Invention Grant
US07866599B2 Integrated inward turning inlets and nozzles for hypersonic air vehicles
有权
集成向内转向入口和喷嘴用于超音速飞行器
- Patent Title: Integrated inward turning inlets and nozzles for hypersonic air vehicles
- Patent Title (中): 集成向内转向入口和喷嘴用于超音速飞行器
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Application No.: US11354358Application Date: 2006-02-14
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Publication No.: US07866599B2Publication Date: 2011-01-11
- Inventor: John D. Elvin
- Applicant: John D. Elvin
- Applicant Address: US MD Bethesda
- Assignee: Lockheed-Martin Corporation
- Current Assignee: Lockheed-Martin Corporation
- Current Assignee Address: US MD Bethesda
- Agency: Koestner Bertani LLP
- Agent Mary Jo Bertani
- Main IPC: B64D33/02
- IPC: B64D33/02
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.
Public/Granted literature
- US20070187550A1 Integrated inward turning inlets and nozzles for hypersonic air vehicles Public/Granted day:2007-08-16
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