Preliminary study on the attitude determination system for cruise missile based on IMM-UKF

A new method for the attitude determination of cruise missile using both satellite sensor and gyro is presented in this paper. An augmented measurement vector in the inertial coordinate system is formed using the original measurements, and the problem of the missile attitude determination is modeled as a nonlinear filtering process. Since it is difficult for conventional non-linear filtering methods to achieve both high accuracy and real-time implementation, the unscented Kalman filter is adopted and high-precision attitude determination is realized. Considering the practical operating conditions, such as the unknown and time-varying noises, a method combining interactive multi-model (IMM) and UKF is adopted for missile attitude determination. Simulation results confirmed the effectiveness and superiority of the proposed method and its feasibility for practical implementation.