CN117944869A - Semi-flexible three-blade hub - Google Patents
Semi-flexible three-blade hub Download PDFInfo
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- CN117944869A CN117944869A CN202410358662.XA CN202410358662A CN117944869A CN 117944869 A CN117944869 A CN 117944869A CN 202410358662 A CN202410358662 A CN 202410358662A CN 117944869 A CN117944869 A CN 117944869A
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- 239000000463 material Substances 0.000 claims abstract description 9
- 230000000712 assembly Effects 0.000 claims description 4
- 238000000429 assembly Methods 0.000 claims description 4
- 230000007423 decrease Effects 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 2
- 230000003139 buffering effect Effects 0.000 description 6
- 230000002159 abnormal effect Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 229920002379 silicone rubber Polymers 0.000 description 1
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Abstract
The application relates to a semi-flexible three-blade hub, which relates to the technical field of civil aircraft and comprises a base, a blade clamp and a buffer assembly, wherein the blade clamp is arranged on the base, the buffer assembly comprises a center piece and a pressure bearing piece, the center piece is arranged between the base and the blade clamp and is positioned at the center of the base, and the center piece is used for connecting a main shaft and the blade clamp; the pressure-bearing pieces are arranged in a plurality, the pressure-bearing pieces are distributed around the periphery of the center piece, two ends of the pressure-bearing pieces are respectively connected with the paddle clamp and the base and used for absorbing shimmy from the paddle clamp, and the pressure-bearing pieces are made of flexible materials. The application has the effect of improving the aeroelastic stability of the rotor wing of the rotorcraft.
Description
Technical Field
The application relates to the technical field of civil aircrafts, in particular to a semi-flexible three-blade hub.
Background
A rotor system of a conventional rotorcraft consists of a plurality of blades and a hub. The hub refers to a part fixed in the center of a ship or aircraft propeller and is mainly responsible for connecting, supporting and protecting the propeller blades. The hub connects the blades with the propeller main shaft, so that the propeller main shaft drives the blades to rotate, and lift force is transmitted to the rotor shaft by the blades.
The rotor form of a rotorcraft is determined by the hub form. Hub forms may include fully hinged, semi-hinged, hingeless, bearingless, and the like. At present, a bearingless hub is generally adopted to realize the flapping, shimmy and pitch-changing movements of a rotor wing.
In the flight process of the gyroplane, the vibration of the bearingless rotor has a great influence on the flight performance of the gyroplane. In particular, in the case of low flying speeds or hovering, the aerodynamic damping is very small, and the rotor shimmy direction can become an important influencing factor for rotor aeroelastic stability. The bearingless rotor wing is provided with a structural damping device for reducing the influence of blade swing on the whole flight performance of the rotorcraft.
In the prior art, laminated shimmy dampers are commonly used on rotorcraft. The laminated shimmy damper mainly utilizes the shearing deformation of high-damping silicon rubber materials to generate elasticity and damping rigidity and absorbs shimmy energy of a rotor wing so as to meet the requirement of preventing the gyroplane from generating resonance on the ground and in the air as far as possible.
However, stacked shimmy dampers are typically provided at the connection of the blade to the center assembly. Because the blade is directly connected at the periphery of the central component, the swing, pitch and shimmy movements of the conventional bearingless rotor are borne by the root of the connecting part, and the connecting part is extremely easy to crack or break under the action of torque.
Therefore, not only are the hub center assembly and the blade life cycle affected, but also the flight safety of the rotorcraft is threatened, and the maintenance cost of the rotorcraft is increased.
Disclosure of Invention
In order to improve the aeroelastic stability of a rotor of a rotorcraft, the application provides a semi-flexible three-blade hub.
