[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 6: 1106 - 1112

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.06.019

Academic article

Research on the Control Technique for Relaxed Stable Stability Canard Configuration Missile

  • ZHANG Weijie ,
  • MIAO Haochun ,
  • GUO Chen
Expand
  • Xi’an Modern Control Technology Research Institute,Xi’an 710065,Shaanxi,China

Received date: 2024-11-02

  Online published: 2026-01-24

Fold

Abstract

Aiming at the problem of control the relaxed stable stability canard missile.First of all,the longitudinal plane motion equations for the missile were established according to the Dynamic model,and the missile dynamic coefficients and missile body transfer function of the missile were obtained using the small perturbation linearization method and Laplace transform method.Then,the linear control method of pseudo-angle of attack three-loop overload autopilot and the nonlinear control method of Backstepping were respectively used to design the relaxed stable stability missile control system.Simulation is carried out with overload step instruction input,the design principles and simulation results of the two methods were both compared.The results show that the linear control method of the pseudo-angle of attack three-loop overload autopilot and the nonlinear control method of Backstepping can both control the relaxed stable stability canard missile.The rudder deflection of angle needs to be deflected first in the negative direction,and then in the positive direction until it is finally stabilized at a certain rudder deflection of angle.It can be seen that the nonlinear control method is simple in design,requires fewer control parameters,and has faster response speed,smaller control demand,which has a good effect and significance for improving the performance of control system.

Key words： canard missile; control technique for relaxed stable stability missile; three-loop autopilot; Backstepping

Cite this article

ZHANG Weijie , MIAO Haochun , GUO Chen . Research on the Control Technique for Relaxed Stable Stability Canard Configuration Missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(6) : 1106 -1112 . DOI: 10.15892/j.cnki.djzdxb.2025.06.019

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
林德福. 战术导弹自动驾驶仪设计与制导律分析[M]. 北京: 北京理工大学出版社, 2012.

LIN D F. Autopilot Design And Guidance Law Analysis For Tactical Missiles[M]. Beijing: Beijing Institute of Technology Press, 2012.

[2]
Sankar R B, Tiwari P K, Bandyopadhyay B, et al. Higher Order Sliding Mode-Based Guidance for Controlling Stactically Ustable Missiles[J]. Transaction of Indian National Academy of Engineer,2021:1-13.

[3]
郭正玉, 梁晓庚. 静不稳定导弹控制系统设计研究[J]. 计算机仿真, 2012, 29(08):97-100.

GUO Z Y, LIANG X G. Simplified Approach for Relaxed Stable Stability Missile Autopilot Design[J]. Computer Simulation, 2012, 29(08):97-100.

[4]
刘明使, 杨壮志. 两类临界静不稳定姿态控制系统设计[J]. 国防科技大学学报, 1996(04):31-35.

LIU M J, YANG Z Z. Two Designs of Critical statically Unstable Attitude Control System[J]. Journal of National University of Defense Technology, 1996(04):31-35.

[5]
万夕干, 余祖铸. 防空导弹控制系统分析[J]. 上海航天, 2009, 26(02):22-26.

WAN X G, YU Z Z. The Analysis on Control System of Air Defense Missile[J]. Aerospace Shanghai, 2009, 26(02):22-26.

[6]
王娟利, 祁载康. 三回路自动驾驶仪特点分析[J]. 北京理工大学学报, 2006(03):239-243.

WANG J L, QI Z K, Analysis of a Three-Loop Autopilot[J]. Transactions of Beijing Institute of Technology, 2006(03):239-243.

[7]
郭正玉, 梁晓庚, 张亚涛. 静不稳定导弹稳定回路简便设计法[J]. 弹箭与制导学报, 2012, 32(03):73-75.

GUO Z Y, LIANG X G. A Simplified Approach for Designing a Stable Loop for Missile with Relaxed Static Stability[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2012, 32(03):73-75.

[8]
孔维宇. 考虑导弹静不稳定性的姿态控制研究[D]. 哈尔滨: 哈尔滨工程大学, 2019.

KONG W Y. Research on Attitude Control Considering the Static Instability of Missile[D].Harbin: Harbin Engineering University, 2019.

