A two-dimensional deployment mechanism and deployment method based on solid surface antenna

Abstract

The present invention discloses a two-dimensional deployment mechanism and deployment method based on a fixed surface antenna, which belongs to the technical field of deployment mechanism, and includes three groups of antenna reflection surface submodules, five pairs of locking mechanisms, four groups of folding and deployment mechanisms, a release mechanism and a guide rail device; each group of antenna reflection surface submodules includes five sections of antenna surface units; wherein there is no connection relationship between the antenna surface units, and the position of the antenna reflection surface is limited by the guide rail device fixed on the side of the reflection surface, and the five antenna reflection surfaces are not locked until the second step of deployment is completed. The deployment mechanism mainly acts in the first deployment, and it is connected to the satellite body. After the first step of deployment is completed, the space robot arm moves the antenna group after the first step of deployment to the waiting position, and then performs the second deployment. The present invention realizes the two-dimensional deployment of the fixed surface antenna, and can realize the simultaneous flipping and locking of multiple groups of antenna reflection surfaces, meeting the high-precision performance requirements of the overall antenna reflection surface.

Description

Technical Field

[0001] The present invention relates to the technical field of deployment mechanisms, and in particular to a structure and mechanism based on deployment of a fixed surface antenna. Background Art

[0002] Compared with inflatable and metal mesh antennas, solid reflector antennas are suitable for use on satellites with small apertures and high operating frequencies, and their surface accuracy is more in line with high-precision requirements. Solid surface antennas have the advantages of high surface accuracy, high rigidity, high reliability, and good thermal stability, and have broad development potential and application background. Solid surface antennas need to be folded into a smaller volume during the launch phase, and need to be unfolded to a larger unfolding area through an unfolding mechanism during in-orbit operation. Therefore, the unfolding mechanism of the solid surface antenna is a key component to ensure the normal operation of the satellite.

[0003] With the development of satellite technology, the application field of space antennas is becoming increasingly broad, and the complexity of tasks is gradually increasing. The design of satellite-borne antennas pays more attention to the design requirements of multi-band, high precision, and large capacity. Therefore, the design of satellite antennas has gradually become more complex. However, due to the limitations of rocket carrying capacity, economy and other factors, the antenna structure needs to be light and small in size. Based on the above contradictions, modular and scalable antenna technology has emerged and developed rapidly, and has become an important way to meet the needs of large-caliber, high-precision, and lightweight satellite antennas.

[0004] At present, there is still a blank in the deployment method, structure and mechanism of fixed-surface antennas that can realize the simultaneous flipping and locking of multiple sets of antenna reflective surfaces. Summary of the invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide an unfolding mechanism for a parabolic cylindrical solid-surface antenna, to realize the two-dimensional unfolding of the solid-surface antenna, to realize the simultaneous flipping and locking of multiple groups of antenna reflective surfaces, and to meet the high-precision performance requirements of the overall antenna reflective surface.

[0006] A two-dimensional deployment mechanism based on a fixed surface antenna, characterized in that the mechanism includes three groups of antenna reflection surface submodules, five pairs of locking mechanisms, four groups of folding and deployment mechanisms, a release mechanism and a guide rail device; the main part of each group of antenna reflection surface submodules is five identical antenna surface units.

[0007] The three groups of antenna reflection surface submodules are arranged in a stacked manner, and are respectively: A antenna submodule, B antenna submodule, and C antenna submodule from top to bottom; the A antenna submodule, B antenna submodule, and C antenna submodule are connected by four groups of folding and unfolding mechanisms; two folding and unfolding mechanisms are laid at the concave connection between the B antenna submodule and the C antenna submodule; two folding and unfolding mechanisms are laid at the convex connection between the A antenna submodule and the B antenna submodule; according to the XYZ axis coordinate system, the folding and unfolding mechanisms at each connection are symmetrically distributed on the XZ plane of the coordinate system; the B antenna submodule is symmetrically distributed at both ends along the X-axis direction of the coordinate system, and five pairs of locking mechanisms are laid from top to bottom in the grooves at both ends.

