Ultra-miniature bionic self-powered aircraft facing environment parameter perception

Abstract

The invention discloses an environment parameter perception-oriented ultra-miniature bionic self-powered aircraft, and relates to the technical field of ultra-miniature aircrafts, and the aircraft mainly comprises a novel bionic pneumatic structure, an ultra-miniature flexible perception communication function circuit, an ultra-miniature self-powered module and a memory alloy control wire. Typical drifting structures such as dandelion-like structures in nature are simulated, a novel patterned bionic pneumatic structure with high Reynolds number, low terminal speed and large drifting range is designed, and core circuits such as an ultra-miniature flexible sensing communication function circuit and a self-powered module are designed. The ultra-miniature bionic self-powered aircraft capable of sensing the self-defined environmental parameters and having the wide-area deployment capability is prepared by combining heterogeneous integration of memory alloy control wires, the ultra-miniature bionic self-powered aircraft can be driven by a miniature unmanned aerial vehicle to a specific environment for large-scale throwing, a sensing network is established after landing deployment, data transmission and coordination are carried out between the aircraft and the unmanned aerial vehicle, and the self-powered aircraft has the wide-area deployment capability. And a large-scale, efficient and reliable ecological environment monitoring network is formed. In addition, the novel structural design, various ultra-miniature circuit structures and the heterogeneous and heterogeneous integration technology can be widely applied to the field of flexible aircrafts or robots, and therefore a series of miniature battery-free designs are achieved.

Description

Technical field:

[0001] The invention relates to the technical field of ultra-micro aircraft, and in particular to an ultra-micro bionic self-powered aircraft for environmental parameter perception. Background technology:

[0002] Long-term real-time monitoring of multiple environmental parameters is the foundation of ecological environmental protection and an important support for the construction of ecological civilization. As the core component for realizing ecological environmental monitoring, hundreds of millions of sensors are integrated into various devices to sense multiple environmental parameters and convert them into electrical signals, which are then transmitted to terminals (such as computers) for real-time analysis, judgment and response. The large-scale automated deployment of sensors for specific outdoor ecological environments is currently a major problem, with a series of problems such as high cost, difficulty in mass production, poor concealment, inability to capture energy from the environment and difficulty in long-term monitoring. Therefore, the present invention proposes an ultra-micro bionic self-powered aircraft for environmental parameter perception, which has a double-layer structure. In the first structural layer, a typical drifting structure such as dandelions in nature is biomimetic, and a patterned polyimide (PI) film with high Reynolds number, low terminal velocity and large drifting range is designed and prepared, which is called a new bionic pneumatic structure. Taking an ultra-micro self-powered module using solar cells as an example, the solar cells are arranged on the surface of the first structural layer; a flexible PI film circuit is prepared in the second structural layer, including an ultra-micro sensing communication functional circuit integrating a low-power long-distance transmission Bluetooth microcontroller, a high-precision humidity / temperature / air pressure and other sensors, and the remaining ultra-micro self-powered modules integrating supercapacitors, voltage-dividing resistors, peripheral capacitors, and low-voltage difference linear regulators; the heterogeneous and heterogeneous integration of the ultra-micro bionic self-powered aircraft for environmental parameter perception is realized by using micro-nano processing technology. The present invention also combines the memory alloy control wire (arranged in the second structural layer) to achieve precise control of the flight attitude and landing range, so as to support the large-scale and precise deployment of the sensor network. The aircraft can be brought to a specific environment by a micro-UAV for large-scale spraying. After landing and deployment, a sensor network is established, and data transmission and coordination are carried out between each other to form a large-scale, efficient and reliable ecological environment monitoring network. It can not only be deployed in harsh environments for long-term stable work, but also can adjust the control network structure and sensor types according to monitoring needs, which significantly improves the accuracy and response speed of ecological environment monitoring.

