CN113247240A - Unmanned helicopter tail rotor pitch adjusting and operating structure - Google Patents
Unmanned helicopter tail rotor pitch adjusting and operating structure Download PDFInfo
- Publication number
- CN113247240A CN113247240A CN202110707491.3A CN202110707491A CN113247240A CN 113247240 A CN113247240 A CN 113247240A CN 202110707491 A CN202110707491 A CN 202110707491A CN 113247240 A CN113247240 A CN 113247240A
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- sliding sleeve
- pitch
- tail
- variable
- tail rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/32—Blade pitch-changing mechanisms mechanical
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
The invention relates to the technical field of unmanned helicopters, and particularly discloses a tail rotor pitch adjusting and operating structure of an unmanned helicopter, which comprises a tail rotor shaft, wherein the tail end of the tail rotor shaft is connected with a tail rotor hub central part, a plurality of support arms are arranged on the tail rotor hub central part, and variable-pitch hinge components for connecting tail blades and adjusting the pitch of the tail blades are arranged on the support arms; a sliding sleeve assembly which synchronously rotates with the tail propeller shaft and slides along the axial direction of the tail propeller shaft is arranged on the tail propeller shaft, and a plurality of variable-pitch pull rods are connected between the sliding sleeve assembly and the variable-pitch hinge assembly; the adjusting and operating structure also comprises a driving component for driving the sliding sleeve component to axially reciprocate, the sliding sleeve component is matched with the tail rotor shaft, and the torque on the tail rotor shaft is directly transmitted to the sliding sleeve component so as to enable the sliding sleeve component to synchronously rotate, thereby avoiding the condition that the sliding sleeve component is damaged due to the torque on the variable-pitch pull rod; the sliding sleeve assembly moves axially along the tail rotor shaft to adjust the inclination angle of the tail rotor blade, so that the integral structure is greatly simplified, and the reliability of blade pitch adjustment is improved.
Description
Technical Field
The invention relates to the technical field of unmanned helicopters, and particularly discloses a tail rotor pitch adjusting and operating structure of an unmanned helicopter.
Background
The tail blade of the unmanned helicopter is an important part for balancing the back torsion of the rotor wing, and the unmanned helicopter can be used for realizing course control of the unmanned helicopter by controlling the tail blade. In the traditional helicopter torque force transmission, a tail rotor hub is driven by a tail rotor shaft, and the tail rotor hub drives a variable-pitch pull rod to drive a propeller disc to rotate; the paddle disc is driven to move on the tail paddle shaft through the hydraulic transmission structure so as to drive the variable-pitch pull rod to move, and therefore the change of the propeller pitch of the tail paddle is achieved. The structure has the advantages of more structural parts and complex structure, increases the weight of the helicopter and reduces the reliability of the tail rotor pitch adjustment operation. Meanwhile, the variable-pitch pull rod not only bears tension and compression loads, but also needs to transmit torque, so that the service life of the pull rod can be shortened, and potential safety hazards are increased. Finally, a mechanism for driving the propeller disc to move on the tail rotor shaft has the defects of long transmission path, large friction area, increased operation clearance and direct influence on the operation energy efficiency of the unmanned helicopter.
Therefore, the existing tail rotor pitch control structure of the unmanned helicopter has a part to be improved urgently, a more reasonable technical scheme needs to be provided, and the defects in the prior art are overcome.
Disclosure of Invention
In order to solve the defects of the prior art mentioned in the above, the invention provides a control structure for adjusting the propeller pitch of a tail rotor of an unmanned helicopter, wherein a pitch-variable structure at a tail rotor shaft of the unmanned helicopter is optimized, and the sliding sleeve assembly and the tail rotor shaft are matched to realize axial reciprocating movement and circumferential synchronous rotation, so that the structure for adjusting the pitch is simplified, the torque on a pitch-variable pull rod is avoided, the service life of the pitch-variable pull rod is prolonged, and the reliability of the propeller pitch adjustment is improved.
