Aluminized plateau-burning solid propellant formulations and methods for their use
US5771679A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 5, 1996 |
| Grant date | Jun 30, 1998 |
| Priority date | — |
| Expiry date | Dec 5, 2016 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC06B45/02
- WIPO fieldBasic materials chemistry
- WIPO sectorChemistry
Abstract
Solid rocket motor propellants which burn at at least one stable burn rate over at least one corresponding pressure range (i.e the burn rate v. pressure curve contains at least one area of low pressure exponent with respect to a normal curve) are described. The propellant compositions comprise a binder, from about 65% to about 90% by weight ammonium perchlorate, the ammonium perchlorate being of at least two distinct particle sizes; from about 0.3% to about 5.0% by weight refractory oxide selected from the group consisting of TiO.sub.2, Al.sub.2 O.sub.3, SiO.sub.2, SnO.sub.2, and ZrO.sub.2 ; and from about 5 to about 25% by weight metal, such as aluminum.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.