JP2015085885A - Development structure and spacecraft equipped with the same - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a development structure capable of certainly developing from a folding state to a development state while eliminating the need of a synchronizing mechanism, and a spacecraft mounted with the development structure.SOLUTION: A panel locking structure 40 is releasably locked to a second panel 24 to regulate rotations of the second panel 24 to a first panel 22. In a folding state of a development structure 10, a body structure 110, the first panel 22, and the second panel 24 are spirally disposed in order, and folded so as to wind in the second panel 24 to a center side of a swirl rather than the first panel 22. By developing the first panel 22 from the folding state by a predetermined angle or more due to the energizing force of a development spring, the panel locking structure 40 releases the locking of the second panel 24. Therefore, the second panel 24 is developed to the first panel 22 to shift the development structure 10 to a development state.

Description

  The present invention relates to a deployment structure attached to a spacecraft such as an artificial satellite or a spacecraft, and a spacecraft including such a deployment structure.

  Spacecraft such as artificial satellites and spacecraft are transported to outer space by transport aircraft such as rockets. This type of transport aircraft has a storage space for mounting a spacecraft, but the size of this storage space is limited. On the other hand, a spacecraft is equipped with equipment that requires a large area on a circular orbit. Examples include solar cell paddles for photovoltaic power generation, antenna bodies for transmitting and receiving radio waves, reflectors such as antenna reflectors and optical reflectors that reflect radio waves and light, and spacecrafts are protected from sunlight and heat. For example, a shield. Such a device is provided as an unfolded structure that can be folded to a small envelope volume when mounted on a transport aircraft, and can be used after being separated from the transport aircraft. .

  Patent Document 1 discloses a general solar battery paddle as an example of a development structure. In this solar cell paddle, a plurality of rectangular panels (6) are arranged with their sides adjacent to each other and are connected to each other by hinges (7) and folded. Specifically, the solar cell paddle is folded into an accordion type (W shape) by alternately folding a plurality of hinges (7) arranged in the longitudinal direction into a mountain and a valley, and a plurality of pieces (4 in Patent Document 1). Sheet) panel (6) can be folded so as to have substantially one envelope volume. When the unfolding cable (1) is extended from this folded state, the solar cell paddle is unfolded, and the panels (6) are shifted to the unfolded state in which they are arranged on a plane.

  Patent Document 2 discloses a parabolic reflector and a heat shield as examples of the development structure. 11 and 12 of Patent Document 2 describe a deployable heat shield (102) connected to a main body (101) of an artificial satellite by a joint system (320). In the folded state, the heat shield (102) is folded so that the primary panel (115) on the distal end side is held between the other primary panel (111) on the proximal end side and the main body (101). The primary panel (115) on the distal end side is deployed after the primary panel (111) on the proximal end side is deployed.

  Patent Document 3 discloses a deployable antenna in which rectangular antenna panels are connected by a hinge mechanism as an example of a deployable structure. As shown in FIGS. 1 to 3 of Patent Document 3, the deployable antenna includes a first panel (11) connected to a spacecraft (10) and a hinge mechanism (15), and a panel (11). And a second panel (12) connected to the distal end side via a hinge mechanism (15). In the folded state, the second panel (12) on the distal end side is folded between the first panel (11) on the proximal end side and the spacecraft (10). And as shown in FIG. 23 of patent document 3, after the 1st panel (11) of a base end side expand | deploys, the 2nd panel (12) of a front end side expand | deploys.

JP-A-9-142400 JP 2012-131492 A JP 2001-048099 A

  When deploying a deployment structure, it is common to control the deployment posture so as not to interfere with the portions of the deployment structure, the structure of the spacecraft, and other equipment. When the solar cell paddle folded in an accordion type as in Patent Document 1 is slightly deviated at the operation timing of a plurality of hinges connecting the panels, the deployment posture changes variously. For this reason, in the solar cell paddle disclosed in Patent Document 1, a cable is installed on the side of the panel along the longitudinal direction of the solar cell paddle, and the solar cell paddle is synchronized with the operation of each hinge by extending this cable little by little. Can be expanded.

  In the case of the heat shield of Patent Document 2, in order for the primary panel (115) on the front end side not to interfere with the main body (101) of the artificial satellite, the front end side after the primary panel (111) on the base end side is sufficiently deployed. The primary panel (115) needs to be expanded. Also, with respect to the deployable antenna of Patent Document 3, the distal end side panel (12) is sufficiently deployed so that the distal end side panel (12) does not interfere with the spacecraft (10) before the distal end side panel (12) is interfered. It is necessary to unfold the second panel (12) on the side. For this reason, although not explicitly disclosed in Patent Document 2 and Patent Document 3, a special synchronization mechanism such as a cable is required to deploy these unfolded structures.

  However, when a malfunction occurs in the synchronization mechanism, the deployment structure does not deploy, and it is extremely difficult for the spacecraft to achieve its purpose. In addition, a deployment structure that does not require a synchronization mechanism such as a cable is also strongly desired from the viewpoint of limiting the launch weight of a transport aircraft and reducing costs.

  The present invention has been made in view of the above-described problems, and a deployment structure capable of reliably deploying from a folded state to a deployed state while eliminating the need for a synchronization mechanism, and a spacecraft equipped with the same Is to provide.

  According to the present invention, the structure attachment portion attached to the structure of the spacecraft and the hinge structure can be folded together and pivotally connected to the structure attachment portion so as to be able to transition from the folded state to the expanded state. A plurality of panels, a deployment structure for a spacecraft, wherein the plurality of panels are proximally positioned proximal to the structure attachment portion in the deployed state. A distal panel positioned at a more distal position than the proximal panel, and the distal panel is urged in a direction to deploy with respect to the proximal panel by a biasing means. The unfolded structure includes a panel locking structure that releasably locks to the distal panel and restricts rotation of the distal panel relative to the proximal panel, and in the folded state , The structure mounting portion, and the proximal side pad And the distal panel are sequentially arranged in a spiral shape, and the distal panel is folded so as to be wound closer to the center of the vortex than the proximal panel, and the folded state From the above, when the proximal panel is expanded beyond a predetermined angle by the biasing force of the biasing means, the panel locking structure unlocks the distal panel, and the distal panel is A deployment structure is provided that deploys to the proximal panel and transitions to the deployed state.

  Further, according to the present invention, there is provided a spacecraft comprising a structure and a deployment structure that is rotatably connected to the structure and configured to be able to transition from a folded state to a deployed state, A deployment structure is foldably connected to each other by a hinge structure and is located proximal to the structure in the deployed state, and a distal position distal to the proximal panel A side panel; a panel locking structure that releasably locks to the distal panel to restrict rotation of the distal panel relative to the proximal panel; and the distal panel to the proximal side Biasing means for biasing the panel in a deploying direction, and in the folded state, the structure, the proximal panel, and the distal panel are arranged in a spiral shape in order and Displace the distal panel more than the proximal panel The panel locking structure is folded so as to be wound around the center side, and the proximal panel is expanded beyond a predetermined angle by the urging force of the urging means from the folded state, whereby the panel locking structure is A spacecraft is provided, wherein the side panel is unlocked, and the distal panel expands with respect to the proximal panel and transitions to the expanded state.

