3D printing layered honeycomb sandwich panel and processing method thereof

Abstract

The invention discloses a 3D printing layered honeycomb sandwich panel and a processing method thereof. The processing method comprises the steps that a digital forming platform is constructed, process parameters are initialized, a functional interface layer is laid on a printing substrate in advance, a three-dimensional model is generated, and the printing substrate is divided into a plurality of gradient areas; collaborative printing of a lower panel structure is executed, and a composite panel base body is formed by adopting a multi-nozzle alternate deposition process; according to the characteristics of the divided gradient areas, honeycomb units are formed layer by layer by dynamically controlling printing rheological parameters, and a gradient honeycomb core layer is constructed; the cooperative growth of the upper panel and the gradient honeycomb core layer is realized by adopting a rotary incongruous printing strategy; the performance of the core layer material is regulated and controlled through a multi-stage heat treatment process, and the functional interface layer is activated to obtain the honeycomb sandwich panel; according to the honeycomb sandwich board, the mechanical property customized distribution of the honeycomb core layer is realized, the surface-core interface bonding strength is improved by combining the directional activation mechanism of the micro interlocking structure and the functional interface layer, and the honeycomb sandwich board with high mechanical property and thermal stability is provided.

Description

Technical Field

[0001] The present invention relates to the technical field of sandwich processing, and in particular to a 3D printed layered honeycomb sandwich panel and a processing method thereof. Background Art

[0002] Due to their lightweight and high specific strength, layered honeycomb sandwich panels are widely used in new energy vehicle battery pack housings, building curtain walls, cold chain logistics equipment, and other fields. For example, the housing of a new energy vehicle battery pack must simultaneously meet core requirements such as lightweight (to reduce overall vehicle energy consumption), impact resistance (to ensure battery cell safety), and thermal stability (to adapt to temperature swings between -30°C and 80°C during charging and discharging). However, traditional honeycomb sandwich panels are susceptible to stress concentration at the core-to-core interface due to differences in thermal expansion coefficients under temperature fluctuations, leading to interfacial delamination and even structural failure, severely restricting their application in long-life, high-reliability scenarios.

[0003] In existing technologies, honeycomb sandwich panels are mostly made using a process that combines hot pressing and adhesive lamination. For example, epoxy resin adhesive is used to bond aluminum alloy panels to aramid paper honeycomb cores. Although this type of process can achieve initial bonding, it has inherent defects: the thermal expansion coefficient of the adhesive is significantly different from that of the metal panel and honeycomb core (anisotropic expansion). Under temperature alternation, the interfacial shear stress can reach 35MPa, far exceeding the tolerance limit of the adhesive layer (usually <20MPa), resulting in interfacial delamination failure. In addition, the bonding process makes it difficult to achieve customized design of the micro-morphology of the face-core interface, and it is impossible to disperse thermal stress through mechanical interlocking effects. This defect directly results in the lifespan of existing products in scenarios such as new energy vehicle battery packs (lower than the warranty requirements of the entire vehicle), becoming a technical bottleneck restricting industry upgrades.

[0004] In view of this, it is necessary to improve the manufacturing technology of the honeycomb sandwich panel in the prior art to solve the technical problem of delamination failure caused by mismatch of thermal expansion coefficient at the core interface under temperature alternating working conditions. Summary of the Invention

[0005] The purpose of the present invention is to provide a 3D printed layered honeycomb sandwich panel and a processing method thereof to solve the above technical problems.

[0006] To achieve this object, the present invention adopts the following technical solutions: A method for processing a 3D printed layered honeycomb sandwich panel comprises the following steps: S1: Build a digital molding platform and initialize process parameters. Pre-lay a functionalized interface layer on the printing substrate. Generate a 3D model based on the mechanical performance requirements of the target component and divide it into multiple gradient regions with different mechanical performance indicators. S2, performs collaborative printing of the lower panel structure, adopts a multi-nozzle alternating deposition process to form the composite panel matrix, and simultaneously generates a microscopic interlocking structure in the preset interface bonding area; S3, according to the characteristics of the divided gradient regions, the honeycomb units are formed layer by layer by dynamically controlling the printing rheological parameters, and directional reinforcement materials are embedded at every predetermined number of layers to construct a gradient honeycomb core layer; S4, uses a rotary anisotropic printing strategy to achieve the coordinated growth of the upper panel and the gradient honeycomb core layer, while applying controllable pressure in the vertical direction to complete the densification of the interlayers; S5, regulating the core layer material properties through a multi-stage heat treatment process, performing a morphological scan of the interface bonding area in combination with a visual inspection device, dynamically adjusting the molding parameters according to the scanning data, and applying a directional energy field to the functionalized interface layer to complete the activation of the functionalized interface layer, thereby obtaining a honeycomb sandwich panel.

[0007] Optionally, step S1 specifically includes the following steps: S11, build a multi-axis 3D printing system equipped with a molding platform, a dual print head module and a laser-assisted device. The first print head is equipped with an extrusion nozzle for extruding carbon fiber reinforced composite materials, and the second print head is equipped with a spray gun for direct writing high-viscosity slurries. The laser-assisted device integrates a near-infrared light source and a high-speed vision camera. S12, initializing the spatial coordinate system of the molding platform, calibrating the positioning accuracy of the dual print head module using a laser interferometer, setting the preheating temperature of the printing substrate to 80±2°C, and loading a carbon fiber / graphene composite film on the printing substrate as an initial functionalized interface layer; S13, preparing a gradient functionalized interface layer, coating a polyetheretherketone prepreg on the surface of the carbon fiber / graphene composite film, and processing dendritic grooves with a depth of 50-150 μm using a pulsed laser microtexturing technique to form a mechanical interlocking preset structure; S14, importing a three-dimensional solid model of the target component, determining the thermal expansion coefficient threshold of each region based on finite element thermal-mechanical coupling analysis, and dividing the gradient honeycomb core layer of the three-dimensional solid model into three mechanical property gradient regions along the thickness direction: a surface strengthening region, a transition gradient region, and a core energy absorption region.

