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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Short duration technique providing simulation of thermodynamic properties and composition of exhaust products of liquid and solid propellant rocket engines
A technical analysis of the solid propellant rocket engines for use with the space shuttle is presented. The subjects discussed are: (1) solid rocket motor stage recovery, (2) environmental effects, (3) man rating of the solid propellant rocket engines, (4) system safety analysis, (5) ground support equipment, and (6) transportation, assembly, and checkout.
Spectrophotometric method for measurement of aluminum oxide particle sizes during burning of solid propellant rocket engine
A parametric study of ballistic modifications to the 120 inch diameter solid propellant rocket engine which forms part of the Air Force Titan 3 system is presented. 576 separate designs were defined and 24 were selected for detailed analysis. Detailed design descriptions, ballistic performance, and mass property data were prepared for each design. It was determined that a relatively simple change in design parameters could provide a wide range of solid propellant rocket engine ballistic characteristics for future launch vehicle applications.
Third 260-inch diameter solid propellant rocket engine test firing
Burning rate, grain geometries and propulsion parameters derived for solid propellant rocket engines
Solid propellant rocket engine performance computer programs using group transformation method
Structural instability of solid-propellant rocket engines
Static and dynamic combustion phenomena effects on grain structural design for solid propellant rocket engine
In-flight performance of solid propellant rocket engine for Delta launch vehicle
Thrust vector control for solid propellant rocket engines - liquid injection system, hot or cold gas systems, and gimballed nozzle systems
Analytical model for thrust-time curve during ignition transient of solid propellant rocket engines, discussing flame spreading
Solid propellant rocket engine environmental and static testing for use as retrograde thrustor in Atlas-Centaur space vehicle
The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.
The technical requirements for the solid propellant rocket engine to be used with the space shuttle orbiter are presented. The subjects discussed are: (1) propulsion system definition, (2) solid rocket engine stage design, (3) solid rocket engine stage recovery, (4) environmental effects, (5) manrating of the solid rocket engine stage, (6) system safety analysis, and (7) ground support equipment.
Fluid state vortex valve secondary injection control system shows considerable promise for future application to solid propellant rocket engine thrust vector control. The single axis injection system tested would be capable of providing secondary injection thrust vector control using 2000 deg F gas.
Tape wrapped ablative steel jacketed nozzle for 156 and 200 inch diameter solid propellant rocket engines
Spontaneous ignition temperature, ignition temperature, and transition temperature for metal-oxidizing gas system models of solid propellant rocket engine combustion processes