  In the unfolded structure of the invention, the second panel is locked to the panel locking structure in the folded state, and the rotation with respect to the first panel is restricted. Then, from the folded state in which the second panel is wound in a spiral shape so as to be wound closer to the center of the vortex than the first panel, the first panel is expanded at a predetermined angle or more so that the second panel becomes the first panel. Expands to and transitions to the expanded state. For this reason, according to the deployment structure of the above invention, even if there is no synchronization mechanism, since the second panel on the distal side is deployed after the first panel on the proximal side is fully deployed, the second panel interferes with the structure. It is possible to make a transition to a deployment state with a predetermined deployment posture without doing so.

  According to the unfolding structure and the spacecraft of the present invention, it is possible to reliably unfold from the folded state to the unfolded state while eliminating the synchronization mechanism.

(A) to (c) are schematic diagrams for explaining the principle of the spacecraft deployment sequence of the first embodiment of the present invention, and (d) is an enlarged view showing the vicinity of the first hinge in (a). . (A) is a perspective view which shows the folding state of the spacecraft of 2nd embodiment, (b) is a perspective view which shows the unfolded state. (A)-(f) is a side view which shows the expansion | deployment sequence of the spacecraft of 2nd embodiment. (A) is a perspective view of the expansion | deployment structure corresponding to Fig.3 (a), (b) is an enlarged view of the area | region X in (a). (A) is a perspective view of the expansion | deployment structure corresponding to FIG.3 (b), (b) is an enlarged view of the area | region Y in (a). It is a perspective view of the expansion | deployment structure corresponding to FIG.3 (e). FIG. 7 is an enlarged view of a region VII in FIG. 6.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In all the drawings, the same constituent elements are denoted by the same reference numerals, and redundant description is omitted as appropriate.

<First embodiment>
FIG. 1A to FIG. 1C are schematic diagrams for explaining the principle of a deployment sequence of the spacecraft 100 according to the first embodiment of the present invention. Specifically, FIG. 1A is an explanatory diagram of the folded state of the spacecraft 100 of the present embodiment. FIG. 1B is an explanatory diagram of the spacecraft 100 during a deployment operation. FIG. 1C is an explanatory diagram of the deployed state of the spacecraft 100. FIG.1 (d) is an enlarged view which shows the vicinity of the 1st hinge 32 in Fig.1 (a).

First, an outline of the present embodiment will be described.
The spacecraft 100 of this embodiment includes a structure 110 and a deployment structure 10 that is rotatably connected to the structure 110 and configured to be able to transition from a folded state to a deployed state.
The deployment structure 10 includes a proximal panel (first panel 22), a distal panel (second panel 24), a panel locking structure 40 and biasing means. The first panel 22 and the second panel 24 are connected to each other by a hinge structure 30 (second hinge 34) so as to be foldable. The first panel 22 is located proximal to the structure 110 in the deployed state, and the second panel 24 is located distal to the structure 110 in the deployed state relative to the first panel 22. The panel locking structure 40 is releasably locked to the second panel 24 to restrict the rotation of the second panel 24 relative to the first panel 22. The urging means (deployment spring 54) urges the second panel 24 in the direction of deploying the first panel 22.
In the folded state of the unfolded structure 10, the structure 110, the first panel 22, and the second panel 24 are sequentially arranged in a spiral shape, and the second panel 24 is wound closer to the center of the vortex than the first panel 22. Is folded. In the unfolded structure 10, the first panel 22 is unfolded at a predetermined angle or more by the urging force of the urging means (the unfolding spring 52) from this folded state, so that the panel locking structure 40 can Release the lock. Thereby, the 2nd panel 24 expand | deploys with respect to the 1st panel 22, and the expansion | deployment structure 10 changes to an expansion | deployment state.

  The spacecraft deployment structure 10 of the present embodiment includes a structure attachment portion 90 attached to the structure 110 of the spacecraft 100. The plurality of panels 20 (the first panel 22 and the second panel 24) are connected to the structure mounting portion 90 so as to be rotatable. Of the plurality of panels 20, the first panel 22 is positioned proximal to the structure mounting portion 90 in the expanded state, and the second panel 24 is positioned relative to the structure mounting portion 90 in the expanded state from the first panel 22. Is also located distally. And in the folding state of the expansion | deployment structure 10, the structure attachment part 90, the 1st panel 22, and the 2nd panel 24 are arrange | positioned in the spiral form in order.

Next, the deployment structure 10 and the spacecraft 100 of this embodiment will be described in detail.
The spacecraft 100 is a space vehicle that navigates space for various purposes, such as artificial satellites such as earth observation satellites and communication satellites, and planetary probes. The spacecraft 100 is launched into outer space by a transport aircraft such as a rocket. The size of the spacecraft 100 is not particularly limited, but a relatively small one such as a 50 kg class to a 300 kg class is preferable.

  The unfolded structure 10 is in a folded state in which the envelope volume is relatively small when mounted on the transport aircraft, and at least part of the unfolded structure is unfolded after being separated from the transport aircraft so that the envelope volume is folded. It is a structure that transitions to a larger expanded state than the state. The unfolding structure 10 includes a plurality of panels 20 (first panel 22 and second panel 24). The panel 20 has a flat plate shape. As the panel 20, various structures are applied depending on the purpose of the development structure 10. As an example, when the deployment structure 10 is a solar battery paddle, the panel 20 is a solar battery panel in which solar battery cells are stacked on a substrate. When the deployment structure 10 is a radar device such as a synthetic aperture radar, the panel 20 is an antenna for transmitting and receiving radio waves. When the deployment structure 10 is a reflector for transmission or reception such as an antenna reflector or an optical reflector, or a shield such as a light shield or a heat shield, the panel 20 is a reflector.

Adjacent panels 20 are connected to each other by a hinge structure 30, and the unfolded structure 10 as a whole transitions from the folded state to the unfolded state by changing the relative positions thereof. The panel 20 is a so-called rigid panel having a predetermined bending rigidity, and the individual panel 20 itself is not substantially deformed during the operation of the hinge structure 30. The panel 20 has at least one straight side. The shape of the panel 20 is not particularly limited, and may be a triangle, a quadrangle (rectangular), or a pentagon or more polygon. The panel 20 of this embodiment is rectangular.
Adjacent panels 20 are connected by a hinge structure 30 in such a manner that adjacent sides (hereinafter sometimes referred to as “adjacent sides”) are arranged in parallel. The hinge structure 30 may be provided at one central position of the adjacent side of the panel 20 or may be provided at both ends of the adjacent side.

  The hinge structure 30 is formed by combining a plurality of members so as to be rotatable around a rotation axis. One and the other of these members are fixed to each of the two adjacent panels 20. The rotation axis of the hinge structure 30 is parallel to the adjacent side, and is the front-rear direction of the drawing sheet of FIG. That is, in the folded state, the plurality of panels 20 are in a state of being folded together in the perpendicular direction. In this embodiment, as shown to Fig.1 (a), the adjacent panels 20 are folded 180 degree | times with the hinge structure 30, and are mutually opposed with a slight clearance gap. Specifically, the angle formed by the normal vector N1 of the surface 22a of the first panel 22 and the normal vector N2 of the surface 24a of the second panel 24 is approximately 180 degrees.

  The structure 110 is a satellite bus of the spacecraft 100, and can take various shapes such as a box shape and a cylindrical shape. The structure 110 according to this embodiment includes a flat mounting surface 112. The unfolded structure 10 is attached to the structure 110 so that the folded panel 20 faces the mounting surface 112. The panel 20 or the mounting surface 112 having a flat plate shape or a planar shape does not mean that the surfaces 22a and 24a or the mounting surface 112 of the panel 20 are geometrically perfect planes. Allow local or global irregularities to be present.

