Unmanned aircraft with external emergency power supply function

Abstract

The invention relates to the technical field of aircrafts, and provides an unmanned aircraft with an external emergency power supply function, the unmanned aircraft comprises a rack, the rack is provided with a power system, a power generation system, a transmission system and a rotor wing system; the power system comprises an engine and an oil tank, and the engine and the oil tank are both arranged on the rack; the power generation system comprises a generator and a power generation control box, the generator is arranged on an output shaft of the engine, and the power generation control box is arranged on the rack; the transmission system comprises a transmission shaft, a transmission structure and a linkage assembly, the transmission shaft is coaxially and rotationally arranged at the end of an output shaft of the engine, the transmission structure is arranged at the end, away from the engine, of the transmission shaft, and the linkage assembly is used for linkage of the transmission shaft and the output shaft of the engine. The rotor wing system comprises a rotor wing main shaft and rotor wing pieces, the rotor wing main shaft is rotationally arranged on the rack, the rotor wing pieces are arranged on the rotor wing main shaft, and the rotor wing main shaft is in transmission connection with the transmission structure.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to an unmanned aircraft with external emergency power supply function. BACKGROUND

[0002] The content of this part only provides background information related to the present application, which may not constitute prior art.

[0003] An unmanned aircraft is an aerial platform that flies through remote control or autonomous program, which has rapidly expanded from early military fields to civilian and emergency rescue scenarios. Current technology development has achieved high-precision positioning, complex environment obstacle avoidance, long-endurance flight and modular load integration. Industrial-grade unmanned aerial vehicles have strong environmental adaptability and task flexibility. Multi-rotor, vertical take-off and landing fixed-wing and other models gradually become key equipment in disaster reconnaissance, material delivery and other actions.

[0004] In the three-disaster area scene of power failure, network failure and circuit failure, unmanned aircrafts bear important rescue functions with air space breakthrough capability, mainly including the following parts: disaster reconnaissance and evaluation, through the optical or thermal imaging sensor carried, quickly obtain the panoramic image of the disaster area, identify road damage, building collapse and personnel trapped position; Emergency material precise delivery, through the tethered air drop or precise throwing system to deliver medical supplies, food, drinking water and other survival materials to isolated areas; Communication relay guarantee, carry mobile communication base station to build temporary communication network, restore the communication channel between rescue teams and disaster victims.

[0005] However, the traditional unmanned aircraft has the following defects in actual use. Under the three-disaster condition, the power supply is seriously affected. Power failure will cause the communication terminal and a large number of medical rescue equipment to be unable to use. At present, the traditional unmanned aircraft, due to its own energy system, only serves the flight and load operation of itself. Even if it can discharge externally through the on-board interface, its power is mostly low, maintained below 5kw, which is difficult to supply power to communication equipment and medical security equipment. SUMMARY

[0006] In order to solve the above technical problems, the purpose of the present application is to provide an unmanned aircraft with external emergency power supply function, which can discharge long-term stable high-power power supply externally and improve the disaster area guarantee effect.

[0007] The purpose of the present application is achieved by the following technical solutions:

[0008] The unmanned aerial vehicle with external emergency power supply function comprises a rack, a power system, a power generation system, a transmission system and a rotor system arranged on the rack; the power system comprises an engine and an oil tank, both of which are arranged on the rack, and the oil outlet end of the oil tank is communicated with the engine; the power generation system comprises a generator and a power generation control box, the generator is arranged on the output shaft of the engine, and the power generation control box is arranged on the rack; the transmission system comprises a transmission shaft, a transmission structure and a linkage assembly, the transmission shaft is coaxially arranged on the end of the output shaft of the engine, the transmission structure is arranged on the end of the transmission shaft away from the engine, and the linkage assembly is used for linking the transmission shaft and the output shaft of the engine; the rotor system comprises a rotor main shaft and a rotor blade, the rotor main shaft is rotatably arranged on the rack, and the rotor blade is arranged on the rotor main shaft; and the rotor main shaft is in transmission connection with the transmission structure.

