Torsion Spring Driven Scissor-Hinge Ring Rib Deployable Antenna Mechanism

Abstract

The present invention provides a torsion spring-driven scissor-joint ring rib type deployable antenna mechanism, which comprises a radially deployable unit and a circumferentially deployable unit. The radially deployable unit includes an inner flower disc, a first scissor rod, a second scissor rod, a third scissor rod and an outer flower disc. The radially deployable units are arranged in a circumferential array outside the inner flower disc. The radially deployable unit is connected to the circumferentially deployable unit through the outer flower disc. The circumferentially deployable units are sequentially connected end to end through the outer flower disc. The circumferentially deployable unit includes folding rods and a torsion spring-driven assembly. The folding rods are connected by the torsion spring-driven assembly. By adjusting the number of the radially deployable unit and the circumferentially deployable unit and the lengths of the scissor rods and folding rods constituting the units, the present invention forms a deployable antenna mechanism with any aperture size, having the advantages of good manufacturing processability, high stiffness and large folding ratio, solving the problems of complex structure, low reliability and poor stiffness and strength of the existing deployable antenna mechanism, and being better applied to communication satellites, space stations and space probes.

Description

Technical Field

[0001] The present invention relates to the technical field of antenna mechanisms, and particularly relates to a torsion spring-driven scissors hinge ring rib type deployable antenna mechanism. Background Art

[0002] With the needs of communication, space science, earth observation, and national defense construction, the demand for large space antennas in various countries has become more urgent. When the size of the antenna exceeds the range that can be accommodated by the fairing of a launch vehicle (or a space shuttle), it is necessary to adopt the structure form of a deployable antenna. During the launch phase, these large antennas must be folded up, and after the spacecraft enters the predetermined orbit, they are then deployed into the working state by a driver. Due to the advantages of light weight, small occupied space, and convenience for storage and transportation, space deployable mechanisms are widely used in spacecraft such as communication satellite platforms, space stations, space telescopes, and space vehicles. The deployable mechanism has become one of the research hotspots in the aerospace field.

[0003] Researchers in various countries have conducted a large amount of research on deployable antenna mechanisms. The existing types of deployable mechanisms are few. As the antenna aperture increases, the antenna stiffness decreases severely. The truss deployable antenna can improve the overall stiffness of the antenna mechanism by using tension cables, but the tension cables are relatively complex, difficult to control, and also reduce the reliability of the overall structure. Entanglement is very likely to occur during the deployment process, causing the truss antenna deployment to fail and resulting in huge economic losses. Therefore, it is urgent to propose a deployable antenna mechanism with excellent performance such as good manufacturability, high stiffness, and large folding ratio to meet the requirements of different space missions. Summary of the Invention

[0004] Aiming at the problems existing in the prior art, the present invention provides a torsion spring-driven scissors hinge ring rib type deployable antenna mechanism. By driving the folding rod with a torsion spring and the combined drive of each scissors rod and the folding rod, the synchronization of the mechanism deployment and the stability of the overall structure during the movement process are ensured. By changing the number of radially deployable units and circumferentially deployable units and the lengths of the scissors rods and folding rods constituting each unit, a deployable antenna mechanism with any aperture size is formed, solving the problems of complex structure, low reliability, and poor stiffness and strength of the existing deployable antenna mechanism, and being better applied to communication satellites, space stations, and space probes.

