Device for generating and storing energy based on carbon nanotubes and method for manufacturing same

Abstract

This invention discloses a device and preparation method for generating and storing energy based on carbon nanotubes, relating to the field of biomimetic aircraft technology, including wing-borne functional components and airborne main components; the wing-borne functional components include a nano-power generation module and a flexible energy storage module stacked inside a flexible biomimetic wing; the nano-power generation module includes a negatively charged triboelectric layer and a carbon nanotube thin film electrode; the flexible energy storage module includes a carbon nanotube fiber skeleton and a gel electrolyte layer; the airborne main components include a biomimetic main module, an energy management module, and a sensor module; this invention integrates the nano-power generation module and the flexible energy storage module into the flapping wing, realizing in-situ acquisition and storage of mechanical energy, solving the problems of traditional biomimetic flapping wing aircraft relying on the main power supply of the fuselage for limited endurance, difficulty in achieving self-powering, and difficulty in environmental perception.

Description

Technical Field

[0001] This invention relates to the field of biomimetic aircraft technology, and in particular to a device and preparation method for generating and storing energy based on carbon nanotubes. Background Technology

[0002] Bionic flapping-wing aircraft, mimicking the flight patterns of birds or insects, possess broad application prospects in fields such as environmental monitoring, search and rescue, and military reconnaissance due to their advantages of small size, high maneuverability, and good stealth. However, flapping-wing aircraft generally face bottlenecks in energy supply: on the one hand, their size and weight are limited, and the energy density of traditional chemical batteries is insufficient to meet the needs of long-endurance flight; on the other hand, the wings continuously perform high-frequency reciprocating motions during flapping flight, containing abundant mechanical energy, but current technologies have failed to effectively recover and utilize this energy, resulting in a significant waste of energy.

[0003] To extend the endurance of flapping-wing aircraft, some studies have attempted to equip them with solar cells or vibration energy harvesting devices. However, solar cells are severely limited by lighting conditions, while traditional electromagnetic or piezoelectric energy harvesters are bulky and their rigid structures are difficult to conformally integrate with flexible wings, increasing flight overhead and affecting aerodynamic performance. Furthermore, most existing flapping-wing aircraft lack the ability to collect environmental information in situ; adding sensors would further exacerbate energy consumption and hinder long-term autonomous monitoring.

[0004] In recent years, carbon nanotube materials have shown great potential in the fields of flexible electronics and energy harvesting due to their excellent electrical conductivity, flexibility, and mechanical properties, as well as their lightweight characteristics. However, there is currently no technical solution that integrates carbon nanotube-based power generation and energy storage modules into the interior of flapping wings to achieve self-powering and environmental sensing for aircraft.

[0005] In summary, there is an urgent need to develop a biomimetic flapping-wing aircraft that can efficiently convert the mechanical energy of flapping wing motion into electrical energy and store it in situ, while also having environmental information collection capabilities, in order to overcome energy limitations and achieve long-endurance, self-powered flight operations. Summary of the Invention

[0006] This invention provides a device and preparation method for generating and storing energy based on carbon nanotubes, in order to solve the problems of traditional biomimetic flapping-wing aircraft relying on the main power supply of the fuselage for limited endurance and difficulty in achieving self-powering and environmental perception.

[0007] To solve the above-mentioned technical problems, the present invention is implemented as follows: This invention provides a device and preparation method for generating and storing energy based on carbon nanotubes, used for self-powering and collecting environmental information in a biomimetic flapping-wing aircraft, including a wing-borne functional component and an airborne main body component; the wing-borne functional component is movably connected to the airborne main body component.

[0008] The wing-borne functional components include a nano-power generation module, a flexible energy storage module, and a packaging module; the airborne main body components include a biomimetic main body module, an energy management module, and a sensor module; the nano-power generation module includes a negatively charged triboelectric layer and a carbon nanotube thin film electrode; the flexible energy storage module includes a carbon nanotube fiber skeleton, a gel electrolyte layer, and an electrode isolation layer; the packaging module includes an insulating isolation layer and a waterproof packaging layer; the biomimetic main body module includes a biomimetic fuselage main body, flexible biomimetic wings, a flapping wing drive mechanism, a flight control system, and a fuselage main power supply; the energy management module includes flexible connecting wires, a bridge rectifier circuit, a voltage limiting unit, a voltage regulating unit, and a charge / discharge controller; the sensor module includes an environmental sensor group, a wireless communication module, and an interface communication module.

