Multi-rotor aircraft

Abstract

The invention relates to a multi-rotor aircraft. The multi-rotor aircraft comprises a fuselage, a pod and a locking structure, the bottom of the fuselage is recessed to form a mounting groove, the pod can be slidably mounted in the mounting groove through the guide rail assembly in the first direction, the locking structure has a locking state and an unlocking state, when the pod is mounted in the mounting groove, the locking structure can be in the locking state so as to fix the pod in the mounting groove, and when the locking structure is in the unlocking state, the pod is locked in the mounting groove. The pod can be detached in a sliding mode relative to the mounting groove, and the locking structure can be switched from the locking state to the unlocking state by pressing the locking structure. Compared with the prior art, the multi-rotor aircraft has the advantage of being fast to disassemble and assemble, extra tools are not needed to unlock the locking structure, so that the pod is disassembled, the multi-rotor aircraft is very convenient to use, and during installation, only the pod needs to be installed in the installation groove in a sliding mode.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to a multi-rotor aerial vehicle. Background Art

[0002] Unmanned aerial vehicles, also known as drones, are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. Because of their ability to quickly take off, land and recover in confined spaces and complex environments, drones play an important role in emergency rescue. However, due to their low functional configuration or small space, existing drones cannot undertake multiple tasks at the same time in one trip. During the use of drones, in order to increase the functionality of drones, pods are generally installed under the fuselage or wings. Adding a pod can give the drone functions that it does not have. The most common pod can be mounted with gimbals, high-definition cameras and other equipment. Of course, in some usage scenarios, the pod can also be mounted with water guns, pesticide sprayers and other equipment.

[0003] The existing pods are very inconvenient in connecting to drones. Their fastening structures are complex and require external tools to assist in disassembly and assembly. The disassembly and assembly efficiency is not high. In some scenarios where the mounting equipment needs to be replaced frequently, the efficiency is low, resulting in a waste of time. Summary of the invention

[0004] Based on this, the purpose of the present invention is to overcome the deficiencies of the prior art and provide a multi-rotor aircraft.

[0005] In order to achieve the above object, the technical solution adopted by the present invention is:

[0006] A multi-rotor aircraft comprises a fuselage, a pod and a locking structure;

[0007] The bottom of the fuselage is recessed to form a mounting groove, the pod is used to mount external devices, and the pod can be slidably mounted in the mounting groove along a first direction through a guide rail assembly, the guide rail assembly includes a first guide rail and a second guide rail that 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;

[0008] The locking structure has a locked state and an unlocked state. When the pod is installed in the mounting slot, the locking structure can be in a locked state to fix the pod in the mounting slot. When the locking structure is in an unlocked state, the pod can be slid and removed relative to the mounting slot. By pressing the locking structure, the locking structure can be switched from the locked state to the unlocked state.

[0009] It can be seen from the above scheme that the pod of the multi-rotor aircraft of this embodiment can be slidably mounted on the fuselage through the guide rail assembly, the installation process is simple, and a locking structure is provided, the locking structure has a locked state and an unlocked state, when the pod is slidably mounted in the mounting slot, the locking structure is automatically in a locked state, so that the pod is fixed, and the locking structure can be switched from the locked state to the unlocked state by pressing the locking structure, thereby the pod can be slid and removed from the mounting slot. It can be seen that the multi-rotor aircraft of this embodiment has the characteristics of rapid disassembly and assembly, and there is no need to use additional tools to unlock the locking structure, so as to disassemble the pod, which is very convenient to use. When installing, the pod only needs to be slid into the mounting slot.

[0010] As an embodiment, the locking structure includes a locking block, a force applying member, an unlocking button and a locking hole arranged on the first guide rail; the locking block is rotatably arranged on the second guide rail, and the locking block can rotate between a first position and a second position relative to the second guide rail, 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 leaves the locking hole; the force applying member is used to apply an elastic force to the locking block to keep the locking block in the first position; the unlocking button is arranged on the pod, a part of the unlocking button is connected to the locking block, and by pressing the unlocking button, the locking block can be driven to rotate from the first position to the second position.

[0011] As an implementation manner, the force applying member is a spring, a tension spring, a torsion spring or an elastic arm.

[0012] As an implementation manner, the force applying member is a spring, a spring bracket is fixedly provided in the pod, one end of the spring is fixed on the spring bracket, and the other end abuts against the locking block.

[0013] As an embodiment, the guide rail assembly is symmetrically arranged in two.

