CN114987744B - Electromagnetic damping shimmy damper for front wheel of airplane - Google Patents
Electromagnetic damping shimmy damper for front wheel of airplane Download PDFInfo
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- CN114987744B CN114987744B CN202210555539.8A CN202210555539A CN114987744B CN 114987744 B CN114987744 B CN 114987744B CN 202210555539 A CN202210555539 A CN 202210555539A CN 114987744 B CN114987744 B CN 114987744B
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- 238000013016 damping Methods 0.000 title claims abstract description 17
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 21
- 229910052802 copper Inorganic materials 0.000 claims abstract description 21
- 239000010949 copper Substances 0.000 claims abstract description 21
- 230000005540 biological transmission Effects 0.000 claims abstract description 6
- 230000033001 locomotion Effects 0.000 abstract description 12
- 230000000694 effects Effects 0.000 abstract description 5
- 230000005674 electromagnetic induction Effects 0.000 abstract description 4
- 230000007246 mechanism Effects 0.000 abstract description 2
- 230000006698 induction Effects 0.000 abstract 3
- 230000004907 flux Effects 0.000 description 5
- 230000005415 magnetization Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 101100233916 Saccharomyces cerevisiae (strain ATCC 204508 / S288c) KAR5 gene Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
- B64C25/505—Shimmy damping
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F6/00—Magnetic springs; Fluid magnetic springs, i.e. magnetic spring combined with a fluid
- F16F6/005—Magnetic springs; Fluid magnetic springs, i.e. magnetic spring combined with a fluid using permanent magnets only
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Vibration Prevention Devices (AREA)
Abstract
Description
技术领域Technical Field
本发明涉及永磁式电磁阻尼器领域，尤其涉及一种飞机前轮电磁阻尼减摆器。The invention relates to the field of permanent magnet electromagnetic dampers, in particular to an electromagnetic damping damper for a front wheel of an aircraft.
背景技术Background Art
起落架摆振现象是一种危害性的自激振动。当发生起落架摆振现象时，飞行员往往无法及时采取应对措施，此时就会对飞机起落架及飞机机构造成破坏。解决飞机起落架摆振问题最为有效可靠的方法是安装减摆器。工程上普遍采用干摩擦式和油液式的减摆器。干摩擦式减摆器在结构及价格方面存在较大优势，但是干摩擦式减摆器在滑跑速度较低或者较高的工况下，会提供超过减摆所需的阻尼值，影响飞机滑跑的稳定性以及操纵性能。油液式减摆器虽然可以克服该问题，但是单独的液压源会增加全电飞机的整体重量。Landing gear shimmy is a harmful self-excited vibration. When the landing gear shimmy occurs, the pilot is often unable to take timely countermeasures, which will cause damage to the aircraft landing gear and aircraft structure. The most effective and reliable way to solve the problem of aircraft landing gear shimmy is to install a shimmy damper. Dry friction and oil-type shimmy dampers are commonly used in engineering. Dry friction shimmy dampers have great advantages in structure and price, but dry friction shimmy dampers will provide a damping value that exceeds the required shimmy reduction under conditions of low or high taxiing speeds, affecting the stability and handling performance of the aircraft taxiing. Although oil-type shimmy dampers can overcome this problem, a separate hydraulic source will increase the overall weight of the all-electric aircraft.
发明内容Summary of the invention
本发明所要解决的技术问题是针对背景技术中所涉及到的缺陷，提供一种飞机前轮电磁阻尼减摆器。The technical problem to be solved by the present invention is to provide an electromagnetic damping device for the front wheel of an aircraft in view of the defects involved in the background technology.
