Improved lift device helicopter

Abstract

The application relates to the technical field of low-altitude aircrafts, in particular to an improved lift device helicopter, which comprises a machine body and a lift device arranged on the top of the machine body, wherein the lift device comprises a supporting installation part, a main motor, a rotating disc and two main rotors or propellers; the main motor is installed on the machine body through the supporting installation part, the two main rotors or propellers are arranged on the rotating disc, the rotating disc is connected to the rotor of the main motor, and the two main rotors or propellers revolve synchronously with the rotating disc; a synchronous mechanism is arranged between the two main rotors or propellers, so that the two main rotors or propellers can revolve synchronously. The main motor drives the rotating disc to rotate, drives the two main rotors or propellers to revolve synchronously, realizes the first rotation, in the revolving process, the two main rotors or propellers realize the self-rotation, form the second rotation, and the revolution and the self-rotation form the superimposed rotation effect, greatly improve the utilization efficiency of air flow, and realize the miniaturization of the rotor type aircraft.

Description

Technical Field

[0001] This invention relates to the field of transportation technology, specifically to an improved helicopter with a lift device. Background Technology

[0002] Although helicopters are relatively far removed from people's daily lives, they are familiar to many due to their advantages such as vertical takeoff and landing, convenient landing, and no need for a runway. The lift system is a crucial component of a helicopter; it generally includes the rotor, which is powered by the engine located in the helicopter's cabin through a transmission mechanism, thus achieving rotation. The main rotor of existing rotorcraft helicopters typically consists of two or more blades located in the same plane. Driven by the engine, they rotate, generating a strong downdraft that lifts the helicopter. However, existing rotorcraft helicopter lift systems have significant drawbacks due to structural design issues: 1. The blades are all located in the same plane, resulting in a simple structure and low aerodynamic efficiency; 2. Significantly increasing the lift capacity of the lift system mainly relies on increasing the engine's output power and the length of the main rotor, which is detrimental to helicopter miniaturization.

[0003] Therefore, there is still considerable room for improvement in the existing technology. Summary of the Invention

[0004] The purpose of this invention is to address the shortcomings and deficiencies of existing technologies by providing an improved helicopter with a lift device that is more compact, has higher air utilization efficiency, and significantly increases lift, thereby effectively reducing the size of the helicopter.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] The present invention discloses an improved helicopter with a lifting device, comprising a fuselage and a lifting device mounted on top of the fuselage. The lifting device includes a support mounting section, a main motor, a turntable, and two main rotors or propellers. The main motor is mounted on the fuselage via the support mounting section. The two main rotors or propellers are mounted on the turntable, which is connected to the rotor of the main motor. The two main rotors or propellers revolve synchronously with the turntable. A synchronization mechanism is provided between the two main rotors or propellers to achieve synchronous rotation of the two main rotors or propellers and ensure that the main rotors or propellers do not collide.

[0007] According to the above technical solution, the synchronization mechanism includes two rotating gears rotatably disposed at both ends of the turntable, and a large gear meshing with the two rotating gears is provided between them. The large gear is fixedly connected to the support mounting part; the two main rotors or propellers are respectively connected to the two rotating gears through a rotating shaft.

[0008] According to the above technical solution, the synchronization mechanism includes two rotating synchronous wheels rotatably disposed at both ends of the turntable. The two rotating synchronous wheels are connected by a synchronous belt, and the two main rotors or propellers are respectively connected to the two rotating synchronous wheels through a rotating shaft.

[0009] According to the above technical solution, the synchronization mechanism includes two servo motors symmetrically arranged at both ends of the turntable, and the two main rotors or propellers are driven to rotate by the two servo motors respectively.

[0010] According to the above technical solution, a universal coupling is provided above each of the two rotary gears or the two rotary synchronous pulleys, and the rotating shaft is connected to the rotary gears or rotary synchronous pulleys through the universal coupling.

[0011] According to the above technical solution, including a bracket, the rotor of the main motor is connected to the turntable and the bracket through a main rotating shaft, and mounting holes are provided at both ends of the bracket. Bearings are provided in the mounting holes, and the rotating shaft is connected to the bearings.