[0009] The nano-power generation module and the flexible energy storage module are electrically connected and disposed inside the flexible bionic wing. The flexible energy storage module stores the electrical energy generated by the flapping of the wing or the blowing of the wind. The energy management module is electrically connected to the flexible energy storage module through the flexible connecting wire. The energy management module is used to rectify, limit, stabilize, and control the charging and discharging of the electrical energy and store it in the main power supply of the fuselage. The flapping wing drive mechanism, the flight control system, and the sensor module are powered by the main power supply of the fuselage.

[0010] At least one side of the negatively charged friction layer has a nanoscale uneven structure to increase the friction contact area; the carbon nanotube thin film electrode is a three-dimensional conductive network structure composed of carbon nanotubes.

[0011] The nano-power generation module adopts the principle of triboelectric nano-power generation. When the wings flap or are blown by the wind, the contact and separation between the negatively charged triboelectric layer and the carbon nanotube thin film electrode drives the flow of electrons to form an electric current, thereby realizing the conversion of mechanical energy into electrical energy.

[0012] The carbon nanotube fiber skeleton is a three-dimensional porous structure composed of carbon nanotube fibers, the gel electrolyte layer is a polymer-based gel electrolyte, and the electrode isolation layer is a porous polymer membrane.

[0013] The three-dimensional porous structure of the carbon nanotube fiber skeleton provides a huge specific surface area and excellent conductivity; the electrode isolation layer separates the positive and negative electrode regions to prevent short circuits; during charging and discharging, ions in the polymer-based gel electrolyte migrate rapidly within the three-dimensional porous network, forming an electric double layer or undergoing a reversible reaction on the electrode surface, thereby realizing the storage and release of electrical energy.

[0014] The insulating isolation layer is disposed between the nano-power generation module and the flexible energy storage module to achieve electrical isolation between the two; the nano-power generation module, the insulating isolation layer, and the flexible energy storage module are stacked in sequence to form a sandwich structure; the sandwich structure can deform accordingly with the flexible deformation of the flexible bionic wing to achieve mechanical energy to electrical energy conversion and in-situ storage when the wing flaps or is blown by the wind; the waterproof encapsulation layer completely covers the nano-power generation module and the flexible energy storage module, and forms an integral structure with the outer surface of the flexible bionic wing.

[0015] The bionic fuselage body is a hollow shell structure, with an internal mounting cavity for accommodating the energy management module and the sensor module; the flexible bionic wings include a wing skeleton and a wing membrane; the flapping wing drive mechanism is electrically connected to the flight control system, and its flapping frequency and amplitude are controlled by the flight control system.

[0016] When the flexible bionic wing (212) is in a non-flapping state, the nano-power generation module (11) continues to generate electricity through friction under the action of wind, and charges the flexible energy storage module (12) to achieve continuous power supply.

[0017] The flexible connecting wire is connected between the flexible bionic wing and the bionic fuselage body to realize the electrical connection between the wing-borne functional component and the airborne body component; the input terminal of the bridge rectifier circuit is electrically connected to the flexible energy storage module; the bridge rectifier circuit, the voltage limiting unit, the voltage regulating unit, and the charge / discharge controller are connected in series; the charge / discharge controller includes an overcharge protection circuit and an over-discharge protection circuit, which are used to cut off charging when the voltage of the fuselage main power supply exceeds the upper limit threshold, or to cut off discharging when it is below the lower limit threshold.

[0018] The environmental sensor group is electrically connected to the flight control system and is used to transmit the collected environmental information to the wireless communication module and the interface communication module; the environmental sensor group includes at least one of a temperature sensor, a humidity sensor and a barometric pressure sensor.

