Integrated inward turning inlets and nozzles for hypersonic air vehicles
US7866599B2 · kind B2 · utility
10Cited by
9References
18Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Feb 14, 2006 |
| Grant date | Jan 11, 2011 |
| Priority date | — |
| Expiry date | May 4, 2029 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/10
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A hypersonic waverider aircraft is disclosed that includes a first engine and an inlet including a throat. The inlet is configured to generate three-dimensional flow compression during hypersonic flight with a weak shock wave that begins at the leading edge surfaces of the inlet and coalesces ahead of the throat, and a weak shock wave that begins at the point of coalescence of the weak shock wave and extends to the throat. The inlet includes a v-shaped lip open to freestream airflow in one side of the inlet.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.