[0005] The present invention provides a torsion spring-driven scissors-joint ring rib deployable antenna mechanism, which includes a radially deployable unit and a circumferentially deployable unit. The radially deployable units are arranged in a circumferential array outside the inner flower plate. The radially deployable units are connected to the circumferentially deployable unit through an outer flower plate. The circumferentially deployable units are sequentially connected end to end through the outer flower plate. The radially deployable unit includes an inner flower plate, a first scissors rod, a second scissors rod, a third scissors rod, and an outer flower plate. The first end of the first scissors rod is rotatably connected to the fork on the inner flower plate. The second end of the first scissors rod is rotatably connected to the first end of the second scissors rod. The second end of the second scissors rod is rotatably connected to the first end of the third scissors rod. The second end of the third scissors rod is rotatably connected to the middle fork on the outer flower plate. The cross positions between the first scissors rod, the second scissors rod, and the third scissors rod are all connected through rotating pairs. The circumferentially deployable unit includes a folding rod and a torsion spring drive assembly. The folding rods are rotatably connected through the torsion spring drive assembly. The first end of the folding rod is rotatably connected to the side fork on the outer flower plate. The torsion spring drive assembly includes a torsion spring, a pin shaft, and a torsion spring support. The torsion spring is sleeved on the pin shaft. The first end of the torsion spring is connected to the second end of the folding rod. The second end of the torsion spring is connected to the torsion spring support. A through hole is provided on the torsion spring support. The second end of the folding rod is a groove structure, and a through hole is provided on the groove. The two ends of the pin shaft are sequentially inserted into the through holes of the torsion spring support and the second end of the folding rod.

[0006] Preferably, the inner flower plate is provided with N forks and is a face-symmetric structure as a whole. The included angle between the symmetry planes of the adjacent fork notches on the inner flower plate is (360 / N)°. The distances between the axes of the rotating pairs of the forks on the inner flower plate and the central axis of the inner flower plate are equal. Grooves are provided on the forks of the inner flower plate for inserting the first scissors rod and connecting through a rotating pair.

[0007] Preferably, the outer flower plate is provided with a middle fork and two side forks, and grooves are provided on the forks. The overall structure is symmetric about the symmetry plane of the middle fork notch. The included angle between the symmetry plane of the middle fork notch and the symmetry plane of the side fork notch is [180(N - 2) / 2N]°. The distances between the axes of the rotating pairs of the middle fork and the side forks and the central axis of the outer flower plate are equal. The middle fork is used for inserting the second end of the third scissors rod and connecting through a rotating pair. The side fork is used for inserting the first end of the folding rod and connecting through a rotating pair.

[0008] Preferably, the axes of the rotating pairs between the scissors rods of the N radially deployable units are all parallel. The axes of the rotating pairs connected to the first scissors rod and the third scissors rod are all parallel. The axes of the rotating pairs connected to the folding rod are all parallel.

[0009] Preferably, by changing the number of the radially expandable units and the circumferentially expandable units and the length of each scissor rod constituting the units, a torsion spring-driven scissor-hinge ring-rib type expandable antenna mechanism of any caliber size is formed.

[0010] Preferably, when the deployable antenna mechanism is fully deployed, the distance between the inner flower discs in the radially deployable unit is shortest, each scissor rod extends radially along the inner flower disc, the folding rods in the circumferentially deployable unit connected by the torsion spring drive assembly are collinear, and N circumferentially deployable units form a circumferential annular truss assembly through the outer flower disc, and the circumferential annular truss assembly is a multi-faceted annular truss structure after deployment and folding; when the deployable antenna mechanism is half-deployed, a certain angle is formed between each scissor rod and the folding rod; when the deployable antenna mechanism is fully folded, each scissor rod and the folding rod are in a folded state, at which time the distance between the inner flower discs in the radially deployable unit is the farthest, and the overall structure shrinks into a cylindrical structure.

[0011] Preferably, the first scissors rod, the second scissors rod, the third scissors rod and the folding rod are all made of carbon fiber composite material or aviation aluminum alloy material.

[0012] Compared with the prior art, the present invention has the following advantages:

[0013] 1. During the unfolding process of the unfoldable antenna of the present invention, the folding rod is driven to move by a torsion spring, and no power source is required, thereby reducing the weight of the overall mechanism. The torsion spring drive has a fast response and can be quickly unfolded after the constraint disappears. Rotary pairs are used at the connection points of the mechanism, and each scissor rod and the folding rod are driven in linkage to ensure the synchronization of the unfolding of the mechanism and the stability of the overall structure during the movement.

