US-12623795-B2 - System and method for deployment of space vehicle solar array

Abstract

A system, including: a satellite; a first solar array including a first solar panel; a second solar array including a second solar panel; a boom having a first end and a second end opposite the first end, where the first end connects to the satellite; and a bracket assembly, where the bracket assembly has a first, second, and third brackets, where the first bracket connects the first solar array to the third bracket, where the second bracket connects the second solar array to the third bracket, and where the third bracket connects the first bracket and the second bracket to the second end of the boom; where the bracket assembly is configured to reorient the first solar array and the second solar array between a stowed position to a deployed position, and where in the deployed position, the first and second solar arrays are oriented at a predetermined angle.

Inventors

• Manraj NAGI

Assignees

• NETWORK ACCESS ASSOCIATES LIMITED

Dates

Publication Date

20260512

Application Date

20240822

Claims (18)

1. 1 . A system, comprising: a satellite; a first solar array, wherein the first solar array comprises at least a first solar panel; a second solar array, wherein the second solar array comprises at least a second solar panel; a boom having a first end and a second end opposite the first end, wherein the first end connects to the satellite; and a bracket assembly, wherein the bracket assembly comprise a first bracket, a second bracket, and a third bracket, wherein the first bracket connects the first solar array to the third bracket, wherein the first bracket comprises a first section and a second section, wherein the second section is angled relative to the first section, and wherein an angle between the first section and the second section is an acute angle, wherein the second bracket connects the second solar array to the third bracket, and wherein the third bracket connects the first bracket and the second bracket to the second end of the boom, wherein the bracket assembly is configured to reorient the first solar array and the second solar array from a stowed position to a deployed position, and wherein in the deployed position, the first and second solar arrays are oriented at a predetermined angle.
2. 2 . The system of claim 1 , wherein the boom comprises an extendable boom.
3. 3 . The system of claim 2 , wherein the extendable boom comprises at least one telescoping tube.
4. 4 . The system of claim 3 , wherein the extendable boom comprises a plurality of telescoping tubes.
5. 5 . The system of claim 1 , wherein the first solar array further comprises a third solar panel, and wherein the third solar panel is foldable relative to the first solar panel.
6. 6 . The system of claim 5 , wherein the second solar array further comprises a fourth solar panel, and wherein the fourth solar panel is foldable relative to the second solar panel.
7. 7 . The system of claim 1 , wherein the satellite has a zenith side and an earth side, wherein the zenith side is configured to face away from the earth when the satellite is in orbit around the earth, wherein the earth side is configured to face toward the earth when the satellite is in orbit around the earth, and wherein the first end of the boom is connected to the zenith side of the satellite.
8. 8 . The system of claim 1 , wherein the bracket assembly further comprises a biasing mechanism, and wherein the biasing mechanism is configured to bias at least one of the first bracket and the second bracket to the deployed position.
9. 9 . The system of claim 8 , wherein the biasing mechanism comprises a spring-biasing mechanism, wherein the spring-biasing mechanism comprises at least one spring urging the first bracket and the second bracket to the deployed position.
10. 10 . The system of claim 1 , wherein the bracket assembly further comprises at least one motor, wherein the at least one motor is operable to position at least one of the first solar array and the second solar array to the deployed position.
11. 11 . The system of claim 1 , wherein the second bracket comprises a third section and a fourth section angled relative to the third section.
12. 12 . The system of claim 11 , wherein an angle between the third section and the fourth section is an obtuse angle.
13. 13 . A method, comprising: deploying a system to a predetermined altitude, wherein the system comprises: a satellite; a first solar array, wherein the first solar array comprises at least a first solar panel; a second solar array, wherein the second solar array comprises at least a second solar panel; a boom having a first end and a second end opposite the first end, wherein the first end connects to the satellite; and a bracket assembly, wherein the bracket assembly comprise a first bracket, a second bracket, and a third bracket, wherein the first bracket connects the first solar array to the third bracket, wherein the first bracket comprises a first section and a second section, wherein the second section is angled relative to the first section, and wherein an angle between the first section and the second section is an acute angle, wherein the second bracket connects the second solar array to the third bracket, and wherein the third bracket connects the first bracket and the second bracket to the second end of the boom; and reorienting the first bracket and the second bracket, thereby to move the first solar array and the second solar array from a stowed position to a deployed position, wherein in the deployed position, the first and second solar arrays are oriented at a predetermined angle.
14. 14 . The method of claim 13 , wherein the boom comprises an extendable boom.
15. 15 . The method of claim 14 , wherein the extendable boom comprises at least one telescoping tube.
16. 16 . The method of claim 13 , wherein the predetermined angle is between 15 and 45 degrees from zenith.
17. 17 . The method of claim 13 , wherein the bracket assembly further comprises a biasing mechanism, and wherein the biasing mechanism is configured to bias at least one of the first bracket and the second bracket to the deployed position.
18. 18 . The method of claim 13 , wherein the bracket assembly further comprises at least one motor, wherein the at least one motor is operable to position at least one of the first solar array and the second solar array to the deployed position.

