A large satellite-borne speed-controlled deployment antenna

Abstract

The present invention relates to a satellite-borne large-scale speed-controlled deployable frame antenna, belonging to the field of antenna technology. It consists of a new large-scale deployable frame antenna and a set of pod rod assemblies. The frame antenna structure is a parabolic cylinder, and its deployment aperture is expandable; the pod rod assembly is an "Ω"-shaped retractable flexible structure. The pod rod assembly is connected to the speed control system and the frame antenna boundary at the same time. During the antenna deployment process, the movement of the speed control system can be transmitted to the frame antenna, thereby controlling the speed of the antenna deployment process. The antenna has the inherent advantages of the frame antenna, such as high storage ratio, reliable deployment, and high repeatability. At the same time, the deployment process and deployment speed are controlled by the speed control system, which effectively avoids the disadvantages of the frame antenna, such as large deployment impact and uncontrollable deployment process. It has broad application prospects.

Description

Technical Field

[0001] The invention discloses a satellite-borne large-scale speed-controlled deployable frame antenna, belonging to the technical field of large-scale deployable antennas and structures in space. Background Art

[0002] To meet the demand for new-type satellite-based SAR antennas for satellite applications such as space-based moving target monitoring, large, deployable satellite antennas with ultra-large aperture parabolic truss antennas are required. However, due to the limited envelope of the launch vehicle's carrier, large deployable space antennas must be designed to be stowed during launch and deployable in orbit. Considering factors such as stowage ratio, deployment stiffness, weight, and engineering feasibility, the currently widely used loop antennas, umbrella antennas, and truss antennas, truss antennas are found to meet the requirements for large, deployable satellite antennas with ultra-large aperture parabolic truss antennas. However, the inherent characteristics of truss antennas dictate their deployment method: in the stowed state, vortex springs and torsion springs store energy, and after unlocking, they release this stored energy to deploy autonomously. This deployment process causes a certain impact on the satellite. For smaller antennas, a smaller spring energy reserve can ensure full deployment, minimizing the impact on the satellite. This impact can be mitigated by strengthening the satellite's stiffness and adding buffer structures. As the antenna aperture increases to a certain level, the energy storage capacity of the spring itself must be increased to ensure that the antenna can be reliably deployed. In addition, the number of energy storage spring elements will inevitably increase exponentially with the increase in aperture. The impact generated by the superposition of these two factors will cause catastrophic damage to the satellite or other mechanical structures. Furthermore, due to the limitations of the launch vehicle's carrying capacity, it is impossible to cope with the impact of the deployment of an ultra-large aperture antenna on the satellite by continuously increasing the stiffness of the satellite or adding a buffer structure. Therefore, the deployment impact must be suppressed from the perspective of the deployable antenna itself. Summary of the Invention

[0003] The technology of the present invention solves the problem: it overcomes the shortcomings of the existing technology and provides a satellite-borne large-scale deployable frame antenna with controlled speed, which achieves the purpose of suppressing the impact by controlling the deployment speed. At the same time, through the application of ultra-large slenderness ratio pod rod components, a rigid boundary is built for the flexible frame antenna with low stiffness to improve its stiffness.

[0004] The above-mentioned purpose of the present invention is mainly achieved through the following technical solutions:

[0005] A large-scale satellite-borne speed-controlled deployable frame antenna comprises a parabolic cylindrical frame antenna and a pod rod assembly; the parabolic cylindrical frame antenna comprises a metal mesh, a web, a foldable synchronization rod, an inner disc, and a boundary disc;

[0006] The internal faceplate, the foldable synchronization rod and the web are assembled by screws and rivets to form an internal tetrahedron unit. The boundary faceplate, the foldable synchronization rod and the web are assembled by screws and rivets to form a boundary tetrahedron unit. Multiple internal tetrahedron units are spliced ​​together to form the internal structure of the parabolic frame antenna. The boundary tetrahedron unit serves as the boundary of the parabolic frame antenna. The internal structure and the boundary ultimately form the main structure of the parabolic frame antenna. The main structure is used for fitting and shaping the antenna emitting surface, that is, the parabolic fitting surface. The metal mesh is fixedly connected to the main structure at the internal faceplate and the boundary faceplate.

