Integrated design and analysis of inlet and missile with two side layout

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2022-12-05 DOI:10.1515/tjj-2022-0076

Fuzhou Liu, Huacheng Yuan, Jun Liu, Lingfeng Xu, Zhenggui Zhou

引用次数: 0

Abstract

Abstract Based on the flow field characteristics of the missile body, an integrated design method for missile and inlet with two side layout is proposed under asymmetric inflow. The result of numerical simulation shows that shock waves hit on cowl lip on the symmetry plane at the design condition, which verifies the method of integrated design. And the flow characteristics of inlet under the influence of the missile body are analyzed. Under the influence of asymmetric incoming flow and missile body, the first shock wave surface of the two-dimensional inlet presents the characteristics of a three-dimensional concave surface, and there is a pair of asymmetric vortex structures in the inner flow path. Finally, a bleed cavity of self-adaptively adjusting bleeding by vortex is proposed to improve the performance of inlet and broaden the inlet start and attack angle boundary. The minimum Mach number of the inlet start is reduced from 2.8 to 2.3 at ɑ = 6° and the maximum attack angle of inlet start is widened from ɑ = −1° to ɑ = 3° at Ma = 2.1.

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进气道与导弹双面布置一体化设计与分析

摘要根据弹体流场特性，提出了非对称来流条件下弹体与进气道两侧布置一体化设计方法。数值模拟结果表明，在设计条件下，激波击中对称面上的整体式设计方法，验证了整体式设计方法的有效性。分析了弹体对进气道流动特性的影响。在非对称来流和弹体的影响下，二维进气道第一激波面呈现三维凹面特征，内流道存在一对非对称涡结构。最后，为了提高进气道的性能，拓宽进气道的启动角和攻角边界，提出了一种利用涡流自适应调节进气道的排气腔。在Ma = 2.1时，进口起动的最小马赫数从2.8减小到2.3，进口起动的最大攻角从- 1°扩大到3°。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.