Connecting rod driving unfolding mechanism for large-scale deployable array plane antenna

Abstract

The invention relates to a connecting rod driving unfolding mechanism for a large-scale deployable array plane antenna, and belongs to the technical field of spaceborne antennas. Comprising two antenna multi-layer array surface structures, a satellite platform and two groups of driving unfolding assemblies, wherein the satellite platform is horizontally placed; the two antenna multi-layer array surface structures are arranged below the satellite platform in a vertical folded state; the two driving unfolding assemblies are symmetrically arranged on the front side wall and the rear side wall of the satellite platform. Each driving unfolding assembly comprises a fixed truss, two short connecting rods, two long connecting rods, two synchronous tooth holders, a driving synchronous belt, two follow-up synchronous belts, ten belt wheels and inter-plate hinges. Power is provided for the two antenna multi-layer array surface structures to be changed from a completely folded state to an unfolded state through the two groups of driving unfolding assemblies, and the unfolding speed of the antenna multi-layer array surface structures is controlled; the connecting rod driving unfolding mechanism for the large-scale deployable array plane antenna provides unfolding power and unfolding rigidity for the antenna, and has the characteristics of high storage ratio, high rigidity, high precision and controllable unfolding.

Description

Technical Field

[0001] This invention belongs to the field of spaceborne antenna technology and relates to a large deployable array antenna linkage drive deployment mechanism. Background Technology

[0002] With the increasing demands for high resolution and wide imaging swath in spaceborne SAR array antennas, the need for large array antennas is growing year by year. However, due to the limitations of the launch vehicle's payload bay envelope, large deployable antennas in space must possess a structure that allows for folding during launch and deployment in orbit. For ultra-large aperture deployable phased array antennas, to ensure the rigidity of the antenna in its folded state and to complete the antenna deployment after orbit insertion, a clamping and releasing device is required to provide antenna folding constraints. This device must achieve characteristics such as clamping between phased array antennas, controllable release and deployment, deployment maintenance, and non-interference with other components of the phased array antenna during the deployment process.

[0003] Large deployable array antennas for space are core payloads for future high-performance aerospace missions, and their performance is highly dependent on the reliable deployment of the antenna panel deployment mechanism and support mechanism, as well as the structural stability after deployment. Current designs for deployable mechanisms for large-aperture space antennas still face significant challenges, particularly in terms of structural complexity, stiffness maintenance, and drive synchronization. Traditional deployable panel mechanisms generally have high degrees of freedom and complex linkages, making it difficult to guarantee stability and reliability during antenna deployment. Furthermore, the low stiffness of the connecting structures affects the accuracy of the antenna profile. As antenna apertures continue to increase, these problems will become more pronounced, limiting the development of phased array antennas in high-performance space applications. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a large deployable array antenna linkage drive deployment mechanism to provide deployment power and deployment stiffness for the antenna, which has the characteristics of high storage ratio, high stiffness, high precision and controllable deployment.

