Multi-rotor aircraft with efficient heat dissipation function

Abstract

The utility model relates to a multi-rotor aircraft capable of dissipating heat efficiently. The multi-rotor aircraft comprises an aircraft body, a tail rotor and a tail motor are arranged at the tail end of the fuselage, a tail containing cavity is formed in the tail of the fuselage, and an electronic speed regulator is arranged in the tail containing cavity; a tail heat dissipation opening is formed in the position, corresponding to the tail containing cavity, of the outer wall of the machine body, a heat dissipation net is installed at the tail heat dissipation opening and makes contact with the electronic speed regulator, the heat dissipation net comprises a plurality of heat dissipation fins arranged in an arrayed mode, and the heat dissipation fins extend in the length direction of the machine body; a battery compartment and an equipment compartment are arranged in the fuselage, a front end heat dissipation opening is formed in the front end of the fuselage, and the front end heat dissipation opening is sequentially communicated with the battery compartment, the equipment compartment and the tail containing cavity through the space in the fuselage; and a pitot tube is also mounted at the heat dissipation opening at the front end. The multi-rotor aircraft provided by the embodiment of the utility model has an efficient heat dissipation effect, and the pitot tube is arranged at the heat dissipation port at the front end, so that the airflow around the pitot tube can flow more smoothly, and the detected airspeed is more accurate.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned aerial vehicle technical field, in particular to a kind of multi-rotor aircraft of high efficiency heat dissipation. BACKGROUND

[0002] Unmanned aerial vehicle, also known as unmanned aerial vehicle, is the unmanned aircraft using radio remote control equipment and self-provided program control device to operate. Because it has the ability to quickly implement take-off and recovery in small space and complex environment, the unmanned aerial vehicle plays an important function in first aid.

[0003] Electronic speed controller is the necessary component in aircraft to control motor speed, which can control motor speed. However, since electronic speed controller has large heat, the aircraft in the prior art does not have a reasonable heat dissipation structure to dissipate heat of electronic speed controller, which can easily cause electronic speed controller to fail to work due to overheating, and even cause damage to electronic speed controller. In addition, the overall heat dissipation structure of the existing aircraft is not reasonable enough, and cannot play the function of high-efficiency heat dissipation, and the installation position of pitot tube has defects, resulting in inaccurate airspeed detection. SUMMARY

[0004] Therefore, the utility model aims at overcoming the defects of the prior art, and provides a kind of multi-rotor aircraft of high efficiency heat dissipation.

[0005] To achieve the above-mentioned purpose, the utility model adopts the technical scheme that:

[0006] A kind of multi-rotor aircraft of high efficiency heat dissipation, it includes: fuselage;

[0007] The tail end of the fuselage is provided with tail rotor and tail motor, and the tail end of the fuselage is provided with tail cavity, and the tail cavity is provided with electronic speed controller, and the electronic speed controller is electrically connected with the tail motor, and the output shaft of the tail motor is connected with the tail rotor;

[0008] The outer wall of the fuselage is provided with tail heat dissipation port at the position corresponding to the tail cavity, and the tail heat dissipation port is provided with heat dissipation net, and the heat dissipation net is in contact with the electronic speed controller, and the heat dissipation net includes a plurality of heat dissipation fins arranged in line, and the heat dissipation fins extend along the length direction of the fuselage;

[0009] The fuselage is provided with battery cabin and equipment cabin, and the front end of the fuselage is provided with front end heat dissipation port, and the front end heat dissipation port is sequentially communicated with the battery cabin, equipment cabin and tail cavity through the space inside the fuselage;

[0010] The front end heat dissipation port is also provided with pitot tube.

[0011] Through the above scheme, the multi-rotor aircraft has the effect of efficient heat dissipation, and the Pitot tube is arranged at the front end heat dissipation opening, so that the airflow around the Pitot tube flows more smoothly, so that the wind pressure detected by the Pitot tube is not disturbed, the airspeed detected is more accurate, and the overall use effect is better.

[0012] As an implementation form, the multi-rotor aircraft further comprises a pod and a locking structure.