[0019] The wing-borne functional component is connected to the airborne main body component through the flexible connecting wire and the flexible hinge structure; the flexible hinge structure is a hollow structure with an average density lower than that of the bionic fuselage main body.

[0020] The preparation method includes the following steps: S1: Carbon nanotubes are prepared by floating catalyst chemical vapor deposition. The obtained carbon nanotubes are dispersed in a solvent, and a carbon nanotube film is obtained by film formation treatment. The film is then pressed and formed to form the carbon nanotube film electrode. S2: A nanoscale uneven structure is formed on the surface of the negatively charged tribological layer material using a template method, and then combined with the carbon nanotube thin film electrode to form the nano-power generation module; S3: Carbon nanotube aerogel prepared by floating catalyst chemical vapor deposition is used to form carbon nanotube fibers in a water bath and then woven to form a three-dimensional porous carbon nanotube fiber skeleton. A gel electrolyte is injected to form the gel electrolyte layer, and the electrode isolation layer is combined to form the flexible energy storage module. S4: The nano-power generation module, the insulating isolation layer, and the flexible energy storage module are stacked in sequence and the waterproof encapsulation layer is completely covered to form a sandwich structure; the sandwich structure is embedded inside the flexible bionic wing, and the sandwich structure is conformally solidified with the flexible bionic wing through a hot pressing process; S5: Electrically connect the sandwich structure to the airborne main body component via a flexible connecting wire.

[0021] In this invention, the nano-power generation module deforms with flapping wing movement and airflow disturbance, converting mechanical energy into electrical energy, effectively capturing low-quality mechanical energy that is difficult to recover. A three-dimensional porous framework composed of carbon nanotube fibers forms continuous electron transport channels, and a gel electrolyte layer fills the pores of the framework, enabling rapid ion migration and charging / discharging. This gives the flexible energy storage module excellent flexibility and deformation adaptability, allowing it to be repeatedly bent with wing flapping without affecting its energy storage performance. The flexible energy storage module and the nano-power generation module are stacked and electrically connected, embedded within the flexible biomimetic wing in a sandwich structure, deforming synchronously with wing flapping, achieving integrated power generation and energy storage, avoiding additional aerodynamic burden on the aircraft. An environmental sensor array allows real-time collection of environmental information such as temperature, humidity, and air pressure to be transmitted via a wireless communication module, facilitating environmental awareness and data feedback during flight. This invention solves the technical problems of existing flapping-wing aircraft, including limited energy, short endurance, difficulty in self-powering, and lack of environmental awareness capabilities. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 A schematic diagram showing the connection relationship of the carbon nanotube-based power generation and energy storage device provided in the embodiments of the present invention; Figure 2 This is a schematic diagram illustrating the structure of the carbon nanotube-based power generation and energy storage device provided in an embodiment of the present invention. Figure 3 This is a schematic diagram showing the structure of the flexible biomimetic wings and wing-borne functional components in the carbon nanotube-based power generation and energy storage device provided in the embodiments of the present invention. Explanation of reference numerals in the attached figures: 10. Wing-borne functional components; 11. Nano-power generation module; 12. Flexible energy storage module; 13. Encapsulation module; 20. Airborne main body components; 21. Bionic main body module; 22. Energy management module; 23. Sensor module; 111. Negatively charged triboelectric layer; 112. Carbon nanotube thin film electrode; 121. Carbon nanotube fiber skeleton; 122. Gel electrolyte layer; 123. Electrode isolation layer; 131. Insulating isolation layer; 132. Waterproof encapsulation layer; 211. Bionic fuselage main body; 212. Flexible bionic wings; 213. Flapping wing drive mechanism; 214. Flight control system; 215. Main power supply of fuselage; 221. Flexible connecting wire; 222. Bridge rectifier circuit; 223. Voltage limiting unit; 224. Voltage regulating unit; 225. Charge and discharge controller; 231. Environmental sensor group; 232. Wireless communication module; 233. Interface communication module. Detailed Implementation

[0024] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] It should be understood that the phrase "one embodiment" or "an embodiment" throughout the specification means that a specific feature, structure, or characteristic related to the embodiment is included in at least one embodiment of the invention. Therefore, "in one embodiment" or "in an embodiment" appearing throughout the specification do not necessarily refer to the same embodiment. Furthermore, these specific features, structures, or characteristics can be combined in any suitable manner in one or more embodiments.