[0003] The present invention proposes an ultra-micro bionic self-powered aircraft for environmental parameter perception. It imitates the phenomenon of wind blowing away dandelion seeds in nature and designs a new bionic pneumatic structure to increase the dispersion distance. It can be carried by a micro-UAV to a specific environment for large-scale spreading. The memory alloy control wire enables the ultra-micro bionic self-powered aircraft to have a certain three-dimensional deformation ability, so as to achieve precise deployment, and form a sensor network after landing deployment; taking the ultra-micro self-powered module using solar cells as an example, the designed ultra-micro self-powered module can absorb solar energy and convert it into electrical energy to supply ultra-micro sensing communication functional circuits to achieve long-term environmental monitoring and data feedback. The programmable Bluetooth microcontroller has a universal asynchronous receiver and transmitter (URAT), a serial peripheral interface (SPI) and an integrated circuit bus (I 2 C) and other serial ports, which can be expanded to add multiple types of sensors (such as temperature, sound, vibration, magnetic field, radiation, pollutants, etc.) to achieve a wider range of environmental monitoring applications. Summary of the invention:

[0004] In view of the problems of environmental parameter perception sensors being difficult to deploy on a large scale, being costly, and being difficult to work for a long time, the present invention discloses an ultra-micro bionic self-powered aircraft for environmental parameter perception, which has the characteristics of large-scale networking, long-term self-sustaining operation, perception of multiple environmental parameters, programmable expansion, and low cost. The ultra-micro bionic self-powered aircraft is designed with a lightweight bionic pneumatic structure to increase the drifting distance, a memory alloy control wire to achieve precise deployment, a lightweight and flexible ultra-micro perception communication functional circuit and an ultra-micro self-powered module to achieve long-term environmental parameter monitoring and data feedback, and a heterogeneous heterogeneous integration technology is proposed to realize the ultra-micro aircraft, ensuring the stability and controllability of the perception communication functional circuit. The novel bionic pneumatic structure, ultra-micro perception communication functional circuit, ultra-micro self-powered module, and heterogeneous heterogeneous integration technology contained in the invention are advanced internationally.

[0005] The present invention provides an ultra-micro bionic self-powered aircraft for environmental parameter perception, which is manufactured by heterogeneous heterogeneous integration of a first structural layer and a second structural layer. The first structural layer of the aircraft is designed with a novel bionic pneumatic structure and solar cells, and the second structural layer integrates an ultra-micro sensing communication function circuit, a partial self-powered module and a memory alloy control wire.

[0006] The novel bionic pneumatic structure is a bionic patterned structure of a layer of lightweight flexible PI, which is prepared in the first structural layer. The pneumatic structure is inspired by the typical drifting structure in nature, and a dandelion-like structure with high Reynolds number, low terminal velocity and long drifting distance is designed in combination with aerodynamics. A planarized fluff hollow structure is drawn through a drawing program, so that the novel bionic pneumatic structure can form turbulence at the edge of the structure during the drifting process, effectively expanding the drifting distance and improving the deployment capability of the ultra-micro bionic self-powered aircraft. The above-mentioned patterned structure is processed into a physical object on a flexible PI sheet by a laser cutting machine. The processed graphics are of high precision and the cutting edges are smooth, which ensures the reliability and stability of the aerodynamic structure when it drifts with the wind.

[0007] The ultra-micro sensing communication function circuit is composed of a Bluetooth microcontroller circuit and a multi-parameter sensing circuit. It is designed and processed on the second structural layer. It is a layer of flexible PI circular thin film with insulating layers on both sides to prevent external current interference. The Bluetooth microcontroller circuit mainly includes a low-power Bluetooth chip, peripheral capacitors and inductors, and an external crystal oscillator. It can be controlled by GPIO serial port, I 2 The C serial port and SPI serial port are connected to various sensors (air pressure / temperature / humidity) to realize device logic control and data information feedback. The multi-parameter sensing circuit mainly includes temperature / air pressure / humidity sensors and surrounding capacitors and resistors, which can form a communication connection with the Bluetooth microcontroller, so that the Bluetooth microcontroller can receive the data obtained by the multi-parameter sensing circuit and transmit the data over a long distance.

