Multifunctional integrated unmanned aerial vehicle landing platform composite material and preparation method

Abstract

The application discloses a multifunctional integrated unmanned aerial vehicle landing platform composite material and a preparation method thereof. The composite material comprises a surface functional layer, an intermediate buffer layer and a bottom substrate layer which are sequentially laminated; the surface functional layer comprises a surface lining plate, a plurality of prismatic protrusions arranged in an array and a flow guide groove, the flow guide grooves are arranged in interweaving and are communicated to form a flow guide path extending to the edge of the surface lining plate; the surface functional layer comprises nano-silicon dioxide modified polyurethane, energy storage light emitting material and a curing agent; the intermediate buffer layer comprises a core material sublayer, a first skin and a second skin located on the upper side and the lower side of the core material sublayer respectively; the bottom substrate layer is basalt fiber reinforced polyether ether ketone or basalt fiber reinforced polyphenylene sulfide; and the volume fraction of the basalt fiber is 55% to 70%. The material provided by the application has the functions of high strength, anti-skid buffer, wide temperature range weather resistance, anti-electromagnetic interference, rapid drainage, energy storage light emission and the like, and has a wide application scenario.

Description

Technical Field

[0001] This invention belongs to the field of materials technology for unmanned aerial vehicle (UAV) take-off and landing platforms, specifically relating to a composite material for a multifunctional integrated UAV take-off and landing platform and its preparation method. Background Technology

[0002] With the increasing application of drones in logistics delivery, facility inspection, environmental monitoring, and emergency rescue, the operating environment of drone take-off and landing platforms is becoming increasingly complex and diverse. Traditional metal or polymer-based take-off and landing platforms can no longer meet the requirements for safe take-off and landing in all weather conditions and multiple scenarios. Existing technologies mainly have the following shortcomings: First, the anti-slip and cushioning functions are separated. Existing take-off and landing platforms mostly use a single anti-slip coating or simple texture treatment, which significantly reduces the coefficient of friction under rain, snow, and frost conditions, making it easy for the landing gear to slip. At the same time, the cushioning structure usually relies on external rubber pads or spring components, which increases the thickness and weight of the platform, and the cushioning effect is limited.

[0003] Secondly, it lacks adaptability to a wide temperature range. The operating environment of drones spans a wide temperature range, from -30°C to 60°C. Existing polymer materials are prone to brittleness at low temperatures and softening and deformation at high temperatures, while metal materials suffer from dimensional instability due to thermal expansion and contraction, making it difficult to meet the requirements for all-weather deployment.

[0004] Third, electromagnetic compatibility is generally overlooked. The flight control system of drones relies on precision sensors such as magnetic compasses and GPS, while some existing take-off and landing platforms use ferromagnetic materials or composite materials containing metal components, which may interfere with airborne navigation equipment and affect landing accuracy.

[0005] Fourth, drainage and anti-slip structure are mutually restrictive. Although surface texture can increase friction, it easily retains water, which can form an ice layer in low-temperature environments, thus increasing the risk of slipping.

[0006] Fifth, due to the constraints of the surrounding environment of the take-off and landing platform, the safety of drones taking off and landing at night or in dim conditions cannot be guaranteed, which limits the scope of application of drones.

[0007] It should be noted that the information disclosed in the background section above is only used to enhance the understanding of the background of the present invention, and therefore may include information that does not constitute prior art known to those skilled in the art. Summary of the Invention

