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Explore propulsion reports from NASA NTRS and DOE OSTI. Search rocket engines, electric propulsion and thrusters; verify designs and performance in the source documents.

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NASA NTRS1993

FNAS/summer faculty fellowship research continuation program. Task 6: Integrated model development for liquid fueled rocket propulsion systems. Task 9: Aspects of model-based rocket engine condition monitoring and control

The objective of Phase I of this research effort was to develop an advanced mathematical-empirical model of SSME steady-state performance. Task 6 of Phase I is to develop component specific modification strategy for baseline case influence coefficient matrices. This report describes the background of SSME performance characteristics and provides a description of the control variable basis of three different gains models. The procedure used to establish influence coefficients for each of these three models is also described. Gains model analysis results are compared to Rocketdyne's power balance model (PBM).

Santi, L. Michael↗
NASA NTRS1968

Advances in Tactical Rocket Propulsion Conference Proceedings

An AGARD Colloquium on 'Progress in Tactical Rocket Propulsion' was held at La Jolla, California, on April 22 and 23, 1965. The unclassified papers, or unclassified versions of classified papers, presented at this meeting form the contents of the present AGARD conference proceedings, which has been identified by a new title that reflects more properly the scope of the remaining technical papers. The articles contained in this volume represent significant evaluations of the status of solid-propellant, liquid-propellant and hybrid-propellant rocket. development. Together with the reviews, they should provide a useful reference source for research workers and students alike.

S S Penner↗
NASA NTRS1968

Advances in solid-fuel propulsion systems for tactical rockets

The objective of this paper is to present a brief survey of three areas in which advances of solid propulsion have enabled improved design of tactical rockets. The three areas are microwave attenuation, acceleration-combustion interactions, and performance optimization. In each of the three areas, improved understanding has significantly contributed to rocket technology. The problems remaining are far from solved, however, and the three subjects are fruitful areas for fundamental investigations.

Charles B Henderson↗
NASA NTRS1971

Rocket propulsion by thermonuclear micro-bombs ignited with intense relativistic electron beams.

Discussion of a method for the ignition of a thermonuclear microbomb by means of an intense relativistic electron beam with regard to its potential application to rocket propulsion. With such a system, exhaust velocities up to 1000 km/sec, corresponding to a specific impulse of 100,000 sec, seem to be within the realm of possibility. The rocket is propelled by a chain of thermonuclear microbombs exploded in a concave magnetic mirror produced by superconducting field coils. The magnetic pressure of the field reflects the fireball generated by the explosion. For the large capacitor bank required to generate the intense relativistic electron beam, a desirable lightweight design may be possible through use of ferroelectric materials. Because of the high cost of the T-D and He 3-D thermonuclear material, the system has to be optimized by minimizing the T-D and He 3-D consumption by a proper TD and He 3-D fuel to hydrogen propellant mass ratio, leading to a larger total system mass than would be absolutely necessary.

Winterberg, F.↗
NASA NTRS1974

Feasibility of rotating fluidized bed reactor for rocket propulsion

The rotating fluidized bed reactor concept is outlined, and its application to rocket propulsion is discussed. Experimental results obtained indicate that minimum fluidization correlations commonly in use for 1-g beds can also be applied to multiple-g beds. It was found that for a low thrust system (20,000 lbf) the fuel particle size and/or particle stress play a limiting role on performance. The superiority of U-233 as a fuel for this type of rocket engine is clearly demonstrated in the analysis. The maximum thrust/weight ratio for a 90,000N thrust engine was found to be approximately 65N/kg.

Ludewig, H.↗
NASA NTRS1978

Optimization and evaluation of main liquid rocket propulsion systems for advanced earth-to-orbit shuttles

A computerized preliminary design system is used to evaluate potential main liquid-rocket propulsion systems for advanced technology winged single-stage-to-orbit launch vehicles. Evaluated are trade-offs between ascent flight trajectory performance and flight vehicle sizing driven by engine mass and propellant requirements. Numerous mission, flight, and vehicle-related requirements and constraints are satisfied in the design process. With the design system, five dual-mode propulsion system concepts are compared to a baseline hydrogen and oxygen system in terms of the changes in vehicle dry mass and gross mass.

Wilhite, A. W.↗
NASA NTRS1986

Solar Thermal Rocket Propulsion

Paper analyzes potential of solar thermal rockets as means of propulsion for planetary spacecraft. Solar thermal rocket uses concentrated Sunlight to heat working fluid expelled through nozzle to produce thrust.

Sercel, J. C.↗
NASA NTRS1989

Effect of Correlation on Multi-Engine Rocket Propulsion Systems

A matter of great concern in the design and operation of multi-engine rocket propulsion systems is the effect of the premature shutdown of one engine on the vehicle. This probability that a premature shutdown will cause a vehicle loss is termed correlation. Based on airbreathing experiences as well as rocket engine data the best estimate of this correlation is made and then applied to the overall multi-engine reliability problem to demonstrate its potential effect. At this point, follow-on analyses are pointed out that illustrate how any potential failures that may cause a correlatable event can be eliminated; thus bringing this correlation to almost 0.

