Piezoelectric pump aerodynamic system for unmanned aerial vehicle

Abstract

A piezoelectric pump aerodynamic system for unmanned aerial vehicle is disclosed and includes a propeller power assembly and a piezoelectric pump. The propeller power assembly includes propeller blades, a rotating shaft, a turbine fan and an airflow channel. The propeller blades and the turbine fan are pivotally connected to both ends of the rotating shaft, respectively, so as to form a linkage. The turbine fan is disposed in the airflow channel. The piezoelectric pump includes a covering plate, an actuator and a tube plate. The covering plate includes a connection pipe. The connection pipe is in communication with the airflow channel. The actuator is controlled and adjusted to generate efficient airflow, and the efficient airflow is output from the connection pipe through the airflow channel, guiding the turbine fan to generate rotational torque, and linking the propeller blades to generate lift and thrust to achieve flight movement.

Description

[Technical Field]

[0001] This invention relates to an aerodynamic system that utilizes piezoelectric pump technology to improve the thrust efficiency of unmanned aerial vehicles (UAVs). By combining airflow control technology with a lightweight, compact, and low-energy piezoelectric pump, and optimizing propeller design, the system can flexibly control airflow to improve the flight efficiency and thrust generation of the UAV, while also reducing noise and extending the flight time of the UAV. [Previous Technology]

[0002] Most existing UAV aerodynamic systems are based on traditional propeller structures and rely on electric motors to drive the propellers to generate thrust. Although this structure has achieved some success in many applications, its reliance on rotating blades to propel air still suffers from insufficient thrust, low energy efficiency, and high noise during high-speed or long-term operation. These problems are particularly prominent in applications requiring higher flight efficiency and extended flight time. Piezoelectric technology, as a novel driving technology, has been widely used in the fields of micro-mechanical actuation and airflow control. Piezoelectric materials can deform under voltage, a characteristic that allows them to be used in micro-pumps to regulate airflow. Therefore, this invention provides a piezoelectric pump aerodynamic system for UAVs, combining piezoelectric pump technology and a propeller structure, which can efficiently control airflow during UAV flight, thereby improving thrust efficiency and reducing energy consumption. [Summary of the Invention]

[0003] The purpose of this invention is to provide a pneumatic pump aerodynamic system for unmanned aerial vehicles (UAVs). This aerodynamic system utilizes pneumatic pump technology to improve the thrust efficiency of UAVs. Furthermore, it combines the lightweight, compact, and low-energy-consumption pneumatic pump with optimized propeller design to flexibly control airflow, thereby improving the flight efficiency and thrust generation of the UAV, reducing noise, and extending the flight time of the UAV.

[0004] To achieve the above objectives, a generalized embodiment of this invention is a pneumatic pump aerodynamic system for an unmanned aerial vehicle (UAV), comprising: at least one propeller power unit, including propeller blades, a shaft, a turbine fan, and an airflow channel. The propeller blades and the turbine fan are pivotally connected to both ends of the shaft to form a linkage. The turbine fan is pivotally disposed in the airflow channel, and the airflow channel, through efficient airflow, guides the turbine fan to generate rotational torque, thereby driving the propeller blades to generate lift and thrust. At least one pneumatic pump is stacked from a cover plate, an actuator, and a tube sheet. The tube sheet is provided with a connecting pipe that connects to the airflow channel. The actuator is controlled to generate efficient airflow, which is output from the connecting pipe of the tube sheet through the airflow channel, guiding the turbine fan to generate rotational torque, thereby driving the propeller blades to generate lift and thrust, thereby propelling the aircraft to move.

Implementation Method

[0005] Embodiments embodying the features and advantages of the present invention will be described in detail in the following description. It should be understood that the present invention can have various variations in different forms without departing from the scope of the present invention, and the descriptions and illustrations herein are for illustrative purposes only and not for limiting the present invention.