[0009] In some possible embodiments, the linkage assembly comprises a linkage rod, a guide ring and a driving assembly; the guide ring is slidably sleeved on the transmission shaft along the axial direction of the transmission shaft; the linkage rod is fixedly arranged on the guide ring along the axial direction of the transmission shaft; the end of the output shaft of the engine is fixedly provided with a linkage flange, and a insertion hole for inserting the linkage rod is formed in the linkage flange; and the driving assembly is used for moving the guide ring on the transmission shaft.

[0010] In some possible embodiments, the driving assembly comprises a driving part, a mounting part and a connecting piece, a support is fixedly arranged on the rack, the driving part is fixedly arranged on the support, the transmission shaft is rotatably arranged on the support, the mounting part is slidably sleeved on the transmission shaft along the axial direction of the transmission shaft, the mounting part is connected with the guide ring, one end of the connecting piece is in transmission connection with the output shaft of the driving part, and the other end is in transmission connection with the mounting part.

[0011] In some possible embodiments, the connecting piece comprises a first connecting rod and a second connecting rod, the end of the first connecting rod and the end of the second connecting rod are rotatably connected, one end of the first connecting rod away from the second connecting rod is in transmission connection with the output shaft of the driving part, and one end of the second connecting rod away from the first connecting rod is rotatably connected with the outer peripheral wall of the mounting part.

[0012] In some possible embodiments, one end of the linkage rod close to the linkage flange is provided as a cone, and a bevel opening is arranged at the hole opening of the insertion hole, and the inclination angle of the bevel opening is matched with the inclination angle of the cone.

[0013] In some possible embodiments, a plurality of linkage rods are arranged, the plurality of linkage rods are uniformly arranged along the circumference of the guide ring, a plurality of insertion holes are formed, and the position and number of the insertion holes are matched with the position and number of the linkage rods.

[0014] In some possible embodiments, the oil tank is provided with two, both of which are fixedly arranged on the frame and are arranged at two ends of the engine, and an oil level sensor is arranged on each of the oil tanks.

[0015] In some possible embodiments, a water tank radiator is arranged on the frame, is arranged above the engine, and is provided with a water inlet at the top, an overflow kettle is fixedly arranged on the frame, the top of the overflow kettle is provided with an opening, the opening of the top of the overflow kettle is provided with a cover, and an overflow pipe is in communication between the overflow kettle and the water tank radiator.

[0016] In some possible embodiments, the frame comprises a main frame body, four landing gears and a skid, the four landing gears are fixedly arranged at the four corners of the main frame body at the top ends, the bottom ends of the four landing gears are arranged in a direction away from the main frame body, and the skid is fixedly connected between two landing gears on the same side.

[0017] In some possible embodiments, the frame is provided with a controller, the frame is provided with a battery module, the battery module is electrically connected with the power generation system, the controller is electrically connected with the battery module, the frame is provided with an illumination warning lamp, the illumination warning lamp is electrically connected with the battery module and the controller, the frame is provided with a camera unit, the camera unit is electrically connected with the battery module and the controller, and the frame is provided with a loudspeaker, the loudspeaker is electrically connected with the battery module and the controller.

[0018] In summary, the technical scheme of the embodiment of the present application has at least the following advantages and beneficial effects:

[0019] 1. After the unmanned aerial vehicle arrives at the disaster area, the power system is connected with the power generation system, the power generation system is driven by the power system to discharge externally, compared with the traditional unmanned aerial vehicle, the present application can fly to the disaster area to complete landing under the condition of three breaks without being limited by the terrain, and since the power generation system is directly connected with the power system to discharge externally, the power generation state can output 30kw of mains electricity externally, which can quickly restore power supply in the lost area and provide strong guarantee for rescue and disaster relief.

[0020] 2. The power transmission path is closed by the linkage assembly when the aircraft is flying, so that the engine power synchronously drives the rotor system and the generator to run in an idle state, after arriving at the disaster area, the linkage is released by the driving assembly, the rotor system power is cut off, the engine power is fully concentrated on the generator to generate electricity, and mains electricity (220V / 380V) is output to directly provide high-power power support for communication equipment, medical facilities and lighting systems in the disaster area, and break through the energy bottleneck under the condition of three breaks.

