| Solid Propellant Ingredient Migration Studies |
JUN 1982 |
42 pages |
| Authors:
L. A. Dee; L. J. Emmanuel; M. E. Fiske; L. Ninomiya; AIR FORCE ROCKET PROPULSION LAB EDWARDSAFB CA
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 | Reported herein is the development of a unique solid propellant ingredient separation device. Use of this separation device was applied to the determination of labile solid propellant ingredient migration rates, propellant/liner plasticizer distribution ratio, and complete solid propellant ingredient analysis. |
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| Aluminum Hydride Propellant Shelflife |
NOV 1974 |
87 pages |
| Authors:
W. E. Baumgartner; LOCKHEED PROPULSION CO REDLANDS CA
|
| The thermal stability and service life capability of an A1H/TVOPA and PCDE based propellants were evaluated relying upon accelerated surveillance tests accompanied by X-ray analyses, off-gas analyses, tensile testing and determination of creep failure distributions. The Halpin statistical cumulative damage analysis principle was implemented for interpreting the creep failure test data. Catalytic gas scavengers were shown to extend the 20C shelflife of A1H/TVOPA propellants to better than 3 years. However, ... |
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| Aluminum Hydride Propellant Shelflife. |
JAN 1972 |
45 pages |
| Authors:
W. E. Baumgartner; Y. A. Tajima; LOCKHEED PROPULSION CO REDLANDS CA
|
| The 70 F shelflife of aluminum hydride propellants can be improved by adding small quantities of noble metal catalysts for condensing internally generated hydrogen gas. This program is designed to provide the factual demonstration that the resulting degree of stabilization is sufficient to assure a minimum five years shelflife under silo conditions. To effect such demonstration, samples of a ballistically optimized AlH3/NF2 propellant have been placed into storage at 20, ... |
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| Fast-Burning Rate/High Slope Propellant Technology Program. |
FEB 1971 |
37 pages |
| Authors:
R. L. Lou; A. Katzakian; AEROJET-GENERAL CORP SACRAMENTO CA
|
| This is the second quarterly progress report on work conducted to advance state-of-the-art with regard to formulation of practical fast-burning and high pressure-exponent propellants. Primary emphasis was directed toward optimization of the processing, mechanical, and ballistic properties. Approaches to improving propellant processability included variation of amount and type of plasticizer, use of blocked or hindered isocyanate curing agents, evaluation of epoxide curing agents and modification of R-45M prepolymer. The last ... |
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| Stability and Compatibility Studies on Advanced Rocket Propellant Components |
JUL 1970 |
166 pages |
| Authors:
Ivan C. Smith; Raymond E. Foscante; John W. Nebgen; A. D. McElroy; MIDWEST RESEARCH INST KANSAS CITY MO
|
| A number of candidate advanced propellant ingredients were studied with the objective of obtaining definitive information regarding their usefulness in new propellant systems. The research was laboratory based, involved small quantities (generally less than 100 mg.) of the ingredient, and dealt generally with the stability of individual ingredients and with stability- compatibility of two or more components of proposed propellants. The ingredients studied include: Perchlorates--HAP, HP-2, DOAP and AP (for ... |
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| DEVELOPMENT OF A COMPOSITE PROPELLANT |
22 JUN 1965 |
39 pages |
| Authors:
James L. Chaille; ROHM AND HAAS CO HUNTSVILLE AL
|
| A program was undertaken to develop a composite propellant technology and capability based on plasticized carboxy-terminated polybutadiene polymer (CTPB). The effects of processing and compositional variables on cure time, curing rate and mechanical properties were studied with dummy propellant formulations. Highly plasticized compositions were shown to have adequate mechanical properties and to be easily castable. Ballistic studies made on the CTPB propellants defined the effect of compositional changes on burning ... |
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Reports by Keyword(s)
SOLID ROCKET PROPELLANT PLASTICIZERSZ
