A combined deployable structure of cable net antenna and solar panels for spacecraft

Abstract

The present application discloses a combined deployable structure of a cable net antenna and a solar panel for a spacecraft, and relates to the field of spacecraft technology. By integrating the solar panel and the cable net antenna of the spacecraft into an integral component, the carrying space of the rocket is saved. The combined deployable structure includes a retractable polygonal cylindrical truss structure, a double-layer cable net component, a foldable solar panel and a metal reflector surface of the spacecraft antenna; the retractable polygonal cylindrical truss structure can form a polygonal cylinder after being deployed; the double-layer cable net component is arranged in the retractable polygonal cylindrical truss structure; the foldable solar panel is connected to the upper layer of the double-layer cable net component, and the metal reflector surface of the spacecraft antenna is connected to the lower layer of the double-layer cable net component; the retractable polygonal cylindrical truss structure can drive the foldable solar panel and the metal reflector surface of the spacecraft antenna to converge or unfold. The present application is used to improve the performance of solar panels.

Description

Technical Field

[0001] The present application relates to the field of spacecraft technology, and in particular to a combined deployable structure of a cable net antenna and a solar panel for a spacecraft. Background Art

[0002] Solar energy is a key source of energy for spacecraft, and solar panels are essential components. Because solar panels require a large area, they are kept in a retracted position until the spacecraft reaches its intended orbit, significantly reducing the space required for transportation. Existing solar panels are typically folded in a zigzag, accordion, or fan-shaped configurations. With the continuous advancement of aerospace technology, spacecraft energy demands are increasing, and with them, the need for larger solar panels is also growing. However, rocket payloads are limited. Therefore, finding ways to accommodate larger solar panels within the available space has become a key research topic in the aerospace field. Summary of the Invention

[0003] An embodiment of the present application provides a combined deployable structure of a cable net antenna and a solar panel for a spacecraft, which saves the carrying space of the rocket by integrating the solar panel and the cable net antenna of the spacecraft into an integral component.

[0004] To achieve the above-mentioned purpose, an embodiment of the present application provides a combined expandable structure of a cable net antenna and a solar panel for a spacecraft, comprising a retractable polygonal cylindrical truss structure, a double-layer cable net assembly, a foldable solar panel and a metal reflective surface for a spacecraft antenna; the retractable polygonal cylindrical truss structure can form a polygonal cylinder after being unfolded; the double-layer cable net assembly is arranged in the retractable polygonal cylindrical truss structure; the foldable solar panel is connected to the upper layer of the double-layer cable net assembly, and the metal reflective surface of the spacecraft antenna is connected to the lower layer of the double-layer cable net assembly; the retractable polygonal cylindrical truss structure can drive the foldable solar panel and the metal reflective surface of the spacecraft antenna to converge or unfold.

[0005] Furthermore, the double-layer cable net assembly includes an upper cable net and a lower cable net; a plurality of vertical cables are provided between the upper cable net and the lower cable net; the vertical cables and the upper cable net and the lower cable net are connected via cable segment connectors.

[0006] Furthermore, after the double-layer cable net group is unfolded, the upper cable net and the lower cable net both present an inwardly concave arc surface.

[0007] Furthermore, the foldable solar panel is bonded to the upper surface of the upper cable net; and the metal reflective surface of the spacecraft antenna is bonded to the lower surface of the lower cable net.

[0008] Furthermore, the retractable polygonal cylindrical truss structure includes a plurality of truss units evenly distributed along the circumference; the truss unit includes a first column assembly and a second column assembly; the upper end of one side of the first column assembly is connected to the upper end of the second column assembly through a first connecting rod; and is connected to the lower end of the second column assembly through a first telescopic rod; the lower end of one side of the first column assembly is connected to the lower end of the second column assembly through a second connecting rod; the first column assembly is hinged to the first connecting rod, the second connecting rod and the first telescopic rod; the second column assembly is also hinged to the first connecting rod, the second connecting rod and the first telescopic rod; the upper end of the other side of the first column assembly is respectively hinged to the first end of the third connecting rod and the first end of the second telescopic rod; one side of the lower end of the first column assembly is hinged to the first end of the fourth connecting rod; the second end of the third connecting rod is used to hinge to the upper end of the adjacent second column assembly; the second end of the second telescopic rod and the second end of the fourth connecting rod are both used to hinge to the lower end of the adjacent second column assembly.

