Unmanned helicopter with middle power

Abstract

The utility model discloses an unmanned helicopter with middle power, and belongs to the technical field of small and medium-sized aviation unmanned helicopters. Comprising a fuselage, an empennage, a power system and a rotor system, the power system is installed in the fuselage, and the rotor system is installed over the power system; a fuel oil system is installed above the power system and surrounds the transmission system, and the center of gravity of the fuel oil system and the center of gravity of the power system are located on the central axis of rotation of the rotor wing system. The unmanned helicopter is subjected to compartment and block layout, a transmission and fuel oil cabin, a power cabin, an electrical cabin and a task cabin are arranged, and a subsystem can be designed in an independent space, so that the unmanned helicopter is compact in structure, the gravity center is easier to trim, the length of a bow increased due to gravity center trim is removed, and the size of the unmanned helicopter is shortened.

Description

Technical Field

[0001] This utility model relates to an unmanned helicopter, specifically a mid-powered unmanned helicopter, belonging to the field of unmanned helicopter technology. Background Technology

[0002] Currently, the contradiction between the convenience of unmanned helicopters in combat and training support (small size) and their superior performance (large payload and strong adaptability to complex environments) is becoming increasingly prominent in China. For emergency response and use scenarios with rugged roads in high-altitude areas, the small size of unmanned helicopters makes them easy to load and transport by vehicles, ensuring the mobility and off-road performance of vehicles and reducing the requirements for take-off and landing sites. Their superior performance is to carry heavier payloads, quickly reach distant mission areas, and perform reconnaissance, monitoring and detection activities at high altitudes, so as to give full play to the advantages of unmanned helicopters and improve the economic efficiency of flight.

[0003] Conventional single-rotor unmanned helicopters with tail rotors follow the layout of manned helicopters, typically with the engine at the rear and electrical and equipment at the front. This layout causes the unmanned helicopter's center of gravity to be shifted rearward. To achieve balance, there are generally two design methods. One is to lengthen the bow and increase the lever arm to achieve balance, which increases the length of the unmanned helicopter and reduces the utilization of internal space. The other is to increase the ballast in the bow, which increases the useless weight of the unmanned helicopter for missions, reducing the effective payload. The increased weight also reduces the unmanned helicopter's flight time, maximum speed, and other performance indicators.

[0004] In view of the above, in order to overcome the above technical problems, this utility model designs a mid-powered unmanned helicopter, which solves the above technical problems. Summary of the Invention

[0005] The technical objective of this invention is to reduce the impact of the heaviest individual components, the engine and fuel system, on the center of gravity of the unmanned helicopter by adopting a centrally located power system layout, thereby facilitating the balance of the center of gravity and shortening the overall size of the unmanned helicopter, thus solving the technical problem of center of gravity balance caused by conventional layouts.

[0006] To achieve the above-mentioned technical objectives, this utility model provides the following technical solution:

[0007] The present invention provides a mid-powered unmanned helicopter, comprising a fuselage and a tail. The front fuselage provides a platform and space for the installation of transmission, power, electrical equipment, and mission equipment; the rear fuselage is connected to the tail. The rotor system is mounted directly above the power system so that the centers of gravity of both are on the same vertical line.

[0008] The fuel system is mounted above and around the transmission system, and the center of gravity of the fuel system and the power system is located on the central axis of rotation of the rotor system. The rotor system includes the hub, blades, and tail rotor.

[0009] The power system includes a power compartment and an engine. The power compartment is located in the middle of the fuselage, and the engine is installed inside the power compartment. The output shaft of the engine is connected to the transmission system.

[0010] The fuel system includes a fuel tank compartment and a fuel tank. The fuel tank compartment is located on the upper part of the power compartment, and the fuel tank is installed inside the fuel tank compartment. A transmission compartment is also located in the center of the fuel tank compartment, and the transmission system is installed inside the transmission compartment.

[0011] As a further optimization of this technical solution, the fuel tank is located above the forward fuselage, and is arranged in a ring around the drive shaft. The fuel tank is generally elongated and flat. The internal shape of the fuel tank ensures that the center of gravity of the fuel is almost located at the center of the rotor system when the fuel load is different.

[0012] As a further optimization of this technical solution, the main drive shaft in the transmission system is installed on the upper part of the fuselage and connected upward to the rotor system. The transmission system transmits the output torque of the power system to the main drive shaft through belt drive. The transmission system is used to drive the rotor system and the engine.

