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Optimal design method of aircraft inner flap mechanism

An optimization design and flap technology, applied in design optimization/simulation, geometric CAD, etc., can solve the problem of incapable of optimal design of flap mechanism, and achieve the effect of rational design optimization, loss reduction, and failure rate reduction.

Active Publication Date: 2020-05-12
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0006] The purpose of the present disclosure is to overcome the deficiency that the above-mentioned prior art cannot carry out a reasonable optimization design for the flap mechanism, and provide a method for optimizing the design of the flap mechanism in an aircraft that can perform a reasonable optimization design for the flap mechanism

Method used

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  • Optimal design method of aircraft inner flap mechanism
  • Optimal design method of aircraft inner flap mechanism
  • Optimal design method of aircraft inner flap mechanism

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Embodiment approach

[0087] During the dynamic analysis of the flap lowering process, it was found that there are two main parameters that can reflect the stiffness and smoothness of the slide rail. One is the torsion angle caused by the deformation of the slide rail during the motion process. When the torsion angle increases, the influence of the roller The ability to move through the slide rail increases the movement resistance of the slide rail; another parameter is the stress. When the force between the slide rail and the roller increases, the stress on the slide rail will inevitably increase, which can also reflect The smoothness of the slide rail movement. On the other hand, whether the weight of aviation components can be improved during optimization is also an important aspect to measure whether the optimization goal can be achieved. Therefore, in the present disclosure, three example implementations are proposed, specifically as follows, example implementation 1: take the maximum stress a...

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Abstract

The invention relates to the technical field of optimization design, and provides an optimization design method of an aircraft inner flap mechanism. The method comprises the following steps: carryingout dynamic simulation analysis on a flap retracting and releasing mechanism in an airplane to obtain a dynamic simulation model; based on a dynamic simulation model, combining a minimum sequence planning method to respectively carry out different optimization on the slide rail by taking the maximum stress, the minimum weight and the minimum torsion angle in the operation process as targets to obtain three groups of optimization results; carrying out dynamic assessment on the three groups of optimization results, and selecting the optimization results meeting preset conditions to carry out optimization design. According to the method, finite element modeling and dynamic analysis are combined through dynamic simulation analysis, the dynamic characteristics of the flap mechanism in the retracting and releasing process can be truly reflected, the accurate dynamic response characteristics are obtained, and the flap mechanism can be reasonably and optimally designed. Furthermore, the failure rate of the inner flap mechanism can be reduced, and losses caused by damage of the inner flap mechanism are reduced.

Description

technical field [0001] The present disclosure relates to the technical field of optimization design, in particular to an optimization design method of an aircraft inner flap mechanism. Background technique [0002] The flap retractable system is an indispensable subsystem of modern aircraft, mainly used to increase the lift and shorten the take-off and landing run distance. Once the flap retractable mechanism breaks down, the light aircraft will be damaged, and the serious one will be destroyed, causing huge losses. Therefore, it is very necessary to strengthen the research on the flap retractable mechanism and optimize its design. [0003] In the prior art, for the simulation of the kinematics and dynamics of the flap mechanism, it is mainly to establish its simplified rigid body model according to the researched flap retraction mechanism, and to carry out kinematics simulation analysis. Although this method can combine graphics It reflects the kinematics characteristics i...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23G06F30/15
Inventor 周长聪岳珠峰吉梦瑶赵浩东黄晓宇
Owner NORTHWESTERN POLYTECHNICAL UNIV
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