Conical surface dimensional space deformable honeycomb mechanism

Abstract

The invention discloses a conical surface dimensional space deformable honeycomb mechanism, and belongs to the technical field of aerospace. The conical surface dimensional space deformable honeycomb mechanism comprises an annular space honeycomb mechanism and a driving system, and the annular space honeycomb mechanism is deformed along a conical surface with a fixed taper by controlling the driving system. The annular space honeycomb mechanism comprises a plurality of honeycomb units which are of concave hexagonal structures, each honeycomb unit comprises two beams with different lengths and four ribs with the same length and structure, the beams are connected through hinges, and the ribs are connected through hinges; the driving system comprises a main body frame, a motor, a synchronous belt wheel, a trapezoidal lead screw and a clamping jaw. The annular space honeycomb mechanism is designed, and fitting of a target conical surface can be achieved by reasonably designing the sizes of the rod pieces in the honeycomb units; meanwhile, a driving system of the honeycomb mechanism is designed, and the honeycomb mechanism can deform along the conical surface with the fixed taper by controlling the driving system.

Description

Technical Field

[0001] The 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 retractable mechanism is a technology that has developed rapidly with the birth of aerospace technology. It is the optimal solution to engineering problems in the aerospace field and the main way to solve the contradiction between the structural requirements of large spacecraft and the envelope restrictions of rocket launch. The retractable mechanism is generally an extension of the basic unit composed of rods, ropes and membranes. It is a super-constrained system with simple structure and good rigidity. 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, the technology of space retractable mechanism has made great progress and has been widely used in space engineering projects such as large-diameter satellite antennas, space station masts, solar arrays, and Mars / lunar probes. However, there are few conical retractable mechanisms in the existing technology, and there are few deformable conical mechanisms in the existing space retractable mechanisms. The main ones with the ability to fit the conical surface are space rod systems and umbrella mechanisms. However, the existing research results are mainly manifested in the transformation of small-volume retracted states to large-scale working states, and they do not have 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 further 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-surface-dimensional space deformable honeycomb mechanism comprises an annular-space honeycomb mechanism and a driving system, wherein the annular-space honeycomb mechanism comprises a plurality of honeycomb units in a concave hexagonal structure, each honeycomb unit comprises 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 driving system comprises a main frame, a motor, a synchronous pulley, a trapezoidal lead screw and a clamping claw, wherein the motor, the synchronous pulley and the trapezoidal lead screw are mounted on the main frame, and the motor drives the trapezoidal lead screw to rotate synchronously through the synchronous pulley, the trapezoidal lead screw is arranged along the direction of the conical surface generatrix, and the taper is the same as that of the annular-space honeycomb mechanism, the clamping claw is mounted on the trapezoidal lead screw and connected to the nut of the trapezoidal lead screw, and the end of the clamping claw is fixedly connected to the uppermost beam of the annular-space honeycomb mechanism, and the deformation of the annular-space honeycomb mechanism along the conical surface of fixed taper is achieved by controlling the driving system.

[0007] Furthermore, the inwardly concave hexagonal structure of the honeycomb unit of the annular space honeycomb structure has a negative Poisson's ratio property, and when subjected to axial pressure, the radial dimension decreases while the axial contraction occurs.

[0008] Furthermore, the annular space honeycomb structure has three layers of honeycomb units, each layer has twelve honeycomb units, and there are five groups of beams with different lengths.

[0009] Furthermore, the size relationship of the honeycomb unit is:

[0010] Assume that the cone angle is 2α, and the length of the i-th layer beam from bottom to top is l i (i=1,2,…,5), the rib length is m, the number of honeycomb units in each layer is n, then the angle between each hinge axis in the annular space honeycomb structure and the bottom surface of the cone should be α, and the angle between the projections of the two hinge axes on the beam on the bottom surface of the cone should be π / n. m=m0 / sinα, then:

[0011]

[0012] Furthermore, in the spatial annular 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.

[0013] Furthermore, the number of honeycomb units and the length relationship between the beams and ribs of the annular hollow honeycomb structure can be adjusted according to the size of the target cone surface to achieve fitting of cone surfaces of different sizes.

[0014] 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. 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.

[0015] Furthermore, the trapezoidal lead screw of the driving system has a self-locking property, which is used to reduce the difficulty of locking the honeycomb mechanism.

[0016] 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.

[0017] Furthermore, the driving system realizes the gradual opening and closing of the honeycomb structure by controlling the opening and closing of the claws.

[0018] The beneficial effects of the present invention are:

[0019] 1. The present invention can realize continuous conical deformation along a fixed taper by designing an annular space honeycomb structure and a matching drive system, meeting the demand for dynamic adjustment of the cone shape in complex space tasks. It has a compact structure, high rigidity, reliable drive and strong adaptability.

