JP5439963B2 - Solar array panel, repair method of solar array panel - Google Patents

Description

  The present invention relates to a method for repairing a solar array panel that supplies electric power to a space structure such as an artificial satellite or a space station.

  Currently, in order to supply power to space structures, it is common to use panels with solar cells (solar array panels), and above all, sandwich panels using composite skins. It is well known that solar array panels in which solar cells are arranged are widely used.

  When such a solar array panel is damaged by an external force, various methods have been proposed as a method for replacing the solar cell (see, for example, Patent Document 1).

JP 2005-251960 A

  However, when damaged by external force, not only the solar cell but also the sandwich panel may be damaged. When the surface on which the solar cell is mounted is damaged, there is a concern that when the composite material skin material for reinforcing the damaged portion is bonded, a step is generated in the repaired portion and the solar cell cannot be joined.

  In addition, the sandwich panel may be damaged before the solar cell is mounted. If the surface on which the solar cell is mounted is damaged, bonding a composite skin material to reinforce the damaged part creates a step in the repaired part, and the solar cell is damaged by the step when mounting the solar cell. There are concerns. Alternatively, a method of joining the surrounding solar cells with electric wires without mounting the solar cells on the stepped portion is conceivable. However, in this case, there is a concern that the power generated by the solar array panel is reduced.

  In repairing a sandwich panel that constitutes a conventional solar array panel, if a skin material made of a composite material is bonded to the surface of the sandwich panel, a step is generated in the bonded portion. When the solar cell is mounted on the stepped portion, the solar cell is damaged, and thus there is a problem that the solar cell cannot be mounted on the repaired portion.

  The present invention has been made in order to solve such problems, and does not limit the position on which the solar cell is mounted without causing a step that impedes the mounting of the solar cell on the surface of the sandwich panel. And to provide a structure for strengthening.

A solar array panel according to the present invention is mounted on a space structure, and includes a core material having a honeycomb structure, and a skin material (front surface) and a skin that are respectively attached to the front surface side and the back surface side of the core material with the core material interposed therebetween. A solar array panel comprising a material (back surface), wherein a plurality of solar cells are mounted on an insulating layer provided on one surface of the skin material (front surface), and the skin material (front surface) is It has a defect part, and the defect part has substantially the same thickness as the skin material (surface), is substantially the same as the area of the defect part, and is the same solar cell side as the skin material (surface) A repair skin material (surface) provided with an insulating layer is fitted on the other surface, the other surface of the repair skin material (surface) different from the surface on the insulating layer side, and the skin around the defect portion The other surface of the material (surface) that is different from the surface on the insulating layer side is It is fixed to a repair reinforcing material having an area larger than the defective portion provided in the space where the core material has been removed around the portion, and the space from which the core material has been removed has substantially the same size as the space. A repair core material having a honeycomb structure is fitted and fixed to the repair reinforcing material. Among the plurality of solar cells, some of the solar cells insulate the skin material (surface) around the defect portion. It is mounted on the insulating layer of the repair skin material (surface) which is substantially flush with the layer.

  According to the present invention, even if the sandwich panel of the solar array panel is damaged, the mounting position of the solar cell is limited without causing a step that interferes with the mounting of the solar cell on the surface of the sandwich panel. It is possible to provide a repair structure of a solar array panel that is not performed.

It is a figure for demonstrating the repair structure of the solar array panel by Embodiment 1 of this invention. It is a figure explaining the repair method of the solar array panel by Embodiment 1 of this invention. It is a figure for demonstrating the solar array panel by Embodiment 2 of this invention. It is a figure for demonstrating the solar array panel by Embodiment 3 of this invention. It is a figure which shows arrangement | positioning in the artificial satellite of a solar array panel. It is sectional drawing of the conventional solar array panel. It is a perspective view of the conventional solar array panel.

Embodiment 1 FIG.
Embodiment 1 according to the present invention will be described below with reference to the drawings.
FIG. 5 is a diagram showing an artificial satellite, in which 20 is a solar array panel, 21 is a satellite structure, and 22 is an antenna reflector. An artificial satellite is composed of structures such as a solar array panel 20, a satellite structure 21, and an antenna reflector 22, and solar cells are frequently used to supply power to space structures such as artificial satellites and space stations. .

