Apparatus For Performing Ground Vibration Tests On Airplanes

• US 20110071778A1
• Filed: 11/29/2010
• Published: 03/24/2011
• Est. Priority Date: 04/23/2007
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE)
• Inventors: Schierenbeck, Detlef
• Granted Patent: US 8,096,185 B2
• Time in Patent Office: Days
• US Class Current: 702/56
• CPC Class Codes: G01M 7/00 Vibration-testing of structures; Shock-testing of structures G01M9/00 takes precedence
• CPC Class Codes: G01N 2291/2694 Wings or other aircraft parts
• CPC Class Codes: G01N 29/045 by imparting shocks to the workpiece and detecting the vibrations or the acoustic waves caused by the shocks measuring resonant frequency G01H13/00; measuring strength properties by application of mechanical stress G01N3/00
• CPC Class Codes: G01N 29/4463 Signal correction, e.g. distance amplitude correction [DAC], distance gain size [DGS], noise filtering

Abstract

The invention relates to improved methods and apparatus for performing ground vibration tests (so-called “ground vibration tests”) on an airplane. In the method according to the invention, the airplane is jacked up essentially undamped (“rigidly”) in conventional holding points with lifting devices. For purposes of the ground vibration test, the airplane is then excited to vibrate in a known manner using a plurality of vibration exciters, and the vibrations are acquired with a plurality of measuring transducers, in particular accelerometers. A dynamic vibration model of the airplane theoretically calculated beforehand can here be adjusted. The boundary conditions are removed during or after the ground vibration test, meaning the influence of the lifting device is “mathematically canceled out”, so that the determined measured values reflect the so-called “free-free” state of the airplane, as if the airplane had actually been in free flight during the ground vibration tests.

Claims

1. A system for performing a ground vibration test on an airplane, comprising:

a plurality of vibration exciters coupled to a plurality of locations on the aircraft that operate to excite the airplane to vibrate;

a plurality of measuring transducers coupled to the aircraft and operating to produce a plurality of measuring values;

at least one holding device, including a hydraulic lift, that provides an undamped, and substantially rigid support for the airplane between the airplane and ground; and

a processing system comprising an evaluator that implements a predetermined, simple, rigid holding model for the substantially rigid support.

2. The system of claim 1, wherein the at least one holding device includes at least three hydraulic lifts, at least one of the hydraulic lifts operating to couple a respective one of at least three holding points on the aircraft to provide the undamped, and substantially rigid support between the airplane and ground.

3. The system of claim 1, wherein the plurality of vibration exciters include electromagnetic exciters.

4. The system of claim 1, wherein the vibration exciters are positioned in at least one of wing ends, elevator unit ends, a rudder unit end, an aft fuselage, engines, and a nose of the airplane.

5. The system of claim 1, wherein the measuring transducers are arranged at at least one of on or inside the airplane.

6. The system of claim 1, wherein the plurality of measuring transducers are up to 1,000 in number.

7. The system of claim 1, wherein the measuring transducers include accelerometers.

8. The system of claim 1, wherein the processing system operates to control the vibration exciters, and receive and evaluate the plurality of measuring values from the measuring transducers.

9. The system of claim 8, wherein the processing system includes a vibration model of the airplane.

10. The system of claim 9, wherein the vibration model mathematically treats the substantially rigid support between the airplane and the ground as rigid when evaluating the plurality of measuring values from the measuring transducers.

11. The system of claim 10, wherein the processing system operates to mathematically cancel out the influence that the rigid support of the airplane has on the vibration of the airplane during the ground vibration test.

12. The system of claim 9, wherein the vibration model of the airplane encompasses up to 5·

10⁶ node points, each with 6 degrees of freedom.

13. The system of claim 12, wherein the processing system operates to adjust the vibration model of the airplane such that the vibration model is continuously harmonized with the measuring values from the measuring transducers duration the ground vibration test.

14. The system of claim 13, wherein the processing system operates to compare vibration characteristics from the measuring values duration the ground vibration test in a specific set of actuation commands to vibration characteristics corresponding to a same set of actuation commands used in formulating the vibration model.

15. The system of claim 14, wherein the processing system operates to change preset parameters of the vibration model if a difference is encountered or a maximum permissible setpoint-actual value deviation is exceeded during the comparison.

16. The system of claim 15, wherein the processing system operates to change the preset parameters of the vibration model such that the setpoint-actual value comparison falls below the maximum setpoint-actual value deviation value.

17. The system of claim 15, wherein the processing system operates to change the preset parameters of the vibration model via an iterative process.