Correction of spacecraft steering control law for unexpected orbital inclination effects

A system and method (30, 50) for correcting pointing errors induced by an inclined orbit (14) for a satellite (20) that is adapted to be in an orbit (12) having zero inclination. The present invention generates (34) a yaw correcting cosine rate command that is integrated (36) by a steering law havin...

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Bibliographische Detailangaben
Hauptverfasser:	YOCUM, JOHN F., JR, EYERLY, BRUCE N
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIRCRAFT AVIATION CONTROLLING COSMONAUTICS PERFORMING OPERATIONS PHYSICS REGULATING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR
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Beschreibung
Zusammenfassung:	A system and method (30, 50) for correcting pointing errors induced by an inclined orbit (14) for a satellite (20) that is adapted to be in an orbit (12) having zero inclination. The present invention generates (34) a yaw correcting cosine rate command that is integrated (36) by a steering law having input parameters dependent upon the angle ( THETA ) of inclination to derive (38) a sinusoidal yaw offset. The present invention also generates (54) a roll correcting cosine rate command that is integrated (56) according to a steering law having input parameters dependent upon the angle ( THETA ) of inclination to derive a sinusoidal roll offset (Fig. 4).