A loading method for flap loads in full-scale fatigue tests

Abstract

The invention belongs to the technical field of fatigue tests and relates to a flap load loading method for full-scale fatigue tests. The method of the present invention starts from the technical field of fatigue testing, and according to the force transmission characteristics of the three-slot flap, the fatigue load of the flap under various angle states of multiple components is processed to the key angle θ, and the main load-bearing component is applied in the main direction. . In addition, according to the distributed load characteristics and structural characteristics of the main load-bearing parts, the divisional processing is carried out. According to the two principles of the design state of the connection point of the flap and the wing and the test state, the main direction load error is not greater than the target error and the fatigue damage of the assessment part is equivalent. Through iterative calculation , on the basis of ensuring the accuracy of flap-to-wing load transfer and assessment, the designed flap load application scheme is optimal, that is, the number of actuators is the least under the same effect. The theoretical basis used in the invention is correct, the analysis steps are clear and simple, and the calculation process is convenient for computer automatic iterative calculation.

Description

technical field [0001] The invention belongs to the technical field of fatigue tests and relates to a flap load loading method for full-scale fatigue tests. Background technique [0002] Flaps are an important lift-increasing device for aircraft structures. For large aircraft, in order to pursue a higher lift coefficient, the flaps use three-slotted flaps, including inner front flaps, inner main flaps, inner rear flaps, outer front flaps, The outer main flap and the outer rear flap, the connection between the flap and the wing considers the safety of damage, and the structure of the multi-path force transmission path is not designed, and because the aerodynamic requirements are different in different stages such as take-off, cruise, landing / go-around, the flap needs swing in different positions. Therefore, the flap structure is complex and the movement is complex, resulting in very complex loads. In the plan of aircraft structure life verification test, the fatigue test of...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is: a full-scale fatigue test flap load design method, which can simply and accurately apply the flap fatigue load, to solve the technical problem of the contradiction between the complexity of the wing load application and the authenticity of the assessment

Images