초록 ▼

A spacecraft system may include a storage portion (e.g., a first portion and a second portion) and a solar array apparatus that may be configurable in at least a stowed configuration and a deployed configuration. The solar array apparatus may include at least one solar array to collect incident radi

A spacecraft system may include a storage portion (e.g., a first portion and a second portion) and a solar array apparatus that may be configurable in at least a stowed configuration and a deployed configuration. The solar array apparatus may include at least one solar array to collect incident radiation when the solar array apparatus is in the deployed configuration. In one or more embodiments, the at least one solar array may extend away from the storage portion. In one or more embodiments, the at least one solar array may extend between the first portion and the second portion. The solar array apparatus may also include an extendable boom operable to extend the at least one solar array apparatus from the stowed configuration to the deployed configuration.

대표청구항 ▼

1. A spacecraft system comprising: a first portion;a second portion, wherein the first and second portions are configured to store one or more electronic components; anda solar array apparatus comprising: at least one solar array coupled to each of the first and second portions, andan extendable boo

1. A spacecraft system comprising: a first portion;a second portion, wherein the first and second portions are configured to store one or more electronic components; anda solar array apparatus comprising: at least one solar array coupled to each of the first and second portions, andan extendable boom coupled to each of the first and second portions,wherein the solar array apparatus is configurable in at least a stowed configuration and a deployed configuration, wherein the at least one solar array extends between the first portion and the second portion to collect incident radiation when the solar array apparatus is in the deployed configuration, wherein the extendable boom extends between the first portion and the second portion when the solar array apparatus is in the stowed configuration and the deployed configuration, wherein the first and second portions are located closer to each other when the solar array apparatus is in the stowed configuration than when in the deployed configuration, wherein the first and second portions are located farther away from each other when the solar array apparatus is in the deployed configuration than when in the stowed configuration. 2. The system of claim 1, wherein the extendable boom is biased to extend along a boom axis, wherein the extendable boom is operable to configure the solar array apparatus from the stowed configuration to the deployed configuration, wherein the extendable boom is restricted from movement when the solar array apparatus is in the stowed configuration, and wherein the extendable boom is released to extend along the boom axis to configure the solar array apparatus in the deployed configuration. 3. The system of claim 1, wherein the solar array apparatus further comprises a release mechanism, wherein the release mechanism restricts movement of the solar array apparatus when the solar array apparatus is in the stowed configuration and the release mechanism releases the restriction of the movement of the solar array apparatus such that the solar array apparatus is configurable in the deployed configuration. 4. The system of claim 1, wherein the solar array apparatus is biased to be configured in the deployed configuration, wherein the solar array apparatus further comprises a deployment actuator apparatus configured to restrict the at least one solar array from movement when the solar array apparatus is in the stowed configuration, and wherein the deployment actuator apparatus is configured to release the at least one solar array to configure the solar array apparatus in the deployed configuration. 5. The system of claim 1, wherein the first portion, the solar array apparatus, and the second portion are arranged along a spacecraft axis, wherein a perpendicular axis is perpendicular to the spacecraft axis, wherein a first moment of inertia is defined along the spacecraft axis and a second moment of inertia is defined along the perpendicular axis, wherein the second moment of inertia is greater than the first moment of inertia and results in a passive attitude orientation from gravity gradient forces. 6. The system of claim 1, wherein the at least one solar array extends along a solar array axis, wherein the at least one solar array defines a solar array width extending perpendicular to the solar array axis that is greater than a width of the first and second portion extending perpendicular to the solar array axis when the solar array apparatus is in the deployed configuration. 7. The system of claim 1, wherein the at least one solar array comprises thin-film photovoltaics. 8. The system of claim 1, wherein the at least one solar array is rolled up when the solar array apparatus is in the stowed configuration and the at least one solar array is unrolled when the solar array apparatus is in the deployed configuration. 9. A spacecraft system comprising: a storage portion defining an interior space and configured to be coupled to one or more payload portions configured to store one or more electronic components;a first solar array apparatus; anda second solar array apparatus, wherein each of the first and second solar array apparatus comprise: at least one solar array coupled to the storage portion, andan extendable boom coupled to the storage portion and couplable to the at least one solar array;wherein the first and second solar array apparatus are configurable in at least a stowed configuration and a deployed configuration, wherein the at least one solar array of the first and second solar array apparatus is extended away from the storage portion outside of the interior space of the storage portion to collect incident radiation when the first and second solar array apparatus are in the deployed configuration, wherein the first and second solar array apparatus are stored within the interior space of the storage portion when the first and second solar array apparatus are in the stowed configuration, wherein the extendable booms of the first and second solar array apparatus extend along a boom axis when in the deployed configuration,wherein the extendable booms of the first and second solar array apparatus provide support to the at least one solar arrays of the first and second solar array apparatus when the first and second solar array apparatus are in the deployed configuration. 