[0008] Furthermore, the peripheral circuit of the Bluetooth microcontroller circuit is composed of an external crystal oscillator, a filter capacitor, a patch ceramic antenna impedance matching capacitor, an inductor, etc. The Bluetooth microcontroller uses a variety of interfaces, including GPIO serial port, SPI communication serial port and I 2 C communication serial port, combined with software code to realize the control of air pressure / temperature / humidity sensors, thereby forming a complete wireless environment perception system. The Bluetooth microcontroller has programmable characteristics. By programming and controlling the Bluetooth microcontroller, data packets can be transmitted at different rates. The Bluetooth microcontroller circuit is designed to match the ultra-micro circuit of the small and light ceramic patch antenna, and by leading out the wire at the antenna end, the distance of Bluetooth communication is greatly increased, so that the aircraft has the function of long-distance reliable communication (data interaction and transmission).

[0009] Furthermore, the multi-parameter sensing circuit preferably selects a digital sensor with pressure and temperature measurement functions, and adopts an extremely compact 10-pin metal cover LGA package to reduce the overall weight of the present invention. The sensor can support multiple communication methods and has high precision. In addition, an industrial-grade digital sensor specifically used for measuring relative humidity is preferred. This sensor meets the stringent requirements of environmental monitoring applications for electrostatic discharge and robustness, and can also be interfaced through multiple pre-configured communication methods to facilitate system integration. The two sensing modules are connected to the Bluetooth microcontroller via a communication interface and are powered by an ultra-micro self-powered module, so as to realize the multi-parameter sensing of the aircraft environment, such as temperature, air pressure, humidity and other data, and send them to the Bluetooth microcontroller.

[0010] Furthermore, taking the ultra-micro self-powered module using solar cells as an example, the ultra-micro self-powered module is composed of micro solar cells, voltage-dividing resistors, peripheral capacitors, low-dropout linear regulators (LDOs) and supercapacitors, which can convert ambient light energy into electrical energy, and drive the memory alloy control wire as needed to adjust the aircraft's falling posture and supply the ultra-micro sensing communication function circuit. The micro solar cell ensures the power required for the sensing communication function (Bluetooth microcontroller and sensor), and the module connects the output end of the micro solar cell to a diode to prevent the reverse flow of current from destroying the circuit. In order to maintain the good working condition of the sensing communication function circuit in weak light, the supercapacitor and other components in the module can store a large amount of energy in a short time, can better collect unstable ambient light energy (intermittent, fluctuating), and provide more electrical energy to the load, realize the battery-free collection of ambient light energy, and achieve the design goals of miniaturization and lightweight. The LDO and voltage-dividing resistor used in the ultra-micro self-powered module are set to enable the LDO to work only after the voltage of the supercapacitor reaches the threshold voltage, so that the voltages of the solar input circuit system and the solar output circuit system both meet the requirements of the device, ensuring the stable operation of the ultra-micro sensing communication function circuit. Furthermore, the ultra-micro self-powered module can also be designed to utilize a variety of different environmental energies (solar energy / vibration energy / heat energy / radio frequency energy, etc.) to convert into electrical energy to meet the special power supply requirements of ultra-micro aircraft or robots.

[0011] Furthermore, the bending angle of the memory alloy control wire can be adjusted in real time by changing the current intensity, so that the aerodynamic structure has a certain three-dimensional deformation ability. The three-dimensional deformation ability can control the terminal speed of the ultra-micro bionic self-powered aircraft, thereby affecting the scattering distance, and realizing the controllable deployment of a large number of ultra-micro aircraft in the same batch in a larger area. After landing and deployment, a sensor network can be established to transmit and coordinate data with each other, forming a large-scale, efficient and reliable ecological environment monitoring network.