[0014] As an embodiment, the multi-rotor aircraft further includes two wings, which are symmetrically arranged on opposite sides of the fuselage in the first direction, and a first rotor is arranged on the wing.

[0015] As an embodiment, a tail rotor and a tail motor are arranged at the tail end of the fuselage, a tail cavity is arranged in the tail of the fuselage, an electronic speed regulator is arranged in the tail cavity, the electronic speed regulator is electrically connected to the tail motor, and the output shaft of the tail motor is connected to the tail rotor.

[0016] As an embodiment, a tail heat dissipation port is provided on the outer wall of the fuselage at a position corresponding to the tail cavity, a heat dissipation net is installed at the tail heat dissipation port, the heat dissipation net is in contact with the electronic speed regulator, the heat dissipation net includes a plurality of arranged heat dissipation fins, and the heat dissipation fins extend along the length direction of the fuselage.

[0017] As an embodiment, a battery compartment and an equipment compartment are provided in the fuselage, and a front end heat dissipation port is provided at the front end of the fuselage. The front end heat dissipation port is connected to the battery compartment, the equipment compartment and the tail cavity in sequence through the space inside the fuselage.

[0018] As an embodiment, an opening is provided on the fuselage at a position corresponding to the equipment compartment, the opening cover is provided with a cabin door, a plug-in column is provided on one side of the cabin door, a plug-in hole adapted to the plug-in column is provided on the edge of the opening, and the other side of the cabin door is fixed to the fuselage through a fixing component; the fixing component includes a matching seat, a latch seat, a latch, a first elastic member, a second elastic member and an unlocking member, the matching seat is fixed to the inner wall of the cabin door, a matching hole is provided on the matching seat, the latch seat is fixed to the inner wall of the fuselage, a sliding hole with openings at both ends is provided in the latch seat, and a fixing member connected to the side of the sliding hole is provided on the side of the latch seat. The locking pin is configured to be slidably arranged in the sliding hole, a receiving hole is provided on the side of the locking pin, a clamping column and the first elastic member are provided in the receiving hole, the first elastic member is used to make the clamping column have a tendency to extend out of the receiving hole, when the part of the clamping column extending out of the receiving hole is clamped into the fixing hole, one end of the locking pin is inserted into the matching hole of the matching seat, the second elastic member is provided in the sliding hole, the second elastic member is used to make the locking pin have a tendency to move in a direction away from the matching hole, the unlocking member is movably arranged on the side of the locking pin seat, and the clamping column can be retracted into the receiving hole by pressing the unlocking member.

[0019] For better understanding and implementation, the present invention is described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic structural diagram of a multi-rotor aircraft from one perspective in an embodiment of the present application;

[0021] Figure 2 This is a schematic structural diagram of a multi-rotor aircraft from another perspective in an embodiment of the present application;

[0022] Figure 3 This is a schematic diagram of the explosion structure when the wing and other structures of the multi-rotor aircraft are removed in the embodiment of the present application;

[0023] Figure 4It is a partial cross-sectional schematic diagram of the pod and the mounting slot in the embodiment of the present application (the locking structure is in a locked state);

[0024] Figure 5 It is a partial cross-sectional schematic diagram of the pod and the mounting slot in the embodiment of the present application (the locking structure is in the unlocked state);

[0025] Figure 6 A schematic diagram of the exploded structure when the wing and other structures of the multi-rotor aircraft are removed in an embodiment of the present application (including a partial enlarged view);

[0026] Figure 7 This is a schematic diagram of the explosion structure when the wing and other structures of the multi-rotor aircraft are removed in the embodiment of the present application;

[0027] Figure 8 It is a partial cross-sectional schematic diagram of the cabin door, fuselage and fixing assembly in the embodiment of the present application (the state shown is the state where the pin is inserted into the matching hole);

[0028] Fig. 9 It is a partial cross-sectional schematic diagram of the cabin door, fuselage and fixed assembly in the embodiment of the present application (the state shown is the state when the unlocking member is pressed);

[0029] Fig.10 It is a partial cross-sectional schematic diagram of the cabin door, fuselage and fixing assembly in the embodiment of the present application (the state shown is the state where the latch is away from the matching hole);

[0030] Fig.11 This is a partial enlarged schematic diagram of the front end heat dissipation port in the embodiment of the present application;

[0031] Description of reference numerals:

[0032] 1. Fuselage; 11. Mounting slot; 12. Tail cavity; 13. Electronic speed controller; 14. Tail heat dissipation port; 15. Heat dissipation net; 151. Heat sink; 16. Battery compartment; 17. Equipment compartment; 18. Front heat dissipation port; 181. Pitot tube; 19. Opening; 2. Pod; 21. External device; 3. Locking structure; 31. Locking block; 32. Force member; 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. Matching seat; 811. Matching hole; 82. Latch seat; 821. Sliding hole; 822. Fixing hole; 83. Latch; 831. Accommodating hole; 832. Clamping column; 84. First elastic member; 85. Second elastic member; 86. Unlocking member. DETAILED DESCRIPTION

[0033] To further illustrate each embodiment, the present invention provides drawings. These drawings are part of the disclosure of the present invention, which are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, ordinary technicians in the field should be able to understand other possible implementation methods and advantages of the present invention.

[0034] In the description of the present invention, it is necessary to understand that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "left", "right", "top", "bottom", "inside", "outside", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0035] See also Figures 1 to 10 This embodiment provides a multi-rotor aircraft, which includes: a fuselage 1, a pod 2 and a locking structure 3.

[0036] In this embodiment, the fuselage 1 is a streamlined columnar structure, the fuselage 1 extends along its length direction, and the bottom of the fuselage 1 is recessed to form a mounting groove 11. The pod 2 is used to mount an external device 21, and a mounting structure is provided on the pod 2. The pod 2 can be slidably mounted in the mounting groove 11 along a first direction through a guide rail assembly 4, wherein the first direction in this embodiment 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.

[0037] When the pod 2 is installed in the installation groove 11 , the outer contour of the pod 2 smoothly transitions with the outer contour of the fuselage 1 , thereby maintaining the streamlined appearance of the fuselage 1 .

[0038] The guide rail assembly 4 includes a first guide rail 41 and a second guide rail 42 that slide 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. The pod 2 can be slidably mounted in the mounting groove 11 through the sliding cooperation of the first guide rail 41 and the second guide rail 42. The first guide rail 41 and the second guide rail 42 are both extended along the first direction.

[0039] The locking structure 3 of this embodiment 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 installed in the installation slot 11, the locking structure 3 can be in the locked state to fix the pod 2 in the installation slot 11. When the locking structure 3 is in the unlocked state, the pod 2 can be slid and removed relative to the installation slot 11. By pressing the locking structure 3, the locking structure 3 can be switched from the locked state to the unlocked state.

[0040] It can be seen from the above scheme that the pod 2 of the multi-rotor aircraft of this embodiment is slidably mounted on the fuselage 1 through 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 mounted on the mounting groove 11, the locking structure 3 is automatically in a locked state, so that the pod 2 is fixed, and the locking structure 3 can be switched from the locked state to the unlocked state by pressing it, so that the pod 2 can be slid and removed from the mounting groove 11. It can be seen that the multi-rotor aircraft of this embodiment has the characteristics of rapid disassembly and assembly, and there is no need to use additional tools to unlock the locking structure 3, so as to disassemble the pod 2, which is very convenient to use. When installing, the pod 2 only needs to be slid into the mounting groove 11.

[0041] 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 provided on the first guide rail 41. The locking block 31 is rotatably provided on the second guide rail 42, and the locking block 31 can rotate between a first position and a second position relative to the second guide rail 42. When the locking block 31 is in the first position, the locking block 31 extends into the locking hole 34, and when the locking block 31 is in the second position, the locking block 31 leaves 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.

[0042] The unlock button 33 is disposed on the pod 2 , and a portion of the unlock button 33 is connected to the locking block 31 . By pressing the unlock button 33 , the locking block 31 can be driven to rotate from the first position to the second position.

[0043] like Figure 4-5As shown, by adopting the above locking structure 3, it can be known that when the pod 2 is installed in the installation groove 11, the locking block 31 is kept in the first position under the action of the force member 32, and the locking block 31 on the second guide rail 42 can extend into the locking hole 34 on the first guide rail 41, so that the relative sliding of the second guide rail 42 and the first guide rail 41 is restricted, so that the pod 2 can be fixed in the installation groove 11. When the unlocking button 33 is pressed, the unlocking button 33 can drive the locking block 31 to rotate, so that the locking block 31 rotates from the first position to the second position, and the locking block 31 on the second guide rail 42 leaves the locking hole 34 on the first guide rail 41, so that the second guide rail 42 and the first guide rail 41 can slide relative to each other, so that the pod 2 can be slid and removed from the installation groove 11. That is, when the locking structure 3 is in the locked state, the locking block 31 is in the first position, and when the locking structure 3 is in the unlocked state, the locking block 31 is in the second position.

