Reversible latching structure housing

Abstract

The utility model relates to composite material structure design technical field especially relates to a reversible locking structure shell, including fiber composite material main part, is the composite structure that reinforcing body layer and elastic matrix layer are laminated to enhance, reinforcing body layer is formed by continuous fiber regular arrangement, and elastic matrix layer is formed by cross fiber regular arrangement, fiber composite material main part is equipped with the buckling guide recess that adapts its stress direction distribution, and the buckling guide recess is the recess structure that the shell surface is pressed to form, when external force is applied to fiber composite material main part and displacement reaches the preset value, buckling guide recess guides the main body to take place controllable deformation and switches to stable stress state to realize the locking, when external force removes, fiber composite material main part automatically rebounds to the initial state, or, fiber composite material main body is under the influence of another external force in the opposite direction and separates the locking, and rebounds to the initial state.

Description

Technical Field

[0001] This utility model relates to the field of composite material structure design technology, and in particular to a reversible locking structure shell. Background Technology

[0002] Fiber-reinforced composite materials are widely used in aerospace, automotive, and robotics industries due to their high specific strength, high specific stiffness, and lightweight properties. They are particularly important in dynamic load scenarios requiring impact resistance and vibration reduction, such as rocket landing legs, vehicle anti-collision beams, and robot feet, where they have become a key alternative to traditional metal materials.

[0003] However, existing reinforced fiber composite structural components have significant technical defects: on the one hand, the material is inherently brittle and is prone to irreversible brittle fracture under dynamic impact loads. Insufficient toughness results in limited energy absorption capacity, and the material cannot recover its initial shape after fracture, making it difficult to reuse. On the other hand, traditional structural designs cannot take into account both locking and rebound functions. They can either only absorb energy through plastic deformation but cannot rebound, or they only have basic elasticity but no stable locking effect. They cannot achieve graded energy absorption through controllable deformation during impact, which limits their application.

[0004] In addition, existing manufacturing processes have insufficient control over the interlayer bonding precision and surface functional structure forming precision of composite structures, which easily leads to interlayer defects or structural morphology deviations, further weakening the impact resistance and functional stability of structural components, making it difficult to meet the high-performance requirements of high-end equipment for material structures. Utility Model Content

[0005] This utility model provides a reversible locking structure shell to solve the defects of traditional fiber composite material structural components in the prior art, such as insufficient toughness, easy irreversible brittle fracture, and difficulty in simultaneously achieving controllable locking and full rebound functions, which limit their application in dynamic load scenarios such as impact resistance and vibration reduction. It enables the structural component to efficiently absorb impact energy through controllable locking after undergoing large deformation under design load, and to fully rebound to the initial state after unloading, while taking into account both high load-bearing capacity and long service life.

[0006] This utility model provides a reversible locking structure shell, including a fiber composite material body; the fiber composite material body is a composite structure formed by stacking a reinforcing layer and an elastic matrix layer, the reinforcing layer is formed by a regular arrangement of continuous fibers, and the elastic matrix layer is formed by a regular arrangement of intersecting fibers; the fiber composite material body is provided with buckling guide grooves adapted to its force distribution, the buckling guide grooves being recessed structures formed by pressing the shell surface; when an external force is applied to the fiber composite material body and the displacement reaches a preset value, the buckling guide grooves guide the body to undergo controllable deformation and switch to a stable force state to achieve locking; when the external force is removed: the fiber composite material body automatically rebounds to its initial state; or, the fiber composite material body disengages from locking under the influence of another external force in the opposite direction and rebounds to its initial state.

[0007] According to one embodiment of the present invention, the cross-section of the buckling guide groove is U-shaped.

[0008] According to one embodiment of the present invention, the arrangement of the cross fibers in the elastic matrix layer includes: a cross arrangement, in which a portion of the cross fibers are arranged along the length direction of the shell and another portion of the cross fibers are arranged perpendicular to the length direction of the shell; and / or, an oblique cross arrangement, in which the cross fibers are arranged at +n° and -n° directions respectively with respect to the length direction of the shell.