[0014] 2. The N circumferentially deployable units of the present invention are connected end to end in sequence through an external faceplate to form a circumferential annular truss assembly. The circumferential annular truss assembly is a multi-faceted annular truss structure when unfolded or folded, thereby enhancing the rigidity of the entire antenna mechanism and effectively solving the problem of reduced rigidity of the existing deployable antenna mechanism due to the increase in antenna aperture. It has the advantages of good manufacturing processability, high rigidity and large folding ratio, and meets the rigidity requirements for large-aperture space antennas.

[0015] 3. The present invention adopts the design of a deployable antenna mechanism. During launch, the antenna mechanism is in a folded state, which effectively saves the launch space of the rocket. After entering orbit, the antenna mechanism is deployed to a working state. Moreover, by changing the number of radial deployable units and circumferential deployable units in the deployable antenna mechanism and the length of each scissor rod, a deployable antenna mechanism of any caliber is formed, thereby solving the problems of the existing deployable antenna mechanism, such as complexity, low reliability, and poor rigidity and strength, and can be better applied to communication satellites, space stations, and space probes. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic diagram of the overall structure of the torsion spring-driven scissors hinge ring rib type deployable antenna mechanism of the present invention when it is fully deployed;

[0017] Figure 2 This is a schematic diagram of the overall structure of the torsion spring-driven scissors hinge ring rib type deployable antenna mechanism of the present invention when it is semi-deployed;

[0018] Figure 3 This is a schematic diagram of the overall structure of the torsion spring-driven scissors hinge ring rib type deployable antenna mechanism of the present invention when it is fully retracted;

[0019] Figure 4 This is a schematic diagram of the overall structure of the radially deployable unit of the present invention when it is fully deployed;

[0020] Figure 5 This is a schematic diagram of the overall structure of the circumferentially deployable unit of the present invention when it is fully deployed;

[0021] Figure 6 This is a schematic diagram of the structure of the torsion spring drive assembly in the radially deployable unit of the present invention;

[0022] Figure 7 This is a schematic diagram of the structure of the inner flower disc in the torsion spring-driven scissors hinge ring rib type deployable antenna mechanism of the present invention;

[0023] Figure 8 This is a schematic diagram of the structure of the outer flower disc in the torsion spring-driven scissors hinge ring rib type deployable antenna mechanism of the present invention.

[0024] Main reference numerals:

[0025] Radially deployable unit 1, inner flower disc 11, first scissors rod 12, second scissors rod 13, third scissors rod 14, outer flower disc 15, intermediate fork 151, side fork 152, circumferentially deployable unit 2, folding rod 21, torsion spring drive assembly 22, torsion spring 221, pin shaft 222, torsion spring support 223. Detailed description of the preferred embodiments

[0026] To elaborate on the technical content, structural features, achieved objectives and effects of the present invention in detail, the following will be described in detail with reference to the accompanying drawings of the specification.

[0027] The torsion spring-driven scissors hinge ring rib type deployable antenna mechanism provided by the present invention, as shown in Figures 1 to 3As shown in the figure, it includes a radially deployable unit 1 and a circumferentially deployable unit 2. The radially deployable units 1 are arranged in a circumferential array outside the inner flower plate 11. The radially deployable units 1 are connected to the circumferentially deployable unit 2 through the outer flower plate 15. The circumferentially deployable units 2 are sequentially connected end to end through the outer flower plate 15. By changing the number of the radially deployable units 1 and the circumferentially deployable units 2 and the lengths of the scissor rods forming each unit, a torsion spring-driven scissor hinge ring rib type deployable antenna mechanism with any aperture size is formed. When the deployable antenna mechanism is fully deployed, the distance between the inner flower plates 11 in the radially deployable units 1 is the closest. Each scissor rod extends along the radial direction of the inner flower plate 11. The folding rods 21 connected by the torsion spring drive assembly 22 in the circumferentially deployable unit 2 are collinear. N circumferentially deployable units 2 form a circumferential ring truss assembly through the outer flower plate 15. The circumferential ring truss assembly is a multi-faceted ring truss structure both after deployment and retraction; when the deployable antenna mechanism is half deployed, a certain angle is formed between each scissor rod and the folding rod 21; when the deployable antenna mechanism is fully retracted, each scissor rod and the folding rod 21 are in a retracted state. At this time, the distance between the inner flower plates 11 in the radially deployable units 1 is the farthest, and the overall structure shrinks into a cylindrical structure.

