Deformation constraint optimization method for strength test wing

Abstract

The invention belongs to the technical field of aircraft strength test design, and particularly relates to a deformation constraint optimization method for a strength test wing, which comprises the following steps: step 1, constructing a mechanical model of the test wing under the action of a water load, the mechanical model being a mechanical balance model of the wing under the action of the water load and a trimming load; 2, determining constraint conditions for deformation constraint optimization of the test wing according to the mechanical model; 3, converting multi-objective optimizationcontaining the two parameters into single-objective optimization based on the degree of influence of the deflection and the rotation angle on wing deformation by taking two optimization objectives ofthe minimum deflection and the minimum deflection angle at the boundary s of the area to be assessed as two optimization objectives; and 4, according to the constraint conditions in the step 2 and theoptimization target in the step 3, performing iterative solution by adopting an ant colony algorithm to obtain an optimal balancing load scheme. According to the invention, aircraft wing displacementand corner change caused by water load can be reduced at the same time, wing deformation is restrained, and the test loading precision is improved.

Description

technical field [0001] The application belongs to the technical field of aircraft strength testing, and in particular relates to a deformation constraint optimization method of a strength testing wing. Background technique [0002] When a large amphibious aircraft lands on water, the buoys and the hull structure of the fuselage will bear a huge water impact load. The water load has the characteristics of large magnitude, uniform distribution in the coverage area, and oblique ballast. Under the action of oblique ballast water load on the surface of the V-shaped structure of the buoy, the wing will have a significant upward displacement (the buoy is located below the wing and connected to the wing), resulting in a large deviation in the direction of the force line of the water load. Shift, load applied distortion. The compression stability of the water load loading device and the ability to adapt to angle changes are limited, which can easily cause the instability of the leve...

AI Technical Summary

Problems solved by technology

For the full-aircraft test of an amphibious aircraft, adding local restraints to the wings will cause super-static problems, which do not meet the relevant regulations of airworthiness and test standards; due to the particularity of the aircraft, the mission statement provided by the test client , it is clearly required that trim loads cannot be applied to the area from the assessment position to the wingtip; the structure of the buoy and the pressure-intensive large load determine that the follow-up loading structure is very complex, and the trajectory of each loading point is complex and different, which cannot be realized by the current follow-up loading technology

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