[0008] To address the technical challenges of existing UAV take-off and landing platform materials in simultaneously achieving good anti-slip and drainage performance, wide-temperature weather resistance, electromagnetic compatibility, cushioning performance, and nighttime take-off and landing safety, this invention provides a multifunctional integrated UAV take-off and landing platform composite material and its preparation method. The technical problem solved by this invention is achieved through the following technical solution: In a first aspect, the present invention provides a composite material for a multifunctional integrated unmanned aerial vehicle (UAV) take-off and landing platform, comprising a surface functional layer, an intermediate buffer layer and a bottom substrate layer stacked sequentially. The surface functional layer includes a surface liner and arrayed polygonal prism-shaped protrusions on the surface liner; a flow guide groove is provided on the upper surface of the surface liner, the flow guide grooves are interwoven and connected to form a flow guide path extending to the edge of the surface liner. The surface functional layer comprises nano-silica modified polyurethane, energy-storing luminescent material, and curing agent; wherein the mass content of nano-silica modified polyurethane is 70% to 85%; the mass content of the curing agent is 10% to 25%; the mass content of the energy-storing luminescent material is 5wt% to 15wt%, and the afterglow time of the energy-storing luminescent material is greater than or equal to 6 hours. The intermediate buffer layer includes a core material sublayer, a first skin located on the upper side of the core material sublayer, and a second skin located on the lower side of the core material sublayer; The bottom substrate layer is basalt fiber reinforced polyether ether ketone or basalt fiber reinforced polyphenylene sulfide; wherein the volume fraction of basalt fiber in the bottom substrate layer is 55% to 70%.

[0009] Secondly, the present invention provides a method for preparing the composite material of the above-mentioned multifunctional integrated UAV take-off and landing platform, comprising the following steps: S1. Prepare the surface functional layer, the intermediate buffer layer and the bottom substrate layer respectively; The preparation of the surface functional layer includes: mixing polyurethane prepolymer, nano-silica, energy storage luminescent material and curing agent to form a pre-formed slurry; and molding the pre-formed slurry according to the structure of a preset surface functional layer to obtain the surface functional layer. The preparation of the intermediate buffer layer includes: placing the core material sublayer between the first skin and the second skin, and holding it under pressure at a temperature of 150℃~250℃ and a pressure of 1.0MPA~3.0MPA for 10min~30min to obtain the intermediate buffer layer; The preparation of the bottom substrate layer includes: alternately stacking multiple layers of basalt fiber layer with polyetheretherketone film or polyphenylene sulfide film, molding at a temperature of 280℃~380℃ and a pressure of 2.0MPA~5.0MPA, holding the pressure for 20min~60min, and obtaining the bottom substrate layer after cooling and demolding; the thickness of the bottom substrate layer is 3mm~10mm. S2. The surface functional layer, the intermediate buffer layer and the bottom substrate layer are stacked in sequence, and the composite material of the multifunctional integrated UAV take-off and landing platform is obtained by hot pressing or adhesive bonding.

[0010] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. The composite material of the multifunctional integrated UAV take-off and landing platform provided by this invention integrates anti-slip, cushioning, light-emitting, and electromagnetic shielding functions into a single composite material structure through a structure in which a surface functional layer, an intermediate buffer layer, and a bottom substrate layer are stacked sequentially. The surface functional layer features polygonal prism-shaped protrusions and interwoven flow channels. The protrusions increase the contact friction during UAV take-off and landing, while the flow channels quickly remove surface moisture, preventing the risk of slippage due to freezing at low temperatures. The inclusion of energy-storing light-emitting material allows the take-off and landing platform to continuously emit light at night or in low-light conditions, providing visual guidance for UAV take-off and landing.

[0011] 2. The composite material of the multifunctional integrated UAV take-off and landing platform provided by the present invention adopts a non-metallic component design as a whole, does not contain ferromagnetic components, and does not interfere with onboard magnetic compasses, GPS and other sensors; at the same time, the non-metallic honeycomb structure has good microwave penetration and dielectric properties, ensuring the quality of communication signals.

[0012] 3. The intermediate buffer layer provided by this invention adopts a honeycomb structure, with the core material sublayer located between the first and second skins, forming an integral structure through hot-pressing. The honeycomb structure absorbs energy through structural deformation upon impact. The first and second skins are made of basalt fiber-reinforced epoxy resin or glass fiber-reinforced epoxy resin, providing excellent mechanical support and impact resistance. This integrated buffer structure replaces traditional external rubber pads or spring assemblies, significantly reducing the thickness and weight of the landing platform, and lowering the areal density by more than 25% compared to aluminum alloys. It also ensures the stability of the buffering effect, exhibits excellent corrosion resistance and fatigue resistance, and is suitable for corrosive environments such as marine salt spray and chemical industrial parks, significantly extending the service life of the landing platform.

