Main structure of a remote-controlled fire-fighting helicopter

Abstract

The present invention relates to the field of unmanned aerial vehicles (UAVs), and more specifically, to a main structure of a remote-controlled fire-fighting helicopter. The remote-controlled helicopter comprises a fuselage, a main rotor, a tail, and a landing gear. An engine, a generator, a starter motor, a gearbox, a battery, and a control circuit board are installed in the fuselage. The landing gear is installed below the fuselage to form a suspension space. Firefighting equipment is mounted in the suspension space for firefighting. The helicopter further comprises distributed fuel tanks, which are respectively arranged at different positions on the fuselage to supply fuel to the engine. The structure is used to solve the problem that the center of gravity of a fire-fighting UAV changes with the counterweight of the firefighting equipment, resulting in insufficient flexibility, balance, and stability. The structure ensures the stability and flexibility of the UAV's flight, reduces the risk of spontaneous combustion, and enhances its flight endurance and extends its service life during the flight of the UAV with the firefighting equipment mounted.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles (UAVs), and more particularly to a main structure of a remote-controlled fire-fighting helicopter. Background Art

[0002] As drone research and development expands, their application areas are also expanding into forestry work, where they can be used for forest disaster inspections, monitoring and tracking, and assisting firefighters in rescue and supervision. Due to their high maneuverability, simple maintenance, and low operating costs, drones can be used for low-altitude monitoring, catching early-stage forest fires in remote areas and providing a comprehensive understanding of the situation at the scene of major forest fires. They can also address issues such as the inability of aircraft to fly at night or when visibility is reduced due to smoke.

[0003] Prior art drones are typically powered by lithium batteries. However, given that firefighting drones are exposed to open flames, and given the high temperatures of flames and smoke in forest fires, using existing lithium batteries as the sole power source could overheat and cause the batteries to explode, exacerbating the fire. Therefore, balancing stability and flexibility for drones carrying heavy firefighting equipment, while also minimizing the risk of spontaneous combustion and extending flight endurance and service life, remains a pressing challenge in existing firefighting drone technology research. Summary of the Invention

[0004] The present invention aims to overcome at least one defect (shortcoming) of the above-mentioned prior art and provide a fire-fighting helicopter to solve the problems of excessive load of drones during fire rescue, insufficient flexibility and balance caused by the center of gravity of the drone changing with the counterweight of the fire-fighting facilities, and lack of stability during the flight of the drone.

[0005] The technical solution adopted by the present invention is a main structure of a remote-controlled fire-fighting helicopter, which includes a fuselage body, a main rotor, a tail and a landing gear. The fuselage body is equipped with an engine, a generator, a starter motor, a gearbox, a battery and a control circuit board. The engine drives the gearbox to drive the main rotor and drives the generator to charge the battery. The battery supplies power to the control circuit board and the starter motor. The starter motor drives the engine through the gearbox. The landing gear is installed under the fuselage body and forms a suspension space. Fire-fighting facilities are mounted in the suspension space for firefighting. Distributed fuel tanks are also included, which are respectively arranged at different positions on the fuselage body to provide fuel to the engine.

[0006] The gearbox is located on the upper side of the fuselage, the engine is located on the front side of the fuselage, below the gearbox, and the generator is located below the engine. The engine's main shaft drives the gearbox upward and the generator downward. The battery is located on the rear side of the fuselage, below the gearbox. The distributed fuel tanks include a main left tank and a main right tank of identical structure, symmetrically located on the left and right sides of the rear fuselage. This distribution of fuel tanks helps reduce the impact of the upward shift in the center of gravity caused by the consumption of firefighting equipment, reduces the impact on the aerodynamic layout of the firefighting helicopter caused by the mounting of firefighting equipment, and improves the maneuverability and flexibility of the firefighting helicopter through the rear-mounted batteries.

[0007] The distributed fuel tank also includes a secondary tank embedded in one side of the fuselage. Pipelines connect the main left and right tanks to the secondary tank, which in turn supplies fuel to the engine. This helps provide more fuel for the firefighting helicopter and improves its endurance.

[0008] The fuselage body includes an outer shell, and left and right support plates. The left and right support plates are mounted within the outer shell and support other components mounted on the fuselage body. A recessed area is provided on one side of the outer shell to accommodate the auxiliary fuel tank embedded in the fuselage body. This helps protect the various components from rain and snow, thereby extending the service life of the firefighting helicopter. The outer shell also helps reduce friction with airflow during flight, thereby affecting the aerodynamic layout of the firefighting helicopter. The recessed area also helps reduce the impact of the auxiliary fuel tank installation on the firefighting helicopter's center of gravity.

