Satellites having autonomously deployable solar arrays

Patent metadata

Field	Value
Publication number	US-11993404-B2
Application number	US-202218065276-A
Country	US
Kind code	B2
Filing date	Dec 13, 2022
Priority date	Dec 18, 2018
Publication date	May 28, 2024
Grant date	May 28, 2024

Abstract

Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

First claim

What is claimed is:

1. A satellite comprising:
a solar array;
a sensor to detect that the satellite has exited a launch vehicle;
a processor to, based on the satellite exiting the launch vehicle, cause release of magnets or locks of an array;
a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array; and
a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

2. The satellite as defined in claim 1 , wherein the sensor is a first sensor, and further including a second sensor to detect a folding condition of the solar array, the sequence analyzer to adapt the release sequence based on the folding condition.

3. The satellite as defined in claim 1 , wherein the sensor is a first sensor, and further including a second sensor to detect relative positions of landmarks external to the satellite to determine an orientation of the satellite.

4. The satellite as defined in claim 1 , wherein the sequence analyzer is to change the order in which the magnets or the locks of the array in the release sequence are released by changing a first magnet from releasing after a second magnet to releasing the first magnet before the second magnet.

5. The satellite as defined in claim 4 , wherein the sequence analyzer is to change the order in which ones of the magnets in the release sequence are released by further removing a third magnet from the release sequence.

6. The satellite as defined in claim 1 , further including a satellite maneuver controller to move the solar array to an orientation in which momentum accumulation is reduced.

7. The satellite of claim 6 , wherein the satellite maneuver controller is to control a first attitude and a first spin about a first axis that defines a position of the satellite to maintain a thermal condition.

8. A method of autonomously deploying a solar array of a satellite, the method comprising:
determining, via a sensor, that the satellite has exited a launch vehicle;
upon determining that the satellite has exited the launch vehicle, releasing magnets or locks of an array based on a release sequence to autonomously deploy the solar array; and
adapting, via instructions executed by a processor, the release sequence of the magnets or locks of the array during execution of the release sequence, wherein the adapting of the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

9. The method as defined in claim 8 , wherein the sensor is a first sensor, and further including detecting, via a second sensor, a folding condition of the solar array and adapting the release sequence based on the folding condition.

10. The method as defined in claim 8 , wherein the sensor is a first sensor, and further including detecting, via a second sensor, relative positions of landmarks external to the satellite to determine an orientation of the satellite.

11. The method as defined in claim 8 , wherein adapting the release sequence includes changing a first magnet from releasing after a second magnet to releasing the first magnet before the second magnet.

12. The method as defined in claim 11 , wherein adapting the release sequence includes removing a third magnet from the release sequence.

13. The method as defined in claim 8 , further including moving the solar array to an orientation in which momentum accumulation is reduced.

14. The method as defined in claim 8 , further including controlling a first attitude and a first spin about a first axis which defines a position of the satellite to maintains a thermal condition.

15. A non-transitory machine readable medium comprising instructions, which when executed, cause a processor of a satellite to at least:
determine that the satellite has exited a launch vehicle based on sensor data;
upon determination that the satellite has exited the launch vehicle, cause release of magnets or locks of an array based on a release sequence; and
adapt the release sequence of the magnets or the locks of the array during execution of the release sequence to autonomously deploy a solar array of the satellite, wherein the release sequence is adapted by changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

16. The non-transitory machine readable medium as defined in claim 15 , wherein the instructions cause the processor to determine a folding condition of the solar array and adapting the release sequence based on the folding condition.

17. The non-transitory machine readable medium as defined in claim 15 , wherein the instructions cause the processor to determine relative positions of landmarks external to the satellite to determine an orientation of the satellite.

18. The non-transitory machine readable medium as defined in claim 15 , wherein the instructions cause the processor to adapt the release sequence by changing a first magnet from releasing after a second magnet to releasing the first magnet before the second magnet.

19. The non-transitory machine readable medium as defined in claim 15 , wherein the instructions cause the processor to cause an adjustment of an orientation of the satellite to an orientation in which momentum accumulation is reduced.

20. The non-transitory machine readable medium as defined in claim 19 , wherein the instructions cause the processor to control a first attitude and a first spin about a first axis which defines a position of the satellite to maintain a thermal condition.

21. A non-transitory machine readable medium comprising instructions, which when executed, cause a processor of a satellite to at least:
determine that the satellite has exited a launch vehicle based on sensor data;
upon determination that the satellite has exited the launch vehicle, cause utilization of squibs, magnets or locks of an array based on a sequence;
cause an adjustment of an orientation of the satellite to an orientation in which momentum accumulation is reduced; and
adapt the sequence of the squibs, the magnets or the locks of the array during execution thereof to autonomously deploy a solar array of the satellite, wherein the sequence is adapted by changing an order in which the squibs, the magnets or the locks of the array are utilized based on a degree to which the solar array is unfolded.

22. The non-transitory machine readable medium as defined in claim 21 , wherein the instructions cause the processor to control a first attitude and a first spin about a first axis which defines a position of the satellite to maintain a thermal condition.

Assignees

• Boeing Co

Inventors

• Lemke Gary E
• Wasson Chris J
• Mills John P
• Cantu Cecilia G

Classifications

• B64G1/2222

  Folding · CPC title

• B64G1/002

  Launch systems · CPC title

• B64G1/443 Primary

  Photovoltaic cell arrays · CPC title

• B64G1/242

  Orbits and trajectories · CPC title

• B64G1/361

  using star sensors · CPC title