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Processing method of aircraft ground lateral load

A processing method and side load technology, applied in the field of aircraft fatigue test, can solve the problems of large side load on the fuselage and difficult to apply side load, and achieve the effect of speeding up the test progress and shortening the test period

Active Publication Date: 2017-12-22
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

Due to the structural characteristics of the wing, the side load is not easy to apply, and it is usually transferred to the fuselage for application, which will cause excessive side load on the fuselage

Method used

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  • Processing method of aircraft ground lateral load
  • Processing method of aircraft ground lateral load
  • Processing method of aircraft ground lateral load

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Embodiment Construction

[0030] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a processing method of aircraft ground lateral load, and belongs to the field of aircraft fatigue tests. The method comprises the steps that 1, in an original loading sequence, total load sigma Fz before adjustment in the vertical direction of all undercarriages is calculated; 2, the loading sequence of case load of a left undercarriage and a right undercarriage is changed, so that the lateral load of the left undercarriage and the right undercarriage maintains short-circuit; 3, after the loading sequence is adjusted, total load sigma Fz after adjustment in the vertical direction of all undercarriages is calculated; 4, the vertical load correction coefficient f is calculated; 5, trimming of the vertical load of the whole aircraft is carried out; 6, lateral load of the other parts of the aircraft is eliminated except all the undercarriages; 7, trimming of the whole aircraft rolling torque Mx, the whole aircraft pitching torque My, a front undercarriage lateral load Fy and the whole aircraft yawing torque Mz is carried out; 8, the fatigue allowance influence on crucial parts is calculated. According to the method, on the basis that the part is accurately examined and early damage to the other parts does not occur, the applying means of ground lateral load is adjusted, and the test period is shortened.

Description

technical field [0001] The invention belongs to the technical field of aircraft fatigue tests, and in particular relates to a processing method for aircraft ground side loads. Background technique [0002] The fatigue test of the whole aircraft structure is an important means to verify whether the life of the aircraft structure can meet the service requirements. When the designer formulates the test implementation plan, he needs to do a lot of theoretical analysis and calculation to ensure that the test loading can not only truly simulate the stress state of the aircraft, but also Issues such as the scale of the test implementation and the test period should also be considered. [0003] For ground turning conditions, the lateral load of the landing gear is relatively large, and the corresponding lateral loads on the fuselage and wings are also relatively large. Due to the structural characteristics of the wing, the side load is not easy to apply, and it is usually transferr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 王亚芳王新波闵强秦剑波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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