[0028] As Figure 4 shown, the radially deployable unit 1 includes an inner flower plate 11, a first scissor rod 12, a second scissor rod 13, a third scissor rod 14 and an outer flower plate 15. The first end of the first scissor rod 12 is rotatably connected to the fork on the inner flower plate 11. The second end of the first scissor rod 12 is rotatably connected to the first end of the second scissor rod 13. The second end of the second scissor rod 13 is rotatably connected to the first end of the third scissor rod 14. The second end of the third scissor rod 14 is rotatably connected to the intermediate fork 151 on the outer flower plate 15. The cross positions among the first scissor rod 12, the second scissor rod 13 and the third scissor rod 14 are all connected through rotating pairs. The axes of the rotating pairs between the scissor rods of N radially deployable units 1 are all parallel. The axes of the rotating pairs connected to the first scissor rod 12 and the third scissor rod 13 are all parallel. The axes of the rotating pairs connected to the folding rod 21 are all parallel.

[0029] As Figure 5 and Figure 6As shown in the figure, the circumferential deployable unit 2 includes folding rods 21 and a torsion spring drive assembly 22. The folding rods 21 are rotationally connected through the torsion spring drive assembly 22. The first end of the folding rod 21 is rotationally connected to the side fork 152 on the outer flower disc 15. The torsion spring drive assembly 22 includes a torsion spring 221, a pin shaft 222, and a torsion spring support 223. The torsion spring 221 is sleeved on the pin shaft 222. The first end of the torsion spring 221 is connected to the second end of the folding rod 21, and the second end of the torsion spring 221 is connected to the torsion spring support 223. A through hole is provided on the torsion spring support 223. The second end of the folding rod 21 is a groove structure, and a through hole is provided on the groove. The two ends of the pin shaft 222 are sequentially inserted into the through holes of the torsion spring support 223 and the second end of the folding rod 21. The first scissor rod 12, the second scissor rod 13, the third scissor rod 14, and the folding rod 21 are all made of carbon fiber composite material or aviation aluminum alloy material.

[0030] As Figure 7 shown, the inner flower disc 11 is provided with N forks and is a face-symmetric structure as a whole. The included angle between the symmetry planes of adjacent fork notches on the inner flower disc 11 is (360 / N)°. The distance between the axis of the fork rotating pair on the inner flower disc 11 and the central axis of the inner flower disc 11 is equal. Grooves are provided on the forks of the inner flower disc 11 for inserting the first scissor rod 12 and connecting through a rotating pair.

[0031] As Figure 8 shown, the outer flower disc 15 is provided with an intermediate fork 151 and two side forks 152, and grooves are provided on the forks. The overall structure is symmetric about the symmetry plane of the intermediate fork 151 notch. The included angle between the symmetry plane of the intermediate fork 151 notch and the symmetry plane of the side fork 152 notch is [180(N - 2) / 2N]°. The distances between the axes of the rotating pairs of the intermediate fork 151 and the side fork 152 and the central axis of the outer flower disc 15 are equal. The intermediate fork 151 is used for inserting the second end of the third scissor rod 14 and connecting through a rotating pair, and the side fork 152 is used for inserting the first end of the folding rod 21 and connecting through a rotating pair.

[0032] The following further describes a torsion spring-driven scissor hinge ring rib type deployable antenna mechanism of the present invention in conjunction with embodiments:

[0033] Embodiment:

[0034] In this embodiment, the torsion spring-driven scissor hinge ring rib type deployable antenna mechanism includes N radial deployable units 1 and N circumferential deployable units 2, where N is an integer greater than or equal to 3. The radial deployable units 1 are connected to each other through sharing two inner flower discs 11 and N circumferential deployable units 2. The multiple circumferential deployable units 2 are sequentially connected end to end through sharing two outer flower discs 15 to form a circumferential ring truss assembly. The circumferential ring truss assembly is a multi-faceted ring truss structure both after deployment and retraction.

