Tandem type unmanned helicopter

Abstract

The tandem type unmanned helicopter comprises a rack, an oil tank is fixedly installed in the middle of the rack, an engine is fixedly installed at the position, located at one end of the rack, of one side of the oil tank, the oil tank is communicated and connected with the engine, and a power supply system is fixedly installed at the position, located at the other end of the rack, of the other side of the oil tank. An oil tank is arranged at the top of the rack, a transmission system is arranged above the oil tank and connected with an engine, rotor systems are arranged at the two ends of the top of the rack, the transmission system is connected with the rotor systems at the two ends at the same time, and an undercarriage is fixedly installed at the bottom of the rack. The loading capacity of the unmanned aerial vehicle is effectively improved, heavier goods can be carried to fly, the requirement of logistics transportation for large or heavy objects is met, meanwhile, the wind resistance of the unmanned helicopter is enhanced through the double-rotor design, stable flight can be kept under the complex weather condition, and the flight safety and reliability are improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane field, specifically, relate to a longitudinal unmanned helicopter. BACKGROUND

[0002] With the rapid development of electronic commerce, consumers' requirements for express speed are higher and higher, unmanned transport machines can realize point-to-point rapid distribution, shorten the logistics time. In some areas where traffic is inconvenient or infrastructure is backward, unmanned transport machines can provide convenient services and solve the last mile problem. In special scenarios, such as emergency transportation of medical supplies, disaster relief, fire emergency, etc., unmanned transport machines have unique advantages. However, the existing unmanned helicopters have limited load capacity, poor wind resistance, high operation difficulty, short flight time and other problems. In particular, single-rotor unmanned helicopters need tail rotor to balance the torque, which may pose a threat to ground personnel in some cases. Although the double-rotor unmanned helicopter has relatively good load capacity and wind resistance, its structure is complex, the maintenance cost is high, and the operation difficulty is still large.

[0003] How to invent a longitudinal unmanned helicopter to improve these problems has become a problem that technicians in the field are eager to solve. CONTENT OF UTILITY MODEL

[0004] In order to make up for the above shortcomings, the utility model provides a longitudinal unmanned helicopter, which aims to improve the problems of the existing unmanned helicopters, such as limited load capacity, poor wind resistance, high operation difficulty, short flight time and other problems. In particular, single-rotor unmanned helicopters need tail rotor to balance the torque, which may pose a threat to ground personnel in some cases. Although the double-rotor unmanned helicopter has relatively good load capacity and wind resistance, its structure is complex, the maintenance cost is high, and the operation difficulty is still large.

[0005] The utility model is realized as follows: a longitudinal unmanned helicopter, comprising a rack, an oil tank is fixedly installed in the middle of the rack, an engine is fixedly installed at one end of the rack on one side of the oil tank, the oil tank is connected with the engine in communication, a power supply system is fixedly installed at the other end of the rack on the other side of the oil tank, a transmission system is arranged above the oil tank, the transmission system is connected with the engine, rotary wing systems are arranged at both ends of the top of the rack, the transmission system is connected with the rotary wing systems at both ends at the same time, and a landing gear is fixedly installed at the bottom of the rack.

[0006] In a preferred technical scheme of the utility model, the transmission system includes driving pulley, driving pulley fixedly sleeved at one end of engine output shaft, transmission main shaft is rotatably installed on the top of frame through bearing seat, driving pulley and driven pulley are connected through belt transmission, one end of front rotor transmission shaft and rear rotor transmission shaft is fixedly connected with transmission main shaft respectively, the other end of front rotor transmission shaft and rear rotor transmission shaft is fixedly connected with input shaft of front rotor main reducer and rear rotor main reducer respectively, reducer output shaft of front rotor main reducer and rear rotor main reducer is connected with corresponding rotor system.

[0007] In a preferred technical scheme of the utility model, each rotor system includes rudder machine fixed disc, the rudder machine fixed disc is fixedly installed with steering gear, one end of a plurality of pull rods is rotatably connected with the steering disc of steering gear, the other end of a plurality of pull rods is rotatably connected on inclined disc assembly, paddle hub is connected above inclined disc assembly, one end of paddle hub is fixedly connected with corresponding reducer output shaft, a plurality of hinged structures are arranged in the periphery of paddle hub, one end of paddle blade is fixedly installed on each hinged structure.

[0008] In a preferred technical scheme of the utility model, the frame is also fixedly installed with navigation system, lighting system, camera system and cooling system, and the navigation system, lighting system, camera system and cooling system are electrically connected with power supply system.