[0013] The bottom of the fuselage is recessed to form a mounting groove, the pod is used for mounting external devices, the pod is slidably mounted into the mounting groove in a first direction through a guide rail assembly, the guide rail assembly comprises a first guide rail and a second guide rail which are slidably matched with each other, the first guide rail is fixed in the mounting groove, and the second guide rail is fixed on the pod.

[0014] The locking structure has a locked state and an unlocked state, when the pod is mounted in the mounting groove, the locking structure can be in the locked state to fix the pod in the mounting groove, when the locking structure is in the unlocked state, the pod can be slidably detached relative to the mounting groove, and the locking structure can be switched from the locked state to the unlocked state by pressing the locking structure.

[0015] As an implementation form, the outer contour of the pod and the outer contour of the fuselage are smoothly transitioned.

[0016] As an implementation form, the locking structure comprises a locking block, a force applying member, an unlocking button and a locking hole arranged on the first guide rail.

[0017] The locking block is rotatably arranged on the second guide rail, the locking block can rotate relative to the second guide rail between a first position and a second position, when the locking block is in the first position, the locking block extends into the locking hole, and when the locking block is in the second position, the locking block is away from the locking hole.

[0018] The force applying member is used for applying an elastic force to the locking block to keep the locking block in the first position.

[0019] The unlocking button is arranged on the pod, a part of the unlocking button is connected with the locking block, and the locking block can be driven to rotate from the first position to the second position by pressing the unlocking button.

[0020] As an implementation form, the force applying member is a spring, a tension spring, a torsion spring or an elastic arm.

[0021] As an implementation form, the force applying member is a spring, a spring support is fixedly arranged in the pod, one end of the spring is fixed on the spring support, and the other end abuts against the locking block.

[0022] As an implementation form, the guide rail assembly is symmetrically arranged in two.

[0023] As an implementation form, the first guide rail and the second guide rail are arranged in extension along the first direction.

[0024] As an implementation form, the multi-rotor aircraft further comprises two wings, the two wings are symmetrically arranged on opposite sides of the fuselage in the first direction, and the wings are provided with first rotors.

[0025] As an implementation form, an opening is arranged on the fuselage corresponding to the equipment cabin, a cabin door is arranged on the opening, a plug-in post is arranged on one side of the cabin door, a plug-in hole matched with the plug-in post is arranged on the edge of the opening, and the other side of the cabin door is fixed to the fuselage through a fixing assembly.

[0026] The fixing assembly comprises a matching seat, a plug-in seat, a plug-in pin, a first elastic member, a second elastic member and an unlocking member, the matching seat is fixed in the inner wall of the cabin door, the matching seat is provided with a matching hole, the plug-in seat is fixed in the inner wall of the fuselage, the plug-in seat is provided with a sliding hole with two open ends, the side of the plug-in seat is provided with a fixing hole communicated to the side of the sliding hole, the plug-in pin is slidably arranged in the sliding hole, the side of the plug-in pin is provided with a containing hole, the containing hole is provided with a clamping post and the first elastic member, the first elastic member is used to make the clamping post have a tendency to protrude out of the containing hole, when the part of the clamping post protruding out of the containing hole is clamped into the fixing hole, one end of the plug-in pin is inserted into the matching hole of the matching seat, the second elastic member is arranged in the sliding hole, and the second elastic member is used to make the plug-in pin have a tendency to move away from the matching hole, and the unlocking member is movably arranged on the side of the plug-in seat, and the clamping post can be retracted into the containing hole by pressing the unlocking member.

[0027] In order to better understand and implement, the utility model is described in detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 It is a structure schematic view of a multi-rotor aircraft in a view angle in the embodiment of the application.

[0029] Figure 2 It is a structure schematic view of a multi-rotor aircraft in another view angle in the embodiment of the application.

