Boron-fuel-rich propellant compositions
US3986909A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Mar 24, 1970 |
| Grant date | Oct 19, 1976 |
| Priority date | — |
| Expiry date | Mar 24, 1990 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S149/114
- WIPO fieldBasic materials chemistry
- WIPO sectorChemistry
Abstract
Fuel-rich propellant compositions, for use in air-augmented rocket propulsion, containing a high-energy fuel component in the form of finely-divided boron, wherein the boron is present in large excess of the amount oxidizable during combustion of the propellant. A major portion of the boron is ejected, largely as free boron particles, together with the combustion products of the propellant and is burned downstream of the propellant by ram air injected into an afterburner combustion zone. The propellant additionally comprises an organic fuel binder comprising an organic polymer, and an inorganic oxidizer salt, preferably ammonium perchlorate, in an amount at least sufficient to maintain stable combustion of the propellant at desired combustion chamber pressures. The propellant compositions may additionally contain small amounts of Mg, Al, or Zr metal as ballistic or afterburner combustion modifiers. Ejection of the boron is substantially improved by incorporating at least a portion of the boron in the propellant composition in the form of agglomerate masses or particles. Preferably the agglomerate particles are spheroidal and the finely-divided boron in the agglomerate particles is …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.