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ABSTRACT: This work discusses a nonlinear midcourse missile controller with thrust vector control (TVC) inputs for the interception of a theater ballistic missile, including autopilot system and guidance system. First, a three degree-of-freedom (DOF) optimal midcourse guidance law is designed to minimize the control effort and the distance between the missile and the target. Then, converting the acceleration command from guidance law into attitude command, a quaternion-based sliding-mode attitude controller is proposed to track the attitude command and to cope with the effects from variations of missile's inertia, aerodynamic force, and wind gusts. The exponential stability of the overall system is thoroughly analyzed via Lyapunov stability theory. Extensive simulations are conducted to validate the effectiveness of the proposed guidance law and the associated TVC.
IEEE Transactions on Aerospace and Electronic Systems 08/2003; · 1.10 Impact Factor
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ABSTRACT: A nonlinear midcourse missile controller with thrust vector control (TVC) inputs for the interception of a theater ballistic missile is presented. First, an optimal midcourse guidance law is designed to minimize the control effort and the distance between the missile and the target. Then, a quaternion-based sliding-mode attitude controller is proposed to track the attitude command and to cope with the effects from variations of missile's inertia, aerodynamic force, and wind gusts. The exponential stability of the overall system is analyzed thoroughly via Lyapunov stability theory. Extensive simulations are conducted to validate the effectiveness of the proposed guidance law and the associated TVC.
American Control Conference, 2002. Proceedings of the 2002; 02/2002
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ABSTRACT: A nonlinear missile guidance controller with Thrust Vector Control
(TVC) inputs for the interception of a theater ballistic missile is
presented. In this paper, the midcourse phase of the missile is
investigated, during which many non-ideal conditions must be considered,
such as variation of the inertia of the missile and existence of the
aerodynamic force, and an effect controller is designed to take into
account the properties of TVC. Specifically, a 3 DOF optimal midcourse
guidance law is designed to minimize the control effort and the distance
between the missile and the target. The asymptotic stability of the
overall system is proved by Lyapunov theory. Extensive simulations are
conducted to validate the effectiveness of the proposed guidance law for
TVC
American Control Conference, 2001. Proceedings of the 2001; 02/2001
