A deployable space truss mechanism based on rope linkage

Abstract

The present invention relates to the technical field of thin film structures, and discloses a deployable space truss mechanism based on rope linkage, comprising an deployment component, a base plate, a top plate, a rod linkage component, a compression and release component and a cable-stayed tensioning component, wherein the deployment component is arranged on the base plate, and comprises at least two groups of connecting rod deployment modules; the connecting rod deployment module comprises a first connecting rod deployment module and a second connecting rod deployment module connected to each other; the top plate is arranged opposite to the base plate, and is connected to the first connecting rod deployment module; a compression and release component is arranged on the base plate, for compressing and releasing the compressed space truss; a cable-stayed tensioning component is also arranged between the base plate and the top plate, for providing tensioning force to the deployed space truss; the present invention realizes a simple deployment process of the space truss, a small storage volume, and improves the structural rigidity after deployment and locking through the first linkage module, the second linkage module, the linkage rope, and the cable-stayed tensioning component.

Description

Technical Field

[0001] The present invention relates to the technical field of membrane structures, and more specifically, to a rope-linked spatial truss deployable mechanism. Background Art

[0002] With the continuous deepening of space exploration activities, the demand for ultra-large and ultra-light space deployable structures in future space missions is increasing. Large space deployable structures have been greatly developed due to their light weight, large storage ratio, and flexible configuration. At present, the main applications include large film deployable antennas, space extension arms, solar sails, etc.

[0003] In 2008, Kutter et al. proposed a scheme for an inflatable cone-shaped membrane deployable mechanism. In 2011, Xu Yan and Guan Fuling designed a new inflatable membrane deployable mechanism that can achieve axial and radial deployment. In 2020, Lin Qiuhong et al. applied origami technology to the design of space membrane structures and inflatable tube structures. All of these deployment methods are inflatable deployment, but the inflation system is relatively complex and prone to air leakage in orbit. Although some have a curing function, the curing effect is not ideal. The sunshade of the space telescope NGST and the James Webb Space Telescope (JWST) orbiting at the Lagrange L2 point also uses space deployable mechanism technology. The rigid bracket membrane deployable mechanism uses a rigid bracket composed of a mechanical structure to achieve the switching between the folded configuration and the unfolded configuration, which makes the deployment high in precision and good in stability, but the complexity of the mechanism reduces the possibility of successful deployment, and the weight of the mechanism increases the transportation cost. Summary of the invention

[0004] The purpose of the present invention is to provide a rope-linked deployable space truss mechanism to address the technical problems existing in the prior art, so as to simplify the deployment process of the space truss, reduce the storage volume, and improve the structural stiffness after deployment and locking.

[0005] In order to solve the above problems, the technical solution adopted by the present invention is:

[0006] The present invention provides a rope-linked spatial truss deployable mechanism, comprising a deployment assembly, a bottom plate, a top plate, a rod linkage assembly, a compression release assembly and a stay cable tensioning assembly, wherein the deployment assembly is arranged on the bottom plate and comprises at least two groups of connecting rod deployment modules; the connecting rod deployment module comprises a first connecting rod deployment module and a second connecting rod deployment module connected to each other;

[0007] The top plate is arranged opposite to the bottom plate and connected to the first connecting rod deployment module; a compression and release assembly is arranged on the bottom plate, used for compressing and releasing the compressed space truss; a cable tensioning assembly is also arranged between the bottom plate and the top plate, used for providing tensioning force to the deployed space truss;

[0008] The base plate is also provided with an inter-rod linkage assembly corresponding to the position of the connecting rod deployment module, and the inter-rod linkage assembly includes a first linkage module and a second linkage module that are relatively arranged, and a linkage rope, the first linkage module is connected to the first connecting rod deployment module, and the second linkage module is connected to the second connecting rod deployment module; the linkage rope connects the first linkage module and the second linkage module to control the synchronization of the deployment process of the first connecting rod deployment module and the second connecting rod deployment module.