[0012] According to the above technical solution, the turntable and the bracket are integrated.

[0013] According to the above technical solution, it also includes a secondary rotor, which is located below the two main rotors or propellers and is connected to the stator of the main motor.

[0014] According to the above technical solution, the installation angle of the blades of the main rotor is 2 to 10 degrees; the installation angle of the blades of the auxiliary rotor is 6 to 15 degrees.

[0015] According to the above technical solution, the rear chamfer of the main rotor or propeller shaft is 6 to 20 degrees.

[0016] According to the above technical solution, the installation angle of the blades of the main rotor is 5 degrees; the installation angle of the blades of the auxiliary rotor is 10 degrees.

[0017] The beneficial effects of the present invention are as follows: the main motor of the present invention is mounted on the body through the support mounting part, the two main rotors or propellers are set on the turntable, the turntable is connected to the rotor of the main motor, and the two main rotors or propellers revolve synchronously with the turntable; a synchronization mechanism is provided between the two main rotors or propellers, thereby realizing the synchronous rotation of the two main rotors or propellers. In use, the main motor drives the turntable to rotate, thereby causing the two main rotors or propellers to revolve synchronously with the turntable, achieving the first rotation. During the revolution, under the drive of external force and / or airflow, the two main rotors or propellers also rotate, forming the second rotation. Since the rotor shaft of the main rotor or propeller has a rear chamfer, and the angle of attack of the blades of the main rotor or propeller is positive, the main rotor or propeller generates a forward and downward airflow when rotating. This airflow merges with the incoming airflow from the front of the main rotor or propeller during its revolution, which reduces the overall downwash flow rate and slows down the flow velocity. The incoming airflow from the front during the revolution also accelerates the rotation of the main rotor, producing an effect similar to that of an autogyro rotor. In this way, it effectively suppresses the airflow from carrying away too much kinetic energy, thereby improving efficiency and producing a ground effect similar to that, increasing lift. The main rotor or propeller's rotation, both on its own axis and in revolution, creates a superimposed rotational effect. This suppresses the downwash airflow from the rotor's rotation and absorbs the energy of the incoming airflow during its revolution, significantly improving airflow utilization efficiency. With the same main motor output power, the lift of this invention is significantly increased. This increased lift is beneficial for helicopter miniaturization. Furthermore, a synchronization mechanism is provided between the two main rotors or propellers to achieve synchronized rotation. This design ensures that the two main rotors or propellers maintain the same rotational speed during rotation, effectively avoiding mutual interference. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0019] Figure 2 This is a schematic diagram of the structure of the first embodiment of the lifting device of the present invention;

[0020] Figure 3 This is a schematic diagram of the second embodiment of the lifting device of the present invention;

[0021] Figure 4 This is a schematic diagram of another embodiment of the lifting device of the present invention in the second embodiment;

[0022] Figure 5 This is a schematic diagram of the third embodiment of the lifting device of the present invention.

[0023] In the picture:

[0024] 1. Airframe; 2. Lifting device; 3. Synchronization mechanism; 4. Universal coupling; 5. Main shaft; 6. Servo motor; 7. Propeller; 21. Support mounting part; 22. Turntable; 23. Main motor; 24. Bracket; 25. Main rotor; 26. Shaft; 27. Mounting hole; 28. Bearing; 29. ​​Secondary rotor; 31. Large gear; 32. Rotary gear; 33. Synchronous belt; 34. Synchronous pulley; 35. Battery box. Detailed Implementation

[0025] The technical solution of the present invention will be described below with reference to the accompanying drawings and embodiments.

[0026] Example 1:

[0027] like Figure 1 and Figure 2 As shown, a helicopter with an improved lift device includes a fuselage 1 and a lift device 2 located on top of the fuselage 1. The above is the basic structure of the present invention, which is not substantially different from the prior art. The fuselage 1 will not be described again.

