A multi-copter aircraft

Abstract

The application discloses a kind of multi-rotor aircraft, wherein the multi-rotor aircraft includes: battery module, electronic speed controller module, flight control module and multiple power modules;Wherein, battery module and electronic speed controller module are mutually assembled, and electronic speed controller module and flight control module are mutually assembled;Multiple power modules and electronic speed controller module are mutually assembled, and locking fastener is arranged on the electronic speed controller module, and the locking fastener is used to reinforce the connection between multiple power modules and the electronic speed controller module in flight state.The embodiment of the application modularizes multi-rotor aircraft, flexibly assembles each main module using assembly components, expands various multi-axis multi-rotor aircraft, greatly improves the expansibility and flexibility of multi-rotor aircraft modularization;And, locking fastener is arranged on the key position, and the connection between modules is reinforced in flight state, which improves the stability of multi-rotor aircraft structure.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) technology, and particularly relates to a multi-rotor aircraft. Background Technology

[0002] With the development of technology and the continuous improvement of people's living standards, electronic toys are becoming increasingly diverse and powerful. Among these electronic toys, aircraft, as a high-end electronic toy, are deeply loved by many model airplane enthusiasts.

[0003] Currently, most aircraft are modular, building-block-style designs. Regardless of size, they can only achieve a single core platform for both quadcopters and octagonals. Furthermore, they require complex configurations and installations, such as adjusting electronic components and matching battery sizes, to achieve their functionality. In addition, such aircraft lack flexibility in installation and disassembly. Moreover, the connections between modules and the modular structure during flight differ from the structural requirements of a stationary modular structure, often leading to damage and disintegration due to collisions and landings.

[0004] Therefore, it is necessary to provide an unmanned aerial vehicle system to solve the problems of poor modular scalability and low structural stability of multi-rotor aircraft. Summary of the Invention

[0005] This invention provides a multi-rotor aircraft that improves the modular scalability of the multi-rotor aircraft and enhances the structural stability of the multi-rotor aircraft.

[0006] To address the aforementioned technical problems, the embodiments of the present invention provide the following technical solutions:

[0007] This invention provides a multi-rotor aircraft, comprising:

[0008] Battery module, ESC module, flight control module, and multiple power modules;

[0009] The battery module and the electronic speed controller module are assembled together, and the electronic speed controller module and the flight control module are assembled together.

[0010] Multiple power modules and the electronic speed controller (ESC) module are assembled together. The ESC module is equipped with locking fasteners, which are used to reinforce the connection between the multiple power modules and the ESC module during flight.

[0011] In the multi-rotor aircraft described in this invention, the battery module and the electronic speed controller module are assembled together by rotation.

[0012] In the multi-rotor aircraft described in this invention, the bottom of the battery module is a battery holder, the bottom of the battery holder is provided with a first spring-loaded fastener, and the top of the electronic speed control module is provided with a first fixing hole that cooperates with the first spring-loaded fastener. The first spring-loaded fastener and the first fixing hole are used to ensure that the battery holder does not shake during flight.

[0013] In the multi-rotor aircraft described in this invention, the electronic speed controller module and the flight control module are assembled together through an embedded combination.

[0014] In the multi-rotor aircraft described in this invention, a second spring-loaded component is provided on the top of the flight control module, and a locking structure that cooperates with the second spring-loaded component is provided on the bottom of the electronic speed controller module. The second spring-loaded component and the locking structure are used to reduce the loosening between the electronic speed controller module and the flight control module during flight.

[0015] In the multi-rotor aircraft described in this invention, the electronic control module is surrounded by a ring-shaped porous insert, which is used to connect with multiple extended power modules, and the multiple power modules are provided with porous strip supports.

[0016] Multiple power modules and electronic control modules are assembled together via annular porous inserts and multiple porous strip supports to form a multi-rotor aircraft.

[0017] In the multi-rotor aircraft described in this invention, the main body of the electronic control module is configured as a ring-shaped porous shell, and the electronic part of the electronic control module is installed inside the shell;

[0018] The upper and lower ends of the main body are respectively ring-shaped electronic ports. The electronic port at the lower end is a motor port, and the electronic port at the upper end is an expandable external device port and a power interface.

