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A three axis attitude orientation system for a spacecraft in orbit which employs a single UV sensor. The single sensor provides roll and pitch information by locating the centroid of the earth and using this as a reference point. The system determines yaw by tracking the position of stars which appe

A three axis attitude orientation system for a spacecraft in orbit which employs a single UV sensor. The single sensor provides roll and pitch information by locating the centroid of the earth and using this as a reference point. The system determines yaw by tracking the position of stars which appear in the field of view around the earth. Three axis attitude is determined through ultraviolet imaging of the earth's limb and adjacent stars. A non-conventional wide angle optics assembly and intensified CCD array are utilized for this purpose.

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1. A method of determining three axis attitude information for a spacecraft in earth's orbit using a single ultraviolet light sensor assembly, comprising the steps of: positioning the ultraviolet light sensor assembly on the spacecraft so as to view the entirety of the earth's ultraviolet limb an

1. A method of determining three axis attitude information for a spacecraft in earth's orbit using a single ultraviolet light sensor assembly, comprising the steps of: positioning the ultraviolet light sensor assembly on the spacecraft so as to view the entirety of the earth's ultraviolet limb and at least one background star; establishing a reference centroid of the earth's ultraviolet limb using an image of the limb detected by the ultraviolet light sensor assembly; determining rotation of the spacecraft about the pitch and roll axis of the spacecraft by monitoring the location of a measured centroid of the earth's ultraviolet limb in relation to the location of the reference centroid; detecting an ultraviolet image of at least one of the background stars; and determining the rotation of the spacecraft about the yaw axis by monitoring the position of the ultraviolet image of the background stars in relation to the predicted locations of the background stars from ephemeris information. 2. The method of determining three axis attitude information of claim 1 wherein the steps of determining the location of the reference and measured centroids are accomplished by locating the mean center of points of maximum intensity at all azimuths of the limb. 3. The method of determining three axis attitude information of claim 1 wherein the step of determining the spacecraft rotation about the pitch and roll axis is accomplished by overlaying images of the measured centroids and the reference centroid in a reference plane and measuring the longitudinal and lateral distances between the measured and reference centroids. 4. The method of determining three axis attitude information of claim 1 wherein the step of determining the spacecraft rotation about the yaw axis is accomplished by overlaying the ultaviolet image of the background stars with an image of the predicted positions of said background in a reference plane and measuring the lateral and longitudinal distance between the ultraviolet image and the predicted position. 5. A method of determining three axis attitude information for a spacecraft in earth's orbit using a single ultraviolet light sensor assembly, comprising the steps of: positioning the ultraviolet light sensor assembly on the spacecraft so as to view the entirety of the earth's ultraviolet limb and at least one background star; establishing a reference centroid of the earth's ultraviolet limb using an image of the limb detected by the ultraviolet light sensor assembly; determining rotation of the spacecraft about the pitch and roll axis of the spacecraft by monitoring the location of a measured centroid of the earth's ultraviolet limb in relation to the location of the reference centroid; detecting an ultraviolet image of at least one of the background stars; and determining the rotation of the spacecraft about the yaw axis of the spacecraft by comparison of a measured location of a terminator crossing of the limb with the predicted location of the terminator crossing from ephemeris information. 6. The method of determining three axis attitude information of claim 5 wherein the steps of determining the location of the reference and measured centroids are accomplished by locating the mean center of points of maximum intensity at all azimuths of the limb. 7. The method of determining three axis attitude information of claim 5 wherein the step of determining the spacecraft rotation about the pitch and roll axis is accomplished by overlaying images of the measured centroids and the reference centroid in a reference plane and measuring the longitudinal and lateral distances between the measured and reference centroids. 8. The method of determining three axis attitude information of claim 5 wherein the step of determining the spacecraft rotation about the yaw axis is accomplished by overlaying an image of the measured position of the terminator crossing with the predicted positions of the terminator crossing in a reference plane and measuring the lateral and longitudinal distance between the ultraviolet image and the predicted position.