Novel main rotor and tail rotor direct-drive type unmanned helicopter

Abstract

The utility model discloses a novel main rotor and tail rotor direct-drive type unmanned helicopter which comprises a helicopter body, a main motor, a main rotor, a tail rod part, a tail motor, a tail rotor, an undercarriage, a camera module, a double-GPS module, a motor speed regulation module, a main control module and a battery box. The tail rod part is horizontally arranged on one side of the machine body; the undercarriages are distributed at the lower parts of the aircraft body and the tail rod part; the camera module and the battery box are arranged at the bottom end of the machine body. According to the unmanned helicopter, the carried battery box provides energy for operation of the whole helicopter, the ground station sends an operation instruction to the main control module, the motor speed regulation module controls the main motor to drive the main rotor to rotate at a high speed so that the whole unmanned helicopter can take off, and the arranged tail rotor can provide lateral force during operation so as to provide course control force for the unmanned helicopter; the operated unmanned helicopter carries out image shooting through the camera module, and the double-GPS module assists the unmanned helicopter in accurately obtaining position information of the unmanned helicopter so as to confirm the position of the unmanned helicopter.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a new type of unmanned helicopter with direct drive of main rotor and tail rotor. Background Art

[0002] An unmanned helicopter refers to an unmanned aircraft that can take off and land vertically (VTOL) and is remotely controlled by radio on the ground and autonomously controlled in flight. In terms of its structural form, it belongs to a rotorcraft, and in terms of its function, it belongs to a vertical takeoff and landing aircraft. In the past decade or so, with the research progress of technologies such as composite materials, power systems, sensors, especially flight control, unmanned helicopters have developed rapidly and are increasingly becoming the focus of people's attention.

[0003] The existing unmanned helicopters in the prior art are generally disc-type unmanned helicopters. For example, an unmanned helicopter disclosed in a Chinese patent of the prior art CN208882121U includes a rotating column, and a front engine installed on the rotating column; and a fuel tank installation structure is provided above the front engine; and the fuel tank can be installed on the upper part of the rotating column through a fuel tank assembly.

[0004] However, the mechanical structure design of the above-mentioned unmanned helicopter is relatively complex, resulting in a relatively bulky body and unable to perform corresponding work well. Summary of the Utility Model

[0005] In view of this, the purpose of the utility model is to provide a new type of unmanned helicopter with direct drive of main rotor and tail rotor, which has a more stable structure and is more convenient to use.

[0006] To achieve the above purpose, the utility model adopts the following content:

[0007] A new type of unmanned helicopter with direct drive of main rotor and tail rotor provided by the utility model includes: a fuselage, a main motor, a main rotor, a tail rod part, a tail motor, a tail rotor, a landing gear, a camera module, a dual GPS module, a motor speed control module, a main control module and a battery box;

[0008] The main motor is vertically arranged at the middle position of the upper part of the fuselage. On both sides of the main motor, a dual GPS module, a motor speed control module and a main control module are respectively distributed. The rotor of the main motor is connected upward to the main rotor;

[0009] The tail rod part is horizontally arranged on one side of the fuselage. The tail motor is horizontally arranged at the tail end of the tail rod part. The rotor of the tail motor is perpendicular to the tail rod part and is connected outward to the tail rotor;

[0010] The landing gear is distributed at the lower parts of the fuselage and the tail rod part;

[0011] The camera module is arranged at the front side of the bottom end of the fuselage, and the battery box is arranged at the middle of the bottom end of the fuselage;

[0012] Among them, the main motor and the tail motor are both electrically connected to the motor speed regulation module, the camera module, the dual GPS module, and the motor speed regulation module are all electrically connected to the main control module, and the battery box supplies power to the entire machine.

[0013] According to a new type of main rotor and tail rotor direct drive unmanned helicopter provided by the present invention, a detachable connection method is adopted between the fuselage and the tail rod part. It is convenient to disassemble and assemble the tail rod part and is convenient to carry.

[0014] Further, an internally threaded connecting pipe is provided on one side of the fuselage, and an externally threaded joint is provided at one end of the tail rod part. The externally threaded joint is in threaded connection and cooperation with the internally threaded connecting pipe. The design of the threaded connection is simple, easy to understand and implement, and can provide a stable connection.

[0015] According to a new type of main rotor and tail rotor direct drive unmanned helicopter provided by the present invention, the battery box is detachably connected to the bottom end of the fuselage; a battery fixing frame is provided on the battery box, a connecting block is provided at the upper end of the battery fixing frame, and two hook parts are arranged in a mirror image at the top end of the connecting block. An installation plate is provided at the bottom end of the fuselage, and embedding parts are formed on both sides of the installation plate. The hook parts are in sliding clamping cooperation with the embedding parts. It is convenient to disassemble and assemble the battery box, which helps to replace the battery box in the later stage.

