乘波构型飞行器磁流体进气道一体化概念设计

吕浩宇; 李椿萱; 曹德一

乘波构型飞行器磁流体进气道一体化概念设计

北京航空航天大学航空科学与工程学院, 北京 100191

详细信息

作者简介:
吕浩宇(1978-),男,甘肃静宁人,博士生,Lvhy@buaa.edu.cn.

中图分类号: V 211.1⁺2
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出版历程
- 收稿日期: 2007-09-21
- 网络出版日期: 2008-10-31

Conceptual study on integrated design of magnetohydrodynamic bypass scramjet for a waverider-based hypersonic vehicle

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 采用准一维的磁流体方程组对设计状态下内磁流体发生器进行参数设计,利用斜激波理论设计磁流体进气道一体化的外形.以该外形为基点,对安装五对电极的内磁流体发生器采用五方程模型进行三维数值模拟,并通过调节其磁作用数以满足准一维假设下设计的进气道外形.研究表明,磁流体进气道最小出口流动均匀参数可以作为判别内发生器最优磁作用数的准则,在该磁作用数下内磁流体发生器可以有效地提高进气道的性能.
- 磁流体动力学(MHD) /
- 磁流体进气道 /
- 一体化设计
Abstract: A parametric study on the conceptual design methodology and optimization criteria for an integrated magnetohydrodynamic (MHD) bypass scramjet of a generic waverider-based hypersonic vehicle was performed. An integrated parametric design of an MHD controlled inlet and a built-in MHD generator was first provided using a quasi-one-dimensional MHD model, in conjunction with the theory of oblique shock. Taking the designed configuration as the baseline configuration, a numerical procedure based on a five-equation model associated with low magnetic Reynolds number MHD flow was utilized to simulate and optimize the integrated MHD controlled inlet. It was found that the minimum nonuniform flow parameter at the exit of the inlet channel might act as the criterion for the built-in generator to possess an optimal magnetic interaction parameter capable of improving the performance of the inlet effectively.
- magnetohydrodynamics(MHD) /
- magnetohydrodynamic controlled inlets /
- integrated design

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参考文献(1)

[1] Gurijanov E P, Harsha P T. AJAX: new directions in hypersonic technology . AIAA-96-4609, 1996 [2] Kuranov A L, Sheikin E G. Magnetohydrodynamic control on hypersonic aircraft under Ajax concept[J]. Journal of Spacecraft and Rockets, 2003, 40(2):174-182 [3] Litchford R J, Cole J W, Bityurin V A, et al. Thermodynamic cycle analysis of magnetohydrodynamic-bypass hypersonic airbreathing engines[J]. Journal of Propulsion and Power, 2001, 17(2):477-480 [4] Bityurin V A. A feasibility study and experimental evaluation on MHD acceleration for application to advanced propulsion and hypervelocity ground testing . AIAA-2000-2301, 2000 [5] Kuranov A L, Sheikin E G. MHD control on hypersonic aircraft under AJAX concept-possibilities of MHD generator . AIAA-2002-0490, 2000 [6] Macheret S O, Shneider M N, Miles R B. Magnetohydrodynamic control of hypersonic flows and scramjet inlets using electron beam ionization[J]. AIAA Journal, 2002, 40(1):74-81 [7] Hunt J C R. Magnetohydrodynamic flow in rectangular ducts[J].Journal of Fluid Mech, 1960, 21:577-590 [8] Steal A. Numerical simulation of liquid-metal MHD flows in rectangular ducts[J]. Journal of Fluid Mech, 1990, 216:161-191 [9] Ishikawa M, Itoh K. Three dimensional constricted electric current near anode and cathode of faraday MHD generator[J]. Energy Conversion and Management, 2003, 44: 2111-2124 [10] 吕浩宇, 李椿萱, 董海涛,等. Hall效应对三维磁流体发生器的影响[J]. 力学学报, 2008, 40(3):306-314 Lü Haoyu,Lee Chunhian,Dong Haitao,et al. Hall effects in three-dimensional MHD generator [J]. Chinese Journal of Theoretical and Applied Mechanics,2008,40(3):306-314(in Chinese) [11] Lee C H, Lu H. Quasi-one-dimensional parametric study for MHD generator in MHD bypass scramjet system . AIAA-2007-0644, 2007 [12] Dong H, Zhang L, Lee C. High order discontinuity decomposition entropy condition schemes for Euler equations[J]. CFD Journal, 2002, 10(4):563-568

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