JP3520202B2 - Holding structure - Google Patents

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a holding structure for holding a deployable structure such as an antenna mounted on an artificial satellite in a housed state.

[0002]

2. Description of the Related Art Space structures such as antennas mounted on artificial satellites must be lightened at the time of launching the satellite due to the weight and capacity limitations of the launch vehicle, and must be housed in a small space in the rocket fairing. . That is, at the time of launching the satellite, a space structure such as a deployable antenna mounted on the satellite as shown in FIG. 17 is folded toward the tower of the satellite structure and stored in the rocket fairing. In outer space, Fig. 1
As shown in 8, a space structure such as a deployable antenna is deployed.

By the way, at the time of launching a satellite, it is necessary to fix the tower of the satellite structure and the deployable antenna to hold the deployable antenna so that the deployable antenna is not subjected to external force due to vibration at the time of launch. . A conventional holding structure for holding the deployable antenna on the tower of the satellite structure is shown in FIGS. FIG. 20 shows a part P1 of FIG.
The cross section of FIG.

The holding structure shown in FIGS. 19 and 20 is composed of a component 6 attached to the tower side of the satellite structure, a component 7 attached to the deployable antenna, and a bolt 8. That is, by inserting the component 7 into the component 6 and passing the bolt 8 through the center of the components 6 and 7 and tightening the bolt 8, the tower of the satellite structure and the deployable antenna are fixed.

[0005]

The deployable antenna as shown in FIG. 19 is called a solid antenna and has a high rigidity because the antenna portion is formed in a plate shape. Further, it is relatively easy to secure a mounting position for connecting to the tower of the satellite structure. Therefore, the tower of the satellite structure and the deployable antenna can be fixed by using the holding structure as shown in FIG.

On the other hand, in the large deployable antenna 9 having a diameter of 18 meters as shown in FIG. 12, the antenna is composed of a metal mesh 10 woven with molybdenum wire plated with gold. Since this metal mesh 1O is supported by the deployable truss structure 11 shown in FIG. 13, the shape of the antenna is determined according to the configuration of the deployable truss structure 11.
Therefore, the large deployable antenna 9 has a more complex deployable structure than the solid antenna.

As shown in FIG. 13, the deployable truss structure 11 has six sets of quadrilateral links 13, 14, 15, 16, 17, 18 which are radially arranged with respect to the central axis 12 and move in synchronization with each other. It can be unfolded and stored as shown in FIGS. 14, 15 and 16. In order to hold the large deployable antenna 9 having such a structure in a housed state and not to receive an external force, a large number of deployable truss structures 11 constituting the large deployable antenna 9 must be fixed to each other.

However, the deployable truss structure 11 has a diameter of 10 in order to construct a large and lightweight antenna.
Since it is composed of a thin member of about 20 mm to 20 mm, it is extremely difficult to attach the large deployable antenna 9 to the tower of the artificial satellite using the holding structure used in the conventional deployable antenna. The present invention provides a holding structure for holding a stored deployable structure mounted on an artificial satellite, which has a large deployed shape and is suitable for holding a lightweight deployable structure. The purpose is to

[0009]

According to a first aspect of the present invention, there is provided a holding structure for holding a stored deployable structure mounted on an artificial satellite, wherein three movable connecting portions are formed on two sides facing each other. A first plate member, a movable connecting portion is formed on one side, and an engaging portion is formed on another side facing the side.
And two second plate members, along the movable coupling portions of the are arranged in adjacent positions first plate member and / or the second plate member, the sides movable coupling part is formed together At least two movable connecting means that are rotatably connected about an axis; a holding and releasing mechanism that separably engages the engaging portions of the second plate members that are arranged adjacent to each other; the first plate member or the second plate member one for securing to the satellite
And a base member for the first plate member and the second plate member.
Of the plate member and the base member adjacent to each other
Except for the engaging portion of the second plate member,
The first plate member and the second plate member and the base , which are connected to each other by a movable connecting means, and are connected to each other.
The expansion type structure in the stored state is held in the space formed inside the member , and the expansion type structure in the stored state is
The pressing mechanism for generating a pressing force toward the first
It is provided on the rate member and the second plate member .