The application provides a semi-flexible three-blade hub, which adopts the following technical scheme:
the semi-flexible three-blade hub comprises a base, a blade clamp and a buffer assembly, wherein the blade clamp is installed on the base, the buffer assembly comprises a center piece and a pressure bearing piece, the center piece is arranged between the base and the blade clamp and is positioned at the center of the base, and the center piece is used for connecting a main shaft and the blade clamp; the pressure-bearing pieces are arranged in a plurality, the pressure-bearing pieces are distributed around the periphery of the center piece, two ends of the pressure-bearing pieces are respectively connected with the paddle clamp and the base and used for absorbing shimmy from the paddle clamp, and the pressure-bearing pieces are made of flexible materials.
By adopting the technical scheme, the plurality of pressure bearing pieces are distributed around the center piece, and the shimmy from the paddle clamp can be effectively absorbed by dispersing and buffering the impact force from the paddle clamp, so that the damage of vibration to the paddle hub and the main shaft can be reduced, the service life of the paddle hub can be prolonged, and the maintenance and replacement cost can be reduced;
in addition, connect main shaft and oar through the center piece and press from both sides, cooperate with the pressure-bearing piece simultaneously to increased the stability of paddle in rotatory in-process, and then improved the rotor aeroelastic stability of gyroplane.
Optionally, the pressure-bearing piece is in a U shape, and the distance between two ends of the pressure-bearing piece gradually decreases along the direction approaching to the center piece.
By adopting the technical scheme, the pressure-bearing piece adopts the U-shaped structure, and can provide larger deformation space when receiving the shimmy force, so that the shimmy buffering capacity is enhanced, and meanwhile, the buffering effect is beneficial to reducing the impact on the hub and the main shaft, so that the overall stability and reliability are improved;
In addition, the design of the U-shaped pressure-bearing piece can more uniformly distribute the shimmy force from the paddle clamp, when the paddle clamp is subjected to shimmy, the two ends of the U-shaped pressure-bearing piece are simultaneously stressed and deform, the deformation can disperse and transfer the shimmy force, and the stress is prevented from being concentrated in a certain local area, so that the risks of material fatigue and fracture are reduced;
In addition, when the oar presss from both sides receives the shimmy, the both ends of U-shaped pressure receiving piece can atress simultaneously and take place deformation, and this kind of deformation can disperse and shift the shimmy power, avoids stress concentration in certain local region to material fatigue and cracked risk have been reduced.
Optionally, one end of the pressure bearing piece is connected with the paddle clamp through a bolt, and the other end of the pressure bearing piece is fixedly connected with the base.
Through adopting above-mentioned technical scheme, through bolted connection oar clamp and pressure-bearing piece for the pressure-bearing piece can take place not hard up or fastening to a certain extent, thereby easily adjust the connection compactness between pressure-bearing piece and the oar clamp, reach different buffering effects, this kind of adjustability makes the oar hub can adapt to different operating conditions and load variation, and then has further improved the cushioning properties;
In addition, the pressure bearing piece and the base are fixedly connected, so that the shimmy force from the paddle clamp can be borne, and the shimmy force from the paddle clamp is dispersed to the base, so that local stress concentration and structural deformation are avoided.
Optionally, the center piece adopts a universal bearing.
By adopting the technical scheme, the universal bearing can absorb and disperse stress caused by mechanical deformation, so that stress concentration in a mechanical system can be effectively reduced, and the stability and reliability of the system are improved.
Optionally, the device further comprises a plurality of groups of early warning components, wherein the plurality of groups of early warning components are in one-to-one correspondence with the plurality of pressure-bearing pieces, the early warning components comprise a fixed plate, an elastic piece and a ranging sensor, and the fixed plate is fixedly connected to the base and is positioned on one side, close to the central piece, of the pressure-bearing piece; the elastic piece is hollow and fixedly connected to one side of the fixing plate, which is close to the pressure bearing piece, and is abutted with the pressure bearing piece; the distance measuring sensor is fixedly connected in the elastic piece and is positioned on one side, close to the fixed plate, of the elastic piece, and the distance measuring sensor is used for outputting a distance signal between the fixed plate and the pressure-bearing piece to a main control display platform of the rotorcraft.
