JP2021146854A - Deployable solar cell, deployment structure, and spacecraft - Google Patents

Abstract

To provide a deployable solar cell having a structure capable of easily obtaining more sufficient rigidity.SOLUTION: A deployable solar cell 100 comprises: a deployment axis 11; a plurality of supports 20 formed in a plane shape parallel to the deployment axis 11 and formed in an elongated shape in a radial direction, respectively; a support film 30 supported by one side edge (upper edge 21a) on the deployment axis 11 of each of the plurality of supports 20; and a solar cell supported by the support film 30. The plurality of supports 20 include a first support 20a and a second support 20b that can open relative to each other with the deployment axis 11 as a reference, and an intermediate support 20c arranged between the first support 20a and the second support 20b in an opening direction of the first support 20a and the second support 20b. The support film 30 is configured so that it can be converted from a folded state to a deployed state between the adjacent supports 20 in step with the opening operation of the first support 20a and the second support 20b.SELECTED DRAWING: Figure 2

Description

The present invention relates to deployable solar cells, deployable structures, and spacecraft.

As a deployable solar cell used in outer space, there is one described in Patent Document 1.
The deployable solar cell of Patent Document 1 has a structure in which a solar cell panel is provided on a film that can be bent along a radial bending line with respect to a deployment axis. The film of this unfoldable solar cell is converted from a folded state to an unfolded state by an unfolding operation.

U.S. Pat. No. 9,352,853

However, according to the study by the present inventors, there is room for improvement in the rigidity of the deployable solar cell of Patent Document 1.

The present invention has been made in view of the above problems, and provides a deployable solar cell, a deployable structure, and a spacecraft having a structure capable of easily obtaining more sufficient rigidity.

According to the present invention, the deployment axis and
A plurality of supports formed in a plane parallel to the development axis and elongated in the radial direction, respectively.
A support film supported by one side edge of each of the plurality of supports on the development axis, and a support film.
The solar cell supported by the support film and
With
The plurality of supports include a first support and a second support that can mutually open with respect to the deployment axis, and the first support in the opening direction of the first support and the second support. An intermediate support, which is arranged between the body and the second support, is included.
Provided is a deployable solar cell in which the support film is configured to be convertible from a folded state to an unfolded state between adjacent supports as the first support and the second support are opened. NS.

Further, according to the present invention, the deployment axis and
A plurality of supports formed in a plane parallel to the development axis and elongated in the radial direction, respectively.
A support film supported by one side edge of each of the plurality of supports on the development axis, and a support film.
With
The plurality of supports include a first support and a second support that can mutually open with respect to the deployment axis, and the first support in the opening direction of the first support and the second support. An intermediate support, which is arranged between the body and the second support, is included.
The support film is provided with an unfolded structure that is configured to be convertible from a folded state to an unfolded state between adjacent supports as the first support and the second support are opened. ..

Further, according to the present invention, the structure and
With the deployable solar cell of the present invention or the deployable structure of the present invention,
A spacecraft equipped with is provided.

According to the present invention, it is possible to realize a deployable solar cell or a deployable structure having a structure capable of easily obtaining more sufficient rigidity.

It is a perspective view of the deployable solar cell which concerns on 1st Embodiment, and shows the deployed state. It is a perspective view of the deployable solar cell which concerns on 1st Embodiment, and shows the state (intermediate state) between the expanded state and the stored state (folded state). It is a perspective view of the deployable solar cell which concerns on 1st Embodiment, and shows the stored state (folded state). It is a top view of the deployable solar cell which concerns on 1st Embodiment, and shows the deployed state. 5 (a), 5 (b) and 5 (c) are views showing the first film member and the second film member constituting the support film of the deployable solar cell according to the first embodiment. Of these, FIG. 5 (a) is a perspective view of the first film member and the second film member in the intermediate state, and FIG. 5 (b) is a side view of the first film member and the second film member in the intermediate state, FIG. 5 (c). Is a side view of the first film member and the second film member in the stored state (folded state). It is a top view which shows the arrangement example of the solar cell in the deployable solar cell which concerns on 1st Embodiment. It is a perspective view for demonstrating the deployment mechanism of the deployable solar cell which concerns on 1st Embodiment. It is sectional drawing for demonstrating the deployment mechanism of the deployable solar cell which concerns on 1st Embodiment. 9 (a) and 9 (b) are diagrams for explaining the support structure of the support film in the deployable solar cell according to the second embodiment, of which FIG. 9 (a) is a view of the deployable solar cell. A perspective view showing the unfolded state, FIG. 9B is a schematic view of the support viewed in the radial direction. It is a perspective view of the deployable solar cell which concerns on 3rd Embodiment, and shows the deployed state. It is a perspective view of the deployable solar cell which concerns on 4th Embodiment, and shows the deployed state. It is a perspective view of the deployable solar cell which concerns on 4th Embodiment, and shows the state (intermediate state) between the expanded state and the stored state (folded state). It is a perspective view of the deployable solar cell which concerns on 4th Embodiment, and shows the stored state (folded state). It is a top view of the deployable solar cell which concerns on 4th Embodiment, and shows the deployed state. It is a perspective view which shows the spacecraft which concerns on embodiment.

Hereinafter, embodiments of the present invention will be described with reference to the drawings. In all the drawings, the same components are designated by the same reference numerals, and the description thereof will be omitted as appropriate.

