Bent mark hinge based on shape memory material and solar panel

Abstract

The invention provides a zigzag mark hinge based on a shape memory material and a solar panel, and belongs to the technical field of space unfolding, the zigzag mark hinge comprises a framework unit, a driving unit and a rigid connecting part, and the framework unit comprises a fiber reinforced composite material panel; the butt-joint ends of the two fiber reinforced composite material panels are attached to each other and connected through polyimide films, the polyimide films are attached to the upper surfaces and the lower surfaces of the butt-joint ends, and preset zigzag marks are formed in the butt-joint positions; the shape memory polymer composite layers are attached to the surfaces of the framework units on the two sides of the zigzag marks, and the heating films are attached to the surfaces of the shape memory polymer composite layers so that the shape memory polymer composite layers can return to the straight state from the bent state and drive the framework units to be flattened; the zigzag mark design generates a self-adaptive nonlinear damping effect in the unfolding process, the damping effect is gradually enhanced along with the increase of the unfolding angle, the impact and vibration in the unfolding process are restrained, and the stability and controllability of the unfolding process are ensured.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space deployment, in particular to a curved trace hinge based on shape memory material and a solar sail. BACKGROUND

[0002] The solar sail is the main power source of a spacecraft, which converts solar energy into electrical energy through the photoelectric effect to provide continuous energy support for various instruments and equipment. Due to the limited space of the launch vehicle, the solar sail must be in a folded state during the launch phase to reduce the volume. The deployment mechanism of the solar sail is a key mechanism for deploying the solar cell array after the spacecraft enters space. After entering the predetermined orbit, the deployment mechanism is triggered by ground command or automatic control, and the solar sail is sequentially deployed and locked to form a large enough light receiving area to capture solar energy.

[0003] With the increasing complexity of space missions and the increasing demand for energy, the deployment structure design of the solar sail also faces many severe challenges. The current deployment structure mainly relies on hinges, torsional springs, motors or rope traction, etc. Traditional mechanical structures often produce a large impact force and vibration at the end of the deployment, which seriously interferes with the normal work of the precision instruments on the spacecraft, and there is a risk of collision and damage to the mechanism itself and the solar cell during locking. In addition, such mechanical structures are complex and contain a large number of moving parts, which are threatened by wear, cold welding and even failure in the extreme environment of space, and their reliability problems are particularly prominent. SUMMARY

[0004] To solve the above technical problems, the present application provides a curved trace hinge based on shape memory material and a solar sail, which solves the impact and reliability problems encountered during the deployment and locking of the solar sail.

[0005] To solve the above problems, the present application provides a curved trace hinge based on shape memory material and a solar sail.

[0006] In one aspect, the present application provides a curved trace hinge based on shape memory material, comprising: A skeleton unit, the skeleton unit comprises at least two fiber-reinforced composite material panels, the butt joint ends of two adjacent fiber-reinforced composite material panels are in close contact with each other and are connected by a polyimide film, the polyimide film is attached to the upper and lower surfaces of the adjacent butt joint ends; the skeleton unit has a preset curved trace at the butt joint position of the two fiber-reinforced composite material panels; A driving unit, comprising a shape memory polymer composite layer and a heating film, the shape memory polymer composite layer is attached to the surface of the framework unit on both sides of the wrinkle, and the heating film is attached to the surface of the shape memory polymer composite layer and used to heat the shape memory polymer composite layer to make the shape memory polymer composite layer recover from the bent state to the flat state and drive the framework unit to flatten; A rigid connecting part, which is arranged one-to-one with the fiber-reinforced composite panel and connected with the corresponding fiber-reinforced composite panel.

[0007] Optionally, each fiber-reinforced composite panel comprises two mirror-symmetrically arranged profiled plate members, and the middle part of each profiled plate member is provided with an arching part, and the two arching parts are attached to form a tubular rigid connecting part.