[0026] See Figures 1 to 3 The present invention provides a device and preparation method for generating and storing energy based on carbon nanotubes, which is used for self-powering and collecting environmental information of a biomimetic flapping-wing aircraft, including a wing-borne functional component (10) and an airborne main body component (20); the wing-borne functional component (10) and the airborne main body component (20) are movably connected.

[0027] The wing-borne functional component (10) includes a nano-power generation module (11), a flexible energy storage module (12), and a packaging module (13); the airborne main component (20) includes a biomimetic main module (21), an energy management module (22), and a sensor module (23); the nano-power generation module (11) includes a negatively charged triboelectric layer (111) and a carbon nanotube thin film electrode (112); the flexible energy storage module (12) includes a carbon nanotube fiber skeleton (121), a gel electrolyte layer (122), and an electrode isolation layer (123); the packaging module (13) includes an insulating isolation layer (131) and a protective layer. Water encapsulation layer (132); the bionic main body module (21) includes a bionic fuselage main body (211), flexible bionic wings (212), flapping wing drive mechanism (213), flight control system (214) and fuselage main power supply (215); the energy management module (22) includes flexible connecting wires (221), bridge rectifier circuit (222), voltage limiting unit (223), voltage regulating unit (224) and charge / discharge controller (225); the sensor module (23) includes an environmental sensor group (231), wireless communication module (232) and interface communication module (233).

[0028] In this embodiment of the invention, the nano-power generation module (11) and the flexible energy storage module (12) are electrically connected and disposed inside the flexible bionic wing (212) to store the electrical energy generated by the flapping of the wing or the blowing of the wind in the flexible energy storage module (12); the energy management module (22) is electrically connected to the flexible energy storage module (12) through the flexible connecting wire (221) to rectify, limit, stabilize and charge / discharge the electrical energy and store it in the fuselage main power supply (215); the flapping wing drive mechanism (213), the flight control system (214) and the sensor module (23) are powered by the fuselage main power supply (215).

[0029] It should be noted that the electrical energy flows along the following path: the electrical energy generated by the nano-power generation module (11) is first directly stored in the flexible energy storage module (12). The three-dimensional porous structure formed by the carbon nanotube fiber skeleton (121) and the gel electrolyte layer (122) enables the flexible energy storage module (12) to have certain voltage stabilization characteristics and perform preliminary voltage smoothing on the input electrical energy. Subsequently, the electrical energy is transmitted to the energy management module (22) through the flexible connecting wire (221) for rectification, voltage limiting, voltage stabilization and charge / discharge control. Finally, the processed electrical energy is stored in the main power supply of the fuselage (215).

[0030] The negatively charged friction layer (111) has a nanoscale uneven structure on at least one side surface to increase the friction contact area; the carbon nanotube thin film electrode (112) is a three-dimensional conductive network structure composed of carbon nanotubes.

[0031] Preferably, the negatively charged tribological layer (111) is selected from at least one of polyimide and polytetrafluoroethylene, and the characteristic size of the uneven structure is 50~500 nm.

[0032] Preferably, the carbon nanotube thin film electrode (112) has a thickness of 0.1~10 μm, a surface density of 0.5~2 mg / cm², and a sheet resistance of less than 10 Ω / sq.

[0033] The carbon nanotube fiber skeleton (121) is a three-dimensional porous structure composed of carbon nanotube fibers, the gel electrolyte layer (122) is a polymer-based gel electrolyte, and the electrode isolation layer (123) is a porous polymer membrane.

[0034] Preferably, the carbon nanotube fiber skeleton (121) has a porosity of 60%~90%, a fiber diameter of 10~50 nm, and a pore size of 1~50 μm.

