CN216660307U

CN216660307U - Rotor structure and aircraft

Info

Publication number: CN216660307U
Application number: CN202220241101.8U
Authority: CN
Inventors: 王谭; 李卫; 徐厚超; 李穆生; 刘波
Original assignee: Guangdong Huitian Aerospace Technology Co Ltd
Current assignee: Guangdong Huitian Aerospace Technology Co Ltd
Priority date: 2022-01-28
Filing date: 2022-01-28
Publication date: 2022-06-03
Anticipated expiration: 2032-01-28

Abstract

The application relates to a rotor structure and an aircraft. This rotor structure includes: the flapping hinge comprises a main shaft, a flapping hinge body fixedly arranged relative to the main shaft, and a hub connecting piece rotationally connected with the flapping hinge body, wherein the hub connecting piece is used for connecting blades of an aircraft, and the rotation axis of the hub connecting piece is vertical to the axial direction of the main shaft; wherein, the main shaft in the week with wave the hinge body and pass through the spacing cooperation of first limit structure, pass through the spacing cooperation of second limit structure with wave the hinge body in the axial. The utility model provides a scheme, the main shaft through first limit structure and second limit structure with wave hinge body relatively fixed, the main shaft is connected with the propeller hub connecting piece through waving the hinge body, so, through optimizing the connected mode of main shaft and propeller hub connecting piece, need not to set up on the main shaft and be used for being connected fixed through-hole with the propeller hub connecting piece, can remain the integrality of main shaft, avoid stress concentration, improve the structural strength of main shaft, promote the life of main shaft.

Description

Rotor structure and aircraft

Technical Field

The application relates to the technical field of aircrafts, in particular to a rotor wing structure and an aircraft.

Background

Helicopter rotors with two blades usually adopt seesaw type hub connectors, the seesaw type hub connectors are connected with a main shaft through a bolt, and the hub can rotate around the bolt.

In the correlation technique, the main shaft of the helicopter rotor wing adopting the seesaw type propeller hub connecting piece usually destroys the structural integrity of the main shaft to a certain extent due to the fact that the through hole for the bolt to penetrate is formed, stress concentration is easily caused at the opening of the main shaft, fatigue damage is aggravated, and the service life of the main shaft is shortened.

SUMMERY OF THE UTILITY MODEL

For solving or partly solve the problem that exists among the correlation technique, this application provides a rotor structure and aircraft, this rotor structure can remain the integrality of main shaft, avoids stress concentration, promotes the life of main shaft.

The first aspect of the present application provides a rotor structure, including a main shaft, a flapping hinge body fixedly arranged relative to the main shaft, and a hub connector rotatably connected to the flapping hinge body, wherein the hub connector is used for connecting blades of an aircraft, and a rotation axis of the hub connector is perpendicular to an axial direction of the main shaft;

the main shaft is in the circumferential direction with wave the hinge body and pass through the spacing cooperation of first limit structure, pass through second limit structure in the axial with wave the spacing cooperation of hinge body.

In some embodiments, the swing hinge body is sleeved on the main shaft, the first limiting structure is a spline structure, the spline structure comprises an external spline arranged on the main shaft and an internal spline arranged on the swing hinge body, and the external spline is in limiting fit with the internal spline;

the second limiting structure comprises a main shaft fixing piece, the main shaft fixing piece is fixed at the end part of the main shaft through a connecting piece and used for limiting the flapping hinge body along the axial direction of the main shaft.

In some embodiments, the flapwise hinge further comprises a buffering and limiting structure arranged between the flapwise hinge body and the hub connecting piece and used for buffering the hub connecting piece when the hub connecting piece rotates.

In some embodiments, the buffering and limiting structure includes a buffering and limiting member disposed on one of the flapping hinge body and the hub connecting member, and a buffering and matching portion disposed on the other of the flapping hinge body and the hub connecting member and configured to be in spacing-matching with the buffering and limiting member.

In some embodiments, the buffering matching part comprises a limiting block arranged on the hub connecting piece, and the limiting block is provided with a limiting hole;

the buffering locating part is located wave the hinge body, the buffering locating part wears to establish spacing hole, the buffering locating part with activity space has between the pore wall in spacing hole the stopper follows when the propeller hub connecting piece rotates, the buffering locating part with the pore wall in spacing hole cushions through the contact cooperation.

