Space deployable unit, planar deployable antenna support truss and spacecraft

Abstract

The present invention discloses a space deployable unit, a planar deployable antenna support truss, and a spacecraft. The space deployable unit includes: a first connecting member and a second connecting member; a lower eight-joint assembly; an upper eight-joint assembly. The space deployable unit has a deployed state and a folded state. When the space deployable unit is in the deployed state, the distance between the first connecting member and the second connecting member is greater than the distance between the first connecting member and the second connecting member when the space deployable unit is in the folded state. The space deployable unit according to the embodiments of the present invention has advantages such as strong load-bearing capacity and high reliability.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology. Specifically, it relates to a space deployable unit, a planar deployable antenna support truss having the space deployable unit, and a spacecraft having the planar deployable antenna support truss. Background Art

[0002] In the aerospace field, spacecraft such as satellites and space stations need to obtain energy, conduct communications, and perform diverse tasks. With the increase in mission complexity, the areas required for solar panels, communication antennas, and various mission payloads represented by synthetic aperture radar are also increasing. However, these devices need to be sent into space by launch vehicles or space shuttles, and there is a prominent contradiction between the small launch space of the launch vehicle and the large areas required by these devices. The deployable mechanism has the advantages of a small storage space and a large deployable area, and is an effective way to solve this problem. The deployable mechanism requires a support truss for support.

[0003] For the spacecraft in the related art, the bearing capacity of its support truss is poor. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention provides a space deployable unit, which has advantages such as strong bearing capacity and high reliability.

[0005] The present invention also provides a planar deployable antenna support truss having the space deployable unit.

[0006] The present invention also provides a spacecraft having the planar deployable antenna support truss.

[0007] To achieve the above object, an embodiment of the first aspect of the present invention provides a space deployable unit, which includes: a first connecting member and a second connecting member; a lower eight-joint assembly, which includes a first inner link of the lower assembly, a first outer link of the lower assembly, a middle connecting member of the lower assembly, a second inner link of the lower assembly and a second outer link of the lower assembly. One end of the first inner link of the lower assembly is pivotally connected to the first connecting member and the other end is pivotally connected to the middle connecting member of the lower assembly. One end of the first outer link of the lower assembly is pivotally connected to the first connecting member and the other end is pivotally connected to the middle connecting member of the lower assembly. One end of the second inner link of the lower assembly is pivotally connected to the second connecting member and the other end is pivotally connected to the middle connecting member of the lower assembly. One end of the second outer link of the lower assembly is pivotally connected to the second connecting member and the other end is pivotally connected to the middle connecting member of the lower assembly. The first inner link of the lower assembly, the first outer link of the lower assembly, the middle connecting member of the lower assembly and the first connecting member form a parallelogram mechanism and the first inner link of the lower assembly is parallel to the first outer link of the lower assembly. The second inner link of the lower assembly, the second outer link of the lower assembly, the middle connecting member of the lower assembly and the second connecting member form a parallelogram mechanism and the second inner link of the lower assembly is parallel to the second outer link of the lower assembly; an upper eight-joint assembly, which includes a first inner link of the upper assembly, a first outer link of the upper assembly, a middle connecting member of the upper assembly, a second inner link of the upper assembly and a second outer link of the upper assembly. One end of the first inner link of the upper assembly is pivotally connected to the first connecting member and the other end is pivotally connected to the middle connecting member of the upper assembly. One end of the first outer link of the upper assembly is pivotally connected to the first connecting member and the other end is pivotally connected to the middle connecting member of the upper assembly. One end of the second inner link of the upper assembly is pivotally connected to the second connecting member and the other end is pivotally connected to the middle connecting member of the upper assembly. One end of the second outer link of the upper assembly is pivotally connected to the second connecting member and the other end is pivotally connected to the middle connecting member of the upper assembly. The first inner link of the upper assembly, the first outer link of the upper assembly, the middle connecting member of the upper assembly and the first connecting member form a parallelogram mechanism and the first inner link of the upper assembly is parallel to the first outer link of the upper assembly. The second inner link of the upper assembly, the second outer link of the upper assembly, the middle connecting member of the upper assembly and the second connecting member form a parallelogram mechanism and the second inner link of the upper assembly is parallel to the second outer link of the upper assembly;Among them, the connecting member in the upper component is located above the connecting member in the lower component in the up-down direction. The space deployable unit has a deployed state and a folded state. When the space deployable unit is in the deployed state, the distance between the first connecting member and the second connecting member is greater than the distance between the first connecting member and the second connecting member when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first inner link of the lower component and the second inner link of the lower component is greater than the angle between the first inner link of the lower component and the second inner link of the lower component when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first outer link of the lower component and the second outer link of the lower component is greater than the angle between the first inner link of the lower component and the second inner link of the lower component when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first inner link of the upper component and the second inner link of the upper component is greater than the angle between the first inner link of the upper component and the second inner link of the upper component when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first outer link of the upper component and the second outer link of the upper component is greater than the angle between the first outer link of the upper component and the second outer link of the upper component when the space deployable unit is in the folded state.;