[0013] 4. The composite material provided by this invention, through the synergy of nano-silica modified polyurethane and basalt fiber reinforced substrate, has a service temperature range of -40℃ to +70℃, and has both low-temperature toughness and high-temperature stability, meeting the requirements for all-weather deployment.

[0014] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0015] Figure 1 This is an exploded view of the composite material structure of a multifunctional integrated UAV take-off and landing platform provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the surface functional layer structure provided in an embodiment of the present invention; Figure 3 This is a flowchart illustrating the preparation process of a composite material for a multifunctional integrated UAV take-off and landing platform provided in an embodiment of the present invention.

[0016] Explanation of reference numerals in the attached figures: 10-Surface functional layer; 11-Surface liner; 12-Protrusion; 13-Flow channel; 20-Intermediate buffer layer; 30-Bottom substrate layer. Detailed Implementation

[0017] To further illustrate the technical means and effects adopted by the present invention to achieve the intended purpose, the following, in conjunction with the accompanying drawings and specific embodiments, provides a detailed description of the composite material and preparation method of a multifunctional integrated unmanned aerial vehicle (UAV) take-off and landing platform proposed according to the present invention.

[0018] The foregoing and other technical contents, features, and effects of the present invention will be clearly presented in the following detailed description of specific embodiments in conjunction with the accompanying drawings. Through the description of the specific embodiments, a more in-depth and concrete understanding can be gained of the technical means and effects adopted by the present invention to achieve its intended purpose. However, the accompanying drawings are for reference and illustration only and are not intended to limit the technical solutions of the present invention.

[0019] It should be noted that, in this document, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "comprising," "including," or any other variations are intended to cover non-exclusive inclusion, such that an article or apparatus comprising a list of elements includes not only those elements but also other elements not explicitly listed.

[0020] This invention provides a composite material for a multifunctional integrated unmanned aerial vehicle (UAV) take-off and landing platform, such as... Figure 1 and Figure 2 As shown, the structure includes a surface functional layer 10, an intermediate buffer layer 20, and a bottom substrate layer 30, which are stacked sequentially. The surface functional layer 10 includes a surface liner 11 and polygonal prism-shaped protrusions 12 arranged in an array on the surface liner 11. A flow channel 13 is provided on the upper surface of the surface liner 11, and the flow channel 13 are interwoven and connected to form a flow path extending to the edge of the surface liner 11. The surface functional layer 10 includes nano-silica modified polyurethane, an energy-storing luminescent material, and a curing agent; wherein the mass content of the nano-silica modified polyurethane is 70%–85%; the mass content of the curing agent is 10%–25%; the mass content of the energy-storing luminescent material is 5 wt%–15 wt%, and the afterglow time of the energy-storing luminescent material is greater than or equal to 6 hours.

[0021] The intermediate buffer layer 20 includes a core material sublayer, a first skin located above the core material sublayer, and a second skin located below the core material sublayer. The bottom substrate layer 30 is basalt fiber reinforced polyetheretherketone (PEEK) or basalt fiber reinforced polyphenylene sulfide (PPS); wherein the volume fraction of basalt fiber in the bottom substrate layer is 55%–70%. The bottom substrate layer 30 uses basalt fiber reinforced PEEK or basalt fiber reinforced PPS, as basalt fiber has excellent temperature resistance and mechanical properties. Both PEEK and PPS have high temperature resistance and corrosion resistance, and the addition of basalt fiber further enhances the mechanical strength and dimensional stability of the material.