[0007] The connection between the pod rod assembly and the boundary flower disk provides a rigid boundary for the parabolic frame antenna, and at the same time serves as an adapter to connect to the drive motor, ensuring that the deployment process and deployment speed of the parabolic frame antenna and the pod rod assembly are controllable, thereby achieving speed control of the deployment process of the parabolic frame antenna.

[0008] Furthermore, the deployable frame antenna proposed by the present invention further includes: a tension rope and a pressure mesh;

[0009] A mesh pressing plate is installed at the connection between the internal faceplate, the boundary faceplate and the metal mesh to increase the contact area between the metal mesh and the tetrahedral unit; a tension rope is installed between adjacent internal faceplates and boundary faceplates to improve the fit of the metal mesh to the fitting surface of the ideal parabolic cylinder.

[0010] Furthermore, the metal mesh is woven from metal wires and has the function of reflecting electromagnetic waves; the tensioning rope material is a carbon fiber inner core + a polyimide outer jacket; and the pressed mesh material is polyimide.

[0011] Furthermore, the foldable synchronization rod is a foldable mechanism formed by two carbon fiber rods engaged by gears. During the folding and unfolding process of the two carbon fiber rods, the rotation speed of the two axes around the foldable synchronization rod shaft is always consistent, and after being unfolded into place, they are locked in the form of complementary shapes.

[0012] Furthermore, the web is formed by bonding metal joints at both ends of a hollow metal rod or a hollow carbon fiber rod, wherein the metal joints bonded at both ends are used to provide external interfaces. In areas susceptible to wear or impact, the web is in the form of a hollow metal rod.

[0013] Furthermore, the inner faceplate and the boundary faceplate are components of the inner tetrahedron unit and the boundary tetrahedron unit respectively, which constrain the movement process of the web bar and the foldable synchronization rod to prevent the folding and unfolding movement stroke of the web bar and the foldable synchronization rod from exceeding the design range.

[0014] Furthermore, when the truss antenna is deployed, there are four boundary lines in the direction parallel to the busbar. Considering the requirements for maintaining the shape of the truss antenna, the overall configuration of the payload and the feasibility of the project, the pod rod assembly is arranged on 1≤N≤4 boundaries of the four boundary lines in the direction parallel to the busbar of the truss antenna; the pod rod assembly is folded under the action of external force, and after the external force is removed, it is deployed to the rigid rod by releasing its own stored energy.

[0015] Furthermore, the pod rod assembly includes: a pod rod, a pulley, a base and a slip ring; the base is the non-movable part of the pod rod assembly, providing an external interface for connection to the drive motor, and the relative position remains fixed; the pod rod is the main structure of the pod rod assembly, used for forming the pod rod assembly, and is not directly connected to the antenna and the drive motor; the pulley is the movable part of the pod rod assembly, which slides along the expansion direction of the pod rod during the expansion of the pod rod; the slip ring, as a component of the pulley, is a circular ring structure, which is used as an adapter to connect the boundary disc of the antenna to the pod rod, and has the function of self-adjustment and adaptation of position.

[0016] Furthermore, the pod rod is made of a carbon fiber thin-walled tube, and the cross-section is a double-arch "Ω" shape.

[0017] Furthermore, when the retraction strap is unlocked, the drive motor is turned on and outputs torque to drive the pod rod assembly to perform one-dimensional extension motion along the pod rod axis. At this time, the slip ring fixed to the boundary flower disc slides relative to the pod rod to achieve the boundary of the frame antenna. During this process, the movement of the boundary flower disc is constrained by the movement of the pod rod assembly, and the movement of the pod rod assembly is constrained by the drive motor.

