Flexible array support structure
View Patent ↗Extensible solar arrays configured to support one or more rollable solar panel units and that feature yoke segments and array segments that are configured to be stowed with their long axes substantially parallel to a spacecraft's roll axis. The yoke segments and array segments may be transitioned to a deployed configuration where the yoke segments are substantially perpendicular to the position the yoke segments were in in the stowed configuration, and the array segments are substantially perpendicular to the yoke segments. Some implementations of the extensible solar arrays may also include a rigid solar panel supported by one of the yoke segments.
1. An extensible boom structure comprising:
at least one yoke segment, each yoke segment having a yoke axis extending between a first end of the yoke segment and a second end of the yoke segment;
a rigid solar panel with a solar power-generating surface; and
at least one array segment, each array segment having an array segment axis extending between a first end of the array segment and a second end of the array segment, wherein:
the at least one yoke segment forms a first extensible assembly with a proximal end and a distal end,
the at least one array segment forms at least one second extensible assembly,
the proximal end of the first extensible assembly is configured to be rotatably connected with a side of a spacecraft, the spacecraft having a pitch axis, a roll axis, and a yaw axis that are all orthogonal to one another,
the at least one second extensible assembly is rotatably connected with the first extensible assembly at the distal end of the first extensible assembly,
the at least one yoke segment and the at least one array segment are movable from a stowed configuration to a deployed configuration, wherein the extensible boom structure is configured such that when the proximal end of the first extensible assembly is connected with the side of the spacecraft and is in the deployed configuration, the at least one yoke segment is substantially aligned with the pitch axis and extends away from the spacecraft and each array segment axis is substantially perpendicular to the pitch axis,
the rigid solar panel is mounted to one of the at least one yoke segment, and
the solar power-generating surface faces away from the spacecraft when the extensible boom structure is mounted to the side of the spacecraft and is in the stowed configuration.
2. The extensible boom structure of claim 1 , further comprising one or more rollable solar panel units, each rollable solar panel unit connected with one of the at least one array segment such that the rollable solar panel unit moves with the array segment with which the rollable solar panel unit is connected.
3. The extensible boom structure of claim 1 , wherein at least one of the at least one second extensible assembly includes at least two array segments that:
are rotatably connected end-to-end,
unfold in a concertinaed manner during movement from the stowed configuration to the deployed configuration, and
are substantially in-line with one another and arranged end-to-end in the deployed configuration.
4. The extensible boom structure of claim 3 , wherein:
there are two second extensible assemblies,
one of the two second extensible assemblies is configured to unfold in a first direction substantially perpendicular to the yoke axis of the yoke segment closest to the distal end, and
the other of the two second extensible assemblies is configured to unfold in a second direction opposite the first direction.
5. The extensible boom structure of claim 1 , wherein the rigid solar panel is mounted to the yoke segment that is furthest from the side of the spacecraft when the extensible boom structure is in the stowed configuration.
6. The extensible boom structure of claim 1 , wherein the at least one array segment includes only one array segment and the rigid solar panel is rotatably mounted to the yoke segment so as to be rotatable about an axis substantially parallel to the yoke axis of the yoke segment when in the deployed configuration.
7. A spacecraft comprising:
a main body, the main body having a yaw axis, a roll axis, and a pitch axis that are all mutually orthogonal to one another;
a first extensible boom structure including:
at least one yoke segment, each yoke segment having a yoke axis extending between a first end of the yoke segment and a second end of the yoke segment;
a rigid solar panel with a solar power-generating surface; and
at least one array segment, each array segment having an array segment axis extending between a first end of the array segment and a second end of the array segment,
wherein:
the at least one yoke segment forms a first extensible assembly with a proximal end and a distal end,
the at least one array segment forms at least one second extensible assembly,
the proximal end of the first extensible assembly is rotatably connected with a first side of the main body,
the at least one second extensible assembly is rotatably connected with the first extensible assembly at the distal end of the first extensible assembly,
the at least one yoke segment and the at least one array segment are movable from a stowed configuration to a deployed configuration, wherein, when the first extensible boom structure is in the deployed configuration, the at least one yoke segment is substantially aligned with the pitch axis and each array segment axis is substantially perpendicular to the pitch axis,
the rigid solar panel is mounted to one of the at least one yoke segment, and
the solar power-generating surface faces away from the spacecraft when the first extensible boom structure is in the stowed configuration.