[0022] The composite material of the multifunctional integrated UAV take-off and landing platform provided by this invention integrates anti-slip, cushioning, light-emitting, and electromagnetic shielding functions into a single composite material structure through a structure in which a surface functional layer 10, an intermediate buffer layer 20, and a bottom substrate layer 30 are stacked sequentially. Polygonal prism-shaped protrusions 12 and interwoven flow channels 13 are provided in the surface functional layer 10. The protrusions 12 increase the contact friction during UAV take-off and landing, while the flow channels 13 quickly remove surface moisture, preventing the risk of slippage due to water freezing in low-temperature environments. The inclusion of energy-storing light-emitting material allows the take-off and landing platform to continuously emit light at night or in low-light conditions, providing visual guidance for UAV take-off and landing.

[0023] In this embodiment, the surface polyurethane elastomer, after being modified with nano-silica, has a glass transition temperature below -50℃ and a thermal decomposition temperature above 280℃. The honeycomb core material sublayer, after weather-resistant modification (reinforced with basalt fiber or glass fiber), has a service temperature range of -40℃ to 80℃. The entire material can withstand a wide temperature range of -30℃ to +60℃ and strong ultraviolet radiation, making it suitable for harsh environments such as extreme cold, high temperature, and high humidity. The overall material uses a non-metallic component design, contains no ferromagnetic components, and does not interfere with airborne magnetic compasses, GPS, or other sensors. Simultaneously, the non-metallic honeycomb structure has good microwave penetration and dielectric properties, ensuring communication signal quality.

[0024] In one example, the arrangement of the flow channels 13 can be radial or grid-like, which can quickly drain the interface moisture, avoid the formation of water film, reduce the risk of icing in low-temperature environments, and meet the anti-slip and drainage specifications of the take-off and landing field.

[0025] In one embodiment of the present invention, the protrusion 12 is a quadrangular prism protrusion, a pentagonal prism protrusion, or a hexagonal prism protrusion. The top end face of the protrusion 12 is a circular arc top, a hemispherical top, or an arched arc surface top with continuous curvature. The columnar protrusion structure provided on the surface functional layer 10 provides mechanical locking force in the vertical direction and increases frictional resistance in the horizontal direction, with a friction coefficient ≥0.8 under rain and snow conditions.

[0026] In some examples, the ratio of the height of the protrusion 12 to the depth of the channel 13 is (1 to 1.5):1.

[0027] For example, the height of the protrusion 12 is 0.5 mm to 2.0 mm, and the distance between the central axes of two adjacent protrusions 12 is 1.5 mm to 5.0 mm. The width of the guide groove 13 is 0.3 mm to 1.0 mm, and the depth of the guide groove 13 is 0.4 mm to 1.2 mm.

[0028] In one embodiment of the present invention, a fluorosilane coating is provided on the surface of the surface functional layer 10 away from the bottom substrate layer 30; the contact angle of the fluorosilane coating is greater than or equal to 110°.

[0029] In one embodiment of the present invention, the intermediate buffer layer 20 is a honeycomb structure layer. The core material is made of polypropylene resin or polyphenylene sulfide resin; the first skin and the second skin are made of basalt fiber reinforced epoxy resin, wherein the volume fraction of basalt fiber is 50% to 65%; or the first skin and the second skin are made of glass fiber reinforced epoxy resin, wherein the volume fraction of glass fiber is 50% to 65%. The honeycomb structure of the intermediate buffer layer 20 absorbs impact energy through the elastic buckling and plastic deformation of the honeycomb cell walls, and the buffering efficiency is 30% to 50% higher than that of traditional rubber pad layers. At the same time, it works in conjunction with the basalt fiber reinforced bottom layer to provide sufficient structural strength to withstand normal landing loads (1.5 times the maximum takeoff weight) and emergency landing loads (2 times the maximum takeoff weight), achieving integrated buffering between the panel and the substrate without the need for additional buffer components.

[0030] The present invention also provides a method for preparing the composite material of the above-mentioned multifunctional integrated UAV take-off and landing platform, see below. Figure 3 This includes the following steps: S1. Prepare the surface functional layer 10, the intermediate buffer layer 20 and the bottom substrate layer 30 respectively.

