CN113942644A - In-shaft control type rotor wing control system - Google Patents
In-shaft control type rotor wing control system Download PDFInfo
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- CN113942644A CN113942644A CN202111176968.6A CN202111176968A CN113942644A CN 113942644 A CN113942644 A CN 113942644A CN 202111176968 A CN202111176968 A CN 202111176968A CN 113942644 A CN113942644 A CN 113942644A
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- assembly
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- ring
- fixed ring
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Abstract
The invention belongs to the technical field of helicopter rotor system structures, and discloses an in-shaft control type rotor control system, which comprises: the device comprises a movable ring fixed ring assembly, an anti-torsion rod assembly, a belt rotating piece, a cross hinge assembly and a pull rod assembly; the rotating piece is funnel-shaped, the upper end of the rotating piece is hollow, and the lower end of the rotating piece is a solid shaft; the upper end of the belt rotating piece is connected with the rotor shaft through a bolt; the lower end of the belt rotating piece is connected with the movable ring fixed ring component through a cross hinge component; one end of the anti-twist rod component is connected with the main reducer fixing end, and the other end of the anti-twist rod component is connected with one support arm of the fixed ring in the fixed ring and fixed ring component; one end of a pull rod assembly is connected with the moving ring in the moving ring fixed ring assembly, the other end of the pull rod assembly is connected with a propeller hub rocker arm, and the pull rod assembly is installed in the rotor shaft; the other three support arms of the fixed ring in the movable ring and fixed ring assembly are connected with three boosters. The application has the advantages of good operation stability, high reliability and excellent performance.
Description
Technical Field
The invention belongs to the technical field of helicopter rotor system structures, and particularly relates to an in-shaft control type rotor control system.
Background
The rotor wing control mechanism is an important component of a helicopter rotor wing system, and the total pitch and periodic pitch-changing movement of the rotor wing are realized through the rotor wing control mechanism, so that the attitude adjustment of the helicopter is finally realized.
The typical structure of rotor operation is mainly a ring type spherical hinge structure, and mainly comprises a movable ring fixed ring component, a torque arm component, an anti-torque arm component, a variable-pitch pull rod component and the like. The movable ring and fixed ring component can slide up and down along a guide cylinder fixed at the upper end of the main reducer to realize the total pitch control of the rotor wing; the periodic pitch-variable operation of the rotor wing is realized through the tilting of the spherical hinge assembly; one end of the torque arm assembly is connected with the rotor shaft, the other end of the torque arm assembly is connected with the rotating ring assembly, and the rotating ring assembly is driven by the torque arm assembly to rotate synchronously with the main shaft when the rotor shaft rotates; one end of the anti-twisting arm component is connected to the main reducer shell, and the other end of the anti-twisting arm component is connected with the non-moving ring component to prevent the non-moving ring component from rotating along with the driven ring component; the three fork lugs of the fixed ring component are respectively connected with the control rudder machine.
The rotor operation of ring type ball pivot structure arranges in the rotor is epaxial outward, has increased part size and weight, has increased the resistance that the helicopter flight in-process produced, and is unfavorable for the helicopter overall arrangement.
Disclosure of Invention
The invention provides an in-shaft control type rotor wing control system, wherein a movable ring fixed ring assembly is arranged below a main reducer, and a control command is transmitted to a propeller hub through a pull rod assembly arranged in a rotor wing shaft, so that the design requirement of reducing aerodynamic resistance is met; meanwhile, the movable ring and fixed ring assembly adopts a cross hinge structure to replace a spherical hinge structure, although the structure is complex, the size of parts is reduced, the operation space arrangement of the rotor wing is facilitated, and the operation stability is good, the reliability is high, and the performance is excellent.
