The purpose of this paper is to develop an optimal guidance law that takes into account both the missilenacceleration limit and a maximum value allowed for the guidance gain. The maximum value of the guidance gain isndictatedmainly by the possible coupling between themissile bodymotions and themeasurement of the inertial targetnline-of-sight angle rate. The tools for this work are the linear quadratic stochastic Gaussian optimal control theoryncoupled with the use of random-input describing functions. Although the use of the random-input describingnfunction introduces an approximation in the work, it has been shown in the past that the use of random-inputndescribing functions inmiss distance calculations results in good approximations for the predictedmiss distance.Thenpaper includes the derivation of the optimal guidance lawthat accounts for both themissile acceleration limit and thenconstraint on the guidance gain and a simple one-dimensionalMonteCarlo simulation to examine the performance ofnthe guidance law.
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