[0008] The A antenna submodule and the C antenna submodule are respectively provided with five groups of locks from top to bottom on the side close to the folding and unfolding mechanism. The locks are located on the mid-vertical plane of each antenna surface unit and are fixed to the antenna surface unit for aligning and connecting the locking mechanism; the A antenna submodule and the C antenna submodule are respectively provided with five groups of release mechanisms and guide rail devices and a group of motor pulleys from top to bottom on the side away from the folding and unfolding mechanism, and a pulley block is arranged on the motor pulley.

[0009] There is no connection relationship inside the antenna surface unit. The position of the antenna surface unit is limited by the release mechanism and guide rail device fixed to the side of the antenna surface unit on the A antenna submodule and the C antenna submodule, and the locking and deployment of the antenna surface unit are controlled by the release mechanism and guide rail device, the motor pulley and the pulley group.

[0010] Furthermore, the folding and unfolding mechanism is composed of a rotating arm, a fixed arm, a large motor and a rotating shaft; the fixed arm of the folding and unfolding mechanism is fixedly connected to the surface of the B antenna submodule, and the rotating arm is fixedly connected to the surfaces of the A antenna submodule and the C antenna submodule; the rotating arm and the fixed arm are hinged through a rotating shaft, and a driving device, i.e., a large motor, is provided at the end of the rotating shaft; the folding and unfolding mechanism is used for flipping and docking between antenna submodules, and the large motor installed on the folding and unfolding mechanism plays a major flipping role.

[0011] Furthermore, the release mechanism and guide rail device are mainly composed of a support frame, a slide groove, a small pulley, a positioning hole, a calibration key, a connecting hole, and a spring lock tongue;

[0012] The slide groove and the small pulley are respectively arranged on the upper convex surface and the lower concave surface of the support frame; a pair of pulley groups are distributed on both sides of the support frame and are fixedly connected to the support frame; positioning holes and calibration keys, connecting holes and spring lock tongues are respectively provided on the square planes at both ends of the support frame, which are used for the connection between the release mechanism and the guide rail device after the antenna mechanism is unfolded; five groups of release mechanisms and guide rail devices are stacked in sequence from top to bottom, and their internal connection method consists of five of the pulley groups, a group of ropes and a small motor; the small motor is located on the bottom support frame and is used to tighten the rope; the rope is wound around the pulleys of each pulley group, the upper end of the rope is fixed to the pulley of the release mechanism and the guide rail device on the top layer, and the lower end of the rope is wound around the motor pulley, and its retraction and release are controlled by the rotation of the small motor.

[0013] Furthermore, the small motor at the lower end of the release mechanism and the guide rail device tightens the rope by rotating, thereby pulling the release mechanism, the guide rail device and the antenna surface unit to slide along the slide groove; the upper end release mechanism, the guide rail device and the antenna surface unit slide to the critical position at the end of the slide groove opening, and continue to slide downward along the plane perpendicular to the slide groove on the lower end support frame; a pair of connecting holes and a pair of calibration keys are located on the vertical plane, and the connecting holes and the calibration keys are symmetrically distributed with the median vertical plane of the vertical plane as a reference; a pair of connecting holes and a pair of spring locking tongues are distributed on the vertical plane on the starting end side of the slide groove; the positioning holes and the spring locking tongues are symmetrically distributed with the median vertical plane as a reference; after the release mechanism, the guide rail device and the antenna surface unit slide to a predetermined position, a pair of spring locking tongues extend into the corresponding connecting holes and lock, and at this time, all the calibration keys should be located in the corresponding positioning holes.

[0014] The present invention also discloses a deployment method based on a two-dimensional deployment mechanism of a fixed surface antenna, characterized in that the deployment method is step-by-step deployment, and the deployment process is divided into two steps: the first step is to realize the docking deployment between the reflective surface submodules through the operation of the folding deployment mechanism, and the second step is to realize the sliding deployment of all antenna surface units by working through a small motor and a motor pulley; before the fixed surface antenna is deployed, the deployment mechanism is fixed on the B antenna submodule and fixedly connected to the satellite body, and explosive bolts are provided at the connection between the antenna submodules as a storage frame to limit the movement of the antenna; during the antenna deployment process, the explosive bolts are automatically blown off, and the motor of the folding deployment mechanism starts to operate to control the rotational docking between the antenna submodules; the steel wire rope is pulled by the deployment mechanism installed on the satellite body to assist the A antenna submodule and the C antenna submodule to rotate and dock with the B antenna submodule; in order to ensure the overall surface accuracy of the antenna, the locking mechanisms located between the A antenna submodule and the B antenna submodule, and between the B antenna submodule and the C antenna submodule are locked after the docking is completed, and the three groups of antenna submodules form a whole, ready for the second stage deployment; at this point, the rotational docking deployment between the antenna submodules is completed;