[0012] Furthermore, the heterogeneous heterogeneous integration technology ensures the stability of the aircraft in the passive flight structure, ensures the stability and controllability of the sensing and communication functional circuit when it is working, and can disperse and deploy sensors over a large range to form a sensing network to achieve long-term environmental monitoring. It mainly includes: the aircraft body is designed as a double-layer structure, the new bionic pneumatic structure is designed on the first layer, the ultra-micro sensing and communication functional circuit is designed on the second layer, the solar cells in the ultra-micro self-powered module are distributed on the first layer, and the supercapacitors and other devices are distributed on the second layer. The first layer and the second layer structure are conformally attached by adhesive glue and pasted with memory alloy control wire; the positive and negative electrodes of the micro solar cells on the upper surface of the first layer can be connected to the power supply end of the ultra-micro sensing and communication functional circuit through the bionic pneumatic structure, through the partial self-powered module of the second layer, and the filling of silver glue realizes the firm attachment between the solar cells, the first layer structure and the second layer structure.

[0013] Compared with the prior art, the beneficial effects brought by the design scheme provided by the embodiment of the present invention include at least: breaking through the deployment limitations of the traditional sensor network, imitating the phenomenon of wind blowing away seeds and leaves in nature, designing a new lightweight bionic pneumatic structure that can be scattered by the wind like dandelions, combining the memory alloy control wire to control the flight posture of the pneumatic structure to achieve long-distance and precise deployment of ultra-micro bionic self-powered aircraft; designing ultra-micro sensing communication functional circuits and ultra-micro self-powered modules based on flexible PI film to improve the integration of aircraft, so that it has long-term environmental monitoring capabilities; using micro-nano processing technology to heterogeneously integrate an ultra-micro bionic self-powered aircraft for environmental parameter perception, with an overall weight of about 213 mg, which can be carried by a micro-man-machine to a specific environment for large-scale throwing, and performing long-term environmental monitoring after control and networking. In addition, the new bionic pneumatic structure, ultra-micro sensing communication functional circuit, ultra-micro self-powered module and heterogeneous heterogeneous integration technology can be widely used in the field of flexible aircraft or robots, thereby realizing a series of miniaturized battery-free designs.

[0014] The above invention content is only an illustrative description of the principles and effects of the present invention, and is not intended to limit the present invention. Anyone familiar with the technology may modify or change the above invention content without violating the spirit and scope of the present invention. Therefore, all equivalent modifications or changes made by those with ordinary knowledge in the technical field without departing from the spirit and technical ideas disclosed by the present invention should still be covered by the claims of the present invention. Other features of the present application will make the specification easy to understand through the following content. Description of the drawings:

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0016] Figure 1 This is a general structural diagram of an ultra-micro bionic self-powered aircraft for environmental parameter perception according to the present invention;

[0017] Figure 2 The overall architecture and functional block diagram of an ultra-micro bionic self-powered aircraft for environmental parameter perception according to the present invention;

[0018] Figure 3 This is a new type of bionic pneumatic structure diagram of an ultra-micro bionic self-powered aircraft for environmental parameter perception according to the present invention;

[0019] Figure 4 This is a diagram of an ultra-micro sensing communication function circuit and a self-powered module of an ultra-micro bionic self-powered aircraft for environmental parameter sensing according to the present invention;

[0020] Figure 5 This is a schematic diagram of a Bluetooth microcontroller circuit for an ultra-micro bionic self-powered aircraft for environmental parameter perception according to the present invention;

[0021] Figure 6 This is a schematic diagram of a multi-parameter sensing circuit of an ultra-micro bionic self-powered aircraft for environmental parameter sensing according to the present invention;

[0022] Figure 7 The present invention is a schematic diagram of an ultra-micro self-powered module of an ultra-micro bionic self-powered aircraft for environmental parameter perception. Specific implementation method:

[0023] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0024] An embodiment of the present invention provides an ultra-micro bionic self-powered aircraft for environmental parameter perception. The present invention is further described in detail below in conjunction with specific embodiments.