[0008] The space deployable unit according to the embodiment of the present invention has advantages such as strong load-bearing capacity and high reliability.

[0009] In addition, the space deployable unit according to the above embodiment of the present invention may further have the following additional technical features:

[0010] According to an embodiment of the present invention, when the space deployable unit is in the deployed state, the first inner link of the lower component and the second inner link of the lower component are coaxially arranged, and the first outer link of the lower component and the second outer link of the lower component are coaxially arranged.

[0011] According to an embodiment of the present invention, the lengths of the first inner link of the lower component, the first outer link of the lower component, the second inner link of the lower component, and the second outer link of the lower component are equal, and the lengths of the first inner link of the upper component, the first outer link of the upper component, the second inner link of the upper component, and the second outer link of the upper component are equal.

[0012] According to an embodiment of the present invention, the distance between the first inner link and the first outer link of the lower component is equal to the distance between the second inner link and the second outer link of the lower component, and the distance between the first inner link and the first outer link of the upper component is equal to the distance between the second inner link and the second outer link of the upper component.

[0013] According to an embodiment of the present invention, the distance between the connection of the first outer link of the lower component and the first connecting member and the connection of the first outer link of the upper component and the first connecting member is equal to the distance between the connection of the second outer link of the lower component and the second connecting member and the connection of the second outer link of the upper component and the second connecting member.

[0014] According to an embodiment of the second aspect of the present invention, a planar deployable antenna support truss is provided. The planar deployable antenna support truss includes: a plurality of support modules arranged along the length direction of the planar deployable antenna after deployment. Each support module includes two space deployable units and an inter-unit connection assembly. The space deployable unit is the space deployable unit according to the embodiment of the first aspect of the present invention. The two space deployable units are arranged opposite to each other in the width direction of the planar deployable antenna after deployment. The two ends of each inter-unit connection assembly are respectively connected to the connecting members in the upper component of the two space deployable units of the support module where it is located. The two space deployable units of each support module are respectively a first unit and a second unit. The first connecting member of the first unit of one of the adjacent two support modules is connected to the second connecting member of the first unit of the other of the adjacent two support modules. The first connecting member of the second unit of one of the adjacent two support modules is connected to the second connecting member of the second unit of the other of the adjacent two support modules; a driving assembly, the driving assembly is in transmission connection with the inter-unit connection assembly of one of the plurality of support modules; a plurality of first inter-module link assemblies, the first inter-module link assembly includes a first component first link and a first component second link, one end of the first component first link and one end of the first component second link are pivotally connected, and the other end of the first component first link and the other end of the first component second link are respectively pivotally connected to the connecting members in the upper component of the first unit of two adjacent support modules; a plurality of second inter-module link assemblies, the second inter-module link assembly includes a second component first link and a second component second link, one end of the second component first link and one end of the second component second link are pivotally connected, and the other end of the second component first link and the other end of the second component second link are respectively pivotally connected to the connecting members in the upper component of the second unit of two adjacent support modules.

[0015] The planar deployable antenna support truss according to the embodiment of the present invention has advantages such as strong load-bearing capacity and high reliability by using the space deployable unit according to the embodiment of the first aspect of the present invention.

[0016] According to an embodiment of the present invention, the driving assembly includes: a driving device; a first driving rod, which is pivotally arranged on the spacecraft body and is in transmission connection with the driving device; a second driving rod, which is pivotally connected to the first driving rod; a driving adapter rod, which is pivotally connected to the second driving rod and is connected to the inter-unit connection assembly of the support module adjacent to the spacecraft body.