The movable connecting means centers the movable connecting portions of the first plate member and / or the second plate member arranged at positions adjacent to each other about an axis along a side where the movable connecting portion is formed. Rotatably connect as. Therefore, the first plate member and the second plate member are swingably connected to each other via the movable connecting means. When the first plate member and the second plate member connected to each other are combined and the engaging portions are engaged with each other by the holding / releasing mechanism, a space is formed inside them by the first plate member and the second plate member. It is formed. In this space, the unfolded deployable structure can be arranged.

That is, since the first plate member and the second plate member surround the expandable structure in the stored state, the entire expandable structure is covered with the first plate member and the second plate member. It can be held together by members. Therefore, the storage state of the deployable structure can be maintained at the time of launching the artificial satellite. In addition, since it surrounds the unfolded deployable structure, its rigidity is improved, and a large load received when the artificial satellite is launched can be tolerated. Further, the first plate member and the second plate member
Surrounding the expandable structure surrounded by
By pressing evenly by the pressing mechanism arranged in
Therefore, the deployable structure can be securely held.

Since the holding / releasing mechanism engages the engaging portions of the second plate member in a separable manner, if the holding / releasing mechanism is released, the first plate member and the first plate member surrounding the deployable structure are released. The second plate member is in the deployed state, and the deployable structure is released. Therefore, the deployable structure can be deployed in outer space. According to a second aspect of the present invention, there is provided a holding structure for holding an unfolded deployable structure mounted on an artificial satellite, wherein movable connecting portions are formed on two sides facing each other.
Four first plate members, a movable connecting portion is formed on one side, and an engaging portion is formed on another side opposite to the side.
And two second plate member, the movable coupling portions of said first plate member and / or the second flop <br/> rate members are located adjacent to each other, the movable connecting portion formed were A plurality of movable connecting means that are rotatably connected to each other about an axis along the defined side;
A holding / releasing mechanism that detachably engages the engaging portions of the second plate member, and one base portion for fixing the first plate member or the second plate member to the artificial satellite. And a member, the first plate member and the second plate
The adjacent sides of the member and the base member are the second
Except for the engaging portion of the plate member of
Connected to each other by stage holds the deployable structures stored state in a space formed inside of the linked first pre <br/> over preparative member and the second plate member and the base member, Push toward the unfolded structure in the stored state.
The first plate member includes a pressing mechanism that generates a pressing force.
And provided on the second plate member .

The movable connecting means connects the movable connecting portions of the plate member to each other so as to be rotatable about an axis along a side on which the movable connecting portion is formed. Therefore, the plurality of plate members are swingably connected to each other via the movable connecting means. When a plurality of plate members connected to each other are combined and the engaging portions are engaged with each other by the holding and releasing mechanism, a space is formed inside by the plate members. In this space, the unfolded deployable structure can be arranged.

That is, since the plurality of plate members surround the unfolded structure in the stored state,
The entire expandable structure can be collectively held by a plurality of connected plate members. Therefore, the storage state of the deployable structure can be maintained at the time of launching the artificial satellite.
Also, since it surrounds the expandable structure in the stored state,
The rigidity is improved, and a large load that is received when the satellite is launched can be tolerated. In addition, the first plate member and the
Expandable structure enclosed by two plate members
The structure is evenly distributed by the pressing mechanism arranged around it.
By pressing, the deployable structure can be held securely
It

Since the holding / releasing mechanism engages the engaging portions of the plate members in a separable manner, when the holding / releasing mechanism is released, the plurality of plate members surrounding the deployable structure are in a deployed state, The deployable structure is released. Therefore, the deployable structure can be deployed in outer space. A third aspect of the present invention is the holding structure according to the first or second aspect, wherein the movable connecting means is provided with a hinge mechanism.

