Application of modern guidance control theory to a bank-to-turn missile

Control laws of a bank-to-turn missile using an optimal estimator in terminal guidance were designed and the effect of increasing the number of measurement sensors in the missile to generate more information on the state was investigated. In design of the control law, modern optimal control theory with a quadratic performance index was used. Implementing this control law required use of a Kalman filter as the optimal estimator. The extended Kalman filter algorithm was used since the measurement states were non-linear functions of the state vectors (relative distance, velocity and target acceleration). To test the effects of implementation of the increased measurement sensors, two-, four- and six-measurement sensors were assumed to be implemented in the optimal estimator. The designed guidance laws were evaluated and the effect of the implementation of increased measurement sensors was tested. Simulation results revealed that the designed guidance law was successful within the specified scenarios. The effect of implementation of increased measurement sensors generated more information about the state vectors, but as the Kalman filter algorithm became more complex, the estimator performance was not enhanced to the degree expected.