WO2022120796A1

WO2022120796A1 - Modular unmanned aerial vehicle and operation method therefor

Info

Publication number: WO2022120796A1
Application number: PCT/CN2020/135691
Authority: WO
Inventors: 刘以奋; 廖然
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2020-12-11
Filing date: 2020-12-11
Publication date: 2022-06-16
Also published as: CN114787032A

Abstract

A modular unmanned aerial vehicle, comprising: a fuselage (10); a high-voltage operation module (12) arranged on the fuselage; and a low-voltage operation module (14) arranged on the fuselage, wherein the working voltage of the high-voltage operation module is greater than the working voltage of the low-voltage operation module, and the high-voltage operation module and the low-voltage operation module are respectively connected to the fuselage in a quick-release connection manner. By means of modular design, the assembly process of the unmanned aerial vehicle can be simplified; and when accidents, such as a crash, occur to the unmanned aerial vehicle, a faulty module can be quickly removed so as to install a new one, such that the faulty module can be quickly replaced, and continuous operation of the unmanned aerial vehicle is ensured.

Description

Modular unmanned aerial vehicle and method of operation

technical field

The present disclosure relates to an unmanned aerial vehicle, and more particularly, to a modular unmanned aerial vehicle capable of separating low-voltage working parts and high-voltage working parts, and an operation method of the unmanned aerial vehicle.

Background technique

For the existing consumer UAVs, the strong electric parts such as power ESCs and the weak electric parts used for image signal processing are usually combined together. The advantage of this design is to simplify the design of the UAV. It is enough to connect each part according to the function. However, for some special-purpose unmanned aerial vehicles, such as the crossing aircraft, there is a greater risk of bombing during the flight mission. Once the aircraft is bombed during the flight, due to the strong electricity and The weak parts are integrated together, so it is easy to cause the weak parts and the strong electric parts to be damaged at the same time, thus making the damaged UAV difficult to repair, or even if it can be repaired, its maintenance cost is high, and sometimes even the whole is scrapped due to serious damage. As a result, the cost of using this special function unmanned aerial vehicle is greatly increased.

SUMMARY OF THE INVENTION

The present disclosure aims to solve at least one of the technical problems existing in the prior art.

A first aspect of the present disclosure provides a modular unmanned aerial vehicle comprising:

body;

a high-voltage operating module disposed on the fuselage; and

a low-voltage operating module arranged on the fuselage,

Wherein, the working voltage of the high-voltage operation module is greater than the working voltage of the low-voltage operation module, and the high-voltage operation module and the low-voltage operation module are respectively connected to the fuselage in a quick-release connection manner.

A second aspect of the present disclosure provides a modular unmanned aerial vehicle comprising:

body;

a high-voltage operating module disposed on the fuselage; and

a low-voltage operating module arranged on the fuselage,

Wherein, the working voltage of the high-voltage operation module is greater than the working voltage of the low-voltage operation module, the first one of the high-voltage operation module and the low-voltage operation module is connected to the body in a quick-release connection manner, and the A second of the high-voltage operating module and the low-voltage operating module is connected to the first of the high-voltage operating module and the low-voltage operating module in a quick release connection.

According to a third aspect of the present disclosure, there is provided an operation method of a modular unmanned aerial vehicle, the operation method comprising:

The detachable module is quickly detached from the fuselage of the unmanned aerial vehicle; wherein, the detachable module is a high-voltage operation module arranged on the fuselage or a low-voltage operation module arranged on the fuselage, The working voltage of the high-voltage operating module is greater than the working voltage of the low-voltage operating module, and the high-voltage operating module and the low-voltage operating module are respectively connected to the fuselage in a quick-release connection manner; and

Reinstall the replacement module to the fuselage of the UAV.

According to a fourth aspect of the present disclosure, there is provided an operation method of a modular unmanned aerial vehicle, the operation method comprising:

The detachable module is quickly detached from the fuselage of the unmanned aerial vehicle; wherein, the detachable module is a high-voltage operation module arranged on the fuselage or a low-voltage operation module arranged on the fuselage, The operating voltage of the high-voltage operating module is greater than the operating voltage of the low-voltage operating module, the first one of the high-voltage operating module and the low-voltage operating module is connected to the body in a quick-release connection manner, and the high-voltage operating module a second one of the module and the low voltage operating module is connected to the first one of the high voltage operating module and the low voltage operating module in a quick release connection; and

Reinstall the replacement module on the fuselage of the UAV.

The modular unmanned aerial vehicle according to the present disclosure makes the high-voltage operating components form a high-voltage operating module and the low-voltage operating components form a low-voltage operating module through a modular design, so that convenience can be provided during the assembly process of the unmanned aerial vehicle, that is, the modules can be combined The specially designed high-voltage operating module and low-voltage operating module are directly assembled to the fuselage of the unmanned aerial vehicle without the need to assemble each component separately. In addition, it is possible to provide appropriate protection for the high-voltage operating module and/or the low-voltage operating module during the flight of the unmanned aerial vehicle, so that the unfailed module can be removed from the unmanned aerial vehicle after an accident such as a bombing of the unmanned aerial vehicle. Quickly detach from the body and form a new UAV with the new components provided to continue the flight mission; or the failed module can be quickly detached from the fuselage of the UAV and utilize the new corresponding The replacement module is replaced so that the unmanned aerial vehicle can continue to perform the flight mission. Therefore, the maintenance time of the unmanned aerial vehicle can be saved, and the components of the unmanned aerial vehicle can be fully utilized, which facilitates the continuous execution of the flight mission.

Description of drawings

FIG. 1A is a schematic structural diagram of a first embodiment of a modular unmanned aerial vehicle according to the present disclosure.

FIG. 1B is a schematic structural diagram of a variant of the first embodiment of the modular unmanned aerial vehicle according to the present disclosure.

FIG. 2 is a schematic structural diagram of a second embodiment of the modular unmanned aerial vehicle according to the present disclosure.

3 is a flowchart of a first embodiment of a method of operating a modular unmanned aerial vehicle according to the present disclosure.

4 is a flowchart of a second embodiment of a method of operating a modular unmanned aerial vehicle according to the present disclosure.

Description of reference numbers:

100: Modular UAV; 10: Fuselage; 102: Shell; 12: High Voltage Operation Module; 122: Battery; 124: Arm; 126: Motor; 128: Rotor; 130: ESC; 14: Low Voltage Operation module; 142: controller; 144: main circuit board; 146: built-in sensor; 148: camera device; 150: external sensor;

200: Modular UAV; 20: Fuselage; 202: Shell; 22: High Voltage Operation Module; 222: Battery; 224: Arm; 226: Motor; 228: Rotor; 230: ESC; 24: Low Voltage Operation module; 242: controller; 244: main circuit board; 246: built-in sensor; 248: camera device; 250: external sensor.

Detailed ways

Embodiments of the present disclosure are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present disclosure, but should not be construed as a limitation of the present disclosure.

In the description of the present disclosure, it should be understood that the terms "first" and "second" are only used for description purposes, and cannot be interpreted as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Thus, features defined as "first", "second" may expressly or implicitly include one or more of said features. In the description of the present disclosure, "plurality" means two or more, unless expressly and specifically defined otherwise.

In the description of the present disclosure, it should be noted that the terms "installed", "connected" and "connected" should be understood in a broad sense, unless otherwise expressly specified and limited, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; it can be a mechanical connection, an electrical connection or can communicate with each other; it can be directly connected or indirectly connected through an intermediate medium, it can be the internal communication of two elements or the interaction of two elements relation. For those of ordinary skill in the art, the specific meanings of the above terms in the present disclosure can be understood according to specific situations.

