Attachment of the solar cell array

Abstract

To provide a solar cell array and a manufacturing method with a "flex on frame" concept for solar cell arrays, for simplifying design and manufacture of the solar cell arrays.SOLUTION: A solar cell array includes at least one solar panel, which comprises: a substrate having one or more solar cells bonded thereto; and a frame for supporting the substrate and the solar cells. The substrate is attached to the frame at a perimeter of the frame along one or more edges of the substrate. The frame has a cutout or an opening under the solar cells. The cutout or opening enables direct cooling of the solar cells through the substrate by exposing a back side of the substrate for transferring or radiating heat directly through the cutout or opening of the frame.SELECTED DRAWING: None

Description

Technical Field

[0001] The present disclosure relates generally to solar panels, and more particularly to the attachment of solar cell arrays.

Background Art

[0002] Spacecraft often use solar cell arrays for power generation. A solar cell array generally consists of solar panels connected together, and each solar panel is equipped with solar cells for power generation. Usually, there is wiring across the solar panels to transfer power to the spacecraft.

[0003] Solar cells and their assemblies need to radiate heat from the sun for cooling. When solar cells are constructed within a solar cell array, the solar cells maintain a high thermal conductivity to the radiation surface.

[0004] To reduce manufacturing costs, it is also desirable to construct solar cells on a thin substrate. This substrate may be a plastic sheet such as polyimide, a thin fiber composite, or a thin metal sheet. This substrate has lateral strength, but is thin, lightweight, and appears flexible.

[0005] Furthermore, it is desirable to have a solar cell array based on a highly rigid panel. This panel has increased strength to provide the rigidity and frequency response required by the program. The panel is often an aluminum (Al) honeycomb with a face sheet of carbon composite. Therefore, it is desirable to attach a thin substrate with solar cells to a highly rigid panel.

[0006] However, this attachment requires a large area of adhesive to ensure thermal contact with the radiation surface of the highly rigid panel. A large area of adhesive is a material with a large mass and is not desirable for space applications.

[0007] Also, it is difficult to attach the two flat surfaces of the substrate and the rigid panel without trapping air. This trapped air can cause delamination or cracking when this assembly enters the vacuum environment of space.

[0008] Therefore, there is a need for means to simplify the design and manufacture of solar cell arrays. SUMMARY OF THE INVENTION

[0009] To overcome the above limitations and other limitations that will become apparent when reading and understanding this specification, the present disclosure describes a solar cell array comprising at least one solar panel composed of a substrate to which one or more solar cells are joined, and a frame for supporting the substrate and the solar cells. The substrate is attached to the frame at the edge of the frame along one or more edges of the substrate. The frame has a notch or opening below the solar cell. The notch or opening allows direct cooling of the solar cell through the substrate by exposing the back side of the substrate to directly transfer or radiate heat through the notch or opening of the frame.

[0010] Next, reference is made to the drawings, in which like reference numerals represent corresponding parts throughout. BRIEF DESCRIPTION OF THE DRAWINGS

[0011]

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DETAILED DESCRIPTION OF THE INVENTION

[0012] In the following description, reference is made to the accompanying drawings, which form a part hereof. These drawings show, by way of example, specific embodiments in which the present disclosure may be practiced. It is to be understood that other embodiments may be utilized and structural changes may be made without departing from the scope of the present disclosure.

[0013] Summary The present disclosure provides a “flex on frame” concept for solar cell arrays. The solar cell array includes at least one solar panel composed of one or more solar cells bonded onto a substrate. The substrate may be a flexible substrate, and then the substrate having the solar cells is attached to a support frame having a notch or opening within the center of the support frame below the solar cells. The substrate is thin to promote heat flow and thus has low rigidity. Therefore, it is not desirable to fly it as it is because it is easily bent and flexible. The substrate is attached to a frame that provides rigidity for use as a solar panel in the structure.

[0014] One advantage of the "Flex-on-Frame" concept is the cutouts or openings within the frame. The cutouts or openings enable the substrate to act as a radiator into space. Thus, eliminating the typically thick rigid panel from the heat flow to the radiating surface.

[0015] Thermal connection to the frame is not required, thereby simplifying the attachment of the substrate to the panel (e.g., simple mechanical fasteners or clamps). This is different from using a solid substrate or other materials (e.g., metal plates) that are designed to transfer heat from the solar cell.

