Hybrid rocket motor with integral oxidizer tank
US11326556B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 29, 2020 |
| Grant date | May 10, 2022 |
| Priority date | — |
| Expiry date | Sep 29, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/53
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.