[0017] According to an embodiment of the present invention, the inter-unit connection assembly is a scissor mechanism and includes: two long connecting rods, the centers of the two long connecting rods are pivotally connected, each long connecting rod has a first end and a second end, and the driving adapter rod is connected to the connection part of the two long connecting rods; two first short connecting rods, one ends of the two first short connecting rods are pivotally connected and are pivotally connected to the connecting piece in the upper assembly of the first unit, and the other ends of the two first short connecting rods are respectively pivotally connected to the first ends of the two long connecting rods; two second short connecting rods, one ends of the two second short connecting rods are pivotally connected and are pivotally connected to the connecting piece in the upper assembly of the second unit, and the other ends of the two second short connecting rods are respectively pivotally connected to the second ends of the two long connecting rods.

[0018] According to an embodiment of the present invention, when the space deployable unit is in the deployed state, the distance between the connecting pieces in the upper assemblies of the two space deployable units of each support module is less than the distance between the connecting pieces in the upper assemblies of the two space deployable units of each support module when the space deployable unit is in the folded state.

[0019] According to an embodiment of the third aspect of the present invention, a spacecraft is provided, which includes the planar deployable antenna support truss according to the embodiment of the second aspect of the present invention.

[0020] The spacecraft according to the embodiment of the present invention, by using the planar deployable antenna support truss according to the embodiment of the second aspect of the present invention, has advantages such as strong reliability.

[0021] The additional aspects and advantages of the present invention will be partly given in the following description, partly become obvious from the following description, or be understood through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The above and / or additional aspects and advantages of the present invention will become obvious and easy to understand from the description of the embodiments in conjunction with the following drawings, wherein:

[0023] Figure 1 is a schematic structural diagram of a spacecraft according to an embodiment of the present invention.

[0024] Figure 2 It is a schematic diagram of a partial structure of a planar deployable antenna support truss according to an embodiment of the present invention.

[0025] Figure 3 It is a schematic diagram of a partial structure of a planar deployable antenna support truss according to an embodiment of the present invention.

[0026] Figure 4 It is a schematic diagram of the structure of a space deployable unit according to an embodiment of the present invention.

[0027] Reference numerals: spacecraft 1, planar deployable antenna support truss 10, space deployable unit 100, first unit 101, second unit 102, first connecting member 110, second connecting member 120, first inner connecting rod 131 of the lower assembly, first outer connecting rod 132 of the lower assembly, middle connecting member 133 of the lower assembly, second inner connecting rod 134 of the lower assembly, second outer connecting rod 135 of the lower assembly, first inner connecting rod 141 of the upper assembly, first outer connecting rod 142 of the upper assembly, middle connecting member 143 of the upper assembly, second inner connecting rod 144 of the upper assembly, second outer connecting rod 145 of the upper assembly, inter-unit connecting assembly 200, long connecting rod 210, first short connecting rod 220, second short connecting rod 230, first connecting rod 311 of the first assembly, second connecting rod 312 of the first assembly, first connecting rod 321 of the second assembly, second connecting rod 322 of the second assembly, first driving rod 410, second driving rod 420, driving adapter rod 430, planar deployable antenna 20, spacecraft body 30. Detailed Description of the Embodiment

[0028] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements with the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary and are only used to explain the present invention and should not be construed as a limitation of the present invention.

[0029] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more.

[0030] In the description of the present invention, it should be noted that, unless otherwise clearly specified and defined, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] The spatial deployable unit 100 according to an embodiment of the present invention will be described below with reference to the accompanying drawings.

[0032] As Figures 1 - 4 shown, the spatial deployable unit 100 according to an embodiment of the present invention includes a first connecting member 110, a second connecting member 120, a lower eight-joint assembly, and an upper eight-joint assembly.

