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WO2019024398A1 - 内外襟翼交联装置 - Google Patents

内外襟翼交联装置 Download PDF

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Publication number
WO2019024398A1
WO2019024398A1 PCT/CN2017/117727 CN2017117727W WO2019024398A1 WO 2019024398 A1 WO2019024398 A1 WO 2019024398A1 CN 2017117727 W CN2017117727 W CN 2017117727W WO 2019024398 A1 WO2019024398 A1 WO 2019024398A1
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WO
WIPO (PCT)
Prior art keywords
wedge
linking device
piston
outer flap
axial
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/CN2017/117727
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English (en)
French (fr)
Inventor
黄勇
田忠良
吴强
邬旭辉
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.)
Commercial Aircraft Corp of China Ltd
Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of China Ltd
Original Assignee
Commercial Aircraft Corp of China Ltd
Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of China Ltd
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Application filed by Commercial Aircraft Corp of China Ltd, Shanghai Aircraft Design and Research Institute Commercial Aircraft Corporation of China Ltd filed Critical Commercial Aircraft Corp of China Ltd
Publication of WO2019024398A1 publication Critical patent/WO2019024398A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
    • B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps

Definitions

  • the invention relates to an inner and outer flap cross-linking device.
  • the highly precise and complex motion mechanism and drive system disposed on the trailing edge compartment of the wing enables free transition of the high lift airfoil between the various aerodynamic configurations/card positions.
  • the drive system is generally composed of a power output unit, a torque transmission line system and a high transmission ratio force/torque output actuator.
  • the main force transmission member of the actuator is generally processed by a high-strength high-quality steel machine, and has a high durability mechanical mechanism. Performance, but fatigue resistance and initial defect crack propagation performance is poor.
  • Airworthiness regulations require that a single failure of such a system must be considered in the design (and no matter how low the probability of failure), and that the aircraft must continue to have safe flight and landing capabilities after a system failure.
  • Each trailing edge flap generally has more than two drive actuators.
  • the airfoil When one of the actuators has a disengagement fault, the airfoil will have a greater degree of tilt (mainly represented by the chordwise movement of the airfoil end ribs). When this deformation displacement is too large, the wings on both sides will generate a rolling moment that exceeds the balance ability of the aircraft, thereby impeding flight safety.
  • a single-degree-of-freedom actuator ie, inner and outer flap cross-linking device, is arranged between the inner and outer flaps to reduce the excessive tilt of the faulty airfoil and provide airfoil auxiliary restraint, thereby ensuring system failure. The aircraft still has the ability to continue safe flight and landing.
  • An object of the present invention is to overcome the defects of the existing inner and outer flap cross-linking device and to provide a new inner and outer flap cross-linking device, which can realize the over-stroke forward buffering function, and has a simple structure and easy installation and maintenance.
  • an inner and outer flap cross-linking device comprising:
  • piston rod assembly disposed in the piston barrel assembly and radially fixed and axially movable relative to the cylinder barrel assembly;
  • An arcuate wedge member fixed to an outer side of the cylinder barrel assembly, the arcuate wedge member including a first wedge-shaped pressing surface;
  • recessed ring being fixed to an outer side of the piston rod assembly, the recessed ring comprising a second wedge-shaped pressing surface;
  • the inner and outer flap cross-linking device of the present invention can achieve the following beneficial technical effects: the over-stroke forward buffering function can be realized, and the structure is simple, and the installation and maintenance are easy.