[0031] The preparation of the surface functional layer 10 includes: mixing polyurethane prepolymer, nano-silica, energy-storing luminescent material and curing agent to form a pre-formed slurry; and molding the pre-formed slurry according to the predetermined structure of the surface functional layer to obtain the surface functional layer 10. The mass ratio of polyurethane prepolymer to nano-silica is 100:(3-8).

[0032] The preparation of the intermediate buffer layer 20 includes: placing the core material sublayer between the first skin and the second skin, and holding it under pressure for 10 min to 30 min at a temperature of 150℃ to 250℃ and a pressure of 1.0 MPa to 3.0 MPa to obtain the intermediate buffer layer 20.

[0033] The preparation of the bottom substrate layer 30 includes: alternately stacking multiple layers of basalt fiber layer with polyether ether ketone film or polyphenylene sulfide film, molding at a temperature of 280℃~380℃ and a pressure of 2.0MPA~5.0MPA, holding the pressure for 20min~60min, and obtaining the bottom substrate layer 30 after cooling and demolding; the thickness of the bottom substrate layer 30 is 3mm~10mm.

[0034] In one example, the process further includes spraying fluorosilane onto the surface of the surface functional layer 10 on the side away from the bottom substrate layer 30, and heat-treating it at a temperature of 80°C to 120°C for 30 to 60 minutes to obtain a fluorosilane coating.

[0035] S2. The surface functional layer 10, the intermediate buffer layer 20 and the bottom substrate layer 30 are stacked in sequence, and the composite material of the multifunctional integrated UAV take-off and landing platform is obtained by hot pressing or adhesive bonding.

[0036] For example, hot-pressing lamination is performed at a temperature of 150℃~250℃ and a pressure of 0.5MPA~2.0MPA for 5min~15min.

[0037] The following detailed description, in conjunction with specific embodiments, further illustrates the composite material and its preparation method for the multifunctional integrated UAV take-off and landing platform provided by the present invention.

[0038] Example 1 This embodiment provides a method for preparing composite materials for a multifunctional integrated UAV take-off and landing platform. The specific preparation process parameters are as follows.

[0039] Step 1: Prepare the surface functional layer, the intermediate buffer layer 20 and the bottom substrate layer.

[0040] Preparation of surface functional layer: (1) 70wt% nano silica modified polyurethane elastomer, 20wt% curing agent and 10wt% energy storage light-emitting material are mixed to obtain pre-slurry; wherein, the mass ratio of polyurethane prepolymer to nano silica is 100:5.

[0041] (2) A surface functional layer with a pre-defined structure is prepared by casting using a mold; the structural parameters of the surface functional layer are: the height of the hexagonal prism protrusion is 1.0 mm and the central axis spacing is 3.0 mm; the flow guiding microchannels on the surface of the surface liner are arranged in a mesh pattern, with a width of 0.5 mm and a depth of 0.6 mm.

[0042] (3) Spray fluorosilane onto the surface of the surface functional layer and heat treat it at 100°C for 45 minutes to form a fluorosilane coating.

[0043] Preparation of intermediate buffer layer 20: Polypropylene (PP) honeycomb core material as core sublayer (density 80 kg / m³) 3(The cell side length is 5mm). The first and second skins are basalt fiber-epoxy resin prepregs with a basalt fiber volume fraction of 60%. They are hot-pressed together at a temperature of 180℃ and a pressure of 2.0MPA for 20 minutes.

[0044] Preparation of the bottom substrate layer: Basalt fiber plain weave fabric and polyether ether ketone film (PEEK) are alternately laminated, wherein the volume fraction of basalt fiber is 65%; molding is performed at a temperature of 360℃ and a pressure of 3.5MPA, and the pressure is held for 40min to form a bottom substrate layer with a thickness of 5mm.

[0045] Step 2, Overall Composite: The surface functional layer, the intermediate buffer layer 20 and the bottom substrate layer are stacked in sequence and hot-pressed for 10 minutes at a hot-pressing temperature of 150℃ and a pressure of 1.0MPA to obtain a composite material for a multifunctional integrated UAV take-off and landing platform.