[0018] The inner flower disc, belly rod and foldable synchronous rod make adaptive movements with the boundary flower disc as the boundary;

[0019] The drive motor continuously inputs drive until the pod rod assembly is unfolded into place, the boundary flower disc is unfolded into place synchronously, the internal flower disc, the belly rod, and the foldable synchronization rod are also unfolded into place; the metal mesh, tensioning rope, and pressing mesh are also unfolded to the designed position at the same time by performing driven motion.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] (1) The invention provides a speed-controlled deployable antenna, the main innovation of which is speed control, which can avoid the disadvantage of large impact during the deployment process of traditional frame antennas;

[0022] (2) The speed-controlled deployable antenna of the present invention is initially designed as an ultra-large aperture antenna, which can break through the aperture limitations of traditional flexible antennas;

[0023] (3) The speed-controlled deployable antenna of the present invention adopts a combination of active deployment and passive deployment, taking into account the reliability of active deployment and the high repeatability of passive deployment;

[0024] (4) The speed-controlled deployable antenna of the present invention optimizes and improves the existing frame antenna, that is, a flexible deployable pod rod mechanism is arranged at the boundary of a larger span, which can effectively improve the boundary stiffness of the frame antenna.

[0025] (5) The speed-controlled deployable antenna of the present invention possesses the inherent advantages of a frame antenna while effectively avoiding its disadvantages. It can be widely used in large and even giant satellite-borne deployable antennas, as well as other deployable structures that require speed control during deployment or are sensitive to impact, and has broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 : Schematic diagram of the speed-controlled deployable antenna of the present invention in the deployed state;

[0027] Figure 2 : The connection between the pod pole and the triangular truss and the reflector of the present invention;

[0028] Figure 3 : Schematic diagram of the connection between the speed-controlled deployable antenna pod pole and the frame antenna of the present invention;

[0029] Figure 4 : Schematic diagram of the speed-controlled deployable antenna pod assembly of the present invention;

[0030] Figure 5 : Schematic diagram of the metal mesh in the speed-controlled deployable antenna of the present invention;

[0031] Figure 6 : Schematic diagram of the "Ω"-shaped half pod rod in the speed-controlled deployable antenna pod rod assembly of the present invention;

[0032] Figure 7 : Schematic diagram of the overall layout of the speed-controlled deployable antenna of the present invention (folded state). DETAILED DESCRIPTION

[0033] To make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0034] The present invention is mainly a large-aperture, speed-controllable, deployable parabolic antenna. Compared with traditional deployable antennas, the main features of the present invention are:

[0035] 1. The antenna structure adopts parabolic cylinder;

[0036] 2. This solution can be used for antenna diameters ranging from a few meters to hundreds of meters;

[0037] 3. The speed of the antenna deployment process can be controlled to avoid the disadvantage of large-structure antenna deployment with large impact;

[0038] 4. Imposing constraints on the boundaries of the parabolic truss antenna can provide an external interface and improve rigidity. The present invention consists of a new large-scale deployable truss antenna and a set of pod rod assemblies. The truss antenna structure is a parabolic cylinder with an expandable deployment diameter; the pod rod assembly is an "Ω"-shaped retractable flexible structure. The pod rod assembly is connected to the speed control system and the boundaries of the truss antenna at the same time. During the antenna deployment process, the movement of the speed control system can be transmitted to the truss antenna, thereby controlling the speed of the antenna deployment process.

[0039] The antenna's perimeter is constrained by the speed control system, and its motion is driven by it. This means the system's speed can be controlled based on the engineering impact performance requirements, indirectly controlling the antenna's deployment speed. Simultaneously, the antenna's deployment is adaptively driven by its own folding rods, geometric constraints, and perimeter constraints. Both the perimeter and interior deploy simultaneously.

[0040] The truss antenna is a deployable flexible antenna. In its deployed state, the antenna's profile is a parabola. The four boundaries parallel to the parabola's generatrix have large spans and are formed by splicing multiple folding rods. Therefore, its stiffness is relatively low. To maintain the required profile and ensure engineering feasibility, the boundaries are connected with pod rod assemblies to form a relatively stiff boundary.