  • the piston barrel assembly is provided with a piston barrel serration at a central portion thereof, the piston rod assembly being provided with piston rod serrations at its outer ends, wherein the first wedge-shaped extrusion surface is When the second wedge-shaped pressing surface is in contact, a radial force is also generated to hold the piston barrel serration and the piston rod serration to achieve reverse locking.
  • the inner and outer flap cross-linking device of the present invention can achieve the following beneficial technical effects: the over-travel reverse locking function can be realized.
  • the piston barrel assembly is three separate centrally convex cylindrical barrel assemblies having radial elastic deformation capabilities.
  • the inner and outer flap cross-linking device further comprises:
  • the detecting sensor being fixed to the axial stroke stop
  • the detecting sensor when the distance between the detecting sensor and the target is less than a predetermined threshold, the detecting sensor sends an electrical signal to achieve overtravel detection.
  • the inner and outer flap cross-linking device of the present invention can achieve the following beneficial technical effects: the overtravel detecting function can be realized.
  • the axial stroke stop further comprises a first axial stop impact surface
  • the recess further includes a second axial stop impact surface
  • the inner and outer flap cross-linking device of the present invention can achieve the following beneficial technical effects: the over-travel positive stop function can be realized.
  • the inner and outer flap cross-linking device further comprises a radial spacer disposed between the arcuate wedge and the piston barrel assembly to achieve an outer diameter adjustment of the curved wedge pressing surface.
  • the inner and outer flap cross-linking device further includes an axial spacer disposed between the recess and the piston rod assembly to achieve free stroke adjustment.
  • FIG. 1 is a perspective view of an inner and outer flap cross-linking apparatus according to an embodiment of the present invention.
  • Figure 2 is a cross-sectional view showing an inner and outer flap cross-linking apparatus according to an embodiment of the present invention.
  • FIG. 1 is a perspective view of an inner and outer flap cross-linking apparatus according to an embodiment of the present invention.
  • Figure 2 is a cross-sectional view showing an inner and outer flap cross-linking apparatus according to an embodiment of the present invention.
  • the inner and outer flap cross-linking apparatus includes:
  • piston rod assembly 1 the piston rod assembly 1 is disposed in the piston barrel assembly 2, and is radially fixed and axially movable relative to the cylinder barrel assembly 2;
  • the arcuate wedge member 3 is fixed on the outer side of the piston barrel assembly 2, the curved wedge member 3 includes a first wedge-shaped pressing surface 7;
  • the recess 4 is fixed on the outer side of the piston rod assembly 1, the recess 4 includes a second wedge-shaped pressing surface 8;
  • the inner and outer flap cross-linking device of the present invention can realize the over-stroke forward buffering function, and has a simple structure and easy installation and maintenance. Moreover, the inner and outer flap cross-linking device of the present invention is small in size and light in weight.
  • the inner and outer flap cross-linking device of the invention can reduce the excessive tilt of the faulty airfoil and avoid the unfavorable vibration of the faulty airfoil to meet the airworthiness regulations. Continued safe flight and landing capability requirements for a single actuator of the aircraft flap to disengage.
  • the distance between the two inner and outer flap cross-linking devices respectively fixed to the mounting points of the inner and outer flap end ribs will be elongated or shortened.
  • the change causes the piston rod assembly 1 to stretch or compress in the axial direction relative to the cylinder barrel assembly 2.
  • the inner and outer flap cross-linking device further comprises:
  • the axial stroke stopper 13 and the axial stroke stopper 13 are fixed on the outer side of the cylinder barrel assembly 2;
  • the detecting sensor 5 is fixed on the axial stroke stopper 13;
  • Target 6 the target 6 is fixed on the recess 4;
  • the detecting sensor 5 when the distance between the detecting sensor 5 and the target 6 is less than a predetermined threshold, the detecting sensor 5 sends an electric signal to realize the overtravel detecting of the distance between the two mounting points of the inner and outer flap cross-linking device.
