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A Method for Optimizing Static Aeroelasticity and Flutter of an All-Motion Stabilizer

A static aeroelasticity, flat tail technology, applied in multi-objective optimization, design optimization/simulation, geometric CAD, etc., can solve static aeroelasticity and flutter, not considering stiffness, mass and aerodynamic shape matching relationship, limiting aircraft flight performance and other problems, to achieve a high degree of matching, solve the effect of static aeroelasticity and flutter

Active Publication Date: 2022-05-06
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology

[0002] The aeroelasticity of the full-motion horizontal tail often limits the flight performance of the aircraft, and the design scheme that conforms to the aeroelasticity is selected when the stiffness, mass and aerodynamic shape are constantly changing. Therefore, it is necessary to optimize the key structure of the full-motion horizontal tail to obtain a structural scheme that meets the constraints

Method used

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[0024] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention will be further elaborated below in conjunction with specific illustrations.

[0025] see Figure 1 ~ Figure 4 A method for optimizing the static aeroelasticity and flutter of the full-motion stabilizer is shown, and the specific steps are as follows:

[0026] 1) Establish a finite element model

[0027] To establish the initial geometric model of the full-motion horizontal tail, first establish the initial geometric model in 3D software such as UG and catia, then import the initial geometric model into MSC.Patran, and then remove redundant lines and surfaces on this basis to establish a complete The initial geometric model of the dynamic horizontal tail;

[0028] Based on the initial geometric model of the full-motion horizontal tail, construct the dynamic model of the full-motion horizontal tail structure, and fi...

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Abstract

A method for optimizing the static aeroelasticity and flutter of a full-motion stabilizer. Firstly, a finite element model is established, and then the static aeroelasticity, flutter, and counterweight are optimized one by one. The matching degree is high, and the requirements of static aeroelasticity and flutter are met. The minimum weight full-motion horizontal tail that does not affect the shape of the horizontal tail meets the constraints and effectively solves the problems of aircraft static aeroelasticity and flutter.

Description

technical field [0001] The invention relates to the technical field of aircraft aeroelastic design, in particular to a method for optimizing the static aeroelasticity and flutter of an all-moving stabilizer tail. Background technique [0002] The aeroelasticity of the full-motion horizontal tail often limits the flight performance of the aircraft, and the design scheme that conforms to the aeroelasticity is selected when the stiffness, mass and aerodynamic shape are constantly changing. Therefore, it is necessary to optimize the key structure of the full-motion horizontal tail to obtain a structural scheme that meets the constraints. Contents of the invention [0003] The technical problem solved by the present invention is to provide a method for optimizing the static aeroelasticity and flutter of the full-motion stabilizer tail, so as to solve the above-mentioned problems in the background technology. [0004] The technical problem solved by the present invention adopts...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/23G06F111/06
Inventor 王钱伟罗敏陈立勇罗士超吴成林孙超亓洪玲龚思楚张海东黄晓霞
Owner JIANGXI HONGDU AVIATION IND GRP
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