[0028] Compared with the prior art, the main inventive point of this invention lies in the structural improvement of the lifting device 2. Specifically, the lifting device 2 includes a support mounting part 21, a main motor 23, a turntable 22, and two main rotors 25 or propellers 7. The main motor 23 is mounted on the body 1 through the support mounting part 21. The two main rotors 25 or propellers 7 are disposed on the turntable 22, which is connected to the rotor of the main motor 23. The two main rotors 25 or propellers 7 revolve synchronously with the turntable 22. A synchronization mechanism 3 is provided between the two main rotors 25 or propellers 7 to achieve synchronous rotation of the two main rotors 25 or propellers 7, ensuring that the main rotors 25 or propellers 7 do not collide when rotating.

[0029] In operation, the main motor 23 drives the turntable 22 to rotate, thereby causing the two main rotors 25 or propellers 7 to revolve synchronously with the turntable, achieving the first rotation. During this revolution, driven by external force and / or airflow, the two main rotors 25 or propellers 7 also rotate on their own axes, forming a second rotation. The simultaneous revolution and rotation create a good superimposed rotation effect, greatly improving the utilization efficiency of airflow. With the same output power of the main motor 23 and the same size of the main rotors 25 or propellers 7, the lift of this invention is significantly greater, greatly improving working efficiency. It also benefits from the miniaturization of helicopters.

[0030] The present invention provides a synchronization mechanism 3 between the two main rotors 25 or propellers 7, thereby realizing the synchronous rotation of the two main rotors 25 or propellers 7. This setting can ensure that the two main rotors 25 or propellers 7 maintain the same speed when rotating, effectively avoiding mutual interference and achieving excellent lift effect.

[0031] The present invention preferably has two main rotors 25 or propellers 7 symmetrically arranged. With the synchronization mechanism 3 effectively overcoming mutual interference, the superposition of revolution and rotation is more effective.

[0032] This embodiment also includes an auxiliary rotor 29, which is located below the two main rotors 25 or propellers 7 and connected to the stator of the main motor 23. With this configuration, the two main rotors 25 or propellers 7 generate a certain counter-torque during their revolution and rotation. To balance this counter-torque, existing technologies mainly rely on a tail rotor. However, tail rotors have certain drawbacks, being unsafe and inefficient. This invention effectively solves this technical problem by incorporating the auxiliary rotor 29. Specifically, when the auxiliary rotor 29 rotates in the opposite direction to the revolution of the main rotors 25 or propellers 7, its rotation effectively overcomes the counter-torque generated by the revolution of the main rotors 25 or propellers 7. This eliminates the need for a tail rotor structure, significantly reducing the helicopter's size and improving safety, as helicopter accidents caused by tail rotors occur frequently every year.

[0033] It should be noted that the turntable 22 can also be connected to the stator of the main motor 23, and the auxiliary rotor 29 can also be connected to the rotor of the main motor 23. These are all conventional adjustments and fall within the scope of protection of this invention. In this case, the main motor 23 is powered by a battery and control circuit arranged in the battery box 35. The battery box 35 is mounted on the stator of the main motor 23, and the battery box 35 rotates together with the stator of the main motor 23.

[0034] In addition, the installation of the auxiliary rotor 29 makes it easier for the main rotor 25 or propeller 7 to rotate under the influence of the airflow from the auxiliary rotor 29, allowing the airflow to be fully utilized and further improving efficiency.

[0035] In this embodiment, the synchronization mechanism 3 includes two rotating gears 32 rotatably mounted at both ends of the turntable 22, with a large gear 31 meshing between the two rotating gears 32. The large gear 31 is fixedly connected to the support mounting part 21. The two main rotors 25 or propellers 7 are respectively connected to the two rotating gears 32 via rotating shafts 26. A universal coupling 4 is provided above each of the two rotating gears 32, and the rotating shaft 26 is connected to the rotating gear 32 via the universal coupling 4.