[0030] Figure 3Figure 1 is a schematic diagram of the exploded structure of a multi-rotor aircraft in the embodiment of the present application when the wing and other structures are removed;

[0031] Figure 4 Figure 2 is a schematic diagram of the partial section at the location of the nacelle and mounting slot in the embodiment of the present application (the locking structure is in the locked state);

[0032] Figure 5 Figure 3 is a schematic diagram of the partial section at the location of the nacelle and mounting slot in the embodiment of the present application (the locking structure is in the unlocked state);

[0033] Figure 6 Figure 4 is a schematic diagram of the exploded structure of a multi-rotor aircraft in the embodiment of the present application when the wing and other structures are removed (including a partial enlarged view);

[0034] Figure 7 Figure 5 is a schematic diagram of the exploded structure of a multi-rotor aircraft in the embodiment of the present application when the wing and other structures are removed;

[0035] Figure 8 Figure 6 is a schematic diagram of the partial section of the door, fuselage and fixing assembly in the embodiment of the present application (the state shown is that of the insertion of the pin into the mating hole);

[0036] Figure 9 Figure 7 is a schematic diagram of the partial section of the door, fuselage and fixing assembly in the embodiment of the present application (the state shown is that when the unlocking piece is pressed);

[0037] Figure 10 Figure 8 is a schematic diagram of the partial section of the door, fuselage and fixing assembly in the embodiment of the present application (the state shown is that of the pin leaving the mating hole);

[0038] Figure 11 Figure 9 is a partial enlarged schematic diagram of the front end heat dissipation opening in the embodiment of the present application;

[0039] Legend of reference signs:

[0040] 1, fuselage; 11, mounting slot; 12, tail cavity; 13, electronic speed controller; 14, tail heat dissipation opening; 15, heat dissipation net; 151, heat dissipation fin; 16, battery cabin; 17, equipment cabin; 18, front end heat dissipation opening; 181, Pitot tube; 19, opening; 2, nacelle; 21, external device; 3, locking structure; 31, locking block; 32, force applying piece; 321, spring bracket; 33, unlocking button; 34, locking hole; 4, guide rail assembly; 41, first guide rail; 42, second guide rail; 5, wing; 51, first rotor; 61, tail rotor; 62, tail motor; 7, door; 8, fixing assembly; 81, mating seat; 811, mating hole; 82, pin seat; 821, sliding hole; 822, fixing hole; 83, pin; 831, accommodating hole; 832, clamping column; 84, first elastic piece; 85, second elastic piece; 86, unlocking piece. DETAILED DESCRIPTION

[0041] To further illustrate the embodiments, the utility model provides the drawings. These drawings are part of the utility model disclosure, which is mainly used to illustrate the embodiments, and can be explained with the related description of the specification to explain the operating principle of the embodiments. With reference to these contents, those skilled in the art should understand other possible embodiments and the advantages of the utility model.

[0042] In the description of the utility model, it should be understood that the orientation or positional relationship indicated by the terms 'center', 'longitudinal', 'transverse', 'length', 'width', 'thickness', 'upper', 'lower', 'left', 'right', 'top', 'bottom', 'inner', 'outer', 'axial', 'radial', 'circumferential' and the like is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the utility model and simplifying the description, and does not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation of the utility model.

[0043] Please refer to Figures 1-3 , Figures 6-7 and Figure 11 , the embodiment provides a multi-rotor aircraft, which comprises a fuselage 1.

[0044] Specifically, the tail end of the fuselage 1 is provided with a tail rotor 61 and a tail motor 62, a tail cavity 12 is arranged in the tail of the fuselage 1, an electronic speed regulator 13 is arranged in the tail cavity 12, the electronic speed regulator 13 is electrically connected with the tail motor 62, and the output shaft of the tail motor 62 is connected with the tail rotor 61. The rotation speed of the motor can be controlled through the electronic speed regulator 13, so as to control the rotation speed of the tail rotor 61.

[0045] It should be noted that, since the electronic speed governor 13 is a necessary component for controlling the rotation speed of the motor in the aircraft, it can control the rotation speed of the motor. However, since the electronic speed governor 13 generates a large amount of heat, the aircraft in the prior art does not have a reasonable heat dissipation structure to dissipate heat for the electronic speed governor 13, which is easy to cause the electronic speed governor 13 to be unable to work due to overheating, and even cause damage to the electronic speed governor 13. Based on this, the tail heat dissipation port 14 is arranged at the position corresponding to the tail cavity 12 of the outer wall of the fuselage 1, the heat dissipation net 15 is arranged at the tail heat dissipation port 14, the heat dissipation net 15 is in contact with the electronic speed governor 13, and the heat dissipation net 15 comprises a plurality of heat dissipation fins 151 arranged in an array and extending along the length direction of the fuselage 1. Through such arrangement, when the aircraft is flying, air can flow through the heat dissipation net 15 to dissipate heat for the electronic speed governor 13, and the heat dissipation fins 151 are arranged to extend along the length direction of the fuselage 1, so that the air flow of the whole machine is stable, and the heat dissipation effect is better.