[9]
Mracek C, Ridgely D. Missile Longitudinal Autopilots: Connections Between Optimal Control and Classical Topologies[C]// AIAA Guidance, Navigation,and Control Conference and Exhibit,2006:485-488.

[10]
Mracek C, Ridgely D. Missile Longitudinal Autopilots: Comparison of Multiple Three Loop Topologies[C]// AIAA Guidance,Navigation,and Control Conference and Exhibit, 2005.

[11]
Ho W K, Xu W. PID tuning for unstable processes based on gain and phase-margin specifications[J]. IEE Proceedings -Control Theory and Applications, 1998, 145(5):392-396.

DOI

[12]
Lee Y, Lee J, Park S. PID controller tuning for integrating and unstable processes with time delay[J]. Chemical Engineering Science, 2000, 55(17):3481-3493.

DOI

[13]
Sree R P, Srinivas M N, Chidambaram M. A simple method of tuning PID controllers for stable and unstable FOPTD systems[J]. Computers & Chemical Engineering, 2004, 28(11):2201-2218.

DOI

[14]
Paraskevopoulos P N, Pasgianos G D, Arvanitis K G. New tuning and identification methods for unstable first order plus dead-time processes based on pseudo derivative feedback control[J]. IEEE Transactions on Control Systems Technology, 2004, 12(3):455-464.

DOI

[15]
李世雄, 张友安, 尹逊青. 基于simulink参数寻优的静不稳定导弹三回路过载控制系统设计[J]. 海军航空工程学院学报, 2010, 25(02):158-162.

LI S X, ZHANG Y A, YIN Xun Qing,Control System Design of Static Unstable Missile Using Three Loop Acceleration Based on Simulink Parameters Optimizing[J]. Journal of Naval Aeronautical and Astronautical University, 2010, 25(02):158-162.

[16]
Krstic M, Kokotovic P V, Kanellakopoulos I. Nonlinear and Adaptive Control Design[M]// Nonlinear and Adaptive Control. Springer Berlin Heidelberg, 2003,(5):4475-4480.

[17]
王双双. 静不稳定无人机着舰控制关键技术研究[D]. 南京: 南京航空航天大学, 2021.

WANG S S. Research on Key Technologies of Carrier Landing Control for Statically Unstable UAV[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2021.

[18]
路遥, 董朝阳, 王青. 高超声速飞行器自适应反步控制器设计[J]. 航空学报, 2015, 36(03):970-978.

LU Y, DONG C Y, WANG Q. Adaptive backstepping controller design for hypersonic vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(03):970-978.

[19]
Xu B, Huang X, Wang D, et al. Dynamic Surface Control of Constrained Hypersonic Flight Models with Parameter Estimation and Actuator Compensation[J]. Asian Journal of Control, 2014, 16(1):162-174.

DOI

[20]
Yao C, Wang X. Adaptive backstepping sliding model control of hypersonic vehicle based on CMAC and dynamic surface[J]. International Journal of Computer Applications in Technology, 2013, 46(3):203-209.

DOI

[21]
张强, 吴庆宪, 姜长生, 王玉惠. 基于Backstepping的近空间飞行器鲁棒自适应姿态控制[J]. 南京航空航天大学学报, 2013, 45(05):590-598.

ZHANG Q, WU Q X, JIANG C S, WANG Y H, Robust Adaptive Control for Attitude System of Near Space Vehicle via Backstepping Method[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2013, 45(05):590-598.

[22]
钱杏芳, 林瑞雄, 赵亚男. 导弹飞行力学[M]. 北京: 北京理工大学出版社,2008:52-56.

QIAN X F, LIN R X, ZHAO Y N, Missile aviation mechanics[M]. Beijing,Beijing Institute of Technology Press,2008:52-56.

[23]
王辉, 林德福, 祁载康, 导弹伪攻角反馈三回路自动驾驶仪设计分析[J]. 系统工程与电子技术, 2012(01):129-135.

WANG H, LIN D F, QI Z K, Design and anlaysis of missile three-loop autopilot with pseudo-angle of attack feedback[J]. Systems Engineering and Electronics, 2012(01):129-135.

Options
Outlines

/

〈 〉

[an error occurred while processing this directive]