[0036] In this embodiment, the large gear 31 is fixedly connected to the support mounting part 21 and is in a stationary state. The main motor 23 drives the turntable 22 to rotate, thereby driving the two main rotors 25 or propellers 7 to revolve synchronously with the turntable 22. At this time, the rotating gear 32, being rotatably mounted on the turntable 22, rotates with the turntable 22. Simultaneously, the rotating gear 32 meshes with the large gear 31, achieving its own rotation, which ultimately drives the main rotors 25 or propellers 7 to rotate. It should be noted that in this embodiment, the main rotors 25 or propellers 7 achieve their rotation under the combined action of the rotating gear 32 and the airflow, because the shaft of the main rotors 25 or propellers 7 has a rear chamfer, that is, the rotor disk of the main rotors 25 or propellers 7 is tilted backward.

[0037] In addition, the present invention can adjust the superimposed rotational effect of revolution and rotation by adjusting the gear ratio of the large gear 31 and the rotating gear 32.

[0038] The invention also includes a bracket 24. The rotor of the main motor 23 is connected to the turntable 22 and the bracket 24 via a main shaft 5. The bracket 24 has mounting holes 27 at both ends, and bearings 28 are installed within the mounting holes 27. The shaft 26 passes through the bearings 28. The bracket 24 of this invention effectively ensures the angle of the shaft 26, that is, effectively ensures the tilt angle of the main rotor 25 or propeller 7.

[0039] Preferably, the turntable 22 and the bracket 24 are integrated into one unit. This design can effectively improve the compactness, rigidity, and coordination of the structure.

[0040] The mounting angle of the blades of the main rotor 25 is 2 to 10 degrees; the mounting angle of the blades of the auxiliary rotor 29 is 6 to 15 degrees.

[0041] The rear chamfer of the shaft of the main rotor 25 or propeller 7 is 6 to 20 degrees.

[0042] The preferred installation angle of the blades of the main rotor 25 is 5 degrees; the preferred installation angle of the blades of the auxiliary rotor 29 is 10 degrees.

[0043] It should be noted that the installation angle of the airfoil is the angle between the chord line of the airfoil and the plane of rotation of the rotor. The line connecting the leading and trailing edges of the airfoil is the chord line of the airfoil. If the plane of rotation of the rotor is horizontal, the installation angle is positive when the leading edge of the airfoil is higher than the trailing edge. If the plane of rotation of the turntable 22 is horizontal, the angle between the axis of rotation of the main rotor 25 or the propeller 7 and the vertical line is the rear chamfer of the axis of rotation of the main rotor 25 or the propeller 7. The rear chamfer is positive when the axis of rotation of the main rotor 25 or the propeller 7 is tilted backwards from the turntable 22.

[0044] Example 2:

[0045] This embodiment differs from Embodiment 1 in that the synchronization mechanism 3 includes two rotating synchronous wheels 34 rotatably mounted at both ends of the turntable 22. The two rotating synchronous wheels 34 are connected by a synchronous belt 33, and the two main rotors 25 are respectively connected to the two rotating synchronous wheels 34 via rotating shafts 26. That is, the two rotating synchronous wheels 34 maintain synchronization through the synchronous belt 33. This results in a fundamental difference between this embodiment and Embodiment 1: the rotating synchronous wheels 34 are not driven to rotate by external force. In this case, the rotational power of the two main rotors 25 mainly comes from the airflow driving the main rotors 25 as they revolve around the turntable 22, similar to a self-rotating rotor. The installation angle of the blades of the main rotors 25 is 2 to 5 degrees, preferably 3 degrees. The function of the rotating synchronous wheels 34 and the synchronous belt 33 is solely for synchronization.

[0046] The other structures are the same as in Example 1, and will not be described again.

[0047] Example 3:

[0048] The difference between this embodiment and Embodiment 1 is that:

[0049] The synchronization mechanism 3 includes two servo motors 6 symmetrically arranged at both ends of the turntable 22. The two main rotors 25 or propellers 7 are driven to rotate by the two servo motors 6 respectively. In this embodiment, the synchronization mechanism 3 directly consists of two servo motors 6, which directly provide driving force for the rotation of the main rotors 25 or propellers 7. The synchronization is mainly determined by the servo motors 6 themselves, that is, the two servo motors 6 can ensure synchronization.