[0009] Furthermore, the first column assembly includes a first upper hinge block, a first lower hinge block and a first column fixedly connected between the first upper hinge block and the first lower hinge block; the second column assembly includes a second upper hinge block, a second lower hinge block and a second column fixedly connected between the second upper hinge block and the second lower hinge block; the first upper hinge block and the second lower hinge block have the same structure; the first lower hinge block and the second upper hinge block have the same structure; the first column and the second column have the same structure.

[0010] Furthermore, the first telescopic rod is an elastic telescopic rod; and the second telescopic rod has the same structure as the first telescopic rod.

[0011] Furthermore, the foldable solar panel includes a backing film and a plurality of solar panel sections fixed to the upper surface of the backing film; the backing film is adhered to the upper cable net; and there are gaps between adjacent solar panel sections.

[0012] Furthermore, the foldable solar panel is folded in a square twist manner.

[0013] Compared with the prior art, this application has the following beneficial effects:

[0014] 1. The embodiment of the present application is a combined deployable structure of a cable net antenna and a solar panel for a spacecraft. By installing the solar panel at one end of a retractable polygonal cylindrical truss structure and installing the metal reflective surface of the spacecraft antenna at the other end of the retractable polygonal cylindrical truss structure, the two separate devices are integrated into an integral component. In this way, the spacecraft will remain in a compact state before entering the predetermined working orbit in space, and will expand into a combined ring structure of polygonal columns when entering the predetermined working orbit in space. In this way, the utilization rate of the carrying space of the spacecraft during the transportation phase can be improved.

[0015] 2. The foldable solar panel in the combined deployable structure of the cable net antenna and solar panel used for the spacecraft in the embodiment of the present application includes a backing film and a plurality of solar panel segments fixed to the upper surface of the backing film, and the folding method of the foldable solar panel is a square twist, so that the height of the solar panel in the folded state does not limit the diameter of the concave arc surface when unfolded. While increasing the number of layers to increase the unfolded diameter, the diameter in the collapsed state is increased to a minimum, thereby saving carrying space. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0017] Figure 1 This is a schematic structural diagram of a deployable structure of a combined cable net antenna and solar panels for a spacecraft according to an embodiment of the present application;

[0018] Figure 2 This is a schematic diagram of the structure of the truss unit in the deployable structure of the combined cable net antenna and solar panel for spacecraft according to the embodiment of the present application.

[0019] Figure 3 This is a schematic structural diagram of a double-layer cable net assembly in a deployable structure of a combined cable net antenna and solar panels for a spacecraft according to an embodiment of the present application;

[0020] Figure 4 This is a schematic structural diagram of a cable segment connector in a deployable structure of a combined cable net antenna and solar panels for a spacecraft according to an embodiment of the present application;

[0021] Figure 5 This is a schematic structural diagram of a foldable solar panel in a deployable structure combining a cable net antenna and a solar panel for a spacecraft according to an embodiment of the present application;

[0022] Figure 6A flattened diagram of a foldable solar panel in a deployable structure combining a cable net antenna and a solar panel for a spacecraft according to an embodiment of the present application;

[0023] Figure 7 The embodiment of the present application is used for the simplified flattening of the foldable solar panels in the deployable structure of the combined cable net antenna and solar panels of the spacecraft. Figure 1 ;

[0024] Figure 8 The embodiment of the present application is used for the simplified flattening of the foldable solar panels in the deployable structure of the combined cable net antenna and solar panels of the spacecraft. Figure 2 ;

[0025] Figure 9 This is a semi-expanded view of a foldable solar panel in a deployable structure combining a cable net antenna and a solar panel for a spacecraft according to an embodiment of the present application. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0027] In the description of this application, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0028] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "install", "connect", and "connect" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0029] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. Throughout this application, unless otherwise specified, "plurality" means two or more.

[0030] Reference Figure 1 An embodiment of the present application provides a combined deployable structure of a cable net antenna and solar panel for a spacecraft, comprising a retractable polygonal cylindrical truss structure 1, a double-layer cable net assembly 2, a foldable solar panel 3, and a metal reflector 4 for a spacecraft antenna. The retractable polygonal cylindrical truss structure 1 presents a polygonal cylindrical structure after deployment. The double-layer cable net assembly 2 is connected within the retractable polygonal cylindrical truss structure 1, the foldable solar panel 3 is connected to the upper layer of the double-layer cable net assembly 2, and the metal reflector 4 for a spacecraft antenna is connected to the lower layer of the double-layer cable net assembly 2. The retractable polygonal cylindrical truss structure 1 can drive the foldable solar panel 3 and the metal reflector 4 for a spacecraft antenna to converge or deploy.