The structure attachment portion 90 is an interface structure for attaching the development structure 10 to the structure 110. The structure attachment portion 90 may be a rigid and non-movable bracket, or may be a movable mechanism including a hinge structure. When the unfolding structure 10 is a solar cell paddle, the structure mounting portion 90 may include a boom or a yoke that holds the panel 20 at an appropriate distance from the structure 110 in the unfolded state. In this case, the structure attachment portion 90 may include a paddle drive motor attached to the structure 110.
In this embodiment, in the folded state shown in FIG. 1A, a state in which the structure attachment portion 90 is attached to a position offset to the side of the panel 20 instead of between the panel 20 and the structure 110 is illustrated. The present invention is not limited to this. For example, when the structure mounting portion 90 is a boom or a yoke, the structure mounting portion 90 may be sandwiched between the panel 20 and the structure 110 in the folded state.

  The hinge structure 30 is an opening / closing mechanism for rotating the panel 20 relative to the structure attachment portion 90. The unfolding structure 10 of the present embodiment includes at least a first hinge 32 and a second hinge 34 as the hinge structure 30. The first hinge 32 is a hinge that rotates the first panel 22 with respect to the structure attachment portion 90 and the structure 110. The second hinge 34 is a hinge that rotates the second panel 24 with respect to the first panel 22. The hinge structure 30 (the first hinge 32 and the second hinge 34) includes deployment springs 52 and 54 (see FIGS. 3 to 6), and the connected panels 20 transition from the folded state to the deployed state. Energize in the direction. The expansion springs 52 and 54 of the present embodiment are torque springs (spring springs) in which a leaf spring is spirally wound.

  In the expanded state shown in FIG. 1C, the angle formed by the normal vector N1 of the surface 22a of the first panel 22 and the normal vector N2 of the surface 24a of the second panel 24 is smaller than 180 degrees. Is less than 90 degrees. In the figure, the first panel 22 and the second panel 24 are arranged on a plane (on a straight line), and the angle formed by the normal vectors N1 and N2 is 0 degrees. It is not limited to this. The angle of the normal vector N2 with respect to the normal vector N1 can be set to −30 degrees or more and +30 degrees or less with the clockwise direction in FIG.

  Of the panel 20, the side close to the structure 110 and the structure mounting portion 90 in the expanded state is referred to as a proximal side, and the side away from the structure 110 and the structure mounting portion 90 in the expanded state is referred to as a distal side. .

  Here, when each panel 20 (the first panel 22 and the second panel 24) is deployed, the hinge structure 30 connected to the proximal side of the panel 20 is rotated, and the panel 20 is moved further therefrom. Also, it means that the direction is changed relative to the site on the proximal side (the structure attachment portion 90 side). In addition, the deployment angle of the panel 20 refers to the rotation angle of the hinge structure 30 that is connected to the proximal side of the panel 20. Specifically, the deployment angle of the first panel 22 refers to an angle at which the first hinge 32 is rotated with respect to the structure attachment portion 90 with reference to the folded state (initial state). The unfolding angle of the second panel 24 refers to an angle at which the second hinge 34 is rotated with respect to the first panel 22 based on the folded state (initial state). The connection direction of the panels 20, that is, the direction from the proximal side to the distal side is referred to as the longitudinal direction of the panels 20 and the unfolded structure 10 regardless of the aspect ratio of each panel 20.

  In FIG. 1A to FIG. 1D, an unfolded structure 10 including two panels 20 is illustrated. In the present embodiment, the first panel 22 is referred to as a proximal panel, and the second panel 24 is referred to as a distal panel. In the case where three or more panels 20 are provided as in a development structure 10 (see FIGS. 3A to 3F) of the second embodiment to be described later, one of the two is relatively The panel 20 on the side close to the structure 110 or the structure mounting portion 90 is referred to as a proximal panel, and the panel 20 on the side away from the structure 110 or the structure mounting portion 90 is referred to as a distal panel.

  In the unfolded structure 10 in the folded state, the first panel 22 and the second panel 24 face each other and face the mounting surface 112 of the structure 110. At this time, the first panel 22 is disposed outside the mounting surface 112, and the second panel 24 is disposed inside the mounting surface 112. In the folded state shown in FIG. 1A, the structure attachment portion 90, the first hinge 32, the first panel 22, the second hinge 34, and the second panel 24 are arranged in a spiral shape in this order. The structure attachment portion 90 and the first panel 22 are on the outer periphery side of the vortex, and the second panel 24 is on the center side of the vortex. That is, the second panel 24 is held between the first panel 22 and the structure 110. From this folded state, the unfolded structure 10 is the panel 20 (first panel 22) located on the outer periphery side of the vortex while maintaining the unfolded angle of the panel 20 (second panel 24) on the vortex center side at zero degrees. Expand in order.

  When the structure mounting portion 90 is a movable mechanism such as a yoke or a boom, and the structure mounting portion 90 can also be expanded with respect to the structure 110, the development of the structure mounting portion 90 and the deployment of the panel 20 are optional. is there. That is, the panel 20 (first panel 22) may be deployed after the structure mounting portion 90 is deployed, or the structure mounting portion 90 is deployed after the first panel 22 and the second panel 24 are deployed. Good.

  FIG. 1 (b) shows that the unfolding structure 10 is being unfolded, and more specifically shows the state where the unfolding of the first panel 22 has been completed. From the folded state shown in FIG. 1 (a), the unfolded structure 10, while the relative positions of the first panel 22, the second hinge 34 and the second panel 24 are fixed, as shown in FIG. 1 (b), The first panel 22 and the second panel 24 rotate with respect to the structure attachment portion 90 about the first hinge 32. That is, the deployment angle of the first panel 22 increases from zero degrees, and the deployment angle of the second panel 24 is zero degrees and is unchanged. The maximum rotation angle of the first hinge 32 of this embodiment is 90 degrees. When the deployment angle of the first panel 22 reaches this maximum rotation angle, the first panel 22 is deployed 90 degrees with respect to the mounting surface 112 and stops. Thereby, the unfolding operation of the first panel 22 ends. The unfolding structure 10 has unfolding maintenance means for maintaining the state in which the individual panels 20 are unfolded. Examples of the deployment maintaining means include a latch method and a residual torque method. In the latch system, when the hinge structure 30 (the first hinge 32 and the second hinge 34) reaches a rotation angle of a predetermined value or more from the initial state (folded state), the latch structure is hooked and reversed in the folding direction. This is a method for restricting rotation. In general, the latch structure is provided on the hinge structure 30 itself. In the residual torque method, torque is applied to the unfolding springs 52 and 54 in the initial state (folded state) at a predetermined rotation angle or more, and the hinge structure 30 is unfolded by the unfolding springs 52 and 54 even when the panel 20 is unfolded. It is a method that continues to bias in the direction. A latch method and a residual torque method may be provided in a mixed manner for each of the plurality of panels 20. In the unfolded structure 10 of the present embodiment, the first hinge 32 has a latch structure (not shown) as an example of the unfolding maintaining means, and the latch structure is latched at the timing when the unfolding operation of the first panel 22 is completed. Thus, the rotation of the first hinge 32 in the reverse return direction is restricted.

