Adaptable solid-hybrid rocket for crew escape and orbital injection propulsion
US6629673B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 28, 2001 |
| Grant date | Oct 7, 2003 |
| Priority date | — |
| Expiry date | Nov 28, 2021 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/52
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The present invention relates to a propulsion system for transporting a crew transfer vehicle. The propulsion system has a casing which defines a chamber, a solid propellant system positioned within the chamber for generating one of emergency escape propulsion during an emergency portion of an ascent flight and orbital injection propulsion during normal flight operations, and a sustain propulsion system communicating with the chamber for sustaining one of the emergency escape propulsion during the emergency portion of the ascent flight and orbital injection propulsion during the normal flight operations. In one embodiment of the present invention, the sustain propulsion system comprises a hybrid solid fuel grain and liquid oxidizer system. In a second embodiment of the present invention, the secondary propulsion system comprises a liquid fuel and liquid oxidizer system.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.