A large deployable solid surface antenna

Abstract

A large deployable fixed surface antenna comprises a base, a plurality of drive systems and a plurality of deployable units; the plurality of drive systems are uniformly arranged along the circumference of the base, and two adjacent drive systems are connected in series; each of the plurality of deployable units comprises an antenna panel, a support, a support rod and a support back frame; the support is rotatably arranged on the side of the base, the two ends of the support rod are connected to the support and the support back frame through deployment hinges respectively, the support rod is self-rotatable relative to the deployment hinges, the antenna panel is fixed on the support back frame, the drive system is connected to the antenna panel through a base hinge, and the antenna panel is self-rotatable relative to the base hinge; the drive system controls the deployment of the antenna panel; and after the antenna is completely deployed, the support is locked through a locking mechanism arranged on the side of the base. The fixed surface antenna has the characteristics of high precision, reliable structure and flexible compactness, and can be used not only in the field of aerospace, but also on the ground.

Description

Technical Field

[0001] This invention relates to the technical field of structural engineering, specifically to a large deployable solid-surface antenna. Background Technology

[0002] Deployable structures are widely used in spacecraft engineering to meet requirements such as lightweight, high packability, and practical performance. This ensures that the spacecraft structure can be packed within a small fairing space during launch and can be successfully deployed and operational after entering orbit. As a crucial component of spacecraft, reflector antennas especially require a rationally designed deployable structure to improve the accuracy of the reflector profile and the reliability of deployment.

[0003] Existing concepts and technologies for deployable solid-surface antennas include:

[0004] The sunflower-shaped fixed-surface unfolding mechanism developed by TRW Company in the United States is driven by a motor. The driving torque is applied to the linkage system and transmitted to the hinge between the disks through the control arm. This unfolding mechanism has a large number of parts, and some parts are large in size, resulting in a large overall mass of the system.

[0005] The DAISY deployable antenna, jointly developed by the European Space Agency (ESA) and the German company Dornier, has panels and a central hub connected by a rotating joint, and the panels are arranged radially around the central hub. The panels still use a hinge structure, but the overall mass of this deployable mechanism is still relatively large, making it unsuitable for large-aperture antennas.

[0006] The MEA deployable antenna, jointly developed by Dornier and the European Space Agency (ESA), has a similar folded shape to the DAISY antenna. However, the MEA antenna has a more complex linkage system and greater structural rigidity. Although it is smaller in mass than the DAISY antenna, its structure is more complex.

[0007] The SSDA (Solid Surface Deployable Antenna) developed by Cambridge University also employs two or more hinges arranged on the same rotational axis to increase structural stiffness by adding virtual constraints. However, the antenna has a large mass and a complex deployment mechanism.

[0008] Hughes Corporation (HSCC) has developed a self-rebound deployable antenna. Self-rebound deployable antennas are lightweight and highly reliable, but have a relatively low packing ratio, low stiffness, and difficult-to-control deployment speed.

[0009] The Spektr.R deployable antenna, developed by Russia, is used as a space radio telescope. The antenna has extremely high angular resolution and sensitivity, but it is relatively heavy and its deployment and locking mechanisms are relatively complex.

[0010] The Aerospace Mechanism and Control Research Center of Harbin Institute of Technology has conducted extensive research on solid and thin-film parabolic deployable mechanisms. By applying the technology of spatial curved surface unfolding mechanism, a prototype of petal-shaped solid deployable antenna has been successfully developed.

[0011] Hunan Aerospace Huanyu Communication Technology Co., Ltd. has designed a linearly driven deployable solid-surface antenna.

[0012] The Shanghai Satellite Research Institute has proposed a petal-shaped deployable spaceborne parabolic antenna. This antenna has high overall structural rigidity, is suitable for large-aperture solid-surface antennas on space, and has good motion synchronization.

[0013] In China, research on the kinematics and dynamics of deployable antennas is mainly concentrated in universities and research institutions, focusing primarily on the kinematics and dynamics of mesh and frame-type deployable antennas. There is almost no research on deployable antennas with solid reflectors.