[First Embodiment]
First, the first embodiment will be described with reference to FIGS. 1 to 8.
7 is a perspective view of the central portion of the deployable solar cell 100 viewed from the lower surface side, and FIG. 8 is a plan sectional view of the central portion of the deployable solar cell 100 viewed from the lower surface side.
As shown in any of FIGS. 1 to 4, the deployable solar cell 100 according to the present embodiment is formed in a plane shape parallel to the deployable shaft 11 and in the radial direction, respectively. A plurality of long supports 20, a support film 30 supported by one side edge (upper edge 21a) of each of the plurality of supports 20 on the development axis 11, and a support film 30. It includes a supported solar cell 71 (FIG. 6). The solar cell 71 is provided on the support film 30 in the form of a cell unit 72 in which a plurality of solar cell 71s are unitized, for example.
The plurality of supports 20 include a first support 20a and a second support 20b that can mutually open with respect to the deployment axis 11, and a first support 20a and a second support 20b in the opening direction of the first support 20a and the second support 20b. An intermediate support 20c, which is arranged between the support 20a and the second support 20b, is included.
The support film 30 is configured so that it can be converted from a folded state to an unfolded state between adjacent supports 20 as the first support 20a and the second support 20b are opened.

According to the present embodiment, since each of the supports 20 supporting the support film 30 is formed in a plane shape parallel to the deployment shaft 11, sufficient rigidity of each support 20 can be ensured. As a result, the overall rigidity of the deployable solar cell 100 can be sufficiently ensured. Therefore, the solar cell 71 can be stably supported.

Further, the deployable structure 80 according to the present embodiment is obtained by removing the solar cell 71 (cell unit 72) from the deployable solar cell 100 according to the present embodiment.
That is, the unfolding structure 80 according to the present embodiment has a plurality of supports 20 formed in a plane shape parallel to the unfolding shaft 11 and elongated in the radial direction, respectively. And a support film 30 supported by one side edge (upper edge 21a) of each of the plurality of supports 20 on the deployment shaft 11, and the plurality of supports 20 are based on the deployment shaft 11. Between the first support 20a and the second support 20b and the first support 20a and the second support 20b in the opening direction of the first support 20a and the second support 20b. The arranged intermediate support 20c and the support film 30 are included, and the support film 30 is unfolded from a folded state between adjacent supports 20 as the first support 20a and the second support 20b are opened. It is configured to be convertible into a state.
In the present embodiment, an example in which the support film 30 of the unfolding structure 80 supports the solar cell 71 (cell unit 72) will be described. However, in the present invention, the unfolding structure 80 is supported by the support film 30. The mode is not limited to supporting the solar cell 71 (cell unit 72), and other objects (for example, sensors) may be supported by the support film 30.

In FIGS. 1, 2, 4 and the like, the solar cell 71 (cell unit 72) is not shown.
In the present specification, for convenience, one side (the side on which the upper edge 21a is located) of the deployment shaft 11 is referred to as an upper side, and the opposite side is referred to as a lower side. This convenient vertical direction does not always coincide with the vertical direction when the deployable solar cell 100 or the deployable structure 80 is manufactured or used. The radial direction is the radial direction centered on the deployment axis 11.

The deployable solar cell 100 or the deployable structure 80 is deployed, for example, in outer space. However, the place where the deployable solar cell 100 or the deployable structure 80 is used is not limited to outer space, and may be, for example, the ground or the stratosphere.

The deployment shaft 11 is formed in the shape of a straight rod extending vertically.
The support structure portion 12 that supports the support film 30 is composed of the plurality of supports 20. The support structure portion 12 can be deployed around the deployment shaft 11. The number of supports 20 included in the support structure portion 12 is not particularly limited, but in the case of the present embodiment, the support structure portion 12 includes, for example, five supports 20.
The supports 20 are arranged substantially rotationally symmetric in a plan view (when the support structure portion 12 is viewed in the axial direction of the deployment axis 11).

As shown in FIG. 4, in the deployed state, the plurality of supports 20 are arranged radially around the deployed shaft 11. That is, in the deployed state, the planar shape of the support structure portion 12 (the planar shape surrounding the distal ends of each support 20) is pentagonal.

As shown in FIG. 3, in the stored state, the plurality of supports 20 are in a state of being stretched in substantially the same direction with respect to the deployment shaft 11. In other words, in the retracted state, the plurality of supports 20 included in the support structure portion 12 are in a state of being close to each other in the circumferential direction and overlapping each other in the circumferential direction.
In the stored state, the portion of the support film 30 erected between the adjacent supports 20 is sandwiched between the supports 20 and folded. Therefore, when the deployable solar cell 100 is launched into outer space or the like, the solar cell 71 on the support film 30 can be protected from the launch environment by the support 20.

Hereinafter, in the deployable solar cell 100, the portion between the pair of adjacent supports 20 may be referred to as a unit module 15. Adjacent unit modules 15 share a support 20 located at their boundary. In the case of the present embodiment, the deployable solar cell 100 includes four unit modules 15.

Each of the first support 20a, the second support 20b, and the intermediate support 20c is formed in a thin plate shape. That is, each support 20 is formed in a thin plate shape that is long in the radial direction centered on the deployment shaft 11 and parallel to the deployment shaft 11.

More specifically, the support 20 includes a flat plate-shaped portion 21 and a first support arm 25 (FIG. 3) and a second support arm 26 (FIG. 3) fixed to the plate-shaped portion 21. It is configured to prepare.
The plate-shaped portion 21 is formed in a thin plate shape that is long in the radial direction about the deployment shaft 11 and parallel to the deployment shaft 11.

