CN114537655A

CN114537655A - Rotor wing mechanism

Info

Publication number: CN114537655A
Application number: CN202210108777.4A
Authority: CN
Inventors: 赵洪; 李建波
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2022-01-28
Filing date: 2022-01-28
Publication date: 2022-05-27
Anticipated expiration: 2042-01-28
Also published as: CN114537655B

Abstract

The invention discloses a rotor wing mechanism, which comprises a hub and blades, wherein the hub comprises a central support arm, two sleeves and a torsion-pull assembly; the central support arm comprises a first support arm extending axially, a second support arm arranged on the first support arm and penetrating through the first support arm radially, and shaft sleeves respectively arranged on the peripheral surfaces of two ends of the first support arm and distributed on two sides of the second support arm; two ends of the first supporting arm are respectively sleeved in a sleeve, and the outer wall of each shaft sleeve is matched with the inner wall of the sleeve; each sleeve is connected with the first support arm through a torsion pulling assembly; each sleeve is axially connected with a blade; the second support arm is used for connecting the rotor shaft. The rotor wing mechanism is compact in structure, and reduces the number and weight of components by replacing traditional metal materials, metal bearings, locking bolts and other complex components, and the lightweight requirement of the propeller hub is met.

Description

Rotor wing mechanism

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a rotor wing mechanism.

Background

The rotor hub of a helicopter is used for connecting and driving rotor blades and transmitting aerodynamic force and torque on the blades to a rotor shaft through the hub. Simultaneously, the rotor blade carries out the displacement control around rotor propeller hub displacement axle, realizes the regulation of rotor aerodynamic force and moment.

The rotor hub of the current light small unmanned helicopter mainly keeps a variable pitch hinge and removes flapping and shimmy hinges. As shown in fig. 1, rotor hub 100 includes a sleeve 101, a bolt 102, a center arm 107, a center shaft 106, a lock bolt 103, a flat thrust bearing 105, a deep groove ball bearing 104, etc.; the rotor blade 200 is connected with the sleeve 101 through a bolt 102, the sleeve 101 is sleeved on the central support arm 107 through a combination of a plane thrust bearing 105 and a deep groove ball bearing 104, and the sleeve 101 and the central shaft 106 are connected through a locking bolt 103, so that the axial positioning and the restraint of the sleeve 101 on the central support arm 107 are realized; wherein the sleeve 101 and the central support arm 107 are both metal structural members; such conventional metal hubs are complex and heavy, and unmanned helicopters are sensitive to size and weight, and are not suitable for use with conventional rotor hubs.

The rotor hub of the current light small-sized unmanned helicopter reserves a plurality of metal structural members and metal bearings, has large structural weight and small size, and is too complex and heavy for being used on the unmanned helicopter.

For this reason, a new technical solution is needed to solve the above technical problems.

Disclosure of Invention

The purpose of the invention is as follows: the utility model provides a rotor mechanism for solve the problem that traditional rotor hub device is complicated heavy and can't satisfy unmanned helicopter or small-size helicopter lightweight demand, realize the purpose that alleviates the weight of hub.

The technical scheme is as follows: the invention provides a rotor wing mechanism, which comprises a hub and blades, wherein the hub comprises two sleeves, a central support arm and a torsion-pull assembly; the central support arm comprises a first support arm extending axially, a second support arm arranged on the first support arm and penetrating through the first support arm radially, and shaft sleeves respectively arranged on the peripheral surfaces of two ends of the first support arm and distributed on two sides of the second support arm; two ends of the first supporting arm are respectively sleeved in a sleeve, and the outer wall of each shaft sleeve is matched with the inner wall of the sleeve; each sleeve is connected with the first support arm through a torsion pulling assembly; each sleeve is axially connected with a blade; the second support arm is used for connecting the rotor shaft; the shaft sleeve is used for replacing a traditional metal bearing, and the torsion-pull assembly is used for replacing a traditional locking bolt, so that the number and the weight of parts are reduced.

Furthermore, each torsion-pulling assembly comprises a torsion-pulling strip axially arranged in the first support arm, the first support arm is connected to one end of the torsion-pulling strip through a second pin shaft, and the other end of the torsion-pulling strip extends out of the first support arm and is connected with a sleeve through a first pin shaft; the twist brace is used for replacing a traditional locking bolt, and the weight of the hub is reduced.

Furthermore, two ends of each torsion bar are respectively provided with a mounting hole, the first support arm is radially provided with two second through holes, and each second through hole is positioned between each shaft sleeve and the second support arm; a second pin shaft penetrates into a second through hole from the outside of the first support arm, is matched in a mounting hole and penetrates out of the other second through hole so as to connect the torsional brace and the first support arm.

