Journal of Astronautics ›› 2017, Vol. 38 ›› Issue (7): 714-722.doi: 10.3873/j.issn.1000-1328.2017.07.006

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Integrated Guidance and Control Design Against Highly Maneuvering Target

LAI Chao, WANG Wei hong, XIONG Shao feng   

  1. 1. School of Automation Science and Eletrical Engineering, Beihang University, Beijing 100191, China;
     2. System Design Department, Second Academy of China Aerospace Science & Industry Corporation, Beijing 100854, China
  • Received:2017-04-06 Revised:2017-05-19 Online:2017-07-15 Published:2017-07-25


A composite control method combining the finite-time stable nonlinear extended state observer (ESO) and the adaptive dynamic surface control is applied to the integrated guidance and control (IGC) for a skid-to-turn (STT) missile against a highly maneuvering target. Firstly, a new three-dimensional integrated guidance and control design model for a skid-to-turn missile is established with fewer assumptions. Next, a nonlinear ESO with the finite time convergence performance is introduced to estimate the uncertainties including the unknown target accelerations. And then, the adaptive control law is introduced to compensate the error of the extended state observer. Based on the nonlinear ESO, adaptive technique and dynamic surface control (DSC), a composite IGC scheme is proposed. The stability of the system is guaranteed by the Lyapunov stability theory. And the numerical simulations demonstrate the improvements on the hitting performance of the proposed control scheme.

Key words: Integrated guidance and control (IGC), Uncertainty, Dynamic surface control (DSC), Adaptive control, Extended state observer (ESO)

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