WO2023142204A1 - 基于液压扭管变距的直升机旋翼操纵装置 - Google Patents

基于液压扭管变距的直升机旋翼操纵装置 Download PDF

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WO2023142204A1
WO2023142204A1 PCT/CN2022/077064 CN2022077064W WO2023142204A1 WO 2023142204 A1 WO2023142204 A1 WO 2023142204A1 CN 2022077064 W CN2022077064 W CN 2022077064W WO 2023142204 A1 WO2023142204 A1 WO 2023142204A1
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rotor
hydraulic
pitch
variable
propeller
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PCT/CN2022/077064
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English (en)
French (fr)
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高亚东
黄大伟
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南京航空航天大学
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Publication of WO2023142204A1 publication Critical patent/WO2023142204A1/zh

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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
    • 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
    • B64C11/16—Blades
    • 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
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic

Definitions

  • the invention relates to the field of straight flight devices, in particular to a helicopter rotor control device based on hydraulic torsion tube pitch change.
  • the new generation of helicopter rotor system mostly adopts hingeless wing design.
  • the specific form of the hingeless rotor is to retain the axial hinge, and use the deformation of the flexible beam section at the root of the composite blade to realize the flapping and shimmy of the blade.
  • the hingeless rotor no longer includes structures such as flapping hinges and shimmy hinges. It has the characteristics of simple structure, high reliability and maintainability, and also improves the control efficiency of the rotor.
  • the existing hingeless rotor still retains the traditional automatic tilter to realize the variable collective pitch and periodic variable pitch of the blades.
  • the present invention provides a helicopter rotor control device based on the hydraulic torsion tube variable pitch, the blade pitch control is realized by twisting the hydraulic section of the composite material torsion tube, and there is no automatic tilter rotor system,
  • the structure of the rotor system is simplified, the reliability of the rotor system is improved, and it also paves the way for the implementation of the high-order harmonic control (HHC) of the rotor to suppress the vibration load.
  • HHC high-order harmonic control
  • the present invention includes a blade structure, a variable-pitch propeller clamp system and a hydraulic system.
  • the blade structure includes a blade, a propeller clamp and a rotor hub sequentially connected by fasteners, and the rotor hub is connected to the rotor main shaft;
  • the variable pitch propeller clamp system includes a first rolling bearing, a fixed rotor propeller clamp, a pitch changing sleeve, a second rolling bearing, and a rotor rotating propeller clamp, wherein the first rolling bearing and the second rolling bearing are respectively installed on two sides of the fixed rotor propeller clamp.
  • the rotor rotating paddle clip is connected with the rotor fixed paddle clip through two rolling bearings;
  • the pitch changing sleeve is located between the rotor fixed paddle clip and the rotor rotating paddle clip, and the outer end surface of the pitch changing sleeve is fixedly connected with the rotor rotating paddle clip.
  • the inner end face of the variable pitch sleeve is fixedly connected with the rotor fixed propeller clip.
  • the hydraulic system controls hydraulic oil to transmit pressure to the inside of the pitch change sleeve.
  • the blades are connected to the variable pitch propeller clamp system through the propeller fastening bolts and the propeller fastening nuts, and the variable pitch propeller clamp system is connected to the horizontal axis of the propeller hub through the propeller clamp fastening bolts, and the propeller hub
  • the transverse shaft is connected with the main shaft of the rotor through axial fastening bolts and rotor brakes.
  • the hydraulic system includes a hydraulic control system, a top hydraulic module, a bottom hydraulic module, and a hydraulic pipeline.
  • the hydraulic control system controls the hydraulic oil to pass through the top hydraulic module and the bottom hydraulic module, and transmits the pressure to the pitch change sleeve through the hydraulic pipeline , to control the pressure inside the variable pitch sleeve.
  • the hydraulic control system uses a hydraulic collector ring to transmit hydraulic signals to the rotor hub.
  • the hydraulic control system uses slip rings to transmit control signals to the rotor hub.
  • the existing typical hingeless rotor realizes the variable pitch control through the variable pitch rod connected with the variable pitch cantilever and the automatic tilter.
  • the rotor system of the present invention realizes the blade pitch control by twisting the hydraulic section of the composite torsion tube , without an automatic tilter rotor system, which simplifies the structure of the rotor system, improves the reliability of the rotor system, and paves the way for the implementation of high-order harmonic control (HHC) of the rotor to suppress vibration loads.
  • HHC high-order harmonic control
  • the present invention can be applied to a helicopter, which simplifies the structure of the rotor system of the helicopter and improves the overall reliability of the helicopter.
  • Figure 1 is a front sectional view of the rotor system
  • Figure 2 is an exploded view of the rotor system as a whole
  • Figure 3 is a cross-sectional view of the pitch variable propeller clamp system
  • Figure 4 is an exploded view of the pitch variable propeller clamp system
  • Figure 5 is a schematic diagram of the assembly of the pitch variable propeller clamp system
  • Fig. 6 is a cross-sectional view of a variable pitch sleeve made of pressure change composite material
  • Fig. 7 is a schematic diagram of a variable pitch sleeve made of pressure change composite material
  • Fig. 8 is a schematic diagram of the internal hydraulic flow of the pressure variable material pitch variable system
  • FIG. 1 The specific structure of the present invention is shown in FIG. 1 , including a blade structure, a variable-pitch propeller clamp system 9 and a hydraulic system.
  • the blade 11 is connected to the variable pitch propeller clamp system 9 through the propeller fastening bolt 7 and the propeller fastening nut 10, and the pitch variable propeller clamp system 9 is connected to the horizontal axis 4 of the propeller hub through the propeller clamp fastening bolt 8.
  • the hub transverse shaft 4 is connected with the rotor main shaft 6 through the axial fastening bolt 1, the rotor brake 2, and jointly constitutes a whole rotor system.
  • the variable pitch propeller clamp system 9 includes a first rolling bearing 9a, a rotor fixed propeller clamp 9b, a pitch variable sleeve 9c, a rolling bearing 2-9d, and a rotor rotating propeller clamp 9e.
  • the rolling bearing 1-9a is installed on the left end surface of the rotor fixed paddle clamp 9b
  • the rolling bearing 2-9d is installed on the right end surface of the rotor fixed paddle clamp 9b
  • the rotor rotating paddle clamp 9e is connected with the rotor fixed paddle clamp 9b by these two bearings .
  • the pitch changing sleeve 9c is located between the fixed rotor blade clamp 9b and the rotor rotating blade clamp 9e, and enough space is left.
  • the outer end surface 12 of the pitch changing sleeve 9c is fixedly connected with the rotor rotating paddle clip 9e, and the inner end face 13 of the pitch changing sleeve 9c is fixedly connected with the rotor fixed paddle clip 9b.
  • the hydraulic system includes a hydraulic control system, a top hydraulic module 3, a bottom hydraulic module 5 and corresponding hydraulic pipelines.
  • the hydraulic control system controls the hydraulic oil to pass through the top hydraulic module 3 and the bottom hydraulic module 5, and transmits the pressure to the pitch-changing sleeve 9c through corresponding hydraulic pipes, so as to control the internal pressure of the pitch-changing sleeve 9c.
  • the hydraulic control system uses a hydraulic collector ring to transmit hydraulic signals to the rotor hub.
  • the hydraulic control system uses slip rings to transmit control signals to the rotor hub.