[0041] The pod rod assembly is a pod structure that can be rolled up to a smaller volume under the action of external force to meet the size restrictions of the carrier compartment. When the external force is applied or removed, it can release its own stored energy and unfold into a rigid rod. In the present invention, the pod rod assembly provides power to the speed control system during the unfolding process, performing driven motion to achieve controllable unfolding process and unfolding speed. In the present invention, the pod rod assembly mainly has the following two functions: to enhance the boundary stiffness of the frame antenna; and to provide an external interface as an adapter to facilitate the connection between the frame antenna and the speed control system, so as to transmit the movement of the speed control system to the antenna to achieve speed control during the unfolding process.

[0042] Specifically, such as Figure 1 As shown, the present invention proposes a large-scale satellite-borne speed-controlled deployable frame antenna, comprising: a parabolic frame antenna and a pod rod assembly 8; the parabolic frame antenna comprises: a metal mesh 1, a web 3, a foldable synchronization rod 4, an inner disc 6, and a boundary disc 7;

[0043] The internal faceplate 6, the foldable synchronization rod 4 and the web 3 are assembled by screws and rivets to form an internal tetrahedron unit. The boundary faceplate 7, the foldable synchronization rod 4 and the web 3 are assembled by screws and rivets to form a boundary tetrahedron unit. Multiple internal tetrahedron units are spliced ​​together to form the internal structure of the parabolic frame antenna. The boundary tetrahedron unit serves as the boundary of the parabolic frame antenna. The internal structure and the boundary ultimately form the main structure of the parabolic frame antenna. The main structure is used for the antenna emitting surface, that is, the fitting molding of the parabolic fitting surface; the metal mesh 1 is fixedly connected to the main structure at the internal faceplate 6 and the boundary faceplate 7;

[0044] The pod rod assembly 8 is connected to the boundary flower disk 7 to provide a rigid boundary for the parabolic frame antenna, and at the same time acts as an adapter to connect to the drive motor to ensure that the deployment process and deployment speed of the parabolic frame antenna and the pod rod assembly 8 are controllable, thereby achieving speed control of the deployment process of the parabolic frame antenna.

[0045] Furthermore, the satellite-borne large-scale speed-controlled deployable frame antenna proposed by the present invention further includes: a tensioning rope 2 and a pressure mesh 5;

[0046] A pressing mesh 5 is installed at the connection between the internal faceplate 6, the boundary faceplate 7 and the metal mesh 1 to increase the contact area between the metal mesh 1 and the tetrahedral unit; a tensioning rope 2 is installed between adjacent internal faceplates 6 and boundary faceplates 7 to improve the fit of the metal mesh 1 to the fitting surface of the ideal parabolic cylinder.

[0047] Preferably, Figure 5 As shown, the metal mesh 1 is woven from metal wires and has the function of reflecting electromagnetic waves; the tension rope 2 is made of a carbon fiber inner core + a polyimide outer jacket; and the pressed mesh sheet 5 is made of polyimide.

[0048] The foldable synchronization rod 4 is a foldable mechanism formed by two carbon fiber rods engaged with each other through gears. During the folding and unfolding process, the rotation speed of the axes of the two carbon fiber rods around the rotating shaft of the foldable synchronization rod 4 is always consistent, and after being unfolded into place, they are locked in the form of complementary shapes.

[0049] The web 3 is formed by bonding metal joints at both ends of a hollow metal rod or a hollow carbon fiber rod, wherein the metal joints bonded at both ends are used to provide external interfaces. In areas susceptible to wear or impact, the web 3 is in the form of a hollow metal rod.

[0050] The internal faceplate 6 and the boundary faceplate 7 are components of the internal tetrahedron unit and the boundary tetrahedron unit respectively, which constrain the movement process of the web member 3 and the foldable synchronization rod 4 to prevent the folding and unfolding movement stroke of the web member 3 and the foldable synchronization rod 4 from exceeding the designed range.

