Device and method for missile wing aerodynamic load simulation loading

Abstract

The invention discloses a device and a method for missile wing aerodynamic load simulation loading, and relates to the technical field of aerospace. The device comprises a first fixing surface, a second fixing surface, a beam, a loading screw, a loading lever system formed by a multi-stage lever, and a loading block. The first fixing surface and the second fixing surface are oppositely arranged, and the beam is fixedly connected between the two fixing surfaces. The first fixing surface is provided with a first fixing block and a second fixing block, and is used for fixing a missile wing on thefirst fixing surface. The loading screw runs through the beam, and the lower end of the loading screw applies total load to a first-stage lever in the lever system. Two ends of each of the final stage levers in the loading lever system are respectively located on the positions of load application points on the loading block. The loading block is located above the missile wing and matches the shape of the missile wing. The device applies load through a simple screw structure, can perform continuously loading, has a simple structure, and has high simulation of a loading mode.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a device and method for simulating the aerodynamic load of a missile wing. Background technique [0002] The wings provide lift for the missile to fly, and during the flight, the wings will be subjected to aerodynamic loads. In order to ensure flight safety and stability, there are corresponding requirements for the strength and stiffness of the wing. The static test of the wing is a crucial verification method. The strength and stiffness of the wing are obtained by fixing the joint surface and applying corresponding loads on the wing surface. characteristics to determine whether the flight requirements are met. [0003] In the existing test methods, the aerodynamic load on the wing is obtained according to the wind tunnel test or calculation software, and combined with the simple force and moment equivalent relationship to obtain the loading point and the load at the loading...

AI Technical Summary

Problems solved by technology

[0003] In the existing test methods, the aerodynamic load on the wing is obtained according to the wind tunnel test or calculation software, and combined with the simple force and moment equivalent relationship to obtain the loading point and the load at the loading point, so as to facilitate static test loading. The load distribution obtained by this method may be quite different from the aerodynamic load obtained by the wind tunnel test or calculation software, and the deformation effect on the wing is different; and, from the test device, the existing loading method is usually hydraulic loading or Suspension loading, the former has a complex structure, expensive equipment, and requires professionals to operate, while the latter is troublesome to load and unload, it is difficult to load continuously, and it is prone to impact, causing damage to equipment, and the existing loading method is usually partial loading. The aerodynamic load generated is surface force, which is quite different

Images