[0006] As shown in Figures 1, 2 and 3, the present invention provides a pneumatic pump aerodynamic system for an unmanned aerial vehicle (UAV), comprising: at least one propeller power unit 1 and at least one pneumatic pump 2, wherein the propeller power unit 1 includes propeller blades 11, a rotating shaft 12, a turbine fan 13 and an airflow channel 14, the propeller blades 11 and the turbine fan 13 are respectively pivotally connected to both ends of the rotating shaft 12 to form a linkage, the turbine fan 13 is pivotally disposed in the airflow channel 14, and the airflow channel 14 guides the turbine fan 13 to generate rotational torque through efficient airflow, thereby driving the propeller blades 11 to generate lift and thrust; the pneumatic pump 2 is used to regulate and control the generation of efficient airflow, and through the airflow channel 14, as shown in Figure 4, guides the efficient airflow through the turbine fan 13 to generate rotational torque, thereby driving the propeller blades 11 to generate lift and thrust, thereby achieving propulsion for flight.

[0007] As shown in Figure 5 and Figures 6A and 6B, the piezoelectric pump 2 has a flat cylindrical shape and is composed of a cover plate 21, an actuator 22 and a tube plate 23 stacked together. The tube plate 23 serves as the main flow path structure for accommodating the gas output and input in the piezoelectric pump 2, while the actuator 22 is the power source for driving the gas flow. The bottom end of the cover plate 21 is combined with the top end of the tube plate 23 to encapsulate the actuator 22.

[0008] As shown in Figure 5, the tube sheet 23 has an inlet pipe 231 and an outlet pipe 232, and the outlet pipe 232 is located on the opposite side of the inlet pipe 231. The tube sheet 23 has an inlet annular layer 233 inside, which is located between the inlet pipe 231 and the outlet pipe 232. An outlet annular layer 234 is provided inward from the inlet annular layer 233. The inlet annular layer 233 has a notch 233A that communicates with the outlet pipe 232. The tube sheet 23 has a gas inlet 238 above the side opposite to the notch 233A of the inlet annular layer 233 that communicates with the inlet pipe 231. The outlet annular layer 234 has a gas outlet 237 that communicates with the notch 233A of the inlet annular layer 233 and the outlet pipe 232.

[0009] Furthermore, the aforementioned tube sheet 23 has a tube sheet protrusion 235 at its outer edge, and several positioning latches 236 are provided on the tube sheet protrusion 235. The actuator 22 is provided with a first electrode 228 and a second electrode 229. The first electrode 228 has a first electrode positioning hole 228A, and the second electrode 229 has a second electrode positioning hole 229A. The first electrode positioning hole 228A can be locked with the positioning latches 236 on the tube sheet protrusion 235. Similarly, the second electrode positioning hole 229A can be locked with the positioning latches 236 on the tube sheet protrusion 235. In this way, the first electrode 228 and the second electrode 229 of the actuator 22 can be fixedly positioned on the tube sheet 23, providing a driving signal to the actuator 22 to form piezoelectric deformation and drive the gas flow. It should be noted that the tube sheet protrusion 235 of the tube sheet 23 is made of PC material (polycarbonate), which can be regarded as an insulator. Therefore, the first electrode 228 and the second electrode 229 will not short-circuit with each other.