The first support arm 25 and the second support arm 26 are pivotally supported by the deployment shaft 11.
That is, an insertion hole is formed at one end of the first support arm 25, and the deployment shaft 11 is inserted into the insertion hole so that the first support arm 25 can rotate around the axis of the deployment shaft 11. It is pivotally supported by.
Similarly, an insertion hole is formed at one end of the second support arm 26, and when the deployment shaft 11 is inserted through the insertion hole, the second support arm 26 rotates around the axis of the deployment shaft 11. It is possible to support the axis.
However, of the plurality of supports 20, the first support arm 25 and the second support arm 26 of the first support 20a may be fixed to the deployment shaft 11.

The other end of the first support arm 25, that is, the tip portion 25b, and the other end portion, that is, the tip portion 26b of the second support arm 26 are fixed to the radial inner end portion of the plate-shaped portion 21.
The plate-shaped portion 21 has, for example, a pair of upper and lower extending portions (first extending portion 22 and second extending portion 23 (FIG. 7)) extending inward in the radial direction.
The tip portion 25b of the first support arm 25 is fixed to the first extension portion 22 of the plate-shaped portion 21, and the tip portion 26b of the second support arm 26 is the second extension portion 23 of the plate-shaped portion 21. It is fixed to. As a result, the plate-shaped portion 21 is pivotally supported on the deployment shaft 11 via a pair of upper and lower support arms (first support arm 25, second support arm 26). That is, the support body 20 including the plate-shaped portion 21, the first support arm 25, and the second support arm 26 is pivotally supported by the deployment shaft 11.
In each support 20, the height difference between the height position where the first extension portion 22 is arranged and the height position where the second extension portion 23 is arranged is such that the first support arm 25 is arranged. It is equal to the height difference between the current height position and the height position where the second support arm 26 is arranged.

Here, the height positions of the first support arms 25 of the supports 20 adjacent to each other are different from each other by the thickness of the first support arm 25.
Similarly, the height positions of the second support arms 26 of the supports 20 adjacent to each other are different from each other by the thickness of the second support arm 26.
As shown in FIG. 3, the first support arms 25 are arranged so as to be overlapped with each other, and the second support arms 26 are arranged so as to be overlapped with each other.

In the case of the present embodiment, the dimensions of the first support 20a, the second support 20b, and the intermediate support 20c are the same in the axial direction of the deployment shaft 11. That is, the vertical dimensions of each support 20 are the same as each other.

More specifically, for example, the vertical dimensions of each support 20 are equal to each other. Further, the longitudinal dimensions (dimensions in the radial direction) of each support 20 are equal to each other.
As shown in FIG. 1, for example, the vertical dimension of the support 20 gradually increases toward the tip side (outward in the radial direction).
More specifically, the upper edge 21a of the plate-shaped portion 21 constituting the support 20 extends (horizontally extends) in a direction orthogonal to the deployment axis 11, for example. On the other hand, the lower edge 21b of the plate-shaped portion 21 is inclined downward as it goes away from the deployment shaft 11, for example. The distal edge 21c of the plate-shaped portion 21 (the edge far from the deployment axis 11) extends parallel to, for example, the deployment axis 11. Further, the proximal end edge 21d of the plate-shaped portion 21 (the end edge on the side closer to the deployment axis 11) extends parallel to, for example, the deployment axis 11.

As shown in FIG. 1, the support film 30 is erected between the edge of the first support 20a on one side of the deployment shaft 11 and the edge of the second support 20b. That is, the support film 30 is erected between the upper edge 21a of the first support 20a and the upper edge 21a of the second support 20b. Each part of the support film 30 is erected between the upper edges 21a of the adjacent supports 20.
When the deployable solar cell 100 shifts from the stored state to the deployed state, the support film 30 converts from the folded state shown in FIG. 3 to the expanded state shown in FIGS. 1 and 4 through the intermediate state shown in FIG. .. For example, in the unfolded state, the entire support film 30 is arranged flat and horizontally.

In the case of the present embodiment, when the first support 20a and the second support 20b are open, the combined shape of the first support 20a and the second support 20b is V-shaped in a plan view. At the same time, the support film 30 becomes substantially fan-shaped, and a blank portion 34 in which the support film 30 does not exist is formed between the first support 20a and the second support 20b.

As shown in FIG. 4, in the case of the present embodiment, the support film 30 includes a first film portion 31 arranged on the outer side in the radial direction, a second film portion 32 arranged on the inner side in the radial direction, and the like. including. The first film portion 31 and the second film portion 32 are separated from each other through the slit 43.
As will be described later, the first film portion 31 and the second film portion 32 each support a separate solar cell 71.

The first film portion 31 may be an integral film as a whole, or may be an aggregate of a plurality of films individually arranged for each portion between adjacent supports 20. In the case of this embodiment, the structure of the first film portion 31 is the latter.
That is, in the case of the present embodiment, the first film portion 31 is, for example, an aggregate of four first film members 35 each having a substantially fan shape. At both ends of each first film member 35 in the circumferential direction, attachment portions 37 for attaching the first film member 35 (FIGS. 1, FIG. 5 (a), FIG. 5 (b), FIG. 5 (c)). ) Are formed respectively.
In the first film member 35, one of the two sticking portions 37 of the first film member 35 is stuck to the upper edge portion (the portion along the upper edge 21a) of one of the adjacent supports 20. The other of the two sticking portions 37 is erected between the adjacent supports 20 by being stuck to the upper edge portion of the other of the adjacent supports 20.