[0008] Optionally, one end of each rigid connecting part extends to the wrinkle, and the other end extends away from the wrinkle, and the ends of two adjacent rigid connecting parts at the wrinkle are opposite and respectively provided with a avoiding notch.

[0009] Optionally, the shape memory polymer composite layer is goose-shaped and covers both sides of the wrinkle, and the goose-shaped profile is the same as the wrinkle.

[0010] Optionally, the shape memory polymer composite layer is rectangular, and the surface of the framework unit corresponding to both sides of the wrinkle is respectively provided with the shape memory polymer composite layer.

[0011] Optionally, the wrinkle is an arc, and the long edges of the two shape memory polymer composite layers are arranged in parallel, the long edge of one shape memory polymer composite layer is close to the vertex of the wrinkle, and the long edge of the other shape memory polymer composite layer is close to the two endpoints of the wrinkle.

[0012] Optionally, the material of the shape memory polymer composite layer is composed of a shape memory polymer and a reinforcing material, wherein the shape memory polymer is one of epoxy resin, polyurethane, polyethylene and polypropylene, and the reinforcing material is one or both of ceramic particles and fiber reinforced material.

[0013] Optionally, the wrinkle hinge further comprises a connecting rod, the connecting rod comprises at least two connecting rods connected end to end in sequence, and adjacent two connecting rods are rotationally connected, the connecting rod is arranged one-to-one with the rigid connecting part, and passes through and is fixedly connected with the corresponding rigid connecting part. Optionally, the connecting rod comprises three connecting rods, the zigzag hinge comprises three fiber-reinforced composite panels connected in sequence, and the connecting rods are fixedly connected through the rigid connecting portions and the fiber-reinforced composite panels one by one.

[0014] In another aspect, the application also provides a solar sail, comprising a solar sail body and the zigzag hinge, and two adjacent solar sail bodies are connected through a pair of zigzag hinges, and the two solar sail bodies are relatively unfolded and folded through the pair of zigzag hinges.

[0015] The application has the following technical effects: The zigzag hinge based on the shape memory material can ensure the reliability of the hinge in folding and unfolding. The polyimide film is pasted on the upper and lower surfaces of the fiber-reinforced composite panel, so as to ensure the flexibility and durability of the connecting part. The shape memory polymer composite layer serves as a driving source and can drive the fiber-reinforced composite panel to smoothly recover to the initial flat state from the pre-set bending state after being heated by the heating film. In the unfolding process, the zigzag design produces a self-adaptive nonlinear damping effect. With the increase of the unfolding angle, the damping effect gradually increases, effectively inhibiting the impact and vibration in the unfolding process, and ensuring the stability and controllability of the unfolding process. After the shape memory polymer composite layer completes the unfolding action, the modulus of the shape memory polymer composite layer significantly increases with the decrease of the temperature, thereby providing stable rigid support for the whole structure. Therefore, the zigzag hinge of the application realizes the impact-free, stable and controllable movement in the unfolding process, and fundamentally solves the vibration in the unfolding process of the traditional unfolding mechanism and the impact at the end of the unfolding.

[0016] The unfolding mechanism of the application efficiently converts the driving force generated by the shape memory polymer composite layer into stable unfolding movement through the fixed cooperation of the connecting rod and the zigzag hinge through the rigid connecting portion. The kinematics optimization of the multi-link mechanism ensures the synchronization and stability of the unfolding process. The unique parallel support structure effectively disperses the unfolding load and avoids single-point stress concentration, thereby significantly improving the deployment reliability of large solar sails and other space structures. At the same time, the unfolding mechanism can maintain a stable configuration through the material self-locking feature after completing the unfolding, without the need for additional locking devices, thereby reducing the system weight and improving the safety and reliability of the on-orbit operation.