Baker, J. R.↗
NASA NTRS1990

Utilizing air-turborocket and rocket propulsion for a single-stage-to-orbit vehicle

With appropriate technology advances, a horizontal-takeoff single-stage-to-orbit (SSTO) launch vehicle could be designed which utilizes a combination of air-turborocket (ATR) and rocket propulsion systems. Such a vehicle is currently under study at Langley, and this paper presents the results of that study. Estimated vehicle weight characteristics, engine characteristics, geometry, aerodynamics, performance, structures, and subsystems are summarized. Trade studies performed on the reference vehicle to optimize the initial thrust-to-weight ratio (T/W) and the T/W after transition to the rocket phase with respect to vehicle weights are also presented. Throughout the vehicle presentation, special attention is given to the design issues, sensitivities, and performance parameters involved.

Lepsch, Roger A., Jr.↗
NASA NTRS1991

Solid rocket propulsion

The solid rocket motor failure database; current programs; and shortfalls of solid rocket propulsion are examined. This presentation is represented by viewgraphs.

Nichols, Ronald L.↗
NASA NTRS1991

The rationale/benefits of nuclear thermal rocket propulsion for NASA's lunar space transportation system

Two nuclear thermal rocket (NTR) technology options are examined - one derived from the graphite-moderated reactor concept developed by NASA and the AEC under the Rover/NERVA (Nuclear Engine for Rocket Vehicle Application) programs, and a second concept, the Particle Bed Reactor. The paper also summarizes NASA's lunar outpost scenario, compares relative performance provided by different lunar space transportation system concepts, and discusses important operational issues (e.g., reusability, engine 'end-of-life' disposal, etc.) associated with using this important propulsion technology.

Borowski, Stanley K.↗
NASA NTRS1991

The NASA/DOE/DOD nuclear rocket propulsion project - FY 1991 status

NASA has initiated planning and critical technology development for nuclear rocket propulsion systems for Space Exploration Initiative missions to the moon and to Mars. Interagency agreements are being negotiated between NASA, the Department of Energy, and the Department of Defense for joint technology development activities. This paper summarizes the activities of the NASA project planning team in FY 1990 that led to the draft Nuclear Propulsion Project Plan, outlines the FY 1991 Interagency activities, and describes the current status of the project plan.

Clark, John S.↗
NASA NTRS1991

On the development of system-theoretic tools for the design of integrated health monitoring and controls for rocket propulsion systems

As NASA continues to develop various advanced propulsion technologies for space exploration, two factors are becoming increasingly dominant in design specifications: increase operational reliability and decrease operational cost. One approach that has been proposed to meet these challenges is to incorporate into current and future rocket propulsion systems some sort of diagnostic/monitoring capability in the form of a Health Monitoring System (HMS). HMS technology offers the promise of increased operational reliability through its ability to assess system performance, detect and isolate degradations and/or failures, and modify system operation so as to minimize negative effects on performance. The purpose of this research is to study, from a systems engineering perspective, the particular issues of analysis and synthesis for generic HMS's.

Helmicki, Arthur J.↗
NASA NTRS1991

Nuclear rocket propulsion technology - A joint NASA/DOE project

NASA and the DOE have initiated critical technology development for nuclear rocket propulsion systems for SEI human and robotic missions to the moon and to Mars. The activities and project plan of the interagency project planning team in FY 1990 and 1991 are summarized. The project plan includes evolutionary technology development for both nuclear thermal and nuclear electric propulsion systems.

Clark, John S.↗
NASA NTRS1991

Nuclear thermal rocket propulsion application to Mars missions

Options for vehicle configurations are reviewed in which nuclear thermal rocket (NTR) propulsion is used for a reference mission to Mars. The scenario assumes an opposition-class Mars transfer trajectory, a 435-day mission, and the use of a single nuclear engine with 75,000 lbs of thrust. Engine parameters are examined by calculating mission variables for a range of specific impulses and thrust/weight ratios. The reference mission is found to have optimal values of 925 s for the specific impulse and thrust/weight ratios of 4.0 and 0.06 for the engine and total stage ratios respectively. When the engine thrust/weight ratio is at least 4/1 the most critical engine parameter is engine specific impulse for reducing overall stage weight. In the context of this trans-Mars three-burn maneuver the NTR engine with an expander engine cycle is considered a more effective alternative than chemical/aerobrake and other propulsion options.

Emrich, W. J., Jr.↗
NASA NTRS1994

Integrated Booster-Rocket Propulsion Module

Report summarizes study of conceptual integrated booster propulsion module for use in launching spacecraft. Substitution of integrated propulsion modules for multiple engines of present booster rockets intended to simplify ground operations and reduce costs.

Rhodes, Russell E.↗