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Guidance Law (guidance + law)
Selected AbstractsThree-dimensional nonlinear H, guidance lawINTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL, Issue 2 2001Ciann-Dong Yang Abstract This paper proposes a novel three-dimensional missile guidance law design based on nonlinear H, control. The complete nonlinear kinematics of pursuit,evasion motion is considered in the three-dimensional spherical co-ordinates system; neither linearization nor small angle assumption is made here. The nonlinear H, guidance law is expressed in a simple form by solving the associated Hamilton,Jacobi partial differential inequality analytically. Unlike adaptive guidance laws, the implement of the proposed robust H, guidance law does not require the information of target acceleration, while ensuring acceptable interceptive performance for arbitrary target with finite acceleration. The resulting pursuit,evasion trajectories for both the H, -guided missile and the worst-case target are determined in closed form, and the performance robustness against variations in target acceleration, in engagement condition, and in control loop gain, is verified by numerical simulations. Copyright © 2001 John Wiley & Sons, Ltd. [source] Design of nonlinear terminal guidance/autopilot controller for missiles with pulse type input devices,ASIAN JOURNAL OF CONTROL, Issue 3 2010Fu-Kuang Yeh Abstract This investigation addresses a nonlinear terminal guidance/autopilot controller with pulse-type control inputs for intercepting a theater ballistic missile in the exoatmospheric region. Appropriate initial conditions on the terminal phase are assumed to apply after the end of the midcourse operation. Accordingly, the terminal controller seeks to minimize the distance between the commanded missile and the target missile to ensure a hit-to-kill interception. In particular, a 3D terminal guidance law is initially developed to eliminate the so-called "sliding velocity, " thus, constraining the relative motion between the missile and the target along the line of sight. Sliding mode control is adopted to design stable pulse-type control systems. Then, a quaternion-based attitude controller is used to orient appropriately the commanded missile, taking into account the fact that the missile is a rigid body, to realize interceptability. The stability of the overall integrated terminal guidance/autopilot system is then analyzed thoroughly, based on Lyapunov stability theory. Finally, extensive simulations are conducted to verify the validity and effectiveness of the integrated controller with the pulse type inputs developed herein. Copyright © 2010 John Wiley and Sons Asia Pte Ltd and Chinese Automatic Control Society [source] Three-dimensional nonlinear H, guidance lawINTERNATIONAL JOURNAL OF ROBUST AND NONLINEAR CONTROL, Issue 2 2001Ciann-Dong Yang Abstract This paper proposes a novel three-dimensional missile guidance law design based on nonlinear H, control. The complete nonlinear kinematics of pursuit,evasion motion is considered in the three-dimensional spherical co-ordinates system; neither linearization nor small angle assumption is made here. The nonlinear H, guidance law is expressed in a simple form by solving the associated Hamilton,Jacobi partial differential inequality analytically. Unlike adaptive guidance laws, the implement of the proposed robust H, guidance law does not require the information of target acceleration, while ensuring acceptable interceptive performance for arbitrary target with finite acceleration. The resulting pursuit,evasion trajectories for both the H, -guided missile and the worst-case target are determined in closed form, and the performance robustness against variations in target acceleration, in engagement condition, and in control loop gain, is verified by numerical simulations. Copyright © 2001 John Wiley & Sons, Ltd. [source] | ||||||||||