Control of impact angle can considerably increase missile's lethality. However, large impact angle will lead to large lateral acceleration requirement during the flight. In order to avoid command saturation, one can choose initial heading angle to decrease the magnitude of the guidance command. Based on impact angle control optimal guidance law of air-to-surface missile, some more in-depth research work is showed in this paper. For a specified impact angle, the methods to select initial heading angle is presented, and, the launch envelope of initial heading angle and terminal impact angle are given. Simulation results demonstrate the obtained conclusions.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Influence of initial heading angle for the optimal guidance law with impact angle constraint


    Contributors:


    Publication date :

    2016-08-01


    Size :

    732697 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



    Nonlinear Optimal Impact-Angle-Constrained Guidance with Large Initial Heading Error

    Li, Hongyan / Wang, Jiang / He, Shaoming et al. | AIAA | 2021



    Optimal Guidance Laws with Terminal Impact Angle Constraint

    Chang-Kyung Ryoo / Hangju Cho / Min-Jea Tahk | AIAA | 2005


    Practical generalized optimal guidance law with impact angle constraint

    Lee, Chang-Hun / Ryu, Moo-Yong | SAGE Publications | 2019