[0019] In the multi-rotor aircraft described in this invention, the power module includes a motor, a motor mount, blades, and a blade protective cover.

[0020] The blade protective cover is connected to the motor base, and the motor and the blade are installed in the assembly formed by connecting the blade protective cover and the motor base;

[0021] The motor is located below the propeller blade, the propeller blade is located below the propeller blade protective cover, and the motor includes a power cable port, which is connected to the aircraft's circuit board socket and installed at the bottom of the motor mount.

[0022] In the multi-rotor aircraft described in this invention, the power module further includes a perforated strip support, and the motor mount and the perforated strip support are locked and fixed together by a nut and a screw.

[0023] In the multi-rotor aircraft described in this invention, the battery module includes a battery body, a battery holder, a porous rectangular bracket, several porous strip brackets, and several connectors.

[0024] The battery holder and the porous rectangular bracket are interconnected by a plurality of porous strip brackets and a plurality of connectors.

[0025] The battery body is installed in the assembly formed by connecting the battery holder and the porous rectangular bracket. The battery holder is located at the bottom of the battery module, and the porous rectangular bracket is located above the battery body.

[0026] In this embodiment of the invention, the main module of the multirotor aircraft includes a battery module, an electronic speed controller (ESC) module, a flight control module, and multiple power modules. The battery module and ESC module are assembled together, the ESC module and flight control module are assembled together, and the multiple power modules are assembled together with the ESC module. This modularizes the multirotor aircraft, flexibly assembling the main modules using assembly components. Through the corresponding configuration of the expandable ESC module and multiple power modules, it can be expanded into various multi-rotor aircraft, greatly improving the modular scalability and flexibility of the multirotor aircraft. Furthermore, the ESC module is equipped with locking fasteners to reinforce the connection between the multiple power modules and the ESC module during flight, reducing the possibility of loosening and damage between modules during flight and improving the structural stability of the multirotor aircraft. Attached Figure Description

[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] Figure 1 This is a schematic diagram of a modular structure for a multi-rotor aircraft provided in an embodiment of the present invention.

[0029] Figure 2 This is a schematic diagram of the structure of a multi-rotor aircraft provided in an embodiment of the present invention.

[0030] Figure 3 This is a schematic diagram of another multi-rotor aircraft provided in an embodiment of the present invention.

[0031] Figure 4 This is a schematic diagram of the structure of another multi-rotor aircraft provided in an embodiment of the present invention.

[0032] Figure 5 This is a schematic diagram of the connection structure between the electronic speed controller (ESC) module and the flight control module in a multi-rotor aircraft provided in an embodiment of the present invention.

[0033] Figure 6 This is a schematic diagram of the connection structure between the electronic control module and the power module in a multi-rotor aircraft provided in an embodiment of the present invention.

[0034] Figure 7 This is a schematic diagram of the battery module in a multi-rotor aircraft provided in an embodiment of the present invention.

[0035] Figure 8 This is a schematic diagram of the connection structure between the battery module and the electronic speed controller module in a multi-rotor aircraft provided in an embodiment of the present invention.

[0036] Figure 9 This is a schematic diagram of the power module in a multi-rotor aircraft provided in an embodiment of the present invention. Detailed Implementation

[0037] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals denote 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 invention, and should not be construed as limiting the present invention.

[0038] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0039] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection, an electrical connection, or a connection that allows for communication; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0040] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0041] The following disclosure provides many different embodiments or examples for implementing various structures of the invention. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the invention. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, examples of various specific processes and materials are provided in this invention, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0042] This invention provides a multi-rotor aircraft. Detailed descriptions will follow.

[0043] In this embodiment, the description will focus on a multi-rotor aircraft, which includes a battery module, an electronic speed controller (ESC) module, a flight control module, and multiple power modules. The battery module and the ESC module are assembled together, and the ESC module and the flight control module are assembled together. The multiple power modules are assembled together with the ESC module, and the ESC module is equipped with locking fasteners for reinforcing the connection between the multiple power modules and the ESC module during flight.

