Aircraft surface leading edge attachment line area extraction method

A technology of aircraft and attachment lines, which is applied to instruments, image data processing, electrical digital data processing, etc., can solve problems such as the discontinuity of the attachment line area, and achieve the effect of improving accuracy and capturing applicability

Pending Publication Date: 2021-11-12
中国空气动力研究与发展中心空天技术研究所
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Problems solved by technology

[0006] The purpose of the present invention is to propose a method that can quickly and automatically extract the attachment line area of ​​the characteristic leading edge of the aircraft, effectiv

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  • Aircraft surface leading edge attachment line area extraction method
  • Aircraft surface leading edge attachment line area extraction method
  • Aircraft surface leading edge attachment line area extraction method

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[0028] Example: a leading edge surface of an aircraft attachment line region extracting method based on the geometry and surface characteristics inviscid flow field of the aircraft, in conjunction with discrete discriminant Jacobian matrix ( "Discriminant method") and a surface geometry of a linear vector field Analyzing common attachment aircraft leading edge curvature flow area, and the extraction line attachment region wherein the leading edge continuously distributed in an aircraft, such as figure 1 As shown, specifically includes the following steps:

[0029] Sl, the aircraft surface discrete unstructured triangular mesh, unstructured mesh using triangles define the aircraft outer mold line surface, a linear vector field acquisition surface by surface inviscid flow parameters of the aircraft, and the aircraft is calculated by a triangular surface patch the discrete curvature;

[0030] S2, Jacobian matrix construct, obtained after the surface of the aircraft velocity vector fi...

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Abstract

The invention discloses an aircraft surface leading edge attachment line area extraction method, and relates to the technical field of aerodynamic thermal engineering. According to the technical scheme, based on aircraft geometric appearance characteristics and a surface non-viscous flow field, the attachment flow area of the leading edge of the aircraft is jointly judged by combining a Jacobian matrix discriminant of the surface linear vector field and the discrete curvature of the geometric shape, wherein the extracted attachment line areas are continuously distributed at the characteristic leading edge of the aircraft. According to the invention, the continuously distributed characteristic leading edge attachment line flow area can be rapidly and automatically extracted, the change of the position of the attachment line area can be captured when the flight working condition changes, and the capture applicability to the attachment line areas of different types of aircrafts is good; the invention is used for aerodynamic thermal environment engineering calculation, the aircraft characteristic leading edge sweepback cylinder heat flow calculation formula of the attachment line area can be conveniently determined, and the accuracy of characteristic leading edge aerodynamic thermal environment calculation by the engineering method is improved.

Description

technical field [0001] The invention relates to the technical field of aerothermal engineering, and more specifically, relates to a method for extracting the attachment line region of the front edge of the aircraft surface. Background technique [0002] The engineering method combined with Reynolds comparison and reference enthalpy method is an important method for fast calculation of aerothermal environment. During the aerodynamic heating process, the aerodynamic heating phenomenon is most obvious in the stagnation point and the attachment line area of ​​the leading edge of the hypersonic vehicle. Whether the attachment line area can be extracted quickly and accurately will directly affect the efficiency and reliability of the aerothermal engineering calculation method. [0003] Attachment lines are mainly obtained through two methods: user observation and feature detection. The characteristic leading edge areas of hypersonic vehicles (such as the leading edge of the wing ...

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Application Information

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IPC IPC(8): G06F30/28G06F30/15G06T3/00G06F113/08G06F119/14
CPCG06F30/28G06F30/15G06T3/0037G06F2113/08G06F2119/14Y02T90/00
Inventor 李正洲马志成张小庆高昌周正吕金洲王琪曲俐鹏
Owner 中国空气动力研究与发展中心空天技术研究所
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