[0014] In summary, existing deployable solid-surface antennas all suffer from complex deployment mechanisms, poor flexibility, and an inability to simultaneously achieve both high reflector surface accuracy and reliable deployment, thus limiting their applications. Summary of the Invention

[0015] To overcome the shortcomings of existing technologies, this invention provides a large, deployable fixed-surface antenna. This fixed-surface antenna features high precision, reliable structure, and flexible, compact design, making it suitable for both aerospace and ground-based applications.

[0016] A large deployable solid surface antenna includes a base, multiple drive systems, and multiple sets of deployable units; the multiple drive systems are evenly arranged along the circumference of the base, and two adjacent drive systems are connected in series; the number of deployable units is the same as the number of drive systems.

[0017] Each deployable unit comprises an antenna panel, a bracket, a support rod, and a support back frame. The bracket is rotatably mounted on the side of the base. The two ends of the support rod are connected to the bracket and the support back frame respectively via unfolding hinges. The support rod can rotate relative to the unfolding hinges, and the hinge rotation axis is perpendicular to the rotation axis. The antenna panel is fixed on the support back frame. The drive system is connected to the antenna panel via a base hinge, and the antenna panel can rotate relative to the base hinge F. The hinge rotation axis is perpendicular to the rotation axis. The drive system controls the unfolding of the antenna panel. The drive system, antenna panel, bracket, and support rod constitute a spatial four-bar linkage mechanism. The planes where the antenna panel and support rod are located are not coplanar with the plane where the bracket is located. After the antenna is fully unfolded, the bracket is locked by a locking mechanism arranged on the side of the base.

[0018] Furthermore, each drive system includes a fixed base, a central shaft, a stop shaft, and a spiral spring; the fixed base is mounted on the base, the central shaft is rotatably mounted on the fixed base, the central shaft is fixed to the other end of the spiral spring, one end of the spiral spring is fixed to the stop shaft mounted on the fixed base, the base hinge is mounted on the central shaft, and the antenna panel is unfolded by the central shaft, and the central shaft drives the unfolding of the antenna panel. The central shafts of two adjacent drive systems are connected in series.

[0019] Furthermore, the locking mechanism includes a locking seat, a top cone, a spring, and a housing; the locking seat is mounted on a base, and two side-by-side supports extend from the locking seat at intervals, each support having a top cone slidably mounted on it; the housing is fixed to the locking seat, and the spring is arranged inside the housing, with both ends of the spring abutting against the inner bottom surface of the housing and the end face of the top cone, respectively, and the tips of the two top cones abutting against each other.

[0020] Furthermore, the antenna panel is composed of three panels joined together, each panel is mounted on a support frame by three linear actuators, and each panel is made of carbon fiber reinforced plastic.

[0021] The advantages of this invention compared to the prior art are:

[0022] The spatial four-bar linkage of this invention enables the deployment of a solid-surface antenna by rotation around a single axis, offering higher deployment reliability compared to traditional solid-surface antennas deployed by rotation around orthogonal dual axes. The adjacent drive systems of this invention are connected by gimbals, and the spatial four-bar linkage's synchronous transmission method enables passive synchronous driving and deployment of multiple panels.

[0023] The positioning and locking functions of the locking mechanism are highly reliable, ensuring the overall rigidity of the antenna when it is fully deployed.

[0024] The solid-surface antenna of the present invention also features high precision, reliable structure, flexibility and compactness, and can be used not only in the aerospace field but also in ground applications.

[0025] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments: Attached Figure Description

[0026] Figure 1 This is a diagram showing the initial retraction state of the antenna in this invention;

[0027] Figure 2 This is a diagram showing the antenna of the present invention fully deployed and locked.

[0028] Figure 3 This is a diagram showing the state of the invention not being fully unfolded;

[0029] Figure 4 This is a schematic diagram of the antenna panel removed after the antenna of the present invention has been fully deployed;

[0030] Figure 5 This is a schematic diagram showing the arrangement of the base and the drive system;

[0031] Figure 6 This is a schematic diagram showing the arrangement of the deployable unit and the base;

[0032] Figure 7 This is a partial schematic diagram showing the connection between the deployable unit and the drive system;

[0033] Figure 8 for Figure 7 A magnified view of a portion of point I;

[0034] Figure 9 A schematic diagram showing the connection between the retaining ring and the support base;

[0035] Figure 10 This is a schematic diagram of the base hinge;