[0025] Example:

[0026] like Figure 1 As shown, the ultra-micro bionic aircraft of this example mainly includes the following structures: 1-micro solar cell group, 2-aircraft first structural layer, 3-aircraft second structural layer, 4-memory alloy control wire. The 1-micro solar cell group is a series connection of two micro solar cells with a length and width of 5mm, located on the top of the ultra-micro bionic self-powered aircraft, and its positive and negative electrodes can be connected to the power supply end of the sensing and communication functional circuit in the 3-aircraft second structural layer through the two reserved openings designed in the 2-aircraft first structural layer. Silver glue is filled in the reserved openings to achieve a firm attachment between the three, ensuring the low power loss of the circuit architecture; the 2-aircraft first structural layer is designed with a new bionic pneumatic structure, which is imitating the typical drifting structure in nature, and combines aerodynamics to design a dandelion-like structure with a high Reynolds number, low terminal velocity and long drifting distance. The physical object is processed on the flexible PI sheet by a laser cutting machine, so that the new bionic pneumatic structure can be used during the drifting process. Turbulence is formed around the structure, which greatly increases the drift distance, and the maximum outer ring radius is 25mm; the second structural layer of the 3-aircraft integrates the Bluetooth microcontroller circuit and multi-parameter sensing circuit of the flexible ultra-micro sensing communication functional circuit, and integrates part of the self-powered module (supercapacitor, peripheral resistor capacitor, low voltage difference regulator), and is made on a layer of copper-plated PI flexible circular thin sheet as a whole, with a radius size of 9mm; the bending angle of the 4-memory alloy control wire can be adjusted in real time by changing the current intensity, so that the aerodynamic structure has a certain three-dimensional deformation ability; the solid disc structure of the first structural layer of the 2-aircraft is conformally attached to the second structural layer of the 3-aircraft with adhesive, and is attached to the central section and the head and tail ends of the 4-memory alloy control wire with a radius of 0.1mm. The above-mentioned new design technology and integrated preparation method ensure the stability and controllability of the aircraft on the passive flight structure, ensure the stability of the sensing communication functional circuit when working, and can effectively disperse and deploy sensors in the wind.

[0027] like Figure 2As shown, the main architecture and functions of the ultra-micro bionic self-powered aircraft in this example are as follows: the bionic pneumatic structure reduces the terminal speed through the patterned design of turbulence formed by the fluttering process, the memory alloy control wire controls and adjusts the flight angle of the aircraft by changing the current intensity, and the memory alloy control wire is attached to the bionic pneumatic structure to achieve large-scale and precise deployment of the sensor network; the ultra-micro sensing communication function circuit integrates the Bluetooth microcontroller circuit and the multi-parameter sensing circuit to enable the interaction of data signals, so that the aircraft has a long-distance reliable communication function, and the ultra-micro self-powered module using solar cells absorbs solar energy and converts it into electrical energy to supply the aircraft for long-term self-sustaining operation The ultra-micro self-powered module is double-layered and distributed in the first and second structures of the aircraft, with higher integration and better mechanical structure stability; the aerodynamic structure design such as the new bionic aerodynamic structure and memory alloy control wire enables the aircraft to accurately deploy sensor networks over a large range, and the core circuits such as the ultra-micro functional circuit and self-powered module enable the aircraft to monitor and transmit back a variety of environmental parameters for a long time; the main architecture is heterogeneous and integrated to prepare an ultra-micro bionic self-powered aircraft for environmental parameter perception, which can eventually be carried by a micro-UAV to a specific environment for large-scale scattering, forming a sensor network to achieve long-term environmental monitoring.

[0028] like Figure 3 As shown, the first structural layer of the aircraft designed in this embodiment is designed with a new type of bionic pneumatic structure, including the planarized fluff hollow structure, the central solid disk structure and the reserved opening structure. The overall patterned design is processed into a physical object on a 25μm thick flexible PI sheet by a laser cutting machine, and the maximum outer ring radius is 25mm.

[0029] like Figure 4 As shown, the second structural layer of the aircraft designed in this embodiment includes an ultra-micro sensing and communication functional circuit and some ultra-micro self-powered modules, which are made as a whole on a 25μm thick copper-plated PI flexible circular sheet. The radius of the circular sheet is 9mm, and there are 18μm thick insulating layers on both sides to prevent external electrical interference.

