侧向收缩比对RBCC侧压式进气道起动性能的影响

吴亚可; 何国强; 刘佩进; 刘晓伟

doi:10.15892/j.cnki.djzdxb.2011.03.029

弹箭与制导学报 >

2011 , Vol. 31 >Issue 3: 146 - 150

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2011.03.029

火箭技术

侧向收缩比对RBCC侧压式进气道起动性能的影响

吴亚可 ,
何国强 ,
刘佩进 ,
刘晓伟

展开

西北工业大学固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安 710072

吴亚可(1984-),男,河南人,博士研究生,研究方向:发动机总体设计。

收稿日期: 2010-08-30

网络出版日期: 2025-05-30

收起

The Influence of Sidewall Contraction Ratio on the Starting Performance of RBCC Supersonic Sidewall-compression Inlet

WU Yake ,
HE Guoqiang ,
LIU Peijin ,
LIU Xiaowei

Expand

National Key Laboratory of Combustion Flow and Thermo-structure, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2010-08-30

Online published: 2025-05-30

Fold

摘要

低来流马赫数时,侧向压缩将是RBCC发动机进气道的主要压缩形式。文中开展了侧向收缩比对RBCC侧压式进气道起动性能的影响研究。采用数值模拟方法获得了进气道的流场分布和性能参数。结果发现,不同侧向收缩比的进气道在起动过程中都伴随着流场结构的突变,且该突变和总压恢复系数的突然增加是同步的,这种同步性对应的来流马赫数就是进气道的起动马赫数。对于RBCC侧压式进气道,需权衡利弊,选取大小合适的侧向收缩比。

关键词： RBCC 发动机; 侧压式进气道; 进气道起动; 侧向收缩比; 数值模拟

本文引用格式

吴亚可 , 何国强 , 刘佩进 , 刘晓伟 . 侧向收缩比对RBCC侧压式进气道起动性能的影响[J]. 弹箭与制导学报, 2011 , 31(3) : 146 -150 . DOI: 10.15892/j.cnki.djzdxb.2011.03.029

Abstract

Sidewall compression is the primary compression form for rocket based combined cycle (RBCC) engine during low operat ing Mach numbers. It was investigated in this paper that the influence of sidewall contraction ratio on the starting performance of a typical RBCC supersonic sidewall-compression inlet Performance parameters and flow field characters were attained by numerical simulation. The investigation shows that mutation of the flow field occurs during the starting process for the inlet with different sidewall contraction ratio. This mutation is synchronous with the sudden augment of the total pressure recovery. The Mach number corresponding with this synchronicity is the starting Mach number. It is advisable to choose RBCC inlet with moderate sidewall contraction ratio.

Key words： RBCC engine; sidewall-compression inlet; inlet starting; sidewall contraction ratio; numerical simulation

参考文献

[1]	Lazarey V. Structure of reusable hypersonic vehicles: Problems of weight, cost and operating effectiveness, AIAA 1999-4865[R].1999.
[2]	Bulman M, siebenhaar A. The strutjet engine-exploding the myths surrounding high speed airbreathing propulsion,AIAA 1995-2475[R].1995.
[3]	Siebenhaar A, Bulman M. The strutjet engine: The overlooked option for space launch, AIAA 1995-3124[R].1995.
[4]	DeBonis JR, Trefny CJ,Steffen CJ. Inlet development for a rocket based combined cycle, single stage to orbit vehicle using computational fluid dynamics, AIAA 1999-2239[R].1999.
[5]	Quinn J E. Oxidizer selection for the ISTAR program (Liquid Oxygen Versus Hydrogen Peroxide), AIAA 2002-4206[R].2002.
[6]	Kanda T,Tomioka S, Ueda S, et al. Design of sub- scale rocket-ramjet combined cycle engine model.IAC-05-A4.5.03[R].
[7]	Smart M K,Trexler CA,Goldman A L. A combined experimental/computational investigation of a rocket based combined cycle Inlet,AIAA 2001-0671[R]. 2001.
[8]	Bouchez M, Levine V, Davidenko D,et al.Airbreathing space launcher interest of a fully variable geometry propulsion system and corresponding french-russia partner ship,AIAA 2000-3340[R].2000.
[9]	Trexler C A. Performance of an inlet for an integrated scramjet concept[J].Aircraft,1974,11(9):589-591.
[10]	Trexler C A. Inlet performance of the integrated lang ley scramjet module, AIAA 75-1212[R]. 1975.
[11]	刘晓伟,何国强,刘佩进.几何高度对RBCC发动机超声速侧压式进气道起动性能的影响[J].航空动力学报,2010,25(8):1799-1804.
[12]	李宇飞.RBCC引射/亚燃模态热力调节机理研究[D].西安:西北工业大学,2008.
[13]	Van Wie D W,Kwok F T,Walsh R F. Starting characteristics of supersonic inlet, AIAA 1996-2914[R]. 1996.
[14]	Smart M K.Trexler C A. Mach 4 performance of a fixed-geometry hypersonic inlet with rectangular-to-elliptical shape transition, AIAA 2003-0012[R]. 2003.
[15]	Reinartz B. Herrmann C D. Ballmann J,et al. Aerodynamic performance analysis of a hypersonic inlet isolator using computation and experiment[J]. Journal of Propulsion and Power,2003,19(5):868-875.

Options

文章导航

模态框（Modal）标题

摘要

本文引用格式

Abstract

参考文献