A cone-shaped spatially deformable honeycomb structure

Abstract

The present invention discloses a cone-dimensional space deformable honeycomb structure, which belongs to the field of aerospace technology. The cone-dimensional space deformable honeycomb structure includes an annular space honeycomb structure and a drive system, and the annular space honeycomb structure is deformed along a cone with a fixed taper by controlling the drive system. The annular space honeycomb structure includes a plurality of honeycomb units with a concave hexagonal structure, each honeycomb unit includes two beams of different lengths and four ribs of the same length and structure, and the beams and ribs, and the ribs and ribs are connected by hinges; the drive system includes a main frame, a motor, a synchronous pulley, a trapezoidal screw and a clamp. The present invention designs an annular space honeycomb structure, which can achieve fitting of the target cone by reasonably designing the rod size in the honeycomb unit; at the same time, a drive system of the honeycomb structure is designed, and the honeycomb structure can be deformed along a cone with a fixed taper by controlling the drive system.

Description

Technical Field

[0001] The present invention relates to a deformable honeycomb structure, in particular to a cone-shaped space deformable honeycomb structure, belonging to the field of aerospace technology. Background Art

[0002] Space retraction and deployment mechanisms have rapidly developed with the advent of aerospace technology. They are the optimal solution for solving engineering problems in the aerospace field and the primary approach to resolving the conflict between the structural requirements of large spacecraft and the limitations of rocket launch envelopes. Retraction and deployment mechanisms are generally represented by extensions of basic units composed of rods, cables, and membranes. They are simple, highly rigid, and super-constrained systems. In recent years, supported by major national projects such as manned space flight, lunar exploration, Mars exploration, large space telescopes, and high-resolution Earth observation, space retraction and deployment mechanism technology has made significant progress and has been widely applied in space engineering projects such as large-diameter satellite antennas, space station masts, solar arrays, and Mars / Lunar rovers. However, conical retraction and deployment mechanisms are relatively rare in existing technologies, and deformable conical mechanisms are relatively rare. Space rod-based mechanisms and umbrella-type mechanisms are primarily capable of conical fitting. Existing research results primarily focus on the transformation from a small-volume retracted state to a large-scale operating state, and lack the ability to continuously deform the conical surface.

[0003] Therefore, it is urgent to propose a cone-shaped spatially deformable honeycomb structure to solve the above technical problems. Summary of the Invention

[0004] In order to solve the problem that a spatial mechanism cannot realize a continuous cone-shaped shape, the present invention proposes a cone-shaped spatially deformable honeycomb mechanism.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions:

[0006] A conical-dimensional spatial deformable honeycomb structure comprises an annular honeycomb structure and a drive system. The annular honeycomb structure comprises multiple honeycomb units with an inwardly concave hexagonal structure. Each honeycomb unit comprises two beams of different lengths and four ribs of identical length and structure. The beams and ribs are connected by hinges. The drive system comprises a main frame, a motor, a synchronous pulley, a trapezoidal screw, and a clamp. The motor, synchronous pulley, and trapezoidal screw are mounted on the main frame. The motor drives the trapezoidal screw to rotate synchronously via the synchronous pulley. The trapezoidal screw is arranged along the generatrix of the conical surface and has the same taper as the annular honeycomb structure. The clamp is mounted on the trapezoidal screw and connected to the nut of the trapezoidal screw. The end of the clamp is fixedly connected to the top beam of the annular honeycomb structure. The annular honeycomb structure is deformed along the conical surface of a fixed taper by controlling the drive system. The inwardly concave hexagonal structure of the honeycomb units of the annular honeycomb structure exhibits a negative Poisson's ratio. When subjected to axial compression, it contracts axially while decreasing radially. The annular space honeycomb structure has three honeycomb unit layers, with n honeycomb units in each layer, and a total of five groups of beams of different lengths. The dimensional relationship of the honeycomb units is:

[0007] Let the cone angle be , the length of the i-th layer beam from bottom to top is ( ), the rib length is m, then the angle between each hinge axis and the cone bottom in the annular space honeycomb structure should be , the angle between the projections of the two hinge axes on the beam on the bottom of the cone should be ,set up , ,but:

[0008] .