[0036] Figure 11 This is an exploded view of the base hinge;

[0037] Figure 12 A schematic diagram for unfolding the hinge;

[0038] Figure 13 An exploded view of the hinge;

[0039] Figure 14 A schematic diagram of the locking mechanism;

[0040] Figure 15 An exploded view of the locking mechanism;

[0041] Figure 16 A schematic diagram showing the arrangement of the outer and inner circumferential clamping mechanisms;

[0042] Figure 17 for Figure 16 Enlarged view at point II;

[0043] Figure 18 for Figure 16 Enlarged view of section III;

[0044] Figure 19 for Figure 2 Enlarged view of point K;

[0045] Figure 20 A schematic diagram of the structure supporting the back frame;

[0046] Figure 21 This is a schematic diagram of the spatial four-bar linkage of the present invention. Detailed Implementation

[0047] The embodiments of the technical solution of the present invention will now be described in detail with reference to the accompanying drawings. These embodiments are merely illustrative of the technical solution of the present invention and are therefore intended to limit the scope of protection of the present invention.

[0048] It should be noted that, unless otherwise stated, the technical or scientific terms used in this application should have the ordinary meaning as understood by one of ordinary skill in the art to which this invention pertains.

[0049] Combination Figures 1-7 As shown, a large deployable solid surface antenna includes a base 1, multiple drive systems 2 and multiple sets of deployable units 3; the multiple drive systems 2 are evenly arranged along the circumference of the base, and two adjacent drive systems 2 are connected in series; the number of deployable units 3 is the same as the number of drive systems 2.

[0050] Each deployable unit 3 includes an antenna panel 31, a bracket 32, a support rod 33, and a support back frame 34. The bracket 33 is rotatably mounted on the side of the base 1. The two ends of the support rod 33 are connected to the bracket 32 ​​and the support back frame 34 respectively via unfolding hinges E. The support rod 33 can rotate relative to the unfolding hinges E. The axis of rotation of the unfolding hinges E is perpendicular to the axis of rotation. The antenna panel 31 is fixed on the support back frame 34. The drive system 2 is connected to the antenna panel 31 via a base hinge F. The antenna panel 31 can rotate relative to the base hinge F. The axis of rotation of the base hinge F is perpendicular to the axis of rotation. The drive system 2 controls the unfolding of the antenna panel 31. The drive system 2, the antenna panel 31, the bracket 32, and the support rod 33 constitute a spatial four-bar linkage mechanism. The planes on which the antenna panel 31 and the support rod 33 are located are not coplanar with the plane on which the bracket 32 ​​is located. After the antenna is fully unfolded, the bracket 32 ​​is locked by a locking mechanism 4 arranged on the side of the base 1.

[0051] To ensure the synchronous deployment of the antenna panel 31 in the spatial four-bar linkage, adjacent drive systems 2 are connected and driven by a universal joint 7, such as... Figure 5 As shown.

[0052] To ensure good forming accuracy of the antenna, this embodiment uses a truss as a support frame to support and form the antenna, thus ensuring the overall forming accuracy of the antenna.

[0053] Optionally, as an embodiment, the antenna is initially set to have 27 lobes. Each antenna panel 31 is divided into three pieces. Good molding accuracy is ensured by assembling the three panels onto the support frame 34. The antenna panel 31 is formed by joining three panels together. Each panel is mounted on the support frame 34 by three linear actuators. The material of each panel is carbon fiber reinforced plastic. The material of the reflector panel is carbon fiber reinforced plastic (CFRP), which has excellent performance in the combination of high specific modulus and low coefficient of thermal expansion (CTE). This implementation can correct for errors in the unfolding process and surface deformation caused by thermoelasticity and hygroscopic effects.