[0005] The solution of the present invention is: A large deployable array antenna linkage-driven deployment mechanism includes two multi-layer antenna array structures, a satellite platform, and two sets of drive deployment components. The satellite platform is horizontally positioned. The two multi-layer antenna array structures are vertically folded and placed below the satellite platform. The two sets of drive deployment components are symmetrically arranged on the front and rear side walls of the satellite platform. Each set of drive deployment components includes a fixed truss, two short connecting rods, two long connecting rods, two synchronous gear seats, a drive synchronous belt, two follower synchronous belts, ten pulleys, and inter-plate hinges. The fixed truss includes long rods, diagonal rods, and support rods. The satellite platform is horizontally positioned; two multi-layer antenna arrays are vertically folded below the satellite platform; long rods, diagonal rods, and support rods are located on the sides of the satellite platform; one end of each of the two short connecting rods is connected via a pivot to the junction of one end of the long rod and the support rod; the other end of each of the two short connecting rods is connected via a pivot to one end of the long connecting rod; the other end of each of the two long connecting rods is connected to the multi-layer antenna array structure via a swivel hinge; two synchronization gear seats are symmetrically arranged on the middle side wall of the satellite platform; each of the two synchronization gear seats is connected via a pivot to the junction of one diagonal rod and one support rod; a total of 1 0 pulleys; the starting end of the driving synchronous belt is sequentially wound around the pulley at one end of the long rod, the pulley at the end of the inclined rod at the satellite boundary, the pulley at the end of the vertical tail of the synchronous gear seat, and the outer semi-circular contour of the synchronous gear seat, and wound symmetrically. The end of the driving synchronous belt is wound around the pulley at the other end of the long rod; two follower synchronous belts are symmetrically arranged; each follower synchronous belt is sequentially wound around the pulley at the junction of the ends of the long rod and the short connecting rod, and the pulley fixed to the center of the synchronous gear seat; the two follower synchronous belts start at the same position and adjust their length to keep the follower synchronous belts always taut; the inter-plate hinge is built into the junction of the two antenna multi-layer array structures and the satellite, and is not connected to the satellite platform; the two linear multi-layer array structures are connected by the inter-plate hinge to achieve relative rotation around the axis of the inter-plate hinge.

[0006] In the aforementioned large deployable array antenna linkage drive deployment mechanism, two sets of drive deployment components provide power for the two antenna multi-layer array structures to change from a fully retracted state to an deployed state, and control the deployment speed of the antenna multi-layer array structures.

[0007] In the aforementioned large deployable array antenna linkage-driven deployment mechanism, the two multi-layer array structures of the antennas in the retracted state are perpendicular to the bottom surface of the satellite platform.

[0008] In the aforementioned large deployable array antenna linkage drive deployment mechanism, four pulleys are installed on the long rod; pulleys are installed at one end of each of the two inclined rods; pulleys are installed at the junctions of the two inclined rods and the support rod; the pulleys rotate around their own axes and have a toothed structure.

[0009] In the aforementioned large deployable array antenna linkage drive deployment mechanism, the synchronous tooth seat is ear-shaped, and a pulley is installed at the vertical tail end of the synchronous tooth seat; two synchronous tooth seats are respectively located at the junction of the inclined rod and the support rod, and the two synchronous tooth seats are respectively fixedly connected to the pulleys at the two junctions, realizing rotation around the pulley axis.

[0010] In the aforementioned large deployable array antenna linkage drive deployment mechanism, one end of the short linkage and one end of the long linkage are connected by a rotating hinge and are symmetrically arranged on the drive deployment assembly; the other end of the short linkage is connected to the pulley in the middle of the long linkage; and the other end of the long linkage is connected to the multi-layer array structure of the antenna by a rotating hinge.

[0011] In the aforementioned large deployable array antenna linkage drive deployment mechanism, the inter-plate hinge is equipped with a self-locking function.

[0012] In the aforementioned large deployable array antenna linkage drive deployment mechanism, both the drive synchronous belt and the follower synchronous belt are toothed structures, which mesh with the toothed structures of the synchronous gear seat and pulley; the synchronous gear seat and pulley contain wound tracks to prevent the drive synchronous belt and the follower synchronous belt from becoming loose.

[0013] In the aforementioned large deployable array antenna linkage-driven deployment mechanism, the process of the two antenna multi-layer array structures moving from a vertical folded state to a fully deployed state is as follows: Under the action of the motor of the winding mechanism inside the satellite platform, the drive synchronous belt at both ends of the long rod is wound around the shaft of the winding mechanism; the overall length of the drive synchronous belt is shortened; as the teeth of the drive synchronous belt mesh with the semi-contour teeth of the synchronous gear seat and the teeth of the pulley at the end of the vertical tail, the left and right synchronous gear seats rotate relative to each other at the same time; at this time, the follower synchronous belt fixed to the pulley in the middle of the long rod and the central shaft of the synchronous gear seat begins to move in a circumferential ring, and drives the short connecting rod and the long connecting rod to move; the multi-layer array structure of the two antennas unfolds in an inverted V shape.