[0008] Optionally, after step S14, the following steps may be further performed: S15, establish a honeycomb orientation optimization model, apply orthotropic material properties to each gradient area, and iteratively calculate the optimal arrangement angle of the honeycomb units through a machine learning algorithm, so that the honeycomb inclination angle in the principal stress direction of the surface strengthening area is 0±2°, and the inclination angle of the core energy absorption area is adjusted to 45±5°; S16, pre-setting the extrusion pressure and printing speed for the surface strengthening area, adopting a dynamic gradient strategy of 0.5-0.8 MPa pressure for the transition gradient area, setting a preset fixed pressure for the core energy absorption area, and associating a temperature compensation coefficient to allocate regional process parameter sets; S17, input the process parameter set into the digital twin system, predict the thermal stress distribution of the interface layer through real-time rendering, and automatically optimize the gradient area boundary curvature radius when it is detected that the local stress concentration exceeds 80% of the material yield strength.

[0009] Optionally, step S2 specifically includes the following steps: S21, initializing the multi-nozzle collaborative printing parameters, setting the extrusion temperature and wire feed speed of the first print head, and the extrusion pressure of the second print head, and associating the phase difference compensation algorithm of the dual-nozzle movement path; S22, performing preheating and interface activation treatment of the printed substrate, heating the functionalized interface layer to 120°C by a laser-assisted device to activate the polar functional groups on the surface of the mechanical interlocking preset structure, and simultaneously starting a vacuum adsorption device to fix the printed substrate; S23, controlling the first print head to print the carbon fiber reinforced composite material along the 0° direction to form the main load-bearing grid, and the second print head to fill the high-viscosity slurry along the 90° direction, implementing a multi-axis linkage deposition process; S24, during the printing of the main bearing grid, when the nozzle moves to the preset interface bonding area, the laser-assisted device is triggered to remelt the surface of the deposited material in a micro-area, forming a molten pool depression with a diameter of 200-500μm. The core layer compatible slurry is simultaneously injected to form mushroom-shaped anchoring protrusions, generating an interface micro-interlocking structure; S25 performs online closed-loop quality control, monitoring fiber orientation and pore distribution in real time through a high-speed visual camera integrated in the print head. When it detects that the local porosity exceeds the preset porosity value, it automatically increases the extrusion pressure in the corresponding area by 10-15% and reduces the printing speed to compensate and repair.

[0010] Optionally, step S3 specifically includes the following steps: S31, initially loading the set process parameter set, setting the initial extrusion pressure for the surface strengthening area, transition gradient area, and core energy absorption area, associating the temperature compensation coefficient, and loading the honeycomb unit size distribution function of each area; S32: Start the core layer substrate printing, using the direct writing process to deposit the shape memory composite material slurry along a 45° deflection direction. The slurry rheological properties are monitored in real time by a piezoelectric sensor. When the viscosity deviation is detected to be greater than 10%, the extrusion pressure adaptive adjustment module is triggered. S33, a regular hexagonal close-packed honeycomb is generated in the surface strengthening area, a gradient diamond honeycomb is used in the transition gradient area, and a chiral spiral honeycomb is arranged in the core energy absorption area; S34, performing a reinforcement material embedding process, after each completion of the first preset layer of honeycomb printing, pre-place nickel-titanium alloy wire at the intersection of the honeycomb unit diagonals, and press the alloy wire into the uncured slurry to form a Z-direction reinforcement channel; S35, implement interlayer performance control, start pulsed laser pre-curing after each layer of honeycomb printing is completed, set the laser with preset energy density to locally cure the overlapping area of ​​the honeycomb wall, and complete the construction of the gradient honeycomb core layer.

[0011] Optionally, the pressure adaptive adjustment module specifically includes: Fuzzy PID controller, with built-in pressure compensation algorithm library, receives sensor data and outputs pressure adjustment value through fuzzy rule library; A piezoelectric sensor, embedded inside the second print head, measures the rheological properties of the slurry in real time; The piezoelectric ceramic actuator is composed of a multi-layer piezoelectric stack and is concentrically arranged with the second print head, and is used to adjust the ejection gap according to the control signal.

[0012] Optionally, step S4 specifically includes the following steps: S41, initializing rotary printing parameters, setting the print head rotation angular velocity, and synchronously loading the three-dimensional data of the gradient honeycomb core layer into the motion control system; S42, controlling the rotary print head to deposit the upper panel material along an alternating path of ±45° along the normal deflection of the core layer surface, while driving the core layer lifting platform to synchronously lift at a preset rate to achieve morphologically matching growth of the upper panel and the gradient honeycomb core layer; S43, performing dynamic pressure densification, after each deposition of the second preset layer of panel material, starting the piezoelectric ceramic array to apply vertical pulse pressure for a preset time, and simultaneously using infrared thermal imaging to monitor the interlayer bonding state; S44, analyzing and monitoring the interlayer bonding state, when detecting that the local gap is greater than 20 μm, triggering the rotary print head to perform secondary imprinting processing, and increasing the pulse pressure in the corresponding area for compensation and strengthening.

[0013] Optionally, step S5 specifically includes the following steps: S51, performing a multi-stage gradient heat treatment, first heating to 120°C at a rate of 5°C / min and holding for 30 minutes under a nitrogen protection environment, then heating to 200°C at a rate of 10°C / min and holding for 15 minutes, and then rapidly cooling at 80°C / s by liquid nitrogen spraying to form a martensitic phase transformation texture of the core layer shape memory material; S52, starting the visual scanning system to reconstruct the three-dimensional topography of the interface bonding area between the face and the core, and extracting key topography data therefrom; S53, build a machine learning optimization model, input the acquired topography data into the trained neural network, and output the optimal compensation parameter combination: when the bonding area ratio is less than 85%, generate a temperature compensation value ΔT = +10~15°C, and when the filling degree deviation is greater than 12%, calculate a pressure compensation value ΔP = 0.3~0.5MPa; S54, applying compensation temperature and compensation pressure in the vacuum hot pressing equipment according to the output optimal compensation parameters, and maintaining the preset compensation time to perform the vacuum hot pressing process with dynamic parameter compensation; S55, taking out the honeycomb sandwich panel after vacuum hot pressing, implementing multi-energy field coordinated activation, first irradiating the functionalized interface layer with near-infrared laser to trigger the expansion of the graphene thermal conductive film, and then switching to the ultrasonic field to induce the dendrite structure to produce a Z-direction deformation displacement of 0.2-0.5mm, so as to activate the functionalized interface layer and obtain the finished honeycomb sandwich panel.

