WO2018095042A1 - 变桨距传动机构 - Google Patents

变桨距传动机构 Download PDF

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Publication number
WO2018095042A1
WO2018095042A1 PCT/CN2017/092054 CN2017092054W WO2018095042A1 WO 2018095042 A1 WO2018095042 A1 WO 2018095042A1 CN 2017092054 W CN2017092054 W CN 2017092054W WO 2018095042 A1 WO2018095042 A1 WO 2018095042A1
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WIPO (PCT)
Prior art keywords
blade
link
transmission mechanism
main shaft
steering gear
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.)
Ceased
Application number
PCT/CN2017/092054
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English (en)
French (fr)
Inventor
刘若鹏
栾琳
黄兹驰
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenzhen Kuang Chi Space Technology Co Ltd
Original Assignee
Shenzhen Kuang Chi Space Technology Co Ltd
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Publication date
Application filed by Shenzhen Kuang Chi Space Technology Co Ltd filed Critical Shenzhen Kuang Chi Space Technology Co Ltd
Publication of WO2018095042A1 publication Critical patent/WO2018095042A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/78—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement in association with pitch adjustment of blades of anti-torque rotor

Definitions

  • the utility model relates to a pitch transmission mechanism.
  • the prior art proposes a variable pitch transmission mechanism for teaching and training of wind power generation, which has a large number of parts and a complicated mechanism, and the mechanism faces wind power generation, and does not consider the key factor of weight, so The agency does not apply to aircraft.
  • the prior art also proposes a variable pitch mechanism in a variable pitch multi-rotor aircraft that is subjected to a small load and cannot be applied to an aircraft requiring a large lift, such as a fixed wing, an airship, or the like.
  • the prior art mainly controls the magnitude of the lift generated by the rotor by changing the motor speed.
  • the problem that arises is that the motor cannot provide more lift through the motor when the motor speed has reached its maximum.
  • the prior art requires a technique that not only controls the magnitude of the lift generated by the rotor by changing the motor speed.
  • the present invention provides a pitch transmission mechanism including: a rotatable main shaft; a blade clamp rotatably coupled to the main shaft about a blade rotation shaft, the blade clamp being fixed with a paddle a blade; the blade rotation axis is perpendicular to the axis of the spindle; a sleeve sleeved on the spindle and axially movable along the spindle and rotating with the spindle; a connecting rod assembly fixedly coupled to the sleeve a connecting rod assembly and one side of the blade clamp are connected by a first link; a slider disposed on the sleeve by a bearing; and sequentially passing through the steering gear link and the right angle link The steering gear connected to the slider, the steering gear drives the blade to rotate around the rotation axis of the blade.
  • the pitch transmission mechanism further includes a spindle mounting box and a link mounting seat fixed to a top surface of the spindle mounting box, the spindle being rotatably mounted through the connecting rod mounting seat
  • the steering gear is fixedly disposed at one side of the spindle mounting box, and a right angle portion of the right angle link is pivotally connected to the link mounting seat by a second link.
  • a free end of the main shaft is fixed with a rotor head, and the blade clamp is coupled to the rotor head by a transverse axis extending along a rotational axis of the blade.
  • the sleeve and the main shaft are provided with an axially extending flat key structure.
  • a plurality of blade clamps are provided along the circumferential direction of the main shaft, and the plurality of blade clamps are coupled to the link assembly by a plurality of the first links.
  • the sleeve is fixedly coupled to the inner ring of the bearing, and the slider is fixedly coupled to the outer ring of the bearing.
  • the steering gear link is coupled between the right angle link and the steering gear via a joint bearing.
  • two ends of the steering gear link are respectively threaded with two joint bearings, and the distance between the two joint bearings can be changed by the rotation of the steering gear link.
  • the blade rotation axis is perpendicular to the axis of the main shaft.
  • the blade angle of the blade is greater than 0 degrees ⁇ , and the pivot connecting the first link and the blade clamp is lower than the top of the rotor head.
  • the blade angle of the blade is less than 0 degrees ⁇ , and the pivot connecting the first link and the blade clamp is higher than the top of the rotor head.