[0046] In addition, the battery cabin 16 and the equipment cabin 17 are arranged in the fuselage 1, the battery cabin 16 is used for mounting a battery, and the equipment cabin 17 is used for mounting electronic components such as controllers required by the aircraft, wherein the front end heat dissipation port 18 is arranged at the front end of the fuselage 1, and the front end heat dissipation port 18 is sequentially communicated with the battery cabin 16, the equipment cabin 17 and the tail cavity 12 through the space inside the fuselage 1. Through such arrangement, the heat dissipation performance of the whole machine can be further improved, when the aircraft is flying, air flows into the space inside the fuselage 1 from the front end heat dissipation port 18, thereby dissipating heat for the battery cabin 16, the equipment cabin 17 and the tail cavity 12, and taking away heat, and finally air is discharged from the tail heat dissipation port 14. The design can improve the heat dissipation performance of the whole machine.

[0047] As shown in Figure 11 Preferably, the pitot tube 181 is arranged at the front end heat dissipation port 18, since the front end heat dissipation port has air flow, by arranging the pitot tube at the front end heat dissipation port, the air flow around the pitot tube is more smooth, so that the wind pressure detected by the pitot tube is not disturbed, and the detected air speed is more accurate. Moreover, the pitot tube is arranged in the front end heat dissipation port, so that the pitot tube and the front end heat dissipation port are more integral and more beautiful.

[0048] Therefore, the multi-rotor aircraft has the effect of efficient heat dissipation, and the pitot tube is arranged at the front end heat dissipation port, so that the air flow around the pitot tube is more smooth, so that the wind pressure detected by the pitot tube is not disturbed, and the detected air speed is more accurate, so that the overall use effect is better.

[0049] Further, the multi-rotor aircraft with high heat dissipation efficiency of the embodiment further comprises the pod 2 and the locking structure 3. The existing pod has great inconvenience in the connection with the aircraft, the fastening structure thereof is complex, external tools need to be used to assist in disassembly and assembly, the disassembly and assembly efficiency is not high, in some scenes where the mounting device needs to be frequently replaced, the efficiency is not high, time is wasted.

[0050] Therefore, preferably, in the embodiment, the fuselage 1 is a columnar structure with a streamlined shape, the fuselage 1 extends along the length direction thereof, and the bottom of the fuselage 1 is recessed to form a mounting groove 11. The pod 2 is used to mount external devices 21, and the pod 2 is provided with a mounting structure. The pod 2 is slidably mounted into the mounting groove 11 through a guide rail assembly 4 in a first direction, wherein in the embodiment, the first direction is a horizontal direction perpendicular to the length direction of the fuselage 1, and of course in some embodiments, the first direction can also be a vertical direction perpendicular to the length direction of the fuselage 1.

[0051] When the pod 2 is mounted in the mounting groove 11, the outer contour of the pod 2 and the outer contour of the fuselage 1 are smoothly transitioned, so that the streamlined shape of the fuselage 1 is maintained in appearance.

[0052] The guide rail assembly 4 comprises a first guide rail 41 and a second guide rail 42 that are slidably matched with each other, the first guide rail 41 is fixed in the mounting groove 11, and the second guide rail 42 is fixed on the pod 2. Through the sliding fit of the first guide rail 41 and the second guide rail 42, the pod 2 is slidably mounted in the mounting groove 11. The first guide rail 41 and the second guide rail 42 both extend along the first direction.

[0053] The locking structure 3 is used to lock the position of the pod 2. Specifically, the locking structure 3 has a locked state and an unlocked state. When the pod 2 is mounted in the mounting groove 11, the locking structure 3 can be in the locked state to fix the pod 2 in the mounting groove 11, and when the locking structure 3 is in the unlocked state, the pod 2 can be slidably disassembled relative to the mounting groove 11. By pressing the locking structure 3, the locking structure 3 can be switched from the locked state to the unlocked state.