[0017] The solar sail of the present application has the same beneficial effects as the above-mentioned one kind of unfolding mechanism, which will not be described here again. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 A state diagram of a zigzag hinge based on shape memory material in a flat state in an embodiment of the present application; Figure 2 A state diagram of a zigzag hinge based on shape memory material in a folded state in an embodiment of the present application; Figure 3 A diagram of a skeleton unit from a flat state to a folded state in an embodiment of the present application; Figure 4 A diagram of a shape memory polymer composite layer in a goose shape in an embodiment of the present application; Figure 5 A diagram of a shape memory polymer composite layer in a rectangular shape in an embodiment of the present application; Figure 6 A diagram of a zigzag hinge structure in an embodiment of the present application; Figure 7 A diagram of a zigzag hinge on a fiber-reinforced composite panel in a flat state in an embodiment of the present application; Figure 8 A diagram of three fiber-reinforced composite panels in an abutting state in an embodiment of the present application; Figure 9 A diagram of a solar sail in a folded state in an embodiment of the present application; Figure 10 A diagram of a solar sail in an unfolded state in an embodiment of the present application.

[0019] Explanation of reference signs: 01 - zigzag hinge; 1 - fiber-reinforced composite panel; 10 - shaped plate; 100 - arch; 11 - zigzag hinge; 2 - polyimide film; 3 - shape memory polymer composite layer; 4 - heating film; 5 - rigid connection; 6 - connecting rod; 7 - solar sail body; 8 - mounting seat. DETAILED DESCRIPTION

[0020] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the specific embodiments of the present application will be described in detail below with reference to the drawings. Although some embodiments of the present application are shown in the drawings, it should be understood that the present application can be implemented in various forms, and should not be interpreted as being limited to the embodiments described herein, on the contrary, these embodiments are provided to make the present application more thorough and complete. It should be understood that the drawings and embodiments of the present application are only for illustrative purposes, and are not intended to limit the scope of protection of the present application.

[0021] The term "comprising" and its variations as used herein are open-ended, meaning "including but not limited to"; the term "based on" means "at least partially based on"; the term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments"; and the term "optionally" means "optional embodiments". Definitions of other terms will be given in the following description. It should be noted that the concepts of "first," "second," etc., mentioned in this invention are used only to distinguish different devices, modules, or units, and are not intended to limit the order of functions performed by these devices, modules, or units or their interdependencies.

[0022] It should be noted that the terms "a" and "a plurality of" used in this invention are illustrative rather than restrictive. Those skilled in the art should understand that, unless otherwise expressly indicated in the context, they should be understood as "one or more".

[0023] Please see Figure 6 In related technologies, the construction of the crease 11 in the crease origami structure is based on a classical differential geometry method. The specific process is as follows: First, the initial flat material is bent in a single direction (longitudinal) to form a developable cylinder. The transverse cross-sectional profile of this cylinder is the key geometric feature defining the performance of the crease 11, and can be a variety of mathematical curves such as elliptic curves, sine curves, periodically arranged wavy lines, or one-dimensional elastic curves that conform to the natural bending state of the material.

[0024] Subsequently, the cylinder surface is cut by a plane that forms a specific spatial angle with the central axis of the cylinder. This cutting operation produces a continuous spatial curve on the cylinder surface, namely the intersection line. The shape of this spatial curve is simultaneously constrained by two parameters: the shape of the cylinder surface and the angle of the cutting plane.

[0025] Finally, the cylindrical surface is flattened back into a two-dimensional plane. During this flattening process, the intersection line that was originally located in three-dimensional space is uniquely mapped to a curve on the plane, which is the final zigzag 11 required.

[0026] The core advantage of this method lies in the clear mapping relationship between its design parameters and the final structural performance: the final unfolding angle of the zigzag 11 is uniquely controlled by the spatial angle between the aforementioned cross-sectional plane and the central axis of the cylinder; while the stiffness and mechanical response characteristics exhibited by the zigzag during unfolding are mainly determined by the geometric shape of the selected transverse cross-sectional profile of the cylinder. This one-to-one correspondence provides a precise theoretical basis and feasible technological path for the customized design of origami hinges with different unfolding angles and stiffness requirements.

