固体火箭冲压发动机燃气流量调节最优前馈控制

赵泽敏; 陈雄; 周长省; 李宏文

doi:10.15892/j.cnki.djzdxb.2014.03.008

弹箭与制导学报 >

2014 , Vol. 34 >Issue 3: 109 - 112

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2014.03.008

火箭技术

固体火箭冲压发动机燃气流量调节最优前馈控制

赵泽敏 ,
陈雄 ,
周长省 ,
李宏文

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¹ 南京理工大学机械工程学院,南京 210094
² 晋西工业集团有限责任公司,太原 030027

赵泽敏(1987-),男,山西晋城人,硕士研究生,研究方向:宇航推进理论与工程。

收稿日期: 2013-08-23

网络出版日期: 2025-05-30

基金资助

总装备部预研基金

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Research on Optimum Feedforward Control of Gas Flow Regulation of Solid Rocket Ramjet

ZHAO Zemin ,
CHEN Xiong ,
ZHOU Changsheng ,
LI Hongwen

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¹ School of Mechanical Engineering, Nanjing University of Science & Technology, Nanjing 210094, China
² Jinxi Industries Group Co. Ltd, Taiyuan 030027, China

Received date: 2013-08-23

Online published: 2025-05-30

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摘要

固体火箭冲压发动机燃气流量调节过程中存在负调节,对正常工作有很大影响。文中根据燃气流量调节小扰动数学模型分析了负调量与调节时间之间存在的矛盾,给出了负调受约束下最小调节时间。然后根据最优响应设计了可实现的最优前馈控制器,建立以内弹道方法为基础的仿真模型。结果表明,该前馈控制方法能够在燃气流量难以测量形成有效反馈控制的实际情况中,实现不同负调约束的最优调节。发动机设计时应根据综合状态折中选择负调量和调节时间。

关键词： 固体火箭冲压发动机; 燃气流量调节; 负调约束; 前馈控制

本文引用格式

赵泽敏 , 陈雄 , 周长省 , 李宏文 . 固体火箭冲压发动机燃气流量调节最优前馈控制[J]. 弹箭与制导学报, 2014 , 34(3) : 109 -112 . DOI: 10.15892/j.cnki.djzdxb.2014.03.008

Abstract

Negative regulation occurring to gas flow adjustment of solid rocket ramjet adversely affects normal operation. In this paper, the inverse relationship between the undershoot and time set was analyzed according to the gas regulating small perturbation dynamic model and the minimum settling time was given subject to undershoot constraint. Then, the optimum feedforward controller was synthesized based on ideal response, the simulation model was established according to mathematic model of interior ballistic. Numerical simulation results illustrate the optimum feedforward controller signals achieve minimize the settling time subject to undershoot constraint.

Key words： solid rocket ramjet; gas flow regulation; negative regulation constraint; optimum feedforward control

参考文献

[1]	周建军固体火箭冲压发动机燃气流量调节技术与实验研究[J]. 弹箭与制导学报, 2005, 25(4): 558-560.
[2]	V Sosounov Research and development of ramjets/ram-rockets. Part 1: integral solid propellant ramrockets,AGARD-94-29291[R].1994.
[3]	HL Besser History of ducted rocket development at Bay-ern-Chemie, AIΑΑ 2008-5261[R].2008.
[4]	Wilkerson FS, Lucac JT Variable flow solid propellant gas generator for missile control systems, AIΑΑ 81 – 1464[R].1981.
[5]	牛文玉, 于达仁, 鲍文, 等. 燃气流量可控的固体火箭冲压发动机燃气发生器动态特性[J]. 固体火箭技术, 2008, 31(2): 145-148.
[6]	牛文玉燃气流量可调的固体火箭冲压发动机控制方法研究[D].哈尔滨:哈尔滨工业大学,2009.
[7]	Jiesheng Wang, Yong Zhang, Wei Wang Optimal design of PI/PD controller for non-minimum phase system[J]. Transactions of the Institute of Measurement and Control, 2006, 28 (1):27-35
[8]	H Elliott Direct adaptive pole placement with application to non-minimum phase systems[J]. IEEE Trans Automat Control, 1982, 27(3):720-722
[9]	G Bartolini, A Ferrara Variable structure approach to the pole assignment control of non-minimum phase systems[J]. Internat. J. Control, 1993, 57(5): 1063-1078
[10]	Ma L K, Xia Z X, Hu JX, et al. Investigation on the an-ti-regulation characteristic of variable flow ducted rocket[J]. Proceedings of the Institution of Mechanical Engi-neers, Part G: Journal of Aerospace Engineering, 2013, 227(9):1488-1497
[11]	Lau K, Middleton R H, Braslavsky J H Undershoot and settling time tradeoffs for nonminimum phase systems[J]. Automatic Control, IEEE Transactions on, 2003, 48(8): 1389-1393

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