System and method for cooling a leading edge of a high speed vehicle
US11577817B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 11, 2021 |
| Grant date | Feb 14, 2023 |
| Priority date | — |
| Expiry date | Feb 11, 2041 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C3/20
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.