[0021] 3. The taper design of the linkage rod end matches the beveled opening of the linkage flange socket. When the drive assembly pushes the guide ring to move axially, the taper automatically guides the linkage rod to accurately insert into the socket. Even if there is a slight assembly deviation or vibration, it can still ensure smooth engagement and avoid jamming or wear. When separated, the drive assembly can accurately pull out the linkage rod, completely disconnecting the mechanical connection between the transmission shaft and the engine output shaft, ensuring the stability of power transmission, avoiding the energy waste of the traditional scheme of continuously idling rotor system, significantly reducing mechanical loss, and prolonging equipment life;

[0022] 4. The double oil tanks are symmetrically distributed on both sides of the engine and equipped with oil quantity sensors. Combined with the cooling system of the water tank radiator and the overflow pot, it ensures the stable operation of the engine under long-time power generation conditions. The controller integrates the management of the battery module, the lighting warning lamp, the camera unit and the loudspeaker. Through the ground control station, the power generation site environment is remotely monitored, the operation power supply is started and stopped, and the disaster image is real-time returned. The unmanned aerial vehicle has the functions of power supply, disaster reconnaissance and safety warning. After completely autonomous flight to the target area, it can build a safe power supply environment without manual site intervention, greatly improving the rescue efficiency;

[0023] 5. The four-corner inclined landing gear and skid combination frame structure provides stable support for heavy components such as engines and generators, while adapting to complex terrain landing. The power generation system is directly integrated into the engine output shaft, eliminating redundant transmission chains, maximizing the use of fuselage space and engine power, and realizing the whole process rescue ability of "fast arrival-precise landing-high efficiency power supply". BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 It is a schematic diagram of the overall structure of the embodiment of the present application;

[0025] Figure 2 It is a schematic diagram of the power generation system and water tank radiator structure of the embodiment of the present application;

[0026] Figure 3 It is a front view of the overall structure of the embodiment of the present application;

[0027] Figure 4 It is Figure 3 the enlarged view of A part in

[0028] Figure 5 It is a schematic diagram of the transmission system of the embodiment of the present application;

[0029] Figure 6 It is a schematic diagram of the external structure of the generator of the embodiment of the present application;

[0030] Figure 7 It is a schematic diagram of the internal structure of the generator of the embodiment of the present application;

[0031] Figure 8 Structure diagram of linkage assembly of the embodiment of the present application;

[0032] Figure 9 Structure diagram of driving assembly of the embodiment of the present application;

[0033] Figure 10 Workflow diagram of the embodiment of the present application.

[0034] Icon: 1, frame; 11, main frame body; 12, landing gear; 13, skid; 101, support; 2, power system; 21, engine; 22, oil tank; 23, oil level sensor; 3, power generation system; 31, power generator; 32, power generation control box; 33, output shaft; 34, stator; 35, rotor; 4, transmission system; 41, transmission shaft; 42, transmission structure; 43, linkage assembly; 5, rotor system; 51, rotor main shaft; 52, rotor blade; 61, linkage rod; 62, guide ring; 63, linkage flange; 64, insertion hole; 7, driving assembly; 71, driving part; 72, mounting part; 73, connecting piece; 731, first connecting rod; 732, second connecting rod; 8, water tank radiator; 81, water inlet; 82, overflow pot; 83, cover; 84, overflow pipe; 9, controller; 91, battery module; 92, lighting warning lamp; 93, camera unit; 94, loudspeaker. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical scheme and advantages of the embodiments of the present application more clear, the technical scheme of the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all the embodiments. The components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0036] The following refers to Figures 1 to 10 The present application is further described in detail.

[0037] The following refers to Figure 1 An unmanned aerial vehicle with external emergency power supply function, comprising a frame 1, the frame 1 is provided with a power system 2, a power generation system 3, a transmission system 4 and a rotor system 5.