The following disclosure provides many different embodiments or examples for implementing different structures of the present disclosure. In order to simplify the disclosure of the present disclosure, the components and arrangements of specific examples are described below. Of course, they are only examples and are not intended to limit the present disclosure. Furthermore, the present disclosure may repeat reference numerals and/or reference letters in different instances for the purpose of simplicity and clarity and not in itself indicative of a relationship between the various embodiments and/or arrangements discussed. In addition, the present disclosure provides examples of various specific processes and materials, but one of ordinary skill in the art will recognize the application of other processes and/or the use of other materials.

The present disclosure provides a modular unmanned aerial vehicle 100. The modular unmanned aerial vehicle 100 can separate the parts that are greatly affected by the bombing and the parts that are not easily damaged during the flight of the unmanned aerial vehicle. During the use of the unmanned aerial vehicle, the damaged parts are quickly replaced, so as to quickly restore the normal use state of the unmanned aerial vehicle 100, so that the unmanned aerial vehicle 100 can be quickly restored after the explosion, so as to quickly resume the flight, and the unmanned aerial vehicle 100 can be quickly restored. The impact of bombing during flight is minimized. In addition, the modular unmanned aerial vehicle 100 according to the present disclosure can improve the assembly efficiency of the unmanned aerial vehicle 100 through the modular design, so that the permanent fixed connection that originally needs to be realized by welding or the like can be assembled by means of quick plugging, thereby The assembly efficiency of the unmanned aerial vehicle 100 can be improved.

The structure of the first embodiment of the modular unmanned aerial vehicle 100 according to the present disclosure will be described in detail below with reference to FIG. 1A . The unmanned aerial vehicle 100 according to the present disclosure includes a fuselage 10 , a high-voltage operating module 12 disposed on the fuselage 10 , and a low-voltage operating module 14 disposed on the fuselage 10 , wherein the operating voltage of the high-voltage operating module 12 is greater than that of the low-voltage operating module 14, the high-voltage operating module 12 and the low-voltage operating module 14 are respectively connected to the fuselage 10 in a quick-release connection manner. Here, the components of the unmanned aerial vehicle 100 are divided into a high-voltage operation module 12 and a low-voltage operation module 14, and the high-pressure operation module 12 and the low-voltage operation module 14 are respectively arranged on the fuselage 10 of the unmanned aerial vehicle 100 in a quick detachable manner. Therefore, the low-voltage operation module with high cost can be well protected during the explosion of the UAV 100, and the relevant flight data of the UAV 100 can be saved through the circuit board or the storage device as the low-voltage operation module 14. , in order to continue to perform subsequent flight operations to ensure the continuity of the flight process.

Further, the high voltage operating module 12 of the modular UAV 100 may be located at least partially outside the housing 102 of the fuselage 10 . That is, the high-voltage operation module 12 may include several components, some of which may be disposed outside the casing 102 of the fuselage 10 , and correspondingly, another part of which may be disposed inside the casing 102 of the fuselage 10 . . Here, for the sake of facilitating the structural design of the UAV 100 , some high-voltage operating components are arranged outside the casing 102 , while another part of the high-voltage operating components can be arranged inside the casing 102 of the fuselage 10 . Of course, the high-voltage operation module 12 can also be disposed on the outside of the casing 102 of the fuselage 10 as a whole.

Similarly, the low pressure operating module 14 is located at least partially inside the housing 102 of the fuselage 10 . That is to say, the low-voltage operation module 14 may also include several components, some of which may be arranged inside the casing 102 of the fuselage 10 , and correspondingly, another part of the components may be arranged inside the casing 102 of the fuselage 10 . external. Here, except for some components that must be arranged outside the casing 102 of the fuselage 10, the rest of the components in the low-voltage operation module 14 can be arranged inside the casing 102 of the fuselage 10, so that the 10 provides a sturdy housing 102 to provide safety protection for the low-voltage operating components disposed within the fuselage 10 to prevent damage to the relevant low-voltage operating components during the explosion of the unmanned aerial vehicle 100 .

Here, the low-voltage operation module 14 may be accommodated in the casing 102 of the body 10 . That is to say, the low-voltage operation module 14 can be accommodated in the interior of the housing 102 of the fuselage 10 as a whole, thereby providing safety protection for the low-voltage operation module through the solid housing 102, preventing or reducing the unmanned aerial vehicle as much as possible. 100 Damage to low voltage operating modules in the event of a bombing during flight. It should be noted here that the working voltage or output voltage of the high-voltage operation module is greater than or equal to 10 volts, while the working voltage or output voltage of the low-voltage operation module is less than 10 volts. That is to say, the voltages of 10 volts and above are referred to as high voltages, and the voltages below 10 volts are referred to as low voltages. The high-voltage operation module may generally include the power system of the UAV 100 and related components that carry the power system, such as the propeller of the UAV 100, the motor that drives the propeller, the battery that supplies power to the motor, and the arms that carry the motor and the propeller. These components generally require higher operating voltages during the flight of the UAV 100 , and thus these components are also referred to as high-power parts of the UAV 100 . The low-voltage operation module may generally include components such as the controller of the UAV 100, the main circuit board, and various sensors including the camera equipment. These components usually require a lower operating voltage during the flight of the UAV 100, so These components are also referred to as the weak current parts of the UAV 100 .

The high-voltage operating module 12 and the low-voltage operating module 14 may be detachably connected to the fuselage 10 through a mechanical coupling mechanism, respectively. That is to say, both the high-voltage operating module 12 and the low-voltage operating module 14 can be installed on the fuselage 10 in a quick and detachable manner through the mechanical coupling mechanism, so that the high-voltage operating module 12 and the low-voltage operating module 14 can be installed when required. In the case of disassembly or replacement, the high-pressure operation module 12 and the low-pressure operation module 14 can be quickly operated. In the embodiment of the present disclosure, the mechanical coupling mechanism may include a locking mechanism or a sliding guide mechanism, and of course, other quick connection mechanisms may also be included herein. The high pressure operation module 12 and/or the low pressure operation module 14 are detachably connected to the body 10 through a locking mechanism; alternatively, the high pressure operation module 12 and/or the low pressure operation module 14 are slidably connected to the body 10 through a sliding guide mechanism. That is, at least one of the high-voltage operating module 12 and the low-voltage operating module 14 can be detachably connected to the body 10 through a locking mechanism, and the high-voltage operating module 12 and/or the low-voltage operating module 12 and/or the low-voltage can be removed from the body 10 when required. When operating the module 14, the locking mechanism can be quickly unlocked, so that the high-voltage operating module 12 and/or the low-voltage operating module 14 can be quickly separated from the fuselage 10, and the high-voltage operating module 12 and/or the low-voltage operating module 14 can be installed to the machine when required. When mounted on the body 10, the high pressure operating module 12 and/or the low pressure operating module 14 can be set in place, and then the high pressure operating module 12 and/or the low pressure operating module 14 can be securely locked on the body 10 by locking the locking mechanism. Alternatively, at least one of the high pressure operating module 12 and the low pressure operating module 14 may be detachably connected to the fuselage 10 through a sliding guide mechanism, ie, the high pressure operating module 12 and/or the low pressure operating module 12 may need to be detached from the fuselage 10 When the module 14 is installed, the high pressure operating module 12 and/or the low pressure operating module 14 can be slid relative to the fuselage 10 until the high pressure operating module 12 and/or the low pressure operating module 14 are separated from the fuselage 10 . When the high-voltage operating module 12 and/or the low-voltage operating module 14 needs to be installed on the fuselage 10, the high-voltage operating module 12 and/or the low-voltage operating module 14 can be aligned with the fuselage 10 through the sliding guide mechanism, and the high-voltage operating module 14 can be aligned with the fuselage 10. The operating module 12 and/or the low-voltage operating module 14 slides relative to the fuselage 10 along the sliding guide mechanism until the high-voltage operating module 12 and/or the low-voltage operating module 14 slides into place relative to the fuselage 10, whereby the high-voltage operating module 12 And/or the low voltage operating module 14 is securely arranged on the fuselage 10 .