[0015] In the second step of deployment, the small motor starts to work, controlling the motor pulley to slowly tighten the rope wrapped around the pulley group in each release mechanism and the guide rail device, so that the surface units from top to bottom are deployed along the slide grooves in each release mechanism and the guide rail device; all surface units and the release mechanism and the guide rail device reach the predetermined position in the above-mentioned deployment steps and are locked by the motor pulley; at this point, the fixed surface antenna is fully deployed.

[0016] Further, the first step of the expansion process is specifically as follows:

[0017] When the large motor drives the A antenna submodule and the C antenna submodule to rotate and dock, that is, all the surface units of the A antenna submodule or the C antenna submodule flip over together, when the upper convex top antenna surface unit of the A antenna submodule or the C antenna submodule flips to a position flush with the top antenna surface unit of the B antenna submodule, the lock is connected to the locking mechanism. At this time, the three flush surface units on each layer form an antenna sub-reflector surface; the limit brake is performed by the limit bolts installed on the unfolding frame in the unfolding mechanism. At this point, the flipping action is completed, and the locking mechanism is locked with the lock: when the locks fixed on the A antenna submodule and the C antenna submodule are respectively rotated and docked to the locks on both sides of the B antenna submodule When the locking mechanism is in the lock shell position, the lock buckle squeezes the pressing block in the locking mechanism to make it move into the lock buckle to a pressed state, and the lock buckle and the lock shell are locked in six directions through the friction angle locking of the lock tongue in the locking mechanism and the squeezing of the pressing block on the lock buckle, thereby achieving high-precision locking between the antenna reflecting surfaces; after the A antenna submodule, the B antenna submodule, and the C antenna submodule are docked and locked, the antenna sub-reflecting surface needs to be unfolded. At this time, the unfolding mechanism pulls all the surface units out of the antenna submodule after the first stage of unfolding through the action of the small motor, completes the release of the antenna reflecting surface, and prepares for the unfolding of the antenna reflecting surface, i.e., the second step of unfolding.

[0018] Further, the second step of the expansion process is specifically as follows:

[0019] Guide rail devices are fixed on the outside of the A antenna submodule and the C antenna submodule respectively so that each antenna reflector can move relative to each other; after the first stage of deployment, the small motors and motor pulleys at the lower ends of the two sides of the antenna pull the ropes on both sides respectively, and the guide rail device starts to move relative to each other under the traction drive, thereby driving the synchronous deployment of the antenna reflector; the deployment speed of the antenna reflector can also be controlled by controlling the speed of tightening the rope; when the deployment reaches a predetermined position, the locking device between each two antenna sub-reflectors is locked, and the locking device consists of a positioning hole, a calibration key, a connecting hole, and a spring lock tongue; during the second stage of deployment, the spring mechanism is used to buffer the guide rail device before locking until it stops, thereby completing the entire process of antenna deployment.

[0020] The beneficial effects of the present invention compared with the prior art are:

[0021] Since the solid surface antenna has the characteristics of high rigidity, the solid surface antenna design in the field of large-scale deployment antennas requires it to have the properties of light weight and large caliber. For the general deployment method of existing solid surface antennas, large solid surface antennas will be subjected to very large bending moments during the deployment process, which is a great test for the bending strength, material properties and fatigue life of the antenna. The deployment method described in the present invention aims to modularize large-caliber solid surface antennas, greatly reduce the bending moments of the antenna reflective surface during the deployment process, and can well improve the design space and safety margin under various indicators of the antenna, and can well ensure the reliability of the antenna while reducing costs and reducing the storage space required for antenna transmission. In addition, compared with the lightweight design of the general modular antenna that can be deployed autonomously, the design of the two-dimensional deployment mechanism ensures that the deployed solid surface antenna is detectable and controllable at any deployment stage, can meet the use requirements of various carriers in various mission environments, and significantly improves the success rate and reliability of antenna deployment. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the folded structure of the parabolic antenna in the present invention;

[0023] Figure 2 This is a schematic diagram of the first step of the present invention;

[0024] Figure 3 It is a schematic diagram of the second step of the unfolding process in the present invention;

[0025] Figure 4 It is a schematic diagram of the second step of the present invention;

[0026] Figure 5 It is a schematic diagram of the structure of the release mechanism and the guide rail device in the present invention.