[0054] As can be seen from the above scheme, the pod 2 of the multi-rotor aircraft in this embodiment is slidably mounted on the fuselage 1 via the guide rail assembly 4. The installation process is simple, and a locking structure 3 is provided. The locking structure 3 has a locked state and an unlocked state. When the pod 2 is slidably installed in the mounting slot 11, the locking structure 3 automatically enters the locked state, thus fixing the pod 2. By pressing the locking structure 3, it can be switched from the locked state to the unlocked state, thereby allowing the pod 2 to be slidably removed from the mounting slot 11. It is evident that the multi-rotor aircraft in this embodiment has the characteristics of quick assembly and disassembly, without the need for additional tools to unlock the locking structure 3, thus disassembling the pod 2. It is very convenient to use; during installation, the pod 2 can simply be slid into the mounting slot 11.

[0055] Specifically, in this embodiment, the locking structure 3 includes a locking block 31, a force-applying member 32, an unlocking button 33, and a locking hole 34 disposed on the first guide rail 41. The locking block 31 is rotatably disposed on the second guide rail 42, and the locking block 31 can rotate relative to the second guide rail 42 between a first position and a second position. When the locking block 31 is in the first position, the locking block 31 extends into the locking hole 34; when the locking block 31 is in the second position, the locking block 31 disengages from the locking hole 34. The force-applying member 32 is used to apply an elastic force to the locking block 31 to keep the locking block 31 in the first position.

[0056] The unlock button 33 is located on the pod 2. A part of the unlock button 33 is connected to the locking block 31. By pressing the unlock button 33, the locking block 31 can be rotated from the first position to the second position.

[0057] like Figures 4-5 As shown, by employing the locking structure 3 described above, when the pod 2 is installed in the mounting slot 11, the locking block 31 is held in the first position under the action of the force-applying member 32. At this time, the locking block 31 on the second guide rail 42 can extend into the locking hole 34 on the first guide rail 41, thereby restricting the relative sliding of the second guide rail 42 and the first guide rail 41, thus allowing the pod 2 to be fixed in the mounting slot 11. When the unlocking button 33 is pressed, the unlocking button 33 can drive the locking block 31 to rotate, causing the locking block 31 to rotate from the first position to the second position. At this time, the locking block 31 on the second guide rail 42 leaves the locking hole 34 on the first guide rail 41, thereby allowing the second guide rail 42 and the first guide rail 41 to slide relative to each other, thus allowing the pod 2 to be slidably removed from the mounting slot 11. In other words, when the locking structure 3 is in the locked state, the locking block 31 is in the first position; when the locking structure 3 is in the unlocked state, the locking block 31 is in the second position.

[0058] The locking structure 3 of the embodiment has a clever and simple structure design, and realizes the locking effect by using less structure, and is convenient to use and manufacture.

[0059] It can be understood that the force applying member 32 is a spring, a tension spring, a torsion spring or an elastic arm, which can provide an elastic force to the locking block 31. Of course, in other embodiments, the force applying member 32 can also be other structures as long as it can provide an elastic force to the locking block 31. Preferably, in the embodiment, the force applying member 32 is a spring, and a spring bracket 321 is fixedly arranged in the gondola 2, one end of the spring is fixed on the spring bracket 321, and the other end abuts against the locking block 31. In this way, the spring can be stably fixed.

[0060] In order to improve the installation stability of the gondola 2, preferably, the guide rail assemblies 4 are symmetrically arranged in two. The two guide rail assemblies 4 can improve the stability of the gondola 2 when sliding, and are convenient to use. The two guide rail assemblies 4 are symmetrically arranged relative to the first direction.

[0061] Specifically, the multi-rotor aircraft of the embodiment further comprises two wings 5, which are symmetrically arranged on opposite sides of the fuselage 1 in the first direction, and the first rotor 51 is arranged on the wing 5. The first rotor 51 is arranged in a plurality, and when the plurality of first rotors 51 rotates, the flight operation of the aircraft can be realized.