[0010] The cover plate 21 is provided with a first protrusion 211 and a second protrusion 212. The cover plate 21 can be locked with the tube plate 23 from top to bottom and fix the actuator 22 between the tube plate 23 and the cover plate 21. The first protrusion 211 is correspondingly arranged above the gas inlet 238, and the second protrusion 212 is correspondingly arranged with the tube plate protrusion 235. It is worth noting that after the first protrusion 211 of the cover plate 21 is sealed, a gas inlet 238 can be formed. The gas inlet 238 is located between the first protrusion 211 of the cover plate and the upper part of the inlet ring layer 233. More precisely, the gas inlet 238 is located between the first protrusion 211 of the cover plate and the actuator 22 above the inlet ring layer 233. When the actuator 22 is actuated, the gas enters through the inlet pipe 231, is transported from above the actuator 22 to below the actuator 22 through the gas inlet 238, and finally flows out of the pneumatic electric pump 2 through the outlet pipe 232 after passing through the gas outlet 237 and the gap 233A of the inlet ring layer 233. Additionally, it is worth noting that the second protrusion 212 of the cover plate 21 is in close contact with the tube plate protrusion 235 of the tube plate 23, but the second protrusion 212 of the cover plate will not come into contact with the first electrode 228 or the second electrode 229 of the actuator 22 to cause a short circuit. Alternatively, sealant or insulating adhesive can be applied between the first electrode 228 or the second electrode 229 and the second protrusion 212 of the cover plate to ensure that the first electrode 228 or the second electrode 229 will not come into contact with the second protrusion 212 of the cover plate to cause a short circuit when the actuator 22 is actuated.

[0011] According to one embodiment of the present invention, in order to optimize the size and driven gas flow rate of the pneumatic pump 2, so that the pneumatic pump aerodynamic system of the UAV can drive the maximum flow rate with a small volume, the total length of the pneumatic pump 2 excluding the inlet pipe 231 and the outlet pipe 232 is between 28 mm ± 10 mm, the total width of the pneumatic pump 2 is between 31 mm ± 10 mm, and the thickness of the pneumatic pump 2 is between 5 mm ± 2 mm. Through the design of the size of the pneumatic pump 2, the output pressure of the pneumatic pump 2 can be between 150 mmHg ± 50 mmHg, and the output flow rate of the pneumatic pump 2 can be between 1000 ml / min ± 300 ml / min. It should be noted that, according to one aspect of the present invention, the above-mentioned total length, total width, thickness, and even the length and diameter of the inlet pipe 231 and the outlet pipe 232 are merely examples and can be modified according to the needs of the application device. Changes in size and corresponding gas flow rate are all within the scope considered during the creation of this invention.

[0012] As stated above, the length of either the inlet pipe 231 or the outlet pipe 232 of the pneumatic pump 2 is equal to or less than 6 mm, and the diameter of either the inlet pipe 231 or the outlet pipe 232 of the pneumatic pump 2 is equal to or less than 5 mm. Furthermore, the cover plate 21 of the pneumatic pump 2 has a ball-pressing hardness value of 333 MPa or higher (tested according to ISO 2039-1), and the material of the cover plate 21 is a heat-transfer material or an aluminum alloy. It is worth noting that the material of the cover plate 21 needs to have sufficient hardness to withstand the vacuum force generated during the operation of the pneumatic pump 2. If the hardness of the cover plate 21 is insufficient, it will cause the pneumatic pump 2 to collapse inward, thereby affecting the output performance of the pneumatic pump 2 and causing internal mechanism interference and collision. In addition, the cover plate 21 can be made of metal (e.g., aluminum alloy). Since metal (heat transfer material) has a thermal conductivity, it enhances the overall heat dissipation capacity of the electric pump 2. The better the overall heat dissipation capacity of the electric pump 2, the more it helps the electric pump 2 maintain its performance above the standard.

[0013] According to another embodiment of the present invention, the length of either the inlet pipe 231 or the outlet pipe 232 of the pneumatic electric pump 2 is greater than or equal to 2.5 mm, and the diameter of either the inlet pipe 231 or the outlet pipe 232 of the pneumatic electric pump 2 is greater than or equal to 2.5 mm. Furthermore, the cover plate 21 of the pneumatic electric pump 2 has a ball-pressing hardness value of 333 MPa or higher (tested according to ISO 2039-1), and the material of the cover plate 21 is a heat-transfer material or an aluminum alloy. It is worth noting that the material of the cover plate 21 needs to have sufficient hardness to resist the vacuum force generated during the operation of the pneumatic electric pump 2, preventing the pneumatic electric pump 2 from collapsing inward, thereby affecting the output performance of the pneumatic electric pump 2 and causing internal mechanism interference and collision.

