Electrically operated propellant for solid rocket motor thrust management
US10563617B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 23, 2016 |
| Grant date | Feb 18, 2020 |
| Priority date | — |
| Expiry date | Sep 17, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/35
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.