An in-shaft steered rotor steering system comprising: the device comprises a movable ring fixed ring assembly, an anti-torsion rod assembly, a belt rotating piece, a cross hinge assembly and a pull rod assembly;
the belt rotating piece is funnel-shaped, the upper end of the belt rotating piece is a hollow funnel, and the lower end of the belt rotating piece is a solid shaft; the upper end of the belt rotating piece is connected with the rotor shaft through a bolt;
the lower end of the belt rotating piece is connected with the movable ring and non-movable ring assembly through a cross hinge assembly;
one end of the anti-twist rod assembly is connected with the main reducer fixing end, and the other end of the anti-twist rod assembly is connected with one support arm of the fixed ring in the fixed ring and fixed ring assembly;
one end of the pull rod assembly is connected with the moving ring in the moving ring fixed ring assembly, the other end of the pull rod assembly is connected with the propeller hub rocker arm, and the pull rod assembly is installed in the rotor shaft;
and the other three support arms of the fixed ring in the movable ring and fixed ring assembly are connected with three boosters.
Further, the cross-hinge assembly includes: a first rotating shaft assembly 12, two second rotating shaft assemblies 21, a sliding barrel and a transition piece;
a rectangular sliding groove is axially formed in the solid shaft at the lower end of the rotating piece; the sliding groove penetrates through the solid shaft in the radial direction;
the sliding cylinder is sleeved on a solid shaft at the lower end of the rotating piece, and the transition piece is sleeved outside the sliding cylinder; a group of through holes are respectively formed in the same circumferential position in the axial vertical direction of the sliding cylinder and the transition piece;
the first rotating shaft assembly penetrates through the sliding cylinder, the through hole in the transition piece and the sliding groove in the solid shaft; the first rotating shaft component drives the sliding cylinder and the transition piece to slide along the sliding groove on the solid shaft at the lower end of the rotating piece;
the two second rotating shaft assemblies are symmetrically arranged on two sides of the transition piece, are coaxial and have axes passing through the intersection point of the axis of the first rotating shaft assembly and the axis of the solid shaft and perpendicular to the plane where the axis of the first rotating shaft assembly and the axis of the solid shaft are located;
one end of the second rotating shaft assembly is connected with the transition piece, and the other end of the second rotating shaft assembly is connected with the movable ring in the movable ring fixed ring assembly.
Further, the first spindle assembly includes: a first bolt 16, two first bushings 17, two first bearings 15, and a first straight bushing 18;
the first bolt penetrates through the sliding cylinder, the transition piece and the sliding groove in the solid shaft at the lower end of the rotating piece, and the first straight bushing sleeve is sleeved on the first bolt and penetrates through the sliding groove in the solid shaft at the lower end of the rotating piece and the circumferential through hole of the sliding cylinder;
the two first bearings are sleeved between the first bolt and the transition piece and are respectively positioned on two sides of the first straight bushing;
the two first bushings are sleeved on the first bolt and are respectively positioned on the outer sides of the two first bearings;
the end of the first bolt section is screwed through a nut.
Further, the second spindle assembly includes: a second bolt 22, a second bushing 23, a second bearing 24, a second straight bushing 25;
one side of the second bolt and the nut is embedded in the inner side of the transition piece; the screw rod section penetrates through a movable ring and a transition piece in the movable ring and fixed ring assembly; the second straight bushing is sleeved between the screw rod section and the movable ring and is positioned outside the second bearing; the end part of the screw rod section of the second bolt is locked by a nut;
the second bearing is sleeved between the second bolt and the transition piece;
the second bushing is sleeved on the second bolt and is located between the nut and the second bearing.
Furthermore, the inclined plane section of the hollow funnel at the upper end of the rotating piece is provided with four openings, and the lower ends of the four groups of pull rod assemblies respectively penetrate through the four openings to be connected with the moving ring in the moving ring fixed ring assembly.
Further, the sliding cylinder is hollow and cylindrical, and an annular groove is formed in the middle of the inner side wall of the sliding cylinder; and a group of through holes are symmetrically formed in the annular groove along the radial direction by 180 degrees so as to allow the first rotating shaft assembly to pass through.
