초록 ▼

A three-axis attitude control system for a spacecraft in an equatorial orbit includes at least a horizon sensor for producing pitch-representative signals. A star sensor has a boresight parallel to the spacecraft pitch axis, and produces signals representative of the two-axis location of a selected

A three-axis attitude control system for a spacecraft in an equatorial orbit includes at least a horizon sensor for producing pitch-representative signals. A star sensor has a boresight parallel to the spacecraft pitch axis, and produces signals representative of the two-axis location of a selected pole star relative to the boresight. The star sensor signals are processed in conjunction with the pitch-representative signals and with orbit-location information, to produce roll and yaw information. The pitch, roll and yaw information controls spacecraft torquing. In a particular embodiment of the invention, the horizon sensor arrangement also produces roll signals, which are processed with the roll signals from the star sensor.

대표청구항 ▼

A 3-axis attitude control system for a spacecraft for operation in an equatorial orbit, comprising: polar star sensing means mounted on said spacecraft, with a boresight parallel to the pitch axis of said spacecraft, for producing star signals representative of the two-axis location of a selected po

A 3-axis attitude control system for a spacecraft for operation in an equatorial orbit, comprising: polar star sensing means mounted on said spacecraft, with a boresight parallel to the pitch axis of said spacecraft, for producing star signals representative of the two-axis location of a selected polar star relative to said pitch axis; earth sensing means mounted on said spacecraft, for generating at least pitch signals representative of the pitch of said spacecraft about said pitch axis; a source of signals, for generating signals representing orbital location and ephemeris information; processing means coupled to said polar star sensing means, said Earth sensing means, and to said source, for processing said two-axis information and said pitch signals and for generating at least signals representative of roll and yaw information; and torquing means coupled to at least said processing means, for responding to said signals representative of said pitch, roll and yaw for torquing said spacecraft to maintain a desired attitude.