an operating electrochemical cell. It can also simulate the operation of an entire string of cells that are used as the energy storage subsystem of a power system.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA 4th ESTEC Spacecraft Power-Conditioning Seminar; p 129-134
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  • 7
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    Nickel-hydrogen bipolar battery system (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Rechargeable nickel-hydrogen systems are described that more closely resemble a fuel cell system than a traditional nickel-cadmium battery pack. This was stimulated by the currently emerging requirements related to large manned and unmanned low Earth orbit applications. The resultant nickel-hydrogen battery system should have a number of features that would lead to improved reliability, reduced costs as well as superior energy density and cycle lives as compared to battery systems constructed from the current state-of-the-art nickel-hydrogen individual pressure vessel cells.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ESA 4th ESTEC Spacecraft Power-Conditioning Seminar; p 115-121
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  • 8
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    Hydrogen chloride measurements in the Space Shuttle exhaust cloud - First launch, April 12, 1981 (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Partitioning of hydrogen chloride between the aerosol and gaseous phases in the first Space Shuttle exhaust cloud was experimentally investigated as the exhaust cloud was diluted with ambient air. Airborne measurements were obtained of gaseous hydrogen chloride (HCl), total HCl, relative humidity, and temperature to determine the conditions controlling HCl aerosol formation in the Shuttle exhaust cloud. Two segments of the cloud, each at a significantly different relative humidity, were monitored. Equilibrium predictions of HCl aerosol formation agreed with the measured HCl partitioning at the higher and lower relative humidity conditions, but do not agree at the aerosol formation threshold region. Measurements were taken in the Shuttle exhaust cloud from 8.6 min until 2 h and 8 min after launch. HCl concentrations ranged from 17.5 to 0.9 ppm and relative humidity from 86% to less than 10%.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets; 19; July-Aug
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  • 9
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    Electric propulsion (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An alternative propulsion subsystem for MSAT is presented which has a potential of reducing the satellite weight by more than 15%. The characteristics of pulsed plasma and ion engines are described and used to estimate of the mass of the propellant and thrusters for attitude control and stationkeeping functions for MSAT. Preliminary estimates indicate that the electric propulsion systems could also replace the large momentum wheels necessary to counteract the solar pressure; however, the fine pointing wheels would be retained. Estimates also show that either electric propulsion system can save approximately 18% to 20% of the initial 4,000 kg mass. The issues that require further experimentation are mentioned.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Land Mobile Satellite Serv. (LMSS): A Conceptual System Design and Identification of the Critical Technol.; 7 p
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  • 10
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    System Design and Integration Panel Workshop summary (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Priorties are identified for spacecraft propulsion system development and for the integration of the propulsion system with various subsystems. Near-term and long-term propulsion technology needs are identified.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 257-260
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  • 11
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    Capabilities in large space systems construction (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Orbital construction, demonstration, space construction system analysis, solar power satellite, and space operations are reviewed. Satellite services, holding and positioning aids, and space construction experiments are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 199-211
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  • 12
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    Systems integration (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The workings of systems integration, its accomplishments, the influences of its character changes on the STS, propulsion out of the orbiter and LSS, and technological demands are discussed. The task of systems integration is to define, understand, and account for interactions between the major systems on a space mission. The safety and propulsion systems and their reliability are outlined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Propulsion Interactions; p 123-126
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  • 13
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    Centralized versus distributed propulsion (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The functions and requirements of auxiliary propulsion systems are reviewed. None of the three major tasks (attitude control, stationkeeping, and shape control) can be performed by a collection of thrusters at a single central location. If a centralized system is defined as a collection of separated clusters, made up of the minimum number of propulsion units, then such a system can provide attitude control and stationkeeping for most vehicles. A distributed propulsion system is characterized by more numerous propulsion units in a regularly distributed arrangement. Various proposed large space systems are reviewed and it is concluded that centralized auxiliary propulsion is best suited to vehicles with a relatively rigid core. These vehicles may carry a number of flexible or movable appendages. A second group, consisting of one or more large flexible flat plates, may need distributed propulsion for shape control. There is a third group, consisting of vehicles built up from multiple shuttle launches, which may be forced into a distributed system because of the need to add additional propulsion units as the vehicles grow. The effects of distributed propulsion on a beam-like structure were examined. The deflection of the structure under both translational and rotational thrusts is shown as a function of the number of equally spaced thrusters. When two thrusters only are used it is shown that location is an important parameter. The possibility of using distributed propulsion to achieve minimum overall system weight is also examined. Finally, an examination of the active damping by distributed propulsion is described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 87-100
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  • 14
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    Storable orbit transfer vehicle (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Orbit transfer vehicles (OTV) are evaluated against mission model requirement. Mission suitability of OTVs using storable propellant, cryogenic propellant, and electric propulsion systems is outlined. Energy required, g-level, spacecraft deploy/return, operational constraints, mission duration, and packaging are considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 53-60
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  • 15
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    Advanced space system concepts and their orbital support needs (1980 - 2000) (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Possible uses of satellite technology up to the year 2000 are suggested and discussed. Included are electronic mail transmission, a personal communications capability, quick location of vehicles or shipments, monitoring of disputed territorial borders, upgraded scientific exploration of the universe, providing better maps of the Earth by remote sensing, space solar power stations and the safe transmission of the electrical energy to Earth, night lighting, and a small personal navigation capability. Support requirements are outlined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 25-37
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  • 16
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    An alternate approach for low cost space cells (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Silicon solar cells manufactured for the terrestrial market are examined as a potential low cost option for low earth orbit (LEO) space flight use. The results of simulated space environmental testing of representative samples are reported and discussed. It is shown that although the terrestrial cells are compatible with most space use requirements significant deficiencies still exist. Cell modifications are discussed which would enhance the space applicability of the various cells examined. In most cases these are expected to be of minimal cost impact. Concern for contact/interconnector designs capable of surviving 30,000 thermal cycles (corresponding to five years in LEO) however, needs to be resolved for the large area terrestrial devices.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 17
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    On the cause of the flat-spot phenomenon observed in silicon solar cells at low temperatures and low intensities (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A model is presented that explains the 'flat-spot' power-loss phenomenon observed in silicon solar cells operating under deep space (low temperature, low intensity) conditions. Evidence is presented suggesting that the effect is due to localized metallurgical interactions between the silicon substrate and the contact metallization. These reactions are shown to result in localized regions in which the PN junction is destroyed and replaced with a metal-semiconductor-like interface. The effects of thermal treatment, crystallographic orientation, junction depth, and metallization are presented along with a method of preventing the effect through the suppression of vacancy formation at the free surface of the contact metallization. Preliminary data indicating the effectiveness of a TiN diffusion barrier in preventing the effect are also given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Applied Physics; 53; Aug. 198
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  • 18
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    Advanced propulsion for future planetary spacecraft (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 19, p. 3284, Accession no. A81-40931)
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 19
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    Active large structures (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Some performance requirements and development needs for the design of large space structures are described. Areas of study include: (1) dynamic response of large space structures; (2) structural control and systems integration; (3) attitude control; and (4) large optics and flexibility. Reference is made to a large space telescope.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 221-237
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  • 20
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    Some interdisciplinary trade-offs in the design of large space structures (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The constraints placed on the design of large space structures by acceleration, attitude control, and stationkeeping forces are discussed. Stiffness requirements for the structures are derived. The use of active versus passive accuracy control methods is also addressed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 213-219
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  • 21
