CN105501434A - Helicopter tail rotor torque changing operating mechanism - Google Patents
Helicopter tail rotor torque changing operating mechanism Download PDFInfo
- Publication number
- CN105501434A CN105501434A CN201610059206.0A CN201610059206A CN105501434A CN 105501434 A CN105501434 A CN 105501434A CN 201610059206 A CN201610059206 A CN 201610059206A CN 105501434 A CN105501434 A CN 105501434A
- Authority
- CN
- China
- Prior art keywords
- rotor
- bending moment
- tail
- rockerarm
- pitch control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
- B64C11/44—Blade pitch-changing mechanisms electric
Abstract
The invention discloses a helicopter tail rotor torque changing operating mechanism which comprises a rotor wing shaft, a torque changing plate, a motor, a tail rotor torque changing operating assembly and a steering engine. The rotor wing shaft is provided with a tail rotor extending in the radial direction of the rotor wing shaft, and the tail rotor can rotate around the axis of the rotor wing shaft; the torque changing plate is movably arranged on the rotor wing shaft in the axial direction of the rotor wing shaft to drive the torque of the tail rotor to be changed; the motor is connected with the rotor wing shaft to drive the rotor wing shaft to rotate; the tail rotor torque changing operating assembly is connected with the torque changing plate to drive the torque changing plate to move; the steering engine is connected with the tail rotor torque changing operating assembly to enable the tail rotor torque changing operating assembly to drive the torque of the tail rotor to be changed. According to the helicopter tail rotor torque changing operating mechanism, by arranging the tail rotor torque changing operating assembly on the rotor wing shaft, the purpose of driving the torque of the tail rotor to be changed can be achieved; operation is easy, and the using reliability is high. The helicopter tail rotor torque changing operating mechanism is simple and compact in structure, easy to machine and manufacture, low in cost, smaller in operation gap among all the parts, more reliable in force transferring path, continuous in movement and accurate in transmission.
Description
Technical field
The present invention relates to technical field of aerospace, more specifically, relate to a kind of helicopter tail rotor bending moment steering unit.
Background technology
The tail-rotor bending moment mechanism of the helicopter in correlation technique, uses the bulb bearing of the other end of servo driving L-type rocking arm, thus realizes driving tail-rotor blade bending moment rim rotor shaft and move up and down, and then realizes blade bending moment.Path of motion due to L-type rocking arm end itself is one section of circular arc in the center of circle around L-type point of transition place, if do not use bulb bearing, then slide block is when moving up and down, and rocking arm will produce the thrust being applied to rotor shaft radial direction.But bulb bearing in use for some time, can produce movement clearance due to friction, thus affect the manipulation of blade bending moment, and due to the size of bulb bearing own less, when the actuating force of needs is larger, there will be insufficient strength problem.
Summary of the invention
The present invention is intended to solve one of technical matters in correlation technique at least to a certain extent.For this reason, the present invention proposes a kind of helicopter tail rotor bending moment steering unit, and the structure of this helicopter tail rotor bending moment steering unit is simple, connects reliably, and simple to operate, motion is coherent, transmission is accurate.
According to the helicopter tail rotor bending moment steering unit of the embodiment of the present invention, comprising: rotor shaft, described rotor shaft is provided with the tail-rotor radially extended, and described tail-rotor is rotatable around the axis of described rotor shaft; Bending moment dish, the axis of rotor shaft described in described bending moment rim is located in described rotor shaft movably to drive described tail-rotor bending moment; Motor, described motor is connected with described rotor shaft to drive described rotor shaft to rotate; Tail-rotor bending moment handles assembly, and described tail-rotor bending moment is handled assembly and is connected to drive described bending moment disk activity with described bending moment dish; Steering wheel, described steering wheel and described tail-rotor bending moment are handled assembly and are connected to make described tail-rotor bending moment handle tail-rotor bending moment described in Component driver.
According to the helicopter tail rotor bending moment steering unit of the embodiment of the present invention, handle assembly by arranging tail-rotor bending moment in rotor shaft, can realize the object driving tail-rotor bending moment, simple to operate, reliability of service is high.The structure of this helicopter tail rotor bending moment steering unit is simple, compact, processing, easy to manufacture, and cost is low, each parts connect reliable, operating clearance is less, Path of Force Transfer is more reliable, motion is coherent, transmission is accurate.