Description

FIELD OF THE INVENTION The field of the invention relates to space vehicles, and, more particularly, to space vehicles, such as satellites, with solar arrays. BACKGROUND OF THE INVENTION Space vehicles such as satellites typically utilize solar arrays to generate electricity for the operation of vehicle systems. Solar arrays generate an amount of electricity that is roughly in proportion to their surface area. Thus, solar arrays are typically positioned in a stowed position for launch in order to provide sufficient launch performance and are then deployed after the vehicle has reached a suitable location in space. SUMMARY OF THE INVENTION The Claims, rather than the Summary, define covered embodiments of the present invention. The Summary is a high-level overview of various aspects of the invention, and introduces some concepts that are further described in the Detailed Description below. The Summary is not intended to identify key or essential features of the claimed subject matter, and also is not intended to be used in isolation to determine the scope of the claimed subject matter. Instead, the claimed subject matter should be understood by reference to appropriate portions of the Specification and drawings, as well as to each claim. In some embodiments, a space vehicle includes a body; an extendable boom coupled to the body; a bracket coupled to an end of the extendable boom opposite the body; and a solar array coupled to the bracket; wherein the bracket is configured to position the solar array at a desired orientation. In some embodiments, the present invention provides a system, comprising: a satellite; a first solar array, wherein the first solar array comprises at least a first solar panel; a second solar array, wherein the second solar array comprises at least a second solar panel; a boom having a first end and a second end opposite the first end, wherein the first end connects to the satellite; and a bracket assembly, wherein the bracket assembly comprise a first bracket, a second bracket, and a third bracket, wherein the first bracket connects the first solar array to the third bracket, wherein the second bracket connects the second solar array to the third bracket, and wherein the third bracket connects the first bracket and the second bracket to the second end of the boom, wherein the bracket assembly is configured to reorient the first solar array and the second solar array from a stowed position to a deployed position, and wherein in the deployed position, the first and second solar arrays are oriented at a predetermined angle. In some embodiments, the boom comprises an extendable boom. In some embodiments, the extendible boom comprises at least one telescoping tube. In some embodiments, the extendible boom comprises a plurality of telescoping tubes. In some embodiments, the first solar array further comprises a third solar panel, and the third solar panel is foldable relative to the first solar panel. In some embodiments, the second solar array further comprises a fourth solar panel, and the fourth solar panel is foldable relative to the second solar panel. In some embodiments, the satellite has a zenith side and an earth side, wherein the zenith side is configured to face away from the earth when the satellite is in orbit around the earth, wherein the earth side is configured to face toward the earth when the satellite is in orbit around the earth, and the first end of the boom is connected to the zenith side of the satellite. In some embodiments, the bracket assembly further comprises a biasing mechanism, wherein the biasing mechanism is configured to bias at least one of the first bracket and the second bracket to the deployed position. In some embodiments, the biasing mechanism comprises a spring-biasing mechanism, wherein the spring-biasing mechanism comprises at least one spring urging the first bracket and the second bracket to the deployed position. In some embodiments, the bracket assembly further comprises at least one motor, wherein the at least one motor is operable to position at least one of the first solar array and the second solar array to the deployed position. In some embodiments, the bracket assembly further comprises two motors, wherein one of the motors is operable to position the first solar array to the deployed position, and the other motor is operable to position the second solar array to the deployed position. In some embodiments, the first bracket comprises a first section and a second section angled relative to the first section. In some embodiments, an angle between the first section and the second section is an acute angle. In some embodiments, the second bracket comprises a third section and a fourth section angled relative to the third section. In some embodiments, an angle between the third section and the fourth section is an obtuse angle. In some embodiments, the present invention provides a method, comprising: deploying a system to a predetermined altitu