Abstract

本发明提供了一种基于液压扭管变距的直升机旋翼操纵装置，包括桨叶结构、变距桨夹系统和液压系统，所述的桨叶结构包括通过紧固件依次连接的桨叶、桨夹和旋翼桨毂，旋翼桨毂与旋翼主轴连接。所述的变距桨夹系统中距套筒位于旋翼固定桨夹和旋翼转动桨夹之间，变距套筒的外部端面与旋翼转动桨夹固连，变距套筒的内部端面与旋翼固定桨夹固连，当变距套筒内部的压力发生变化时，变距套筒两端会产生的扭转角度驱动旋翼转动桨夹产生角位移从而控制桨叶迎角。本发明采用无自动倾斜器设计，简化了结构，提高了旋翼系统的可靠性，同时也可以减少操纵结构，从而减轻结构重量，降低维护成本，进一步提高直升机的可靠性。

Description

基于液压扭管变距的直升机旋翼操纵装置 技术领域
本发明涉及直飞行装置领域，具体是一种基于液压扭管变距的直升机旋翼操纵装置。
背景技术
新一代直升机旋翼系统多采用无铰式翼设计。无铰式旋翼的具体形式是保留了轴向铰，利用复合材料桨叶根部的柔性梁段变形来实现桨叶挥舞、摆振。与传统的全铰接式旋翼相比，无铰式旋翼不再包含挥舞铰、摆振铰等结构，具有结构形式简单、可靠性和可维护性高的特点，同时也提高了旋翼的操纵功效。现有的无铰式旋翼仍然保留了传统的自动倾斜器来实现桨叶的变总距和周期变距。随着复合材料技术和控制技术的进步，在无铰式旋翼的基础上，利用新型复合材料的性质发展新型式的无自动倾斜器的旋翼系统成为了可能。
发明内容
本发明为了解决现有技术的问题，提供了一种基于液压扭管变距的直升机旋翼操纵装置，通过复合材料扭管的液压截面扭转来实现桨叶变距控制，无自动倾斜器旋翼系统，简化了旋翼系统结构，提高了旋翼系统的可靠性，也为实施旋翼的高阶谐波控制(HHC)抑制振动载荷铺平道路。
本发明包括桨叶结构、变距桨夹系统和液压系统，所述的桨叶结构包括通过紧固件依次连接的桨叶、桨夹和旋翼桨毂，旋翼桨毂与旋翼主轴连接；
所述的变距桨夹系统包括第一滚动轴承、旋翼固定桨夹、变距套筒、第二滚动轴承、旋翼转动桨夹，其中，第一滚动轴承和第二滚动轴承分别安装在旋翼固定桨夹的两端，旋翼转动桨夹通过两个滚动轴承与旋翼固定桨夹相连接；变距套筒位于旋翼固定桨夹和旋翼转动桨夹之间，变距套筒的外部端面与旋翼转动桨夹固连，变距套筒的内部端面与旋翼固定桨夹固连，当变距套筒内部的压力发生变化时，变距套筒两端会产生的扭转角度驱动旋翼转动桨夹产生角位移从而控制桨叶迎角；
所述的液压系统控制液压油将压力传输至变距套筒内部。
进一步改进，所述的桨叶通过桨叶紧固螺栓、桨叶紧固螺母与变距桨夹系统相连接，变距桨夹系统通过桨夹紧固螺栓与桨毂横轴相连接，桨毂横轴通过轴向紧固螺栓、 旋翼刹车与旋翼主轴相连接。
进一步改进，所述的液压系统包括液压控制系统、顶部液压模块、底部液压模块及液压管道，液压控制系统控制液压油通过顶部液压模块和底部液压模块，经由液压管道将压力传递至变距套筒，控制变距套筒内部的压力。
进一步改进，所述的液压控制系统采用液压集流环，将液压信号传递到旋翼桨毂上。
