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 to control helicopter response about the yaw axis. The control system processes information from a variety of helicopter sensors in order to provide an output command signal to the tail rotor. Yaw control is accomplished by applying a force on a sidearm controller which provides a yaw axis command signal that is used to schedule a desired yaw rate of change. The lateral acceleration and airspeed signals are used to compute a synthesized yaw rate signal which is compared against the desired yaw rate of change, thus allowing the pilot to control lateral acceleration when he applies force on the sidearm controller.
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申请公布号 |
US5178307(A) |
申请公布日期 |
1993.01.12 |
申请号 |
US19910751432 |
申请日期 |
1991.08.28 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
WRIGHT, STUART C.;ADAMS, DON L.;GOLD, PHILLIP J. |
分类号 |
B64C13/50;G05D1/00;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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