CN217100460U - Tail rotor driving device and helicopter - Google Patents

Abstract

The utility model provides a tail-rotor drive arrangement and helicopter. The tail rotor driving device comprises a blade assembly, a direct-drive assembly and a variable pitch assembly. The blade assembly comprises a tail rotor blade, the direct-drive assembly comprises a first driving unit and a first transmission mechanism, and the variable-pitch assembly comprises a second driving unit and a second transmission mechanism. The first driving unit drives the first transmission mechanism to drive the tail rotor blade to do circular motion along a first plane, and tail power perpendicular to the first plane is generated. The second driving unit drives the second transmission mechanism to adjust an included angle between the tail rotor blade and the first plane so as to adjust the size and the direction of the tail power. The tail rotor driving device adjusts the pitch of the tail rotor blades through the variable pitch assembly, so that positive and negative torque output is realized, and the tail locking effect is good when the helicopter flies at a large pitch.

Description

Tail rotor driving device and helicopter

Technical Field

The utility model relates to a helicopter field, concretely relates to tail-rotor drive arrangement and helicopter.

Background

The helicopter tail rotor is used for balancing the reactive torque which is generated when the main rotor of the helicopter rotates and acts on the fuselage, and is an important component for stabilizing the fuselage and adjusting the heading.

Fig. 1 is a schematic perspective view of a helicopter according to the prior art. The helicopter 200 comprises a fuselage 201, a main rotor 202 and a tail rotor 203. When the helicopter 200 is locked, the main rotor 202 rotates to generate a reaction torque acting on the fuselage 201, and the tail rotor 203 is required to provide a tail power F with the same magnitude as the reaction torque and in the opposite direction to balance the reaction torque. When helicopter 200 locks the tail under different states, because main oar 202 rotational speed and direction are different, produce reaction torque size and direction are different, need tail rotor 203 provides tail power F size and direction are different, consequently need tail rotor 203 follows the different tail power F of size is exported to the left and right sides of fuselage 201.

In the prior art, direct drive of the tail rotor 203 is unidirectional power output, so that the tail locking effect of a helicopter directly driven by the tail rotor 203 is poor when the helicopter frequently flies at a large pitch. And the tail rotor 203 directly drives the motor to rotate by means of electric regulation, the rotating speed of the motor is controlled and regulated by the electric regulation according to the flight attitude of the airplane, and then the rotating speed of the tail rotor 203 is regulated, so that the tail power F for balancing the reactive torque provided by the tail rotor 203 is regulated. The electric regulation control frequency is limited, and the range of the tail power F for balancing the reaction torque provided by the tail rotor 203 driven by the electric regulation direct drive motor is limited.

Therefore, there is a need to provide a new helicopter tail rotor driving device to solve the above problems.

SUMMERY OF THE UTILITY MODEL

The utility model discloses a solve prior art helicopter tail-rotor and adopt the electricity to adjust directly to drive, the tail power of tail-rotor output only is the little technical problem of one-way output and moment scope, provides a tail-rotor drive arrangement of tail power both way output and moment scope.

Simultaneously the utility model also provides an adopt above-mentioned tail-rotor drive arrangement's helicopter.

The utility model discloses the first aspect provides a tail-rotor drive arrangement, include the paddle subassembly, directly drive subassembly and displacement subassembly. The blade assembly includes a tail rotor blade. The direct-drive assembly comprises a first drive unit and a first transmission mechanism, and the first drive unit drives the tail rotor blades to do circular motion along a first plane through the first transmission mechanism. The pitch-variable assembly comprises a second driving unit and a second transmission mechanism, and the second driving unit drives the second transmission mechanism to adjust an included angle between the tail rotor blade and the first plane.

Preferably, the second drive mechanism includes a variable-pitch disc and a variable-pitch disc sleeve, the variable-pitch disc is sleeved on the first drive mechanism and connected with the tail rotor blade, and the variable-pitch disc sleeve is sleeved on the variable-pitch disc.

Preferably, the second transmission mechanism further comprises a variable pitch disc rotating member, and the variable pitch disc rotating member is arranged between the variable pitch disc and the variable pitch disc sleeve.

Preferably, the second transmission mechanism further comprises a rotating connecting piece and a connecting rod, the rotating connecting piece is connected with the variable-pitch disc sleeve, one end of the connecting rod is connected with the rotating connecting piece, and the other end of the connecting rod is connected with the second driving unit.

Preferably, the rotation link includes a first link arm, a second link arm, and a rotation portion. The first connecting arm is connected with the connecting rod, the second connecting arm is connected with the variable-pitch disc, and the first connecting arm and the second connecting arm are connected with the rotating part.