[0009] The helicopter also includes a cooling device, which is located on the front side of the fuselage body and in front of the gearbox. This helps cool the engine, reduces the impact of high temperature on the fire scene on the fire helicopter, and helps extend the rescue service time of the fire helicopter.

[0010] The cooling device includes a cooling water tank, a cooling fan, and a coolant pump. The cooling water tank is tilted, and the cooling fan is installed below the cooling water tank, blowing air from the bottom up. The coolant pump drives the coolant in the cooling water tank, flowing from the upper end to the lower end of the cooling water tank, and then flows through the engine to cool it. This helps to enhance the cooling effect of the cooling water tank, cooling fan, and coolant pump.

[0011] The engine is a twin-cylinder opposed engine, with two cylinders positioned opposite each other on the fuselage. The cylinder mufflers are curved tubes, extending from the front of the fuselage toward the rear, where they connect to the landing gear. A buffer connection is provided between the mufflers and the landing gear. This dual-cylinder engine enhances the firefighting helicopter's power and reduces fuel consumption. The sudden change in the muffler's cross-section during sound propagation causes impedance changes, thereby reducing outward radiation of sound energy.

[0012] The landing gear comprises a ladder-shaped frame, a skid-shaped structure, and sliding wheels. The ladder-shaped frame has a height-to-base ratio (h:D) between 1.0 and 2.0, and a height-to-top ratio (h:d) between 1.5 and 2.5, creating a suspension space that is wider at the bottom and narrower at the top. The skid-shaped structure is mounted at the bottom of the ladder-shaped frame, and the sliding wheels are mounted on the ladder-shaped frame, located below the engine, with at least a portion of their lower edge extending beyond the skid-shaped structure. This facilitates the landing gear's ground clearance by increasing the ladder-shaped frame and skid-shaped structure, facilitating the safe landing of a firefighting helicopter on slopes. Furthermore, the sliding wheels facilitate the easy movement of the firefighting helicopter on the ground without the use of other auxiliary equipment.

[0013] The tail is a rotor structure, driven by a gearbox or a separate drive motor. It includes symmetrically arranged rotor blades, a rotating head, a rotating shaft, a torque converter, and a torque-converting servo. The rotating shaft drives the rotating head, and the rotor blades are rotationally connected to the rotating head, with the rotation direction perpendicular to the rotation of the rotating shaft. The torque converter is mounted on the rotating shaft, and the torque-converting servo drives the rotor blades relative to the rotating head through the torque converter. This facilitates the formation of a vertical stabilizer by the rotor blades, rotating head, and rotating shaft to balance counter-torque and achieve directional control of the firefighting helicopter. It also facilitates dual control of the tail through the torque-converting servo and gearbox.

[0014] The torque converter mechanism includes a sliding frame and a seesaw mechanism. The sliding frame is slidably mounted on the rotating shaft, with its upper end connected to the rotor blade via a connecting rod. Both ends of the connecting rod are rotatably connected. The seesaw mechanism has a rotating end at one end, a pushing part in the middle, and an actuating end at the other end. The pushing part is mounted on the sliding frame. The torque converter servo pushes and pulls the actuating end, causing the seesaw mechanism to tilt around the rotating end. This causes the pushing part to push the sliding frame up and down along the rotating shaft, which in turn drives the connecting rod to rotate the rotor blade relative to the rotating head. This helps reduce the size of the torque converter mechanism and minimizes the impact on the center of gravity of the firefighting helicopter.

[0015] Compared with the existing technology, the beneficial effects of the present invention are: it can ensure the stability and flexibility of the flight of the fire-fighting drone when carrying heavy fire-fighting equipment; it can reduce the risk of spontaneous combustion of the fire-fighting drone powered by pure lithium batteries, enhance its flight endurance and extend its service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the present invention.

[0017] Figure 2 It is a structural explosion diagram of the present invention.

[0018] Figure 3 This is a schematic diagram of the installation position of the water-based bomb of the present invention.

[0019] Figure 4 This is a schematic diagram of the fire tank installation position of the present invention.

[0020] Figure 5 It is a partially enlarged schematic side view of the present invention.

[0021] Figure 6 It is a partially enlarged schematic top view of the present invention.

[0022] Figure 7 It is a partially enlarged schematic diagram of the isometric side view of the present invention.