Further, the system further comprises a sliding bushing; the sliding bush is in a hollow cylindrical shape, and the inner diameter of the sliding bush is matched with the outer diameter of the solid shaft with the rotating piece; the outer diameter of the sliding bush is matched with the inner diameter of the annular groove of the sliding barrel; the height of the sliding bush is equal to the height of the annular groove;
the sliding bush is arranged in the sliding barrel annular groove, and through holes with the same diameter are formed in the sliding bush and the sliding barrel annular groove at the same circumferential positions.
Furthermore, an opening is arranged on the side wall of the sliding bush and penetrates from the upper end face to the lower end face of the sliding bush; and the opening is far away from the through hole on the side wall of the sliding bush.
Further, the moving ring stationary ring assembly includes: a movable ring, a fixed ring and a large bearing;
the outer side of the upper end of the movable ring is provided with four support arms, double fork lugs are arranged on the support arms and are penetrated by through holes, and the fork lug holes are used for connecting a pull rod assembly; and the outer side of the upper end of the movable ring and the same plane of the axis of the fork lug hole are symmetrically provided with a group of through holes in a radial 180-degree manner, and the through holes are positioned on the symmetrical surfaces of two adjacent support arms and are used for connecting two second rotating shaft assemblies.
Has the advantages that:
the rotor wing operation structure operated in the shaft is arranged in the rotor wing shaft for operation, so that the design requirement of reducing aerodynamic resistance is met; meanwhile, a cross hinge structure is adopted to replace a spherical hinge structure, so that the size of parts is reduced, the operation space arrangement of the rotor wing is facilitated, and the operation stability is good, the reliability is high, and the performance is excellent.
Drawings
FIG. 1 is a schematic view of a rotor handling system installation;
figure 2 is a top view of the rotor handling system;
figure 3 is a cross-sectional view a-a of the rotor from a top view of the rotor;
figure 4 is a cross-sectional view B-B of a top view of the rotor manipulation;
FIG. 5 is a partial enlargement of region C of FIG. 3;
FIG. 6 is an enlarged view of a portion of the area D in FIG. 4;
the main reducing end, the moving ring fixed ring assembly 6, the cross hinge assembly 7, the bolt 8, the moving ring fixed ring assembly 9, the large bearing 10, the moving ring assembly 11, the first rotating shaft assembly 12, the sliding bush 13, the sliding barrel 14, the first bearing 15, the first bolt 16, the first bush 17, the first straight bush 18, the transition piece 19, the nut 20, the second rotating shaft assembly 21, the second bolt 22, the second bush 23, the second bearing 24, the second straight bush 25 and the nut 26 are arranged on the main reducing end of the rotor shaft 1.
Detailed Description
The invention relates to an in-shaft rotor wing control structure which mainly comprises a moving ring fixed ring assembly 6, an anti-torsion rod assembly 4, a rotating piece 2, a cross hinge assembly 7 and a pull rod assembly 3, and is shown in figure 1. Wherein the belt rotating piece 2 is funnel-shaped, the upper end of the funnel is hollow, the tail end of the funnel is provided with an annular step, and the lower end of the funnel is provided with a solid shaft; the rotor shaft 1 is inserted into a hollow funnel at the upper end of the rotating piece 2 and is connected with the rotor shaft 1 through 4 circumferentially arranged bolts 8, and an annular step is arranged at the tail end of the inner side of the funnel and used for limiting the rotor shaft 1; the lower end of the belt rotating piece 2 is connected with a movable ring and immovable ring assembly 6 through a cross hinge assembly 7; 3 support arms of the fixed ring in the movable ring fixed ring assembly 6 are connected to the booster through bolts, and the other 1 support arm of the fixed ring is connected with the anti-torsion arm rod assembly 4 to prevent the fixed ring from being rotated. The other end of the anti-twist arm bar assembly 4 is bolted to the main reduction end 5. The lower end of the pull rod assembly 3 penetrates through an opening formed in the inclined plane section of the hollow funnel of the rotating piece 2 and is connected with a moving ring in the moving ring fixed ring assembly 6, the other end of the pull rod assembly is connected with a propeller hub rocker arm, and the pull rod assembly 3 is located inside the rotor shaft 1.