[0035] Preferably, the matrix of the polymer-based gel electrolyte is selected from at least one of polyvinylidene fluoride-hexafluoropropylene copolymer, polymethyl methacrylate, and polyethylene oxide. The matrix has good ionic conductivity, flexibility, and interfacial compatibility, and can be combined with the carbon nanotube fiber skeleton (121) to form a stable flexible energy storage module (12), which can be repeatedly bent with the flapping of the wings without affecting the energy storage performance; the thickness of the gel electrolyte layer (122) is 10~100 μm, and the ionic conductivity is 10⁻ 4 ~10⁻² S / cm.

[0036] Preferably, the electrode insulating layer (123) is selected from at least one of polypropylene, polyethylene and polyimide, with a thickness of 10~50 μm, a uniformly distributed microporous structure, a pore size of 0.01~1 μm, and a porosity of 40%~70%.

[0037] The insulating isolation layer (131) is disposed between the nano-power generation module (11) and the flexible energy storage module (12) to achieve electrical isolation between the two; the nano-power generation module (11), the insulating isolation layer (131), and the flexible energy storage module (12) are stacked in sequence to form a sandwich structure; the sandwich structure can deform accordingly with the flexible deformation of the flexible bionic wing (212) to achieve mechanical energy-electric energy conversion and in-situ storage when the wing flaps or the wind blows the wing; the waterproof encapsulation layer (132) completely covers the nano-power generation module (11) and the flexible energy storage module (12), and forms an integral structure with the outer surface of the flexible bionic wing (212).

[0038] Preferably, the insulating layer (131) is selected from at least one of polyimide and polyethylene terephthalate, and has a thickness of 5 to 20 μm; the waterproof encapsulation layer (132) is selected from at least one of polyurethane and polydimethylsiloxane, and has a thickness of 10 to 50 μm, and is coated by spraying or impregnation.

[0039] The bionic fuselage body (211) is a hollow shell structure, and its interior is provided with an installation cavity for accommodating the energy management module (22) and the sensor module (23); the flexible bionic wing (212) includes a wing skeleton and a wing membrane; the flapping wing drive mechanism (213) is electrically connected to the flight control system (214), and its flapping frequency and flapping amplitude are controlled by the flight control system (214).

[0040] In this embodiment of the invention, the biomimetic main body module (21) is designed based on a biomimetic butterfly, the biomimetic fuselage (211) adopts a butterfly-shaped structure, and the flexible biomimetic wings (212) simulate the shape and flexibility of butterfly wings to achieve efficient flapping flight. In other embodiments, the biomimetic main body module (21) can also be designed based on biomimetic birds or biomimetic dragonflies to adapt to different flight mission requirements.

[0041] Preferably, the flapping wing drive mechanism (213) adopts a micro servo motor with a flapping amplitude of 30°~100°.

[0042] Preferably, when the power of the main power supply (215) is lower than the flight safety threshold, the flight control system (214) controls the flapping wing drive mechanism (213) to adjust the flapping frequency and amplitude, so that the bionic aircraft decelerates, descends and lands smoothly on the ground or the predetermined landing position, avoiding loss of control and crash due to power depletion; the flight safety threshold is set to 10% of the rated capacity of the main power supply (215).

[0043] Preferably, a pair of takeoff brackets are fixedly installed at the bottom of the bionic fuselage body (211). The takeoff brackets adopt a lightweight hollow structure and are used to support the aircraft to maintain a preset takeoff attitude before takeoff.

[0044] The flexible connecting wire (221) is connected between the flexible bionic wing (212) and the bionic fuselage body (211) to realize the electrical connection between the wing-borne functional component (10) and the airborne main body component (20); the input end of the bridge rectifier circuit (222) is electrically connected to the flexible energy storage module (12); the bridge rectifier circuit (222), the voltage limiting unit (223), the voltage regulating unit (224) and the charge and discharge controller (225) are connected in series in sequence; the charge and discharge controller (225) includes an overcharge protection circuit and an over-discharge protection circuit, which are used to cut off charging when the voltage of the fuselage main power supply (215) exceeds the upper limit threshold, or cut off discharging when it is below the lower limit threshold.