[0009] Furthermore, both the first linkage module and the second linkage module include a hinge linkage wheel unit, a guide wheel unit and a double wheel unit arranged in parallel, and the linkage rope uses two steel ropes; the hinge linkage wheel unit is connected to the corresponding first connecting rod deployment module or the second connecting rod deployment module, and the starting point of the two steel ropes is the hinge linkage wheel of the first linkage module, and they cross after passing through the guide wheel unit and the double wheel unit, and then pass through the double wheel unit and the guide wheel unit of the second linkage module, and the end point is the hinge linkage wheel of the second linkage module.

[0010] Furthermore, the hinge linkage wheel unit includes a linkage wheel, a pre-tightening screw and a connecting angle piece. A notch is formed on the end face of the linkage wheel, and connecting angle pieces are respectively arranged at both ends of the notch and fixed by the pre-tightening screws; a groove is arranged on the surface of the linkage wheel along the circumferential direction; the two steel ropes respectively pass through the pre-tightening screw and the connecting angle piece in turn, and pass through the groove of the linkage wheel in opposite directions to reach the guide wheel unit.

[0011] Furthermore, the guide wheel unit includes a guide wheel support, a double-groove guide wheel, an upper row of guide wheels and a lower row of guide wheels, the guide wheel support is arranged on the base plate, and the upper row of guide wheels and the lower row of guide wheels are coaxially arranged; the surface of the double-groove guide wheel is provided with an annular groove along the circumferential direction, and is arranged on the guide wheel support; the two steel ropes respectively pass through the surface of the double-groove guide wheel, and then pass through the upper row of guide wheels and the lower row of guide wheels respectively.

[0012] Furthermore, the axis of the double-groove guide wheel is parallel to the axis of the linkage wheel in the hinge linkage wheel unit, and two parallel annular grooves are circumferentially arranged on the surface of the double-groove guide wheel for passing the two steel ropes respectively.

[0013] Furthermore, the double-wheel unit includes a guide wheel bracket, a first guide wheel, a second guide wheel, and a rope limiting plate. The guide wheel bracket is arranged on the base plate, and is coaxially provided with a first guide wheel and a second guide wheel of different diameters, which are used to pass the two steel ropes respectively; the rope limiting plate is arranged on the guide wheel bracket and is located on one side of the first guide wheel and the second guide wheel.

[0014] Furthermore, the cable-stayed cable tensioning assembly includes an outer guide seat, a compression spring, a sliding column and a cable-stayed cable arranged on the base plate; a sliding column is arranged in the guide cylinder of the outer guide seat, and a compression spring is also arranged between the two; the end of the sliding column is connected to one end of the cable-stayed cable, and the other end of the cable-stayed cable is connected to the top plate.

[0015] Furthermore, the surfaces of the upper row guide wheels, the lower row guide wheels, and the first guide wheels and the second guide wheels are respectively machined with annular grooves along the circumferential direction.

[0016] Furthermore, linkage rods are respectively arranged between the first link deployment modules of the two groups of link deployment modules, and between the top of the second link deployment module and the first link deployment module for connection, and all the linkage rods are located on the same horizontal plane.

[0017] Furthermore, the first link deployment module and the second link deployment module include four links and two links respectively, and the adjacent links and the links and the corresponding bottom plate and top plate are connected by hinges respectively, and energy storage springs are provided.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] (1) The present invention drives the first link deployment module and the second link deployment module to deploy respectively through the first linkage module and the second linkage module of the inter-rod linkage assembly, and connects the first linkage module and the second linkage module through a linkage rope, thereby improving the linkage of the deployment movements of the first link deployment module and the second link deployment module, that is, controlling the synchronization of the deployment processes of the two. The overall structure is simple and the operation is reliable. The storage volume of the space truss is small and the stiffness is high after deployment and locking. In addition, by setting a cable tensioning assembly, tensioning force is provided to the deployed space truss to improve the stiffness of the overall structure.

[0020] (2) The first and second linkage modules of the present invention are linked by a hinge to a wheel unit, a guide wheel unit and a double wheel unit, and the wheel unit, the guide wheel unit and the double wheel unit are respectively hinged by two steel wire ropes, and the first linkage module is cross-connected with the second linkage module, thereby realizing the linkage between the first linkage module and the second linkage module, which has a simple structure, reliable functions and is easy to implement.

