High-performance propellant combinations for a rocket engine

Explosive and thermic compositions or charges – Containing free boron or binary compounds of boron or boranes

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149 36, 149 42, 149 76, 149 88, C06B 4300

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active

049503413

ABSTRACT:
A solid high-performance propellant for a rocket engine is described. The propellant is constituted by a combination of polyglycidylazide (GAP) ([C.sub.3 H.sub.5 N.sub.3 O].sub.n) or poly-3,3-bis(azidomethyl)oxetane (BAMO) ([C.sub.4 H.sub.6 N.sub.6 O].sub.n) with boron, aluminum, or aluminum hydride (AlH.sub.3) and a compound selected from the group consisting of hydrazinium nitroformate (N.sub.2 H.sub.5 C(NO.sub.2).sub.3), nitronium perchlorate (NO.sub.2 ClO.sub.4), or ammonium perchlorate (NH.sub.4 ClO.sub.4), together with other conventional additives.

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Dadieu et al., Raketentreibstoffe, pp. 109-112, 638, 675-676, Springer-Verlag, (1968).
Greleci et al., A.R.S. Journal, 32(8), 1189-1195, (1962), (especially 1190-1192.
Haberman, Chemical Engineering Progress, 68(7), 72-76, (1964).
Urbanski, Chemistry and Technology of Explosives, vol. 4, pp. 568-573.

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