[0044] Please see Figure 1 , Figure 1This is a schematic diagram of the modular structure of a multi-rotor aircraft provided in an embodiment of the present invention. The multi-rotor aircraft includes:

[0045] Battery module 101, electronic speed controller module 102, flight control module 103, and multiple power modules 104;

[0046] The battery module 101 and the electronic speed controller module 102 are assembled together, and the electronic speed controller module 102 and the flight control module 103 are assembled together.

[0047] Multiple power modules 104 are assembled with the electronic speed controller (ESC) module 102. The ESC module 102 is equipped with locking fasteners, which are used to reinforce the connection between the multiple power modules 104 and the ESC module 102 during flight.

[0048] In this embodiment, both the ESC module 102 and the power module 104 are expandable main modules. Depending on the corresponding settings of each functional main module, they can be expanded into various multi-rotor aircraft (such as quadcopters, hexacopters, octagonals, etc.). (See reference...) Figure 2 This is the quadcopter multi-rotor aircraft obtained after assembly.

[0049] Multirotor aircraft are simple in structure, flexible in control, and stable in flight attitude. Common types include quadcopters, hexacopter, and octocopters. With the development of microelectromechanical systems (MEMS) and sensor technology in recent years, multirotor aircraft have been widely used in model aircraft, aerial photography platforms, and other fields. Multirotor aircraft use various sensors to sense their flight status and use a microprocessor to send speed commands to the rotor motors to adjust the aircraft's different flight attitudes.

[0050] Understandably, the expandable ESC module 102 and power module 104 can be configured accordingly based on actual needs. For example, adding a corresponding number of power modules 104 (i.e., adding more arms to the aircraft) and connecting them with the ESC module 102 can achieve the following: Figure 3 The six-rotor aircraft shown, and such as Figure 4 The eight-axis multi-rotor aircraft shown here is for illustrative purposes only and does not constitute a limitation of the present invention.

[0051] Furthermore, the mutual assembly between battery module 101 and ESC module 102, the mutual assembly between ESC module 102 and flight control module 103, and the mutual assembly between multiple power modules 104 and ESC module 102 can be achieved by connecting the modules with corresponding splicing components 105 (such as plastic screws and nuts, support legs, and other building blocks). The splicing components 105 include locking fasteners on the ESC module 102. Of course, the mutual assembly of the modules can also be achieved through the structural design of each module itself, which is not specifically limited here.

[0052] Furthermore, the locking fasteners provided on the ESC module 102 are used to reinforce the connection between the multiple power modules 104 and the ESC module 102 during flight. For example, the locking fasteners include plastic screws and nuts. Through the cooperation of the plastic screws and nuts, the connection between the modules can be reinforced, thereby reducing the occurrence of loosening and damage between modules during flight.

[0053] As can be seen from the above, in this embodiment of the invention, the multi-rotor aircraft is modularized, and the main modules are flexibly assembled using assembly components. Through the corresponding settings of the expandable ESC module 102 and multiple power modules 104, it can be expanded into various multi-rotor aircraft (such as quadcopters, hexacopters, octagons, etc.), greatly improving the scalability and flexibility of the multi-rotor aircraft modularization. Furthermore, locking fasteners are provided at key locations to reinforce the connection between modules during flight, thereby improving the stability of the multi-rotor aircraft structure.

[0054] Based on the multi-rotor aircraft described in the previous embodiment, the following will use a quadcopter multi-rotor aircraft as an example to further illustrate the details.

[0055] Please refer to the reference. Figure 1 , Figure 2 and Figure 5 ,in Figure 5 This is a schematic diagram of the connection structure between the electronic speed controller module 102 and the flight control module 103 in a multi-rotor aircraft; for example... Figure 5 As shown, in this multi-rotor aircraft, the electronic speed controller module 102 and the flight control module 103 are assembled together by embedding.

[0056] In some embodiments, the flight control module 103 is provided with a second spring-loaded fastener 1031 at its top, and the electronic speed controller module 102 is provided with a locking structure at its bottom that cooperates with the second spring-loaded fastener 1031. The second spring-loaded fastener 1031 and the locking structure are used to reduce the loosening between the electronic speed controller module 102 and the flight control module 103 in flight. That is, the second spring-loaded fastener 1031 and the locking structure are used to achieve the engagement between the electronic speed controller module 102 and the flight control module 103 and the locking structure of the spring-loaded fastener.