In addition, according to the helicopter tail rotor bending moment steering unit of the embodiment of the present invention, following additional technical characteristic can also be had:
According to one embodiment of present invention, also comprise rotor axle sleeve, described rotor shaft to be set in described rotor shaft and axially movable along described rotor shaft, and described bending moment dish is located at described rotor shaft and puts.
According to one embodiment of present invention, described tail-rotor bending moment is handled assembly and is comprised: fixing rocker arm support, and described fixing rocker arm support is located on described motor; Fixing rocking arm, one end of described fixing rocking arm is connected with described fixing rocker arm support; Operating rock arm, described operating rock arm is connected with described steering wheel to make operating rock arm described in described servo driving movable; Pitch control rockerarm, described pitch control rockerarm is located at described rotor shaft and puts and the middle part of described pitch control rockerarm is connected pivotly with described rotor axle sleeve, the first end of described pitch control rockerarm is connected pivotly with the other end of described fixing rocking arm, and the second end of described pitch control rockerarm is connected pivotly with described operating rock arm.
According to one embodiment of present invention, described pitch control rockerarm is set in described rotor shaft and puts and the middle part of the relative both sides of described pitch control rockerarm is connected pivotly with described rotor axle sleeve respectively.
According to one embodiment of present invention, described pitch control rockerarm comprises the first pole and the second pole, and the coupling end of described first pole and described second pole is positioned at the middle part of described pitch control rockerarm, and the angle between described first pole and described second pole is obtuse angle.
According to one embodiment of present invention, described bending moment dish is provided with drive spindle, and the first end of described drive spindle is connected with described bending moment dish, and the second end of described drive spindle divides and is connected rotationally to drive described tail-rotor bending moment with described tail-rotor.
According to one embodiment of present invention, described tail-rotor comprises two, and two described tail-rotors are located at the relative both sides of described rotor shaft respectively, and described motor drives described rotor shaft to rotate to drive described tail-rotor around the center axis thereof of described rotor shaft.
According to one embodiment of present invention, two described tail-rotors realize synchronous bending moment respectively by two described drive spindles.
According to one embodiment of present invention, realize being connected pivotly with the unitized construction of bolt respectively by bearing between described pitch control rockerarm with described rotor axle sleeve, between described pitch control rockerarm with described fixing rocking arm, between described pitch control rockerarm with described operating rock arm, between described drive spindle with described tail-rotor.
According to one embodiment of present invention, described bending moment dish and described rotor axle sleeve are integrally formed.
According to one embodiment of present invention, also comprise controller, described controller is electrically connected with described steering wheel.
Additional aspect of the present invention and advantage will part provide in the following description, and part will become obvious from the following description, or be recognized by practice of the present invention.
Accompanying drawing explanation
Fig. 1 is the structural representation of the helicopter tail rotor bending moment steering unit according to the embodiment of the present invention;
Fig. 2 is the cutaway view of the structure shown in Fig. 1;
Fig. 3 is the partial enlarged drawing of the structure shown in Fig. 1.
Reference numeral:
100: helicopter tail rotor bending moment steering unit;
10: rotor shaft; 11: tail-rotor; 12: propeller hub;
20: bending moment dish; 21: drive spindle;
30: motor;
40: tail-rotor bending moment handles assembly;
41: fixing rocker arm support;
42: fixing rocking arm;
43: operating rock arm;
44: pitch control rockerarm; 441: the first poles; 442: the second poles;
50: steering wheel;
60: rotor axle sleeve;
70: controller.
Detailed description of the invention
Be described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.
The helicopter tail rotor bending moment steering unit 100 of embodiment is according to a first aspect of the present invention specifically described below in conjunction with accompanying drawing 1 to Fig. 3.
As depicted in figs. 1 and 2, rotor shaft 10, bending moment dish 20, motor 30, tail-rotor bending moment manipulation assembly 40 and steering wheel 50 is comprised according to the helicopter tail rotor bending moment steering unit 100 of the embodiment of the present invention.Specifically, rotor shaft 10 is provided with the tail-rotor 11 radially extended, tail-rotor 11 is rotatable around the axis of rotor shaft 10, bending moment dish 20 is located in rotor shaft 10 along the axis of rotor shaft 10 movably to drive tail-rotor 11 bending moment, motor 30 is connected to drive rotor shaft 10 to rotate with rotor shaft 10, tail-rotor bending moment is handled assembly 40 and is connected to drive bending moment dish 20 activity with bending moment dish 20, and steering wheel 50 and tail-rotor bending moment are handled assembly 40 and be connected to make tail-rotor bending moment handle assembly 40 and drive tail-rotor 11 bending moment.