[0009] According to one embodiment of the present invention, the single-layer thickness of the reinforcing layer and / or the elastic matrix layer is greater than 0 and less than or equal to 1 mm.

[0010] According to one embodiment of the present invention, the overall shape of the fiber composite material body is flat or arched.

[0011] According to one embodiment of the present invention, the outer surface of the fiber composite material body and the inner wall of the buckling guide groove are both covered with a heat-resistant and corrosion-resistant coating.

[0012] The reversible locking structure shell provided by this utility model can solve the defects of traditional fiber composite material structural components in the prior art, such as insufficient toughness, easy irreversible brittle fracture, and difficulty in achieving both controllable locking and complete rebound functions, which limit their application in dynamic load scenarios such as impact resistance and vibration reduction. It enables the structural component to efficiently absorb impact energy through controllable locking after undergoing large deformation under design load, and to completely rebound to the initial state after unloading, while taking into account both high load-bearing capacity and long service life.

[0013] The reversible locking structure shell features a fiber composite material body with alternating reinforcing layers and elastic matrix layers. The reinforcing layers, composed of regularly arranged continuous fibers, provide core stiffness and strength, while the elastic matrix layers fill the spaces between adjacent reinforcing layers to transfer loads and store elastic strain energy. Simultaneously, buckling guide grooves distributed along the force direction are pressed onto the surface of the main body. When an external force is applied and the displacement reaches a preset value, the grooves guide the main body to undergo controllable deformation and switch to a stable stress state to achieve locking, efficiently absorbing impact energy. After the external force is removed, the elastic strain energy stored in the elastic matrix and reinforcing layers drives the main body to spring back to its initial state, avoiding the irreversible fracture problem of traditional structures. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the reversible locking structure shell provided by this utility model.

[0016] Figure 2 This is a schematic diagram of the layered structure of the reversible locking structure shell provided by this utility model.

[0017] Figure 3 This is a schematic diagram of the springback test data of the reversible locking structure shell of this utility model.

[0018] Figure 4 This is a schematic diagram of the destructive test data of the reversible locking structure shell of this utility model.

[0019] Figure label: 10. Fiber composite material body; 11. Reinforcing layer; 12. Elastic matrix layer; 13. Buckling guide groove. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0021] In the description of the embodiments of this utility model, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. It should also be noted that in the description of this utility model, unless otherwise explicitly specified and limited, the terms "set," "install," and "connect" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0022] Fiber composite materials, with their excellent specific strength, high rigidity, and lightweight properties, have been widely used in aerospace structures, military protective equipment, and industrial machinery. However, existing technologies still face significant bottlenecks: traditional methods of increasing material thickness or density to enhance rigidity often result in brittle behavior under stress, leading to fracture after deformation, especially under dynamic loads, impacts, or vibrations. This not only compromises safety but can also cause catastrophic failures. While some solutions attempt to improve toughness by introducing flexible components such as elastomers and polymers, these often come at the cost of rigidity and fail to achieve precise control over deformation behavior and shape recovery, severely limiting their application in high-performance fields. Therefore, there is an urgent need for a novel fiber composite structural component that integrates elastic deformation and recoverable characteristics while maintaining high rigidity, thereby improving overall mechanical performance and reliability. Based on this, this invention aims to overcome the shortcomings of existing technologies by providing a reversible locking structure shell of reinforced fiber composite material through a combination of material system and structural design. This reversible locking structure shell, after being subjected to a design load and undergoing large deformation, can achieve almost 100% shape recovery and also possesses the function of reversibly locking at a specific location.

[0023] The following is combined Figures 1-4 This invention describes a specific embodiment of the reversible locking structure housing.

