초록 ▼

By using the GPS satellite transmitted signals that are tracked on a satellite and those that should be tracked but are not due to the attitude of the satellite and rotating the satellite, two estimations of satellite attitude are made that are used to change the satellite attitude so that all the G

By using the GPS satellite transmitted signals that are tracked on a satellite and those that should be tracked but are not due to the attitude of the satellite and rotating the satellite, two estimations of satellite attitude are made that are used to change the satellite attitude so that all the GPS signals are tracked.

대표청구항 ▼

1. An attitude control for a spacecraft, comprising: means for providing stored locations for GPS satellites; a GPS antenna; means for tracking the OPS satellites; means for determining a first GPS antenna bore sight estimation from a characteristic comprising the location of a tracked GPS sat

1. An attitude control for a spacecraft, comprising: means for providing stored locations for GPS satellites; a GPS antenna; means for tracking the OPS satellites; means for determining a first GPS antenna bore sight estimation from a characteristic comprising the location of a tracked GPS satellite and OPS satellites that should be tracked; means for rotating the spacecraft relative to an antenna bore sight for the GPS antenna; means for determining & second antenna bore sight estimation relative to the GPS satellites from said characteristic following said rotation; means for determining a desired spacecraft attitude change to point the antenna bore sight in a desired direction, as a function of the first bore sight estimation and the second bore sight estimation, to track satellites that should be tracked within a constrained region required for GPS attitude initialization; and means for changing the spacecraft to said desired attitude. 2. The attitude control of claim 1 wherein said desired direction is the zenith for the GPS antenna. 3. The attitude control of claim 1 wherein the rotation is 90 degrees along the X axis of the satellite. 4. The attitude control of claim 1 wherein the bore eight estimations comprise vectors that manifest azimuth and altitude. 5. A method for aligning the bore sight of a GPS antenna on a spacecraft comprising: tracking GPS satellites; determining a GPS satellite that should be tracked; making a first estimation of the bore sight orientation as a function of the azimuth and elevation between the spacecraft and GPS satellites that are tracked and satellites that are not tracked. rotating to spacecraft to change the bore sight orientation; tracking a second set of GPS satellites and determining the remaining GPS satellites that could be tracked; following rotating the spacecraft, making a second estimation of the bore sight orientation as a function of the azimuth and elevation between the space craft and the second GPS satellite set and a third satellite set that could be tracked; determining a desired spacecraft attitude to align the antenna bore sight as a function of the first and second estimations of bore sight orientation to track the satellites within a constrained region required for GPS Attitude Initialization; and changing the spacecraft attitude to the desired orientation. 6. A method for controlling the attitude of a spacecraft, comprising: receiving GPS signals from a first set of satellites; determining OPS signals from a second set of satellites that are not being received; making a first estimation of attitude as function of the line of sight bearing between the spacecraft and the first and second set of satellites; rotating the spacecraft; receiving GPS signals from a third set of satellites following rotating the spacecraft; determining GPS signals that are not being received from a fourth set of satellites following rotating the spacecraft; making a second estimation of attitude as function of the line of sight bearing between the spacecraft and the third and fourth set of satellites; and changing the attitude of the spacecraft to align the GPS antenna bore sight along a desired vector based on the first and second estimations of attitude. 7. The method described in claim 6, wherein the vector is relative to the earth. 8. The method described in claim 7, wherein the vector is inertial space relative.