Liquid propulsion - Material compatibility
Compatibility during long term storage of liquid rocket propellants with spacecraft propulsion system materials
Keller, O. F.↗
Engineering topics
Propulsion
Explore propulsion reports from NASA NTRS and DOE OSTI. Search rocket engines, electric propulsion and thrusters; verify designs and performance in the source documents.
Parametric sensitivity analysis for staged propulsive vehicles
Random variable method of analyzing propulsion system performance and stage inert weight of two stage rocket vehicles
Woodcock, G. R.↗
The utility of nuclear rockets in inter-orbit transportation
Nuclear rockets for interorbit transportation, discussing reuse economics, propulsion system performance, etc
Johnson, P. G.↗
Advanced propulsion techniques
High and low thrust hybrid rocket propulsion systems involving combinations of chemical, nuclear, thermal and electric propellants for interplanetary flights
Evvard, J. C.↗
Nuclear rocket applications
Nuclear rocket applications in Nuclear Flight Propulsion Module /NFPM/ and Reusable Nuclear Shuttle /RNS/
Gronich, S.↗
Fusion rocket concepts
Steady state thermonuclear fusion rockets, considering specific impulse, space propulsion and research priorities
Reinmann, J. J.↗
Feasibility of using a nuclear rocket engine for electrical power generation
NERVA nuclear rocket engine for space propulsion and long duration auxiliary power generation
Beveridge, J. H.↗
Laser propulsion
The use of an earth-based high-power laser beam to provide energy for earth-launched rocket vehicle is investigated. The laser beam energy is absorbed in an opaque propellant gas and is converted to high-specific-impulse thrust by expanding the heated propellant to space by means of a nozzle. This laser propulsion scheme can produce specific impulses of several thousand seconds. Payload to gross-weight fractions about an order of magnitude higher than those for conventional chemical earth-launched vehicles appear possible. There is a potential for a significant reduction in cost per payload mass in earth orbit.
Rom, F. E.↗
Development of a digital control system for a spacecraft propulsion test facility
A digital computer control and abort system which is used at NASA-Lewis research center is described. The system was designed to control test operations such as rocket engine testing, structure testing, and wind tunnel tests. Because of the nature of spacecraft system testing, particularly rocket engine testing, the unique features of the system are, control function updating at a 20 millisecond rate, continuous abort monitoring and a software system designed for short duration tests rather than continuous on-line control. To accomplish these system requirements, special hardware was designed. The presentation includes a description of the computer system and special interface hardware as well as a general description of the software used.
Smalley, R. R.↗
Mariner 9 propulsion subsystem performance during interplanetary cruise and Mars orbit insertion
On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
Cork, M. J.↗
Fusion power for space propulsion.
Principles of operation, interplanetary orbit-to-orbit mission capabilities, technical problems, and environmental safeguards are examined for thermonuclear fusion propulsion systems. Two systems examined include (1) a fusion-electric concept in which kinetic energy of charged particles from the plasma is converted into electric power (for accelerating the propellant in an electrostatic thrustor) by the van de Graaf generator principle and (2) the direct fusion rocket in which energetic plasma lost from the reactor has a suitable amount of added propellant to obtain the optimum exhaust velocity. The deuterium-tritium and the deuterium/helium-3 reactions are considered as suitable candidates, and attention is given to problems of cryogenic refrigeration systems, magnet shielding, and high-energy particle extraction and guidance.
Roth, R.↗
Development of a digital control system for a spacecraft propulsion test facility.
A digital computer control and abort system which is used at NASA-Lewis Research Center's Plum Brook Test Facilities is described. The system was designed by NASA personnel to control test operations such as rocket engine testing, structure testing, and wind tunnel tests. Because of the nature of spacecraft system testing, particularly rocket engine testing, the unique features of the system are, control function updating at a 20 millisecond rate, continuous abort monitoring and a software system designed for short duration tests rather than continuous on-line control. To accomplish these system requirements, special hardware was designed. The presentation will include a description of the computer system including special interface hardware as well as a general description of the software used.
Smalley, R. R.↗
Development of a digital control system for a spacecraft propulsion test facility.
Description of a digital computer control and abort system designed by NASA personnel to control test operations such as rocket engine testing, structure testing, and wind tunnel tests. Because of the nature of spacecraft system testing, particularly rocket engine testing, the unique features of the system are, control function updating at a 20 millisecond rate, continuous abort monitoring, and a software system designed for short duration tests rather than continuous on-line control. The presentation includes a description of the computer system and special interface hardware as well as a general description of the software used.
Smalley, R. R.↗
Hydrogen-oxygen auxiliary propulsion for the space shuttle. Volume 1: High pressure thrusters
Technology for long life, high performing, gaseous hydrogen-gaseous oxygen rocket engines suitable for auxiliary propulsion was provided by a combined analytical and experimental program. Propellant injectors, fast response valves, igniters, and regeneratively and film-cooled thrust chambers were tested over a wide range of operating conditions. Data generated include performance, combustion efficiency, thermal characteristics film cooling effectiveness, dynamic response in pulsing, and cycle life limitations.
Source record↗
Electrostatic propulsion beam divergence effects on spacecraft surfaces, volume 2
The third phase of a program to develop understanding of and tolerance-level criteria for the deleterious effects of electrostatic rocket exhaust (Cs, Cs(+), Hg, Hg(+)) and materials of rocket construction impinging on typical classes of spacecraft (S/C) surfaces was completed. Models of ion engine effluents and models describing the degradation of S/C surfaces by these effluents are presented. Experimental data from previous phases are summarized and Phase 2 data and analysis are presented in detail. The spacecraft design implications of ion engine contaminants are discussed.
Hall, D. F.↗
A brief survey of carbon/carbon refractory composites at the Jet Propulsion Laboratory
Refractory composites of carbon-carbon material are considered for application in: (a) rocket motor nozzles and skirts, (b) a unique integrated propulsion structure, and (c) planetary atmospheric entry shells. Technical developments and plans in each of these areas are described.
Robinson, E. Y.↗
Development of the Astrobee F sounding rocket system.
The development of the Astrobee F sounding rocket vehicle through the first flight test at NASA-Wallops Station is described. Design and development of a 15 in. diameter, dual thrust, solid propellant motor demonstrating several new technology features provided the basis for the flight vehicle. The 'F' motor test program described demonstrated the following advanced propulsion technology: tandem dual grain configuration, low burning rate HTPB case-bonded propellant, and molded plastic nozzle. The resultant motor integrated into a flight vehicle was successfully flown with extensive diagnostic instrumentation.-
Jenkins, R. B.↗
Investigation of matter-antimatter interaction for possible propulsion applications
Matter-antimatter annihilation is discussed as a means of rocket propulsion. The feasibility of different means of antimatter storage is shown to depend on how annihilation rates are affected by various circumstances. The annihilation processes are described, with emphasis on important features of atom-antiatom interatomic potential energies. A model is developed that allows approximate calculation of upper and lower bounds to the interatomic potential energy for any atom-antiatom pair. Formulae for the upper and lower bounds for atom-antiatom annihilation cross-sections are obtained and applied to the annihilation rates for each means of antimatter storage under consideration. Recommendations for further studies are presented.
Morgan, D. L., Jr.↗