[0044] The locking structure 3 of this embodiment is cleverly and simply designed, achieves the locking effect with fewer structures, and is easy to use and manufacture.

[0045] It can be understood that the force-applying member 32 is a spring, a tension spring, a torsion spring or an elastic arm, and these components can provide elastic force to the locking block 31. Of course, in some other embodiments, the force-applying member 32 can also be other structures, as long as it can provide elastic force to the locking block 31. Preferably, in this embodiment, the force-applying member 32 is a spring, and a spring bracket 321 is fixedly provided in the pod 2. One end of the spring is fixed to the spring bracket 321, and the other end abuts against the locking block 31. Such a configuration can ensure that the spring is stably fixed.

[0046] In order to improve the installation stability of the pod 2, preferably, the guide rail assembly 4 of this embodiment is symmetrically arranged as two. The two guide rail assemblies 4 can improve the stability of the pod 2 when sliding, and are easy to use, wherein the two guide rail assemblies 4 are symmetrically arranged relative to the first direction.

[0047] Specifically, the multi-rotor aircraft of this embodiment further includes two wings 5, which are symmetrically arranged on opposite sides of the fuselage 1 in the first direction, and a first rotor 51 is arranged on the wing 5. A plurality of first rotors 51 are arranged, and when the plurality of first rotors 51 rotate, the flight operation of the aircraft can be realized.

[0048] Specifically, a tail rotor 61 and a tail motor 62 are provided at the tail end of the fuselage 1, a tail cavity 12 is provided in the tail of the fuselage 1, an electronic speed regulator 13 is provided in the tail cavity 12, the electronic speed regulator 13 is electrically connected to the tail motor 62, and the output shaft of the tail motor 62 is connected to the tail rotor 61. The speed of the motor can be controlled by the electronic speed regulator 13, thereby controlling the speed of the tail rotor 61.

[0049] It should be noted that, since the electronic speed regulator 13 is an essential component for controlling the motor speed in the aircraft, it can play a role in controlling the motor speed. However, since the electronic speed regulator 13 generates a large amount of heat, the aircraft in the prior art does not have a reasonable heat dissipation structure designed to dissipate the heat of the electronic speed regulator 13, which can easily cause the electronic speed regulator 13 to fail to work due to overheating, and in severe cases, damage to the electronic speed regulator 13. Based on this, the outer wall of the fuselage 1 described in this embodiment is provided with a tail heat dissipation port 14 at a position corresponding to the tail cavity 12, and a heat dissipation net 15 is installed at the tail heat dissipation port 14, the heat dissipation net 15 is in contact with the electronic speed regulator 13, and the heat dissipation net 15 includes a plurality of arranged heat dissipation fins 151, and the heat dissipation fins 151 extend along the length direction of the fuselage 1. Through such a setting, when the aircraft is flying, air can flow through the heat dissipation net 15 to dissipate the heat of the electronic speed regulator 13, and the heat dissipation fins 151 are extended along the length direction of the fuselage 1, so that the airflow of the whole machine can be guaranteed to be stable and the heat dissipation effect is better.

[0050] In addition, the fuselage 1 of this embodiment is provided with a battery compartment 16 and an equipment compartment 17. The battery compartment 16 is used to install batteries, and the equipment compartment 17 is used to install electronic components such as controllers required by the aircraft. The front end of the fuselage 1 of this embodiment is provided with a front heat dissipation port 18, and the front heat dissipation port 18 is connected to the battery compartment 16, the equipment compartment 17 and the tail cavity 12 in sequence through the space inside the fuselage 1. By such a configuration, the heat dissipation performance of the whole machine can be further improved. When the aircraft is flying, air flows from the front heat dissipation port 18 into the internal space of the fuselage 1, thereby dissipating heat from the battery compartment 16, the equipment compartment 17 and the tail cavity 12, taking away the heat, and finally the air is discharged from the tail heat dissipation port 14. This design can improve the heat dissipation performance of the whole machine.