[0030] like Figure 5As shown, in this example, the Bluetooth microcontroller circuit includes a first micro capacitor (0201 package) CS1, a second micro capacitor CS2, a second micro capacitor CS3, a fourth micro capacitor CS4, a fifth micro capacitor CS5, a sixth micro capacitor CS6, a seventh micro capacitor CS7, an eighth micro capacitor CS8, a ninth micro capacitor CS9, a fifth capacitor (0805 package) C5, a first capacitor L1, a Bluetooth microcontroller IC1, a 32MHz crystal oscillator X1 and a patch ceramic antenna. The A1 end and B2 end of the Bluetooth microcontroller IC1 are connected to one end of the first micro capacitor CS1 and the second micro capacitor CS2, and the other end of the first micro capacitor CS1 and the second micro capacitor CS2 are connected to the 1st and 3rd ends of the crystal oscillator X1, and the 2nd and 4th ends of the 32MHz crystal oscillator X1 are both grounded. The A2 end of the Bluetooth microcontroller IC1 is connected in series with the seventh micro capacitor CS7 and the third micro capacitor CS3, and finally connected to the C2 end of the Bluetooth microcontroller IC1, wherein the other end of the seventh micro capacitor CS7 is grounded. The A7 terminal of the Bluetooth microcontroller IC1 is connected in series with one end of the fourth micro capacitor CS4, and the other end of the fourth micro capacitor CS4 is grounded. The B7 terminal of the Bluetooth microcontroller IC1 is connected to the fifth micro capacitor CS5, and the other end is grounded. The D2 terminal of the Bluetooth microcontroller IC1 is connected in series with one end of the sixth micro capacitor CS6, and the other end of the sixth micro capacitor CS6 is respectively connected to one end of the first inductor L1 and the D1 terminal of IC1, and the other end of the first inductor L1 is connected to the 4th terminal of the antenna. The H7 terminal of the Bluetooth microcontroller IC1 is respectively connected in series with one end of the ninth micro capacitor CS9 and the fifth capacitor C5, the other end of the fifth capacitor C5 is grounded, and the other end of the ninth micro capacitor is respectively connected to the E3 and F5 terminals of IC1. The A6 terminal of the Bluetooth microcontroller IC1 is connected in series with the eighth micro capacitor CS8, and the eighth micro capacitor CS8 is respectively connected to the ground terminal, C4 terminal and C5 terminal. The Bluetooth microcontroller circuit can realize the reuse of solar cells by the GPIO serial port (NET4, i.e., the A4 terminal), and can be realized by I 2 C serial port and SPI serial port (NET1, i.e., B4 end and NET2, i.e., D3 end) are connected to various sensors (air pressure / temperature / humidity) to realize device logic control and data information feedback.

