To ensure that the shipboard satellite receiver get enough of their own real-time, accurate attitude information, considering the requirements low-cost, this paper introduced micro-electro-mechanical system (MEMS) inertial device to design attitude positioning system for satellite receiver. The high precision laser gyro navigation system in the bow is used to combine MEMS inertial navigation system (INS) in the stern. The errors of the MEMS strapdown inertial navigation system are analyzed and the dynamic model of the integrated navigation system was established. In order to solve the low accuracy problem of MEMS INS attitude Sage-Husa adaptive filter is utilized to estimate inertial navigation system error, and correct the attitude calculation results of the MEMS INS. The experimental verification is feasible.