In order to achieve the purpose, the invention specifically adopts the technical scheme that:
a tail rotor pitch adjusting and operating structure of an unmanned helicopter comprises a tail rotor shaft, wherein the tail end of the tail rotor shaft is connected with a tail rotor hub central part, a plurality of support arms are arranged on the tail rotor hub central part, and variable-pitch hinge assemblies used for connecting tail blades and adjusting the pitch of the tail blades are arranged on the support arms; a sliding sleeve assembly which synchronously rotates with the tail propeller shaft and slides along the axial direction of the tail propeller shaft is arranged on the tail propeller shaft, and a plurality of variable-pitch pull rods are connected between the sliding sleeve assembly and the variable-pitch hinge assembly; the adjustment and manipulation structure further comprises a driving assembly for driving the sliding sleeve assembly to axially reciprocate.
According to the adjusting and operating structure, the variable-pitch hinge assembly is in relative rotation fit with the support arm, and the blade inclination angle of the tail rotor can be driven to change through rotation of the variable-pitch hinge assembly, so that blade pitch adjustment of the tail rotor is realized. Above-mentioned sliding sleeve subassembly realizes axial synchronous rotation through self and the cooperation of tail-rotor shaft, has avoided transmitting the moment of torsion through outside displacement pull rod to optimize the atress on the displacement pull rod, can avoid the displacement pull rod to receive the damage, improved the life of displacement pull rod and the reliability of displacement regulation greatly.
Further, the sliding sleeve assembly employed in the present invention may be configured in various forms, which are not limited only, and is optimized and one of the possible options is: the sliding sleeve assembly comprises a sliding sleeve which is arranged on the tail rotor shaft in a sliding mode and synchronously rotates with the tail rotor shaft, a fork-shaped piece which is relatively fixed with the sliding sleeve is arranged on the sliding sleeve, a plurality of connecting bosses are arranged on the fork-shaped piece, one end of the variable-pitch pull rod is matched with the connecting bosses, and the other end of the variable-pitch pull rod is hinged with the variable-pitch hinge assembly and drives the variable-pitch hinge assembly. When the scheme is adopted, the sliding sleeve and the tail rotor shaft synchronously rotate and drive the forked piece to synchronously rotate, when the sliding sleeve axially displaces along the tail rotor shaft, the forked piece synchronously displaces, and the variable-pitch pull rod synchronously pushes or pulls the variable-pitch hinge assembly to correspondingly deflect, so that the angle adjustment of the tail rotor blade is realized.
Further, in order to transmit the circumferential load of the tail rotor shaft to the sliding sleeve and enable the sliding sleeve to synchronously rotate in the circumferential direction, the torque is transmitted without the pitch-variable pull rod in the process so as to optimize the stress condition on the pitch-variable pull rod, various feasible schemes can be adopted to achieve the purpose, and the following feasible options are optimized and listed here: the cross section of the propeller shaft is in an oval shape, a polygonal shape or a shape combining the polygonal shape and the arc shape, a circumference positioning block is arranged on the end face of the sliding sleeve and abuts against the surface of the propeller shaft, and the circumference positioning block is fixedly connected with the sliding sleeve relatively and drives the sliding sleeve to rotate synchronously. When the scheme is adopted, the sliding sleeve is driven to rotate through the circumferential positioning block, so that the torque transmission of the propeller shaft is ensured not to pass through the variable-pitch pull rod; meanwhile, a certain space is left between the sliding sleeve and the tail rotor shaft, so that lubrication is facilitated.
Still further, the optimization is continued here, and another possible scheme for transferring the propeller shaft is given: the cross section of the tail rotor shaft is in an oval shape, a polygonal shape or a shape combining the polygonal shape and the arc shape, and the sliding sleeve is provided with a sleeve hole correspondingly matched with the tail rotor shaft. When the scheme is adopted, the torque of the propeller shaft is directly transmitted to the sliding sleeve, the structure is simple, and the matching is convenient.
Still further, the optimization is continued here, and another possible scheme for transferring the propeller shaft is given: and a meshing structure or a clamping structure in the circumferential direction is arranged between the tail rotor shaft and the sliding sleeve. When adopting such scheme, the moment of torsion direct transmission of propeller shaft is for the sliding sleeve, makes the cooperation of sliding sleeve and propeller shaft simpler, and the cooperation also makes things convenient for structure of meshing or block structure more can adopt structures such as meshing tooth, keyway.