[0027] In one aspect, the present application provides a shape memory material-based zigzag hinge, characterized in that it comprises a framework unit, a driving unit and a rigid connecting part 5, the framework unit comprises at least two fiber-reinforced composite panels 1, the butt joint ends of two adjacent fiber-reinforced composite panels 1 are in close contact with each other and are connected by a polyimide film 2, the polyimide film 2 is attached to the upper and lower surfaces of the adjacent butt joint ends, so that the framework unit has a preset zigzag mark 11 at the butt joint position of the two fiber-reinforced composite panels 1; the driving unit comprises a shape memory polymer composite layer 3 and a heating film 4, the shape memory polymer composite layer 3 is attached to the surface of the framework unit on both sides of the zigzag mark 11, and the heating film 4 is attached to the surface of the shape memory polymer composite layer 3 and is used to heat the shape memory polymer composite layer 3 to make the shape memory polymer composite layer 3 recover from the bent state to the flat state and drive the framework unit to flatten; the rigid connecting part 5 is arranged one by one corresponding to the fiber-reinforced composite panel 1 and is connected with the corresponding fiber-reinforced composite panel 1.

[0028] Referring to Figure 1 , further, the polyimide film 2 covers the upper surface and the lower surface of the fiber-reinforced composite panel 1, the shape memory polymer composite layer 3 covers the surface of the polyimide film 2 corresponding to the upper surface of the fiber-reinforced composite panel 1, and the heating film 4 covers the surface of the shape memory polymer composite layer 3.

[0029] Referring to Figure 2 , it should be noted that the fiber-reinforced composite panel 1 of the present application is composed of a resin matrix material and high-strength fiber materials such as carbon fiber and glass fiber, and has a thickness in the range of 0.5mm to 1.5mm, which can provide lightweight and high-strength framework support, and at the same time, when the zigzag hinge 01 is folded, the fiber-reinforced composite panel 1 can produce uniform elastic bending deformation along the preset zigzag mark 11, and the bending radius can be several times the thickness without fiber breakage or matrix cracking; when the zigzag hinge 01 is flattened, the fiber-reinforced composite panel 1 can quickly recover to the initial flat shape due to the high resilience of its fiber-reinforced structure, and can provide stable out-of-plane stiffness and carrying capacity for the overall structure. Ensure the reliability of the hinge in folding and unfolding.

[0030] The polyimide film 2 is attached to the upper and lower surfaces of the fiber-reinforced composite panel 1 to ensure the flexibility and durability of the connecting part. The heating film 4 can be a super-thin and flexible electrothermal element, usually made of etched metal alloy (such as nichrome wire) circuit or carbon nanotube material, and insulated by polyimide film, and tightly attached to one side surface of the shape memory polymer composite layer 3 by high-temperature resistant adhesive. The shape memory polymer composite layer 3 serves as a driving source and can drive the fiber-reinforced composite panel 1 from the pre-set bent state (such asFigure 2 to the initial flat state (as shown in the state Figure 1 the state shown). Wherein the zigzag crease 11 is designed to produce adaptive nonlinear damping effect in the unfolding process, and the damping effect gradually increases with the increase of the unfolding angle, effectively inhibiting the impact and vibration in the unfolding process, ensuring the stability and controllability of the unfolding process. After completing the unfolding action, the shape memory polymer composite layer 3 significantly improves its modulus as the temperature drops, providing stable rigid support for the entire structure.

[0031] Therefore, the zigzag crease hinge 01 of the present application realizes the impact-free, stable and controllable motion in the unfolding process, fundamentally solving the vibration in the unfolding process of the traditional unfolding mechanism and the impact at the end of the unfolding. The material phase change characteristics of the shape memory polymer composite layer 3 realize the self-locking function after unfolding, eliminating the need for complex mechanical locking devices, greatly improving the reliability of use and reducing the weight of the structure. All materials have good space environment adaptability and can withstand extreme temperature changes and vacuum radiation environment, meeting the demand of spacecraft (solar panel) for high reliability, lightweight and compact unfolding mechanism.