  The panel locking structure 40 is a means for restricting the rotation of the second panel 24 relative to the first panel 22 by releasably locking to the second panel 24 at least in the folded state. As shown in FIG. 1B, the panel locking structure 40 releases the locking of the second panel 24 immediately before or after the first panel 22 is unfolded, and the second panel 24 is moved to the first panel. 22 can be rotated.

  As shown in FIG. 1A and FIG. 1D, the panel locking structure 40 is used when the hinge structure 30 (second hinge 34) urges the second panel 24 in the rotational direction in the folded state. The distal end 25 of the second panel 24 is positioned in front of the distal direction 25 in the displacement direction, and the distal end 25 is locked. The distal end of the panel 20 refers to a region of the panel 20 on the opposite side in the longitudinal direction from the attachment position of the hinge structure 30 that deploys the panel 20. The distal end is not a specific point on the panel 20 but a region having a predetermined area.

1, the second hinge 34 applies a biasing force so as to rotate the second panel 24 clockwise. The displacement direction of the distal end 25 of the second panel 24 faces the structure 110 as shown by an arrow in FIG. The displacement direction of the distal end 25 here is a direction in which the distal end 25 is slightly displaced by the urging force applied by the second hinge 34 to the second panel 24, in other words, the second hinge 34 is moved to the second panel. 24 is tangential to the distal end 25 with respect to the moment applied to it. In the folded state, the distal end 25 of the second panel 24 is directly or indirectly restricted from rotating by the panel locking structure 40, but the displacement direction of the distal end 25 is defined as described above. .
When the first panel 22 (proximal side panel) is deployed, the relative angle between the panel locking structure 40 and the second panel 24 (distal side panel) changes. Then, when the first panel 22 is expanded at a predetermined angle or more (approximately 90 degrees in this embodiment), the locking of the distal end 25 by the panel locking structure 40 is released.

  The second panel 24 is constrained by the panel locking structure 40 in a state of being folded facing the first panel 22 until the first panel 22 is sufficiently unfolded with respect to the structure mounting portion 90 and the structure 110. In this state, the second panel 24 rotates together with the first panel 22 around the first hinge 32. For this reason, the second panel 24 does not interfere with the structure 110 in the initial stage of deployment of the first panel 22.

  As shown in FIG. 1 (d), the panel locking structure 40 includes a holding shaft 42 and a panel holding portion 44. The holding shaft 42 is provided at the distal end 25 of the second panel 24 in parallel with the rotation shaft of the first panel 22 (the front-rear direction in FIG. 1D). The panel holding part 44 has an opening 46 that opens in one direction, and holds the holding shaft 42 in a rotatable manner. In the folded state of the deployment structure 10, the opening 46 is located at a position different from the front of the distal end 25 in the displacement direction with respect to the holding shaft 42. In the present embodiment, the opening 46 in the folded state is located in a direction perpendicular to the displacement direction of the distal end 25 with respect to the holding shaft 42. Then, as shown in FIG. 1B, when the first panel 22 is expanded at a predetermined angle or more with respect to the structure mounting portion 90, the opening 46 is forward of the distal end 25 in the displacement direction with respect to the holding shaft 42. Move to. As a result, the holding shaft 42 can be detached from the panel holding portion 44 through the opening 46.

  When the holding shaft 42 can be detached from the panel holding portion 44, the second panel 24 expands with respect to the first panel 22 by the urging force of the second hinge 34 as indicated by an arrow in FIG. As shown by the broken line in FIG. 1C, the second panel 24 increases the deployment angle and reaches the deployed state as shown by the solid line. The maximum deployment angle of the second hinge 34 of this embodiment is 180 degrees, and the deployed second panel 24 is located on the same plane as the first panel 22. The second hinge 34 is provided with a latch structure (not shown) as an example of the unfolding maintaining means. The latch structure is latched at the timing when the unfolding operation of the second panel 24 is completed, and the second hinge 34 is moved in the reverse direction. Regulates rotation.

  The panel holding portion 44 is provided at a position that does not follow the unfolding operation of the first panel 22, specifically, closer to the structure mounting portion 90 than the rotation shaft of the first hinge 32. The specific attachment position of the panel holding portion 44 is not particularly limited, and may be provided integrally with the first hinge 32 or may be provided on the structure attachment portion 90 as a member different from the first hinge 32. .

Here, in the case of the general accordion type (W-shaped) deployment structure described in Patent Document 1, the deployment is performed in order from the distal panel spaced away from the satellite structure. Therefore, it is necessary to deploy the deployment structure in which the moment of inertia increases at an accelerating rate while being swung by the hinge structure on the proximal side. For this reason, a large torque is particularly required for the hinge structure for unfolding the nearest panel, and the latch impact at the moment when the unfolding of the panel is completed becomes large.
On the other hand, according to the deployment structure 10 of the present embodiment, the panel 20 is deployed sequentially from the proximal panel among the plurality of panels 20, so that when a certain panel 20 is deployed, it is more distal than that. The side panel is in a folded state. For this reason, the moment of inertia when the panel 20 is expanded is small, and the latch impact at the moment when the expansion of each panel 20 is completed is small.
Thereby, the expansion | deployment structure 10 of this embodiment can also make a damper structure for absorbing the impact at the time of completion | finish of expansion | deployment unnecessary.

In addition, in the case of a general accordion type (W-shaped) deployment structure, each panel is deployed at the same time, so a synchronization mechanism such as a deployment cable is used to avoid interference between panels or between the panel and the structure or other equipment. Must be used (see Patent Document 1).
On the other hand, in the deployment structure 10 of the present embodiment, when a certain panel 20 is deployed, the deployment of the other panel closer to the proximal side is substantially completed, and the deployment structure 10 is more than the panel 20. The other panel on the distal side is restricted by the panel locking structure 40 in a folded state and is not movable. Therefore, the degree of freedom during deployment of the deployment structure 10 of the present embodiment is only the deployment angle of the hinge structure 30 on the proximal side of any one panel 20 during deployment (one degree of freedom). For this reason, the synchronization mechanism for controlling the timing which each panel expand | deploys desired can be made unnecessary, and the expansion | deployment structure 10 of this embodiment is not provided with this synchronization mechanism.

<Second embodiment>
FIG. 2A is a perspective view showing a folded state of the spacecraft 100 of the second embodiment, and FIG. 2B is a perspective view showing a deployed state of the spacecraft 100 of the second embodiment.
FIG. 3A to FIG. 3F are side views showing a deployment sequence of the spacecraft 100 of the present embodiment.

  The unfolded structure 10 of this embodiment is different from the first embodiment in that three or more panels 20 are connected in series. In this embodiment, in addition to the 1st panel 22 and the 2nd panel 24, the 3rd panel (3rd panel 26) located in the further distal side rather than the 2nd panel 24 in the expanded state is included. The first panel 22 is located on the most proximal side with respect to the structure 110 and the structure mounting portion 90 in the deployed state, and the second panel 24 is adjacent to the distal side with respect to the first panel 22. The third panel 26 is adjacent to the second panel 24 on the distal side and is located on the most distal side of the panel 20. That is, the second panel 24 corresponds to the distal panel in relation to the first panel 22 and corresponds to the proximal panel in relation to the third panel 26.

