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ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2023 , Vol. 44 >Issue 7: 326909 - 326909

DOI: https://doi.org/10.7527/S1000-6893.2022.26909

Electronics and Electrical Engineering and Control

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

  • Yuanhe LIU ,
  • Kebo LI ,
  • Shaoming HE ,
  • Yangang LIANG
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  • 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
E-mail： likeboreal@nudt.edu.cn

Received date: 2022-01-07

  Revised date: 2022-02-21

  Accepted date: 2022-06-13

  Online published: 2022-06-24

Supported by

National Natural Science Foundation of China(12002370)

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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

Cite this article

Yuanhe LIU , Kebo LI , Shaoming HE , Yangang LIANG . Flying range control guidance for varying⁃speed missiles based on optimal error dynamics[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(7) : 326909 -326909 . DOI: 10.7527/S1000-6893.2022.26909

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Total visits: 6658907 Today visits: 1341