[0035] The operation process of this embodiment is realized as follows:

[0036] For the torsion spring-driven scissors-joint ring rib deployable antenna mechanism of the present invention, according to the changes in the satellite folding and deploying antenna mission, it is adjusted by the dimensions and quantities of the radial deployable unit 1 and the circumferential deployable unit 2 to form a deployable antenna mechanism with any aperture size. When the folding and deploying antenna mechanism is launched by a rocket, it is housed in the payload compartment of the rocket. The radial deployable unit 1 and the circumferential deployable unit 2 are in a fully retracted state. At this time, the overall volume of the folding and deploying antenna mechanism is the smallest. At the initial moment, the deployable antenna mechanism is in a retracted state, the folding rod 21 is in a folded state, the radial deployable unit 1 is in a retracted state, and the torsion spring 221 is compressed and deformed under the pressure of the two ends of the folding rod 21, storing elastic potential energy. At this time, the whole mechanism is retracted into a cylinder, and the radial deployable unit 1 is arranged along the radial direction of the cylinder. The mechanism is constrained and housed by a container to form a cylinder with a smaller volume, effectively saving the launch space of the rocket.

[0037] When the satellite enters the orbit, the folding and deploying antenna mechanism executes unlocking according to the mission command. When it reaches the designated position of the antenna and starts to work, the binding force disappears, and the circumferential deployable unit 2 starts to deploy. The elastic potential energy stored in the torsion spring 221 is released. Under the action of the elastic force of the torsion spring, the folding rod 21 rotates 90° along the axis direction from its original position, and the adjacent folding rods 21 form a straight line, becoming a circumferential deployable unit 2 of the outer ring circumference. At this time, the elastic force of the torsion spring 221 disappears, and the folding rod 21 remains in a straight state. During the deployment process, the folding rod 21 is affected by the elastic force of the torsion spring 221, and the first scissors rod 12, the second scissors rod 13, and the third scissors rod 14 expand radially outward along the inner flower disc 11, and the lateral distance of the radial deployable unit 1 increases. During the expansion process, the elastic force of the torsion spring 221 gradually decreases, and continuously provides sufficient elastic driving force for the movement of the folding rod 21 during the deployment process, so that the whole mechanism expands from a cylinder structure into a regular N-sided polygon structure.

[0038] In the retracted state of the deployable antenna, the folding rod 21 is in a folded shape. At this time, the deformation amount of the torsion spring 221 is the largest, and the elastic force is also the largest. During the deployment process, the rebound of the torsion spring 221 drives the folding rod 21 to expand outward, driving the third scissors rod 14 connected to the outer flower disc 15 to also extend outward. After the folding rod 21 extends to the limit position, at this time, the adjacent folding rods 21 connected by the torsion spring drive assembly 22 are collinear, and the first scissors rod 12, the second scissors rod 13, and the third scissors rod 14 no longer expand outward. The torsion spring 221 maintains a certain elastic force acting on the adjacent two folding rods 21, forcing the two folding rods 21 not to rotate in the reverse direction, preventing the deployable antenna mechanism from retracting, and enabling it to continuously maintain the deployed state, realizing locking and solidification.

[0039] The embodiments described above are only descriptions of the preferred embodiments of the present invention, and do not limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made by those of ordinary skill in the art to the technical solutions of the present invention shall fall within the protection scope determined by the claims of the present invention.

