The invention discloses a sidereal hour angle based attitude control method. The method comprises S1) a Julian century corresponding to present onboard time of a satellite is obtained; S2) a sidereal hour angle is calculated; S3) an attitude conversion quaternion between a track coordinate system and an inertia coordinate system is obtained by calculation; S4) an attitude quaternion, relative to a track system, of a satellite body system is obtained by calculation; S5) an Euler angle of the satellite body system in a pitching-rolling-yawing turn order is calculated, and an attitude determining angle based on star sensor information is obtained; S6) a PD control algorithm is executed, and a control moment is obtained by calculation; and the steps S1) to S6) are repeated to realize autonomous continuous navigation and attitude control of the satellite. According to the invention, autonomous navigation and attitude control for the aircraft position are carried out only by calculating the sidereal hour angle, the problem that ground or GNSS measuring track information cannot be obtained in an abnormal state is solved, autonomous management of the satellite is realized, and the reliability and survival capability of the satellite are improved.