As shown in fig. 3 and 4, the cross-hinge assembly 7 is mainly composed of two second spindle assemblies 21, one first spindle assembly 12, the slide cartridge 14, the transition piece 19, and the like. As shown in fig. 3, the rotating shaft assembly 12 is composed of a first bolt 16, two first bushings 17, two first bearings 15 on a transition piece 19, and a first straight bushing 18; the first bolt 16 is sequentially pressed with the first bush 17, the first bearing 15 inner ring, the first straight bush 18, the first bearing 15 inner ring and the first bush 17, and is screwed by the nut 20; the first straight bushing 18 is hollow and cylindrical, the outer cylinder is symmetrically flattened from the upper end face to the lower end face, and the flattened surface is matched with the inner plane of the sliding chute of the rotating part 2 and can slide up and down in the sliding chute; two pairs of first bearing 15 outer races are mounted to the transition piece 19 so that the transition piece 19 can be tilted about the first axis of rotation 12. The rotating shaft assembly 12 is mainly connected with the rotating member 2, the sliding barrel 14 and the transition member 19; when the collective movement is performed, the slide cylinder 14 and the transition piece 19 can slide up and down along the lower end solid shaft portion of the belt rotating member 2 together under the connection action of the first rotating shaft assembly 12. The sliding bush 13 is arranged in an annular groove on the inner side of the sliding barrel 14, a circumferential through hole is aligned with a circumferential through hole of the sliding barrel 14 and is connected by the first rotating shaft assembly 12, and the sliding bush 13 plays a role in wear resistance and support. As shown in fig. 4, the second rotating shaft assembly 21 is composed of a second bolt 22, a second bushing 23, a second bearing 24 mounted on the transition piece 19, and a second straight bushing 25; the second bolt 22 is sequentially pressed against the second bush 23, the inner ring of the second bearing 24 and the second straight bush 25, and is screwed by the nut 26; the second straight bushing 25 is inserted into the circumferential hole of the moving ring from the outside of the moving ring of the stationary ring assembly 6. The outer race of second bearing 24 is mounted to transition piece 19 such that transition piece 19 can be tilted about rotary shaft 21. The axes of the two second rotating shaft assemblies 21 and the first rotating shaft assembly 12 are mutually perpendicular and in the same plane, and the intersection points of the second rotating shaft assemblies 21 and the first rotating shaft assembly 12 are formed, so that transverse periodic variable pitch and longitudinal periodic variable pitch motion are realized, and the independence of the transverse periodic variable pitch and the longitudinal periodic variable pitch is ensured.
As shown in fig. 3, the moving ring stationary ring assembly 6 is composed of a moving ring assembly 11, a stationary ring assembly 9 and a pair of large bearings 10, wherein the moving ring assembly 11 rotates and the stationary ring assembly 9 does not rotate, and the large bearings 10 are used for isolating the rotating motion of the moving ring assembly 11 from the non-rotating motion of the stationary ring assembly 9. The outer side of the upper end of the movable ring 11 is provided with four support arms, double fork lugs are arranged on the support arms, through holes penetrate through the support arms in the radial direction, and the fork lug holes are used for being connected with the pull rod assembly 3; and a group of through holes are symmetrically arranged on the outer side of the upper end of the movable ring 11 and on the same plane of the axes of the fork lugs in a radial 180-degree manner, are positioned on the symmetrical surfaces of two adjacent support arms and are used for connecting two second rotating shaft assemblies 21.
When the rotor wing is operated to carry out total distance operation, the movable ring fixed ring assembly 6 moves up and down along the solid shaft at the lower end of the rotating part 2, the transition part 19 is driven to move up and down under the connecting action of the two second rotating shaft assemblies 21, and the transition part 19 drives the sliding cylinder 14 to move up and down along the solid shaft at the lower end of the rotating part 2 under the action of the first rotating shaft assembly 12.