  The space structure requires a large number of solar cells, and a flat sandwich panel is used to hold these solar cells, and the solar cells are arranged on the surface thereof. As the skin material of this sandwich panel, carbon fiber reinforced composite materials and aluminum are frequently used in order to increase specific modulus and specific strength.

  FIG. 6 is a sectional view showing a conventional solar array, and FIG. 7 is a perspective view showing the conventional solar array. In the figure, 40 is a sandwich panel, 1 is a skin material (front surface) of the sandwich panel 40, 2 is a skin material (back surface) of the sandwich panel 40, 3 is a core of the sandwich panel, 8 is a solar cell, and 11 is an insulator film layer. It is.

The insulator layer 11 is attached to the skin material (surface) 1 of the sandwich panel. In order to reduce the weight of the space structure, a polyimide film is used for the insulator film layer.
The solar cell 8 is mounted on the insulator layer 11 with an adhesive or the like.

FIG. 1 shows a repair structure of a solar array panel according to the first embodiment.
The sandwich panel constituting the solar array panel 20 has a structure in which a core material 3 is sandwiched between a skin material (front surface) 1 and a skin material (back surface) 2. The core material 3 has, for example, a honeycomb structure. Members having the same functions as those of the conventional solar array panel shown in FIG. 6 are denoted by the same reference numerals, and description thereof is omitted unless necessary.

The repair structure of the repair location 30 of the solar array panel 20 has a structure in which the skin material (surface) 1 and the repair skin material (surface) 4 are arranged and reinforced by the repair reinforcing material 5 from the inside. Further, a repair core material 6 is provided, and a repair skin material (back surface) 7 is provided outside the skin material (back surface) 2.
In this repair structure, the skin material (surface) 1 and the repair skin material (surface) 4 are arranged side by side, so that no step is produced. Therefore, the solar cell 8 can be mounted without being affected by the position of the repair portion.

A method for repairing the solar array panel according to the first embodiment will be described with reference to FIG.
FIG. 2 is a diagram showing a repair flow of the solar array panel.

FIG. 2A is a cross-sectional view of the solar array panel when the solar array panel 40 is damaged due to external force before the solar cell 8 is mounted, and repair is started from now. The insulator film layer 11 is omitted.
First, as shown in FIG. 2A, the core material 3 under the defect portion 35 is removed in a range wider than the defect portion 35 of the damaged skin material (surface) 1. Further, the skin material (back surface) 2 is removed in substantially the same range as the removed core material 3.
Next, as shown in FIG. 2 (b), a repair skin material (surface) 4 having the same or slightly smaller size than the area of the defect 35 is prepared, and the repair skin material (surface) 4 is covered with the skin. It fits into the defect part 35 of the material (surface) 1. The repair skin material (surface) 4 uses a plate having the same thickness as the skin material (surface) 1. The skin material for repair (surface) 4 has an insulating layer on the surface, and when the skin material for repair (surface) 4 is fitted into the defect portion 35, the insulating layer of the skin material for repair (surface) 4 is the skin material ( (Surface) 1 is arranged so as to be on the insulating layer 11 side. The repair skin material (surface) 4 may be the same material as the skin material (surface) 1. Further, the insulating layer on the surface of the repair skin material (surface) 4 may be the same material as the insulating layer 11 on the skin material (surface) 1.
Next, the reinforcing material 5 for repair is applied from the inside (the side of the core material 3), and the skin material (surface) 1 and the reinforcing material 5 for repairing, and the reinforcing material 5 for repairing and the skin material for repairing (surface) 4 Is fixed with an adhesive or the like. Thereby, the surface of the skin material for repair (surface) 4 and the surface of the skin material (surface) 1 are not uneven and are substantially flush with each other.
Next, as shown in FIG. 2C, the repair core material 6 having the same size as the space is fitted into the space below the repair reinforcing material 5 and fixed with an adhesive 15 or the like.
The back surface side of the solar array panel uses a repair skin material (back surface) 7 having a larger area than the cross section of the repair core material 6 as shown in FIG. Adhering between the material (back surface) 2 and between the repair skin material (back surface) 7 and the repair core material 6 with an adhesive 15 or the like, the repair skin material (back surface) 7 and the skin material (back surface) 2 It fixes so that the core material 6 for repair may become united.
After repairing the sandwich panel 40 in this way, the solar cell 8 is mounted on the sandwich panel 40 as shown in FIG.