[0050] It should also be noted that if the auxiliary rotor is not provided, the support mounting part 21 can be configured as a hollow structure, and the wires supplying power to the main motor 23 and the servo motor 6 pass through the hollow structure of the support mounting part 21 and are powered by the battery installed on the body 1.

[0051] The above description is only a preferred embodiment of the present invention. Therefore, all equivalent changes or modifications made to the structure, features and principles described in the claims of this patent application are included in the scope of this patent application.

Claims

1. A helicopter with an improved lift device, comprising a fuselage (1) and a lift device (2) disposed on the top of the fuselage (1), characterized in that: The lifting device (2) includes a support mounting part (21), a main motor (23), a turntable (22), and two main rotors (25) or propellers (7); the main motor (23) is mounted on the body (1) through the support mounting part (21), the two main rotors (25) or propellers (7) are mounted on the turntable (22), the turntable (22) is connected to the rotor of the main motor (23), and the two main rotors (25) or propellers (7) revolve synchronously with the turntable (22); A synchronization mechanism (3) is provided between the two main rotors (25) or propellers (7) to achieve synchronous rotation of the two main rotors (25) or propellers (7); the synchronization mechanism (3) adopts a gear structure, a synchronous wheel structure, or a servo motor structure. When the synchronization mechanism (3) adopts a gear structure, the synchronization mechanism (3) includes two rotating gears (32) rotatably disposed at both ends of the turntable (22), and a large gear (31) meshing with the two rotating gears (32) is provided between them. The large gear (31) is fixedly connected to the support mounting part (21); the two main rotors (25) or propellers (7) are respectively connected to the two rotating gears (32) through a rotating shaft (26). When the synchronization mechanism (3) adopts the form of a synchronization wheel structure, the synchronization mechanism (3) includes two rotating synchronization wheels (34) rotatably disposed at both ends of the turntable (22). The two rotating synchronization wheels (34) are connected by a synchronization belt (33), and the two main rotors (25) are respectively connected to the two rotating synchronization wheels (34) through a rotating shaft (26). When the synchronization mechanism (3) adopts a servo motor structure, the synchronization mechanism (3) includes two servo motors (6) symmetrically arranged at both ends of the turntable (22), and the two main rotors (25) or propellers (7) are driven to rotate by the two servo motors (6) respectively. The mounting angle of the blades of the main rotor (25) is 2 to 8 degrees; The rear chamfer of the shaft of the main rotor (25) or propeller (7) is 6 to 20 degrees; The revolution of the main rotor (25) or the propeller (7) and the rotation of the rotor form a superposition rotation. The airflow generated by the rotation in front and below the rotor merges with the incoming flow in front of the revolution, which inhibits the loss of kinetic energy of the downwash air and absorbs the energy of the incoming flow, forming a ground effect to enhance lift.

2. The improved helicopter with a lifting device according to claim 1, characterized in that: Universal couplings (4) are provided above both of the two rotating gears (32) or the rotating synchronous pulley (34), and the rotating shaft (26) is connected to the rotating gear (32) or the rotating synchronous pulley (34) through the universal couplings (4).

3. The improved helicopter with a lifting device according to claim 2, characterized in that: Includes a bracket (24), the rotor of the main motor (23) is connected to the turntable (22) and the bracket (24) through the main shaft (5), the bracket (24) has mounting holes (27) at both ends, the mounting holes (27) are provided with bearings (28), and the shaft (26) passes through the bearings (28); the turntable (22) and the bracket (24) are integrally set.

4. The improved helicopter with a lifting device according to claim 1, characterized in that: It also includes a secondary rotor (29), which is located below the two main rotors (25) or propellers (7) and is connected to the stator of the main motor (23).

5. The improved helicopter with a lifting device according to claim 4, characterized in that: The mounting angle of the blades of the secondary rotor (29) is 6 to 15 degrees.

6. The improved helicopter with a lifting device according to claim 4, characterized in that: The blades of the main rotor (25) have an installation angle of 5 degrees; the blades of the auxiliary rotor (29) have an installation angle of 10 degrees.

Images