[0016] Further, a number of parallel and spaced partition grooves are formed in an array on the embedding part. In this way, the connection friction force between the hook part and the embedding part is enhanced through the design of the spaced partition grooves to ensure the stable loading of the battery box.

[0017] According to a new type of main rotor and tail rotor direct drive unmanned helicopter provided by the present invention, the landing gear includes inclined side frames and an inclined tail frame. A total of four groups of inclined side frames are arranged at the lower part of the fuselage, and the inclined side frames on both sides of the fuselage are symmetrically distributed in an outward V shape; the inclined tail frame is arranged at the lower part of the tail rod part and is coaxially arranged with the vertical axis line of the fuselage as the axis. Through the above design of the inclined side frames and the inclined tail frame, the impact and jolt resistance of the unmanned helicopter during landing and ground movement are borne, consumed, and absorbed, and the vibration of the fuselage is reduced.

[0018] Further, the upper end of the inclined side frame is detachably connected to the fuselage; fixed socket sleeves that can be inserted and matched with the inclined side frames are provided on the lower side walls of the fuselage, and two ear parts are provided on the outer wall of the fixed socket sleeves, and the two ear parts are fastened by screws and nuts. It is convenient to disassemble and assemble the inclined side frames to facilitate carrying the fuselage.

[0019] A new type of main rotor and tail rotor direct-drive unmanned helicopter provided by the present utility model, the surface of the fuselage has a plurality of protective housings, which are respectively used to install the dual GPS module, the motor speed control module, and the main control module. The protective housings effectively protect the modules carried on the fuselage, reduce the maintenance cost, and greatly improve the performance and safety of the unmanned helicopter.

[0020] Compared with the prior art, the present utility model has the following technical effects: The structure of the present utility model is simple and reasonably designed; the battery box carried provides energy for the operation of the entire machine, the ground station sends an operation instruction to the main control module, and the motor speed control module controls the main motor to drive the main rotor to rotate at a high speed, so that the entire unmanned helicopter takes off, and the set tail rotor can provide a lateral force during operation to provide a heading control force for the unmanned helicopter; the unmanned helicopter after operation takes pictures through the camera module, and the dual GPS module assists the unmanned helicopter to accurately obtain its position information to confirm the position of the unmanned helicopter itself. Description of the Drawings

[0021] The following further details the specific implementation manners of the present utility model with reference to the drawings.

[0022] Figure 1 is an overall schematic diagram of a new type of main rotor and tail rotor direct-drive unmanned helicopter according to an embodiment of the present utility model;

[0023] Figure 2 is a connection diagram of the corresponding modules on a new type of main rotor and tail rotor direct-drive unmanned helicopter according to an embodiment of the present utility model;

[0024] Figure 3 is a related schematic diagram of the connection between the fuselage and the battery box of a new type of main rotor and tail rotor direct-drive unmanned helicopter according to an embodiment of the present utility model;

[0025] Figure 4 is a related schematic diagram of the inclined side frame in the landing gear part of a new type of main rotor and tail rotor direct-drive unmanned helicopter according to an embodiment of the present utility model;

[0026] 1 - fuselage, 2 - main motor, 3 - tail motor, 4 - tail rod part, 5 - battery box, 6 - mounting plate; 10 - main control module, 20 - camera module, 30 - dual GPS module, 40 - motor speed control module; 11 - protective housing, 12 - inclined side frame, 13 - inclined tail frame, 14 - internal thread connecting pipe, 15 - fixed socket, 151 - ear part, 41 - external thread joint, 51 - battery fixing bracket, 52 - connecting block, 521 - hook part, 61 - embedding part, 62 - separating groove. Specific Embodiments

[0027] To more clearly illustrate the present utility model, the following further describes the present utility model in conjunction with preferred embodiments. Those skilled in the art should understand that the specific content described below is illustrative rather than restrictive, and should not be used to limit the protection scope of the present utility model.

[0028] In the description of the present utility model, it should be noted that unless otherwise clearly specified and limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0029] Please refer to Figures 1 to 4 as shown. An embodiment of the present utility model provides a new type of main rotor and tail rotor direct drive unmanned helicopter, including a fuselage 1, a main motor 2, a main rotor (not shown), a tail motor 3, a tail rod part 4, a tail rotor (not shown), a landing gear, a camera module 20, a dual GPS module 30, a motor speed control module 40, a main control module 10, and a battery box 5.