[0016] By having such cutouts or openings, the frame does not participate in the transfer of heat from the solar cell. Instead, the frame provides mechanical support for the substrate to which the solar cell is bonded. This allows for the separation of the thermal role and the mechanical role.

[0017] This configuration eliminates the need for a multi-functional adhesive. Multi-functional adhesives are difficult to work with during the assembly of solar panels and can fail over time during operation when exposed to the space environment.

[0018] In an alternative embodiment, optional reinforcing materials or support members may fill or cross the cutouts or openings of the frame, and then the substrate to which the solar cell is bonded is attached to those materials inside the frame. This can result in a more rigid solar panel.

[0019] The wiring for the solar cell can be bent around the frame. This can also provide certain advantages. This can simplify the electrical connection of the solar cell and reduce its cost.

[0020] These and other novel aspects of the "Flex-on-Frame" concept are described in more detail below.

[0021] Technical Description FIG. 1 is a schematic view of a spacecraft 10 having one or more solar cell arrays 11 composed of one or more solar panels 12. In this embodiment, the spacecraft 10 includes a satellite, there are two (2) solar cell arrays 11, and four (4) solar panels 12. Each of the solar cell arrays 11 is composed of two of the solar panels 12, and the solar cell arrays 11 and the solar panels 12 extend on both sides of the spacecraft 10. The solar cell arrays 11 are attached to the spacecraft 10 by a truss 13 or other mechanism, and each of the solar panels 12 is attached to an adjacent solar panel 12 by a hinge 14 or other mechanism. In that case, the truss 13 and the hinge 14 enable the solar arrays 11 and the solar panels 12 to be folded for storage during launch and then extended and deployed during operation.

[0022] FIGS. 2A, 2B, and 2C are a top schematic view, a top schematic view, and a cross-sectional side schematic view, respectively, showing the components and assembly of one of the solar panels 12, including a solar power module (SPM) 15 and a frame 16.

[0023] FIG. 2A shows an SPM 15 composed of an array of solar cells 17 bonded to a substrate 18. In one embodiment, the substrate 18 is a flexible substrate, i.e., a flexible circuit composed of a laminate of one or more Kapton (trademark) insulating layers and one or more metal layers providing electrical connection.

[0024] FIG. 2B shows a frame 16 for supporting the solar cell 17 and the substrate 18. The frame 16 is, for example, a rectangular structure formed from joined elements defining an edge around a notch or opening in the center of the frame 16 below the solar cell 17.

[0025] FIG. 2C shows the SPM 15 mounted and attached on the frame 16. The substrate 18 is attached to the frame 16 at the edge of the frame 16 along one or more edges of the substrate 18. Once mounted and attached, the SPM 15 and the frame 16 form the solar panel 12.

[0026] Conventional highly rigid solar panels are solid in shape, often rectangular, but can be of any shape. In the present disclosure, the solar panel 12 is mostly hollow due to the shape of the frame 16.

[0027] In this embodiment, the substrate 18 is a thermal structure for radiating heat from the solar cell 17 into outer space, and the frame 16 is a mechanical structure for supporting the solar cell 17 and the substrate 18. Specifically, a notch or opening in the center of the frame 16 exposes the back side of the substrate 18 to enable direct heat transfer or radiation through the notch or opening in the frame 16, thereby allowing cooling of the solar cell 17 through the substrate 18. The purpose is to minimize the radiant heat flow of the solar cell 17 and the substrate 18 into outer space by the mechanical structure of the frame 16.

[0028] In another embodiment, reinforcing materials and / or support members (not shown) inside the frame 16 can enhance rigidity. In that case, the reinforcing material can be a mesh, honeycomb material, etc., and the support member can be various bars, channels, etc. This will be described in more detail below in conjunction with FIGS. 6A and 6B.

[0029] FIGS. 3A and 3B are respectively a schematic cross-sectional side view and a schematic top view of the SPM 15, the frame 16, the solar cell 17, and the substrate 18. The substrate 18 is attached to the frame 16 using one or more fasteners 19 and reinforcing areas 20.

