发明名称 |
Method and apparatus for in-flight shake testing of an aircraft fuselage |
摘要 |
A force-generating actuator connected at or across points of a structure capable of relative motion at an exciting frequency is operated to input a predetermined load into the structure and the response of the structure is measured for analysis. In one form of the invention the actuator is one of a plurality of actuators of an active vibration control system which is isolated and operated independently in a shake test mode. Advantageously, especially in a helicopter application, the remaining actuators can continue to be operated to reduce background vibration.
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申请公布号 |
US5390543(A) |
申请公布日期 |
1995.02.21 |
申请号 |
US19930069356 |
申请日期 |
1993.06.01 |
申请人 |
WESTLAND HELICOPTERS LIMITED |
发明人 |
STAPLE, ALAN E.;WELLS, DANIEL M.;JORDAN, ANDREW L. |
分类号 |
B64F5/00;G01M7/00;G01M7/02;(IPC1-7):G01H1/00 |
主分类号 |
B64F5/00 |
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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