[0045] Preferably, the main power supply (215) of the fuselage uses a lithium polymer battery with a nominal voltage of 3.7 V, a full charge voltage of 4.2 V, and a discharge cutoff voltage of 3.0 V. The upper limit threshold of the overcharge protection circuit is set to 4.2 V ± 0.05 V. When the voltage of the main power supply (215) of the fuselage reaches this threshold, the charge and discharge controller (225) cuts off the charging circuit to prevent overcharging. The lower limit threshold of the over-discharge protection circuit is set to 3.0 V ± 0.05 V. When the voltage of the main power supply (215) of the fuselage is lower than this threshold, the charge and discharge controller (225) cuts off the discharge circuit to prevent over-discharge, thereby protecting battery life and flight safety.

[0046] The environmental sensor group (231) is electrically connected to the flight control system (214) and is used to transmit the collected environmental information to the wireless communication module (232) and the interface communication module (233); the environmental sensor group (231) includes at least one of a temperature sensor, a humidity sensor and a barometric pressure sensor.

[0047] Preferably, the wireless communication module (232) adopts at least one of Bluetooth, ZigBee and LoRa communication protocols, operates at a frequency of 2.4 GHz, and is used to transmit the data collected by the environmental sensor group (231) to the ground station or mobile terminal in real time.

[0048] Preferably, the interface communication module (233) includes at least one of a USB interface, a serial interface and an I²C interface, for exchanging data or burning programs with external devices.

[0049] The wing-borne functional component (10) is connected to the airborne main body component (20) through the flexible connecting wire (221) and the flexible hinge structure; the flexible hinge structure is a hollow structure, and its average density is lower than that of the bionic fuselage main body (211).

[0050] Preferably, the flexible hinge structure is made of at least one of polyimide and polydimethylsiloxane, and is formed by 3D printing. The porosity of the hollow structure is 30% to 60%, and the thickness is 0.1 to 0.5 mm, so as to ensure good flexibility and fatigue life during repeated flapping.

[0051] The preparation method includes the following steps: S1: Carbon nanotubes are prepared by floating catalyst chemical vapor deposition. The obtained carbon nanotubes are dispersed in a solvent and then subjected to film formation treatment to obtain a carbon nanotube film. The film is then pressed and formed to form the carbon nanotube film electrode (112). Preferably, in step S1, the reaction temperature of the floating catalyst chemical vapor deposition method is 1100~1250 ℃, the reaction time is 30~60 min, the carbon source is selected from ethanol, the catalyst is selected from ferrocene, the co-catalyst is selected from thiophene, the thiophene concentration is 0.5~8 wt%, the hydrogen flow rate is 400~1200 sccm, and the argon flow rate is 200~1000 sccm; the obtained carbon nanotubes are dispersed in N-methylpyrrolidone or dimethylformamide, ultrasonically dispersed for 30~60 min, coated into a film by scraping, and then pressed into shape by pressing at a pressure of 5~20 MPa for 5~20 min to form the carbon nanotube thin film electrode (112).

[0052] S2: The negatively charged tribological layer material is used to form a nanoscale uneven structure on the surface by a template method, and then combined with the carbon nanotube thin film electrode (112) to form the nano-power generation module (11). Preferably, in step S2, the template method uses an anodic aluminum oxide template or a polystyrene microsphere template to form a concave-convex structure through hot embossing or plasma etching processes, wherein the feature size of the concave-convex structure is 50~500 nm.

[0053] S3: Carbon nanotube aerogel prepared by floating catalyst chemical vapor deposition is used to form carbon nanotube fibers in a water bath and then woven to form a three-dimensional porous carbon nanotube fiber skeleton (121). A gel electrolyte is injected to form the gel electrolyte layer (122), and the electrode isolation layer (123) is combined to form the flexible energy storage module (12). Preferably, in step S3, the process parameters of the floating catalyst chemical vapor deposition method are the same as in step S1; the temperature of the water bath is 15~35℃, and the time is 30 s~3 min; the weaving is done by twisting or winding.