进一步改进，所述的液压控制系统采用集电环将控制信号传递到旋翼桨毂上。
本发明有益效果在于：
1、现有典型的无铰式旋翼是通过与变距悬臂和自动倾斜器相连的变距拉杆实现变距控制，本发明旋翼系统通过复合材料扭管的液压截面扭转来实现桨叶变距控制，无自动倾斜器旋翼系统，简化了旋翼系统结构，提高了旋翼系统的可靠性，也为实施旋翼的高阶谐波控制(HHC)抑制振动载荷铺平道路。
2、本发明可以应用在直升机上，简化了直升机的旋翼系统结构，提高了直升机整体的可靠性。
附图说明
图1为旋翼系统正向剖视图；
图2为旋翼系统整体爆炸图；
图3为变距桨夹系统剖视图；
图4为变距桨夹系统爆炸图；
图5为变距桨夹系统组装示意图；
图6为压变复合材料变距套筒剖视图；
图7为压变复合材料变距套筒示意图；
图8为压变材料变距系统内部液压流动示意图；
图中，1-轴向紧固螺栓、2-旋翼刹车、3-顶部液压模块、4-桨毂横轴、5-底部液压模块、6-旋翼主轴、7-桨叶紧固螺栓、8-桨夹紧固螺栓、9-变距桨夹系统、10-桨叶紧固螺母、11-桨叶、12-外部端面、13-内部端面、9a-第一滚动轴承、9b-旋翼固定桨夹、9c-变距套筒、9d-第二滚动轴承、9e-旋翼转动桨夹。
具体实施方式
下面结合附图对本发明作进一步说明。
本发明具体结构如图1所示，包括桨叶结构、变距桨夹系统9和液压系统。
所述的桨叶11通过桨叶紧固螺栓7、桨叶紧固螺母10与变距桨夹系统9相连接，变距桨夹系统9通过桨夹紧固螺栓8与桨毂横轴4相连接，桨毂横轴4通过轴向紧固螺栓1、旋翼刹车2与旋翼主轴6相连接，共同构成一整个旋翼系统。
所述的变距桨夹系统9包括第一滚动轴承9a、旋翼固定桨夹9b、变距套筒9c、滚动轴承2-9d、旋翼转动桨夹9e。其中，滚动轴承1-9a安装在旋翼固定桨夹9b的左端面，滚动轴承2-9d安装在旋翼固定桨夹9b的右端面，旋翼转动桨夹9e通过这两个轴承与旋翼固定桨夹9b相连接。变距套筒9c位于旋翼固定桨夹9b和旋翼转动桨夹9e二者之间，且留有足够的空间。变距套筒9c的外部端面12与旋翼转动桨夹9e固连，变距套筒9c的内部端面13与旋翼固定桨夹9b固连。当变距套筒内部的压力发生变化时，变距套筒两端会产生一个扭转角度，从而驱动旋翼转动桨夹产生角位移，来进行桨叶迎角的控制。
所述的液压系统包括液压控制系统、顶部液压模块3、底部液压模块5及相对应的液压管道。液压控制系统控制液压油通过顶部液压模块3和底部液压模块5，经由相对应的液压管道，将压力传递至变距套筒9c，从而起到控制变距套筒9c内部压力的作用。
进一步改进，所述的液压控制系统采用液压集流环，将液压信号传递到旋翼桨毂上。
进一步改进，所述的液压控制系统采用集电环将控制信号传递到旋翼桨毂上。
本发明具体应用途径很多，以上所述仅是本发明的优选实施方式，应当指出，对于本技术领域的普通技术人员来说，在不脱离本发明原理的前提下，还可以做出若干改进，这些改进也应视为本发明的保护范围。