[0033] The lower eight-joint assembly includes a lower assembly first inner link 131, a lower assembly first outer link 132, a lower assembly middle connecting member 133, a lower assembly second inner link 134, and a lower assembly second outer link 135. One end of the lower assembly first inner link 131 is pivotally connected to the first connecting member 110 and the other end is pivotally connected to the lower assembly middle connecting member 133. One end of the lower assembly first outer link 132 is pivotally connected to the first connecting member 110 and the other end is pivotally connected to the lower assembly middle connecting member 133. One end of the lower assembly second inner link 134 is pivotally connected to the second connecting member 120 and the other end is pivotally connected to the lower assembly middle connecting member 133. One end of the lower assembly second outer link 135 is pivotally connected to the second connecting member 120 and the other end is pivotally connected to the lower assembly middle connecting member 133. The lower assembly first inner link 131, the lower assembly first outer link 132, the lower assembly middle connecting member 133, and the first connecting member 110 form a parallelogram mechanism and the lower assembly first inner link 131 is parallel to the lower assembly first outer link 132. The lower assembly second inner link 134, the lower assembly second outer link 135, the lower assembly middle connecting member 133, and the second connecting member 120 form a parallelogram mechanism and the lower assembly second inner link 134 is parallel to the lower assembly second outer link 135.

[0034] The upper eight-joint component includes an upper component first inner link 141, an upper component first outer link 142, an upper component middle connecting piece 143, an upper component second inner link 144, and an upper component second outer link 145. One end of the upper component first inner link 141 is pivotally connected to the first connecting piece 110, and the other end is pivotally connected to the upper component middle connecting piece 143. One end of the upper component first outer link 142 is pivotally connected to the first connecting piece 110, and the other end is pivotally connected to the upper component middle connecting piece 143. One end of the upper component second inner link 144 is pivotally connected to the second connecting piece 120, and the other end is pivotally connected to the upper component middle connecting piece 143. One end of the upper component second outer link 145 is pivotally connected to the second connecting piece 120, and the other end is pivotally connected to the upper component middle connecting piece 143. The upper component first inner link 141, the upper component first outer link 142, the upper component middle connecting piece 143, and the first connecting piece 110 form a parallelogram mechanism, and the upper component first inner link 141 and the upper component first outer link 142 are parallel. The upper component second inner link 144, the upper component second outer link 145, the upper component middle connecting piece 143, and the second connecting piece 120 form a parallelogram mechanism, and the upper component second inner link 144 and the upper component second outer link 145 are parallel.

[0035] The upper component middle connecting piece 143 is located above the lower component middle connecting piece 133 in the up-down direction (the up-down direction is shown by the arrow in the figure and is only for the convenience of description, not a limitation on the actual setting direction). The space deployable unit 100 has a deployed state and a folded state. When the space deployable unit 100 is in the deployed state, the distance between the first connecting piece 110 and the second connecting piece 120 is greater than the distance between the first connecting piece 110 and the second connecting piece 120 when the space deployable unit 100 is in the folded state. When the space deployable unit 100 is in the deployed state, the angle between the lower component first inner link 131 and the lower component second inner link 134 is greater than the angle between the lower component first inner link 131 and the lower component second inner link 134 when the space deployable unit 100 is in the folded state. When the space deployable unit 100 is in the deployed state, the angle between the lower component first outer link 132 and the lower component second outer link 135 is greater than the angle between the lower component first inner link 131 and the lower component second inner link 134 when the space deployable unit 100 is in the folded state. When the space deployable unit 100 is in the deployed state, the angle between the upper component first inner link 141 and the upper component second inner link 144 is greater than the angle between the upper component first inner link 141 and the upper component second inner link 144 when the space deployable unit 100 is in the folded state. When the space deployable unit 100 is in the deployed state, the angle between the upper component first outer link 142 and the upper component second outer link 145 is greater than the angle between the upper component first outer link 142 and the upper component second outer link 145 when the space deployable unit 100 is in the folded state.

[0036] Specifically, the first outer link 132 of the lower component and the second outer link 135 of the lower component are adapted to be connected to the planar deployable antenna 20 of the spacecraft 1 to support the planar deployable antenna 20 of the spacecraft 1.

[0037] For the space deployable unit 100 according to an embodiment of the present invention, by providing the upper eight-joint assembly and the lower eight-joint assembly, a space deployable mechanism can be formed by using the upper eight-joint assembly and the lower eight-joint assembly, and the folding and unfolding of the space deployable unit 100 can be realized, so as to support the unfolding and folding of the planar deployable antenna 20 of the spacecraft 1.

[0038] Moreover, by forming a space deployable mechanism by using the upper eight-joint assembly and the lower eight-joint assembly, compared with the method of supporting a deployable antenna by using a planar deployable method in the related art, the deployable antenna can be supported three-dimensionally in space, enabling the space deployable unit 100 to have better load-bearing capacity and improving the support reliability for the deployable antenna.