Further, in order to facilitate the actual pitch control operation, the structure of the sliding sleeve assembly can be further optimized and improved, which is one of the possible options: the sliding sleeve assembly further comprises a fixing ring, the fixing ring is rotatably arranged on the sliding sleeve through a bearing, and the fixing ring and the sliding sleeve are relatively fixed in the axial direction; the driving assembly is connected with the fixing ring and pushes the fixing ring to move back and forth along the axial direction of the tail rotor shaft. When adopting such scheme, solid fixed ring and sliding sleeve rotate relatively, nevertheless gu fixed ring can adjust the ascending position of sliding sleeve in the axial of propeller shaft to realize the displacement and adjust.
Still further, in order to reduce the jamming caused by the external impurities entering between the sliding sleeve assembly and the tail rotor shaft, the structure of the sliding sleeve assembly is optimized, and the following feasible options are provided: the sliding sleeve assembly further comprises a plurality of dust covers, and the dust covers are arranged at the front end or the rear end of the sliding sleeve assembly and wrap the sliding fit sections of the sliding sleeve assembly and the tail propeller shaft. When adopting such scheme, the dust cover is the flexible cover, and when the sliding sleeve subassembly took place axial displacement along the tail-rotor shaft, the dust cover also still can cover the protection with sliding fit section.
Further, when actually performing the pitch adjustment, the driving assembly drives the sliding sleeve assembly, and the driving assembly may adopt various possible options, which are not limited only, and is optimized and one of the possible options is shown here: the driving assembly comprises a corner rocker arm, the middle of the corner rocker arm is arranged at a fixed hinged position, the front end of the corner rocker arm is hinged with the fixed ring, the rear end of the corner rocker arm is hinged with an adjusting pull rod, and the adjusting pull rod is connected to the driver. When the scheme is adopted, a hinge joint is arranged on one fixed part of the tail rotor system and is used for connecting the corner rocker arm to serve as a supporting point of the corner rocker arm.
Still further, in order to improve the smoothness of the adjusting pull rod in the adjusting process and avoid the situation that the driving assembly is jammed in the process of pushing the sliding sleeve assembly, the structure of the corner rocker arm can be optimized and improved, and one of the feasible options is given here: and a bearing is arranged at the hinged position of the middle part of the corner rocker arm. When the scheme is adopted, the corner rocker arm is provided with the bearing hole, the inner ring of the bearing is connected and matched with the hinged shaft, and the outer ring of the bearing is connected and matched with the corner rocker arm.
Further, in the present invention, the tail rotor blades are connected and arranged by the variable pitch hinge assembly, specifically, the present invention is optimized and one of the feasible options is shown: the variable-pitch hinge assembly comprises a variable-pitch hinge shell and a variable-pitch hinge gland which are rotatably arranged on the support arm, and the variable-pitch hinge shell is relatively and fixedly connected with the variable-pitch hinge gland; the variable-pitch pull rod is hinged with the variable-pitch hinge pressing cover or the variable-pitch hinge shell, and the tail rotor blade is arranged on the variable-pitch hinge shell. When the scheme is adopted, the number of the variable-pitch hinge shells is at least two, more variable-pitch hinges can be arranged according to actual requirements, and each variable-pitch hinge can be connected with one blade.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, the sliding sleeve assembly is matched with the tail rotor shaft, and the torque on the tail rotor shaft is directly transmitted to the sliding sleeve assembly, so that the sliding sleeve assembly synchronously rotates, and the condition that the sliding sleeve assembly is damaged due to the torque on the variable-pitch pull rod is avoided; meanwhile, the sliding sleeve assembly moves axially along the tail rotor shaft to adjust the inclination angle of the tail rotor blade, so that the overall structure is greatly simplified, and the reliability of blade pitch adjustment is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is an overall schematic view of a pitch adjustment steering structure.
FIG. 2 is an overall schematic view of another perspective of the pitch adjustment steering arrangement.
Fig. 3 is a front view of the variable pitch hinge assembly.
Fig. 4 is a cross-sectional view of the arm.
FIG. 5 is a schematic view of the sliding sleeve assembly and the variable pitch hinge assembly.
FIG. 6 is a schematic side view of the sliding sleeve assembly engaged with the tail rotor shaft.
FIG. 7 is a schematic cross-sectional view of the sliding sleeve assembly engaged with the tail rotor shaft.