[0024] like Figure 1 and Figure 2As shown, this utility model provides a reversible locking structure shell, including a fiber composite material body 10; the fiber composite material body 10 is a composite structure formed by stacking a reinforcing layer 11 and an elastic matrix layer 12, the reinforcing layer 11 is formed by a continuous and regularly arranged fiber, and the elastic matrix layer 12 is formed by a cross-arranged and regularly arranged fiber; the fiber composite material body 10 is provided with a buckling guide groove 13 adapted to its force distribution, the buckling guide groove 13 is a recessed structure formed by pressing the shell surface; when an external force is applied to the fiber composite material body 10 and the displacement reaches a preset value, the buckling guide groove 13 guides the body to undergo controllable deformation and switch to a stable force state to achieve locking; when the external force is removed: the fiber composite material body 10 automatically rebounds to the initial state; or, the fiber composite material body 10 disengages from locking under the influence of another external force in the opposite direction and rebounds to the initial state. Specifically, the continuous fibers can be selected from high-strength, high-modulus fibers such as carbon fiber, aramid fiber, basalt fiber, or glass fiber. They can be arranged in a regular unidirectional bundle to form the reinforcing layer 11, providing core stiffness and strength to the shell. The elastic matrix layer 12 is composed of regularly arranged cross-fibers and can also be selected from high-strength, high-modulus fibers such as carbon fiber, aramid fiber, basalt fiber, or glass fiber. It can absorb and store elastic strain energy during structural deformation. The buckling guide grooves 13, distributed along the preset force direction, serve as pre-set weak points. Their concave shape can precisely guide stress concentration. When an external force is applied and the displacement reaches a preset value (corresponding to the critical value of the "locking force" in the structural design), a controllable sudden buckling instability occurs preferentially at the groove, allowing the shell to quickly switch to a new stable mechanical equilibrium state, achieving "locking" and efficiently dissipating impact energy. After the external force is removed, the elastic matrix layer 12 and the unbuckled reinforcement layer 11 can automatically release the stored elastic strain energy, driving the shell to recover to the initial shape through reverse elastic jump; or, the fiber composite body 10 can also be configured to automatically remain in the locked state until it is released from the locked state under the influence of another external force in the opposite direction and springs back to the initial state.

[0025] In practical applications, the aforementioned reversible locking structure shell can be adapted to dynamic load scenarios such as rocket landing legs, robot feet, and vehicle anti-collision beams. When used for rocket landing legs, the shell is provided with buckling guide grooves 13 along the direction of the impact force. At the moment of landing, when the external force reaches the locking threshold, the grooves guide the shell to deform controllably and lock, absorbing huge impact energy and preventing rigid fracture of the landing leg. After the force is released, the shell rebounds and resets, ensuring the landing leg can be reused. When used for vehicle anti-collision beams, the grooves are distributed along the width of the vehicle. During a collision, the locking deformation absorbs the collision energy, reducing impact damage to the vehicle body. After the force is released, the shell rebounds and restores its initial shape, eliminating the need for frequent replacement. When used for robot feet, the layered structure and groove design of the shell can adapt to the complex forces on the foot, improving the robot's movement stability and foot lifespan. By locking and absorbing energy when the robot is impacted during walking and rebounding after force release, the energy consumption during robot walking is saved, extending the robot's endurance.

[0026] Furthermore, according to the reversible locking structure shell of this utility model, the cross-section of the buckling guide groove 13 is U-shaped. The curvature of the U-shaped cross-section can be proportionally set to the effective area of ​​the overall reversible locking structure to reduce stress abrupt changes at the groove edge, prevent premature breakage of local fibers due to stress concentration, and ensure the stability of sudden rebound. The curvature of the cross-section can also be selected according to the actual stress scenario. For example, in scenarios with large impact loads, a buckling guide groove 13 with a larger curvature is preferred to improve structural durability, while in scenarios with smaller loads, a buckling guide groove 13 with a smaller curvature can be selected to optimize the locking response speed.