  In the unfolded structure 10, the panel locking structure 40 unlocks the distal panel when the proximal panel is expanded at a predetermined angle or more from the folded state, and the distal panel is proximal. Expands to the side panel and transitions to the expanded state. In the unfolded structure 10 of the present embodiment, the panel locking structure 40 (first locking portion 40a) is expanded from the folded state by the first panel 22 (proximal side panel) being expanded at a predetermined angle or more. The locking of the second panel 24 (distal side panel) is released. Thereby, the 2nd panel 24 (distal side panel) expand | deploys with respect to the 1st panel 22 (proximal side panel). Further, when the second panel 24 (proximal side panel) expands beyond a predetermined angle, the panel locking structure 40 (second locking portion 40b) locks the third panel 26 (distal side panel). The third panel 26 (distal panel) is deployed relative to the second panel 24 (proximal panel). Thereby, the expansion | deployment structure 10 changes to an expansion | deployment state.

The three panels 20 are connected to each other, and these panels 20 are rotatably connected to a base panel corresponding to the structure mounting portion 90.
In the folded state of FIG. 3A, all of the three or more panels 20 (from the first panel 22 to the third panel 26) are arranged in a spiral shape with the third panel 26 as the center. The third panel 26 is a panel located on the most distal side with respect to the structure attachment portion 90 in the unfolded state shown in FIG. The unfolded structure 10 is sequentially unfolded from the third panel 26 which is a panel disposed on the outer peripheral side of the spiral from the folded state and transitions to the unfolded state.

  The base panel (structure attachment portion 90) has a flat plate shape and is fixed to the structure 110 by a bracket 92 in a rigid and non-movable manner. The base panel may have functions such as a solar battery panel and a reflector as with the panel 20.

  As shown in FIG. 2A, the spacecraft 100 of the present embodiment includes two sets of deployment structures 10. The two types of unfolded structures 10 are configured integrally by sharing one base panel (structure attachment portion 90), and are excellent in handling properties. Specifically, the first panel 22 in each unfolded structure 10 is rotatably attached to the opposite side of the rectangular base panel. For simplicity, only the unfolded structure 10 on one side is shown in FIGS.

  The hinge structure 30 that deploys the panel 20 specifically includes a first hinge 32, a second hinge 34, and a third hinge 36. The first hinge 32 is provided between the structure attachment portion 90 and the first panel 22 and rotates the first panel 22 with respect to the structure attachment portion 90. The second hinge 34 is provided between the first panel 22 and the second panel 24 and rotates the second panel 24 with respect to the first panel 22. The third hinge 36 is provided between the second panel 24 and the third panel 26 and rotates the third panel 26 with respect to the second panel 24.

  The plurality of panels 20 are connected linearly and in series from the structure mounting portion 90. That the plurality of panels 20 are connected in series means that these panels 20 are linearly or bent and connected one-dimensionally. Each panel 20 has a rectangular shape and is connected by a hinge structure 30 (from the first hinge 32 to the third hinge 36) in a state where adjacent sides are arranged in parallel. The panels 20 of this embodiment are linearly connected, and the three pairs of adjacent sides connected by the first hinge 32 to the third hinge 36 are parallel to each other.

  The hinge structure 30 (from the first hinge 32 to the third hinge 36) includes deployment springs 52, 54, and 56 as urging means for deploying the panel 20, respectively.

FIG. 3A shows a folded state of the unfolded structure 10. FIG. 3B shows a state in which the first panel 22 has been expanded to a predetermined deployment angle and the first locking portion 40 a has released the locking of the second panel 24. FIG. 3C shows a state in which the first panel 22 has been unfolded. FIG. 3D shows a state in which the second panel 24 is expanded to a predetermined deployment angle and the second locking portion 40b releases the locking of the third panel 26. FIG. 3E shows a state in which the development of the second panel 24 has been completed. FIG. 3F shows the expanded state of the expanded structure 10 after the third panel 26 has been expanded.
FIG. 4 is a perspective view of the development structure 10 corresponding to FIG. FIG. 4B is an enlarged view of the region X in FIG. 4A and is an enlarged view of the vicinity of the first hinge 32. Fig.5 (a) is a perspective view of the expansion | deployment structure 10 corresponding to FIG.3 (b). FIG. 5B is an enlarged view of the region Y in FIG. 5A, and is an enlarged view in the vicinity of the first hinge 32. FIG. 6 is a perspective view of the developed structure 10 corresponding to FIG. FIG. 7 is an enlarged view of the region VII in FIG. 6, and is an enlarged view of the vicinity of the second hinge 34.

  The unfolded structure 10 according to the present embodiment includes the structure mounting portion 90, the first hinge 32, the first panel 22, the second hinge 34, the second panel 24, the third hinge 36, and the second panel 24 in the folded state. In this order, they are arranged in a spiral shape from the outer peripheral side toward the center side.

  The panel locking structure 40 of this embodiment includes a first locking portion 40a and a second locking portion 40b. The first locking portion 40a can release the rotation of the distal panel (second panel 24) and the third panel (third panel 26) folded relative to each other with respect to the first panel 22. regulate. The 2nd latching | locking part 40b regulates that the 3rd panel 26 rotates with respect to the 2nd panel 24 so that cancellation | release is possible.

  In the folded state shown in FIGS. 3A and 4, the third panel 26 is locked to the second panel 24 by the second locking portion 40 b, and the deployment spring 56 (FIG. 4) provided in the third hinge 36. The rotation of the third panel 26 relative to the second panel 24 is restricted against the urging force (see (b)). Therefore, from the initial stage to the middle stage of deployment of the deployment structure 10, specifically, until the second panel 24 is fully deployed as shown in FIG. The three panel 26 behaves as a non-movable rigid body. The second panel 24 and the third panel 26 in the folded state are locked by the second locking portion 40b, and a deployment spring 54 (see FIG. 4A) provided in the second hinge 34 is attached. The rotation with respect to the first panel 22 is restricted against the force. Thereby, in the initial stage of deployment of the deployment structure 10, specifically, as shown in FIGS. 3B and 5, the first panel 22 and the second panel 24 until the first panel 22 is fully deployed. And the third panel 26 behaves as a non-movable rigid body.

  The first locking portion 40a locks any one or more of the third panel 26 and the second panel 24 locked to each other by the second locking portion 40b and the third hinge 36 connecting them. These are allowed to rotate together with the first panel 22 and are restricted from rotating relative to the first panel 22.

  The first locking portion 40a (panel locking structure 40) includes a holding shaft 42a provided at the distal end 25 of the second panel 24 in parallel with the rotation axes of the first panel 22 and the third hinge 36, and one A panel holding portion 44a having an opening 46a that opens in the direction and holding the holding shaft 42 in a rotatable manner. The holding shaft 42a of this embodiment is integrally formed with the third hinge 36 as shown in FIGS. 4B and 5B.

  The panel holding portion 44 a has a curved arm shape, and its base end is fixed to the structure mounting portion 90. Instead of this embodiment, the panel holding portion 44a may be fixed to the hinge structure 30 provided on the proximal side of the first panel 22. Specifically, in the first hinge 32, the panel holding portion 44a may be provided closer to the structure attachment portion 90 than the rotation axis.

  The front end of the panel holding portion 44 a is curved in an arc shape at a central angle of about 90 degrees so as to surround the first hinge 32. A region opened forward in the protruding direction from the tip of the arc-shaped panel holding portion 44a corresponds to the opening 46a of the present embodiment. The holding shaft 42a has a curved surface corresponding to the curved shape of the panel holding portion 44a, and slides along the panel holding portion 44a.