Fig. 8 is a schematic view of the overall structure of the sliding sleeve assembly in cooperation with the tail rotor shaft.
Fig. 9 is a general schematic view of the matching structure of the driving assembly and the sliding sleeve assembly.
FIG. 10 is a side view of the engagement structure of the driving assembly and the sliding sleeve assembly.
FIG. 11 is a schematic cross-sectional view of the engagement structure of the driving assembly and the sliding sleeve assembly.
In the above drawings, the meaning of each symbol is: 1. adjusting the pull rod; 2. a corner rocker arm; 3. a speed reducer; 4. a fixing ring; 5. a fork-shaped piece; 501. connecting the bosses; 6. an oil injection nozzle; 7. a variable-pitch pull rod; 8. a dust cover; 9. a variable pitch hinge assembly; 901. a variable-pitch hinge gland; 902. a variable pitch hinge housing; 10. a circumferential positioning block; 11. a tail rotor hub centerpiece; 12. a support arm; 13. a tail rotor shaft; 14. and (4) a sliding sleeve.
Detailed Description
The invention is further explained below with reference to the drawings and the specific embodiments.
It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Specific structural and functional details disclosed herein are merely illustrative of example embodiments of the invention. This invention may, however, be embodied in many alternate forms and should not be construed as limited to the embodiments set forth herein.
Examples
Aiming at the phenomena of large quantity of parts, poor regulation reliability and easy damage of the structure of the existing unmanned helicopter tail rotor pitch regulation structure, the embodiment is optimized to improve the problems existing in the prior art.
Specifically, as shown in fig. 1 and fig. 2, the embodiment discloses a tail rotor pitch adjusting and operating structure of an unmanned helicopter, which includes a tail rotor shaft 13, wherein the tail end of the tail rotor shaft 13 is connected with a tail rotor hub central part 11, the tail rotor hub central part 11 is provided with a plurality of support arms 12, and the support arms 12 are provided with a variable pitch hinge assembly 9 for connecting tail blades and adjusting the pitch of the tail blades; a sliding sleeve component which synchronously rotates with the propeller shaft 13 and slides along the axial direction of the propeller shaft is arranged on the propeller shaft, and a plurality of variable-pitch pull rods 7 are connected between the sliding sleeve component and the variable-pitch hinge component 9; the adjustment and manipulation structure further comprises a driving assembly for driving the sliding sleeve assembly to axially reciprocate.
In the adjusting and operating structure disclosed above, the pitch-variable hinge assembly 9 and the support arm 12 are in relative rotation fit, and the blade inclination angle of the tail rotor can be driven to change through the rotation of the pitch-variable hinge assembly 9, so that pitch-variable adjustment is realized. Above-mentioned sliding sleeve subassembly realizes axial synchronous rotation through self and the cooperation of tail-rotor shaft 13, has avoided transmitting the moment of torsion through outside displacement pull rod 7 to optimized the atress on the displacement pull rod 7, can avoid displacement pull rod 7 to receive the damage, improved the life of displacement pull rod 7 and the reliability of displacement regulation greatly.
The sliding sleeve assembly used in the present embodiment can be constructed in various forms, which are not limited only, and the present embodiment is optimized and adopts one of the feasible options: as shown in fig. 5 to 11, the sliding sleeve assembly includes a sliding sleeve 14 slidably disposed on the tail rotor shaft 13 and synchronously rotating with the tail rotor shaft 13, a fork 5 relatively fixed to the sliding sleeve 14 is disposed on the sliding sleeve 14, a plurality of connecting bosses 501 are disposed on the fork 5, one end of the variable pitch link 7 is engaged with the connecting bosses 501, and the other end of the variable pitch link 7 is hinged to the variable pitch hinge assembly 9 and drives the variable pitch hinge assembly 9. When the scheme is adopted, the sliding sleeve 14 and the tail rotor shaft 13 synchronously rotate and drive the forked piece 5 to synchronously rotate, when the sliding sleeve 14 axially displaces along the tail rotor shaft 13, the forked piece 5 synchronously displaces, and the variable-pitch pull rod 7 synchronously pushes or pulls the variable-pitch hinge assembly 9 to correspondingly deflect, so that the angle adjustment of the tail rotor blade is realized.
