Abstract: Mobile ballistic missile is associated with poor initial attitude alignment of the inertial platform and poor initial position data. Stellar-inertial integrated guidance system can update the initial errors and overcome the shortcomings of the inertial platform. A kind of stellar-inertial integrated guidance system based on follow-up platform is introduced in detail. The computing formulae are deduced required for controlling the follow-up platform to rotate; the principle of the follow-up platform's tracking star is researched; the measurement process of stellar-tracker to the platform's error angles is discussed; and the relationship between the output of stellar-tracker and the error angle of inertial platform is deduced. The simulating results show that the scheme is valid.

Key words: follow-up platform, stellar-tracker, integrated guidance, platform error