Min-Max Guidance Law Integration
This chapter deals with air-to-air missile guidance law design. We model the terminal engagement of a ramjet missile with radar seeker lock on a single target (generic aircraft). We consider a realistic interception simulation with measurement errors and, more particularly, radome aberration errors.We define an extended Kalman filter to compensate in line those errors and to stabilize the guidance loop. Then, to decrease the miss distance against manoeuverable targets we implement an optimized guidance law. The guidance law we propose is based on a linear quadratic differential game linearized around the collision course using the target acceleration estimation provided by the Kalman filter. In this game, the evader control is defined around the Kalman target acceleration estimation to take into account delays and lags due to the filters we apply. The Kalman target acceleration estimation (assumed constant) is a parameter of the differential game kinematics.
KeywordsInertial Measurement Unit Manoeuvrable Target Target Acceleration Proportional Navigation Linear Quadratic Differential Game
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