Adaptive Fuzzy Sliding-Mode Control for Non-minimum Phase Overload System of Missile

  • Yongping Bao
  • Wenchao Du
  • Daquan Tang
  • Xiuzhen Yang
  • Jinyong Yu
Part of the Lecture Notes in Control and Information Sciences book series (LNCIS, volume 344)


An adaptive fuzzy logic system is incorporated with the Varibale Structure Control (VSC) system for the purpose of improving the performance of the control system. A sliding surface with an additional tunable parameter is defined as a new output based on the idea of output redefinition, as a result the overload system of missile with the characteristic of non-minimum phase can be transformed into minimum-phase system by tuning the parameters of the sliding surface, and a sliding-mode controller can be designed. For the existence of uncertainty of the parameters, a fuzzy logic system is used to approximate it, thus the chattering effects can be alleviated. Finally, the simulation results have been given to show the effectiveness of the proposed control scheme.


Fuzzy Logic System Propose Control Scheme Fuzzy Slide Mode Controller Nonminimum Phase Overload System 
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  1. 1.
    Kravaris, C., Wright, R.A.: Nonminimum-phase Compensation for Nonlinear Processes. AIChE. J. 38 (1992) 26–40MathSciNetCrossRefGoogle Scholar
  2. 2.
    Yang, H., Hariharn, K., Marcelo, H.: Tip-trajectory Tracking Control of Single-link Flexible Robots via Output Redefinition. Proceedings of International Conference on Robotics and Automation Detroit, Michigan. (1999) 1102–1107Google Scholar
  3. 3.
    Zinober, A., Owens, D. (Eds.): Nonlinear and Adaptive Control. LNCIS 281, Springer-Verlag Berlin Heidelberg (2003) 239–248zbMATHGoogle Scholar
  4. 4.
    Iiya, A.S., Yuri, B.S.: Aircraft Nonminimum Phase Control in Dynamic Sliding Manifolds. Journal of guidance, control and dynamics, 24(3) (2001) 566–572CrossRefGoogle Scholar
  5. 5.
    Chwa, D.K., Choi, J.Y.: New Parametric Affine Modeling and Control for Skid-to-Turn Missiles. IEEE Transactions on Control Systems Technology, 9(2) (2001) 335–347CrossRefGoogle Scholar
  6. 6.
    Lee, J.I., Ha, I.J.: Autopilot Design for Highly Maneuvering STT Missiles via Singular Perturbation-Like Technique. IEEE Transactions on Control System Technology, 7(5) (1999) 527–541CrossRefGoogle Scholar
  7. 7.
    Ryu, J.H., Park, C.S., Tank, M.J.: Plant Inversion Control of Tail-Controlled Missiles. AIAA-97. 3766 (1997) 1691–1696Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2006

Authors and Affiliations

  • Yongping Bao
    • 1
  • Wenchao Du
    • 2
    • 3
  • Daquan Tang
    • 4
  • Xiuzhen Yang
    • 5
  • Jinyong Yu
    • 5
  1. 1.School of Mathematics and InformationLu Dong UniversityYantaiP.R. China
  2. 2.Graduate Students’ BrigadeNaval Aeronautical Engineering InstituteYantaiP.R. China
  3. 3.Special Missiles Representatives Office in Beijing of Military Representatives Bureau of NED in TianjinBeijingP.R. China
  4. 4.School of Automation Science and Electrical EngineeringBeijing University of Aeronautics and AstronauticsBeijingP.R. China
  5. 5.Department of Automatic Control EngineeringNaval Aeronautical Engineering InstituteYantaiP.R. China

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