[0038] Among them, referring to Figure 2 and Figure 3 The power system 2 comprises an engine 21 and an oil tank 22, both of which are arranged on the frame 1, and the oil outlet end of the oil tank 22 is communicated with the engine 21.

[0039] Referring to Figure 3 The power generation system 3 comprises a power generator 31 and a power generation control box 32, and the power generation control box 32 is arranged on the frame 1, for exampleFigure 4 and Figure 5 As shown in

[0040] Referring to Figure 3 , Figure 4 and Figure 5 , the transmission system 4 comprises a transmission shaft 41, a transmission structure 42 and a linkage assembly 43, the transmission shaft 41 is coaxially arranged at the end of the output shaft 33 of the engine 21, the transmission structure 42 is arranged at the end of the transmission shaft 41 away from the engine 21, and the linkage assembly 43 is used to link the transmission shaft 41 and the output shaft 33 of the engine 21.

[0041] As an embodiment of the present application, referring to Figure 3 and Figure 4 , the transmission structure 42 is arranged as a belt pulley transmission device.

[0042] Referring to Figure 1 and Figure 2 , the rotor system 5 comprises a rotor main shaft 51 and a rotor blade 52, the rotor main shaft 51 is arranged to rotate on the frame 1, and the rotor blade 52 is arranged on the rotor main shaft 51, the rotor main shaft 51 is in transmission connection with the transmission structure 42, and as an embodiment of the present application, the rotor system 5 is provided with two, and the two rotor systems 5 are arranged on the two sides of the frame 1.

[0043] Referring to Figures 5 to 9 , as an embodiment of the present application, the linkage assembly 43 comprises a linkage rod 61, a guide ring 62 and a driving assembly 7.

[0044] Among them, referring to Figure 8 and Figure 9 , the guide ring 62 is slidably arranged on the transmission shaft 41 along the axis direction of the transmission shaft 41.

[0045] Referring to Figure 9 , the linkage rod 61 is fixedly arranged on the guide ring 62 along the axis direction of the transmission shaft 41.

[0046] As shown in Figure 6 and Figure 7 , the end of the output shaft 33 of the engine 21 is fixedly provided with a linkage flange 63, and the linkage flange 63 is provided with a insertion hole 64 for inserting the linkage rod 61.

[0047] Referring to Figure 6 and Figure 7The stator 34 of the generator 31 is rotatably sleeved on the output shaft 33 of the engine 21, and the stator 34 is rotatably connected with the output shaft 33 of the engine 21 through a bearing. The bracket 101 is fixedly arranged on the frame 1, and one end of the stator 34 is fixedly connected with the bracket 101. The bottom end of the bracket 101 is sleeved on the output shaft 33 of the engine 21. Therefore, in the actual use process, the bracket 101 and the stator 34 do not rotate relative to the frame 1 as a whole. When the output shaft 33 of the engine 21 rotates, the stator 34 and the bracket 101 rotate relative to each other.

[0048] With reference to Figure 6 and Figure 7 , the rotor 35 of the generator 31 is fixedly connected with the output shaft 33 of the engine 21. In the actual use process, with the rotation of the output shaft 33 of the engine 21, the rotor 35 rotates relative to the stator 34, thereby realizing power generation.

[0049] With reference to Figure 8 and Figure 9 , the driving assembly 7 is used to drive the guide ring 62 to move on the transmission shaft 41. As an embodiment of the present application, the driving assembly 7 comprises a driving part 71, a mounting part 72 and a connecting piece 73. The bracket 101 is fixedly arranged on the frame 1, and the driving part 71 is fixedly arranged on the bracket 101. The transmission shaft 41 is rotatably arranged on the bracket 101. The mounting part 72 is slidably sleeved on the transmission shaft 41 along the axial direction of the transmission shaft 41. The mounting part 72 is connected with the guide ring 62. As an embodiment of the present application, the inner diameter of the mounting part 72 is greater than the diameter of the guide ring 62. The mounting part 72 is rotatably sleeved on the outer circumferential wall of the guide ring 62, and the mounting part 72 and the guide ring 62 are rotatably connected through a bearing (not shown in the figure). One end of the connecting piece 73 is in transmission connection with the output shaft 33 of the driving part 71, and the other end is in transmission connection with the mounting part 72.