[0062] Preferably, the opening 19 corresponding to the position of the equipment cabin 17 is arranged on the fuselage 1, and the hatch 7 is arranged on the opening 19. Since the equipment cabin 17 is a relatively important cabin in the whole machine, the electronic components in the equipment cabin 17 do not need to be frequently maintained, and therefore, the fixing of the hatch 7 is particularly important, and needs to ensure that the hatch 7 is fixed firmly. Therefore, preferably, one side of the hatch 7 is provided with a plug-in column, the edge of the opening 19 is provided with a plug-in hole matched with the plug-in column, and the other side of the hatch 7 is fixed to the fuselage 1 by the fixing assembly 8. During installation, first, the plug-in column of the hatch 7 is inserted into the plug-in hole for pre-positioning, and then the fixing assembly 8 is operated to fix the hatch 7 and the fuselage 1.

[0063] As shown in the figure, Figures 8-10 Specifically, in the embodiment, the fixing assembly 8 comprises a matching seat 81, a bolt seat 82, a bolt 83, a first elastic member 84, a second elastic member 85 and an unlocking member 86.

[0064] The mating seat 81 is fixed to the inner wall of the hatch 7. The mating seat 81 is provided with a mating hole 811. The pin seat 82 is fixed to the inner wall of the fuselage 1. The pin seat 82 is provided with a sliding hole 821 with openings 19 at both ends. The side of the pin seat 82 is provided with a fixing hole 822 communicating with the side of the sliding hole 821. The pin 83 is slidably disposed in the sliding hole 821. The side of the pin 83 is provided with a receiving hole 831. The receiving hole 831 is provided with a locking post 832 and the first elastic member 84. The first elastic member 84 is used to make the locking post 832 tend to extend out of the receiving hole 831. In other words, the first elastic member 84 can provide elastic force to the locking post 832 so that the locking post 832 can partially extend out of the receiving hole 831 in its natural state. When the portion of the locking pin 832 extending out of the receiving hole 831 engages with the fixing hole 822, the position of the pin 83 within the sliding hole 821 is determined. At this time, one end of the pin 83 is inserted into the mating hole 811 of the mating seat 81, thereby fixing the pin seat 82 and the mating seat 81 to each other, i.e., fixing the hatch 7 and the fuselage 1 to each other. The second elastic element 85 is disposed within the sliding hole 821. The second elastic element 85 is used to give the pin 83 a tendency to move away from the mating hole 811. In other words, the second elastic element 85 provides elastic force to the pin 83, allowing the pin 83 to slide away from the mating hole 811 in its natural state. At this time, the end of the pin 83 away from the mating hole 811 extends from one end of the sliding hole 821 of the pin seat 82.

[0065] The unlocking element 86 is movably disposed on the side of the pin seat 82. By pressing the unlocking element 86, the locking pin 832 can be retracted into the receiving hole 831. As can be seen from the above configuration, when it is necessary to open the hatch 7, pressing the unlocking element 86 can retract the locking pin 832 into the receiving hole 831, thereby disengaging the engagement between the locking pin 832 and the fixing hole 822. At this time, the pin 83 moves away from the mating hole 811 under the action of the second elastic element 85, thereby disengaging the engagement between the pin 83 and the mating hole 811, and the hatch 7 can be removed from the fuselage 1. When installing the hatch 7, the hatch 7 is placed on the opening 19. At this time, the end of the pin 83 away from the mating hole 811 is pressed, causing the pin 83 to slide towards the mating hole 811 until the locking pin 832 extends out of the receiving hole 831 and inserts into the fixing hole 822 under the action of the first elastic member 84. At this point, the position of the pin 83 is determined, and the pin 83 is inserted into the mating hole 811. Therefore, the pin seat 82 and the mating seat 81 are relatively fixed, and the hatch 7 can be fixed to the fuselage 1. The fixing assembly 8 configured as described above can effectively fix the hatch 7, and it has high stability, ingenious structure, and is easy to use. In this embodiment, both the first elastic member 84 and the second elastic member 85 are springs.