[0009] In a preferred technical scheme of the utility model, the frame is also fixedly installed with navigation system, lighting system, camera system and cooling system, and the navigation system, lighting system, camera system and cooling system are electrically connected with power supply system.

[0010] In a preferred technical scheme of the utility model, the frame is also fixedly installed with navigation system, lighting system, camera system and cooling system, and the navigation system, lighting system, camera system and cooling system are electrically connected with power supply system.

[0011] In a preferred technical scheme of the utility model, each transportation wheel assembly includes buckle, the buckle is fixedly sleeved on the landing gear, the buckle is provided with extension at one end, the extension is fixedly connected with connecting shaft, one end of rotating part is rotatably connected with one end of connecting shaft, mounting shaft is fixedly installed on the other end of rotating part, transportation wheel is rotatably connected on both ends of mounting shaft, and one end of pressing rod is also fixedly connected on the other end of rotating part.

[0012] The beneficial effects of the present invention are as follows: the present invention obtains a tandem unmanned helicopter through the above-mentioned design. When in use, the dual-rotor design (i.e., front and rear rotor systems) is adopted to effectively improve the load-bearing capacity of the UAV, so that it can carry heavier cargo for flight, meeting the needs of e-commerce rapid delivery for large or heavy items. At the same time, the dual-rotor design also enhances the wind resistance of the unmanned helicopter, so that it can maintain stable flight under complex climatic conditions, thereby improving the safety and reliability of the flight. Compared with traditional single-rotor unmanned helicopters, the tandem unmanned helicopter in this scheme does not require a tail rotor to balance the torque, thereby avoiding the safety threat posed by the tail rotor to ground personnel and reducing the risk during operation. In addition, by optimizing the design of the transmission system and the rotor system, the overall structure of the unmanned helicopter is made simpler and clearer, the difficulty of operation and maintenance is reduced, and the usability and maintainability of the equipment are improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0014] Figure 1 It is a schematic diagram of the overall structure provided by the embodiment of the utility model;

[0015] Figure 2 A schematic diagram of the overall structure of the other side provided for an embodiment of the utility model;

[0016] Figure 3 A schematic diagram of the overall structure of the transmission system provided by the embodiment of the utility model;

[0017] Figure 4 Schematic diagram of the overall structure of the rotor system provided by the utility model embodiment;

[0018] Figure 5 A schematic diagram of the overall structure of the landing gear provided in an embodiment of the present utility model;

[0019] Figure 6 A schematic three-dimensional diagram of the overall structure of the other side landing gear provided in an embodiment of the present utility model;

[0020] Figure 7 This is a schematic three-dimensional diagram of the overall structure of the transport wheel provided in an embodiment of the present utility model.

[0021] In the figure: 1-frame; 2-engine; 3-transmission system; 4-power supply system; 5-navigation system; 6-lighting system; 7-cooling system; 8-fuel tank; 9-rotor system; 10-landing gear; 301-driving pulley; 302-belt; 303-driven pulley; 304-drive main shaft; 305-front rotor main reducer; 306-front rotor drive shaft; 307-rear rotor drive shaft; 308-rear rotor main reducer; 309-reducer output shaft; 901-servo fixing plate; 902-servo; 903-pull rod; 904-swash plate assembly; 905-propeller hub; 906-propeller blade; 101-clip; 102-connecting shaft; 103-rotating part; 104-mounting shaft; 105-transport wheel; 106-pressure rod. DETAILED DESCRIPTION

[0022] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0023] See also Figures 1 to 7 The utility model provides a technical solution: a tandem unmanned helicopter, comprising a frame 1, a fuel tank 8 fixedly mounted in the middle of the frame 1, an engine 2 fixedly mounted on one side of the fuel tank 8 at one end of the frame 1, the fuel tank 8 is connected to the engine 2, the other side of the fuel tank 8 is located at the other end of the frame 1 and a power supply system 4 fixedly mounted, a transmission system 3 is arranged above the fuel tank 8, the transmission system 3 is connected to the engine 2, rotor systems 9 are arranged at both ends of the top of the frame 1, the transmission system 3 is simultaneously connected to the rotor systems 9 at both ends, and a landing gear 10 is fixedly mounted on the bottom of the frame 1.

[0024] See also Figures 1 to 4 The transmission system 3 includes a driving pulley 301, which is fixedly sleeved on one end of the output shaft of the engine 2. A transmission main shaft 304 is rotatably installed on the top of the frame 1 through a bearing seat. A driven pulley 303 is fixedly sleeved on the transmission main shaft 304. The driving pulley 301 and the driven pulley 303 are connected by a belt 302. The front and rear ends of the transmission main shaft 304 are respectively fixedly connected to one end of the front rotor transmission shaft 306 and the rear rotor transmission shaft 307. The other ends of the front rotor transmission shaft 306 and the rear rotor transmission shaft 307 are respectively fixedly connected to the input shafts of the front rotor main reducer 305 and the rear rotor main reducer 308. The reducer output shafts 309 of the front rotor main reducer 305 and the rear rotor main reducer 308 are connected to the corresponding rotor system 9.