[0032] In an optional embodiment of the present application, each fiber-reinforced composite panel 1 includes two mirror-symmetrically arranged shaped plate members 10, and the middle part of each shaped plate member 10 is provided with an arching part 100. The two arching parts 100 are attached to form a tubular rigid connecting part 5.

[0033] Referring to Figure 7 It should be noted that the above zigzag crease folding method is used to form zigzag creases 11 on a panel, and the panel is cut and separated at the zigzag creases 11, so that two panels with zigzag crease contours at the cut ends are obtained. After the zigzag crease 11 is constructed, the panel is flattened from the cylindrical surface, and the to-be-arched part 100 is inserted in the middle to obtain a complete shaped plate member 10. The two shaped plate members 10 are symmetrically bonded together to obtain the fiber-reinforced composite panel 1.

[0034] The driving principle of the shape memory polymer composite layer 3 is that when the shape memory polymer composite layer 3 is heated to recover, the shrinkage force generated will conduct along the topological path of the zigzag crease 11, forcing the curvature radius of the crease line to change. This curvature change is further transmitted to the adjacent curved surface area through material continuity, forming a coordinated deformation motion. That is, because the shape of the zigzag crease 11 corresponds one-to-one to the curved shape of the curved surface, the curvature change of one side of the curved surface will cause the zigzag crease 11 to change, and the zigzag crease 11 will continue to transmit the force to the other side of the curved surface, so that the curvatures on both sides of the curved surface change synchronously.

[0035] Therefore, by the geometric constraint of the zigzag creases 11, the isotropic shrinkage of the material itself is converted into directional deformation movement, realizing the controllability of the unfolding process; secondly, the linkage of the crease line and the curved surface ensures the uniform distribution of strain energy in the structure, avoiding local stress concentration; finally, this principle fully utilizes the intrinsic properties of shape memory materials and the geometric properties of origami structures, realizing the integration of driving function and structural function.

[0036] It should be noted that the fiber-reinforced composite panel 1 greatly reduces the manufacturing difficulty of the structure through split design, and a single forming plate 10 can be formed by hot pressing once through a mold, ensuring the high precision and consistency of the geometry of the arching part 100; secondly, the mirror image symmetric combination of the two forming plate parts 10 makes the structure more balanced in stress; the rigid connection part 5 provides a stable and reliable force transmission path for the hinge, which can not only ensure high stiffness connection with the external structure, but also ensure uniform transmission of the moment during the unfolding process, thereby effectively avoiding the problem of structural deformation or damage caused by excessive local stress.

[0037] In an optional embodiment of the present application, one end of each rigid connection part 5 extends to the zigzag crease 11, the other end extends away from the zigzag crease 11, and the ends of the two adjacent rigid connection parts 5 at the zigzag crease 11 are oppositely arranged and respectively provided with an avoiding notch.

[0038] It should be noted that the above arrangement makes the axial direction of the rigid connection part 5 parallel to the length direction of the fiber-reinforced composite panel 1, which can ensure the transmission of load along the main axis of the structure and avoid additional bending moment caused by eccentric force. The avoiding notch provides avoidance for the adjacent connection part in the folded state of the hinge, which not only ensures the compactness of the structure during folding, but also ensures that there is no interference between moving parts during the unfolding process.

[0039] Referring to Figure 4 , in an optional embodiment of the present application, the shape memory polymer composite layer 3 is in the shape of a goose and covers both sides of the zigzag crease 11, and the goose-shaped contour is the same as the zigzag crease 11.