[0031] Reference Figure 2 The collapsible polygonal cylindrical truss structure 1 includes a plurality of truss units 11 uniformly distributed along the circumference. Each truss unit 11 includes a first column assembly 12, a second column assembly 13, a first connecting rod 14, a second connecting rod 15, a third connecting rod 16, a fourth connecting rod 17, a first telescopic rod 18, and a second telescopic rod 19.

[0032] Specifically, the first column assembly 12 includes a first upper hinge block 121, a first lower hinge block 122, and a first column 123 fixedly connected between the first upper hinge block 121 and the first lower hinge block 122. The second column assembly 13 includes a second upper hinge block 131, a second lower hinge block 132, and a second column 133 fixedly connected between the second upper hinge block 131 and the second lower hinge block 132. The first upper hinge block 121 and the second lower hinge block 132 have the same structure, the first lower hinge block 122 and the second upper hinge block 131 have the same structure, and the first column 123 and the second column 133 have the same structure. In other words, the second column assembly 13 is equivalent to an inverted first column assembly 12.

[0033] The first upper hinge block 121 is hinged to the left and right sides of its upper end, respectively, and the first telescopic rod 18 and the second telescopic rod 19 are hinged to the left and right sides of its lower end, respectively. The second connecting rod 15 and the fourth connecting rod 17 are hinged to the left and right sides of the first lower hinge block 122, respectively. The first connecting rod 14 and the third connecting rod 16 are symmetrically arranged relative to the centerline of the first upright 123; the first telescopic rod 18 and the second telescopic rod 19 are also symmetrically arranged relative to the centerline of the first upright 123; and the second connecting rod 15 and the fourth connecting rod 17 are also symmetrically arranged relative to the centerline of the first upright 123.

[0034] The left end of the first connecting rod 14 is hinged to the second upper hinge block 131 of the left second column assembly 13. The left end of the first telescopic rod 18 and the left end of the second connecting rod 15 are both hinged to the second lower hinge block 132 of the left second column assembly 13. The right end of the third connecting rod 16 is hinged to the second upper hinge block 131 of the right second column assembly 13. The right ends of the second telescopic rod 19 and the right ends of the fourth connecting rod 17 are both hinged to the second lower hinge block 132 of the right second column assembly 13.

[0035] The first telescopic rod 18 and the second telescopic rod 19 are both elastic telescopic rods that can be freely retracted and have the same structure. It should be noted that the elastic telescopic rod is automatically retracted by pulling the inner rod of the telescopic rod by a spring. Since it is a prior art, the specific structure is no longer described in detail here.

[0036] Reference Figure 3 and Figure 4 The double-layer cable net assembly 2 includes an upper cable net 21 and a lower cable net 22. The upper and lower cable nets 21 and 22 are connected by multiple vertical cables 23 of varying lengths. Specifically, the vertical cables 23 are connected to both the upper and lower cable nets 21 and 22 via cable segment connectors 24. The cable segment connectors 24 are arranged at the center of the central hexagon of the first layer of the cable net, at the centers of the adjacent hexagons of the second layer, and so on.

[0037] Cable segment connectors 24 are also provided on the outer periphery of the upper and lower cable nets 21 and 22. These connectors connect the upper and lower cable nets 21 and 22 to the collapsible polygonal cylindrical truss structure 1. When the double-layer cable net assembly 2 is deployed, the pull of vertical cables 33 of varying lengths causes both the upper and lower cable nets 21 and 22 to assume an inwardly concave arc. The foldable solar panel 3 is bonded to the upper surface of the upper cable net 21, and the metal reflector 4 for the spacecraft antenna is bonded to the lower surface of the lower cable net 22. Consequently, the upper and lower cable nets 31 and 32, respectively, tension the foldable solar panel assembly 3 and the metal reflector 4 for the spacecraft antenna, forming inwardly concave arcs.

[0038] Reference Figure 5 and Figure 6 The foldable solar panel 3 includes a backing film 31 and a plurality of solar panel segments 32 secured to the upper surface of the backing film 31. The backing film 31 is bonded to the upper surface of the upper cable net 21, with gaps between adjacent solar panel segments 32, the gap width being approximately 10 to 14 times the segment thickness. Materials for the backing film 31 include, but are not limited to, PI film and Kapton film. The foldable solar panel 3 is folded using a square twist technique. Since this foldable solar panel 3 is conventional, only a brief description will be provided below.