8. The spacecraft of claim 7 , further comprising a second extensible boom structure substantially the same as the first extensible boom structure wherein the proximal end of the first extensible assembly of the second extensible boom structure is rotatably connected with a second side of the spacecraft opposite the first side.
9. The spacecraft of claim 7 , further comprising at least one rollable solar panel unit, wherein the at least one rollable solar panel unit:
includes a flexible solar power-generating element and a deployment spool configured to rotate about a roll-up axis of the rollable solar panel unit,
is configured to deploy the flexible solar power-generating element along an extension axis substantially perpendicular to the roll-up axis, and
is connected with one of the array segments such that the roll-up axis of the rollable solar panel unit is substantially parallel to the array segment axis of the array segment.
10. The spacecraft of claim 9 , wherein the flexible solar power-generating element is:
wound around the deployment spool when the first extensible boom structure is in the stowed configuration, and
substantially unwound from the deployment spool and extended along the extension axis in a direction substantially normal to the first side of the main body when the first extensible boom structure is in the deployed configuration.
11. The spacecraft of claim 7 , wherein each second extensible assembly includes a plurality of array segments that:
are rotatably connected end-to-end,
unfold in a concertinaed manner during movement from the stowed configuration to the deployed configuration, and
are substantially in line with one another and arranged end-to-end in the deployed configuration.
12. The spacecraft of claim 11 , wherein:
the first extensible boom structure includes two second extensible assemblies,
one of the two second extensible assemblies is configured to unfold in a first direction substantially perpendicular to the at least one yoke segment, and
the other of the two second extensible assemblies is configured to unfold in a second direction opposite the first direction.
13. The spacecraft of claim 7 , wherein the at least one array segment includes only one array segment and the rigid solar panel is rotatably mounted to the yoke segment so as to be rotatable about an axis substantially parallel to the yoke axis of the yoke segment when in the deployed configuration.
14. An extensible boom structure comprising:
at least one yoke segment, each yoke segment having a yoke axis extending between a first end of the yoke segment and a second end of the yoke segment; and
at least three array segments, each array segment having an array segment axis extending between a first end of the array segment and a second end of the array segment, wherein:
the at least one yoke segment forms a first extensible assembly with a proximal end and a distal end,
the at least three array segments form two second extensible assemblies, one second extensible assembly having at least one array segment and the other second extensible assembly having at least two array segments that are rotatably connected end-to-end, that unfold in a concertinaed manner during movement from the stowed configuration to the deployed configuration, and that are substantially in-line with one another and arranged end-to-end in the deployed configuration,
one of the two second extensible assemblies is configured to unfold in a first direction substantially perpendicular to the yoke axis of the yoke segment closest to the distal end,
the other of the two second extensible assemblies is configured to unfold in a second direction opposite the first direction,
the proximal end of the first extensible assembly is configured to be rotatably connected with a side of a spacecraft, the spacecraft having a pitch axis, a roll axis, and a yaw axis that are all orthogonal to one another,
each of the second extensible assemblies is rotatably connected with the first extensible assembly at the distal end of the first extensible assembly, and
the at least one yoke segment and the at least one array segment are movable from a stowed configuration to a deployed configuration, wherein the extensible boom structure is configured such that when the proximal end of the first extensible assembly is connected with the side of the spacecraft and is in the deployed configuration, the at least one yoke segment is substantially aligned with the pitch axis and extends away from the spacecraft and each array segment axis is substantially perpendicular to the pitch axis.
15. The extensible boom structure of claim 14 , the extensible boom structure further comprising a rigid solar panel with a solar power-generating surface, wherein:
the rigid solar panel is mounted to one of the at least one yoke segment, and
when the extensible boom structure is mounted to the side of the spacecraft and is in the stowed configuration, the solar power-generating surface faces away from the spacecraft.