[0027] Furthermore, according to a reversible locking structure housing of this utility model, such as Figure 2 As shown, the arrangement of the cross fibers in the elastic matrix layer 12 can include: a cross-shaped arrangement, where some cross fibers are arranged along the length of the shell and others are arranged perpendicular to the length of the shell; and / or, an oblique cross-shaped arrangement, where the cross fibers are arranged at +n° and -n° angles to the length of the shell, respectively. Elastic matrix layers 12 with cross fibers arranged in different ways can be applied to the same reversible locking structure shell. The cross-arranged cross fibers can significantly improve the structural shear strength, cope with lateral shear forces under stress, and prevent interlaminar slippage. The +n° and -n° directions can be set according to requirements; for example, the cross fibers can be arranged at +45° and -45° angles to the length of the shell, respectively. When higher strength is required, more elastic matrix layers 12 with cross fibers having smaller absolute n values ​​can be used; while when a larger elastic margin is required, more elastic matrix layers 12 with cross fibers having larger absolute n values ​​can be used.

[0028] Furthermore, according to the reversible locking structure shell of this utility model, the single-layer thickness of the reinforcing layer 11 and / or the elastic matrix layer 12 is preferably greater than 0 and less than or equal to 1 mm. The minimum single-layer thickness of the reinforcing layer 11 and the elastic matrix layer 12 depends on the specific dimensions of the continuous and intersecting fibers therein; the smaller the fiber diameter, the denser the fiber layer structure can be achieved. To adapt to the differentiated requirements of weight and strength in different scenarios, and due to limitations in production difficulty and cost, the single-layer reinforcing layer 11 and / or the elastic matrix layer 12 are preferably set to be greater than 0 and less than or equal to 1 mm, respectively used to prepare reversible locking structure shells with overall thickness requirements ranging from thin to thick.

[0029] Furthermore, according to the reversible locking structure shell of this utility model, the overall shape of the fiber composite material body 10 is either flat or arched. Specifically, the flat shape is suitable for scenarios requiring planar force, facilitates planar assembly with surrounding components, and provides a more uniform stress distribution under load. The arched shape can utilize the mechanical advantages of the arch structure to convert vertical loads into pressure along the arch axis, making it suitable for scenarios requiring vertical impact, such as rocket landing leg support sections and robot foot arches, thus improving the structure's compressive strength. Both shapes are based on the structure of the reinforcing layer 11 + elastic matrix layer 12, and can be achieved simply by adjusting the mold shape, without changing the layering and groove design, reducing development costs for adapting to different scenarios.

[0030] Furthermore, according to the reversible locking structure shell of this utility model, the outer surface of the fiber composite material body 10 and the inner wall of the buckling guide groove 13 are both covered with a heat-resistant and corrosion-resistant coating. The thickness of this heat-resistant and corrosion-resistant coating is preferably set to 50-100 μm. The coating is preferably made of a corrosion-resistant material with a temperature resistance of 200℃ or higher, such as a modified epoxy resin coating. A thickness of 50-100 μm ensures coating adhesion, preventing the coating from peeling off during shell deformation, without excessively increasing the structural thickness and weight. Covering the outer surface can resist the erosion of humidity and corrosive gases in the external environment, such as in vehicle anti-collision beams dealing with rain and salt spray environments. Covering the inner wall of the groove can prevent fiber exposure and corrosion caused by repeated friction during deformation, while reducing frictional resistance at the groove, ensuring smooth transitions and extending the service life of the shell.

[0031] According to a preferred embodiment of the present invention, the reversible locking structure shell is primarily a composite structure consisting of alternating reinforcing layers 11 and elastic matrix layers 12, balancing lightweight design with load-bearing requirements. The reinforcing layers 11 can be made of T1100 grade carbon fiber, arranged in a unidirectional, regularly distributed bundle. The elastic matrix layers 12 are made of the same or different material as the reinforcing layers 11, arranged in a diagonally or cross-shaped bundle, achieving uniform load transfer and elastic strain energy storage.

[0032] The main body surface is pressed with a U-shaped buckling guide groove 13 along the direction of force to precisely guide stress concentration as a pre-set weak point. The outer surface and the inner wall of the groove are preferably coated with a modified epoxy resin heat-resistant and corrosion-resistant coating to resist environmental erosion and reduce deformation friction.