[0039] Reference Figures 7 to 9The foldable solar panel 3 has a layered, wound, folded structure, with n layers. The innermost layer is the first layer, i.e., n = 1, and the number of layers extending outward is similar. For ease of notation, the first layer is designated A1, the second layer is designated A2, the third layer is designated A3, and so on. Except for the first layer, the configuration diagram of each layer consists of a fold vertex 321, a diagonal fold line 322, an extension of the central figure edge 323, an axial bend line 324, and an extension of the quasi-central figure edge 325. Line names and numbers do not correspond to specific layers; rather, corresponding points and lines in each layer are assigned corresponding names. The configuration diagram of the first layer consists of folding vertices 321, diagonal folding lines 322, extension lines 323 of the center figure edges, and axial bending lines 324. The configuration diagram of the second layer A1 consists of the folding vertices 321, diagonal folding lines 322, extension lines 323 of the center figure edges, axial bending lines 324 and extension lines 325 of the quasi-center figure edges of its corresponding layer; the diagonal folding lines 322, extension lines 323 of the center figure edges, axial bending lines 324 and extension lines 325 of the quasi-center figure edges are all folding lines. The folding vertex 321 is the starting point of the new layer, and is also the top (bottom) point on the diagonal fold line within the layer when folded; the diagonal fold line 322 is a line segment passing through the central polygon vertex and the folding vertex 321, and extends outward from the inside to the outside as the number of layers increases; the extension line of the center pattern edge is the extension line of the area corresponding to the edge of the center pattern, and extends outward from the inside to the outside as the number of layers increases; the extension line 325 of the quasi-center pattern edge is the line segment drawn from the folding vertex 321 starting from the second layer. Line segments forming acute angles with the diagonal fold lines 322 extend continuously outward from the inside out as the number of layers increases. Axial bending lines 324 are all line segments in the configuration diagram that are perpendicular to the extension lines 323 of the central figure edge and the extension lines 325 of the quasi-central figure edge. The axial bending lines between each layer from the inside out are the first axial bending line 324-1, the second axial bending line 324-2, and so on. There is no specific requirement for the number of axial bending lines between layers and can be adjusted according to the size of the solar panel.

[0040] The line types of the diagonal fold line 322, the extension line 323 of the center figure edge, the axial bending line 324, and the extension line 325 of the quasi-center figure edge are all composed of peak lines and valley lines. The peak line indicates that the fold is convex out of the surface, and the valley line indicates that the fold is concave into the surface along the fold. The diagonal fold line 322, from the inner layer to the outer layer, has a line type that alternates between peak lines and valley lines, and the line type changes every time it passes a fold vertex. It is a peak line when the number of layers is odd, and a valley line when the number of layers is even. The extension line 323 of the center figure edge, from the inner layer to the outer layer, is a valley line. The line type of the extension line 325 of the quasi-center figure edge is opposite to the line type of the diagonal fold line 322 in the layer, that is, it is a valley line when the number of layers is odd, and a peak line when the number of layers is even.

[0041] It should be noted that the number of folding layers of the foldable solar panel assembly 3 is actually adjusted according to the size of each solar panel segment 32 and the antenna aperture, and there is no specific number limit.

[0042] The working principle of the deployable structure of a combined cable net antenna and solar panels for a spacecraft according to the embodiment of the present application is as follows:

[0043] Before the spacecraft enters the predetermined working orbit in space, the embodiment of the present application is in a converged state. At this time, the first telescopic rod 18 and the second telescopic rod 19 in the retractable polygonal cylindrical truss structure 1 are forcibly extended. Figure 2 In the state shown, the first column assembly 12 moves upward, and at the same time, the second column assembly 13 moves downward and moves closer to the first column assembly 12, the first connecting rod 14, the second connecting rod 15, the third connecting rod 16 and the fourth connecting rod 17 rotate around the corresponding hinge points respectively, and the retractable polygonal cylindrical truss structure 1 drives the foldable solar panel 3 and the metal reflective surface 4 of the spacecraft antenna to be in a retracted state. The outer periphery of the retractable polygonal cylindrical truss structure 1 is bound by straps, and the two ends of the straps are connected by explosive bolts.