[0014] In the aforementioned large deployable array antenna linkage drive deployment mechanism, when the working surfaces of the two antenna multi-layer array structures are deployed to the same plane, the inter-plate hinges are locked in place, and at the same time, the two antenna multi-layer array structures are locked to the boundary of the satellite platform, improving the overall rigidity of the antenna; when the inter-plate hinges are locked in place, an electrical signal is transmitted to the tape winding mechanism controller to stop the tape winding mechanism from rotating.

[0015] The advantages of this invention compared to the prior art are: (1) This invention proposes a deployment technology of “single degree of freedom truss + rope drive”, which solves the contradiction between ultra-large size structure and high storage ratio. The envelope of the single degree of freedom truss system of the array is comparable to that of the star, and the motion envelope will not exceed the star, so it can be hidden in the star, realizing the folding and unfolding of the antenna array under the action of rope drive. (2) The truss system of the present invention can be directly connected to the complete antenna array interface, avoiding the design problem of occupying the antenna array by installing deployable hinges at the array boundary, and can effectively improve the antenna aperture index of the array. (3) The large deployable array antenna linkage drive deployment mechanism of the present invention provides deployment power and deployment stiffness for the antenna, and has the characteristics of high storage ratio, high stiffness, high precision and controllable deployment. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the retracted state of the linkage drive deployment mechanism for the large deployable array antenna of the present invention. Figure 2 This is a schematic diagram of the synchronous gear seat and pulley winding track of the present invention; Figure 3 This is a schematic diagram of the deployed state of the large deployable array antenna linkage drive deployment mechanism of the present invention. Detailed Implementation

[0017] The present invention will be further described below with reference to the embodiments.

[0018] This invention provides a large deployable array antenna linkage drive deployment mechanism, which provides deployment power and deployment stiffness for the antenna, and features high storage ratio, high stiffness, high precision, and controllable deployment.

[0019] Large deployable array antenna linkage drive deployment mechanism, such as Figure 1 As shown, it specifically includes two antenna multi-layer array structures 8, a satellite platform 10, and two sets of drive deployment assemblies; wherein, the satellite platform 10 is placed horizontally; the two antenna multi-layer array structures 8 are placed below the satellite platform 10 in a vertically folded state; the two sets of drive deployment assemblies are symmetrically arranged on the front and rear side walls of the satellite platform 10; each set of drive deployment assemblies includes a fixed truss 1, two short connecting rods 2, two long connecting rods 3, two synchronous gear seats 4, a drive synchronous belt 5, two follower synchronous belts 6, ten pulleys 7, and a plate hinge 9; the fixed truss 1 includes a long rod 101, a diagonal rod 102, and a support rod 103.

