Integration test verification method of airplane movable wing surface

A technology of movable wings and test pieces, which is applied in the field of comprehensive test and verification of aircraft movable airfoils, can solve the problems of rash test results, deformation of folding mechanism, and influence of folding function, etc., and achieve the effect of comprehensive strength assessment.

Active Publication Date: 2014-08-20
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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AI Technical Summary

Problems solved by technology

For example, when the foldable outer wing of an aircraft is subjected to flight loads, the large load may cause deformation of the relevant components of the folding mechanism, thereby affecting the folding function, and after repeated folding several times, the deformation or damage of the folding mechanism may affect the For the local static strength of the wing, it is obvious that the separate tests of two mutually independent test pieces cannot fully reflect this influence relationship, and the test results are too aggressive.

Method used

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  • Integration test verification method of airplane movable wing surface
  • Integration test verification method of airplane movable wing surface
  • Integration test verification method of airplane movable wing surface

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Embodiment Construction

[0025] Taking the foldable outer wing as an example, the specific implementation of the method is further described.

[0026] First, determine the technical conditions of the test piece;

[0027] Separately produce a right outer wing with the same technical status as the right outer wing of the same batch of aircraft as a test piece. Use the ground pump source with the same system pressure (26MPa) as the on-board pump source to provide pressure output for folding and unfolding of the folding wings.

[0028] Second, determine the test load according to the limitations of the aircraft, including the static test load and the functional load of the wing surface;

[0029] The maximum positive overload design condition of the wing static strength of this type of aircraft (hereinafter referred to as case 1) is selected as the static test load, and several typical folding weight states of folding wings are selected as the functional durability test load. Specifically, the design loa...

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Abstract

The invention belongs to the field of airplane design, and relates to a method suitable for function and strength integration test verification method of an airplane movable wing surface. The method is characterized in that a function endurance test and a static strength test are simultaneously finished on one test piece. The advantages are as follows: the mutual influences between wing surface bearing deformation and function endurance can be examined, the test period can be shortened, and the function endurance and static strength of the movable wing surface can be more really verified.

Description

technical field [0001] The invention belongs to the field of aircraft design, and relates to a comprehensive test verification method for an aircraft movable wing surface. Background technique [0002] The design of the active airfoil of an aircraft wing must not only meet the requirements of functional durability, but also meet the design requirements of static strength and fatigue strength. Therefore, for this type of structure, functional durability tests are usually used to verify its functional durability throughout its life, and static strength tests are used to verify its static strength, that is, two independent test pieces are required. However, the above verification method is only applicable to some active airfoils with small aerodynamic loads (such as rudders, ailerons, etc.), and this method is not applicable to active airfoils with severe loads. For example, when the foldable outer wing of an aircraft is subjected to flight loads, the larger load may cause def...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00
Inventor 曹奇凯隋福成吴德锋王鄢
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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