[0025] The power output by the engine 2 drives the driving pulley 301 to rotate, which drives the driven pulley 303 to rotate through the transmission of the belt 302, and then drives the transmission main shaft 304 to rotate. The front rotor transmission shaft 306 and the rear rotor transmission shaft 307 are respectively fixedly connected to the two ends of the transmission main shaft 304, thereby realizing the power transmission of the engine 2 to the rotor systems 9 at both ends, and the front rotor transmission shaft 306 and the rear rotor transmission shaft 307 are respectively connected to the corresponding reducer output shaft 309 through the front rotor main reducer 305 and the rear rotor main reducer 308. The front rotor main reducer 305 and the rear rotor main reducer 308 are connected to decelerate and increase the torque of the power transmitted from the transmission main shaft 304, and then the power is output to the rotor system 9. The input shafts of the front rotor main reducer 305 and the rear rotor main reducer 308 and the reducer output shaft 309 can be connected by a structure that can change the transmission direction, such as a bevel gear. At the same time, the relative position of the transmission structure can be adjusted to achieve the opposite rotation direction of the reducer output shafts 309 at the front and rear ends, thereby offsetting the torque generated by the two rotor systems 9.

[0026] Furthermore, each rotor system 9 includes a servo fixing plate 901, on which a servo 902 is fixedly mounted. The steering plate of the servo 902 is circumferentially connected to one end of a plurality of pull rods 903, and the other ends of the plurality of pull rods 903 are rotatably connected to the swash plate assembly 904. A propeller hub 905 is connected above the swash plate assembly 904, and the propeller hub 905 is fixedly connected to one end of the corresponding reducer output shaft 309. The propeller hub 905 is circumferentially provided with a plurality of hinged structures, and one end of a blade 906 is fixedly mounted on each hinged structure.

[0027] The propeller hub 905 is fixedly connected to the end of the corresponding reducer output shaft 309, and rotates synchronously with the reducer output shaft 309. It uses a number of hinged structures arranged around the circumference to connect the drag rod blades 906 to generate lift. The steering wheel in the servo 902 is connected to the swash plate assembly 904 through a number of tie rods 903. When the steering wheel changes its angle, the swash plate assembly 904 will also change the corresponding angle through the pulling of the tie rods 903. The swash plate assembly 904 includes a number of second tie rods, and the two ends of each second tie rod are respectively rotatably connected to the swash plate body and the corresponding hinge structure. Structurally, changing the angle of the swashplate drives the angle of several hinged structures relative to the hub 905, thereby changing the angle of attack of each blade 906. The hinged structures include a flapping hinge, a shimmying hinge, and a pitch-variable hinge, which respectively enable blades 906 to swing up and down around the horizontal axis to adapt to airflow changes during flight; shimmying around the vertical axis to reduce vibration and stress; and a joint that allows blades 906 to rotate around the axial axis, which changes the installation angle (i.e., angle of attack) of blades 906, thereby adjusting the lift and torque generated by the rotor. The specific structure and operating principle are identical to those of a helicopter rotor system, enabling the entire system to maintain stable lift and attitude during flight, as well as perform various complex flight maneuvers.

[0028] Furthermore, a navigation system 5 , a lighting system 6 and a cooling system 7 are fixedly installed on the rack 1 , and the navigation system 5 , the lighting system 6 , the camera system and the cooling system 7 are all electrically connected to the power supply system 4 .

[0029] Navigation System 5 consists of a Global Positioning System (GPS) receiver, an Inertial Navigation System (INS), a flight control computer, a Terrain Awareness and Obstacle Avoidance (TAOA), and a communications module. The GPS receiver receives satellite signals to determine the UAV's precise location. The INS uses sensors such as gyroscopes and accelerometers to measure the UAV's attitude, velocity, and acceleration, providing continuous navigation information. The flight control computer processes this navigation information and generates appropriate flight commands. The TAOA system (e.g., LiDAR and cameras) provides real-time environmental awareness and collision avoidance. The communications module transmits and communicates data with ground stations or other UAVs. Navigation System 5's primary function is to provide the UAV with precise navigation and positioning information, ensuring safe and accurate mission execution in complex environments. It also automatically adjusts the UAV's flight attitude and speed according to a pre-set flight path and altitude, enabling precise flight control. This reliable navigation system improves the UAV's flight accuracy and safety, enabling precise flight operations in complex terrain and adverse weather conditions. At the same time, through real-time perception and obstacle avoidance functions, the navigation system can also effectively prevent the unmanned helicopter from colliding with obstacles, thereby extending its service life and reducing maintenance costs.