本发明为解决上述技术问题采用以下技术方案：The present invention adopts the following technical solutions to solve the above technical problems:
一种飞机前轮电磁阻尼减摆器，包括第一转子盘、第二转子盘、定子盘、N对磁极、转轴和法兰铜套，N为大于等于3的自然数；An electromagnetic damping device for front wheels of an aircraft comprises a first rotor disk, a second rotor disk, a stator disk, N pairs of magnetic poles, a rotating shaft and a flange copper sleeve, wherein N is a natural number greater than or equal to 3;
所述法兰铜套套在所述转轴上、和转轴间隙配合，且法兰铜套在转轴上轴向固定，使得法兰铜套能够相对转轴自由转动；The copper flange sleeve is sleeved on the rotating shaft and has clearance with the rotating shaft, and the copper flange sleeve is axially fixed on the rotating shaft, so that the copper flange sleeve can rotate freely relative to the rotating shaft;
所述第一转子盘、第二转子盘、定子盘均呈圆盘状，中心均设有通孔；The first rotor disk, the second rotor disk and the stator disk are all in the shape of disks, and are provided with through holes in the centers;
所述定子盘套在所述法兰铜套外、和所述法兰铜套过盈配合；所述第一转子盘、第二转子盘对称设置在所述定子盘两侧，均通过其中心通孔和所述转轴同轴固连；The stator disc is sleeved outside the flange copper sleeve and has an interference fit with the flange copper sleeve; the first rotor disc and the second rotor disc are symmetrically arranged on both sides of the stator disc, and are both coaxially fixedly connected to the rotating shaft through their central through holes;
所述N对磁极周向均匀设置在所述定子盘上；每一对磁极均对称设置在定子盘的两个端面上、和定子盘固连，且充磁方向相反；所述定子盘同一侧上相邻磁极的充磁方向相反，且磁极远离定子盘的一端均设有极靴；The N pairs of magnetic poles are evenly arranged on the stator disk in the circumferential direction; each pair of magnetic poles is symmetrically arranged on the two end surfaces of the stator disk, fixedly connected to the stator disk, and has opposite magnetization directions; the magnetization directions of adjacent magnetic poles on the same side of the stator disk are opposite, and a pole shoe is provided at one end of the magnetic pole away from the stator disk;
所述第一转动盘、第二转动盘和所述定子盘上的磁极之间存在气隙；There is an air gap between the first rotating disk, the second rotating disk and the magnetic poles on the stator disk;
所述定子盘通过支架和飞机前起落架外筒固连，所述转轴通过传动装置和飞机前起落架转动套筒相连。The stator disc is fixedly connected to the outer cylinder of the front landing gear of the aircraft through a bracket, and the rotating shaft is connected to the rotating sleeve of the front landing gear of the aircraft through a transmission device.
作为本发明一种飞机前轮电磁阻尼减摆器进一步的优化方案，N=6。As a further optimization solution of the electromagnetic damping device for the front wheel of an aircraft according to the present invention, N=6.
当飞机前轮产生的摆振运动通过传动装置譬如齿轮箱传递到电磁阻尼器后，摆振运动转化为转轴的转动，运用电磁感应原理，第一、第二转子盘在跟随转轴转动时，在磁场中切割磁感线产生感应电流，感应电流的磁场会阻碍第一、第二转子盘在磁场中的运动，并且使第一、第二转子盘的动能转变为热能。When the oscillating motion generated by the front wheel of the aircraft is transmitted to the electromagnetic damper through a transmission device such as a gear box, the oscillating motion is converted into the rotation of the rotating shaft. Using the principle of electromagnetic induction, the first and second rotor disks cut the magnetic flux lines in the magnetic field to generate induced current when they rotate with the rotating shaft. The magnetic field of the induced current will hinder the movement of the first and second rotor disks in the magnetic field and convert the kinetic energy of the first and second rotor disks into heat energy.
本发明采用以上技术方案与现有技术相比，具有以下技术效果：Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects:
本发明通过永磁式电磁阻尼器设计，运用电磁感应原理，转子盘在磁场中切割磁感线的运动会产生感应电流，感应电流的磁场会阻碍转子盘在磁场中的运动，并且使转子盘的动能转变为热能，从而达到前轮减摆的效果，与传统的摩擦阻尼器、油液阻尼器相比，电磁阻尼器的材料属性不会受到影响，并且便于维护，对环境友好。The present invention adopts the design of permanent magnet electromagnetic damper and applies the principle of electromagnetic induction. The movement of the rotor disk cutting the magnetic flux lines in the magnetic field will generate an induced current. The magnetic field of the induced current will hinder the movement of the rotor disk in the magnetic field and convert the kinetic energy of the rotor disk into heat energy, thereby achieving the effect of reducing the swing of the front wheel. Compared with traditional friction dampers and oil dampers, the material properties of the electromagnetic damper will not be affected, and it is easy to maintain and environmentally friendly.
附图说明BRIEF DESCRIPTION OF THE DRAWINGS
图1是本发明的结构示意图；Fig. 1 is a schematic structural diagram of the present invention;
图2是本发明的剖视示意图；Fig. 2 is a schematic cross-sectional view of the present invention;
图3是本发明工作时的原理示意图；Fig. 3 is a schematic diagram of the working principle of the present invention;
图4是本发明具体应用时的组装示意图。FIG. 4 is a schematic diagram of the assembly of the present invention when it is used in a specific application.