[0044] When the spacecraft enters the predetermined working orbit in space, a signal is sent to the explosive bolt, and the explosive bolt explodes. The first telescopic rod 18 and the second telescopic rod 19 in the retractable polygonal cylindrical truss structure 1 are automatically retracted, and at the same time, the first column assembly 12 and the second column assembly 13 are driven downward. The first connecting rod 14, the second connecting rod 15, the third connecting rod 16 and the fourth connecting rod 17 respectively rotate around the corresponding hinge points, and the retractable polygonal cylindrical truss structure 1 drives the foldable solar panel 3 and the metal reflective surface 4 of the spacecraft antenna to unfold.

[0045] The above are only specific embodiments of the present application, but the scope of protection of the present application is not limited thereto. Any changes or replacements within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A deployable structure combining a cable net antenna and a solar panel for a spacecraft, characterized in that: It includes a retractable polygonal cylindrical truss structure, a double-layer cable net component, a foldable solar panel and a metal reflective surface for a spacecraft antenna; the retractable polygonal cylindrical truss structure can form a polygonal cylinder after being unfolded; The double-layer cable net assembly is arranged in the retractable polygonal cylindrical truss structure; the foldable solar panel is connected to the upper layer of the double-layer cable net assembly, and the metal reflector surface of the spacecraft antenna is connected to the lower layer of the double-layer cable net assembly; the retractable polygonal cylindrical truss structure can drive the foldable solar panel and the metal reflector surface of the spacecraft antenna to converge or unfold; the retractable polygonal cylindrical truss structure includes a plurality of truss units evenly distributed along the circumference; the truss unit includes a first column assembly and a second column assembly; the upper end of one side of the first column assembly is connected to the upper end of the second column assembly through a first connecting rod; and is connected to the lower end of the second column assembly through a first telescopic rod; the upper end of the other side of the first column assembly is respectively hinged to the first end of the third connecting rod and the first end of the second telescopic rod; the first telescopic rod is an elastic telescopic rod; the second telescopic rod has the same structure as the first telescopic rod; the folding method of the foldable solar panel is square twist.

2. The combined deployable structure of cable net antenna and solar panel for spacecraft according to claim 1, characterized in that: The double-layer cable net assembly includes an upper cable net and a lower cable net; a plurality of vertical cables are arranged between the upper cable net and the lower cable net; the vertical cables and the upper cable net and the lower cable net are connected via cable segment connectors.

3. The combined deployable structure of cable net antenna and solar panel for spacecraft according to claim 2, characterized in that: After the double-layer cable net group is unfolded, the upper cable net and the lower cable net both present an inwardly concave arc surface.

4. The combined deployable structure of cable net antenna and solar panel for spacecraft according to claim 2, characterized in that: The foldable solar panel is adhered to the upper surface of the upper cable net; the metal reflective surface of the spacecraft antenna is adhered to the lower surface of the lower cable net.

5. The combined deployable structure of cable net antenna and solar panel for spacecraft according to claim 1, characterized in that: The lower end of one side of the first column assembly is connected to the lower end of the second column assembly via a second connecting rod; the first column assembly is hinged to the first connecting rod, the second connecting rod and the first telescopic rod; the second column assembly is also hinged to the first connecting rod, the second connecting rod and the first telescopic rod; One side of the lower end of the first column assembly is hinged to the first end of the fourth connecting rod; the second end of the third connecting rod is used to hinge the upper end of the adjacent second column assembly; the second end of the second telescopic rod and the second end of the fourth connecting rod are both used to hinge the lower end of the adjacent second column assembly.

6. The combined deployable structure of cable net antenna and solar panel for spacecraft according to claim 5, characterized in that: The first column assembly includes a first upper hinge block, a first lower hinge block and a first column fixedly connected between the first upper hinge block and the first lower hinge block; the second column assembly includes a second upper hinge block, a second lower hinge block and a second column fixedly connected between the second upper hinge block and the second lower hinge block; the first upper hinge block and the second lower hinge block have the same structure; the first lower hinge block and the second upper hinge block have the same structure; the first column and the second column have the same structure.

7. The combined deployable structure of cable net antenna and solar panel for spacecraft according to claim 2, characterized in that: The foldable solar panel comprises a backing film and a plurality of solar panel sections fixed on the upper surface of the backing film; the backing film is adhered to the upper cable net; and gaps are provided between adjacent solar panel sections.

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