JPS6240873B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a method for manufacturing a solar cell array, and particularly to an adhesive process for fixing a plurality of solar cell elements to a substrate.

Silicon is usually used as the semiconductor material for solar cell elements, but there is a limit to the output due to the characteristics of the semiconductor material. Therefore, when using it for electric power, it is necessary to use multiple solar cells to obtain the desired high output. These solar cell elements are electrically connected in series and parallel to each other to provide power to various devices. A plurality of solar cell elements are generally supported on a flat substrate, and as shown in FIG.
... were arranged at a constant pitch, weights w, w, ... were placed on each solar cell element, and the adhesive 3 was fixed by curing under pressure.

However, in the case of the above-mentioned conventional pressure curing method using a weight w, it is necessary to place a weight on each solar cell element, which not only has very poor workability but also ensures that the substrate 1 is properly leveled. If the solar cell elements are not held in the same position, the positional deviation of the solar cell elements becomes large due to the action of the weight w, and there is a drawback that a solar cell array having a uniform plane cannot be obtained. It also had the disadvantage of being susceptible to vibrations and shocks.

The present invention eliminates the drawbacks of the conventional manufacturing methods described above and provides a method for manufacturing a solar cell array that can efficiently and uniformly fix a plurality of solar cell elements. Next, the present invention will be explained in detail with reference to Examples.

In FIG. 2, a substrate 1 is a plate made of an insulating material or a metal material that has been cut in advance to have a large enough area to mount a plurality of solar cells 2, 2... in an array. It is manufactured in a honeycomb structure in consideration of heat dissipation and mechanical strength when configuring a power supply device for space equipment such as a satellite. A thin insulating sheet 1a is laminated on the surface of the substrate 1 in order to smooth out the holes of the honeycomb. The surface of the insulating sheet 1a is pretreated for adhesive, if necessary, and then adhesive 3 is applied at a constant pitch. The adhesive 3 hardens by applying pressure for a considerable period of time, for example, about 24 hours, and exhibits stronger adhesive force, such as two-component silicone.
RTV is used.

Solar cell elements 2, 2, . . . are arranged in a line shape, matrix shape, etc. on a substrate 1 coated with an adhesive 3 and temporarily fixed. The substrate 1 on which the solar cell elements 2, 2, . The opening 5 of the container 4 allows the substrate 1 to be placed inside the container 4.
After being installed, it is covered with a transparent flexible sheet 6. As the flexible sheet 6, a resin film or the like that can airtightly seal the inside of the container 4 is used. The interior of container 4 is pipe 7.
After being covered with the flexible sheet 6, the vacuum pump is operated to remove the container 4.
The air inside the room is sucked out. Since atmospheric pressure is always acting on the sheet 6, each solar cell element 2 is
A pressing force is applied to the surface of the As a result glue 3
spreads into the gap between the substrate 1 and the solar cell element 2, hardens under pressure, and attaches the solar cell element 2 to the substrate 1.
Fix it firmly. In the adhesive curing step,
By controlling the degree of vacuum within the container 4, the thickness and spread of the adhesive 3 can be controlled.

Mutual electrical connection between the solar cell elements 2, 2... is performed using the connector 8, but the connection of the connector 8 may be performed in any step after or before the adhesive 3 hardens. Can be done.

According to the vacuum pressurization method described above, since atmospheric pressure is used, all of the plurality of solar cell elements can be pressurized uniformly and simultaneously. Further, the solar cell module can be made into various shapes as long as the substrate has a shape that can fit inside the chamber of the container 4.

FIG. 3 is a diagram showing another embodiment according to the present invention,
The substrate 1 is manufactured in the same manner as the embodiment shown in FIG. 2 above. On the other hand, the solar cell elements 2, 2, . . . are aligned and placed on the holding table 9 with their adhesive surfaces facing upward. Adhesives 3, 3, . . . are applied to the adhesive surface facing onto each solar cell element 2, 2, . The substrate 1 is placed on the solar cell element group coated with the adhesive 3.
are placed facing each other, and a pressing force is applied from the back surface of the substrate 1 toward the solar cell element 2 surface, and the adhesive 3
is cured under pressure. The pressing force from the back surface of the substrate is simply applied by tightening screws 10 provided at a plurality of locations on the back surface of the board.

According to this embodiment, not only can a pressing force be applied to a plurality of groups of solar cell elements at once, but also each solar cell element can be positioned in advance on the holding table, and the mutual positional relationship can be precisely determined. Become.

FIG. 4 shows yet another embodiment of the present invention;
Similar to the embodiment shown in the figure, after adhesive 3 is applied onto substrate 1, solar cell elements 2 are placed in each adhesive area and temporarily fixed. Next, in order to pressurize the adhesive 3 from the solar cell element 2 surface, in this embodiment, a pressing plate 12 is used, to which springs 11, 11, . . .
By facing the solar cell element 2 with the elastic force of the spring 11, the adhesive 3 is cured.

As described above, according to the present invention, it is possible to efficiently and uniformly apply a pressing force to the surface of the solar cell array, which has irregularities corresponding to the shape of the solar cell elements, and the adhesive takes a relatively long time to cure. Even when an element is fixed to a substrate using an adhesive, it is possible to adhesively fix the element with high precision, simplifying the production of the solar cell array, and reducing the labor required for the device production process.

[Brief explanation of the drawing]

FIG. 1 is a sectional view for explaining a conventional method, FIG. 2 is a sectional view for explaining an embodiment according to the present invention, and FIGS. 3 and 4 are for explaining other embodiments according to the present invention. FIG. 1: Substrate, 2: Solar cell element, 3: Adhesive,
4: Container, 6: Flexible sheet, 7: Pipe, 9: Holding stand, 10: Screw, 11: Spring.

Claims (1)

[Scope of Claims] 1. In a method for manufacturing a solar cell array in which a plurality of solar cell elements are fixedly arranged on a substrate, a method for manufacturing a solar cell array in which a plurality of solar cell elements arranged in a desired positional relationship is Applying an adhesive to at least one surface between the surface of the substrate that supports the battery element, and simultaneously applying a pressing force to the plane formed by the plurality of solar cell elements and the opposing surface of the substrate, A method for producing a solar cell array, comprising curing the above adhesive under pressure. 2. The method of manufacturing a solar cell array according to claim 1, wherein the pressing force between the opposing surfaces is applied by vacuum suction. 3. The method of manufacturing a solar cell array according to claim 1, wherein the pressing force between the opposing surfaces is applied from the back side of the substrate. 4. The method of manufacturing a solar cell array according to claim 1, wherein the pressing force between the opposing surfaces is applied by elastic force from a spring on the solar cell element surface.