[0040] It should be noted that the shape memory polymer composite layer 3 of the goose shape can be provided as a whole structure or two separate structures. The goose design makes the shape memory polymer composite layer 3 completely fit the geometric track of the wrinkle 11, and can generate accurate directional driving force along the wrinkle 11 when activated by heating, ensuring that the unfolding process strictly follows the preset motion track. More importantly, the design forms an effective deformation constraint mechanism in the material phase change process through the full coverage of the shape memory polymer composite layer 3 on the wrinkle 11 area, which inhibits the local buckling and plastic deformation of the fiber reinforced composite material panel 1 material in the wrinkle 11 area, and maintains the integrity of the wrinkle geometric characteristics. This constraint makes the structure have higher form accuracy and position stability after unfolding, and at the same time, due to the increase of the stiffness of the wrinkle 11 area, the vibration energy dissipation capacity of the structure is significantly improved, thereby giving the whole hinge excellent vibration isolation performance. This design scheme cleverly utilizes the dual characteristics of active driving and passive constraint of the shape memory polymer composite layer 3, ensuring the reliability of the unfolding while effectively improving the stability and vibration resistance of the structure during on-orbit operation after unfolding.

[0041] Referring to Figure 5 In an optional embodiment of the present application, the shape memory polymer composite layer 3 is rectangular, and the surfaces of the two skeleton units corresponding to the two sides of the wrinkle 11 are respectively provided with the shape memory polymer composite layer 3. The wrinkle 11 is arc-shaped, and the long edges of the two shape memory polymer composite layers 3 are arranged in parallel, and the long edge of one shape memory polymer composite layer 3 is close to the vertex of the wrinkle 11, and the long edge of the other shape memory polymer composite layer 3 is close to the two endpoints of the wrinkle 11.

[0042] It should be noted that by arranging the shape memory polymer composite layer 3 at a specific position away from the wrinkle 11, sufficient driving torque is ensured, and necessary deformation space is reserved for the wrinkle 11 area. During the unfolding process, this design allows the fiber reinforced composite material panel 1 to produce controllable elastic deformation in the wrinkle 11 area, effectively relieving the concentrated stress generated when the shape memory polymer composite layer 3 material recovers deformation, and avoiding the cracking or delamination damage of the matrix material caused by excessive stress concentration. At the same time, this arrangement optimizes the distribution of the unfolding torque by adjusting the position of the driving force point, making the unfolding process more smooth and smooth. This design scheme significantly improves the damage tolerance and service life of the hinge structure under the premise of ensuring the reliability of the unfolding, and is particularly suitable for spacecraft deployable structure application scenarios that need to be repeatedly unfolded / folded.

[0043] Further, the size of the shape memory polymer composite layer 3 is reasonably designed. When a larger driving force is needed to flatten the fiber reinforced composite material panel 1, a full coverage arrangement can be selected, in which the shape memory polymer composite layer 3 fully covers the upper surface of the fiber reinforced composite material panel 1, as shown inFigure 1 If the driving force is not required to be large, i.e. the force provided by the shape memory polymer composite layer 3 is sufficient, the size of the shape memory polymer composite layer 3 can be reduced, which can be designed as a goose shape or a rectangle, as shown in Figure 4 and Figure 5 .

[0044] In an optional embodiment of the present application, the shape memory polymer composite layer 3 is made of a shape memory polymer and a reinforcing material, wherein the shape memory polymer is one of epoxy resin, polyurethane, polyethylene and polypropylene, and the reinforcing material is one or both of ceramic particles and fiber reinforced material.

[0045] It should be noted that the polyimide film 2 mainly plays a reliable adhesive connection role. In actual application, two implementation modes can be used according to specific working condition requirements: one is to extend the polyimide film 2 to cover the entire upper and lower surfaces of the fiber reinforced composite panel 1 to provide maximum connection strength and force transmission efficiency, as shown in Figure 1 ; the other is to appropriately reduce the size of the polyimide film 2 according to the mechanical analysis results, and only cover the necessary connection area of the butt joint end of the adjacent two fiber reinforced composite panels 1, so as to realize the maximum utilization of materials and further optimization of weight while ensuring reliable connection.

