초록 ▼

A system for providing attitude and antenna steering for a spacecraft is disclosed. The spacecraft has a number of reaction wheels and a number of antennas. The system includes control logic configured to: determine a beta angle, the beta angle being the angle between a sun vector and an orbit plane

A system for providing attitude and antenna steering for a spacecraft is disclosed. The spacecraft has a number of reaction wheels and a number of antennas. The system includes control logic configured to: determine a beta angle, the beta angle being the angle between a sun vector and an orbit plane of the spacecraft, and alternately engage either a first mode or a second mode to provide attitude and antenna steering based on the beta angle.

대표청구항 ▼

What is claimed is: 1. A system for providing attitude and antenna steering for a spacecraft having a plurality of reaction wheels and a plurality of antennas, wherein the plurality of antennas are configured to provide an antenna coverage pattern, the system comprising: control logic configured to

What is claimed is: 1. A system for providing attitude and antenna steering for a spacecraft having a plurality of reaction wheels and a plurality of antennas, wherein the plurality of antennas are configured to provide an antenna coverage pattern, the system comprising: control logic configured to: determine a beta angle, the beta angle being the angle between a sun vector and an orbit plane of the spacecraft; and alternately engage either a first mode or a second mode to provide attitude and antenna steering based on the beta angle, and engage the second mode for all values of the beta angle if the plurality of antennas are sufficient to maintain the antenna coverage pattern, wherein the plurality of antennas includes a plurality of phased array antennas, and wherein the antenna steering based on the beta angle includes modulating the plurality of phased array antennas based on the beta angle. 2. The system of claim 1 wherein the control logic is further configure to alternately engages either the first mode or the second mode based on whether the beta angle is below a threshold value. 3. The system of claim 2 wherein the threshold value is about 10-15 degrees. 4. The system of claim 2 wherein the control logic is further configured to: engage the first mode when the beta angle is above the threshold value, wherein the first mode utilizes the Sun Nadir Pointing strategy; and engage the second mode when the beta angle is below the threshold value. 5. The system of claim 1 wherein when the second mode is engaged, the control logic is further configured to adjust the plurality of reaction wheels to rotate the spacecraft such that the sun vector is in a yaw or roll plane of the spacecraft at all times. 6. The system of claim 5 wherein when the second mode is engaged, the control logic is further configured to rotate the antenna coverage pattern by an angle equal to a body rotation angle of the spacecraft. 7. The system of claim 5 wherein the spacecraft further includes a plurality of radiator panels that are parallel to the yaw or roll plane of the spacecraft; and wherein when the second mode is engaged, the control logic is further configured to adjust the plurality of reaction wheels to rotate the spacecraft such that there is nominally no sun exposure to the plurality of radiator panels. 8. The system of claim 1 wherein the spacecraft includes a satellite. 9. The system of claim 1 wherein the system is implemented as part of flight software configured to control the spacecraft; and wherein the flight software resides on a computer-readable medium executable by a processor onboard the spacecraft. 10. A spacecraft comprising: a plurality of sensors; a plurality of reaction wheels; a plurality of antennas configured to provide an antenna coverage pattern; and a processor having flight control logic residing thereon; wherein the flight control logic is configured to: receive input information from the plurality of sensors; determine a beta angle, the beta angle being the angle between a sun vector and an orbit plane of the spacecraft; and alternately engage either a first mode or a second mode to provide attitude and antenna steering based on the beta angle, and engage the second mode for all values of the beta angle if the plurality of antennas are sufficient to maintain the antenna coverage pattern, wherein the plurality of antennas includes a plurality of phased array antennas, and wherein the antenna steering based on the beta angle includes modulating the plurality of phased array antennas based on the beta angle. 11. The spacecraft of claim 10 wherein the flight control logic is further configured to alternately engage either the first mode or the second mode based on whether the beta angle is below a threshold value. 12. The spacecraft of claim 11 wherein the threshold value is about 10-15 degrees. 13. The spacecraft of claim 11 wherein the flight control logic is further configured to: engage the first mode when the beta angle is above the threshold value, wherein the first mode utilizes the Sun Nadir Pointing strategy; and engage the second mode when the beta angle is below the threshold value. 14. The spacecraft of claim 10 wherein when the second mode is engaged, the flight control logic is further configured to adjust the plurality of reaction wheels to rotate the spacecraft such that the sun vector is in a yaw or roll plane of the spacecraft at all times. 15. The spacecraft of claim 14 wherein when the second mode is engaged, the flight control logic is further configured to rotate the antenna coverage pattern by an angle equal to a body rotation angle of the spacecraft. 16. The spacecraft of claim 14 further comprising a plurality of radiator panels that are parallel to the yaw or roll plane of the spacecraft; wherein when the second mode is engaged, the flight control logic is further configured to adjust the plurality of reaction wheels to rotate the spacecraft such that there is nominally no sun exposure to the plurality of radiator panels. 17. The spacecraft of claim 10 wherein the spacecraft includes a satellite. 18. The spacecraft of claim 10 wherein the flight control logic resides on a computer-readable medium executable by a processor onboard the spacecraft.