In some embodiments, the hub connector is provided with a mounting hole, a step structure is arranged in the mounting hole, and the limiting block is embedded in the mounting hole and connected with the step structure.

In some embodiments, the flapping hinge body and the hub connecting piece are rotatably connected through a shaft hole structure, the shaft hole structure includes a central shaft disposed on one of the flapping hinge body and the hub connecting piece, and a connecting hole disposed on the other of the flapping hinge body and the hub connecting piece, the central shaft is perpendicular to the main shaft, and the central shaft and the connecting hole are rotatably connected through a rotating piece.

In some embodiments, the center shaft is disposed on the flapping hinge body, the connection hole is disposed on the hub connection member, and the rotation member includes a bearing, an inner ring of the bearing is in interference fit with the center shaft, and an outer ring of the bearing is in interference fit with the connection hole.

In some embodiments, the central shaft and the buffer stoppers are disposed on the flapping hinge body and are spaced apart from each other in the axial direction of the main shaft.

A second aspect of the present application provides an aircraft comprising a rotor structure as described above.

The technical scheme provided by the application can comprise the following beneficial effects:

the rotor structure comprises a main shaft, a flapping hinge body fixedly arranged relative to the main shaft, and a hub connecting piece rotationally connected with the flapping hinge body, wherein the hub connecting piece is used for connecting blades of an aircraft, and the rotation axis of the hub connecting piece is perpendicular to the axial direction of the main shaft; wherein, the main shaft in the week with wave the hinge body and pass through the spacing cooperation of first limit structure, pass through the spacing cooperation of second limit structure with wave the hinge body in the axial. After setting up like this, the main shaft through first limit structure and second limit structure with wave the hinge body relatively fixed, the main shaft is connected with the propeller hub connecting piece through waving the hinge body, the main shaft can rotate jointly with waving the hinge body, and then drive and wave the propeller hub connecting piece that the hinge body is connected, and locate the paddle rotation on the propeller hub connecting piece, thus, through the connected mode of optimizing main shaft and propeller hub connecting piece, need not to set up on the main shaft and be used for being connected fixed through-hole with the propeller hub connecting piece, can remain the integrality of main shaft, avoid stress concentration, improve the structural strength of main shaft, the life of promotion main shaft.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the application.

Drawings

The foregoing and other objects, features and advantages of the application will be apparent from the following more particular descriptions of exemplary embodiments of the application, as illustrated in the accompanying drawings wherein like reference numbers generally represent like parts throughout the exemplary embodiments of the application.

Fig. 1 is a schematic view of the overall structure of a rotor structure according to an embodiment of the present application;

FIG. 2 is an exploded schematic view of the rotor structure shown in FIG. 1;

FIG. 3 is a cross-sectional structural schematic view of the rotor structure shown in FIG. 1;

FIG. 4 is a schematic cross-sectional view of a flapping hinge body of a rotor structure according to an embodiment of the present disclosure;

figure 5 is a schematic view of a rotor hub attachment for a rotor configuration according to an embodiment of the present disclosure;

figure 6 is a schematic cross-sectional view of a hub attachment of a rotor configuration according to an embodiment of the present application.

Reference numerals:

100. a main shaft; 200. waving the hinge body; 300. a hub connection; 310. a step structure; 301. mounting holes; 400. a first limit structure; 410. an external spline; 420. an internal spline; 500. a second limit structure; 510. a main shaft fixing member; 520. a connecting member; 610. buffering the limiting part; 621. a limiting block; 6211. a limiting hole; 710. a central shaft; 720. a rotating member; 701. and connecting the holes.

Detailed Description

Embodiments of the present application will be described in more detail below with reference to the accompanying drawings. While embodiments of the present application are illustrated in the accompanying drawings, it should be understood that the present application may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

It should be understood that although the terms "first," "second," "third," etc. may be used herein to describe various information, these information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present application. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

In the description of the present application, it is to be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be considered limiting of the present application.

Unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and encompass, for example, being fixedly connected, releasably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

To above-mentioned problem, this application embodiment provides a rotor structure and aircraft, and this rotor structure can remain the integrality of main shaft, avoids stress concentration, promotes the life of main shaft.

The technical solutions of the embodiments of the present application are described in detail below with reference to the accompanying drawings.