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    System Requirements and Operations Panel Workshop summary (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The low Earth orbit (LEO) versus the geosynchronous Earth orbit (GEO) deployment systems were discussed. The following items are emphasized: (1) large area systems, such as deployment, altitude, orbit transfer, and on orbit operation; (2) propulsion oriented issues such as the orbit transfer vehicle and the auxiliary propulsion systems; (3) programmatic issues. The LEO versus GEO deployment is a significant driver on propulsion requirements for an orbit transfer vehicle. It is suggested that early systems will be deployed at LEO. The Shuttle remote manipulator system (RMS) will not be involved in early demonstration activities. It is concluded that an integrated large space system/propulsion approach is essential and that propulsion development requirements need to be established.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 135-171
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  • 22
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    Structures-propulsion interactions and requirements (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The effects of low-thrust primary propulsion system characteristics on the mass, area, and orbit transfer characteristics of large space systems (LSS) were determined. Three general structural classes of LSS were considered, each with a broad range of diameters and nonstructural surface densities. While transferring the deployed structure from LEO and to GEO, an acceleration range of 0.02 to 0.1 g's was found to maximize deliverable payload based on structural mass impact. After propulsion system parametric analyses considering four propellant combinations produced values for available payload mass, length and volume, a thrust level range which maximizes deliverable LSS diameter was determined corresponding to a structure and propulsion vehicle. The engine start and/or shutdown thrust transients on the last orbit transfer (apogee) burn can impose transient loads which would be greater than the steady-state loads at the burnout acceleration. The effect of the engine thrust transients on the LSS was determined from the dynamic models upon which various engine ramps were imposed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 81-86
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  • 23
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    Cryogenic orbit transfer vehicle (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Studies determined that shuttle optimized design, allowing the large space system and transfer vehicle in one shuttle flight, greatly reduces transportation costs and minimizes orbital operations. Careful attention to design resulted in efficient payload packaging. A minimum volume, high energy (liquid oxygen and liquid hydrogen) transfer vehicle is described that allows maximum volume for the payload in the orbiter cargo bay.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 43-51
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  • 24
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    Power Systems integration (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Power systems integration in large flexible space structures is discussed with emphasis upon body control. A solar array is discussed as a typical example of spacecraft configuration problems. Information on how electric batteries dominate life-cycle costs is presented in chart form. Information is given on liquid metal droplet generators and collectors, hot spot analysis, power dissipation in solar arrays, solar array protection optimization, and electromagnetic compatibility for a power system platform.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 239-255
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  • 25
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    The 100-meter radiometer spacecraft study (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A rigid body analysis of a baseline Large Space System (LSS) which is to function as a radiometer is presented. The LSS is placed in circular orbit about the Earth at an altitude of 650 km, subjected to environmental and vehicle interaction forces and torques, without an active control system of any type on board. The environment forces and torques are gravity gradient, solar radiation, and aerodynamic. Normal operation is in nadir pointing along the Z-local vertical axis. Orbital velocity is assigned to the x-axis of the spacecraft. The analysis is then used to demonstrate the ability or lack of the gravity gradient torques to stabilize the LSS over one complete orbit.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 173-197
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  • 26
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    System requirements (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Requirements of future space systems, including large space systems, that operate beyond the space shuttle are discussed. Typical functions required of propulsion systems in this operational regime include payload placement, retrieval, observation, servicing, space debris control and support to large space systems. These functional requirements are discussed in conjunction with two classes of propulsion systems: (1) primary or orbit transfer vehicle (OTV) and (2) secondary or systems that generally operate within or relatively near an operational base orbit. Three propulsion system types are described in relation to these requirements: cryogenic OTV, teleoperator maneuvering system and a solar electric OTV.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space System(Propulsion Interactions; p 101-121
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  • 27
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    Structures: Propulsion interactions and requirements (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The dynamics of the interaction of space structures and their propellant systems are outlined. Optimization for a platform type of space structure is discussed. Static and transient loads, propellant accelerations, tolerances, attitude control, and distributed thrust are considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 71-79
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  • 28
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    Electric propulsion: Synergy of orbit transfer and maintenance (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Electric propulsion systems for transferring large payload masses to geosynchronous Earth orbits and providing accurate on-orbit stationkeeping are evaluated. Orbit boosting, inclination change, attitude control, stationkeeping, relocation, disposal, and power sharing on orbits using electric propulsion are compared with the use of chemical propulsion.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 61-69
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  • 29
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    Missions panel workshop summary (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A workshop panel defined missions that would require the potential use of very large, advanced space systems, and ranked them on the basis of need from both a civilian and military perspective. The panel also pointed out those that would need advanced propulsion technology. Surveillance, communications, and defense were given the highest priority, followed by command and control, orbital support, terrestrial support, and space science.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 39-42
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  • 30
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    Potential large space systems mission opportunities for the post 1990's (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Potential mission opportunities outlined and illustrated are missile defense; space defense; command, control, and communications; defense suppression; force support; space transportation; and orbital support.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 19-24
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  • 31
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    NASA space system technology model future mission system needs (1982)
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    Publication Date: 2011-08-18
    Description: The overall technology model is outlined and the objectives and descriptions of the primary and secondary propulsion drives presented. The primary propulsion driver missions are the geostationary platform; the coherent optical system of modular imaging collectors (COSMIC); the 100 meter thinned aperature telescope; and the orbiting deep space relay station (ODSRS). The secondary propulsion driver missions are space platform alpha, the space station, and the automated planetary station.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 7-18
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  • 32
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    Free radical propulsion concept (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 14, p. 2320, Accession no. A81-32905)
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  • 33
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    Measurements of cloud nuclei in the effluents from launches of liquid- and solid-fueled rockets (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Airborne measurements of two types of cloud nuclei, cloud condensation nuclei (CCN) and ice nuclei (IN), were conducted in the stabilized ground clouds which resulted from the launches of a liquid-fueled ATLAS/Centaur rocket and a solid-fueled TITAN III rocket. Results show that the concentrations of CCN in both types of clouds were greater than ambient values for the 2 hours duration of the measurements. The initial production of CCN active at 0.5% supersaturation in the ATLAS and TITAN clouds was found to be equivalent to a 20 and 700 sec emission, respectively, by the city of Denver, Colorado. After the initial production, the clouds continued to generate CCN at a rate of about 1/cu cm sec. However, concentrations of IN in the ATLAS cloud were greater than ambient values for only a short period after launch, and it appears that the nuclei resulted from entrained launch pad and ground debris. The concentrations of IN in the TITAN cloud were found to be at or below ambient levels until about 2 hours after launch when they increased substantially above ambient values.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Applied Meteorology; 21; Sept
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  • 34
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    NASA's laser-propulsion project (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Design concepts, study results, and research directions toward development of CW laser heating of remotely flying spacecraft fuels to provide high impulse thrust are presented. The incident laser radiation would be absorbed by hydrogen through a medium of a laser-supported plasma. The laser energy could be furnished from an orbiting solar-powered laser platform and used to drive the engines of an orbital transfer vehicle (OTV) at costs less than with a chemical propulsion system. The OTV propulsion chamber would be reduced in size comparable to the volume addition of the incident laser energy absorber. The temperatures in the hydrogen-fueled system could reach 5000-15,000 K, and studies have been done to examine the feasibility of ion-electron recombination. Kinetic performance, temperature field, and power necessary to sustain a laser thrust augmented system modeling results are discussed, along with near-term 30 kW CO2 laser system tests.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 20; Sept
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  • 35
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    Technology status report on hydrocarbon-fueled engines for space transportation systems (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Liquid oxygen/hydrocarbon (LOX/HC) fueled engines are being considered for use in future high-pressure engines for launch vehicles and as possible replacements for the orbital maneuvering system and reaction control system engines on the Space Shuttle. High performance, reusability, and low life cycle cost are required for these applications. A technology base for these engines is now being established. This paper provides a review of recent results from LOX/HC technology contracts for the National Aeronautics and Space Administration.