In other words, this helicopter tail rotor bending moment steering unit 100 forms primarily of rotor shaft 10, bending moment dish 20, motor 30, tail-rotor bending moment manipulation assembly 40 and steering wheel 50.Wherein, rotor shaft 10 vertically (above-below direction as shown in Figure 1) extends, the lower end of rotor shaft 10 is connected with motor 30, motor 30 is made to drive rotor shaft 10 to rotate, the upper end of rotor shaft 10 is provided with the propeller hub 12 extended in the horizontal direction, namely the central axis of propeller hub 12 can be arranged with the central axis of rotor shaft 10 is mutually vertical, propeller hub 12 can along with rotor shaft 10 be together around the center axis thereof of rotor shaft 10, and propeller hub 12 is provided with tail-rotor 11 and tail-rotor 11 can be swingable around the central axis of propeller hub 12.
Further, rotor shaft 10 is provided with can along its axially movable bending moment dish 20, and, this bending moment dish 20 is positioned at the below of tail-rotor 11, and be provided with tail-rotor bending moment between bending moment dish 20 and motor 30 and handle assembly 40, this tail-rotor bending moment is handled assembly 40 and to be located at movably in rotor shaft 10 and to be connected with steering wheel 50, it is movable that steering wheel 50 can drive tail-rotor bending moment to handle assembly 40, then tail-rotor bending moment manipulation assembly 40 drives bending moment dish 20 to move up and down along the axis of rotor shaft 10, when bending moment dish 20 is upwards movable, tail-rotor 11 is driven to carry out bending moment.
Here it should be noted that, of the present invention " on ", the noun of locality such as D score just for convenience of description each parts of helicopter tail rotor bending moment steering unit 100 structure, annexation and arrange orientation etc., particularly, any direction can be arranged in when this helicopter tail rotor bending moment steering unit 100 is applied on helicopter.
Thus, according to the helicopter tail rotor bending moment steering unit 100 of the embodiment of the present invention, handle assembly 40 by arranging tail-rotor bending moment in rotor shaft 10, can realize the object driving tail-rotor 11 bending moment, simple to operate, reliability of service is high.The structure of this helicopter tail rotor bending moment steering unit 100 is simple, compact, processing, easy to manufacture, and cost is low, each parts connect reliable, operating clearance is less, Path of Force Transfer is more reliable, motion is coherent, transmission is accurate.
Wherein, according to one embodiment of present invention, helicopter tail rotor bending moment steering unit 100 also comprises rotor axle sleeve 60, and rotor axle sleeve 60 to be located in rotor shaft 10 and axially movable along rotor shaft 10, and bending moment dish 20 is located on rotor axle sleeve 60.
With reference to figure 1, rotor axle sleeve 60 to be set in rotor shaft 10 and movably between motor 30 and bending moment dish 20, the upper end of rotor axle sleeve 60 is only supported with bending moment dish 20 and is connected, and tail-rotor bending moment manipulation assembly 40 is located on the sidewall of rotor axle sleeve 60 movably, when steering wheel 50 drives tail-rotor bending moment to handle assembly 40 activity, tail-rotor bending moment is handled assembly 40 and is promoted rotor axle sleeve 60 and move up along the axis of rotor shaft 10, then rotor axle sleeve 60 promotes bending moment dish 20 and moves up along the axis of rotor shaft 10, thus realizes the object of tail-rotor 11 bending moment.
Thus, by arranging rotor axle sleeve 60 in rotor shaft 10, the object promoting the motion of bending moment dish 20 can be realized, thus be conducive to realizing tail-rotor 11 bending moment, the structure of this helicopter tail rotor bending moment steering unit 100 is simple, compact, and between each parts, mounting or dismounting are easily, simple to operate, reliability is high.
Alternatively, tail-rotor bending moment manipulation assembly 40 comprises fixing rocker arm support 41, fixing Rocker arm 42, operating rock arm 43 and pitch control rockerarm 44.Specifically, fixing rocker arm support 41 is located on motor 30, one end of fixing Rocker arm 42 is connected with fixing rocker arm support 41, operating rock arm 43 is connected with steering wheel 50 to make steering wheel 50 drive operating rock arm 43 movable, pitch control rockerarm 44 is located on rotor the axle sleeve 60 and middle part of pitch control rockerarm 44 and is connected pivotly with rotor axle sleeve 60, the first end of pitch control rockerarm 44 is connected pivotly with the other end of fixing Rocker arm 42, and the second end of pitch control rockerarm 44 is connected pivotly with operating rock arm 43.