Preferably, the sliding sleeve 14 is provided with an oil nozzle 6 for injecting lubricating grease between the sliding sleeve 14 and the tail rotor shaft 13.
Preferably, the fork 5 in this embodiment comprises two connecting bosses 501, and the two connecting bosses 501 are opposite to each other by 180 ° and are arranged in a rotational symmetry manner. The connecting boss 501 is provided with a hinge shaft which is matched with the variable pitch pull rod 7 in a hinged manner.
Preferably, in the present embodiment, the pitch link 7 is an elongated rod with a fixed length.
In order to transmit the circumferential load of the tail rotor shaft 13 to the sliding sleeve 14 and enable the sliding sleeve 14 to synchronously rotate in the circumferential direction, in the process, the torque transmission of the pitch-variable pull rod 7 is not needed, so as to optimize the stress condition on the pitch-variable pull rod 7, the above purpose can be achieved by adopting various feasible schemes, and the embodiment is optimized and adopts one feasible choice as follows: the cross section of the tail rotor shaft 13 is in an oval shape, a polygonal shape or a shape combining the polygonal shape and the arc shape, a plurality of circumference positioning blocks 10 are sleeved on the sliding sleeve 14, the circumference positioning blocks 10 are abutted against the surface of the tail rotor shaft 13 and are in tight contact with the surface of the tail rotor shaft 13, and the torque of the tail rotor shaft is transferred to the sliding sleeve 14, so that the sliding sleeve 14 rotates synchronously along with the tail rotor shaft 13. When the scheme is adopted, the sliding sleeve 14 is driven to rotate through the circumferential positioning block 10, and the torque of the tail rotor shaft 13 is ensured not to pass through the pitch-variable pull rod 7.
Preferably, in this embodiment, the sliding sleeve 14 is provided with a locking groove, and the circumferential positioning block 10 is disposed in the locking groove and fixedly connected to the sliding sleeve 14 through a fastening member. It can also be optimized that the draw-in groove is along circumference symmetric distribution on the terminal surface of sliding sleeve, can set up a plurality ofly, all sets up a circumference fixed block 10 in every draw-in groove. When adopting such scheme, there is certain accommodation space between the sliding sleeve is inside and the tail-rotor shaft, the lubrication of being convenient for.
In other embodiments, another possible solution for transferring the propeller shaft 13 may be used: the cross section of the tail rotor shaft 13 is in the shape of an ellipse, a polygon or a combination of the polygon and an arc, and the sliding sleeve 14 is provided with a sleeve hole correspondingly matched with the tail rotor shaft 13. When the scheme is adopted, the torque of the tail rotor shaft 13 is directly transmitted to the sliding sleeve 14, the structure is simple, and the matching is convenient.
In other embodiments, another possible solution for transferring the propeller shaft 13 may be used: and a meshing structure or a clamping structure in the circumferential direction is arranged between the tail rotor shaft 13 and the sliding sleeve 14. When adopting such scheme, the moment of torsion direct transmission of tail-rotor shaft 13 is for sliding sleeve 14, makes sliding sleeve 14 and tail-rotor shaft 13's cooperation simpler, and the cooperation also makes things convenient for structure such as meshing tooth, keyway to adopt meshing structure or block structure more.
In order to facilitate the actual pitch-variable control operation, the structure of the sliding sleeve assembly can be further optimized and improved, and the embodiment adopts one feasible option: the sliding sleeve assembly further comprises a fixing ring 4, the fixing ring 4 is rotatably arranged on the sliding sleeve 14 through a bearing, and the fixing ring 4 and the sliding sleeve 14 are relatively fixed in the axial direction; the driving assembly is connected with the fixing ring 4 and pushes the fixing ring 4 to move back and forth along the axial direction of the tail rotor shaft 13. When the scheme is adopted, the fixing ring 4 and the sliding sleeve 14 rotate relatively, but the fixing ring 4 can adjust the position of the sliding sleeve 14 in the axial direction of the tail rotor shaft 13, so that the variable-pitch adjustment is realized.
Preferably, in the present embodiment, two bearings are disposed between the fixed ring 4 and the sliding sleeve 14.
