A light aircraft vibration simulation test and data usage method
A light aircraft and vibration mode technology, which is applied in the direction of aircraft component testing, etc., can solve the problems that the aircraft exerts excitation force and the test vibration mode is difficult to effectively stimulate, and achieves high accuracy
Active Publication Date: 2019-12-31
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
For light aircraft, when the weight is too small, the excitation force cannot be applied to the aircraft during the vibration modal test under free-free boundary conditions, so the phase resonance method (currently recognized as the most effective method for modal testing) cannot be used to obtain Valid Vibration Modal Data
[0003] At present, the development trend of the booming light aircraft and various fixed-wing unmanned aerial vehicles is light weight and miniaturization, and it is difficult to effectively stimulate the vibration mode under free-free boundary conditions.
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[0023] To make the objectives, technical solutions, and advantages of the implementation of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, but not all of the embodiments. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention, but should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.
[002...
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The invention provides a vibration simulation test and data using method for a light aircraft. The data using method comprises the steps of allowing the light aircraft to be in a suspension state, determining and marking a center of gravity of the whole light aircraft and centers of gravity of left and right wings of the light aircraft, determining weight to be applied at the three centers of gravity in the previous step, exciting the whole light aircraft and testing a rigid mode and an elastic mode, applying a same counterweight to a theoretical calculation model according to the position and weight of the counterweight on the light aircraft, calculating characteristics of the rigid mode and the elastic mode of the theoretical calculation model, modifying the theoretical calculation model to allow the characteristic of the elastic mode to meet accuracy requirements, and removing the counterweight applied to the theoretical calculation model and then recalculating the rigid mode and the elastic mode. The data using method provided by the invention can obtain effective vibration mode data and an ideal calculation model.
Description
Technical field [0001] The invention belongs to the field of aircraft aeroelastic design, and specifically relates to a light aircraft vibration simulation test and data usage method. Background technique [0002] Vibration modal data is the basic data for aeroelastic stability analysis and response analysis, and it is also the basic data for confirming and correcting the calculation model. For light aircraft, when the weight is too small, the vibration modal test under free-free boundary conditions cannot be applied to the aircraft. Therefore, the phase resonance method (currently recognized as the most effective method for modal testing) cannot be used. Effective vibration mode data. [0003] The current booming development of light aircraft and various fixed-wing UAVs are lightening and miniaturizing, and there is a problem that it is difficult to effectively stimulate the vibration modes under free-free boundary conditions. Summary of the invention [0004] The purpose of the ...
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IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 霍应元程芳罗务揆党云卿
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA