发明名称 |
Dual response aircraft reference synchronization |
摘要 |
In an aircraft automatic flight control system having a reference parameter synchronizing system (70) operable in response to a trim release switch (44), an initial trim release period (139), on the order of a large fraction of a second (137) causes (217, 218) a relatively slow effect trim reference integrator (208, 211) time constant, for smooth transitions of any error signal, followed by a relatively fast (216) effective reference integrator time constant for close, rapid tracking of the reference signal with the actual aircraft parameter.
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申请公布号 |
US4477876(A) |
申请公布日期 |
1984.10.16 |
申请号 |
US19810248768 |
申请日期 |
1981.03.30 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
WRIGHT, STUART C.;ADAMS, DON L.;FISCHER, WILLIAM C.;VERZELLA, DAVID J. |
分类号 |
B64C13/18;B64C27/56;G05D1/00;G05D1/08;(IPC1-7):G06F15/50 |
主分类号 |
B64C13/18 |
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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