  • the axial stroke stop 13 further includes a first axial stop impact surface 9;
  • the recess 4 further includes a second axial stop impact surface 10;
  • the detecting sensor 5 will emit an electrical signal to realize overtravel detection.
  • the first wedge-shaped pressing surface 7 of the curved wedge member 3 is brought into contact with the second wedge-shaped pressing surface 8 of the recessed ring 4 to generate an axial force to achieve positive (axial) cushioning.
  • the first axial stop impact surface 9 of the axial travel stop 13 is in contact with the second axial stop impact surface 10 of the recess 4 to effect a positive (axial) stop.
  • the inner and outer flap cross-linking device of the present invention has an axis substantially along the chord of the flap, the rear end is attached to the inner flap end rib, and the front end is attached to the outer flap end rib.
  • the free travel stroke limit along the axial direction needs to be determined by combining the full-stroke multi-body dynamics and finite element deformation simulation results.
  • the free motion stroke limit needs to cover the change of the distance between the two installation points of the inner and outer flap cross-linking device caused by the difference of the flap motion mechanism and the aerodynamic load in the full stroke range, and the inner and outer flap cross-linking device must not obstruct the flap Normal use.
  • the piston barrel assembly 2 is provided with a piston barrel serration 11 at its inner central portion
  • the piston rod assembly 1 is provided with piston rod serrations 12 at its outer ends, wherein the first wedge-shaped extrusion of the curved wedge member 3
  • a radial force is also generated to hold the piston serration 11 and the piston rod serration 12 to achieve reverse locking.
  • the inner and outer flap cross-linking device can provide an overtravel reverse lock function in addition to the overtravel target proximity detection and forward buffer stop function.
  • the piston barrel assembly 2 is a three-part, split, centrally convex piston barrel assembly, piston
  • the cartridge assembly 2 has a radial elastic deformation ability.
  • the piston barrel assembly 2 is a centrally convex pre-deformed piston barrel assembly.
  • the piston barrel assembly 2 has a certain convex shape and/or a certain pre-deformation in the middle, so that when the first wedge-shaped pressing surface 7 of the curved wedge member 3 and the second wedge-shaped pressing surface of the recessed ring 4 At the time of contact, a radial force is also generated to hold the piston serration 11 and the piston rod serration 12 to achieve reverse locking. That is to say, the above-mentioned central convex pre-deformation of the cylinder barrel assembly 2 provides a margin for the piston barrel serrations 11 and the piston rod serrations 12 to be gripped.
  • the cylinder barrel assembly 2 and the recessed ring 4 are made of a high strength metal material, such as a Ti-6Al-4V material.
  • the piston serration 11 and the piston rod serration 12 are made of a high strength metal material, such as Ti-6Al-4V material.
  • Ti-6Al-4V material is only a preferred material form of the piston barrel assembly, the recessed ring, the piston barrel serration and/or the piston rod serration in the inner and outer flap cross-linking device of the present application, and those skilled in the art are It is to be understood on the basis of the disclosure of the present application that other suitable materials may be employed without departing from the scope of the invention as claimed.
  • the detecting sensor 5 is a proximity detecting sensor.
  • the inner and outer flap cross-linking device further comprises a radial gasket (for example, a metal peelable gasket) disposed between the curved wedge member 3 and the cylinder barrel assembly 2 to realize the curved wedge-shaped pressing surface.
  • a radial gasket for example, a metal peelable gasket
  • the outer diameter of the first wedge-shaped pressing surface of the curved wedge member can be changed, and the buffer field external field adjustment can be better achieved.
  • the inner and outer flap cross-linking device further includes an axial spacer (e.g., a metal spacer) disposed between the recess 4 and the piston rod assembly 1 to achieve free stroke adjustment.
  • an axial spacer e.g., a metal spacer