The repair reinforcing material 5 functions as follows.
The skin material (surface) 1 and the repair skin material (surface) 4 are arranged side by side. When there is no repair reinforcing material 5, the boundary cannot transmit the stress applied to the sandwich panel. Strength will fall.
By providing the reinforcing material 5 for repair, stress can be transmitted and the strength of the sandwich panel can be maintained.
The repair reinforcing material 5 is larger in size than the skin material (surface) 1 so that the stress of the skin material (surface) 1 can be transmitted.
In FIG. 1, the repair skin material (surface) 4 and the repair reinforcing material 5 are separated, but these members may have an integral structure.

The repair skin material (back surface) 7 is also larger in size than the skin material (back surface) 2 in order to transmit the stress of the skin material (back surface) 2.

  Here, the repair of the sandwich panel has been described as an example, but this structure is also applied to the case where the sandwich panel is strengthened when it is necessary to partially increase the strength after the sandwich panel is formed. be able to.

Embodiment 2. FIG.
FIG. 3 shows the configuration of the solar array panel according to the second embodiment.
In general, the skin material (surface) 1 is made of carbon fiber reinforced composite material or aluminum and has conductivity. The skin material (surface) 1 is provided with an insulating layer on the solar cell 8 side so that the potential generated in the solar cell is not short-circuited with the skin material (surface) 1. A polyimide film is frequently used for the insulating layer.

In this case, the repairing skin material (front surface) 4 can similarly prevent the short circuit of the potential of the solar cell 8 by providing an insulating layer on the surface on the solar cell side.
Furthermore, in order to prevent the potential of the solar cell 8 from being short-circuited from the boundary between the skin material (surface) 1 and the repair skin material (surface) 4, it is suitable to provide an insulating layer 9 as shown in FIG. . By providing the insulating layer 9 so as to cover the repair skin material (surface) 4, a short circuit at the boundary between the skin material (surface) 1 and the repair skin material (surface) 4 can be prevented.

  In addition, as a method of providing the insulating film, the insulating layer 9 may be bonded to the skin material (surface) 1 and the repairing skin material (surface) 4 with an adhesive, and the insulating layer 9 may be bonded to the skin material (surface) with an adhesive. ) 1 and repair skin material (surface) 4 may be attached.

  In the case of Embodiment 2, the insulating layer 9 protrudes from the surface of the sandwich panel. However, the thickness of the adhesive for mounting the solar cell is in the range of 0.05 mm to 0.2 mm, and by making the thickness of the insulating layer 9 thinner than the thickness of the adhesive for mounting the solar cell, The influence at the time of solar cell loading can be suppressed.

Embodiment 3 FIG.
FIG. 4 shows the configuration of the solar array panel according to the third embodiment.
The solar array panel may be held vertically during its assembly. The member for repair is generally attached by adhesion or the like, but it is difficult to hold the member at the time of attachment in a vertical state. In FIG. 4, by providing the screw member 10, the member can be held by inserting a bolt into the screw.

  In FIG. 4, the screw member 10 has screws on the front and back surfaces of the sandwich panel, but it goes without saying that a structure having screws on only one side is also possible depending on the form of attachment. For example, if the repair core material 6, the repair skin material (back surface) 7, and the screw member 10 are connected in advance, the screws on the repair skin material (back surface) 7 side can be eliminated.

  1 skin material (front surface), 2 skin material (back surface), 3 core material, 4 skin material for repair (front surface), 5 repair material, 6 core material for repair, 7 skin material for repair (back surface), 8 sun Battery, 9 Insulating layer, 10 Screw member, 11 Insulating film layer, 15 Adhesive, 20 Solar array panel, 21 Satellite structure, 22 Antenna reflector, 30 Repair location, 35 Defect, 40 Sandwich panel.