Similarly, the second film portion 32 may be an integral film as a whole, or may be an aggregate of a plurality of films individually arranged for each portion between adjacent supports 20. good. In the case of this embodiment, the structure of the second film portion 32 is the latter.
That is, in the case of the present embodiment, the second film portion 32 is, for example, an aggregate of four second film members 36 each having a substantially fan shape. At both ends of each second film member 36 in the circumferential direction, attachment portions 37 for attaching the second film member 36 (FIGS. 1, FIG. 5 (a), FIG. 5 (b), FIG. 5 (c)). ) Are formed respectively.
In the second film member 36, one of the two attachment portions 37 of the second film member 36 is attached to the upper edge portion (the portion along the upper edge 21a) of one of the adjacent supports 20. The other of the two sticking portions 37 is erected between the adjacent supports 20 by being stuck to the upper edge portion of the other of the adjacent supports 20.

As shown in FIG. 4, a slit 43 is formed between the first film member 35 and the second film member 36 so that the first film member 35 and the second film member 36 do not interfere with each other.

When the support film 30 is in the folded state, the number of bending lines 41 (see FIG. 2) of the first film portion 31 between the adjacent supports 20 is larger than the number of the second film between the adjacent supports 20. The number of bending lines 42 of the portion 32 is smaller.
As a result, the support film 30 can be folded so that the support film 30 has a small vertical dimension on the outer side (outer peripheral side) in the radial direction of the deployable solar cell 100 in the stored state, and the deployable solar cell 30 can be folded. On the inner side (central portion) of the battery 100 in the radial direction, the bulkiness of the support film 30 in the circumferential direction can be suppressed.

In the case of the present embodiment, the first film portion 31 is folded in a W shape between the adjacent supports 20. That is, as shown in FIGS. 2 and 5A, the portion of the first film portion 31 located between the adjacent supports 20 is a folding line 41, which is two valley folding lines 41a and one. It is folded into a shape having a mountain fold line 41b. Each bending line 41 extends radially around the development axis 11 in a plan view. Here, the valley fold line is a fold line that is convex downward, and the mountain fold line is a fold line that is convex upward.
Further, the second film portion 32 is folded in a V shape between the adjacent supports 20. That is, as shown in FIGS. 2 and 5A, the portion of the second film portion 32 located between the adjacent supports 20 has a shape having one bending line 42 which is a valley fold line. It can be folded. The folding line 42 extends radially around the development axis 11 in a plan view.

As shown in FIG. 4, each first film member 35 has a substantially fan-shaped shape as if four isosceles triangles having the same shape are connected in the circumferential direction. Among the isosceles triangles constituting the first film member 35, the boundary line between the adjacent isosceles triangles is a bending line 41 (valley fold line 41a or mountain fold line 41b).
Similarly, each of the second film members 36 has a substantially fan-shaped shape as if two isosceles triangles having the same shape are connected in the circumferential direction. Of the isosceles triangles constituting the second film member 36, the boundary line between the adjacent isosceles triangles is the bending line 42.
The substantially fan-shaped central angle of the first film member 35 and the substantially fan-shaped central angle of the second film member 36 are equal to each other, and the substantially fan-shaped center of the first film member 35 and the second film member The center of the substantially fan-shaped shape of 36 is the position of the deployment shaft 11.

As an example, in the central portion of the deployable solar cell 100 in a plan view, a substantially fan-shaped opening (central opening 39) is formed in a portion between adjacent supports 20 around the deployable shaft 11. ing. The support film 30 (second film portion 32 and first film portion 31) is arranged outside the central opening 39.

For example, the support film 30 is preliminarily habituated so that it can be easily bent at the bending line (folding line 41, bending line 42). In the case of the present embodiment, the first film member 35 is preliminarily habituated at the valley fold line 41a and the mountain fold line 41b so as to be easily bent into the valley fold and the mountain fold, respectively. Similarly, the second film member 36 is pre-habited so that it can be easily bent in a valley fold at the bending line 42.

However, in the support film 30, it is also preferable that the portions on both sides of the support film 30 with the bending line as the boundary are formed of separate films and are connected to each other via a surface bonding material such as a flexible tape. Also in this case, the support film 30 can be easily bent at the bending line.

The material of the support film 30 is not particularly limited, but as an example, the support film 30 is made of a resin material such as polyimide.

Here, it is preferable that the outer edge (outer edge 33) of the support film 30 in the radial direction is reinforced as compared with the portion of the support film 30 adjacent to the edge.
In the case of the present embodiment, a reinforcing tape is attached to the back surface (lower surface) of the support film 30 along the outer edge 33. As a result, the outer edge 33 of the support film 30 becomes the reinforcing portion 38. That is, the edge is reinforced by attaching the reinforcing tape to the outer edge (outer edge 33) of the support film 30 in the radial direction.
As shown in FIGS. 1 and 4, the reinforcing portion 38 is preferably divided with each bending line as a boundary. By doing so, the support film 30 can be easily bent at each bending line.

