Multicopter

Abstract

This utility model provides a multi-rotor aircraft, relating to unmanned aerial vehicle (UAV) technology. The multi-rotor aircraft includes a fuselage and a battery holder mounted on the fuselage. The battery holder includes a first base and a second base. A reserved gap for battery insertion is provided between the first base and the second base. The first base has a first guide portion and a first polarity connector. The second base has a second guide portion and a second polarity connector. The guide alignment axis of the first guide portion and the guide alignment axis of the second guide portion are coplanar in a first vertical plane. The connection alignment axis of the first polarity connector and the connection alignment axis of the second polarity connector are coplanar in a second vertical plane. The first vertical plane and the second vertical plane are parallel. This utility model can reduce the occurrence of incorrect battery insertion by operators.

Description

Technical Field

[0001] This utility model relates to unmanned aerial vehicle (UAV) technology, and in particular to a multi-rotor aircraft. Background Technology

[0002] In existing multi-rotor aircraft, the airframe and battery are usually connected in a detachable manner, which allows operators to replace the battery when the battery power is low, thus enabling the multi-rotor aircraft to perform rapid go-around operations and improving the operational efficiency of the multi-rotor aircraft.

[0003] However, operators often insert the battery incorrectly when changing batteries, which will cause unnecessary structural wear and pose safety hazards. Utility Model Content

[0004] To address the above problems or situations, this utility model provides a multi-rotor aircraft that can reduce the occurrence of operators mistakenly inserting batteries.

[0005] This utility model provides a multi-rotor aircraft, including a fuselage and a battery mount disposed on the fuselage, the battery mount including a first mount body and a second mount body;

[0006] A reserved gap for battery insertion is provided between the first base and the second base. The first base is provided with a first guide and a first polarity connector; the second base is provided with a second guide and a second polarity connector.

[0007] The guide center axis of the first guide part and the guide center axis of the second guide part are coplanar in the first vertical plane;

[0008] The connection center axis of the first polarity connector and the connection center axis of the second polarity connector are coplanar in the second vertical plane;

[0009] The first vertical plane is parallel to the second vertical plane.

[0010] In one embodiment of a multi-rotor aircraft, the first guide portion includes a first protrusion that protrudes from the first base body, and the first protrusion has a first guide surface that extends vertically.

[0011] The second guide portion includes a second protrusion that protrudes from the second seat body, and the second protrusion has a second guide surface that extends vertically.

[0012] The first guide surface and the second guide surface are arranged facing each other.

[0013] In one embodiment of the multi-rotor aircraft, a plurality of first mounting holes arranged vertically are provided on the first guide surface, and a first roller with a wheel protruding from the first guide surface is provided in the first mounting hole.

[0014] And / or,

[0015] A plurality of second mounting holes arranged vertically are provided on the second guide surface, and a second roller with a wheel body protruding from the second guide surface is provided in the second mounting hole.

[0016] In one embodiment of a multi-rotor aircraft, the first protrusion further has two first vertical sides located on both sides of the first guide surface, and at least one of the first vertical sides is provided with a plurality of third mounting holes arranged vertically, and a third roller with a wheel body protruding out of the vertical side is provided in the third mounting hole.

[0017] And / or,

[0018] The second protrusion also has two second vertical sides located on both sides of the second guide surface, and at least one of the second vertical sides is provided with a plurality of fourth mounting holes arranged vertically, and a fourth roller with a wheel body protruding out of the vertical side is provided in the fourth mounting hole.

[0019] In one embodiment of a multi-rotor aircraft, the first polarity connector includes a first connection body that extends horizontally in a direction away from the aircraft body.

[0020] The second polarity connector includes a second connection body that extends horizontally in a direction away from the body;

[0021] The first connecting body and the second connecting body extend in parallel directions.

[0022] In one embodiment of the multirotor aircraft, two first positioning posts are further formed on the first connecting body, and a plurality of inserts or slots are provided between the two first positioning posts. The apex height of the first positioning posts is higher than the apex height of the inserts or slots; and / or

[0023] Two second positioning posts are also formed on the second connecting body, and a plurality of inserts or slots are provided between the two second positioning posts; the apex height of the second positioning post is higher than the apex height of the insert or the slot.