[0054] In this embodiment, the drive system 2, antenna panel 31, bracket 32, and support rod 33 constitute a spatial four-bar linkage, the working principle of which is as follows: Figure 21 As shown, during the rotation of crank DB, the trajectory of joint B is a curve in space, meaning there is displacement in the X, Y, and Z directions within the coordinate system. Since members AC and BC are in the same plane, the movement of joint B will cause the antenna panel to undergo a combined radial unfolding and self-flipping motion, thereby achieving the staggered retraction and unfolding of the antenna panel. The antenna configuration is as follows: Figure 21 As shown, in Figure 21 In the basic configuration shown, connecting rods AC (antenna panel 31), BC (support rod 33) and connecting rods AD (drive system 2 and bracket 32), BD (bracket 32) are not on the same plane; that is, plane ACB and plane ADB are not coplanar. To enable the antenna panel to rotate radially outward and about its own axis, a hinge is installed at node A. Through the misalignment changes of the structure itself during movement, the antenna panel achieves the movement process from retracting to unfolding. The locking method after the antenna is unfolded is as follows... Figure 6 and Figure 7 As shown.

[0055] As one possible implementation method, such as Figure 8 As shown, each drive system 2 includes a fixed base 21, a central shaft 23, a stop shaft 24, and a spiral spring 25. The fixed base 21 is mounted on the base 1, and the central shaft 23 is rotatably mounted on the fixed base 21. The central shaft 23 is fixed to the other end of the spiral spring 25, and one end of the spiral spring 25 is fixed to the stop shaft 24 mounted on the fixed base 21. The base hinge F is mounted on the central shaft 23 and is driven by the central shaft 23 to unfold the antenna panel 31. The central shafts 23 of two adjacent drive systems 2 are connected in series.

[0056] To ensure the synchronous unfolding of the antenna panel 31 in the spatial four-bar linkage, two adjacent central shafts 23 are connected and driven by a universal joint 7, such as... Figure 5As shown. During antenna deployment, it is necessary to ensure that interference between antenna elements is avoided, that is, the deployment of each antenna element should be synchronized. This embodiment proposes to ensure synchronization through the transmission of the universal joint 7, and the antenna deployment power is provided by the elastic potential energy of the planar spiral spring 25.

[0057] As another possible implementation, the structural design of the key hinges is crucial to ensure the smooth deployment of the spatial four-bar linkage. To achieve rotation in two dimensions, a base hinge F and a deployment hinge E were designed.

[0058] like Figure 10 and Figure 11 As shown, the base hinge F includes a hinge seat F1-1, a connector F1-2, and ball bearings F1-3. A support column F1-11 extends from one side of the hinge seat F1-1. The connector F1-2 is a hollow structure. Multiple annular grooves F1-0 that cooperate with each other are machined on the inner surface of the connector F1-2 and the outer surface of the support column F1-11. Multiple ball bearings F1-3 are arranged in the annular grooves F1-0. The connector F1-2 is inserted into the support column F1-11, and the two form a rotating pair through the ball bearings F1-3.

[0059] The base hinge F mentioned above can achieve rotation in two dimensions, such as... Figure 7 , Figure 10 and Figure 11 As shown, one dimension is to realize the rotation of the hinge around the central axis 23, thereby enabling the antenna panel 31 to unfold. The other dimension is to realize the rotation of the connector F1-2 around the hinge seat F1-11, so that the spatial four-bar linkage can be smoothly folded and unfolded.

[0060] There are two ways to set the base hinge F, but it is not limited to these two methods:

[0061] Example 1, such as Figures 8-10 As shown, the base hinge F is sleeved on the central shaft 23 and the two can rotate relative to each other. A retaining ring 22-5 is fixed on the central shaft 23, and a positioning ring is provided on the base hinge F. The retaining ring 22-5 and the positioning ring 1-12 each have alternating protrusions and grooves. The retaining ring 22-5 and the protrusions and grooves on the positioning ring 1-12 are inserted and connected together to transmit power. Figure 9 The support seat 22-4 is mounted on the base 1. The central shaft 23 is supported on the support seat 22-4 by a bearing. The retaining ring 22-5 is fixed to the end of the central shaft 23 and is inserted into the positioning ring 1-12 to realize power transmission.

[0062] In this embodiment, the hinge seat F1-1 is fitted onto the central shaft 23, and the two can rotate relative to each other. During operation, the central shaft 23 rotates under the drive of the spiral spring 25. The power is transmitted to the base hinge F through the engagement of the snap ring 22-5 of the coupling structure with the positioning ring 1-11, thus maintaining the independent transmission of the central shaft 23 and the base hinge F without interference between them.