Preferably, the second transmission mechanism further comprises a fixed seat, and one end of the fixed seat is hinged to the rotating part.

Preferably, the tail rotor driving device further comprises a supporting component, and one end, far away from the rotating part, of the fixing seat is fixedly arranged on the supporting component.

Preferably, the blade assembly further includes a tail rotor shaft and a tail rotor clip, the tail rotor clip is disposed on the tail rotor shaft, the tail rotor blade is fixed to the tail rotor shaft through the tail rotor clip, one end of the first transmission mechanism is connected to the tail rotor shaft, and the other end of the first transmission mechanism is connected to the first driving unit.

Preferably, the tail rotor blade clamp includes radial connecting portion, radial connecting portion with the displacement dish is connected, the displacement dish is followed first drive mechanism extending direction slides, drives the tail rotor blade clamp around the tail rotor blade axle is rotatory.

A second aspect of the present invention provides a helicopter, comprising the first aspect of the present invention provides a tail rotor driving device.

Compared with the prior art, the utility model discloses a helicopter includes tail-rotor drive arrangement, tail-rotor drive arrangement includes the supporting component, directly drives subassembly, displacement subassembly and paddle subassembly, wherein, the paddle subassembly includes the tail-rotor paddle. The tail rotor driving device drives the first transmission mechanism to rotate through the first driving unit of the direct-drive assembly, and then drives the tail rotor blades connected with the first transmission mechanism to do circular motion in a first plane so as to generate tail power perpendicular to the plane. First drive unit passes through first drive mechanism with power transmission extremely the tail-rotor paddle, the power that first drive unit provided does not pass through gear or belt drive, direct output extremely the tail-rotor paddle, no power loss, the noise is little, and does not have gear and belt drive and has reduced part quantity, makes helicopter simple to operate, later stage maintenance are simple.

The tail rotor driving device drives a second transmission mechanism to adjust the pitch of the tail rotor blades through a second driving unit of the variable-pitch assembly. First drive unit is with the constant speed output, through the displacement subassembly adjustment tail oar paddle pitch changes the size and the direction of tail power realize the positive and negative moment output of tail power makes the helicopter is effectual at the lock tail when the flight of coarse pitch.

Drawings

FIG. 1 is a schematic perspective view of a helicopter of the prior art;

FIG. 2 is a schematic perspective view of a helicopter according to the present invention;

FIG. 3 is a schematic perspective view of the tail rotor drive of FIG. 2;

FIG. 4 is an exploded view of the tail rotor drive arrangement of FIG. 3;

FIG. 5 is a perspective view of the tail rotor shaft of FIG. 4;

FIG. 6 is a perspective view of the pivotal connection illustrated in FIG. 4;

FIG. 7 is a perspective view of the variable pitch disk sleeve of FIG. 4;

FIG. 8a is a schematic view of the relationship of the tail rotor blade of FIG. 3 to a first plane;

FIG. 8b is another state schematic view of the tail rotor blade of FIG. 3 with a first plane;

fig. 8c is a schematic view of a further state of the tail rotor blade of fig. 3 with the first plane.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely below, and it should be apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

Please refer to fig. 2, which is a schematic diagram of a three-dimensional structure of a helicopter according to the present invention. The helicopter 100 comprises a main body 10 and a tail rotor drive 30. The tail rotor driving device 30 is used for stabilizing the orientation of the main body 10 and adjusting the heading of the helicopter 100. The flight space in which the helicopter 100 is located is defined as a three-dimensional space defined by mutually perpendicular x, y and z axes.

The main body 10 is a core component of the helicopter 100, and generally includes a main blade 11, a main blade power assembly (not shown), a transmission assembly (not shown), and a data acquisition device (not shown).

Please refer to fig. 3, which is a schematic perspective view of the tail rotor driving device shown in fig. 2. The tail rotor driving device 30 comprises a supporting assembly 31, a direct-drive assembly 33, a variable-pitch assembly 35 and a blade assembly 37, wherein the blade assembly 37 comprises a tail rotor blade 371. The support assembly 31 supports the direct drive assembly 33, the pitch assembly 35 and the blade assembly 37. The direct drive assembly 33 drives the blade assembly 37 to rotate to generate tail power F so as to balance the reaction torque acting on the main body 10 when the main blades 11 of the helicopter 100 rotate, so that the helicopter 100 is in a steady state. The pitch changing assembly 35 is used for adjusting the magnitude and direction of the tail power F generated by the tail rotor blades 371.