[0039] In addition, since the upper eight-joint assembly includes two parallelogram mechanisms and the lower eight-joint assembly includes two parallelogram mechanisms, the structures of the upper eight-joint assembly and the lower eight-joint assembly can be made more stable and reliable, further improving the load-bearing capacity of the space deployable unit 100 and the support reliability for the deployable antenna.

[0040] Therefore, the space deployable unit 100 according to an embodiment of the present invention has advantages such as strong load-bearing capacity and high reliability.

[0041] Next, the space deployable unit 100 according to specific embodiments of the present invention will be described with reference to the accompanying drawings.

[0042] In some specific embodiments of the present invention, as Figures 1 - 4 shown, the space deployable unit 100 according to an embodiment of the present invention includes a first connecting member 110, a second connecting member 120, a lower eight-joint assembly, and an upper eight-joint assembly.

[0043] Advantageously, in the deployed state of the space deployable unit 100, the first inner link 131 of the lower component and the second inner link 134 of the lower component are coaxially arranged, and the first outer link 132 of the lower component and the second outer link 135 of the lower component are coaxially arranged. This can keep the two outer links and the two inner links of the lower eight-joint assembly horizontal after deployment, facilitating the support for the horizontally deployed planar deployable antenna 20.

[0044] Optionally, as Figures 1 - 4As shown, the lengths of the first inner link 131, the first outer link 132, the second inner link 134, and the second outer link 135 of the lower component are equal, and the lengths of the first inner link 141, the first outer link 142, the second inner link 144, and the second outer link 145 of the upper component are equal. This facilitates the symmetric arrangement of the space deployable unit 100, enables the free movement of the space deployable unit 100 between the deployed state and the folded state, and facilitates the connection and installation of multiple space deployable units 100.

[0045] Specifically, as Figures 1 - 4 shown, the distance between the first inner link 131 and the first outer link 132 of the lower component is equal to the distance between the second inner link 134 and the second outer link 135 of the lower component, and the distance between the first inner link 141 and the first outer link 142 of the upper component is equal to the distance between the second inner link 144 and the second outer link 145 of the upper component. This further facilitates the symmetric arrangement of the space deployable unit 100, enables the free movement of the space deployable unit 100 between the deployed state and the folded state, and facilitates the connection and installation of multiple space deployable units 100.

[0046] More specifically, as Figures 1 - 4 shown, the distance between the connection point of the first outer link 132 of the lower component and the first connector 110 and the connection point of the first outer link 142 of the upper component and the first connector 110 is equal to the distance between the connection point of the second outer link 135 of the lower component and the second connector 120 and the connection point of the second outer link 145 of the upper component and the second connector 120. This further facilitates the symmetric arrangement of the space deployable unit 100, enables the free movement of the space deployable unit 100 between the deployed state and the folded state, and facilitates the connection and installation of multiple space deployable units 100.

[0047] The planar deployable antenna support truss 10 according to an embodiment of the present invention will be described below. The planar deployable antenna support truss 10 according to an embodiment of the present invention includes a plurality of support modules, a drive assembly, a plurality of first inter-module link assemblies, and a plurality of second inter-module link assemblies.

[0048] A plurality of the support modules are arranged along the length direction after the planar deployable antenna 20 is deployed. Each support module includes two space deployable units and an inter-unit connection assembly 200. The space deployable unit is the space deployable unit 100 according to the above embodiments of the present invention. The two space deployable units 100 are oppositely arranged in the width direction after the planar deployable antenna 20 is deployed. Two ends of each inter-unit connection assembly 200 are respectively connected to the connectors 143 in the upper assemblies of the two space deployable units 100 of the support module where it is located. The two space deployable units 100 of each support module are respectively a first unit 101 and a second unit 102. The first connector 110 of the first unit 101 of one of the adjacent two support modules is connected to the second connector 120 of the first unit 101 of the other of the adjacent two support modules. The first connector 110 of the second unit 102 of one of the adjacent two support modules is connected to the second connector 120 of the second unit 102 of the other of the adjacent two support modules.

[0049] The drive assembly is in transmission connection with the inter-unit connection assembly 200 of one of the plurality of support modules.