By providing the hinge mechanism, a plurality of members can be connected so as to rotate about a predetermined axis at the position of the hinge mechanism. According to a fourth aspect of the present invention, in the holding structure according to the first or second aspect, the holding and releasing mechanism is provided with a separate nut. The separate nut can be used to connect a plurality of members. Further, the explosion of the explosive incorporated in the separate nut can release the connection of the plurality of members, so the separate nut can be used as a means for releasing the deployable structure from the holding structure.

Although the separate nut can be used only once, the deployable structure of an artificial satellite mounted on a rocket and launched is not stored again after the deployable structure is deployed. sufficient and is wasted is not the name as a holding release mechanism.

[0018]

According to a fifth aspect of the present invention, in the holding structure according to the first or second aspect , a pressure pin that generates a pressing force by an elastic member is provided as the pressing mechanism.

According to a sixth aspect of the present invention, in the holding structure according to the first or second aspect , the pressing mechanism is located at a position where the pressing mechanism is engaged with a load path supporting the deployable structure to press the load path. It is characterized in that it is provided with an engaging member having a hole for connecting a part of the deployable structure and the load path. The load path is used to support the deployable structure and maintain a constant gap between a plurality of members constituting the deployable structure. By pressing this load path with the pressing mechanism,
The deployable structure supported by the load path and the holding structure are reliably connected. Further, since the engaging member connects a part of the deployable structure and the load path, the deployable structure is connected to the load path at a plurality of locations, and the rigidity is further improved.

[0021]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will be described with reference to FIGS.
6 shows. This form corresponds to all the claims. FIG. 1 is a perspective view showing a holding state of the holding structure of the embodiment. FIG. 2 is a vertical sectional view of a portion of the holding structure 19A in FIG. FIG. 3 is a partially enlarged view showing details of the PA portion of FIG. FIG. 4 is a vertical cross-sectional view of the holding structure 19B of FIG. FIG. 5 is a partially enlarged view showing details of the PB portion of FIG.

FIG. 6 shows the pressure pins 81 and 83 and the load path 3.
It is a front view which shows the shape of the part which engages with 2. FIG. 7 is a view seen from the line VII-VII in FIG. FIG. 8 shows VIII of FIG.
It is the figure seen from the -VIII line. FIG. 9 is a partially enlarged view showing the configuration of the connecting mechanism 90. FIG. 10 is a perspective view showing a state when the holding structure of FIG. 1 releases the holding state.
FIG. 11 is a perspective view showing a satellite that holds the large deployable antenna 9 with the holding structure of FIG.

FIG. 12 is a perspective view showing a deployed state of the large deployable antenna 9 using the deployable truss structure 11. Figure 1
3 is a perspective view showing one deployable truss structure 11 and the metal mesh 10. FIG. 14, FIG. 15 and FIG. 16 are perspective views showing the deployed state, intermediate state and stored state of one deployable truss structure 11, respectively. In this form, the first plate member of claim 1 is the plate 21, 24, 25.
The second plate member of claim 1 corresponds to the plate 2
2 and 23, the movable connecting means of claim 1 is a hinge 51.
To 55, the holding and releasing mechanism of claim 1 corresponds to the separate nut 20A, and the base member of claim 1 corresponds to the mounting base 3
1 and the deployable structure of claim 1 corresponds to the deployable truss structures 11A to 11G.

The plate member of claim 2 corresponds to the plates 43 and 44, and the movable connecting means of claim 2 is the hinge 6.
Corresponding to 1 to 66, the holding and releasing mechanism is a separate nut 2
0B, the base member of claim 2 corresponds to the mount 31, and the deployable structure of claim 2 corresponds to the deployable truss structure 11A.
Corresponds to ~ 11G. The pressing mechanism according to claims 1 and 2 corresponds to the pressure pins 81 and 83. Further, claim 6
The load path of No. 6 corresponds to the load path 32, and the engaging member of claim 6 corresponds to the connecting members 71 to 73.