When the rotor wing is operated to carry out periodic variable-pitch operation, the moving ring and fixed ring assembly 6 can independently tilt around the second rotating shaft 21, the transition piece 19 does not tilt, and simultaneously can tilt around the first rotating shaft assembly 12 together with the transition piece 19 in the same posture; meanwhile, the different postures of the movable ring fixed ring assembly 6 and the transition piece 19 can be tilted around the first rotating shaft 12, namely, the transition piece 19 is firstly kept immovable, the movable ring fixed ring assembly 6 is tilted around the second rotating shaft assembly 21, and then the movable ring fixed ring assembly and the transition piece 19 are tilted around the first rotating shaft assembly 12.
When the rotor shaft 1 rotates, the belt rotating member 2 and the rotor shaft 1 rotate synchronously under the connecting action of the bolt 8, the slide cylinder 14 and the transition member 19 are driven to rotate under the connecting action of the first rotating shaft assembly 12, and the rotating ring assembly is driven to rotate under the connecting action of the second rotating shaft assembly 21.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (9)
1. An in-shaft control type rotor wing control system is characterized in that: the system comprises: the device comprises a movable ring fixed ring assembly, an anti-torsion rod assembly, a belt rotating piece, a cross hinge assembly and a pull rod assembly;
the belt rotating piece is funnel-shaped, the upper end of the belt rotating piece is a hollow funnel, and the lower end of the belt rotating piece is a solid shaft; the upper end of the belt rotating piece is connected with the rotor shaft through a bolt;
the lower end of the belt rotating piece is connected with the movable ring and non-movable ring assembly through a cross hinge assembly;
one end of the anti-twist rod assembly is connected with the main reducer fixing end, and the other end of the anti-twist rod assembly is connected with one support arm of the fixed ring in the fixed ring and fixed ring assembly;
one end of the pull rod assembly is connected with the moving ring in the moving ring fixed ring assembly, the other end of the pull rod assembly is connected with the propeller hub rocker arm, and the pull rod assembly is installed in the rotor shaft;
and the other three support arms of the fixed ring in the movable ring and fixed ring assembly are connected with three boosters.
2. The in-shaft operated rotor steering system according to claim 1, wherein: the cross hinge assembly includes: the device comprises a first rotating shaft assembly (12), two second rotating shaft assemblies (21), a sliding barrel and a transition piece;
a rectangular sliding groove is axially formed in the solid shaft at the lower end of the rotating piece; the sliding groove penetrates through the solid shaft in the radial direction;
the sliding cylinder is sleeved on a solid shaft at the lower end of the rotating piece, and the transition piece is sleeved outside the sliding cylinder; a group of through holes are respectively formed in the same circumferential position in the axial vertical direction of the sliding cylinder and the transition piece;
the first rotating shaft assembly penetrates through the sliding cylinder, the through hole in the transition piece and the sliding groove in the solid shaft; the first rotating shaft component drives the sliding cylinder and the transition piece to slide along the sliding groove on the solid shaft at the lower end of the rotating piece;
the two second rotating shaft assemblies are symmetrically arranged on two sides of the transition piece, are coaxial and have axes passing through the intersection point of the axis of the first rotating shaft assembly and the axis of the solid shaft and perpendicular to the plane where the axis of the first rotating shaft assembly and the axis of the solid shaft are located;
one end of the second rotating shaft assembly is connected with the transition piece, and the other end of the second rotating shaft assembly is connected with the movable ring in the movable ring fixed ring assembly.
