Large-scale space-based solar power station: packaging, deployment and stabilization of lightweight structures

• US 10,340,698 B2
• Filed: 05/14/2015
• Issued: 07/02/2019
• Est. Priority Date: 05/14/2014
• Status: Active Grant

• Current Assignee: California Institute of Technology
• Original Assignee: California Institute of Technology
• Inventors: Pellegrino, Sergio, Atwater, Harry A., Hajimiri, Seyed Ali, Arya, Manan, Lee, Nicolas, Delapierre, Melanie
• Primary Examiner(s): Wong, Jessica B
• Application Number:
  US14/712,812
• Publication Number:
  US 20160376037A1
• Time in Patent Office: 1,510 Days
• Field of Search: 2441595, 136245
• CPC Class Codes: B64G 1/1085 Swarms and constellations
• CPC Class Codes: B64G 1/222 for deploying structures between a stowed and deployed state
• CPC Class Codes: B64G 1/283 using reaction wheels
• CPC Class Codes: B64G 1/286 using control momentum gyroscopes (CMGs)
• CPC Class Codes: B64G 1/36 using sensors, e.g. sun-sensors, horizon sensors
• CPC Class Codes: B64G 1/369 using gyroscopes as attitude sensors
• CPC Class Codes: B64G 1/401 Liquid propellant rocket engines Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415
• CPC Class Codes: B64G 1/403 Solid propellant rocket engines
• CPC Class Codes: B64G 1/405 Ion or plasma engines per se F03H1/00
• CPC Class Codes: B64G 1/407 Solar sailing
• CPC Class Codes: B64G 1/415 Arcjets or resistojets
• CPC Class Codes: B64G 1/428 Power distribution and management
• CPC Class Codes: B64G 1/44 using radiation, e.g. deployable solar arrays
• CPC Class Codes: B64G 1/443 Photovoltaic cell arrays
• CPC Class Codes: B64G 1/66 Arrangements or adaptations of apparatus or instruments, not otherwise provided for
• CPC Class Codes: H01L 31/042 PV modules or arrays of single PV cells supporting structures for PV modules H02S20/00
• CPC Class Codes: H02J 2300/24 of photovoltaic origin
• CPC Class Codes: H02J 3/381 Dispersed generators
• CPC Class Codes: H02J 3/40 Synchronising a generator for connection to a network or to another generator
• CPC Class Codes: H02J 50/23 characterised by the type of transmitting antennas, e.g. directional array antennas or Yagi antennas
• CPC Class Codes: H02J 50/30 : using light, e.g. lasers
• CPC Class Codes: H02J 50/80 : involving the exchange of data, concerning supply or distribution of electric power, between transmitting devices and receiving devices
• CPC Class Codes: H02J 50/90 : involving detection or optimisation of position, e.g. alignment
• CPC Class Codes: H02S 10/40 : Mobile PV generator systems
• CPC Class Codes: H02S 20/25 : Roof tile elements
• CPC Class Codes: H02S 20/30 : Supporting structures being movable or adjustable, e.g. for angle adjustment
• CPC Class Codes: H02S 30/10 : Frame structures
• CPC Class Codes: H02S 30/20 : Collapsible or foldable PV modules
• CPC Class Codes: H02S 40/30 : Electrical components
• CPC Class Codes: H02S 40/36 : characterised by special electrical interconnection means between two or more PV modules, e.g. electrical module-to-module connection
• CPC Class Codes: H02S 40/38 : Energy storage means, e.g. batteries, structurally associated with PV modules
• CPC Class Codes: H02S 40/42 : Cooling means cooling means directly associated or integrated with the PV cell H01L31/052
• CPC Class Codes: Y02B 10/10 : Photovoltaic [PV]
• CPC Class Codes: Y02E 10/52 : PV systems with concentrators
• CPC Class Codes: Y02E 10/56 : Power conversion systems, e.g. maximum power point trackers
• CPC Class Codes: Y02E 70/30 : Systems combining energy storage with energy generation of non-fossil origin

Abstract

A space-based solar power station, a power generating satellite module and/or a method for collecting solar radiation and transmitting power generated using electrical current produced therefrom, and/or compactible structures and deployment mechanisms used to form and deploy such satellite modules and power generation tiles associated therewith are provided. Each satellite module and/or power generation tile may be formed of a compactable structure and deployment mechanism capable of reducing the payload area required to deliver the satellite module to an orbital formation within the space-based solar power station and reliably deploy it once in orbit.

Claims

1. A space-based solar power station comprising:

a plurality of independently operable unconnected compactible satellite modules disposed in space in an orbital array formation, wherein each of the compactible satellite modules comprises;

a plurality of moveably interconnected structural elements each having a finite thickness and are foldable relative to each other along at least one fold axis via a slip-fold and are configured to slip relative to each other in a direction parallel to the at least one fold axis such that the dimensional extent of the satellite modules is compactible;

a plurality of independent power generation tiles disposed on each of the plurality of moveably interconnected structural elements, each of the independent power generation tiles having at least one photovoltaic cell and at least one power transmitter collocated thereon, the at least one photovoltaic cell and the at least one power transmitter in signal communication with each other such that an electrical current generated by the collection of solar radiation by the at least one photovoltaic cell powers the at least one power transmitter, and where each of the at least one power transmitters comprises;

an antenna configured to receive a radio frequency power signal; and

control electronics in signal communication with the antenna and configured to control the phase of the radio frequency power signal such that the at least one power transmitter is in phased signal coordination with at least one other power transmitter on the plurality of other power generation tiles thereby forming an independent phased array of power transmitters;

wherein the independent phased array of power transmitters is configured to transmit a power signal to a remote location.

