초록 ▼

For controlling the attitude of the body of an earth satellite placed on a low orbit, values of components of the geomagnetic field of the earth are measured along three axes of a frame of reference bound to the body. The values are derivated with respect to time, and multiplied by a gain. Currents

For controlling the attitude of the body of an earth satellite placed on a low orbit, values of components of the geomagnetic field of the earth are measured along three axes of a frame of reference bound to the body. The values are derivated with respect to time, and multiplied by a gain. Currents responsive to the multiplicated derivatives are passed through magnetic torquers located along the three axes of the body to create magnetic torques that bias the body to a fixed angular position relative to the field lines of the geomagnetic field. Such steps are continuously carried out during eclipse periods. Out of eclipse periods, the pitch of the body is controlled by modifying an internal momentum in response to a signal provided by a solar sensor, so as to maintain solar generators carried by the body of the satellite oriented towards the Sun.

대표청구항 ▼

[ I claim:] [1.] A method of controlling an attitude of a body of an earth satellite placed on a low orbit, comprising the steps of:(a) measuring values of components of the geomagnetic field of the earth, along three axes of a frame of reference bound to said body of the satellite,(b) derivating sa

[ I claim:] [1.] A method of controlling an attitude of a body of an earth satellite placed on a low orbit, comprising the steps of:(a) measuring values of components of the geomagnetic field of the earth, along three axes of a frame of reference bound to said body of the satellite,(b) derivating said values with respect to time,(c) multiplying the so obtained derivatives by a gain,(d) passing currents responsive to the multiplicated derivatives through magnetic torquers located along said three axes of said body to create magnetic torques that bias said body of the satellite to a fixed angular position relative to field lines of said geomagnetic field,said steps (a) to (d) being continuously carried out during eclipse periods, and(e) out of said eclipse periods, controlling an amount of pitch of said body of the satellite by modifying an internal momentum thereof in response to a signal provided by a solar sensor carried by said body, so as to maintain solar generators carried by said body of the satellite oriented towards the Sun.