Abstract In this paper, a new optimal linear-quadratic guidance law with terminal acceleration constraints is proposed for intercepting maneuvering target. Because the angle of attack is approximately proportional to the normal acceleration for aerodynamic control missile, not only miss distance, but also terminal acceleration is required to converge to zero for increasing effectiveness of the warhead for destroying armored target in the proposed guidance law. The gain characteristic of proposed guidance law is studied by comparing with traditional optimal guidance law with considering autopilot dynamics lags. Numerical simulations are performed to examine performance of the proposed optimal guidance law, and its robustness with respect to the time constant of autopilot dynamic lags is also studied by considering time constant typical errors.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Optimal Linear-Quadratic Guidance Law Considering Autopilot First-Order Lag with Terminal Acceleration Constraint


    Contributors:
    Zheng, Duo (author) / Xu, Xinghua (author) / Yan, Ruyi (author) / Lin, Defu (author)


    Publication date :

    2019-01-01


    Size :

    21 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English






    Linear Quadratic Integrated Versus Separated Autopilot-Guidance Design

    Levy, Maital / Shima, Tal / Gutman, Shaul | AIAA | 2013


    Terminal-Phase Optimal Guidance Law for BTT Missiles Considering Significant Autopilot Dynamics

    Yeom, J. / Yoo, S. / Hong, J. et al. | British Library Conference Proceedings | 2011


    Energy-Optimal Waypoint-Following Guidance Considering Autopilot Dynamics

    He, Shaoming / Shin, Hyo-Sang / Tsourdos, Antonios et al. | IEEE | 2020

    Free access