Claims (6)

A solar array comprising a core material mounted on a space structure and having a honeycomb structure, and a skin material (front surface) and a skin material (back surface) that are respectively attached to the front surface side and the back surface side of the core material with the core material interposed therebetween A panel,
  A plurality of solar cells are mounted on an insulating layer provided on one surface of the skin material (surface),
  The skin material (surface) has a defect portion, and the defect portion has substantially the same thickness as the skin material (surface), and substantially the same as the area of the defect portion, A skin material for repair (surface) with an insulating layer is fitted on the same surface of the solar cell as the surface)
  The other surface different from the surface on the insulating layer side of the skin material for repair (surface) and the other surface different from the surface on the insulating layer side of the skin material (surface) around the defect portion are around the defect portion. And fixed with a reinforcing material for repair having an area larger than the defective portion provided in the space from which the core material has been removed,
  In the space from which the core material has been removed, a repair core material having a honeycomb structure substantially the same size as the space is fitted and fixed to the repair reinforcing material.
  Among the plurality of solar cells, some of the solar cells are on the insulating layer of the repairing skin material (surface) that is substantially flush with the insulating layer of the skin material (surface) around the defect portion. A solar array panel characterized by being mounted on. Provided with an insulating layer covering the boundary part at the boundary part of the skin material for repair (surface) and the skin material around the defect part (surface) forming a substantially flush surface,
  The solar array panel according to claim 1, wherein some of the plurality of solar cells are mounted on an insulating layer covering the boundary portion. The solar array panel according to claim 1, wherein the repair core material and the repair reinforcing material are fixed by screw members. A solar array panel repair method,
  The solar array panel is mounted on a space structure and has a core material having a honeycomb structure, and a skin material (front surface) and a skin material (back surface) that are respectively attached to the front surface side and the back surface side of the core material with the core material interposed therebetween. A plurality of solar cells are mounted on an insulating layer provided on one surface of the skin material (surface),
  The skin material (surface) has a defect portion, and the defect portion has substantially the same thickness as the skin material (surface), and substantially the same as the area of the defect portion, A skin material for repair (surface) with an insulating layer is fitted on the same surface of the solar cell as the surface)
  The other surface different from the surface on the insulating layer side of the skin material for repair (surface) and the surface on the core material side of the skin material (surface) around the defect portion are the core material around the defect portion. It is fixed with a repairing reinforcing material having an area larger than the defective part provided in the space removed in advance,
  In the space from which the core material has been removed, a repair core material having a honeycomb structure of approximately the same size as the space is fitted and fixed to the repair reinforcing material,
  A solar cell for repair is mounted on the insulating layer of the skin material for repair (surface) that is substantially flush with the insulating layer of the skin material (surface) around the defect portion of the solar array panel. A solar array panel repair method characterized by the above. A solar array comprising a core material mounted on a space structure and having a honeycomb structure, and a skin material (front surface) and a skin material (back surface) that are respectively attached to the front surface side and the back surface side of the core material with the core material interposed therebetween A panel,
  On one surface of the skin material (surface), an insulating layer for mounting a solar cell on the skin material (surface) via an insulator is provided,
  The skin material (surface) has a defect,
  The defect portion has substantially the same thickness as the skin material (surface), is substantially the same as the area of the defect portion, and is the same as the skin material (surface) on the surface on which the solar cell is mounted. The skin material for repair (surface) equipped with an insulating layer is fitted in,
  The other surface different from the surface on the insulating layer side of the skin material for repair (surface) and the other surface different from the surface on the insulating layer side of the skin material (surface) around the defect portion, It is fixed with a reinforcing material for repair having a larger area than the defective part provided in the space where the core material is removed around the defect part,
  In the space from which the core material has been removed, a repair core material having a honeycomb structure of approximately the same size as the space is fitted and fixed to the repair reinforcing material,
  The solar array panel, wherein the insulating layer of the skin material (surface) around the defect portion and the insulating layer of the repairing skin material (surface) are substantially flush with each other. Insulation covering the boundary portion for mounting a solar cell via an insulator on the boundary portion between the repair skin material (surface) and the skin material (surface) around the defect portion, which are substantially flush with each other. The solar array panel according to claim 5, further comprising a layer.

Images