Next, an arrangement example of the solar cell 71 in the deployable solar cell 100 will be described with reference to FIG.
As shown in FIG. 6, in the case of the present embodiment, the solar cell 71 is provided on the support film 30 in the form of a cell unit 72 in which a plurality of solar cells 71 are connected in series and unitized, for example. Has been done.
In addition, in FIG. 6, among the solar cell 71 included in the deployable solar cell 100, the solar cell 71 arranged in a half portion in the circumferential direction of one first film member 35 and one second. Only the solar cell 71 arranged in a half portion in the circumferential direction of the film member 36 is shown, and the other solar cell 71 is not shown. The solar cells 71 (not shown) are arranged with the same regularity as the illustrated solar cells 71.
On the second film member 36 of the second film portion 32, for example, two cell units 72 are arranged in parallel with each other along the radial direction in a region on one side with the bending line 42 as a boundary.
On the first film member 35 of the first film portion 31, for example, in a region on one side with the valley fold line 41a as a boundary, two rows of cell units along the radial direction are arranged in order from the center side in the radial direction of the folding line 41. 72, 1 row of cell units 72 along the circumferential direction, 3 rows of cell units 72 along the radial direction, 4 rows of cell units 72 along the radial direction, 4 more rows of cell units 72 along the radial direction, and diameter Five more rows of cell units 72 are arranged along the direction.
The arrangement of the cell unit 72 and the solar cell 71 described here is an example, and is changed according to the required power generation capacity and the like.

Here, the cell unit 72 is arranged so as not to straddle any of the bending lines. Further, in the first film portion 31 and the second film portion 32, cell units 72 are arranged in regions on both sides sandwiching each bending line.
That is, in the first film portion 31, the solar cell 71 is not arranged on the folding line 41 (valley fold line 41a, mountain fold line 41b), and each of them is on both regions sandwiching the folding line 41. The solar cell 71 is arranged. Similarly, in the second film portion 32, the solar cell 71 is not arranged on the folding line 42, and the solar cell 71 is arranged on both regions sandwiching the folding line 42.
Therefore, it is possible to prevent the solar cell 71 from hindering the bending of the support film 30, and it is possible to realize a structure in which the solar cell 71 is evenly arranged in each region on the support film 30.

Here, as shown in FIG. 1, it is preferable that a cross cable 51 is provided at the distal end of the support structure portion 12. The cross cable 51 connects, for example, the upper end (upper corner portion 21e) and the lower end (lower corner portion 21f) of the distal end edges 21c of the plate-shaped portions 21 of the supports 20 adjacent to each other. Note that the cross cable 51 is not shown in FIGS. 2 and 3 and the like.

Next, an example of a deployment mechanism for deploying the deployable solar cell 100 will be described with reference to FIGS. 7 and 8.
In the case of the present embodiment, the deployable solar cell 100 performs a deployable operation using, for example, the urging force of the deployable leaf spring 52 as a power source. The unfolding leaf spring 52 is a winding spring that is spirally wound. One end of the deploying leaf spring 52 is fixed to the first fixing portion 53, and the first fixing portion 53 is fixed to the deploying shaft 11. Further, the first support arm 25 and the second support arm 26 of the first support 20a are fixed to, for example, the deployment shaft 11.
In the initial state, the deploying leaf spring 52 is in a state of accumulating elastic restoring force. Then, the deploying leaf spring 52 is held in a state in which the elastic restoring force is stored by a restraining member (not shown). After launching the deployable solar cell 100 into outer space or the like, the deployable leaf spring 52 is elastically restored by, for example, destroying the restraint member by blasting. As a result, the first support 20a and the second support 20b rotate and open relatively on the deployment shaft 11, and the support film 30 changes from the folded state to the deployed state.
The deployment mechanism of the deployable solar cell 100 is not limited to this example, and may be configured to include, for example, a motor.

Further, the deployable solar cell 100 may include a latch mechanism (not shown) for maintaining the deployable solar cell 100 in the deployed state.
Further, the deployable solar cell 100 may be capable of being deformed from the deployed state to the stored state (folded state) again after being deployed once. Further, if necessary, it may be possible to stop the unfolding operation in the middle, fold the deployable solar cell 100, and then redo the unfolding operation.

The material of the plate-shaped portion 21 of the support 20 is not particularly limited, but the plate-shaped portion 21 can be made of, for example, carbon fiber reinforced plastics (CFRP).
The material of each part other than the plate-shaped part 21 and the support film 30 in the deployable solar cell 100 is not particularly limited, but is preferably a material that is lightweight and can secure sufficient strength, and as an example, carbon fiber reinforced plastic is used. It may be used, or a metal material may be used.

Here, the deployable solar cell 100 is fixed to the boom 61. The boom 61 is connected to the structure of the spacecraft (hereinafter, space mechanism) via, for example, a boom deployment mechanism (not shown).
The boom 61 is formed, for example, in the shape of a long rod in one direction. The boom 61 extends in the radial direction centered on the deployment shaft 11. For example, one end of the boom 61 is connected to the upper end of the deployment shaft 11 via a connecting member (not shown).
For example, after the first support 20a and the second support 20b are mutually opened by the above-mentioned deployment mechanism to bring the support film 30 into the deployed state, the boom is further caused by the rotation of the deploying shaft 11 around the axis. The deployment structure 80 is provided with a stopper mechanism (not shown) so that the deployment 61 rotates and the rotation of the deployment shaft 11 and the rotation of the boom 61 stop at the positions shown in FIGS. 1 and 4. As a result, in a plan view, the boom 61 extends radially at an intermediate position between the first support 20a and the second support 20b.