[0033] During operation, when the external force reaches the locking threshold, a controllable spring-loaded transition is triggered at the groove, and the shell switches to a stable state to achieve locking and energy absorption. After the external force is removed, the energy is released automatically or under the influence of another opposite external force, driving a reverse spring-loaded transition to restore the initial shape. The deformation recovery rate is ≥99%, which can be adapted to dynamic load scenarios such as rocket landing legs, vehicle anti-collision beams, and robot feet.

[0034] like Figure 3 As shown, based on the reversible locking structure shell of the above embodiments, this utility model conducts a rebound test to explore the rebound force behavior of the shell under diverse loading conditions and evaluate its elastic deformation characteristics and structural stability.

[0035] The experiment strictly followed standard testing specifications, ensuring the reliability and repeatability of data acquisition by precisely controlling the loading rate, displacement parameters, and environmental conditions. During the test, a 10mm displacement load was first applied to the structure (beam), and the force-displacement curve was recorded in real time. After entering the unloading phase, the shell deformation recovery process was continuously monitored to quantify its resilience performance.

[0036] Experimental data analysis shows that the shell exhibits a highly linear mechanical response during loading and unloading cycles, and the stress-strain relationship conforms to the basic laws of elasticity theory, indicating that no significant plastic deformation or energy dissipation occurred within the test range. Further observation from the mechanical curves reveals that the shell rapidly absorbs energy during loading, and the deformation is almost completely recovered after unloading, with negligible residual deformation. This linear trend not only verifies the applicability of Hooke's law to the shell within the elastic range but also highlights its excellent energy storage and release efficiency.

[0037] Experimental results confirm that the reversible locking structure shell possesses excellent deformation recovery capability within a predetermined elastic range. After deformation, it can stably and efficiently return to its initial geometric state. This characteristic stems from the uniformity of its micro-layered structure design (alternating reinforcing layers 11 and elastic matrix layers 12) and the precise control of deformation by the buckling guide groove 13. These characteristics ensure the long-term durability and reliability of the shell in engineering applications such as vibration damping devices, flexible structures, and high-precision equipment components.

[0038] like Figure 4As shown, based on the reversible locking structure shell described above, this invention further conducts destructive testing. This experiment aims to systematically investigate the failure behavior of the reversible locking structure shell under diverse loading conditions, focusing on comparing the fracture characteristics of traditional carbon plates and the reversible locking structure shell of this invention during quasi-static loading, providing reliable experimental evidence for material performance optimization.

[0039] The experiment used a universal testing machine to implement continuous loading, and the loading rate strictly followed international standards to ensure the accuracy and repeatability of data acquisition. At the same time, high-precision sensors recorded the load-displacement curves in real time, and extracted key mechanical parameters such as elastic modulus, yield strength, ultimate bearing capacity and fracture point to comprehensively characterize the mechanical properties of the shell.

[0040] Experimental data show that traditional carbon plate samples exhibit typical brittle fracture when the load reaches 1.26 kN and the displacement is 13.5 mm, with the fracture surface showing a cleavage morphology, demonstrating defects such as low toughness and limited energy absorption capacity. In contrast, the corresponding structure (beam) of this utility model does not fracture until the load increases to 1.41 kN and the displacement expands to 25.6 mm, and the fracture behavior shows significant ductility characteristics. This difference confirms the design advantages of "orderly arrangement of reinforcing layer 11 + optimized combination of elastic matrix layer 12" inside the shell, which effectively improves the toughness of the material.

[0041] Quantitative analysis further shows that, compared to traditional carbon steel plates, the ultimate load-bearing capacity of the reversible locking structure shell of this invention increases from 1.26 kN to 1.41 kN (an increase of 12%), and the fracture displacement increases from 13.5 mm to 25.6 mm (an increase of 89.6%), demonstrating that it possesses both higher strength and superior toughness. The material failure mechanism conforms to the critical stress criterion; when the loaded stress exceeds the yield limit, the propagation of microscopic defects triggers macroscopic fracture. The above experimental conclusions are based on the average value of multiple independent repeated tests, with low data dispersion, meeting the statistical significance requirement (p<0.05), ensuring the scientific reliability of the results.