Referring to fig. 1 to 4 together, the present embodiment provides a rotor structure, including a main shaft 100, a flapwise hinge body 200 fixedly disposed with respect to the main shaft 100, and a hub connector 300 rotatably connected to the flapwise hinge body 200, wherein the hub connector 300 is used for connecting a blade of an aircraft, and a rotation axis of the hub connector 300 is perpendicular to an axial direction of the main shaft 100; wherein, main shaft 100 is in the peripheral with wave hinge body 200 through first limit structure 400 spacing cooperation, in the axial through second limit structure 500 with wave hinge body 200 spacing cooperation. After so setting up, main shaft 100 is through first limit structure 400 and second limit structure 500 and wave hinge body 200 relatively fixed, main shaft 100 is connected with hub connecting piece 300 through waving hinge body 200, main shaft 100 can rotate jointly with waving hinge body 200, and then drive and wave the hub connecting piece 300 that hinge body 200 is connected, and locate the paddle rotation on the hub connecting piece 300, thus, through optimizing the connected mode of main shaft 100 and hub connecting piece 300, need not to set up on main shaft 100 and be used for being connected fixed through-hole with hub connecting piece 300, can keep the integrality of main shaft 100, the traditional use of waving the hinge bolt has been avoided, the installation is convenient with the maintenance, avoid stress concentration, improve the structural strength of main shaft 100, promote the life of main shaft 100.

In some embodiments, the swing hinge body 200 is sleeved on the main shaft 100, the first limiting structure 400 is a spline structure, the spline structure includes an external spline 410 disposed on the main shaft 100 and an internal spline 420 disposed on the swing hinge body 200, and the external spline 410 is in limiting fit with the internal spline 420; the second limiting structure 500 includes a spindle fixing member 510, and the spindle fixing member 510 is fixed to an end of the spindle 100 by a connecting member 520, and is used for limiting the flapping hinge body 200 along an axial direction of the spindle 100. After setting up like this, first limit structure 400 can realize main shaft 100 and wave the circumferential direction location between the hinge body 200, and second limit structure 500 can realize main shaft 100 and wave the axial positioning between the hinge body 200, so, when main shaft 100 is rotatory, can transmit the moment of torsion to waving the hinge body 200 through the spline structure, realize and wave the joint rotation of hinge body 200.

In this embodiment, the spindle fixing member 510 may be fixed to the end of the spindle 100 in a threaded manner, for example, the end of the spindle 100 is provided with an external thread, the spindle fixing member 510 is provided with an internal thread, and the spindle fixing member 510 is threaded on the end of the spindle 100. The main shaft fixing member 510 is fixed to the swing hinge body 200 by a connecting member 520, and the connecting member 520 may be a fixing bolt, so as to axially position the swing hinge body 200 on the main shaft 100. Preferably, the number of the connecting members 520 is four, and the connecting members are respectively distributed at four corners of the spindle fixing member 510, so as to connect the four corners of the spindle fixing member 510 to the swing hinge body 200, respectively, thereby improving the connection firmness between the spindle fixing member 510 and the swing hinge body 200.

In the related art, when a helicopter flies forward, the relative air flow speed of a forward side blade in a rotor is higher than that of a backward side blade, the aerodynamic loads of the blades at different orientations of a blade disc plane are different, and the blades periodically flap. In order to prevent the blade from fluttering and contacting the ground during the shutdown, a limiting mechanism is usually required to limit the flapping angle range of the blade.

The limiting mechanism in the related art is generally provided with a coupler knuckle on a blade joint and is in direct contact with a limiting block on a main shaft, the structure is relatively complex, the processing and manufacturing cost is high, and the coupler knuckle and the limiting block are subjected to frequent rigid collision impact, so that stress concentration of the blade joint and the limiting block of the main shaft is easily caused, and fatigue failure is aggravated.

In some embodiments, the rotor structure further includes a damping structure disposed between flapwise hinge body 200 and hub connection 300 for damping rotation of hub connection 300. So, buffering limit structure rotates through restriction propeller hub connecting piece 300 to the angle scope of waving of restriction paddle, and then position when avoiding the paddle to wave is crossed lowly.

In this embodiment, the buffering and limiting structure includes a buffering and limiting member 610 disposed on one of the flapping hinge body 200 and the hub connector 300, and a buffering and matching portion disposed on the other of the flapping hinge body 200 and the hub connector 300 and configured to be in limiting matching with the buffering and limiting member 610. Thus, when hub connector 300 rotates to a predetermined position around the rotation axis, buffer position-limiting member 610 can be in contact fit with the buffer fitting portion to buffer, so as to reduce the impact force between hub connector 300 and flapping hinge body 200. In addition, the buffering stopper 610 may also be referred to as a stopper boss.

