On the characterization of multiaxial data in terms of the strain energy concept
Continuous media theory for characterization of multiaxial mechanical behavior of solid propellants - strain energy concept
SOLID PROPELLANT↗
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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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The ''delta p'' approach from Nike combustion instability
Applicability of delta p approach to study of combustion instability in liquid and solid propellant rocket engines
STAGNATION FLOW↗
Results from short-duration altitude-chamber techniques for simulating rocket base heating problems.
Short duration technique providing simulation of thermodynamic properties and composition of exhaust products of liquid and solid propellant rocket engines
SOLID PROPELLANT ROCKET ENGINE↗
Casting propellant in rocket engine
A method is described for casting a solid propellant in the casing of a rocket engine having a continuous wall with a single opening which is formed by leaves of a material which melt at a temperature of the propellant and with curved edges concentric to the curvature of the spherical casing. The leaves are inserted into the spherical casing through the opening forming a core having a greater width than the width of the single opening and with curved peripheral edges. The cast propellant forms a solid mass and then heated to melt the leaves and provide a central opening with radial projecting flutes.
Roach, J. E.↗
ON THE ANALYSIS OF LINEAR PYROLYSIS EXPERIMENTS
Linear pyrolysis experiments - fluid mechanics - equations for pyrolysis rate determinations - solid propellant combustion
PYROLYSIS↗
A biaxial tester
Biaxial sheet tester with capability of changing or maintaining uniform rectangular boundary geometry on sheet of solid propellant as function of time
SOLID PROPELLANT↗
Work on rocketry in Russia from the second half of the 19th century down to 1917 /according to the materials of the AIM ARCHIVE/
Early Soviet rocketry achievements, and solid propellant rocket theories
U.S.S.R.↗
Manufacture and deflagration of an atomic hydrogen propellant
It is observed that the use of very low temperatures (in the range from 0.1 to 1.5 K) produced by advanced cryogenic apparatus and the use of very strong magnetic fields (in the range from 50 to 100 kG) produced by superconducting magnets can yield a significant improvement in the atomic hydrogen trapping effectiveness of an H2 matrix. The use of a radioactive beta-ray emiter isotope may yield H-H2 propellants (with a specific impulse of about 740 sec) by secondary electron impact dissociations of H2 in an impregnated matrix maintained below 1 K in a strong magnetic field. Another method for manufacturing an H-H2 propellant involves bombardment of supercooled solid H2 with a cyclotron-produced beam of 10-MeV hydrogen atoms. The matrix-isolated atomic hydrogen must be used directly without prior melting as a solid propellant, and an analysis of the steady deflagration is presented.
Rosen, G.↗
Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles
A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced Earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus liquid hydrogen addition, and the addition of an aluminum/liquid hydrogen slurry on the theoretical performance of a PBAN solid propellant rocket. The space shuttle solid rocket booster was used as a reference point. All three quasi-hybrid systems theoretically offer higher specific impulse when compared with the space shuttle solid rocket boosters. However, based on operational and safety considerations, the quasi-hybrid rocket is not a practical choice for near-term Earth-to-orbit booster applications. Safety and technology issues pertinent to quasi-hybrid rocket systems are discussed.
Zurawski, Robert L.↗
Analysis of quasi-hybrid solid rocket booster concepts for advanced earth-to-orbit vehicles
A study was conducted to assess the feasibility of quasi-hybrid solid rocket boosters for advanced earth-to-orbit vehicles. Thermochemical calculations were conducted to determine the effect of liquid hydrogen addition, solids composition change plus liquid hydrogen addition, and the addition of an aluminum/liquid hydrogen slurry on the theoretical performance of a PBAN solid propellant rocket. The Space Shuttle solid rocket booster was used as a reference point. All three quasi-hybrid systems theoretically offer higher specific impulse when compared with the Space Shuttle solid rocket boosters. However, based on operational and safety considerations, the quasi-hybrid rocket is not a practical choice for near-term earth-to-orbit booster applications. Safety and technology issues pertinent to quasi-hybrid rocket systems are discussed.
Zurawski, Robert L.↗
JANNAF Combustion Subcommittee Meeting
This volume, the first of four volumes, is a collection of 33 unclassified/unlimited papers which were presented at the 33rd Joint Army-Navy-NASA-Air Force (JANNAF) Combustion Subcommittee Meeting in conjunction with the Propulsion Systems Hazards at the Naval Postgraduate School, Monterey, CA. The JANNAF papers contained in this volume review airbreathing combustion measurement, performance and control; electrothermal-chemical gun experiment and modeling; liquid propellant gun experiment and modeling; solid propellant gun interior ballistics; formulation modeling and diagnostics, ignition, and gun barrel wear modeling, blast and flash; and ram, fastcore and gas generator gun propulsion concepts.
Fry, Ronald S.↗
Manufacturing and NDE of Large Composite Aerospace Structures at MSFC
NASA's vision for transportation to orbit calls for new vehicles built with new materials technology. The goals of this new launch system development are to improve safety, dramatically reduce cost to orbit, and improve vehicle turn around time. Planned Space Shuttle upgrades include new reusable liquid propellant boosters to replace the solid propellant boosters. These boosters are to have wings and return to the launch site for a horizontal landing on an airport runway. New single and two stages to orbit concepts are being investigated. To reduce weight and improve performance composite materials are proposed for fuel and oxidizer tanks, fuel feedlines, valve bodies, aerostructures, turbomachinery components. For large composite structures new methods of fabrication are being proposed and developed. Containment of cryogenic fuel or oxidizer requires emphases on composite material densification and chemical compatibility. Ceramic matrix and fiber composites for hot rotating turbomachinery have been developed with new fabrication processes. The new requirements on the materials for launcher components are requiring development of new manufacturing and inspection methods. This talk will examine new and proposed manufacturing methods to fabricate the revolutionary components. New NDE methods under consideration include alternative X-ray methods, X-ray laminagraphy, advanced CT, Thermography, new ultrasonic methods, and imbedded sensors. The sizes, complexity, use environment, and contamination restrictions will challenge the inspection process. In flight self-diagnosis and rapid depot inspection are also goals of the NDE development.
Whitaker, Ann↗
A study of energy release in rocket propellants by a projectile impact method Annual report, 9 May 1966 - 9 May 1967
Projectile impact method for measuring rates of energy release in solid propellants subjected to strong shock waves
SOLID PROPELLANT↗
RELIABILITY ASPECTS OF AN ENGINEERING AND PLANNING STUDY FOR LARGE SOLID ROCKET BOOSTERS
Study of techniques for reliability evaluation of solid-propellant rocket motor designs
ROCKET ENGINE↗
A theoretical model for predicting aluminum oxide particle size distributions in rocket exhausts.
Model derived describing oxide particle distribution obtained from internal burning cylindrically-perforated aluminized solid propellant grains
ROCKET EXHAUST↗
Second 260-Inch Solid Motor Set for Test Firing
Second 260-inch diameter solid propellant rocket engine set for test firing
TEST FIRING↗
Low-pressure combustion studies
Low pressure combustion instability tests on solid propellants, and pressure oscillation rate of depressurization
SOLID PROPELLANT↗
Effects of Ionizing Radiation on Solid Rocket Motor Components
Problems which the solid propellant rocket engineer will encounter in designing for long-term storage in a radiation environment are discussed. A summary of present knowledge of the radiation environment is given. Mechanisms of radiation degradation and its effects on tensile properties of propellant binders are discussed qualitatively. Data from a program of irradiation of several propellants is presented. Properties of two of the propellants were changed significantly by doses of the order of 4 x 10(exp 6) rads.
RADIATION↗