[0020] The satellite platform 10 is placed horizontally; two antenna multi-layer array structures 8 are vertically folded below the satellite platform 10; long rods 101, diagonal rods 102, and support rods 103 are arranged on the side of the satellite platform 10; one end of each of the two short connecting rods 2 is connected to the junction of one end of the long rod 101 and the support rod 103 via a pivot; the other end of each of the two short connecting rods 2 is connected to one end of each of the long connecting rods 3 via a pivot; the other end of each of the two long connecting rods 3 is connected to the antenna multi-layer array structure 8 via a swivel hinge; two synchronous gear seats 4 are symmetrically arranged on the middle side wall of the satellite platform 10; the two synchronous gear seats 4 are connected to the junction of one diagonal rod 102 and one support rod 103 via pivots; and the two ends of the long rod 101, the two pivots connecting the long rod 101 and the two short connecting rods 2, the two ends of the diagonal rods 102, and the vertical tail ends of the two synchronous gear seats 4 are also connected to the satellite platform 100. A total of 10 pulleys 7 are arranged; the starting end of the driving synchronous belt 5 is sequentially wound around the pulley 7 at one end of the long rod 101, the pulley 7 at the end of the inclined rod 102 at the satellite boundary, the pulley 7 at the end of the vertical tail of the synchronous tooth seat 4 and the outer semi-circular contour of the synchronous tooth seat 4, and is wound symmetrically. The end of the driving synchronous belt 5 is wound around the pulley 7 at the other end of the long rod 101; two follower synchronous belts 6 are arranged symmetrically; each follower synchronous belt 6 is sequentially wound around the pulley 7 at the junction of the long rod 101 and the short connecting rod 2 and the pulley 7 fixed in the center of the synchronous tooth seat 4; the two follower synchronous belts 6 have the same starting position and can adjust their length to keep the follower synchronous belts 6 in a taut state; the inter-plate hinge 9 is built into the junction of the two antenna multi-layer array structures 8 and the satellite, and is not connected to the satellite platform 10; the two linear multi-layer array structures 8 are connected by the inter-plate hinge 9 to achieve relative rotation around the axis of the inter-plate hinge 9. Two sets of drive deployment components provide power for the two multi-layer antenna array structures 8 to change from a fully retracted state to an deployed state, and control the deployment speed of the multi-layer antenna array structures 8. In the retracted state, the two multi-layer antenna array structures 8 are perpendicular to the bottom surface of the satellite platform 10.

[0021] In this invention, four pulleys 7 are installed on the long rod 101; pulleys 7 are installed at one end of each of the two inclined rods 102; pulleys 7 are installed at the junction of the two inclined rods 102 and the support rod 103; the pulleys 7 can rotate around the wheel axis and have a toothed structure.

[0022] like Figure 2 As shown, the synchronous gear seat 4 is ear-shaped, and a pulley 7 is installed at the vertical tail end of the synchronous gear seat 4; the two synchronous gear seats 4 are located at the junction of the inclined rod 102 and the support rod 103 respectively, and the two synchronous gear seats 4 are fixedly connected to the pulleys 7 at the two junctions respectively, so as to realize the rotation around the axis of the pulley 7.

[0023] One end of the short connecting rod 2 and one end of the long connecting rod 3 are connected by a rotating hinge and are symmetrically arranged on the drive deployment assembly; the other end of the short connecting rod 2 is connected to the pulley 7 in the middle of the long rod 101; the other end of the long connecting rod 3 is connected to the antenna multi-layer array structure 8 by a rotating hinge.

[0024] The inter-plate hinge 9 is equipped with a self-locking function.

[0025] Both the driving synchronous belt 5 and the follower synchronous belt 6 have toothed structures, which mesh with the toothed structures of the synchronous gear seat 4 and the pulley 7; the synchronous gear seat 4 and the pulley 7 contain a winding track to prevent the driving synchronous belt 5 and the follower synchronous belt 6 from becoming loose.

[0026] like Figure 3 As shown, the process of the two-antenna multi-layer array structure 8 changing from the vertical folded state to the fully deployed state is as follows: Under the action of the motor of the winding mechanism inside the satellite platform 10, the drive synchronous belt 5 at both ends of the long rod 101 is wound around the shaft of the winding mechanism; the overall length of the drive synchronous belt 5 is shortened; as the teeth of the drive synchronous belt 5 mesh with the semi-contour teeth of the synchronous gear seat 4 and the teeth of the pulley 7 at the end of the vertical tail, the left and right synchronous gear seats 4 rotate relative to each other at the same time; at this time, the follower synchronous belt 6, which is fixed at the central axis of the pulley 7 in the middle of the long rod 101 and the synchronous gear seat 4, begins to move in a circumferential ring, and drives the short connecting rod 2 and the long connecting rod 3 to move; the two antenna multi-layer array structures 8 unfold in an inverted V shape.

[0027] When the working surfaces of the two antenna multi-layer array structures 8 are unfolded to the same plane, the inter-plate hinge 9 is locked in place, and at the same time the boundaries of the two antenna multi-layer array structures 8 and the satellite platform 10 are locked, improving the overall rigidity of the antenna; when the inter-plate hinge 9 is locked in place, an electrical signal is transmitted to the tape winding mechanism controller to stop the tape winding mechanism from rotating.