[0020] 2. The honeycomb unit of the present invention adopts a concave hexagonal structure with a negative Poisson's ratio. When the axial pressure is applied, the radial dimension is reduced synchronously, so that the mechanism can be folded in a highly compact manner in the folded state. The space occupied by the mechanism in the folded state is significantly reduced, which is particularly suitable for scenarios with strict envelope restrictions such as rocket launches. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of an embodiment of the annular space honeycomb structure of the present invention;

[0022] Figure 2 It is a structural schematic diagram of an embodiment of a honeycomb unit of the present invention;

[0023] Figure 3 yes Figure 2 Schematic diagram of the three-dimensional structure;

[0024] Figure 4 It is a schematic diagram of the structure of the annular space honeycomb mechanism of the present invention in the collapsed and expanded state;

[0025] Figure 5 It is a structural schematic diagram of an implementation mode of the drive system of the present invention.

[0026] 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. claw. DETAILED DESCRIPTION

[0027] Specific implementation method 1: Combination Figure 1-4 The present embodiment is described as a cone-shaped spatial deformable honeycomb structure, which includes an annular space honeycomb structure and a driving system. The annular space honeycomb structure is deformed along a cone with a fixed taper by controlling the driving system.

[0028] like Figure 1 and Figure 2As shown, 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 hinge connection forms a super-constrained system, and the overall structure has high rigidity and stability. The common two-dimensional honeycomb structure / structure is converted into a three-dimensional form, wherein the honeycomb unit adopts a concave hexagonal honeycomb structure. From a mechanical point of view, the concave hexagonal structure of the honeycomb unit has a negative Poisson's ratio property, that is, when axially compressed, the axial size of the honeycomb unit shrinks while the radial size also shrinks. Specifically, when axially compressed, the axial size of the honeycomb unit shrinks, and the radial size also shrinks, which enables the honeycomb structure to achieve compact folding in the folded state. When axially pulled, the axial size of the honeycomb unit stretches, and the radial size expands, which enables the honeycomb structure to achieve large-scale expansion in the open state. In the folded state, the mechanism can be more compact, reduce the occupied space, and improve the efficiency of folding and unfolding; in the open state, the mechanism can better maintain the shape and rigidity, adapt to complex external loads, and enhance the structural stability. This enables the honeycomb structure to achieve smooth continuous deformation, meeting the needs of continuous deformation of the cone surface, while improving the energy absorption capacity and impact resistance of the structure. This feature significantly reduces the space occupied by the structure in the folded state, which is particularly suitable for scenarios such as rocket launches that have strict envelope restrictions. At the same time, it is particularly important in space environments and can effectively cope with complex external loads and vibrations.

[0029] Specifically, the annular space honeycomb structure has three layers of honeycomb units, each layer has twelve honeycomb units, and there are five groups of beams with different lengths. By reasonably controlling the length relationship between beams and beams, and between beams and ribs, honeycomb structures with cones of different sizes can be obtained.

[0030] The dimensional relationship of the honeycomb unit is:

[0031] Assume that the cone angle is 2α, and the length of the i-th layer beam from bottom to top is l i (i=1,2,…,5), the rib length is m, the number of honeycomb units in each layer is n, then the angle between each hinge axis in the annular space honeycomb structure and the bottom surface of the cone should be α, and the angle between the projections of the two hinge axes on the beam on the bottom surface of the cone should be π / n. (taken from the chord length corresponding to the central angle π / n in the circle of radius R), m = m0 / sinα, then:

[0032]

[0033] The length of the beam or rib is the distance between the centers of the rotating shafts at both ends of the rod.

[0034] Preferably, the number n of honeycomb units in each layer is 6 or 12, ensuring a good fitting effect on the target cone surface.

[0035] 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 between the beams and the ribs to achieve the fitting of the target cone surface. Preferably, the number of honeycomb units and the length relationship between the beams and the ribs of the annular hollow honeycomb structure can be adjusted according to the size of the target cone surface to achieve the fitting of cone surfaces of different sizes, with strong adaptability and good scalability.

[0036] like Figure 4 As shown, the driving system includes a main frame, a motor, a synchronous pulley, a trapezoidal screw and a clamping claw. The main frame as a whole is in the shape of a truncated cone with the same taper as the annular space honeycomb mechanism. The motor, synchronous pulley and trapezoidal screw are installed on the main frame. The trapezoidal screw assembly and the synchronous pulley assembly are all installed on the main frame to ensure the stability and synchronization of the driving 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 generatrix and has the same taper as the annular space honeycomb mechanism. 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 top beam of the annular space honeycomb mechanism. The driving system realizes the gradual opening and closing of the honeycomb mechanism by controlling the opening and closing of the clamping claw. This allows the claw with the nut to translate along the conical surface during the rotation of the trapezoidal screw. The end of the claw is fixed to the top beam of the honeycomb structure. As the claw opens, the honeycomb structure can also gradually open to achieve the purpose of deforming the conical surface. The trapezoidal screw is used to utilize its self-locking characteristics to reduce the difficulty of locking the honeycomb structure.