  • variable pitch transmission mechanism of the present invention drives the steering gear link and the right angle link through the steering gear to drive the slider to move axially, and then controls the blade clamp through the link assembly and the first link.
  • the blade angle of the blade changes the lift of the aircraft. Compared with the original technology, the lift of the aircraft is adjusted by another way.
  • the adjustment time has been shortened a lot.
  • FIG. 1 is a perspective view of a pitch drive mechanism of the present invention.
  • FIG. 2 is a side view of the pitch transmission mechanism of the present invention.
  • 3 is a partial cross-sectional view of the pitch transmission mechanism of the present invention.
  • FIG. 5 is a perspective view of an embodiment of a pitch drive mechanism of the present invention.
  • FIG. 6 is a perspective view of another embodiment of the pitch drive mechanism of the present invention.
  • the pitch transmission mechanism of the present invention includes: a rotatable main shaft 7; a blade clamp 1 rotatably coupled to the main shaft 7 about a blade rotation shaft 16, a blade clamp 1 fixed with a blade 17; the blade rotating shaft 16 is perpendicular to the axis of the spindle 7; a sleeve 15 sleeved on the spindle 7 and axially movable along the spindle 7 and rotating with the spindle 7; fixedly coupled to the sleeve 15 a link assembly 4, the link assembly 4 and one side of the blade clamp 1 are connected by a first link 2; a slider 5 disposed on the sleeve 15 through a bearing 18; and sequentially passing through the servo link 12 and The steering gear 10 of the right angle link 6 and the slider 5, the steering gear 10 drives the blade clamp 1 to rotate about the blade rotation shaft 16.
  • the blade rotation axis 16 is perpendicular to the axis of the spindle 7.
  • the pitch transmission mechanism of the present invention further includes a spindle mounting box 11 and a link mounting seat 8 fixed to a top surface of the spindle mounting box 11, and the spindle 7 passes through the link mounting seat.
  • 8 is rotatably mounted to the spindle mounting case 11, the steering gear 10 is fixedly disposed on one side of the spindle mounting case 11, and the right angle portion of the right angle link 6 is pivotally coupled to the link mounting seat 11 via the second link 13.
  • the free end of the main shaft 7 is fixed with a rotor head 3 which is coupled to the rotor head 3 by a transverse axis 14 extending along the blade rotation axis 16.
  • the sleeve 15 and the main shaft 7 are provided with an axially extending flat key structure (not shown).
  • a plurality of blade clamps 1 are disposed along the circumferential direction of the main shaft 7, and a plurality of blade clamps 1 are coupled to the link assembly 4 through a plurality of first links 2.
  • the sleeve 15 is fixedly coupled to the inner ring of the bearing 18, and the slider 5 is fixedly coupled to the outer ring of the bearing 18.
  • the servo link 12 is connected between the right angle link 6 and the steering gear 10 via a joint bearing 9.
  • Two joint bearings are threadedly coupled to the two ends of the steering gear link 12, and the distance between the two joint bearings 9 can be changed by the rotation of the servo link 12.
  • the device works as follows: The power input by the motor passes through a coupling or flange in the spindle mounting box 11
  • the main shaft 7 is connected, and the main shaft 7 provides rotational power to the rotor.
  • the same steering gear 10 controls the rotation of the right angle link 6 through the steering gear link 12 to control the axial movement of the slider 5.
  • the length of the steering gear link 12 is adjustable to control the stroke of the axial slider 5.
  • the steering gear connecting rod 12 is equipped with joint bearings 9 at both ends to accommodate different types of steering gears.
  • the axial slider 5 has a bearing 18 inside, and the connecting rod assembly 4 is mounted on the inner ring of the bearing through the sleeve 15, so that the connecting rod assembly 4 can rotate around the inner ring of the bearing 18 under the driving of the main shaft 7, the outer ring of the bearing 18 Fixed to the slider 5, by adjusting the slider 5, the axial movement can maintain the same axial movement as the axial slider 5, and the spindle 7 can rotate at the same speed as the spindle 7.
  • the link assembly 4 controls the movement of the first link 2 by axial sliding, thereby controlling the angle of rotation of the blade clamp 1.