By adopting the technical scheme, when the pressure-bearing piece is deformed, the distance between the two ends of the pressure-bearing piece is reduced, the distance between the convex end of the U-shaped pressure-bearing piece and the central piece is reduced, the elastic piece is extruded by the convex end of the U-shaped pressure-bearing piece, and the elastic piece is deformed;
because the pressure-bearing piece is made of flexible materials, when the materials and the structure are subjected to repeated load changes, the protruding end of the pressure-bearing piece is easy to fatigue fracture under the repeated load changes, and when the protruding end of the pressure-bearing piece is cracked, the elastic piece is pressed, and the side surface of the elastic piece, which is tightly abutted with the protruding end of the pressure-bearing piece, is embedded into the crack of the pressure-bearing piece;
The distance measuring sensor measures the distance between the two sides of the elastic piece and outputs a distance signal to the main control display platform of the rotorcraft, when the pressure-bearing piece is cracked, the distance between the two sides of the elastic piece changes suddenly, and abnormal data signals on the main control display platform are used, so that operators can replace damaged parts easily in time, and the life safety of the operators can be guaranteed easily.
Optionally, the oar presss from both sides including linking firmly board one and linking firmly board two, link firmly board one with link firmly board two parallel arrangement, the one end of center piece wears to establish in proper order link firmly board one with link firmly on the board two, and through the bolt with link firmly board one with link firmly board two fixed connection.
Through adopting above-mentioned technical scheme, the parallel structure of linking firmly board one and linking firmly board two can increase the overall rigidity of oar clamp for the oar hub can resist deformation better when receiving the shimmy force, thereby helps keeping the geometry and the performance stability of oar hub, and then has improved entire system's reliability.
Optionally, the device further comprises three groups of paddles, wherein the three groups of paddles are uniformly distributed around the axis of the central piece in a circle; the paddle comprises a paddle handle and a blade, wherein the paddle handle is fixedly connected between the first fixing plate and the second fixing plate through bolts, and the blade is fixedly connected to one end, far away from the paddle clamp, of the paddle handle.
Through adopting above-mentioned technical scheme, through the fixed connection between bolt and the board of linking firmly one and the board of linking firmly two to can ensure the steadiness and the reliability of oar handle, and then easily improve the structural strength of whole oar hub.
Optionally, a yielding groove is formed in one side, close to the base, of the paddle handle.
Through adopting above-mentioned technical scheme, through setting up the groove of stepping down, can ensure that the oar handle can not take place to interfere or conflict between base or other adjacent parts when rotatory or during operation to help keeping the neatly and smooth and easy of oar hub inner space, and then improved overall structure's reliability.
Optionally, the first fixing plate and the second fixing plate are both provided with through holes.
Through adopting above-mentioned technical scheme, through seting up the through-hole to can alleviate the weight of linking firmly board one and linking firmly board two to a certain extent.
In summary, the present application includes at least one of the following beneficial technical effects:
through setting up central part and pressure-bearing piece, can improve the rotor aeroelastic stability of gyroplane to can reduce the harm of vibration to oar hub and main shaft, and then can improve the life of oar hub;
The first fixing plate and the second fixing plate are arranged, so that the geometrical shape and the performance stability of the hub can be maintained, and the reliability of the whole system is improved;
through the through holes, the weight of the first fixing plate and the second fixing plate can be reduced to a certain extent.
Drawings
FIG. 1 is a schematic diagram of an embodiment of the present application;
FIG. 2 is an enlarged view at A in FIG. 1;
Fig. 3 is an enlarged view at B in fig. 2;
FIG. 4 is a cross-sectional view of an early warning assembly in an embodiment of the application.
Reference numerals illustrate:
1. a base; 2. a paddle clamp; 21. the first fixing plate is fixedly connected; 22. a second fixing plate; 23. a relief groove; 24. a through hole; 3. a paddle; 31. a paddle handle; 32. a blade; 4. a buffer assembly; 41. a center piece; 42. a pressure-bearing member; 5. an early warning component; 51. a fixing plate; 52. an elastic member; 53. a distance measuring sensor.