Claims

1. A torsion spring driven shear hinge ring rib type deployable antenna mechanism, It is characterized in that It comprises radially expandable units and circumferentially expandable units, wherein the radially expandable units are arranged in a circumferential array outside the inner faceplate, the radially expandable units are connected to the circumferentially expandable units through the outer faceplate, and the circumferentially expandable units are sequentially connected end to end through the outer faceplate. The radially expandable unit comprises an inner faceplate, a first scissor rod, a second scissor rod, a third scissor rod and an outer faceplate, wherein the first end of the first scissor rod is rotatably connected to a branch fork on the inner faceplate, the second end of the first scissor rod is rotatably connected to the first end of the second scissor rod, the second end of the second scissor rod is rotatably connected to the first end of the third scissor rod, the second end of the third scissor rod is rotatably connected to the middle branch fork on the outer faceplate, and the first scissor rod, the second scissor rod and the third scissor rod are all connected at their intersections through a rotating pair; The inner faceplate is provided with N forks and is a plane-symmetrical structure as a whole. The angle between the symmetry planes of adjacent fork notches on the inner faceplate is (360 / N)°. The distance between the rotational sub-axis of the forks of the inner faceplate and the central axis of the inner faceplate is equal. The forks of the inner faceplate are provided with notches for inserting the first scissor rod and connecting through a rotational pair. The circumferentially expandable unit comprises a folding rod and a torsion spring drive assembly, the folding rods are rotatably connected through the torsion spring drive assembly, the first end of the folding rod is rotatably connected to the side branch fork on the outer faceplate, the torsion spring drive assembly comprises a torsion spring, a pin shaft and a torsion spring support, the torsion spring is sleeved on the pin shaft, the first end of the torsion spring is connected to the second end of the folding rod, the second end of the torsion spring is connected to the torsion spring support, a through hole is provided on the torsion spring support, the second end of the folding rod is a groove structure, and a through hole is provided on the groove, and the two ends of the pin shaft are successively penetrated in the through holes of the torsion spring support and the second end of the folding rod; The torsion spring drive assembly drives the folding rod to move. At the same time, the torsion spring drive assembly is unfolded after the constraint disappears. The connection parts of the mechanism all adopt rotating pairs, and each scissor rod and the folding rod are driven in linkage.

2. The torsion spring driven shear hinge ring rib type deployable antenna mechanism according to claim 1, It is characterized in that The outer flower disc is provided with a middle branch fork and two side branch forks, and the branches are provided with slots. The overall structure is symmetrical with the symmetry plane of the middle branch fork slot. The angle between the symmetry plane of the middle branch fork slot and the symmetry plane of the side branch fork slot is [180(N-2) / 2N]°. The distances between the rotational secondary axes of the middle branch fork and the side branch forks and the central axis of the outer flower disc are equal. The middle branch fork is used to insert into the second end of the third scissor fork rod and is connected through a rotational secondary. The side branch fork is used to insert into the first end of the folding rod and is connected through a rotational secondary.

3. The torsion spring driven shear hinge ring rib type deployable antenna mechanism according to claim 1, It is characterized in that The axes of the rotating pairs between the scissors rods of the N radial deployable units are all parallel, the axes of the rotating pairs connected to the first scissors rod and the third scissors rod are all parallel, and the axes of the rotating pairs connected to the folding rod are all parallel.

4. The torsion spring-driven scissor hinge ring rib type deployable antenna mechanism according to claim 1, characterized in that, by changing the number of the radial deployable units and the circumferential deployable units and the lengths of the scissors rods constituting the units, a torsion spring-driven scissor hinge ring rib type deployable antenna mechanism with any aperture size is formed.

5. The torsion spring-driven scissor hinge ring rib type deployable antenna mechanism according to any one of claims 1 to 4, characterized in that, when the deployable antenna mechanism is fully deployed, the distance between the inner flower discs in the radial deployable units is the closest, each scissors rod extends along the radius of the inner flower disc, the folding rods connected by the torsion spring drive assembly in the circumferential deployable units are collinear, the N circumferential deployable units form a circumferential ring truss assembly through the outer flower discs, and the circumferential ring truss assembly is a multi-faceted ring truss structure after deployment and retraction; when the deployable antenna mechanism is semi-deployed, a certain angle is formed between each scissors rod and the folding rod; when the deployable antenna mechanism is fully retracted, each scissors rod and the folding rod are in a retracted state, and at this time the distance between the inner flower discs in the radial deployable units is the farthest, and the overall structure shrinks into a cylindrical structure.

6. The torsion spring-driven scissor hinge ring rib type deployable antenna mechanism according to any one of claims 1 to 5, characterized in that, the first scissors rod, the second scissors rod, the third scissors rod and the folding rod are all made of carbon fiber composite material or aviation aluminum alloy material.

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