[0063] Example 2: In this example, the base hinge F is fixed to the central shaft 23. The base hinge F can be a U-shaped structure, with its two arms inserted and fixed to the central shaft 23. The base hinge F also rotates with the central shaft 23.

[0064] like Figure 12 and Figure 13 As shown, the unfolding hinge E includes a hinge seat E2-1, a connector E2-2, and ball bearings E2-3. A support column E2-11 extends from one side of the hinge seat E2-1. The connector E2-2 is a hollow structure. Multiple annular grooves E2-0 that cooperate with each other are machined on the inner surface of the connector E2-2 and the outer surface of the support column E2-11. Multiple ball bearings E2-3 are arranged in the annular grooves E2-0. The connector E2-2 is inserted into the support column E2-11, and the two form a rotating pair through the ball bearings E2-3.

[0065] The aforementioned unfolding hinge E allows for rotation in two dimensions, such as... Figure 7 , Figure 12 and Figure 13 As shown, one dimension enables rotation between the hinges on the bracket 32 ​​and the support rod 33, allowing the antenna panel 31 to unfold. The other dimension enables the connector E2-2 to rotate around the hinge seat E2-1, allowing the spatial four-bar linkage to smoothly fold and unfold, and adapting to situations where the spatial four-bar linkage is not coplanar. The hinges can achieve rotation in two dimensions; the axial rotation is achieved using ball bearings, similar to bearing manufacturing processes, thus achieving rotational motion while maintaining a certain degree of bending stiffness.

[0066] In another possible implementation, such as Figure 14 and Figure 15 As shown, the locking mechanism 4 includes a locking seat 41, a top cone 42, a spring 43, and a housing 44. The locking seat 41 is mounted on the base 1, and two side-by-side lugs 41-1 extend from the locking seat 41. A top cone 42 is slidably provided on each lug 41-1. The housing 44 is fixed on the locking seat 41, and the spring 43 is arranged inside the housing 44. The two ends of the spring 43 abut against the inner bottom surface of the housing 44 and the end face of the top cone 42, respectively, and the tips of the two top cones 42 abut against each other.

[0067] In this embodiment, after the antenna is fully deployed, the through hole of the triangular support 32 engages between the tips of the two top cones 42 of the locking mechanism 4. The wedge shape of the top cones 42 achieves positioning and locking. Since the triangular support 32 can only rotate relative to the base 1 around its rotation axis, the positioning and locking functions of the locking mechanism 4 are highly reliable, ensuring the overall rigidity of the antenna in its fully deployed state. The elastic potential energy of the spring 43 facilitates the locking and deployment of the support 32.

[0068] Based on the above scheme, in order to ensure the rigidity and stability of the antenna when it is retracted, a circumferential clamping mechanism was designed, namely the outer ring circumferential clamping mechanism 5 and the inner ring circumferential clamping mechanism 6. Figure 16 This shows the antenna's attitude after it has been retracted and is subjected to a circumferential clamping mechanism. Figure 17 Display of outer ring circumferential clamping mechanism 5. Figure 18 Display the inner ring circumferential clamping mechanism 6.

[0069] like Figure 17 As shown, the outer ring circumferential pressing mechanism 5 includes a frame 51, a rope 52, a pre-tension spring 53, and a pyrotechnic cutting rod 54. The pyrotechnic cutting rod 54 is fixed on one side of the frame 51, and the rope 52 is fixed on the other side of the frame 51. The pre-tension spring 53 is arranged inside the frame 51 and sleeved on the rope 52. The two ends of the pre-tension spring 53 abut against the ends of the rope 52 and the frame 51, respectively. The pyrotechnic cutting rods 54 of two adjacent outer ring circumferential pressing mechanisms 5 are connected to the rope 52. Multiple outer ring circumferential pressing mechanisms 5 are connected in series and covered on the support frame 34 of the antenna retractor.

[0070] like Figure 18 As shown, the inner ring circumferential clamping mechanism 6 includes a feed inner ring 61 and locking connectors 62. The feed inner ring 61 is disposed above the base 1 and is connected to the base 1 via a connecting rod. Multiple locking connectors 62 are evenly distributed circumferentially on the feed inner ring 61, and the central rod 621 on the locking connector 62 abuts against the inner surface of the antenna panel 31 of the retracted antenna. The circumferential clamping mechanisms of the inner and outer rings work together to ensure the overall rigidity of the antenna in the retracted state.