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    A technology data base for the design of 500 to 5000-lb thrust class liquid rocket engines utilizing hydrogen and oxygen as propellants (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: This paper presents an overview of the results of experimental evaluations of candidate designs for igniters, injectors, and propellant-cooled thrust chambers applicable to restartable high-performance, high-reliability upper-stage engines and to pulsing-type reaction control engines (RCE). Injection element types best suited for liquid, gas, and liquid/gas phase propellant supply are identified. The resulting interactions between element type, combustion efficiency, and chamber wall heating are compared. The distinction between thrust chamber design requirements for upper stage vs RCE applications as measured by cycle life requirements is translated into design configurations consisting of all-film-cooled, all-regeneratively-cooled, and composites of the two cooling approaches. The validity of the design approaches is confirmed by data from engine durability testing involving over 90,000 starts and 9,000 thermal cycles on RCE-type designs and multiple long-duration burns (up to 2,000 sec) on regeneratively cooled upper-stage designs.
    Keywords: SPACECRAFT PROPULSION AND POWER
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    Results of tests of MTA-2 TPS on the SRB hold-down bolt blast container (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The four solid rocket booster (SRB) hold-down posts are fastened to the mobile launch platform (MLP) with four large nuts. At liftoff the nuts are split with explosive changes to release the SRB/Shuttle. A blast container is placed over the nuts to protect the vehicle from flying debris. The blast container is a reusable part and has to be protected from aerodynamic heating during flight. The thermal protection system (TPS) used to protect these blast containers is cork. Fitting the flat cork sheet to this hemispherical shaped blast container is both time consuming and expensive. Another problem is removing the charred cork and epoxy glue from the blast containers. Replacements of this cork with another TPS material such as MTA-2 was examined. Heating rates along the centerline of the forward facing areas of the blast container were determined. The feasibility of using 1/2 in. MTA-2 on the SRB blast containers for protection from ascent, plume impingement and reentry heating is demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170891 , NAS 1.26:170891 , LMSC-HREC-TN-D867571
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  • 38
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    Effects of translational nonequilibrium on vacuum plume expansions (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The plume flowfield of a helium vent nozzle exhausting into a vacuum is defined by two techniques: the method of characteristics and the direct-simulation Monte Carlo method. The method of characteristics is shown to severely underpredict gas static temperatures due to the assumption of translational equilibrium inherent in the continuum formulation. Mass flow per unit solid angle is shown to be accurately predicted for this flowfield by the method of characteristics until the flow angle approaches within 10 deg of the maximum Prandtl-Meyer expansion angle. Improved treatment of the noncontinuum flow within the nozzle (near the lip) is postulated to have minor effects on the accuracy of this continuum method in comparison with translational nonequilibrium in the external flowfield. Possible treatment of translational nonequilibrium by the method of characteristics is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA Journal; 20; July 198
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  • 39
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    Mass driver reaction engine characteristics and performance in earth orbital transfer missions (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Configurations of a typical mass driver reaction engine (MDRE) are presented and its use for delivery of payloads to geosynchronous orbit (GEO) from low earth orbit (LEO) is discussed. Basic rocket equations are developed for LEO to GEO round-trip missions using a single exhaust velocity. It is shown that exhaust velocities in the 5-10 km/sec range (specific impulse of 500-1000 sec) are well suited for mass drivers, minimizing the overall cost of missions. Payload delivery rate fractions show that there is little to be gained by stretching out LEO to GEO transfer times from 90 to 180 days. It therefore pays to use the shorter trip time, approximately doubling the amount of delivered payload during any fixed time of use of the MDRE.
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  • 40
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    PLASIM: A computer code for simulating charge exchange plasma propagation (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The propagation of the charge exchange plasma for an electrostatic ion thruster is crucial in determining the interaction of that plasma with the associated spacecraft. A model that describes this plasma and its propagation is described, together with a computer code based on this model. The structure and calling sequence of the code, named PLASIM, is described. An explanation of the program's input and output is included, together with samples of both. The code is written in ANSI Standard FORTRAN.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-169209 , NAS 1.26:169209
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  • 41
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    Electric and magnetic fields (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A number of energy momentum anomalies are described that result from the use of Abraham-Lorentz electromagnetic theory. These anomalies have in common the motion of charged bodies or current carrying conductors relative to the observer. The anomalies can be avoided by using the nonflow approach, based on internal energy of the electromagnetic field. The anomalies can also be avoided by using the flow approach, if all contributions to flow work are included. The general objective of this research is a fundamental physical understanding of electric and magnetic fields which, in turn, might promote the development of new concepts in electric space propulsion. The approach taken is to investigate quantum representations of these fields.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165604 , NAS 1.26:165604
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  • 42
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    Large Space Systems/Propulsion Interactions (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Material illustrating the presentations on and the conclusions of workshop panels considering the missions, systems requirements and operations, and systems design and integration is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-82904 , E-1288 , NAS 1.15:82904
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    Ion accelerator systems for high power 30 cm thruster operation (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two and three-grid accelerator systems for high power ion thruster operation were investigated. Two-grid translation tests show that over compensation of the 30 cm thruster SHAG grid set spacing the 30 cm thruster radial plasma density variation and by incorporating grid compensation only sufficient to maintain grid hole axial alignment, it is shown that beam current gains as large as 50% can be realized. Three-grid translation tests performed with a simulated 30 cm thruster discharge chamber show that substantial beamlet steering can be reliably affected by decelerator grid translation only, at net-to-total voltage ratios as low as 0.05.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168001 , NAS 1.26:168001
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    Concepts for the design of an antimatter annihilation rocket (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: (Previously announced in STAR as N82-21050)
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: vol. 35; Sept
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  • 45
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    Low-thrust chemical propulsion system propellant expulsion and thermal conditioning study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thermal conditioning systems for satisfying engine net positive suction pressure (NPSP) requirements, and propellant expulsion systems for achieving propellant dump during a return-to-launch site (RTLS) abort were studied for LH2/LO2 and LCH4/LO2 upper stage propellant combinations. A state-of-the-art thermal conditioning system employing helium injection beneath the liquid surface shows the lowest weight penalty for LO2 and LCH4. A technology system incorporating a thermal subcooler (heat exchanger) for engine NPSP results in the lowest weight penalty for the LH2 tank. A preliminary design of two state-of-the-art and two new technology systems indicates a weight penalty difference too small to warrant development of a LH2 thermal subcooler. Analysis results showed that the LH2/LO2 propellant expulsion system is optimized for maximum dump line diameters, whereas the LCH4/LO2 system is optimized for minimum dump line diameter (LCH4) and maximum dump line diameter (LO2). The primary uncertainty is the accurate determination of two-phase flow rates through the dump system; experimentation is not recommended because this uncertainty is not considered significant.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-167841 , GDC-NAS-82-002 , NAS 1.26:167841
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  • 46
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    Large area space solar cell assemblies (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Results of the development of a 34.3 sq cm space solar cell and integral glass cover are presented. Average AM(0) cell efficiency is 14 percent. The cell design includes a high performance back surface reflector yielding a thermal alpha of approximately 0.66. A novel process is described which integrates cell fabrication and encapsulation thereby achieving a reduction of encapsulation cost. Test results indicate the potential of this new technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 47