[0050] The first inter-module link assembly includes a first component first link 311 and a first component second link 312. One end of the first component first link 311 and one end of the first component second link 312 are pivotally connected, and the other end of the first component first link 311 and the other end of the first component second link 312 are respectively pivotally connected to the connectors 143 in the upper assemblies of the first units 101 of two adjacent support modules.

[0051] The second inter-module link assembly includes a second component first link 321 and a second component second link 322. One end of the second component first link 321 and one end of the second component second link 322 are pivotally connected, and the other end of the second component first link 321 and the other end of the second component second link 322 are respectively pivotally connected to the connectors 143 in the upper assemblies of the second units 102 of two adjacent support modules.

[0052] Specifically, the drive assembly drives the inter-unit connection assembly 200 of one of the plurality of support modules to move. The inter-unit connection assembly 200 drives the two space deployable units 100 of the support module where it is located to be deployed. At the same time, the first inter-module link assembly and the second inter-module link assembly drive the adjacent support modules to be deployed, so as to realize the deployment of the planar deployable antenna support truss 10 and the planar deployable antenna 20.

[0053] The planar deployable antenna support truss 10 according to an embodiment of the present invention has the advantages of strong load-bearing capacity and high reliability by using the space deployable unit 100 according to the above embodiments of the present invention.

[0054] Specifically, as Figure 3 shown, the driving assembly includes a driving device, a first driving rod 410, a second driving rod 420, and a driving adapter rod 430. The first driving rod 410 is pivotally arranged on the spacecraft body 30 and is in transmission connection with the driving device. The second driving rod 420 is pivotally connected to the first driving rod 410. The driving adapter rod 430 is pivotally connected to the second driving rod 420 and is connected to the inter-unit connection assembly 200 of the support module adjacent to the spacecraft body 30. In this way, the second driving rod 420 and the driving adapter rod 430 can be driven by driving the first driving rod 410, so as to straighten and bend the first driving rod 410 and the second driving rod 420, drive the inter-unit connection assembly 200 to approach or move away from the spacecraft body 30, drive the two space deployable units 100 connected by the inter-unit connection assembly 200 to deploy and fold, and drive the space deployable units 100 of the remaining support modules to deploy and fold through the inter-module link assembly.

[0055] More specifically, as Figure 2 and Figure 3 shown, the inter-unit connection assembly 200 is a scissor mechanism and includes long connecting rods 210, two first short connecting rods 220, and two second short connecting rods 230. The centers of the two long connecting rods 210 are pivotally connected. Each long connecting rod 210 has a first end and a second end, and the driving adapter rod 430 is connected to the connection part of the two long connecting rods 210. One ends of the two first short connecting rods 220 are pivotally connected and are pivotally connected to the connecting member 143 in the upper assembly of the first unit 101, and the other ends of the two first short connecting rods 220 are respectively pivotally connected to the first ends of the two long connecting rods 210. One ends of the two second short connecting rods 230 are pivotally connected and are pivotally connected to the connecting member 143 in the upper assembly of the second unit 102, and the other ends of the two second short connecting rods 230 are respectively pivotally connected to the second ends of the two long connecting rods 210. Specifically, in this way, not only can the inter-unit connection assembly 200 have a stable support structure to ensure the reliable transmission of the driving force in the length direction after the planar deployable antenna 20 is deployed, but also the length of the inter-unit connection assembly 200 can change in the width direction after the planar deployable antenna 20 is deployed, so as to adapt to the position changes of the two connected space deployable units 100 in the deployed and folded states, further improving the reliability of the planar deployable antenna support truss 10.

[0056] Advantageously, when the space deployable unit 100 is in the deployed state, the distance between the connectors 143 in the upper assemblies of two space deployable units 100 of each support module is less than the distance between the connectors 143 in the upper assemblies of two space deployable units 100 of each support module when the space deployable unit 100 is in the folded state. This can enable the planar deployable antenna support truss 10 to form a more stable spatial structure after deployment, further improving the load-bearing capacity and reliability of the planar deployable antenna support truss 10.

[0057] The spacecraft 1 according to an embodiment of the present invention will be described below. The spacecraft 1 according to an embodiment of the present invention includes the planar deployable antenna support truss 10 according to the above embodiment of the present invention.