[0066] The above-described embodiments only express several implementation manners of the utility model, the description is more specific and detailed, but can not therefore be understood as the limitation to the utility model range. It should be pointed out that for ordinary skilled person in the art, under the premise of not departing from the utility model concept, still can make several deformation and improvement, these all belong to the protection range of the utility model.

Claims

1. A multi-copter aircraft with high heat dissipation, characterized in that, The utility model relates to a high -efficient heat dissipation's multi -rotor aircraft, including: The fuselage is provided with tail rotor and tail motor at the tail end, and the tail cavity is arranged in the tail of the fuselage, and the electronic speed controller is arranged in the tail cavity, and the electronic speed controller is electrically connected with the tail motor, and the output shaft of the tail motor is connected with the tail rotor; The outer wall of the fuselage is provided with tail heat dissipation opening at the position corresponding to the tail cavity, and the heat dissipation net is installed at the tail heat dissipation opening, and the heat dissipation net is in contact with the electronic speed controller, and the heat dissipation net comprises a plurality of heat dissipation fins arranged in line, and the heat dissipation fins extend along the length direction of the fuselage; The battery cabin and the equipment cabin are arranged in the fuselage, and the front end heat dissipation opening is arranged at the front end of the fuselage, and the front end heat dissipation opening is sequentially communicated with the battery cabin, the equipment cabin and the tail cavity through the space inside the fuselage; The pitot tube is also installed at the front end heat dissipation opening.

2. The high-efficiency heat dissipation multi-rotor aircraft of claim 1, further comprising a pod and a locking structure.

3. The high-efficiency heat dissipation multi-rotor aircraft of claim 2, wherein an outer contour of the pod smoothly transitions to an outer contour of the fuselage.

4. The high-efficiency heat dissipation multi-rotor aircraft of claim 2, wherein the locking structure comprises a locking block, a biasing member, an unlocking button, and a locking hole defined in the first rail.

5. The high-efficiency heat dissipation multi-rotor aircraft of claim 4, wherein the biasing member is a spring, a tension spring, a torsion spring, or an elastic arm.

6. The high-efficiency heat dissipation multi-rotor aircraft of claim 5, wherein the first rail and the second rail are slidably coupled to each other. ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ The force applying member is a spring, a spring support is fixedly arranged in the pod, one end of the spring is fixed on the spring support, and the other end abuts against the locking block.

7. The multi-rotor aircraft of claim 2, wherein: The guide rail assemblies are symmetrically arranged in two.

8. The multi-rotor aircraft of claim 2, wherein: The first guide rail and the second guide rail are arranged in extension along the first direction.

9. The multi-rotor aircraft of claim 2, wherein: Two wings are further included, the two wings are symmetrically arranged on opposite sides of the fuselage in the first direction, and the wings are provided with first rotors.

10. The multi-rotor aircraft of any one of claims 1-9, wherein: An opening is arranged on the fuselage corresponding to the position of the equipment cabin, a hatch is arranged on the opening, one side of the hatch is provided with a plug-in column, the edge of the opening is provided with a plug-in hole matched with the plug-in column, and the other side of the hatch is fixed to the fuselage through a fixing assembly; The fixing assembly includes a matching seat, a plug-in seat, a plug-in pin, a first elastic member, a second elastic member, and an unlocking member, the matching seat is fixed in the inner wall of the hatch, the matching seat is provided with a matching hole, the plug-in seat is fixed in the inner wall of the fuselage, the plug-in seat is provided with a sliding hole with open ends, the side of the plug-in seat is provided with a fixed hole communicated to the side of the sliding hole, the plug-in pin is slidably arranged in the sliding hole, the side of the plug-in pin is provided with a containing hole, the containing hole is provided with a clamping column and the first elastic member, the first elastic member is used to make the clamping column have a tendency to protrude out of the containing hole, when the part of the clamping column protruding out of the containing hole is clamped into the fixed hole, one end of the plug-in pin is inserted into the matching hole of the matching seat, the second elastic member is arranged in the sliding hole, and the second elastic member is used to make the plug-in pin have a tendency to move away from the matching hole, the unlocking member is movably arranged on the side of the plug-in seat, and the clamping column can be retracted into the containing hole by pressing the unlocking member.

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