[0023] Description of the accompanying symbols: fuselage body 100, shell 110, recessed position 111, left support plate 120, right support plate 130, main rotor 200, tail 300, rotor blade 310, rotating head 320, rotating shaft 330, torque converter 340, sliding frame 341, rocker mechanism 342, connecting rod 343, rotating end 344, pushing part 345, action end 346, torque converter servo 350, landing gear 400, ladder frame 410, skid Structure 420, sliding wheel 430, engine 510, engine cylinder 511, muffler 512, buffer connection 513, generator 520, starter motor 530, gear box 540, battery 550, control circuit board 560, cooling device 570, cooling water tank 571, cooling fan 572, coolant pump 573, fire fighting facility 600, distributed fuel tank 700, main left tank 710, main right tank 720, auxiliary tank 730. DETAILED DESCRIPTION

[0024] The accompanying drawings are for illustrative purposes only and are not to be construed as limiting the present invention. To better illustrate the following embodiments, some components in the accompanying drawings may be omitted, enlarged, or reduced in size, and do not represent actual product dimensions. Those skilled in the art will appreciate that some well-known structures and their descriptions may be omitted from the accompanying drawings.

[0025] Example 1

[0026] like Figures 1 to 7As shown, in this embodiment, a main structure of a remote-controlled fire-fighting helicopter is adopted. The remote-controlled helicopter includes a main fuselage 100, a main rotor 200, a tail 300 and a landing gear 400. The main fuselage 100 is equipped with an engine 510, a generator 520, a starter motor 530, a gear box 540, a battery 550 and a control circuit board 560. The engine 510 drives the gear box 540 to drive the main rotor 200, and drives the generator 520 to charge the battery 550. The battery 550 supplies power to the control circuit board 550 and the starter motor 530. The starter motor 530 drives the engine 510 through the gear box 540. The landing gear 400 is installed below the main fuselage 100 and forms a suspension space. Firefighting equipment 600 is mounted in the suspension space for firefighting. The helicopter is characterized in that it also includes distributed fuel tanks 700, which are respectively arranged at different positions on the main fuselage 100 to provide fuel to the engine 510.

[0027] The gearbox 540 is arranged on the upper side of the fuselage body 100. The engine 510 is located on the front side of the fuselage body 100, below the gearbox 540. The generator 520 is located below the engine 510. The main shaft of the engine 510 drives the gearbox 540 upward and the generator 510 downward. The battery 550 is located on the rear side of the fuselage body 100, below the gearbox 540. The distributed fuel tanks 700 include a main left tank 710 and a main right tank 720 of identical structure, symmetrically arranged on the left and right sides of the rear of the fuselage body. In this embodiment, the weight of the engine 510, the generator 520, the gearbox 540, the battery 550, and the symmetrically arranged main left tank 710 and main right tank 720 are all designed and distributed according to calculations to ensure that the center of gravity of the firefighting helicopter is within the front and rear limits.

[0028] The distributed fuel tank 700 also includes a subsidiary fuel tank 730, which is embedded in a side of the main fuselage 100. The main left fuel tank 710 and the main right fuel tank 720 supply fuel to the subsidiary fuel tank 730 via pipelines, and the subsidiary fuel tank 730 supplies fuel to the engine 510 via pipelines. In this embodiment, before flight, the main left fuel tank 710, the main right fuel tank 720, and the subsidiary fuel tank 730 in the distributed fuel tank 700 are all filled with gasoline according to specifications. During flight, the subsidiary fuel tank 730 supplies gasoline to the engine 510, and the main left fuel tank 710 and the main right fuel tank 720 simultaneously supply gasoline to the subsidiary fuel tank 730 to maintain the balance of the helicopter. The volume of each of the main left fuel tank 710 and the main right fuel tank 720 is approximately 3L.

[0029] The fuselage body 100 includes an outer shell 110, a left support plate 120 and a right support plate 130. The left support plate 120 and the right support plate 130 are installed in the outer shell 110 to support other components installed on the fuselage body. A recessed position 111 is provided on one side of the outer shell 110 to accommodate the auxiliary fuel tank 730 embedded in the fuselage body 100. In this embodiment, the outer shell 110 is made of carbon fiber material, which has the characteristics of light weight and high tensile strength. It can not only reduce the weight of the fuselage itself and thus enhance its flight flexibility, but also resist stretching under the complex airflow conditions above the forest fire scene, thereby extending the service life of the fire-fighting helicopter; the left support plate 120 and the right support plate 130 are made of aluminum alloy material, which has the characteristics of not being easy to rust, high strength and light weight. Therefore, during use, the sprayed water mist or other fire-fighting foam is not easy to rust the left support plate 120 and the right support plate 130; the opening of the recessed position 111 faces the side of the outer shell 110, does not affect the airflow distribution of the fuselage body 100 at the nose, and the cross-section of the recessed position 111 is almost equal to the cross-section of the auxiliary fuel tank 730, and the auxiliary fuel tank 730 can be removed from the recessed position 111.