[0030] A wide variety of types of fasteners 19, including pins, posts, rivets, or other structures, may be used, and the fasteners 19 may be composed of metal, polymer, or other types of materials. A variety of adhesives may be used with or in place of the fasteners 19 in continuous or spot applications.

[0031] Fastener 19 may be attached to a single surface of frame 16 or may extend through frame 16. Desirably, fastener 19 is reversible so as to be disassemblable for repair, and removing fastener 19 may include destroying them (such as cutting or perforating fastener 19). It should not be a major concern due to their low cost.

[0032] As shown in FIG. 3B, fastener 19 may be disposed within reinforcement area 20 of substrate 18 near the edge of substrate 18 or within other areas of substrate 18 to prevent tearing of substrate 18. Reinforcement area 20 may be composed of a further Kapton (trademark) insulating layer, carbon fiber, Kevlar (trademark), and / or a metal layer, or some other combination of layers, or other materials. It would be relatively easy to pattern a copper (Cu) trace layer as a reinforcement. Further, the material of frame 16 may also be reinforced in the vicinity of fastener 19.

[0033] In this embodiment, four (4) or five (5) of fasteners 19 are disposed around the edge of frame 16 and near the edge of substrate 18, on each of the four (4) sides of frame 16. In other embodiments, it may only be necessary for SPM 15 to be attached to both sides of two (2) of frame 16. On the other hand, attaching SPM 15 to all four (4) sides of frame 16 provides a guarantee regarding the safety of attaching SPM 15 to frame 16.

[0034] Figures 4A and 4B are, respectively, a schematic cross-sectional side view and a schematic top view of the SPM15, frame 16, solar cell 17, substrate 18, fastener 19, and reinforcement area 20. The substrate 18 is attached to the frame 16 using, for example, one or more bars 21 positioned along one or more sides of the frame 16 within the reinforcement area 20 near the edge of the substrate 18 and between at least some of the fasteners 19 and the substrate 18. These bars 21 serve to distribute the forces applied by the fasteners 19 and thus help minimize the risk of breaking the substrate 18. These bars 21 may be rectangular or another shape, and preferably match the geometric dimensional shape of the frame 16. The bars 21 can also be composed of a series of one or more shorter segments. Figure 3B shows reinforcement at a single attachment location, while Figure 4B shows reinforcement extending over multiple attachment locations.

[0035] Figures 5A, 5B, 5C, and 5D are schematic top views providing more details about the electrical connection to the solar cell 17, and Figure 5E is a schematic cross-sectional side view thereof. For collecting solar energy, it is preferable that the wiring for the electrical connection to the solar cell 17 be on the back side of the substrate 18 so that as much area as possible on the front side of the solar cell 17 is used.

[0036] Figure 5A is a schematic top view of the SPM15, solar cell 17, and substrate 18 before being mounted and attached to the frame 16. The substrate 18 has one or more tabs 22 extending from one or more sides of the substrate 18. Each of the tabs 22 may be composed of the same material as the substrate 18 and may be a continuous part of the substrate 18. Each of the tabs 22 may include one or more conductors 23 patterned from one or more metal layers disposed on the surface of the tab 22 and / or embedded within the layer of the tab 22 for making an electrical connection to at least one of the solar cells 17.

[0037] Figure 5B is a schematic top view of SPM15, frame 16, solar cell 17, substrate 18, fastener 19, reinforcement area 20, and bar 21. Substrate 18 is attached to frame 16 at reinforcement area 20 and bar 21 using fastener 19, and tabs 22 and conductor 23 extend beyond frame 16.

[0038] Figure 5C is a schematic top view of SPM15, frame 16, solar cell 17, substrate 18, fastener 19, reinforcement area 20, and bar 21. Tabs 22 and conductor 23 are bent around and under frame 16.

[0039] Figure 5D is a schematic bottom view of frame 16, substrate 18, fastener 19, and bar 21. Tabs 22 and conductor 23 are bent around and under frame 16, and tab 22 is attached to the back side of substrate 18 using, for example, an adhesive, fastener, bar, etc. Tab 22 may also be attached to one or more sides of frame 16, including the back side, front side, and edge side of frame 16.

