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A Simulation Method for Heading Stiffness of Landing Gear

A technology of stiffness simulation and landing gear, applied in instruments, geometric CAD, calculations, etc., can solve the problems of inaccurate spin and rebound load simulation, and achieve the effect of a wide range of applications

Active Publication Date: 2019-02-12
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] The purpose of the present invention is to provide a method for simulating the heading stiffness of landing gear to solve the problem of inaccurate simulation of spin-up and rebound loads in the dynamic analysis of landing gear

Method used

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  • A Simulation Method for Heading Stiffness of Landing Gear
  • A Simulation Method for Heading Stiffness of Landing Gear
  • A Simulation Method for Heading Stiffness of Landing Gear

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Embodiment Construction

[0022] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

An undercarriage course stiffness simulating method includes the following steps of exerting course loads on an undercarriage axle under the compression amount of any buffer, measuring the course displacement of the undercarriage axle, calculating the course stiffness value of the undercarriage axle, drawing the curve of the correspondence between the course stiffness value of the undercarriage axle and the compression amount of the buffer, establishing an undercarriage model, calculating the stiffness value of an elastic component, and conducting undercarriage landing simulating according to the correspondence between the stiffness value of the elastic component and the compression amount of the buffer as the data to obtain startup loads and springback loads of a tire. The problem that startup and springback loads are not accurately simulated in existing undercarriage analysis is solved, the startup and springback loads of the undercarriage are effectively analyzed, and the method is easy and convenient to implement and wide in application range.

Description

technical field [0001] The invention belongs to the field of aircraft structure design, in particular to the field of structural mechanics, and specifically relates to a simulation method for heading stiffness of landing gear. Background technique [0002] Part 25 of the Civil Aviation Regulations of China clearly stipulates that the dynamic characteristics, spin and rebound of the landing gear should be taken into account in the analysis of the landing gear load. There are two main dynamic analysis methods for landing gear: one is to make all parts of the landing gear rigid. This method is simple in modeling and high in analysis efficiency. However, because the elasticity of the landing gear parts is not considered, the spin load obtained by the analysis is not real. , and there is no rebound load at the same time; the other is to make all parts of the landing gear flexible. This method effectively reflects the elasticity of the parts, but the modeling is complicated, and t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17G06F30/20
Inventor 张红方威孙琳贾锦
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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