[0014] The depressurization electric pump 2 drives the actuator 22 to generate high-flow gas transmission for intake and exhaust. The detailed structure and operation mode of the actuator 22 will be explained below.

[0015] As shown in Figures 6A and 6B, the actuator 22 includes, from top to bottom, a piezoelectric sheet 221, an inlet plate 222, a frame 223, a first plate 224, a second plate 225, a valve plate 226, and an outlet plate 227.

[0016] The piezoelectric sheet 221 described above is circular in shape and is in contact with the first electrode 228 to receive the drive signal (the drive voltage and drive frequency transmitted by the first electrode 228). Through the inverse piezoelectric effect, electrical energy is converted into mechanical energy. The deformation amount of the piezoelectric sheet 221 is controlled according to the magnitude of the drive voltage, and the deformation frequency of the piezoelectric sheet 221 is controlled by the operation drive frequency. The deformation of the piezoelectric sheet 221 drives the actuator 22 to start transmitting gas.

[0017] The aforementioned inlet plate 222 has a plurality of inlet holes 222A, which are arranged in a shape on the plane of the inlet plate 222. In this embodiment of the invention, the inlet holes 222A are arranged in a circle. The shape of the arrangement of the inlet holes 222A defines an actuating region 222B and a fixing region 222C. The actuating region 222B is surrounded by the inlet holes 222A, and a piezoelectric sheet 221 is attached thereto. The actuating region 222B can be driven to bend up and down by the action of the attached piezoelectric sheet 221. The fixing region 222C is located around the inlet holes 222A and is used to fix the inlet plate 222 in the actuator 22. It is worth noting that the aforementioned inlet holes 222A are tapered, which can improve the intake efficiency and has the effect of easy intake and difficult exhaust to prevent gas backflow. The number of inlet holes 222A is even. Furthermore, in one embodiment, the number of inlet holes 222A is 48, and in another embodiment, the number of inlet holes 222A is 52, but this is not a limitation. Moreover, the arrangement shape of the inlet holes 222A can be rectangular, square, circular, etc. The shape of the piezoelectric sheet 221 corresponds to the shape of the actuation area 222B of the inlet plate 222. In this embodiment, when the inlet holes 222A are arranged in a circle, the actuation area 222B is defined as circular, and the piezoelectric sheet 221 is also circular. As mentioned above, the arrangement shape of the inlet holes 222A can be rectangular, square, or circular, etc., and the shape of the actuation area 222B changes with the arrangement of the inlet holes 222A, and the piezoelectric sheet 221 also corresponds to its shape. In one embodiment of the present invention, to match the piezoelectric sheet 221 being set as circular, and the inlet holes 222A being arranged in a circle, the external configuration of the actuator 22 is also set as circular.

[0018] An inlet plate 222 is stacked on the frame 223 and is stacked with the fixing area 222C of the inlet plate 222. The frame 223 is positioned on the first plate 224, which is fixed to the second plate 225. The thickness of the first plate 224 is greater than the thickness of the second plate 225. Thus, an air intake chamber 223A is formed between the frame 223 and the first plate 224. The first plate 224 is provided with a plurality of first through holes 224A. The second plate 225... The component 225 is provided with a plurality of second through holes 225A, wherein the number, position, and diameter of the second through holes 225A correspond to the first through holes 224A located on the first plate 224. In this embodiment, the diameter of the second through holes 225A is the same as the diameter of the first through holes 224A. The bottom surface of the second plate 225 has a recess 225B formed by surface depression to a certain depth (as shown in Figure 6B), and the second plate 225 and the second electrode 229 are in contact and electrically connected. It is worth noting that in the embodiment, the second plate 225 is a metal plate.