[0040] In this embodiment, tab 22 extends around the outside of frame 16 and then passes under and is fixed by bar 21. Another option could be to pass tab 22 through a slot or channel within frame 16. In yet another option, substrate 18 could be constructed to terminate at an opening in frame 16. This could allow tab 22 to be bent down inside frame 16 instead of outside the edge of frame 16. In still another option, tab 22 may also be attached to one or more sides of frame 16 and simply extend in the opposite direction away from the sun.

[0041] Conductor 23 can be electrically connected to conductors or traces (not shown) disposed on the back side of substrate 18 and / or embedded within substrate 18 through the use of exposed conductors or traces, vias, etc.

[0042] Figure 5E is a schematic cross-sectional side view of the SPM15, frame 16, solar cell 17, substrate 18, fastener 19, bar 21, and tab 22. The tab 22 is wound around the back side of the substrate 18 around the frame 16. Alternatively, the tab 22 may be attached to the edge of the frame 16.

[0043] Here, the substrate 18 is visible above the frame 16 and bends around the outside of the frame 16. Preferably, the tab 22 is arranged to block radiation from the back side of the substrate 18 at the minimum source. For example, the tab 22 may be arranged behind the structure of the frame 16 to block it minimally.

[0044] The ends of the tab 22 are available for connection to other conductors such as a wiring harness (not shown) to transfer power to the adjacent frame 16, panel 12, array 11, other structures, and the spacecraft 10 itself. For example, the wiring harness may be arranged along the back of the substrate 18, the back of the frame 16, or the side of the frame 16. The wiring harness may extend partially or completely inside the frame 16 when the frame 16 is composed of a hollow member. The conductors in the wiring harness may form part of the frame 16 when the frame 16 is constructed as a composite material or via additive manufacturing.

[0045] Figure 6A is a schematic top view showing a reinforcing material 24 that can be used to fill a notch or opening in the center of the frame 16, and Figure 6B is a schematic cross-sectional side view thereof. Figure 6A shows only the frame 16 and the reinforcing material 24, and Figure 6B shows the SPM15 mounted and attached on the frame 16 in a state where the substrate 18 is attached to both the frame 16 and the reinforcing material 24, and the solar cell 17 is joined to the substrate 18 above the reinforcing material 24.

[0046] In one embodiment, these reinforcing materials 24 can be designed to block vertically incident radiation from reaching the solar cell 17 and non-vertically incident radiation from reaching the solar cell 17. For example, cosmic radiation (e.g., electrons, protons, gamma rays) impinges on the solar cell array 11 and the solar panel 12 at all angles. By using the honeycomb structure as the reinforcing material 24 within the frame 16, radiative cooling 25 can occur at normal incidence while blocking non-vertically incident cosmic radiation, and thus, damage to the solar cell 17 can be prevented.

[0047] It is important for the solar panel 12 to pass acoustic and vibration tests. By attaching the substrate 18 to the reinforcing material 24 below the substrate 18, vibrations can be limited and survivability can be improved. The acoustic and vibration environment occurs during the launch phase while the solar panel 12 is folded and housed against the side of the spacecraft 10. In this state, the solar cells 17 from one panel 12 can face the reinforcing material 24 from the second panel 12. Their mechanical engagement should be designed to withstand acoustic and vibration requirements. It may be advantageous to employ shock-absorbing materials or soft materials such as foams between the solar cell 17 or the substrate 18 and the reinforcing material 24 of the next panel 12.

[0048] Functional Block Diagram Embodiments of the present disclosure can be described in the context of a method 26 for manufacturing an apparatus comprising a solar cell array 11 for a spacecraft 10. The method 26 includes steps 27 - 33 as shown in FIG. 7. The resulting spacecraft 10 having the solar cell array 11 is shown in FIG. 8.

[0049] As shown in FIG. 7, in the pre-manufacturing stage, an exemplary method 26 may include the specifications and design 27 of the spacecraft 10 and / or the solar cell array 11, as well as the procurement 28 of their materials. During manufacturing, the manufacturing and system integration 30 of the components and sub-assemblies 29 of the spacecraft 10 and / or the solar cell array 11 occur. They include manufacturing the spacecraft 10 and / or the solar cell array 11, including joining one or more solar cells 17 to a substrate 18 and then attaching the substrate 18 and the solar cells 17 to a frame 16 for support. Thereafter, the spacecraft 10 and / or the solar cell array 11 may undergo approval and delivery 31 for use in operation 32. The spacecraft 10 and / or the solar cell array 11 may also be scheduled for servicing and maintenance 33 (including retrofitting, reconfiguration, modification, etc.) prior to launch.

