Load monitoring device and method for buffeting test of airplane key structure

Abstract

The invention discloses a load monitoring device and method for a buffeting test of an airplane key structure. The device comprises an airplane vertical fin test piece vertically arranged on a test bed, a load transmission structure arranged at the bottom of the airplane vertical fin test piece, and a load monitoring structure connected to the load transmission structure. The load transmission structure comprises a mounting seat, a fixed seat and a connecting rod; the method comprises the following steps: 1, calibrating a load range; 2, mounting a load monitoring device; 3, acquiring and storing a strain limit range; and 4, monitoring the buffeting test of the airplane vertical fin test piece. According to the invention, the load transmission structure is utilized to transmit the rotation load borne by the airplane vertical fin test piece to the connecting rod, and the strain gauge arranged on the connecting rod is utilized to obtain the strain range of the connecting rod in the calibrated load range. And comparing the strain value obtained by the strain gauge in the subsequent buffeting test with the calibrated strain range, and judging whether the test load in the buffeting test is normally loaded or not.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure test, in particular to a load monitoring device and method for buffeting test of key aircraft structures. Background technique [0002] The key structure of the aircraft mainly includes the wing, fuselage, engine, control system, and landing gear. Among them, the main function of the tail in the wing is to control the lift and deflection of the aircraft and ensure the smooth flight of the aircraft, mainly including the horizontal tail and vertical tail. The vertical tail is the vertical tail of the aircraft. In the test of the aircraft tail, it is necessary to carry out the buffeting test. The buffeting is the irregular pressure pulsation caused by the separation flow, the shock wave-boundary layer interference and the wake flow of the aircraft. In the buffeting test of the vertical tail structure of the aircraft, the fatigue test of the vertical tail structure of the aircraft will be ...

AI Technical Summary

Problems solved by technology

In the chattering test of the vertical tail structure of the aircraft, the fatigue test will be carried out on the vertical tail structure of the aircraft. In order to achieve the purpose of protecting the test piece in the test, the connection of the load loading point of the test piece generally cannot be fixed. The clamping connection method is used for loading, and the loading point of the load may be shifted or detached during the loading process, but the loading system will not stop loading due to the shifting or detachment of the loading point, which will cause the loading value to deviate from the normal load value , there is a risk of over-testing in severe cases, which may cause the test piece to be destroyed

In order to avoid the problem of the damage of the test piece, the safety of the test can be ensured by manual real-time observation of the state of the test piece and the loading point, but manual real-time observation cannot stop the test immediately when a problem occurs, and there is also a risk of the test piece being destroyed

Images