That is, this tail-rotor bending moment manipulation assembly 40 forms primarily of fixing rocker arm support 41, fixing Rocker arm 42, operating rock arm 43 and pitch control rockerarm 44.Wherein, rotor shaft 10 is installed with fixing rocker arm support 41, arranged spaced apart with fixing rocker arm support 41 on the sidewall that pitch control rockerarm 44 is located at rotor axle sleeve 60 pivotly, pitch control rockerarm 44 can move up and down with the axis of rotor axle sleeve 60 along rotor shaft 10, further, fixing Rocker arm 42 and operating rock arm 43 lay respectively at the both sides of pitch control rockerarm 44, and the first end of pitch control rockerarm 44 is connected with one end of fixing Rocker arm 42, second end of pitch control rockerarm 44 is connected with one end of operating rock arm 43, and the other end of fixing Rocker arm 42 is connected with fixing rocker arm support 41, the other end of operating rock arm 43 and steering wheel 50.
When this helicopter needs tail-rotor 11 bending moment, start steering wheel 50, steering wheel 50 drives operating rock arm 43 upward movement, because fixing Rocker arm 42 is installed on fixing rocker arm support 41, therefore, fixing Rocker arm 42 is constant all the time relative to the position of rotor shaft 10, namely the first end of pitch control rockerarm 44 is constant all the time relative to the position of rotor shaft 10, therefore, drive in the process of operating rock arm 43 at steering wheel 50, operating rock arm 43 drives the second end of pitch control rockerarm 44 to move up, pitch control rockerarm 44 is made to drive rotor axle sleeve 60 to move up along rotor shaft 10, bending moment dish 20 is made to drive tail-rotor 11 bending moment further.
Thus, the structure that this tail-rotor bending moment handles assembly 40 is simple, manufacture, handling ease, cost is low, each parts connect reliable, can regard laborsaving lever construction as, thus reduce pulling force needed for steering wheel 50 widely, and then reduce the power of steering wheel 50, further, the compensate for lateral displacement that this structure can be moved, promotes bending moment dish 20 and drives tail-rotor 11 bending moment, operating clearance is little, and accuracy is high.
In detailed description of the invention more of the present invention, pitch control rockerarm 44 is set on rotor the axle sleeve 60 and middle part of the relative both sides of pitch control rockerarm 44 and is connected pivotly with rotor axle sleeve 60 respectively.
That is, pitch control rockerarm 44 can be formed as annular, pitch control rockerarm 44 is set in the outside of rotor axle sleeve 60, and being connected pivotly with the lateral wall of rotor axle sleeve 60 respectively of the relative both sides of pitch control rockerarm 44, namely pitch control rockerarm 44 is oppositely arranged connection structure with rotor axle sleeve 60 by two and realizes being connected pivotly, like this, pitch control rockerarm 44 can promote rotor axle sleeve 60 together from the both sides of rotor axle sleeve 60 and move, be conducive to the structural strength improving pitch control rockerarm 44, extend the service life of this pitch control rockerarm 44.
In other detailed description of the invention of the present invention, pitch control rockerarm 44 comprises the first pole 441 and the second pole 442, the coupling end of the first pole 441 and the second pole 442 is positioned at the middle part of pitch control rockerarm 44, and the angle between the first pole 441 and the second pole 442 is obtuse angle.In other words, pitch control rockerarm 44 is located at the side of rotor axle sleeve 60, and, first pole 441 of pitch control rockerarm 44 is connected with the lateral wall of rotor axle sleeve 60 pivotly with the connection location of the second pole 442, and one end of the first pole 441 is connected pivotly with fixing Rocker arm 42, one end of the second pole 442 is connected pivotly with one end of operating rock arm 43.The structure of this pitch control rockerarm 44 is simple, and connect reliable, transmission is accurate.
Wherein, according to one embodiment of present invention, bending moment dish 20 is provided with drive spindle 21, and the first end of drive spindle 21 is connected with bending moment dish 20, and the second end of drive spindle 21 divides and is connected to drive tail-rotor 11 bending moment rotationally with tail-rotor 11.
