Solar array assemblies and systems and methods for deploying solar cell arrays from a spacecraft. A solar cell panel assembly comprises a first flexible solar panel and a rotational member. A first extension assembly is disposed proximate to a first end of the rotational member and a second extensi
Solar array assemblies and systems and methods for deploying solar cell arrays from a spacecraft. A solar cell panel assembly comprises a first flexible solar panel and a rotational member. A first extension assembly is disposed proximate to a first end of the rotational member and a second extension assembly is disposed proximate to a second end of the rotational member. The solar cell panel assembly further comprises a first support member and a second support member. The first end of the first support member is coupled to the first end of the rotational member and the first end of the second support member is coupled to the second end of the rotational member. The second ends of the support members are coupled to the first flexible solar panel. A tether assembly couples the extension assemblies to the support members.
대표청구항▼
What is claimed is: 1. A solar cell panel assembly for deployment from a spacecraft, the solar cell panel assembly comprising: a first flexible solar panel comprising a plurality of solar cells; a rotational member having a first end and a second end; a first extension assembly disposed proximate
What is claimed is: 1. A solar cell panel assembly for deployment from a spacecraft, the solar cell panel assembly comprising: a first flexible solar panel comprising a plurality of solar cells; a rotational member having a first end and a second end; a first extension assembly disposed proximate to said first end of said rotational member; a second extension assembly disposed proximate to said second end of said rotational member; a first support member and a second support member, each having a first end and a second end, said first end of said first support member coupled to said first end of said rotational member and said first end of said second support member coupled to said second end of said rotational member, wherein said second ends of said first and said second support members are coupled to said first flexible solar panel; and a tether assembly that couples said first and second extension assemblies to said first and second support members. 2. The solar cell panel assembly of claim 1, said first and second extension assemblies each comprising an extension member, wherein when in a deployed mode said extension member is disposed substantially perpendicularly to said first and second support members. 3. The solar cell panel assembly of claim 1, said first and second extension assemblies each comprising a first extension member and a second extension member, wherein when in a deployed mode said first and second extension members are disposed substantially perpendicularly to said first and second support members. 4. The solar cell panel assembly of claim 3, wherein said rotational member is configured to rotate about an axis and said first and second extension members each comprises a toothed surface, and wherein said solar cell panel assembly further comprises: a first gear operatively connected to said rotational member and configured to rotate about said axis when said rotational member rotates; a second gear in meshing engagement with said first gear; a third gear connected to said second gear and configured to rotate when said second gear rotates, said third gear in meshing engagement with said toothed surfaces of said first and second extension members. 5. The solar cell panel assembly of claim 3, wherein said rotational member is configured to rotate about a first axis and wherein said solar cell panel assembly further comprises a first rotating wheel connected to a first end of said first extension member and a first end of said second extension and configured to rotate about a second axis. 6. The solar cell panel assembly of claim 5, wherein said first axis and said second axis are the same axis. 7. The solar cell panel assembly of claim 3, further comprising a housing coupled to said rotational member wherein, when in a stored mode, at least a portion of said first and second extension members are disposed within said housing. 8. The solar cell panel assembly of claim 1, wherein said rotational member has a cylinder shape. 9. The solar cell panel assembly of claim 1, wherein, when the solar cell panel assembly is in a stored mode, said flexible solar panel is wound about said rotational member. 10. The solar cell panel assembly of claim 9, wherein said rotational member has an axis about which said rotational member is configured to rotate and wherein, during deployment of said solar cell panel assembly, said rotational member rotates about said axis so that said flexible solar panel is unwound from said rotational member. 11. The solar cell panel assembly of claim 1, further comprising: a second flexible solar panel having a plurality of solar cells; and a third support member and a fourth support member, each having a first end and a second end, said first end of said third support member coupled to said first end of said rotational member and said first end of said fourth support member coupled to said second end of said rotational member, wherein said second ends of said third and fourth support members are coupled to said second flexible solar panel. 12. The solar cell panel assembly of claim 11, wherein an end of said first flexible solar panel and an end of said second flexible solar panel are coupled to said rotational member. 13. The solar cell panel assembly of claim 11, wherein said first flexible solar panel and said second flexible solar panel are integral. 14. The solar cell panel assembly of claim 1, said tether assembly comprising a first tether apparatus and a second tether apparatus, wherein said first tether apparatus is coupled to said first support member and is configured to exert a compressive force on said first support member and wherein said second tether apparatus is coupled to said second support member and is configured to exert a compressive force on said second support member. 