图中，1-电磁阻尼器，2-飞机前起落架外筒，3-飞机前起落架转动套筒，4-第一转子盘，5-定子盘，6-磁极，7-极靴，8-转轴，9-法兰铜套，10-第二转子盘。In the figure, 1-electromagnetic damper, 2-aircraft front landing gear outer cylinder, 3-aircraft front landing gear rotating sleeve, 4-first rotor disk, 5-stator disk, 6-magnetic pole, 7-pole shoe, 8-rotating shaft, 9-flange copper sleeve, 10-second rotor disk.
具体实施方式DETAILED DESCRIPTION
下面结合附图对本发明的技术方案做进一步的详细说明：The technical solution of the present invention is further described in detail below in conjunction with the accompanying drawings:
本发明可以以许多不同的形式实现，而不应当认为限于这里所述的实施例。相反，提供这些实施例以便使本公开透彻且完整，并且将向本领域技术人员充分表达本发明的范围。在附图中，为了清楚起见放大了组件。The present invention can be implemented in many different forms and should not be considered to be limited to the embodiments described herein. On the contrary, these embodiments are provided to make this disclosure thorough and complete, and will fully express the scope of the present invention to those skilled in the art. In the accompanying drawings, components are enlarged for clarity.
应当理解，尽管这里可以使用术语第一、第二、第三等描述各个元件、组件和/或部分，但这些元件、组件和/或部分不受这些术语限制。这些术语仅仅用于将元件、组件和/或部分相互区分开来。因此，下面讨论的第一元件、组件和/或部分在不背离本发明教学的前提下可以成为第二元件、组件或部分。It should be understood that, although the terms first, second, third, etc. can be used here to describe various elements, components and/or parts, these elements, components and/or parts are not limited by these terms. These terms are only used to distinguish elements, components and/or parts from each other. Therefore, the first element, component and/or part discussed below can become the second element, component or part without departing from the teaching of the present invention.
如图1、图2所示，本发明公开了一种飞机前轮电磁阻尼减摆器，包括第一转子盘、第二转子盘、定子盘、N对磁极、转轴和法兰铜套，N为大于等于3的自然数；As shown in FIG. 1 and FIG. 2 , the present invention discloses an electromagnetic damping device for front wheels of an aircraft, comprising a first rotor disk, a second rotor disk, a stator disk, N pairs of magnetic poles, a rotating shaft and a flange copper sleeve, where N is a natural number greater than or equal to 3;
所述法兰铜套套在所述转轴上、和转轴间隙配合，且法兰铜套在转轴上轴向固定，使得法兰铜套能够相对转轴自由转动；The copper flange sleeve is sleeved on the rotating shaft and has clearance with the rotating shaft, and the copper flange sleeve is axially fixed on the rotating shaft, so that the copper flange sleeve can rotate freely relative to the rotating shaft;
所述第一转子盘、第二转子盘、定子盘均呈圆盘状，中心均设有通孔；The first rotor disk, the second rotor disk and the stator disk are all in the shape of disks, and are provided with through holes in the centers;
所述定子盘套在所述法兰铜套外、和所述法兰铜套过盈配合；所述第一转子盘、第二转子盘对称设置在所述定子盘两侧，均通过其中心通孔和所述转轴同轴固连；The stator disc is sleeved outside the flange copper sleeve and has an interference fit with the flange copper sleeve; the first rotor disc and the second rotor disc are symmetrically arranged on both sides of the stator disc, and are both coaxially fixedly connected to the rotating shaft through their central through holes;
所述N对磁极周向均匀设置在所述定子盘上；每一对磁极均对称设置在定子盘的两个端面上、和定子盘固连，且充磁方向相反，如图3所示；所述定子盘同一侧上相邻磁极的充磁方向相反，且磁极远离定子盘的一端均设有极靴；The N pairs of magnetic poles are evenly arranged on the stator disk in the circumferential direction; each pair of magnetic poles is symmetrically arranged on the two end surfaces of the stator disk, fixedly connected to the stator disk, and has opposite magnetization directions, as shown in FIG3 ; the magnetization directions of adjacent magnetic poles on the same side of the stator disk are opposite, and a pole shoe is provided at one end of the magnetic pole away from the stator disk;
所述第一转动盘、第二转动盘和所述定子盘上的磁极之间存在气隙；There is an air gap between the first rotating disk, the second rotating disk and the magnetic poles on the stator disk;
如图4所示，所述定子盘通过支架和飞机前起落架外筒固连，所述转轴通过传动装置和飞机前起落架转动套筒相连。As shown in FIG. 4 , the stator disc is fixedly connected to the outer cylinder of the front landing gear of the aircraft via a bracket, and the rotating shaft is connected to the rotating sleeve of the front landing gear of the aircraft via a transmission device.