With reference to figure 3, drive spindle 21 vertically (above-below direction as shown in Figure 3) extends, and wherein, the upper end of drive spindle 21 is connected to drive tail-rotor 11 to swing relative to propeller hub 12 with tail-rotor 11, the lower end of drive spindle 21 is connected with bending moment dish 20.When steering wheel 50 drives tail-rotor bending moment to handle assembly 40 activity, tail-rotor bending moment is handled assembly 40 and is promoted rotor axle sleeve 60 and move up along the axis of rotor shaft 10, then rotor axle sleeve 60 promotes bending moment dish 20 and moves up along the axis of rotor shaft 10, distance between bending moment dish 20 and tail-rotor 11 is reduced, thus makes bending moment dish 20 promote tail-rotor 11 bending moment by drive spindle 21.
The structure of this helicopter tail rotor bending moment steering unit 100 is simple, compact, manufacture, handling ease, and cost is low, and each parts connect reliable, and motion is coherent, and can promote bending moment dish 20 and drive tail-rotor 11 bending moment, reliability of service is high.
Alternatively, tail-rotor 11 comprises two, and two tail-rotors 11 are located at the relative both sides of rotor shaft 10 respectively, and motor 30 drives rotor shaft 10 to rotate the center axis thereof driving tail-rotor 11 around rotor shaft 10.Wherein, two tail-rotors 11 realize synchronous bending moment respectively by two drive spindles 21.
With reference to figure 2, in the present embodiment, two tail-rotor 11 (left and right directions as shown in Figure 2) extensions in the horizontal direction respectively, and the below of each tail-rotor 11 is equipped with the drive spindle 21 be connected with corresponding tail-rotor 11 and bending moment dish 20 respectively, when bending moment dish 20 moves up, two drive spindles 21 can be promoted movable simultaneously, thus realize the synchronous bending moment of two tail-rotors 11.
Certainly, the present invention is not limited to this, and propeller hub 12 can also be arranged at least three (comprising three) tail-rotors 11, each tail-rotor 11 can swing relative to propeller hub 12, and the driving being handled assembly 40 by tail-rotor bending moment can realize multiple tail-rotor 11 bending moment.
Alternatively, according to one embodiment of present invention, realize being connected pivotly with the unitized construction of bolt respectively by bearing between pitch control rockerarm 44 with rotor axle sleeve 60, between pitch control rockerarm 44 with fixing Rocker arm 42, between pitch control rockerarm 44 with operating rock arm 43, between drive spindle 21 with tail-rotor 11.Thus, the friction pair in correlation technique is replaced by use bearing and bolted structure, can reduce wear and handle gap, make that the Path of Force Transfer of helicopter tail rotor bending moment steering unit 100 is more reliable, transmission is more accurate, structure is simple, and mounting or dismounting are convenient, and structural strength is high, can bear larger bending moment power, the life-span is longer.
Preferably, according to one embodiment of present invention, bending moment dish 20 and rotor axle sleeve 60 are integrally formed.Thus, the structure be integrally formed not only can ensure the properity stability of this helicopter tail rotor bending moment steering unit 100, and facilitate shaping, manufacture simple, and eliminate unnecessary assembly parts and connect operation, substantially increase the efficiency of assembling of this helicopter tail rotor bending moment steering unit 100, ensure the connection reliability between parts, moreover, bulk strength and the stability of the structure be integrally formed are higher, and assemble more convenient, the life-span is longer.
In addition, according to one embodiment of present invention, helicopter tail rotor bending moment steering unit 100 also comprises controller 70, and controller 70 is electrically connected with steering wheel 50.That is, this helicopter tail rotor bending moment steering unit 100 is handled assembly 40, steering wheel 50, rotor axle sleeve 60 and controller 70 form primarily of rotor shaft 10, bending moment dish 20, motor 30, tail-rotor bending moment.This controller 70 is connected with steering wheel 50, can control the start and stop of steering wheel 50, thus can in time control tail-rotor 11 bending moment according to the flight condition of helicopter.
According to the helicopter of the embodiment of the present invention other form and operation be all known for those of ordinary skills, be not described in detail here.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ", " thickness ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", " outward ", " cw ", " conter clockwise ", " axis ", " radial direction ", orientation or the position relationship of the instruction such as " circumference " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.
In addition, term " first ", " second " only for describing object, and can not be interpreted as instruction or hint relative importance or imply the quantity indicating indicated technical characteristic.Thus, be limited with " first ", the feature of " second " can express or impliedly comprise at least one this feature.In describing the invention, the implication of " multiple " is at least two, such as two, three etc., unless otherwise expressly limited specifically.