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    Solar array Shuttle flight experiment - Hardware development and testing (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This paper reports on the fabrication and ground testing of (a) a large area, light-weight, flexible substrate developmental solar array wing that has been built for NASA-MSFC and of (b) the supporting structure and data acquisition system (DAS) which, with the wing, will be flown in the Shuttle as an experiment in 1984. The experiment will verify the dynamics, thermodynamic, and electrical performance predictions of the array wing and will demonstrate the structural capability of the array wing for Orbiter launch and re-entry environments. The experiment hardware verification program was designed to minimize costs and risk of experiment performance degradation while maintaining Shuttle and crew safety. The previous full-scale wing hardware tests included an extension mast water table test and wing testing for random vibration, thermal vacuum, and acoustic environments. The results of these tests were used to define wing design modifications and to scope the test program for the experiment hardware.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 48
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    A study of mesospheric rocket contrails and clouds produced by liquid-fueled rockets (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Changes in the atmospheric composition, particularly through the condensation of rocket vehicle exhaust, caused by the flights of 400 heavy lift launch vehicles (HLLV) to carry crews and materials into space to build a satellite solar power system (SPS) were examined. Attention was given to the formation of mesospheric contrails and clouds. A one-dimensional model was used to formulate the photochemistry and vertical transport of water vapor, its nucleation into an ice cloud, and the microphysical development of the cloud. Considering one HLLV launch per day for a decade, it is projected that the upper atmosphere water vapor concentration would be increased by 10-20%, thereby augmenting the size and opacity of natural noctilucent clouds by 50%. No climatological consequences are foreseen from the clouds, although spectacular noctiluminescent cloud displays are thought to be possible.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Space Solar Power Review; 3; 3, 19; 1982
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  • 49
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    Microwave plasma generation of hydrogen atoms for rocket propulsion (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: (Previously cited in issue 12, p. 1959, Accession no. A81-29533)
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 50
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    Thrust imbalance of the Space Shuttle solid rocket motors (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: (Previously cited in issue 19, p. 3285, Accession no. A81-40975)
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 51
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    Ion thruster charge-exchange plasma flow (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: (Previously cited in issue 07, p. 996, Accession no. A82-19802)
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 52
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    Results of tests of the SRB aft skirt heat shield curtain in the MSFC Hot Gas Facility (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During the first two space shuttle flights the aft skirt heat shield curtain performed well during ascent but failed during reentry. This exposed the inside of the skirt and its subsystems to reentry heating. The resulting exposure damaged various expensive systems items and therefore a curtain reassessment is required. As a part of this reassessment, tests were conducted in the MSFC Hot Gas Facility (HGF). The purposes of these tests were to determine if the curtain would fail in a manner similar to that in flight and to demonstrate that meaningful tests of the curtain can be conducted in the HGF.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170888 , NAS 1.26:170888 , LMSC-HREC-TM-D784643
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  • 53
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    Component technology for space power systems (1982)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Progress made by NASA toward implementation of equipment for the conversion, management, and distribution of voltage power in space applications are reviewed. Work has been carried forward on components such as bipolar transistors, deep impurity semiconductors, conductors, dielectrics, magnetic devices, and rotary power transfer. Specific programs for the high voltage systems have included research on lightweight, low-cost conductors featuring graphite fibers containing electron donor materials for wires and cables with reduced mass and the conductivity of copper. Attention has also been given p-n junction technology for high-speed, high-current, high-voltage materials and diamond-like dielectric films which are hard, have high dielectric strength, and can operate up to 300 C. A transistor has been fabricated with a voltage of 1200 V at 100 A, with a gain of 10 and a 0.5 microsec rise/fall time. A 25 kW transformer has also been built which performs at 20 kHz with an efficiency of 99.2%.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 82-408
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  • 54
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    Low-thrust chemical propulsion system propellant expulsion and thermal conditioning study. Executive summary (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preferred techniques for providing abort pressurization and engine feed system net positive suction pressure (NPSP) for low thrust chemical propulsion systems (LTPS) were determined. A representative LTPS vehicle configuration is presented. Analysis tasks include: propellant heating analysis; pressurant requirements for abort propellant dump; and comparative analysis of pressurization techniques and thermal subcoolers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165622 , GDC-NAS-82-001 , NAS 1.26:165622
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  • 55
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    Low-thrust Isp sensitivity study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A comparison of the cooling requirements and attainable specific impulse performance of engines in the 445 to 4448N thrust class utilizing LOX/RP-1, LOX/Hydrogen and LOX/Methane propellants is presented. The unique design requirements for the regenerative cooling of low-thrust engines operating at high pressures (up to 6894 kPa) were explored analytically by comparing single cooling with the fuel and the oxidizer, and dual cooling with both the fuel and the oxidizer. The effects of coolant channel geometry, chamber length, and contraction ratio on the ability to provide proper cooling were evaluated, as was the resulting specific impulse. The results show that larger contraction ratios and smaller channels are highly desirable for certain propellant combinations.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165621 , NAS 1.26:165621
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    Improvement of Rocket Engine Plume Analysis Techniques (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A nozzle plume flow field code was developed. The RAMP code which was chosen as the basic code is of modular construction and has the following capabilities: two phase with two phase transonic solution; a two phase, reacting gas (chemical equilibrium reaction kinetics), supersonic inviscid nozzle/plume solution; and is operational for inviscid solutions at both high and low altitudes. The following capabilities were added to the code: a direct interface with JANNAF SPF code; shock capturing finite difference numerical operator; two phase, equilibrium/frozen, boundary layer analysis; a variable oxidizer to fuel ratio transonic solution; an improved two phase transonic solution; and a two phase real gas semiempirical nozzle boundary layer expansion.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-167516 , LMSC-HREC-TR-D784753
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    A study of the selection of microcomputer architectures to automate planetary spacecraft power systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Performance and reliability models of alternate microcomputer architectures as a methodology for optimizing system design were examined. A methodology for selecting an optimum microcomputer architecture for autonomous operation of planetary spacecraft power systems was developed. Various microcomputer system architectures are analyzed to determine their application to spacecraft power systems. It is suggested that no standardization formula or common set of guidelines exists which provides an optimum configuration for a given set of specifications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168412 , JPL-PUB-82-1
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    Method and apparatus for suppressing ignition overpressure in solid rocket propulsion systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The transient overpressure wave produced upon ignition of a solid rocket booster is suppressed by providing within the launch platform, a plurality of pipes and spray heads disposed around the periphery of the exhaust gas plume near its upper end and spraying water into the upper end of the plume during ignition. A large amount of water, preferably equivalent in mass of exhaust products being ejected, is sprayed into the plume in a direction generally perpendicular to plume flow.