[0028] The fixed truss 1 in this invention is a rod structure, composed of long rods 101, diagonal rods 102, and supporting rods 103. Pulley structures 7 are installed at 8 locations on the fixed truss 1, with 4 pulley structures 7 installed on the long rods 101, 1 pulley structure 7 installed at one end of each of the two diagonal rods 102, and pulley structures 7 installed at the junctions of the two diagonal rods 102 and the supporting rods 103. The pulleys 7 are rotatable around their axles and contain toothed structures. Synchronous gear seats 4 are ear-shaped, with pulley structures 7 installed at their vertical tail ends. Two synchronous gear seats 4 are located at the junctions of the diagonal rods 102 and the supporting rods 103, and are fixedly connected to the pulleys 7 at the two junctions, and are rotatable around their axles.

[0029] One end of the short connecting rod 2 and the long connecting rod 3 are connected to each other by a rotating hinge and are symmetrically arranged on the drive deployment mechanism. The other end of the short connecting rod 2 is fixedly connected to the pulley 7 in the middle of the long rod 101, and the other end of the long connecting rod 3 is connected to the antenna multi-layer array structure 8 by a rotating hinge. The antenna multi-layer array structure 8 is symmetrically arranged below the satellite platform 10. The two antenna multi-layer array structures 8 are connected by an inter-plate hinge 9, and the inter-plate hinge 9 has a self-locking function.

[0030] The driving synchronous belt 5 and the follower synchronous belt 6 have a toothed structure, which can mesh with the toothed structures of the synchronous gear seat 4 and the pulley 7. Furthermore, the synchronous gear seat 4 and the pulley 7 contain a winding track to prevent the synchronous belt from loosening. Figure 2 As shown, the drive synchronous belt 5 is sequentially wound around the pulley 7 at the end of the long rod 101, the pulley 7 at the end of the short connecting rod 2, the pulley 7 at the tail end of the synchronous gear seat 4, and the outer semi-circular contour of the synchronous gear seat 4, and is wound symmetrically. The drive synchronous belt 5 has a winding mechanism installed at the pulley 7 structures at both ends of the long rod 101, and is placed inside the satellite platform 10. The follower synchronous belt 6 is sequentially wound around the pulley 7 in the middle of the long rod 101 and the pulley 7 fixed to the synchronous gear seat 4, and its length is adjustable to keep the follower synchronous belt 6 in a taut state.

[0031] During the process of a large deployable array antenna moving from a fully retracted state to a fully deployed state, such as... Figure 3 As shown, firstly, under the action of the winding mechanism motor inside the satellite platform 10, the driving synchronous belt 5 at both ends of the long rod 101 winds around the winding mechanism shaft, shortening the overall length of the driving synchronous belt 5. Since the teeth of the driving synchronous belt 5 mesh with the semi-contour teeth of the synchronous gear seat 4 and the teeth of the pulley 7 at the end of the vertical tail, the left and right synchronous gear seats 4 rotate relative to each other simultaneously. At this time, the follower synchronous belt 6, which connects the pulley 7 in the middle of the long rod 101 and the pulley 7 fixed at the central axis of the synchronous gear seat 4, begins circumferential circular motion, driving the short connecting rod 2 and the long connecting rod 3 to move. The antenna multi-layer array structure 8 also unfolds in an inverted "V" shape. When the working surfaces of the two antenna multi-layer array structures 8 unfold to the same plane, the inter-plate hinge 9 locks in place, and simultaneously the boundaries of the two antenna multi-layer array structures 8 and the satellite platform 10 are locked, improving the overall rigidity of the antenna. When the inter-plate hinge 9 locks in place, an electrical signal is transmitted to the winding mechanism controller to stop the winding mechanism from rotating.