[0009] Furthermore, in the annular space honeycomb structure, the number n of honeycomb units in each layer is 6 or 12, ensuring a good fitting effect on the target cone surface.

[0010] Furthermore, the number of honeycomb units and the length relationship between the beams and ribs of the annular space honeycomb structure can be adjusted according to the size of the target cone surface to achieve fitting of cone surfaces of different sizes.

[0011] Furthermore, the number of synchronous pulleys and trapezoidal screws in the drive system is four, and the four trapezoidal screws are evenly distributed on the main frame along the same circumference with the center of the main frame as the center of the circle. The four synchronous pulleys are respectively installed above the trapezoidal screws, and the four synchronous pulleys are driven to rotate synchronously by a motor, thereby driving the four groups of trapezoidal screws to rotate synchronously.

[0012] Furthermore, the trapezoidal lead screw of the drive system has a self-locking feature, which is used to reduce the difficulty of locking the honeycomb mechanism.

[0013] Furthermore, the expansion and contraction states of the honeycomb structure include an open state, an intermediate state and a collapsed state, and the deformation of the annular space honeycomb structure is controlled by the driving system to achieve continuous conical surface deformation.

[0014] Furthermore, the driving system controls the opening and closing of the claws to achieve the gradual opening and closing of the honeycomb structure.

[0015] The beneficial effects of the present invention are:

[0016] 1. The present invention, through the design of an annular space honeycomb structure and a supporting drive system, can achieve continuous conical deformation along a fixed taper, meeting the demand for dynamic adjustment of the cone shape in complex space missions. It has a compact structure, high rigidity, reliable drive and strong adaptability.

[0017] 2. The honeycomb unit of this invention adopts a concave hexagonal structure, which has a negative Poisson's ratio. When subjected to axial compression, the radial dimension decreases simultaneously, enabling the mechanism to achieve a highly compact folding state. This significantly reduces the space occupied by the mechanism in the collapsed state, making it particularly suitable for scenarios with strict envelope constraints, such as rocket launches. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic structural diagram of an embodiment of the annular space honeycomb structure of the present invention;

[0019] Figure 2 It is a structural schematic diagram of an embodiment of the honeycomb unit of the present invention;

[0020] Figure 3 yes Figure 2 Schematic diagram of the three-dimensional structure;

[0021] Figure 4 It is a schematic structural diagram of the annular space honeycomb structure of the present invention in the collapsed and expanded states;

[0022] Figure 5 It is a structural schematic diagram of an embodiment of the drive system of the present invention.

[0023] In the figure: 1. Annular space honeycomb structure; 11. Beam; 12. Rib; 2. Drive system; 21. Motor assembly; 22. Guide wheel; 23. Synchronous pulley assembly; 24. Synchronous belt; 25. Main frame; 26. Trapezoidal screw assembly; 27. Clamping claw. DETAILED DESCRIPTION

[0024] Specific implementation method 1: Combination Figure 1-4This embodiment describes a conical-dimensional space deformable honeycomb structure, which includes an annular space honeycomb structure and a drive system. The annular space honeycomb structure is deformed along a conical surface with a fixed taper by controlling the drive system.

[0025] like Figure 1 and Figure 2 As shown, the annular honeycomb structure comprises multiple honeycomb units with an inward-concave hexagonal structure. Each unit consists of two beams of different lengths and four ribs of identical length and structure. The beams and ribs are connected by hinges, and the ribs are connected to each other. This hinged connection forms a super-constrained system, resulting in a highly rigid and stable overall structure. A common two-dimensional honeycomb structure is converted into a three-dimensional form, where the honeycomb units adopt an inward-concave hexagonal structure. From a mechanical perspective, this inward-concave hexagonal structure exhibits a negative Poisson's ratio, meaning that when subjected to axial compression, the units contract axially and radially simultaneously. Specifically, under axial compression, the units contract in both the axial and radial dimensions, enabling the honeycomb structure to achieve a compact fold in the collapsed state. Under axial tension, the units extend in the axial direction and expand in the radial direction, enabling the structure to expand over a large area in the expanded state. In the collapsed state, the structure is more compact, reducing space usage and improving expansion and contraction efficiency. In the expanded state, the structure is better able to maintain its shape and rigidity, adapt to complex external loads, and enhance structural stability. This enables the honeycomb structure to achieve smooth, continuous deformation, meeting the requirements for continuous conical surface deformation while also improving the structure's energy absorption capacity and impact resistance. This characteristic significantly reduces the space occupied by the structure in its collapsed state, making it particularly suitable for scenarios with strict envelope constraints, such as rocket launches. It is also particularly important in space environments, effectively handling complex external loads and vibrations.