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Fluid-Damping Devices (AREA)
  • Actuator (AREA)
  • Vibration Dampers (AREA)

Abstract

一种内外襟翼交联装置，包括：活塞筒组件(2)；活塞杆组件(1)，所述活塞杆组件设置于所述活塞筒组件内，且相对于所述活塞筒组件径向固定、轴向可动；弧形楔形件(3)，所述弧形楔形件固定于所述活塞筒组件的外侧上，所述弧形楔形件包括第一楔形挤压面(7)；凹圈(4)，所述凹圈固定于所述活塞杆组件的外侧上，所述凹圈包括第二楔形挤压面(8)；当所述第一楔形挤压面与所述第二楔形挤压面接触时，产生轴向力以实现正向缓冲。该内外襟翼交联装置能实现超行程正向缓冲功能，而且结构简单，安装维护容易。

Description

内外襟翼交联装置 技术领域
本发明涉及内外襟翼交联装置。
背景技术
由于受到机场跑道长度、起落架轮胎速度的限制以及为了提高飞机起降安全性，高升力装置在现代大型飞机设计中得以不断发展和广泛应用。布置在机翼后缘舱的高度精密和复杂的运动机构和驱动系统，实现了高升力翼面在各气动构型/卡位之间的自由转换。驱动系统一般由动力输出单元、力矩传递线系和高传动比力/力矩输出作动器组成，作动器主要传力构件一般为高强度优质钢机加工而成，具有较高的耐久性机械性能，但抗疲劳和初始缺陷裂纹扩展性能较差。在飞机运营过程中不拆卸和分解作动器情况下，地面维护人员无法对其进行有效的损伤检查。适航规章要求在设计中必须对此类系统的单一故障加以考虑(并无论其故障发生概率多低)，须确保系统故障后飞机仍然具有继续安全飞行和着陆能力。
每块后缘襟翼一般具有两个以上驱动作动器，当其中某一作动器发生脱开故障时，翼面将产生较大程度的倾斜(主要表现为翼面端肋弦向运动)，当这种变形位移过大时，两侧机翼将产生超出飞机配平能力的滚转力矩，从而妨碍飞行安全。在内外襟翼之间布置一个沿襟翼弦向单自由度作动器即内外襟翼交联装置，可起到降低故障翼面过度倾斜和提供翼面辅助约束的作用，进而确保系统故障后飞机仍然具有继续安全飞行和着陆能力。
然而，现有技术的内外襟翼交联装置一般结构较为复杂，且安装维护不便。
发明内容
本发明的一个目的在于，克服现有内外襟翼交联装置的缺陷，提供一种新的内外襟翼交联装置，其能实现超行程正向缓冲功能，而且结构简单，安装维护容易。
本发明的以上目的通过一种内外襟翼交联装置来实现，该内外襟翼交联装置包括：
活塞筒组件；
活塞杆组件，所述活塞杆组件设置于所述活塞筒组件内，且相对于所述活塞筒组件径向固定、轴向可动；
弧形楔形件，所述弧形楔形件固定于所述活塞筒组件的外侧上，所述弧形楔形件包括第一楔形挤压面；
凹圈，所述凹圈固定于所述活塞杆组件的外侧上，所述凹圈包括第二楔形挤压面；
当所述第一楔形挤压面与所述第二楔形挤压面接触时，产生轴向力以实现正向缓冲。
根据上述技术方案，本发明的内外襟翼交联装置能起到以下有益技术效果：能实现超行程正向缓冲功能，而且结构简单，安装维护容易。
较佳的是，所述活塞筒组件在其内侧中部设有活塞筒锯齿，所述活塞杆组件在其外侧两端设有活塞杆锯齿，其中，当所述第一楔形挤压面与所述第二楔形挤压面接触时，还产生径向力，以将所述活塞筒锯齿和所述活塞杆锯齿抱紧，实现逆向锁死。
根据上述技术方案，本发明的内外襟翼交联装置能起到以下有益技术效果：能实现超行程逆向锁死功能。
较佳的是，所述活塞筒组件是三块分离式中部外凸的活塞筒组件，所述活塞筒组件具有径向弹性变形能力。
较佳的是，所述内外襟翼交联装置还包括：
轴向行程止动件，所述轴向行程止动件固定于所述活塞筒组件的外侧上；
探测传感器，所述探测传感器固定于所述轴向行程止动件上；
标靶，所述标靶固定于所述凹圈上；