[0054] Preferably, in step S3, the preparation method of the gel electrolyte layer (122) is as follows: the matrix of the polymer-based gel electrolyte is dissolved in an organic solvent, lithium salt or ionic liquid is added, and the mixture is stirred evenly to form a sol. The sol is then injected into the carbon nanotube fiber skeleton (121) by vacuum impregnation or drop coating and cured at 60~80 ℃ for 2~6 h.

[0055] S4: The nano-power generation module (11), the insulating isolation layer (131), and the flexible energy storage module (12) are stacked in sequence and the waterproof encapsulation layer (132) is completely covered to form a sandwich structure; the sandwich structure is embedded inside the flexible bionic wing (212), and the sandwich structure is conformally solidified with the flexible bionic wing (212) through a hot pressing process; Preferably, in step S4, the temperature of the hot pressing process is 100~150 ℃, the pressure is 1~5 MPa, and the time is 10~30 min.

[0056] S5: The sandwich structure is electrically connected to the airborne main body assembly (20) via a flexible connecting wire (221).

[0057] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0058] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods of the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk) and includes several instructions to cause a terminal (which may be a mobile phone, computer, server, air conditioner, or network device, etc.) to execute the methods described in the various embodiments of the present invention.

[0059] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims, and all of these forms are within the protection scope of the present invention.

Claims

1. A device for power generation and energy storage based on carbon nanotubes, characterized in that, The device is used for self-powering and collecting environmental information for a biomimetic flapping-wing aircraft, including a wing-borne functional component (10) and an airborne main body component (20); the wing-borne functional component (10) and the airborne main body component (20) are movably connected; The wing-borne functional component (10) includes a nano-power generation module (11), a flexible energy storage module (12), and a packaging module (13); the airborne main component (20) includes a biomimetic main module (21), an energy management module (22), and a sensor module (23); the nano-power generation module (11) includes a negatively charged triboelectric layer (111) and a carbon nanotube thin film electrode (112); the flexible energy storage module (12) includes a carbon nanotube fiber skeleton (121), a gel electrolyte layer (122), and an electrode isolation layer (123); the packaging module (13) includes an insulating isolation layer (131) and a protective layer. Water encapsulation layer (132); the bionic main body module (21) includes a bionic fuselage main body (211), flexible bionic wings (212), flapping wing drive mechanism (213), flight control system (214) and fuselage main power supply (215); the energy management module (22) includes flexible connecting wires (221), bridge rectifier circuit (222), voltage limiting unit (223), voltage regulating unit (224) and charge / discharge controller (225); the sensor module (23) includes an environmental sensor group (231), wireless communication module (232) and interface communication module (233); The nano-power generation module (11) and the flexible energy storage module (12) are electrically connected and disposed inside the flexible bionic wing (212) to store the electrical energy generated by the flapping of the wing or the blowing of the wind in the flexible energy storage module (12); the energy management module (22) is electrically connected to the flexible energy storage module (12) through the flexible connecting wire (221) to rectify, limit, stabilize and charge / discharge the electrical energy and store it in the fuselage main power supply (215); the flapping wing drive mechanism (213), the flight control system (214) and the sensor module (23) are powered by the fuselage main power supply (215).

2. The device for power generation and energy storage based on carbon nanotubes according to claim 1, characterized in that, The negatively charged friction layer (111) has a nanoscale uneven structure on at least one side surface to increase the friction contact area; the carbon nanotube thin film electrode (112) is a three-dimensional conductive network structure composed of carbon nanotubes.

3. The device for power generation and energy storage based on carbon nanotubes according to claim 1, characterized in that, The carbon nanotube fiber skeleton (121) is a three-dimensional porous structure composed of carbon nanotube fibers, the gel electrolyte layer (122) is a polymer-based gel electrolyte, and the electrode isolation layer (123) is a porous polymer membrane.