Here, the locking mechanism may include at least one of the following mechanisms: snaps, threaded fasteners, latches, and Velcro. Of course, the locking mechanism can also adopt other mechanisms than the above-mentioned mechanisms, as long as the high-voltage operation module 12 and/or the low-voltage operation module 14 can be quickly locked to the body 10, and the high-voltage operation module can be quickly removed from the body 10. Module 12 and/or low voltage operating module 14 suffice. The sliding guide mechanism may include at least one of the following mechanisms: a sliding rail, a sliding groove, a guide rod, and a sliding block. Correspondingly, the sliding guide mechanism may also include other types of mechanisms other than the above-mentioned mechanisms, as long as the high-pressure operation module 12 and/or the low-pressure operation module 14 can be quickly installed to the body 10 in a sliding manner, and can be removed from the body 10 in a sliding manner. The high-voltage operation module 12 and/or the low-voltage operation module 14 can be quickly disassembled from the body 10 .

After the high-voltage operating module 12 and the low-voltage operating module 14 are mounted on the airframe 10, the high-voltage operating module 12 and the low-voltage operating module 14 are electrically connected to each other with an electrical coupling mechanism. That is to say, after the high-voltage operation module 12 and the low-voltage operation module 14 are mechanically connected to the fuselage 10, the electrical connection between the high-voltage operation module 12 and the low-voltage operation module 14 is realized, so as to realize the signal connection between the two. and/or power connection. The electrical coupling mechanism described herein may include at least one of the following electrical connection mechanisms: a male electrical connector and a female electrical connector that cooperate with each other, and an electromagnetic coil that is electrically coupled to each other. That is to say, the electrical connection between the high-voltage operation module 12 and the low-voltage operation module 14 can be realized through a mechanical electrical coupling mechanism, and the electrical connection between the two can also be realized through an electromagnetic electrical coupling mechanism.

Further, the high-voltage operation module 12 can be divided into a first high-voltage operation component and a second high-voltage operation component, and the high-voltage operation module 12 can include a first high-voltage operation component disposed inside the fuselage 10 of the unmanned aerial vehicle 100 and a set of unmanned aerial vehicles. A second high pressure operating assembly external to the fuselage 10 of the 100 . That is to say, a part of the components in the high-voltage operation module 12 (this part of the components constitute the first high-voltage operation assembly) is disposed inside the fuselage 10 of the unmanned aerial vehicle 100 , and another part of the components in the high-voltage operation module 14 (the other part of the components constitute A second high voltage operating assembly) is provided outside the fuselage 10 of the unmanned aerial vehicle 100 . Here, the high-voltage operation module 12 is divided into a first high-voltage operation component disposed inside the fuselage 10 and a second high-voltage operation component disposed outside the fuselage 10 , the main purpose of which is to improve the convenience of the structural design of the UAV 100 Therefore, the high-voltage operating components that need to be arranged outside the fuselage 10 are arranged on the outside of the fuselage 10 . Here, the first high pressure operating assembly and/or the second high pressure operating assembly may be connected to the fuselage 10 by a mechanical coupling mechanism. The mechanical coupling mechanism here is the above-mentioned mechanical coupling mechanism including the locking mechanism or the sliding guide mechanism, as long as it can realize the quick disassembly and assembly of the first high-voltage operating assembly and/or the second high-voltage operating assembly and the fuselage 10 , namely Can.

Here, in particular, the first high-voltage operating component provided inside the fuselage 10 of the unmanned aerial vehicle 100 may include a battery 122 for supplying power to the unmanned aerial vehicle 100 . Of course, the first high-voltage operating assembly may also include other high-voltage operating components of the UAV 100 . The battery 122 usually needs to be protected. Therefore, the battery 122 needs to be arranged inside the casing 102 of the fuselage 10 to provide a certain degree of protection for the battery 122 , and at the same time, the battery 122 should be arranged inside the casing 102 of the fuselage 10 . It can also provide reliable support for the battery 122 .

In this case, the second high-voltage operating component disposed outside the fuselage 10 may include the arm 124 of the UAV 100, the motor 126 disposed on the arm 124, the rotor 128 disposed on the motor 126, and the ESC 130 on arm 124. That is to say, the other components except the battery 122 in the high voltage operation module 12 are basically arranged outside the casing of the fuselage 10 . Of course, there may also be other high-voltage operating components not listed here, which may be disposed inside or outside the casing of the fuselage 10 according to the convenience of the structural design of the UAV 100 .

Further, the first high-voltage operating component disposed inside the housing 102 of the fuselage 10 may include a battery 122 for supplying power to the UAV 100 and an electrical regulator 130 for adjusting the motor 126 of the UAV 100, namely Both the battery 122 and the ESC 130 are provided inside the casing 102 of the main body 10, as shown in FIG. 1B, which may be a variation of the first embodiment according to the present disclosure. Correspondingly, the second high voltage operating assembly disposed on the exterior of the housing 102 of the fuselage 10 may include the arm 124 of the UAV 100, the motor 126 disposed on the arm 124, and the rotor 128 disposed on the motor 126. That is to say, the ESC 130 can be disposed on the arm 124 of the UAV 100 along with the motor 126 , that is, disposed outside the casing 102 of the fuselage 10 , or can also be disposed on the casing 102 of the fuselage 10 . Internally, the battery 122 can here be arranged as part of the first high-voltage operating assembly inside the housing 102 of the fuselage 10 .

As the high-voltage operation module 12 of the unmanned aerial vehicle 100 , it can be divided into a first high-voltage operation component disposed inside the casing 102 of the fuselage 10 and a second high-voltage operation component disposed outside the casing 102 of the fuselage 10 , the first high-voltage operating component disposed in the housing 102 of the fuselage 10 can be protected by the housing 102, so that the second high-voltage can be ensured as far as possible in the event of an explosion during the flight of the unmanned aerial vehicle 100 Safety of the operating assembly so that the second high voltage operating assembly can be reused when repairing or replacing the UAV 100 . For example, when the unmanned aerial vehicle 100 hits an obstacle and is in a bombing state during flight, the rotor 128 , the arm 124 or the motor 126 of the unmanned aerial vehicle 100 may be damaged, if only the rotor 128 is damaged If damaged, the UAV 10 can be repaired by replacing the rotor 128 . However, when the UAV 10 is seriously damaged, for example, the rotor 128, the arm 124 and/or the motor 126 are damaged, and the UAV 100 cannot continue to fly through simple repair, at this time, the UAV 100 can be set on the fuselage 10. The first high-voltage operating assembly in the housing 102 is quickly disassembled from the main body 10, for example, the battery 122 or the first high-voltage operating assembly composed of the battery 122 and the ESC 130 is quickly disassembled from the main body 10, and a new one is prepared in advance. The intact fuselage 10, for example, the fuselage 10 may include the fully installed arm 124, the motor 126 and the rotor 128, and the disassembled first high-voltage operation component is quickly installed on the fuselage 10, which can realize unmanned operation. Rapid repair of the aircraft 100 so that the unmanned aircraft 100 can continue the subsequent flight mission. Thereby, reuse of the components of the unmanned aerial vehicle 100 is achieved, and rapid assembly of the unmanned aerial vehicle 100 can be achieved. Alternatively, if a component disposed inside the fuselage 10 fails or is damaged during the flight, the UAV 100 can be quickly repaired by replacing the corresponding module or component with a replacement module or component.