[0019] The second plate 225 is stacked on the outlet plate 227 and maintains a distance G. The valve plate 226 is housed in the recess 225B on the bottom surface of the second plate 225 and can move up and down. The valve plate 226 has a plurality of valve holes 226A, and the valve holes 226A are offset from the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225. The outlet plate 227 has a plurality of air outlet holes 227A, which are corresponding to the valve holes 226A. The diameter d2 of the valve hole 226A is greater than or equal to the diameter d1 of the air outlet hole 227A. This design of the diameter of the air outlet hole 227A allows a large flow of air to be quickly discharged through the valve hole 226A and then through the air outlet hole 227A when the actuator 22 opens the flow path. It is worth noting that in this embodiment, the outflow plate 227 is a metal plate and the valve plate 226 is a flexible film with a thickness of approximately 0.4 to 0.6 micrometers (µm), preferably 0.5 micrometers (µm). In this embodiment, the valve plate 226 is preferably a polyimide film, but it is not limited thereto.

[0020] With this actuator 22 design, when the valve plate 226 is offset upwards towards the second plate 225, the valve plate 226 closes the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225. The actuator 22 operates in a way that closes the flow path (as shown in Figure 7B). When the valve plate 226 is offset downwards towards the outlet plate 227, the valve plate 226 vibrates the airflow within the gap G, and the airflow (the path indicated by the arrow) passes through the valve hole 226A and then quickly passes through the outlet hole 227A and is discharged. The actuator 22 operates in a way that opens the flow path (as shown in Figure 7C). This actuator 22 is designed to prevent backflow and generate a large flow rate control effect of unidirectional airflow.

[0021] Referring again to Figure 7B, after receiving the drive signal, the piezoelectric element 221 begins to deform, causing the inlet plate 222 to bend upward. At this time, the volume of the inlet chamber 223A increases, forming a negative pressure, which causes the valve plate 226 to be attracted upward and close the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225. At this time, as shown in Figure 7D, the gas on the inlet pipe 231 side of the tube sheet 23 is drawn into the gas inlet 238 of the tube sheet 23, and enters the inlet chamber 223A through the actuator 22. It enters the enlarged inlet chamber 223A and causes the valve plate 226 to deflect. The actuator 22 displaces upward toward the second plate 225, causing the valve plate 226 to close the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225. The actuator 22 then closes the flow path. Referring to Figure 7C, the piezoelectric plate 221 deforms upon receiving the drive signal, causing the inlet plate 222 to bend downward, compressing the inlet chamber 223A. At this time, as shown in Figure 7D, the gas on the inlet pipe 231 side of the tube sheet 23 is drawn into the gas inlet 238 of the tube sheet 23, and enters the actuator 22. Simultaneously, it pushes the gas inside the inlet chamber 223A through the first plate 224... The first through hole 224A and the second through hole 225A of the second plate 225 transmit downwards, causing the kinetic energy to be transmitted downwards from the actuator 22 to the gap G. This kinetic energy can push the valve plate 226 to move, causing the valve plate 226 to disengage from the second through hole 225A of the second plate 225 and abut against the outlet plate 227, thereby opening the flow path. The gas is then transmitted downwards through the valve hole 226A to the outlet hole 227A of the outlet plate 227, and then through the outlet hole 227A, and finally through the gas outlet 237 of the outlet ring layer 234 and the notch 233A of the inlet ring layer 233 to connect with the outlet pipe 232 to discharge the gas (as shown in Figure 7D). After that... As shown in Figure 7B, when the piezoelectric element 221 drives the inlet plate 222 to bend upward, increasing the volume of the inlet chamber 223A, a negative pressure is formed in the inlet chamber 223A. This causes the valve plate 226 to close the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225, preventing gas from flowing back into the inlet chamber 223A through the valve hole 226A and the first through hole 224A and the second through hole 225A. Furthermore, when the gas from the actuator 22 enters the inlet chamber 223A, the gas pressure inside the actuator 22 will be lower than the gas pressure outside the piezoelectric pump 2. The gas outside the piezoelectric pump 2 then enters the actuator 22 through the inlet pipe 231. (As shown in Figure 7D); when the piezoelectric element 221 receives the drive signal and deforms again, it drives the actuator 22 to move downward again. As previously described, the gas in the intake chamber 223A is guided downward and finally discharged through the outlet pipe 232. By continuously performing the aforementioned steps through the drive signal, the gas can be quickly introduced through the intake pipe 231 and discharged through the outlet pipe 232, achieving the effect of high-flow-rate transmission of efficient airflow.