[0027] Among them, 1-antenna surface unit, 2-unfolding mechanism, 3-releasing mechanism and guide rail device, 4-small motor, 5-motor pulley, 6-pulley block, 7-locking mechanism, 8-lock buckle, 9-large motor, 10-rope, 11-antenna submodule, 12-antenna submodule, 13-antenna submodule, 14-rotating arm, 15-fixed arm, 16-rotating shaft, 17-support frame, 18-slide, 19-small pulley, 20-positioning hole, 21-calibration key, 22-connecting hole, 23-spring lock tongue. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical solution and effect of the present invention clearer and more specific, the present invention is further described in detail by enumerating examples below. It should be noted that the specific implementation described here is only used to explain the present invention and is not used to limit the present invention.

[0029] like Figure 1 As shown, the mechanism of the present invention includes three groups of antenna reflection surface submodules, five pairs of locking mechanisms 7, four groups of folding and unfolding mechanisms 2, a release mechanism and a guide rail device 3; the main part of each group of antenna reflection surface submodules is five identical antenna surface units 1. The three groups of antenna reflection surface submodules are arranged in a stacked manner, from top to bottom, respectively: A antenna submodule 11, B antenna submodule 12, C antenna submodule 13.

[0030] The A antenna submodule 11, the B antenna submodule 12, and the C antenna submodule 13 are connected by four groups of folding and unfolding mechanisms 2; two folding and unfolding mechanisms 2 are laid at the concave connection between the B antenna submodule 12 and the C antenna submodule 13; and two folding and unfolding mechanisms 2 are laid at the convex connection between the A antenna submodule 11 and the B antenna submodule 12.

[0031] According to the XYZ axis coordinate system, the folding and unfolding mechanisms 2 at each connection are symmetrically distributed on the left and right sides of the XZ plane of the coordinate system; the B antenna submodule 12 is symmetrically distributed at both ends along the X-axis direction of the coordinate system, and five pairs of locking mechanisms 7 are laid from top to bottom in the grooves at both ends; the A antenna submodule 11 and the C antenna submodule 13 are respectively provided with five groups of lock buckles 8 from top to bottom on one side close to the folding and unfolding mechanism 2, and the lock buckles 8 are located on the median vertical plane of each antenna surface unit 1 and are fixed to the antenna surface unit 1, and are used to align and connect the locking mechanism 7.

[0032] The A antenna submodule 11 and the C antenna submodule 13 are respectively provided with five sets of release mechanisms and guide rail devices 3 and a set of motor pulleys 5 from top to bottom on the side away from the folding and unfolding mechanism 2, and a pulley group 6 is provided on the motor pulley 5; the antenna surface unit 1 has no internal connection relationship, and the position of the antenna surface unit 1 is limited by the release mechanism and guide rail device 3 fixed to the side of the antenna surface unit 1 on the A antenna submodule 11 and the C antenna submodule 13, and the locking and unfolding of the antenna surface unit 1 are controlled by the release mechanism and guide rail device 3, the motor pulley 5 and the pulley group 6.

[0033] like Figure 2 The folding and unfolding mechanism 2 shown in the figure is composed of a rotating arm 14, a fixed arm 15, a large motor 9 and a rotating shaft 16; the fixed arm 15 of the folding and unfolding mechanism 2 is fixedly connected to the surface of the B antenna submodule 12, and the rotating arm 14 is fixedly connected to the surfaces of the A antenna submodule 11 and the C antenna submodule 13; the rotating arm 14 and the fixed arm 15 are hinged through the rotating shaft 16, and a driving device, namely the large motor 9, is provided at the end of the rotating shaft 16; the folding and unfolding mechanism 2 is used for flipping and docking between antenna submodules, and the large motor 9 installed on the folding and unfolding mechanism 2 plays a major flipping role.

