High-performance propellant combinations for a rocket engine
US4938814A · kind A · utility
10Cited by
5References
2Claims
0Family size
Assignee
Key dates
| Filing date | Jul 7, 1989 |
| Grant date | Jul 3, 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
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.