A Frequency Error Correction Method for Aircraft Flutter Model
A technology of flutter model and frequency error, which is applied in the field of manufacturing aircraft wind tunnel composite flutter test models, can solve problems such as calculation errors, dispersion errors, and easy to exceed the allowable range of model design errors, so as to improve accuracy and process Convenience and the effect of reducing the scrap rate
Active Publication Date: 2016-01-13
DALIAN UNIV OF TECH
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However, due to calculation errors caused by engineering assumptions in the model design process, dispersion errors of composite materials, geometric errors in model manufacturing and additional stiffness errors in assembly, etc., the modal frequency of the manufactured model is likely to exceed the model design. Error tolerance range
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[0036] The specific embodiments of the present invention will be described in detail below in conjunction with the technical solutions and accompanying drawings.
[0037] figure 1 It is a structural diagram of a transonic flutter model similar to the wing composite material structure, which is composed of wing root joint 1, upper and lower wing skins 2, multiple vertical spars 3 and transverse ribs 4.
[0038] figure 2 It is the skeleton structure diagram of the composite material model after the skin is removed, and it is composed of multiple transverse wing ribs 3 and vertical wing beams 4 .
[0039] The wing skin 2, the spar 3 and the wing rib 4 of the composite material model are all made of resin-based fiber-reinforced composite materials.
[0040] Use vernier calipers and side thickness calipers to measure the length and thickness of each component of the model, including variable thickness skin 2, variable cross-section spar 3 and wing rib 4, to obtain the geometric ...
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The invention relates to a method for correcting frequency errors of an aircraft flutter model, and belongs to the technical field of manufacture of an aircraft wind tunnel composite material flutter test model. The method is characterized in that according to errors of each main natural frequency and design value of a composite material structure similar model (hereafter referred to as a composite material model), obtaining a correction scheme by a finite element simulating, analyzing and optimizing method; according to the correction scheme, adding a composite material paving layer on each correction area of the inner side of a skin of the composite material model by a secondary forming process; and changing the rigidity distribution of the composite material model, meanwhile, adjusting the weight distribution feature of the composite material model by counterweight, keeping the weight distribution feature constant, and then correcting the error of each main frequency of the composite material model, so as to allow the error to be within the design allowance range. The method has the beneficial effects that the pointed performance is high, the process is easy and convenient, the manufacture accuracy of the composite material model is improved, the defective rate is reduced, and the manufacture period is shortened.
Description
technical field [0001] The invention belongs to the technical field of manufacturing aircraft wind tunnel composite material flutter test models, and in particular relates to a frequency error correction method for a transonic aircraft flutter model with similar composite material structures based on optimization technology and composite material secondary molding technology. Background technique [0002] In the process of aircraft development, a large number of wind tunnel tests must be conducted to obtain the aeroelastic response characteristics of the aircraft, to study and check the flutter performance of the aircraft structure, and to provide a reference for structural design. The precise manufacturing of the aircraft flutter model is the key to the success of the wind tunnel test, so it is necessary to ensure that the main natural frequencies of the flutter model meet the design requirements. [0003] At present, the most commonly used wind tunnel flutter test of aircr...
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IPC IPC(8): G06F17/50
Inventor 杨睿贾振元张强孙士勇李龙涛钱卫郭东明
Owner DALIAN UNIV OF TECH