15. The solar cell panel assembly of claim 14, wherein said first tether apparatus is coupled to said first extension assembly and said second tether apparatus is coupled to said second extension assembly. 16. The solar cell panel assembly of claim 15, said first and second extension assemblies each comprising a first extension member and a second extension member, and said first and second tether apparatus each comprising a first tether member and a second tether member, wherein said first tether member of said first tether apparatus couples said first extension member of said first extension assembly to said first support member, said second tether member of said first tether apparatus couples said second extension member of said first extension assembly to said first support member, said first tether member of said second tether apparatus couples said first extension member of said second extension assembly to said second support member, and said second tether member of said second tether apparatus couples said second extension member of said second extension assembly to said second support member. 17. The solar cell panel assembly of claim 1, wherein when the solar cell panel assembly is in a stored mode said first and second support members are wound about said rotational member. 18. The solar cell panel assembly of claim 1, further comprising a first motor assembly operatively connected to said rotational member and configured to rotate said rotational member about an axis. 19. The solar cell panel assembly of claim 18, further comprising a second motor assembly operatively connected to at least one of said first extension assembly and said second extension assembly and configured to cause said at least one of said first and second extension assemblies to move from a stored position to a deployed position. 20. The solar cell panel assembly of claim of claim 19, wherein said first motor assembly and said second motor assembly are the same. 21. The solar cell panel assembly of claim 1, further comprising a housing coupled to said rotational member and a hinge assembly coupled to said housing. 22. The solar cell panel assembly of claim 21, further comprising a motor assembly operatively connected to said hinge assembly and configured to cause the solar cell panel assembly to rotate about an axis of said hinge assembly. 23. The solar cell panel assembly of claim 21, said hinge assembly comprising a pin and clevis device. 24. The solar cell panel assembly of claim 21, further comprising a locking device connected to said housing. 25. The solar cell panel assembly of claim 24, said locking device disposed substantially remotely from said hinge assembly. 26. The solar cell panel assembly of claim 1, further comprising an end member connected to an end of said flexible solar panel and said second ends of said first and second support members. 27. The solar cell panel assembly of claim 1, wherein said first and second support members each comprise a storable tubular extendible member (Bi-stem). 28. The solar cell panel assembly of claim 1, wherein said first and second support members each comprise telescoping members. 29. The solar cell panel assembly of claim 1, wherein said first and second support members each comprise folding members. 30. A solar cell array system for deployment from a spacecraft, the solar cell array system having a first and a second solar cell panel assembly, each solar cell panel assembly comprising: a flexible solar panel; a rotational member connected to said flexible solar panel, said rotational member having a first end and a second end; a hinge assembly disposed proximate to at least one of said first end and said second end of said rotational member, wherein said hinge assembly of the first solar cell panel assembly is connected to said hinge assembly of the second solar cell panel assembly; and a locking device disposed proximate to at least one of said first end and said second end of said rotational member, wherein said locking assembly of the first solar cell panel assembly is configured to lock with said locking assembly of the second solar cell panel assembly. 31. The solar cell array system of claim 30, said hinge assembly comprising a pin and clevis device. 32. The solar cell array system of claim 30, the first and second solar cell panel assemblies each further comprising a first housing portion disposed at said first end of said rotational member and a second housing portion disposed at said second end of said rotational member, wherein said hinge assembly of the first solar cell panel assembly is connected to said second housing portion and said hinge assembly of the second solar cell panel assembly is connected to first housing portion. 33. The solar cell array system of claim 32, wherein said locking device of the first solar cell panel assembly is connected to said second housing portion and said locking device of the second solar cell panel assembly is connected to said first housing portion. 34. The solar cell array system of claim 32, wherein said first housing portion and said second housing portion of the first solar cell panel assembly are connected and said first housing portion and said second housing portion of the second solar cell panel assembly are connected. 35. The solar cell array system of claim 32, further comprising a deployment yoke that couples a portion of the spacecraft to said first housing portion of the first solar cell panel assembly. 36. The solar cell array system of claim 32, wherein said first and second housing portions of the first solar cell panel assembly are electrically coupled and said first and second housing portions of the second solar cell panel assembly are electrically coupled, and wherein said first housing portion, said second housing portion, and said locking devices of the first and second solar cell panel assemblies are comprised of electrically conductive material such that the first and second solar cell panel assemblies form an electrically conductive path. 37. The solar cell array system of claim 30, further comprising a deployment yoke that couples a portion of the spacecraft to the first solar cell panel assembly. 