[0046] As shown in Figure 3 , the polyimide film 2 of the skeleton unit before and after bending presents different strain states at the butt joint. Therefore, the implementation of the conformal adhesion state of the polyimide film 2 and the fiber reinforced composite panel 1 can be achieved by: for the polyimide film 2 on the outside after bending, since it is in a tensile state when the hinge is bent (folded), a certain pre-tension along the length direction of the fiber reinforced composite panel 1 needs to be applied during the bonding process. This pre-introduced tensile strain can compensate for the relaxation tendency of the film caused by the decrease of the curvature of the curved surface when the skeleton unit is flattened from the bent state, so as to ensure that the outside film is always in a tension state during the entire unfolding process, avoiding the formation of wrinkles due to material relaxation and accumulation.

[0047] For the polyimide film 2 on the inside after bending, since it is in a compression state when the hinge is bent (folded), it should be kept in a natural adhesion or non-tension state during bonding, avoiding any additional tensile pre-stress. In this way, it can be prevented that during the unfolding process, when the inside film changes from a compression state to a tensile state, an excessive tensile stress is generated due to the superposition of pre-tension, resulting in premature failure of the film or debonding with the panel. The coordinated deformation and force balance of the polyimide films 2 on both sides during the entire movement of the hinge not only ensures the conformal adhesion during bending, but also ensures the flatness and force transmission efficiency during unfolding, and finally maintains the integrity and reliability of the structure.

[0048] As shown inFigure 8 In an optional embodiment of the present application, the zigzag hinge further comprises a connecting rod member, the connecting rod member comprises at least two connecting rods 6 connected in sequence end to end, adjacent two connecting rods 6 are rotationally connected, the connecting rod 6 is provided in one-to-one correspondence with the rigid connecting part 5, and passes through the corresponding tubular rigid connecting part 5 and is fixedly connected with the corresponding rigid connecting part 5. In an optional embodiment of the present application, the connecting rod member comprises three connecting rods 6, and the zigzag hinge 01 comprises three fiber-reinforced composite panels 1 connected in sequence in abutment, and the connecting rod 6 is fixedly connected in one-to-one correspondence with the rigid connecting part 5 and the fiber-reinforced composite panel 1.

[0049] It should be noted that the stable support structure formed by the three groups of hinges and connecting rod units significantly improves the carrying capacity and deployment stability of the deployment mechanism; each connecting rod 6 provides precise motion guidance and torque transmission for the corresponding fiber-reinforced composite panel 1, ensuring the synchronization of the deployment process of the multiple hinge units; at the same time, effectively dispersing the load during deployment, avoiding single-point stress concentration, providing a uniform and reliable support foundation for large planar structures such as solar sails. The coordinated deployment of multiple hinges greatly improves the deployment reliability of large space deployable structures.

[0050] Referring to Figure 9 and Figure 10 On the other hand, a solar sail comprises a solar sail body 7 and the above-mentioned zigzag hinge 01, and adjacent two solar sail bodies 7 are connected by a pair of zigzag hinges 01, and the deployment and folding movement of the zigzag hinge 01 realizes the relative deployment and folding between the adjacent two solar sail bodies 7.

[0051] It should be noted that one connecting rod 6 of each deployment mechanism is arranged parallel to the upper side of the solar sail body 7, the other connecting rod 6 is arranged perpendicular to the side of the solar sail body 7, effectively providing transverse support stiffness, and the third connecting rod 6 is arranged parallel to the lower side of the solar sail body 7. The three connecting rods 6 form a symmetrical force flow transmission path, so that the solar sail can maintain the best photoelectric conversion attitude after deployment, and at the same time significantly improve its adaptability to space environmental disturbances (such as attitude adjustment, thermal deformation, etc.).

