Solid rocket motor propellants with reticulated structures embedded therein to provide variable burn rate characteristics
US4756251A · kind A · utility
20Cited by
46References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 18, 1986 |
| Grant date | Jul 12, 1988 |
| Priority date | — |
| Expiry date | Sep 18, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/26
- WIPO fieldBasic materials chemistry
- WIPO sectorChemistry
Abstract
A solid propellant grain which comprises an homogeneous mass of propellant material including an oxidant. A variable burn rate is provided by embedding a reticulated structure in a portion only of the propellant mass. The reticulated structure may be coated with a high thermal conductivity material to provide an increased burning rate. The coat of material is selected to preferably provide improved bonding to the propellant mass.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.