其中，当所述探测传感器与所述标靶之间的距离小于预定阈值时，所述探测传感器发出电信号以实现超行程探测。
根据上述技术方案，本发明的内外襟翼交联装置能起到以下有益技术效果：能实现超行程探测功能。
较佳的是，所述轴向行程止动件还包括第一轴向止动冲击面；
所述凹圈还包括第二轴向止动冲击面；
当所述第一轴向止动冲击面与所述第二轴向止动冲击面接触时，实现正向止动。
根据上述技术方案，本发明的内外襟翼交联装置能起到以下有益技术效果：能实现超行程正向止动功能。
较佳的是，所述内外襟翼交联装置还包括设置于所述弧形楔形件与所述活塞筒组件之间的径向垫片，以实现弧形楔形件挤压面外径调节。
较佳的是，所述内外襟翼交联装置还包括设置于所述凹圈与所述活塞杆组件之间的轴向垫片，以实现自由行程调节。
附图说明
图1是本发明一实施例的内外襟翼交联装置的立体图。
图2是本发明一实施例的内外襟翼交联装置的剖视图。
附图标记列表
1、活塞杆组件
2、活塞筒组件
3、弧形楔形件
4、凹圈
5、探测传感器
6、标靶
7、第一楔形挤压面
8、第二楔形挤压面
9、第一轴向止动冲击面
10、第二轴向止动冲击面
11、活塞筒锯齿
12、活塞杆锯齿
13、轴向行程止动件
具体实施方式
以下将描述本发明的具体实施方式，需要指出的是，在这些实施方式的具体描述过程中，为了进行简明扼要的描述，本说明书不可能对实际的实施方式的所有特征均作详尽的描述。应当可以理解的是，在任意一种实施方式的实际实施过程中，正如在任意一个工程项目或者设计项目的过程中，为了实现开发者的具体目标，为了满足系统相关的或者商业相关的限制，常常会做出各种各样的具体决策，而这也会从一种实施方式到另一种实施方式之间发生改变。此外，还可以理解的是，虽然这种开发过程中所作出的努力可能是复杂并且冗长的，然而对于与本发明公开的内容相关的本领域的普通技术人员而言，在本公开揭露的技术内容的基础上进行的一些设计、制造或者生产等变更只是常规的技术手段，不应当理解为本公开的内容不充分。
除非另作定义，权利要求书和说明书中使用的技术术语或者科学术语应当为本发明所属技术领域内具有一般技能的人士所理解的通常意义。本发明专利申请说明书以及权利要求书中使用的“第一”、“第二”以及类似的词语并不表示任何顺序、数量或者重要性，而只是用来区分不同的组成部分。“一个”或者“一”等类似词语并不表示数量限制，而是表示存在至少一个。“包括”或者“包含”等类似的词语意指出现在“包括”或者“包含”前面的元件或者物件涵盖出现在“包括”或者“包含”后面列举的元件或者物件及其等同元件，并不排除其他元件或者物件。“连接”或者“相连”等类似的词语并非限定于物理的或者机械的连接，也不限于 是直接的还是间接的连接。
图1是本发明一实施例的内外襟翼交联装置的立体图。图2是本发明一实施例的内外襟翼交联装置的剖视图。
如图1-2所示，根据本发明一示例性而非排他性的实施例，内外襟翼交联装置包括：
活塞筒组件2；
活塞杆组件1，活塞杆组件1设置于活塞筒组件2内，且相对于活塞筒组件2径向固定、轴向可动；
弧形楔形件3，弧形楔形件3固定于活塞筒组件2的外侧上，弧形楔形件3包括第一楔形挤压面7；
凹圈4，凹圈4固定于活塞杆组件1的外侧上，凹圈4包括第二楔形挤压面8；
当第一楔形挤压面7与第二楔形挤压面8接触时，产生轴向力以实现正向缓冲。
这样，本发明的内外襟翼交联装置能实现超行程正向缓冲功能，而且结构简单，安装维护容易。而且，本发明的内外襟翼交联装置体积较小，重量较轻。
当后缘襟翼任一驱动作动器脱开故障时，本发明的内外襟翼交联装置能起到降低故障翼面过度倾斜和避免故障翼面不利振动的作用，以满足适航规章对飞机襟翼单一作动器脱开故障下的继续安全飞行和着陆能力要求。
具体地说，当后缘襟翼任一驱动作动器脱开故障时，内外襟翼交联装置两个分别固定于内外襟翼端肋的安装点之间的距离将发生伸长或缩短的变化，从而导致活塞杆组件1相对于活塞筒组件2沿轴线方向拉伸或压缩运动。
