The application discloses a method for calibrating a roll angle of an emergency anti-
solar time of a
satellite on the earth, which is beneficial to reestablishing a three-axis attitude of the
satellite on the earth. Firstly, an angle between a projection of a sun vector on an
orbit plane and an
orbit system-X axis is calculated; then, whether a current
orbit position meets a requirement is determined according to the angle between the projection of the sun vector on the
orbit plane and the orbit
system-X axis, and whether an absolute attitude reference is available at present is determined, if the current orbit position meets the requirement and the absolute attitude reference is available at present, the roll angle is calibrated at a current control beat; otherwise, the roll angle is not calibrated at the current control beat; if the roll angle is calibrated at the current control beat, the roll angle is calculated based on the absolute attitude reference; if the roll angle is not calibrated at the current control beat, the roll angle is calculated by using gyro
inertia angular velocity integration. The application can provide high-precision and reliable attitude information for reestablishing the attitude of the
satellite on the earth.