Strength testing device for aircraft fuselage wall panel

Abstract

The invention relates to an aircraft fuselage panel strength test device. The aircraft fuselage panel strength test device is used for carrying out a strength test on a fuselage panel under the combined action of a pressurizing load and an annular load, and comprises a pressurizing loading assembly, a skin annular loading assembly and a frame annular loading assembly, the pressurizing loading assembly is used for applying the pressurizing load to the fuselage panel, and the skin annular loading assembly is used for applying the skin annular loading assembly to the frame annular loading assembly. The skin annular loading assembly is used for applying an annular load to a skin of a fuselage wall plate, the frame annular loading assembly is used for applying an annular load to a frame of the fuselage wall plate, and the pressurizing loading assembly, the skin annular loading assembly and the frame annular loading assembly are mutually independent. The loading of each frame of the fuselage wall plate by the frame annular loading assembly is mutually independent. According to the technical scheme, the device has the following beneficial technical effects that different annular loads can be applied to the skin and the frame at different frame positions while the pressurizing load is simulated, and the load borne by the fuselage wall plate can be simulated more truly.

Description

technical field [0001] The invention relates to a device for testing the strength of an aircraft fuselage wall plate. Background technique [0002] The fuselage of a civil aircraft is similar to a barrel section, and the fuselage panel is a part of the fuselage barrel section. In operation, from the ground to the air and then to the ground, the fuselage panel bears the load along the fuselage ring and the internal The pressurized load, in which the pressurized load in the entire fuselage barrel section is uniform, because the hoop loads at different positions of the fuselage are different, and the relative magnitudes of the hoop loads borne by the frame and the skin will also change. It is necessary to study the static, fatigue and damage tolerance qualities of the fuselage panel under the combined action of hoop load and internal pressurization. [0003] In the prior art, a variety of fuselage panel test devices have been announced at home and abroad, the typical ones are ...

AI Technical Summary

Problems solved by technology

The Boeing Company of the United States discloses a test device (E-fixture device) for testing curved surface panels. This device applies hoop loads through independent actuators, but cannot separately adjust the hoop loads applied to the frame and skin. The relative size of the load; the D-Box device of the Boeing Company of the United States and the fuselage panel test device of the German IMA cannot actively apply hoop loads; a composite loading test device of the fuselage panel of the China Aircraft Strength Research Institute can apply hoop loads , but the hoop loads of each frame cannot be adjusted separately, nor can the relative size of the hoop loads applied to the frame and the skin be adjusted separately; Realize the simulation of pressurized load, and cannot actively apply hoop load

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