Next, the spacecraft 200 according to the present embodiment will be described with reference to FIG.
The spacecraft 200 according to the present embodiment includes a structure (space mechanism) 210 and a deployable solar cell 100 or a deployable structure 80 according to the present embodiment.

Here, it can be mentioned that the spacecraft 200 is provided in the structure 210 and includes an imaging unit 220 (camera) for capturing an image. In this case, it is preferable that the blank portion 34 is located in the field of view of the imaging unit 220 (particularly, the imaging unit 220a shown in FIG. 15). That is, it is preferable that the deployable solar cell 100 or the deployable structure 80 has a structure that secures the field of view of the imaging unit 220a.
As described above, as a preferable example, in a state where the first support 20a and the second support 20b are open, the first support 20a and the second support 20b are V-shaped, and the support film 30 is formed. A fan-shaped blank portion 34 is formed between the first support 20a and the second support 20b in which the support film 30 does not exist, and the blank portion 34 is located in the visual field direction of the imaging unit 220a.

[Second Embodiment]
Next, the second embodiment will be described with reference to FIGS. 9 (a) and 9 (b).
The deployable solar cell 100 according to the present embodiment is different from the deployable solar cell 100 according to the first embodiment in that it will be described below, and in other respects, it is the same as the first embodiment. It is configured in the same manner as the deployable solar cell 100.

In the first embodiment described above, the support film 30 (first film portion) is formed by attaching the sticking portions 37 at both ends of the first film member 35 and the second film member 36 to the plate-shaped portion 21 of the support body 20. An example in which 31 and the second film portion 32) are supported by a plurality of supports 20 has been described. Further, an example in which the first film portion 31 and the second film portion 32 are divided into a plurality of portions in the circumferential direction has been described (the first film portion 31 is composed of a plurality of first film members 35, and the first film portion 31 is composed of a plurality of first film members 35. An example in which the second film portion 32 is composed of a plurality of second film members 36 has been described).
On the other hand, in the case of the present embodiment, the deployable solar cell 100 includes a support member 62 provided on the upper edge 21a of the support 20, and the support film 30 is supported via the support member 62. Supported by body 20.
Further, as shown in FIG. 9A, it is preferable that the support members 62 are provided at a plurality of positions in the longitudinal direction of the upper edge 21a. Further, in the stored state, in order to prevent the support members 62 provided on the adjacent supports 20 from interfering with each other, the support members 62 provided on the adjacent supports 20 are displaced from each other in the radial direction. It is preferable that it is arranged in a vertical position.
For example, the support member 62 is arranged horizontally, and the shape of the support member 62 and the plate-shaped portion 21 combined is T-shaped (FIG. 9B).
In the case of the present embodiment, the support film 30 can be continuously present in the circumferential direction over both side portions straddling the support member 62 provided on the plate-shaped portion 21. That is, for example, each of the first film member 35 and the second film member 36 can be made to exist continuously in the circumferential direction over both side portions straddling the support member 62 provided on the plate-shaped portion 21. .. Therefore, for example, the first film portion 31 may be composed of one first film member 35, or the second film portion 32 may be composed of one second film member 36.

[Third Embodiment]
Next, the third embodiment will be described with reference to FIG.
The deployable solar cell 100 according to the present embodiment is different from the deployable solar cell 100 according to the first embodiment in that it will be described below, and in other respects, it is the same as the first embodiment. It is configured in the same manner as the deployable solar cell 100.

As shown in FIG. 10, in the case of the present embodiment, the deployable solar cell 100 further includes a second support film 90 provided on the back surface side (lower surface side). That is, since each support 20 is formed in a plane shape parallel to the development shaft 11, the support film (second support film 90) can be easily attached to the back surface side as well. The second support film 90 supports, for example, a specific function unit 95 such as a sensor.
That is, in the case of the present embodiment, the deployable solar cell 100 has the other edge (lower edge 21b) of each of the first support 20a, the second support 20b, and the intermediate support 20c on the deployment shaft 11. It includes a second support film 90 supported by the second support film 90 and a specific functional portion supported by the second support film 90.
The second support film 90 is erected between the edge (lower edge 21b) of the first support 20a on the other side of the deployment shaft 11 and the edge (lower edge 21b) of the second support 20b, and the second support film 90 is erected. It is configured so that it can be converted from a folded state to an unfolded state between adjacent supports 20 as the 1 support 20a and the second support 20b are opened.
Further, the specific function unit 95 is configured to include, for example, a sensor.
As an example, the specific function unit 95 may be a film-shaped debris sensor for detecting debris, a film-shaped flat antenna, a solar sail, or the like.

[Fourth Embodiment]
Next, the fourth embodiment will be described with reference to FIGS. 11 to 14.
The deployable solar cell 100 according to the present embodiment is different from the deployable solar cell 100 according to the first embodiment in that it will be described below, and in other respects, it is the same as the first embodiment. It is configured in the same manner as the deployable solar cell 100.