38. The solar cell array system of claim 30, said rotational members of the first and the second solar cell panel assemblies each having a longitudinal axis, wherein, when the solar cell panel system is in a stored mode, said longitudinal axes of said rotational members are disposed substantially parallel to a surface of a portion of the spacecraft. 39. The solar cell array system of claim 38, wherein, when the solar cell panel system is in a stored mode, said longitudinal axis of said rotational member of the first solar cell panel assembly is disposed substantially parallel to said longitudinal axis of said rotational member of the second solar cell panel assembly. 40. The solar cell array system of claim 30, said rotational members of the first and the second solar cell panel assemblies each having a longitudinal axis, wherein, when the solar cell panel system is in a deployed mode, said longitudinal axes of the rotational members are disposed substantially perpendicular to a surface of a portion of the spacecraft. 41. A solar cell array system for deployment from a spacecraft, the solar cell array system comprising: a solar cell panel assembly comprising: a flexible solar panel having a first end, a second end, and a first longitudinal axis; a rotating member coupled to said first end of said flexible solar panel, said rotating member having a second longitudinal axis and a first and a second end, wherein, when said solar cell panel assembly is in a stored mode, said flexible solar panel is wound about said rotating member and, when said solar cell panel is being deployed, said rotating member is configured to rotate about said second longitudinal axis so that said flexible solar panel may be unwound from said rotating member; a first and second longitudinal stabilizing means for stabilizing said flexible solar panel along said first longitudinal axis, said first longitudinal stabilizing means coupled to said first end of said rotating member and said second longitudinal means coupled to said second end of said rotating member; a first tether means for applying a compressive force to an end of said first longitudinal stabilizing means; and a second tether means for applying a compressive force to an end of said second longitudinal stabilizing means; and a deployment means for deploying said solar cell panel assembly from said spacecraft. 42. The solar cell array system of claim 41, further comprising: a first extension assembly disposed proximate to said first end of said rotating member and coupled to said first tether means; and a second extension assembly disposed proximate to said second end of said rotating member and coupled to said second tether means. 43. The solar cell array system of claim 41, said rotating member comprising a cylinder-shaped member. 44. The solar cell array system of claim 41, wherein said first and second longitudinal stabilizing means comprise telescoping members. 45. The solar cell array system of claim 41, wherein said first and second longitudinal stabilizing means comprise folding members. 46. The solar cell array system of claim 41, wherein said first and second longitudinal stabilizing means comprise Bi-stems. 47. The solar cell array system of claim 41, wherein, when said solar cell panel assembly is in a stored mode, said first and second longitudinal stabilizing means are wound about said rotating member and, when said solar cell panel is being deployed, said first and second longitudinal stabilizing means are unwound from said rotating member. 48. The solar cell array system of claim 41, each of said first tether means and said second tether means comprising a tether cable, wherein an end of said tether cable of said first tether means is coupled to an end of said first longitudinal stabilizing means and wherein an end of said tether cable of said second tether means is coupled to an end of said second longitudinal stabilizing means. 49. The solar cell array system of claim 41, each of said first tether means and said second tether means comprising a first tether cable and a second tether cable, wherein an end of each of said first tether cable and said second tether cable of said first tether means is coupled to an end of said first longitudinal stabilizing means and wherein an end of each of said first tether cable and said second tether cable of said second tether means is coupled to an end of said second longitudinal stabilizing means. 50. A method for deploying a stowable solar cell array from a spacecraft, the method comprising the steps of: configuring the array as a plurality of flexible solar cell panels, wherein each flexible solar cell panel is wound about a rotating member, the rotating members coupled in series; orienting said rotating members along an imaginary substantially straight line that is substantially perpendicular to a surface of the spacecraft; rotating said rotating members, causing each of said plurality of flexible solar cell panels to unwind from said rotating members; extending at least two support members along each of said plurality of flexible solar cell panels; and applying a compressive force to each of said at least two support members. 51. The method of claim 50, the step of orienting comprising the step of rotating hinge assemblies coupled to said rotating members. 52. The method of claim 50, the step of orienting comprising the step of interlocking locking devices coupled to said rotating members. 53. The method of claim 50, the step of applying comprising the steps of: extending a first extension assembly disposed proximate to a first end of a first of said at least two support members; extending a second extension assembly disposed proximate to a first end of a second of said at least two support members; coupling said first extension assembly to a second end of said first of said at least two support members; and coupling said second extension assembly to a second end of said second of said at least two support members.
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