[0030] The lighting system 6 includes headlights, taillights, landing lights, warning lights and other parts. The headlights and taillights are used to provide lighting and warning functions at night or in low-light environments; the landing lights are used to illuminate the ground during landing to ensure that the unmanned helicopter can land safely; and the warning lights are used to issue alarm signals in emergency situations to alert surrounding personnel. The main function of the lighting system 6 is to provide lighting and warning functions at night or in low-light environments to ensure that the unmanned helicopter can maintain sufficient visibility and safety during flight and landing. At the same time, the warning lights can also issue alarm signals in emergency situations to remind surrounding personnel to take necessary avoidance measures. The lighting system 6 improves the flight safety of the unmanned helicopter at night and in low-light environments, enabling it to perform safe flight and landing operations in various environments. At the same time, by issuing alarm signals, the lighting system can also effectively reduce conflicts and misunderstandings with surrounding personnel and reduce the probability of accidents.

[0031] The camera system primarily consists of a high-definition optical lens, an image sensor, an image processor, and a data transmission module. The high-definition optical lens is responsible for capturing a clear, wide field of view. Its adjustable focal length allows it to precisely focus on the target object or area, tailored to the shooting requirements and flight altitude, to produce high-quality image information. The image sensor converts the light signals captured by the optical lens into electrical signals. Its high sensitivity and low noise enable it to effectively capture image data in a variety of lighting conditions, especially low-light environments, ensuring clarity and detail in captured images. The image processor processes the raw image data transmitted by the image sensor, performing a series of optimization operations such as noise reduction, contrast enhancement, and color correction to achieve a clearer, more realistic image that is easier to identify and analyze. The data transmission module ensures the rapid and stable transmission of processed image data to the unmanned helicopter's control system or ground control station, enabling operators to obtain real-time image information of the flight area.

[0032] Cooling system 7 consists of a radiator, fan, coolant circulation pump, and heat exchanger. The radiator dissipates heat generated by the engine and other heat sources into the air; the fan accelerates air flow and improves heat dissipation efficiency; the coolant circulation pump circulates the coolant between the engine and radiator to remove heat; and the heat exchanger transfers heat from the coolant to the outside air or water. Cooling system 7 ensures the normal operating temperature of the unmanned helicopter's engine and other heat sources, extending its service life and improving its reliability. By lowering the engine's operating temperature, the cooling system also reduces fuel consumption and emissions, improving the unmanned helicopter's economic and environmental performance.

[0033] See also Figures 5 to 7Transport wheel assemblies are provided on the frame ends on both sides of the landing gear 10.

[0034] By arranging two sets of transport wheel assemblies on both sides of one end of the landing gear 10, it is convenient for personnel to lift the other end to support the whole through the transport wheel assembly when the whole needs to be moved, thereby pushing the whole through the transport wheel assembly.

[0035] Furthermore, a transport box is fixedly installed in the middle of the landing gear 10.

[0036] The unmanned helicopter features an additional storage compartment at its base for storing and transporting various items and equipment. This expands the unmanned helicopter's functionality and application range. Using a transport box (not shown), the unmanned helicopter can carry and transport a variety of items and equipment, such as sensors, cameras, and cargo, meeting a wider range of mission requirements. The addition of a transport box (not shown) significantly expands the unmanned helicopter's capabilities. It can not only perform traditional flight missions but also serve as a transportation tool, playing a greater role in a variety of scenarios. This enhances the unmanned helicopter's usability and market competitiveness.

[0037] Furthermore, each transport wheel assembly includes a buckle 101, which is fixedly mounted on the landing gear 10. An extension portion is provided at one end of the buckle 101, and a connecting shaft 102 is fixedly connected to the extension portion. One end of the connecting shaft 102 is rotatably connected to one end of a rotating member 103, and a mounting shaft 104 is fixedly installed on the other end of the rotating member 103. Both ends of the mounting shaft 104 are rotatably connected to transport wheels 105, and one end of a pressure rod 106 is also fixedly connected to the other end of the rotating member 103.

[0038] When the user presses the corresponding pressure rod 106 to change the angle, the rotating part 103 as a whole will drive the two transport wheels 105 to rotate independently relative to the buckle 101, thereby realizing that the two transport wheels 105 are separated from or in contact with the ground, so that the transport wheel assembly can be flexibly unfolded and stored, thereby improving the overall convenience and flexibility during use.