[0051] When the frame antenna is deployed, there are four boundary lines parallel to the busbar direction. Considering the requirements for maintaining the frame antenna surface, the overall configuration of the payload and the feasibility of the project, the pod rod assembly 8 is arranged on 1≤N≤4 of the four boundary lines parallel to the busbar direction of the frame antenna; the pod rod assembly 8 is retracted under the action of external force, and after the external force is removed, it is deployed to the rigid rod by releasing its own stored energy.

[0052] like Figure 2 、 Figure 3 、 Figure 4 As shown, the pod rod assembly 8 includes: a pod rod 9, a pulley 10, a base 11 and a slip ring 12; the base 11 is the non-movable part of the pod rod assembly 8, providing an external interface for connection with the drive motor, and the relative position remains fixed; the pod rod 9 is the main structure of the pod rod assembly 8, used for forming the pod rod assembly 8, and is not directly connected to the antenna and the drive motor; the pulley 10 is a movable part of the pod rod assembly 8, which slides along the expansion direction of the pod rod 9 during the expansion of the pod rod 9. The slip ring 12, as a component of the pulley 10, is a circular ring structure. It is used as an adapter to connect the boundary disc 7 of the antenna to the pod rod 9, and has the function of self-position adjustment and adaptation.

[0053] like Figure 6 As shown, the pod rod 9 is made of a carbon fiber thin-walled tube, and its cross-section is a double-arch "Ω" shape.

[0054] like Figure 7 As shown, when the retracting strap is unlocked, the drive motor is turned on and outputs torque to drive the pod rod assembly 8 to perform one-dimensional extension movement along the axis of the pod rod 9. At this time, the slip ring 12 fixed to the boundary disc 7 slides relative to the pod rod 9 to achieve the boundary of the frame antenna. During this process, the movement of the boundary disc 7 is constrained by the movement of the pod rod assembly 8, and the movement of the pod rod assembly 8 is constrained by the drive motor.

[0055] The inner flower disc 6, the belly rod 3, and the foldable synchronization rod 4 perform adaptive movement with the boundary flower disc 7 as the boundary;

[0056] The driving motor continuously inputs drive until the pod rod assembly 8 is unfolded into place, the boundary flower disc 7 is unfolded into place synchronously, the internal flower disc 6, the belly rod 3, and the foldable synchronization rod 4 are also unfolded into place; the metal mesh 1, the tensioning rope 2, and the pressing mesh sheet 5 perform driven motion and are also unfolded to the designed position at the same time.

[0057] The speed of the speed-controlled deployable antenna is mainly controlled by controlling the driving speed of the driving motor to control the antenna deployment speed. In theory, as long as the driving motor movement speed is small enough, the requirement of low impact of the celestial body can be met.

[0058] Example:

[0059] like Figure 1As shown, the frame antenna and the pod rod assembly in the speed-controlled deployable antenna are in a stable state after being deployed into position at the same time.

[0060] The specific implementation process is now explained using a truss antenna with a deployed aperture of XX meters (in the direction of the parabola's main axis) and XX meters (in the direction of the parabola). The corresponding pod assembly 8 has an deployed length of XX meters. (Note: Based on theoretical analysis and experience with previous engineering prototypes, the XX-meter aperture is scalable and can accommodate micro, small, large, and even ultra-large apertures.)

[0061] The antenna is assembled from various components, each independently assembled. After assembly is complete, the components are assembled according to the designed layout. In this state, the retraction straps compress and retract the antenna frame, but the drive motor is not yet activated, and the antenna is in a stable state. Upon receiving the unlock command, the retraction straps are disconnected, preparing for deployment. The antenna will not deploy until the drive motor is activated.

