A linear quadratic guidance law for a missile with a time varying acceleration constraint is presented. By introducing the constraint into the running cost, the optimization produces time varying gains that shape the missile’s trajectory for avoiding no-capture zones. The guidance law is derived for a missile with high-order autopilot dynamics and a terminal intercept angle constraint against a maneuvering target. The acceleration constraint of aerodynamic steering missiles is usually trajectory dependent rather than time dependent. Transforming the constraint into a time-dependent function by analytical means might not be possible, due to the nonlinear nature of the constraint. The problem is alleviated using a simple iterative calculation. For practical implementation reasons, and in order to improve the guidance performance under model uncertainties and disturbances, the guidance command is decomposed into two separate optimizations: one for the acceleration constraint, for which the guidance gains are calculated by a predicted time to go, and the other for the autopilot dynamics, for which the gains are obtained by a real-time time-to-go calculation, resulting in a suboptimal guidance law. The performance of the proposed law is investigated using nonlinear planar simulation, for a missile with first-order autopilot dynamics.


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    Title :

    Intercept Angle Missile Guidance Under Time Varying Acceleration Bounds


    Contributors:
    Taub, Ilan (author) / Shima, Tal (author)

    Published in:

    Publication date :

    2013-05-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Intercept Angle Missile Guidance under Time-Varying Acceleration Bounds

    Taub, I. / Shima, T. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2012




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