Detailed Description
The application is described in further detail below with reference to fig. 1-4.
The embodiment of the application discloses a semi-flexible three-blade hub. Referring to fig. 1,2 and 3, a semi-flexible three-blade hub comprises a base 1, a blade clamp 2, a blade 3, a buffer assembly 4 and an early warning assembly 5, wherein the blade clamp 2 is arranged on the base 1, the blade 3 is arranged on the blade clamp 2, and the blade clamp 2 is used for bearing the blade 3; the buffer component 4 is arranged on the base 1 and is used for absorbing the shimmy from the paddle clamp 2; the early warning assembly 5 is provided on the base 1 and is used for detecting the fatigue strength of the buffer assembly 4.
During the use, buffer assembly 4 is pressed from both sides 2 with the oar and is installed on base 1, and oar presss from both sides 2 and fixes paddle 3, can absorb the shimmy from oar clamp 2 effectively, simultaneously, early warning assembly 5 detects buffer assembly 4's fatigue strength to the stability of paddle 3 in rotatory in-process has been increased, and then the rotor aeroelastic stability of gyroplane is improved.
Referring to fig. 2 and 3, the base 1 has a circular plate shape. The paddle clamp 2 comprises a first fixing plate 21 and a second fixing plate 22, the first fixing plate 21 and the second fixing plate 22 are triangular, three side edges of the first fixing plate 21 are sunken towards the axis direction close to the first fixing plate 21 along the center point of the side edges, and the second fixing plate 22 is arranged the same as the first fixing plate 21.
Referring to fig. 2 and 3, the first fixing plate 21 and the second fixing plate 22 are disposed in parallel and are both disposed on the base 1, and the second fixing plate 22 is located at a side of the first fixing plate 21 away from the base 1.
Referring to fig. 2 and 3, the paddles 3 are provided with three groups, and the three groups of paddles 3 are uniformly arranged around the axis of the first fixing plate 21. The paddle 3 comprises a paddle handle 31 and a blade 32, wherein the paddle handle 31 is fixedly connected between the first fixing plate 21 and the second fixing plate 22 through bolts and is positioned at three top ends of the first fixing plate 21.
Referring to fig. 2 and 3, one end of the blade 32 is fixedly connected to the end of the paddle handle 31 remote from the first securing plate 21. The side of the paddle handle 31 near the base 1 is provided with a yielding groove 23. Through holes 24 are formed in the three top ends of the first fixing plate 21, and the through holes 24 are located on one side, close to the axis of the first fixing plate 21, of the joint of the paddle handles 31. The second fixing plate 22 is arranged the same as the first fixing plate 21.
Referring to fig. 2 and 3, the buffer assembly 4 includes a center member 41 and a bearing member 42, the center member 41 is located between the base 1 and the first fastening plate 21 and is located at the center of the base 1, and both ends of the center member 41 are respectively penetrated on the base 1 and the first fastening plate 21.
Referring to fig. 2 and 3, one end of the center member 41 near the base 1 is for coaxial fixed connection with the spindle, and the other end is for connecting the first fixing plate 21 and the second fixing plate 22. The center member 41 is a universal bearing, and in this embodiment, the universal bearing is a self-lubricating knuckle bearing.
Referring to fig. 2 and 3, the pressure bearing members 42 are provided in three, and the three pressure bearing members 42 are uniformly arranged around the circumference of the center member 41 and are in one-to-one correspondence with the three paddle handles 31. The pressure-receiving member 42 has a U-shape, and the distance between both ends of the pressure-receiving member 42 gradually decreases in a direction approaching the center member 41.
Referring to fig. 2 and 3, one end of the pressure receiving piece 42 is bolted to the top end of the first fastening plate 21, and the other end is fixedly connected to the base 1. The pressure piece 42 is manufactured from a flexible material and serves to absorb the shimmy from the blade clamp 2.