The supporting assembly 31 includes a tail beam 311, a first fixing plate 313, a second fixing plate 315, and a supporting plate 317, wherein one end of the tail beam 311 is fixedly disposed on the main body 10. The side of helicopter 100 close to main rotor 11 is defined as the upper side, and the side far from main rotor 11 is defined as the lower side. One end of the supporting plate 317 is connected to the end of the tail boom 311 far away from the main body 10, and the other end of the supporting plate 317 extends to the lower side of the tail boom 311, so as to support the helicopter 100 when landing, and protect the tail rotor driving device 30. The first fixing plate 313 and the second fixing plate 315 are arranged in parallel at intervals, and one ends of the first fixing plate 313 and the second fixing plate 315 are both fixedly arranged at one end of the tail beam 311 far away from the main body 10. An interlayer space is formed between the first fixing plate 313 and the second fixing plate 315.

Referring to fig. 2, fig. 3 and fig. 4, fig. 4 is an exploded view of the tail rotor driving apparatus shown in fig. 3.

The direct drive assembly 33 includes a first drive unit 331 and a first transmission mechanism 333, in this embodiment, the first drive unit 331 is a motor. The first driving unit 331 is disposed in an interlayer space formed between the first fixing plate 313 and the second fixing plate 315, and the first driving unit 331 is fixedly disposed in the second fixing plate 315 such that the first fixing plate 313 and the second fixing plate 315 protect the first driving unit 331. The first fixing plate 313 is provided with an avoiding hole, the first transmission mechanism 333 penetrates through the avoiding hole of the first fixing plate 313, and one end of the first transmission mechanism 333 is connected with the first driving unit 331. An end of the first transmission mechanism 333 away from the first driving unit 331 is provided with a fixing plane 3331 for fixing the blade assembly 37.

The blade assembly 37 further includes a tail rotor shaft 373, a tail rotor clip 375, and a blade clip rotor 377, wherein the tail rotor blade 371 is secured to the tail rotor shaft 373 via the tail rotor clip 375.

Please refer to fig. 5, which is a schematic perspective view of the shaft of the tail rotor shown in fig. 4. The tail paddle shaft 373 is provided with a connection through hole 3731 and a fixing through hole 3733, the first transmission mechanism 333 penetrates through the connection through hole 3731, the fixing plane 3331 is exposed out of the fixing through hole 3733, the fixing through hole 3733 is provided with a fixing screw 3735, the plane of the fixing screw 3735 abuts against the fixing plane 3331, so that the tail paddle shaft 373 is fixedly arranged at one end of the first transmission mechanism 333 away from the first driving unit 331. The number of the tail rotor clips 375 is two, the tail rotor clips 375 are respectively sleeved on the tail rotor shaft 373, and the tail rotor clips 375 are located on two sides of the connecting through hole 3731. One end of the tail rotor clamp 375, which is far away from the first transmission mechanism 333, is connected with the tail rotor blade 371. A connection point of the tail rotor shaft 373 and the first transmission mechanism 333 (i.e., a central point between the tail rotor blades 371) is defined as an origin O of a three-dimensional space defined by an x-axis, a y-axis and a z-axis which are perpendicular to each other, the first transmission mechanism 333 is arranged along the y-axis direction, the first driving unit 331 drives the first transmission mechanism 333 to rotate, and further drives the tail rotor blades 371 to circumferentially move around the first transmission mechanism 333 with the O-point as a center, that is, the tail rotor blades 371 rotate in a first plane passing through the O-point formed by the x-axis and the z-axis, so as to generate the tail motive force F perpendicular to the first plane.

The tail rotor rotating member 377 is disposed between the tail rotor grip 375 and the tail rotor shaft 373. In this embodiment, the tail rotor rotating member 377 is a bearing, the tail rotor driving member 377 is sleeved on the tail rotor shaft 373, and the tail rotor clip 375 is sleeved on the tail rotor driving member 377, so that the tail rotor clip 375 can rotate around the tail rotor shaft 373. When the tail rotor clip 375 rotates around the tail rotor shaft 373, the tail rotor blade 371 is driven to rotate around the tail rotor shaft 373, so as to change the pitch of the tail rotor blade 371, that is, change the included angle between the tail rotor blade 371 and the first plane. One end of the tail rotor clamp 375 close to the first transmission mechanism 333 is provided with a radial connecting portion 3751.