In the present invention, unless otherwise clearly defined and limited, the term such as term " installation ", " being connected ", " connection ", " fixing " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or integral; Can be mechanical connection, also can be electrical connection or each other can communication; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals or the interaction relationship of two elements, unless otherwise clear and definite restriction.For the ordinary skill in the art, above-mentioned term concrete meaning in the present invention can be understood as the case may be.
In the present invention, unless otherwise clearly defined and limited, fisrt feature second feature " on " or D score can be that the first and second features directly contact, or the first and second features are by intermediary indirect contact.And, fisrt feature second feature " on ", " top " and " above " but fisrt feature directly over second feature or oblique upper, or only represent that fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " below " and " below " can be fisrt feature immediately below second feature or tiltedly below, or only represent that fisrt feature level height is less than second feature.
In the description of this specification sheets, specific features, structure, material or feature that the description of reference term " embodiment ", " some embodiments ", " example ", " concrete example " or " some examples " etc. means to describe in conjunction with this embodiment or example are contained at least one embodiment of the present invention or example.In this manual, to the schematic representation of above-mentioned term not must for be identical embodiment or example.And the specific features of description, structure, material or feature can combine in one or more embodiment in office or example in an appropriate manner.In addition, when not conflicting, the feature of the different embodiment described in this specification sheets or example and different embodiment or example can carry out combining and combining by those skilled in the art.
Although illustrate and describe embodiments of the invention above, be understandable that, above-described embodiment is exemplary, can not be interpreted as limitation of the present invention, and those of ordinary skill in the art can change above-described embodiment within the scope of the invention, revises, replace and modification.
Claims (11)
1. a helicopter tail rotor bending moment steering unit, is characterized in that, comprising:
Rotor shaft, described rotor shaft is provided with the tail-rotor radially extended, and described tail-rotor is rotatable around the axis of described rotor shaft;
Bending moment dish, the axis of rotor shaft described in described bending moment rim is located in described rotor shaft movably to drive described tail-rotor bending moment;
Motor, described motor is connected with described rotor shaft to drive described rotor shaft to rotate;
Tail-rotor bending moment handles assembly, and described tail-rotor bending moment is handled assembly and is connected to drive described bending moment disk activity with described bending moment dish;
Steering wheel, described steering wheel and described tail-rotor bending moment are handled assembly and are connected to make described tail-rotor bending moment handle tail-rotor bending moment described in Component driver.
2. helicopter tail rotor bending moment steering unit according to claim 1, is characterized in that, also comprise rotor axle sleeve, and described rotor shaft to be set in described rotor shaft and axially movable along described rotor shaft, and described bending moment dish is located at described rotor shaft and puts.
3. helicopter tail rotor bending moment steering unit according to claim 2, is characterized in that, described tail-rotor bending moment is handled assembly and comprised:
Fixing rocker arm support, described fixing rocker arm support is located on described motor;
Fixing rocking arm, one end of described fixing rocking arm is connected with described fixing rocker arm support;
Operating rock arm, described operating rock arm is connected with described steering wheel to make operating rock arm described in described servo driving movable;
Pitch control rockerarm, described pitch control rockerarm is located at described rotor shaft and puts and the middle part of described pitch control rockerarm is connected pivotly with described rotor axle sleeve, the first end of described pitch control rockerarm is connected pivotly with the other end of described fixing rocking arm, and the second end of described pitch control rockerarm is connected pivotly with described operating rock arm.
4. helicopter tail rotor bending moment steering unit according to claim 3, is characterized in that, described pitch control rockerarm is set in described rotor shaft and puts and the middle part of the relative both sides of described pitch control rockerarm is connected pivotly with described rotor axle sleeve respectively.
5. helicopter tail rotor bending moment steering unit according to claim 3, it is characterized in that, described pitch control rockerarm comprises the first pole and the second pole, the coupling end of described first pole and described second pole is positioned at the middle part of described pitch control rockerarm, and the angle between described first pole and described second pole is obtuse angle.
6. helicopter tail rotor bending moment steering unit according to claim 3, it is characterized in that, described bending moment dish is provided with drive spindle, and the first end of described drive spindle is connected with described bending moment dish, and the second end of described drive spindle divides and is connected rotationally to drive described tail-rotor bending moment with described tail-rotor.