Similarly, low pressure operating module 14 may include a first low pressure operating assembly disposed within fuselage 10 of unmanned aerial vehicle 100 and a second low pressure operating assembly disposed outside fuselage 10 of unmanned aircraft 100 . That is to say, the low-voltage operating module 14 can be divided into two parts, namely, the first low-voltage operating assembly and the second low-voltage operating assembly, wherein the first low-voltage operating assembly is arranged inside the fuselage 10 of the unmanned aerial vehicle 100 , corresponding to Ground, the second low-voltage operating assembly is provided outside the fuselage 10 of the UAV 100 . The low-voltage operation module 14 is arranged to include a first low-voltage operation component and a second low-voltage operation component, the purpose of which is to facilitate the overall structural design of the unmanned aerial vehicle 100 and to facilitate the arrangement of the low-voltage operation components inside the fuselage 10 of the unmanned aerial vehicle 100 The low-voltage operating components that are inconvenient to be arranged inside the fuselage 10 of the unmanned aerial vehicle 100 are arranged outside the fuselage 10 .

The first low pressure operating assembly and/or the second low pressure operating assembly are connected to the fuselage 10 through a mechanical coupling mechanism, where the first low pressure operating assembly and the second low pressure operating assembly may be formed as separate assemblies, respectively, and mechanically coupled The mechanism is connected to the fuselage 10, and the first low-voltage operating assembly and the second low-voltage operating assembly can also be provided as an integral structure. For example, the first low-voltage operating assembly disposed in the fuselage 10 can be connected to the body 10 , and the second low-voltage operating assembly is protruded from the body 10 through a window provided in the body 10 , so that the second low-voltage operating assembly is arranged outside the body 10 . The mechanical coupling mechanism here can also be a mechanical coupling mechanism for connecting the first high-voltage operating assembly and/or the second high-voltage operating assembly and the fuselage 10 .

Specifically, the first low voltage operating assembly may include a controller 142 for controlling the UAV, a main circuit board 144 and built-in sensors 146 . Here, the controller 142 for controlling the unmanned aerial vehicle is the flight controller of the unmanned aerial vehicle 100, the main circuit board 144 is the circuit board on which the control circuit and related electronic components of the unmanned aerial vehicle are arranged, and the built-in sensor 146 is mainly Including inertial measurement unit, barometer, magnetic compass, gyroscope and other components. Further, the second low-voltage operation assembly may include a camera device 148 and an external sensor 150 . The camera device 148 is, for example, a camera provided on a PTZ, and the external sensor 150 is, for example, an external compass.

Here, the low-voltage operating module is divided into a first low-voltage operating component disposed inside the body 10 and a second low-voltage operating component disposed outside the fuselage 10 , which can be paired with the casing 102 of the fuselage 10 . The first low-voltage operating component inside 10 provides reliable protection to prevent damage to the first low-voltage operating component when the unmanned aerial vehicle 10 explodes during flight, so as to ensure the integrity of the first low-voltage operating component as much as possible and security. Here, the first low-voltage operating assembly includes, for example, a controller 142 , a main circuit board 144 and a built-in sensor 146 . After a bombing situation occurs, the first low-voltage operating assembly can be quickly detached from the interior of the housing 102 of the fuselage 10 and quickly installed to the fuselage 10 of a new UAV 100 prepared in advance, such as this Airframe 10 may include fully installed arms 124 , motors 126 and rotors 128 . By quickly installing the disassembled first low-voltage operation component on the fuselage 10, the UAV 100 can be quickly repaired, so that the UAV 100 can continue to perform subsequent flight missions. Here, it can be quickly installed on the provided new fuselage 10 together with the first high-voltage operating assembly that is quickly detached from the fuselage 10 of the UAV 100 as described above. Thereby, reuse of the components of the unmanned aerial vehicle 100 is achieved, and rapid assembly of the unmanned aerial vehicle 100 can be achieved. In addition, since the relevant flight data of the UAV 100 during the execution of the flight mission is stored in the memory on the main circuit board 144, the flight data of the UAV 100 can be directly migrated to the main circuit board 144 by replacing the first low-voltage operation component. The newly assembled unmanned aerial vehicle 100 can enable the unmanned aerial vehicle 100 to continuously perform its flight mission after the explosion occurs.

The second embodiment according to the present disclosure will be described below with reference to FIG. 2 . In this embodiment, most of the structure of the unmanned aerial vehicle 200 is the same as that of the unmanned aerial vehicle 100 described above, which will not be repeated here. 100 differences are explained. The difference between the unmanned aerial vehicle 200 according to the second embodiment of the present disclosure and the unmanned aerial vehicle 100 of the first embodiment mainly lies in the connection relationship between the high-voltage operation module and the low-voltage operation module and the fuselage.

The unmanned aerial vehicle 200 according to the second embodiment of the present disclosure includes a fuselage 20 , a high-voltage operating module 22 provided on the fuselage 20 , and a low-voltage operating module 24 provided on the fuselage 20 , wherein the operation of the high-voltage operating module 22 The voltage is greater than the working voltage of the low-voltage operating module, the first one of the high-voltage operating module 22 and the low-voltage operating module 24 is connected to the fuselage 20 in a quick-release connection, and the second one of the high-voltage operating module 22 and the low-voltage operating module 24 is fast Detachable connection is made to the first one of the high-voltage operating module 22 and the low-voltage operating module 24 . For example, in the embodiment shown in FIG. 2 , the high-voltage operation module 22 is connected to the fuselage 20 in a manner capable of quick connection, so as to facilitate the rapid installation or rapid disassembly of the high-voltage operation module 22 and the fuselage 20, and the low-voltage operation The module 24 can be installed to the high-voltage operating module 22 in a quick-connect manner, thereby enabling quick installation or quick disassembly between the low-voltage operating module 24 and the high-voltage operating module 22 . Of course, the low-voltage operation module 24 can also be connected to the fuselage 20 in a way that can be quickly connected, so that the low-voltage operation module 24 can be quickly installed or disassembled from the fuselage 20, and the high-voltage operation module 22 can be quickly connected. Installed to the low pressure operating module 24 , thereby enabling quick installation or quick disassembly between the high pressure operating module 22 and the low pressure operating module 24 . Since the high-voltage operation module 22 and the low-voltage operation module 24 only need to be quickly installed or removed to be quickly installed or removed from the high-voltage operation module 22 and the low-voltage operation module 24 to be quickly installed or removed from the fuselage 20, it can be further improved. The disassembly and assembly efficiency of the two modules. If the unmanned aerial vehicle 200 according to the second embodiment of the present disclosure is bombed, the high-voltage operation module 22 or the low-voltage operation module 24 that is quickly detachable from the fuselage 20 can be directly detached from the fuselage 20 , thereby The high-voltage operating module 22 and the low-voltage operating module 24 can be quickly disassembled at the same time, so that the UAV 200 can be reassembled by using the high-voltage operating module 22 and the low-voltage operating module 24 that are quickly disassembled, so as to realize the subsequent flight after the UAV 200 explodes.

Here, the first one of the high-voltage operating module 22 and the low-voltage operating module 24 is detachably connected to the fuselage 20 through a mechanical coupling mechanism. Then, the second one of the high-voltage operating module 22 and the low-voltage operating module 24 can also be mechanically connected to the first of them by a mechanical coupling mechanism, that is, the high-voltage operating module 22 and the low-voltage operating module 24 are mechanically connected to each other by a mechanical coupling mechanism . In this way, in the event of damage to either of the high-voltage operating module 22 and the low-voltage operating module 24, the two can be quickly separated by a mechanical coupling mechanism therebetween, so that the module that remains functionally intact can be reused.