[0026] Specifically, the annular honeycomb structure has three layers of honeycomb cells, with twelve cells per layer. Five groups of beams of varying lengths are used. By properly controlling the length relationships between beams and between beams and ribs, honeycomb structures with tapered surfaces of varying sizes can be created.

[0027] The dimensional relationship of the honeycomb units is:

[0028] Let the cone angle be , the length of the i-th layer beam from bottom to top is ( ), the rib length is m, the number of honeycomb units in each layer is n, then the angle between each hinge axis and the bottom surface of the cone in the annular space honeycomb structure should be , the angle between the projections of the two hinge axes on the beam on the bottom of the cone should be ,set up (taken from the radius RThe central angle of a circle The corresponding chord length), ,but:

[0029] .

[0030] The length of the beam or rib is the distance between the centers of the rotating shafts at both ends of the rod.

[0031] Preferably, the number n of honeycomb units in each layer is 6 or 12, ensuring a good fitting effect on the target cone surface.

[0032] The length relationship between the beams and ribs of the honeycomb unit is achieved by controlling the length ratio between the beams and the beams and the ribs to achieve fitting to the target conical surface. Preferably, the number of honeycomb units and the length relationship between the beams and the ribs of the annular honeycomb structure can be adjusted according to the size of the target conical surface to achieve fitting to conical surfaces of different sizes, thereby achieving strong adaptability and good scalability.

[0033] like Figure 4 As shown, the drive system includes a main frame, a motor, a synchronous pulley, a trapezoidal screw and a clamping claw. The main frame is in the shape of a truncated cone with the same taper as the annular space honeycomb structure. The motor, synchronous pulley and trapezoidal screw are mounted on the main frame. The trapezoidal screw assembly and the synchronous pulley assembly are all mounted on the main frame to ensure the stability and synchronization of the drive system. The motor drives the trapezoidal screw to rotate synchronously through the synchronous pulley. The trapezoidal screw is arranged along the direction of the cone main line and has the same taper as the annular space honeycomb structure. The clamping claw is mounted on the trapezoidal screw and connected to the nut of the trapezoidal screw. The end of the clamping claw is fixedly connected to the top beam of the annular space honeycomb structure. The drive system realizes the gradual opening and closing of the honeycomb structure by controlling the opening and closing of the clamping claw. This allows the claw, equipped with the nut, to translate along the tapered surface as the trapezoidal screw rotates. The end of the claw is fixed to the top beam of the honeycomb structure. As the claw opens, the honeycomb structure gradually expands, achieving the desired tapered surface. The trapezoidal screw is used to take advantage of its self-locking properties, making locking the honeycomb structure easier.

[0034] Preferably, the number of synchronous pulleys and trapezoidal screws of the drive system is four, and the four trapezoidal screws are evenly distributed on the main frame along the same circumference with the center of the main frame as the center. The four synchronous pulleys are respectively installed above the trapezoidal screws, and a motor drives the four synchronous pulleys to rotate synchronously, thereby driving the four sets of trapezoidal screws to rotate synchronously, thereby achieving smooth expansion and contraction of the honeycomb mechanism. The expansion and contraction states of the honeycomb mechanism include an open state, an intermediate state, and a contracted state. Figure 3As shown, when viewed from the radial direction, the spatial honeycomb structure is sequentially in the open state, the intermediate state, and the collapsed state. The honeycomb structure can continuously deform from the collapsed state to the open state. The deformation of the annular spatial honeycomb structure is controlled by the drive system to achieve continuous conical surface deformation.

[0035] This invention designs an annular honeycomb structure. By rationally designing the rod dimensions within the honeycomb units, it can be fitted to a target conical surface. A drive system for the honeycomb structure is also designed, and by controlling the drive system, the structure can be deformed along a fixed taper. By achieving highly compact stowage and efficient deployment, this invention can significantly reduce the launch volume and mass of a spacecraft, thereby lowering launch costs. Furthermore, this invention offers advantages such as a compact structure, high rigidity, reliable drive, and strong adaptability, promising broad application prospects and significant technical advantages in the aerospace field.