[0022] According to Figure 7D of the present invention, when the piezoelectric element 221 receives a drive signal (drive voltage and drive frequency), it converts electrical energy into mechanical energy through the inverse piezoelectric effect. The deformation amount of the piezoelectric element 221 is controlled according to the magnitude of the drive voltage, and the deformation frequency of the piezoelectric element 221 is controlled by the drive frequency. The deformation of the piezoelectric element 221 drives the actuator 22 to start transmitting gas. When the inlet plate 222 bends upward, the valve plate 226 is attracted upward and closes the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225. At this time, the gas is drawn into the actuator 22 through the inlet hole 222A. When the piezoelectric element 221 bends upward, the valve plate 226 is attracted upward and closes the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225. At this time, the gas is drawn into the actuator 22 through the inlet hole 222A. When the drive signal received by the piezoelectric element 221 causes deformation, the inlet plate 222 bends downward. At this time, the gas in the actuator 22 is transmitted downward through the first through hole 224A of the first plate 224 and the second through hole 225A of the second plate 225. The kinetic energy of the gas during downward transmission pushes the valve plate 226 to displace, causing the valve plate 226 to disengage from the second through hole 225A of the second plate 225 and abut against the outlet plate 227, thereby opening the flow path and allowing the gas to be output from the outlet hole 227A. Therefore, by using the piezoelectric element 221 to drive the inlet plate 222 to bend repeatedly, the actuator 22 can drive the gas, enabling the piezoelectric pump 2 to achieve the effect of driving a large flow of gas. It is worth noting that in this embodiment of the invention, as shown in Figure 8, in order to achieve a higher flow rate of gas in the airflow channel 14, multiple piezoelectric pumps 2 can be connected in series to improve the overall airflow delivery capacity and generate a high-efficiency airflow in this airflow channel 14.

[0023] As can be seen from the above description, the total flow rate of the fluid in the above-mentioned outlet plate 227, valve plate 226, and first plate 224 can be designed and implemented based on the diameter or number of the air outlet 227A, valve hole 226A, and first through hole 224A. Please refer to Table 1 below for the relationship between the diameter and number of the air outlet 227A and the number of valve holes 226A and first through holes 224A, so as to achieve the best effect of the pneumatic electric pump 2 to achieve a large flow rate.

[0024] Table 1 Air outlet diameter 100 μm 200 μm 300 μm 400 μm 500 μm 600 μm 700 μm 800 μm Number of air vents 49 49 36 36 25 25 25 25 Number of valve holes twenty four twenty four 18 18 12 12 12 12 Number of first through holes 20 20 18 18 12 10 10 10

[0025] Furthermore, in the specific embodiment of this case, the valve plate 226 is designed to be a flexible film with a thickness of approximately 0.4 to 0.6 micrometers (µm), and the distance G maintained between the outlet plate 227 and the recess 225B of the second plate 225 falls within the range of approximately 40 to 70 micrometers (µm). Therefore, when the piezoelectric sheet 221 of the actuator 22 is maintained at an operating frequency of 20 to 22 kilohertz (kHz), preferably at 21 kilohertz (kHz), the pressure difference is maintained at a wavelength of 30 micrometers (µm). Matching the 0.5 micrometer (µm) valve plate 226 with a distance G maintained within the range of 40 to 70 micrometers (µm) in the recess 225B of the second plate 225, the oscillation within this distance G can form a unidirectional flow of a rarefaction wave to prevent backflow. This can result in the maximum flow rate. Minimizing the pressure drop that occurs as air flows through is important for maximizing valve performance.