[0013] As a further optimization of this technical solution, the engine is located in the engine compartment, with hatches on both the left and right sides of the engine to facilitate daily inspection and maintenance of the engine.

[0014] As a further optimization of this technical solution, a mission bay and an electrical bay are respectively located at the bow and stern of the fuselage. Both the mission bay and the electrical bay are equipped with lightweight avionics equipment to enhance the functionality of the UAV. Lightweight electrical equipment with different functions is located in the electrical bay and mission bay of the unmanned helicopter to correct and balance the center of gravity. This makes the unmanned helicopter more compact and easier to balance, eliminating the increased bow length caused by center of gravity balancing and shortening the overall size of the unmanned helicopter.

[0015] It is worth noting that lightweight electrical equipment is a further balancing feature relative to the engine and fuel tank, taking into account the overall weight of the fuselage. Its weight should be between 0-30kg. Lightweight electrical equipment at the front and rear of the fuselage improves the balance of the fuselage.

[0016] The beneficial effects of this utility model are as follows:

[0017] 1. This utility model reduces the complexity of subsystem communication and coordination through a modular layout. The centrally located power unit reduces the overall length of the unmanned helicopter, improving its transport mobility and off-road performance. Heavy individual components do not affect the overall center of gravity, reducing the difficulty of weight balancing.

[0018] 2. By providing hatches on both sides of the engine, this utility model allows operators to open the hatches to observe and adjust the engine's condition, while closing the hatches provides a good environment for the engine, thus greatly improving the convenience and efficiency of routine inspections and daily maintenance. Attached Figure Description

[0019] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] The above and other aspects of the present invention will now be described by way of example only, with reference to the accompanying drawings, in which:

[0021] Figure 1 This is a schematic diagram of the overall structural layout of this utility model;

[0022] Figure 2 This is a schematic diagram of the structure of the fuel tank of this utility model;

[0023] Figure 3 This is a schematic diagram of the internal structure of this utility model.

[0024] In the diagram: 1. Power system; 11. Power compartment; 12. Engine; 13. Door; 2. Rotor system; 3. Fuel system; 31. Fuel tank compartment; 32. Fuel tank; 33. Transmission compartment; 4. Transmission system; 41. Main drive shaft; 5. Mission compartment; 6. Electrical compartment. Detailed Implementation

[0025] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0026] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., may be used here to describe the spatial positional relationship of a device or feature to other devices or features as shown in the figure. It should be understood that spatial relative terms are intended to include different orientations in use or operation in addition to the orientation of the device as described in the figure.

[0027] like Figure 1-3 As shown, the mid-powered unmanned helicopter provided by this utility model includes a fuselage and a tail. The front fuselage and tail boom are manufactured using composite material molds and are connected by locating pins and mounting screws. The front fuselage provides a platform and space for the installation of transmission, power, electrical equipment and mission equipment; the rear fuselage is connected to the tail.

[0028] The power system 1 is fixed to the pre-drilled mounting holes in the fuselage with screws, and the rotor system 2 is connected to the main shaft of the drive unit with screws. The rotor system 2 is mounted directly above the power system 1 so that the centers of gravity of both are on the same vertical line.

[0029] In this embodiment, a fuel system 3 is mounted above and around the transmission system 4, and the center of gravity of the fuel system 3 and the power system 1 is located on the central axis of rotation of the rotor system 2. The rotor system 2 includes a hub, blades, and a tail rotor.

[0030] The power system 1 includes a power nacelle 11 and an engine 12. The power nacelle 11 is located in the middle of the fuselage, and the engine 12 is installed inside the power nacelle 11. The output shaft of the engine 12 is connected to the rotor system 2. The fuel system 3 includes a fuel tank compartment 31 and a fuel tank 32. The fuel tank compartment 31 is located above the power nacelle 11, and the fuel tank 32 is installed inside the fuel tank compartment 31. A transmission compartment 33 is also provided at the center of the fuel tank compartment 31, and a transmission system 4 is installed inside the transmission compartment 33.

[0031] like Figure 2 and Figure 3 As shown, in this embodiment, the fuel tank 32 is located above the forward fuselage and is fixed to the fuselage via a limiting groove and screw holes. The fuel tank 32 is arranged in a roughly annular shape around the main drive, and is generally elongated. The internal shape of the fuel tank 32 ensures that the center of gravity of the fuel is almost located at the center of the rotor system 2 when the fuel load is different.

