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A Lightweight Design Method for Landing Gear Brake Components

A lightweight design and landing gear technology, applied in the field of aircraft landing gear, can solve problems such as not considering fatigue life, falling into local solutions, and relying on initial design points, so as to improve safety and maneuverability, and optimize the process reliably.

Active Publication Date: 2021-11-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] Throughout the existing literature, about combining approximate models and intelligent optimization algorithms for lightweight design of landing gear structures, the optimization algorithms in some literatures are relatively traditional, with high reliability but low efficiency; some literatures use experimental design methods with sample uniformity is not high, and cannot accurately fit the real situation; the gradient optimization algorithm used in some literatures is very dependent on the initial design point, and it is more likely to fall into a local solution; most of them only meet the strength requirements as constraints, and do not consider fatigue life, making Optimization results are not feasible

Method used

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  • A Lightweight Design Method for Landing Gear Brake Components
  • A Lightweight Design Method for Landing Gear Brake Components
  • A Lightweight Design Method for Landing Gear Brake Components

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Embodiment Construction

[0037] The present invention will be further described below in conjunction with the accompanying drawings and examples.

[0038] Such as figure 1 As shown, the present invention provides a method for lightweight design of landing gear brake components based on response surface model and multi-island genetic algorithm, comprising the following steps:

[0039] Step 1: Considering the safety factor, the mises stress range of the brake component that meets the normal functional requirements of the landing gear is given as σ max ≤0.67σ b , σ b is the strength limit of the material used, and the range of fatigue life K is 1.5K a ≤K≤2K a , K a Design fatigue life for the original;

[0040] Step 2: Determine the variation range of the brake component design variables, such as figure 2 Shown: the outer diameter of the lug D∈[D 1 ,D 2 ], cross beam longitudinal width K 1 ∈[K 1a , K1b ], cross beam transverse width K 2 ∈[K 2a , K 2b ], the longitudinal thickness of the c...

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Abstract

The invention discloses a light-weight design method for landing gear brake components based on a response surface model and a multi-island genetic algorithm, including: 1. Given the range of mises stress and fatigue life of the brake components that meet the normal functional requirements of the landing gear; 2. Determine the variation range of the design variables of the brake components; 3. Combining the design variables, mises stress, and fatigue life variation ranges, give constraints and establish the objective function; 4. Use the optimal Latin hypercube test design method to select sample points; 5. , calculate the comprehensive parameters of the brake components according to the sample point parameters, including component quality, fatigue life, and maximum mises stress; Sixth, combine the M group of sample points and the M group of brake component comprehensive parameter data, and use the method of complete search to establish a fourth-order response surface model Seventh, based on the established response surface model, the multi-island genetic algorithm is used to optimize the lightweight structure design problem, and the optimal solution is taken as the final structural optimization parameter in the converged solution.

Description

technical field [0001] The invention belongs to the technical field of aircraft landing gear, and in particular relates to a lightweight design method for braking components of landing gear based on a response surface model and a multi-island genetic algorithm. Background technique [0002] Aircraft landing gear is the main load-bearing device of the aircraft during take-off, landing, taxiing and ground parking. In the traditional aircraft design process, the design of landing gear parts adopts static strength design, supplemented by a large safety factor for strength check , but the landing gear parts designed by this design method often have larger stress margin and fatigue life margin. In the process of modern aircraft design, using CAD and CAE auxiliary tools for lightweight design has become an important research direction of aircraft landing gear design. The lightweight design of the aircraft landing gear structure helps to improve the safety and maneuverability of th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/17G06F30/15G06F30/23G06F111/04G06F119/14
CPCG06F30/15G06F30/17G06F30/23
Inventor 魏小辉谢欣宏陈虎张钊王添翼
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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