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    Mass Driver Two - A status report (1982)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The current status of Mass Driver Two, a linear synchronous motor for accelerating payloads or reaction mass, is discussed. Mass Driver Two combines all the essential elements of an operational mass driver with the exception of bucket recirculation and payload handling. These essential elements include: magnetic flight, vacuum environment, superconducting bucket coils, high acceleration (nominally 500 g's), optical position sensing and electronic triggering, power circuitry similar to that of a flight article, and regenerative braking. Mass Driver Two is operated on a single shot basis.
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  • 60
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    Effects of processing and dopant on radiation damage removal in silicon solar cells (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Gallium and boron doped silicon solar cells, processed by ion-implantation followed by either laser or furnace anneal were irradiated by 1 MeV electrons and their post-irradiation recovery by thermal annealing determined. During the post-irradiation anneal, gallium-doped cells prepared by both processes recovered more rapidly and exhibited none of the severe reverse annealing observed for similarly processed 2 ohm-cm boron doped cells. Ion-implanted furnace annealed 0.1 ohm-cm boron doped cells exhibited the lowest post-irradiation annealing temperatures (200 C) after irradiation to 5 x 10 to the 13th e(-)/sq cm. The drastically lowered recovery temperature is attributed to the reduced oxygen and carbon content of the 0.1 ohm-cm cells. Analysis based on defect properties and annealing kinetics indicates that further reduction in annealing temperature should be attainable with further reduction in the silicon's carbon and/or divacancy content after irradiation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-82892 , E-1270 , NAS 1.15:82892
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    LOX/hydrocarbon auxiliary propulsion system study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Liquid oxygen/hydrocarbon propulsion systems applicable to a second generation orbiter OMS/RCS were compared, and major system/component options were evaluated. A large number of propellant combinations and system concepts were evaluated. The ground rules were defined in terms of candidate propellants, system/component design options, and design requirements. System and engine component math models were incorporated into existing computer codes for system evaluations. The detailed system evaluations and comparisons were performed to identify the recommended propellant combination and system approach.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171655 , NAS 1.26:171655 , MDC-E2576
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    LOX/hydrocarbon auxiliary propulsion system study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Liquid oxygen (LOX)/hydrocarbon propulsion concepts for a "second generation' orbiter auxiliary propulsion system was evaluated. The most attractive fuel and system design approach identified, and the technology advancements that are needed to provide high confidence for a subsequent system development were determined. The fuel candidates were ethanol, methane, propane, and ammonia. Even though ammonia is not a hydrocarbon, it was included for evaluation because it is clean burning and has a good technology base. The major system design options were pump versus pressure feed, cryogenic versus ambient temperature RCS propellant feed, and the degree of OMS-RCS integration. Ethanol was determined to be the best fuel candidate. It is an earth-storable fuel with a vapor pressure slightly higher than monomethyl hydrazine. A pump-fed OMS was recommended because of its high specific impulse, enabling greater velocity change and greater payload capability than a pressure fed system.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171656 , NAS 1.26:171656 , MDC-E2548
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    Rail accelerator research at Lewis Research Center (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A rail accelerator was chosen for study as an electromagnetic space propulsion device because of its simplicity and existing technology base. The results of a mission feasibility study using a large rail accelerator for direct launch of ton-size payloads from the Earth's surface to space, and the results of initial tests with a small, laboratory rail accelerator are presented. The laboratory rail accelerator has a bore of 3 by 3 mm and has accelerated 60 mg projectiles to velocities of 300 to 1000 m/s. Rail materials of Cu, W, and Mo were tested for efficiency and erosion rate.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-83015 , E-1449 , NAS 1.15:83015 , AIAA PAPER 82-1938 , Intern. Electric Propulsion Conf; Nov 17, 1982 - Nov 19, 1982; New Orleans
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    Parallel plate radiofrequency ion thruster (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An 8-cm-diam. argon ion thruster is described. It is operated by applying 100 to 160 Mhz rf power across a thin plasma volume in a strongly divergent static magnetic field. No cathode or electron emitter is required to sustain a continuous wave plasma discharge over a broad range of propellant gas flow. Preliminary results indicate that a large fraction of the incident power is being reflected by impedance mismatching in the coupling structure. Resonance effects due to plasma thickness, magnetic field strength, and distribution are presented. Typical discharge losses obtained to date are 500 to 600 W per beam ampere at extracted beam currents up to 60 mA.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-83014 , E-1432 , NAS 1.15:83014 , Intern. Electric Propulsion Conf.,; Nov 17, 1982 - Nov 19, 1982; New Orleans
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    Simplification of power electronics for ion thruster neutralizers (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A need exists for less complex and lower cost ion thruster systems. Design approaches and the demonstration of neutralizer power electronics for relaxed neutralizer keeper, tip heater, and vaporizer requirements are discussed. The neutralizer circuitry is operated from a 200 to 400 V bus and demonstrates an order of magnitude reduction in parts count. Furthermore, a new technique is described for regulating tip heater power and automatically switching over to provide keeper power with only four additional components. A new design to control the flow rate of the neutralizer with one integrated circuit is also presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-83004 , E-1441 , NAS 1.15:83004 , AIAA PAPER 82-1880 , Intern. Electric Propulsion Conf.; Nov 17, 1982 - Nov 19, 1982; New Orleans
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    Thermionic technology infrastructure for space power (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An assessment is made of the potential effectiveness, designs, and technological difficulties involved in the construction of space nuclear reactors coupled to thermionic energy converters (TEC). The TECs can be positioned either inside or outside of the reactor core. The out-of-core design lowers the reactor shielding requirements, as well as removing the need for mechanically pumped coolant for the reactor. R&D is still needed for the heat pipes for the reactor and the collectors, electrical insulation, and to reduce the potential losses in the interelectrode space. A cylindrical converter for the out-of-core configuration consists of a tungsten emitter heated by a tungsten-lithium heat pipe. The collector is a layer of tungsten oxide deposited on a Nb-1%Zr alloy, and has been tested at emitter temperatures of 1300-1850 K and a collector temperature range of 700-850 K. A design of a superheated thermionic converter is described, noting that a prototype has been operated at 1730 K for 12,000 hr.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 67
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    Design of large, low-concentration-ratio solar arrays for low earth orbit applications (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 68
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    Space solar cell technology development - A perspective (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The developmental history of photovoltaics is examined as a basis for predicting further advances to the year 2000. Transistor technology was the precursor of solar cell development. Terrestrial cells were modified for space through changes in geometry and size, as well as the use of Ag-Ti contacts and manufacture of a p-type base. The violet cell was produced for Comsat, and involved shallow junctions, new contacts, and an enhanced antireflection coating for better radiation tolerance. The driving force was the desire by private companies to reduce cost and weight for commercial satellite power supplies. Liquid phase epitaxial (LPE) GaAs cells are the latest advancement, having a 4 sq cm area and increased efficiency. GaAs cells are expected to be flight ready in the 1980s. Testing is still necessary to verify production techniques and the resistance to electron and photon damage. Research will continue in CVD cell technology, new panel technology, and ultrathin Si cells.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 69
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    Cassegrainian concentrator solar array exploratory development module (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A miniaturized Cassegrainian concentrator solar array concept is under development to reduce the cost of multi-kW spacecraft solar arrays. A primary parabolic reflector directs incoming solar energy to a secondary, centrally mounted inverted hyperbolic reflector and down onto a solar cell mounted on an Mo heat spreader on a 0.25 mm thick Al heat fin. Each unit is 12.7 mm thick, which makes the concentrator assembly roughly as thick as a conventional panel. The output is 100 W/sq and 20 W/kg, considering 20% efficient Si cells at 100 suns. A tertiary light catcher is mounted around the cell to ameliorate optic errors. The primary reflector is electroformed Ni with protective and reflective coatings. The cells have back surface reflectors and a SiO antireflective coating. An optical efficiency of 80% is projected, and GaAs cells are being considered in an attempt to raise cell efficiencies to over 30%.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 70