[0034] like Figure 5As shown, the release mechanism and the guide rail device 3 are mainly composed of a support frame 17, a slide groove 18, a small pulley 19, a positioning hole 20, a calibration key 21, a connecting hole 22, and a spring lock tongue 23; the slide groove 18 and the small pulley 19 are respectively arranged on the upper convex surface and the lower concave surface of the support frame 17, and a pair of pulley groups 6 are distributed on both sides of the support frame 17 and fixedly connected to the support frame 17; the square planes at both ends of the support frame 17 are respectively provided with positioning holes 20 and calibration keys 21, connecting holes 22 and spring lock tongues 23, which are used for the antenna mechanism to be deployed after the antenna mechanism is deployed. The connection between the release mechanism and the guide rail device 3; five groups of release mechanisms and guide rail devices 3 are stacked in sequence from top to bottom, and their internal connection method consists of five pulley groups 6, a group of ropes 10 and a small motor 4; the small motor 4 is located on the bottom support frame 17, and is used to tighten the rope 10; the rope 10 is wound around the pulleys of each pulley group 6, and the upper end of the rope 10 is fixed to the pulley of the release mechanism and guide rail device 3 on the top layer, and the lower end of the rope 10 is wound around the motor pulley 5, and its retraction and release are controlled by the rotation of the small motor 4.

[0035] The small motor 4 at the lower end of the release mechanism and the guide rail device 3 tightens the rope 10 by rotating, thereby pulling the release mechanism and the guide rail device 3 and the antenna surface unit 1 to slide along the slide groove 18; the upper end release mechanism and the guide rail device 3 and the antenna surface unit 1 slide to the critical position at the end of the slide groove opening, and continue to slide downward along the plane perpendicular to the slide groove 18 on the lower end support frame 17; a pair of connecting holes 22 and a pair of calibration keys 21 are located on the vertical plane, and the connecting holes 22 and the calibration keys 21 are symmetrically distributed with the median vertical plane of the vertical plane as the reference; a pair of connecting holes 22 and a pair of spring lock tongues 23 are distributed on the vertical plane on the starting end side of the slide groove; the positioning holes 20 and the spring lock tongues 23 are symmetrically distributed with the median vertical plane as the reference; after the release mechanism and the guide rail device 3 and the antenna surface unit 1 slide to the predetermined position, a pair of spring lock tongues 23 extend into the corresponding connecting holes 22 and lock, and at this time, all the calibration keys 21 should be located in the corresponding positioning holes 20.

[0036] like Figure 3~4 As shown, the unfolding method is step-by-step unfolding, and the unfolding process is divided into two steps: the first step is to realize the docking and unfolding between the reflecting surface submodules through the folding and unfolding mechanism 2, and the second step is to realize the flat sliding unfolding of all antenna surface units 1 through the small motor 4 and the motor pulley 5.

[0037] The first step of the unfolding process is specifically as follows: when the large motor 9 drives the A antenna submodule 11 and the C antenna submodule 13 to rotate and dock, that is, all the surface units 1 of the A antenna submodule 11 or the C antenna submodule 13 flip over together, when the upper convex top antenna surface unit 1 of the A antenna submodule 11 or the C antenna submodule 13 flips to a position flush with the top antenna surface unit 1 of the B antenna submodule 12, the lock 8 is connected to the locking mechanism 7. At this time, the three flush surface units 1 on each layer form an antenna sub-reflection surface; the limit brake is performed by the limit bolts installed on the unfolding frame in the unfolding mechanism, and the flipping action is completed. The locking mechanism 7 is locked with the lock 8: when the locks 8 fixed on the A antenna submodule 11 and the C antenna submodule 13 are rotated respectively When the B antenna submodule 12 is docked to the lock shell position of the locking mechanism 7 on both sides, the lock buckle 8 squeezes the pressing block in the locking mechanism 7 to make it move into the lock buckle to a pressed state. The friction angle locking of the lock buckle by the lock tongue in the locking mechanism 7 and the squeezing of the lock buckle by the pressing block realize the locking in six directions between the lock buckle and the lock shell, thereby realizing high-precision locking between the antenna reflecting surfaces. After the A antenna submodule 11, the B antenna submodule 12, and the C antenna submodule 13 are docked and locked, the antenna sub-reflecting surfaces need to be unfolded. At this time, the unfolding mechanism pulls all the surface units out of the antenna submodule after the first stage of unfolding through the action of the small motor, completes the release of the antenna reflecting surface, and prepares for the unfolding of the antenna reflecting surface, i.e., the second step of unfolding.