  In the folded state, the third hinge 36 is positioned inside the opening 46a and is held by the panel holding portion 44a. In the folded state, the panel holding portion 44a is configured so that the distal end 25 of the second panel 24 is displaced when the deployment spring 54 of the second hinge 34 urges the third panel 26 in the rotational direction (FIG. 4B). The distal end 25 is locked in front of the arrow). That is, in the folded state, the panel holding portion 44a is located on an extension line between the first hinge 32 and the third hinge 36, and the opening 46a is located at a position different from the extension line.

  Since the panel holding portion 44a is fixed to the structure mounting portion 90, the panel holding portion 44a and the panel 20 are relatively rotated around the first hinge 32 when the panel 20 (first panel 22) is deployed. The direction changes. When the first panel 22 is unfolded from the folded state and reaches a predetermined unfolded angle as shown in FIGS. 3B and 5, the opening 46a is displaced by the distal end 25 with respect to the holding shaft 42a. The panel holding portion 44a is disengaged from the extension line of the first hinge 32 and the third hinge 36. Thereby, the second panel 24 can be rotated with respect to the first panel 22 by the urging force of the deployment spring 54 provided in the second hinge 34. As shown in FIG. 5 (b), the holding shaft 42a and the third hinge 36 are separated from the panel holding portion 44a through the front (opening 46a) of the panel holding portion 44a so that the tip of the panel holding portion 44a is squeezed.

  The second panel 24 released from the restriction by the first locking portion 40a is developed with respect to the first panel 22 as shown in FIG. During this time, the second locking portion 40 b restricts the third panel 26 from rotating with respect to the second panel 24. When the second panel 24 reaches a predetermined deployment angle with respect to the first panel 22 as shown in FIGS. 3D and 6, the second locking portion 40 b restricts the rotation of the third panel 26. To release. As a result, the third panel 26 expands with respect to the second panel 24 by the urging force of the expansion spring 56.

  The detail of the 2nd latching | locking part 40b is shown in FIG. The second locking portion 40b is located forward of the distal end 27 of the third panel 26 in the displacement direction when the hinge structure 30 (third hinge 36) biases the third panel 26 in the rotational direction in the folded state. This distal end 27 is locked in position. When the second panel 24 (proximal side panel) is deployed, the relative angle between the second locking portion 40b and the third panel 26 (distal side panel) changes. And when the 2nd panel 24 expand | deploys more than a predetermined angle (in this embodiment, about 90 degree | times), the latching of the distal end 27 by the 2nd latching | locking part 40b is cancelled | released.

The second locking portion 40b includes a holding shaft 42b and a panel holding portion 44b. The holding shaft 42b is provided at the distal end 27 of the third panel 26 in parallel with the rotation shafts of the second panel 24 and the second hinge 34 (the front-rear direction in FIG. 3D). The panel holding portion 44b has an opening 46b that opens in one direction, and holds the holding shaft 42b in a rotatable manner. The panel holding portion 44 b is provided on the structure mounting portion 90 side of the hinge structure 30 (second hinge 34) provided on the proximal side of the second panel 24, that is, on the first panel 22.
Accordingly, when the second panel 24 rotates around the second hinge 34, the holding shaft 42 b rotates with respect to the panel holding portion 44 b fixed to the first panel 22.

  The panel holding portion 44b of this embodiment has a U-shape and is formed to protrude from the second hinge 34 toward the inside in the width direction of the first panel 22. The holding shaft 42b has a cylindrical shape, and is formed to protrude outward in the width direction of the third panel 26 along the end surface of the distal end 27 of the third panel 26.

  In the folded state of the unfolded structure 10, the opening 46b is at a position different from the front in the displacement direction of the distal end 27 with respect to the holding shaft 42b. In the present embodiment, the folded opening 46b is positioned in a direction perpendicular to the displacement direction of the distal end 25 with respect to the holding shaft 42b. Then, as shown in FIG. 3D, when the second panel 24 is expanded at a predetermined angle or more with respect to the first panel 22, the opening 46b is forward of the displacement direction of the distal end 27 with respect to the holding shaft 42b. (See FIG. 7). The direction of displacement of the distal end 27 is indicated by an arrow in FIG. As a result, the holding shaft 42b can be detached from the panel holding portion 44b through the opening 46b.

  When the holding shaft 42b can be detached from the panel holding portion 44b, the third panel 26 is developed around the third hinge 36 as shown in FIG. 3E, and the expanded state shown in FIG.

  As shown in FIG. 4B, the panel holding portion 44 a of the first locking portion 40 a is formed on the outer side in the width direction than the structure mounting portion 90, and is provided on the outer side in the width direction of the second panel 24. Locks to the third hinge 36 and the holding shaft 42a. On the other hand, the panel holding portion 44 b and the holding shaft 42 b of the second locking portion 40 b are provided inside the second hinge 34. That is, the first locking portion 40 a and the second locking portion 40 b are provided at different positions in the width direction of the panel 20. By providing the first locking portion 40a on the outer side in the width direction of the panel 20, the arm-shaped panel holding portion 44a can be formed with sufficient bending rigidity and strength. During the folded state and when the first panel 22 is unfolded, the panel holding part 44a resists the urging force of the plurality of hinge structures 30 (second hinge 34 and third hinge 36), and the plurality of panels 20 (second panel). 24 and the third panel 26) are restricted from rotating with respect to the first panel 22. For this reason, a larger load is applied to the panel holding portion 44a than the panel holding portion 44b. Therefore, the mechanical characteristics of the developed structure 10 can be improved by making the panel holding portion 44a into an arm shape with sufficient bending rigidity and strength as in the present embodiment. On the other hand, by providing the holding shaft 42b of the second locking portion 40b on the inner side in the width direction of the panel 20, the holding shaft 42b does not interfere with the second hinge 34 during the folded state or the unfolding operation.

  As shown in each drawing of FIG. 3 and FIG. 4A, the unfolded structure 10 includes a holding / releasing portion 60. The holding / releasing unit 60 according to the present embodiment is a mechanism that restrains a plurality of panels 20 that are folded and stacked in a folded state to each other in a plane direction and releases the restraint of the panels 20 by a releasing operation. Thereby, the panel 20 can be fixed to the structure 110 against the urging force of the deployment spring that deploys the panel 20, and the panel 20 is caused by a large acceleration load applied to the panel 20 in the launch environment of the spacecraft 100. Prevents rocking. The holding / releasing unit 60 of this embodiment includes a structure-side bracket 62 attached to the mounting surface 112 of the structure 110 and panel-side brackets 64 a to 64 c provided on each panel 20. The structure-side bracket 62 and the panel-side brackets 64 a to 64 c are in the same position when the unfolded development structure 10 is viewed from the direction perpendicular to the panel 20. In the folded state, the structure-side bracket 62 and the panel-side brackets 64a to 64c are overlapped with each other and mechanically connected together by a connecting tool (not shown). As the coupling tool, a separation bolt that can be broken by an explosion of pyrotechnics, a latch mechanism that can be released, or the like can be used. After the spacecraft 100 is separated from the transport aircraft, the unfolding operation of the first panel 22 is started by operating the holding and releasing unit 60 to separate the structure side bracket 62 and the panel side brackets 64a to 64c.