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    Thermoelectric conversion for space nuclear power (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A lightweight, high performance nuclear reactor power system can offer significant advantages for many space missions. Conceptual design has been completed for the SP-100, a system which utilizes many thermoelectric converters and is capable of delivering 100 kilowatts of electrical power. A reference design, using thermoelectric materials with an average figure of merit of 0.001/K and a reactor heat pipe temperature of 1500 K, is presented which has a mass of 2280 kg not including contingency. The sensitivity of system mass to changes in the configuration and thermoelectric material properties are presented
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 71
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    Computer modeling of thermoelectric generator performance (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Features of the DEGRA 2 computer code for simulating the operations of a spacecraft thermoelectric generator are described. The code models the physical processes occurring during operation. Input variables include the thermoelectric couple geometry and composition, the thermoelectric materials' properties, interfaces and insulation in the thermopile, the heat source characteristics, mission trajectory, and generator electrical requirements. Time steps can be specified and sublimation of the leg and hot shoe is accounted for, as are shorts between legs. Calculations are performed for conduction, Peltier, Thomson, and Joule heating, the cold junction can be adjusted for solar radition, and the legs of the thermoelectric couple are segmented to enhance the approximation accuracy. A trial run covering 18 couple modules yielded data with 0.3% accuracy with regard to test data. The model has been successful with selenide materials, SiGe, and SiN4, with output of all critical operational variables.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 72
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    Alkaline regenerative fuel cell energy storage system for manned orbital satellites (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: It is pointed out that the alkaline regenerative fuel cell system represents a highly efficient, lightweight, reliable approach for providing energy storage in an orbiting satellite. In addition to its energy storage function, the system can supply hydrogen and oxygen for attitude control of the satellite and for life support. A summary is presented of the results to date obtained in connection with the NASA-sponsored fuel cell technology advancement program, giving particular attention to the requirements of the alkaline regenerative fuel cell and the low-earth mission. Attention is given to system design guidelines, weight considerations, gold-platinum cathode cell performance, matrix development, the electrolyte reservoir plate, and the cyclical load profile tests.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 73
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    Design of a 35-kilowatt bipolar nickel-hydrogen battery for low-earth-orbit applications (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N82-24647)
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 74
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    Development of improved hydrogen recombination in sealed nickel-cadmium aerospace cells (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The identification and measurement of a hydrogen recombination mechanism in nickel-cadmium cells has made deep reconditioning on a battery basis safe and feasible. Deep reconditioning has been shown to improve performance and increase life of nickel-cadmium batteries in geosynchronous orbit applications. The hydrogen recombination mechanism and data supporting the mechanism are presented. Parameteric cell design experiments are described which have lead to the definition of nickel-cadmium cells capable of high rate overdischarge. Nickel-cadmium cells with optimum hydrogen recombination capability were successfully cycled for 7 seasons in simulation of the geosynchronous orbit regime at 75 percent depth-of-discharge with extensive midseason and end-of-season overdischarge at rates ranging from C/4 to C/20.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 75
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    High voltage distribution and grounding in high power spacecraft (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Many space missions proposed for the time period from 1985 to 2000 will require large spacecraft to support the onboard loads. In some cases, large electrical power systems will be needed to supply the electrical/electronic equipment loads. These electronic systems will be used for communications, radar, and experimental equipment for aid to earth's overcrowded communication systems, exploration of new energy resources, space exploration, and eventually to supplement terrestrial electric power utilities. For the near term (1985-1990), some of these systems have power levels to 50 kW. The long-term programs, 1990 to post-2000, could possibly have demands in the order of multimegawatts. The problems which have to be solved to construct the required high-voltage power supply systems are considered. Data and conceptual designs generated are found to indicate that grounding and bonding for high power systems can be accomplished in spacecraft by using either manual or automatic joining of the structural members.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 76
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    Galileo spacecraft power distribution and autonomous fault recovery (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: There is a trend in current spacecraft design to achieve greater fault tolerance through the implemenation of on-board software dedicated to detecting and isolating failures. A combination of hardware and software is utilized in the Galileo power system for autonomous fault recovery. Galileo is a dual-spun spacecraft designed to carry a number of scientific instruments into a series of orbits around the planet Jupiter. In addition to its self-contained scientific payload, it will also carry a probe system which will be separated from the spacecraft some 150 days prior to Jupiter encounter. The Galileo spacecraft is scheduled to be launched in 1985. Attention is given to the power system, the fault protection requirements, and the power fault recovery implementation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 77
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    Development of management technology for large power systems (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Autonomous power management has been proposed as a method to perform optimization of power subsystem performance in connection with the management of multikilowatt space platforms. A concept for a 250-kW utility-type power subsystem was developed. A Cassegrain concentrator solar array primary source is conditioned by a solar array switching unit which supplies seventeen 220 +20 Vdc power channels. A power management subsystem provides the monitoring and control of the overall electrical power subsystem. The discussed system concept for autonomous management of high power space platforms utilizes on-board microprocessors in a decentralized data management architecture. A data bus protocol and a data bus contention resolution scheme were selected in conjunction with the dencentralized management architecture.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 78
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    Results of the automated power systems management /APSM/ program and future technology implementation (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The APSM program was initiated in 1975. The purpose of this program was to develop and demonstrate the technology and benefits of autonomous operation of planetary spacecraft power systems to meet the projected requirements of future missions. Development of the APSM program was based on implementing a selected set of autonomous functions in a state-of-the-art breadboard power system. A distributed microcomputer system was developed to implement the functions. Several critical programmatic elements were identified as necessary to implement autonomous functions. These elements, including proper skill combination, well defined autonomous functions, and management of the software design and development task, were found to be more significant than hardware management. The incorporation of APSM technology in future space programs is also discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 79
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    A perspective of power management for large space platforms (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: NASA and military applications for high power spacecraft are presently being planned. A perspective of autonomous power management for low earth orbit large space platforms is presented. A multichannel 250 kWe utility-type power subsystem is used as a baseline system. The need for automation is reviewed, based on power subsystem complexity, survivability requirements, and cost benefits. On-board versus ground management is discussed with respect to these needs. In addition, the utilization of autonomous power management to enable technology readiness of large complex power subsystems is described. Recommendations are made for further technology thrusts.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 80
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    NASA space power system automation (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Investigations were conducted with the objective to identify technology issues in automating space power systems, rank critical technology needs, and recommend technology objectives. It was found that automation can offer significant benefits to space power systems. Automation, or even autonomy, may become an absolute requirement for system implementation. Automation of large power systems will be achieved through evolution. It is pointed out that 'systems engineering' or more specifically, 'automation systems engineering' must be strongly emphasized and done early in the development process. System control can be centralized, distributed or a combination of the two. An important requirement for automation implementation is related to the availability of qualified hardware and software components.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 81