The pitch-varying assembly 35 includes a second driving unit 351 and a second transmission mechanism 353, wherein the second driving unit 351 is fixedly disposed on the main body 10, and in this embodiment, the second driving unit 351 is a servo motor. The second transmission mechanism 353 includes a link 3531, a rotary connector 3533, a pitch disc sleeve 3535, a pitch disc rotary member 3536, a pitch disc 3537, and a transmission rod 3539. The link 3531 is disposed along the extending direction of the tail boom 311, and one end of the link 3531 is connected to the second driving unit 351, and the other end is connected to the rotary connector 5353.

Please refer to fig. 6, which is a schematic perspective view of the rotational connector shown in fig. 4. The rotary link 3533 includes a rotary portion 3533A, a first link arm 3533B and a second link arm 3533C, and the first link arm 3533B and the second link arm 3533C are connected to the rotary portion 3533A. One end of the second connecting arm 3533C, which is far away from the rotating portion 3533A, is arc-shaped, and protrusions 3533D are arranged at two ends of the arc-shaped. The fixing portion 3534 is fixed to the first fixing plate 313 at one end and hinged to the rotating portion 3533A at the other end, so that the first connecting arm 3533B and the second connecting arm 3533C can rotate around the connecting portion 3533A.

The variable-pitch disc sleeve 3535, the variable-pitch disc rotating piece 3536 and the variable-pitch disc 3537 are sequentially sleeved from outside to inside on the first transmission mechanism 333, in the embodiment, the variable-pitch disc rotating piece 3536 is a bearing and is arranged between the variable-pitch disc sleeve 3535 and the variable-pitch disc 3537, so that the variable-pitch disc 3537 rotates along with the first transmission mechanism 333, and the variable-pitch disc sleeve 3535 does not rotate along with the first transmission mechanism 333.

Please refer to fig. 7, which is a schematic perspective view of the distance-changing disc sleeve shown in fig. 4. Two grooves 3535A are arranged on the outer side surface of the variable-pitch disc sleeve 3535, and the protrusions 3533D are clamped in the two grooves 3535A.

The variable-pitch disc 3537 is correspondingly provided with two variable-pitch disc connecting arms 3537A, the two variable-pitch disc connecting arms 3537A are respectively connected with the radial connecting portion 3751 through transmission rods 3539, one end of each transmission rod 3539 is hinged with the radial connecting portion 3751, and the other end of each transmission rod 3539 is hinged with the two variable-pitch disc connecting arms 3537A. When the variable-pitch disc 3537 slides along the extending direction of the first transmission mechanism 333, that is, when the variable-pitch disc 3537 slides along the y-axis direction, the radial connecting portion 3751 is driven to rotate around the tail rotor shaft 373, the tail rotor clamp 375 is further driven to rotate around the tail rotor shaft 373, and the tail rotor blade 371 is further driven to rotate around the tail rotor shaft 373, so as to change the pitch of the tail rotor blade 371, that is, change the included angle between the tail rotor blade 371 and the first plane.

Referring to fig. 8a, 8b and 8c, fig. 8a is a schematic view of a relationship between the tail rotor blade shown in fig. 3 and the first plane, fig. 8b is a schematic view of another state between the tail rotor blade shown in fig. 3 and the first plane, and fig. 8c is a schematic view of another state between the tail rotor blade shown in fig. 3 and the first plane.

As shown in fig. 8a, when the tail rotor blade 371 is parallel to the first plane formed by the x-axis and the z-axis passing through the point O, the included angle between the tail rotor blade 371 and the first plane is 0 °. As shown in fig. 8b, after the tail rotor blade 371 rotates around the tail rotor shaft 373, the included angle between the tail rotor blade 371 and the first plane changes from 0 ° to α. As shown in fig. 8c, after the tail rotor blade 371 rotates around the tail rotor shaft 373, an included angle between the tail rotor blade 371 and the first plane may also be α'. When the tail rotor blade 371 uses the point O as a center, the directions of circumferential movement around the first transmission mechanism 333 in the first plane are the same, and the tail power F directions generated by the tail rotor blade 371 shown in fig. 8b and the tail rotor blade 371 shown in fig. 8c are opposite.

The pitch principle of the pitch assembly 35: the second driving unit 351 drives the link 3531 to move in a direction parallel to the extending direction of the link 3531, such that the first link arm 3533B connected with the link 3531 rotates around the rotating portion 3533A, and thus drives the second link arm 3533C to rotate around the rotating portion 3533A. The second connecting arm 3533C drives the variable-pitch disc sleeve 3535 and the variable-pitch disc 3537 arranged in the variable-pitch disc sleeve 3535 slide along the extending direction of the first transmission mechanism 333, and further drives the tail rotor clamp 375 to rotate around the tail rotor shaft 373 so as to drive the tail rotor blade 371 to rotate around the tail rotor shaft 373, and further adjusts the included angle between the tail rotor blade 371 and the first plane, so that variable pitch is realized. The magnitude and direction of the tail power F are adjusted by the pitch-changing assembly 35, so that the direction of the tail power F can be positive direction of the y-axis or negative direction of the y-axis.