In this embodiment, the buffering matching portion includes a limiting block 621 disposed on the hub connector 300, and the limiting block 621 is provided with a limiting hole 6211; buffering locating part 610 is located and is waved hinge body 200, and spacing hole 6211 is worn to establish by buffering locating part 610, has the free space between the pore wall of buffering locating part 610 and spacing hole 6211, and when limiting block 621 rotated along with propeller hub connecting piece 300, buffering locating part 610 cushioned through the contact cooperation with spacing hole 6211's pore wall. When hub connector 300 rotates around the rotation axis, buffering limiting part 610 can move in limiting hole 6211, and when hub connector 300 rotates to a preset position, buffering limiting part 610 contacts and cooperates with the hole wall of limiting hole 6211 to buffer the impact of hub connector 300 on flapping hinge body 200. Therefore, compared with the related art, a coupler knuckle does not need to be arranged on the blade joint, so that stress concentration caused by frequent rigid collision impact of the coupler knuckle and the limiting block 621 is avoided, and the service life of the rotor wing structure is prolonged; and, buffering limit structure's structure is also simpler, and manufacturing cost is lower.

Referring to fig. 5 to 6, in the present embodiment, the hub connector 300 is provided with a mounting hole 301, a step structure 310 is disposed in the mounting hole 301, and the limiting block 621 is embedded in the mounting hole 301 and connected to the step structure 310. The limiting block 621 may be fixed to the step structure 310 through a plurality of connection fixing manners, for example, a clamping plate is disposed on the hub connector 300, after the limiting block 621 is embedded in the mounting hole 301, the clamping plate is fixed to the hole of the mounting hole 301 through a connector such as a bolt, and the limiting block 621 can be further installed in the mounting hole 301. It should be noted that the step structure 310 may be a ring-shaped protrusion protruding toward the hole center of the hole wall of the mounting hole 301.

In some embodiments, in order to avoid collision impact between the limiting block 621 and the buffering limiting block 610, the limiting block 621 is made of an elastic material (e.g., rubber or silicone) to perform a buffering protection function.

In some embodiments, flapping hinge body 200 is rotatably coupled to hub coupling 300 via a shaft-in-hole arrangement that includes a central shaft 710 disposed on one of flapping hinge body 200 and hub coupling 300, and a coupling hole 701 disposed on the other of flapping hinge body 200 and hub coupling 300, wherein central shaft 710 is perpendicular to main shaft 100, and central shaft 710 is rotatably coupled to coupling hole 701 via a rotating member 720. In this embodiment, the central axis 710 may also be referred to as a flapping stage.

In this embodiment, the central shaft 710 is disposed on the flapping hinge body 200, the connection hole 701 is disposed on the hub connection member 300, the rotation member 720 includes a bearing, an inner ring of the bearing is in interference fit with the central shaft 710, and an outer ring of the bearing is in interference fit with the connection hole 701. Preferably, the bearing may be a combination thrust needle bearing, which can bear radial load and axial load, so that hub connection 300 can maintain a certain pre-tightening connection with flapping hinge body 200, and can rotate around the axis of central shaft 710, thereby making the entire rotor structure more compact.

Referring to fig. 4, in some embodiments, the central shaft 710 and the buffer stoppers 610 are disposed on the flap hinge body 200 and are spaced apart from each other along the axial direction of the spindle 100. After the arrangement, the central shaft 710 and the buffering limiting part 610 are integrated on the flapping hinge body 200, which is beneficial to the simplification of the structure and the reduction of the weight of the rotor structure.

It should be noted that the rotor structure of the present application may be applied to a see-saw helicopter, where the rotor structure of the see-saw helicopter uses the main shaft 100 as a symmetry axis to form a symmetric structure, and the above-mentioned embodiment only describes a structure of one side of the main shaft 100, and the structure of the other side of the main shaft 100 is the same, and is not described herein again.

The above detailed description describes the rotor structure of the present application, which also provides an aircraft including the rotor structure described in the above embodiments.