Claims (5)

  1. 一种基于液压扭管变距的直升机旋翼操纵装置，其特征在于：包括桨叶结构、变距桨夹系统和液压系统，所述的桨叶结构包括通过紧固件依次连接的桨叶、桨夹和旋翼桨毂，旋翼桨毂与旋翼主轴连接；
    所述的变距桨夹系统包括第一滚动轴承、旋翼固定桨夹、变距套筒、第二滚动轴承、旋翼转动桨夹，其中，第一滚动轴承和第二滚动轴承分别安装在旋翼固定桨夹的两端，旋翼转动桨夹通过两个滚动轴承与旋翼固定桨夹相连接；变距套筒位于旋翼固定桨夹和旋翼转动桨夹之间，变距套筒的外部端面与旋翼转动桨夹固连，变距套筒的内部端面与旋翼固定桨夹固连，当变距套筒内部的压力发生变化时，变距套筒两端会产生的扭转角度驱动旋翼转动桨夹产生角位移从而控制桨叶迎角；
    所述的液压系统控制液压油将压力传输至变距套筒内部。
  2. 根据权利要求1所述的基于液压扭管变距的直升机旋翼操纵装置，其特征在于：所述的桨叶通过桨叶紧固螺栓、桨叶紧固螺母与变距桨夹系统相连接，变距桨夹系统通过桨夹紧固螺栓与桨毂横轴相连接，桨毂横轴通过轴向紧固螺栓、旋翼刹车与旋翼主轴相连接。
  3. 根据权利要求1所述的基于液压扭管变距的直升机旋翼操纵装置，其特征在于：所述的液压系统包括液压控制系统、顶部液压模块、底部液压模块及液压管道，液压控制系统控制液压油通过顶部液压模块和底部液压模块，经由液压管道将压力传递至变距套筒，控制变距套筒内部的压力。
  4. 根据权利要求3所述的基于液压扭管变距的直升机旋翼操纵装置，其特征在于：所述的液压控制系统采用液压集流环，将液压信号传递到旋翼桨毂上。
  5. 根据权利要求3所述的基于液压扭管变距的直升机旋翼操纵装置，其特征在于：所述的液压控制系统采用集电环将控制信号传递到旋翼桨毂上。
PCT/CN2022/077064 2022-01-27 2022-02-21 基于液压扭管变距的直升机旋翼操纵装置 WO2023142204A1 (zh)

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CN205707301U (zh) * 2016-04-20 2016-11-23 程靖 一种变桨距机构
CN113799971A (zh) * 2021-11-19 2021-12-17 中国航天空气动力技术研究院 一种被动式变距螺旋桨及螺旋桨驱动的无人机

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