Multi-pulse solid rocket motor ignition method
US11512668B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 28, 2020 |
| Grant date | Nov 29, 2022 |
| Priority date | — |
| Expiry date | Nov 28, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K9/94
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rocket motor has an electrically operated propellant initiator for a propellant grain that includes an electrode arrangement configured to concentrate an electric field at an ignition electrode for igniting an electrically operated propellant. The rocket motor includes a combustion chamber containing at least one propellant grain and an electrically operated propellant initiator operatively coupled to the propellant grain to initiate combustion of the propellant grain. The electrically operated propellant initiator includes the electrically operated propellant and at least one pair of electrodes configured to ignite the electrically operated propellant. The pair of electrodes includes a ground plane electrode and an ignition electrode. When an electrical input is applied to the electrically operated propellant initiator, the electric field is concentrated at the ignition electrode to ignite the electrically operated propellant at the location where the ignition electrode is arranged.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.