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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2023, Vol. 44 ›› Issue (7): 326909-326909.doi: 10.7527/S1000-6893.2022.26909

• Electronics and Electrical Engineering and Control • Previous Articles     Next Articles

Flying range control guidance for varying⁃speed missiles based on optimal error dynamics

Yuanhe LIU1,2, Kebo LI1,2(), Shaoming HE3, Yangang LIANG1,2   

  1. 1.College of Aerospace Science and Engineering,National University of Defense Technology,Changsha  410072,China
    2.Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions,Changsha  410072,China
    3.School of Aerospace Engineering,Beijing Institute of Technology,Beijing  100081,China
  • Received:2022-01-07 Revised:2022-02-21 Accepted:2022-06-13 Online:2023-04-15 Published:2022-06-24
  • Contact: Kebo LI E-mail:likeboreal@nudt.edu.cn
  • Supported by:
    National Natural Science Foundation of China(12002370)

Abstract:

To solve the problem of performance degradation of current impact time control guidance based on constant speed assumption in practical application, a feasible flying range control guidance scheme with time-varying speed is proposed in this paper. The relative motion equation of the missile against the stationary target in the arc-length domain is derived based on the classical differential geometric curve principle, which reduces the influence of time-varying speed on the relative motion of missile and target. Furthermore, the exact solution for the range-to-go guided by pure proportional navigation is derived using the Gaussian hypergeometric function. On this basis, a flying range control guidance law is designed with the optimal error dynamics method, and the effectiveness of the proposed guidance is verified by simulation.

Key words: classical differential geometric curve theory, varying-speed missile, Gaussian hypergeometric function, optimal error dynamics, flying range control

CLC Number: