WO2019211964A1 - Réflecteur expansible et structure d'expansion pour réflecteur expansible - Google Patents

Réflecteur expansible et structure d'expansion pour réflecteur expansible Download PDF

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Publication number
WO2019211964A1
WO2019211964A1 PCT/JP2019/014833 JP2019014833W WO2019211964A1 WO 2019211964 A1 WO2019211964 A1 WO 2019211964A1 JP 2019014833 W JP2019014833 W JP 2019014833W WO 2019211964 A1 WO2019211964 A1 WO 2019211964A1
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WO
WIPO (PCT)
Prior art keywords
support
reflector
main
deployable
sub
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Application number
PCT/JP2019/014833
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English (en)
Japanese (ja)
Inventor
和行 中村
中村　信子
小澤　悟
顕太郎 西
Original Assignee
株式会社テクノソルバ
国立研究開発法人宇宙航空研究開発機構
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Publication date
Priority claimed from JP2018239922A external-priority patent/JP7179290B2/ja
Application filed by 株式会社テクノソルバ, 国立研究開発法人宇宙航空研究開発機構 filed Critical 株式会社テクノソルバ
Publication of WO2019211964A1 publication Critical patent/WO2019211964A1/fr

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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
    • H01Q15/14—Reflecting surfaces; Equivalent structures
    • H01Q15/18—Reflecting surfaces; Equivalent structures comprising plurality of mutually inclined plane surfaces, e.g. corner reflector
    • H01Q15/20—Collapsible reflectors

Definitions

  • the present invention relates to a deployable reflector and a deployable structure for a deployable reflector.
  • Patent Document 1 describes a deployable antenna that has a plurality of flat trusses arranged radially around a folding center axis, and can be folded and unfolded like a folding umbrella around the folding center axis. .
  • the present invention has been made in view of the above-described problems, and a deployable reflector having a structure capable of suppressing an error in the shape of the reflector surface caused by an error in the end position of the deploying operation, and for the deployable reflector An unfolding structure is provided.
  • a reference axis A support structure configured to be deployable around the reference axis, and forming a concave support surface on one surface side in the expanded state;
  • a reflector part supported by the support surface of the support structure part and forming a reflector surface along the support surface;
  • the support structure is A plurality of main supports elongated in a radial direction around the reference axis;
  • a sub-support that is laid between adjacent main supports; It is composed including At least one of the plurality of main supports is pivotally supported by the reference shaft, and an angle between the adjacent main support can be opened and closed around the reference shaft as an axis, When the angle between the main support that is pivotally supported by the reference shaft and the main support adjacent to the main support is widened, the sub support is installed between the main supports.
  • the support is developed in a circumferential direction centered on the reference axis to form a lattice structure that defines a plurality of facets,
  • a deployable reflector in which the support surface is formed by the plurality of main supports and the sub-support provided between the main supports.
  • a reference axis It is configured to be deployable with reference to the reference axis, and a support structure portion that forms a concave support surface on one surface side in the expanded state;
  • a deployable structure for a deployable reflector that supports a reflector portion forming a reflector surface of a deployable reflector by the support surface
  • the support structure is A plurality of main supports elongated in a radial direction around the reference axis; A sub-support that is laid between adjacent main supports; It is composed including At least one of the plurality of main supports is pivotally supported by the reference shaft, and an angle between the adjacent main support can be opened and closed around the reference shaft as an axis, When the angle between the main support that is pivotally supported by the reference shaft and the main support adjacent to the main support is widened, the sub support is installed between the main supports.
  • the support is developed in a circumferential direction centered on the reference axis to form a lattice structure that defines a plurality of facets,
  • a deployable structure for a deployable reflector in which the support surface is formed by the plurality of main supports and the sub-support provided between the main supports in the unfolded state.
  • the reflector surface is formed by the support structure portion being deployed in the circumferential direction centered on the reference axis, the shape error of the reflector surface due to the error in the end position of the deployment operation is suppressed. be able to.
  • FIG. 9A and FIG. 9B are views for explaining a connecting structure between a main support and a support element constituting the deployable reflector according to the embodiment, among which FIG. 9A is an exploded view.
  • FIG. 9B are perspective views of a connection state. It is a figure for demonstrating the connection structure of the main support body and support element which comprise the expandable reflector which concerns on embodiment, and the connection structure of support elements, among these, Fig.10 (a) is an exploded perspective view, FIG.
  • FIG. 13 (B) is a perspective view of a connection state. It is a top view for demonstrating the connection structure of the support elements which comprise the expandable reflector which concerns on embodiment.
  • FIG. 3 is a cross-sectional view taken along line AA in FIG. 2.
  • 13 (a) and 13 (b) are diagrams for explaining a structure for fixing the mesh (reflector portion) to the support element. Of these, FIG. 13 (a) shows the support element and the mesh as the plate surface of the support element.
  • FIG. 13B is a perspective view as viewed in the longitudinal direction. It is a figure for demonstrating the expansion
  • FIG. 15 (a) and 15 (b) are diagrams for explaining a modification of the connecting structure of the support elements constituting the deployable reflector, in which FIG. 15 (a) is a plan view and FIG. b) is a perspective view of the support element.
  • FIG. 16A is a schematic plan view showing a first modification of the arrangement of the support elements in the unit module
  • FIG. 16B is a schematic plan view showing a second modification of the arrangement of the support elements in the unit module.
  • FIG. 17 (a) and 17 (b) are schematic plan views for explaining Modification Example 1 of the unfolding mechanism. Of these, FIG. 17 (a) shows the storage state (folded state), and FIG. (B) shows a developed state.
  • FIG. 18 (a) and 18 (b) are schematic plan views for explaining Modification Example 2 of the unfolding mechanism.
  • FIG. 18 (a) shows the storage state (folded state)
  • FIG. (B) shows a developed state. It is a typical top view for demonstrating the modification 3 of an expansion
  • FIG. 20A and FIG. 20B is a schematic partial view for explaining a third modification of the deployment mechanism, in which FIG. 20A is a plan view and FIG. 20B is a plan view. It is a perspective view.
  • FIG. 21A and FIG. 21B is a schematic partial view for explaining Modification Example 4 of the deployment mechanism, in which FIG. 21A is a plan view and FIG. It is a perspective view.
  • FIG. 22A is a schematic plan view (partial view) for explaining Modification Example 5 of the deployment mechanism
  • FIG. 22B is a schematic plan view for explaining Modification Example 6 of the deployment mechanism.
  • FIG. 22A is a schematic plan view (partial view
  • the deployable reflector 100 includes a reference shaft 11, a support structure portion 12, and a reflector portion 50 (FIGS. 2, 13A, and 13B).
  • the reflector unit 50 is a mesh composed of a metal wire 51 as shown in FIG.
  • the support structure 12 is configured to be deployable around the reference shaft 11. In the unfolded state, the support structure portion 12 forms a concave support surface 13 (see FIG. 12) on one surface side of the support structure portion 12. In FIG. 2, the outline 52 of the reflector part 50 in the unfolded state is shown.
  • the reflector unit 50 covers substantially the entire support surface 13 of the support structure unit 12. Moreover, in each of FIG. 13A and FIG. 13B, only a part of the reflector unit 50 is shown.
  • the reflector unit 50 is supported by the support surface 13 of the support structure unit 12 and forms a reflector surface along the support surface 13.
  • the reference shaft 11 is formed in a linear bar shape.
  • the support structure portion 12 includes a plurality of main supports 20 that are long in the radial direction around the reference axis 11 and a sub-support 30 that is installed between adjacent main supports 20. It is configured. At least one of the plurality of main supports 20 is supported by the reference shaft 11, and an angle between the main support 20 and the adjacent main support 20 can be opened and closed with the reference shaft 11 as an axis center. When the angle between the main support 20 pivotally supported by the reference shaft 11 and the main support 20 adjacent to the main support 20 is opened, the main support 20 is installed between the main supports 20.
  • the sub support 30 expands in the circumferential direction around the reference axis 11.
  • the sub-support 30 has a lattice structure that defines a plurality of facets 37 (FIGS. 2 and 15).
  • a support surface 13 is formed by the plurality of main supports 20 and the sub-support 30 that is installed between the main supports 20.
  • the deployable structure 80 for a deployable reflector according to the present embodiment is obtained by removing the reflector portion 50 from the deployable reflector 100 according to the present embodiment. That is, the deployable structure 80 for a deployable reflector according to the present embodiment is configured to be deployable with reference to the reference shaft 11 and the reference shaft 11, and the concave support surface 13 is provided on one surface side in the deployed state.
  • a deployable structure for a deployable reflector that includes a support structure 12 and supports a reflector portion 50 that forms a reflector surface of the deployable reflector 100 with a support surface 13.
  • 11 includes a plurality of main supports 20 that are long in the radial direction around the center 11 and a sub-support 30 that is installed between adjacent main supports 20.
  • At least one of the bodies 20 is pivotally supported by the reference shaft 11, and an angle between the body 20 and the adjacent main support 20 can be opened and closed with the reference shaft 11 as an axis center.
  • the main support 20 is installed between the main supports 20.
  • the sub-support 30 is expanded in the circumferential direction around the reference axis 11 to form a lattice structure that defines a plurality of facets 37.
  • the sub-support 30 is between the main supports 20 and the main supports 20.
  • the support surface 13 is formed by the sub-support body 30 that is installed. It can be said that the deployable structure 80 for the deployable reflector is a framework that supports the reflector portion 50.
  • the reflector unit 50 is not shown.
  • the side on which the support surface 13 is located may be referred to as “up” and the opposite side may be referred to as “down”.
  • This convenient vertical direction does not necessarily coincide with the vertical direction when the deployable reflector 100 is manufactured or used.
  • the radial direction around the reference axis 11 may be referred to as the radial direction.
  • the deployable reflector 100 is, for example, deployed in outer space and used to reflect radio waves for transmitting or receiving radio waves.
  • the deployable reflector 100 can be used as, for example, a SAR (SAR: Synthetic Aperture Radar), a synthetic aperture radar, or a transmission or reception antenna for communication.
  • SAR Synthetic Aperture Radar
  • the place where the deployable reflector 100 is used is not limited to outer space, and may be, for example, the ground or the stratosphere.
  • each of the plurality of main supports 20 is formed in a plane shape parallel to the reference axis 11. More specifically, in the case of this embodiment, each of the plurality of main supports 20 is formed in a thin plate shape. That is, each of the plurality of main supports 20 is formed in a thin plate shape that is long in the radial direction around the reference axis 11 and parallel to the reference axis 11.
  • the main supports 20 are arranged so as to be substantially rotationally symmetric in plan view (when the support structure 12 is viewed in the axial direction of the reference shaft 11).
  • the support surface 13 is, for example, substantially circular in plan view. However, in the case of this embodiment, the support surface 13 is an offset parabolic surface.
  • the length of the main support body 20 in the radial direction around the reference axis 11 is slightly different from each other, for example (see FIG. 3).
  • the number of main supports 20 included in the support structure 12 is not particularly limited.
  • the support structure 12 includes, for example, 13 main supports 20.
  • one main support body 20 (fixed support body 20b described later) is fixed to a boom 61 described later.
  • another main support 20 (drive support 20a described later) adjacent to one side with respect to the fixed support 20b is in a state of being in surface contact with the fixed support 20b in the unfolded state (FIG. 2). reference).
  • the sub support 30 is not installed between the drive support 20a and the fixed support 20b.
  • eleven main supports 20 other than the drive support 20a and the fixed support 20b are referred to as driven supports 20c.
  • the support structure 12 includes a total of 12 sub-supports 30 (FIGS. 1 and 2).
  • a portion between a pair of adjacent main supports 20 may be referred to as a unit module 15.
  • Adjacent unit modules 15 share a main support 20 located at the boundary between them.
  • the unit module 15 does not exist between the drive support 20a and the fixed support 20b.
  • the support structure 12 is configured by twelve unit modules 15.
  • the main support 20 is more specifically, for example, as shown in FIGS. 7 and 8, a flat plate-like portion 21, a first support arm 25 fixed to the plate-like portion 21, and And a second support arm 26.
  • the plate-like portion 21 is formed in a thin plate shape that is long in the radial direction about the reference axis 11 and parallel to the reference axis 11.
  • Each of the first support arm 25 and the second support arm 26 is formed long in the radial direction.
  • Each of the first support arm 25 and the second support arm 26 is, for example, a flat plate member whose plate surface faces up and down, and is gradually tapered outward in the radial direction. That is, the dimensions of the first support arm 25 and the second support arm 26 in the circumferential direction around the reference axis 11 are reduced toward the outside in the radial direction.
  • the first support arm 25 and the second support arm 26 are pivotally supported on the reference shaft 11. That is, an insertion hole 25 a is formed at one end of the first support arm 25, and the first support arm 25 is arranged around the axis of the reference axis 11 by inserting the reference shaft 11 into the insertion hole 25 a. It is pivotally supported so that it can rotate. Similarly, an insertion hole 26 a is formed at one end of the second support arm 26, and the second support arm 26 is rotated around the axis of the reference axis 11 by inserting the reference shaft 11 into the insertion hole 26 a. It is pivotally supported by the shaft.
  • the first support arm 25 and the second support arm 26 of the fixed support 20b may be fixed to the reference shaft 11 or may be supported by the reference shaft 11. That is, the fixed support body 20 b may be fixed to the reference shaft 11 without being supported by the reference shaft 11, or may be supported by the reference shaft 11.
  • the other end of the first support arm 25, that is, the tip 25b, and the other end of the second support arm 26, that is, the tip 26b, are fixed to the radially inner end of the plate-like portion 21.
  • the plate-like portion 21 has, for example, two or three extending portions that extend radially inward.
  • each of the plate-like portions 21 of the fixed support body 20b and the driven support body 20c includes a first extension portion 22 located at a lower portion of the radially inner end portion of the plate-like portion 21 and the plate-like portion.
  • a second extending portion 23 located at the upper portion of the end portion on the radially inner side of the 21, and a third extending portion 24 located on the upper end portion of the end portion on the radially inner side of the plate-like portion 21.
  • the plate-like portion 21 of the drive support 20a includes a first extending portion 22 located at a lower portion of an end portion on the radially inner side of the plate-like portion 21 and an end portion on the radially inner side of the plate-like portion 21.
  • the second extending portion 23 is located at the upper end of the second extending portion 23, and the third extending portion 24 is not included.
  • the second support arm 26 is spaced apart from the first support arm 25.
  • the distal end portion 25 b of the first support arm 25 is fixed to the first extending portion 22 of the plate-like portion 21, and the distal end portion 26 b of the second support arm 26 is fixed to the second extending portion 23 of the plate-like portion 21. It is fixed to. Accordingly, the plate-like portion 21 is pivotally supported on the reference shaft 11 via a pair of upper and lower support arms (first support arm 25 and second support arm 26). That is, the main support 20 including the plate-like portion 21, the first support arm 25, and the second support arm 26 is pivotally supported on the reference shaft 11.
  • the first support arm 25 and the second support arm 26 of the fixed support 20b may be fixed to the reference shaft 11 as described above. Therefore, the fixed support 20b is fixed to the reference shaft 11. It may be.
  • the height difference between the height position where the first extension portion 22 is arranged and the height position where the second extension portion 23 is arranged is that the first support arm 25 is arranged. Is equal to the height difference between the height position where the second support arm 26 is disposed and the height position where the second support arm 26 is disposed.
  • first support arms 25 of the main support bodies 20 adjacent to each other have different height positions from each other by the thickness of the first support arm 25.
  • second support arms 26 of the main support bodies 20 adjacent to each other are different in height from each other by the thickness of the second support arm 26.
  • first support arms 25 are arranged to overlap each other, and the second support arms 26 are arranged to overlap each other.
  • the first support arm 25 at the uppermost position among the plurality of first support arms 25 and the second support arm 26 at the lowermost position among the plurality of second support arms 26 are disposed so as to overlap each other.
  • the boom 61 is connected to a structure of a spacecraft (hereinafter referred to as a space mechanism body) via, for example, a boom deployment mechanism (not shown).
  • the boom 61 is formed in a bar shape that is long in one direction.
  • the boom 61 extends in the radial direction about the reference shaft 11.
  • the fixed support body 20 b is fixed to the boom 61. More specifically, the lower edge portion of the plate-like portion 21 of the fixed support 20b is fixed along the longitudinal direction of the boom 61 (see FIGS. 4 and 12).
  • the plurality of main supports 20 13 main supports 20 in the case of the present embodiment
  • at least the 12 main supports 20 excluding the fixed supports 20 b are the reference shafts 11.
  • the plurality of main support bodies 20 included in the support structure 12 are close to each other in the circumferential direction and overlap each other in the circumferential direction.
  • the angle between the adjacent main supports 20 is opened (for example, each is opened at 30 degrees), and accordingly, it is installed between the adjacent main supports 20.
  • the sub-support 30 is expanded.
  • the sub-support 30 has a shape (lattice structure) that defines a plurality of facets 37.
  • the sub-support 30 includes a plurality of support elements 31 that form a lattice structure.
  • Each of the support elements 31 is formed in a plane shape parallel to the reference axis 11. More specifically, in the case of the present embodiment, each of the plurality of support elements 31 is formed in a thin plate shape.
  • the bending rigidity of the main support 20 is preferably larger than the bending rigidity of the support element 31.
  • the main support 20 and the support element 31 are made of the same material, and the plate thickness of the main support 20 is larger than the plate thickness of the support element 31.
  • the material of the plate-like portion 21 of the support element 31 and the main support 20 is not particularly limited, but each of the support element 31 and the plate-like portion 21 is made of, for example, carbon fiber reinforced plastic (CFRP: Carbon Fiber Reinforced Plastics). can do.
  • CFRP Carbon Fiber Reinforced Plastics
  • the plurality of support elements 31 intersect in a lattice pattern.
  • a facet 37 is formed by the plurality of support elements 31.
  • the shape of the facet 37 formed by the plurality of support elements 31 of the sub-support 30 is a rhombus.
  • the facet 37 includes a facet 37 surrounded by a plurality of support elements 31 and a facet 37 surrounded by the plurality of support elements 31 and the main support 20.
  • the majority of the plurality of facets 37 defined by the sub-support 30 in the expanded state preferably has a shape elongated in the radial direction around the reference axis 11. Longer in the radial direction means that the dimension of the facet 37 in the radial direction is larger than the dimension of the facet 37 in the direction orthogonal to the radial direction in the plane of the facet 37.
  • the majority of the plurality of facets 37 is a rhombus that is long in the radial direction around the reference axis 11. More specifically, in the case of the present embodiment, substantially all facets 37 (the facets 37 except for the facets 37 at the peripheral edge of the support structure 12) are long diamonds in the radial direction around the reference axis 11. It is.
  • the sub-support body 30 includes a plurality of support elements 31 (which are arranged in parallel to one main support body 20 among the pair of main support bodies 20 sandwiching the sub-support body 30 therebetween.
  • a plurality of support elements 31 which are arranged in parallel to one main support body 20 among the pair of main support bodies 20 sandwiching the sub-support body 30 therebetween.
  • seven support elements 31 and a plurality of support elements 31 arranged in parallel to the other main support 20 (for example, seven support elements as shown in FIG. 5). 31).
  • a plurality of support elements 31 arranged in parallel to one main support 20 and a plurality of support elements 31 arranged in parallel to the other main support 20 intersect each other. .
  • FIGS. 5 and 7 it is possible to easily realize a structure in which each facet 37 has a diamond shape in the unfolded state.
  • the facet shape is square (the length of one side is 300 mm) and the case where the facet shape is an equilateral triangle (the length of one side is 300 mm), it was found that the latter has a smaller error. . If the facet shape is an equilateral triangle (the length of one side is 300 mm) and the facet shape is a rhombus (the length of one side is 312.5 mm, the apex angle is 45 degrees), the latter However, the error was found to be small.
  • the apex angle of the rhombus facet 37 is preferably less than 60 degrees, and more preferably less than 45 degrees.
  • the plurality of support elements 31 of the sub-support 30 intersect each other in a lattice shape.
  • the intersecting portion 32 (FIG. 5) between the support elements 31 is a swinging portion that allows the support elements 31 that intersect each other to swing each other.
  • the swinging axis of this swinging part is parallel to the reference shaft 11.
  • the swinging portion is a hinge configured by connecting the support elements 31 by an insertion structure.
  • the present invention is not limited to this example, and the swinging portion may be a portion that swings due to elastic deformation of the support element 31 itself.
  • one end portion 34 (FIG. 5) of the support element 31 is connected to the main support body 20, and this connection portion is also a swinging portion.
  • the swing axis of this swing part is also parallel to the reference axis 11.
  • connection structure between the main support 20 and the support element 31 and an example of a connection structure between the support elements 31 will be described with reference to FIGS. 9A to 10B.
  • the plate-like portion 21 of each main support 20 is formed with a plurality of slits 21c opened upward in a straight line. That is, the upper end of the slit 21 c reaches the upper edge 21 a of the plate-like portion 21, and the lower end of the slit 21 c does not reach the lower edge 21 b of the plate-like portion 21.
  • the plurality of slits 21c are arranged at equal intervals in the radial direction (radial direction).
  • each plate-like portion 21 has seven slits 21c.
  • the vertical dimension of each slit 21 c corresponds to the vertical dimension of the support element 31 at the connection point between the main support 20 and the support element 31. That is, the vertical dimension of the slit 21c located on the radially outer side is larger.
  • the support elements 31 of the adjacent sub-support bodies 30 are formed integrally with each other.
  • a support element 31 (support element 31 a) that constitutes one sub-support 30 and a support element 31 that constitutes the other sub-support 30 ( The support element 31b) is integrally formed.
  • the support elements 31a and 31b are bent with respect to each other at the boundary lines (end portions 34 of the support elements 31a and 31b), and can swing with respect to each other using the boundary lines as swing axes. . That is, the end portion 34 is a swinging portion between the support element 31a and the support element 31b.
  • the support elements 31a and 31b swingable, for example, a structure in which the resin thickness of the carbon fiber reinforced plastic constituting the support element 31 is locally thin at the end 34, or A structure in which carbon fibers are not locally impregnated with resin can be adopted.
  • the support element assembly 310 is a thin plate having a bent shape with a V shape in plan view.
  • the support elements 31 constituting the sub-support 30 have a plurality of types of lengths (for example, seven types of lengths).
  • the support element 31 connected to the radially inner portion of the plate-like portion 21 has a longer length, and the support element 31 connected to the radially outer portion of the plate-like portion 21 has a shorter length.
  • the support element assembly 310 is also prepared with a plurality of types of dimensions according to the type of length of the support element 31 (see FIG. 10A).
  • the deployable reflector 100 includes a support element 31 having a slit 33 opened upward as shown in FIGS. 9A and 9B and a slit 33 opened downward as shown in FIG. 10A. And a supporting element 31. That is, the deployable reflector 100 includes the support element assembly 310 having the slits 33 opened upward and the support element assembly 310 having the slits 33 opened downward.
  • the slit 33 of the support element 31 is formed at a position corresponding to the intersection 32 of the support elements 31 in the sub-support 30. More slits 33 are formed in the support element 31 that intersects more support elements 31.
  • the central portion of the support element assembly 310 (the end portion 34 of the support element 31) having the slit 33 that opens upward is moved to the main support 20. Insert into slit 21c.
  • the support element aggregate 310 having the slits 33 opened upward is inserted into the odd-numbered main support 20 in the circumferential order.
  • the center portion of the support element assembly 310 having the slit 33 that opens downward is inserted into the slit 21 c of the main support 20.
  • the support element assembly 310 having the slits 33 opened downward is inserted into the main support 20 that is even-numbered in the circumferential order.
  • the other is inserted into the slit 33 of each support element 31.
  • the intersection part 32 the rocking
  • the end part 34 of the support element 31 is connected to the fixed support 20b and the drive support 20a so as to be swingable.
  • each of the plurality of support elements 31 is formed in a thin plate shape, and the other of the support elements 31 that intersect each other is inserted into the slits 33 formed in the corresponding positions.
  • this engagement portion is a swinging portion (in this embodiment, a hinge). For this reason, while being able to connect the support elements 31 with a simple structure, it is possible to realize a configuration in which the support elements 31 swing.
  • the support element aggregate 310 is shared between the adjacent sub-supports 30. For this reason, a structure in which the sub-supports 30 are highly integrated can be realized.
  • a flexible adhesive tape 91 such as Kapton tape (registered trademark) is attached to the support elements 31 that intersect each other across the intersection 32.
  • Kapton tape registered trademark
  • the support elements 31 that intersect each other may be bonded to each other with a sheet made of the same material as that of the support element 31 straddling the intersection 32. That is, the intersecting portion 32 may be reinforced with a doubler structure.
  • the support surface 13 includes an upper edge 21 a of the plate-like portion 21 of the main support 20 and an upper edge 35 of the support element 31.
  • the curved surface is the support surface 13 (see FIGS. 1 and 12).
  • the shape of the support surface 13 may be a part of the surface of the polyhedron (lattice surface).
  • the vertical dimension of the plate-like part 21 gradually increases toward the tip side (radially outer side). More specifically, as shown in FIG. 12, the lower edge 21 b of the plate-like portion 21 extends in a straight line perpendicular to the reference axis 11, whereas the upper edge 21 a of the plate-like portion 21. Is gradually curved upward toward the tip side. Similarly, the vertical dimension of each support element 31 gradually increases as the distance from the reference axis 11 increases. More specifically, the lower edge 36 of the support element 31 extends in parallel to a plane including the upper edges 21 a of the plate-like portions 21 of the plurality of main supports 20.
  • the upper edge 35 of the support element 31 is gradually curved upward as it moves away from the reference axis 11.
  • the support surface 13 which is a smooth concave curved surface can be implement
  • the vertical dimension of the plate-like portion 21, that is, the vertical dimension of the main support 20 (the dimensions of the plate-like portion 21 and the main support 20 in the direction parallel to the axial direction of the reference shaft 11) It is larger than the vertical dimension (the dimension of the support element 31 in the direction parallel to the axial direction of the reference shaft 11). That is, the lower edge 36 of each support element 31 is located above a plane including the lower edges 21b of the plate-like portions 21 of the plurality of main supports 20.
  • the sub support 30 is provided on the upper part of the main support 20 (part on the support surface 13 side).
  • the reflector unit 50 is configured by knitting a plurality of metal wires 51 in a fine mesh shape.
  • the metal wire 51 constituting the reflector part 50 is fixed to the upper edge 35 of the support element 31 and the upper edge 21a of the plate-like part 21 of the main support 20.
  • FIG. 13B shows a state in which the metal wire 51 is fixed to the upper edge 35 of the support element 31.
  • a method for fixing the metal wire 51 is not particularly limited. For example, in a state where the reflector portion 50 is disposed along the support surface 13, a relatively soft adhesive 92 is supported on the support surface as shown in FIG. 13 may be bonded and fixed by potting from the lower side to the joint between the upper edge 35 or the upper edge 21a and the metal wire 51.
  • the reflector portion 50 is extended so as to have a shape along a mandrel (not shown) having a convex surface that fits the support surface 13.
  • the support surface 13 of the support structure portion 12 in the deployed state is abutted with the convex surface of the mandrel via the reflector portion 50.
  • the reflector line 50 is provided so as to cover almost the entire region of the support structure 12 in the unfolded state. In the unfolded state, the reflector portion 50 has a shape along the support surface 13.
  • the reflector portion 50 is fixed to the support structure portion 12 so as to be bent in a shape along the offset parabolic surface in the deployed state.
  • the support structure part 12 is slightly curved by the tension of the reflector part 50 by pulling the mandrel away from the reflector part 50.
  • the shape of the convex surface of the mandrel corresponds to the ideal shape of the support surface 13 and the reflector portion 50 so that the support surface 13 and the reflector portion 50 have an ideal shape when the support structure portion 12 is bent by the tension of the reflector portion 50.
  • the shape may be slightly different from the shape to be made.
  • the shape of the convex surface of the mandrel may be a shape corresponding to the ideal shape of the support surface 13 and the reflector portion 50.
  • each edge (upper edge 35) of the plurality of support elements 31 on one surface side (upper side) of the support structure portion 12 is a linear first support portion capable of supporting the reflector portion 50. . That is, the first support portion is continuously disposed on the upper edge 35 of each of the plurality of support elements 31. For this reason, the reflector part 50 can be supported by the support element 31 with high positional accuracy and high flexibility.
  • Each of the plurality of main supports 20 on the one surface side (upper side) of the support structure portion 12 has a linear second support capable of supporting the reflector portion 50.
  • the second support portion is continuously arranged on the upper edges 21 a of the plurality of main support bodies 20. For this reason, the reflector part 50 can be supported by the main support 20 with high positional accuracy and high flexibility.
  • one of the plurality of main supports 20 is a drive support 20a.
  • the drive support 20a is rotationally driven about the reference shaft 11 as a rotational axis by a rotational power applying mechanism 70 described below.
  • the deployable reflector 100 is folded (stored) (FIGS. 3, 4, and 12) (FIGS. 6 and 8 for the unit module 15) (FIG. 6, FIG. 8). 1, FIG. 2, FIG. 5) (the unit module 15 is transformed into FIG. 7).
  • the rotational power applying mechanism 70 rotates the motor 71 with respect to a motor 71 fixed to the boom 61 and a drive shaft (not shown) inserted into the reference shaft 11. And a drive transmission mechanism 72 that transmits power.
  • the drive transmission mechanism 72 has a pair of bevel gears meshed with each other, for example, to rotate the output shaft. The rotation is converted to a rotation in a direction orthogonal to the rotation and transmitted to the drive shaft.
  • the drive transmission mechanism 72 may include a speed reducer that reduces the rotational speed in the process of transmitting rotational power from the output shaft of the motor 71 to the drive shaft.
  • the rotational power applying mechanism 70 may include a power source (not shown) that supplies electric power to the motor 71, or electric power may be supplied from the space mechanism body to the motor 71 via a cable.
  • the drive support 20a is rotated in the circumferential direction about the reference shaft 11 by the rotational power applying mechanism 70. That is, the drive support 20a is rotated counterclockwise in FIG. In FIG. 14, the counterclockwise direction around the reference axis 11 is referred to as the rotation direction, and the opposite direction (clockwise direction) is referred to as the rotation direction rearward.
  • the angle between the drive support 20a and the driven support 20c adjacent to the drive support 20a on the rear side in the rotational direction is first increased. Open gradually. Along with this, the sub-support 30 between the drive support 20a and the driven support 20c is gradually developed.
  • the state shown in FIG. 14 is a state in which the development of the sub-support 30 between the drive support 20a and the driven support 20c adjacent to the drive support 20a on the rear side in the rotation direction is completed.
  • the angle between the drive support 20a and the driven support 20c adjacent to the drive support 20a on the rear side in the rotational direction is 30 degrees.
  • the main supports 20 are connected to each other (not always connected), or the drive shaft and the main support 20 are engaged.
  • the unfoldable reflector 100 is in the unfolded state as shown in FIG.
  • the drive support 20a and the fixed support 20b are in surface contact. Note that after the unfolded state, the drive of the motor 71 is stopped.
  • the unfolded reflector 100 In the retracted state (folded state), the unfolded reflector 100 has a fan-shaped planar shape as shown in FIG. 3, and in the unfolded state, the planar shape is substantially circular as shown in FIG.
  • the rotation axis of each main support 20 in the unfolding operation of the unfoldable reflector 100, is the common reference axis 11 (that is, there is one rotation axis). For this reason, since an error (variation) in the unfolding operation can be suppressed, the support surface 13 having a highly accurate shape can be easily formed. Further, since the unfolding operation itself is simple, a simple configuration can be adopted as the drive transmission mechanism 72.
  • the reference shaft 11 is formed in a cylindrical shape, and a rod-shaped drive shaft is inserted into the reference shaft 11.
  • the drive shaft is disposed through the reference shaft 11.
  • a lower fixing member 42 is fixed to one end portion (lower end portion) of the drive shaft outside (lower side) one end (lower end) of the reference shaft 11.
  • the rotational power application mechanism 70 rotates the drive shaft about the axis center of the reference shaft 11 by rotating the lower fixing member 42, for example.
  • an upper fixing member 43 is fixed to the other end portion (upper end portion) of the drive shaft.
  • the upper fixing member 43 is disposed on the upper surface of the second support arm 26 of the drive support 20a.
  • the second support arm 26 of the drive support 20a is fixed to the upper fixing member 43.
  • the second support arm 26 of each main support 20 is disposed adjacent to the top and bottom.
  • the second support arm 26 of the drive support 20a is disposed at the top, and the second support arm 26 of the driven support 20c adjacent to the drive support 20a is viewed from above.
  • the second support arm 26 of each driven support 20c is arranged in order from the top in the clockwise order in FIG.
  • the 2nd support arm 26 of the fixed support body 20b is arrange
  • the first support arm 25 of each main support 20 is disposed adjacent to the top and bottom.
  • the first support arm 25 of the drive support 20a is disposed at the top, and the first support arm 25 of the driven support 20c adjacent to the drive support 20a is from above. Arranged second.
  • the first support arm 25 of each driven support 20c is arranged in order from the top in the clockwise order in FIG.
  • the 1st support arm 25 of the fixed support body 20b is arrange
  • each main support 20 is supported by the reference shaft 11 with the same support strength. Can do.
  • first support arms 25 of the main support bodies 20 are arranged in a stepwise manner, and the second support arms 26 of the main support bodies 20 are arranged in a stepped manner.
  • positioned are divided up and down. Therefore, the first support arms 25 do not interfere with each other, the second support arms 26 do not interfere with each other, and the first support arm 25 and the second support arm 26 do not interfere with each other. For this reason, the dimension (fan-shaped angle) in the retracted state of the deployable reflector 100 can be made compact, and the unfolding operation can be performed smoothly.
  • the number of the main supports 20 that are supported by the reference shaft 11 is two or more, and the main supports 20 that are supported by the reference shaft 11. At least one of them is a drive support 20a that is rotationally driven.
  • the deployable reflector 100 further includes a rotational power applying mechanism 70 that rotates the drive support body 20a in the circumferential direction about the reference shaft 11 as a center of rotation, thereby bringing the support structure portion 12 into a deployed state.
  • the deployable reflector 100 may include a latch mechanism (not shown) that maintains the deployable reflector 100 in the deployed state.
  • the latch mechanism restricts the drive support 20a and the fixed support 20b from being separated from each other after the unfolding operation is completed. Further, it may be possible to deform the deployable reflector 100 from the deployed state to the retracted state (folded state) by rotating the drive support 20a in the circumferential direction in the opposite direction to the unfolding operation. Further, if necessary, the unfolding operation may be stopped halfway, the unfoldable reflector 100 may be folded, and then the unfolding operation may be performed again.
  • each part other than the plate-like part 21 and the support element 31 in the deployable reflector 100 is not particularly limited, but is preferably a material that is lightweight and can ensure sufficient strength.
  • a material that is lightweight and can ensure sufficient strength As an example, carbon fiber reinforced plastic is used. Alternatively, a metal material may be used.
  • the reflector surface is formed by the support structure portion 12 expanding in the circumferential direction (circumferential direction) centering on the reference axis 11. For this reason, unlike the case where the antenna unfolding operation is performed in a direction having a component perpendicular to the plane of the antenna as in Patent Document 1, the shape error of the reflector surface due to the error of the end position of the unfolding operation is greatly increased. Therefore, it is possible to form a highly accurate reflector surface.
  • the metal wire 51 of the reflector unit 50 is fixed directly to the upper edge 21 a of the plate-like part 21 of the main support 20 and the upper edge 35 of the support element 31.
  • the deployable reflector 100 according to the present embodiment does not need to include a cable network that is used in a general deployable reflector. Therefore, it is not necessary to take measures against pillow deformation due to cable catenary deformation, and it is possible to prevent problems caused by increasing the tension of the cable in order to reduce the pillow deformation.
  • connection structure between the support elements 31 constituting the sub-support 30 will be described with reference to FIGS.
  • the sub-support 30 has a joint 38 in which the support elements 31 are partially joined (surface joined), and the joint 38 is a swinging part.
  • bent portions 39 that can be bent more flexibly than other portions are formed on both sides of the portion where the joint portion 38 is formed.
  • the bent portion 39 may be a portion where the resin thickness of the carbon fiber reinforced plastic constituting the support element 31 is locally thinned, or a portion where the carbon fiber is not locally impregnated with resin.
  • the sub-support 30 constituting the unit module 15 has a support element 111 extending in the circumferential direction. More specifically, the support element 111 extends in a tangential direction with respect to the circumference around the reference axis 11. Further, the sub-support 30 has a plurality of support elements 111, and these support elements 111 extend in parallel with each other in the deployed state. For example, the support element 111 is installed between adjacent main supports 20. Each facet 37 has a triangular shape (for example, an isosceles triangular shape).
  • the edge (upper edge) of the support element 111 constitutes the support surface 13 together with the edge of the support element 31 (upper edge 35 described in the embodiment) and the edge of the main support 20 (upper edge 21a described in the embodiment). Then, the reflector unit 50 is supported.
  • the support element 111 is configured to be more flexible than the support element 31 so that the support element 111 can easily expand and contract in the circumferential direction. In the case of this modification, the other structures are the same as those in the above embodiment, and thus the description thereof is omitted.
  • the sub-support 30 does not include the support element 112 that is the outermost support element 111 among the support elements 111. However, the configuration including the support element 112 may also be adopted in the above embodiment.
  • the sub-support 30 constituting the unit module 15 includes a support element 111 that extends in the circumferential direction, as in Modification 1 of the arrangement of the support elements in the unit module.
  • the support element 31 extends in a direction orthogonal to the support element 111.
  • the edge (upper edge) of the support element 111 constitutes the support surface 13 together with the edge (upper edge 35) of the support element 31 and the edge (upper edge 21a) of the main support 20, and the reflector.
  • the part 50 is supported.
  • the support element 111 is configured more flexibly than the support element 31 so that it can be easily expanded and contracted in the circumferential direction.
  • the sub-support 30 does not include the support element 112 which is the outermost support element 111 among the support elements 111.
  • modified example 1 multi-joint deployment method of the deployment mechanism of the deployable reflector will be described with reference to FIGS. 17 (a) and 17 (b).
  • the sub-support 30 and the reflector unit 50 are not shown.
  • the deployable reflector 100 according to the present modification is different from the deployable reflector 100 according to the above-described embodiment in the points described below, and is otherwise different from the deployable reflector 100 according to the above-described embodiment. It is constituted similarly.
  • the deployable reflector 100 includes a plurality of relative rotation members 121 that individually support the main support bodies 20 and a connection hinge 122 that connects the adjacent relative rotation members 121 so as to be mutually rotatable. And.
  • Each relative rotating member 121 has a trapezoidal planar shape, for example.
  • the relative rotation member 121 is formed in a shape having a thickness in a direction orthogonal to the paper surface of FIG. 17A, that is, a three-dimensional shape having a trapezoidal cross section.
  • the relative rotation members 121 are arranged in a line, and each main support 20 protrudes in one direction from the opposing relative rotation member 121.
  • the main supports 20 are arranged in parallel to each other.
  • the corners of the upper and lower bases of the trapezoidal shape (hereinafter referred to as long sides) are connected to each other via a connecting hinge 122.
  • the deployable reflector 100 further deforms the deployable reflector 100 into a deployed state shown in FIG. 17A by winding the cable 123 between the plurality of relative rotating members 121 and winding the cable 123.
  • Cable take-up mechanism 124 The cable 123 is routed along a smaller dimension (hereinafter referred to as a short side) of the trapezoidal upper and lower bases of the relative rotating member 121.
  • a ring member (not shown) is fixed to the short side of the relative rotation member 121, and the cable 123 is sequentially passed through the ring member of each relative rotation member 121.
  • the deployable reflector 100 includes, for example, two (or two sets) of cables 123, and one cable 123 is connected to the central relative rotation member 121 in FIG. 17A.
  • the ring members of the other six relative rotating members 121 arranged on the left side of the central relative rotating member 121 are sequentially inserted.
  • the tip of one cable 123 is fixed to the ring member of the relative rotation member 121 farthest from the central relative rotation member 121 among the six relative rotation members 121.
  • the other cable 123 is sequentially connected to the central relative rotating member 121 and the ring members of the other five relative rotating members 121 arranged on the right side of the central relative rotating member 121 in FIG. Is inserted.
  • the tip of the other cable 123 is fixed to the ring member of the relative rotation member 121 farthest from the central relative rotation member 121 among the five relative rotation members 121. Note that the deployable reflector 100 according to this modification does not include the rotational power applying mechanism 70 described in the above embodiment.
  • the cable winding mechanism 124 is provided, for example, at the central relative rotation member 121.
  • the cable winding mechanism 124 includes a motor 125 for winding two sets of cables 123 in synchronization with each other. By driving the motor 125 and winding the two sets of cables 123 in synchronism with each other, the portions of the adjacent relative rotation members 121 that become the hypotenuses in plan view are close to each other. Thereby, as shown in FIG.17 (b), the expansion
  • the planar shape of the deployable reflector 100 is a rectangular shape in the housed state. For this reason, at the time of launch, the deployable reflector 100 can be easily held by the space mechanism.
  • Modification Example 2 of Deployment Mechanism> modification 2 (elastic hinge deployment method) of the deployment mechanism of the deployable reflector will be described with reference to FIGS. 18 (a) and 18 (b). 18A and 18B, the sub support 30 and the reflector unit 50 are not shown.
  • the deployable reflector 100 according to the present modified example is different from the deployable reflector 100 according to the modified example 1 shown in FIGS. 17A and 17B in the points described below.
  • the configuration is the same as that of the deployable reflector 100 according to the first modification.
  • the deployable reflector 100 does not include the cable 123, the cable winding mechanism 124 (including the motor 125), and the connecting hinge 122 shown in FIGS. 17 (a) and 17 (b). Instead, the deployable reflector 100 according to this modification includes an elastic hinge 131 and a latch mechanism 134 (including a motor 135).
  • the elastic hinge 131 is continuously disposed across the long sides of the plurality of relative rotating members 121.
  • the elastic hinge 131 may be locally constructed only between the long side ends of the adjacent relative rotating members 121.
  • the elastic hinge 131 is in a distorted state having an internal stress in the retracted state of the deployable reflector 100 shown in FIG. 18A, and is in an unstrained state in the expanded state shown in FIG. 18B.
  • the unfolding can be performed to some extent by the elastic energy of the spring of the elastic hinge 131.
  • the deployable reflector 100 includes a latch mechanism 134 for finally maintaining the deployable reflector 100 in the deployed state.
  • the latch mechanism 134 includes a motor 135 as an actuator for operating the latch mechanism 134.
  • deployment type reflector 100 becomes a rectangular shape in the accommodation state. For this reason, at the time of launch, the deployable reflector 100 can be easily held by the space mechanism.
  • the connection hinge 122 is not used for the connection between the relative rotation members 121. It is possible to eliminate the error of the unfolding operation due to the above, and it is possible to form the support surface 13 with higher accuracy.
  • Modification 3 of the deployment mechanism of the deployable reflector will be described with reference to FIGS. 19 to 20B.
  • the sub-support 30 and the reflector unit 50 are not shown.
  • the deployable reflector 100 according to the present modification is different from the deployable reflector 100 according to the above-described embodiment in the points described below, and is otherwise different from the deployable reflector 100 according to the above-described embodiment. It is constituted similarly.
  • the deployable reflector 100 connects the main supports 20 adjacent to each other and separates the main supports 20 from each other.
  • a biasing portion 150 that biases elastically in the direction is provided.
  • the adjacent main supports 20 are elastically coupled to each other via the biasing portion 150.
  • the urging unit 150 is disposed between the main support tables 20 adjacent to each other.
  • the urging portion 150 is not disposed between the drive support 20a and the fixed support 20b. That is, for example, as shown in FIG.
  • the urging portions 150 are disposed between the support bodies 20c and between the driven support bodies 20c adjacent to each other.
  • the deployable reflector 100 is in the unfolded state as shown in FIG. 19 by the force by which each of the urging portions 150 urges the main supports 20 adjacent to each other in the direction of separating them.
  • each urging portion 150 is constituted by a single leaf spring 151, and the elastic force of the leaf spring 151 causes each other to
  • the adjacent main support bodies 20 are urged in a direction in which they are separated from each other.
  • Each part of the plate surface of each leaf spring 151 is parallel to the axial direction of the reference shaft 11.
  • the shape of each leaf spring 151 when viewed in the axial direction of the reference shaft 11 is bent into a convex V shape toward the radially inner side of the deployable reflector 100.
  • Both end portions of each leaf spring 151 are fixed portions 152 fixed to one of the main supports 20 adjacent to each other.
  • each leaf spring 151 excluding both end portions (a pair of fixing portions 152) is an erection portion 153 that is erected between adjacent main support bodies 20 and floats in the air.
  • the erection part 153 exerts an elastic force that urges the main supports 20 adjacent to each other in a direction in which they are separated from each other.
  • plate spring 151 is not specifically limited, From a viewpoint of weight reduction, it is preferable that it is a carbon fiber reinforced plastic. However, the leaf spring 151 may be made of other materials such as metal.
  • a method for fixing the fixing portion 152 of the leaf spring 151 to the main support 20 is not particularly limited, and may be adhesive fixing or fixing by fixing using a fixing member such as a bolt. .
  • the fixing portion 152 is fixed to the plate-like portion 21 of the main support 20 by surface bonding.
  • the deployable reflector 100 can be deployed by the elastic force of the urging unit 150 regardless of the power of the motor or the like.
  • the axial direction of the reference shaft 11 that is, substantially in the direction perpendicular to the reflector portion 50, that is, out of the plane of the reflecting mirror). Misalignment between the main supports 20 in the direction) can be regulated by the urging unit 150.
  • the urging portion 150 is configured by the leaf spring 151 and the surface direction of the leaf spring 151 is parallel to the axial direction of the reference shaft 11.
  • the deploying operation of the deployable reflector 100 can be performed with high positional accuracy.
  • the shape of the reflector unit 50 can be made closer to an ideal shape. That is, the reflector unit 50 can be developed into a desired shape with higher accuracy.
  • the deployable reflector is shown.
  • the number of urging portions 150 included in 100 is 12, and the angle between adjacent main supports 20 (excluding the angle between the drive support 20a and the fixed support 20b) is, for example, 30 degrees. .
  • the V-shaped opening angle of the leaf spring 151 is preferably an angle larger than 30 degrees.
  • the leaf springs 151 of the urging portions 150 adjacent to each other are interposed via the main support 20 positioned therebetween. It is preferable that they are pressed against each other. It is preferable that the spring force of the leaf spring 151 of each urging portion 150 is equal to each other.
  • the adjacent main supports 20 are close to each other, the V-shaped opening angle of each leaf spring 151 is narrowed, and each leaf spring 151 is The spring force is stored.
  • the deployable reflector 100 may include a deployment control mechanism (not shown) that controls the opening angle between adjacent main supports 20 during deployment.
  • the unfolding control mechanism includes a cable that is stretched between the main supports 20 in the circumferential direction of the unfolding type reflector 100, a winder that drives the cable out by a motor, and an operation of the winder. And a control unit that performs control.