[0050] Each step of method 26 may be performed or executed by a system integrator, third party, and / or operator (e.g., a customer). For the purposes of this description, a system integrator may include, without limitation, any number of manufacturers and subcontractors of the solar cells 17, solar panels 12, solar cell arrays 11, or spacecraft 10, a third party may include, without limitation, any number of vendors, subcontractors, and suppliers, and an operator may be a satellite communications company, military organization, service agency, etc.

[0051] As shown in FIG. 8, a spacecraft 10 manufactured by an exemplary method 26 may include a plurality of systems 34, a body 35, one or more solar cell arrays 11, and one or more antennas 36. Examples of the plurality of systems 34 included with the spacecraft 10 include, but are not limited to, one or more of a propulsion system 37, an electrical system 38, a communication system 39, and a power system 40. Any number of other systems 34 may also be included.

[0052] FIG. 9 is a diagram of a method for housing, deploying, and operating a solar cell array 11 in the form of a functional block diagram according to one embodiment.

[0053] When housed and when deployed, the solar cell array 11 is composed of one or more solar panels 12. Each of the solar panels 12 includes one or more of the SPMs 15. Each of the SPMs 15 may be a flexible substrate 18 to which one or more solar cells 17 are joined, and a frame 16 for supporting the substrate 18 and the solar cells. The frame 16 supports the substrate 18 at the edge of the frame 16 along one or more edges of the substrate 18. The frame 16 has a notch or opening in the center of the frame 16 below the solar cell 17. The notch or opening exposes the back side of the substrate 18 to allow cooling of the solar cell 17 through the substrate 18 in order to transfer or radiate heat directly from the one or more solar cells 17 joined to the substrate 18 through the notch or opening of the frame 16.

[0054] During operation, each of the solar cells 17 absorbs light 41 from the light source 42 and generates an electrical output 43 in response thereto. It results in excess heat generated by the solar cell 17.

[0055] The substrate 18 may have one or more conductive layers for making electrical connections to the solar cells 17 and one or more insulating layers for insulating the conductive layers, and the conductive layers may be embedded within the substrate 18 and / or may be on the substrate 18.

[0056] The substrate 18 may be attached to the frame 16 using one or more fasteners 19, and the fasteners 19 may be disposed within a reinforcement area 20 of the substrate 18 near the edge of the substrate 18 to prevent tearing of the substrate 18. The substrate 18 may be attached to the frame 16 using one or more bars 21 positioned along one or more sides of the frame 16 to distribute the force applied by the fasteners 19 that attach the substrate 18 to the frame 16.

[0057] The substrate 18 may have one or more tabs 22 that are bent around and under the frame 16, and the tabs 22 may be attached to the back side of the substrate 18. The tabs 22 may include one or more conductors 23 for making electrical connections to the solar cell 17. The tabs 22 may be attached to one or more sides of the frame 16.

[0058] The reinforcing material 24 or support member may fill a notch or opening in the frame 16, and the substrate 18 having the solar cell 17 may be attached to the reinforcing material 24 inside the frame 16. The reinforcing material 24 may include a shock absorber that interacts with the substrate 18 and the solar cell 17 when contained. The reinforcing material 24 may also be able to prevent radiation with a vertical incidence from reaching the solar cell 17 and radiation with a non-vertical incidence from reaching the solar cell 17.