[0062] Next, the drive motor is turned on at a low speed. It then generates torque, driving the pod rod assembly 8 in a one-dimensional extension motion along the axis of the pod rod 9. At this point, the slip ring 12, connected to the antenna boundary faceplate 7, slides relative to the pod rod, thereby limiting the antenna's perimeter. During this process, the movement of the boundary faceplate 7 is constrained by the movement of the pod rod assembly 7, while the movement of the pod rod assembly 8 is constrained by the drive motor. Therefore, the drive motor indirectly constrains the antenna's deployment process and speed, achieving the speed control of the antenna deployment process outlined in this patent. The internal faceplate 6, web 3, and foldable synchronization rod 4 adaptively move around the boundary faceplate 7. The motor continues to drive until the pod rod assembly 8 fully deploys. Simultaneously, the boundary faceplate 7, the internal faceplate 6, web 3, and foldable synchronization rod 4 also deploy. The metal mesh 1, tensioning rope 2, and pressure mesh sheet 5 also deploy to their designed positions through driven motion. At this point, the antenna deployment motion is complete.

[0063] The process of folding the antenna is opposite to the process of unfolding it.

[0064] The antenna storage ratio is greater than 15.

[0065] The antenna of the present invention has the inherent advantages of a truss antenna, such as a high storage ratio, reliable deployment, and high repeatability. At the same time, the deployment process and deployment speed are controlled by a speed control system, effectively avoiding the disadvantages of the truss antenna, such as large deployment impact and uncontrollable deployment process. The parabolic cylindrical structure allows the antenna aperture to be expanded as needed. Compared with traditional truss antennas, a set of pod rod assemblies is added, which can achieve better rigidity even when expanded to a larger aperture. This antenna can be widely used in large and even giant satellite-borne deployable truss antennas. At the same time, other flexible deployable antennas can also refer to its design to adapt to impact-sensitive space missions. It has broad application prospects.

[0066] The above description is only the best specific implementation method of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or replacements that can be easily thought of by any technician familiar with this technical field within the technical scope disclosed by the present invention should be covered by the scope of protection of the present invention.

[0067] The contents not described in detail in the present invention belong to the common knowledge of professionals in this field.

Claims

1. A large-scale satellite-borne speed-controlled deployment antenna, characterized in that include: Parabolic cylindrical frame antenna and pod pole assembly (8); The parabolic cylindrical frame antenna comprises: a metal mesh (1), a web (3), a foldable synchronization rod (4), an internal flower disc (6), and a boundary flower disc (7); The internal faceplate (6), the foldable synchronization rod (4) and the web (3) are assembled by screws and rivets to form an internal tetrahedron unit, the boundary faceplate (7), the foldable synchronization rod (4) and the web (3) are assembled by screws and rivets to form a boundary tetrahedron unit, and a plurality of internal tetrahedron units are spliced ​​to form the internal structure of the parabolic frame antenna. The boundary tetrahedron unit serves as the boundary of the parabolic frame antenna. The internal structure and the boundary eventually form the main structure of the parabolic frame antenna. The main structure is used for the antenna emitting surface, that is, the parabolic fitting surface. The metal mesh (1) is fixedly connected to the main structure at the internal faceplate (6) and the boundary faceplate (7). The pod rod assembly (8) is connected to the boundary flower disk (7) to provide a rigid boundary for the parabolic frame antenna, and is also connected to the driving motor as an adapter to ensure that the deployment process and deployment speed of the parabolic frame antenna and the pod rod assembly (8) are controllable, thereby achieving speed control of the deployment process of the parabolic frame antenna.

2. The large-scale, speed-controlled deployment antenna for spacecraft according to claim 1, characterized in that: Also includes: Tension rope (2) and pressure mesh (5); A mesh pressing sheet (5) is installed at the connection between the internal faceplate (6), the boundary faceplate (7) and the metal mesh (1) to increase the contact area between the metal mesh (1) and the tetrahedron unit; and a tensioning rope (2) is installed between adjacent internal faceplates (6) and boundary faceplates (7) to improve the fit of the metal mesh (1) to the fitting surface of the ideal parabolic cylinder.

3. The large-scale, speed-controlled deployment antenna for spacecraft according to claim 2, characterized in that: The metal mesh (1) is woven from metal wires and has the function of reflecting electromagnetic waves; the tension rope (2) is made of a carbon fiber inner core and a polyimide outer jacket; and the pressed mesh sheet (5) is made of polyimide.