  • the response time of the device depends on the response of the servo, up to the millisecond level.
  • the stroke of the coaxial axial slide 5 can be adjusted by the length of the connecting rod 12, so that the adjustable angle of the rotor is quite wide.
  • the rotation mode of the steering gear 10 in FIG. 2 is taken as an example to analyze how to realize the angle adjustment of the blade:
  • the steering gear 10 rotates counterclockwise according to the direction of the arrow a in FIG.
  • the thrust is generated to push the steering gear link 12 to move in the direction of the b arrow; one end of the right angle link 6 is rotated by the direction of the c arrow by the push of the link 12; the axial slider 5 is driven by the rotating right angle link 6 Sliding downward, the same link drives the movement of the entire connecting rod assembly 4 according to the d arrow; and due to the movement of the connecting rod assembly 4, the first connecting rod 2 produces a movement tendency of the arrow e as shown in FIG. 2, and finally the blade is pulled.
  • Clip 1 achieving the working state as shown in FIG.
  • the utility model can be applied to a fixed-wing aircraft, which cooperates with a vertical take-off and landing mechanism, and can provide more lift by changing the angle of the rotor when the motor speed has reached the maximum. Pull straight up.
  • the utility model can be applied to an airship. Since the pitch drive mechanism of the present invention can provide positive lift and negative lift. As shown in Fig. 5, a positive lift ⁇ is provided, the blade angle of the blade is greater than 0 degrees, and the pivot 19 connecting the first link 2 and the blade clamp 1 is lower than the top of the rotor head 3. As shown in FIG. 6, a negative lift ⁇ is provided, and the blade angle of the blade is less than 0 degrees. Therefore, the pivot 19 connecting the first link 2 and the blade clamp 1 is higher than the top of the rotor head 3, so that The airship quickly returns the airship without turning around.
