Quasi-static undercarriage dynamics model construction method

A dynamic model and construction method technology, applied in the field of aircraft simulation, can solve problems such as dependence on flight test data, high development costs, and complexity, and achieve the effects of simplifying the solution process, improving operating efficiency, and reducing dependence

Active Publication Date: 2017-12-22
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

At present, the dynamics simulation of the landing gear is either too simple to simulate the ground motion process of the airc

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  • Quasi-static undercarriage dynamics model construction method
  • Quasi-static undercarriage dynamics model construction method

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[0028] 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

The invention discloses a quasi-static undercarriage dynamics model construction method, and belongs to the technical field of aircraft simulation. The method includes: step 1, inputting aircraft state parameters, and internally constructing main undercarriage-system parameters; step 2, constructing a tire coordinate system, a half-wheel-axis coordinate system, a shock-absorbing pillar coordinate system and an aircraft body coordinate system, and establishing conversion matrices of mutual conversion of all the coordinate system; step 3, calculating whether aircraft wheels are in contact with ground and whether shock-absorbing pillars are compressed, and calculating corresponding tire pressure; step 4, using the iterative initial values to calculate stress of each shock-absorbing pillar, stress of each wheel axis and stress of each tire until difference values between two frames thereof meet a threshold value requirement; step 5, obtaining received resultant force and a resultant moment of a body axis system at a gravity center of the aircraft by solving through coordinate conversion; and step 6, outputting calculation process parameters according to needs. According to the method, a solving process of undercarriage system parameters is simplified while aircraft ground-motion simulation precision is guaranteed, running efficiency of a simulation program is improved, and dependence of the model parameters on flight test data is reduced.

Description

technical field [0001] The invention belongs to the technical field of aircraft simulation, and in particular relates to a method for constructing a dynamic model of a quasi-static landing gear. Background technique [0002] During the ground movement of the aircraft (taxi, brake, turn, wheel lift, liftoff and touchdown, etc.), the tires are in contact with the surface of the runway to provide the necessary support and friction for the aircraft. The dynamics simulation modeling of the landing gear system plays a vital role in simulating the ground motion process of the aircraft, and is an important part of the flight simulation field. The dynamic model of the landing gear is an indispensable part in the type test evaluation and pilot training equipment development. It is also an important influencing factor of some standard evaluation items in the equipment grade identification and use efficiency evaluation. For example, in aircraft single-engine failure assessment, the de...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20Y02T90/00
Inventor 林皓
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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