[0057] The locking structure can be configured as a groove corresponding to the size of the second spring buckle component 1031, or it can be configured as an opening corresponding to the size of the second spring buckle component 1031, which is combined with the second spring buckle component 1031 to form a locking structure of fitting and spring buckle.

[0058] Furthermore, the interlocking and spring-loaded locking structure between the ESC module 102 and the flight control module 103 ensures that, in the event of a collision during flight, it is less likely to cause poor contact due to loosening between the modules. Meanwhile, the flight control module 103 can also be used independently for other aircraft or remote-controlled vehicles, etc., without specific limitations here.

[0059] Please refer to this as well. Figure 6 , Figure 6 This is a schematic diagram of the connection structure between the ESC module 102 and the power module 104 in a multi-rotor aircraft; as shown. Figure 6 As shown, in this multi-rotor aircraft, the main body of the ESC module 102 is configured as an annular porous housing 1021, and the electronic part of the ESC module 102 is installed inside the housing 1021.

[0060] The upper and lower ends of the main body are respectively ring-shaped electronic ports. The lower electronic port 1022 is a motor port, and the upper electronic port 1023 is an expandable external device port and a power interface.

[0061] For example, in this embodiment of the invention, the lower electronic port 1022 is a motor port that can connect up to eight motors, and the upper electronic port 1023 can specifically be a port for external devices such as image transmission and cameras, as well as a power port.

[0062] like Figure 6 As shown, in this multi-rotor aircraft, the ESC module 102 is surrounded by annular porous inserts 1024. The annular porous inserts 1024 can be formed by two annular porous building blocks that interlock with each other. The annular porous inserts 1024 are used to connect with the extended multiple power modules 104.

[0063] In this multi-rotor aircraft, multiple power modules 104 are provided with perforated strip supports 1041. The multiple power modules 104 and the electronic control module 102 are assembled with each other through the annular perforated plug 1024 and the multiple perforated strip supports 1041 to form a multi-axis multi-rotor aircraft.

[0064] For example, in this quadcopter multirotor aircraft, each of the four power modules 104 is provided with a perforated strip bracket 1041. The four power modules 104 and the electronic speed control module 102 are assembled with each other through the annular perforated plug 1024 and the four perforated strip brackets 1041 to form a quadcopter multirotor aircraft.

[0065] like Figure 6As shown, the ESC module 102 is equipped with locking fasteners (i.e., assembly components 105) to reinforce the connection between the multiple power modules 104 and the ESC module 102 during flight. For example, the locking fasteners may include plastic screws and nuts. The cooperation between the plastic screws and nuts can strengthen the connection between modules, thereby reducing the occurrence of loosening and damage between modules during flight.

[0066] Please refer to Figure 7 , Figure 7 This is a schematic diagram of the structure of the battery module 101 in a multi-rotor aircraft. The battery module 101 includes a battery body 1011, a battery holder 1012, a perforated rectangular bracket 1013, several perforated strip brackets 1014, and several connectors 1015.

[0067] The battery holder 1012 and the porous rectangular bracket 1013 are interconnected by a plurality of porous strip brackets 1014 and a plurality of connectors 1015.

[0068] Furthermore, the battery body 1011 is installed in the assembly formed by connecting the battery holder 1012 and the porous rectangular bracket 1013. The battery holder 1012 is located at the bottom of the battery module 101, the battery body 1011 is located above the battery holder 1012, and the porous rectangular bracket 1013 is located above the battery body 1011.

[0069] In other words, the battery holder 1012 and the porous rectangular bracket 1013 are assembled from several porous strip brackets 1014 and several connectors 1015, and the battery body 1011 is installed in the formed assembly. All the structures in this part are interlocking connections. These connectors 1015 can use several common assembly components or building blocks, which are easy to assemble and disassemble.

[0070] Furthermore, the multi-hole rectangular bracket 1013 allows for the unlimited use of universal connectors or modular components to expand related external accessories, such as cameras, image transmission devices, etc. Figure 7 The WiFi image transmission unit 1016 shown is designed to better meet product needs and improve user experience.

