发明名称 |
HIGH SPEED YAW CONTROL SYSTEM FOR ROTARY WING AIRCRAFT |
摘要 |
A helicopter flight control system includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a banked turn. The control system processes information from a variety of helicopter sensors in order to provide the coordinating yaw command signal on an output line to the tail rotor of the helicopter.
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申请公布号 |
CA2113730(C) |
申请公布日期 |
2000.05.30 |
申请号 |
CA19922113730 |
申请日期 |
1992.07.31 |
申请人 |
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发明人 |
WRIGHT, STUART C.;ADAMS, DON L.;GOLD, PHILLIP J. |
分类号 |
B64C13/50;G05D1/00;G05D1/08;(IPC1-7):G05D1/08 |
主分类号 |
B64C13/50 |
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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