Method and apparatus for in-flight shake testing of an aircraft fuselage

• US 5,390,543 A
• Filed: 06/01/1993
• Issued: 02/21/1995
• Est. Priority Date: 06/03/1992
• Status: Expired due to Term

• Current Assignee: Westland Helicopters Limited (Leonardo S.p.A.)
• Original Assignee: Westland Helicopters Limited (Leonardo S.p.A.)
• Inventors: Wells, Daniel M., Jordan, Andrew L., Staple, Alan E.
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): Kwok, Helen C.
• Application Number:
  US08/069,356
• Time in Patent Office: 630 Days
• Field of Search: 73/583, 73/662, 73/669, 364/508, 244/17.13, 244/17.11
• US Class Current: 73/583
• CPC Class Codes: G01M 7/00 Vibration-testing of structures; Shock-testing of structures G01M9/00 takes precedence

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.

Claims

1. A method for in-flight shake testing of an aircraft structure having an active vibration control system comprising a plurality of force-generating actuators connected on the structure for inputting controlling forcing loads into the structure to reduce vibration thereof, comprising the steps of isolating one of said actuators from the vibration control system, operating said one of said actuators independently of the vibration control system so as to input a predetermined load at a predetermined frequency into said aircraft structure to excite said aircraft structure to vibrate, sensing the vibration of said aircraft structure to said input and recording said vibration.

2. A method according to claim 1, including the further step of continuing to operate the active vibration control system through said plurality of force-generating actuators so as to reduce background vibration of the structure and enable a high ratio of response signal to a background vibration signal to be achieved.

3. Apparatus for in-flight shake testing of an aircraft structure having an active vibration control system including a plurality of force-generating actuators connected on said structure for inputting controlling forcing loads into said aircraft structure to reduce vibration thereof, control means for isolating one of said actuators from the vibration control system and operating said one of said actuators to input predetermined shake test excitation forces into said aircraft structure to excite said aircraft structure to vibrate for shake testing said aircraft structure, sensing means for sensing the vibration of said aircraft structure to said shake test excitation forces and recording means for recording said vibration.

4. Apparatus as claimed in claim 3, wherein said control means comprise a device containing predetermined test signals and an electronic actuator control unit for receiving said test signals, converting said test signals to actuator control signals and supplying said control signals to said one of said actuator.

5. Apparatus as claimed in claim 4, wherein said device comprises a cassette tape recorder including a pre-recorded audio tape containing said predetermined test signals.

6. Apparatus as claimed in claim 4, wherein said predetermined test signals are swept sinusoid signals.

7. Apparatus as claimed in claim 3 wherein said sensing means comprise a plurality of accelerometers located at predetermined locations on the structure.

8. Apparatus as claimed in claim 7 wherein said recording means comprise at least one vibration recorder connected to record signals output by said accelerometers.

9. Apparatus as claimed in claim 4 wherein said electronic actuator control unit is adapted to selectively enable and disable said actuators and to supply an actuator force reference signal to said recording means.