[0058] Specifically, the spacecraft 1 may include a spacecraft body 30, a plurality of planar deployable antennas 20, and a plurality of planar deployable antenna support trusses 10. The plurality of planar deployable antennas 20 are spaced apart on the spacecraft body 30, and each planar deployable antenna support truss 10 is used to support one planar deployable antenna 20.

[0059] The spacecraft 1 according to an embodiment of the present invention has advantages such as strong reliability by using the planar deployable antenna support truss 10 according to the above embodiment of the present invention.

[0060] Other configurations and operations of the spacecraft 1 according to an embodiment of the present invention are known to those of ordinary skill in the art and will not be described in detail here.

[0061] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0062] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and purposes of the present invention. The scope of the present invention is defined by the claims and their equivalents.

Claims

1. A space deployable unit, characterized in that, Comprising: A first connecting member and a second connecting member; A lower eight-joint assembly, the lower eight-joint assembly comprising a first inner link of the lower assembly, a first outer link of the lower assembly, a middle connecting member of the lower assembly, a second inner link of the lower assembly, and a second outer link of the lower assembly. One end of the first inner link of the lower assembly is pivotally connected to the first connecting member, and the other end is pivotally connected to the middle connecting member of the lower assembly. One end of the first outer link of the lower assembly is pivotally connected to the first connecting member, and the other end is pivotally connected to the middle connecting member of the lower assembly. One end of the second inner link of the lower assembly is pivotally connected to the second connecting member, and the other end is pivotally connected to the middle connecting member of the lower assembly. One end of the second outer link of the lower assembly is pivotally connected to the second connecting member, and the other end is pivotally connected to the middle connecting member of the lower assembly. The first inner link of the lower assembly, the first outer link of the lower assembly, the middle connecting member of the lower assembly, and the first connecting member form a parallelogram mechanism, and the first inner link of the lower assembly is parallel to the first outer link of the lower assembly. The second inner link of the lower assembly, the second outer link of the lower assembly, the middle connecting member of the lower assembly, and the second connecting member form a parallelogram mechanism, and the second inner link of the lower assembly is parallel to the second outer link of the lower assembly; An upper eight-joint assembly, the upper eight-joint assembly comprising a first inner link of the upper assembly, a first outer link of the upper assembly, a middle connecting member of the upper assembly, a second inner link of the upper assembly, and a second outer link of the upper assembly. One end of the first inner link of the upper assembly is pivotally connected to the first connecting member, and the other end is pivotally connected to the middle connecting member of the upper assembly. One end of the first outer link of the upper assembly is pivotally connected to the first connecting member, and the other end is pivotally connected to the middle connecting member of the upper assembly. One end of the second inner link of the upper assembly is pivotally connected to the second connecting member, and the other end is pivotally connected to the middle connecting member of the upper assembly. One end of the second outer link of the upper assembly is pivotally connected to the second connecting member, and the other end is pivotally connected to the middle connecting member of the upper assembly. The first inner link of the upper assembly, the first outer link of the upper assembly, the middle connecting member of the upper assembly, and the first connecting member form a parallelogram mechanism, and the first inner link of the upper assembly is parallel to the first outer link of the upper assembly. The second inner link of the upper assembly, the second outer link of the upper assembly, the middle connecting member of the upper assembly, and the second connecting member form a parallelogram mechanism, and the second inner link of the upper assembly is parallel to the second outer link of the upper assembly; Among them, the connecting member in the upper component is located above the connecting member in the lower component in the up-and-down direction. The space deployable unit has a deployed state and a folded state. When the space deployable unit is in the deployed state, the distance between the first connecting member and the second connecting member is greater than the distance between the first connecting member and the second connecting member when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first inner link of the lower component and the second inner link of the lower component is greater than the angle between the first inner link of the lower component and the second inner link of the lower component when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first outer link of the lower component and the second outer link of the lower component is greater than the angle between the first inner link of the lower component and the second inner link of the lower component when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first inner link of the upper component and the second inner link of the upper component is greater than the angle between the first inner link of the upper component and the second inner link of the upper component when the space deployable unit is in the folded state. When the space deployable unit is in the deployed state, the angle between the first outer link of the upper component and the second outer link of the upper component is greater than the angle between the first outer link of the upper component and the second outer link of the upper component when the space deployable unit is in the folded state.