[0024] In one embodiment of the multi-rotor aircraft, the first seat body includes a first connecting part and a second connecting part, and the second seat body includes a third connecting part and a fourth connecting part;

[0025] The machine body includes a rear crossbeam, and a first machine arm connector and a second machine arm connector are respectively provided at both ends of the rear crossbeam;

[0026] The first connecting part is connected to the rear crossbeam, the second connecting part is connected to the first arm connecting piece; the third connecting part is connected to the rear crossbeam, and the fourth connecting part is connected to the second arm connecting piece.

[0027] In one embodiment of a multi-rotor aircraft, the second connecting portion includes a vertically arranged mounting plane, which is parallel to the first vertical plane;

[0028] The first connecting part includes two protrusions on the mounting plane, and the two protrusions are respectively connected to the top side wall and the bottom side wall of the rear crossbeam;

[0029] Both the first and second bases are provided with multiple weight-reducing holes.

[0030] In one embodiment of the multi-rotor aircraft, a wiring channel is also formed on the first base, one channel port of the wiring channel is located below the first polarity connector, and the other channel port of the wiring channel is located on the mounting plane.

[0031] Wiring holes are provided on the first arm connector and the rear crossbeam, and the position of each wiring hole corresponds to another channel port of the wiring channel.

[0032] In one embodiment of the multirotor aircraft, it further includes a front crossbeam and two longitudinal beams, the front crossbeam and the rear crossbeam being positioned opposite each other, one longitudinal beam connecting the same side ends of the front crossbeam and the rear crossbeam respectively, and the other longitudinal beam connecting the other side ends of the front crossbeam and the rear crossbeam respectively.

[0033] The front crossbeam, the rear crossbeam, and the longitudinal beam are all pipes with hollow cavities, and the front crossbeam is installed at a higher height than the rear crossbeam.

[0034] Beneficial effects:

[0035] In the multi-rotor aircraft provided by this utility model, the guide alignment axis of the first guide part of the battery holder and the guide alignment axis of the second guide part are coplanar in the first vertical plane, while the connection alignment axis of the first polarity connector of the battery holder and the connection alignment axis of the second polarity connector are coplanar in the second vertical plane. The first vertical plane and the second vertical plane are parallel, so that the first vertical plane and the second vertical plane are not coplanar. Based on this structure, the battery cannot be connected with the corresponding polarity connector when it is inserted in reverse, thereby reducing the occurrence of incorrect battery insertion by the operator. It can also prevent unnecessary wear on the battery or the corresponding polarity connector when the operator incorrectly places the battery on the battery holder, and can also reduce the risk of short circuit in electrical connection.

[0036] Other features and advantages of this invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objectives and other advantages of this invention are realized and obtained through the structures particularly pointed out in the description and the accompanying drawings.

[0037] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0038] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0039] Figure 1 A schematic diagram of the principle structure of a part of the multi-rotor aircraft provided by this utility model from a top-down perspective;

[0040] Figure 2 A top-view structural schematic diagram of one embodiment of the multi-rotor aircraft provided by this utility model;

[0041] Figure 3 A schematic diagram of the rear crossbeam in one embodiment of the multi-rotor aircraft provided by this utility model;

[0042] Figure 4 A three-dimensional structural diagram of the first seat in one embodiment of the multi-rotor aircraft provided by this utility model, viewed from a first perspective.

[0043] Figure 5 A three-dimensional structural diagram of the first seat in a embodiment of the multi-rotor aircraft provided by this utility model, viewed from a second perspective.

[0044] Figure 6 A three-dimensional structural diagram of the first polarity connector in one embodiment of the multi-rotor aircraft provided by this utility model.

[0045] Explanation of reference numerals in the attached figures:

[0046] 1. Multi-rotor aircraft;

[0047] 11. Organism;

[0048] 12. Battery holder; 121. First base body; 122. Second base body; 123. Reserved gap; 124. First guide part; 125. Second guide part;

[0049] 13. First polarity connector;

[0050] 14. Second polarity connector;

[0051] 2. Multirotor aircraft;

[0052] 21. Body; 211. Rear crossbeam; 2111. Cable guide hole; 212. First arm connector; 213. Front crossbeam; 214. Longitudinal beam;