[0032] This invention proposes a deployment technology of "single degree of freedom truss + rope drive", which solves the contradiction between ultra-large size structure and high storage ratio. The envelope of the single degree of freedom truss system of the array is comparable to that of the star, and the motion envelope will not exceed the star, so it can be hidden in the star. This realizes the folding and unfolding of the antenna array under the action of rope drive.

[0033] The truss system of the present invention can be directly connected to the complete antenna array interface, avoiding the design problem of installing deployable hinges at the array boundary and occupying the antenna array surface, and can effectively improve the electrical aperture index of the array antenna.

[0034] The large deployable array antenna linkage drive deployment mechanism of the present invention provides deployment power and deployment stiffness for the antenna, and has the characteristics of high storage ratio, high stiffness, high precision and controllable deployment.

[0035] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A large deployable array antenna link drive deployment mechanism, characterized by: The application relates to a satellite antenna structure, which comprises two antenna multilayer array structures (8), a satellite platform (10) and two groups of driving and unfolding assemblies; wherein the satellite platform (10) is horizontally placed; the two antenna multilayer array structures (8) are placed in a vertical and folded state below the satellite platform (10); the two groups of driving and unfolding assemblies are symmetrically arranged at the front and rear sidewalls of the satellite platform (10); each group of driving and unfolding assemblies comprises a fixed truss (1), two short connecting rods (2), two long connecting rods (3), two synchronous tooth seats (4), a driving synchronous belt (5), two follow-up synchronous belts (6), ten belt pulleys (7) and an interplate hinge (9); the fixed truss (1) comprises a long rod piece (101), an inclined rod piece (102) and a supporting rod piece (103); The satellite platform (10) is horizontally placed; the two antenna multilayer array structures (8) are placed in a vertical and folded state below the satellite platform (10); the long rod piece (101), the inclined rod piece (102) and the supporting rod piece (103) are arranged at the side of the satellite platform (10); one end of each of the two short connecting rods (2) is connected to the intersection of one end of the long rod piece (101) and the supporting rod piece (103) through a rotating shaft; the other end of each of the two short connecting rods (2) is connected to one end of the long connecting rod (3) through a rotating shaft; the other end of each of the two long connecting rods (3) is connected to the antenna multilayer array structure (8) through a rotary hinge; the two synchronous tooth seats (4) are symmetrically arranged at the middle sidewalls of the satellite platform (10); the two synchronous tooth seats (4) are connected to the intersection of one inclined rod piece (102) and one supporting rod piece (103) through rotating shafts; a total of ten belt pulleys (7) are arranged at the two ends of the long rod piece (101), the two rotating shafts where the long rod piece (101) is connected to the two short connecting rods (2), the two ends of the two inclined rod pieces (102) and the vertical tail ends of the two synchronous tooth seats (4); the starting end of the driving synchronous belt (5) is sequentially wound on the belt pulley (7) at one end of the long rod piece (101), the belt pulley (7) at the end of the star boundary of the inclined rod piece (102), the belt pulley (7) at the vertical tail end of the synchronous tooth seat (4) and the outer edge semicircular contour of the synchronous tooth seat (4) and is symmetrically wound; the end of the driving synchronous belt (5) is wound on the belt pulley (7) at the other end of the long rod piece (101); the two follow-up synchronous belts (6) are symmetrically arranged; each follow-up synchronous belt (6) is sequentially wound on the belt pulley (7) at the intersection of the end of the long rod piece (101) and the short connecting rod (2) and the belt pulley (7) fixedly connected to the center of the synchronous tooth seat (4); the starting positions of the two follow-up synchronous belts (6) are the same and the lengths of the two follow-up synchronous belts (6) can be adjusted, so that the follow-up synchronous belts (6) are always in a tension state; the interplate hinge (9) is arranged in the intersection of the two antenna multilayer array structures (8) and the star body and is not connected to the satellite platform (10); the two antenna multilayer array structures (8) are connected through the interplate hinge (9) and can relatively rotate around the axis of the interplate hinge (9).