  • the utility model can be applied to a large multi-rotor aircraft, and adjusts the magnitude of the lift by adjusting the angle of the rotor, thereby improving the wind resistance capability of the large multi-rotor aircraft. It can also be used for aerobatics of multi-rotor aircraft. [0037]
  • the utility model can be applied to the power system of the aircraft, can quickly adjust the lift generated by the rotor under a certain speed condition, and can even achieve negative lift.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种变桨距传动机构，包括：可旋转的主轴（7）；可绕桨叶转动轴（16）旋转地连接至所述主轴的桨叶夹（1），所述桨叶夹固定有桨叶（17）；桨叶转动轴与主轴的轴线垂直；套设在所述主轴上并可沿所述主轴轴向运动且随所述主轴旋转的套筒（15）；固定连接至所述套筒的连杆总成（4），所述连杆总成与所述桨叶夹的一侧通过第一连杆（2）连接；通过轴承（18）设置在所述套筒上的滑块（5）；以及依次通过舵机连杆（12）和直角连杆（6）与所述滑块连接的舵机（10），舵机带动桨叶夹绕桨叶转动轴转动。

Description

发明名称：变桨距传动机构
技术领域
[0001] 本实用新型涉及变桨距传动机构。
背景技术
[0002] 现有技术提出一种用于风力发电教学实训的变距传动机构， 该机构零件数量多 、 机构复杂， 而且该机构面向风力发电， 并没有考虑到重量这一关键因素， 因 此该机构不适用于飞行器。 现有技术还提出一种变距多旋翼飞行器中的变距机 构， 所承受的载荷较小， 不能应用于需要的升力较大的飞行器上， 例如固定翼 、 飞艇等。
[0003] 而且， 现有技术主要是通过改变电机转速来控制旋翼产生的升力大小。 由此产 生的问题是在电机转速已达到最大的情况下， 不能通过电机提供更多的升力。 技术问题
[0004] 因此， 现有技术需要一种不单通过改变电机转速来控制旋翼产生的升力大小的 技术。
问题的解决方案
技术解决方案
[0005] 针对相关技术中存在的问题， 本实用新型的目的在于提供一种通过改变桨叶的 桨翼角来控制旋翼产生的升力的变桨距传动机构。
[0006] 本实用新型的提供了一种变桨距传动机构， 包括： 可旋转的主轴； 可绕桨叶转 动轴旋转地连接至所述主轴的桨叶夹， 所述桨叶夹固定有桨叶； 桨叶转动轴与 主轴的轴线垂直； 套设在所述主轴上并可沿所述主轴轴向运动且随所述主轴旋 转的套筒； 固定连接至所述套筒的连杆总成， 所述连杆总成与所述桨叶夹的一 侧通过第一连杆连接； 通过轴承设置在所述套筒上的滑块； 以及依次通过舵机 连杆和直角连杆与所述滑块连接的舵机， 舵机带动桨叶夹绕桨叶转动轴转动。
[0007] 根据本实用新型， 变桨距传动机构还包括主轴安装箱以及固定在所述主轴安装 箱的顶面的连杆安装座， 所述主轴穿过所述连杆安装座可旋转地安装于所述主 轴安装箱， 所述舵机固定设置在所述主轴安装箱的一侧， 所述直角连杆的直角 部通过第二连杆可枢转地连接至所述连杆安装座。
[0008] 根据本实用新型， 所述主轴的自由端固定有旋翼头， 所述桨叶夹通过沿所述桨 叶转动轴延伸的横轴连接至所述旋翼头。
[0009] 根据本实用新型， 所述套筒与所述主轴设置有轴向延伸的平键结构。
[0010] 根据本实用新型， 沿所述主轴的周向设置有多个桨叶夹， 所述多个桨叶夹通过 多个所述第一连杆连接至所述连杆总成。
[0011] 根据本实用新型， 所述套筒固定连接至所述轴承的内圈， 所述滑块固定连接至 所述轴承的外圈。
[0012] 根据本实用新型， 所述舵机连杆通过关节轴承连接在所述直角连杆与所述舵机 之间。
[0013] 根据本实用新型， 所述舵机连杆的两端分别螺纹连接有两个关节轴承， 所述两 个关节轴承之间的距离可通过所述舵机连杆的旋转而改变。
[0014] 根据本实用新型， 所述桨叶转动轴垂直于所述主轴的轴线。
[0015] 根据本实用新型， 桨叶的桨翼角大于 0度吋， 连接第一连杆和桨叶夹的枢轴低 于旋翼头的顶部。
发明的有益效果
有益效果
[0016] 根据本实用新型， 桨叶的桨翼角小于 0度吋， 连接第一连杆和桨叶夹的枢轴高 于旋翼头的顶部。 本实用新型的有益技术效果在于：