[0050] With reference to Figure 9 , as an embodiment of the present application, the connecting piece 73 comprises a first connecting rod 731 and a second connecting rod 732. The first connecting rod 731 and the second connecting rod 732 are rotatably connected at the ends. One end of the first connecting rod 731, which is away from the second connecting rod 732, is in transmission connection with the output shaft 33 of the driving part 71. One end of the second connecting rod 732, which is away from the first connecting rod 731, is rotatably connected with the outer circumferential wall of the mounting part 72.

[0051] With reference to Figure 8 and Figure 9 , as an embodiment of the present application, the driving part 71 is a steering engine.

[0052] With reference to Figure 6 and Figure 8The end of the linkage rod 61 close to the linkage flange 63 is designed as a cone, and the orifice of the insertion hole 64 is designed as a bevel opening, the inclination angle of which is adapted to the inclination angle of the cone.

[0053] The design of the cone at the end of the linkage rod 61 is adapted to the bevel opening of the insertion hole 64 of the linkage flange 63. When the driving assembly 7 pushes the guide ring 62 to move axially, the taper automatically guides the linkage rod 61 to be inserted into the insertion hole 64 accurately. Even if there is a slight assembly deviation or vibration, it can still ensure smooth engagement, avoid jamming or wear, and when separated, the driving assembly 7 can accurately pull out the linkage rod 61, completely disconnecting the mechanical connection between the transmission shaft 41 and the output shaft 33 of the engine 21, ensuring the stability of power transmission, and avoiding the energy waste of the continuous idling rotor system 5 in the traditional scheme, significantly reducing mechanical loss and prolonging equipment life.

[0054] Referring to Figure 6 and Figure 8 , multiple linkage rods 61 are provided, and the multiple linkage rods 61 are evenly arranged along the circumference of the guide ring 62. Multiple insertion holes 64 are provided, and the positions and numbers of the insertion holes 64 are adapted to the positions and numbers of the linkage rods 61.

[0055] The design of the multiple linkage rods 61 evenly distributed along the circumference of the guide ring 62 makes the torque transmission between the transmission shaft 41 and the output shaft 33 of the engine more uniform and balanced, effectively disperses the load stress, avoids single-point overload, and enhances the torsional rigidity and load-carrying capacity of the connection part.

[0056] Referring to Figure 1 , Figure 3 , two oil tanks 22 are provided, and the two oil tanks 22 are fixedly arranged on the rack 1. The two oil tanks 22 are arranged at the two ends of the engine 21, and an oil level sensor 23 is arranged on each oil tank 22.

[0057] Referring to Figure 1 , Figure 2 and Figure 3 , a water tank radiator 8 is arranged on the rack 1, and the water tank radiator 8 is arranged above the engine 21. An injection opening 81 is arranged at the top of the water tank radiator 8. An overflow pot 82 is fixedly arranged on the rack 1. An opening is arranged at the top of the overflow pot 82. A cover 83 is arranged on the opening at the top of the overflow pot 82. An overflow pipe 84 is in communication between the overflow pot 82 and the water tank radiator 8.

[0058] The two oil tanks 22 are symmetrically distributed on the two sides of the engine 21 and are equipped with oil level sensors 23. In combination with the cooling system of the water tank radiator 8 and the overflow pot 82, the stable operation of the engine 21 under the long-time power generation working condition is ensured. By arranging the overflow pot 82, the liquid level height in the water tank radiator 8 can be observed conveniently and quickly, and the water can be replenished quickly.

[0059] Referring to Figure 1 and Figure 3 , the rack 1 comprises a main frame body 11, landing gears 12 and skids 13, the landing gears 12 are provided with four, the top ends of the four landing gears 12 are fixedly arranged at the four corners of the main frame body 11, the bottom ends of the four landing gears 12 are arranged in a direction away from the main frame body 11, and the skids 13 are fixedly connected between two landing gears 12 on the same side.