[0039] Working principle: Engine 2 acts as a power source, generating power through the fuel inside the fuel tank 8. The transmission system 3 transmits the power generated by the engine 2 to the two rotor systems 9. The two rotor systems 9 generate rotation through a number of blades 906 to obtain lift so that the drone as a whole can take off. The power supply system 4 includes a power supply device and connecting lines, which are electrically connected to the navigation system 5, lighting system 6 and cooling system 7 through the connecting lines. The navigation system 5 is used for autonomous navigation and positioning of the unmanned helicopter. The lighting system 6 provides lighting at night or in low-light environments to ensure flight and landing safety. The cooling system 7 maintains the normal operating temperature of the engine and other heat sources to prevent overheating damage. The landing gear 10 is used for landing and supporting the unmanned helicopter. Two sets of transport wheel assemblies are set on the landing gear 10, which can be adjusted to expand and retract by the pressure rod 106 to facilitate the ground movement of the unmanned helicopter.

[0040] It should be noted that the specific models and specifications of the engine 2, the front rotor main reducer 305, the rear rotor main reducer 308, the power supply system 4, the navigation system 5, the lighting system 6, the camera system and the cooling system 7 need to be selected and determined based on the actual specifications of the device. The specific selection calculation method adopts the existing technology in this field, so it will not be described in detail.

[0041] The power supply and principles of the engine 2, the front rotor main reducer 305, the rear rotor main reducer 308, the power supply system 4, the navigation system 5, the lighting system 6 and the camera system cooling system 7 are clear to those skilled in the art and will not be described in detail here.

[0042] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. A tandem unmanned helicopter, characterized in that: It includes a frame, a fuel tank is fixedly installed in the middle of the frame, an engine is fixedly installed on one side of the fuel tank at one end of the frame, the fuel tank is communicated with the engine, a power supply system is fixedly installed on the other side of the fuel tank at the other end of the frame, a transmission system is provided above the fuel tank, the transmission system is connected to the engine, rotor systems are provided at both ends of the top of the frame, the transmission system is simultaneously connected to the rotor systems at both ends, and a landing gear is fixedly installed on the bottom of the frame.

2. The tandem unmanned helicopter according to claim 1, characterized in that: The transmission system includes a driving pulley, which is fixedly sleeved on one end of the engine output shaft, and a transmission main shaft is rotatably installed on the top of the frame through a bearing seat. A driven pulley is fixedly sleeved on the transmission main shaft, and the driving pulley and the driven pulley are connected by belt transmission. The front and rear ends of the transmission main shaft are respectively fixedly connected to one end of the front rotor transmission shaft and the rear rotor transmission shaft, and the other ends of the front rotor transmission shaft and the rear rotor transmission shaft are respectively fixedly connected to the input shafts of the front rotor main reducer and the rear rotor main reducer, and the reducer output shafts of the front rotor main reducer and the rear rotor main reducer are connected to the corresponding rotor system.

3. The tandem unmanned helicopter according to claim 2, characterized in that: Each of the rotor systems includes a servo fixing plate, on which a servo is fixedly mounted, and a plurality of pull rods are circumferentially connected to one end of the servo steering plate, and the other ends of the plurality of pull rods are rotatably connected to a swash plate assembly, and a propeller hub is connected above the swash plate assembly, and the propeller hub is fixedly connected to one end of the corresponding reducer output shaft, and a plurality of hinged structures are circumferentially arranged on the propeller hub, and one end of a blade is fixedly mounted on each of the hinged structures.

4. The tandem unmanned helicopter according to claim 1, wherein: The frame is also fixedly mounted with a navigation system, a lighting system, a camera system and a cooling system, and the navigation system, the lighting system, the camera system and the cooling system are all electrically connected to the power supply system.

5. The tandem unmanned helicopter according to claim 1, wherein: Transport wheel assemblies are provided on the frame ends on both sides of the landing gear.

6. The tandem unmanned helicopter according to claim 1, characterized in that: A transport box is fixedly installed on the bottom of the fuselage in the middle of the landing gear.

7. The tandem unmanned helicopter according to claim 5, characterized in that: Each of the transport wheel assemblies includes a buckle, which is fixedly sleeved on the landing gear. An extension portion is provided at one end of the buckle, and a connecting shaft is fixedly connected to the extension portion. One end of the connecting shaft is rotatably connected to one end of a rotating member, and a mounting shaft is fixedly installed on the other end of the rotating member. Both ends of the mounting shaft are rotatably connected to the transport wheels, and one end of the pressure rod is also fixedly connected to the other end of the rotating member.

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