2. A large deployable planar antenna linkage drive deployment mechanism according to claim 1, characterized in that: The two groups of driving and unfolding assemblies provide power for changing the two antenna multilayer array structures (8) from a completely folded state to an unfolded state and control the unfolding speed of the antenna multilayer array structures (8).

3. A large deployable planar antenna linkage drive deployment mechanism according to claim 1, characterized in that: The two antenna multilayer array structures (8) in the folded state are perpendicular to the bottom surface of the satellite platform (10).

4. A large deployable planar antenna linkage drive deployment mechanism according to claim 1, characterized in that: Four pulleys (7) are mounted on the long rod member (101); one end of each of the two inclined rod members (102) is mounted with a pulley (7); the intersection of the two inclined rod members (102) and the support rod member (103) is respectively mounted with a pulley (7); the pulleys (7) are capable of rotating around the wheel shaft and have a tooth structure.

5. A large deployable planar antenna linkage drive deployment mechanism according to claim 4 wherein: The synchronous tooth seat (4) is in the shape of an ear, and a pulley (7) is mounted at the trailing end of the synchronous tooth seat (4); the two synchronous tooth seats (4) are respectively located at the intersections of the inclined rod members (102) and the support rod member (103), and the two synchronous tooth seats (4) are respectively fixedly connected with the pulleys (7) at the two intersections, so as to realize rotation around the pulley (7) shaft.

6. A large deployable planar antenna linkage drive deployment mechanism according to claim 5 wherein: One end of the short connecting rod (2) and one end of the long connecting rod (3) are connected through a rotary hinge, and are symmetrically arranged on the driving and unfolding assembly; the other end of the short connecting rod (2) is butted against the pulley (7) at the middle of the long rod member (101); the other end of the long connecting rod (3) is connected with the antenna multilayer array structure (8) through a rotary hinge.

7. A large deployable planar antenna linkage drive deployment mechanism according to claim 6, characterised in that: The inter-plate hinge (9) is provided with a self-locking function.

8. A large deployable planar antenna linkage drive deployment mechanism according to claim 6, characterized in that: The driving synchronous belt (5) and the following synchronous belt (6) are both tooth structures, which are engaged with the tooth structures of the synchronous tooth seat (4) and the pulley (7); the synchronous tooth seat (4) and the pulley (7) have a winding track, so as to prevent the driving synchronous belt (5) and the following synchronous belt (6) from loosening.

9. A large deployable planar antenna linkage drive deployment mechanism according to claim 8, characterised in that: The process of the two antenna multilayer array structures (8) from the vertical folded state to the fully unfolded state is as follows: Under the action of the motor of the satellite platform (10) inside the winding mechanism, the driving synchronous belt (5) at both ends of the long rod member (101) is wound on the winding mechanism shaft; the overall length of the driving synchronous belt (5) is shortened; due to the engagement of the tooth structure of the driving synchronous belt (5) with the half-profile tooth structure of the synchronous tooth seat (4) and the tooth structure of the pulley (7) at the trailing end, the left and right synchronous tooth seats (4) simultaneously rotate relative to each other; at this time, the following synchronous belt (6) fixedly connected at the center shaft of the synchronous tooth seat (4) and the pulley (7) connected with the middle of the long rod member (101) starts to move in a circumferential ring shape, and drives the short connecting rod (2) and the long connecting rod (3) to move; the two antenna multilayer array structures (8) are unfolded in an inverted V shape.

10. A large deployable planar antenna linkage drive deployment mechanism according to claim 9, characterized in that: When the working surfaces of the two antenna multilayer array structures (8) are unfolded to the same plane, the inter-plate hinge (9) is locked in place, and at the same time, the two antenna multilayer array structures (8) are locked with the boundary of the satellite platform (10), so as to improve the overall stiffness of the antenna; when the inter-plate hinge (9) is locked in place, the electrical signal is transmitted to the winding mechanism controller to stop the rotation of the winding mechanism.

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