CN219635479U

CN219635479U - Helicopter drive coupling assembling and helicopter

Info

Publication number: CN219635479U
Application number: CN202321345485.9U
Authority: CN
Inventors: 王玉林; 黄少强
Original assignee: Suzhou Lanzhong Technology Co ltd
Current assignee: Suzhou Lanzhong Technology Co ltd
Priority date: 2023-05-30
Filing date: 2023-05-30
Publication date: 2023-09-05
Anticipated expiration: 2033-05-30

Abstract

The utility model relates to a helicopter driving connection assembly and a helicopter, comprising a mounting seat; a hub disposed on the mount; the elastic pieces are positioned between the mounting seat and the hub, the elastic pieces are multiple, and the elastic pieces are symmetrically arranged relative to the hub; the driving source is connected with the mounting seat and drives the mounting seat to rotate so as to drive the hub to rotate. The elastic piece and the hub form a teeterboard structure, and the teeterboard structure can generate transverse and longitudinal motion damping to achieve the optimal control effect, so that the coaxial double-rotor aircraft is more stable, has strong anti-interference capability, has variable damping, has the vibration reduction effect, and reduces structural fatigue of parts.

Description

Helicopter drive coupling assembling and helicopter

Technical Field

The utility model relates to the technical field of helicopters, in particular to a helicopter driving connection assembly and a helicopter.

Background

The hub of the coaxial double-rotor helicopter is a connection structure of a motor rotor and rotor blades, and has the main effects of two points, namely, the motor rotor rotates to drive the hub, and the hub drives the blades to rotate to generate lift force, so that ascending, descending and flying are realized. Secondly, the hub drives the blades to perform periodic pitch change to generate pitch control moment and roll control moment, so that front-back left-right flight is realized. The rotor fixed connection of traditional oar hub and motor, though in operation is simpler and more simple, but stability is poor, in case the control volume of flight control or flight hand give is too big, the organism appears unusual maneuver easily. Moreover, the traditional helicopter has poor anti-interference capability, and once the external interference exceeds the control range of flight control, the helicopter body is easy to shake. When the engine body is abnormally maneuvered and continuously dithered, the coaxial double-rotor aircraft is easy to generate the conditions of shooting and pitching, engine body disassembly, stall and the like, so that forced landing or crash is caused.

In addition, the helicopter always bears continuous periodic vibration during flight, the periodic pneumatic vibration load of the rotor wing is the main source of vibration, and parts or connecting fasteners can cause structural fatigue damage during vibration, so that the service life of the helicopter is reduced; and high vibration also reduces the reliability of the device and increases the risk of loose connection of the harness plug.

Disclosure of Invention

Therefore, the technical problems to be solved by the utility model are to overcome the technical defects of poor stability, poor anti-interference capability and part structure fatigue damage in the prior art when the traditional hub is used in flight.

In order to solve the technical problems, the utility model provides a helicopter driving connection assembly, which comprises:

a mounting base;

a hub disposed on the mount;

the elastic pieces are positioned between the mounting seat and the hub, the elastic pieces are multiple, and the elastic pieces are symmetrically arranged relative to the hub;

the driving source is connected with the mounting seat and drives the mounting seat to rotate so as to drive the hub to rotate.

Preferably, the elastic member is a spring.

Preferably, the device further comprises guide members, the guide members and the elastic members are arranged in one-to-one correspondence, the elastic members are sleeved on the guide members, and the guide members are arranged in parallel with the rotating shafts of the mounting seats.

Preferably, the number of the elastic members is 2 to 8.

Preferably, the mounting seat comprises a first mounting part, a second mounting part and a third mounting part;

the second installation portion and the third installation portion are symmetrically arranged relative to the first installation portion, the hub is arranged on the first installation portion, and the elastic piece is symmetrically arranged on the second installation portion and the third installation portion.

Preferably, the hub is provided with a through hole in a penetrating manner, and the first mounting part is arranged in the through hole in a penetrating manner.

Preferably, the hub is locked with the first mounting portion by a first fastener.

Preferably, the driving source includes a stator and a rotor, and the rotor is connected with the mounting seat to drive the mounting seat to rotate.

Preferably, the motor further comprises a motor base, and the motor base fixes the stator and the main shaft.

The utility model discloses a helicopter, which comprises the helicopter driving connection assembly.

Compared with the prior art, the technical scheme of the utility model has the following advantages:

1. according to the seesaw structure hub, the waving angle offset is zero, and the generated transverse and longitudinal motion damping ratio is larger, so that the coaxial double-rotor helicopter is more stable; and because the elastic piece is arranged between the paddle hub and the mounting seat, the elastic piece can modify the damping force according to the different environmental wind speeds so as to adapt to different environmental conditions.

2. The elastic piece is combined with the teeterboard structure hub, so that the coaxial double-rotor aircraft can be more stable, and the optimal control effect can be achieved; and, this kind of variable damping's teeterboard structure can absorb the periodic vibration that offsets the rotor. In coaxial double-rotor systems, the variable damping teeterboard has the characteristic of reducing the vibration amplitude in the system vibration, and can reduce the risks of structural fatigue and the like caused by vibration.