In the first embodiment described above, an example in which the deployable solar cell 100 has a pentagonal shape in the deployed state has been described. On the other hand, in the case of the present embodiment, the deployable solar cell 100 has a hexagonal shape in the deployed state.
Further, in the case of the present embodiment, the deployable solar cell 100 has a shape that does not have a blank portion 34 in the deployed state. Therefore, in the deployed state, the first support 20a and the second support 20b are in surface contact with each other (see FIG. 11).
In the case of the present embodiment, the boom 61 may be provided on, for example, any support 20 (for example, the second support 20b).
Further, in the first embodiment described above, an example in which the support film 30 is configured to include the first film portion 31 and the second film portion 32 has been described, but in the case of the present embodiment, the support film 30 is configured. The film member 30a to be formed is not separated between the inner side and the outer side in the radial direction, and is divided into a plurality of parts only in the circumferential direction.
In the case of the present embodiment, the portion of the support film 30 located between the adjacent supports 20 is folded in a W shape (see FIG. 12). Therefore, three bending lines 44 of the support film 30 are formed between the adjacent supports 20. Each film member 30a is folded into a shape having two valley fold lines 44a and one mountain fold line 44b. Each bending line 44 extends radially around the development axis 11 in a plan view.

As an example, FIG. 14 and the like show an example in which the outer edge 33 is linear in each unit module 15. In this case, the support film 30 can be better flattened in the unfolded state, and the outer edge 33 becomes linear, so that a larger tension can be easily applied to the outer edge 33. In this case, the portions of the support film 30 bordered by the bending lines 44a and 44b have a shape in which they do not completely overlap each other in the folded state (adjacent portions have different shapes).
However, the portions bordered by the folding lines 44a and 44b may be congruent and substantially isosceles triangles so as to completely overlap each other in the folded state. In this case, the area of the support film 30 can be increased.

Although each embodiment has been described above with reference to the drawings, these are examples of the present invention, and various configurations other than the above can be adopted.

For example, in the above-mentioned third embodiment, the example in which the deployable solar cell 100 is provided with the second support film 90 on the back surface side and the specific function portion 95 such as a sensor is supported by the second support film 90 has been described. The present invention is not limited to this example, and the deployable solar cell 100 may include a reflector portion (antenna portion) instead of the second support film 90.
That is, the deployable solar cell 100 is supported by, for example, the other edge (lower edge 21b) of each of the first support 20a, the second support 20b, and the intermediate support 20c on the deployment shaft 11. It is equipped with a reflector section.
The reflector unit may be, for example, a SAR (SAR: Synthetic Aperture Radar), a synthetic aperture radar, a transmission or reception antenna for communication, or the like.

Further, in each of the above embodiments, the example in which the solar cell 71 is supported by the support film 30 has been described, but in the present invention, the developed structure 80 does not necessarily support the solar cell 71. good. For example, the support film 30 of the deployable structure 80 may support any one or more of a flat antenna, a sensor, a solar sail, and the like instead of supporting the solar cell 71.

In addition, each of the above embodiments can be appropriately combined as long as the gist of the present invention is not deviated.

This embodiment includes the following technical ideas.
(1) Deployment axis and
A plurality of supports formed in a plane parallel to the development axis and elongated in the radial direction, respectively.
A support film supported by one side edge of each of the plurality of supports on the development axis, and a support film.
The solar cell supported by the support film and
With
The plurality of supports include a first support and a second support that can mutually open with respect to the deployment axis, and the first support in the opening direction of the first support and the second support. An intermediate support, which is arranged between the body and the second support, is included.
The support film is a deployable solar cell configured so that it can be converted from a folded state to a deployed state between adjacent supports as the first support and the second support are opened.
(2) The deployable solar cell according to (1), wherein each of the first support, the second support, and the intermediate support is formed in a thin plate shape.
(3) The deployable solar cell according to (1) or (2), wherein the dimensions of the first support, the second support, and the intermediate support are the same in the axial direction of the deploy axis. ..
(4) The deployable sun according to any one of (1) to (3), wherein the outer edge of the support film in the radial direction is reinforced as compared with a portion of the support film adjacent to the edge. battery.
(5) The deployable solar cell according to (4), wherein the edge is reinforced by attaching a reinforcing tape to the outer edge of the support film in the radial direction.
(6) The support film includes a first film portion arranged on the outer side in the radial direction and a second film portion arranged on the inner side in the radial direction.
The first film portion and the second film portion are separated from each other through a slit.
Separate solar cells are supported by the first film portion and the second film portion.
When the support film is in the folded state, the number of bending lines of the first film portion between the adjacent supports is larger than the number of bending lines of the second film portion between the adjacent supports. The deployable solar cell according to any one of (1) to (5), wherein the number of solar cells is smaller.
(7) In the first film portion, the solar cell is not arranged on the bending line, and the solar cell is arranged on both regions sandwiching the bending line.
The second film portion, according to (6), wherein the solar cell is not arranged on the bending line, and the solar cell is arranged on both regions sandwiching the bending line. Deployable solar cell.
(8) A second support film supported by the other edge of the development axis of each of the first support, the second support, and the intermediate support.
The specific functional part supported by the second support film and
With
The second support film is configured to be convertible from a folded state to an unfolded state between the adjacent supports as the first support and the second support are opened (1). The deployable solar cell according to any one of 7).
(9) The deployable solar cell according to (8), wherein the specific function unit includes a sensor.
(10) Each of the first support, the second support, and the intermediate support is provided with a reflector portion supported by the other edge of the deployment axis (1) to (7). The deployable solar cell according to any one item.
(11) Deployment axis and
A plurality of supports formed in a plane parallel to the development axis and elongated in the radial direction, respectively.
A support film supported by one side edge of each of the plurality of supports on the development axis, and a support film.
With
The plurality of supports include a first support and a second support that can mutually open with respect to the deployment axis, and the first support in the opening direction of the first support and the second support. An intermediate support, which is arranged between the body and the second support, is included.
The support film is a developed structure that can be converted from a folded state to an unfolded state between adjacent supports as the first support and the second support are opened.
(12) Structure and
The deployable solar cell according to any one of (1) to (10) or the deployable structure according to (11).
Spacecraft equipped with.
(13) An image pickup unit provided in the structure for capturing an image is further provided.
In a state where the first support and the second support are open, the first support and the second support have a V shape, and the support film has a fan shape, so that the first support has a fan shape. The spacecraft according to (12), wherein a blank portion in which the support film does not exist is formed between the spacecraft and the second support, and the blank portion is located in the visual field direction of the imaging unit.