  • the deployment control mechanism gradually extends the cable, so that the deployable reflector 100 gradually deploys according to the urging force of each urging portion 150.
  • the V-shaped opening angles of the leaf springs 151 are spread evenly, so that the sub-supports 30 unfold in parallel.
  • the deployable reflector 100 may include a latch mechanism for maintaining the deployable reflector 100 in the deployed state when the deploying operation is completed.
  • the latch mechanism locks the drive support 20a and the fixed support 20b to maintain the deployable reflector 100 in the deployed state.
  • FIG. 19 to FIG. 20B show an example in which the urging portion 150 is disposed at the central portion in the radial direction of the deployable reflector 100. More specifically, for example, as shown in FIG. 20 (b), the erection part 153 is preferably disposed at a position closer to the center than the plate-like part 21 in the radial direction of the deployable reflector 100. By disposing the urging portion 150 at the central portion in the radial direction of the deployable reflector 100, the size of the leaf spring 151 can be further reduced.
  • the arrangement of the urging portion 150 in the radial direction of the deployable reflector 100 is not particularly limited.
  • the urging portion 150 may be disposed at an intermediate portion in the radial direction of the deployable reflector 100. Further, the urging portion 150 may be disposed on an outer portion in the radial direction of the deployable reflector 100 (a peripheral edge portion of the deployable reflector 100). That is, the urging portion 150 may be provided at the distal end portion of the main support 20 with the reference shaft 11 as the base end. As the urging portion 150 is arranged at a position closer to the peripheral portion of the deployable reflector 100, the size of the leaf spring 151 becomes larger, but the displacement of the main supports 20 in the axial direction of the reference shaft 11 is urged. The effect of regulating by the portion 150 is enhanced.
  • the positions of the plurality of urging portions 150 may be equal to each other, or the urging portions 150 arranged at different positions such as different from each other may be provided. May be present. Further, the urging portions 150 may be provided at a plurality of locations in the radial direction of the deployable reflector 100 between the main supports 20 adjacent to each other.
  • an urging unit 150 may be provided on the upper portion of the main support 20 like an urging unit 150 indicated by a solid line in FIG. 20B, or a two-dot chain line in FIG. Like the urging portion 150 shown, the urging portion 150 may be provided in the lower portion of the main support 20. Moreover, the urging
  • the sub-support 30 is provided on the upper portion (the portion on the support surface 13 side) of the main support 20 (see FIGS. 4 and 7). For this reason, when the urging portion 150 is disposed in the intermediate portion or the outer portion (peripheral portion of the deployable reflector 100) in the radial direction of the deployable reflector 100, interference between the urging portion 150 and the sub support 30 is prevented. In order to avoid this, it is preferable to provide the urging portion 150 below the main support 20.
  • Modification 4 of the deployment mechanism of the deployable reflector will be described with reference to FIGS. 21 (a) and 21 (b). 21A and 21B, the sub support 30 and the reflector unit 50 are not shown.
  • the shape of each leaf spring 151 when viewed in the axial direction of the reference shaft 11 is bent into a convex shape toward the radially outer side of the deployable reflector 100.
  • the deployable reflector 100 according to the present modification is otherwise configured in the same manner as the deployable reflector 100 according to the modification shown in FIGS. 19 to 20B. In the case of this modification, the same effect as that of Modification 3 of the deployment mechanism can be obtained.
  • the direction of bending of the leaf spring 151 is not limited to the direction of the third and fourth modifications, and may be convex downward, convex upward, or convex in other directions.
  • modified example 5 of the deployment mechanism of the deployable reflector will be described with reference to FIG. In FIG. 22A, illustration of the sub-support 30 and the reflector unit 50 is omitted.
  • the deployable reflector 100 according to the present modified example is different from the deployable reflector 100 according to the modified example shown in FIGS. 19 to 20B in the points described below, and from other points in FIG.
  • the configuration is the same as that of the deployable reflector 100 according to the modification shown in FIG.
  • the urging unit 150 includes a block unit 155 and two leaf springs 151.
  • the block portion 155 is a block shape having a trapezoidal shape or a sector shape when viewed in the axial direction of the reference shaft 11.
  • the material of the block part 155 is not specifically limited, For example, it can be set as a carbon fiber reinforced plastic.
  • the block portion 155 is arranged in such a direction that the dimension of the block portion 155 increases in the circumferential direction of the deployable reflector 100 toward the radially outer side of the deployable reflector 100.
  • each leaf spring 151 is a flat plate in a normal state where no external force is applied to the leaf spring 151.
  • each leaf spring 151 projects outward in the radial direction of the deployable reflector 100 with the block portion 155 as a reference.
  • the other surface of each leaf spring 151 is fixed to one plate-like portion 21 of the adjacent main supports 20 by surface bonding.
  • each leaf spring 151 in the retracted state of the deployable reflector 100, as shown by the two-dot chain line in FIG. It is bent against. That is, in each leaf spring 151, each leaf spring 151 is bent in a direction in which the portions protruding radially outward of the deployable reflector 100 from the block portion 155 approach each other, and each leaf spring 151 is a spring. It is in a state where power is stored.
  • the unfoldable reflector 100 is unfolded, the unfoldable reflector 100 is unfolded by a spring force that causes each leaf spring 151 to return to a flat plate state.
  • FIG.22 (b) illustration is abbreviate
  • FIG. The deployable reflector 100 according to the present modified example is different from the deployable reflector 100 according to the modified example shown in FIGS. 19 to 20B in the points described below, and from other points in FIG.
  • the configuration is the same as that of the deployable reflector 100 according to the modification shown in FIG.
  • the urging portion 150 includes a pair of leaf springs 151 in which one end portions 156 are fixed to each other by surface bonding.
  • the other end of each of the pair of leaf springs 151 is a fixed portion 152 that is fixed to one of the main supports 20 adjacent to each other.
  • the fixing portion 152 is fixed to the plate-like portion 21 of the main support 20 by surface bonding.
  • Each of the pair of leaf springs 151 is formed in an arcuate shape so that the distance between the pair of leaf springs 151 increases toward the other end (fixed portion 152 side) in a natural state where no external force is applied. Yes.
  • the portions other than the one end 156 of the pair of leaf springs 151 are in proximity to or in surface contact with each other. For this reason, in the storage state of the deployable reflector 100, the deployable reflector 100 can be made more compact.
  • the support element aggregate 310 is shared by the adjacent sub-supports 30
  • the support elements 31 constituting the individual sub-supports 30 may be completely separated from each other. That is, the support element 31a and the support element 31b may be separate from each other.
  • the end part 34 of each support element 31 is attached to the plate-like part 21 of the main support 20 so as to be swingable, for example.
  • the edge part 34 of each support element 31 may be connected with respect to the plate-shaped part 21 via the hinge mechanism which is not shown in figure.
  • the main support 20 is a thin plate
  • the main support 20 may be a frame (such as a frame having a truss structure).
  • the main support 20 is formed in a plane shape parallel to the reference axis 11 has been described.
  • the main support 20 may be a rod-shaped one.
  • the support element 31 is a thin plate has been described.
  • the support element 31 may be a frame (such as a frame having a truss structure).
  • This embodiment includes the following technical ideas.
  • the support structure is A plurality of main supports elongated in a radial direction around the reference axis; A sub-support that is laid between adjacent main supports; It is composed including At least one of the plurality of main supports is pivotally supported by the reference shaft, and an angle between the adjacent main support can be opened and closed around the reference shaft as an axis, When the angle between the main support that is pivotally supported by the reference shaft and the main support adjacent to the main support is widened, the sub support is installed between the main supports.
  • the support is developed in a circumferential direction centered on the reference axis to form a lattice structure that defines a plurality of facets,
  • An unfoldable reflector in which the support surface is formed by the plurality of main supports and the sub-support provided between the main supports in the unfolded state.
  • the sub-support is configured to include a plurality of support elements that form the lattice structure, Each of the said support elements is a expandable reflector as described in any one of (1) to (3) currently formed in the planar shape parallel to the said reference axis.