[0060] The rack 1 combined with the four-corner inclined landing gears 12 and the skids 13 provides stable support for heavy components such as the engine 21 and the generator 31, and is suitable for landing on complex terrain.

[0061] As an embodiment of the present application, the rack 1 is provided with a controller 9, the rack 1 is provided with a battery module 91, the battery module 91 is electrically connected with the power generation system 3, the controller 9 is electrically connected with the battery module 91, the rack 1 is provided with an illumination warning lamp 92, the illumination warning lamp 92 is electrically connected with the battery module 91 and the controller 9, the rack 1 is provided with a camera unit 93, the camera unit 93 is electrically connected with the battery module 91 and the controller 9, and the rack 1 is provided with a loudspeaker 94, the loudspeaker 94 is electrically connected with the battery module 91 and the controller 9.

[0062] As shown in Figure 10 , the electrical connection relationship between the controller 9 and the illumination warning lamp 92, the loudspeaker 94, the camera unit 93, the battery module 91, the power generation system 3 and the power system 2 is as shown in the figure. In actual use, the controller 9 can be selected from a plc single-chip microcomputer or an industrial-grade cpu processor.

[0063] The controller 9 integrates the management of the battery module 91, the illumination warning lamp 92, the camera unit 93 and the loudspeaker 94, remotely monitors the power generation site environment through the ground control station, operates the power supply start-stop, and real-time returns the disaster image, so that the unmanned aerial vehicle has the functions of power supply, disaster reconnaissance and safety warning. After completely autonomous flight to the target area, a safe power supply environment can be constructed without manual site intervention, and the rescue efficiency is greatly improved.

[0064] The implementation principle of the unmanned aerial vehicle with external emergency power supply function provided in the embodiment of the present application is as follows:

[0065] When the unmanned aerial vehicle arrives at the disaster area, the power system 2 is connected with the power generation system 3, the power system 2 can drive the power generation system 3 to discharge externally, compared with the traditional unmanned aerial vehicle, the present application can fly to the disaster area for landing under the condition of three breaks, because the power system 2 is directly connected with the power generation system 3 to discharge externally, the power generation state can output 30kw mains externally, and the power supply in the lost area can be quickly restored, which provides strong guarantee for rescue and disaster relief.

[0066] The above merely describes the preferred embodiments of the present application, and is not used to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An unmanned aerial vehicle with an external emergency power supply function, characterized in that: Includes a frame (1), on which a power system (2), a power generation system (3), a transmission system (4) and a rotor system (5) are provided; The power system (2) includes an engine (21) and a fuel tank (22). Both the engine (21) and the fuel tank (22) are mounted on the frame (1). The oil outlet of the fuel tank (22) is connected to the engine (21). The power generation system (3) includes a generator (31) and a power generation control box (32). The generator (31) is mounted on the output shaft (33) of the engine (21), and the power generation control box (32) is mounted on the frame (1). The generator (31) and the power generation control box (32) are electrically connected. The transmission system (4) includes a transmission shaft (41), a transmission structure (42), and a linkage assembly (43). The transmission shaft (41) is coaxially rotatably disposed at the end of the output shaft (33) of the engine (21). The transmission structure (42) is disposed at the end of the transmission shaft (41) away from the engine (21). The linkage assembly (43) is used to link the transmission shaft (41) and the output shaft (33) of the engine (21). The rotor system (5) includes a rotor shaft (51) and rotor blades (52). The rotor shaft (51) is rotatably mounted on the frame (1), and the rotor blades (52) are mounted on the rotor shaft (51). The rotor shaft (51) is connected to the transmission structure (42).