[0014] The present invention further provides a honeycomb sandwich panel, characterized in that it is manufactured using the above-mentioned processing method of the 3D printed layered honeycomb sandwich panel, and the honeycomb sandwich panel specifically comprises: The upper panel is composed of alternating layers of carbon fiber reinforced composite materials and high-viscosity slurry, with an interface micro-interlocking structure formed on its surface; The gradient honeycomb core layer includes a surface strengthening area, a transition gradient area, and a core energy absorption area in the thickness direction; The functionalized interface layer, located between the lower panel and the core layer, contains a dendritic interlocking structure and a graphene thermal conductive film, which is activated by a near-infrared laser to produce a 0.2-0.5mm deformation displacement in the Z direction; The directional reinforcement network consists of nickel-titanium alloy wires distributed along the diagonal lines of the honeycomb, arranged in a 45° spiral, forming a three-dimensional reinforcement skeleton with the honeycomb units.

[0015] Compared with the prior art, the present invention has the following beneficial effects: BRIEF DESCRIPTION OF THE DRAWINGS In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0016] The structures, proportions, sizes, etc. depicted in the drawings of this specification are only used to match the contents disclosed in the specification so as to facilitate understanding and reading by persons familiar with this technology. They are not intended to limit the conditions under which the present invention can be implemented and therefore have no substantive technical significance. Any structural modifications, changes in proportional relationships, or adjustments in size should still fall within the scope of the technical contents disclosed in the present invention without affecting the effects and objectives that can be achieved by the present invention.

[0017] Figure 1 This is a schematic diagram of a process of manufacturing a 3D printed layered honeycomb sandwich panel according to the first embodiment of the present invention; Figure 2 This is a second flow chart of the method for processing the 3D printed layered honeycomb sandwich panel of the first embodiment; Figure 3 This is a schematic structural diagram of the 3D printed layered honeycomb sandwich panel of the second embodiment; Figure 4 This is a planar schematic diagram of the functionalized interface layer of the 3D printed layered honeycomb sandwich panel of the second embodiment. DETAILED DESCRIPTION

[0018] In order to make the purpose, features, and advantages of the present invention more obvious and easy to understand, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described below are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. In the description of the present invention, it should be understood that the terms "upper," "lower," "top," "bottom," "inner," "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of the present invention and simplify the description. They are not intended to indicate or imply that the devices or elements referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. It should be noted that when a component is considered to be "connected" to another component, it may be directly connected to the other component or there may be a centrally located component.

[0019] The technical solution of the present invention will be further described below with reference to the accompanying drawings and through specific implementation methods.

[0020] Example 1: Combine Figure 1 and Figure 2 As shown, an embodiment of the present invention provides a method for processing a 3D printed layered honeycomb sandwich panel, comprising the following steps: S1: Build a digital molding platform and initialize process parameters. Pre-lay a functionalized interface layer on the printing substrate. Generate a 3D model based on the mechanical performance requirements of the target component and divide it into multiple gradient regions with different mechanical performance indicators. By constructing a digital molding platform and dividing it into gradient regions, it is possible to match the mechanical performance requirements of the target component and achieve customized material distribution design. The pre-laying of the functionalized interface layer not only provides a deformation buffering mechanism for subsequent interface bonding but also releases preset functional properties (such as shape memory or stress response) after energy field activation, significantly improving the compatibility of the surface-core interface. The gradient division of the 3D model, combined with parameter initialization, lays the data foundation for multi-material collaborative printing and performance gradient transitions, avoiding the stress concentration problems caused by traditional uniform structures.

[0021] S2, performs collaborative printing of the lower panel structure, adopts a multi-nozzle alternating deposition process to form the composite panel matrix, and simultaneously generates a microscopic interlocking structure in the preset interface bonding area; The multi-nozzle alternating deposition process, through the coordinated extrusion of heterogeneous materials, creates a highly strong and tough composite panel matrix, eliminating the performance shortcomings of a single material. The simultaneously generated microscopic interlocking structure significantly increases the contact area between the panel and the core layer. Combined with subsequent pressure densification, this enhances interfacial bonding strength.

[0022] S3, according to the characteristics of the divided gradient regions, the honeycomb units are formed layer by layer by dynamically controlling the printing rheological parameters, and directional reinforcement materials are embedded at every predetermined number of layers to construct a gradient honeycomb core layer; Dynamic rheological parameter control (such as extrusion rate and temperature gradient) combined with layer-by-layer honeycomb unit molding achieves a gradient distribution of core mechanical properties. Embedding directional reinforcements specifically enhances the compressive and shear resistance of the honeycomb core, while periodic reinforcements disrupt crack propagation paths and enhance energy absorption efficiency.

[0023] S4, uses a rotary anisotropic printing strategy to achieve the coordinated growth of the upper panel and the gradient honeycomb core layer, while applying controllable pressure in the vertical direction to complete the densification of the interlayers; The rotational anisotropic printing strategy effectively eliminates anisotropic defects and enhances the interlaminar shear strength of the upper panel by varying the direction of material deposition. Combined with the coordinated growth of the core layer and vertical pressure loading, this process effectively eliminates interlaminar porosity and forms a densified metallurgical bond interface. This process also maintains synchronous deformation coordination between the face and core in irregularly curved structures, avoiding the risk of interfacial delamination associated with traditional split-body bonding and improving impact resistance.

[0024] S5, through a multi-stage heat treatment process to regulate the core layer material properties, combined with a visual inspection device to perform a morphological scan of the interface bonding area, dynamically adjust the molding parameters according to the scanning data, and apply a directional energy field to the functionalized interface layer to complete the activation of the functionalized interface layer to obtain a honeycomb sandwich panel.

[0025] Multi-stage heat treatment, through temperature-time coupled control, allows for targeted regulation of the core material's phase transition behavior, achieving synergistic optimization of strength and toughness. Visual inspection and dynamic parameter correction form a closed-loop control system, compensating for printing errors in real time. Directed energy fields (such as lasers or microwaves) activate the preset response characteristics of the functionalized interface layer, simultaneously releasing residual stress and enhancing chemical bonding, improving product thermal stability and fatigue life.