[0038] The second step of the deployment process is as follows: the outer sides of the A antenna submodule 11 and the C antenna submodule 13 are respectively fixed with a guide rail device 3 so that each antenna reflection surface can move relative to each other; Figure 3 As shown, after the first stage of deployment, the small motors 4 and the motor pulleys 5 at the lower ends of both sides of the antenna pull the ropes 10 on both sides respectively, and the guide rail device starts to move relative to each other under the traction drive, thereby driving the synchronous deployment of the antenna reflector; the deployment speed of the antenna reflector can also be controlled by controlling the speed of tightening the rope; when the deployment reaches a predetermined position, the locking device between each two sections of the antenna sub-reflector is locked, and during the second stage of deployment, the spring mechanism is used to buffer the guide rail device 3 before locking until it stops, thereby completing the entire process of antenna deployment.

[0039] Before the fixed surface antenna is deployed, the deployment mechanism is fixed on the B antenna submodule 12 and fixedly connected to the satellite body, and explosive bolts are provided at the connection between the antenna submodules as a storage frame to limit the movement of the antenna; during the antenna deployment process, the explosive bolts are automatically blown off, and the motor of the folding and deployment mechanism starts to operate to control the rotational docking between the antenna submodules; the steel wire rope is pulled by the deployment mechanism installed on the satellite body to assist the A antenna submodule 11 and the C antenna submodule 13 to rotate and dock with the B antenna submodule 12; in order to ensure the overall surface accuracy of the antenna, the locking mechanisms located between the A antenna submodule 11 and the B antenna submodule 12, and between the B antenna submodule 12 and the C antenna submodule 13 are locked after the docking is completed, and the three groups of antenna submodules form a whole, ready for the second stage of deployment; at this point, the rotational docking deployment between the antenna submodules is completed.

[0040] In the second step of deployment, the small motor 4 starts to work, controlling the motor pulley 5 to slowly tighten the rope 10 wound around the pulley group 6 in each release mechanism and the guide rail device 3, thereby allowing the surface unit 1 from top to bottom to be deployed along the slide groove 18 in each release mechanism and the guide rail device 3; all surface units 1 and the release mechanism and the guide rail device 3 reach the predetermined position according to the deployment steps described in the present invention and are locked by the motor pulley 5; at this point, the full deployment of the fixed surface antenna is completed.

[0041] The present invention takes 3 antenna submodules and 5 sub-reflection surfaces as an example. According to actual requirements, the number of antenna submodules and sub-reflection surfaces is not limited thereto, and the deployment principle is the same as the deployment principle of each stage described in the present invention. In addition, the above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements can be made without departing from the principle of the present invention, and these improvements should also be regarded as the protection scope of the present invention.