In the second embodiment, the mechanical coupling mechanism may also include a locking mechanism or a sliding guide mechanism as described above. The high-voltage operation module 22 or the low-voltage operation module 24 and the fuselage 20 of the UAV 200 can be quickly connected by a locking mechanism or a sliding guide mechanism, and further, the high-voltage operation module 22 and the low-voltage operation module 24 can also be connected by using The locking mechanism or the sliding guide mechanism is used for quick connection, and the mechanical coupling mechanism between the high-voltage operating module 22 or the low-voltage operating module 24 and the fuselage 20 of the UAV 200 can be mechanically coupled between the high-voltage operating module 22 and the low-voltage operating module 24 The organization is the same, or it can be different. The locking mechanism may include at least one of snaps, threaded fasteners, latches, and Velcro. The sliding guide mechanism may include at least one of a sliding rail, a sliding groove, a guide rod, and a sliding block.

Further, the high voltage operating module 22 and the low voltage operating module 24 may be electrically connected to each other through an electrical coupling mechanism. Here, the electrical coupling mechanism between the high-voltage operating module 22 and the low-voltage operating module 24 may be integrally formed with the mechanical coupling mechanism therebetween, or may be formed independently. In the case where the electrical coupling mechanism between the high-voltage operating module 22 and the low-voltage operating module 24 is integrally formed with the mechanical coupling mechanism therebetween, in the case where the mechanical coupling mechanism is used to couple the high-voltage operating module 22 and the low-voltage operating module 24 together At the same time, the electrical coupling between the two is also realized. Of course, a separate electrical coupling mechanism may also be provided between the high-voltage operating module 22 and the low-voltage operating module 24 . The electrical coupling mechanism herein may include at least one of a mutually mating male electrical connector and a female electrical connector and an electromagnetic coil that is electrically coupled to each other.

In the second embodiment of the present disclosure, the high-voltage operating module 22 may also include a first high-voltage operating component disposed inside the fuselage 20 of the UAV 200 and a second high-voltage operating component disposed outside the fuselage 20 of the UAV 200 Operating components. At this time, the first high-voltage operating assembly and/or the second high-voltage operating assembly may be connected to the fuselage 20 through a mechanical coupling mechanism. The components of the unmanned aerial vehicle 200 included in the first high-voltage operation assembly and the second high-voltage operation assembly are substantially the same as those of the unmanned aerial vehicle 100 in the first embodiment. For example, the first high voltage operating assembly may include a battery 222 for powering the unmanned aerial vehicle 200 . The second high-voltage operating assembly may include an arm 224 of the UAV 200 , a motor 226 disposed on the arm 224 , a rotor 228 disposed on the motor 226 , and an electric regulator 230 disposed on the arm 224 . Correspondingly, the ESC 230 may also be disposed inside the fuselage 20 of the UAV 200 , that is, the first high-voltage operation component may include a battery 222 for supplying power to the UAV 200 and a battery for regulating the UAV 200 . ESC 230 for motor 226 . At this time, the second high-voltage operation assembly may include the arm 224 of the UAV 200 , the motor 226 provided on the arm 224 , and the rotor 228 provided on the motor 226 .

Similarly, the low pressure operating module 24 may also include a first low pressure operating assembly disposed within the fuselage 20 of the unmanned aerial vehicle 200 and a second low pressure operating assembly disposed outside the fuselage 20 of the unmanned aircraft 200. The first low pressure operating assembly and/or the second low pressure operating assembly are connected to the fuselage 20 by a mechanical coupling mechanism. For example, the first high-pressure operation component disposed in the body 20 may be connected to the body 20 through a mechanical coupling mechanism, while the first low-voltage operation component disposed in the body 20 may be connected to the first high-pressure operation through a mechanical coupling mechanism The first high-pressure operation assembly and the first low-pressure operation assembly are quickly disassembled and detached from the fuselage 20, so that the first high-pressure operation assembly and the first low-pressure operation assembly can be easily removed from the fuselage 20. And quickly install it on the new fuselage 20. Similarly, the first low pressure operating assembly may also be connected to the fuselage 20 through a mechanical coupling mechanism, while the first high pressure operating assembly may be connected to the first low pressure operating assembly through a mechanical coupling mechanism. The components of the unmanned aerial vehicle 200 included in the first low pressure operation assembly and the second low pressure operation assembly are substantially the same as those of the unmanned aerial vehicle 100 in the first embodiment. For example, the first low voltage operating assembly may include a controller 242 for controlling the UAV, a main circuit board 244 and built-in sensors 246 . The second low voltage operating assembly may include a camera 248 and an external sensor 250 .

Further, the present disclosure also relates to an operation method of a modular unmanned aerial vehicle. As shown in FIG. 3 , the operation method includes the following steps: S1, quickly dismounting the detachable module from the fuselage of the unmanned aerial vehicle; wherein , the detachable module is a high-voltage operation module arranged on the fuselage or a low-voltage operation module arranged on the fuselage, the working voltage of the high-voltage operation module is greater than the working voltage of the low-voltage operation module, and the high-voltage operation module and the low-voltage operation module are respectively connected to the fuselage in a quick-release connection manner; and, S2, re-installing the replacement module to the fuselage of the unmanned aerial vehicle.

By quickly detaching the detachable modules in the high-voltage operating module and the low-voltage operating module connected to the fuselage in a quick-release manner from the fuselage of the UAV, and then replacing the detachable module with an intact replacement module, and The replacement module can be quickly installed on the fuselage, thereby realizing the rapid replacement of the detachable module of the unmanned aerial vehicle, so that the flight function of the unmanned aerial vehicle can be quickly restored, the maintenance cycle of the unmanned aerial vehicle is shortened, and it is convenient for unmanned aerial vehicles. The rapid elimination of the faults caused by the accident during the flight of the aircraft, and the restoration of the flight function of the unmanned aircraft in the shortest possible time.

In an embodiment of the method of operation of a modular unmanned aerial vehicle according to the present disclosure, the high voltage operation module is located at least partially outside the shell of the fuselage. Alternatively, the high-voltage operation module is disposed outside the casing of the fuselage. That is, at least a part or all of the high-voltage operating module may be arranged outside the casing of the fuselage, that is, the high-voltage operating module may have components arranged inside the casing of the fuselage.

Further, the low-voltage operating module is located at least partially inside the casing of the fuselage. Alternatively, the low-voltage operating module may be housed inside the casing of the body. That is, at least a part or all of the low-voltage operating module may be provided inside the housing of the fuselage, i.e., the low-voltage operating module may have components provided outside the housing of the fuselage.

Here, the operating voltage or output voltage of the high-voltage operating module is greater than or equal to 10 volts. The operating or output voltage of the low-voltage operating module is less than 10 volts. It should be noted that the difference between high voltage and low voltage is not completely limited to 10 volts, and may be determined according to the actual working voltage of each working component of the unmanned aerial vehicle 100 . Of course, the modules of the UAV can also be further subdivided, for example, they can be divided into high-voltage operation modules, medium-voltage operation modules and low-voltage operation modules, or can be divided into more operation modules.

The high-voltage operating module and the low-voltage operating module may be detachably connected to the fuselage through a mechanical coupling mechanism, respectively. The mechanical coupling mechanism may include a locking mechanism or a sliding guide mechanism, wherein the high-voltage operating module and/or the low-voltage operating module can be detachably connected to the body through the locking mechanism; or, the high-voltage operating module and/or the low-voltage operating module It can be slidably connected with the fuselage through a sliding guide mechanism. Specifically, the locking mechanism may include at least one of the following: a buckle, a threaded fastener, a latch, and a Velcro. The sliding guide mechanism includes at least one of the following: a sliding rail, a sliding groove, a guide rod, and a sliding block. In the case where the high-voltage operation module and the low-voltage operation module are mechanically coupled to the fuselage through a mechanical coupling mechanism, the high-voltage operation module and the low-voltage operation module are electrically connected to each other by an electrical coupling mechanism, and the electrical coupling mechanism includes at least one of the following: The male electrical connector and the female electrical connector are electromagnetic coils that are electrically coupled to each other.