2. The space deployable unit according to claim 1, characterized in that When the space deployable unit is in the deployed state, the first inner link of the lower component and the second inner link of the lower component are coaxially arranged, and the first outer link of the lower component and the second outer link of the lower component are coaxially arranged.

3. The space deployable unit according to claim 1, wherein, The lengths of the first inner link of the lower component, the first outer link of the lower component, the second inner link of the lower component, and the second outer link of the lower component are equal, and the lengths of the first inner link of the upper component, the first outer link of the upper component, the second inner link of the upper component, and the second outer link of the upper component are equal.

4. The space deployable unit according to claim 1, wherein The distance between the first inner link and the first outer link of the lower component is equal to the distance between the second inner link and the second outer link of the lower component, and the distance between the first inner link and the first outer link of the upper component is equal to the distance between the second inner link and the second outer link of the upper component.

5. The space deployable unit according to claim 1, characterized in that, The distance between the connection of the first outer link of the lower component and the first connecting member and the connection of the first outer link of the upper component and the first connecting member is equal to the distance between the connection of the second outer link of the lower component and the second connecting member and the connection of the second outer link of the upper component and the second connecting member.

6. A planar deployable antenna support truss, characterized in that, Including: A plurality of support modules, the plurality of support modules being arranged along the length direction after the planar deployable antenna is deployed. Each support module includes two space deployable units and an inter-unit connection assembly. The space deployable unit is the space deployable unit according to any one of claims 1-5. The two space deployable units are oppositely arranged in the width direction after the planar deployable antenna is deployed. The two ends of each inter-unit connection assembly are respectively connected to the connectors in the upper assembly of the two space deployable units of the support module where it is located. The two space deployable units of each support module are respectively a first unit and a second unit. The first connector of the first unit of one of the adjacent two support modules is connected to the second connector of the first unit of the other of the adjacent two support modules. The first connector of the second unit of one of the adjacent two support modules is connected to the second connector of the second unit of the other of the adjacent two support modules; A drive assembly, the drive assembly being in transmission connection with the inter-unit connection assembly of one of the plurality of support modules; A plurality of first inter-module link assemblies, the first inter-module link assembly including a first assembly first link and a first assembly second link. One end of the first assembly first link and one end of the first assembly second link are pivotally connected, and the other end of the first assembly first link and the other end of the first assembly second link are respectively pivotally connected to the connectors in the upper assembly of the first units of two adjacent support modules; A plurality of second inter-module link assemblies, the second inter-module link assembly including a second assembly first link and a second assembly second link. One end of the second assembly first link and one end of the second assembly second link are pivotally connected, and the other end of the second assembly first link and the other end of the second assembly second link are respectively pivotally connected to the connectors in the upper assembly of the second units of two adjacent support modules.

7. The planar deployable antenna support truss according to claim 6, wherein, The drive assembly includes: A drive device; A first drive rod, the first drive rod being adapted to be pivotally arranged on the spacecraft body and in transmission connection with the drive device; A second drive rod, the second drive rod being pivotally connected to the first drive rod; A drive adapter rod, the drive adapter rod being pivotally connected to the second drive rod and connected to the inter-unit connection assembly of the support module adjacent to the spacecraft body.

8. The planar deployable antenna support truss according to claim 7, wherein, The inter-unit connection assembly is a scissor mechanism and includes: Two long links, the centers of the two long links being pivotally connected. Each long link has a first end and a second end, and the drive adapter rod is connected to the connection part of the two long links; Two first short links, one end of the two first short links being pivotally connected and pivotally connected to the connector in the upper assembly of the first unit, and the other ends of the two first short links being respectively pivotally connected to the first ends of the two long links; Two second short linkages, one end of the two second short linkages are pivotally connected to each other and pivotally connected to the connecting member in the upper assembly of the second unit, and the other ends of the two second short linkages are respectively pivotally connected to the second ends of the two long linkages.

9. The planar deployable antenna support truss according to claim 8, wherein, When the space deployable unit is in the deployed state, the distance between the connecting members in the upper assemblies of the two space deployable units of each support module is less than the distance between the connecting members in the upper assemblies of the two space deployable units of each support module when the space deployable unit is in the folded state.

10. A spacecraft, characterized in that, Comprising a planar deployable antenna support truss according to any one of claims 6-9.

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