Airplane body wallboard pressurizing test device

Abstract

An airplane body wallboard pressurizing test device relates to the technical field of airplane strength test device designing. Long bottom beams are parallely and fixedly arranged on a same plane. Short bottom beams are fixedly arranged on the long bottom beams and are perpendicular with the long bottom beams; a square steel frame is fixed on the short bottom beams and furthermore the shape of the square steel frame matches a supporting bottom box. Each connecting part comprises a small pulling plate, a middle pulling plate, a large pulling plate, a long pulling plate, double ears, a load equalizer and a single ear; wherein the small pulling plate, the middle pulling plate, the large pulling plate, the long pulling plate, the double ears, the load equalizer and the single ear are successively connected. A tested member covers and presses the supporting bottom box, and furthermore the tested member is connected with a supporting part through the connecting part. The tested member is connected with a hydraulic servo control device and inflates the tested member for realizing a pressurizing test on the airplane body wallboard. The airplane body wallboard pressurizing test device provided by the invention has advantages of saving testing space, reducing weight of the test device; effectively ensuring uniform load bearing in an adaptive loading manner; reducing a connecting process, effectively increasing loading frequency, realizing uniform boundary load, saving space and realizing repeated use.

Description

technical field [0001] The invention relates to the technical field of aircraft structure design, in particular to a fuselage panel pressure charging test device. Background technique [0002] In the static or fatigue test of the aircraft fuselage structure, it is often necessary to simulate the internal air pressure of the fuselage cylinder, but usually the whole fuselage cylinder is not used for the test, but a part of the fuselage panel structure is used for the test . See the force of the fuselage panel figure 1 . Therefore, the test must seal and fix the fuselage panels. When fixing fuselage panels in the prior art, multi-stage lever connections are usually used to occupy a large amount of test sites, and due to the accumulation of processing errors, the boundary load is not very uniform, and the connecting levers cannot be reused, which increases the cost of use. [0003] The problem that needs to be solved urgently now is how to design a fuselage panel pressure te...

AI Technical Summary

Problems solved by technology

When fixing the fuselage panels in the prior art, usually using multi-level lever connections will occupy a lot of test sites, and due to the accumulation of processing errors, the boundary load is not very uniform, and the connecting levers cannot be reused, which increases the cost of use

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