High-performance propellant combinations for a rocket engine

Details High-performance propellant combinations for a rocket engine High-performance propellant combinations for a rocket engine

1989-07-07

1990-07-03

Lechert, Jr., Stephen J.

Explosive and thermic compositions or charges

Structure or arrangement of component or product

Solid particles dispersed in solid solution or matrix

149 22, 149 36, 149 88, C06B 4510

Patent

active

049388142

ABSTRACT:
Hybrid, high-performance propellant combinations for a rocket engine are described, characterized by being constituted by a combination of polyglycidyl axide (GAP) ([C.sub.3 H.sub.5 N.sub.3 O].sub.n), poly-3,3-bis(azidomethyl)oxetane (BAMO) ([C.sub.4 H.sub.6 N.sub.6 O].sub.n) or hydroxy-terminated polybutadiene (HTPB) with hydrazinium nitroformate (N.sub.2 H.sub.5 C(NO.sub.2).sub.3) as a solid oxidizer and pentaborane (B.sub.5 H.sub.9) or diborane (B.sub.2 H.sub.6) as a fuel, together with other conventional additives.

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Haberman, Chemical Engineering Progress, 68(7), 72-76 (1964).
Urbanski, Chemistry and Technology of Explosives, vol. 4, pp. 568-573 Pergamon Press, (1985).

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