[0046] The composite material of the multifunctional integrated UAV take-off and landing platform prepared in Example 1 is defined as composite material 1. The performance of composite material 1 was tested, and the results are shown in Table 1.

[0047] Table 1. Performance test results of composite material 1

[0048] Example 2 This embodiment provides a method for preparing composite materials for a multifunctional integrated UAV take-off and landing platform. The specific preparation process parameters are as follows.

[0049] Step 1: Prepare the surface functional layer, the intermediate buffer layer and the bottom substrate layer.

[0050] Preparation of surface functional layer: (1) 78wt% nano silica modified polyurethane elastomer, 14wt% curing agent and 8wt% energy storage light-emitting material are mixed to obtain pre-slurry; wherein, the mass ratio of polyurethane prepolymer to nano silica is 100:5.

[0051] (2) A surface functional layer with a pre-defined structure is prepared by casting using a mold; the structural parameters of the surface functional layer are: the height of the hexagonal prism protrusion is 1.0 mm and the central axis spacing is 3.0 mm; the flow guiding microchannels on the surface of the surface liner are arranged radially, with a width of 0.6 mm and a depth of 0.8 mm, which increases the drainage rate by 30%.

[0052] (3) Spray fluorosilane onto the surface of the functional layer and heat-treat it at 100°C for 50 minutes to form a fluorosilane coating.

[0053] Preparation of intermediate buffer layer: Polyphenylene sulfide (PPS) honeycomb core material as core sublayer (density 80 kg / m³) 3(The cell side length is 5mm). The first and second skins are basalt fiber-epoxy resin prepregs with a basalt fiber volume fraction of 60%. They are hot-pressed at a temperature of 180℃ and a pressure of 2.0MPA for 30 minutes.

[0054] Preparation of the bottom substrate layer: Basalt fiber plain weave fabric and polyether ether ketone film (PEEK) are alternately laminated, wherein the volume fraction of basalt fiber is 65%; molding is performed at a temperature of 360℃ and a pressure of 3.5MPA, and the pressure is held for 40min to form a bottom substrate layer with a thickness of 5mm.

[0055] Step 2, Overall Composite: The surface functional layer, the intermediate buffer layer and the bottom substrate layer are stacked in sequence and hot-pressed at a temperature of 180℃ and a pressure of 1.2MPA for 12 minutes to obtain a composite material for a multifunctional integrated UAV take-off and landing platform.

[0056] The composite material of the multifunctional integrated UAV take-off and landing platform prepared in Example 2 is defined as composite material 2. The performance of composite material 2 was tested, and the results are shown in Table 2.

[0057] Table 2. Performance test results of composite material 2

[0058] Comparative Example A commercially available aluminum alloy lifting platform was compared with that of Embodiment 1 of the present invention. The performance parameters of the aluminum alloy lifting platform are shown in Table 3.

[0059] Table 3. Comparative Performance Test Results

[0060] Based on the results in Tables 1-3, both composite material 1 and composite material 2, as composite materials for UAV take-off and landing platforms, exhibit performance superior to or at least not inferior to existing commercially available aluminum alloy take-off and landing platform materials.

[0061] Specifically, in terms of friction performance, composite material 1 has a dry friction coefficient of 1.12 and a wet friction coefficient of 0.85, composite material 2 has a dry friction coefficient of 1.25 and a wet friction coefficient of 0.93, while the comparative aluminum alloy material has a dry friction coefficient of only 0.68 and a wet friction coefficient of only 0.45. This demonstrates that both composite materials exhibit higher surface friction coefficients in both dry and wet conditions, significantly improving the anti-slip performance of the UAV landing platform surface and enhancing the adhesion between the UAV landing gear and the platform surface. Especially in wet environments, they maintain relatively stable friction performance, thereby reducing the risk of slippage or deviation during UAV takeoff, landing, or taxiing, and improving takeoff and landing safety and platform environmental adaptability.