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    OAO-3 end of mission power subsystem evaluation (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N83-11583)
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 82
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    Solar array switching power management (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Solar array power switching concepts are explored for a 250 kWe manned LEO platform, a 50-250 kWe load for an orbit transfer vehicle (OTV), and an unmanned platform with a 50 kWe load in GEO. A solar array switching power management (SASPM) system is under study to satisfy the switching demands. Direct connections to arrays would be implemented for voltage regulations, power distribution, and the capability of reconfiguring the arrays to meet requirements. Mission characteristics that would require the power sources were explored. The LEO platform was projected to use a concentrator, have no reconfigurability, use 250 NiH2 batteries, supply 80-0 Vdc to an ion drive, and have a 20-30 yr life. Both GEO and OTV arrays were planar, would feature reconfigurability, and supply 800 Vdc to an ion drive. NiH2 batteries would be on the OTV, while the GEO spacecraft would use AgH2 cells. A block diagram of the basic switching configuration is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 83
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    Comparison of evolving photovoltaic and nuclear power systems for earth orbital applications (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Photovoltaic and fission reactor orbital power systems are compared in terms of the end-to-end system power-to-mass ratios. Three PV systems are examined, i.e., a solid substrate with a cell array and a NiCd battery, a modified SEP array and an NiH2 battery, and a 62-micron Si cell array and a fuel cell. All arrays were modeled to be 13.5% efficient and to produce 25 kW dc. The SP-100 reactor consists of the heat source, radiation shield, heat pipes to transfer thermal energy from the reactor to thermoelectric elements, and a waste heat radiator. Consideration is given to system applications in orbits ranging from LEO to GEO, and to mission durations of 1, 5, and 10 yr. PV systems are concluded to be flight-proven, useful out of radiation belts, and best for low to moderate power levels. Limitations exist for operations where atmospheric drag may become a factor and due to the size of a large PV power supply. Space nuclear reactors will continue under development and uses at high power levels and in low altitude orbits are foreseen.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 84
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    Long titanium heat pipes for high-temperature space radiators (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Titanium heat pipes are being developed to provide light weight, reliable heat rejection devices as an alternate radiator design for the Space Reactor Power System (SP-100). The radiator design includes 360 heat pipes, each of which is 5.2 m long and dissipates 3 kW of power at 775 K. The radiator heat pipes use potassium as the working fluid, have two screen arteries for fluid return, a roughened surface distributive wicking system, and a D-shaped cross-section container configuration. A prototype titanium heat pipe, 5.5-m long, has been fabricated and tested in space-simulating conditions. Results from startup and isothermal operation tests are presented. These results are also compared to theoretical performance predictions that were used to design the heat pipe initially.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IECEC ''82; Seventeenth Intersociety Energy Conversion Engineering Conference; Aug 08, 1982 - Aug 12, 1982; Los Angeles, CA
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  • 85
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    Operation of the J-series thruster using inert gas (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N83-17587)
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1929 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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  • 86
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    A simplified design procedure for life prediction of rocket thrust chambers (1982)
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    Publication Date: 2019-07-13
    Description: An analytical procedure for predicting thrust chamber life is developed. The hot-gas-wall ligaments separating the coolant and combustion gas are subjected to pressure loading and severe thermal cycling. The resulting stresses interact during plastic straining causing incremental bulging of the ligaments during each firing cycle. This mechanism of plastic ratcheting is analyzed and a method using a yield surface for combined bending and membrane loading developed for determining the incremental permanent deflection and progressive thinning near the center of the ligaments. Fatigue and tensile instability are analyzed as possible failure modes. Results of the simplified analyses compare favorably with available experimental data and finite element analysis results for OFHC (Oxygen Free High Conductivity) copper. They are also in reasonably good agreement with experimental data for NARloy Z, a copper-zirconium-silver alloy developed by the Rocketdyne Division of Rockwell International.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1251 , Joint Propulsion Conference; Jun 21, 1982 - Jun 23, 1982; Cleveland, OH
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  • 87
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    The electrothermal ramjet (1982)
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    Publication Date: 2019-07-13
    Description: An electrothermal ramjet configuration is examined as a possible alternative to rail guns and mass drivers for high acceleration launch missions. For a specific mission (earth escape) the idealized performance of the electrothermal ramjet, the electrothermal rocket and the electromagnetic acceleration system are compared. This comparison indicates that the gross performance of the ramjet compares favorably with that of the ideal electromagnetic acceleration system. A specific configuration for the ramjet is chosen and models for the dynamics, thermodynamics and fluid mechanics are presented. Results of calculations for a typical supersonic launch cycle suggest that pressure, temperature and power demand profiles associated with ramjet operation should be reasonable. A light gas gun is proposed to accelerate the vehicle to the critical velocity where efficient ramjet operation can begin. The theoretical performance of the ramjet is also shown to be substantially better than that of the light gas gun at high velocities.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1216 , Joint Propulsion Conference; Jun 21, 1982 - Jun 23, 1982; Cleveland, OH
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  • 88
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    Propulsion system options for low-acceleration orbit transfer (1982)
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    Publication Date: 2019-07-13
    Description: The present inventory of developed bipropellant engines suitable for the orbit transfer of large space structures is based on the use of storable propellants (nitrogen tetroxide/monomethyl hydrazine). A range of engine sizes from 22N (5 lbF) to over 26,690N (6000 lbF) is available. These engines are capable of delivering specific impulse values from 2795 to 3089 N-s/kg (285 to 315 lbF-sec/lbm). A comparison is made between the attainable specific impulse of these demonstrated engines and future low-thrust engine designs which can utilize LOX/RP-1, LOX-methane, and LOX/hydrogen propellants. The requirements for cooling these small engines for multi-hour burns as well as the merits of operating at nonoptimum performance mixture ratios to improve cooling margins and reduce tank volumes are addressed in this paper.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1196 , Joint Propulsion Conference; Jun 21, 1982 - Jun 23, 1982; Cleveland, OH
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  • 89
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    Characterization of advanced electric propulsion systems (1982)
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    Publication Date: 2019-07-13
    Description: Characteristic parameters of several advanced electric propulsion systems are evaluated and compared. The propulsion systems studied are mass driver, rail gun, argon MPD thruster, hydrogen free radical thruster and mercury electron bombardment ion engine. Overall, ion engines have somewhat better characteristics as compared to the other electric propulsion systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1246 , Joint Propulsion Conference; Jun 21, 1982 - Jun 23, 1982; Cleveland, OH
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  • 90
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    Analytical modeling of spacecraft power systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Power system components are reviewed. Battery and solar array models are discussed. Shunt regulators, dc-dc converters, and cabling are also discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-166820 , NAS 1.26:166820 , TRW-38651-000
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  • 91