When the rotary wing aircraft is used, the central piece 41 is connected with the main shaft and the oar clamp 2, the three pressure-bearing pieces 42 are uniformly distributed around the central piece 41 and are matched with the pressure-bearing pieces 42, then the oar handle 31 is arranged between the first fixing plate 21 and the second fixing plate 22, and through the bolt connection, the shimmy from the oar clamp 2 can be effectively absorbed through dispersing and buffering the impact force from the oar clamp 2, the damage of vibration to the oar hub and the main shaft is reduced, the stability of the blade 3 in the rotating process is improved, and the aeroelastic stability of the rotary wing aircraft is improved.
Referring to fig. 2,3 and 4, the pre-warning assemblies 5 are provided with three groups, and the three groups of pre-warning assemblies 5 are in one-to-one correspondence with the three pressure-bearing members 42. The early warning assembly 5 comprises a fixing plate 51, an elastic piece 52 and a distance measuring sensor 53, wherein the fixing plate 51 is rectangular plate-shaped and is vertically arranged, a distance is reserved between the top end of the fixing plate 51 and the second fixedly connected plate 22, the bottom end of the fixing plate 51 is fixedly connected to the base 1 and is positioned on one side, close to the center piece 41, of the pressure-bearing piece 42, and a distance is reserved between the fixing plate 51 and the center piece 41.
Referring to fig. 2 and 4, the elastic member 52 is rectangular and hollow, air flows in the elastic member 52, the elastic member 52 is fixedly connected to one side of the fixing plate 51, which is close to the pressure-bearing member 42, and the elastic member 52 abuts against the pressure-bearing member 42. The distance measuring sensor 53 is fixedly connected in the elastic member 52 and is located at one side of the elastic member 52 close to the fixed plate 51, and the distance measuring sensor 53 is used for outputting a distance signal between the fixed plate 51 and the pressure-bearing member 42 to a main control display platform of the rotorcraft.
When the rotary wing aircraft is used, when the pressure-bearing piece 42 deforms, the protruding end of the U-shaped pressure-bearing piece 42 extrudes the elastic piece 52, the distance between the two side surfaces of the elastic piece 52 changes, the distance measuring sensor 53 measures the distance between the two side surfaces of the elastic piece 52 and outputs a distance signal to the main control display platform of the rotary wing aircraft, when the pressure-bearing piece 42 is cracked, the distance between the two side surfaces of the elastic piece 52 changes suddenly, abnormal data signals appear on the main control display platform, so that operators can easily collect abnormal data, damaged parts can be easily replaced in time by the operators, and life safety of the operators can be easily guaranteed.
The implementation principle of the semi-flexible three-blade hub provided by the embodiment of the application is as follows: the center piece 41 is connected with the main shaft and the paddle clamp 2, three pressure-bearing pieces 42 are uniformly distributed around the center piece 41 and are matched with the pressure-bearing pieces 42, then the paddle handle 31 is arranged between the first fixing plate 21 and the second fixing plate 22, and through bolt connection, the shimmy from the paddle clamp 2 can be effectively absorbed by dispersing and buffering the impact force from the paddle clamp 2;
Meanwhile, when the pressure-bearing member 42 is cracked, the distance measuring sensor 53 measures the distance between the two side surfaces of the elastic member 52 and outputs an abnormal data signal to the main control display platform of the rotorcraft, so that an operator can replace damaged parts easily in time, damage of vibration to the hub and the main shaft can be reduced, and the service life of the hub can be prolonged.
The above embodiments are not intended to limit the scope of the present application, so: all equivalent changes in structure, shape and principle of the application should be covered in the scope of protection of the application.