7. helicopter tail rotor bending moment steering unit according to claim 6, it is characterized in that, described tail-rotor comprises two, two described tail-rotors are located at the relative both sides of described rotor shaft respectively, and described motor drives described rotor shaft to rotate to drive described tail-rotor around the center axis thereof of described rotor shaft.
8. helicopter tail rotor bending moment steering unit according to claim 7, is characterized in that, two described tail-rotors realize synchronous bending moment respectively by two described drive spindles.
9. helicopter tail rotor bending moment steering unit according to claim 6, it is characterized in that, realize being connected pivotly with the unitized construction of bolt respectively by bearing between described pitch control rockerarm with described rotor axle sleeve, between described pitch control rockerarm with described fixing rocking arm, between described pitch control rockerarm with described operating rock arm, between described drive spindle with described tail-rotor.
10. helicopter tail rotor bending moment steering unit according to claim 2, is characterized in that, described bending moment dish and described rotor axle sleeve are integrally formed.
11. helicopter tail rotor bending moment steering units according to claim 1, it is characterized in that, also comprise controller, described controller is electrically connected with described steering wheel.
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| CN201610059206.0A CN105501434B (en) | 2016-01-28 | 2016-01-28 | Helicopter tail rotor bending moment operating mechanism |
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| CN201610059206.0A CN105501434B (en) | 2016-01-28 | 2016-01-28 | Helicopter tail rotor bending moment operating mechanism |
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| CN105501434B CN105501434B (en) | 2018-02-27 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857578A (en) * | 2016-05-20 | 2016-08-17 | 辽宁辽飞航空科技有限公司 | Pitch-variable system for oil-driven multi-rotor wing aircraft |
| CN106005389A (en) * | 2016-05-27 | 2016-10-12 | 燕山大学 | Helicopter rotor wing compound motion parallel driving device |
| CN106081102A (en) * | 2016-08-11 | 2016-11-09 | 深圳天鹰兄弟无人机创新有限公司 | A kind of unmanned plane and bar thick stick formula tail-rotor distance changing mechanism thereof |
| CN112874779A (en) * | 2020-10-30 | 2021-06-01 | 中国直升机设计研究所 | Pure electric drive's light-duty helicopter |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573873A (en) * | 1983-01-13 | 1986-03-04 | Hughes Helicopters, Inc. | Collective and cyclic in-mast pitch control system for a helicopter |
| US5511947A (en) * | 1995-02-17 | 1996-04-30 | The Boeing Company | Cyclic pitch control having torsion spring system |
| CN101134506A (en) * | 2007-08-27 | 2008-03-05 | 万涛 | Helicopter rotor control mechanism |
| CN202609078U (en) * | 2012-05-14 | 2012-12-19 | 乐清市飓风精密机械有限公司 | Tail control system for unmanned helicopter |
-
2016
- 2016-01-28 CN CN201610059206.0A patent/CN105501434B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4573873A (en) * | 1983-01-13 | 1986-03-04 | Hughes Helicopters, Inc. | Collective and cyclic in-mast pitch control system for a helicopter |
| US5511947A (en) * | 1995-02-17 | 1996-04-30 | The Boeing Company | Cyclic pitch control having torsion spring system |
| CN101134506A (en) * | 2007-08-27 | 2008-03-05 | 万涛 | Helicopter rotor control mechanism |
| CN202609078U (en) * | 2012-05-14 | 2012-12-19 | 乐清市飓风精密机械有限公司 | Tail control system for unmanned helicopter |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857578A (en) * | 2016-05-20 | 2016-08-17 | 辽宁辽飞航空科技有限公司 | Pitch-variable system for oil-driven multi-rotor wing aircraft |
| CN106005389A (en) * | 2016-05-27 | 2016-10-12 | 燕山大学 | Helicopter rotor wing compound motion parallel driving device |
| CN106005389B (en) * | 2016-05-27 | 2018-01-23 | 燕山大学 | Lifting airscrew compound motion parallel drive unit |
| CN106081102A (en) * | 2016-08-11 | 2016-11-09 | 深圳天鹰兄弟无人机创新有限公司 | A kind of unmanned plane and bar thick stick formula tail-rotor distance changing mechanism thereof |
| CN112874779A (en) * | 2020-10-30 | 2021-06-01 | 中国直升机设计研究所 | Pure electric drive's light-duty helicopter |
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| CN105501434B (en) | 2018-02-27 |
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