[0021] (3) The hinge linkage wheel unit of the present invention is connected to the corresponding first link deployment module or second link deployment module through the linkage wheel, and the steel wire rope is conveniently compressed and fixed by connecting the angle piece and the pre-tightening screw. A groove is also arranged on the surface of the linkage wheel to facilitate the two steel wire ropes to pass through and reach the guide wheel unit in the opposite direction, thereby ensuring the reliability of the overall operation of the mechanism.

[0022] (4) The guide wheel unit of the present invention guides the two steel wire ropes through the double-groove guide wheel, the upper guide wheel and the lower guide wheel. That is, the two steel wire ropes pass through the surface of the double-groove guide wheel respectively, and then pass through the upper guide wheel and the lower guide wheel respectively. This can reliably guide the two steel wire ropes and avoid interference between the two steel wire ropes, which would affect the reliability of their linkage process.

[0023] (5) The double-wheel unit of the present invention further guides the two steel wire ropes led out of the guide wheel unit through the coaxially arranged first guide wheel and second guide wheel, and adopts two guide wheels with different diameters to avoid contact between the two steel wire ropes, thereby avoiding wear and affecting their service life; in addition, a rope limiting plate is used to limit the position of the steel wire rope to ensure the reliability of the mechanism operation.

[0024] (6) The cable-stayed tensioning assembly of the present invention connects the top plate and the bottom plate by setting up cable-stayed cables. The cable-stayed cables can be unfolded along with the unfolding mechanism. After being unfolded into place, the cable is tightened by compressing the spring and the sliding column, thereby strengthening the rigidity of the unfolding mechanism and further ensuring the reliability of the mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the scheme of the present invention, the following is a brief introduction to the drawings required for the description of the embodiments. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. Among them:

[0026] Figure 1 It is a schematic diagram of the unfolded state of the unfoldable mechanism of the space truss of the present invention;

[0027] Figure 2 It is a schematic diagram of the folded state of the deployable space truss mechanism of the present invention;

[0028] Figure 3 is a schematic diagram of the inter-rod linkage assembly of the present invention;

[0029] Figure 4 is a schematic diagram of the first linkage module of the present invention;

[0030] Figure 5 is a schematic diagram of the second linkage module of the present invention;

[0031] Figure 6 is a schematic diagram of a hinge linkage wheel unit of the present invention;

[0032] Figure 7 is a schematic diagram of a guide wheel unit of the present invention;

[0033] Figure 8 is a schematic diagram of a double-wheel unit of the present invention;

[0034] Fig. 9 It is a schematic diagram of the inclined cable tensioning assembly of the present invention.

[0035] Among them: 1-first link deployment module; 2-second link deployment module; 3-bottom plate; 4-linkage rod; 5-top plate; 6-inter-rod linkage assembly; 61-first linkage module; 62-second linkage module; 7-compression release assembly; 8-stayed cable tensioning assembly; 9-hinge linkage wheel unit; 10-guide wheel unit; 11-double wheel unit; 12-wire rope; 13-linkage wheel; 131-groove; 141-first pre-tightening screw; 142-second pre-tightening screw; 15-nut; 16-connecting angle piece; 17-guide wheel support; 18-double-groove guide wheel; 19-upper row guide wheel; 20-lower row guide wheel; 21-guide wheel bracket; 22-first guide wheel; 23-second guide wheel; 24-rope limiting plate; 25-outer guide seat; 26-compression spring; 27-sliding column; 28-stayed cable. DETAILED DESCRIPTION

[0036] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field of the present invention; the terms used in this specification are only for the purpose of describing specific embodiments and are not intended to limit the present invention. For example, the directions or positions indicated by the terms "length", "width", "up", "down", "left", "right", "front", "back", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc. are based on the directions or positions shown in the drawings, which are only for the convenience of description and should not be understood as limitations on the present technical solution.

