固体火箭冲压发动机流量可调燃气发生器控制算法

周景亮; 陈雄; 柴金宝

doi:10.13224/j.cnki.jasp.2020.05.022

固体火箭冲压发动机流量可调燃气发生器控制算法

doi: 10.13224/j.cnki.jasp.2020.05.022

基金项目: 总装备部预先研究项目(404040301)；国家自然科学基金(51606098)；江苏省自然科学基金(BK20140772)

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- 文章访问数: 350
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出版历程
- 收稿日期: 2019-11-17
- 刊出日期: 2020-05-28

Control algorithms for adjustable flow gas generator of ducted ramjet

1.
School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China
2.
General Design Institute of Hubei Aerospace Technology Academy, China Aerospace Science and Industry Corporation Limited,Wuhan 430040,China

摘要

摘要: 固体火箭冲压发动机流量调节系统具有很强的时变性和非线性,在调节的初期存在流量负调现象,且推进剂不完全燃烧产生的颗粒容易附着于喉道,这些因素都将对调节性能产生消极影响。为处理上述问题,设计线性自抗扰控制器(LADRC)。仿真试验表明,所设计的LADRC对比于比例-积分-微分控制器(PID)具有更好的响应速度、精度、流量负调抑制能力以及抗干扰能力,在低压力和高压力两种工况下的响应时间均不超过1.5 s,超调量在1.5%以内;流量负调减小了3~4倍;对干扰的反应时间在0.4 s左右,干扰的偏离值仅为0.25 MPa,显著提高了燃气发生器的工作性能。
- 固体火箭冲压发动机 /
- 流量可调燃气发生器 /
- 线性自抗扰控制器(LADRC)
Abstract: The gas generator system with adjustable flow of ducted ramjet has strong time-varying and non-linearity. Anti-regulation of gas flow exists in the initial stage of regulation. And the in the gas generator system with adjustable flow of ducted ramjet has strong time-varying and non-linearity attributes. Anti-regulation of gas flow exists in the initial stage of regulation. And the incomplete combustion of propellant is easily adhered to throat. These factors will have a negative impact on the regulation performance. In order to solve this problem, the linear active disturbance rejection controller (LADRC) was designed. Simulation results showed that: compared with the proportion-integration-differentiation (PID) controller, the LADRC had better response speed, accuracy, flow anti-regulation suppression ability and anti-interference ability. The response time under low and high pressure conditions was less than 1.5 s, the overshoot was less than 1.5%, and the flow anti-regulation was reduced by 3-4 times. The reaction time to interference was about 0.4 s, and the deviation value of interference was only 0.25 MPa, thus significantly improving the performance of gas generator.
- ducted ramjet /
- adjustable flow gas generator /
- linear active disturbance rejection controller（LADRC）

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参考文献(28)

