Stagnation pressure activated fuel release mechanism for hypersonic projectiles
US6536350B2 · kind B2 · utility
23Cited by
13References
10Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 7, 2001 |
| Grant date | Mar 25, 2003 |
| Priority date | — |
| Expiry date | Mar 7, 2021 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K7/10
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A propulsion-assisted projectile has a body, a cowl forming a combustion section and a nozzle section. The body has a fuel reservoir within a central portion of the body, and a fuel activation system located along the central axis of the body and having a portion of the fuel activation system within the fuel reservoir. The fuel activation system has a fuel release piston with a forward sealing member where the fuel release piston is adapted to be moved when the forward sealing member is impacted with an air flow, and an air-flow channel adapted to conduct ambient air during flight to the fuel release piston.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.