[0026] The working principle of the present invention is as follows: first, a digital molding platform is constructed, a functionalized interface layer is laid on the printing substrate, and the three-dimensional model is divided into multiple gradient areas based on the mechanical performance requirements; then, a multi-nozzle alternating deposition process is used to form the lower panel and simultaneously generate a microscopic interlocking structure; then, the printing rheological parameters are dynamically regulated according to the characteristics of the gradient area, and a honeycomb core layer containing directional reinforcement materials is constructed layer by layer; then, a rotary anisotropic printing strategy is adopted to synchronously grow the upper panel, and vertical pressure is applied to achieve interlayer densification and bonding; the core layer performance is regulated by multi-stage heat treatment, the process parameters are dynamically corrected in combination with visual inspection data, and a directional energy field is used to activate the preset deformation mechanism of the functionalized interface layer to complete the preparation of a high-performance honeycomb sandwich panel; this method realizes the customized distribution of the mechanical properties of the honeycomb core layer through gradient area division and dynamic rheological control, combines the microscopic interlocking structure with the directional activation mechanism of the functionalized interface layer, so as to improve the surface-core interface bonding strength, and the synergistic effect of rotary anisotropic printing and vertical pressure loading reduces the interlayer porosity and improves the impact resistance, thereby providing a honeycomb sandwich panel with high mechanical properties and thermal stability.

[0027] In this embodiment, it is specifically explained that step S1 specifically includes the following steps: S11, build a multi-axis 3D printing system equipped with a molding platform, a dual print head module and a laser-assisted device. The first print head is equipped with an extrusion nozzle for extruding carbon fiber reinforced composite materials, and the second print head is equipped with a spray gun for direct writing high-viscosity slurries. The laser-assisted device integrates a near-infrared light source and a high-speed vision camera. Specifically, a five-degree-of-freedom linkage machine tool is configured as the forming platform. The first print head is equipped with a 0.4mm carbon fiber composite material special nozzle and heated to 380℃±10℃. The second print head is equipped with a direct-writing stainless steel spray gun with an inner diameter of 1.2mm. The laser module integrates a 1064nm near-infrared fiber laser and a high-speed camera.

[0028] S12, initializing the spatial coordinate system of the molding platform, calibrating the positioning accuracy of the dual print head module using a laser interferometer, setting the preheating temperature of the printing substrate to 80±2°C, and loading a carbon fiber / graphene composite film on the printing substrate as an initial functionalized interface layer; Laser interferometry is used for four-axis calibration of the X / Y / Z axes. The substrate is uniformly preheated to 80±0.5°C (maintained for ≥5 minutes) using a graphene heating film. The carbon fiber / graphene composite film is fixed by vacuum adsorption to ensure the flatness of the interface layer. This process reduces the slurry wetting angle at the interface layer to 15°.

[0029] S13, preparing a gradient functionalized interface layer, coating a polyetheretherketone prepreg on the surface of the carbon fiber / graphene composite membrane, and processing dendritic grooves with a depth of 50-150 μm using pulsed laser microtexturing technology to form a mechanically interlocking preset structure; It should be noted that, combined with Figure 4 Figure 2 shows the microstructure of dendritic grooves. Laser processing of these grooves creates a network of microgrooves with a branch spacing of 200-500μm (a depth-to-width ratio of 1:3) on the surface of a polyetheretherketone (PEEK) prepreg. A copper nanoparticle reinforcement layer is premixed at the bottom of the grooves, forming metal-polymer mechanical interlocking points during subsequent heat treatment.

[0030] S14, importing a three-dimensional solid model of the target component, determining the thermal expansion coefficient threshold of each region based on finite element thermal-mechanical coupling analysis, and dividing the gradient honeycomb core layer of the three-dimensional solid model into three mechanical property gradient regions along the thickness direction: a surface strengthening region, a transition gradient region, and a core energy absorption region.

[0031] A finite element thermomechanical coupling model was established to calculate that the surface reinforcement zone must maintain a CTE of less than 25 × 10⁻⁶ / °C, the transition zone allows for a CTE of up to 45 × 10⁻⁶ / °C, and the core energy absorption zone is limited to a CTE of more than 60 × 10⁻⁶ / °C. The model is divided along the thickness into the following sections: the surface (20% of the thickness, suitable for accommodating high stresses), the transition zone (40% for deformation coordination), and the core (40% for energy absorption).

[0032] S15, establish a honeycomb orientation optimization model, apply orthotropic material properties to each gradient area, and iteratively calculate the optimal arrangement angle of the honeycomb units through a machine learning algorithm, so that the honeycomb inclination angle in the principal stress direction of the surface strengthening area is 0±2°, and the inclination angle of the core energy absorption area is adjusted to 45±5°; A Bayesian optimization model (honeycomb orientation optimization model) was established based on the GRU neural network, with maximizing specific stiffness and energy absorption efficiency as the objective function. The honeycomb angles of each partition were determined after iteration: 0° (hexagonal cells) in the surface layer, 22.5° (gradient honeycomb) in the transition zone, and the inclination angle of the core energy absorption zone was adjusted to 45°.

[0033] S16, pre-set the extrusion pressure and printing speed for the surface strengthening area, adopt a dynamic gradient strategy of 0.5-0.8 MPa pressure in the transition gradient area, set a preset fixed pressure in the core energy absorption area, and associate the temperature compensation coefficient to allocate the regional process parameter set to reduce the slurry flow rate during continuous gradient printing.

[0034] S17, input the process parameter set into the digital twin system, predict the thermal stress distribution of the interface layer through real-time rendering, and automatically optimize the gradient area boundary curvature radius when it is detected that the local stress concentration exceeds 80% of the material yield strength.

[0035] A coupled physical model of the print head, material, and process was established, and real-time thermal stress cloud images were used to assess risk areas in the interface layer. When critical areas were detected, a parametric sweep algorithm was used to adjust the curvature of the gradient zone boundary to the optimal radius R = 3t (where t is the panel thickness), thereby reducing the equivalent stress peak.

[0036] In this embodiment, it is specifically explained that step S2 specifically includes the following steps: S21, initialize the multi-nozzle collaborative printing parameters, set the extrusion temperature and wire feeding speed of the first print head, and the extrusion pressure of the second print head, and associate the phase difference compensation algorithm of the dual-nozzle movement path; preferably, set the extrusion temperature of the first print head to 380±5℃, the wire feeding speed to 15-25mm / s, and the extrusion pressure of the second print head to 0.3-0.8MPa.

[0037] The phase difference compensation algorithm for the linked dual-nozzle movement paths uses a genetic algorithm to optimize the phase difference between the two nozzles (phase angle Φ = 22.5°) to ensure a stable path overlap ratio. This strategy solves the trajectory interference problem of traditional asynchronous printing and improves molding efficiency.