[0071] Based on the above scheme, for example, when the deployable reflective solid-surface antenna has a deployed aperture of 13m, its retracted aperture is 3.55m and its retracted height is 6985mm, which meets the design specifications. Figure 16 The shape shown.

[0072] Additionally, a locking mechanism is shown on the back of antenna panel 31 to prevent the antenna panels from springing back after the antenna is fully deployed, as illustrated in the diagram. Figure 19The structure shown has a panel locking mechanism on the back of the antenna panel 31, including a locking buckle 8 and a locking baffle 9. The locking baffle 9 is fixed to the back of the antenna panel 31, and the locking buckle 8 is rotatably mounted on one of the locking baffles 9. When the antenna panel is fully extended, the locking buckle 8 abuts against the side of the other locking baffle 9. The locking buckle 8 and the locking baffle 9 are magnetically attached.

[0073] To improve the structural rigidity of the antenna during operation, a support mechanism for the parabolic panel is designed. For the panel support structure, a truss support structure is proposed to be added to the back of the parabolic panel, forming a support back frame 34. Due to the high stability of tetrahedrons, the tetrahedron is used as the basic configuration. The truss is composed of multiple tetrahedrons assembled together, and a shaped parabolic shape is formed by fitting multiple hard nodes at the top of the truss. This shape is then assembled with the parabolic panel to form the antenna panel. Specifically, as shown... Figure 20 As shown.

[0074] The present invention has been disclosed above with reference to preferred embodiments, but it is not intended to limit the present invention. Any person skilled in the art can make some modifications or alterations to the above-disclosed structure and technical content to create equivalent embodiments without departing from the scope of the present invention, and all such modifications or alterations shall still fall within the scope of the present invention.

Claims

1. A large deployable solid-surface antenna, characterized in that: It includes a base (1), multiple drive systems (2) and multiple deployable units (3); the multiple drive systems (2) are evenly arranged along the circumference of the base, and two adjacent drive systems (2) are connected in series. The number of deployable units (3) is the same as the number of drive systems (2). Each deployable unit (3) includes an antenna panel (31), a bracket (32), a support rod (33), and a support frame (34); the bracket (32) is rotatably mounted on the side of the base (1), the antenna panel (31) is fixed on the support frame (34), and the two ends of the support rod (33) are connected to the bracket (32) and the support frame (34) respectively through the unfolding hinge (E). The support rod (33) can rotate relative to the unfolding hinge (E), and the axis of rotation of the unfolding hinge (E) is perpendicular to the axis of rotation. The unfolding hinge (E) includes a hinge seat E (2-1), a connector E (2-2), and ball bearings E (2-3); a support column E (2-11) extends from one side of the hinge seat E (2-1), the connector E (2-2) is a hollow structure, and multiple annular grooves E (2-0) that cooperate with each other are machined on the inner surface of the connector E (2-2) and the outer surface of the support column E (2-11), and multiple ball bearings E (2-3) are arranged in the annular grooves E (2-0). The connector E (2-2) is inserted into the support column E (2-11), and the two form a rotating pair through the ball bearings E (2-3); the drive system (2) is connected to the antenna panel (31) through the base hinge (F), and the antenna panel (31) can rotate relative to the base hinge (F). The rotation axis of the base hinge (F) is perpendicular to the rotation axis. The drive system (2) controls the unfolding of the antenna panel (31). The drive system (2) and the antenna panel (31) The bracket (32) and the support rod (33) constitute a spatial four-bar linkage mechanism. The plane where the antenna panel (31) and the support rod (33) are located is not coplanar with the plane where the bracket (32) is located. After the antenna is fully deployed, the bracket (32) is locked by a locking mechanism (4) arranged on the side of the base (1). The locking mechanism (4) includes a locking seat (41), a top cone (42), a spring (43) and a housing (44). The locking seat (41) is installed on the base (1). Two lugs (41-1) are arranged side by side at intervals on the locking seat (41). A top cone (42) is slidably provided on each lug (41-1). The housing (44) is fixed on the locking seat (41). The spring (43) is arranged inside the housing (44). The two ends of the spring (43) abut against the bottom surface of the inner surface of the housing (44) and the end face of the top cone (42) respectively. The tips of the two top cones (42) abut against each other.

