DOI QR코드

DOI QR Code

Time-Delay Control for Integrated Missile Guidance and Control

  • Park, Bong-Gyun (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Kim, Tae-Hun (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology) ;
  • Tahk, Min-Jea (Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology)
  • 투고 : 2011.04.30
  • 심사 : 2011.09.06
  • 발행 : 2011.09.30

초록

In this paper, integrated missile guidance and control systems using time-delay control (TDC) are developed. The next generation missile requires that an interceptor hits the target, maneuvering with small miss-distances, and has lower weight to reduce costs. This is possible if the synergism existing between the guidance and control subsystems is exploited by the integrated controller. The TDC law is a robust control technique for nonlinear systems, and it has a very simple structure. The feature of TDC is to directly estimate the unknown dynamics and the unexpected disturbance using one-step time-delay. To investigate the performance of the integrated controller, numerical simulations are performed as the maneuver of the target. The results show that the integrated guidance and control system has a good performance.

키워드

참고문헌

  1. Chang, P. H. and Lee, J. W. (1994). An observer design for time-delay control and its application to DC servo motor. Control Engineering Practice, 2, 263-270. https://doi.org/10.1016/0967-0661(94)90206-2
  2. Hsia, T. C. and Gao, L. S. (1990). Robot manipulator control using decentralized linear time-invariant time-delayed joint controllers. Proceedings of the IEEE International Conference on Robotics and Automation, Cincinnati, OH. pp. 2070-2075.
  3. Koren, A., Idan, M., and Golan, O. M. (2008). Integrated sliding mode guidance and control for a missile with on-off actuators. Journal of Guidance, Control, and Dynamics, 31, 204-214. https://doi.org/10.2514/1.31328
  4. Menon, P. K. and Ohlmeyer, E. J. (2001). Nonlinear integrated guidance-control laws for homing missiles. AIAA Guidance, Navigation, and Control Conference, Montreal, Canada.
  5. Prasanth Kumar, R., Dasgupta, A., and Kumar, C. S. (2007). Robust trajectory control of underwater vehicles using time delay control law. Ocean Engineering, 34, 842-849. https://doi.org/10.1016/j.oceaneng.2006.04.003
  6. Shima, T., Idan, M., and Golan, O. M. (2006). Sliding-mode control for integrated missile autopilot guidance. Journal of Guidance, Control, and Dynamics, 29, 250-260. https://doi.org/10.2514/1.14951
  7. Shtessel, Y. B. and Tournes, C. H. (2009). Integrated higher-order sliding mode guidance and autopilot for dual-control missiles. Journal of Guidance, Control, and Dynamics, 32, 79-94. https://doi.org/10.2514/1.36961
  8. Vaddi, S. S., Menon, P. K., and Ohlmeyer, E. J. (2009). Numerical state-dependent riccati equation approach for missile integrated guidance control. Journal of Guidance, Control, and Dynamics, 32, 699-703. https://doi.org/10.2514/1.34291
  9. Zarchan, P. (1997). Tactical and Atrategic Missile Guidance. Progress in Astronautics and Aeronautics Vol. 176. 3rd ed. Reston: American Institute of Aeronautics and Astronautics.

피인용 문헌

  1. Single Versus Two-Loop Full-State Multi-Input Missile Guidance vol.38, pp.5, 2015, https://doi.org/10.2514/1.G000171
  2. Single Versus Two-Loop Full-State Guidance and Control vol.40, pp.8, 2017, https://doi.org/10.2514/1.G002722
  3. Linear Quadratic Integrated Versus Separated Autopilot-Guidance Design vol.36, pp.6, 2013, https://doi.org/10.2514/1.61363
  4. Continuous-Time Predictive Control-Based Integrated Guidance and Control vol.40, pp.7, 2017, https://doi.org/10.2514/1.G002661
  5. Full-State Autopilot-Guidance Design Under a Linear Quadratic Differential Game Formulation vol.47, pp.3, 2014, https://doi.org/10.3182/20140824-6-ZA-1003.01240
  6. Adaptive Integrated Guidance and Control Design for a Missile With Input Constraints vol.46, pp.20, 2013, https://doi.org/10.3182/20130902-3-CN-3020.00114
  7. Integrated versus two-loop guidance-autopilot for a dual control missile with high-order aerodynamic model vol.230, pp.1, 2016, https://doi.org/10.1177/0954410015586862
  8. Improved line of sight robot tracking toward a moving target vol.6, pp.3, 2018, https://doi.org/10.1080/21642583.2018.1547886