较佳的是，内外襟翼交联装置还包括：
轴向行程止动件13，轴向行程止动件13固定于活塞筒组件2的外侧上；
探测传感器5，探测传感器5固定于轴向行程止动件13上；
标靶6，标靶6固定于凹圈4上；
其中，当探测传感器5与标靶6之间的距离小于预定阈值时，探测传感器5发出电信号以实现内外襟翼交联装置两安装点距离的超行程探测。
较佳的是，轴向行程止动件13还包括第一轴向止动冲击面9；
凹圈4还包括第二轴向止动冲击面10；
当第一轴向止动冲击面9与第二轴向止动冲击面10接触时，实现正向止动。
具体地说，当活塞杆组件1相对于活塞筒组件2沿任意方向运动超行程，探测传感器5与标靶6之间的距离小于预定阈值时，探测传感器5将发出电信号以实现超行程探测。接着，弧形楔形件3的第一楔形挤压面7与凹圈4的第二楔形挤压面8接触，产生轴向力，以实现正向(轴向)缓冲。最后，轴向行程止动件13的第一轴向止动冲击面9与凹圈4的第二轴向止动冲击面10接触，实现正向(轴向)止动。
较佳的是，本发明的内外襟翼交联装置轴线大致沿襟翼弦向，后端安装于内襟翼端肋，前端安装于外襟翼端肋。沿轴向自由运动行程限制，需要结合全行程多体动力学和有限元变形仿真结果进行确定。该自由运动行程限制需覆盖全行程范围内外襟翼运动机构差异和气动载荷作用导致的内外襟翼交联装置两个安装点之间距离的变化，且内外襟翼交联装置不得妨碍襟翼的正常使用。
较佳的是，活塞筒组件2在其内侧中部设有活塞筒锯齿11，活塞杆组件1在其外侧两端设有活塞杆锯齿12，其中，当弧形楔形件3的第一楔形挤压面7与凹圈4的第二楔形挤压面8接触时，还产生径向力，以将活塞筒锯齿11和活塞杆锯齿12抱紧，实现逆向锁死。
也就是说，根据本发明的以上较佳实施例，内外襟翼交联装置除了可提供超行程靶标接近探测和正向缓冲止动功能以外，还可提供超行程逆向锁死功能。
较佳的是，活塞筒组件2是三块分离式中部外凸的活塞筒组件，活塞 筒组件2具有径向弹性变形能力。
这样，活塞筒锯齿11和活塞杆锯齿12可在径向力下较好地实现抱紧。
较佳的是，活塞筒组件2是中部外凸预变形的活塞筒组件。
这样，活塞筒组件2在中部具有一定的外凸形状和/或具有一定的预变形，因此，当弧形楔形件3的第一楔形挤压面7与凹圈4的第二楔形挤压面8接触时，还产生径向力，以将活塞筒锯齿11和活塞杆锯齿12抱紧，实现逆向锁死。也就是说，活塞筒组件2的上述中部外凸预变形提供了活塞筒锯齿11和活塞杆锯齿12抱紧的裕度。
较佳的是，活塞筒组件2和凹圈4由高强度金属材料制成，例如由Ti-6Al-4V材料制成。
较佳的是，活塞筒锯齿11和活塞杆锯齿12由高强度金属材料制成，例如由Ti-6Al-4V材料制成。
当然，上述Ti-6Al-4V材料仅仅是本申请内外襟翼交联装置中的活塞筒组件、凹圈、活塞筒锯齿和/或活塞杆锯齿的一种较佳材料形式，本领域技术人员在本申请公开内容的基础上可以理解，也可采用其他合适的材料，而不脱离本申请权利要求的保护范围。
较佳的是，探测传感器5是接近探测传感器。
较佳的是，内外襟翼交联装置还包括设置于弧形楔形件3与活塞筒组件2之间的径向垫片(例如金属可剥垫片)，以实现弧形楔形件挤压面外径调节。
这样，通过在弧形楔形件与活塞筒组件之间加装(设置)径向垫片，可改变弧形楔形件的第一楔形挤压面的外径，可以较好地实现缓冲性能外场调节。
较佳的是，内外襟翼交联装置还包括设置于凹圈4与活塞杆组件1之间的轴向垫片(例如金属垫片)，以实现自由行程调节。
这样，通过在凹圈与活塞杆组件之间加装(设置)轴向垫片，可以较好地实现自由行程调节。
上面已经描述了一些示例性实施例。然而，应该理解的是，可以做出 各种修改。例如，如果所描述的技术以不同的顺序执行和/或如果所描述的系统、架构、设备或电路中的组件以不同方式被组合和/或被另外的组件或其等同物替代或补充，则可以实现合适的结果。相应地，其他实施方式也落入权利要求的保护范围内。