[0017] 本实用新型的变桨距传动机构通过舵机驱动舵机连杆和直角连杆， 从而驱动滑 块作轴向运动， 进而通过连杆总成及第一连杆控制桨叶夹上的桨叶的桨翼角来 改变飞行器升力的大小， 相对于原有技术， 通过另外的途径调整飞行器的升力
， 调整吋间缩短了很多。
对附图的简要说明
附图说明
[0018] 图 1是本实用新型的变桨距传动机构的立体示意图。
[0019] 图 2是本实用新型的变桨距传动机构的侧视图。 [0020] 图 3是本实用新型的变桨距传动机构的局部剖面图。
[0021] 图 4是本实用新型的变桨距传动机构的另一局部剖面图。
[0022] 图 5是本实用新型的变桨距传动机构的一实施例的立体图。
[0023] 图 6是本实用新型的变桨距传动机构的另一实施例的立体图。
本发明的实施方式
[0024] 参考图 1至图 3， 本实用新型的变桨距传动机构， 包括： 可旋转的主轴 7; 可绕 桨叶转动轴 16旋转地连接至主轴 7的桨叶夹 1， 桨叶夹 1固定有桨叶 17; 桨叶转动 轴 16与主轴 7的轴线垂直； 套设在主轴 7上并可沿主轴 7轴向运动且随主轴 7旋转 的套筒 15; 固定连接至套筒 15的连杆总成 4， 连杆总成 4与桨叶夹 1的一侧通过第 一连杆 2连接； 通过轴承 18设置在套筒 15上的滑块 5; 以及依次通过舵机连杆 12 和直角连杆 6与滑块 5连接的舵机 10， 舵机 10带动桨叶夹 1绕桨叶转动轴 16转动。 桨叶转动轴 16垂直于主轴 7的轴线。 桨翼角是指桨叶所在的平面相对于与主轴垂 直的平面的夹角。
[0025] 参照图 1及图 2， 本实用新型的变桨距传动机构还包括主轴安装箱 11以及固定在 主轴安装箱 11的顶面的连杆安装座 8， 主轴 7穿过连杆安装座 8可旋转地安装于主 轴安装箱 11， 舵机 10固定设置在主轴安装箱 11的一侧， 直角连杆 6的直角部通过 第二连杆 13可枢转地连接至连杆安装座 11。
[0026] 参照图 2和图 4， 主轴 7的自由端固定有旋翼头 3， 桨叶夹 1通过沿桨叶转动轴 16 延伸的横轴 14连接至旋翼头 3。
[0027] 参照图 3， 套筒 15与主轴 7设置有轴向延伸的平键结构 （未示出） 。
[0028] 参照图 1及图 2， 沿主轴 7的周向设置有多个桨叶夹 1， 多个桨叶夹 1通过多个第 一连杆 2连接至连杆总成 4。
[0029] 参照图 3， 套筒 15固定连接至轴承 18的内圈， 滑块 5固定连接至轴承 18的外圈。
[0030] 参照图 2， 舵机连杆 12通过关节轴承 9连接在直角连杆 6与舵机 10之间。 舵机连 杆 12的两端分别螺纹连接有两个关节轴承 9， 两个关节轴承 9之间的距离可通过 舵机连杆 12的旋转而改变。
[0031] 该装置工作方式如下： 电机输入的动力通过主轴安装箱 11内的联轴器或法兰与 主轴 7连接， 主轴 7为旋翼提供旋转地动力。 同吋舵机 10通过舵机连杆 12控制直 角连杆 6的转动进而控制滑块 5的轴向运动。 舵机连杆 12的长短可调， 可控制轴 向滑块 5的行程。 舵机连杆 12两头装有关节轴承 9以适应不同型号的舵机。 轴向 滑块 5内部有轴承 18， 连杆总成 4通过套筒 15安装于轴承的内圈， 使得连杆总成 4 在主轴 7的带动下能绕轴承 18内圈旋转， 轴承 18外圈固定于滑块 5， 通过调节滑 块 5能实现轴向运动与轴向滑块 5保持相同的轴向运动的同吋能与主轴 7以相同的 转速旋转。 连杆总成 4通过轴向滑动来控制第一连杆 2的运动， 进而控制桨叶夹 1 的旋转角度。 该装置的响应吋间取决于舵机的响应吋间， 可达毫秒级别。 同吋 轴向滑块 5的行程可以通过连杆 12长短来调整， 使得旋翼可调的角度相当宽泛。
[0032] 以下以图 2中的舵机 10的转动方式为例， 解析如何实现桨叶的角度调整： 在一 个可实现例子中， 舵机 10按照图 2中的 a箭头方向逆吋针转动， 产生推力， 推动舵 机连杆 12按照 b箭头方向移动； 直角连杆 6的一端受到连杆 12的推动按照 c箭头的 方向转动； 在转动的直角连杆 6的带动下， 轴向滑块 5向下滑动， 同吋带动整个 连杆总成 4按照 d箭头的移动； 而由于连杆总成 4的移动， 使得第一连杆 2产生如 图 2中 e箭头的运动趋势， 最终拉动桨叶夹 1， 实现如图 5中的工作状态。
[0033] 同理， 当舵机 10的转动方式翻转， 则上述各个箭头一并反向， 最终实现如图 6 所示的工作状态。
[0034] 参照图 5至图 6， 本实用新型可应用于固定翼飞机， 配合垂直起降机构， 在电机 转速已达到最大的情况下， 能通过改变旋翼的角度提供更多的升力， 将飞机直 接拉起。
