Abstract: A space shuttle is a large system engineering of high complexity. To ensure the safety and success of its flight, the navigation system of the space shuttle usually consists of an inertial reference system combined with others.During flight, especially re-entery, specified attitudes with certain precision are required. However, the inertial reference system exhibits accumulating drift errors in a long-term flight. To cope with this, a star-tracker is usually used to provide a basis for correcting the inertial reference. This results in an astro/inertial reference system. By heading and tracking some selected stars with known position and trajectory, the star-tracker provides necessary offsets for the gyro drift in the inertial system, thereby making the latter be able to give attitude information that meets the overall accuracy requirement.In this paper a formula is developed for the attitude stabilization of a space shuttle with a new type-charge-coupled sensor devices （CCD） used in the star-tracker. A scheme of the star-tracker is also presented.