高超声速飞行器推进系统建模

肖地波; 陆宇平; 姚克明; 刘燕斌; 陈柏屹

doi:10.13224/j.cnki.jasp.2015.04.022

高超声速飞行器推进系统建模

doi: 10.13224/j.cnki.jasp.2015.04.022

1. 南京航空航天大学航天学院, 南京 210016;
2. 江苏理工学院电气信息工程学院, 江苏常州 213001

基金项目:

常州市科技支撑计划项目(CE20145056)

江苏省自然科学基金(BK20130234,BK20130817)

江苏省普通高校研究生科研创新计划资助项目(CXZZ13_0169)

详细信息

作者简介:
肖地波(1986-),男,四川罗江人,博士生,研究方向为高超声速飞行器建模和控制.

中图分类号: V271.9
计量
- 文章访问数: 1432
- HTML浏览量: 0
- PDF量: 916
- 被引次数: 0
出版历程
- 收稿日期: 2014-07-07
- 刊出日期: 2015-04-28

Modeling of hypersonic vehicles propulsion system

1. College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. College of Electrical and Information Engineering, Jiangsu University of Technology, Changzhou Jiangsu 213001, China

摘要

摘要: 为在高超声速飞行器设计初期快速地获得推力和推力矩,以满足控制相关分析和建模需要.提出一种推进系统建模方法,基于激波/膨胀波相交理论来建模与机身耦合的进气道模型;用有摩擦变截面加热管来描述双模态燃烧室;将内喷管建模成一维变截面摩擦管,采用动量定理估算推力,并通过曲线拟合得到推力的解析表达式.与CFD计算结果相比,该模型计算得到双模态冲压发动机入口气流马赫数和温度误差小于5%,压强误差小于10%;计算得到的推力随马赫数、燃油当量比和迎角的增大而增加,随高度增加而减小,单个状态平均计算时间小于0.5s.计算结果表明:该建模方法满足面向控制建模的效率和精度需求,有助于此类飞行器设计初期的动力学和控制相关的分析和设计.
- 降阶模型 /
- 高超声速飞行器 /
- 推进系统模型 /
- 非量热完全气体 /
- 激波相交
Abstract: In order to quickly obtain the thrust and moment of thrust at the early design stage, and satisfy relevant modeling and analysis control, a model for the propulsion system of hypersonic vehicle was proposed. An inlet model was developed based on the wave interaction method. Moreover, the dual-mode combustor was modeled by an increasing area duct with heat addition and friction, whereas the internal nozzle was modeled by a variable area duct with friction. Accordingly, the thrust was estimated according to the momentum theory, and then analytical expression was obtained by a curve-fitting method. Compared with the result of CFD, the error of Mach number and temperature at the dual mode ramjet engine inlet was less than 5%, and the pressure error was less than 10%; the computed thrust increased as Mach number, stoichiometrically normalized fuel-to-air ratio and angle of attack increased, and decreased as height increased; the time cost of one state point was less than 0.5s averagely. Computation result demonstrates that the proposed modeling approach meets the high efficiency and accuracy required in the control-oriented modeling process, contributing to the analysis and design related to dynamics and control of the hypersonic vehicles.
- reduced-order model /
- hypersonic vehicles /
- propulsion system model /
- calorically imperfect gas /
- shcok wave interaction

HTML

参考文献(18)

[1]	Soloway D I, Ouzts P J, Wolpert D H, et al.The role of guidance, navigation, and control in hypersonic vehicle multidisciplinary design and optimization[R].AIAA-2009-7329, 2009.
[2]	Kelkar A G, Vogel J M, Inger G, et al.Modeling and analysis framework for early stage trade-off studies for scramjet-powered hypersonic vehicles[R].AIAA-2009-7325, 2009.
[3]	王成鹏, 杨永阳, 刘晨, 等.超燃燃烧室流场计算方法比较分析[J].航空动力学报, 2009, 24(5):963-969. WANG Chengpeng, YANG Yongyang, LIU Chen, et al.Comparative analysis of computational methods of supersonic combustor flowfield[J].Journal of Aerospace Power, 2009, 24(5):963-969.(in Chinese)
[4]	Bolender M A, Doman D B.Nonlinear longitudinal dynamical model of an air-breathing hypersonic vehicle[J].Journal of Spacecraft and Rockets, 2007, 44(2):374-387.
[5]	Kelkar A G, Vogel J M, Whitmer C E, et al.Design tool for control-centric modeling, analysis, and trade studies for hypersonic vehicles[R].AIAA-2011-2225, 2011.
[6]	Rodriguez A A, Dickeson J J, Sridharan S, et al.Control-relevant modeling, analysis, and design for scramjet-powered hypersonic vehicles[R].AIAA-2009-7287, 2009.
[7]	Whitmer C E, Kelkar A G, Vogel J M, et al.Control centric parametric trade studies for scramhet-powered hypersonic vehicles[R].AIAA-2010-8283, 2010.
[8]	SU Erlong, LUO Jianjun.Control-oriented 3D modeling of flexible hypersonic vehicles[R].AIAA-2012-5952, 2012.
[9]	张勇, 陆宇平, 刘燕斌, 等.高超声速飞行器控制一体化设计[J].航空动力学报, 2012, 27(12):2724-2732. ZHANG Yong, LU Yuping, LIU Yanbin, et al.Control integrated design for hypersonic vehicle[J].Journal of Aerospace Power, 2012, 27(12):2724-2732.(in Chinese)
[10]	廉筱纯, 吴虎.航空发动机原理[M].西安:西北工业大学出版社, 2005.
[11]	Dalle D J, Fotia M L, Driscoll J F.Reduced order modeling of two dimensional supersonic flows with applications to scramjet inlets[J].Journal of Propulsion and Power, 2010, 26(3):545-555.
[12]	Dalle D J, Torrez S M, Driscoll J F.Rapid analysis of scramjet and linear plug nozzles[J].Journal of Propulsion and Power, 2012, 28(3):545-555.
[13]	Birzer C, Doolan C J.Quasi-one-dimensional model of hydrogen-fueled scramjet combustors[J].Journal of Propulsion and Power, 2009, 25(6):1220-1225.
[14]	黄兴, 陈玉春, 李洁, 等.双模态超燃冲压发动机流量匹配的临界面积法[J].航空动力学报, 2013, 28(6):1305-1312. HUANG Xing, CHEN Yuchun, LI Jie, et al.Critical aera method for mass flow matching of dual-mode scramjet[J].Journal of Aerospace Power, 2013, 28(6):1305-1312.(in Chinese)
[15]	余勇.超燃冲压发动机燃烧室工作过程理论和实验研究[D].长沙:国防科技大学, 2004. YU Yong.Theoretical analysis, experimental study of scramjet combustor operations process[D].Changsha:National University of Defense Technology, 2004.(in Chinese)
[16]	Mcbride B J, Zehe M J, Gordon S.NASA glenn coefficients for calculating thermo-dynamic properties of individual species[R].NASA TP 2002-21156, 2002.
[17]	Hazelton D M, Bowersox R D W.Skin friction correlations for high enthalpy flows[R].AIAA 98-1636, 1998.
[18]	Orth R C, Billig F S, Grenleski S E.Measurement techniques for supersonic combustion testing[R].NASA 19740045550, 1974.