[0051] Preferably, an opening 19 is provided on the fuselage 1 at a position corresponding to the equipment compartment 17, and the opening 19 is covered with a door 7. Since the equipment compartment 17 is a relatively important compartment in the whole machine, and the electronic components located in the equipment compartment 17 do not require frequent maintenance operations, the fixation of the door 7 is particularly important, and it is necessary to ensure that the door 7 is firmly fixed. Therefore, preferably, a plug-in column is provided on one side of the door 7 in this embodiment, and a plug-in hole adapted to the plug-in column is provided on the edge of the opening 19, and the other side of the door 7 is fixed to the fuselage 1 through a fixing assembly 8. During installation, the plug-in column of the door 7 is first inserted into the plug-in hole and pre-positioned, and then the fixing assembly 8 is operated so that the fixing assembly 8 fixes the door 7 and the fuselage 1.

[0052] like Figure 8-10 As shown, specifically, in this embodiment, the fixing assembly 8 includes a matching seat 81, a latch seat 82, a latch 83, a first elastic member 84, a second elastic member 85 and an unlocking member 86.

[0053] The matching seat 81 is fixed to the inner wall of the cabin door 7, and a matching hole 811 is provided on the matching seat 81. The latch seat 82 is fixed to the inner wall of the fuselage 1. A sliding hole 821 with openings 19 at both ends is provided in the latch seat 82. A fixing hole 822 connected to the side of the sliding hole 821 is provided on the side of the latch seat 82. The latch 83 is slidably arranged in the sliding hole 821. A receiving hole 831 is provided on the side of the latch 83. A clamping column 832 and the first elastic member 84 are provided in the receiving hole 831. The first elastic member 84 is used to make the clamping column 832 have a tendency to extend out of the receiving hole 831. In other words, the first elastic member 84 can provide elastic force to the clamping column 832 so that the clamping column 832 can partially extend out of the receiving hole 831 in a natural state. When the portion of the clamping column 832 extending out of the accommodating hole 831 is clamped into the fixing hole 822, the position of the latch 83 in the sliding hole 821 is determined, and at this time, one end of the latch 83 is inserted into the matching hole 811 of the matching seat 81, so that the latch seat 82 and the matching seat 81 are fixed to each other, that is, the cabin door 7 and the fuselage 1 are fixed to each other. The second elastic member 85 is arranged in the sliding hole 821, and the second elastic member 85 is used to make the latch 83 have a tendency to move away from the matching hole 811. In other words, the second elastic member 85 provides elastic force to the latch 83 so that the latch 83 can slide in the direction away from the matching hole 811 in a natural state, and at this time, the end of the latch 83 away from the matching hole 811 extends from one end of the sliding hole 821 of the latch seat 82.

[0054] The unlocking member 86 is movably arranged on the side of the latch seat 82, and the clamping column 832 can be retracted into the accommodating hole 831 by pressing the unlocking member 86. As can be seen from the above arrangement, when the cabin door 7 needs to be opened, the clamping column 832 can be retracted into the accommodating hole 831 by pressing the unlocking member 86, so that the matching between the clamping column 832 and the fixing hole 822 is released, and at this time, the latch 83 moves in a direction away from the matching hole 811 under the action of the second elastic member 85, so that the matching between the latch 83 and the matching hole 811 is released, and the cabin door 7 can be removed from the fuselage 1. When installing the cabin door 7, the cabin door 7 is placed on the opening 19, and the end of the latch 83 away from the matching hole 811 is pressed, so that the latch 83 slides in the direction close to the matching hole 811 until the clamping column 832 extends out of the accommodating hole 831 under the action of the first elastic member 84 and is inserted into the fixing hole 822. At this time, the position of the latch 83 is determined, and the latch 83 is inserted into the matching hole 811. Therefore, the latch seat 82 and the matching seat 81 are relatively fixed, and the cabin door 7 can be fixed on the fuselage 1. The cabin door 7 can be effectively fixed by the fixing assembly 8 set as above, and it has high stability, ingenious structure, and is easy to use. In this embodiment, the first elastic member 84 and the second elastic member 85 are both springs.

[0055] like Fig.11 As shown, preferably, a pitot tube 181 is also installed at the front heat dissipation port 18. Since the front heat dissipation port has air flow, by arranging the pitot tube at the front heat dissipation port, the air flow around the pitot tube can be smoother, so that the wind pressure detected by the pitot tube will not be turbulent, and the detected airspeed is more accurate. And the pitot tube is arranged in the front heat dissipation port, which can make the pitot tube and the front heat dissipation port more integrated and more beautiful.