[0037] The terms "including" and "having" and any variations thereof in the specification and claims of the present invention and the above-mentioned drawings are intended to cover non-exclusive inclusions; the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish different objects rather than to describe a specific order. In the specification and claims of the present invention and the above-mentioned drawings, when an element is referred to as being "fixed to" or "mounted on" or "disposed on" or "connected to" another element, it may be directly or indirectly located on the other element. For example, when an element is referred to as being "connected to" another element, it may be directly or indirectly connected to the other element.

[0038] In addition, reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present invention. The appearance of the phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0039] See also Figure 1 and Figure 2 As shown, the present invention provides a deployable space truss mechanism based on rope linkage, comprising a deployment assembly, a bottom plate 3, a top plate 5, a rod linkage assembly 6, a compression release assembly 7 and a stay cable tensioning assembly 8, wherein the deployment assembly is arranged on the bottom plate 3 and comprises at least two groups of connecting rod deployment modules; the connecting rod deployment module comprises a first connecting rod deployment module 1 and a second connecting rod deployment module 2 connected to each other;

[0040] The top plate 5 is arranged opposite to the bottom plate 3 and is connected to the first link deployment module 1 of the link deployment module. The bottom plate 3 is also provided with an inter-rod linkage assembly 6 corresponding to the position of the link deployment module, which is used to control the synchronization of the deployment process of the first link deployment module 1 and the second link deployment module 2. The bottom plate 3 is provided with a compression release assembly 7, which is used to compress and release the compressed space truss; a cable tensioning assembly 8 is also provided between the bottom plate 3 and the top plate 5, which is used to provide tensioning force to the deployed space truss.

[0041] Specifically, the second link deployment module 2 and the first link deployment module 1 are arranged side by side when folded and parallel to each other when unfolded, so that the folded envelope size of the deployment mechanism is greatly reduced, the structure is simple, and the storage volume is small.

[0042] Furthermore, a linkage rod 4 is respectively arranged between each group of the connecting rod deployment modules and the two groups of the connecting rod deployment modules for connection, that is, a linkage rod 4 is respectively arranged between the middle part of each group of the first connecting rod deployment modules 1 and the top part of the second connecting rod deployment module 2, and between the middle parts of the two groups of the first connecting rod deployment modules 1, that is, they are connected by three linkage rods 4, and the three linkage rods 4 are located in the same horizontal plane, thus forming a stable spatial truss structure.

[0043] Furthermore, the first link deployment module 1 adopts four links, and the second link deployment module 2 adopts two links. The adjacent links, and the links and the bottom plate 3 and the top plate 5 are respectively connected by hinges, and energy storage springs (not shown in the figure) are provided.

[0044] Specifically, the number of links used in the first link deployment module 1 and the second link deployment module 2 can be increased or decreased according to actual needs, and are connected in sequence through hinges. Energy storage springs are also provided to facilitate folding, stowing and unfolding of the two.

[0045] like Figure 3 to Figure 5 As shown, the inter-rod linkage assembly 6 includes a first linkage module 61 and a second linkage module 62 which are relatively arranged and located on one side of the link deployment module, and a linkage rope. The first linkage module 61 is connected to the first link deployment module 1, and the second linkage module 62 is connected to the second link deployment module 2. The linkage rope connects the first linkage module 61 and the second linkage module 62, driving the synchronization of the movement of the first linkage module 61 and the second linkage module 62, thereby controlling the synchronization of the deployment process of the first link deployment module 1 and the second link deployment module 2.

[0046] Furthermore, both the first linkage module 61 and the second linkage module 62 include a hinge linkage wheel unit 9, a guide wheel unit 10 and a double wheel unit 11 which are arranged in parallel on the base plate 3, and the linkage ropes are two steel wire ropes 12; the hinge linkage wheel unit 9 is connected to the corresponding first connecting rod deployment module 1 or the second connecting rod deployment module 2, and the starting points of the two steel wire ropes 12 are the hinge linkage wheel unit 9 of the first linkage module 61, which cross after passing through the guide wheel unit 10 and the double wheel unit 11, and then pass through the double wheel unit 11 and the guide wheel unit 10 of the second linkage module 62, and the end point is the hinge linkage wheel unit 9 of the second linkage module 62.