16. The extensible boom structure of claim 15 , wherein the at least one array segment includes only one array segment and the rigid solar panel is rotatably mounted to the yoke segment so as to be rotatable about an axis substantially parallel to the yoke axis of the yoke segment when in the deployed configuration.
17. The extensible boom structure of claim 14 , further comprising one or more rollable solar panel units, each rollable solar panel unit connected with one of the at least one array segment such that the rollable solar panel unit moves with the array segment with which the rollable solar panel unit is connected.
18. The extensible boom structure of claim 14 , wherein at least one of the at least one second extensible assembly includes at least two array segments that:
are rotatably connected end-to-end,
unfold in a concertinaed manner during movement from the stowed configuration to the deployed configuration, and
are substantially in-line with one another and arranged end-to-end in the deployed configuration.
19. A spacecraft comprising:
a main body, the main body having a yaw axis, a roll axis, and a pitch axis that are all mutually orthogonal to one another;
a first extensible boom structure including:
at least one yoke segment, each yoke segment having a yoke axis extending between a first end of the yoke segment and a second end of the yoke segment; and
at least three array segments, each array segment having an array segment axis extending between a first end of the array segment and a second end of the array segment, wherein:
the at least one yoke segment forms a first extensible assembly with a proximal end and a distal end,
the at least three array segments form two second extensible assemblies, one second extensible assembly having at least one array segment and the other second extensible assembly having at least two array segments that are rotatably connected end-to-end, that unfold in a concertinaed manner during movement from the stowed configuration to the deployed configuration, and that are substantially in-line with one another and arranged end-to-end in the deployed configuration,
one of the two second extensible assemblies is configured to unfold in a first direction substantially perpendicular to the yoke axis of the yoke segment closest to the distal end,
the other of the two second extensible assemblies is configured to unfold in a second direction opposite the first direction,
the proximal end of the first extensible assembly is rotatably connected with a first side of the main body,
each of the second extensible assemblies is rotatably connected with the first extensible assembly at the distal end of the first extensible assembly, and
the at least one yoke segment and the at least one array segment are movable from a stowed configuration to a deployed configuration, wherein, when the first extensible boom structure is in the deployed configuration, the at least one yoke segment is substantially aligned with the pitch axis and each array segment axis is substantially perpendicular to the pitch axis.
20. The spacecraft of claim 19 , the spacecraft further comprising a rigid solar panel with a solar power-generating surface, wherein:
the rigid solar panel is mounted to one of the at least one yoke segment, and
when the first extensible boom structure is mounted to the first side of the spacecraft and is in the stowed configuration, the solar power-generating surface faces away from the spacecraft.
21. The spacecraft of claim 19 , further comprising a second extensible boom structure substantially the same as the first extensible boom structure wherein the proximal end of the first extensible assembly of the second extensible boom structure is rotatably connected with a second side of the spacecraft opposite the first side.
22. The spacecraft of claim 19 , further comprising at least one rollable solar panel unit, wherein the at least one rollable solar panel unit:
includes a flexible solar power-generating element and a deployment spool configured to rotate about a roll-up axis of the rollable solar panel unit,
is configured to deploy the flexible solar power-generating element along an extension axis substantially perpendicular to the roll-up axis, and
is connected with one of the array segments such that the roll-up axis of the rollable solar panel unit is substantially parallel to the array segment axis of the array segment.
23. The spacecraft of claim 22 , wherein the flexible solar power-generating element is:
wound around the deployment spool when the first extensible boom structure is in the stowed configuration, and
substantially unwound from the deployment spool and extended along the extension axis in a direction substantially normal to the first side of the main body when the first extensible boom structure is in the deployed configuration.
24. The spacecraft of claim 19 , wherein each second extensible assembly includes a plurality of array segments that:
are rotatably connected end-to-end,
unfold in a concertinaed manner during movement from the stowed configuration to the deployed configuration, and
are substantially in line with one another and arranged end-to-end in the deployed configuration.