[0026] As described above, the piezoelectric pump 2 is implemented in the piezoelectric pump aerodynamic system of the UAV of the present invention. As shown in Figures 1 and 4, in this embodiment of the present invention, the UAV has four propeller power units 1. The four propeller power units 1 are used to regulate and control the generation of efficient airflow through the piezoelectric pump 2. In the airflow channel 14, the efficient airflow is guided through the turbine fan 13 to generate rotational torque, which in turn drives the propeller blades 11 to generate lift and thrust, thereby propelling the UAV to move. Therefore, the present invention provides a piezoelectric pump aerodynamic system for UAVs, which has the following advantages: By driving the piezoelectric pump 2, the piezoelectric pump 2 generates stable airflow through high-frequency vibration. Due to the high-speed vibration characteristics of the piezoelectric material, these airflows can be guided to provide precise airflow control to the turbine fan 13 to generate rotation and drive the propeller blades 11 without adding extra weight, thus optimizing the thrust generation of the propeller blades 11; the dynamic adjustment mechanism adjusts the operating frequency and intensity of the piezoelectric pump 2 according to real-time data (such as flight speed, airflow changes, etc.), thereby achieving optimal airflow control. This ensures that the drone maintains optimal performance under various flight conditions.

[0027] In summary, the present invention provides a pneumatic pump aerodynamic system for unmanned aerial vehicles (UAVs). This aerodynamic system utilizes pneumatic pump technology to improve the thrust efficiency of UAVs. Furthermore, by combining the lightweight, compact, and low-energy-consumption pneumatic pump with optimized propeller design, the system can flexibly control airflow to improve the flight efficiency and thrust generation of UAVs, reduce noise, and extend the flight time of UAVs, making it highly applicable to industrial applications. [Simplified Explanation of the Diagram]

[0028] Figure 1 is a schematic diagram of the appearance of the UAV of the present invention. Figure 2 is a schematic diagram of the pneumatic pump aerodynamic system of the UAV of the present invention. Figure 3 is a schematic diagram of the appearance of the pneumatic pump and propeller power unit related assembly of the pneumatic pump aerodynamic system of the UAV of the present invention. Figure 4 is a cross-sectional schematic diagram of the propeller power unit of the pneumatic pump aerodynamic system of the UAV of the present invention. Figure 5 is an exploded schematic diagram of the pneumatic pump of the pneumatic pump aerodynamic system of the UAV of the present invention. Figure 6A is an exploded schematic diagram of the top view of the actuator of the pneumatic pump of the present invention. Figure 6B is an exploded schematic diagram of the bottom view of the actuator of the pneumatic pump of the present invention. Figure 7A is a cross-sectional schematic diagram of the actuator of the pneumatic pump of the present invention. Figure 7B is an enlarged schematic diagram of the actuator of the pneumatic pump of the present invention in part A of Figure 7A, showing its operation. Figure 7C is an enlarged schematic diagram of the actuator of the pneumatic pump of the present invention in part A of Figure 7A, showing its operation. Figure 7D is a cross-sectional schematic diagram of the pneumatic pump of the present invention operating and transmitting gas. Figure 8 is a schematic diagram of the series transmission of gas by the complex pneumatic electric pumps of the present invention.

Claims

1. A piezoelectric pump aerodynamic system for an unmanned aerial vehicle (UAV), comprising: at least one propeller power unit, including a propeller blade, a shaft, a turbine fan, and an airflow channel, wherein the propeller blade and the turbine fan are pivotally connected to both ends of the shaft to form a linkage, and the turbine fan is pivotally disposed in the airflow channel; and at least one piezoelectric pump, comprising a cover plate, an actuator, and a tube sheet stacked sequentially, the tube sheet having a connecting pipe connecting to the airflow channel, and the actuator being controlled to generate efficient airflow, which is output from the connecting pipe of the tube sheet through the airflow channel, guiding the turbine fan to generate rotational torque to drive the propeller blade to generate lift and thrust, thereby propelling the UAV to move, wherein the actuator includes: a piezoelectric element, an outlet plate, a first electrode, and a second electrode, the first electrode of the actuator being in contact with the piezoelectric element, and the second electrode being in contact with the outlet plate, providing a drive signal to the actuator to form piezoelectric deformation and drive gas flow.