[0052] Although the present application is disclosed as above, the protection scope of the present application is not limited to this. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present application, and these changes and modifications will fall within the protection scope of the present application.

Claims

1. A serpentine score hinge based on shape memory material, characterized in that, The application relates to a foldable frame unit. The frame unit comprises at least two fiber-reinforced composite panels (1), the butt-joining ends of two adjacent fiber-reinforced composite panels (1) are in close contact with each other and are connected by a polyimide film (2), the polyimide film (2) is arranged on the upper and lower surfaces of the butt-joining ends, and the frame unit has preset bending marks (11) at the butt-joining positions of the two fiber-reinforced composite panels (1); The driving unit comprises a shape memory polymer composite layer (3) and a heating film (4), the shape memory polymer composite layer (3) is arranged on the surface of the frame unit on both sides of the bending marks (11), and the heating film (4) is arranged on the surface of the shape memory polymer composite layer (3) and is used for heating the shape memory polymer composite layer (3) so that the shape memory polymer composite layer (3) recovers from the bent state to the flat state and drives the frame unit to be flat; The rigid connecting part (5) is arranged in one-to-one correspondence with the fiber-reinforced composite panel (1) and is connected with the corresponding fiber-reinforced composite panel (1).

2. The zigzag score hinge of claim 1, wherein, Each fiber-reinforced composite panel (1) comprises two mirror-symmetrically arranged profiled plate members (10), the middle parts of the two profiled plate members (10) are provided with arching parts (100), and the two arching parts (100) are combined to form a tubular rigid connecting part (5).

3. The zigzag score hinge of claim 2, wherein, One end of each rigid connecting part (5) extends to the bending mark (11), the other end extends away from the bending mark (11), and the ends of two adjacent rigid connecting parts (5) at the bending mark (11) are arranged in opposition and are respectively provided with avoiding notches.

4. The zigzag score hinge of claim 1, wherein, The shape memory polymer composite layer (3) is goose-shaped and covers both sides of the bending mark (11), and the goose-shaped contour is the same as the bending mark (11).

5. The zigzag score hinge of claim 1, wherein, The shape memory polymer composite layer (3) is rectangular, and the surfaces of the frame unit corresponding to the two sides of the bending mark (11) are respectively provided with the shape memory polymer composite layer (3).

6. The zigzag score hinge of claim 5, wherein, The bending mark (11) is an arc line, the long edges of the two shape memory polymer composite layers (3) are arranged in parallel, the long edge of one shape memory polymer composite layer (3) is close to the vertex of the bending mark (11), and the long edge of the other shape memory polymer composite layer (3) is close to the two end points of the bending mark (11).

7. The zigzag score hinge of any one of claim 1, wherein, The material of the shape memory polymer composite layer (3) is composed of a shape memory polymer and a reinforcing material, wherein the shape memory polymer is one of epoxy resin, polyurethane, polyethylene and polypropylene, and the reinforcing material is one or both of ceramic particles and fiber-reinforced material.

8. The zigzag score hinge of claim 2, wherein, The application further relates to a connecting rod member, the connecting rod member comprises at least two connecting rods (6) which are sequentially and end-to-end connected, adjacent connecting rods (6) are rotationally connected, the connecting rod (6) is arranged in one-to-one correspondence with the rigid connecting part (5), and passes through and is fixedly connected with the corresponding rigid connecting part (5).

9. The zigzag score hinge of claim 8, wherein, The connecting rod comprises three connecting rods (6), the zigzag hinge (01) comprises three fiber-reinforced composite panels (1) which are connected in sequence, and the connecting rod (6) is fixedly connected with the rigid connecting part (5) and the fiber-reinforced composite panel (1) one by one.

10. A solar sail, characterized by The solar panel body (7) and the zigzag hinge (01) as claimed in any one of claims 1-9 are connected by a pair of zigzag hinges (01), and the two solar panel bodies (7) are relatively unfolded and folded by a pair of zigzag hinges (01).

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