[0031] like Figure 6As shown, in this example, the multi-parameter sensing circuit includes a first resistor R1, a second resistor R2, a fifth resistor R5, a sixth resistor R6, a temperature barometer U4, a hygrometer U5, a tenth micro-capacitor CS10, an eleventh micro-capacitor CS11 and a twelfth micro-capacitor CS12. Terminal 1 of the temperature barometer U4 is connected in series to one end of the second resistor R2, and the other end of the second resistor R2 is connected to terminal 2 and terminal NET1 of the temperature barometer U4. Terminal 3 of the temperature barometer U4 is connected to one end of the tenth micro-capacitor CS10 and the ground terminal, and terminal 4 of the temperature barometer U4 is connected to the first resistor R1 and terminal NET2. The NET1 terminal and the NET2 terminal are connected to the B4 terminal and the D3 terminal of the Bluetooth microcontroller IC1, and the Bluetooth microcontroller IC1 is connected to the I of the two interfaces. 2 C communication receives the temperature and air pressure data of the multi-parameter sensing circuit, and then can send it to the terminal via Bluetooth to achieve long-distance data transmission. The 5-terminal of the temperature barometer U4 is connected to the ground terminal and the eleventh micro-capacitor CS11, and is connected to the 8- and 9-terminals of the temperature barometer U4. The 6-terminal of the temperature barometer U4 is connected to the NET7 terminal, and is connected to the 1-terminal on the temperature barometer U4, and the 7-terminal of the temperature barometer U4 is connected to the NET3 terminal. The 1-terminal of the hygrometer U5 is connected in parallel with one end of the fifth resistor R5, the 2-terminal of U5 is connected in parallel with one end of the sixth resistor R6, the 3-terminal of the hygrometer U5 is connected in parallel with the other ends of R5 and R6, one end of the twelfth micro-capacitor is connected to the 4-terminal of the hygrometer U5 and the GND ground terminal, the other end of the twelfth micro-capacitor is connected to the 3-terminal of the hygrometer U5, the 1-terminal and 2-terminal of the hygrometer U5 are respectively connected to the NET2-terminal and the NET7-terminal, and form communication with the Bluetooth microcontroller. After the connection is finally completed, a multi-parameter sensing circuit is formed, which can simultaneously collect air pressure, temperature and humidity data and send them to the Bluetooth microcontroller for processing.

[0032] like Figure 7As shown, in this example, the ultra-micro self-powered module comprises a first diode D1, a 2.5V low voltage dropout linear regulator U2, a 1.9V low voltage dropout linear regulator U3, a third resistor R3, a fourth resistor R4, a first super capacitor C1, a twelfth micro capacitor C12, a thirteenth micro capacitor C13 and a fourteenth micro capacitor C14. The solar cell VCC terminal is connected to one end of the first diode D1, and the other end is connected in series to one end of the twelfth micro capacitor C12, and is connected in series to the 1st and 3rd ends of the 2.5V low voltage dropout linear regulator U2, and the other end of the twelfth micro capacitor C12 is grounded. The 2nd end of the 2.5V low voltage dropout linear regulator U2 is grounded, and the 5th end is connected in parallel to one end of the first super capacitor C1 and the thirteenth capacitor CS13, and the 5th end of the 2.5V low voltage dropout linear regulator U2 is connected in series to the 1st end of the 1.9V low voltage dropout linear regulator U3, and the 2nd end of the 1.9V low voltage dropout linear regulator U3 is grounded. The 3-terminal of the 1.9V low-voltage difference linear regulator U3 is connected to one end of two voltage-dividing resistors, a third resistor R3 and a fourth resistor R4, to play a voltage-dividing role, and the voltage regulator U3 can only be turned on after the voltage of the supercapacitor is controlled to reach a trigger threshold. The 5-terminal of the 1.9V low-voltage difference linear regulator U3 is connected to one end of the fourteenth micro-capacitor CS14, and is connected to NET7, i.e., the VDD end of the Bluetooth microcontroller, the barometer and the hygrometer, so that the Bluetooth microcontroller, the barometer and the hygrometer operate at a suitable voltage.

Claims

1. An ultra-micro bionic self-powered aircraft for environmental parameter perception, characterized by: It is obtained by heterogeneous and heterogeneous integration of new bionic pneumatic structure, ultra-micro sensing and communication functional circuit, ultra-micro self-powered module and memory alloy control wire; the main structure of the aircraft is designed into two layers, called the first structural layer and the second structural layer.

2. The novel bionic pneumatic structure according to claim 1, characterized in that: By imitating the typical drifting structures in nature, a dandelion-like structure with high Reynolds number, low terminal velocity and long drifting distance was designed in combination with aerodynamics. The physical object was processed on a flexible polyimide (PI) sheet by a laser cutting machine; the new bionic pneumatic structure can form turbulence around the structure during the drifting process, greatly increasing the drifting distance and improving the large-scale deployment capability of the ultra-micro bionic self-powered aircraft. The new bionic pneumatic structure is designed in the first structural layer, avoiding the impact of multi-layer electrical wire integration on the aerodynamic characteristics of the aircraft and improving the integration of the aircraft.