[0071] Please refer to the reference. Figure 7 and Figure 8 ,in Figure 8 This is a schematic diagram of the connection structure between the battery module 101 and the electronic speed controller module 102 in a multi-rotor aircraft; as shown. Figure 8 As shown, in this multi-rotor aircraft, the battery module 101 and the electronic speed controller module 102 are assembled together by rotation.

[0072] In some implementations, such as Figure 8As shown, the bottom of the battery module 101 is a battery holder 1012, and the bottom of the battery holder 1012 is provided with a first spring-loaded fastener. The top of the ESC module 102 is provided with a first fixing hole that cooperates with the first spring-loaded fastener. The first spring-loaded fastener and the first fixing hole are used to ensure that the battery holder 1012 does not shake during flight.

[0073] That is, the rotation and spring-loaded fixation between the battery module 101 and the ESC module 102 are achieved through the first spring-loaded latch component and the first fixing hole. The rotation ensures the connection between the battery holder 1012 and the housing of the ESC module 102, while the spring-loaded latch ensures that the battery holder 1012 does not wobble during flight, thus ensuring flight stability. For ease of understanding, Figure 8 The assembly orientation of the battery module 101 and the ESC module 102 is also shown.

[0074] Please refer to Figure 9 , Figure 9 This is a schematic diagram of the structure of the power module 104 in a multi-rotor aircraft provided in an embodiment of the present invention. In this multi-rotor aircraft, the power module 104 includes a motor 1045, a motor mount 1042, a blade 1043, and a blade protective cover 1044.

[0075] like Figure 9 As shown, the blade protection cover 1044 is connected to the motor mount 1042, and the motor 1045 and the blade 1043 are installed in the assembly formed by connecting the blade protection cover 1044 and the motor mount 1042.

[0076] The motor 1045 is located below the propeller 1043, and the propeller 1043 is located below the propeller protective cover 1044. The motor 1045 includes a power cable port, which is connected to the circuit board socket 1046 of the aircraft and installed at the bottom of the motor mount 1042.

[0077] In this embodiment of the invention, the motor mount 1042 can be used to assemble the 1106 series motors, the 1104 series motors, and so on. The power cable port of the motor 1045 is connected to the circuit board (PCB) socket 1046 and installed at the bottom of the motor mount 1042. The propeller guard 1044 can be freely assembled with the motor mount 1042, and its function can effectively reduce the damage to the multirotor aircraft caused by external collisions during flight and landing.

[0078] In addition, in the multi-rotor aircraft, each power module 104 also includes a perforated strip bracket 1041, and the motor mount 1042 and the perforated strip bracket 1041 can be locked and fixed by the cooperation of the nut 1047 and the screw 1048.

[0079] After the motor mount 1042 is assembled, the multi-hole strip bracket 1041 can be used to assemble the required aircraft arm. For the stability of the multi-rotor aircraft during flight, the motor mount 1042 and the multi-hole strip bracket 1041 can be locked and fixed with plastic nuts and screws or other locking fasteners to reinforce the structure of the power module 104. This example is not intended to be limiting.

[0080] As described above, in order to flexibly expand the scope of modularity and diversification of aircraft, this embodiment of the invention provides a multi-rotor aircraft based on the concept of multi-functional modular building blocks. The main modules of the multi-rotor aircraft include a battery module 101, an ESC module 102, a flight control module 103, and multiple power modules 104. The battery module 101 and the ESC module 102 are assembled together, the ESC module 102 and the flight control module 103 are assembled together, and the multiple power modules 104 and the ESC module 102 are assembled together. In other words, the multi-rotor aircraft is modularized, and the main modules are flexibly assembled using assembly components. Through the corresponding settings of the expandable ESC module and multiple power modules, it can be expanded into various multi-rotor aircraft (such as quadcopters, hexacopters, octagonals, etc.), which greatly improves the expandability and flexibility of the multi-rotor aircraft modularity.

