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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2018, Vol. 39 ›› Issue (11): 322215-322225.doi: 10.7527/S1000-6893.2018.22215

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

Time and angle control guidance law based on optimal error dynamics

LI Bin1,2, LIN Defu1,2, HE Shaoming1,2, BAI Bing3   

  1. 1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
    2. Beijing Key Laboratory of UAV Autonomous Control, Beijing Institute of Technology, Beijing 100081, China;
    3. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China
  • Received:2018-04-17 Revised:2018-05-16 Online:2018-11-15 Published:2018-08-01
  • Supported by:
    National Natural Science Foundation of China (U1613225)

Abstract: To solve the missile guidance with constraints of impact time and terminal impact angle, a time and angle control guidance law based on optimal error dynamics is designed, and a definite performance index is given. The expression of time to go estimation under generalized optimal angle control guidance law is derived. To reach zero tracking error in the finite time with the optimal convergence pattern, the designed guidance law adds the feedback of impact time error to the generalized guidance law of optimal angle control and considers the impact time error as the tracking error, achieving the joint control of the impact time and the terminal impact angle. The effectiveness of the proposed guidance law is validated through numerical simulations under different conditions.

Key words: impact time control, impact angle control, optimal error dynamics, time to go, tracking error convergence pattern

CLC Number: