Whole-aircraft dynamic model main gear designing method and simplified structure

A technology of mechanical model and design method, applied in the direction of design optimization/simulation, calculation, special data processing application, etc., can solve the problems of high processing requirements, complex structure, high cost of main landing gear buffer, etc., to achieve clear constraints, Simple structure, low manufacturing cost and low process requirements

Active Publication Date: 2017-01-04
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0003] (1) The design of the main landing gear of the model is exactly the same as that of the real aircraft. This kind of main landing gear buffer is expensive and complex in structure; at the same time, due to the limited size and space of the main landing gear of the model, the proces

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  • Whole-aircraft dynamic model main gear designing method and simplified structure
  • Whole-aircraft dynamic model main gear designing method and simplified structure
  • Whole-aircraft dynamic model main gear designing method and simplified structure

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[0024] In order to make the objectives, technical solutions, and advantages of the implementation 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 accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals indicate the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention, but should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the protection scope of the present inventio...

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Abstract

The invention relates to a whole-aircraft dynamic model main gear designing method, comprising the steps of first, acquiring design dimensions of a whole-aircraft dynamic model main gear at predetermined scale according to dimensions of a true main gear; second, acquiring a force transmission structure of the model main gear according to a force transmission structure of the true main gear, and simulate-calculating physical properties of the simplified main gear force transmission structure; third, fitting according to performance parameters of hydraulic dampers and tires in the true main gear to obtain spring stiffness coefficient and tire performance parameters in the main gear simplified structure; fourth, re-calculating dimensions of springs and tires according to the physical properties of step two and the spring stiffness coefficient and tire performance parameters of step three; fifth, iteratively optimizing to obtain optimal dimensions of the whole-aircraft dynamic model main gear. The whole-aircraft dynamic model main gear designing method provides full guarantee on force transmission structure and force transmission characteristics and enables the design to meet dynamic test requirements.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure strength tests, and in particular relates to a method for designing a main landing gear of a dynamic model of the whole aircraft and a simplified structure. Background technique [0002] The main landing gear is the medium between the aircraft and the ground. In the previous dynamic model design, the main landing gear buffer design has the following methods: [0003] (1) The design of the main landing gear of the model is exactly the same as that of the real aircraft. This kind of main landing gear buffer is expensive and complex in structure; at the same time, due to the limited size and space of the main landing gear of the model, the processing requirements are extremely high; [0004] (2) The main landing gear of the model is a combination of a single rod and a tire, without a buffer part. In the test, the main landing gear only provides support and cannot meet the requirements of t...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 方威金鑫张建刚
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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