Further, the high-voltage operating module includes a first high-voltage operating assembly disposed within the fuselage of the UAV and a second high-voltage operating assembly disposed outside the fuselage of the UAV. The first high pressure operating assembly and/or the second high pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism. Here, the first high-voltage operation assembly may include a battery for supplying power to the unmanned aerial vehicle; meanwhile, the second high-voltage operation assembly includes an arm of the unmanned aerial vehicle, a motor disposed on the arm, a The rotor on the motor and the ESC arranged on the arm. In another case, the first high-voltage operating assembly includes a battery for supplying power to the unmanned aerial vehicle and an electrical regulator for regulating the motor of the unmanned aerial vehicle; in this case, the second high-voltage operating assembly includes all the The arm of the unmanned aerial vehicle, the motor arranged on the arm, and the rotor arranged on the motor.

The low pressure operating module includes a first low pressure operating assembly disposed within the fuselage of the unmanned aerial vehicle and a second low pressure operating assembly disposed outside the fuselage of the unmanned aerial vehicle. The first low pressure operating assembly and/or the second low pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism. The first low voltage operating assembly includes a controller for controlling the UAV, a main circuit board, and built-in sensors. Accordingly, the second low-voltage operating assembly includes a camera and an external sensor.

The embodiment of the present disclosure also relates to an operation method of a modular unmanned aerial vehicle. As shown in FIG. 4 , the operation method includes the following steps: S1, quickly dismounting the detachable module from the fuselage of the unmanned aerial vehicle ; Wherein, the detachable module is a high-voltage operation module arranged on the fuselage or a low-voltage operation module arranged on the fuselage, and the working voltage of the high-voltage operation module is greater than the working voltage of the low-voltage operation module , the first one of the high-voltage operating module and the low-voltage operating module is connected to the fuselage by a quick-release connection, and the second of the high-voltage operating module and the low-voltage operating module is connected by a quick-release connection connecting to a first of the high pressure operating module and the low pressure operating module; and, S2, reinstalling a replacement module to the fuselage of the UAV.

In this embodiment of the operating method of the modular unmanned aerial vehicle according to the present disclosure, the high-voltage operating module or the low-voltage operating module can be detached from the fuselage of the unmanned aerial vehicle or quickly installed in a quick release connection. The fuselage can realize the rapid installation or disassembly of the high-voltage operation module or the low-voltage operation module and the fuselage, and at the same time, the high-voltage operation module and the low-voltage operation module can be quickly connected by means of the quick-release connection between the high-voltage operation module and the low-voltage operation module. Assembly or quick disassembly, which enables quick replacement of damaged high-voltage and low-voltage operating modules, or quick disassembly of undamaged high-voltage and low-voltage operating modules so that they can be quickly installed on the fuselage for reuse .

In this embodiment, the high-voltage operating module is located at least partially outside the housing of the fuselage; alternatively, the high-voltage operating module is provided outside the housing of the fuselage. The low-voltage operating module is at least partially located inside the casing of the fuselage; or, the low-voltage operating module is accommodated inside the casing of the fuselage. Similar to the above embodiments, the working voltage or output voltage of the high-voltage operation module is greater than or equal to 10 volts; the working voltage or output voltage of the low-voltage operation module is less than 10 volts.

Further, the first one of the high-voltage operating module and the low-voltage operating module is detachably connected to the fuselage through a mechanical coupling mechanism. The high-voltage operating module and the low-voltage operating module are mechanically connected to each other by a mechanical coupling mechanism. Thereby, the fast mechanical connection between the high-voltage operation module or the low-voltage operation module and the fuselage is realized, and at the same time, the fast mechanical connection between the high-voltage operation module and the low-voltage operation module is realized. Here, the mechanical coupling mechanism includes a locking mechanism or a sliding guide mechanism. The locking mechanism includes at least one of the following: a buckle, a threaded fastener, a latch, and a Velcro. The sliding guide mechanism includes at least one of the following: a sliding rail, a sliding groove, a guide rod, and a sliding block.

After the mechanical coupling between the high-voltage operating module and the low-voltage operating module is achieved, the high-voltage operating module and the low-voltage operating module are electrically connected to each other through an electrical coupling mechanism, that is, a mechanical coupling relationship exists between the high-voltage operating module and the low-voltage operating module , there is also an electrical coupling relationship. The electrical coupling mechanism includes at least one of the following: a male electrical connector and a female electrical connector that cooperate with each other, and an electromagnetic coil that is electrically coupled to each other.

According to the operating method of the modular unmanned aerial vehicle of the present disclosure, the high-voltage operating module includes a first high-voltage operating assembly disposed within the fuselage of the unmanned aerial vehicle and a second high-voltage operating assembly disposed outside the fuselage of the unmanned aerial vehicle High pressure operating components. The first high pressure operating assembly and/or the second high pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism. The first high-voltage operation assembly includes a battery for supplying power to the unmanned aerial vehicle; the second high-voltage operation assembly includes an arm of the unmanned aerial vehicle, a motor disposed on the arm, a The rotor on the motor and the ESC arranged on the arm. In another embodiment, the first high voltage operating assembly includes a battery for powering the unmanned aerial vehicle and an electrical regulator for regulating a motor of the unmanned aerial vehicle. Correspondingly, the second high-voltage operating assembly includes an arm of the unmanned aerial vehicle, a motor provided on the arm, and a rotor provided on the motor.

The low pressure operating module may include a first low pressure operating assembly disposed within the fuselage of the unmanned aerial vehicle and a second low pressure operating assembly disposed outside the fuselage of the unmanned aerial vehicle. The first low pressure operating assembly and/or the second low pressure operating assembly are detachably connected to the body by a mechanical coupling mechanism. Here, the first low-voltage operating assembly includes a controller for controlling the UAV, a main circuit board, and built-in sensors. Correspondingly, the second low-voltage operating assembly includes a camera device and an external sensor.

The above descriptions are only preferred embodiments of the present disclosure, and are not intended to limit the present disclosure. For those skilled in the art, the present disclosure may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present disclosure shall be included within the protection scope of the present disclosure.

Claims

A modular unmanned aerial vehicle, comprising:

body;

a high-voltage operating module disposed on the fuselage; and

a low-voltage operating module arranged on the fuselage,

Wherein, the working voltage of the high-voltage operation module is greater than the working voltage of the low-voltage operation module, and the high-voltage operation module and the low-voltage operation module are respectively connected to the fuselage in a quick-release connection manner.
The modular unmanned aerial vehicle of claim 1, wherein:

The high voltage operating module is located at least partially outside the housing of the fuselage.
The modular unmanned aerial vehicle of claim 2, wherein:

The high-voltage operation module is disposed outside the casing of the fuselage.
The modular unmanned aerial vehicle of claim 1, wherein:

The low pressure operating module is located at least partially inside the housing of the fuselage.
The modular unmanned aerial vehicle of claim 4, wherein:

The low-voltage operation module is accommodated inside the casing of the fuselage.
The modular unmanned aerial vehicle of claim 1, wherein:

The operating voltage or output voltage of the high-voltage operating module is greater than or equal to 10 volts.
The modular unmanned aerial vehicle of claim 1, wherein:

The operating voltage or output voltage of the low voltage operating module is less than 10 volts.
The modular unmanned aerial vehicle of claim 1, wherein:

The high-voltage operation module and the low-voltage operation module are respectively detachably connected to the fuselage through a mechanical coupling mechanism.
The modular unmanned aerial vehicle of claim 8, wherein:

The mechanical coupling mechanism includes a locking mechanism or a sliding guide mechanism;

Wherein, the high-voltage operation module and/or the low-voltage operation module are detachably connected to the fuselage through the locking mechanism; or,