[0053] 22. Battery holder; 221. First base body; 2211. First connecting part; 2212. Second connecting part; 2213. Lug; 2214. Weight reduction hole; 2215. Cable routing channel; 222. Second base body; 223. Reserved spacing; 224. First guide part; 2241. First protrusion; 2242. First guide surface; 2243. First mounting hole; 2244. First roller; 2245. First vertical side; 2246. Third mounting hole; 2247. Third roller;

[0054] 23. First polarity connector; 231. First connecting body; 232. First positioning post; 233. Insert;

[0055] 24. Second polarity connector;

[0056] 25. Head assembly. Detailed Implementation

[0057] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0058] In the description of the embodiments of this utility model, 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 or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0059] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model 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 this utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0060] When performing battery replacement operations, operators can use the guide part and corresponding polarity connector provided by this utility model to avoid the situation of reverse insertion.

[0061] See Figure 1 The present invention provides an exemplary structure of a multi-rotor aircraft. The multi-rotor aircraft 1 provided by the present invention includes a body 11 and a battery mount 12 disposed on the body 11. The battery mount 12 can typically be disposed at the rear, side or middle of the body 11.

[0062] The battery holder 12 may include a first body 121 and a second body 122, which are spaced apart to form a reserved gap 123 for inserting a battery. The reserved gap 123 is adapted to the width of the battery to be inserted. The first body 121 and the second body 122 are respectively provided with electrical connectors of different polarities. The first body 121 is provided with a first polarity connector 13, and the second body 122 is provided with a second polarity connector 14. The first polarity connector 13 and the second polarity connector 14 are positive and negative terminals of each other.

[0063] Here, the first seat 121 may further include a first guide portion 124, and correspondingly, the second seat 122 may similarly include a second guide portion 125. The first guide portion 124 and the second guide portion 125 are used together to provide insertion guidance for the battery. It is understood that the first guide portion 124 and the second guide portion 125 each include a guide pair of central axes, that is, the portion providing the guiding function has a pair of central axes, and the battery can be inserted or removed based on the guidance of the pair of central axes.

[0064] Similarly to the aforementioned guide center axis, the first polarity connector 13 and the second polarity connector 14 also have a connecting center axis, that is, the connecting part of the connector has a pair of center axes, and the connector mating part on the battery can mate with the corresponding polarity connector based on the pair of center axes, such as a plug-in mating.

[0065] In this invention, the guide centering axis of the first guide portion 124 and the guide centering axis of the second guide portion 125 are coplanar in the first vertical plane A1, and the connection centering axis of the first polarity connector 13 and the connection centering axis of the second polarity connector 14 are coplanar in the second vertical plane A2. The first vertical plane A1 and the second vertical plane A2 are parallel, thus making the first vertical plane A1 and the second vertical plane A2 non-coplanar. Based on this structure, the battery cannot be connected with the corresponding polarity connector when inserted in reverse, thereby reducing the occurrence of incorrect battery insertion by operators. It also avoids unnecessary wear on the battery or the corresponding polarity connector when the operator incorrectly places the battery into the battery holder, and reduces the risk of short circuit in the electrical connection.

[0066] See Figures 2 to 6 This paper exemplarily illustrates a multi-rotor aircraft and its related structural components according to an embodiment of the present invention. The multi-rotor aircraft 2 includes a fuselage 21, which may include a rear crossbeam 211, arm connectors, a front crossbeam 213, and longitudinal beams 214. The rear crossbeam 211 and the front crossbeam 213 are positioned opposite each other. The rear crossbeam 211, the front crossbeam 213, and the two longitudinal beams 214 can form a frame with a square frame. The space within the square frame can be used to place and fix loads such as solution tanks or dispensing devices. The arm connector may include a first arm connector 212 disposed on one side of the rear crossbeam 211 and a second arm connector (not shown) disposed on the other side. The first arm connector 212 is used to connect the rear crossbeam 211 and the longitudinal beam 214. Similarly, the front crossbeam 213 may be connected to the longitudinal beam 214 by an arm connector. That is, one longitudinal beam 214 is connected to the same side of the front crossbeam 213 and the rear crossbeam 211, and another longitudinal beam 214 is connected to the other same side of the front crossbeam 213 and the rear crossbeam 211. A head assembly 25 may be disposed on the front crossbeam 213. The head assembly 25 may specifically include a main control module and a sensing module, etc., as electrical modules.

