| Citation: | ZHANG Kai, YANG Suochang, ZHANG Kuanqiao, et al. Novel guidance law accounting for dynamics of missile autopilot[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(8): 1693-1704. doi: 10.13700/j.bh.1001-5965.2016.0630(in Chinese)
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Interception of air targets requires zero miss-distance and impact angle constraint to improve the missile guidance performance. First, the acceleration of the target was estimated by extended disturbance observer which also considered the noise interference. Second, a nonsingular terminal sliding mode surface was improved, which considered autopilot ideally. Third, a sliding-mode guidance law was designed based on the terminal sliding mode control theory and the theory of finite time convergence. Finally, considering the second-order dynamic characteristics of autopilot, the novel guidance law was developed combining both sliding-mode guidance law and dynamic surface control method. In simulation experiments, both maneuvering targets and constant velocity targets were intercepted with different impact angle. A large number of simulation results demonstrate that the proposed guidance law canguarantee that the missile hits the target and at the same time achieves a desired angle of impact, which performs well.
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