Elastomeric aircraft flight simulation method, system and computer storage medium

A technology of flight simulation and aircraft, applied in computer-aided design, calculation, design optimization/simulation, etc., can solve problems such as difficult to apply to engineering applications, large amount of calculation, low calculation efficiency, etc., to improve aircraft performance, ensure calculation accuracy, The effect of improving computational efficiency

Active Publication Date: 2021-08-31
INST OF MECHANICS - CHINESE ACAD OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are defects that it is difficult to apply to engineering applications, the amount of calculation is large, and the calculation efficiency is low. For the flight dynamics simulation of elastic body aircraft with high efficiency and high progress, it is necessary to seek other ideas

Method used

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  • Elastomeric aircraft flight simulation method, system and computer storage medium
  • Elastomeric aircraft flight simulation method, system and computer storage medium
  • Elastomeric aircraft flight simulation method, system and computer storage medium

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Experimental program
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Effect test

Embodiment approach

[0056] As an embodiment of the present invention, the simulation method also includes, judging whether the current number of steps k is N f Integer multiples of , if it is, then output the current grid, flow field and continuous calculation data, so as to output the intermediate flow field data. Among them, N f The number of interval steps saved for the set flow field output can be set according to the requirements. If the frequency of the intermediate flow field data that needs to be output is relatively high, you can set N f The value of is too small, if the frequency of the intermediate flow field data to be output is relatively low, you can set N f The value of is too large, if you do not need to output intermediate flow field data, you can directly set N f Just equal to N.

[0057] Among them, before performing CFD / CSD / RBD coupling calculation or UAM / CSD coupling calculation, or after performing CFD / CSD / RBD coupling calculation or UAM / CSD coupling calculation, it is ju...

Embodiment approach

[0059] As an implementation method of the present invention, such as figure 1 As shown, the specific simulation method steps include,

[0060] S1, read the main program setting parameters, grid, structural model table parameters, flight mechanics parameters and aerodynamic model; among them, in the main program setting parameters, set the initial time step ts′, reference time step ts, CFD / CSD / RBD coupling calculation interval n, total simulation steps N, initial solution steps m and flow field output saved interval steps N f value;

[0061] S2, judge whether the current step number k is less than or equal to N, if yes, enter S3; if not, output the grid, flow field and continuous calculation data, and the simulation ends;

[0062] S3, judging whether the current step number k is less than or equal to m or k is an integer multiple of n, if yes, then enter S4, if not, then enter S6;

[0063] S4, according to the grid node coordinates obtained in step k-1, perform dynamic defo...

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Abstract

The invention relates to a flight simulation method, system and computer storage medium of an elastic body aircraft. In the method, the CFD method is used to calculate the aerodynamic force in the first m steps, and the CFD / CSD / RBD coupling calculation is performed so as to accurately calculate the initial excitation to the structure. For the influence of dynamic response, the time step is ts′; when m<k≤N, combine CFD and UAM methods to calculate aerodynamic forces, and perform multi-time scale UAM / CFD / CSD / RBD coupling calculations to determine whether k is n Integer multiples of , if yes, perform CFD / CSD / RBD coupling calculation, where RBD time step is n ts, CSD time step is ts; if not, UAM / CSD coupling calculation is performed, time step is ts . Compared with CFD / CSD / RBD coupling calculation, the technical solution of the present invention reduces the number of CFD calls and improves calculation efficiency under the premise of ensuring calculation accuracy, and is more suitable for engineering applications.

Description

technical field [0001] The invention relates to the technical field of aircraft flight simulation, in particular to the flight simulation of elastic body aircraft. Background technique [0002] All aircraft are elastic bodies, and in the traditional aircraft design process, the aircraft is simplified into a rigid body. However, the aircraft design tends to be refined, and the dynamics of elastomeric aircraft cannot be ignored. The flight dynamics simulation problem of elastic body aircraft is a multi-disciplinary dynamic problem that couples aircraft unsteady aerodynamics, aircraft structural dynamics, flight mechanics, etc., but it is difficult for engineering applications to greatly improve the accuracy of calculations. Improve computational efficiency. [0003] For the flight dynamics simulation problem of elastic body vehicles, the current solution is to use the CSD / RBD coupling solution method based on CFD to simulate the flight dynamic response of elastic body vehicl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/28G06F119/14G06F113/08
CPCY02T90/00
Inventor 杨磊张陈安刘文李文皓
Owner INST OF MECHANICS - CHINESE ACAD OF SCI
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