[0035] 本实用新型可应用于飞艇。 由于本实用新型的变桨距传动机构能提供正升力和 负升力。 如图 5所示， 提供正升力吋， 桨叶的桨翼角大于 0度， 此吋， 连接第一 连杆 2和桨叶夹 1的枢轴 19低于旋翼头 3的顶部。 如图 6所示， 提供负升力吋， 桨 叶的桨翼角小于 0度， 此吋， 连接第一连杆 2和桨叶夹 1的枢轴 19高于旋翼头 3的 顶部， 如此能使飞艇在不掉头的情况下使飞艇迅速返航。
[0036] 本实用新型可应用于大型多旋翼飞行器， 通过调整旋翼的角度调整升力的大小 ， 进而提高大型多旋翼飞行器的抗风能力。 也可以用于多旋翼飞行器的特技飞 行。 [0037] 本实用新型可应用于飞行器的动力系统， 能够在一定的转速条件下快速调整旋 翼产生的升力大小， 甚至能实现负升力。
[0038] 以上所述仅为本实用新型的优选实施例而已， 并不用于限制本实用新型， 对于 本领域的技术人员来说， 本实用新型可以有各种更改和变化。 凡在本实用新型 的精神和原则之内， 所作的任何修改、 等同替换、 改进等， 均应包含在本实用 新型的保护范围之内。

Claims

权利要求书
[权利要求 1] 一种变桨距传动机构， 其特征在于， 包括：
可旋转的主轴；
可绕桨叶转动轴旋转地连接至所述主轴的桨叶夹， 所述桨叶夹固定有 桨叶； 所述桨叶转动轴与所述主轴的轴线垂直； 套设在所述主轴上并可沿所述主轴轴向运动且随所述主轴旋转的套筒 固定连接至所述套筒的连杆总成， 所述连杆总成与所述桨叶夹的一侧 通过第一连杆连接；
通过轴承设置在所述套筒上的滑块； 以及
依次通过舵机连杆和直角连杆与所述滑块连接的舵机；
所述舵机带动所述桨叶夹绕桨叶转动轴转动。
[权利要求 2] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 还包括主轴安 装箱以及固定在所述主轴安装箱的顶面的连杆安装座， 所述主轴穿过 所述连杆安装座可旋转地安装于所述主轴安装箱， 所述舵机固定设置 在所述主轴安装箱的一侧， 所述直角连杆的直角部通过第二连杆可枢 转地连接至所述连杆安装座。
[权利要求 3] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 所述主轴的自 由端固定有旋翼头， 所述桨叶夹通过沿所述桨叶转动轴延伸的横轴连 接至所述旋翼头。
[权利要求 4] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 所述套筒与所 述主轴设置有轴向延伸的平键结构。
[权利要求 5] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 沿所述主轴的 周向设置有多个桨叶夹， 所述多个桨叶夹通过多个所述第一连杆连接 至所述连杆总成。
[权利要求 6] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 所述套筒固定 连接至所述轴承的内圈， 所述滑块固定连接至所述轴承的外圈。
[权利要求 7] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 所述舵机连杆 通过关节轴承连接在所述直角连杆与所述舵机之间。
[权利要求 8] 根据权利要求 7所述的变桨距传动机构， 其特征在于， 所述舵机连杆 的两端分别螺纹连接有两个关节轴承， 所述两个关节轴承之间的距离 通过所述舵机连杆的旋转而改变。
[权利要求 9] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 所述桨叶的桨 翼角大于 0度吋， 连接所述第一连杆和所述桨叶夹的枢轴低于所述旋 翼头的顶部。
[权利要求 10] 根据权利要求 1所述的变桨距传动机构， 其特征在于， 所述桨叶的桨 翼角小于 0度吋， 连接所述第一连杆和所述桨叶夹的枢轴高于所述旋 翼头的顶部。
PCT/CN2017/092054 2016-11-25 2017-07-06 变桨距传动机构 Ceased WO2018095042A1 (zh)

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CN107618660A (zh) * 2017-10-23 2018-01-23 郑州方达电子技术有限公司 无人直升机尾旋翼机构
CN109050884B (zh) * 2018-06-21 2022-02-18 深圳市龙云创新航空科技有限公司 一种自动变距的螺旋桨旋翼头以及无人机
CN113247240A (zh) * 2021-06-25 2021-08-13 四川腾盾科技有限公司 一种无人直升机尾桨桨距调节操纵结构
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