Method and apparatus for in-flight shake testing of an aircraft fuselage
US5390543A · kind A · utility
9Cited by
12References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 1, 1993 |
| Grant date | Feb 21, 1995 |
| Priority date | — |
| Expiry date | Jun 1, 2013 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01M7/00
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.