Compared to the prior art, the helicopter 100 disclosed in the present invention comprises a tail rotor driving device 30, said tail rotor driving device 30 comprises a supporting component 31, a direct driving component 33, a variable pitch component 35 and a blade component 37, wherein said blade component 37 comprises a tail rotor blade 371. The tail rotor driving device 30 drives the first transmission mechanism 333 to rotate through the first driving unit 331 of the direct drive assembly 33, and further drives the tail rotor blade 371 connected with the first transmission mechanism 333 to make a circular motion in a first plane, so as to generate a tail power F perpendicular to the first plane. First drive unit 331 passes through first drive mechanism 333 with power transmission extremely tail-rotor paddle 371, the power that first drive unit 331 provided is not through gear or belt drive, directly exports to tail-rotor paddle 371, no power loss, the noise is little, and does not have gear and belt drive and has reduced part quantity, makes helicopter 100 simple to operate, later maintenance are simple.

The tail rotor driving device 30 drives the second transmission mechanism 353 through the second driving unit 351 of the pitch changing assembly 35 to adjust the pitch of the tail rotor blade 371. First drive unit 331 is exported with the constant speed, through displacement subassembly 35 adjusts tail oar paddle 371 pitch changes tail power F's size and direction realize tail power F's positive and negative moment output makes helicopter 100 is effectual at the lock tail when the flight of coarse pitch.

The above only is the partial embodiment of the present invention, not therefore the limitation of the patent scope of the present invention, all the equivalent structures or equivalent flow changes made by the contents of the specification and the drawings, or directly or indirectly applied to other related technical fields, are included in the patent protection scope of the present invention.

Claims (10)

1. A tail rotor drive arrangement, includes the paddle subassembly, the paddle subassembly includes the tail rotor paddle, its characterized in that, tail rotor drive arrangement still includes:

the direct-drive assembly comprises a first drive unit and a first transmission mechanism, and the first drive unit drives the tail rotor blade to do circular motion along a first plane through the first transmission mechanism; and

the variable pitch assembly comprises a second driving unit and a second transmission mechanism, the second driving unit drives the second transmission mechanism to adjust the included angle between the tail rotor blade and the first plane.

2. The tail rotor drive of claim 1, wherein the second transmission mechanism includes a pitch disc and a pitch disc sleeve, the pitch disc being sleeved on the first transmission mechanism and being connected to the tail rotor blade, the pitch disc sleeve being sleeved on the pitch disc.

3. The tail rotor drive of claim 2, wherein the second transmission further comprises a pitch disk rotating member disposed between the pitch disk and the pitch disk sleeve.

4. The tail rotor driving device according to claim 2, wherein the second transmission mechanism further comprises a rotary connecting member and a connecting rod, the rotary connecting member is connected with the variable pitch disc sleeve, one end of the connecting rod is connected with the rotary connecting member, and the other end of the connecting rod is connected with the second driving unit.

5. The tailrotor drive of claim 4, wherein the rotational coupling comprises:

a first connecting arm connected with the connecting rod;

the second connecting arm is connected with the variable-pitch disc; and

a rotating portion, the first connecting arm and the second connecting arm are connected with the rotating portion.

6. The tail rotor drive of claim 5, wherein the second transmission mechanism further comprises a fixed seat, one end of the fixed seat being hinged to the rotating portion.

7. The tail rotor driving device according to claim 6, further comprising a support assembly, wherein an end of the fixing base away from the rotating portion is fixedly disposed on the support assembly.

8. The tail rotor driving device according to claim 2, wherein the blade assembly further includes a tail rotor shaft and a tail rotor clip, the tail rotor clip is disposed on the tail rotor shaft, the tail rotor blade is fixed to the tail rotor shaft by the tail rotor clip, one end of the first transmission mechanism is connected to the tail rotor shaft, and the other end of the first transmission mechanism is connected to the first driving unit.

9. The tail rotor drive of claim 8, wherein the tail rotor clip includes a radial link portion that is coupled to the pitch disk, the pitch disk sliding along a direction of extension of the first drive mechanism to rotate the tail rotor clip about the tail rotor shaft.

10. A helicopter comprising a tail rotor drive as claimed in any one of claims 1 to 9.

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