[0059] Furthermore, the present disclosure includes embodiments according to the following clauses. Clause 1. An apparatus comprising a substrate to which one or more solar cells are joined, and a frame for supporting the substrate and the solar cells, wherein the substrate is attached to the frame along one or more edges of the substrate, the frame has a notch or opening below the solar cell, and the notch or the opening allows direct cooling of the solar cell through the substrate by exposing the back sides of the substrate and the solar cells to directly transfer or radiate heat through the notch or the opening of the frame. Clause 2. The apparatus according to clause 1, wherein the substrate is a flexible substrate. Clause 3. The apparatus according to clause 1 or 2, wherein the substrate is attached to the frame using one or more fasteners, and the fasteners are placed within a reinforcing area of the substrate to prevent breakage of the substrate. Clause 4. The apparatus according to any one of clauses 1 to 3, wherein one or more bars positioned along one or more side portions of the frame are used to disperse the force applied by a fastener that attaches the substrate to the frame, and the substrate is attached to the frame. Clause 5. The apparatus according to any one of clauses 1 to 4, wherein the substrate has one or more tabs that are bent around and under the frame. Clause 6. The apparatus according to clause 5, wherein the tab includes one or more conductors for making an electrical connection to the solar cell. Clause 7. The apparatus according to clause 5 or 6, wherein the tab is attached to one or more side portions of the frame. Clause 8. The apparatus according to any one of clauses 1 to 7, further comprising a reinforcing material or a support member within the notch or the opening of the frame. Clause 9. The apparatus according to clause 8, wherein the substrate having the solar cell is attached to the reinforcing material inside the frame. Clause 10. The apparatus according to clause 8 or 9, wherein the reinforcing material includes a shock absorber that interacts with the substrate and the solar cell when housed. Clause 11. The apparatus according to any one of clauses 8 to 10, wherein the reinforcing material enables radiative cooling from the solar cell to occur at normal incidence and blocks non-normal incidence of electrons and protons radiation from reaching the solar cell. Clause 12. The apparatus according to any one of clauses 1 to 11, wherein the substrate has one or more conductive layers for making an electrical connection to the solar cell, the substrate includes one or more insulating layers for insulating the conductive layer, and the conductive layer is embedded within the substrate or on the substrate. Clause 13. The apparatus according to any one of clauses 1 to 12, wherein the frame, the substrate, and the solar cell include a solar panel for a spacecraft. Clause 14. Bonding one or more solar cells to a substrate, and attaching the substrate and the solar cells to a frame for support, the method comprising: the substrate being attached to the frame along one or more edges of the substrate, the frame having a notch or an opening below the solar cell, the notch or the opening exposing the back side of the substrate to enable direct cooling of the solar cell through the substrate for direct heat transfer or radiation through the notch or the opening of the frame. Clause 15. The method according to clause 14, wherein the substrate is a flexible substrate. Clause 16. The method according to clause 14 or 15, wherein the substrate is attached to the frame using one or more fasteners, the fasteners being placed within a reinforcement area of the substrate to prevent tearing of the substrate. Clause 17. The method according to any one of clauses 14 to 16, wherein the substrate is attached to the frame using one or more bars positioned along one or more sides of the frame to disperse the force applied by the fasteners attaching the substrate to the frame. Clause 18. The method according to any one of clauses 14 to 17, wherein the substrate has one or more tabs bent around and under the frame, the tabs including one or more conductors for making electrical connection to the solar cell. Clause 19. The method according to clause 18, wherein the tabs are attached to one or more sides of the frame. Clause 20. The method according to any one of clauses 14 to 19, further comprising a reinforcing material or a support member within the notch or the opening of the frame, the substrate having the solar cell being attached to the reinforcing material inside the frame. Clause 21. The method according to clause 20, wherein the reinforcing material includes a shock absorber that interacts with the substrate and the solar cell when contained. Clause 22. The device according to clause 20 or 21, wherein the reinforcing material enables radiative cooling from the solar cell to occur at normal incidence and blocks non-normal incident electrons and protons from reaching the solar cell. Clause 23. The method according to any one of clauses 14 to 22, wherein the substrate has one or more conductive layers for electrically connecting to the solar cell, the substrate includes one or more insulating layers for insulating the conductive layer, and the conductive layer is embedded in the substrate or on the substrate. Clause 24. A method including transferring heat from one or more solar cells bonded to a substrate, wherein the substrate is mounted on a frame for support, the substrate is mounted to the frame along one or more edges of the substrate, the frame has a notch or opening below the solar cell, and the notch or opening exposes the back side of the substrate to enable direct cooling of the solar cell through the substrate by directly radiating heat through the notch or opening of the frame.

[0060] Conclusion The descriptions of the examples set forth above are presented for purposes of illustration and description and are not intended to be exhaustive or to limit to the examples disclosed. Many alternative examples, modifications, and variations may be used in place of the specific examples described above.