[1]	FRY R S.A century of ramjet propulsion technology evolution［J］.Journal of Propulsion and Power,2004,20(1):27-58.
[2]	曹军伟,何国强,王希亮,等.空空导弹固体火箭冲压发动机设计参数优化［J］.航空动力学报,2015,30(8):2018-2024. CAO Junwei,HE Guoqiang,WANG Xiliang,et al.Parameter optimization design of air-ducted rocket for airborne missile［J］.Journal of Aerospace Power,2015,30(8):2018-2024.(in Chinese)
[3]	TOKUNAGA H,KOORI K,IKEGAMI Y,et al.Development of wide-range dupersonic intake for variable flow ducted rocket engine［R］.AIAA-2009-5223,2009.
[4]	何勇攀,陈玉春,于守志,等.固体火箭冲压发动机燃气发生器动态特性影响分析［J］.航空动力学报,2017,32(1):228-232. HE Yongpan,CHEN Yuchun,YU Shouzhi,et al.Analysis on influence of dynamic characteristics of gas generator in solid propellant ducted rockets［J］.Journal of Aerospace Power,2017,32(1):228-232.(in Chinese)
[5]	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. ZHOU Jianjun.Gas flow control technique of rocket ram-jet［J］.Journal of Projectiles,Rockets,Missiles and Guid-ance,2005,25(4):558-560.(in Chinese)
[6]	MAYER A E H J,HALSWIJK W H C,KOMDUUR H J.A modular ducted rocket missile model for threat and performance assessment［R］.AIAA 2005-6013,2005.
[7]	BESSER H L,WEINREICH H L,KURTH G.Fit for mission-design tailoring aspects of throttleable ducted rocket propulsion systems［R］.AIAA 2008-5262,2008.
[8]	李博,于新宇,谢侃,等.固体火箭发动机流体喉部推力矢量特性［J］.航空动力学报,2016,31(12):2996-3003. LI Bo,YU Xinyu,XIE Kan,et al.Thrust vectoring fea-tures about fluidic throat for solid rocket motor［J］.Journal of Aerospace Power,2016,31(12):2996-3003.(in Chinese)
[9]	何坤.锥阀式燃气流量调节系统设计与实验研究［D］.南京:南京理工大学,2017. HE Kun.Design and experimental study of cone valve type gas flow regulating system［D］.Nanjing:Nanjing University of Science and Technology,2017.(in Chinese)
[10]	何坤,陈雄,郑健,等.模糊PI控制算法在燃气发生器上的应用［J］.推进技术,2017,38(8):1878-1884. HE Kun,CHEN Xiong,ZHENG Jian,et al.Fuzzy PI control algorithm for gas generator［J］.Journal of Propulsion Technology,2017,38(8):1878-1884.(in Chinese)
[11]	聂聆聪,刘志明,刘源祥.流量可调燃气发生器压力闭环模糊控制算法［J］.推进技术,2013,34(4):551-556. NIE Lingcong,LIU Zhiming,LIU Yuanxiang.Pressure close loop fuzzy control method of a flow adjustable gas generator［J］.Journal of Propulsion Technology,2013,34(4):551-556.(in Chinese)
[12]	刘源翔,姚晓先,聂聆聪,等.一种流量可调燃气发生器压强控制算法的研究［J］.固体火箭技术,2014,37(1):43-47. LIU Yuanxiang,YAO Xiaoxian,NIE Lingcong,et al.Research on pressure control algorithm of flow adjustable gas generatol［J］.Journal of Solid Rocket Technology,2014,37(1):43-47.(in Chinese)
[13]	赵泽敏.固体火箭冲压发动机燃气流量调节控制系统研究［D］.南京:南京理工大学,2014. ZHAO Zemin.Research on gas flow control system of solid rocket ramjet［D］.Nanjing:Nanjing University of Science and Technology,2014.(in Chinese)
[14]	韩京清.自抗扰控制技术:估计补偿不确定因素的控制技术［M］.北京:国防工业出版社,2008.
[15]	朱斌.自抗扰控制入门［M］.北京:北京航空航天大学出版社,2017.
[16]	武晓松,陈军,王栋.固体火箭发动机原理［M］.北京:兵器工业出版社,2010:236-239.
[17]	马立坤.燃气流量可调固体火箭冲压发动机动态响应过程研究［D］.长沙:国防科技大学,2011. MA Likun.Investigation of the response process of variable flow ducted rocket［D］.Changsha:National University of Defense Technology,2011.(in Chinese)
[18]	钱秋朦,但志宏,张松,等.航空发动机过渡态试验进气压力线性自抗扰控制方法［J］.航空动力学报,2019,34(10):2271-2279. QIAN Qiumeng,DAN Zhihong,ZHANG Song,et al.Linear active disturbance rejection control method for intake pressure control in aero-engine transient test［J］.Journal of Aerospace Power,2019,34(10):2271-2279.(in Chinese)
[19]	ALONGE F,CIRRINCIONE M,D’IPPOLITO F,et al.Robust active disturbance rejection control of induction motor systems based on additional sliding-mode component［J］.IEEE Transactions on Industrial Electronics,2017,64(7):5608-5621.
[20]	TAN W,FU C.Linear active disturbance-rejection control:analysis and turning via IMC［J］.IEEE Transactions on Industrial Electronics,2016,63(4):2350-2359.
[21]	张海波,孙健国,孙立国.一种涡轴发动机转速抗扰控制器设计及应用［J］.航空动力学报,2010,25(4):943-950. ZHANG Haibo,SUN Jianguo,SUO Liguo.Design and application of a disturbance rejection rotor speed control method for turbo-shaft engines［J］.Journal of Aerospace Power,2010,25(4):943-950.(in Chinese)
[22]	徐秋坪,常思江,王中原.自适应网格跟踪微分器设计［J］系统工程与电子技术,2018,40(6):1212-1220. XU Qiuping,CHANG Sijiang,WANG Zhongyuan.Design of adaptive mesh tracking differentiator［J］.Systems Engineering and Electronics,2018,40(6):1212-1220.(in Chinese)
[23]	WEI Y H,HU Y S,SONG L,et al.Tracking differentiator based fractional order model reference adaptive control the 1<α<2 case［C］∥Proceedings of the 53rd IEEE Annual Conference on Design and Control.Los Angeles,US:IEEE,2014:6902-6907.
[24]	WEI J X,GAO Z.Design and analysis on fractional-order tracking differentiator［C］∥Proceedings of the 27th IEEE Chinese Control and Decision Conference.Qingdao:IEEE,2015:6128-6132.
[25]	王建华,刘鲁华,王鹏,等.带三维落角约束的寻的导弹制导与姿控系统设计［J］.国防科技大学学报,2017,39(1):30-39. WANG Jianhua,LIU Luhua,WANG Peng,et al.Guidance and control system design for homing missiles with three dimensional impact angle constraints［J］.Journal of National University of Defense Technology,2017,39(1):30-39.(in Chinese)
[26]	GUO B Z,ZHAO Z L.On the convergence of extended state observer for nonlinear systems with experimentation［J］.System and Control Letters,2011,60(6):420-430.
[27]	孙佃升,章跃进.线性扩张状态观测器的改进及观测精度分析［J］.国防科技大学学报,2017,39(6):111-117. SUN Diansheng,ZHANG Yuejin.Improvement and observation accuracy analysis of linear extended state observer［J］.Journal of National University of Defense Technology,2017,39(6):111-117.(in Chinese)
[28]	GAO Z Q.Scaling and bandwidth-parameterization based controller tuning［C］∥Proceedings of the 2003 American Control Conference.Denver,US:IEEE,2003:4989-4996.