[0030] The main motor 2 is vertically arranged at the middle position on the upper part of the fuselage 1. On both sides of the main motor 2, the dual GPS module 30, the motor speed control module 40, and the main control module 10 are respectively distributed. The rotor of the main motor 2 is vertically upward connected to the main rotor, and the main rotor is driven by the main motor 2 to rotate at a high speed.

[0031] The tail rod part 4 is arranged on one side of the fuselage 1 in a horizontal posture, and the tail motor 3 is horizontally arranged at the tail end of the tail rod part 4. Among them, the rotor of the tail motor 3 is perpendicular to the tail rod part 4 and is outwardly connected to the tail rotor, that is, the rotation direction of the tail rotor is within a vertical plane.

[0032] The landing gear is distributed at the lower parts of the fuselage 1 and the tail rod part 4, mainly playing a supporting role for the unmanned helicopter.

[0033] The camera module 20 is arranged at the front side of the bottom end of the fuselage 1 for convenient photographing, and the battery box 5 is arranged at the middle of the bottom end of the fuselage 1. The carried battery box provides energy for the operation of the entire machine.

[0034] Among them, the main motor 2 and the tail motor 3 are both electrically connected to the motor speed control module 40. The camera module 20, the dual GPS module 30, and the motor speed control module 40 are all electrically connected to the main control module 10, and the battery box 5 supplies power to the entire machine.

[0035] In one implementation manner, a detachable connection method is adopted between the fuselage 1 and the tail rod part 4, which is convenient for disassembling and assembling the tail rod part and is convenient for carrying.

[0036] Specifically, an internally threaded pipe joint 14 is provided on one side of the body 1, and an externally threaded joint 41 is provided at one end of the tail rod portion 4. The externally threaded joint 41 is in threaded connection and cooperation with the internally threaded pipe joint 14. The design of the threaded connection is simple, easy to understand and implement, and can provide a firm connection. Of course, a screw fastening connection method can also be adopted.

[0037] In one implementation, the battery box 5 is detachably connected to the bottom end of the body 1; a battery fixing bracket 51 is provided on the battery box 5, a connecting block 52 is provided at the upper end of the battery fixing bracket 51, and two hook portions 521 are arranged in a mirror image at the top end of the connecting block 52. An installation plate 6 is provided at the bottom end of the body 1, and embedding portions 61 are formed on both sides of the installation plate 6. The hook portions 521 are in sliding clamping fit with the embedding portions 61. Slide the battery box from one side of the bottom end of the body and snap it onto the installation plate, that is, use the hook portions to slide and snap into the embedding portions, which is convenient for disassembling and assembling the battery box and helps to replace the battery box later.

[0038] Among them, a number of parallel and spaced partition grooves 62 are formed in an array on the embedding portion 61. In this way, the connection friction force between the hook portion and the embedding portion is enhanced through the design of the spaced partition grooves to ensure the stable loading of the battery box.

[0039] In one implementation, the landing gear includes inclined side frames 12 and an inclined tail frame 13. A total of four groups of inclined side frames 12 are provided at the lower part of the body 1, and the inclined side frames 12 on both sides of the body 1 are symmetrically distributed in an outward V shape; the inclined tail frame 13 is provided at the lower part of the tail rod portion 4, and the inclined tail frame 13 is coaxially arranged with the vertical axis line of the body 1 as the axis. Through the above design of the inclined side frames and the inclined tail frame, the ability to withstand, consume, and absorb the impact and bumps of the unmanned helicopter during landing and ground movement is achieved, and the vibration of the body is reduced.

[0040] Among them, the upper end of the inclined side frame 12 is detachably connected to the body 1; a fixed socket 15 that can be inserted and matched with the inclined side frame 12 is provided on the lower side wall of the body 1, and two spaced ears 151 are provided on the outer wall of the fixed socket 15. The two ears 151 are fastened by screws and nuts, and the screws are used to control the approach or separation of the two ears to achieve the tightening and loosening of the fixed socket, so as to realize the firm connection between the fixed socket and the inclined side frame. In the above way, it is convenient to disassemble and assemble the inclined side frame to facilitate carrying the body.

[0041] In one implementation, the surface of the body 1 has a plurality of protective housings 11, which are respectively used to install a dual GPS module, a motor speed control module, and a main control module. The protective housings effectively protect the modules carried on the body, reduce the maintenance cost, and greatly improve the performance and safety of the unmanned helicopter.