  The holding / releasing portion 60 of the present embodiment is provided only on the side farther from the structure mounting portion 90 than the center of the stacked panels 20, that is, on the distal side in the longitudinal direction of the first panel 22. The holding / releasing portion 60 may be provided at one position in the center of the width of the panel 20 or may be provided on both sides in the width direction of the panel 20. In the present embodiment, one holding / releasing portion 60 is provided on each side of the panel 20 in the width direction.

In general, when attaching a plurality of panels folded to each other to the structure 110, holding and releasing portions 60 are provided at four or more positions of the panel 20, and the panels 20 are held on surfaces having the four holding and releasing portions 60 as apexes. To do. In particular, an accordion type (W-shaped) solar cell paddle as described in Patent Document 1 deploys the panel 20 by adding together the urging forces of the hinge-structured deployment springs provided on each panel. Energize in the direction to make it. For this reason, since a large holding force is required for the holding and releasing portion, it is necessary to disperse the holding and releasing portions at four or more places to avoid concentration of the load on the panel.
On the other hand, in the deployment structure 10 of the present embodiment, the urging force of the deployment spring 56 of the third hinge 36 is canceled by the second locking portion 40b, and the urging force of the deployment spring 54 of the second hinge 34 is the first. Since it is offset by the locking portion 40a, the holding / release portion 60 is substantially loaded only with the urging force of the deployment spring 52 of the first hinge 32. For this reason, in this embodiment, it is sufficient to provide a small number of holding and releasing portions 60 on the first panel 22 on the opposite side (distal side) of the first hinge 32 in the longitudinal direction. Therefore, the cost can be reduced by reducing the number of holding and releasing units 60 and the reliability of the deployment operation can be improved.

  A connecting portion 70 is provided on the side closer to the structure attachment portion 90 than the center of the panel 20 in the folded state. The connecting portions 70 connect the plurality of stacked panels 20 to each other in an orthogonal direction. The connecting portion 70 according to the present embodiment includes a structure fixing portion 72 that is attached to the mounting surface 112 of the structure 110 and fitting portions 74 a to 74 c that are provided on each panel 20.

  In the folded state, the structure fixing portion 72 and the fitting portions 74 a to 74 c are fitted in a non-fixed manner in the direction perpendicular to the panel 20. When the holding and releasing unit 60 is operated and the first panel 22 starts to rotate, the second panel 24 is separated from the mounting surface 112 of the structure 110. At this time, the structure side bracket 62 and the panel side brackets 64a to 64c are separated, and the structure fixing part 72 and the fitting parts 74a to 74c are separated (see FIG. 2B).

  By providing the connecting part 70 separately from the holding / releasing part 60, the panel 20 is held at a plurality of points, in this embodiment, at four points, so that the load resistance when the spacecraft 100 is launched is excellent. However, since the connecting portion 70 merely connects the panels 20 to each other in a non-connected manner, a release mechanism such as a pyrotechnic is unnecessary.

  The holding / releasing portion 60 and the connecting portion 70 are provided so as to protrude outward in the width direction of the panel 20. In addition, columnar reinforcing members (not shown) are mounted on both sides in the width direction of each panel 20 (first panel 22, second panel 24, third panel 26) along the longitudinal direction of the panel. Yes. The holding / releasing portion 60 (panel-side brackets 64 a to 64 c) and the connecting portion 70 (fitting portions 74 a to 74 c) are attached to the reinforcing member and project outward in the width direction of the panel 20. The holding / releasing portion 60 and the connecting portion 70 are portions where a large acceleration load is applied when the spacecraft 100 is launched, and the holding / releasing portion 60 and the connecting portion 70 are attached to the reinforcing member of the panel 20 as in this embodiment. Thus, the load on the panel 20 is substantially eliminated. Since the deployment structure 10 of the present embodiment has only one degree of freedom during deployment, a synchronization mechanism such as a deployment cable is unnecessary and is not provided. Therefore, since it is not necessary to prepare a space for routing the deployment cable on the side of the panel 20, the holding / releasing portion 60 and the connecting portion 70 are provided along both sides in the width direction of the panel 20 as in the present embodiment. Is possible.

The present invention is not limited to the above-described embodiment, and includes various modifications and improvements as long as the object of the present invention is achieved.
For example, in the first or second embodiment described above, the deployment springs 52, 54, and 56 are illustrated as being provided on the hinge structure 30 (the first hinge 32, the second hinge 34, and the third hinge 36), respectively. The present invention is not limited to this. An urging means such as a deployment spring that applies an urging force for rotating the hinge structure 30 may be provided separately from the hinge structure 30.
In the first embodiment, two panels and in the second embodiment three panels 20 are linearly connected from the proximal side to the distal side. However, the present invention is not limited to this. . Four or more panels 20 may be connected, or may be bent into an L shape instead of being linear, or branched into a T shape.

  The various components of the deployment structure or spacecraft of the present invention need not be individually independent. A plurality of components are formed as one member, a component is formed of a plurality of members, one component is a part of another component, and one component is And a part of other components are allowed to overlap.

The above embodiment includes the following technical idea.
(1) A plurality of structure attachment parts attached to the structure of the spacecraft and a plurality of structures that are foldable to each other by a hinge structure and pivotably connected to the structure attachment part so as to be able to transition from a folded state to an expanded state. A plurality of panels, the plurality of panels comprising: a proximal panel positioned proximal to the structure mounting portion in the deployed state; and A distal panel positioned distal to the distal panel, wherein the distal panel is biased in a direction to deploy relative to the proximal panel by biasing means, The unfolding structure includes a panel locking structure that releasably locks to the distal panel and restricts rotation of the distal panel with respect to the proximal panel, and in the folded state, the structure An attachment, said proximal panel and The distal side panels are sequentially arranged in a spiral shape, and the distal side panel is folded so as to be wound closer to the center side of the vortex than the proximal side panel, and from the folded state, When the proximal panel is expanded by a biasing force of the biasing means at a predetermined angle or more, the panel locking structure releases the locking of the distal panel, and the distal panel is moved to the near side. An unfolded structure that unfolds with respect to the position side panel and changes to the unfolded state.
(2) Three or more panels are connected in series, and in the folded state, three or more panels centered on the panel positioned most distal to the structure mounting portion in the expanded state The panel according to (1), wherein all of the panels are arranged in a spiral shape, and are successively deployed from the panel arranged on the outer peripheral side of the spiral from the folded state to transition to the deployed state. Structure.
(3) The panel locking structure is positioned forward in the displacement direction of the distal end of the distal panel when the hinge structure biases the distal panel in the rotation direction in the folded state. Then, when the distal end is locked and the proximal panel is deployed, the relative angle between the panel locking structure and the distal panel is changed, and the proximal panel is The deployment structure according to (1) or (2), wherein the distal end is unlocked by the panel locking structure when deployed at an angle equal to or greater than.
(4) The panel locking structure has a holding shaft provided in parallel to the rotation axis of the proximal side panel at the distal end of the distal side panel, and an opening portion opened in one direction. A panel holding portion that rotatably holds the holding shaft, and in the folded state, the opening is at a position different from the front in the displacement direction of the distal end with respect to the holding shaft, When the proximal panel is expanded beyond the predetermined angle, the opening moves forward in the displacement direction of the distal end with respect to the holding shaft, and the holding shaft holds the panel through the opening. The unfolded structure according to (3) above, wherein the unfolded structure can be detached from the portion.
(5) The unfolded structure according to (4), wherein the panel holding portion is provided on the structure mounting portion side in the hinge structure provided on the proximal side of the proximal panel.
(6) The plurality of panels include a third panel positioned more distally than the distal panel in the deployed state, and the panel locking structure is folded to each other. And a first locking portion for releasably restricting the third panel from rotating relative to the proximal panel, and the third panel rotating relative to the distal panel. (2), wherein the first locking portion and the second locking portion are provided at different positions in the width direction of the panel. The unfolded structure described.
(7) The plurality of panels that are folded and stacked in a folded state are constrained to each other in a direction perpendicular to each other, and a holding and releasing part that releases the restraint of the panel by a releasing operation is provided, and the holding and releasing part includes: The unfolded structure according to any one of (1) to (6), which is provided only on a side farther from the structure mounting portion than the center of the laminated panel.
(8) The connecting portion for connecting the stacked plurality of panels in a direction perpendicular to each other in a non-constraining manner is provided closer to the structure mounting portion than the center of the panel in the folded state. (7) The unfolded structure.
(9) The unfolded structure according to (8), wherein the holding and releasing portion and the connecting portion are provided so as to protrude outward in the width direction of the panel.
(10) A spacecraft comprising a structure and a deployment structure that is rotatably coupled to the structure and configured to be able to transition from a folded state to a deployed state, wherein the deployment structure includes: A proximal panel foldably connected to each other by a hinge structure and positioned proximal to the structure in the deployed state; a distal panel positioned distal to the proximal panel; and A panel locking structure that releasably locks to the distal panel to restrict rotation of the distal panel relative to the proximal panel, and deploys the distal panel relative to the proximal panel And, in the folded state, the structure, the proximal panel, and the distal panel are sequentially arranged in a spiral shape, and the distal panel is disposed in the folded state. Wrapped around the center of the vortex than the proximal panel The proximal panel is expanded beyond a predetermined angle by the urging force of the urging means from the folded state, so that the panel locking structure locks the distal panel. And the distal panel expands with respect to the proximal panel and transitions to the expanded state.