Claims (7)

  1. 一种内外襟翼交联装置，包括：
    活塞筒组件；
    活塞杆组件，所述活塞杆组件设置于所述活塞筒组件内，且相对于所述活塞筒组件径向固定、轴向可动；
    弧形楔形件，所述弧形楔形件固定于所述活塞筒组件的外侧上，所述弧形楔形件包括第一楔形挤压面；
    凹圈，所述凹圈固定于所述活塞杆组件的外侧上，所述凹圈包括第二楔形挤压面；
    当所述第一楔形挤压面与所述第二楔形挤压面接触时，产生轴向力以实现正向缓冲。
  2. 如权利要求1所述的内外襟翼交联装置，其特征在于，所述活塞筒组件在其内侧中部设有活塞筒锯齿，所述活塞杆组件在其外侧两端设有活塞杆锯齿，其中，当所述第一楔形挤压面与所述第二楔形挤压面接触时，还产生径向力，以将所述活塞筒锯齿和所述活塞杆锯齿抱紧，实现逆向锁死。
  3. 如权利要求2所述的内外襟翼交联装置，其特征在于，所述活塞筒组件是三块分离式中部外凸的活塞筒组件，所述活塞筒组件具有径向弹性变形能力。
  4. 如权利要求1-3中的任意一项所述的内外襟翼交联装置，其特征在于，所述内外襟翼交联装置还包括：
    轴向行程止动件，所述轴向行程止动件固定于所述活塞筒组件的外侧上；
    探测传感器，所述探测传感器固定于所述轴向行程止动件上；
    标靶，所述标靶固定于所述凹圈上；
    其中，当所述探测传感器与所述标靶之间的距离小于预定阈值时，所述探测传感器发出电信号以实现超行程探测。
  5. 如权利要求4所述的内外襟翼交联装置，其特征在于，
    所述轴向行程止动件还包括第一轴向止动冲击面；
    所述凹圈还包括第二轴向止动冲击面；
    当所述第一轴向止动冲击面与所述第二轴向止动冲击面接触时，实现正向止动。
  6. 如权利要求1-3中的任意一项所述的内外襟翼交联装置，其特征在于，所述内外襟翼交联装置还包括设置于所述弧形楔形件与所述活塞筒组件之间的径向垫片，以实现弧形楔形件挤压面外径调节。
  7. 如权利要求1-3中的任意一项所述的内外襟翼交联装置，其特征在于，所述内外襟翼交联装置还包括设置于所述凹圈与所述活塞杆组件之间的轴向垫片，以实现自由行程调节。
PCT/CN2017/117727 2017-07-31 2017-12-21 内外襟翼交联装置 Ceased WO2019024398A1 (zh)

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CN107161325B (zh) * 2017-07-31 2018-09-11 中国商用飞机有限责任公司 内外襟翼交联装置
CN112678151B (zh) * 2021-01-13 2022-04-01 中国商用飞机有限责任公司 襟翼间交联装置
CN113291458B (zh) * 2021-06-25 2024-07-19 庆安集团有限公司 飞机高升力系统用内外襟翼交联装置

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