11 Deployment shaft 12 Support structure 15 Unit module 20 Support 20a First support 20b Second support 20c Intermediate support 21 Plate-shaped portion 21a Upper edge (one side edge on the deployment axis)
21b Lower edge (the other edge on the deployment axis)
21c Distal edge 21d Proximal edge 21e Upper corner 21f Lower corner 22 First extension 23 Second extension 25 First support arm 25b Tip 26 Second support arm 26b Tip 30 Support film 30a Membrane member 31 First film part 32 Second film part 33 Outer edge 34 Blank part 35 First film member 36 Second film member 37 Attached part 38 Reinforcing part 39 Central opening 41 Bending line (Bending line of the first film part)
41a valley fold line (folding line of the first film part)
41b mountain fold line (folding line of the first film part)
42 Bending line (Bending line of the second film part)
43 Slit 44 Bending line 44a Valley fold line 44b Mountain fold line 51 Cross cable 52 Deployment leaf spring 53 First fixing part 54 Second fixing part 61 Boom 62 Support member 71 Solar cell 72 Cell unit 80 Deployment structure 90 Second Support film 95 Specific function unit 100 Deployable solar cell 200 Spacecraft 210 Space mechanism (structure)
220 Imaging unit

Claims (13)

Deployment axis and
A plurality of supports formed in a plane parallel to the development axis and elongated in the radial direction, respectively.
A support film supported by one side edge of each of the plurality of supports on the development axis, and a support film.
The solar cell supported by the support film and
With
The plurality of supports include a first support and a second support that can mutually open with respect to the deployment axis, and the first support in the opening direction of the first support and the second support. An intermediate support, which is arranged between the body and the second support, is included.
The support film is a deployable solar cell configured so that it can be converted from a folded state to a deployed state between adjacent supports as the first support and the second support are opened. The deployable solar cell according to claim 1, wherein each of the first support, the second support, and the intermediate support is formed in a thin plate shape. The deployable solar cell according to claim 1 or 2, wherein the dimensions of the first support, the second support, and the intermediate support are equivalent to each other in the axial direction of the deploy axis. The deployable solar cell according to any one of claims 1 to 3, wherein the outer edge of the support film in the radial direction is reinforced as compared with a portion of the support film adjacent to the edge. The deployable solar cell according to claim 4, wherein the edge is reinforced by attaching a reinforcing tape to the outer edge of the support film in the radial direction. The support film includes a first film portion arranged on the outer side in the radial direction and a second film portion arranged on the inner side in the radial direction.
The first film portion and the second film portion are separated from each other through a slit.
Separate solar cells are supported by the first film portion and the second film portion.
When the support film is in the folded state, the number of bending lines of the first film portion between the adjacent supports is larger than the number of bending lines of the second film portion between the adjacent supports. The deployable solar cell according to any one of claims 1 to 5, wherein the number of solar cells is smaller. In the first film portion, the solar cell is not arranged on the bending line, and the solar cell is arranged on both regions sandwiching the bending line.
The sixth aspect of claim 6, wherein in the second film portion, the solar cell is not arranged on the bending line, and the solar cell is arranged on both regions sandwiching the bending line. Deployable solar cell. A second support film supported by the other edge of the deployment axis of each of the first support, the second support, and the intermediate support.
The specific functional part supported by the second support film and
With
Claims 1 to 7 are such that the second support film can be converted from a folded state to an unfolded state between the adjacent supports as the first support and the second support are opened. The deployable solar cell according to any one of the above. The deployable solar cell according to claim 8, wherein the specific function unit includes a sensor. 10. One of claims 1 to 7, wherein each of the first support, the second support, and the intermediate support includes a reflector portion supported by the other edge of the deployment axis. The described deployable solar cell. Deployment axis and
A plurality of supports formed in a plane parallel to the development axis and elongated in the radial direction, respectively.
A support film supported by one side edge of each of the plurality of supports on the development axis, and a support film.
With
The plurality of supports include a first support and a second support that can mutually open with respect to the deployment axis, and the first support in the opening direction of the first support and the second support. An intermediate support, which is arranged between the body and the second support, is included.
The support film is a developed structure that can be converted from a folded state to an unfolded state between adjacent supports as the first support and the second support are opened. Structure and
The deployable solar cell according to any one of claims 1 to 10, or the deployable structure according to claim 11.
Spacecraft equipped with. It is provided in the structure and further includes an imaging unit for capturing an image.
In a state where the first support and the second support are open, the first support and the second support have a V shape, and the support film has a fan shape, so that the first support has a fan shape. The spacecraft according to claim 12, wherein a blank portion in which the support film does not exist is formed between the spacecraft and the second support, and the blank portion is located in the visual field direction of the imaging unit.

Images