[0067] In one embodiment, the rear crossbeam 211, the front crossbeam 213, and the longitudinal beam 214 are all tubular materials with hollow cavities, and the front crossbeam 213 is set at a higher height than the rear crossbeam 211, so that the crossbeam for installing the battery holder 22 is set at a relatively low height, making it easier for operators to insert or remove the battery.

[0068] The aforementioned battery holder 22 is mounted on the rear crossbeam 211, and a reserved gap 223 for battery insertion is formed between the first holder 221 and the second holder 222. Figure 4 and Figure 5 As shown, the first seat 221 is provided with a first guide portion 224. Specifically, the first guide portion 224 may include a first protrusion 2241 protruding from the first seat 221. The first protrusion 2241 protrudes towards the direction of the second seat 222 and extends vertically. Here, the first protrusion 2241 has a first guide surface 2242 extending vertically. Similarly, the second seat 222 is provided with a second guide portion (not shown in the figure). The second guide portion includes a second protrusion (not shown in the figure) protruding towards the direction of the first seat 221, and the second protrusion has a second guide surface extending vertically.

[0069] Here, the vertically extending centering axis of the first guide surface 2242 can serve as the guide centering axis of the first seat 221. Similarly, the vertically extending centering axis of the second guide surface can serve as the guide centering axis of the second seat 222. The two guide centering axes are coplanar in the first vertical plane A1.

[0070] It is understood that in this embodiment, both the first seat 221 and the second seat 222 include a protrusion as a guide for the battery. Correspondingly, the battery has a groove that matches the protrusion to support the two to achieve a guiding engagement through the convex-concave fit. In other modified embodiments, both the first seat 221 and the second seat 222 may include a groove, and correspondingly, the battery has a protrusion that matches the groove to support the two to achieve a guiding engagement through the convex-concave fit as well.

[0071] In this embodiment, the first polarity connector 23 may include a first connecting body 231, which is fixedly mounted on the first base 221. For example... Figure 2 and Figure 6 As shown, the first connecting body 231 extends horizontally in a direction away from the base. Two first positioning posts 232 are formed on the first connecting body 231, and multiple inserts 233 are provided between the two first positioning posts 232. The inserts are arranged in a row, and the apex height of the first positioning posts 232 is higher than the apex height of the inserts 233. The first positioning posts 232 provide connection guidance and positioning for the connector when the operator correctly inserts the battery, and prevent unnecessary damage to the inserts or slots when the operator incorrectly inserts the battery, thus avoiding contact with the battery. Here, the surface of each insert is perpendicular to the extending direction of the first connecting body 231.

[0072] Similar to the structure of the first polar connector 23, the second polar connector 24 includes a second connecting body (not shown in the figure). Two second positioning posts and corresponding inserts or slots are also formed on the second connecting body, and the second positioning posts and the corresponding inserts or slots can satisfy the same height setting relationship.

[0073] Here, the alignment axis perpendicular to the extending direction of the first connecting body 231 serves as the connection alignment axis of the first polarity connector 23. Similarly, in the second connecting body of the second polarity electrical connection 24, the alignment axis perpendicular to the extending direction of the second connecting body serves as the connection alignment axis of the second polarity connector 24. Simultaneously, the connection alignment axes of the first polarity connector 23 and the second polarity connector 24 are coplanar within the second vertical plane A2. The second vertical plane A2 is parallel to the aforementioned first vertical plane A1, ensuring that the guide alignment axis of the battery holder 22 is not coplanar with the connection alignment axis. This ensures that an electrical connection between the battery and the battery holder 22 is only established when the guide portion and polarity connector on the battery holder 22 are correctly aligned, preventing operator error that could damage related components and enhancing safety.

[0074] See Figure 4 and Figure 5 On the first protrusion 2241 of the first base 221, a plurality of first mounting holes 2243 arranged vertically are provided on the first guide surface 2242. A first roller 2244, with its wheel protruding beyond the first guide surface 2242, can be further provided within the first mounting holes 2243. The first roller 2244 can roll in contact with the battery, improving the smoothness of battery insertion and removal and enhancing the user experience. Similarly, the second base 222 is provided with a plurality of second mounting holes (not shown in the figure) arranged vertically, and a second roller (not shown in the figure) with its wheel protruding beyond the second guide surface is provided within the second mounting holes.

