Hydrazinium nitroformate based high performance solid propellants
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
C06B-045/10
C06B-047/08
출원번호
US-0700325
(1999-05-19)
우선권정보
EP-0201696 (1998-05-20)
국제출원번호
PCT//NL99/00307
(2001-03-16)
§371/§102 date
20010316
(20010316)
국제공개번호
WO99//59940
(1999-11-25)
발명자
/ 주소
Louwers, Jeroen
Van Der Heijden, Antonius Eduard Dominicus Maria
Elands, Petrus Johannes Maria
출원인 / 주소
Nederlandse Organisatie voor toegepast-natuurwetenschappelijk Onderzoek TNO
대리인 / 주소
Muserlian, Lucas and Mercanti, LLP
인용정보
피인용 횟수 :
0인용 특허 :
8
초록
The present invention is directed to a solid propellant for rocket motors, gas generators and comparable devices, comprising a cured composition of hydrazinium nitroformate and an unsaturated hydroxyl terminated hydrocarbon compound.
대표청구항▼
1. A solid propellant for rocket motors, gas generators and comparable devices, comprising a cured composition of solid hydrazinium nitroformate, an unsaturated hydroxyl terminated hydrocarbon compound binder and a curing agent, wherein the hydrazinium nitroformate when dissolved in water as a 10 wt
1. A solid propellant for rocket motors, gas generators and comparable devices, comprising a cured composition of solid hydrazinium nitroformate, an unsaturated hydroxyl terminated hydrocarbon compound binder and a curing agent, wherein the hydrazinium nitroformate when dissolved in water as a 10 wt. % aqueous solution prior to being incorporated into the propellant has a pH of at least 4.2. Propellant according to claim 1, wherein hydroxyl terminated polybutadiene is used as the unsaturated hydroxy terminated hydrocarbon compound.3. Propellant according to claim 2, wherein the molecular weight of the uncured hydroxyl terminated polybutadiene is between 2000 and 3500 g/mol.4. Propellant according to claim 1, wherein the hydrazinium nitroformate is prepared from hydrazine and nitroform in substantially equimolar ratios.5. Propellant according to claim 4, wherein the molar ratio of hydrazine to nitroform ranges from 0.99:1 to 1:0.99.6. Propellant according to claim 1, wherein the curing agent comprises a polyfunctional isocyanate.7. Propellant according to claim 6, wherein the polyfunctional isocyanate is a polyisocyanate is selected from the group consisting of isophoron di-isocyanate, hexamethylene di-isocyanate, methylene, diphenyl, disocyanate, toluene 2,4-disocyanate and oligomers thereof.8. Propellant according to claim 1, wherein a stabilizing agent is present in the composition, selected from the group consisting of magnesium salts, aluminum salts, diphenylamine, 2-nitrodiphenylamine, p-nitromethyl-aniline, p-nitromethylaniline, centralites and combinations thereof.9. Propellant according to claim 1, wherein the hydrazinium nitroformate has a purity of between 98.8 and 100.3, based on H3O+ and pH-value of a 10 wt. % aqueous solution of hydrazinium nitroformate of at least 4.10. The propellant of claim 7, wherein said polyisocyanate is methylenediphenyldisocyanate.11. A process for the preparation of a propellant of claim 1 comprising curing a composition comprising hydrazinium nitroformate having a pH of at least 4 when dissolved in water as a 10 wt % aqueous solution prior to curing, an unsaturated hydroxy terminated hydrocarbon and curing agent optionally in the presence of an accelerator for the curing agent.12. Process of claim 11 wherein said composition is cured in the presence of an accelerator for the curing agent.13. In a rocket motor, the improvement comprising using as the solid propellant a cured composition of claim 1.14. A propellant of claim 1 wherein the curing agent and hydrocarbon have a water content less than 0.01 wt %.15. A solid propellent for rocket motors, gas generators and comparable devices comprising a cured composition of containing hydrazinium nitroformate, an unsaturated hydroxyl terminated hydrocarbon compound binder and a curing agent, said propellant being obtained by preparing a mixture of solid hydrazinium nitroformate, an unsaturated hydroxyl terminated hydrocarbon compound binder and a curing agent, followed by curing said mixture, the solid hydrazinium nitroformate, prior to being incorporated into the propellant, having a pH of at least 4 when dissolved in water as a 10 wt. % aqueous solution.
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이 특허에 인용된 특허 (8)
Wallace ; II Ingvar A. (Brigham City UT), Ambient temperature mix, cast, and cure composite propellant formulations.
Schyer H. F. R. (Zoetermeer NLX) Korting P. A. O. G. (Uwintsheul NLX) Mul J. M. (Delft NLX), High-performance propellant combinations for a rocket engine.
Thomas K. Highsmith ; Andrew J. Sanderson ; Louis F. Cannizzo ; Robert M. Hajik, Polymerization of poly(glycidyl nitrate) from high purity glycidyl nitrate synthesized from glycerol.
Mul Johannes Maria,NLX ; Schoyer Herman Fedde Rein,NLX ; Schnorhk Ared Jean-Louis,NLX, Propellants, in particular for the propulsion of vehicles such as rockets, and process for their preparation.
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