10. The system of claim 9, wherein the extendable boom of the first and second solar array apparatus is biased to extend along a boom axis and is operable to configure the first and second solar array apparatus from the stowed configuration to the deployed configuration, wherein the extendable boom is restricted from movement when the first and second solar array apparatus is in the stowed configuration, and wherein the extendable boom is released to extend along the corresponding boom axis to configure the first and second solar array apparatus in the deployed configuration. 11. The system of claim 9, wherein the extendable boom comprises: a web portion,a first flange portion extending from the web portion,a second flange portion extending from the web portion opposite the first flange portion,a third flange portion extending from the web portion, anda fourth flange portion extending from the web portion opposite the third flange portion,wherein the first flange portion, the second flange portion, and the web portion define a first concave surface and the third flange portion, the fourth flange portion, and the web portion define a second concave surface facing opposite the first concave surface when the first and second solar array apparatus are in the deployed configuration. 12. The system of claim 9, wherein each of the first and second solar array apparatus further comprises a release mechanism, wherein the release mechanism restricts movement of the first and second solar array apparatus when the first and second solar array apparatus are in the stowed configuration and the release mechanism releases the restriction of the movement of the first and second solar array apparatus such that the first and second solar array apparatus are configurable in the deployed configuration. 13. The system of claim 9, wherein the first and second solar array apparatus are located entirely within the interior space of the storage portion when the first and second solar array apparatus are in the stowed configuration. 14. The system of claim 9, wherein the storage portion comprises 2U of a CubeSat. 15. A spacecraft system comprising: a storage portion defining an interior space and configured to be coupled to one or more payload portions configured to store one or more electronic components; anda solar array apparatus comprising: at least one solar array coupled to the storage portion, andan extendable boom coupled to the storage portion and couplable to the at least one solar array, wherein the extendable boom is biased to extend along a boom axis and comprises: a web portion,a first flange portion extending from the web portion,a second flange portion extending from the web portion opposite the first flange portion,a third flange portion extending from the web portion, anda fourth flange portion extending from the web portion opposite the third flange portion, wherein the first flange portion, the second flange portion, and the web portion define a first concave surface and the third flange portion, the fourth flange portion, and the web portion define a second concave surface facing opposite the first concave surface when the solar array apparatus is in the deployed configuration;wherein the solar array apparatus is configurable in at least a stowed configuration and a deployed configuration, wherein the at least one solar array of the solar array apparatus is extended away from the storage portion outside of the interior space of the storage portion to collect incident radiation when the solar array apparatus is in the deployed configuration, wherein the solar array apparatus is stored within the interior space of the storage portion when the solar array apparatus is in the stowed configuration,wherein the extendable boom provides support to the at least one solar array and is operable to configure the at least one solar array to extend away from the storage portion when the solar array apparatus moves from the stowed configuration to the deployed configuration. 16. The system of claim 15, wherein the extendable boom is configurable in at least a normal, linear configuration and a nonlinear configuration, wherein the first flange portion, second flange portion, and web portion extends along the boom axis when in the normal, linear configuration and extends nonlinearly when in the nonlinear configuration. 17. The system of claim 15, wherein the extendable boom is symmetric about at least one symmetry axis perpendicular to the boom axis when in a normal, linear configuration. 18. The system of claim 15, wherein the extendable boom is symmetric about at least two symmetry axes, each of the at least two symmetry axes perpendicular to the boom axis when in a normal, linear configuration. 19. The system of claim 15, wherein the solar array apparatus further comprises a release mechanism, wherein the release mechanism restricts movement of the solar array apparatus when the solar array apparatus is in the stowed configuration and the release mechanism releases the restriction of the movement of the solar array apparatus such that the solar array apparatus is configurable in the deployed configuration. 20. The system of claim 15, wherein the solar array apparatus is located entirely within the interior space of the storage portion when the solar array apparatus is in the stowed configuration.