In this embodiment, a large number of deployable truss structures 11 constituting a large deployable antenna 9 as shown in FIG. 12 are folded and stored, and the holding structures 19A and 19B shown in FIG. Hold. Holding structure 19
The large deployable antenna 9 held by A and 19B is shown in FIG.
It is mounted on the satellite in the form as shown in FIG. In addition, FIG.
By releasing the holding of the holding structures 19A and 19B as shown in FIG. 4 and deploying the respective deployable truss structures 11, the large deployable antenna 9 can be deployed as shown in FIG.

In this embodiment, each deployed truss structure 11 to be held has six sets of quadrilateral links 13, 14, 1 which are radially arranged and connected to each other as shown in FIG.
It is composed of 5, 16, 17 and 18. The six sets of quadrilateral links 13, 14, 15, 16, 17, and 18 are movable structures that move in cooperation with each other. The deployable truss structure 11 including the quadrilateral links 13, 14, 15, 16, 17, and 18 can be transformed into the deployed state shown in FIG. 14, the intermediate state shown in FIG. 15, and the stored state shown in FIG. .

When the satellite is launched, each deployable truss structure 11 is housed as shown in FIG. 16 and holding structure 19A,
Hold at 19B. In this form, seven deployable truss structures 11A, 11 having the same structure as the deployable truss structure 11 are provided.
It is assumed that the large deployable antenna 9 composed of B, 11C, 11D, 11E, 11F and 11G is held by holding structures 19A and 19B as shown in FIG.

In order to maintain the spacing, protection and support among the many constituent elements of the deployable truss structure 11, the space of the deployed truss structure 11 (see FIG. 16) in the accommodated state is shown in FIG. 2 and a load path 32 as shown in FIG. 4 are arranged. The position and structure of each member constituting the deployable truss structure 11 differ depending on the longitudinal position of the deployed truss structure 11 as shown in FIG.
The position and shape of the load path 32 provided therein also differ depending on the position in the longitudinal direction of the deployable truss structure 11.

In this embodiment, the deployable truss structure 11 is held by two holding structures 19A and 19B at two different positions in the longitudinal direction. Therefore, the configurations and shapes of the two holding structures 19A and 19B are slightly different. First, the holding structure 19A will be described. As shown in FIG. 2, the holding structure 19A is configured such that the outer periphery thereof forms a substantially regular hexagon, and surrounds the seven deployable truss structures 11A to 11G arranged in the inner space thereof.

The holding structures 19A are connected to each other by 5
One plate 21, 22, 23, 24, 25 and mounting base 3
1 and. The mount 31 is fixed to the tower 4 of the satellite structure. As shown in FIG. 1, five plates 2
1, 22, 23, 24, 25 and the mount 31 are formed in a substantially rectangular shape. And the plates 21, 22, 2
Adjacent sides of 3, 24, 25 and the mount 31 are connected to each other as shown in FIG.

In practice, the side of the mounting base 31 and the side of the plate 21 which are adjacent to each other are connected by a hinge 51 so as to be rotatable about an axis along the side. Similarly, the side of the adjacent plate 21 and the side of the plate 22 are connected by the hinge 52, the side of the adjacent plate 23 and the side of the plate 24 are connected by the hinge 53, and the side of the adjacent plate 24 and the plate 25 are connected. Of the plate 25 and the side of the mounting base 31 which are adjacent to each other are connected by a hinge 55.

The side of the plate 22 and the side of the plate 23 which are adjacent to each other are connected by a separate nut 20A. The separate nut 20A can be disconnected by blasting the gunpowder contained therein. When the separate nut 20A is disconnected, the plate 22 and the plate 23 are separated. In addition, the plates 21 and 2
2, 23, 24, 25 and the mount 31 are hinges 51, 5
2, 53, 54 and 55 are connected, so that when the plate 22 and the plate 23 are separated, the plates 21, 22, 23, 24 and 25 are expanded as shown in FIG.
The holding of the deployable truss structures 11A to 11G is released.

