| Recent years, Rendezvous and Docking, space attack and defense, space detection is the focus of astronautics research. It results in space vehicle doing long-time and extensive orbit transfer. Autonomous navigation of orbital transfer vehicle which has the characters of independence, high reliability and low cost is an attractive and challenged subject of Chinese astronautics.The SINS navigation system and GPS system each has its own advantage and disadvantage. But the error propagation property is complementary. Long time stability of fist is bad, but its short time stability is good. So the combined navigation system which can compensate each other can realize real-time and high accuracy of position fixing for orbit transfer vehicle.For orbit transfer vehicle, it's not suitable that using geographic coordinate system or terrestrial coordinate system as navigation coordinate system. Its navigation parameters should be in geometric inertial coordinate system. In this study, geometric inertial coordinate system is navigation coordinate system. And the position, velocity and attitude error propagation equation is established in geometric inertial coordinate system.SINS/GPS navigation system of orbit transfer vehicle is established by making the equation combination with error equation of C/A code GPS receiver. To validate the feasibility of this algorithm through arithmetic simulation by using centralized Kalman filter.The dimension of state equation is 48. It could cause the lowering of calculated speed. So it's adopted that using singular value decomposition method to analyze the observability and degree and descend the dimensions of combined navigation system. And make the arithmetic simulation of combined navigation system which the dimensions is descended. Then contrast with undescended navigation system to test and verify the validity of observability and its degree results and the feasibility of combined navigation system which is descended.
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