2. The large deployable solid-surface antenna according to claim 1, characterized in that: Each drive system (2) includes a fixed base (21), a central shaft (23), a stop shaft (24), and a spiral spring (25). The fixed base (21) is mounted on the base (1), the central shaft (23) is rotatably mounted on the fixed base (21), the other end of the central shaft (23) is fixed to the spiral spring (25), one end of the spiral spring (25) is fixed to the stop shaft (24) mounted on the fixed base (21), the base hinge (F) is mounted on the central shaft (23), and the antenna panel (31) is unfolded by the central shaft (23). The central shafts (23) of two adjacent drive systems (2) are connected in series.

3. The large deployable solid-surface antenna according to claim 2, characterized in that: The base hinge (F) includes a hinge seat F (1-1), a connector F (1-2), and a ball bearing F (1-3). One side of the hinge seat F (1-1) extends a support column F (1-11), and the other side of the hinge seat F (1-1) is set on the central shaft (23), and the antenna panel (31) is unfolded by the central shaft (23). The connector F (1-2) is a hollow structure. The inner surface of the connector F (1-2) and the outer surface of the support column F (1-11) are respectively machined with multiple annular grooves F (1-0) that cooperate with each other. Multiple balls F (1-3) are arranged in the annular grooves F (1-0). The connector F (1-2) is inserted into the support column F (1-11), and the two form a rotating pair through the balls F (1-3).

4. A large deployable solid-surface antenna according to claim 3, characterized in that: The base hinge (F) is sleeved on the central shaft (23) and the two can rotate relative to each other. A retaining ring (22-5) is fixed on the central shaft (23). A positioning ring is provided on the base hinge (F). The retaining ring (22-5) and the positioning ring (1-12) each have alternating protrusions and grooves. The protrusions and grooves on the retaining ring (22-5) and the positioning ring (1-12) are inserted and connected together to transmit power.

5. A large deployable solid-surface antenna according to claim 3, characterized in that: The base hinge (F) is fixed on the central shaft (23).

6. A large deployable solid-surface antenna according to claim 1, characterized in that: The antenna panel (31) is made of three panels joined together. Each panel is mounted on a support frame (34) by three linear actuators. The material of each panel is carbon fiber reinforced plastic.

7. A large deployable solid-surface antenna according to claim 1, characterized in that: It also includes an outer circumferential clamping mechanism (5) and an inner circumferential clamping mechanism (6); The outer circumferential pressing mechanism (5) includes a frame (51), a rope (52), a pre-tension spring (53), and a pyrotechnic cutting rod (54). A pyrotechnic cutting rod (54) is fixed to one side of the frame (51), and a rope (52) is fixed to the other side of the frame (51). The pre-tension spring (53) is arranged inside the frame (51) and looped around the rope (52). Both ends of the pre-tension spring (53) abut against the ends of the rope (52) and the frame (51), respectively. The pyrotechnic cutting rods (54) of two adjacent outer circumferential pressing mechanisms (5) are connected to the rope (52). 52) Connected, multiple outer ring circumferential pressing mechanisms (5) are connected in series and covered on the support frame (34) of the retractable antenna; the inner ring circumferential pressing mechanism (6) includes a feed inner ring (61) and a locking connector (62). The feed inner ring (61) is provided above the base (1). The feed inner ring (61) is connected to the base (1) through a connecting rod. Multiple locking connectors (62) are evenly distributed along the circumference on the feed inner ring (61). The center rod (621) on the locking connector (62) abuts against the inner surface of the antenna panel (31) of the retractable antenna.

8. A large deployable solid-surface antenna according to claim 1, characterized in that: The antenna panel (31) has a panel locking mechanism on the back, including a locking buckle (8) and a locking baffle (9). The locking baffle (9) is fixed on the back of the antenna panel (31). The locking buckle (8) is rotatably mounted on a locking baffle (9). After the antenna panel is fully unfolded, the locking buckle (8) abuts against the side of another locking baffle (9). The locking buckle (8) and the locking baffle (9) are magnetically attached.

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