At the position of the holding structure 19A, as shown in FIG. 2, a load path 32 formed by combining a plurality of members is arranged at a position along the outer circumference of each of the deployable truss structures 11A to 11G. The seven deployable truss structures 11A to 11G are connected to each other by a connecting mechanism 90. For example, a connecting mechanism 90 that connects three deployable truss structures 11A, 11F, and 11G that are adjacent to each other.
Are configured as shown in FIG.

Referring to FIG. 9, the deployable truss structure 11
A connecting member 91 fixed to the rod-shaped member 11Ab of A,
The connection member 92 fixed to the rod-shaped member 11Ga of the deployment truss structure 11G and the connection member 93 fixed to the rod-shaped member 11Fa of the deployment truss structure 11F are engaged with each other to form three deployment truss structures 11A. , 11F and 11G
Are connected.

In practice, the connecting members 91, 92 and 93
Is a plate-shaped member having a hole formed at the tip thereof, the holes of the connecting members 91, 92 and 93 are overlapped with each other, and the engaging pin 94 is inserted so as to penetrate the holes. The three deployable truss structures 11A to 11G arranged at positions adjacent to each other by the connecting mechanism 90 having the same configuration as the above.
All of them are connected.

Further, for example, the deployable truss structure 11A, the deployable truss structure 11G and the plate 23 are adjacent to each other in FIG.
In the PA portion of FIG. 3, as shown in FIG. 3, the connecting member 71 fixed to the rod-shaped member 11Aa of the deployment truss structure 11A and the rod-shaped member 11B of the deployment truss structure 11B.
The connecting member 72 fixed to a and the connecting member 73 fixed to a portion 32 a of the load path 32 are connected to each other.

The connecting members 71, 72 and 73 are plate-shaped members each having a hole at the tip thereof. The holes of the connecting members 71, 72 and 73 are overlapped with each other, and the engaging pin 74 is inserted so as to penetrate the holes to engage them. As shown in FIG. 2, the deployed truss structures 11A, 11B, 11
C, 11D, 11E and 11F are plates 21 to 25
And is supported by the plates 21 to 25 and the mounting base 31 in contact with the supporting mechanism 34A provided on each of the mounting base 31. The support mechanism 34A includes the deployable truss structures 11A and 11A.
Press B, 11C, 11D, 11E and 11F inward to fix them.

As shown in FIG. 3, a support mechanism 34A is provided at a position facing a portion 32a of the load path 32. Referring to FIG. 3, the support mechanism 34A includes the plate 23
It is fixed to the mounting portion 23a formed thin. The support mechanism 34A includes a pressure pin 81 and a mounting bolt 36A. The mounting position of the pressure pin 81 can be adjusted by rotating the mounting bolt 36A. As shown in FIG. 6, a recess 82 is formed at the tip of the pressure pin 81,
A convex portion 32b is formed on a portion 32a of the load path 32 that faces it.

Therefore, since the concave portion 82 at the tip of the pressure pin 81 and the convex portion 32b of the portion 32a of the load path 32 are engaged with each other, the deployable truss structures 11A to 11G connected to the load path 32 are held. . Since the pressure pin 81 has a built-in spring, a pressing force in the inward direction is applied to the load path 32 that engages with the tip of the pressure pin 81. The magnitude of the pressing force can be changed by adjusting the position of the mounting bolt 36A.

The structure of the holding structure 19B is the same as that of the holding structure 19A except that the shape and the like are slightly different. Figure 4
As shown in FIG. 5, in the holding structure 19B, the plates 41, 42, 43, 44, 45, 46 and the mounting base 31 are arranged so as to surround the deployable truss structures 11A to 11G.