[0056] The above-mentioned embodiments only express several implementation methods of the present invention, and the description thereof is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention. It should be pointed out that for ordinary technicians in this field, several variations and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention.

Claims

1. A multi-rotor aircraft, characterized in that: include: fuselage, pod and locking structure; The bottom of the fuselage is recessed to form a mounting groove, the pod is used to mount external devices, and the pod can be slidably mounted in the mounting groove along a first direction through a guide rail assembly, the guide rail assembly includes a first guide rail and a second guide rail that 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; The locking structure has a locked state and an unlocked state. When the pod is installed in the mounting slot, the locking structure can be in a locked state to fix the pod in the mounting slot. When the locking structure is in an unlocked state, the pod can be slid and removed relative to the mounting slot. By pressing the locking structure, the locking structure can be switched from the locked state to the unlocked state.

2. The multi-rotor aircraft according to claim 1, characterized in that: The locking structure comprises a locking block, a force applying member, an unlocking button and a locking hole arranged on the first guide rail; The locking block is rotatably disposed on the second guide rail, and 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 leaves the locking hole. The force applying member is used to apply an elastic force to the locking block so that the locking block is kept in the first position; The unlocking button is arranged on the pod, and a part of the unlocking button is connected with the locking block. By pressing the unlocking button, the locking block can be driven to rotate from the first position to the second position.

3. The multi-rotor aircraft according to claim 2, characterized in that: The force applying member is a spring, a tension spring, a torsion spring or an elastic arm.

4. The multi-rotor aircraft according to claim 3, characterized in that: The force applying member is a spring, a spring bracket is fixedly arranged in the pod, one end of the spring is fixed on the spring bracket, and the other end abuts against the locking block.

5. The multi-rotor aircraft according to claim 1, characterized in that: The guide rail components are symmetrically arranged in two.

6. The multi-rotor aircraft according to claim 1, characterized in that: It also includes two wings, which are symmetrically arranged on opposite sides of the fuselage in the first direction, and a first rotor is arranged on the wings.

7. The multi-rotor aircraft according to any one of claims 1 to 6, characterized in that: A tail rotor and a tail motor are arranged at the tail end of the fuselage, a tail cavity is arranged in the tail of the fuselage, an electronic speed regulator is arranged in the tail cavity, the electronic speed regulator is electrically connected to the tail motor, and an output shaft of the tail motor is connected to the tail rotor.

8. The multi-rotor aircraft according to claim 7, characterized in that: A tail heat dissipation port is arranged at a position of the outer wall of the fuselage corresponding to the tail cavity, a heat dissipation net is installed at the tail heat dissipation port, the heat dissipation net is in contact with the electronic speed regulator, the heat dissipation net includes a plurality of arranged heat dissipation fins, and the heat dissipation fins extend along the length direction of the fuselage.

9. The multi-rotor aircraft according to claim 8, characterized in that: A battery compartment and an equipment compartment are arranged in the fuselage, and a front heat dissipation port is arranged at the front end of the fuselage. The front heat dissipation port is connected to the battery compartment, the equipment compartment and the tail cavity in sequence through the space inside the fuselage.

10. The multi-rotor aircraft according to claim 9, characterized in that: An opening is provided on the fuselage at a position corresponding to the equipment compartment, the opening cover is provided with a door, a plug-in column is provided on one side of the door, a plug-in hole adapted to the plug-in column is provided on the edge of the opening, and the other side of the door is fixed to the fuselage through a fixing assembly; The fixing assembly comprises a matching seat, a latch seat, a latch, a first elastic member, a second elastic member and an unlocking member, wherein the matching seat is fixed to the inner wall of the cabin door, the matching seat is provided with a matching hole, the latch seat is fixed to the inner wall of the fuselage, a sliding hole with two ends opening is provided in the latch seat, a fixing hole connected to the side of the sliding hole is provided on the side of the latch seat, the latch can be slidably arranged in the sliding hole, a receiving hole is provided on the side of the latch, a clamping column and the first elastic member are provided in the receiving hole, the first elastic member is used to make the clamping column have a tendency to extend out of the receiving hole, when the part of the clamping column extending out of the receiving hole is clamped into the fixing hole, one end of the latch is inserted into the matching hole of the matching seat, the second elastic member is provided in the sliding hole, the second elastic member is used to make the latch have a tendency to move in a direction away from the matching hole, and the unlocking member is movably arranged on the side of the latch seat, and the clamping column can be retracted into the receiving hole by pressing the unlocking member.

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