[0038] S22, performing preheating and interface activation treatment of the printed substrate, heating the functionalized interface layer to 120°C by a laser-assisted device to activate the polar functional groups on the surface of the mechanical interlocking preset structure, and simultaneously starting a vacuum adsorption device to fix the printed substrate; The functionalized interface layer is irradiated with a continuous laser at an energy density of 15 J / cm2, activating the epoxy groups within the dendritic grooves and reducing the contact angle to 12. Simultaneously activating the vacuum adsorption system maintains flatness and prevents substrate warping caused by thermal expansion.

[0039] S23, controlling the first print head to print the carbon fiber reinforced composite material along the 0° direction to form the main load-bearing grid, and the second print head to fill the high-viscosity slurry along the 90° direction, implementing a multi-axis linkage deposition process; The first printhead prints the primary CF / PEEK mesh at a linear speed of 30 mm / s along a 0° orientation, while the second printhead fills the mesh with chopped carbon fiber / SMP slurry in a cross-sectional 90° path. Piezoelectric microvibration is applied simultaneously during printing to allow the slurry to penetrate the pores of the CF mesh, enhancing shear strength.

[0040] S24, during the printing of the main bearing grid, when the nozzle moves to the preset interface bonding area, the laser-assisted device is triggered to remelt the surface of the deposited material in a micro-area, forming a molten pool depression with a diameter of 200-500μm. The core layer compatible slurry is simultaneously injected to form mushroom-shaped anchoring protrusions, generating an interface micro-interlocking structure; When the nozzle enters the interface, a pulsed laser beam (spot diameter 400μm) is triggered to generate an instantaneous molten pool, into which a core-compatible slurry containing ceramic microspheres is injected through an auxiliary nozzle. After rapid cooling, a mushroom-shaped anchoring structure is formed.

[0041] S25 performs online closed-loop quality control, monitoring fiber orientation and pore distribution in real time through a high-speed visual camera integrated in the print head. When it detects that the local porosity exceeds the preset porosity value, it automatically increases the extrusion pressure in the corresponding area by 10-15% and reduces the printing speed to compensate and repair.

[0042] A high-speed vision system captures fiber orientation distribution and porosity defects. A morphological algorithm is used to analyze the porosity distribution map in real time. If the porosity in a local area exceeds 2% (area percentage), a compensation command is triggered: the extrusion pressure is increased by 15%, the speed is reduced to 10 mm / s, and micro-area remelting is performed through arc micro-melting to achieve a final average porosity of 0.7% ± 0.2%.

[0043] In this embodiment, it is specifically explained that step S3 specifically includes the following steps: S31, initially loading the set process parameter set, setting the initial extrusion pressure for the surface strengthening area, transition gradient area, and core energy absorption area, associating the temperature compensation coefficient, and loading the honeycomb unit size distribution function of each area; For the surface reinforcement zone (pressure 0.8MPa / compensation coefficient 1.2), the transition gradient zone (pressure 0.5-0.8MPa gradient / compensation coefficient 1.0), and the core energy absorption zone (pressure fixed at 0.3MPa / compensation coefficient 0.8), honeycomb size functions were applied to each zone: the surface regular hexagon had a side length of 3mm±0.1, the transition zone rhombus had a long axis of 5-2mm gradient, and the core spiral diameter was 0.5mm. The parameter model was verified through fluid dynamics simulation to improve the matching of the slurry shear thinning index.

[0044] S32: Start the core layer substrate printing, using the direct writing process to deposit the shape memory composite material slurry along a 45° deflection direction. The slurry rheological properties are monitored in real time by a piezoelectric sensor. When the viscosity deviation is detected to be greater than 10%, the extrusion pressure adaptive adjustment module is triggered. During direct writing, the piezoelectric sensor monitors the apparent viscosity of the slurry in real time. When a deviation of >10% is detected, the fuzzy PID controller is triggered to instantly correct the extrusion pressure (range 0.2-1.0MPa / response <10ms) and simultaneously adjust the screw speed to dynamically compensate for fluctuations in rheological parameters.

[0045] S33, a regular hexagonal close-packed honeycomb is generated in the surface strengthening area, a gradient diamond honeycomb is used in the transition gradient area, and a chiral spiral honeycomb is arranged in the core energy absorption area.

[0046] S34, performing a reinforcement material embedding process, after each completion of the first preset layer of honeycomb printing, pre-place nickel-titanium alloy wire at the intersection of the honeycomb unit diagonals, and press the alloy wire into the uncured slurry to form a Z-direction reinforcement channel; It should be noted that after every five layers of printing, an ultrasonic generator vertically presses a preheated NiTi wire (100μm diameter, phase transition temperature 60°C) into the honeycomb nodes, with the force monitored in real time. The ultrasonic cavitation effect causes the molten slurry to penetrate the micropores on the wire surface, forming a metal-polymer micromechanical bond and enhancing the structural bending stiffness in the Z direction.

[0047] S35, implement interlayer performance control, start pulsed laser pre-curing after each layer of honeycomb printing is completed, set the laser with preset energy density to locally cure the overlapping area of ​​the honeycomb wall, and complete the construction of the gradient honeycomb core layer.

[0048] After each layer is printed, the fiber laser is triggered to perform dot-matrix pre-curing along the intersection of the honeycomb walls at a scanning speed of 15 mm / s. The surface temperature is raised to the material's Tg + 20°C (for example, 170°C for PEEK) to enhance the interlayer molecular chain complexation. Simultaneously, an orthogonal magnetic field (0.3T) is applied to orient the chopped fibers and reduce interlayer porosity.

[0049] In this embodiment, it is further explained that the pressure adaptive adjustment module specifically includes: The fuzzy PID controller has a built-in pressure compensation algorithm library. After receiving sensor data, it outputs the pressure adjustment value through the fuzzy rule library. The fuzzy PID controller receives two inputs of μ(t) and Δμ / Δt (viscosity change rate) and solves the output through 20 sets of fuzzy rule libraries: When Δμ>+10% and Δμ / Δt>2Pa·s / ms→output pressure compensation ΔP=Kp×0.15MPa+Ki×∫Δμdt; When Δμ<-10% and Δμ / Δt<-1.5Pa·s / ms→ emergency flow correction is triggered, ΔP=-0.1MPa; The controller response time is less than 5ms, and parameter tuning is optimized based on the Lyapunov stability criterion.

[0050] A piezoelectric sensor, embedded within the second printhead, measures the slurry's rheological properties in real time. Embedded within the printhead flow channel, the piezoelectric sensor measures the shear stress τ and shear rate γ̇ as the slurry flows through it, calculating the apparent viscosity μ = τ / γ̇ in real time. A control program is triggered when a viscosity deviation Δμ > 10% (|μ measured -500 Pa·s| > 50 Pa·s) is detected.