The mount 31 and the plate 41 are connected by a hinge 61, the plate 41 and the plate 42 are connected by a hinge 62, the plate 42 and the plate 43 are connected by a hinge 63, and the plate 44 and the plate 45 are connected. It is connected by a hinge 64, the plate 45 and the plate 46 are connected by a hinge 65, the plate 46 and the mounting base 31 are connected by a hinge 66, and the plate 43 and the plate 44 are connected by a separate nut 20B.

As shown in FIG. 5, in the PB portion of FIG. 4, the support mechanism 34B is fixed to the thin mounting portion 44a of the plate plate 44. The support mechanism 34B includes
A pressure pin 83 and a mounting bolt 36B are provided. By rotating the mounting bolt 36B, the pressure pin 83
The mounting position of can be adjusted. As shown in FIG. 6, a concave portion 84 is formed at the tip of the pressure pin 83, and a convex portion 32d is formed at a portion 32c of the load path 32 facing the concave portion 84.

Therefore, since the concave portion 82 at the tip of the pressure pin 83 and the convex portion 32d of the portion 32c of the load path 32 are engaged with each other, the deployable truss structures 11A to 11G connected to the load path 32 are held. . Since the pressure pin 83 has a built-in spring, the load path 32 that engages with the tip of the pressure pin 83 receives a pressing force directed inward. The magnitude of the pressing force can be changed by adjusting the position of the mounting bolt 36B.

The plates 21 to 25 and 41 to 46
The shape and structure of the above may be changed to a special shape in order to reduce the weight and enhance the rigidity.

[0045]

As described above, according to the present invention, since the expandable structure in the housed state is held by the holding structure surrounding it, the expandable type having a complicated expandable structure such as a large expandable antenna. Even a structure can maintain a predetermined storage state when the satellite is launched. Further, if the holding state is released by the holding and releasing mechanism, the deployable structure can be deployed in outer space after launch. Furthermore, since the rigidity of the deployable structure surrounded by the holding structure is improved as compared with the conventional one, a large load applied at the time of launch can be allowed.

[Brief description of drawings]

FIG. 1 is a perspective view showing a holding state of a holding structure according to an embodiment.

FIG. 2 is a vertical sectional view of a portion of a holding structure 19A in FIG.

FIG. 3 is a partially enlarged view showing details of a PA portion of FIG.

FIG. 4 is a vertical cross-sectional view of a portion of a holding structure 19B of FIG.

FIG. 5 is a partial enlarged view showing details of a PB portion in FIG.

FIG. 6 is a front view showing a shape of a portion where pressure pins 81 and 83 and a load path 32 are engaged with each other.

FIG. 7 is a diagram viewed from the line VII-VII in FIG.

FIG. 8 is a view seen from the line VIII-VIII in FIG.

FIG. 9 is a partially enlarged view showing the configuration of a connecting mechanism 90.

10 is a perspective view showing a state when the holding structure of FIG. 1 is released from a held state. FIG.

11 is a perspective view showing a satellite holding the large deployable antenna 9 with the holding structure of FIG. 1. FIG.

FIG. 12 is a perspective view showing a deployed state of a large deployable antenna 9 using a deployable truss structure 11.

FIG. 13 is a perspective view showing one deployable truss structure body 11 and a metal mesh 10.

FIG. 14 is a perspective view showing a developed state of one deployable truss structure body 11.

FIG. 15 is a perspective view showing an intermediate state of one deployable truss structure body 11.

FIG. 16 is a perspective view showing a stored state of one deployable truss structure body 11.

FIG. 17 is a perspective view showing a satellite accommodating a conventional deployable antenna.

FIG. 18 is a perspective view showing a deployed state of a conventional satellite.

FIG. 19 is a front view showing an antenna holding state of a satellite that accommodates a conventional deployable antenna.

20 is an enlarged cross-sectional view showing the conventional antenna holding structure of FIG.