4. The device for power generation and energy storage based on carbon nanotubes according to claim 1, characterized in that, The insulating isolation layer (131) is disposed between the nano-power generation module (11) and the flexible energy storage module (12) to achieve electrical isolation between the two; the nano-power generation module (11), the insulating isolation layer (131), and the flexible energy storage module (12) are stacked in sequence to form a sandwich structure; the sandwich structure can deform accordingly with the flexible deformation of the flexible bionic wing (212) to achieve mechanical energy-electric energy conversion and in-situ storage when the wing flaps or the wind blows the wing; the waterproof encapsulation layer (132) completely covers the nano-power generation module (11) and the flexible energy storage module (12), and forms an integral structure with the outer surface of the flexible bionic wing (212).

5. The device for power generation and energy storage based on carbon nanotubes according to claim 1, characterized in that, The bionic fuselage body (211) is a hollow shell structure, and its interior is provided with an installation cavity for accommodating the energy management module (22) and the sensor module (23); the flexible bionic wing (212) includes a wing skeleton and a wing membrane; the flapping wing drive mechanism (213) is electrically connected to the flight control system (214), and its flapping frequency and flapping amplitude are controlled by the flight control system (214).

6. The device for power generation and energy storage based on carbon nanotubes according to claim 1, characterized in that, The flexible connecting wire (221) is connected between the flexible bionic wing (212) and the bionic fuselage body (211) to realize the electrical connection between the wing-borne functional component (10) and the airborne main body component (20); the input end of the bridge rectifier circuit (222) is electrically connected to the flexible energy storage module (12); the bridge rectifier circuit (222), the voltage limiting unit (223), the voltage regulating unit (224) and the charge and discharge controller (225) are connected in series in sequence; the charge and discharge controller (225) includes an overcharge protection circuit and an over-discharge protection circuit, which are used to cut off charging when the voltage of the fuselage main power supply (215) exceeds the upper limit threshold, or cut off discharging when it is below the lower limit threshold.

7. The device for power generation and energy storage based on carbon nanotubes according to claim 1, characterized in that, The environmental sensor group (231) is electrically connected to the flight control system (214) and is used to transmit the collected environmental information to the wireless communication module (232) and the interface communication module (233); the environmental sensor group (231) includes at least one of a temperature sensor, a humidity sensor and a barometric pressure sensor.

8. A device for power generation and energy storage based on carbon nanotubes, characterized in that, The wing-borne functional component (10) is connected to the airborne main body component (20) through the flexible connecting wire (221) and the flexible hinge structure; the flexible hinge structure is a hollow structure, and its average density is lower than that of the bionic fuselage main body (211).

9. A method for preparing the apparatus according to any one of claims 1 to 8, characterized in that, Includes the following steps: S1: Carbon nanotubes are prepared by floating catalyst chemical vapor deposition. The obtained carbon nanotubes are dispersed in a solvent and then subjected to film formation treatment to obtain a carbon nanotube film. The film is then pressed and formed to form the carbon nanotube film electrode (112). S2: The negatively charged tribological layer material is used to form a nanoscale uneven structure on the surface by a template method, and then combined with the carbon nanotube thin film electrode (112) to form the nano-power generation module (11). S3: Carbon nanotube aerogel prepared by floating catalyst chemical vapor deposition is used to form carbon nanotube fibers in a water bath and then woven to form a three-dimensional porous carbon nanotube fiber skeleton (121). A gel electrolyte is injected to form the gel electrolyte layer (122), and the electrode isolation layer (123) is combined to form the flexible energy storage module (12). S4: The nano-power generation module (11), the insulating isolation layer (131), and the flexible energy storage module (12) are stacked in sequence and the waterproof encapsulation layer (132) is completely covered to form a sandwich structure; the sandwich structure is embedded inside the flexible bionic wing (212), and the sandwich structure is conformally solidified with the flexible bionic wing (212) through a hot pressing process; S5: The sandwich structure is electrically connected to the airborne main body assembly (20) via a flexible connecting wire (221).

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