[0051] The piezoelectric ceramic actuator, consisting of a multi-layer piezoelectric stack, is concentrically arranged with the second print head and is used to adjust the ejection gap according to the control signal. The piezoelectric ceramic stack (120 layers of PZT-5H, total displacement 50μm) generates axial expansion and contraction according to the ΔP command: ΔP=+0.15MPa→driving voltage+150V→ceramic elongation 30μm→nozzle gap reduction 12%; ΔP=-0.1MPa→driving voltage -100V→ceramic shrinks 20μm→nozzle gap expands 8%; The adjusted slurry flux Q correction amount ΔQ=3α×(Δd)^2 (α is the flow channel morphology coefficient) ensures that the flow fluctuation is less than ±2.5%.

[0052] In this embodiment, it is specifically explained that step S4 specifically includes the following steps: S41, initializing rotary printing parameters, setting the print head rotation angular velocity, and synchronously loading the three-dimensional data of the gradient honeycomb core layer into the motion control system; The angular velocity of the rotating print head is set, and the core layer's 3D point cloud data is loaded into the linkage control system. The motion control system uses a graphical interpolation algorithm to convert the B-spline surface path into a pulse sequence for the drive motor, establishing a geometric mapping relationship between the print head's tilt angle and the core layer's topography.

[0053] S42, controlling the rotary print head to deposit the upper panel material along an alternating path of ±45° along the normal deflection of the core layer surface, while driving the core layer lifting platform to synchronously lift at a preset rate to achieve morphologically matching growth of the upper panel and the gradient honeycomb core layer; The print head adaptively deflects according to the NURBS surface trajectory, with the path spacing dynamically adjusted to 0.6 × (1 + z / h) mm (z is the current height as a percentage, h is the total height). The lifting platform rises at a rate of 0.25 mm / s, compensating for thermal expansion errors (temperature coefficient Kt = 2.3 × 10-6 / °C) in real time. Material deposition uses a pulsed extrusion mode to ensure that the wetting angle θ between the slurry and the core surface is less than 10°, and the lateral bond strength reaches 38 MPa.

[0054] S43, performing dynamic pressure densification, after each deposition of the second preset layer of panel material, starting the piezoelectric ceramic array to apply vertical pulse pressure for a preset time, and simultaneously using infrared thermal imaging to monitor the interlayer bonding state; Specifically, after every two layers are deposited, a piezoelectric ceramic array (36 elements, 0-100μm stroke) is triggered to apply vertical pulse pressure: the pressure amplitude is 0.8-1.2MPa (increasing with depth according to the rule P(z) = 0.8 + 0.4z / h), the frequency is 5Hz, and the pulse duration is 60 seconds. Simultaneously, an uncooled infrared thermal imager is used to obtain interface temperature distribution data. The interlayer bond strength is estimated according to the Arrhenius equation. If T_local > T_g + 15°C (T_g is the substrate glass transition temperature), the pressure is automatically reduced by 10%.

[0055] S44, analyzing and monitoring the interlayer bonding state, when detecting that the local gap is greater than 20 μm, triggering the rotary print head to perform secondary imprinting processing, and increasing the pulse pressure in the corresponding area for compensation and strengthening.

[0056] Specifically, when infrared image analysis shows local gaps or temperature abnormalities (ΔT>8°C), the secondary imprinting procedure is triggered: the print head re-presses the defective area at 80% of the diameter (the pressure is increased to 1.5MPa), and at the same time, the laser in-situ annealing equipment irradiates the area 2mm above the interface for 5 seconds to improve the viscoelastic recovery rate of the material. After compensation, the interlayer porosity is less than 0.3%.

[0057] In this embodiment, it is specifically explained that step S5 specifically includes the following steps: S51, performing a multi-stage gradient heat treatment, first heating to 120°C at a rate of 5°C / min and holding for 30 minutes under a nitrogen protection environment, then heating to 200°C at a rate of 10°C / min and holding for 15 minutes, and then rapidly cooling at 80°C / s by liquid nitrogen spraying to form a martensitic phase transformation texture of the core layer shape memory material; Under nitrogen protective atmosphere, three-stage temperature control is adopted: Pre-orientation stage: heating to 120°C at 5°C / min and holding for 30 min to orient the shape memory polymer molecular chains along the principal stress direction; Diffusion bonding stage: heating at 10°C / min to 200°C and holding for 15 minutes to trigger the softening and flow of the PEEK matrix, with the interfacial atomic diffusion depth reaching 0.8 μm; Microstructure control stage: Liquid nitrogen jet achieves ultra-rapid cooling of 80°C / s, promoting the austenite to martensite phase transformation (Ms=65°C), generating an interlaced lath-shaped martensite texture (lath width ≤100nm), and increasing the core layer shape recovery stress to 120MPa.

[0058] S52, starting the visual scanning system to reconstruct the three-dimensional topography of the interface bonding area between the face and the core, and extracting key topography data therefrom; Laser scanning is used to collect point clouds of the interface area and reconstruct a 3D topography model. Two core parameters are extracted through morphological algorithms: Actual bonding area ratio (Ab / At): calculates the effective contact area ratio of the dendrite interlocking structure; Geometric filling deviation (ΔF): evaluates the integrity of the slurry-filled groove (ΔF=1-Fmeasured / Fdesign×100%).

[0059] S53, build a machine learning optimization model, input the acquired morphology data into the trained neural network, and output the optimal compensation parameter combination: when the bonding area ratio is less than 85%, the temperature compensation value ΔT=+10~15℃ is generated, and when the filling degree deviation is greater than 12%, the pressure compensation value ΔP=0.3~0.5MPa is calculated.

[0060] S54, applying compensation temperature and compensation pressure in the vacuum hot pressing equipment according to the output optimal compensation parameters, and maintaining the preset compensation time to perform the vacuum hot pressing process with dynamic parameter compensation; In vacuum hot pressing equipment, temperature compensation: set the gradient target T* = T setting + ΔT (ΔT = 10~15℃), and use PID temperature control (overshoot ≤ 0.5℃); Pressure compensation: Optimize pressure distribution according to the Hertz contact model, and correct the local pressure to P=1.1P0+ΔP (P0 initial pressure 0.8MPa); The compensation time tc is calculated using the creep equation: tc=η0 / (E·ΔT²) (η0 matrix creep viscosity), ensuring sufficient rearrangement of the molecular chains (crosslinking degree increased to 92%).