[Explanation of symbols]

4 Satellite structure tower 9 Large deployment antenna 10 metal mesh 11, 11A-11G Deployable truss structure 12 Central axis of deployable truss structure 13,14,15,16,17,18 Quadrilateral link 19A, 19B holding structure 20A, 20B Separate nut 21,22,23,24,25 plate 31 mounting base 32 Road Pass 32b, 32d convex part 34A, 34B support mechanism 36A, 36B mounting bolt 41, 42, 43, 44, 45, 46 plates 44a mounting part 51,52,53,54,55 Hinge 61,62,63,64,65,66 Hinge 71, 72, 73 Connection member 74 Engagement pin 81,83 Pressure pin 82, 84 recess 90 Connection mechanism 91, 92, 93 Connecting member 94 engagement pin

─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Mitsuteru Yamato 2-3-2 Marunouchi, Chiyoda-ku, Tokyo Mitsubishi Electric Corporation (56) Reference JP-A-57-160800 (JP, A) JP-A-9 -118300 (JP, A) JP-A-9-124000 (JP, A) JP-A-10-145137 (JP, A) Actual development 62-171400 (JP, U) (58) Fields investigated (Int.Cl . ^7, DB name) B64G 1/44 H01Q 1/08 H01Q 1/12 H01Q 1/28 H01Q 15/14

Claims (6)

(57) [Claims] 1. A holding structure for holding an unfolded deployable structure mounted on an artificial satellite, comprising: three first plate members having movable connecting portions formed on two sides facing each other; and two second plate member engaging portion to another one side is formed to the side facing the movable connection section is formed on the sides, the first plate member to be located adjacent to each other and / Alternatively, the movable connecting portions of the second plate member are
At least two movable connecting means that are rotatably connected about an axis along the side where the movable connecting portion is formed, and the engaging portions of the second plate members that are arranged adjacent to each other can be separated from each other. A holding / releasing mechanism for engaging with the first plate member or the second plate member and a base member for fixing the first plate member or the second plate member to the artificial satellite, and the first plate member and the second plate member.
The adjacent sides of the base member are the second plates.
Except for the engaging portion of the member, by the movable connecting means
Are connected to each other, it holds the deployable structures stored state in a space formed inside of the linked first plate member and the second plate member and the base member, deployable structures of the receiving state Generates a force to push toward
The pressing mechanism that generates the force is applied to the first plate member and the second plate member.
A holding structure provided on the rate member . 2. A holding structure for holding an unfolded deployable structure mounted on an artificial satellite, wherein four movable connecting parts are formed on two sides facing each other.
A first plate member, the movable connecting portion is formed on one side and another one side engaging portion formed on the two second plate member opposing the side said to be positioned adjacent to each other First plate part
The movable connecting portions of the material and / or the second plate member,
A plurality of movable connecting means for rotatably connecting about an axis along a side on which the movable connecting portion is formed, and an engaging portion of the second plate member arranged adjacent to each other can be separated from each other. A holding / releasing mechanism to be engaged and one base member for fixing the first plate member or the second plate member to the artificial satellite are provided, and the first plate member and the second plate member are arranged.
The adjacent sides of the base member are the second plates.
Except for the engaging portion of the member, by the movable connecting means
The first plate member and the second plate connected to each other
It holds the member and deployable structures stored state in a space formed inside the base member, calling the force pressing toward the deployable structure of the receiving state
The pressing mechanism that generates the force is applied to the first plate member and the second plate member.
A holding structure provided on the rate member . 3. The holding structure according to claim 1, wherein the movable connecting means is provided with a hinge mechanism. 4. The holding structure according to claim 1, wherein the holding and releasing mechanism is provided with a separate nut. 5. The holding structure according to claim 1 or 2, wherein a pressure pin that generates a pressing force by an elastic member is provided as the pressing mechanism. 6. The holding structure according to claim 1 or 2, wherein the pressing mechanism is arranged at a position where the pressing mechanism is engaged with a load path supporting the deployable structure to press the load path. A holding structure, wherein an engaging member having a hole for connecting a part of the deployable structure and the load path is provided.