Hypersonic speed isolation section optimization design method and system

An optimized design, hypersonic technology, used in computer-aided design, computing, special data processing applications, etc., can solve problems such as inability to achieve design

Active Publication Date: 2019-09-06
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0006] In the geometric fusion method in the existing optimal design method, the spatial position of the discrete point obtained by discretizing the fusion section is uniquely determined. As long as the fusi...

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  • Hypersonic speed isolation section optimization design method and system
  • Hypersonic speed isolation section optimization design method and system
  • Hypersonic speed isolation section optimization design method and system

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[0055] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. 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.

[0056] In this embodiment, the present invention is discussed by taking the optimal design of a certain curved isolation section in engineering research as an example, and its initial configuration is as follows figure 1 As shown, among them, Inlet for the air intake, Outlet for the combustion chamber.

[0057] Such as figure 2 A hypersonic isolation section optimization design method shown includes the following steps:

[0058] 201. According...

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Abstract

The invention provides a hypersonic speed isolation section optimization design method and system. The hypersonic speed isolation section optimization design method comprises the steps of extracting molded lines of an air inlet channel outlet and a combustion chamber inlet to obtain an isolation section inlet and an isolation section outlet; dividing the inlet of the isolation section into A1A2, A2A3,..., AnA<n+1>, and dividing the outlet of the isolation section into B1B2, B2B3,..., BnB<n+1>; obtaining a jth on-way transition molded line CijC<(i+1)j> of AiA<i+1> to BiB<i+1> smooth transition,and integrating CijC<(i+1)j> to obtain a jth on-way transition section of smooth transition from an isolation section inlet to an isolation section outlet; acquiring a bias control line, and assembling all the transition sections on corresponding bias points in the bias control line to obtain a three-dimensional variable cross-section bending isolation section; and generating a grid from the three-dimensional variable cross-section bending isolation section, performing cyclic simulation, and adjusting the value of the control parameter by adopting an optimization algorithm until a simulationoptimization target reaches convergence. And the defects of optimization design of an isolation section in the prior art are effectively overcome. The method is applied to the technical field of hypersonic engines.

Description

technical field [0001] The invention relates to the technical field of hypersonic engines, in particular to a hypersonic isolation section optimization design method and system. Background technique [0002] A hypersonic vehicle is an aircraft powered by a scramjet engine and a combined engine that can fly at hypersonic speeds in the atmosphere and across the atmosphere. Among them, the isolation section is an important part of the scramjet engine. Its function is to isolate the influence of the back pressure in the combustion chamber on the upstream intake port, and accommodate the shock wave train, decelerate and pressurize the incoming flow, and improve the quality of the flow field. The quality of its performance directly affects the performance of the scramjet engine. [0003] The isolation section can be divided into straight isolation section and curved isolation section according to whether the entrance and exit are offset. The flow field in the equal-straight isol...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17
Inventor 范晓樯陈镜帆王翼蒙泽威熊冰莫然刘俊兵徐阳
Owner NAT UNIV OF DEFENSE TECH
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