发明名称 |
Multi-mode pulsed detonation propulsion system |
摘要 |
A multi-mode propulsion system for potential application to hypersonic and aerospace planes. The system can employ various propulsion modes at various points in time, with the propulsion system employed at a given point in time being selected according to the velocity of the inlet airflow. In one embodiment, the propulsion system of the present invention has an ejector-augmented pulsed detonation rocket propulsion mode, a pulsed normal detonation wave engine mode, a steady oblique detonation wave engine mode, and a pure pulsed detonation rocket mode.
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申请公布号 |
US6857261(B2) |
申请公布日期 |
2005.02.22 |
申请号 |
US20030337920 |
申请日期 |
2003.01.07 |
申请人 |
BOARD OF REGENTS, THE UNIVERSITY OF TEXAS SYSTEM |
发明人 |
WILSON DONALD R.;LU FRANK K. |
分类号 |
F02K7/02;F02K7/08;F02K7/10;F02K7/20;(IPC1-7):F02K7/02 |
主分类号 |
F02K7/02 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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