3. The in-shaft operated rotor steering system according to claim 2, wherein: the first spindle assembly includes: a first bolt (16), two first bushings (17), two first bearings (15), and a first straight bushing (18);
the first bolt penetrates through the sliding cylinder, the transition piece and the sliding groove in the solid shaft at the lower end of the rotating piece, and the first straight bushing is sleeved on the first bolt and penetrates through the sliding groove in the solid shaft at the lower end of the rotating piece and the circumferential through hole of the sliding cylinder;
the two first bearings are sleeved between the first bolt and the transition piece and are respectively positioned on two sides of the first straight bushing;
the two first bushings are sleeved on the first bolt and are respectively positioned on the outer sides of the two first bearings;
the end of the first bolt section is screwed through a nut.
4. The in-shaft operated rotor steering system according to claim 2, wherein: the second spindle assembly includes: a second bolt (22), a second bushing (23), a second bearing (24), and a second straight bushing (25);
one side of the second bolt and the nut is embedded in the inner side of the transition piece; the screw rod section penetrates through a movable ring and a transition piece in the movable ring and fixed ring assembly; the second straight bushing is sleeved between the screw rod section and the movable ring and is positioned outside the second bearing; the end part of the screw rod section of the second bolt is locked by a nut;
the second bearing is sleeved between the second bolt and the transition piece;
the second bushing is sleeved on the second bolt and is located between the nut and the second bearing.
5. The in-shaft operated rotor steering system according to claim 4, wherein: the inclined plane section of the hollow funnel at the upper end of the rotating piece is provided with four openings, and the lower ends of the four groups of pull rod assemblies respectively penetrate through the four openings to be connected with the moving ring in the moving ring fixed ring assembly.
6. The in-shaft operated rotor steering system according to claim 5, wherein: the sliding cylinder is hollow and cylindrical, and an annular groove is formed in the middle of the inner side wall of the sliding cylinder; and a group of through holes are symmetrically formed in the annular groove along the radial direction by 180 degrees so as to allow the first rotating shaft assembly to pass through.
7. The in-shaft operated rotor steering system according to claim 6, wherein: the system further includes a sliding bushing; the sliding bush is in a hollow cylindrical shape, and the inner diameter of the sliding bush is matched with the outer diameter of the solid shaft with the rotating piece; the outer diameter of the sliding bush is matched with the inner diameter of the annular groove of the sliding barrel; the height of the sliding bush is equal to the height of the annular groove;
the sliding bush is arranged in the sliding barrel annular groove, and through holes with the same diameter are formed in the sliding bush and the sliding barrel annular groove at the same circumferential positions.
8. The in-shaft operated rotor steering system according to claim 7, wherein: the side wall of the sliding bush is provided with an opening, and the opening penetrates from the upper end face to the lower end face of the sliding bush; and the opening is far away from the through hole on the side wall of the sliding bush.
9. The in-shaft operated rotor steering system according to claim 8, wherein: the moving ring stationary ring subassembly includes: a movable ring, a fixed ring and a large bearing;
the outer side of the upper end of the movable ring is provided with four support arms, double fork lugs are arranged on the support arms and are penetrated by through holes, and the fork lug holes are used for connecting a pull rod assembly; and the outer side of the upper end of the movable ring and the same plane of the axis of the fork lug hole are symmetrically provided with a group of through holes in a radial 180-degree manner, and the through holes are positioned on the symmetrical surfaces of two adjacent support arms and are used for connecting two second rotating shaft assemblies.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111176968.6A CN113942644B (en) | 2021-10-09 | 2021-10-09 | In-shaft control type rotor wing control system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111176968.6A CN113942644B (en) | 2021-10-09 | 2021-10-09 | In-shaft control type rotor wing control system |
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| CN113942644A true CN113942644A (en) | 2022-01-18 |
| CN113942644B CN113942644B (en) | 2023-04-28 |
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2021
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| US5110260A (en) * | 1990-12-17 | 1992-05-05 | United Technologies Corporation | Articulated helicopter rotor within an improved blade-to-hub connection |
| CN101973399A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Constant-speed universal hinged propeller hub for tilt-rotor aircraft |
| CN102211663A (en) * | 2011-05-11 | 2011-10-12 | 王略 | Gear tilting type coaxial machine |
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| CN113942644B (en) | 2023-04-28 |
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