[0047] like Figure 6 As shown, the hinge linkage wheel unit 9 includes a linkage wheel 13, a pre-tightening screw, a nut 15, and a connecting angle piece 16 connecting the corresponding first link deployment module 1 and the second link deployment module 2, wherein the pre-tightening screw has a through hole with a diameter of 1.6 mm.

[0048] A notch is formed on the end surface of the linkage wheel 13, and two sets of connecting angle pieces 16 and nuts 15 are respectively arranged at the ends of the notch, and are fixed by pre-tightening screws, namely, a first pre-tightening screw 141 and a second pre-tightening screw 142. A groove 131 is arranged on the surface of the linkage wheel 13 along the circumferential direction to facilitate the passage and position limiting of the steel wire rope 12. The two steel wire ropes 12 pass through the through holes on the two pre-tightening screws 14, namely, the first pre-tightening screw 141 and the first pre-tightening screw 142 on the linkage wheel 13, respectively, and pass through the groove 131 of the linkage wheel 13 in opposite directions to reach the guide wheel unit 10.

[0049] Specifically, the linkage wheel 13 is also connected to the corresponding links in the first link deployment module 1 and the second link deployment module 2 through a hinge, and is also provided with an energy storage spring to facilitate the deployment of the spatial truss structure.

[0050] In this embodiment, when the steel wire rope 12 is stressed, one end of the steel wire rope 12 is tightened by a tension machine, and when the predetermined value is reached, the rope end of the steel wire rope 12 is flattened, and then the connecting angle piece 16 on the hinge linkage wheel unit 9 is fixed. The connecting angle piece 16 is an L-shaped angle piece, which is convenient for installation and connection, and also makes it more convenient to stress the steel wire rope 12.

[0051] like Figure 7 As shown, the guide wheel unit 10 includes a guide wheel support 17, a double-groove guide wheel 18, an upper row guide wheel 19 and a lower row guide wheel 20. The guide wheel support 17 is arranged on the bottom plate 3. The surface of the double-groove guide wheel 18 is provided with two annular grooves along the circumferential direction and is arranged on the guide wheel support 17. The upper row guide wheel 19 and the lower row guide wheel 20 are coaxially arranged on the guide wheel support 17 and located on one side of the double-groove guide wheel 18.

[0052] Furthermore, the axis of the double-groove guide wheel 18 is parallel to the axis of the linkage wheel 13, and two parallel annular grooves are arranged on the surface along the circumferential direction to facilitate the passage of the two steel ropes 12.

[0053] Specifically, the two steel wire ropes 12 pass through the two annular grooves in the double groove guide wheel 18, one steel wire rope 12 passes through the middle of the surface of the upper guide wheel 19 and comes out tangent to the upper guide wheel 19. The other steel wire rope 12 passes through the middle of the surface of the lower guide wheel 20 and comes out tangent to the lower guide wheel 20.

[0054] In this embodiment, in order to ensure the reliability of the deployable mechanism, the upper guide wheels 19 and the lower guide wheels 20 are respectively arranged in two groups in parallel, and the upper guide wheels 19 and the lower guide wheels 20 of each group are respectively coaxially arranged.

[0055] like Figure 8 As shown, the double wheel unit 11 includes a guide wheel bracket 21, a first guide wheel 22, a second guide wheel 23, and a rope limiting plate 24. The guide wheel bracket 21 is arranged on the bottom plate 3, and is coaxially provided with a first guide wheel 22 and a second guide wheel 23 having different diameters. The rope limiting plate 24 is arranged on the guide wheel bracket 21 and is located on one side of the first guide wheel 22 and the second guide wheel 23.

[0056] Specifically, when the two steel ropes 12 pass through the double-wheel unit 11, they pass through the first guide wheel 22 and the second guide wheel 23 respectively, so that there is a certain gap between the two steel ropes 12 after they cross. By adopting the first guide wheel 22 and the second guide wheel 23 with different diameters, it can be ensured that the two steel ropes 12 do not contact each other, thereby avoiding friction between the two steel ropes 12.