[0062] In terms of impact absorption performance, composite material 1 shows a 42% increase in impact absorption energy compared to traditional rubber pads, and composite material 2 shows a 55% increase compared to traditional rubber pads, while the comparative example only shows an impact absorption energy greater than or equal to 50 joules. The composite materials provided in this embodiment of the invention, through structural design or synergistic effects of components, exhibit superior buffering and energy absorption effects. They can effectively absorb the impact loads and vibration energy during UAV landing, reducing repeated impact damage to the UAV body, landing gear, and platform structure, thus improving the service life of the landing platform and enhancing the landing stability of the UAV.

[0063] Regarding temperature adaptability, composite material 1 has an applicable temperature range of -35℃ to 65℃, composite material 2 has a range of -40℃ to 70℃, while the comparative aluminum alloy material can cover -30℃ to 60℃. The examples provide a wider temperature range, further expanding the environmental adaptability. For typical outdoor, shipboard, or near-shore applications, this temperature range is practically feasible. Furthermore, the composite materials also offer comprehensive advantages in terms of friction resistance, energy absorption, and lightweighting.

[0064] In terms of areal density, both composite material 1 and composite material 2 have an areal density of 8.5 kg / m³. 2 It also reduces the surface density by 25% compared to aluminum alloys of equivalent strength; while the surface density of the comparative aluminum alloy material is 11.9 kg / m³. 2 This indicates that the composite material provided by the present invention has a significant lightweighting effect while achieving or maintaining the corresponding structural strength.

[0065] Regarding magnetic permeability, composite material 1, composite material 2, and the comparative material all have a permeability of 1.0, exhibiting characteristics of no magnetic interference. The composite material provided by this invention has a magnetic permeability close to 1.0, which can avoid or significantly reduce the risk of magnetic interference, thereby ensuring the magnetic sensing accuracy and flight safety during UAV take-off, landing, hovering, and navigation.

[0066] The composite material provided by this invention significantly outperforms the comparative example in terms of wet-state anti-slip properties, wide-temperature stability, electromagnetic compatibility, and cushioning efficiency. Compared to commercially available aluminum alloy landing platform materials, its overall comprehensive performance is superior.

[0067] In the description of this invention, it should be understood that the terms "height," "depth," "width," "upper," "lower," "top," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention 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 this invention.

[0068] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. In addition, those skilled in the art can combine and integrate the different embodiments or examples described in this specification.

[0069] The above description, in conjunction with specific preferred embodiments, provides a further detailed explanation of the present invention. It should not be construed that the specific implementation of the present invention is limited to these descriptions. For those skilled in the art, various simple deductions or substitutions can be made without departing from the concept of the present invention, and all such modifications and substitutions should be considered within the scope of protection of the present invention.

Claims

1. A composite material for a multifunctional integrated unmanned aerial vehicle (UAV) take-off and landing platform, characterized in that, It includes a surface functional layer, an intermediate buffer layer and a bottom substrate layer stacked in sequence; The surface functional layer includes a surface liner and an array of polygonal prism-shaped protrusions arranged on the surface liner; A flow guide groove is provided on the upper surface of the surface liner. The flow guide grooves are interwoven and connected to form a flow guide path extending to the edge of the surface liner. The surface functional layer comprises nano-silica modified polyurethane, energy-storing luminescent material, and curing agent; wherein, the mass content of nano-silica modified polyurethane is 70% to 85%; the mass content of the curing agent is 10% to 25%; the mass content of the energy-storing luminescent material is 5% to 15%, and the afterglow time of the energy-storing luminescent material is greater than or equal to 6 hours. The intermediate buffer layer includes a core material sublayer, a first skin located on the upper side of the core material sublayer, and a second skin located on the lower side of the core material sublayer; The bottom substrate layer is basalt fiber reinforced polyether ether ketone or basalt fiber reinforced polyphenylene sulfide; wherein the volume fraction of basalt fiber in the bottom substrate layer is 55% to 70%.