10: Deployment structure, 20: Panel, 22: First panel, 24: Second panel, 22a, 24a: Surface, 25: Distal end, 26: Third panel, 27: Distal end, 30: Hinge structure 32: 1st hinge, 34: 2nd hinge, 36: 3rd hinge, 40: Panel locking structure, 40a: 1st locking part, 40b: 2nd locking part, 42 * 42a * 42b: Holding shaft 44, 44a, 44b: panel holding portion, 46, 46a, 46b: opening, 52, 54, 56: deployment spring, 60: holding release portion, 62: structure side bracket, 64a to 64c: panel side bracket, 70 : Articulated part, 72: structure fixing part, 74a to 74c: fitting part, 90: structure attaching part, 92: bracket, 100: spacecraft, 110: structure, 112: mounting surface, N1 / N2: normal vector

Claims (10)

A plurality of panels configured to be foldable from each other by a hinge structure and pivotably connected to the structure mounting part so as to be able to transition from a folded state to an unfolded state. A deployment structure for a spacecraft comprising:
The plurality of panels include: a proximal panel located proximal to the structure mounting portion in the deployed state; and a distal panel located distal to the proximal panel. The distal panel is biased by a biasing means in a direction to deploy relative to the proximal panel;
The unfolded structure is
A panel locking structure that releasably locks to the distal panel and restricts rotation of the distal panel relative to the proximal panel;
In the folded state, the structure mounting portion, the proximal side panel, and the distal side panel are arranged in a spiral shape in order, and the distal side panel is closer to the center of the vortex than the proximal side panel. It is folded so that it can be involved, and
When the proximal panel is expanded beyond a predetermined angle by the biasing force of the biasing means from the folded state, the panel locking structure unlocks the distal panel, and the far panel A deployment structure, wherein a distal side panel is deployed relative to the proximal panel and transitions to the deployed state. Three or more panels are connected in series,
In the folded state, all of the three or more panels are arranged in a spiral shape around the panel located on the most distal side with respect to the structure mounting portion in the expanded state.
The unfolded structure according to claim 1, wherein the unfolded structure sequentially unfolds from the panel disposed on the outer peripheral side of the spiral and transitions to the unfolded state. The panel locking structure is located in front of a displacement direction of a distal end of the distal panel when the hinge structure urges the distal panel in a rotating direction in the folded state. Locking the distal end, and
When the proximal panel expands, the relative angle between the panel locking structure and the distal panel changes, and when the proximal panel expands beyond the predetermined angle, the panel locking structure The deployment structure according to claim 1, wherein the locking of the distal end due to is released. The panel locking structure has a holding shaft provided at the distal end of the distal side panel in parallel with a rotation axis of the proximal side panel, and an opening portion opened in one direction. A panel holding portion for holding the
In the folded state, the opening is at a position different from the front in the displacement direction of the distal end with respect to the holding shaft,
When the proximal panel is expanded beyond the predetermined angle, the opening moves forward in the displacement direction of the distal end with respect to the holding shaft, and the holding shaft holds the panel through the opening. The unfolded structure according to claim 3, wherein the unfolded structure can be detached from the portion.   The deployment structure according to claim 4, wherein the panel holding portion is provided on a side of the structure attaching portion in the hinge structure provided on the proximal side of the proximal panel. The plurality of panels includes a third panel positioned more distally than the distal panel in the deployed state;
The panel locking structure includes a first locking portion that releasably restricts the distal panel and the third panel folded relative to each other from being rotated relative to the proximal panel; A second locking part for releasably restricting rotation of the three panels with respect to the distal panel,
The deployment structure according to claim 2, wherein the first locking portion and the second locking portion are provided at different positions in the width direction of the panel. A plurality of panels that are folded and stacked in a folded state are constrained to each other in a perpendicular direction, and a holding and releasing unit that releases the restraint of the panels by a release operation is provided.
The unfolded structure according to any one of claims 1 to 6, wherein the holding and releasing portion is provided only on a side farther from the structure mounting portion than the center of the laminated panel.   The connection part which connects the said several laminated | stacked said panel to each other in the direction of a surface non-restraining is provided in the side near the said structure attachment part rather than the center of the surface of the said panel of the folded state. The unfolded structure described.   The unfolded structure according to claim 8, wherein the holding and releasing portion and the connecting portion are provided so as to protrude outward in the width direction of the panel. A spacecraft comprising a structure and a deployment structure that is rotatably connected to the structure and configured to be able to transition from a folded state to a deployed state;
The unfolded structure is
A proximal panel foldably connected to each other by a hinge structure and positioned proximal to the structure in the deployed state; a distal panel positioned distal to the proximal panel; and A panel locking structure that releasably locks to the distal panel to restrict rotation of the distal panel relative to the proximal panel, and deploys the distal panel relative to the proximal panel Biasing means for biasing in a direction to perform,
In the folded state, the structure, the proximal panel, and the distal panel are sequentially arranged in a spiral shape, and the distal panel is wound closer to the center of the vortex than the proximal panel. When the proximal panel is expanded beyond a predetermined angle by the biasing force of the biasing means from the folded state, the panel locking structure locks the distal panel. And the distal panel expands with respect to the proximal panel and transitions to the expanded state.

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