[0057] Furthermore, in order to facilitate the passage of the two steel wire ropes 12, the surfaces of the upper guide wheel 19 and the lower guide wheel 20 in the guide wheel unit 10, and the first guide wheel 22 and the second guide wheel 23 in the double wheel unit 11 are all processed with annular grooves along the circumferential direction to ensure that the two steel wire ropes 12 do not deviate when passing.

[0058] In this embodiment, through the action of the guide wheel unit 10 and the double wheel unit 11, the two steel ropes 12 can be reliably guided. It has a simple structure, reliable functions, wide applicability, a wide range of applications, and can realize linkage between multiple rods according to actual needs.

[0059] like Fig. 9 As shown, the cable tensioning assembly 8 includes an outer guide seat 25, a compression spring 26, a sliding column 27 and a cable 28. The outer guide seat 25 is arranged on the bottom plate 3. The sliding column 27 is arranged in the guide cylinder of the outer guide seat 25, and a compression spring 26 is arranged between the two. A through hole is arranged at the end of the sliding column 27, and one end of the cable 28 is connected. The other end of the cable 28 is connected to the top plate 5.

[0060] Specifically, when the space truss structure is unfolded into place, the sliding column 27 translates in the guide tube of the outer guide seat 25 and compresses the compression spring 26, providing a certain tensioning force to the inclined cable 28 to ensure the stability of the connection between the top plate 5 and the bottom plate 3. Under the tension of the inclined cable 28, the structural stiffness of the entire space truss is improved.

[0061] In this embodiment, when the space truss structure is in the collapsed state ( Figure 2 As shown in , the unfolding mechanism presses the top plate 5 and the folded unfolding assembly onto the bottom plate 3 through the compression release assembly 7; when the compression release assembly 7 is unlocked, the spatial truss structure unfolds through the energy storage spring, and the folded first link unfolding module 1 and the second link unfolding module 2 will slowly unfold, and the connecting rods connected to the bottom plate 3 will deflect. Since the first linkage module 61 and the second linkage module 62 in the inter-rod linkage assembly 6 are respectively connected to the corresponding connecting rods in the first link unfolding module 1 and the second link unfolding module 2, that is, the linkage wheel 13 in the hinge linkage wheel unit 9 connected to the corresponding connecting rod performs a deflection movement, through the action of the two steel wire ropes 12 in the linkage rope, the linkage wheels 13 of the first linkage module 61 and the second linkage module 62 are linked to each other, driving the first link unfolding module 1 and the second link unfolding module 2 to unfold stably. After the spatial truss structure is unfolded into place, it is locked, and with the reinforcement of the inclined cable 28 in the inclined cable tensioning assembly 8, a body structure with high rigidity is formed ( Figure 1 ).

[0062] The rope-linked deployable space truss mechanism provided by the present invention realizes a simple deployment process of the space truss, a small storage volume, and improved structural stiffness after deployment and locking through the first linkage module 6 and the second linkage module 61 and 62 in the inter-rod linkage assembly 6, as well as the linkage rope and the inclined cable tensioning assembly 8.

[0063] The above embodiments are preferred implementation modes of the present invention, but the implementation modes of the present invention are not limited to the above embodiments. Any other changes, modifications, substitutions, combinations, and simplifications that do not deviate from the spirit and principles of the present invention should be equivalent replacement methods and are included in the protection scope of the present invention.