[0042] This utility model also provides a method for manufacturing a reversible locking structure shell, used to manufacture the reversible locking structure shell of the above embodiments. The manufacturing method of the reversible locking structure shell provided by this utility model is described below. The manufacturing method of the reversible locking structure shell described below can be referred to in correspondence with the reversible locking structure shell described above.

[0043] The manufacturing method of the reversible locking structure housing includes the following steps: S1: Prepare the reinforcing layer 11 and the elastic matrix layer 12 respectively. The continuous fibers of the reinforcing layer 11 and / or the cross fibers of the elastic matrix layer 12 are selected from carbon fiber, aramid fiber, or hybrid fibers. This ensures both the high strength and high modulus of the reinforcing layer 11 and, with the help of the elastic matrix, imparts buffering and rebound properties to the material, laying the material foundation for subsequent locking and rebound functions. The thickness uniformity of the single-layer prefabricated structure must be controlled to avoid local fiber agglomeration affecting the structural mechanical properties.

[0044] S2: Mold preparation. Based on the shape of the plate-shaped reversible locking structure shell and the morphology of the buckling guide groove 13, a mold with protrusions on the inner surface that match the buckling guide groove 13 is manufactured. The inner surface of the mold is polished to a roughness Ra≤0.8μm, and then a release agent is applied. The mold is made of steel or aluminum alloy to ensure morphological stability during the molding process; the protrusion shape matches the U-shaped cross-section of the buckling guide groove 13 to ensure the molding accuracy of the groove; polishing to Ra≤0.8μm can prevent mold defects from being imprinted on the shell surface and reduce structural weak points; a high-temperature resistant silicone-based release agent is selected, and after uniform application, it ensures smooth demolding of the shell after curing, while preventing damage to the fine structure of the buckling guide groove 13 during the demolding process.

[0045] S3: Layup molding involves sequentially laying the reinforcing layer 11 and the elastic matrix layer 12 within the mold to form a shell structure where the reinforcing layer 11 and the elastic matrix layer 12 are stacked. The reinforcing layer 11 and the elastic matrix layer 12 can be laid alternately, or more reinforcing layers 11 or elastic matrix layers 12 can be laid as needed. Appropriate tension is applied during each layer laying to ensure a tight fit between the reinforcing layer 11 and the elastic matrix layer 12, avoiding interlayer air bubbles. This orderly layup design achieves a synergy between high material rigidity and controllable deformation, while providing structural support for a preset ultimate deformation threshold.

[0046] S4: Curing treatment. The mold after layup is placed in an autoclave, pressure is applied at 0.5-1.0 MPa, and the temperature is increased to 120-150°C at a rate of 2-5°C / min, held for 60-120 minutes, and then cooled to room temperature at a rate of 1-3°C / min to cure the shell. Autoclave pressure control ensures a tight bond between the reinforcing layer 11 and the elastic matrix layer 12, reducing interlayer porosity, improving interfacial bonding efficiency, and preventing interlayer separation during subsequent deformation. Controlled heating rate prevents excessively rapid matrix curing, which could lead to stress concentration, while controlled cooling rate prevents excessive temperature differences that could cause structural cracking. For shells used in heavy-load scenarios such as rocket landing legs, the pressure can be adjusted to 0.7 MPa, the temperature increased to 180°C, and held for 2 hours to further enhance the curing strength. The entire curing process, through precise temperature and pressure control, ensures uniform curing of the shell, providing a stable microstructural foundation for achieving a controllable deformation threshold.

[0047] S5: Post-processing involves demolding the cured shell to obtain a reversible locking structure shell. The shell edges can be trimmed and / or mounting holes can be machined as needed. Edge trimming can be performed using CNC laser cutting to ensure dimensional accuracy and avoid burrs caused by mechanical trimming. Mounting holes can be machined using a diamond drill bit at a speed of 1000-1500 r / min. A modified epoxy resin coating with a thickness of 50-100 μm ensures adhesion without adding excessive weight. Covering the outer surface and the inner walls of the grooves, the coating resists corrosion from rainwater and salt spray, while reducing deformation friction at the grooves and extending the shell's service life. If environmental requirements are needed, a biodegradable resin can be used for the coating, aligning with green manufacturing trends.