[0030] The vehicle further includes a cooling device 570, which is disposed on the front side of the main body 100, in front of the gearbox 540. In this embodiment, the cooling device 570 removes heat from the engine 510 during operation via a heat exchange pipe connected to the engine 510, minimizing the impact of high temperature smoke in a fire on the engine 510 and extending its service life.

[0031] The cooling device 570 includes a cooling water tank 571, a cooling fan 572, and a coolant pump 573. The cooling water tank 571 is tilted, and the cooling fan 572 is installed below the cooling water tank 571, blowing air from the bottom up. The coolant pump 573 drives the coolant in the cooling water tank 571, flowing from the upper end to the lower end of the cooling water tank 571, and then flows through the engine 510 for cooling. In this embodiment, the coolant is cooled by the coolant pump 573 and then discharged from the cooling water tank 571 into the engine 510. The coolant flows within the heat exchange tubes, which are parallel but have gaps between them. The tilted cooling water tank 571 further increases the contact area between the heat exchange tubes and the air. The cooling fan 572, blowing air from the bottom up, accelerates the air flow in the gaps, further enhancing the heat exchange effect of the cooling device 570.

[0032] The engine 510 is a twin-cylinder opposed engine, with two engine cylinders 511 positioned opposite each other on the fuselage 100. The muffler 512 of the engine cylinder 511 is in the form of a curved tube, extending from the front of the fuselage 100 to the rear, connected to the landing gear 400. A buffer connection 513 is provided between the muffler 512 and the landing gear 400. In this embodiment, the twin-cylinder opposed engine 510 effectively enhances the power of the firefighting helicopter while reducing fuel consumption. The muffler 512 is in the form of a curved tube, with a sudden change in cross-section, which further increases the impedance of the muffler 512 and enhances its sound energy attenuation effect. The curved tube of the muffler 512 is made of 304 stainless steel, and the buffer connection 513 is made of noise-absorbing material to further enhance the sound-absorbing effect.

[0033] The landing gear 400 includes a ladder frame 410, a skid-shaped structure 420 and a sliding wheel 430. The height-to-bottom ratio h:D of the ladder frame 410 is between 1.0-2.0, and the height-to-top ratio h:d is between 1.5-2.5, forming a suspension space that is wider at the bottom and narrower at the top. The skid-shaped structure 420 is installed at the bottom of the ladder frame 410, and the sliding wheel 430 is installed on the ladder frame 410, located below the engine 510, and at least part of the lower edge exceeds the skid-shaped structure 420. In this embodiment, the height-to-base ratio of the trapezoidal frame 410, h:D, is 1.5, and the height-to-top ratio, h:d, is 2. The trapezoidal frame 410 and the skid-shaped structure 420 increase the ground contact width of the landing gear 400, enabling it to operate on a variety of complex terrains, including grasslands, slopes, mountains, and muddy ground. After the flight, firefighters can maneuver the firefighting helicopter using the curved tail handle and the sliding wheels 430. In this embodiment, a detachable loudspeaker is also installed on the landing gear 400 to warn ground personnel of evacuation and provide guidance to firefighters on rescue operations.

[0034] The tail 300 is a rotor structure, driven by a gearbox 540 or independently provided with a drive motor, including symmetrically arranged rotor blades 310, a rotating head 320, a rotating shaft 330, a torque converter 340 and a torque converter servo 350. The rotating shaft 330 drives the rotating head 320 to rotate. The rotor blades 310 are rotationally connected to the rotating head 320, and the rotation direction is perpendicular to the rotation of the rotating shaft 330. The torque converter 340 is mounted on the rotating shaft 330. The torque converter 340 drives the rotor blades 310 to rotate relative to the rotating head 320 through the torque converter 340. In this embodiment, the tail wing can be driven to rotate by the gearbox 540 or can achieve rotation and torque conversion through the torque converter 350; the rotor structure of the tail wing 300 is arranged on one side, the rotor blades 310 are provided with two pieces, the rotating head 320 is made of aluminum alloy, and the rotating shaft 330 is connected to the torque converter mechanism 340 and rotates relative to the rotating head 320 to help the tail wing 300 resist the counter-torque of the main rotor 200; the torque converter servo 350 is a small transmission device with an output shaft. This output shaft can be positioned to the angle position specified by the firefighter by inputting a coded signal to the servo, thereby achieving a constant remotely controlled flight angle.

