High-performance propellant combinations for a rocket engine
US4950341A · kind A · utility
7Cited by
4References
2Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 7, 1989 |
| Grant date | Aug 21, 1990 |
| Priority date | — |
| Expiry date | Jul 7, 2009 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC06B47/10
- WIPO fieldBasic materials chemistry
- WIPO sectorChemistry
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.