4. The large-scale, speed-controlled deployment antenna for spacecraft according to claim 1 or 2, characterized in that: The foldable synchronization rod (4) is a foldable mechanism formed by two carbon fiber rods in the form of gear meshing. During the folding and unfolding process of the two carbon fiber rods, the rotation speeds of the axes of the two carbon fiber rods around the rotating shaft of the foldable synchronization rod (4) are always consistent, and after being unfolded into place, they are locked in the form of complementary shapes.

5. The large-scale, speed-controlled deployable satellite antenna according to claim 1 or 2, characterized in that: The web (3) is formed by bonding metal joints at both ends of a hollow metal rod or a hollow carbon fiber rod, wherein the metal joints bonded at both ends are used to provide external interfaces. In areas susceptible to wear or impact, the web (3) is in the form of a hollow metal rod.

6. The large-scale, speed-controlled deployable satellite antenna according to claim 1 or 2, characterized in that: The internal faceplate (6) and the boundary faceplate (7) are components of the internal tetrahedron unit and the boundary tetrahedron unit respectively, and constrain the movement process of the web rod (3) and the foldable synchronization rod (4), so as to prevent the folding and unfolding movement stroke of the web rod (3) and the foldable synchronization rod (4) from exceeding the design range.

7. The large-scale, speed-controlled deployment antenna for spacecraft according to claim 1 or 2, characterized in that: When the frame antenna is in an unfolded state, there are four boundary lines in a direction parallel to the busbar. Considering the requirements for maintaining the shape of the frame antenna, the overall configuration of the effective load and the feasibility of the project, the pod rod assembly (8) is arranged on 1≤N≤4 boundaries of the four boundary lines in the direction parallel to the busbar of the frame antenna; the pod rod assembly (8) is folded under the action of an external force, and is unfolded to the rigid rod by releasing its own stored energy after the external force is removed.

8. The large-scale, speed-controlled deployable satellite antenna according to claim 7, characterized in that: The pod rod assembly (8) comprises: a pod rod (9), a pulley (10), a base (11) and a slip ring (12); the base (11) is a non-movable part of the pod rod assembly (8), providing an external interface for connection with a drive motor, and the relative position is kept fixed; the pod rod (9) is the main structure of the pod rod assembly (8), used for forming the pod rod assembly (8), and is not directly connected to the antenna and the drive motor; the pulley (10) is a movable part of the pod rod assembly (8), and slides along the expansion direction of the pod rod (9) during the expansion of the pod rod (9); the slip ring (12) is a component of the pulley (10), and is a circular ring structure. It is used as an adapter for connecting the boundary flower disc (7) of the antenna with the pod rod (9), and has the function of position self-adjustment and adaptation.

9. The large-scale, speed-controlled deployment antenna for spacecraft according to claim 7, characterized in that: The bean pod rod (9) is made of a carbon fiber thin-walled tube, and its cross-section is a double-arch "Ω" shape.

10. The large-scale, speed-controlled deployable satellite antenna according to claim 7, characterized in that: When the retracting band is unlocked, the drive motor is turned on and outputs torque to drive the pod rod assembly (8) to perform one-dimensional stretching movement along the axis of the pod rod (9). At this time, the slip ring (12) fixedly connected to the boundary flower disc (7) slides relative to the pod rod (9) to achieve the boundary of the frame antenna. In this process, the movement of the boundary flower disc (7) is constrained by the movement of the pod rod assembly (8), and the movement of the pod rod assembly (8) is constrained by the drive motor. The inner flower disc (6), the belly rod (3), and the foldable synchronization rod (4) perform adaptive movement with the boundary flower disc (7) as the boundary; The driving motor continuously inputs driving until the pod rod assembly (8) is unfolded into place, the border flower disc (7) is unfolded into place synchronously, the inner flower disc (6), the belly rod (3), and the foldable synchronous rod (4) are also unfolded into place; the metal mesh (1), the tensioning rope (2), and the mesh pressing sheet (5) are also unfolded to the designed position by performing driven motion.

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