[0061] S55, the honeycomb sandwich panel after vacuum hot pressing is taken out and multi-energy field synergistic activation is implemented. First, the functionalized interface layer is irradiated with near-infrared laser to trigger the expansion of the graphene thermal conductive film, and then the ultrasonic field is switched to induce the dendrite structure to produce a Z-direction deformation displacement of 0.2-0.5mm to activate the functionalized interface layer and obtain the finished honeycomb sandwich panel.

[0062] During the photothermal expansion stage, 980nm near-infrared laser irradiation is used, and the graphene thermal conductive film absorbs it, causing thermal expansion displacement in the Z direction (0.3mm±0.05); During the ultrasonic micro-forging stage, the ultrasonic wave was switched to 40kHz, and the dendrite structure was induced to produce plastic rheology by the alternating stress, which increased the depth of the anchoring protrusion embedded in the core honeycomb wall by 0.2mm and improved the mechanical bite force. During the deformation locking stage, the material is naturally cooled to below Tg under pressure to ensure the displacement recovery rate.

[0063] Example 2: Combine Figure 3 and Figure 4 As shown, the present invention further provides a honeycomb sandwich panel, which is manufactured using the processing method of the 3D printed layered honeycomb sandwich panel as in Example 1. The honeycomb sandwich panel specifically includes: The upper panel 10 and the lower panel 40 are formed by alternately laminating carbon fiber reinforced composite materials and high-viscosity slurry, and an interface micro-interlocking structure is formed on the surface of the lower panel 40.

[0064] The gradient honeycomb core layer 20 includes a surface strengthening area, a transition gradient area, and a core energy absorption area in sequence along the thickness direction.

[0065] The functionalized interface layer 30 is located between the lower panel 40 and the gradient honeycomb core layer 20, and comprises a dendritic interlocking structure and a graphene thermal conductive film, which generates a Z-axis deformation displacement of 0.2-0.5 mm through near-infrared laser activation.

[0066] The directional reinforcement network consists of nickel-titanium alloy wires distributed along the diagonal lines of the honeycomb, arranged in a 45° spiral, forming a three-dimensional reinforcement skeleton with the honeycomb units.

[0067] As described above, the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that the technical solutions described in the above embodiments can still be modified, or some of the technical features thereof can be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for processing a 3D printed layered honeycomb sandwich panel, characterized in that: The following steps are involved: S1: Build a digital transformation platform and initialize process parameters. Pre-lay a functionalized interface layer on the printing substrate. Generate a 3D model based on the mechanical performance requirements of the target component and divide it into multiple gradient regions with different mechanical performance indicators. S2, performs collaborative printing of the lower panel structure, adopts a multi-nozzle alternating deposition process to form the composite panel matrix, and simultaneously generates a microscopic interlocking structure in the preset interface bonding area; S3, according to the characteristics of the divided gradient regions, the honeycomb units are formed layer by layer by dynamically controlling the printing rheological parameters, and directional reinforcement materials are embedded at every predetermined number of layers to construct a gradient honeycomb core layer; S4, uses a rotary anisotropic printing strategy to achieve the coordinated growth of the upper panel and the gradient honeycomb core layer, while applying controllable pressure in the vertical direction to complete the densification of the interlayers; S5, regulating the core layer material properties through a multi-stage heat treatment process, performing a morphological scan of the interface bonding area in combination with a visual inspection device, dynamically adjusting the molding parameters according to the scanning data, and applying a directional energy field to the functionalized interface layer to complete the activation of the functionalized interface layer, thereby obtaining a honeycomb sandwich panel.

2. The method for processing a 3D printed layered honeycomb sandwich panel according to claim 1, characterized in that: The step S1 specifically includes the following steps: S11, build a multi-axis 3D printing system equipped with a molding platform, a dual print head module and a laser-assisted device. The first print head is equipped with an extrusion nozzle for extruding carbon fiber reinforced composite materials, and the second print head is equipped with a spray gun for direct writing high-viscosity slurries. The laser-assisted device integrates a near-infrared light source and a high-speed vision camera. S12, initializing the spatial coordinate system of the molding platform, calibrating the positioning accuracy of the dual print head module using a laser interferometer, setting the preheating temperature of the printing substrate to 80±2°C, and loading a carbon fiber / graphene composite film on the printing substrate as an initial functionalized interface layer; S13, preparing a gradient functionalized interface layer, coating a polyetheretherketone prepreg on the surface of the carbon fiber / graphene composite film, and processing dendritic grooves with a depth of 50-150 μm using a pulsed laser microtexturing technique to form a mechanical interlocking preset structure; S14, importing a three-dimensional solid model of the target component, determining the thermal expansion coefficient threshold of each region based on finite element thermal-mechanical coupling analysis, and dividing the gradient honeycomb core layer of the three-dimensional solid model into three mechanical property gradient regions along the thickness direction: a surface strengthening region, a transition gradient region, and a core energy absorption region.

3. The processing method of the 3D printed layered honeycomb sandwich panel according to claim 1, characterized in that: After step S14, the following steps are further included: S15, establish a honeycomb orientation optimization model, apply orthotropic material properties to each gradient area, and iteratively calculate the optimal arrangement angle of the honeycomb units through a machine learning algorithm, so that the honeycomb inclination angle in the principal stress direction of the surface strengthening area is 0±2°, and the inclination angle of the core energy absorption area is adjusted to 45±5°; S16, pre-setting the extrusion pressure and printing speed for the surface strengthening area, adopting a dynamic gradient strategy of 0.5-0.8 MPa pressure for the transition gradient area, setting a preset fixed pressure for the core energy absorption area, and associating a temperature compensation coefficient to allocate regional process parameter sets; S17, input the process parameter set into the digital twin system, predict the thermal stress distribution of the interface layer through real-time rendering, and automatically optimize the gradient area boundary curvature radius when it is detected that the local stress concentration exceeds 80% of the material yield strength.

