An integrated design for missile guidance/ control /tracking system

摘要

An integrated information system (IIS) which contains strapdown inertial navigation system (SINS), automatic pilot and terminal guidance seeker is proposed. Using rotating modulation approach, the performance of the low cost MEMS inertial sensor is improved by 20-30 times. The precision of the modulated MEMS gyro is available for strapdown navigation system and autopilot. The IIS gyros replace gimbal-based gyros are used in the line-of-sight (LOS) stabilization system. The seeker's LOS angular rate is estimated by combining the missile-fixed gyro information with gimbal coordinate rate information. The indirect LOS stabilization control loop is elaborately designed according to the gimbal kinematical relationship and dynamics models. The study and analysis results show that the compensation torque is available to null the disturbance and make the LOS stabilization. The proposed US saves two sets of gyros and make the SINS, autopilot, seeker integrated designing. It owns many advantages such as compact configuration, prominent low cost etc.