2. The composite material of the multifunctional integrated UAV take-off and landing platform according to claim 1, characterized in that, The protrusion is a quadrangular prism protrusion, a pentagonal prism protrusion, or a hexagonal prism protrusion; The top end face of the protrusion is a circular arc top, a hemispherical top, or an arched arc surface with continuous curvature.

3. The composite material of the multifunctional integrated UAV take-off and landing platform according to claim 1 or 2, characterized in that, The ratio of the height of the protrusion to the depth of the guide groove is (1~1.5):

1.

4. The composite material of the multifunctional integrated UAV take-off and landing platform according to claim 3, characterized in that, The height of the protrusion is 0.5 mm to 2.0 mm, and the distance between the central axes of two adjacent protrusions is 1.5 mm to 5.0 mm. The width of the guide channel is 0.3 mm to 1.0 mm, and the depth of the guide channel is 0.4 mm to 1.2 mm.

5. The composite material of the multifunctional integrated UAV take-off and landing platform according to claim 1, characterized in that, A fluorosilane coating is provided on the surface of the surface functional layer on the side away from the bottom substrate layer; The contact angle of the fluorosilane coating is greater than or equal to 110°.

6. The composite material of the multifunctional integrated UAV take-off and landing platform according to claim 1, characterized in that, The intermediate buffer layer is a honeycomb structure layer; The core material sublayer is made of polypropylene resin or polyphenylene sulfide resin. The first skin and the second skin are made of basalt fiber reinforced epoxy resin, wherein the volume fraction of basalt fiber is 50% to 65%. Alternatively, the materials for the first skin and the second skin may be glass fiber reinforced epoxy resin, wherein the volume fraction of glass fiber is 50% to 65%.

7. A method for preparing the composite material of the multifunctional integrated UAV take-off and landing platform according to claim 1, characterized in that, Includes the following steps: S1. Prepare the surface functional layer, the intermediate buffer layer and the bottom substrate layer respectively; The preparation of the surface functional layer includes: mixing polyurethane prepolymer, nano-silica, energy storage luminescent material and curing agent to form a pre-formed slurry; and molding the pre-formed slurry according to the structure of a preset surface functional layer to obtain the surface functional layer. The preparation of the intermediate buffer layer includes: placing the core material sublayer between the first skin and the second skin, and holding it under pressure at a temperature of 150℃~250℃ and a pressure of 1.0MPA~3.0MPA for 10min~30min to obtain the intermediate buffer layer; The preparation of the bottom substrate layer includes: alternately stacking multiple layers of basalt fiber layer with polyetheretherketone film or polyphenylene sulfide film, molding at a temperature of 280℃~380℃ and a pressure of 2.0MPA~5.0MPA, holding the pressure for 20min~60min, and obtaining the bottom substrate layer after cooling and demolding; the thickness of the bottom substrate layer is 3mm~10mm. S2. The surface functional layer, the intermediate buffer layer and the bottom substrate layer are stacked in sequence, and the composite material of the multifunctional integrated UAV take-off and landing platform is obtained by hot pressing or adhesive bonding.

8. The method for preparing the composite material of the multifunctional integrated UAV take-off and landing platform according to claim 7, characterized in that, In the pre-formed slurry, the mass ratio of the polyurethane prepolymer to the nano-silica is 100:(3-8).

9. The method for preparing the composite material of the multifunctional integrated UAV take-off and landing platform according to claim 7, characterized in that, Step S1 further includes spraying fluorosilane onto the surface of the surface functional layer on the side away from the bottom substrate layer, and heat-treating it at a temperature of 80°C to 120°C for 30 min to 60 min to obtain a fluorosilane coating.

10. The method for preparing the composite material of the multifunctional integrated UAV take-off and landing platform according to claim 7, characterized in that, In step S2, the hot-pressing composite is performed at a temperature of 150℃~250℃ and a pressure of 0.5MPA~2.0MPA for 5 min~15 min.

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