2. The unmanned aerial vehicle with external emergency power supply function according to claim 1, characterized in that: The linkage component (43) includes a linkage rod (61), a guide ring (62), and a drive component (7). The guide ring (62) is slidably sleeved on the drive shaft (41) along the axial direction of the drive shaft (41); The linkage rod (61) is fixedly mounted on the guide ring (62) along the axial direction of the transmission shaft (41). The end of the output shaft (33) of the engine (21) is fixedly mounted with a linkage flange (63). The linkage flange (63) has an insertion hole (64) for the linkage rod (61) to be inserted. The drive assembly (7) is used to drive the guide ring (62) to move on the drive shaft (41).

3. The unmanned aerial vehicle with external emergency power supply function according to claim 2, characterized in that: The drive assembly (7) includes a drive unit (71), a mounting unit (72), and a connector (73). A bracket (101) is fixedly mounted on the frame (1). The drive unit (71) is fixedly mounted on the bracket (101). The drive shaft (41) is rotatably mounted on the bracket (101). The mounting unit (72) is slidably mounted on the drive shaft (41) along the axial direction of the drive shaft (41). The mounting unit (72) is connected to the guide ring (62). One end of the connector (73) is connected to the output shaft (33) of the drive unit (71), and the other end is connected to the mounting unit (72).

4. The unmanned aerial vehicle with external emergency power supply function according to claim 3, characterized in that: The connector (73) includes a first link (731) and a second link (732), the ends of the first link (731) and the second link (732) are rotatably connected, the end of the first link (731) away from the second link (732) is connected to the output shaft (33) of the drive unit (71) for transmission, and the end of the second link (732) away from the first link (731) is rotatably connected to the outer peripheral wall of the mounting part (72).

5. The unmanned aerial vehicle with external emergency power supply function according to claim 2, characterized in that: The end of the linkage rod (61) near the linkage flange (63) is set as a cone, and the opening of the insertion hole (64) is set as a beveled opening, the inclination angle of the beveled opening being adapted to the inclination angle of the cone.

6. The unmanned aerial vehicle with external emergency power supply function according to claim 2, characterized in that: Multiple linkage rods (61) are provided, and the multiple linkage rods (61) are evenly arranged along the circumference of the guide ring (62). Multiple insertion holes (64) are provided, and the position and number of insertion holes (64) are adapted to the position and number of linkage rods (61).

7. The unmanned aerial vehicle with external emergency power supply function according to claim 1, characterized in that: There are two oil tanks (22), both of which are fixedly mounted on the frame (1). The two oil tanks (22) are located at both ends of the engine (21), and each oil tank (22) is equipped with an oil quantity sensor (23).

8. The unmanned aerial vehicle with external emergency power supply function according to claim 1, characterized in that: A water tank radiator (8) is provided on the frame (1). The water tank radiator (8) is located above the engine (21). A water inlet (81) is provided on the top of the water tank radiator (8). An overflow tank (82) is fixedly provided on the frame (1). An opening is provided on the top of the overflow tank (82). A cap (83) is provided on the opening on the top of the overflow tank (82). An overflow pipe (84) is connected between the overflow tank (82) and the water tank radiator (8).

9. The unmanned aerial vehicle with external emergency power supply function according to claim 1, characterized in that: The frame (1) includes a main frame (11), landing gear (12) and skids (13). There are four landing gears (12). The tops of the four landing gears (12) are fixedly installed at the four corners of the main frame (11). The bottoms of the four landing gears (12) are inclined in the direction away from the main frame (11). Skids (13) are fixedly connected between two landing gears (12) on the same side.

10. The unmanned aerial vehicle with external emergency power supply function according to claim 1, characterized in that: A controller (9) is provided on the frame (1), and a battery module (91) is provided on the frame (1). The battery module (91) is electrically connected to the power generation system (3), and the controller (9) is electrically connected to the battery module (91). The frame (1) is equipped with a lighting warning light (92), which is electrically connected to the battery module (91) and the controller (9); A camera unit (93) is provided on the frame (1), and the camera unit (93) is electrically connected to the battery module (91) and the controller (9); A speaker (94) is provided on the frame (1), and the speaker (94) is electrically connected to the battery module (91) and the controller (9).

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