Abstract:With the increase of the slenderness ratio of the interceptor missile body and the effect of the direct lateral force, the measurement information of the full strap down seeker on the interceptor missile is seriously affected by the elastic oscillation of the missile body and the excitation of the control torque, resulting in the decline of the missile guidance accuracy. Aiming at the disadvantage that the existing inertial navigation system can’t detect the seeker oscillation at the oscillating wave belly near the missile body center of mass, a new state model of differential observation is proposed by installing a MEMS gyroscope device in the seeker to measure the oscillating angular rate. The line of sight angular rate is decoupled and accurately extracted through the interactive multi model Cubature Kalman Filtering algorithm. The mathematical simulation experiment verifies the effectiveness of the algorithm by building a six degree of freedom guidance and control simulation model of the missile and using Monte Carlo shooting simulation. The simulation results show that the filtering algorithm after model reconstruction can compress the root mean square error of missile body oscillation to within 0.5 ° and effectively track the angular rate of the line of sight of the missile and target.