Claims (9)
1. A semi-flexible three-blade hub, characterized by: the device comprises a base (1), a paddle clamp (2) and a buffer assembly (4), wherein the paddle clamp (2) is installed on the base (1), the buffer assembly (4) comprises a central piece (41) and a pressure-bearing piece (42), the central piece (41) is arranged between the base (1) and the paddle clamp (2) and is positioned at the center of the base (1), and the central piece (41) is used for connecting a main shaft and the paddle clamp (2); the pressure-bearing pieces (42) are arranged in a plurality, the pressure-bearing pieces (42) are distributed around the center piece (41) in a circle, two ends of the pressure-bearing pieces (42) are respectively connected with the paddle clamp (2) and the base (1) and used for absorbing shimmy from the paddle clamp (2), and the pressure-bearing pieces (42) are made of flexible materials.
2.A semi-flexible three-blade hub according to claim 1, wherein: the pressure-bearing member (42) is U-shaped, and the distance between the two ends of the pressure-bearing member (42) gradually decreases along the direction approaching the center member (41).
3. A semi-flexible three-blade hub according to claim 1, wherein: one end of the pressure-bearing piece (42) is connected with the paddle clamp (2) through bolts, and the other end of the pressure-bearing piece is fixedly connected with the base (1).
4. A semi-flexible three-blade hub according to claim 1, wherein: the center piece (41) adopts a universal bearing.
5. A semi-flexible three-blade hub according to claim 1, wherein: the intelligent automatic detection device is characterized by further comprising a plurality of groups of early warning assemblies (5), wherein the groups of early warning assemblies (5) are in one-to-one correspondence with the plurality of pressure-bearing pieces (42), each early warning assembly (5) comprises a fixed plate (51), an elastic piece (52) and a distance measuring sensor (53), and the fixed plates (51) are fixedly connected to the base (1) and are positioned on one side, close to the center piece (41), of the pressure-bearing piece (42); the elastic piece (52) is hollow and fixedly connected to one side, close to the pressure-bearing piece (42), of the fixing plate (51), and the elastic piece (52) is abutted with the pressure-bearing piece (42); the distance measuring sensor (53) is fixedly connected in the elastic piece (52) and is positioned on one side, close to the fixed plate (51), of the elastic piece (52), and the distance measuring sensor (53) is used for outputting a distance signal between the fixed plate (51) and the pressure-bearing piece (42) to a main control display platform of the rotorcraft.
6. A semi-flexible three-blade hub according to claim 1, wherein: the paddle clamp (2) comprises a first fixed connecting plate (21) and a second fixed connecting plate (22), the first fixed connecting plate (21) and the second fixed connecting plate (22) are arranged in parallel, one end of the center piece (41) sequentially penetrates through the first fixed connecting plate (21) and the second fixed connecting plate (22), and the first fixed connecting plate (21) and the second fixed connecting plate (22) are fixedly connected through bolts.
7. A semi-flexible three-blade hub as defined in claim 6, wherein: the utility model also comprises paddles (3), wherein the paddles (3) are provided with three groups, the three groups of paddles (3) are uniformly distributed around the axis of the central piece (41) in a circle; the paddle (3) comprises a paddle handle (31) and a blade (32), the paddle handle (31) is fixedly connected between the first fixing plate (21) and the second fixing plate (22) through bolts, and the blade (32) is fixedly connected to one end, far away from the paddle clamp (2), of the paddle handle (31).
8. A semi-flexible three-blade hub as defined in claim 7, wherein: and a yielding groove (23) is formed in one side, close to the base (1), of the paddle handle (31).
9. A semi-flexible three-blade hub as defined in claim 7, wherein: and through holes (24) are formed in the first fixing plate (21) and the second fixing plate (22).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410358662.XA CN117944869A (en) | 2024-03-27 | 2024-03-27 | Semi-flexible three-blade hub |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410358662.XA CN117944869A (en) | 2024-03-27 | 2024-03-27 | Semi-flexible three-blade hub |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117944869A true CN117944869A (en) | 2024-04-30 |
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ID=90793041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410358662.XA Pending CN117944869A (en) | 2024-03-27 | 2024-03-27 | Semi-flexible three-blade hub |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117944869A (en) |
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2024
- 2024-03-27 CN CN202410358662.XA patent/CN117944869A/en active Pending
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