  • the deployable reflector according to (4) wherein the bending rigidity of the main support is greater than the bending rigidity of the support element.
  • the plurality of support elements intersect in a lattice pattern, and the intersection of the support elements is a swinging portion that allows the support elements to swing relative to each other (4) or The expandable reflector according to (5).
  • each of the plurality of support elements is formed in a thin plate shape.
  • Each of the plurality of support elements is formed in a thin plate shape, The support elements intersecting each other are engaged with each other by inserting the other into slits formed at corresponding positions, and this engagement position is the swinging portion (6).
  • the deployable reflector as described.
  • each of the plurality of support elements on the one surface side of the support structure portion are linear first support portions that can support the reflector portion (4) to (9).
  • Each edge of the plurality of main supports on the one surface side of the support structure portion is a linear second support portion capable of supporting the reflector portion (1) to (10 )
  • the deployable reflector according to (12), wherein a majority of the plurality of facets is a rhombus elongated in the radial direction.
  • the number of the main supports supported by the reference shaft is two or more, At least one of the main supports pivotally supported by the reference shaft is a drive support that is rotationally driven;
  • the unfoldable reflector further includes a rotational power applying mechanism (1) to (13) that causes the support structure to be unfolded by rotating the drive support in the circumferential direction around the reference axis as a rotation center.
  • the main supports adjacent to each other are connected to each other, and are provided with biasing portions that elastically bias the main supports in a direction to separate them from each other (1) to (13).
  • the expandable reflector according to any one of the above.
  • a reference axis It is configured to be deployable with reference to the reference axis, and a support structure portion that forms a concave support surface on one surface side in the expanded state;
  • a deployable structure for a deployable reflector that supports a reflector portion forming a reflector surface of a deployable reflector by the support surface
  • the support structure is A plurality of main supports elongated in a radial direction around the reference axis; A sub-support that is laid between adjacent main supports; It is composed including At least one of the plurality of main supports is pivotally supported by the reference shaft, and an angle between the adjacent main support can be opened and closed around the reference shaft as an axis, When the angle between the main support that is pivotally supported by the reference shaft and the main support adjacent to the main support is widened, the sub support is installed between the main supports.
  • the support is developed in a circumferential direction centered on the reference axis to form a lattice structure that defines a plurality of facets,
  • a deployable structure for a deployable reflector in which the support surface is formed by the plurality of main supports and the sub-support provided between the main supports in the unfolded state.
  • Reference shaft 12 Support structure 13 Support surface 15 Unit module 20 Main support 20a Drive support 20b Fixed support 20c Driven support 21 Plate-like portion 21a Upper edge (second support) 21b Lower edge 21c Slit 22 First extending portion 23 Second extending portion 24 Third extending portion 25 First support arm 25a Insertion hole 25b Tip portion 26 Second support arm 26a Insertion hole 26b Tip portion 30 Sub support 31 Support element 31a Support element 31b Support element 310 Support element assembly 32 Intersection 33 Slit 34 End 35 Upper edge (first support) 36 Lower edge 37 Facet 38 Joint part 39 Bent part 42 Lower fixing member 43 Upper fixing member 50 Reflector part 51 Metal wire 52 Outline line 61 Boom 70 Rotating power application mechanism 71 Motor 72 Drive transmission mechanism 80 Deployable structure for deployable reflector 91 Adhesive Tape 92 Adhesive 100 Deployable Reflector 111 Support Element 112 Support Element 121 Relative Rotating Member 122 Connection Hinge 123 Cable 124 Cable Winding Mechanism 125 Motor 131 Elastic Hinge 134 Latch

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  • Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Engineering & Computer Science (AREA)
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  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
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  • Aerials With Secondary Devices (AREA)

Abstract

Un réflecteur expansible (100) comprend : une section de structure de support (12) pour former une surface de support concave dans un état expansé ; et une section de réflecteur qui est supportée sur la surface de support et qui forme une surface de réflecteur. La section de structure de support (12) comprend : une pluralité de corps de support principaux (20) qui sont allongés le long de directions de rayonnement à partir d'un axe de référence (11) au centre ; et un corps de sous-support (30) qui est construit entre des corps de support principaux voisins (20). Au moins l'un de la pluralité de corps de support principaux (20) est supporté de manière pivotante sur l'axe de référence (11), et l'angle par rapport à un corps de support principal voisin (20) peut être augmenté et diminué autour de l'axe de référence 11 servant de centre axial. En conséquence de l'angle entre le corps de support principal (20) supporté de manière pivotante par l'axe de référence (11) et le corps de support principal voisin (20) qui est augmenté, le corps de sous-support (30) se déploie dans une direction circonférentielle de façon à établir une structure réticulaire pour définir une pluralité de facettes (37). Dans un état expansé, la surface de support est formée par la pluralité de corps de support principaux (20) et le corps de sous-support (30).
PCT/JP2019/014833 2018-05-01 2019-04-03 Réflecteur expansible et structure d'expansion pour réflecteur expansible WO2019211964A1 (fr)

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JP2018239922A JP7179290B2 (ja) 2018-05-01 2018-12-21 展開式リフレクタ及び展開式リフレクタ用展開構造物

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Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60113503A (ja) * 1983-11-24 1985-06-20 Nippon Telegr & Teleph Corp <Ntt> 展開形アンテナ
JPH01252007A (ja) * 1988-03-31 1989-10-06 Nec Eng Ltd 組立型パラボラアンテナ
JPH02133300A (ja) * 1988-11-15 1990-05-22 Toshiba Corp 伸展構造物、及びこれを用いたアンテナと展開型太陽電池
JPH10200329A (ja) * 1997-01-14 1998-07-31 Nippon Telegr & Teleph Corp <Ntt> 球面近似骨組み構造
JPH11112228A (ja) * 1997-09-29 1999-04-23 Nippon Telegr & Teleph Corp <Ntt> 展開アンテナ
JP2001036334A (ja) * 1999-06-18 2001-02-09 Trw Inc 反射性メッシュのパッキング方法、懸垂線装置及び周辺トラス反射鏡の配置補助装置
JP2002220096A (ja) * 2001-01-29 2002-08-06 Natl Space Development Agency Of Japan 収納・展開型枠組み構造物
US20060102796A1 (en) * 2004-10-20 2006-05-18 Clark Paul R Folding retractable protective dome for space vehicle equipment
JP2008100652A (ja) * 2006-10-20 2008-05-01 Japan Aerospace Exploration Agency 可動ヒンジ
JP2014171091A (ja) * 2013-03-04 2014-09-18 Nec Corp 折りたたみ式反射器

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS60113503A (ja) * 1983-11-24 1985-06-20 Nippon Telegr & Teleph Corp <Ntt> 展開形アンテナ
JPH01252007A (ja) * 1988-03-31 1989-10-06 Nec Eng Ltd 組立型パラボラアンテナ
JPH02133300A (ja) * 1988-11-15 1990-05-22 Toshiba Corp 伸展構造物、及びこれを用いたアンテナと展開型太陽電池
JPH10200329A (ja) * 1997-01-14 1998-07-31 Nippon Telegr & Teleph Corp <Ntt> 球面近似骨組み構造
JPH11112228A (ja) * 1997-09-29 1999-04-23 Nippon Telegr & Teleph Corp <Ntt> 展開アンテナ
JP2001036334A (ja) * 1999-06-18 2001-02-09 Trw Inc 反射性メッシュのパッキング方法、懸垂線装置及び周辺トラス反射鏡の配置補助装置
JP2002220096A (ja) * 2001-01-29 2002-08-06 Natl Space Development Agency Of Japan 収納・展開型枠組み構造物
US20060102796A1 (en) * 2004-10-20 2006-05-18 Clark Paul R Folding retractable protective dome for space vehicle equipment
JP2008100652A (ja) * 2006-10-20 2008-05-01 Japan Aerospace Exploration Agency 可動ヒンジ
JP2014171091A (ja) * 2013-03-04 2014-09-18 Nec Corp 折りたたみ式反射器

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