[0032] The two heaviest individual components of the unmanned helicopter, engine 12 and fuel tank 32, have their centers of gravity located below the center of rotor system 2. During normal cruise flight of the unmanned helicopter, the pitching moment generated by the fuel on the center of gravity is almost zero.

[0033] like Figure 3 As shown, the main drive shaft 41 in the transmission system 4 is installed on the upper part of the fuselage and connected upward to the rotor system 2. The transmission system 4 transmits the output torque of the power system 1 to the main drive shaft 41 through belt drive. The transmission system 4 is used to drive the rotor system 2 and the engine 12.

[0034] like Figure 3 As shown, the engine 12 is located in the engine compartment, and the engine 12 is provided with doors 13 on the left and right sides to facilitate the daily inspection and maintenance of the engine 12.

[0035] The fuselage has a mission compartment 5 at the front and an electrical compartment 6 at the rear. Each of the mission compartment 5 and the electrical compartment 6 contains about 10 kg of avionics equipment to improve the functionality of the UAV. Electrical equipment with different functions is located in the UAV helicopter's electrical compartment 6 and mission compartment 5 to correct and balance the UAV helicopter's center of gravity.

[0036] In this embodiment, for emergency rescue and high-altitude canyon flight scenarios, the unmanned helicopter is required to be of a length that facilitates deployment and transportation in confined environments. The unmanned helicopter's engine 12 is a 100kg-class aviation piston engine 12, with its center of gravity located below the rotor system 2, thus not affecting changes in the center of gravity.

[0037] The fuel tank 32 has a capacity sufficient for long-duration flight, and changes in fuel volume during flight have a relatively small impact on the helicopter's center of gravity, thus reducing the alternating load on the unmanned helicopter rotor system 2.

[0038] The technical features disclosed above are not limited to combinations of the disclosed features with other features. Those skilled in the art may also make other combinations of the technical features according to the purpose of the disclosure in order to achieve the purpose of this disclosure.

[0039] The description herein is provided to enable those skilled in the art to implement or use the present disclosure. Various modifications to the present disclosure will be readily apparent to those skilled in the art, and the general principles defined herein can be applied to other variations without departing from the scope of the disclosure. Therefore, this disclosure is not limited to the examples and designs described herein, but should be given the broadest scope consistent with the principles and novel features disclosed herein.

Claims

1. A mid-powered unmanned helicopter, comprising a fuselage and a tail, characterized in that: It also includes a power system (1), a rotor system (2), a fuel system (3), and a transmission system (4). The rotor system (2) is mounted directly above the power system (1). The rotor system (2) is connected to the power system (1) through the transmission system (4); The fuel system (3) is arranged around the transmission system (4) and located above the power system (1); The centers of gravity of both the fuel system (3) and the power system (1) are located on the central axis of rotation of the rotor system (2).

2. The mid-powered unmanned helicopter according to claim 1, characterized in that: The power system (1) includes a power compartment (11) and an engine (12). The power compartment (11) is located in the middle of the fuselage. The engine (12) is installed inside the power compartment (11). The output shaft of the engine (12) is connected to the transmission system (4).

3. The mid-powered unmanned helicopter according to claim 2, characterized in that: The fuel system (3) includes a fuel tank compartment (31) and a fuel tank (32). The fuel tank compartment (31) is located on the upper part of the power compartment (11). The fuel tank (32) is installed inside the fuel tank compartment (31). A transmission compartment (33) is also provided in the center of the fuel tank compartment (31). The transmission system (4) is installed inside the transmission compartment (33).

4. The mid-powered unmanned helicopter according to claim 3, characterized in that: The main drive shaft (41) in the transmission system (4) is installed on the upper part of the fuselage and connected upward to the rotor system (2). The transmission system (4) transmits the output torque of the power system (1) to the main drive shaft (41) by belt drive. The transmission system (4) is used to drive the rotor system (2) and the engine (12).

5. The mid-powered unmanned helicopter according to claim 4, characterized in that: The fuel tank (32) is arranged in a ring around the drive shaft, and the fuel tank (32) is generally flat and elongated.

6. The mid-powered unmanned helicopter according to any one of claims 2-5, characterized in that: The engine (12) has hatches (13) on both sides and on the power compartment (11).

7. The mid-powered unmanned helicopter according to claim 1, characterized in that: The fuselage is provided with a mission compartment (5) and an electrical compartment (6) at the front and rear, respectively, and both the mission compartment (5) and the electrical compartment (6) are equipped with lightweight avionics equipment.

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