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    Characterization of advanced electric propulsion systems (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Characteristics of several advanced electric propulsion systems are evaluated and compared. The propulsion systems studied are mass driver, rail gun, MPD thruster, hydrogen free radical thruster and mercury electron bombardment ion engine. These are characterized by specific impulse, overall efficiency, input power, average thrust, power to average thrust ratio and average thrust to dry weight ratio. Several important physical characteristics such as dry system mass, accelerator length, bore size and current pulse requirement are also evaluated in appropriate cases. Only the ion engine can operate at a specific impulse beyond 2000 sec. Rail gun, MPD thruster and free radical thruster are currently characterized by low efficiencies. Mass drivers have the best performance characteristics in terms of overall efficiency, power to average thrust ratio and average thrust to dry weight ratio. But, they can only operate at low specific impulses due to large power requirements and are extremely long due to limitations of driving current. Mercury ion engines have the next best performance characteristics while operating at higher specific impulses. It is concluded that, overall, ion engines have somewhat better characteristics as compared to the other electric propulsion systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-167885 , NAS 1.26:167885
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  • 92
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    Space power subsystem automation technology (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The technology issues involved in power subsystem automation and the reasonable objectives to be sought in such a program were discussed. The complexities, uncertainties, and alternatives of power subsystem automation, along with the advantages from both an economic and a technological perspective were considered. Whereas most spacecraft power subsystems now use certain automated functions, the idea of complete autonomy for long periods of time is almost inconceivable. Thus, it seems prudent that the technology program for power subsystem automation be based upon a growth scenario which should provide a structured framework of deliberate steps to enable the evolution of space power subsystems from the current practice of limited autonomy to a greater use of automation with each step being justified on a cost/benefit basis. Each accomplishment should move toward the objectives of decreased requirement for ground control, increased system reliability through onboard management, and ultimately lower energy cost through longer life systems that require fewer resources to operate and maintain. This approach seems well-suited to the evolution of more sophisticated algorithms and eventually perhaps even the use of some sort of artificial intelligence. Multi-hundred kilowatt systems of the future will probably require an advanced level of autonomy if they are to be affordable and manageable.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CP-2213 , M-371 , NAS 1.55:2213 , Oct 28, 1981 - Oct 29, 1981; Marshall Space Flight Center, AL; United States
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  • 93
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    Geometry and starvation effects in hydrodynamic lubrication (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Numerical methods were used to determine the effects of lubricant starvation on the minimum film thickness under conditions of a hydrodynamic point contact. Starvation was effected by varying the fluid inlet level. The Reynolds boundary conditions were applied at the cavitation boundary and zero pressure was stipulated at the meniscus or inlet boundary. A minimum-film-thickness equation as a function of both the ratio of dimensionless load to dimensionless speed and inlet supply level was determined. By comparing the film generated under the starved inlet condition with the film generated from the fully flooded inlet, an expression for the film reduction factor was obtained. Based on this factor a starvation threshold was defined as well as a critically starved inlet. The changes in the inlet pressure buildup due to changing the available lubricant supply are presented in the form of three dimensional isometric plots and also in the form of contour plots.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-82807 , E-1147 , NAS 1.15:82807 , AVRADCOM-TR-82-C-17 , Meeting of the Propulsion and Energetics Panel Symp. on Problems in Bearings and Lubrication; May 31, 1982 - Jun 03, 1982; Ottawa; Canada
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  • 94
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    Reusable Rocket Engine Maintenance Study (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Approximately 85,000 liquid rocket engine failure reports, obtained from 30 years of developing and delivering major pump feed engines, were reviewed and screened and reduced to 1771. These were categorized into 16 different failure modes. Failure propagation diagrams were established. The state of the art of engine condition monitoring for in-flight sensors and between flight inspection technology was determined. For the 16 failure modes, the potential measurands and diagnostic requirements were identified, assessed and ranked. Eight areas are identified requiring advanced technology development.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165569 , RI/RD81-226
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  • 95
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    Parallel plate radiofrequency ion thruster (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N83-12142)
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1937 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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  • 96
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    Improved ion containment using a ring-cusp ion thruster (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N83-13164)
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1928 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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  • 97
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    The flexible magnetic field thruster (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The thruster is designed so that ion currents to various internal surfaces can be measured directly; these measurements facilitate calculations of the distribution of ion currents inside the discharge chamber. Experiments are described suggesting that the distribution of ion currents inside the discharge chamber is strongly dependent on the shape and strength of the magnetic field but independent of the discharge current, discharge voltage, and neutral flow rate. Measurements of the energy cost per plasma ion suggest that this cost decreases with increasing magnetic field strength as a consequence of increased anode shielding from the primary electrons. Energy costs per argon plasma ion as low as 50 eV are measured. The energy cost per beam ion is found to be a function of the energy cost per plasma ion, extracted ion fraction, and discharge voltage. Part of the energy cost per beam ion has to do with creating many ions in the plasma and then extracting only a fraction of them into the beam. The balance of the energy goes into accelerating the remaining plasma ions into the walls of the discharge chamber.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1936 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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  • 98
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    A model for mercury orificed hollow cathodes - Theory and experiment (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A phenomenological model is developed which provides a qualitative description of the basic physical processes taking place within a mercury orifice hollow cathode. This model can be used to predict, to first order, the important cathode operating parameters such as emission length and insert temperature. By assuming an idealized ion production region within which most of the plasma processes are concentrated, the model can be expressed analytically as a simple set of equations which relate cathode dimensions and specifiable operating conditions, such as mass flow rate and discharge current, to such important parameters as insert temperature and plasma properties. A comparison of theoretical and experimental results shows that, if the excited state energy flux is neglected, the model provides relatively accurate predictions of emission length, emission surface temperature, plasma density, and fraction of discharge current due to volume ionization
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1889 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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  • 99
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    The design and technology development for A 150 mlb resistojet for H2 or NH3 (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A 150 mlb thrust level hybrid resistojet which may operate on either H2 or NH3 is described whose design technique allows temperature distribution forecasting by means of a microcomputer-implemented mathematical model. The longer computer run times that accompany the exclusive use of BASIC, relative to assembled languages, are offset by the flexibility offered and the reduction of reprogramming and debugging efforts. The integration of a compact first-stage coiled heater with a concentric tubular gas heater offers direct matching of the 28 V terminal of the spacecraft system, while keeping maximum heater wall temperatures to less than 60 K over that of the gas temperature at the throat. Among the novel materials employed are grain-stabilized rhenium for heating elements and high purity aluminas for insulators.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1949 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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    Results of the mission profile life test (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Seven J series 30-cm diameter thrusters have been tested in segments of up to 5,070 hr, for 14,541 hr in the Mission Profile Life Test facility. Test results have indicated the basic thruster design to be consistent with the lifetime goal of 15,000 hr at 2-A beam. The only areas of concern identified which appear to require additional verification testing involve contamination of mercury propellant isolators, which may be due to facility constituents, and the ability of specially covered surfaces to contain sputtered material and prevent flake formation. The ability of the SCR, series resonant inverter power processor to operate the J series thruster and autonomous computer control of the thruster/processor system were demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1905 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
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