[0035] The torque converter mechanism 340 includes a sliding frame 341 and a seesaw mechanism 342. The sliding frame 341 is slidably mounted on the rotating shaft 330, and the upper end is connected to the rotor piece 310 through a connecting rod 343. Both ends of the connecting rod 343 are rotatably connected. One end of the seesaw mechanism 342 is a rotating end 345, the middle is a pushing part 345, and the other end is an action end 346. The pushing part 345 is mounted on the sliding frame 341. The torque converter servo 350 pushes and pulls the action end 346 to tilt the seesaw mechanism 342 around the rotating end 345, causing the pushing part 345 to push the sliding frame 341 to slide up and down along the rotating shaft 330, and the connecting rod 343 drives the rotor piece 310 to rotate relative to the rotating head 320. In this embodiment, the seesaw structure 342 is used to convert linear motion into rotational motion, which takes up only a small space to achieve the same torque conversion effect as other torque converters, without increasing the tail weight of the fire helicopter, thereby reducing its impact on the center of gravity of the entire aircraft.

[0036] Example 2

[0037] In this embodiment, while using the remote-controlled firefighting helicopter, rescuers need to use a matching voice terminal, control center, and remote controller to control the helicopter's flight status. Rescuers issue commands to the voice terminal, which parses the commands into digital signals and wirelessly transmits them to the control center. The control center then centrally processes and calculates the commands for multiple firefighting helicopters controlled by multiple remote controllers. It then transmits the commands from the voice terminal to the nearest remote controller, which in turn sends them to a program pre-installed in the firefighting helicopter to control its flight path and direction.

[0038] In this embodiment, a camera is mounted on the front of the remote-controlled fire helicopter. The camera takes pictures of the scene where the fire has occurred and sends them to the control center. The control center calculates and predicts the possible direction and scale of the fire development based on the received pictures and the preset fire prediction model. Rescue personnel then make rescue plans for the forests that have not been on fire and the forests that have been on fire, and deploy firefighters, fire helicopters and firefighting facilities to the forests where the fire has occurred.

[0039] In this embodiment, a loudspeaker is mounted on the side of the remote-controlled fire helicopter, which is connected to the battery of the fire helicopter for power supply. Rescue personnel record warning words in advance and play them in a loop on the loudspeaker, controlling the remote-controlled fire helicopter to fly over isolated mountain and forest areas and warn people on land not to move around at will.

[0040] In this embodiment, the remote-controlled firefighting helicopter has a flight altitude between 100m and 600m. It is a hybrid electric helicopter. Compared with pure electric helicopters, the remote-controlled firefighting helicopter has a better flight endurance. In addition, when the fire is in a high-temperature area, the remote-controlled firefighting helicopter has a better safety factor, avoiding the situation where the large-capacity lithium battery on board explodes in the air and aggravates the fire.

