Method for performing a ground vibration test in airplanes
The invention relates to an improved method for a ground vibration test (so-called “ground vibration test”) 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.
1. A method for performing a ground vibration test on an airplane, comprising the following steps:
a) placing measuring transducers in an area of the airplane,
b) keeping the airplane undamped and rigidly in place in at least three holding points such that the holding points bring about a substantially rigid coupling between the airplane and ground,
c) exciting the airplane to vibrate with a plurality of vibration exciters,
d) measuring values and evaluating the measured values obtained by the measuring transducers, and
e) mathematically canceling out influence of rigid holding at the holding points during the ground vibration test or after the ground vibration test.
2. The method according to claim 1 , wherein holding takes place at each of the at least three holding points by means of a respective hydraulic lift.
3. The method according to claim 1 , wherein the measured values are acquired with accelerometers.
4. The method according to claim 1 , wherein the airplane is excited to vibrate by means of a plurality of electromagnetic exciters.
5. The method according to claim 1 , wherein a vibration model of the airplane is adjusted to the measured values determined by the measuring transducers during the ground vibration test.
6. The method according to claim 1 , wherein forces acting on the lifting devices during the ground vibration test are acquired with one or more of accelerometers or dynamometers, and the ground vibration test is immediately terminated if preset limits are exceeded.
7. The method according to claim 1 , wherein the vibration exciters are positioned in an area of wing ends, elevator unit ends, a rudder unit end, an aft fuselage, engines as well as a nose of the airplane.
8. The method according to claim 1 , wherein the measuring transducers are arranged at least one of on or inside the airplane.
9. The method according to claim 1 , wherein up to 1,000 measuring transducers are used.
10. The method according to claim 1 , wherein a vibration model of the airplane encompasses up to 5·10 6 node points, each with 6 degrees of freedom.
11. The method of claim 10 , further comprising including an adjustment function into the vibration model of the airplane such that the vibration model is continuously harmonized with measured acceleration values determined by the measuring transducers within a duration of the ground vibration test.
12. The method of claim 11 , further comprising comparing vibration excitations caused by the vibration exciters and acquired by the measuring transducers in a specific set of actuation commands to the vibrations exciters with excitations corresponding to the same set of actuation commands to the vibration exciters used to calculate the vibration model.
13. The method of claim 12 , further comprising, changing preset parameters of the vibration model if a difference is encountered or a maximum permissible setpoint-actual value deviation is exceeded during the comparison.
14. The method of claim 13 , wherein the preset parameters of the vibration model are changed such that the setpoint-actual value comparison falls below the maximum setpoint-actual value deviation value.
15. The method of claim 13 , wherein changing the preset parameters of the vibration model is systematically achieved via an iterative process comprised within the adjustment function.
16. The method of claim 11 , wherein the adjustment function is based on one or more of an estimation or a filter function used to change or optimize a predetermined set of parameters for the vibration model based on a required maximum deviation value.
17. The method of claim 1 , further comprising mathematically treating as rigid, the substantially rigid coupling between the airplane and the ground, in an evaluation function within an evaluator.
18. The method of claim 17 , wherein the mathematical treatment comprises implementing within an evaluator, a predetermined simple rigid holding model for the substantially rigid coupling.
19. A system for performing a ground vibration test on an airplane, comprising:
at least one holding device that provides an undamped, and substantially rigid support for the airplane in at least three holding points such that the holding points bring about a substantially rigid coupling between the airplane and ground;
a plurality of vibration exciters operating to vibrate the airplane;
a plurality of measuring transducers located in or around the airplane and operating to measure vibration values therefrom; and
a processing device comprising an evaluator that implements a predetermined simple rigid holding model for the substantially rigid coupling, that evaluates the measured values obtained by the measuring transducers, and that mathematically cancels out influence of the rigid holding at the holding points.