Journal of Astronautics ›› 2017, Vol. 38 ›› Issue (10): 1068-1078.doi: 10.3873/j.issn.1000-1328.2017.10.007

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Integrated Guidance and Control Design for Reentry Warhead Based on ADRC

ZHAO Kun, CAO Deng qing, HUANG Wen hu   

  1. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China
  • Received:2017-06-15 Revised:2017-08-24 Online:2017-10-15 Published:2017-10-25


An integrated guidance and control system is designed based on the active disturbance rejection control (ADRC) method, which is aimed at the problems of strong coupling, fast time-varying, and uncertainty caused by aerodynamic parameter perturbation during the reentry of a warhead. Firstly, the integrated dynamics system of guidance and control with cascading form is established, which includes the parameter uncertainties and external random disturbances as well as channel coupling factors. Then, the controller of the system is hierarchically designed according to the ADRC method of the cascade system, and the controllers of each layer are associated with each other to form an integrated control system. The extended state observer (ESO) embedded in ADRC is employed to realize the real-time observation of the integrated uncertainties in each channel of the subsystem, and the results are used to compensate dynamically in the error feedback control quantity to achieve the decoupling control among the channels. The simulation results indicate that the designed integrated control system can adapt to the guidance requirements of various complex flight environments, and the control system has good dynamic characteristics and strong robustness.

Key words: Reentry warhead, Integrated guidance and control, Active disturbance rejection control (ADRC), Extended state observer (ESO), BTT vehicle, Uncertainty

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