The high pressure operation module and/or the low pressure operation module are slidably connected to the body through the sliding guide mechanism.
The modular unmanned aerial vehicle of claim 9, wherein:

The locking mechanism includes at least one of the following: a buckle, a threaded fastener, a latch, and a Velcro.
The modular unmanned aerial vehicle of claim 9, wherein:

The sliding guide mechanism includes at least one of the following: a sliding rail, a sliding groove, a guide rod, and a sliding block.
The modular unmanned aerial vehicle of claim 1, wherein:

The high voltage operating module and the low voltage operating module are electrically connected to each other by an electrical coupling mechanism.
The modular unmanned aerial vehicle of claim 12, wherein:

The electrical coupling mechanism includes at least one of the following:

A male electrical connector and a female electrical connector that cooperate with each other, and electromagnetic coils that are electrically coupled to each other.
The modular unmanned aerial vehicle of claim 1, wherein:

The high voltage operating module includes a first high voltage operating assembly disposed within the fuselage of the UAV and a second high voltage operating assembly disposed outside the fuselage of the UAV.
The modular unmanned aerial vehicle of claim 14, wherein:

The first high pressure operating assembly and/or the second high pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism.
The modular unmanned aerial vehicle of claim 14 or 15, wherein:

The first high voltage operating assembly includes a battery for powering the UAV.
The modular unmanned aerial vehicle of claim 16, wherein:

The second high-voltage operation assembly includes an arm of the unmanned aerial vehicle, a motor arranged on the arm, a rotor arranged on the motor, and an electric regulator arranged on the arm.
The modular unmanned aerial vehicle of claim 14 or 15, wherein:

The first high voltage operating assembly includes a battery for powering the unmanned aerial vehicle and an electrical regulator for regulating a motor of the unmanned aerial vehicle.
The modular unmanned aerial vehicle of claim 18, wherein:

The second high voltage operating assembly includes an arm of the unmanned aerial vehicle, a motor provided on the arm, and a rotor provided on the motor.
The modular unmanned aerial vehicle of claim 1, wherein:

The low pressure operating module includes a first low pressure operating assembly disposed within the fuselage of the unmanned aerial vehicle and a second low pressure operating assembly disposed outside the fuselage of the unmanned aerial vehicle.
The modular unmanned aerial vehicle of claim 20, wherein:

The first low pressure operating assembly and/or the second low pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism.
The modular unmanned aerial vehicle of claim 20 or 21, wherein:

The first low voltage operating assembly includes a controller for controlling the UAV, a main circuit board, and built-in sensors.
The modular unmanned aerial vehicle of claim 22, wherein:

The second low-voltage operating assembly includes a camera and an external sensor.
A modular unmanned aerial vehicle, comprising:

body;

a high-voltage operating module disposed on the fuselage; and

a low-voltage operating module arranged on the fuselage,

Wherein, the working voltage of the high-voltage operation module is greater than the working voltage of the low-voltage operation module, the first one of the high-voltage operation module and the low-voltage operation module is connected to the body in a quick-release connection manner, and the A second of the high-voltage operating module and the low-voltage operating module is connected to the first of the high-voltage operating module and the low-voltage operating module in a quick release connection.
The modular unmanned aerial vehicle of claim 24, wherein:

The high voltage operating module is located at least partially outside the housing of the fuselage.
The modular unmanned aerial vehicle of claim 25, wherein:

The high-voltage operation module is disposed outside the casing of the fuselage.
The modular unmanned aerial vehicle of claim 24, wherein:

The low pressure operating module is located at least partially inside the housing of the fuselage.
The modular unmanned aerial vehicle of claim 27, wherein:

The low-voltage operation module is accommodated inside the casing of the fuselage.
The modular unmanned aerial vehicle of claim 24, wherein:

The operating voltage or output voltage of the high-voltage operating module is greater than or equal to 10 volts.
The modular unmanned aerial vehicle of claim 24, wherein:

The operating voltage or output voltage of the low voltage operating module is less than 10 volts.
The modular unmanned aerial vehicle of claim 24, wherein:

The first one of the high-voltage operating module and the low-voltage operating module is detachably connected to the fuselage through a mechanical coupling mechanism.
The modular unmanned aerial vehicle of claim 24, wherein:

A second one of the high pressure operation module and the low pressure operation module is connected to the first one of the high pressure operation module and the low pressure operation module in a quick release connection manner including the high pressure operation module and the low pressure operation module The modules are mechanically connected to each other by a mechanical coupling mechanism.
The modular unmanned aerial vehicle of claim 31 or 32, wherein:

The mechanical coupling mechanism includes a locking mechanism or a sliding guide mechanism.
The modular unmanned aerial vehicle of claim 33, wherein:

The locking mechanism includes at least one of the following: a buckle, a threaded fastener, a latch, and a Velcro.
The modular unmanned aerial vehicle of claim 33, wherein:

The sliding guide mechanism includes at least one of the following: a sliding rail, a sliding groove, a guide rod, and a sliding block.
The modular unmanned aerial vehicle of claim 32, wherein:

The high-voltage operating module and the low-voltage operating module are electrically connected to each other through an electrical coupling mechanism.
The modular unmanned aerial vehicle of claim 36, wherein:

The electrical coupling mechanism includes at least one of the following:

A male electrical connector and a female electrical connector that cooperate with each other, and electromagnetic coils that are electrically coupled to each other.
The modular unmanned aerial vehicle of claim 24, wherein:

The high-voltage operating module includes a first high-voltage operating assembly disposed within the fuselage of the UAV and a second high-voltage operating assembly disposed outside the fuselage of the UAV.
The modular unmanned aerial vehicle of claim 38, wherein:

The first high pressure operating assembly and/or the second high pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism.
The modular unmanned aerial vehicle of claim 39, wherein:

The first high voltage operating assembly includes a battery for powering the UAV.
The modular unmanned aerial vehicle of claim 40, wherein:

The second high-voltage operation assembly includes an arm of the unmanned aerial vehicle, a motor arranged on the arm, a rotor arranged on the motor, and an electric regulator arranged on the arm.
The modular unmanned aerial vehicle of claim 39, wherein:

The first high voltage operating assembly includes a battery for powering the UAV and an ESC for regulating the motors of the UAV.
The modular unmanned aerial vehicle of claim 42, wherein:

The second high voltage operating assembly includes an arm of the UAV, a motor provided on the arm, and a rotor provided on the motor.
The modular unmanned aerial vehicle of claim 24, wherein:

The low pressure operating module includes a first low pressure operating assembly disposed within the fuselage of the unmanned aerial vehicle and a second low pressure operating assembly disposed outside the fuselage of the unmanned aerial vehicle.
The modular unmanned aerial vehicle of claim 44, wherein:

The first low pressure operating assembly and/or the second low pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism.
The modular unmanned aerial vehicle of claim 44, wherein:

The first low voltage operating assembly includes a controller for controlling the UAV, a main circuit board, and built-in sensors.
The modular unmanned aerial vehicle of claim 46, wherein:

The second low-voltage operating assembly includes a camera and an external sensor.
A method of operating a modular unmanned aerial vehicle, characterized in that the method comprises:

The detachable module is quickly detached from the fuselage of the unmanned aerial vehicle; wherein, the detachable module is a high-voltage operation module arranged on the fuselage or a low-voltage operation module arranged on the fuselage, The working voltage of the high-voltage operating module is greater than the working voltage of the low-voltage operating module, and the high-voltage operating module and the low-voltage operating module are respectively connected to the fuselage in a quick-release connection manner; and

Reinstall the replacement module to the fuselage of the UAV.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The high voltage operating module is located at least partially outside the housing of the fuselage.
A method of operating a modular unmanned aerial vehicle according to claim 49, wherein:

The high-voltage operation module is disposed outside the casing of the fuselage.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The low pressure operating module is located at least partially inside the housing of the fuselage.
A method of operating a modular unmanned aerial vehicle according to claim 51, wherein:

The low-voltage operation module is accommodated inside the casing of the fuselage.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The operating voltage or output voltage of the high-voltage operating module is greater than or equal to 10 volts.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The operating voltage or output voltage of the low voltage operating module is less than 10 volts.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The high-voltage operation module and the low-voltage operation module are respectively detachably connected to the fuselage through a mechanical coupling mechanism.
A method of operating a modular unmanned aerial vehicle according to claim 55, wherein:

The mechanical coupling mechanism includes a locking mechanism or a sliding guide mechanism;

Wherein, the high-voltage operation module and/or the low-voltage operation module are detachably connected to the body through the locking mechanism; or,

The high pressure operation module and/or the low pressure operation module are slidably connected to the body through the sliding guide mechanism.
A method of operating a modular unmanned aerial vehicle according to claim 56, wherein:

The locking mechanism includes at least one of the following: a buckle, a threaded fastener, a latch, and a Velcro.
A method of operating a modular unmanned aerial vehicle according to claim 56, wherein:

The sliding guide mechanism includes at least one of the following: a sliding rail, a sliding groove, a guide rod, and a sliding block.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The high voltage operating module and the low voltage operating module are electrically connected to each other by an electrical coupling mechanism.
A method of operating a modular unmanned aerial vehicle according to claim 59, wherein:

The electrical coupling mechanism includes at least one of the following:

A male electrical connector and a female electrical connector that cooperate with each other, and electromagnetic coils that are electrically coupled to each other.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The high-voltage operating module includes a first high-voltage operating assembly disposed within the fuselage of the UAV and a second high-voltage operating assembly disposed outside the fuselage of the UAV.
The method of operating a modular unmanned aerial vehicle of claim 61, wherein:

The first high pressure operating assembly and/or the second high pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism.
The method of operating a modular unmanned aerial vehicle of claim 61, wherein:

The first high voltage operating assembly includes a battery for powering the UAV.
A method of operating a modular unmanned aerial vehicle according to claim 63, wherein:

The second high-voltage operation assembly includes an arm of the unmanned aerial vehicle, a motor arranged on the arm, a rotor arranged on the motor, and an electric regulator arranged on the arm.
The method of operating a modular unmanned aerial vehicle of claim 61, wherein:

The first high voltage operating assembly includes a battery for powering the UAV and an ESC for regulating the motors of the UAV.
A method of operating a modular unmanned aerial vehicle according to claim 65, wherein:

The second high voltage operating assembly includes an arm of the UAV, a motor provided on the arm, and a rotor provided on the motor.
A method of operating a modular unmanned aerial vehicle according to claim 48, wherein:

The low pressure operating module includes a first low pressure operating assembly disposed within the fuselage of the unmanned aerial vehicle and a second low pressure operating assembly disposed outside the fuselage of the unmanned aerial vehicle.
A method of operating a modular unmanned aerial vehicle according to claim 67, wherein:

The first low pressure operating assembly and/or the second low pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism.
A method of operating a modular unmanned aerial vehicle according to claim 67, wherein:

The first low voltage operating assembly includes a controller for controlling the UAV, a main circuit board, and built-in sensors.
A method of operating a modular unmanned aerial vehicle according to claim 69, wherein:

The second low-voltage operating assembly includes a camera and an external sensor.
A method of operating a modular unmanned aerial vehicle, characterized in that the method comprises:

The detachable module is quickly detached from the fuselage of the unmanned aerial vehicle; wherein, the detachable module is a high-voltage operation module arranged on the fuselage or a low-voltage operation module arranged on the fuselage, The operating voltage of the high-voltage operating module is greater than the operating voltage of the low-voltage operating module, the first one of the high-voltage operating module and the low-voltage operating module is connected to the fuselage in a quick-release connection manner, and the high-voltage operating module a second one of the module and the low voltage operating module is connected to the first one of the high voltage operating module and the low voltage operating module in a quick release connection; and

Reinstall the replacement module on the fuselage of the UAV.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The high voltage operating module is located at least partially outside the housing of the fuselage.
A method of operating a modular unmanned aerial vehicle according to claim 72, wherein:

The high-voltage operation module is disposed outside the casing of the fuselage.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The low pressure operating module is located at least partially inside the housing of the fuselage.
The method of operating a modular unmanned aerial vehicle of claim 74, wherein:

The low-voltage operation module is accommodated inside the casing of the fuselage.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The operating voltage or output voltage of the high-voltage operating module is greater than or equal to 10 volts.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The operating voltage or output voltage of the low voltage operating module is less than 10 volts.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The first one of the high-voltage operating module and the low-voltage operating module is detachably connected to the fuselage through a mechanical coupling mechanism.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

A second one of the high pressure operation module and the low pressure operation module is connected to the first one of the high pressure operation module and the low pressure operation module in a quick release connection manner including the high pressure operation module and the low pressure operation module The modules are mechanically connected to each other by a mechanical coupling mechanism.
A method of operating a modular unmanned aerial vehicle according to claim 78 or 79, wherein:

The mechanical coupling mechanism includes a locking mechanism or a sliding guide mechanism.
The method of operating a modular unmanned aerial vehicle of claim 80, wherein:

The locking mechanism includes at least one of the following: a buckle, a threaded fastener, a latch, and a Velcro.
The method of operating a modular unmanned aerial vehicle of claim 80, wherein:

The sliding guide mechanism includes at least one of the following: a sliding rail, a sliding groove, a guide rod, and a sliding block.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The high-voltage operating module and the low-voltage operating module are electrically connected to each other through an electrical coupling mechanism.
The method of operating a modular unmanned aerial vehicle of claim 83, wherein:

The electrical coupling mechanism includes at least one of the following:

A male electrical connector and a female electrical connector that cooperate with each other, and electromagnetic coils that are electrically coupled to each other.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The high voltage operating module includes a first high voltage operating assembly disposed within the fuselage of the UAV and a second high voltage operating assembly disposed outside the fuselage of the UAV.
The method of operating a modular unmanned aerial vehicle of claim 85, wherein:

The first high pressure operating assembly and/or the second high pressure operating assembly are connected to the fuselage by a mechanical coupling mechanism.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The first high voltage operating assembly includes a battery for powering the UAV.
The method of operating a modular unmanned aerial vehicle of claim 87, wherein:

The second high-voltage operation assembly includes an arm of the unmanned aerial vehicle, a motor arranged on the arm, a rotor arranged on the motor, and an electric regulator arranged on the arm.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The first high voltage operating assembly includes a battery for powering the unmanned aerial vehicle and an electrical regulator for regulating a motor of the unmanned aerial vehicle.
The method of operating a modular unmanned aerial vehicle of claim 89, wherein:

The second high voltage operating assembly includes an arm of the unmanned aerial vehicle, a motor provided on the arm, and a rotor provided on the motor.
The method of operating a modular unmanned aerial vehicle of claim 71, wherein:

The low pressure operating module includes a first low pressure operating assembly disposed within the fuselage of the unmanned aerial vehicle and a second low pressure operating assembly disposed outside the fuselage of the unmanned aerial vehicle.
A method of operating a modular unmanned aerial vehicle according to claim 91, wherein:

The first low pressure operating assembly and/or the second low pressure operating assembly are detachably connected to the body by a mechanical coupling mechanism.
A method of operating a modular unmanned aerial vehicle according to claim 91, wherein:

The first low voltage operating assembly includes a controller for controlling the UAV, a main circuit board, and built-in sensors.
A method of operating a modular unmanned aerial vehicle according to claim 93, wherein:

The second low-voltage operating assembly includes a camera and an external sensor.