[0081] Furthermore, the ESC module 102 is equipped with locking fasteners, which are used to reinforce the connection between the multiple power modules 104 and the ESC module 102 during flight, reducing the possibility of loosening and damage between modules during flight. The ESC module 102 and the flight control module 103 are locked together by a locking structure of interlocking and spring-loaded fasteners, which ensures that in the event of a collision during flight, it is not easy for the modules to become loose and have poor contact. The battery module 101 and the ESC module 102 are connected by a rotating and spring-loaded fastener structure. The rotation ensures that the battery holder 1012 is connected to the outer shell of the ESC module 102, and the spring-loaded fastener ensures that the battery holder 1012 does not shake during flight, thereby ensuring the structural integrity of the multi-rotor aircraft and the stability of flight.

[0082] It is understood that the descriptions of each embodiment in the above embodiments have different focuses. For the parts not described in detail in a certain embodiment, please refer to the detailed description of the multi-rotor aircraft above, which will not be repeated here.

[0083] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0084] In summary, specific examples have been used to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. At the same time, those skilled in the art will know that there will be changes in the specific implementation methods and application scope based on the ideas of the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A multi-rotor aircraft, characterized in that, include: Battery module, ESC module, flight control module, and multiple power modules; The electronic speed controller (ESC) module is located between the battery module and the flight control module. The battery module and the ESC module are assembled together, and the ESC module and the flight control module are assembled together. Multiple power modules and the electronic speed controller (ESC) module are assembled together. The ESC module is equipped with locking fasteners, which are used to reinforce the connection between the multiple power modules and the ESC module during flight. The ESC module has a main body, which is a ring-shaped porous shell. The electronic part of the ESC module is installed inside the shell. The upper and lower ends of the main body are respectively ring-shaped electronic ports. The electronic port at the lower end is a motor port, and the electronic port at the upper end is an expandable external device port and a power interface. The multi-rotor aircraft also includes a ring-shaped porous insert and a porous strip support. The ring-shaped porous insert includes two ring-shaped porous building blocks, which are arranged around the main body and located between the electronic ports at the upper and lower ends. The porous strip support is connected between the two ring-shaped porous building blocks. Multiple power modules are respectively connected to the porous strip support. The multiple power modules and the electronic speed control module are assembled together through the ring-shaped porous insert and the porous strip support to form the multi-rotor aircraft.

2. The multi-rotor aircraft according to claim 1, characterized in that, The battery module and the ESC module are assembled together by rotation.

3. The multi-rotor aircraft according to claim 2, characterized in that, The bottom of the battery module is a battery holder, and the bottom of the battery holder is provided with a first spring-loaded fastener. The top of the ESC module is provided with a first fixing hole that cooperates with the first spring-loaded fastener. The first spring-loaded fastener and the first fixing hole are used to ensure that the battery holder does not shake during flight.

4. The multi-rotor aircraft according to claim 1, characterized in that, The electronic speed controller (ESC) module and the flight control module are assembled together through an embedded combination.

5. The multi-rotor aircraft according to claim 4, characterized in that, The flight control module is provided with a second spring-loaded fastener at the top, and the electronic speed controller (ESC) module is provided with a locking structure at the bottom that cooperates with the second spring-loaded fastener. The second spring-loaded fastener and the locking structure are used to reduce the loosening between the ESC module and the flight control module during flight.

6. The multi-rotor aircraft according to claim 1, characterized in that, The power module includes a motor, a motor mount, blades, and a blade protective cover. The blade protective cover is connected to the motor base, and the motor and the blade are installed in the assembly formed by connecting the blade protective cover and the motor base; The motor is located below the propeller blade, the propeller blade is located below the propeller blade protective cover, and the motor includes a power cable port, which is connected to the aircraft's circuit board socket and installed at the bottom of the motor mount.

7. The multi-rotor aircraft according to claim 6, characterized in that, The power module also includes a perforated strip bracket, and the motor mount and the perforated strip bracket are locked together by a nut and a screw.

8. The multi-rotor aircraft according to claim 1, characterized in that, The battery module includes a battery body, a battery holder, a porous rectangular bracket, several porous strip brackets, and several connectors. The battery holder and the porous rectangular bracket are interconnected by a plurality of porous strip brackets and a plurality of connectors. The battery body is installed in the assembly formed by connecting the battery holder and the porous rectangular bracket. The battery holder is located at the bottom of the battery module, and the porous rectangular bracket is located above the battery body.

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