The rotor structure comprises a main shaft 100, a flapwise hinge body 200 fixedly arranged relative to the main shaft 100, and a hub connector 300 rotatably connected with the flapwise hinge body 200, wherein the hub connector 300 is used for connecting blades of an aircraft, and the rotating axis of the hub connector 300 is vertical to the axial direction of the main shaft 100; wherein, main shaft 100 in the week with wave hinge body 200 through the spacing cooperation of first limit structure 400, in the axial through second limit structure 500 with wave hinge body 200 spacing cooperation. After setting up like this, main shaft 100 is through first limit structure 400 and second limit structure 500 and wave hinge body 200 relatively fixed, main shaft 100 is connected with hub connecting piece 300 through waving hinge body 200, main shaft 100 can rotate jointly with waving hinge body 200, and then drive and wave hub connecting piece 300 that hinge body 200 is connected, and locate the paddle rotation on hub connecting piece 300, so, through the connected mode of optimizing main shaft 100 and hub connecting piece 300, need not to set up on main shaft 100 and be used for being connected the fixed through-hole with hub connecting piece 300, can keep the integrality of main shaft 100, avoid stress concentration, improve the structural strength of main shaft 100, promote the life of main shaft 100.

The aspects of the present application have been described in detail hereinabove with reference to the accompanying drawings. In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and for parts that are not described in detail in a certain embodiment, reference may be made to related descriptions of other embodiments. Those skilled in the art should also appreciate that the acts and modules referred to in the specification are not necessarily required in the present application. In addition, it can be understood that the steps in the method of the embodiment of the present application may be sequentially adjusted, combined, and deleted according to actual needs, and the modules in the device of the embodiment of the present application may be combined, divided, and deleted according to actual needs.

Having described embodiments of the present application, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen in order to best explain the principles of the embodiments, the practical application, or improvements made to the technology in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A rotor structure, comprising:

the flapping hinge comprises a main shaft, a flapping hinge body fixedly arranged relative to the main shaft, and a hub connecting piece in rotating connection with the flapping hinge body, wherein the hub connecting piece is used for connecting blades of an aircraft, and the rotating axis of the hub connecting piece is perpendicular to the axial direction of the main shaft;

2. A rotor structure according to claim 1, wherein:

the flapping hinge body is sleeved on the main shaft, the first limiting structure is a spline structure, the spline structure comprises an external spline arranged on the main shaft and an internal spline arranged on the flapping hinge body, and the external spline is in limiting fit with the internal spline;

the second limiting structure comprises a main shaft fixing piece, the main shaft fixing piece is fixed to the end portion of the main shaft through a connecting piece and used for limiting the flapping hinge body along the axial direction of the main shaft.

3. A rotor structure according to claim 1, wherein:

the flapping hinge comprises a flapping hinge body, a hub connecting piece and a buffering limiting structure, wherein the flapping hinge body is arranged on the hub connecting piece, and the hub connecting piece is arranged on the hub connecting piece.

4. A rotor structure according to claim 3, wherein:

the buffering limiting structure comprises a buffering limiting part and a buffering matching part, wherein the buffering limiting part is arranged on the flapping hinge body and one of the hub connecting pieces, and the buffering matching part is arranged on the other of the flapping hinge body and the hub connecting piece and is used for being in limiting matching with the buffering limiting part.

5. A rotor structure according to claim 4, wherein:

the buffering matching part comprises a limiting block arranged on the propeller hub connecting piece, and the limiting block is provided with a limiting hole;

6. A rotor structure according to claim 5, wherein:

the propeller hub connecting piece is provided with a mounting hole, a step structure is arranged in the mounting hole, and the limiting block is embedded in the mounting hole and connected with the step structure.

7. A rotor structure according to claim 4, wherein:

wave the hinge body with the propeller hub connecting piece passes through the shaft hole structure and rotates and be connected, the shaft hole structure is including locating wave the hinge body with the center pin of one of propeller hub connecting piece and locate wave the hinge body with another connecting hole of propeller hub connecting piece, the center pin perpendicular to the main shaft, the center pin with the connecting hole rotates through rotating and is connected.

8. A rotor structure according to claim 7, wherein:

the center pin is located wave the hinge body, the connecting hole is located the propeller hub connecting piece, it includes the bearing to rotate the piece, the inner circle of bearing with center pin interference fit, the outer lane of bearing with connecting hole interference fit.

9. A rotor structure according to claim 8, wherein:

the central shaft and the buffering limiting part are arranged on the flapping hinge body and are arranged at intervals along the axial direction of the main shaft.

10. An aircraft comprising a rotor structure according to any of claims 1-9.