Journal of Astronautics ›› 2021, Vol. 42 ›› Issue (9): 1108-1118.doi: 10.3873/j.issn.1000-1328.2021.09.006

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Integrated Guidance and Control Design for Spiral Maneuvering Missile with Multiple Constraints

HUANG Lu yu, QU Xin, FAN Yong hua, WANG Jun bo   

  1. 1. Beijing Institute of Electronic System Engineering, Beijing 100854, China;2. School of Astronautics, Northwestern Polytechnical University, Xi ’an 710072, China
  • Received:2020-08-18 Revised:2020-10-26 Online:2021-09-15 Published:2021-09-15

Abstract: Based on active disturbance rejection control (ADRC) and backstepping sliding mode control (SMC), an integrated design method of spiral maneuver guidance and control for missile with limited angle of attack and limited angle of landing is proposed. Firstly, according to the typical spiral maneuver penetration trajectory, and considering the constraint of specified landing angle in the longitudinal plane, the integrated mathematical model of guidance and control is derived in different channels. Then, the backstepping sliding mode control is used to guide the integrated control algorithm design, and the compensator is designed to modify the control variables to realize the constraint on the angle of attack. In addition, the disturbance observer is used to estimate and compensate the bounded uncertainty and unknown disturbance of the system to improve the robustness of the system. Finally, the stability of the system is proved by the Lyapunov theory. The simulation results show that the proposed method has strong robustness, and can ensure that the missile attacks the target with high precision and large landing angle under the condition of satisfying the constraint of attack angle in the spiral maneuver trajectory.

Key words: Missile, Integrated guidance and control, Spiral maneuver, Backstepping sliding mode control, Active disturbance rejection control

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