4. The method for processing a 3D printed layered honeycomb sandwich panel according to claim 3, characterized in that: The step S2 specifically includes the following steps: S21, initializing the multi-nozzle collaborative printing parameters, setting the extrusion temperature and wire feed speed of the first print head, and the extrusion pressure of the second print head, and associating the phase difference compensation algorithm of the dual-nozzle movement path; S22, performing preheating and interface activation treatment of the printed substrate, heating the functionalized interface layer to 120°C by a laser-assisted device to activate the polar functional groups on the surface of the mechanical interlocking preset structure, and simultaneously starting a vacuum adsorption device to fix the printed substrate; S23, controlling the first print head to print the carbon fiber reinforced composite material along the 0° direction to form the main load-bearing grid, and the second print head to fill the high-viscosity slurry along the 90° direction, implementing a multi-axis linkage deposition process; S24, during the printing of the main bearing grid, when the nozzle moves to the preset interface bonding area, the laser-assisted device is triggered to remelt the surface of the deposited material in a micro-area, forming a molten pool depression with a diameter of 200-500μm. The core layer compatible slurry is simultaneously injected to form mushroom-shaped anchoring protrusions, generating an interface micro-interlocking structure; S25 performs online closed-loop quality control, monitoring fiber orientation and pore distribution in real time through a high-speed visual camera integrated in the print head. When it detects that the local porosity exceeds the preset porosity value, it automatically increases the extrusion pressure in the corresponding area by 10-15% and reduces the printing speed to compensate and repair.

5. The method for processing a 3D printed layered honeycomb sandwich panel according to claim 3, characterized in that: The step S3 specifically includes the following steps: S31, initially loading the set process parameter set, setting the initial extrusion pressure for the surface strengthening area, transition gradient area, and core energy absorption area, associating the temperature compensation coefficient, and loading the honeycomb unit size distribution function of each area; S32: Start the core layer substrate printing, using the direct writing process to deposit the shape memory composite material slurry along a 45° deflection direction. The slurry rheological properties are monitored in real time by a piezoelectric sensor. When the viscosity deviation is detected to be greater than 10%, the extrusion pressure adaptive adjustment module is triggered. S33, a regular hexagonal close-packed honeycomb is generated in the surface strengthening area, a gradient diamond honeycomb is used in the transition gradient area, and a chiral spiral honeycomb is arranged in the core energy absorption area; S34, performing a reinforcement material embedding process, after each completion of the first preset layer of honeycomb printing, pre-place nickel-titanium alloy wire at the intersection of the honeycomb unit diagonals, and press the alloy wire into the uncured slurry to form a Z-direction reinforcement channel; S35, implement interlayer performance control, start pulsed laser pre-curing after each layer of honeycomb printing is completed, set the laser with preset energy density to locally cure the overlapping area of ​​the honeycomb wall, and complete the construction of the gradient honeycomb core layer.

6. The method for processing a 3D printed layered honeycomb sandwich panel according to claim 5, characterized in that: The pressure adaptive adjustment module specifically includes: Fuzzy PID controller, with built-in pressure compensation algorithm library, receives sensor data and outputs pressure adjustment value through fuzzy rule library; A piezoelectric sensor, embedded inside the second print head, measures the rheological properties of the slurry in real time; The piezoelectric ceramic actuator is composed of a multi-layer piezoelectric stack and is concentrically arranged with the second print head, and is used to adjust the ejection gap according to the control signal.

7. The method for processing a 3D printed layered honeycomb sandwich panel according to claim 1, characterized in that: The step S4 specifically includes the following steps: S41, initializing rotary printing parameters, setting the print head rotation angular velocity, and synchronously loading the three-dimensional data of the gradient honeycomb core layer into the motion control system; S42, controlling the rotary print head to deposit the upper panel material along an alternating path of ±45° along the normal deflection of the core layer surface, while driving the core layer lifting platform to synchronously lift at a preset rate to achieve morphologically matching growth of the upper panel and the gradient honeycomb core layer; S43, performing dynamic pressure densification, after each deposition of the second preset layer of panel material, starting the piezoelectric ceramic array to apply vertical pulse pressure for a preset time, and simultaneously using infrared thermal imaging to monitor the interlayer bonding state; S44, analyzing and monitoring the interlayer bonding state, when detecting that the local gap is greater than 20 μm, triggering the rotary print head to perform secondary imprinting processing, and increasing the pulse pressure in the corresponding area for compensation and strengthening.

8. The method for processing a 3D printed layered honeycomb sandwich panel according to claim 1, characterized in that: The step S5 specifically includes the following steps: S51, performing a multi-stage gradient heat treatment, first heating to 120°C at a rate of 5°C / min and holding for 30 minutes under a nitrogen protection environment, then heating to 200°C at a rate of 10°C / min and holding for 15 minutes, and then rapidly cooling at 80°C / s by liquid nitrogen spraying to form a martensitic phase transformation texture of the core layer shape memory material; S52, starting the visual scanning system to reconstruct the three-dimensional topography of the interface bonding area between the face and the core, and extracting key topography data therefrom; S53, build a machine learning optimization model, input the acquired topography data into the trained neural network, and output the optimal compensation parameter combination: when the bonding area ratio is less than 85%, generate a temperature compensation value ΔT = +10~15°C, and when the filling degree deviation is greater than 12%, calculate a pressure compensation value ΔP = 0.3~0.5MPa; S54, applying compensation temperature and compensation pressure in the vacuum hot pressing equipment according to the output optimal compensation parameters, and maintaining the preset compensation time to perform the vacuum hot pressing process with dynamic parameter compensation; S55, taking out the honeycomb sandwich panel after vacuum hot pressing, implementing multi-energy field coordinated activation, first irradiating the functionalized interface layer with near-infrared laser to trigger the expansion of the graphene thermal conductive film, and then switching to the ultrasonic field to induce the dendrite structure to produce a Z-direction deformation displacement of 0.2-0.5mm, so as to activate the functionalized interface layer and obtain the finished honeycomb sandwich panel.

9. A honeycomb sandwich panel, characterized in that: The 3D printed layered honeycomb sandwich panel is manufactured using the processing method according to any one of claims 1 to 8, wherein the honeycomb sandwich panel specifically comprises: The upper panel is composed of alternating layers of carbon fiber reinforced composite materials and high-viscosity slurry, with an interface micro-interlocking structure formed on its surface; The gradient honeycomb core layer includes a surface strengthening area, a transition gradient area, and a core energy absorption area in the thickness direction; The functionalized interface layer, located between the lower panel and the core layer, contains a dendritic interlocking structure and a graphene thermal conductive film, which is activated by a near-infrared laser to produce a 0.2-0.5mm deformation displacement in the Z direction; The directional reinforcement network consists of nickel-titanium alloy wires distributed along the diagonal lines of the honeycomb, arranged in a 45° spiral, forming a three-dimensional reinforcement skeleton with the honeycomb units.

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