[0048] Furthermore, according to the manufacturing method of the reversible locking structure shell of this utility model, when preparing a reversible locking structure shell for applications with high load requirements, such as rocket legs, the curing pressure of the autoclave is preferably adjusted to 0.7 MPa, the curing temperature to 180°C, and the curing time extended to 2 hours; when machining the mounting holes, a diamond drill bit is preferably used, and the drilling speed is controlled at 1000-1500 r / min. Specifically, adjusting the curing parameters for scenarios with high load requirements is because the shell needs to withstand extreme vertical impact loads, and the requirements for interlayer bonding strength, overall rigidity, and fatigue resistance are much higher than in ordinary scenarios. For example, a curing pressure of 0.7 MPa is higher than the median of the conventional 0.5-1.0 MPa range, which can further compress the interlayer porosity, making the reinforcing layer 11 and the elastic matrix layer 12 adhere more tightly and preventing interlayer separation during impact. A curing temperature of 180℃ and a curing time of over 2 hours promote the full cross-linking and curing of the epoxy resin matrix, forming a more stable three-dimensional network structure. This enhances the material's creep resistance and load-bearing capacity, ensuring the landing legs maintain structural integrity after multiple impacts, meeting the rocket's reusable design requirements. Diamond drill bits are used to machine the mounting holes, avoiding defects such as fiber tearing and burrs that occur when cutting carbon fiber with ordinary drill bits, ensuring a smooth hole wall. A drilling speed of 1000-1500 r / min is the optimal range for drilling carbon fiber composite materials. Too low a speed can easily lead to fiber compression and breakage, while too high a speed can easily cause the matrix to soften due to frictional heat, both of which will affect the strength of the mounting holes.

[0049] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "method," "specific method," or "some methods," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or method is included in at least one embodiment or method of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or method. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or methods. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or methods described in this specification, as well as the features of different embodiments or methods.

[0050] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A reversible locking structure housing, characterized in that, Includes a fiber composite material body (10); The fiber composite material body (10) is a composite structure formed by stacking a reinforcing layer (11) and an elastic matrix layer (12). The reinforcing layer (11) is formed by a regular arrangement of continuous fibers, and the elastic matrix layer (12) is formed by a regular arrangement of cross fibers. The fiber composite material body (10) is provided with buckling guide grooves (13) adapted to the distribution of its force direction. The buckling guide grooves (13) are recessed structures formed by pressing the shell surface. When an external force is applied to the fiber composite material body (10) and the displacement reaches a preset value, the buckling guide groove (13) guides the body to undergo controllable deformation and switch to a stable force state to achieve locking; After the external force is removed: The fiber composite material body (10) automatically springs back to its initial state; Alternatively, the fiber composite body (10) may be disengaged from the jamming state under the influence of another external force in the opposite direction and spring back to its initial state.

2. The reversible locking structure housing according to claim 1, characterized in that, The cross-section of the buckling guide groove (13) is U-shaped.

3. The reversible locking structure housing according to claim 1, characterized in that, The arrangement of the cross fibers in the elastic matrix layer (12) includes: In the cross-arrangement method, a portion of the cross fibers are arranged along the length direction of the shell, and another portion of the cross fibers are arranged perpendicular to the length direction of the shell; And / or, in an obliquely cross arrangement, the cross fibers are respectively arranged in a +n° and -n° direction relative to the length direction of the shell.

4. The reversible locking structure housing according to any one of claims 1 to 3, characterized in that, The thickness of a single layer of the reinforcing layer (11) and / or the elastic matrix layer (12) is greater than 0 and less than or equal to 1 mm.

5. The reversible locking structure housing according to any one of claims 1 to 3, characterized in that, The overall shape of the fiber composite material body (10) is flat or arched.

6. The reversible locking structure housing according to any one of claims 1 to 3, characterized in that, The outer surface of the fiber composite material body (10) and the inner wall of the buckling guide groove (13) are covered with a heat-resistant and corrosion-resistant coating.

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