2. The pneumatic system of the UAV with a pneumatic pump as claimed in claim 1, wherein the cover plate and the tube sheet are interlocked vertically, and the actuator is fixed between the tube sheet and the cover plate.

3. The pneumatic pump aerodynamic system for a drone as claimed in claim 1, wherein the tube sheet comprises: an inlet pipe; an outlet pipe located on the opposite side of the inlet pipe; and a tube sheet protrusion located at the outer edge between the inlet pipe and the outlet pipe, having a plurality of positioning latches thereon; an inlet annular layer disposed inside, having a notch communicating with the outlet pipe, and having a gas inlet at its top communicating with the inlet pipe; and an outlet annular layer disposed inside the inlet annular layer, having a gas outlet communicating with the notch of the inlet annular layer and the outlet pipe.

4. The piezoelectric pump aerodynamic system for a drone as described in claim 3, wherein the actuator is positioned on the inlet ring layer and the outlet ring layer, and the actuator includes the first electrode and the second electrode, wherein the first electrode has a first electrode positioning hole and the second electrode has a second electrode positioning hole, wherein the first electrode positioning hole and the second electrode positioning hole are respectively engaged with the positioning latch on the protrusion of the tube sheet, the first electrode and the second electrode of the actuator are fixedly located on the tube sheet, and a drive signal is provided to the actuator to form piezoelectric deformation to drive gas flow.

5. The piezoelectric pump aerodynamic system for a drone as claimed in claim 4, wherein the actuator comprises: the piezoelectric sheet; an inlet plate having a plurality of inlet holes, each of the inlet holes being arranged in a shape that defines an actuation region and a fixing region, the piezoelectric sheet being stacked on the actuation region; a frame having the fixing region of the inlet plate stacked thereon; a first plate having the frame stacked thereon, and an air intake chamber being formed between the frame and the first plate, the first plate having a plurality of first through holes; a second plate having the first plate stacked and fixed thereon, the first plate having a thickness greater than the second plate having a plurality of second through holes, the number, position, and diameter of each second through hole corresponding to each of the first through holes located on the first plate, wherein the bottom surface of the second plate has a recess of a depth formed by surface depression; A valve plate has a plurality of valve holes, which are respectively offset from the plurality of first through holes of the first plate and the plurality of second through holes of the second plate; and an outlet plate on which the second plate is stacked and maintained at a distance, wherein the valve plate is accommodated in a recess on the bottom surface of the second plate and can move up and down, and the outlet plate has a plurality of air outlet holes, which are corresponding to the valve holes.

6. The pneumatic pump system for a drone as described in claim 5, wherein the diameter of the valve port of the actuator is greater than or equal to the diameter of the air outlet port.

7. The piezoelectric pump aerodynamic system of the UAV as described in claim 5, when the piezoelectric element receives a drive signal that causes deformation, causing the actuation area of ​​the inlet plate to bend upward, the valve plate will be attracted upward and close the plurality of first through holes of the first plate and the plurality of second through holes of the second plate. At this time, fluid is drawn into the actuator body through the plurality of inlet holes. When the piezoelectric element receives a drive signal that causes deformation, causing the actuation area to bend downward, the fluid is transmitted downward through the plurality of first through holes of the first plate and the plurality of second through holes of the second plate and pushes the valve plate to displace, causing the valve plate to disengage from the plurality of first through holes of the first plate and the plurality of second through holes of the second plate and abut against the outlet plate. The valve plate opens the flow path, allowing gas to be output from the outlet hole.

8. The pneumatic pump aerodynamic system for a drone as claimed in claim 1, wherein a plurality of the pneumatic pumps are arranged in series to improve the overall airflow delivery capacity and generate efficient airflow in the airflow channel.

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