[0036] The above description is merely a preferred embodiment of the present invention and does not constitute any form of limitation to the present invention. Although the present invention has been disclosed as a preferred embodiment as above, it is not intended to limit the present invention. Any technician familiar with the present profession can make some changes or modifications to equivalent embodiments of equivalent changes using the technical content disclosed above without departing from the scope of the technical solution of the present invention. However, any simple modification, equivalent replacement and improvement of the above embodiments made according to the technical essence of the present invention, within the spirit and principles of the present invention, without departing from the content of the technical solution of the present invention, shall still fall within the scope of protection of the technical solution of the present invention.

Claims

1. A conical-dimensional space-deformable honeycomb structure, characterized by: It includes an annular space honeycomb structure and a drive system. The annular space honeycomb structure includes a plurality of honeycomb units with a concave hexagonal structure. Each honeycomb unit includes two beams of different lengths and four ribs of the same length and structure. The beams and ribs, and the ribs and ribs are connected by hinges. The drive system includes a main frame, a motor, a synchronous pulley, a trapezoidal screw and a clamping claw. The motor, synchronous pulley and trapezoidal screw are installed on the main frame. The motor drives the trapezoidal screw to rotate synchronously through the synchronous pulley. The trapezoidal screw is arranged along the direction of the cone busbar, and the taper is the same as the taper of the annular space honeycomb structure. Similarly, the clamping claw is installed on the trapezoidal screw and connected to the nut of the trapezoidal screw. The end of the clamping claw is fixedly connected to the beam of the uppermost layer of the annular space honeycomb structure. The deformation of the annular space honeycomb structure along the conical surface of the fixed taper is achieved by controlling the drive system. The concave hexagonal structure of the honeycomb unit of the annular space honeycomb structure has a negative Poisson's ratio. When axially compressed, the radial size decreases while the axial contraction occurs. The number of honeycomb unit layers of the annular space honeycomb structure is three, and the number of honeycomb units in each layer is n. There are five groups of beams with different lengths. The size relationship of the honeycomb unit is: let the cone angle be , the length of the i-th layer beam from bottom to top is ( ), the rib length is m, then the angle between each hinge axis and the cone bottom in the annular space honeycomb structure should be , the angle between the projections of the two hinge axes on the beam on the bottom of the cone should be ,set up , ,but: 。 2. The cone-shaped spatially deformable honeycomb structure according to claim 1, characterized in that: In the annular space honeycomb structure, the number n of honeycomb units in each layer is 6 or 12, ensuring a good fitting effect on the target cone surface.

3. The cone-shaped spatially deformable honeycomb structure according to claim 2, characterized in that: The number of honeycomb units and the length relationship between the beams and ribs of the annular space honeycomb structure can be adjusted according to the size of the target cone surface to achieve fitting of cone surfaces of different sizes.

4. The cone-shaped spatially deformable honeycomb structure according to claim 1, characterized in that: The number of synchronous pulleys and trapezoidal screws in the drive system is four. The four trapezoidal screws are evenly distributed on the main frame along the same circumference with the center of the main frame as the center of the circle. The four synchronous pulleys are respectively installed above the trapezoidal screws. The four synchronous pulleys are driven to rotate synchronously by a motor, thereby driving the four groups of trapezoidal screws to rotate synchronously.

5. The cone-shaped spatially deformable honeycomb structure according to claim 4, characterized in that: The trapezoidal lead screw of the driving system has a self-locking feature, which is used to reduce the difficulty of locking the honeycomb mechanism.

6. The cone-shaped spatially deformable honeycomb structure according to claim 5, characterized in that: The expansion and contraction states of the honeycomb structure include an open state, an intermediate state and a collapsed state. The deformation of the annular space honeycomb structure is controlled by the driving system to achieve continuous conical surface deformation.

7. The cone-shaped spatially deformable honeycomb structure according to claim 6, characterized in that: The driving system realizes the gradual opening and closing of the honeycomb structure by controlling the opening and closing of the claws.

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