[0075] Furthermore, the first protrusion 2241 also has two first vertical side surfaces 2245 located on both sides of the first guide surface 2242. At least one of the first vertical side surfaces 2245 is provided with a plurality of third mounting holes 2246 arranged vertically. A third roller 2247, with its wheel protruding outside the first vertical side surface 2245, is provided within each of the third mounting holes 2246. The third roller 2247 can roll into contact with the battery, further improving the smoothness of battery insertion and removal for the operator. Here, corresponding mounting holes and rollers are provided on both sides of the first vertical side surfaces 2245 of the first guide surface 2242. Similarly, in the second protrusion of the second seat 222, the second protrusion also has two second vertical side surfaces located on both sides of the second guide surface. Each of the two second vertical side surfaces is provided with a plurality of fourth mounting holes arranged vertically. A fourth roller, with its wheel protruding outside the second vertical side surface, is provided within each of the fourth mounting holes.

[0076] In this embodiment, to ensure that both the first seat 221 and the second seat 222 can be stably mounted on the fuselage 21, taking the first seat 221 as an example, the first seat 221 may include a first connecting part 2211 and a second connecting part 2212. The first connecting part 2211 can be connected to the rear crossbeam 211, and the second connecting part 2212 can be connected to the first arm connector 212 connected to the rear crossbeam 211. Specifically, the first connecting part 2211 may be formed on the second connecting part 2212, and the second connecting part 2212 may have a vertically arranged mounting plane. The first connecting part 2211 may have two lugs 2213 protruding from the mounting plane. The two lugs 2213 may be connected to the top side wall and the bottom side wall of the rear crossbeam 211 respectively to form a stable connection relationship for clamping the rear crossbeam 211 and to suppress the vibration of the seat during the flight of the multi-rotor aircraft. The rear crossbeam 211 and the lug 2213 can be fixed by bolt connection. In addition, the second connecting part 2212 is connected to the first arm connecting piece 212, and the battery holder 22 is connected to both the rear crossbeam 211 and the first arm connecting piece 212, which helps to improve the stability of the battery holder 22.

[0077] In this embodiment, to mitigate the adverse effects of the battery holder 22 potentially reducing the load capacity of the multirotor aircraft, multiple weight-reducing holes 2214 are provided on both the first seat body 221 and the second seat body 222. Furthermore, each weight-reducing hole 2214 contains an X-shaped or cross-shaped reinforcing rib to ensure the structural strength of the seat body. It is understood that the first connecting portion 2211 and the second connecting portion 2212 in the first seat body 221 are integrally formed, which helps to improve the structural strength of the battery holder.

[0078] In this embodiment, to achieve more concealed wiring in the multi-rotor aircraft and prevent potential safety hazards caused by exposed wiring, the battery holder 22 is also equipped with a wiring structure. Taking the first base 221 as an example, a wiring channel 2215 is formed on the first base 221. This wiring channel 2215 has two channel ports. One channel port is located at the mounting position of the first polarity connector 23 and is located below the first polarity connector 23, while the other channel port is located on the mounting plane of the aforementioned second connection part 2212. Correspondingly, wiring holes 2111 are provided on the first arm connector 212 and the rear crossbeam 211. The location of each wiring hole 2111 corresponds to the other channel port of the wiring channel 2215, thereby supporting the supply of power from the battery to the relevant power modules through the wiring channel 2215 and the crossbeams or longitudinal beams with hollow cavities. This is beneficial to achieving a simple external appearance of the multi-rotor aircraft and makes the wiring safer.

[0079] Finally, it should be noted that the above-described embodiments are merely specific implementations of this utility model, used to illustrate the technical solutions of this utility model, and not to limit it. The protection scope of this utility model is not limited thereto. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any person skilled in the art can still modify or easily conceive of changes to the technical solutions described in the foregoing embodiments, or make equivalent substitutions for some of the technical features, within the technical scope disclosed in this utility model. Such modifications, changes, or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model, and should all be covered within the protection scope of this utility model.