3. The utility model increases the static stability of the coaxial double-rotor aircraft, so that the aircraft can maintain stable flight during hovering and flying.

4. The utility model increases the dynamic stability of the coaxial double-rotor aircraft, so that the aircraft resists the interference of external environment in the flight process.

Drawings

In order that the utility model may be more readily understood, a more particular description of the utility model will be rendered by reference to specific embodiments thereof that are illustrated in the appended drawings.

FIG. 1 is a schematic view of the structure of a helicopter drive connection assembly of the present utility model;

FIG. 2 is a front view of the helicopter drive coupling assembly of the present utility model;

fig. 3 is a schematic structural view of the mounting base and the hub.

Description of the specification reference numerals: 10. a mounting base; 11. a first mounting portion; 12. a second mounting portion; 13. a third mounting portion; 20. a hub; 201. a first through hole; 30. a stator; 31. a rotor; 32. a main shaft; 33. a motor base; 40. a first fastener; 42. a second fastener; 43. a third fastener; 44. a fourth fastener; 50. deep groove ball bearings; 60. an elastic member; 61. a guide member; 70. a locking member.

Detailed Description

The present utility model will be further described with reference to the accompanying drawings and specific examples, which are not intended to be limiting, so that those skilled in the art will better understand the utility model and practice it.

Referring to fig. 1-3, the present utility model discloses a helicopter drive connection assembly comprising a mount 10, a hub 20, an elastic member 60, and a drive source.

The mount 10 is of a symmetrical construction, so that stability is just good. The material of the mounting seat 10 can be CNC machined by aluminum alloy, so that sufficient strength and accuracy are ensured.

The hub 20 is disposed on the mount 10, and in particular, the hub 20 may be disposed symmetrically with respect to a central axis of the mount 10. Hub 20 is a connecting structure of motor rotor 31 and rotor blade, and the material is CNC processing is carried out to the aluminum alloy of selecting, guarantees sufficient intensity and precision.

The elastic member 60 is located between the mounting base 10 and the hub 20, and the elastic member 60 has a plurality of elastic members 60 symmetrically disposed with respect to the hub 20.

The driving source is connected with the mounting seat 10, and the driving source drives the mounting seat 10 to rotate so as to drive the hub 20 to rotate.

Static stability is the initial reaction of the helicopter after being disturbed, and the whole movement process of the helicopter after being disturbed is a dynamic stability problem. The dynamic stability is used for researching the dynamic state of the helicopter after being disturbed, and determining whether and how the movement of the helicopter after being disturbed finally tends to the original balance state is an unsteady problem.

The dynamic stability of the coaxial double rotor is directly related to the damping of the coaxial double rotor, and the moment of retarding rotation of the helicopter after disturbed rotation becomes damping.

The working principle of the utility model is as follows: the teeter-totter hub 20 of the present utility model has zero flapping angle offset and produces greater transverse to longitudinal motion damping ratio, resulting in a more stable coaxial dual rotor helicopter. And because the elastic piece 60 is arranged between the hub 20 and the mounting seat 10, the elastic piece 60 can modify the damping force according to the different environmental wind speeds so as to adapt to different environmental conditions. The elastic piece 60 and the hub 20 form a teeter-totter structure, and the teeter-totter structure can generate transverse and longitudinal motion damping to achieve the optimal control effect, so that the coaxial double-rotor aircraft is more stable; and, this kind of variable damping's teeterboard structure can absorb the periodic vibration that offsets the rotor. In coaxial double-rotor systems, the variable damping teeterboard has the characteristic of reducing the vibration amplitude in the system vibration, and can reduce the risks of structural fatigue and the like caused by vibration.

In one embodiment, the elastic member 60 is a spring. One end of the spring is connected to the hub 20 and the other end of the spring is connected to the mount 10, and by providing the spring, variable damping can be provided. Also, the springs are provided in plurality, and the springs are symmetrically arranged relative to the hub 20, and a teeter-totter structure is formed by the cooperation of the springs, so that the periodic vibration of the rotor wing is absorbed and counteracted, and the flight of the aircraft is more stable.

The utility model also comprises guide pieces 61, the guide pieces 61 and the elastic pieces 60 are arranged in one-to-one correspondence, the elastic pieces 60 are sleeved on the guide pieces 61, and the guide pieces 61 are arranged in parallel with the rotating shaft of the mounting seat 10. The guide member 61 can limit the elastic expansion and contraction direction of the elastic member 60, thus improving the overall structural stability. The guide 61 may be a cylindrical structure that is mounted on the mounting member. A further mounting hole is provided in the hub 20, in which a locking member 70 is provided, the locking member 70 being locked to the guide member 61 such that the resilient member 60 is located between the mounting seat 10 and the hub 20. And the locking member 70 may alternatively be a screw fastener. Specifically, the locking member 70 may be a female hex male end jack. The locking member 70 can adjust the length of the elastic member 60, increase and decrease the elasticity of the elastic member, and modify the damping force according to different environmental wind speeds to adapt to different environmental conditions.