Claims

1. A two-dimensional deployment mechanism based on a fixed surface antenna, characterized in that: The mechanism comprises three groups of antenna reflection surface submodules, five pairs of locking mechanisms (7), four groups of folding and unfolding mechanisms (2), a release mechanism and a guide rail device (3); the main body of each group of antenna reflection surface submodules is five identical antenna surface units (1); The three groups of antenna reflection surface submodules are arranged in a stacked manner, and from top to bottom are: A antenna submodule (11), B antenna submodule (12), and C antenna submodule (13); The A antenna submodule (11), the B antenna submodule (12), and the C antenna submodule (13) are connected by four groups of folding and unfolding mechanisms (2); wherein two folding and unfolding mechanisms (2) are laid at the concave connection between the B antenna submodule (12) and the C antenna submodule (13); and two folding and unfolding mechanisms (2) are laid at the convex connection between the A antenna submodule (11) and the B antenna submodule (12); According to the XYZ axis coordinate system, the folding and unfolding mechanisms (2) at each connection are symmetrically distributed on the XZ plane of the coordinate system; the B antenna submodule (12) is symmetrically distributed at both ends along the X axis direction of the coordinate system, and five pairs of locking mechanisms (7) are laid from top to bottom in the grooves at both ends; The A antenna submodule (11) and the C antenna submodule (13) are respectively provided with five groups of lock buckles (8) from top to bottom on one side close to the folding and unfolding mechanism (2), wherein the lock buckles (8) are located on the mid-vertical plane of each antenna surface unit (1) and are fixedly connected to the antenna surface unit (1) and are used for aligning and connecting the locking mechanism (7); The A antenna submodule (11) and the C antenna submodule (13) are respectively provided with five sets of release mechanisms and guide rail devices (3) and a set of motor pulleys (5) from top to bottom on a side away from the folding and unfolding mechanism (2), and a pulley block (6) is provided on the motor pulley (5); The antenna surface unit (1) has no internal connection relationship, and the position of the antenna surface unit (1) is limited by a release mechanism and a guide rail device (3) fixedly connected to the side of the antenna surface unit (1) on the A antenna submodule (11) and the C antenna submodule (13), and the locking and unfolding of the antenna surface unit (1) are controlled by the release mechanism and the guide rail device (3), the motor pulley (5) and the pulley group (6); The folding and unfolding mechanism (2) is composed of a rotating arm (14), a fixed arm (15), a large motor (9) and a rotating shaft (16); The fixed arm (15) of the folding and unfolding mechanism (2) is fixedly connected to the surface of the B antenna submodule (12), and the rotating arm (14) is fixedly connected to the surfaces of the A antenna submodule (11) and the C antenna submodule (13); the rotating arm (14) and the fixed arm (15) are hingedly connected via a rotating shaft (16), and a driving device, i.e., a large motor (9), is provided at the end of the rotating shaft (16); the folding and unfolding mechanism (2) is used for flipping and docking between the antenna submodules, and the large motor (9) installed on the folding and unfolding mechanism (2) plays a major flipping role; The release mechanism and guide rail device (3) are mainly composed of a support frame (17), a slide groove (18), a small pulley (19), a positioning hole (20), a calibration key (21), a connecting hole (22), and a spring lock tongue (23); The slide groove (18) and the small pulley (19) are respectively arranged on the upper convex surface and the lower concave surface of the support frame (17); a pair of pulley groups (6) are distributed on both sides of the support frame (17) and are fixedly connected to the support frame (17); the square planes at both ends of the support frame (17) are respectively provided with positioning holes (20) and calibration keys (21), connecting holes (22) and spring lock tongues (23), which are used for connecting the release mechanism and the guide rail device (3) after the antenna mechanism is unfolded; the five sets of release mechanisms and the guide rail device (3) are arranged from top to bottom. The ropes (10) are stacked in sequence, and the internal connection method thereof is composed of five pulley groups (6), a group of ropes (10) and a small motor (4); the small motor (4) is located on the bottom support frame (17) and is used to tighten the ropes (10); the ropes (10) are wound around the pulleys of each pulley group (6), the upper ends of the ropes (10) are fixed to the release mechanism and the pulleys of the guide rail device (3) on the top layer, and the lower ends of the ropes (10) are wound around the motor pulley (5), and the retraction and release thereof are controlled by the rotation of the small motor (4); The small motor (4) at the lower end of the release mechanism and guide rail device (3) rotates and tightens the rope (10), thereby pulling the release mechanism and guide rail device (3) and the antenna surface unit (1) to slide along the slide groove (18); the upper end release mechanism and guide rail device (3) and the antenna surface unit (1) slide to a critical position at the end of the slide groove opening, and continue to slide downward along a plane on the lower end support frame (17) that is perpendicular to the slide groove (18); A pair of connection holes (22) and a pair of calibration keys (21) are located on the vertical plane, and the connection holes (22) and the calibration keys (21) are symmetrically distributed with the mid-vertical plane of the vertical plane as a reference; a pair of connection holes (22) and a pair of spring lock tongues (23) are distributed on the vertical plane on the starting end side of the slide slot; the positioning holes (20) and the spring lock tongues (23) are symmetrically distributed with the mid-vertical plane as a reference; after the release mechanism and the guide rail device (3) and the antenna surface unit (1) slide to a predetermined position, the pair of spring lock tongues (23) extend into the corresponding connection holes (22) and lock, and at this time, the calibration keys (21) should all be located in the corresponding positioning holes (20).