Furthermore, each sleeve is provided with two first through holes along the radial direction, and a first pin shaft penetrates into one first through hole from the outside of the sleeve, is matched in one mounting hole and penetrates out of the other first through hole so as to connect the torsional brace and the sleeve; the sleeve is connected with the tension and torsion bar through the first pin shaft, the central support arm is connected with the tension and torsion bar, so that centrifugal force generated by rotation of the paddle is transmitted to the central support arm, and axial positioning and constraint of the sleeve on the central support arm are achieved.

Furthermore, the sleeve and the central support arm are both carbon fiber composite structural members; the hub is used for replacing the traditional metal sleeve and the metal center support arm, and the weight of the hub is reduced.

Further, the shaft sleeve is made of polyether-ether-ketone; the shaft sleeve has the wear-resisting self-lubricating function and is used for replacing the traditional metal bearing part, and the weight of the part is reduced.

Furthermore, the tension-torsion strip is a structural member formed by stacking thin metal sheets; the locking bolt is used for replacing the traditional locking bolt, and the weight of the propeller hub is greatly reduced.

Furthermore, the tension-torsion strip is a structural member formed by laminating unidirectional glass fibers; the locking bolt is used for replacing the traditional locking bolt, and the weight of the propeller hub is greatly reduced.

Furthermore, each sleeve is integrally connected with one blade; the first support arm and the second support arm are integrally connected; the number of parts of the hub is reduced.

Further, each shaft sleeve is glued with the outer peripheral surface of the first support arm; the bearing is used for replacing the traditional metal bearing part, so that the structure is more compact.

Has the advantages that: according to the rotor wing mechanism, the hub comprises the sleeve, the central support arm, the shaft sleeve and the torsion-pull assembly, the hub is compact in design structure and used for replacing traditional complex parts such as metal materials, metal bearings and locking bolts, the number and weight of the parts are reduced, and the light weight requirement of the hub is met.

Drawings

FIG. 1a is a schematic structural view of a rotor hub of a present light and small unmanned helicopter;

FIG. 1b is a schematic view of the rotor hub and rotor blade assembly of FIG. 1 a;

figure 2a is an overall schematic view of a rotor mechanism of the present invention;

FIG. 2b is an enlarged schematic view of position A in FIG. 2 a;

FIG. 3 is a schematic view of the hub configuration;

FIG. 4 is a schematic structural view of the sleeve and the blade;

FIG. 5 is a schematic view of a center arm;

FIG. 6 is a schematic view of the twist tie;

fig. 7 is an assembly schematic of the twist-pull assembly.

Detailed Description

The technical scheme provided by the invention is explained in detail in the following with the accompanying drawings.

As shown in fig. 2a to 3, the present invention provides the rotor mechanism, which includes a hub 1, a blade 2; hub 1 includes a sleeve 11, a center arm 12, a bushing 13, and a twist-pull assembly.

As shown in fig. 3 and 5, the center support arm 12 includes a first support arm 121 extending axially, and a second support arm 122 disposed on the first support arm 121 and radially penetrating the first support arm 121; the central support arm 12 is cross-shaped, that is, the second support arm 122 vertically penetrates the first support arm 121, and both the first support arm 121 and the second support arm 122 are hollow structural members; the first support arm 121 and the second support arm 122 are integrally connected; and the center arm 12 is a carbon fiber composite structural member.

As shown in fig. 3, the outer peripheral surfaces of the two ends of the first support arm 121 are respectively sleeved in a sleeve 11, specifically, the two sleeves 11 are coaxially connected through the first support arm 121, and the two sleeves 11 coaxially extend; the second arm 122 is adapted to be fixedly coupled to the rotor shaft.

As shown in fig. 4, each sleeve 11 is connected to one blade 2, the sleeve 11 is a carbon fiber composite structural member, and compared with the prior art that a metal sleeve is adopted, the weight of the sleeve is reduced, and the sleeve 11 and the blade 2 are integrally formed, so that the number of connecting parts of the hub is reduced.

As shown in fig. 3, the outer peripheral surfaces of the two ends of the first support arm 121 are respectively provided with a shaft sleeve 13, and the shaft sleeves 13 are distributed on the two sides of the second support arm 122; each shaft sleeve 13 is glued to the outer peripheral surface of the first arm 121; the shaft sleeve 13 is made of polyether ether ketone (PEEK), belongs to a special polymer material, and has a wear-resistant self-lubricating function; when the two ends of the first support arm 121 are respectively adapted to the inside of a sleeve 11, the outer wall of each shaft sleeve 13 is matched with the inner wall of the sleeve 11; each sleeve 11 is fitted over the outer peripheral surface of the boss 13 of the first arm 121 and is rotatable about the center arm 12 to form a revolute pair. The invention adopts a wear-resistant self-lubricating material structural member as the shaft sleeve 13, replaces the traditional metal bearing, realizes the purpose of reducing the weight of the propeller hub and meets the requirement of lightening the rotor wing mechanism.