Claims

1. A deployable space truss mechanism based on rope linkage, characterized in that: It includes a deployment assembly, a bottom plate, a top plate, an inter-rod linkage assembly, a compression release assembly and a cable tensioning assembly, wherein the deployment assembly is arranged on the bottom plate and includes at least two groups of connecting rod deployment modules; the connecting rod deployment module includes a first connecting rod deployment module and a second connecting rod deployment module connected to each other; The top plate is arranged opposite to the bottom plate and connected to the first connecting rod deployment module; a compression and release assembly is arranged on the bottom plate, used for compressing and releasing the compressed space truss; a cable tensioning assembly is also arranged between the bottom plate and the top plate, used for providing tensioning force to the deployed space truss; The bottom plate is also provided with an inter-rod linkage assembly corresponding to the position of the connecting rod deployment module, and the inter-rod linkage assembly includes a first linkage module and a second linkage module that are relatively arranged, and a linkage rope, wherein the first linkage module is connected to the first connecting rod deployment module, and the second linkage module is connected to the second connecting rod deployment module; the linkage rope connects the first linkage module and the second linkage module to control the synchronization of the deployment process of the first connecting rod deployment module and the second connecting rod deployment module; Both the first linkage module and the second linkage module include a hinge linkage wheel unit, a guide wheel unit and a double wheel unit arranged in parallel, and the linkage rope adopts two steel wire ropes; the hinge linkage wheel unit is connected to the corresponding first connecting rod deployment module or the second connecting rod deployment module, and the starting point of the two steel wire ropes is the hinge linkage wheel of the first linkage module, and they cross after passing through the guide wheel unit and the double wheel unit, and then pass through the double wheel unit and the guide wheel unit of the second linkage module, and the end point is the hinge linkage wheel of the second linkage module; The hinge linkage wheel unit comprises a linkage wheel, a pre-tightening screw and a connecting angle piece. A notch is formed on the end surface of the linkage wheel. Connecting angle pieces are respectively arranged at both ends of the notch and fixed by the pre-tightening screw. A groove is arranged on the surface of the linkage wheel along the circumferential direction. The two steel wire ropes respectively pass through the pre-tightening screw and the connecting angle piece in sequence, and pass through the groove of the linkage wheel in opposite directions to reach the guide wheel unit. The guide wheel unit comprises a guide wheel support, a double-groove guide wheel, an upper row guide wheel and a lower row guide wheel. The guide wheel support is arranged on the bottom plate and is coaxially provided with an upper row guide wheel and a lower row guide wheel. The surface of the double-groove guide wheel is provided with an annular groove along the circumferential direction and is arranged on the guide wheel support. The two steel wire ropes respectively pass through the surface of the double-groove guide wheel and then pass through the upper row guide wheel and the lower row guide wheel respectively. The double-wheel unit includes a guide wheel bracket, a first guide wheel, a second guide wheel, and a rope limiting plate. The guide wheel bracket is arranged on the bottom plate and is coaxially provided with a first guide wheel and a second guide wheel of different diameters for passing the two steel ropes respectively. The rope limiting plate is arranged on the guide wheel bracket and is located on one side of the first guide wheel and the second guide wheel.

2. The deployable space truss mechanism based on rope linkage according to claim 1 is characterized in that: The axis of the double-groove guide wheel is parallel to the axis of the linkage wheel in the hinge linkage wheel unit, and two parallel annular grooves are arranged on the surface of the double-groove guide wheel along the circumferential direction for passing the two steel ropes respectively.

3. The deployable space truss mechanism based on rope linkage according to claim 1 is characterized in that: The cable-stayed cable tensioning assembly includes an outer guide seat, a compression spring, a sliding column and a cable-stayed cable arranged on the base plate. The sliding column is arranged in the guide cylinder of the outer guide seat, and a compression spring is also arranged between the two. The end of the sliding column is connected to one end of the cable-stayed cable, and the other end of the cable-stayed cable is connected to the top plate.

4. The deployable space truss mechanism based on rope linkage according to claim 1, characterized in that: The surfaces of the upper row guide wheels, the lower row guide wheels, and the first guide wheels and the second guide wheels are respectively processed with annular grooves along the circumferential direction.

5. The deployable space truss mechanism based on rope linkage according to claim 1, characterized in that: Linkage rods are respectively arranged between the first link deployment modules of the two groups of link deployment modules, and between the top of the second link deployment module and the first link deployment module for connection, and all the linkage rods are located on the same horizontal plane.

6. The deployable space truss mechanism based on rope linkage according to claim 1, characterized in that: The first link deployment module and the second link deployment module include four links and two links respectively. Adjacent links and the links and the corresponding bottom plate and top plate are connected by hinges respectively, and energy storage springs are provided.

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