2. The method for deploying a two-dimensional deployment mechanism based on a fixed surface antenna according to claim 1, characterized in that: The deployment method is step-by-step deployment, and the deployment process is divided into two steps: the first step is to realize docking and deployment between the reflector surface submodules through the operation of the folding and deployment mechanism (2), and the second step is to realize the flat sliding deployment of all antenna surface units (1) through the operation of the small motor (4) and the motor pulley (5); before the fixed surface antenna is deployed, the deployment mechanism is fixed on the B antenna submodule (12) and fixedly connected to the satellite body, and explosive bolts are provided at the connection between the antenna submodules as a storage frame to limit the movement of the antenna; during the antenna deployment process, the explosive bolts are automatically blown off, and the motor of the folding and deployment mechanism is opened. The operation starts to control the rotational docking between the antenna submodules; the steel wire rope is pulled by the deployment mechanism installed on the satellite body to assist the A antenna submodule (11) and the C antenna submodule (13) to rotate and dock with the B antenna submodule (12); in order to ensure the surface accuracy of the entire antenna, the locking mechanisms located between the A antenna submodule (11) and the B antenna submodule (12), and between the B antenna submodule (12) and the C antenna submodule (13) are locked after the docking is completed, and the three groups of antenna submodules form a whole, ready for the second stage of deployment; at this point, the rotational docking deployment between the antenna submodules is completed; In the second step of deployment, the small motor (4) starts to work, controlling the motor pulley (5) to slowly tighten the rope (10) wound around the pulley block (6) in each release mechanism and guide rail device (3), thereby causing the surface unit (1) from top to bottom to be deployed along the slide groove (18) in each release mechanism and guide rail device (3); all the surface units (1) and the release mechanism and guide rail device (3) reach a predetermined position and are locked by the motor pulley (5); thus, the fixed surface antenna is fully deployed.

3. The method for deploying a two-dimensional deployment mechanism based on a fixed surface antenna according to claim 2, characterized in that: The first step of the expansion process is specifically as follows: When the large motor (9) drives the A antenna submodule (11) and the C antenna submodule (13) to rotate and dock, all the surface units (1) of the A antenna submodule (11) or the C antenna submodule (13) are flipped together. When the upper convex top antenna surface unit (1) of the A antenna submodule (11) or the C antenna submodule (13) is flipped to a position flush with the top antenna surface unit (1) of the B antenna submodule (12), the lock (8) is connected to the locking mechanism (7). At this time, the three flush surface units (1) on each layer form an antenna sub-reflector surface. The limit brake is performed by the limit bolt installed on the unfolding frame in the unfolding mechanism. At this point, the flipping action is completed. The locking mechanism (7) and the lock (8) are locked: when the lock fixed on the A antenna submodule (11) and the C antenna submodule (13) (8) When the antenna submodules (11, 12, 13) are rotated and docked to the lock shell positions of the locking mechanisms (7) on both sides of the B antenna submodule (12), the lock buckle (8) squeezes the pressing block in the locking mechanism (7) to make it move into the lock buckle to form a pressing state. The locking of the lock buckle in six directions is achieved by the friction angle locking of the lock tongue in the locking mechanism (7) and the squeezing of the lock buckle by the pressing block, thereby achieving high-precision locking between the antenna reflector surfaces. After the antenna submodules (11, 12, 13) are docked and locked, the antenna subreflector surfaces need to be unfolded. At this time, the unfolding mechanism pulls all the surface units out of the antenna submodule after the first stage of unfolding through the action of the small motor, completes the release action of the antenna reflector surface, and prepares for the unfolding of the antenna reflector surface, i.e., the second stage of unfolding.

4. The method for deploying a two-dimensional deployment mechanism based on a fixed surface antenna according to claim 2, characterized in that: The second step of the expansion process is specifically as follows: Guide rail devices (3) are fixed on the outside of the A antenna submodule (11) and the C antenna submodule (13), respectively, so that each antenna reflector surface can move relative to each other; after the first stage of deployment, the small motors (4) and the motor pulleys (5) at the lower ends of the two sides of the antenna respectively pull the ropes (10) on the two sides, and under the traction drive of the small motors (4) and the motor pulleys (5), the guide rail devices begin to move relative to each other, thereby driving the synchronous deployment of the antenna reflectors; the deployment speed of the antenna reflectors can also be controlled by controlling the speed of tightening the ropes; when the deployment reaches a predetermined position, the locking devices between each two sections of the antenna sub-reflectors are locked, and during the second stage of deployment, the guide rail devices (3) before locking are buffered by the spring mechanism until they stop, thereby completing the entire process of antenna deployment.

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