Terminal angle constraint finite-time guidance law with input saturation and autopilot dynamics |
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| Institution: | 1. Center for Control Theory and Guidance Technology, Harbin Institute of Technology, Harbin 150001, China;2. School of Electronics and Information Engineering, Suzhou University of Science and Technology, Suzhou 215000, China;1. School of Internet Finance and Information Engineering, Guangdong University of Finance, Guangzhou,510521, China;2. School of Automation, Guangdong University of Technology, Guangzhou, 510006, China;3. Guangdong-HongKong-Macao Joint Laboratory for Smart Discrete Manufacturing, Guangzhou, 510006, China;4. School of Computer Science and Engineering, South China University of Technology, Guangzhou, 510006, China;1. Defence Research and Development Laboratory, Hyderabad, India;2. Indian Institute of Technology Bombay, Mumbai, India |
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| Abstract: | This paper proposes a finite-time command filtered backstepping guidance law (FCFBGL) with the terminal angle constraint while accounting for the input saturation and the autopilot dynamics. To eliminate the adverse effect induced by the filtering errors and the acceleration saturation, a new finite-time error compensation mechanism is integrated in the guidance law design. The proposed FCFBGL not only guarantees the the line-of-sight (LOS) angle error to converge to a small neighborhood of the origin in finite time but also achieves the continuity of the input signal. in finite time. Moreover, with the aid of the fractional power extended state observer (FPESO), the proposed FCFBGL requires no information on the target acceleration and the acceleration derivative of the missile, which is preferable in the practical application. The finite-time stability of the proposed guidance law is derived with the Lyapunov methodology. Simulation results illustrate the effectiveness and superiority of the proposed guidance law. |
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