In the present utility model, the number of elastic members 60 can be set by a skilled person according to the need. Specifically, the number of elastic members 60 may be 2 to 8. The positions of the elastic members 60 may be set according to the requirements, and in particular, the elastic members 60 on one side of the hub 20 may be set at equal intervals or may be set at unequal intervals.

The mount 10 includes a first mount 11, a second mount 12, and a third mount 13. The second mounting portion 12 and the third mounting portion 13 are symmetrically arranged with respect to the first mounting portion 11, the hub 20 is arranged on the first mounting portion 11, and the elastic member 60 is symmetrically arranged on the second mounting portion 12 and the third mounting portion 13. The second mounting portion 12 and the third mounting portion 13 may be disposed parallel to the hub 20, the second mounting portion 12 and the third mounting portion 13 may have a lower height than the first mounting portion 11, when the hub 20 is mounted on the first mounting portion 11, a gap exists between the hub 20 and the second mounting portion 12 and the third mounting portion 13, and the elastic member 60 is disposed between the gaps.

The hub 20 is provided with a first through hole 201, and the first mounting portion 11 is provided in the first through hole 201. Hub 20 is locked with first mount 11 by first fastener 40. Specifically, the hub 20 is fixed to the first mounting portion 11 by first fasteners 40 on both sides thereof. The first mounting portion 11 may be of cylindrical configuration. The first fastener 40 is a pin.

Further, the driving source includes a stator 30 and a rotor 31, and the rotor 31 is connected to the mount 10 to drive the mount 10 to rotate. Rotor 31 interacts with stator 30 to generate energy rotation, and rotor 31 rotates to drive rotor of hub 20 to generate lift.

The utility model further comprises a motor base 33, wherein the motor base 33 fixes the stator 30 and the main shaft 32. A fourth fastener 44 is disposed between the motor mount 33 and the spindle 32, and the fourth fastener 44 may be a male end fastener. A second through hole is vertically formed through the first mounting portion 11, the spindle 32 is disposed through the second through hole, and a deep groove ball bearing 50 may be disposed between the spindle 32 and the first mounting portion 11. By providing the deep groove ball bearing 50, the friction force between the first mounting portion 11 and the main shaft 32 can be reduced. Further, by providing the first fastener 40, the hub 20 and the deep groove ball bearing 50 may be acted upon.

The present utility model further includes a second fastener 42 and a third fastener 43, the second fastener 42 securing the mount 42 to the rotor 31, the third fastener 43 securing the motor mount 33 to the stator 30. The second fastener 42 and the third fastener 43 are both screw fasteners.

The utility model also discloses a helicopter, which comprises the helicopter driving connection assembly. The helicopter provided by the utility model has the advantages of stable structure, high anti-interference capability and capability of stably flying.

Compared with the prior art, the utility model has the following technical effects:

1. stability enhancement: the teeter-totter hub 20 of the present utility model has zero flapping angle offset and produces greater transverse to longitudinal motion damping ratio, resulting in a more stable coaxial dual rotor helicopter.

2. Anti-interference: the static stability and the dynamic stability of the coaxial double-rotor aircraft are improved, so that the aircraft can keep self-stability and resist external environment interference in the flight process.

3. Variable damper: the damping force can be adjusted according to different environmental conditions to adapt to different environments.

4. Damping: the periodic vibration of the rotor wing can be reduced or counteracted, the vibration amplitude is reduced, and the structural fatigue of parts is reduced.

It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations and modifications of the present utility model will be apparent to those of ordinary skill in the art in light of the foregoing description. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the utility model.

Claims

1. A helicopter drive connection assembly comprising:

a mounting base;

a hub disposed on the mount;

2. The helicopter drive connection assembly of claim 1 wherein said resilient member is a spring.

3. The helicopter driving connection assembly of claim 1, further comprising a guide member disposed in one-to-one correspondence with the elastic members, wherein the elastic members are sleeved on the guide member, and wherein the guide member is disposed in parallel with the rotational axis of the mounting base.

4. The helicopter drive connection assembly of claim 1 wherein said resilient member has 2-8.

5. The helicopter drive connection assembly of claim 1, wherein the mount includes a first mount, a second mount, and a third mount;

6. The helicopter driving connection assembly of claim 5, wherein a through hole is formed through the hub, and the first mounting portion is disposed through the through hole.

7. The helicopter drive connection assembly of claim 1 wherein the hub is locked with the first mount portion by a first fastener.

8. The helicopter drive connection assembly of claim 1 wherein the drive source includes a stator and a rotor coupled to the mount for rotation of the mount.

9. The helicopter drive connection assembly of claim 8 further comprising a motor mount securing the stator to the main shaft.

10. A helicopter comprising a helicopter drive connection assembly as claimed in any of claims 1 to 9.