In order to reduce the jamming caused by the foreign matters entering between the sliding sleeve assembly and the tail rotor shaft 13, the structure of the sliding sleeve assembly is optimized, and the following feasible options are provided: the sliding sleeve assembly further comprises a plurality of dust covers 8, and the dust covers 8 are arranged at the front end or the rear end of the sliding sleeve assembly and wrap the sliding fit sections covering the sliding sleeve assembly and the tail rotor shaft 13. When adopting such scheme, dust cover 8 is the flexible cover, and when the sliding sleeve subassembly took place axial displacement along tail rotor shaft 13, dust cover 8 also still can cover the protection with sliding fit section.
Preferably, in this embodiment, the dust cover 8 is made of a rubber material, and the dust cover 8 is a telescopic elastic sleeve structure, and can stretch under its own elastic action.
In the actual pitch adjustment, the driving assembly drives the sliding sleeve assembly, and the driving assembly can adopt a plurality of feasible options, which are not limited only, and the embodiment is optimized and adopts one feasible option: the driving assembly comprises a corner rocker arm 2, the middle of the corner rocker arm 2 is arranged at a fixed hinged position, the front end of the corner rocker arm 2 is hinged with a fixed ring 4, the rear end of the corner rocker arm 2 is hinged with an adjusting pull rod 1, and the adjusting pull rod 1 is connected to the driver. When the scheme is adopted, a hinge joint is arranged on one fixed part of the tail rotor system and is used for connecting the corner rocker arm 2 to serve as a supporting point of the corner rocker arm 2.
Preferably, the steering engine is arranged to be matched with the adjusting pull rod 1 in the embodiment, the steering engine is used for adjusting the adjusting pull rod 1 in a telescopic matching mode, and the reciprocating displacement of the sliding sleeve assembly on the tail rotor shaft 13 is achieved through transmission of the corner rocker arm 2. Wherein, the hinged position of the middle part of the corner rocker arm 2 is arranged on the speed reducer 3.
In order to improve the smoothness of the adjusting pull rod 1 in the adjusting process and avoid the situation that the driving assembly is stuck in the process of pushing the sliding sleeve assembly, the structure of the corner rocker arm 2 can be optimized and improved, and the embodiment adopts one of the feasible options: and a bearing is arranged at the hinged position of the middle part of the corner rocker arm 2. When adopting such scheme, set up the dead eye on the turning rocking arm 2, the inner circle and the articulated shaft of bearing are connected the cooperation, and the outer lane and the turning rocking arm 2 of bearing are connected the cooperation. In this embodiment, the middle part of turning rocking arm 2 is articulated with reduction gear 3 and rotates along articulated department, and solid fixed ring 4's surface is provided with the articulated shaft, and the cell body and the articulated shaft cooperation are established to the front end of turning rocking arm 2, and when turning rocking arm 2 rotated, the cell body of its front end and articulated shaft cooperation back turning rocking arm 2 made solid fixed ring 4 drive sliding sleeve 14 along the tail rotor axle back-and-forth movement through promoting the articulated shaft, and articulated shaft and cell body relative slip. In other embodiments, the hinge shaft on the fixing ring 4 can be exchanged with the slot body on the corner rocker arm 2, that is, the slot body is arranged on the fixing ring 4, and the hinge shaft is arranged on the corner rocker arm, so that the same adjustment purpose can be achieved.
In this embodiment, the variable pitch hinge assembly 9 is used to connect and set a tail rotor blade, specifically, as shown in fig. 3 and 4, which is optimized and one of the possible options is shown: the variable-pitch hinge assembly 9 comprises a variable-pitch hinge shell 902 and a variable-pitch hinge cover 901 which are rotatably arranged on the support arm 12, wherein the variable-pitch hinge shell 902 is relatively and fixedly connected with the variable-pitch hinge cover 901; the variable pitch pull rod 7 is hinged with a variable pitch hinge cover 901 or a variable pitch hinge shell 902, and the tail rotor blade is arranged on the variable pitch hinge shell 902. When the scheme is adopted, the number of the variable-pitch hinge shells 902 is at least two, more variable-pitch hinge shells can be arranged according to actual requirements, and each variable-pitch hinge can be connected with one blade.
Preferably, the corner rocker arm 2 used in this embodiment is a 90 ° corner.