[0042] Compared with traditional helicopters, the direct-drive unmanned helicopter of the present application eliminates complex transmission structures such as gears and belts, mainly uses electric motors for driving, has a simple structure and fewer components, greatly improves the driving efficiency, and at the same time reduces the difficulty and cost of machine maintenance;

[0043] Moreover, the direct-drive unmanned helicopter adopts dual GPS modules and optional dual RTK modules. In this way, it can provide heading guidance for the flight of the unmanned aircraft without relying on a magnetic compass. Compared with traditional unmanned aircraft using a magnetic compass to determine the heading, it has higher reliability and anti-interference ability;

[0044] In addition, the main significance and advantage of the battery mounting design on the direct-drive unmanned helicopter, which is designed to be movable back and forth, is that it can conveniently adjust the center of gravity position of the aircraft according to the weights of different payloads (pods, cameras, gimbals, etc.), achieve multi-payload adaptation, ensure flight safety and controllability, and achieve flexible adjustment of the center of gravity with good adaptability.

[0045] Obviously, the above embodiments of the present utility model are merely examples for clearly illustrating the present utility model, rather than limitations on the implementation manners of the present utility model. For those of ordinary skill in the art, other different forms of changes or variations can be made based on the above description. It is impossible to enumerate all the implementation manners here. Any obvious changes or variations derived from the technical solutions of the present utility model still fall within the protection scope of the present utility model.

Claims

1. A new type of main rotor and tail rotor direct drive unmanned helicopter, characterized in that, Comprising: Airframe, main motor, main rotor, tail rod part, tail motor, tail rotor, landing gear, camera module, dual GPS module, motor speed control module, main control module and battery box; The main motor is vertically arranged at the middle position of the upper part of the airframe. The dual GPS module, motor speed control module and main control module are respectively distributed on both sides of the main motor. The rotor of the main motor is connected upward to the main rotor; The tail rod part is horizontally arranged on one side of the airframe. The tail motor is horizontally arranged at the tail end of the tail rod part. The rotor of the tail motor is perpendicular to the tail rod part and is connected outward to the tail rotor; The landing gear is distributed at the lower parts of the airframe and the tail rod part; The camera module is arranged at the front side of the bottom end of the airframe, and the battery box is arranged at the middle of the bottom end of the airframe; Wherein, the main motor and the tail motor are both electrically connected to the motor speed control module. The camera module, dual GPS module and motor speed control module are all electrically connected to the main control module. The battery box supplies power to the whole machine.

2. The novel main rotor and tail rotor direct drive unmanned helicopter according to claim 1, characterized in that A detachable connection mode is adopted between the airframe and the tail rod part.

3. A novel main rotor and tail rotor direct drive unmanned helicopter according to claim 2, characterized in that, An internally threaded connection pipe is arranged on one side of the airframe. An externally threaded joint is arranged at one end of the tail rod part. The externally threaded joint is in threaded connection and cooperation with the internally threaded connection pipe.

4. A novel main rotor and tail rotor direct drive unmanned helicopter according to claim 1, characterized in that, A detachable connection is provided between the battery box and the bottom end of the airframe; A battery fixing frame is arranged on the battery box. A connection block is arranged at the upper end of the battery fixing frame. Two hook parts are arranged in a mirror image at the top end of the connection block. An installation plate is arranged at the bottom end of the airframe. Embedding parts are formed on both sides of the installation plate. The hook parts are in sliding clamping cooperation with the embedding parts.

5. A novel main rotor and tail rotor direct drive unmanned helicopter according to claim 4, characterized in that, A plurality of parallel and spaced partition grooves are formed in an array on the embedding part.

6. A novel main rotor and tail rotor direct drive unmanned helicopter according to claim 1, characterized in that, The landing gear includes inclined side frames and an inclined tail frame. A total of four groups of inclined side frames are arranged at the lower part of the airframe. The inclined side frames on both sides of the airframe are symmetrically distributed in an outward V shape; The inclined tail frame is arranged at the lower part of the tail rod part and is coaxially arranged with the vertical axis line of the airframe as the axis.

7. A novel main rotor and tail rotor direct drive unmanned helicopter according to claim 6, characterized in that, A detachable connection is provided between the upper end of the inclined side frame and the airframe; Fixed sockets capable of being inserted and matched with the inclined side frames are arranged on the side wall of the lower part of the airframe. Two ears are arranged on the outer wall of the fixed socket. The two ears are fastened by screws and nuts.

8. A novel main rotor and tail rotor direct drive unmanned helicopter according to claim 1, characterized in that, A plurality of protective shells are provided on the surface of the airframe and are respectively used for installing the dual GPS module, motor speed control module and main control module.

Images