Flap load loading method for full scale fatigue test

A technology of fatigue test and fatigue load, applied in the field of fatigue test, to achieve the effect of facilitating computer automatic iterative calculation, optimal application scheme, and fewer actuators

Active Publication Date: 2019-03-19
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

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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

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  • Flap load loading method for full scale fatigue test
  • Flap load loading method for full scale fatigue test
  • Flap load loading method for full scale fatigue test

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Embodiment Construction

[0026] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0027] The full-scale fatigue test flap load loading method of the present invention is from the fatigue test technical field, and according to the force transmission characteristics of the three-slot flap, the flap fatigue loads under various angle states of multiple components are all processed to the critical angle θ , the main bearing part, 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 fla...

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Abstract

The invention belongs to the technical field of fatigue test and relates to a flap load loading method for a full scale fatigue test. The method disclosed by the invention comprises the following steps: from the technical field of fatigue test, according to load transferring characteristics of three-slotted flaps, processing flap fatigue loads of multiple components in a multi-angle state to a keyangle theta, and applying to a main bearing component in a principal direction; performing zoning processing according to distribution load features and structural characteristics of the main bearingcomponent; and according to two principles that a load error in a principle direction of a design state and a test state of the flap and wing connection points is not more than a target error and fatigue damage of the assessment part is equivalent, performing iterative computations, optimizing the designed flap load application scheme on the basis of ensuring flap-to-wing transferring and assessing accuracy, namely the number of actuator cylinders is minimum under the same effect. According to the method disclosed by the invention, the used theoretical basis is accurate, the analytical procedures are clear and simple, and the computer automated iterative computation is conveniently performed in the computation process.

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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/32
CPCG01N3/32G01N2203/0073
Inventor 雷晓欣秦剑波张彦军王新波朱亮
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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