Airplane suspension joint structure fatigue test design method

Abstract

The invention relates to an airplane suspension joint structure fatigue test design method comprising the following steps: 1, building a whole-aircraft finite element model and carrying out whole-aircraft solution; 2, carrying out load distribution according to each flange rigidity proportion so as to obtain the load of each flange, and simplifying a testpiece structure form; 3, building a local detail model and carrying out calculation solution; 4, obtaining fatigue margin of a test zone and a transition segment; 5, enhancing the rigidity of the transition segment structure according to the obtained fatigue margin; 6, determining transition segment length L1 and L2; 7, loading according to a preset cycle sequence and cycle frequency so as to carry out fatigue tests. The airplane suspension joint structure fatigue test design method is based on the features that the airplane suspension joint structure is complex in jointing, more in transfer lines, and hard to design tests; the airplane suspension joint structure fatigue test design method can provide loads and load distribution rules of joints and each bolt, thus finally determining a testpiece structure form and loading scheme.

Description

technical field [0001] The invention belongs to the field of aviation fatigue damage tolerance test, in particular to a design method for fatigue test of aircraft suspension joint structure. Background technique [0002] The key points and difficulties of aircraft structural fatigue tests are usually reflected in the planning and formulation of test programs. When formulating the test plan, a lot of theoretical analysis and calculations are required to ensure that the test plan can not only truly simulate the stress state of the test piece, but also consider the feasibility of the test. [0003] For a simple connection joint structure, the position of the load point and the direction of the load are fixed, but the value of the load changes under various load conditions, so only a single point load can be applied to simulate the test state. For the connection joint structure with complex structure and complex stress state, because the load magnitude and load action point are...

AI Technical Summary

Problems solved by technology

[0005] Regarding the research on the formulation of the aircraft structural fatigue test program, there are many public researches at home and abroad, but most of them are from the consistency of the stress state of the test piece, the design of the transition section and support section of the test piece, the simulation of the test piece constraint, the test Theoretically elaborated on the optimization of load, but failed to give a practical fatigue test design method for the aircraft suspension joint structure itself in terms of its stress and load characteristics

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