[0041] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the technical solutions of the present invention, and are not intended to limit the specific implementation methods of the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the claims of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A main structure of a remote-controlled fire-fighting helicopter, comprising a fuselage body (100), a main rotor (200), a tail (300) and a landing gear (400), wherein an engine (510), a generator (520), a starter motor (530), a gear box (540), a battery (550) and a control circuit board (560) are installed in the fuselage body (100), wherein the engine (510) drives the gear box (540) to drive the main rotor (200) to drive the generator (520) to charge the battery (550), wherein the battery (550) supplies power to the control circuit board (560) and the starter motor (530), wherein the starter motor (530) drives the engine (510) through the gear box (540), wherein the landing gear (400) is installed below the fuselage body (100) and forms a suspension space, wherein a fire-fighting facility (600) is mounted in the suspension space for firefighting, wherein the fire-fighting facility (600) is mounted in the suspension space for firefighting, wherein the fire-fighting facility (600) is mounted in the suspension space for firefighting, It also includes distributed fuel tanks (700), which are respectively arranged at different positions on the fuselage body (100) for providing fuel to the engine (510); The gearbox (540) is arranged on the upper side of the fuselage body (100), the engine (510) is arranged on the front side of the fuselage body (100) and below the gearbox (540), the generator (520) is arranged below the engine (510), the main shaft of the engine (510) drives the gearbox (540) upward and drives the engine (510) downward, the battery (550) is arranged on the rear side of the fuselage body (100) and below the gearbox (540), and the distributed fuel tank (700) includes a main left tank (710) and a main right tank (720) of the same structure and are symmetrically arranged on the left and right sides of the rear of the fuselage body respectively; The distributed fuel tank (700) further includes an auxiliary fuel tank (730), wherein the auxiliary fuel tank (730) is embedded in one side of the fuselage body (100), the main left fuel tank (710) and the main right fuel tank (720) supply fuel to the auxiliary fuel tank (730) through pipelines, and the auxiliary fuel tank (730) supplies fuel to the engine (510) through pipelines; The engine (510) is a twin-cylinder opposed engine, with two engine cylinders (511) disposed oppositely on the fuselage body (100) on the left and right sides. The muffler (512) of the engine cylinder (511) is in the shape of a curved tube and bends at the front side of the fuselage body (100) to extend toward the rear side and is connected to the landing gear (400). A buffer connection (513) is provided between the muffler (512) and the landing gear (400). The landing gear (400) includes a ladder frame (410), a skid structure (420) and a sliding wheel (430). The ladder frame (410) has a height-to-bottom ratio h:D between 1.0 and 2.0, and a height-to-top ratio h:d between 1.5 and 2.5, forming a suspension space that is wider at the bottom and narrower at the top. The skid structure (420) is mounted on the bottom of the ladder frame (410), and the sliding wheel (430) is mounted on the ladder frame (410) and is located below the engine (510), with at least a portion of its lower edge extending beyond the skid structure (420).

2. The main structure of the remote-controlled fire-fighting helicopter according to claim 1, characterized in that: The fuselage body (100) comprises an outer shell (110), a left support plate (120), and a right support plate (130). The left support plate (120) and the right support plate (130) are installed in the outer shell (110) and are used to support other components installed on the fuselage body. A recessed position (111) is provided on one side of the outer shell (110) for accommodating an auxiliary fuel tank (730) embedded in the fuselage body (100).

3. The main structure of the remote-controlled fire-fighting helicopter according to claim 1, characterized in that: It also includes a cooling device (570), which is arranged on the front side of the fuselage body (100) and located at the front end of the gear box (540).

4. The main structure of the remote-controlled fire-fighting helicopter according to claim 3, characterized in that: The cooling device (570) includes a cooling water tank (571), a cooling fan (572) and a coolant pump (573). The cooling water tank (571) is arranged at an angle. The cooling fan (572) is installed below the cooling water tank (571) and blows air from the bottom to the top. The coolant pump (573) drives the coolant in the cooling water tank (571) to flow from the high end to the low end of the cooling water tank (571) and flows through the engine (510) for cooling.

5. The main structure of the remote-controlled fire-fighting helicopter according to any one of claims 1 to 4, characterized in that: The tail wing (300) is a rotor structure. The tail wing (300) is driven by a gear box (540) or by an independently arranged drive motor. The tail wing (300) comprises a symmetrically arranged rotor blade (310), a rotating head (320), a rotating shaft (330), a torque conversion mechanism (340), and a torque conversion servo (350). The rotating shaft (330) drives the rotating head (320) to rotate. The rotor blade (310) is rotationally connected to the rotating head (320), and the rotation direction is perpendicular to the rotation of the rotating shaft (330). The torque conversion mechanism (340) is sleeved on the rotating shaft (330). The torque conversion servo (350) drives the rotor blade (310) to rotate relative to the rotating head (320) through the torque conversion mechanism (340).

6. The main structure of the remote-controlled fire-fighting helicopter according to claim 5, characterized in that: The torque conversion mechanism (340) includes a sliding frame (341) and a seesaw mechanism (342). The sliding frame (341) is slidably mounted on the rotating shaft (330). The upper end of the sliding frame (341) is connected to the rotor blade (310) via a connecting rod (343). Both ends of the connecting rod (343) are rotatably connected. One end of the seesaw mechanism (342) is a rotating end (344), the middle is a pushing portion (345), and the other end is an action end (346). The pushing portion (345) is mounted on the sliding frame (341). The torque conversion servo (350) pushes and pulls the action end (346) to tilt the seesaw mechanism (342) around the rotating end (344), causing the pushing portion (345) to push the sliding frame (341) to slide up and down along the rotating shaft (330), thereby driving the connecting rod (343) to drive the rotor blade (310) to rotate relative to the rotating head (320).

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