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Simple and quick geometric-constraint and weight-function calculation method suitable for use in complex aerodynamic shape of aircraft

A technology of aerodynamic shape and geometric constraints, which is applied in the evaluation of geometric constraints of complex aerodynamic shapes and the selection of multi-point optimization weight functions.

Active Publication Date: 2018-06-22
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

[0016] For the requirement of multiple design indicators, it is impossible to give a reasonable distribution of weight coefficients, and manual experience is insufficient

Method used

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  • Simple and quick geometric-constraint and weight-function calculation method suitable for use in complex aerodynamic shape of aircraft
  • Simple and quick geometric-constraint and weight-function calculation method suitable for use in complex aerodynamic shape of aircraft
  • Simple and quick geometric-constraint and weight-function calculation method suitable for use in complex aerodynamic shape of aircraft

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Embodiment Construction

[0041] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0042] The present invention adopts two parts to design, wherein:

[0043] The first part is the evaluation of geometric constraints for the optimization design of complex aerodynamic shapes, using the following steps:

[0044] 1. Based on the digital model, convert it into a data format that can be recognized by CFD software;

[0045] 2. Determine the design section, as well as the thickness and volume constraint position;

[0046] Three, divided as figure 1 As shown in the volume and thickness calculation medium grid, the volume calculation medium grid can be a structured grid or an unstructured grid, and the thickness calculation medium grid must be a structured grid;

[0047] 4. Read the medium grid and the discrete surface grid together into the parameterization program. The parameteri...

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Abstract

The invention discloses a simple and quick geometric-constraint and weight-function calculation method suitable for use in a complex aerodynamic shape of an aircraft. An entirely new evaluation methodof complex-aerodynamic-shape optimization design geometric-constraint and a method of weight-function selection of sensitivity-based multi-point optimization are adopted, geometric constraints of thickness, volume and the like of the any complex shape are accurately and conveniently calculated, and the calculation method is compatible with discrete surface multi-block-butt-joint-connection-grids,discrete surface unstructured-grids and the like; and weight-function selection can fully utilize valid information of existing weight-function data, and has weight coefficient selection instructiveness, and thus design potential of sensitivity-based optimization technology is fully exploited.

Description

technical field [0001] The invention relates to the field of geometric constraint evaluation of aircraft aerodynamic optimization design and multi-point design based on sensitivity, especially the geometric constraint evaluation and multi-point optimization weight function selection of complex aerodynamic shape. Background technique [0002] In the optimization design of complex aerodynamic shapes of aircraft, the evaluation of geometric constraints is a key factor in engineering design. Geometric constraints directly affect the determination of the design space and the distribution characteristics of the objective function, which further affects the optimization design efficiency and aircraft design quality. A simple geometric constraint evaluation method is the premise of carrying out rigorous engineering design and providing effective geometric information for the optimization decision-making system. [0003] In the actual model engineering design, the aerodynamic design ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F2111/04G06F2111/10Y02T90/00
Inventor 黄江涛刘红阳周铸余永刚余雷张培红余婧郑传宇
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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