Claims

1. A multi-rotor aircraft, comprising a fuselage and a battery mount disposed on the fuselage, characterized in that, The battery holder includes a first body and a second body; A reserved gap for battery insertion is provided between the first base and the second base. The first base is provided with a first guide and a first polarity connector; the second base is provided with a second guide and a second polarity connector. The guide center axis of the first guide part and the guide center axis of the second guide part are coplanar in the first vertical plane; The connection center axis of the first polarity connector and the connection center axis of the second polarity connector are coplanar in the second vertical plane; The first vertical plane is parallel to the second vertical plane.

2. The multi-rotor aircraft as described in claim 1, characterized in that, The first guide portion includes a first protrusion that protrudes from the first seat body, and the first protrusion has a first guide surface that extends vertically. The second guide portion includes a second protrusion that protrudes from the second seat body, and the second protrusion has a second guide surface that extends vertically. The first guide surface and the second guide surface are arranged facing each other.

3. The multi-rotor aircraft as described in claim 2, characterized in that, A plurality of first mounting holes arranged vertically are provided on the first guide surface, and a first roller with a wheel body protruding from the first guide surface is provided in the first mounting hole; And / or, A plurality of second mounting holes arranged vertically are provided on the second guide surface, and a second roller with a wheel body protruding from the second guide surface is provided in the second mounting hole.

4. The multi-rotor aircraft as described in claim 2, characterized in that, The first protrusion also has two first vertical sides located on both sides of the first guide surface, and at least one of the first vertical sides is provided with a plurality of third mounting holes arranged vertically, and a third roller with a wheel body protruding out of the vertical side is provided in the third mounting hole; And / or, The second protrusion also has two second vertical sides located on both sides of the second guide surface, and at least one of the second vertical sides is provided with a plurality of fourth mounting holes arranged vertically, and a fourth roller with a wheel body protruding out of the vertical side is provided in the fourth mounting hole.

5. The multi-rotor aircraft as described in claim 1, characterized in that, The first polarity connector includes a first connection body, which extends horizontally in a direction away from the body; The second polarity connector includes a second connection body that extends horizontally in a direction away from the body; The first connecting body and the second connecting body extend in parallel directions.

6. The multi-rotor aircraft as described in claim 5, characterized in that, Two first positioning posts are also formed on the first connecting body, and a plurality of inserts or slots are provided between the two first positioning posts. The apex height of the first positioning posts is higher than the apex height of the inserts or slots; and / or Two second positioning posts are also formed on the second connecting body, and a plurality of inserts or slots are provided between the two second positioning posts; the apex height of the second positioning post is higher than the apex height of the insert or the slot.

7. The multi-rotor aircraft as described in any one of claims 1 to 6, characterized in that, The first base includes a first connecting part and a second connecting part, and the second base includes a third connecting part and a fourth connecting part; The machine body includes a rear crossbeam, and a first machine arm connector and a second machine arm connector are respectively provided at both ends of the rear crossbeam; The first connecting part is connected to the rear crossbeam, the second connecting part is connected to the first arm connecting piece; the third connecting part is connected to the rear crossbeam, and the fourth connecting part is connected to the second arm connecting piece.

8. The multi-rotor aircraft as described in claim 7, characterized in that, The second connecting part includes a vertically arranged mounting plane, which is parallel to the first vertical plane; The first connecting part includes two protrusions on the mounting plane, and the two protrusions are respectively connected to the top side wall and the bottom side wall of the rear crossbeam; Both the first and second bases are provided with multiple weight-reducing holes.

9. The multi-rotor aircraft as described in claim 8, characterized in that, A wiring channel is also formed on the first base body, one channel port of the wiring channel is located below the first polarity connector, and the other channel port of the wiring channel is located on the mounting plane; Wiring holes are provided on the first arm connector and the rear crossbeam, and the position of each wiring hole corresponds to another channel port of the wiring channel.

10. The multi-rotor aircraft as described in claim 7, characterized in that, It also includes a front crossbeam and two longitudinal beams, the front crossbeam and the rear crossbeam being positioned opposite each other, one of the longitudinal beams connecting the front crossbeam and the rear crossbeam to the same side, and the other longitudinal beam connecting the front crossbeam and the rear crossbeam to the other side. The front crossbeam, the rear crossbeam, and the longitudinal beam are all pipes with hollow cavities, and the front crossbeam is installed at a higher height than the rear crossbeam.

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