Claims

1. One or more solar cells (17) are joined, a substrate (18) which is a flexible substrate (18), and a frame (16) for supporting the substrate (18) and the solar cell (17), the device comprising: the substrate (18) is attached to the frame (16) along one or more edges of the substrate (18), the frame (16) has a notch or an opening below the solar cell (17), and the notch or the opening exposes the back side of the substrate (18) to directly radiate heat through the notch or the opening of the frame (16), enabling cooling of the solar cell (17) through the substrate (18), the substrate (18) has one or more tabs (22) that are bent around and below the frame (16), the device.

2. the substrate (18) is attached to the frame (16) using one or more fasteners (19), the fasteners (19) are placed within a reinforcement area (20) of the substrate (18) to prevent tearing of the substrate (18), and / or one or more bars (21) positioned along one or more sides of the frame (16) are used to disperse the force applied by the fasteners (19) that attach the substrate (18) to the frame (16), the device according to claim 1, wherein the substrate (18) is attached to the frame (16).

3. Each of the tabs (22) is composed of the same material as the substrate (18) and is a continuous part of the substrate (18), the device according to claim 1 or 2.

4. the tabs (22) include one or more conductors (23) for making an electrical connection to the solar cell (17), the device according to claim 3.

5. the device according to any one of claims 1 to 4, further comprising a reinforcing material (24) or a support member within the notch or the opening of the frame (16).

6. the substrate (18) having the solar cell (17) is attached to the reinforcing material (24) inside the frame (16), the device according to claim 5.

7. The reinforcing material (24) includes a shock absorber that interacts with the substrate (18) and the solar cell (17) when housed, and / or the reinforcing material (24) enables radiative cooling (25) from the solar cell (17) to occur at normal incidence and blocks non-normal incident electrons and protons from reaching the solar cell (17). The device according to claim 5 or 6.

8. The substrate (18) has one or more conductive layers for making electrical connection to the solar cell (17), the substrate (18) includes one or more insulating layers for insulating the conductive layers, and the conductive layers are embedded in the substrate (18) or are on the substrate (18). The device according to any one of claims 1 to 7.

9. The frame (16), the substrate (18), and the solar cell (17) constitute a solar panel (12) for a spacecraft (10). The device according to any one of claims 1 to 8.

10. Bonding one or more solar cells (17) to a substrate (18) that is a flexible substrate (18), and attaching the substrate (18) and the solar cell (17) to a frame (16) for support. A method, wherein the substrate (18) is attached to the frame (16) along one or more edges of the substrate (18), the frame (16) has a notch or an opening below the solar cell (17), and the notch or the opening exposes the back side of the substrate (18) to directly radiate heat through the notch or the opening of the frame (16), thereby enabling cooling of the solar cell (17) through the substrate (18). The substrate (18) has one or more tabs (22) that are bent around and under the frame (16). A method.

11. The substrate (18) is attached to the frame (16) using one or more fasteners (19), the fasteners (19) are placed within a reinforcing area (20) of the substrate (18) to prevent tearing of the substrate (18), and / or one or more bars (21) positioned along one or more sides of the frame (16) are used to disperse the force applied by the fasteners (19) that attach the substrate (18) to the frame (16). The substrate (18) is attached to the frame (16). The method according to claim 10. **Claim 12**: The method according to claim 10 or 11, wherein the tab (22) comprises one or more conductors (23) for making an electrical connection to the solar cell (17). **Claim 13** The method according to any one of claims 10 to 12, further comprising a reinforcing material (24) or a support member within the notch or the opening of the frame (16), wherein the substrate (18) having the solar cell (17) is attached to the reinforcing material (24) inside the frame (16). **Claim 14** The method according to claim 13, wherein the reinforcing material (24) comprises a shock absorber that interacts with the substrate (18) and the solar cell (17) when housed, and / or the reinforcing material (24) enables radiative cooling (25) from the solar cell (17) to occur at normal incidence and blocks non-normal incidence of electrons and protons radiation from reaching the solar cell (17). **Claim 15** The method according to any one of claims 10 to 14, wherein the substrate (18) has one or more conductive layers for making an electrical connection to the solar cell (17), the substrate (18) includes one or more insulating layers for insulating the conductive layers, and the conductive layers are embedded within the substrate (18) or are on the substrate (18).

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