When specifically adopting the disclosed pitch regulation manipulation structure of this embodiment, through the steering wheel to unmanned aerial vehicle to send the instruction, the steering wheel received the instruction and carries out the action, drives adjusting pull rod 1 and carries out the back-pull or pushes forward, and then turning rocking arm 2 turns into the action the advancing or retreating action of sliding sleeve 14, and sliding sleeve 14's action drives the action of displacement pull rod and promotes the displacement hinge subassembly and change, and displacement hinge casing 902 of displacement hinge subassembly takes place reciprocal rotation around support arm 12 to this regulation that realizes the pitch.
The above embodiments are just exemplified in the present embodiment, but the present embodiment is not limited to the above alternative embodiments, and those skilled in the art can obtain other various embodiments by arbitrarily combining with each other according to the above embodiments, and any other various embodiments can be obtained by anyone in light of the present embodiment. The above detailed description should not be construed as limiting the scope of the present embodiments, which should be defined in the claims, and the description should be used for interpreting the claims.
Claims (10)
1. The utility model provides a structure is controld in regulation of unmanned helicopter tail-rotor pitch which characterized in that: the tail rotor propeller comprises a tail rotor shaft (13), wherein the tail end of the tail rotor shaft (13) is connected with a tail rotor hub central part (11), a plurality of support arms (12) are arranged on the tail rotor hub central part (11), and variable-pitch hinge assemblies (9) used for connecting tail blades and adjusting the pitches of the tail blades are arranged on the support arms (12); a sliding sleeve component which synchronously rotates with the tail propeller shaft (13) and slides along the axial direction of the tail propeller shaft is arranged on the tail propeller shaft, and a plurality of variable-pitch pull rods (7) are connected between the sliding sleeve component and the variable-pitch hinge component (9); the adjustment and manipulation structure further comprises a driving assembly for driving the sliding sleeve assembly to axially reciprocate.
2. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 1, wherein: the sliding sleeve assembly comprises a sliding sleeve (14) which is arranged on a tail propeller shaft (13) in a sliding mode and synchronously rotates with the tail propeller shaft (13), a fork-shaped piece (5) which is fixed relative to the sliding sleeve (14) is arranged on the sliding sleeve (14), a plurality of connecting bosses (501) are arranged on the fork-shaped piece (5), one end of a variable-pitch pull rod (7) is matched with the connecting bosses (501), and the other end of the variable-pitch pull rod (7) is hinged to a variable-pitch hinge assembly (9) and drives the variable-pitch hinge assembly (9).
3. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 2, wherein: the cross section of the tail propeller shaft (13) is in an oval shape, a polygonal shape or a shape combining the polygonal shape and the arc shape, the end face of the sliding sleeve (14) is provided with a circumference positioning block (10), the circumference positioning block (10) abuts against the surface of the tail propeller shaft (13), and the circumference positioning block (10) is relatively fixedly connected with the sliding sleeve (14) and drives the sliding sleeve (14) to rotate synchronously.
4. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 2, wherein: the cross section of the tail propeller shaft (13) is in an oval shape, a polygonal shape or a shape combining the polygonal shape and the arc shape, and a sleeve hole correspondingly matched with the tail propeller shaft (13) is formed in the sliding sleeve (14).
5. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 2, wherein: and a meshing structure or a clamping structure in the circumferential direction is arranged between the tail rotor shaft (13) and the sliding sleeve (14).
6. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 2, wherein: the sliding sleeve assembly further comprises a fixing ring (4), the fixing ring (4) is rotatably arranged on the sliding sleeve (14) through a bearing, and the fixing ring (4) and the sliding sleeve (14) are relatively fixed in the axial direction; the driving assembly is connected with the fixing ring (4) and pushes the fixing ring (4) to move back and forth along the axial direction of the tail rotor shaft (13).
7. The unmanned helicopter tail rotor pitch control structure of any one of claims 1-6, characterized in that: the sliding sleeve assembly further comprises a plurality of dust covers (8), and the dust covers (8) are arranged at the front end or the rear end of the sliding sleeve assembly and wrap the sliding fit sections covering the sliding sleeve assembly and the tail propeller shaft (13).
8. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 6, wherein: the driving assembly comprises a corner rocker arm (2), the middle of the corner rocker arm (2) is arranged at a fixed hinged position, the front end of the corner rocker arm (2) is hinged to a fixed ring (4), the rear end of the corner rocker arm (2) is hinged to an adjusting pull rod (1), and the adjusting pull rod (1) is connected to the driver.
9. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 8, wherein: and a bearing is arranged at the hinged position in the middle of the corner rocker arm (2).
10. The unmanned helicopter tail rotor pitch modulation manipulation structure of claim 1, wherein: the variable-pitch hinge assembly (9) comprises a variable-pitch hinge shell (902) and a variable-pitch hinge cover (901) which are rotatably arranged on the support arm (12), and the variable-pitch hinge shell (902) is relatively and fixedly connected with the variable-pitch hinge cover (901); the variable-pitch pull rod (7) is hinged with the variable-pitch hinge pressing cover (901) or the variable-pitch hinge shell (902), and the tail rotor blade is arranged on the variable-pitch hinge shell (902).
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| CN202110707491.3A CN113247240A (en) | 2021-06-25 | 2021-06-25 | Unmanned helicopter tail rotor pitch adjusting and operating structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275148A (en) * | 2022-01-13 | 2022-04-05 | 广东汇天航空航天科技有限公司 | Control method and system of aircraft, aircraft and computing equipment |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| GB611398A (en) * | 1946-01-09 | 1948-10-28 | Pierre Jayer | Lifting rotors with variable pitch blades and aircraft provided with rotors |
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| US20070123107A1 (en) * | 2005-11-29 | 2007-05-31 | Eurocopter | Anti-impact shield for a mechanical part |
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| CN205589477U (en) * | 2016-05-05 | 2016-09-21 | 武汉捷特航空科技有限公司 | Unmanned helicopter rotor head |
| CN206384149U (en) * | 2016-11-25 | 2017-08-08 | 深圳光启空间技术有限公司 | Variable-pitch transmission gear |
| CN209142380U (en) * | 2018-11-14 | 2019-07-23 | 天峋创新（北京）科技有限公司 | A kind of unmanned helicopter tail rotor pitch control |
| CN112896502A (en) * | 2021-03-04 | 2021-06-04 | 四川腾盾科技有限公司 | Unmanned helicopter rotor displacement hinge structure |
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| GB611398A (en) * | 1946-01-09 | 1948-10-28 | Pierre Jayer | Lifting rotors with variable pitch blades and aircraft provided with rotors |
| GB2050978A (en) * | 1979-05-24 | 1981-01-14 | Ampep Ltd | Rotary assembly, particularly a helicopter tail rotor |
| US20070123107A1 (en) * | 2005-11-29 | 2007-05-31 | Eurocopter | Anti-impact shield for a mechanical part |
| CN101134506A (en) * | 2007-08-27 | 2008-03-05 | 万涛 | Helicopter rotor control mechanism |
| CN205524955U (en) * | 2016-02-05 | 2016-08-31 | 湖南省库塔科技有限公司 | Variable -pitch propeller oar and unmanned aerial vehicle |
| CN205524970U (en) * | 2016-02-26 | 2016-08-31 | 天峋创新（北京）科技有限公司 | Three rotor tail -rotor hubs of unmanned helicopter |
| CN205589477U (en) * | 2016-05-05 | 2016-09-21 | 武汉捷特航空科技有限公司 | Unmanned helicopter rotor head |
| CN206384149U (en) * | 2016-11-25 | 2017-08-08 | 深圳光启空间技术有限公司 | Variable-pitch transmission gear |
| CN209142380U (en) * | 2018-11-14 | 2019-07-23 | 天峋创新（北京）科技有限公司 | A kind of unmanned helicopter tail rotor pitch control |
| CN112896502A (en) * | 2021-03-04 | 2021-06-04 | 四川腾盾科技有限公司 | Unmanned helicopter rotor displacement hinge structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114275148A (en) * | 2022-01-13 | 2022-04-05 | 广东汇天航空航天科技有限公司 | Control method and system of aircraft, aircraft and computing equipment |
| CN114275148B (en) * | 2022-01-13 | 2024-02-20 | 广东汇天航空航天科技有限公司 | Control method and system of aircraft, aircraft and computing equipment |
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Application publication date: 20210813 |