As shown in fig. 3, 6 and 7, each sleeve 11 is connected to the first arm 121 by a torsion assembly. Each torsion assembly comprises a torsion bar 15 axially disposed within the first arm 121, the first arm 121 is connected to one end of the torsion bar 15 by a second pin 16, and the other end of the torsion bar 15 extends out of the first arm 121 and is connected to a sleeve 11 by a first pin 14. Specifically, two ends of each torsion bar 15 are respectively provided with a mounting hole 151, the first support arm 121 is radially provided with two second through holes 161, and each second through hole 161 is located between each shaft sleeve 13 and the second support arm 122; a second pin 16 passes through a second through hole 161 from the outside of the first arm 121, fits into a mounting hole 151 and passes through another second through hole 161 to connect the torsion bar 15 and the first arm 121. Moreover, each sleeve 11 is radially provided with two first through holes 141, and a first pin 14 penetrates into one first through hole 141 from the outside of the sleeve 11, is adapted to a mounting hole 151 and penetrates out from the other first through hole 141 to connect the torsion bar 15 and the sleeve 11.

The sleeve 11 is connected with the tension and torsion bar 15 through the first pin shaft 14, and the center support arm 12 is connected with the tension and torsion bar 15 through the second pin shaft 16, so that the centrifugal force generated by the rotation of the blade 2 is transmitted to the center support arm 12, and the axial positioning and the restraint of the sleeve 11 on the center support arm 12 are realized.

Preferably, the tension and torsion bar 15 is a structural member formed by laminating thin metal sheets or a structural member formed by laminating unidirectional glass fibers, and the tension and torsion bar 15 has a larger tensile stiffness and a smaller torsional stiffness, can better bear the centrifugal force of the blade 2, and has a smaller requirement on the torsional moment. The invention replaces the locking bolt in the prior art with the torsional brace 15, reduces the weight of the hub and simplifies the structure.

According to the rotor wing mechanism, the composite material and the high-strength wear-resistant plastic are applied to the hub to replace a metal material and a metal bearing on the traditional hub, on the premise of ensuring the functions and the performance of the hub, the number and the weight of parts are reduced, the maintenance can be avoided in the service life, the light weight requirement of the hub is met, the structure is compact, the rotor wing mechanism has positive significance for reducing the structural weight of an unmanned helicopter and improving the structural reliability, and therefore the rotor wing mechanism is more suitable for being used by light-weight helicopters and small helicopters.

Claims

1. A rotor wing mechanism comprises a hub (1) and blades (2), and is characterized in that the hub comprises two sleeves (11), a central support arm (12) and a torsion-pull assembly; the central support arm comprises a first support arm (121) extending axially, a second support arm (122) arranged on the first support arm and penetrating through the first support arm radially, and shaft sleeves (13) respectively arranged on the peripheral surfaces of two ends of the first support arm and distributed on two sides of the second support arm; two ends of the first supporting arm are respectively sleeved in a sleeve, and the outer wall of each shaft sleeve is matched with the inner wall of the sleeve; each sleeve is connected with the first support arm through a torsion pulling assembly; each sleeve is axially connected with a blade; the second support arm is used for connecting the rotor shaft.

2. A rotor mechanism according to claim 1, wherein each twist assembly includes a twist tie (15) axially disposed within the first arm, the first arm being connected to one end of the twist tie by a second pin (16), the other end of the twist tie extending beyond the first arm and being connected to a sleeve by a first pin (14).

3. A rotor mechanism according to claim 2, wherein each torsion bar has a mounting hole (151) at each end, the first arm has two second through holes (161) formed radially therein, and each second through hole is located between each bushing and the second arm; a second pin shaft penetrates into a second through hole from the outside of the first support arm, is matched in a mounting hole and penetrates out of the other second through hole (161) so as to connect the torsional brace and the first support arm.

4. A rotor mechanism according to claim 3, wherein each sleeve has two first through holes (141) formed therein along a radial direction, and a first pin passes through one of the first through holes from outside the sleeve and fits into one of the mounting holes and passes out of the other first through hole to connect the torsion bar to the sleeve.

5. A rotor mechanism according to claim 1, wherein the sleeve and the center arm are both carbon fiber composite structural members.

6. A rotor mechanism according to claim 1, wherein the material of the bushing is polyetheretherketone.

7. A rotor mechanism according to claim 2, wherein the tension/torsion strap is a laminated structure of thin metal sheets.

8. A rotor mechanism according to claim 2, wherein the tension/torsion bars are structural members of unidirectional glass fiber laminates.

9. A rotor mechanism according to claim 1 or claim 5, wherein each sleeve is integrally connected to a blade; the first support arm and the second support arm are integrally connected.

10. A rotor mechanism according to claim 1 or claim 6, wherein each boss is cemented to the outer peripheral surface of the first arm.