High-performance propellant combinations for a rocket engine
patent
A solid high-performance propellant for a rocket engine is described. The propellant is constituted by a combination of polyglycidylazide (GAP) ([C3H5N3O]n) or poly-3,3-bis(azidomethyl)oxetane (BAMO) ([C4H6N6O]n) with boron, aluminium, or aluminium hydride (AlH3) and a compound selected from the group consisting of hydrazinium nitroformate (N2H5C(NO2)3), nitronium perchlorate (NO2ClO4), or ammonium perchlorate (NH4ClO4), together with other conventional additives.
TNO Identifier
993160
Publisher
ESTEC/Prins Maurits Laboratorium TNO
Collation
4 p.
Place of publication
Rijswijk
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