3. The ultra-micro sensing communication functional circuit according to claim 1, characterized in that: The Bluetooth microcontroller circuit mainly includes a Bluetooth microcontroller, peripheral capacitors and inductors, a patch ceramic antenna and an external crystal oscillator. The Bluetooth microcontroller can be connected to the multi-parameter sensing circuit through multiple serial ports to realize sensor data acquisition interaction, wireless communication interaction and other functions. By leading out wires at the antenna end, the distance of Bluetooth communication is greatly increased, so that the aircraft has a long-distance reliable communication function. The multi-parameter sensing circuit mainly includes multiple sensors such as air pressure / temperature / humidity. It is connected to the Bluetooth microcontroller through multiple pre-configured communication interfaces to sense multiple environmental parameters (air pressure / temperature / humidity, etc.) from the environment and transmit them back. The integration of multiple sensors and the Bluetooth microcontroller interface system enables the aircraft to have multi-field environment perception capabilities. The integrated reuse of similar capacitors in the circuit design simplifies the multi-parameter sensing circuit.

4. The ultra-micro self-powered module according to claim 1, characterized in that: Taking the ultra-micro self-powered module using solar cells as an example, the module mainly includes solar cells, voltage-dividing resistors, voltage regulators and supercapacitors, which can convert light energy in the environment into electrical energy, and drive the memory alloy control wire as needed to adjust the aircraft's falling posture and supply the ultra-micro sensing communication function circuit. In order to ensure the stable operation of the aircraft under weak light conditions, the supercapacitor and other components used in the ultra-micro self-powered module can better collect unstable ambient light energy (intermittent, volatile), store a large amount of electrical energy in a short time and output it stably, meet the working requirements of different components, realize the collection of solar energy without energy storage batteries, and the circuit is more miniaturized and lightweight. In addition, the ultra-micro self-powered module can also be designed to utilize a variety of different environmental energies (solar energy / vibration energy / thermal energy / radio frequency energy, etc.) to convert into electrical energy to meet the special power supply needs of ultra-micro aircraft or robots.

5. The memory alloy control wire according to claim 1, characterized in that: The bending angle of the memory alloy control wire can be adjusted in real time by changing the current intensity, so that the aerodynamic structure has a certain three-dimensional deformation ability. The three-dimensional deformation ability can control the terminal speed of the ultra-micro bionic self-powered aircraft, thereby affecting the scattering distance, and realize the controllable deployment of a large number of ultra-micro aircraft in the same batch in a larger area. After landing and deployment, a sensor network can be established to transmit and coordinate data with each other, forming a large-scale, efficient and reliable ecological environment monitoring network.

6. The heterogeneous heterogeneous integration technology according to claim 1, characterized in that: The main body of the aircraft is designed as a double-layer structure, with a new bionic pneumatic structure designed on the first layer, an ultra-micro sensing and communication functional circuit designed on the second layer, solar cells of the ultra-micro self-powered module distributed on the first layer, and supercapacitors and other devices distributed on the second layer. The first and second layers are conformally attached by adhesive and pasted with memory alloy control wires; the positive and negative poles of the solar cell group on the upper surface of the first layer can pass through the reserved opening of the bionic pneumatic structure, and be connected to the power supply end of the ultra-micro sensing and communication functional circuit through the partial self-powered module of the second layer, and the filling of silver glue realizes the firm attachment of the solar cell, the first layer structure and the second layer structure. The heterogeneous heterogeneous integration technology ensures the structural stability of the aircraft, the stability and controllability of the sensing and communication functional circuit during operation, and can disperse and deploy sensors over a large range to form a sensor network for long-term environmental monitoring.

7. The novel bionic pneumatic structure, ultra-micro sensing and communication functional circuit, ultra-micro self-powered module and heterogeneous heterogeneous integration technology as described in claim 1 can be widely used in the field of flexible aircraft or robots, thereby realizing a series of miniaturized battery-free designs.

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