This note studies the problem of impact angle guidance by considering the seeker's field-of-view angle constraint and proposes a new guidance parameter design strategy based on the classical time-to-go weighted impact angle optimal guidance law. To this end, firstly, the analytic expression of the field-of-view angle throughout the guidance process is presented. It is demonstrated that the max field-of-view angle can be controlled by designing the correct time-to-go weighted parameter and initial guidance conditions. Then, a guidance strategy, which includes the optimal guidance law, guidance condition selection, and guidance parameter design, is given. When using the strategy, the suitable time-to-go weighted parameter is modified to ensure the seeker's field-of-view angle would not exceed the boundary value. Finally, the results of a numerical simulation based on the simple missile-target kinematics are presented; these results validate the proposed strategy.


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    Title :

    A parameter design strategy for seeker's field-of-view constraint in impact angle guidance


    Contributors:


    Publication date :

    2015




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik
    Local classification TIB:    275/7040