Controlled burn rate, reduced smoke, solid propellant formulations
US5334270A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Nov 25, 1992 |
| Grant date | Aug 2, 1994 |
| Priority date | — |
| Expiry date | Nov 25, 2012 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC06B45/02
- WIPO fieldBasic materials chemistry
- WIPO sectorChemistry
Abstract
Solid rocket motor propellant formulations are provided which are capable of burning at at least two selected burn rates. The burn rate is controlled by controlling the pressure at which the propellant burns. For example, it is possible to mechanically modify the container, such as a rocket motor casing, in which the propellant is held in order to modify the pressure under which the propellant burns. Alternatively, the propellant may be configured or molded such that the pressure changes at a chosen time due to the process of burning the propellant. The propellant is capable of burning at a relatively constant burn rate at a chosen pressure. Once the pressure changes within chosen limits, the burn rate of the propellant is rapidly modified to another relatively constant burn rate. The solid rocket motor propellant is formulated with the addition of from about 0.5% to about 4.0% TiO.sub.2. The specific operating pressures and burn rates can be selected by modifying the amount of TiO.sub.2 added, the modifying particle size of the various ingredients, and modifying the specific ingredients used.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.