Airplane airfoil static force and vibration combined loading system and method for airplane strength test

Abstract

The invention provides an aircraft airfoil static force and vibration combined loading system and method for aircraft strength testing, and belongs to the technical field of aircraft testing. Comprising a combined loading frame, a static loading assembly, a vibration loading assembly, a gas source connecting element and a control element for controlling the normal operation of the whole system, when a static force loading test of an airplane strength test is carried out, a common commercial air bag is adopted to carry out static force loading at the position, close to the root, of the airplane wing surface, and a mode of'air cylinder and air bag 'is adopted to carry out static force loading at the position, close to the wingtip, of the airplane wing surface, so that the load loaded at the small-deformation part of the airplane wing surface can meet the requirement; the additional rigidity and damping of the part with large deformation on the wing surface of the aircraft can be reduced; when a vibration loading test is carried out, the elastic fixing device is arranged, so that excessive mass added to an aircraft airfoil structure by the excitation table is reduced, the potential safety hazard of abnormal vibration caused by overlarge excitation force is effectively avoided, and the working efficiency and the manufacturing cost of the excitation table are not influenced.

Description

technical field [0001] The invention belongs to the technical field of aircraft testing, in particular to a system and method for combined static force and vibration loading of an aircraft wing surface for aircraft strength testing. Background technique [0002] Aircraft structures, especially some specific airfoil components, such as canards, vertical tails, flat tails and other structures, are always in a vibration environment during use. The aircraft structure is always subjected to different vibration loads while bearing static loads. , make the aircraft structure produce vibration response, when this kind of response is excessive, it will cause the vibration fatigue damage of the aircraft structure, and then the damage will occur, and this combined effect will accelerate the damage and appear a new form of damage. The problem of structural vibration fatigue not only seriously affects the development cycle of the aircraft, but also seriously affects the attendance rate o...

AI Technical Summary

Problems solved by technology

[0004] In the static load superimposed vibration load test of the aircraft strength test, the excitation equipment is generally connected with the test piece through a fixture. This connection will completely add the mass of the fixture and the moving coil of the shaking table to the test piece, causing change in motion

The traditional static loading is generally loaded through the elastic element rubber rope. This loading method will not limit the structural displacement caused by vibration, and also minimize the additional stiffness and damping of the loading system to the structure. However, for some tests with higher requirements Components, such as the static loading of the tip part of the aircraft wing, this loading method will still add too much stiffness and mass, resulting in unacceptable changes in its natural frequency and mode shape; in addition, for the typical airfoil structure of the aircraft, due to During the static load loading process, large deformation will occur, which will cause the general vibration table or vibration excitation equipment to fail to vibrate normally vertically, and the static load loading of the tip structure of the airfoil cannot adopt the traditional static load loading due to the same problem. Way

Images