[0037] Preferably, the number of synchronous pulleys and trapezoidal screws of the driving 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, so as to achieve smooth expansion and folding of the honeycomb mechanism. The folding and unfolding states of the honeycomb mechanism include an open state, an intermediate state, and a folded state. Figure 3 As shown, when viewed from the radial direction, the spatial honeycomb structure is in the open state, the intermediate state and the closed state. The honeycomb structure can be continuously deformed from the closed state to the open state, and the deformation of the annular spatial honeycomb structure is controlled by the driving system to achieve continuous conical deformation.

[0038] The present invention designs an annular space honeycomb mechanism, which can achieve fitting of the target cone by reasonably designing the rod size in the honeycomb unit; at the same time, a driving system of the honeycomb mechanism is designed, and the deformation of the honeycomb mechanism along the cone of a fixed taper can be achieved by controlling the driving system. By achieving highly compact folding and efficient unfolding of the mechanism, the present invention can significantly reduce the launch volume and mass of the spacecraft, thereby reducing the launch cost. At the same time, the present invention has the advantages of compact structure, high rigidity, reliable drive, strong adaptability, etc., and has broad application prospects and significant technical advantages in the aerospace field.

[0039] The above is only a preferred embodiment of the present invention and does not limit the present invention in any form. Although the present invention has been disclosed as a preferred embodiment as above, it is not used to limit the present invention. Any technician familiar with this profession can make some changes or modify the technical contents disclosed above into equivalent embodiments without departing from the scope of the technical solution of the present invention. However, any simple modification, equivalent replacement and improvement made to the above embodiments without departing from the content of the technical solution of the present invention, based on the technical essence of the present invention, within the spirit and principles of the present invention, still fall within the protection scope of the technical solution of the present invention.

Claims

1. A cone-shaped spatially deformable honeycomb structure, characterized in that: It includes an annular space honeycomb mechanism and a driving system. The annular space honeycomb mechanism 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 are connected to the ribs and the ribs are connected to each other by hinges. The driving system includes a main frame, a motor, a synchronous pulley, a trapezoidal screw and a clamp. The motor, the synchronous pulley and the 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 generatrix direction of the conical surface, and the taper is the same as that of the annular space honeycomb mechanism. The clamp is installed on the trapezoidal screw and connected to the nut of the trapezoidal screw. The end of the clamp is fixedly connected to the uppermost beam of the annular space honeycomb mechanism. The deformation of the annular space honeycomb mechanism along the conical surface of the fixed taper is achieved by controlling the driving system.

2. The cone-shaped spatially deformable honeycomb structure according to claim 1, characterized in that: The inwardly concave hexagonal structure of the honeycomb unit of the annular space honeycomb structure has a negative Poisson's ratio property. When subjected to axial pressure, the radial dimension decreases while the axial direction contracts.

3. The cone-shaped spatially deformable honeycomb structure according to claim 2, characterized in that: The annular space honeycomb structure has three layers of honeycomb units, each layer has twelve honeycomb units, and there are five groups of beams with different lengths.

4. The cone-shaped spatially deformable honeycomb structure according to claim 3, characterized in that: The dimensional relationship of the honeycomb unit is: Assume that the cone angle is 2α, and the length of the i-th layer beam from bottom to top is l i (i=1,2,…,5), the rib length is m, the number of honeycomb units in each layer is n, then the angle between each hinge axis in the annular space honeycomb structure and the bottom surface of the cone should be α, and the angle between the projections of the two hinge axes on the beam on the bottom surface of the cone should be π / n. m=m0 / sinα, then:

5. The cone-shaped spatially deformable honeycomb structure according to claim 4, characterized in that: In the spatial annular honeycomb structure, the number n of honeycomb units in each layer is 6 or 12, which ensures a good fitting effect on the target cone surface.

6. The cone-shaped spatially deformable honeycomb structure according to claim 5, characterized in that: The number of honeycomb units and the length relationship between the beams and ribs of the annular hollow honeycomb structure can be adjusted according to the size of the target cone surface to achieve fitting of cone surfaces of different sizes.

7. The cone-shaped spatially deformable honeycomb structure according to claim 1, characterized in that: The number of synchronous pulleys and trapezoidal screws in the driving 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. The four synchronous pulleys are respectively installed above the trapezoidal screws. The four synchronous pulleys are driven by a motor to rotate synchronously, thereby driving the four groups of trapezoidal screws to rotate synchronously.

8. The cone-shaped spatially deformable honeycomb structure according to claim 7, characterized in that: The trapezoidal lead screw of the driving system has a self-locking characteristic, which is used to reduce the difficulty of locking the honeycomb mechanism.

9. The cone-shaped spatially deformable honeycomb structure according to claim 8, 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 cone deformation.

10. The cone-shaped spatially deformable honeycomb structure according to claim 9, 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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