发明名称 |
Rotatable non-circular forebody flow controller |
摘要 |
The invention is a rotatable, non-circular forebody flow controller. The apparatus comprises a small geometric device located at a nose of a forebody of an aircraft or missile. The geometric device has a circular base that fits flush upon the remaining forebody of the aircraft and a non-circular cross-sectional area that extends toward the apex of the aircraft. The device is symmetrical about a reference plane and preferably attaches to an axle which in turn attaches to a rotating motor. The motor rotates the device about an axis of rotation. Preferably, a control unit connected to an aircraft flight control computer signals to the rotating motor the proper rotational positioning of the geometric device.
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申请公布号 |
US5050819(A) |
申请公布日期 |
1991.09.24 |
申请号 |
US19900565090 |
申请日期 |
1990.08.10 |
申请人 |
THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION |
发明人 |
MOSKOVITZ, CARY A. |
分类号 |
B64C19/00;B64C21/00;B64C23/06 |
主分类号 |
B64C19/00 |
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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