Load applying method under condition of large deformation of long-strut landing gear

Abstract

The invention provides a load applying method under the condition of large deformation of a long-strut landing gear. The load applying method under the condition of large deformation of the long-strutlanding gear comprises the following steps: step 1, calculating vertical and course theoretical displacements delta x and delta y of each loading stage; step 2, presetting vertical and heading mounting positions of the loading device; step 3, establishing an undercarriage load application mechanical simplification model, and calculating an included angle between an ith loading stage load application direction and a theoretical load direction; step 4, establishing a course mechanical balance equation and a vertical mechanical balance equation; step 5, calculating to obtain an ith-stage test vertical load and a course load; step 6, calculating the test applied loads of all the loading stages; and step 7, carrying out a test pre-test according to the calculated load, and obtaining a corrected final load and a preset position result. According to the load applying method under the condition of large deformation of the long-strut landing gear, accurate processing of the landing gear test load can be conveniently achieved, and universality is high.

Description

technical field [0001] The application belongs to the technical field of aircraft landing gear, and in particular relates to a load applying method under the condition of large deformation of a long-strut landing gear. Background technique [0002] As an important part of the aircraft, the landing gear must be accurately assessed in the test for its strength. For most military aircraft and general small aircraft, the landing gear is located on the fuselage of the aircraft, and the deformation is small in the static test of the whole aircraft, so the load change caused by the deformation may not be considered. However, for long-strut landing gear, especially when the landing gear is fixed on the wing, the loading accuracy will be significantly affected due to the large deformation of the wing and the landing gear body during the test. [0003] At present, in the static test of the whole aircraft, the heading and side loads of the landing gear are directly applied by hydrauli...

AI Technical Summary

Problems solved by technology

[0004] The above load application method can ensure that the final load application of the landing gear is relatively accurate, but the disadvantages are also obvious: 1. This method can only ensure that the final load application direction is close to the theoretical load direction, and cannot guarantee the load applic

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