2. The space-based power station of claim 1, wherein the folded movably interconnected structural elements are further configured to wrap about a wrap axis with a rotational symmetry.

3. The space-based solar power station of claim 1, wherein the plurality of moveably interconnected structural elements are configured to slip a predetermined distance relative to each other.

4. The space-based solar power station of claim 3, wherein the moveably interconnected structural elements further comprise at least one open space formed along at least a portion of the at least one fold axis between the structural elements.

5. The space-based solar power station of claim 4, further comprising interconnections along at least another portion of the at least one fold axis that bridge the at least one open space.

6. The space-based solar power station of claim 5, wherein the interconnections along at least another portion of the at least one fold axis comprise ligament folds.

7. The space-based solar power station of claim 5, wherein the interconnections along at least another portion of the at least one fold axis are at least one hinge selected from the group consisting of latachable, frictionless, and slippage.

8. The space-based solar power station of claim 3, wherein the folded moveably interconnected structural elements form a stack having a first and second longitudinal end running transverse to the fold axis.

9. The space-based solar power station of claim 8, wherein the stack of a plurality of moveably interconnected structural elements is configured to wrap into a curved structure having a bend radius at which plastic deformation of the moveably interconnected structural elements is avoided.

10. The space-based solar power station of claim 9, wherein the bend radius does not exceed a minimum bend radius R_min given by:

11. The space-based solar power station of claim 9, wherein the plurality of moveably interconnected structural elements are configured such that when disposed in a wrapped configuration the first and second longitudinal ends of the stack of a plurality of structural elements undergo no slip relative to each other.

12. The space-based solar power station of claim 1, wherein the plurality of moveably interconnected structural elements are configured to compact such that a packaging efficiency, of the satellite module when in a compacted state, as determined by the ratio of the packaged volume of the compacted satellite module to the material volume of the satellite module, is greater than 50%.

13. The space-based solar power station of claim 12, wherein the moveably interconnected structural elements have a deployed dimensionalized length λ

ranging from 103 to 106 and a dimensionalized spacing ϕ

between the moveably interconnected structural elements in a compacted state between 1 and 1.5 wherein the dimensionalized length and spacing are determined based on the overall packing efficiency.

14. The space-based solar power station of claim 3, wherein each of the plurality of independent power generation tiles further comprise a plurality of moveable interconnection elements;

and where the at least one photovoltaic cell and the at least one power transmitter of each independent power generation tile are movable relative to each other via the moveable interconnection elements.

15. The space-based solar power station of claim 14, wherein the moveable interconnection elements of the power generation tiles are interconnected through one or more resilient members.

16. The space-based solar power station of claim 14, wherein at least the photovoltaic cell and the power transmitter on each power generation tile are disposed on separate moveable interconnection elements such that an offset transverse to the planes of the photovoltaic cell and power transmitter is opened therebetween when the separate moveable elements are displaced.

17. The space-based solar power station of claim 16, wherein the separate moveable elements are interconnected through one or more resilient members.

18. The space-based solar power station of claim 17, wherein the resilient members are springs.

19. The space-based solar power station of claim 18, wherein the resilient members and the power transmitter are configured to compact within the same plane.

20. The space-based solar power station of claim 16, further comprising one or more conductive elements that extend between the offset to conductively couple the power transmitter and the photovoltaic cell.

21. The space-based solar power station of claim 14, wherein each of the independent power generation tiles further comprise one or more collectors configured to concentrate incoming solar radiation onto each of the photovoltaic cells, and wherein the collectors are configured to engage with one or more resilient support structures configured to displace the collectors into and out of the plane of the photovoltaic cell.

22. The space-based power station of claim 1, wherein the moveably interconnected structural elements are under a prestress tensional force, the prestress tensional force being sufficient to resist any out-of-plane spatial deformation of the satellite module.

23. The space-based power station of claim 22, further comprising at least one stabilizing boom arm connected to the plurality of moveably interconnected structural elements wherein the prestress tensional force is distributed across the plurality of moveably interconnected structural elements through the at least one stabilizing boom arm.

24. The space-based power station of claim 22, wherein the prestress tension is distributed across the structural elements by one or more weighted elements being subject to a centrifugal force applied by the rotation of the satellite module.

25. The space-based power station of claim 22, wherein the plurality of moveably interconnected structural elements are interconnected through a plurality of slip-folds each having a slip fold axis, and wherein the prestress tensional force is distributed anisotropically across the plurality of moveably interconnected structural elements such that the tension applied along each slip-fold axis is much greater than the tension applied transverse to each slip-fold axis.

26. The space-based power station of claim 25, wherein the edges of the structural elements transverse to each slip-fold axis are continuously interconnected with respect to each other, and wherein the prestress tensional force is distributed to the plurality of structural elements through the edges of the structural elements.

27. The space-based power station of claim 22, wherein the plurality of structural elements comprise a plurality of edges, and wherein the edges of the structural elements are disposed in a parabolic profile.

28. The space-based power station of claim 22, wherein the structural elements comprise an outer supportive frame through which the prestress tension is applied, the power generation tiles being disposed within the outer supportive frame such that no prestress tension is distributed into the power generation tiles.

29. The space-based power station of claim 1, further comprising a deployment mechanism configured to engage with the at least two structural elements to apply a force thereto such that the elements are moved relative to each other on application of the force.

30. The space-based power station of claim 29, wherein the deployment mechanism comprises one or more booms configured to elongate.

31. The space-based power station of claim 29, wherein the deployment mechanism comprises weighted elements, and wherein the force is applied by rotation of the satellite module.