发明名称 |
Flight control system employing complementary filter |
摘要 |
Strake, flap and canard control surfaces of an aircraft are driven by an error signal which is comprised of a pilot stick command signal and feedback components including measured vertical acceleration and pitch rate of the aircraft and a third feedback component derived from a complementary filter. The filter has a high-pass filter section which operates upon canard position data and a low-pass filter section which operates upon pitch rate. A summation of the signals passing both filtering sections is summed with the vertical acceleration and pitch rate feedback signals to form a combined feedback signal.
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申请公布号 |
US4697768(A) |
申请公布日期 |
1987.10.06 |
申请号 |
US19850797089 |
申请日期 |
1985.11.12 |
申请人 |
GRUMMAN AEROSPACE CORPORATION |
发明人 |
KLEIN, ROBERT W. |
分类号 |
B64C13/16;G05D1/08;(IPC1-7):B64C13/16 |
主分类号 |
B64C13/16 |
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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