N优先取6。N is preferably 6.
该机构的工作原理是：当飞机前轮产生的摆振运动通过传动装置譬如齿轮箱传递到电磁阻尼减摆器后，将摆振运动转化转轴的转动，转轴带动第一、第二转子盘转动，第一、第二转子盘和磁极的极靴之间留有气隙，所以第一、第二转子盘与定子之间的相对转动不会产生摩擦。根据电磁感应原理可知，导线在磁场中切割磁感线的运动会产生感应电流，而根据楞次定律，感应电流的磁场会阻碍导线在磁场中的运动，并且由于导线本身存在电阻，感应电流流过导线将会使导线的动能转变为热能，从而达到阻碍运动的效果。因此当电磁阻尼减摆器的第一、第二转子盘旋转时，第一、第二转子盘的转动会切割磁极磁场中的磁感线，通过第一、第二转子盘的磁通量产生变化，从而在第一、第二转子盘上感应出旋窝形状的感应电流，简称涡流。当感应出涡流之后会激发感应磁场，而感应磁场所产生的阻尼力矩方向与第一、第二转子盘的旋转方向相反，第一、第二转子盘的旋转会受到阻碍，同时由于永磁体自身的电阻不为零，根据欧姆定律，涡流将以热能的形式耗散，因此第一、第二转子盘上感应出的涡流将使其动能将转变为热能，达到阻碍第一、第二转子盘转动的效果，从而实现飞机前轮的减摆操纵。The working principle of the mechanism is: when the shimmying motion generated by the front wheel of the aircraft is transmitted to the electromagnetic damping damper through a transmission device such as a gear box, the shimmying motion is converted into the rotation of the rotating shaft, and the rotating shaft drives the first and second rotor disks to rotate. There is an air gap between the first and second rotor disks and the pole shoes of the magnetic poles, so the relative rotation between the first and second rotor disks and the stator will not generate friction. According to the principle of electromagnetic induction, the movement of the wire cutting the magnetic flux lines in the magnetic field will generate an induced current, and according to Lenz's law, the magnetic field of the induced current will hinder the movement of the wire in the magnetic field, and because the wire itself has resistance, the induced current flowing through the wire will convert the kinetic energy of the wire into heat energy, thereby achieving the effect of hindering movement. Therefore, when the first and second rotor disks of the electromagnetic damping damper rotate, the rotation of the first and second rotor disks will cut the magnetic flux lines in the magnetic field of the magnetic poles, and the magnetic flux through the first and second rotor disks will change, thereby inducing a vortex-shaped induced current on the first and second rotor disks, referred to as eddy current. When eddy currents are induced, an induced magnetic field is stimulated. The direction of the damping torque generated by the induced magnetic field is opposite to the rotation direction of the first and second rotor disks. The rotation of the first and second rotor disks will be hindered. At the same time, since the resistance of the permanent magnet itself is not zero, according to Ohm's law, the eddy currents will dissipate in the form of heat energy. Therefore, the induced eddy currents on the first and second rotor disks will convert their kinetic energy into heat energy, thereby achieving the effect of hindering the rotation of the first and second rotor disks, thereby realizing the anti-sway control of the aircraft's front wheels.
与传统的摩擦阻尼器、油液阻尼器相比，电磁阻尼减摆器在产生阻尼力的过程中，转子盘和定子盘不发生接触，对电磁阻尼减摆器的材料属性不会产生影响。另外，电磁阻尼减摆器在维护、环境保护、使用寿命、结构原理等方面具有优势。Compared with traditional friction dampers and oil dampers, the electromagnetic damping damper does not have contact between the rotor disc and the stator disc during the process of generating damping force, which will not affect the material properties of the electromagnetic damping damper. In addition, the electromagnetic damping damper has advantages in maintenance, environmental protection, service life, structural principles, etc.
本技术领域技术人员可以理解的是，除非另外定义，这里使用的所有术语（包括技术术语和科学术语）具有与本发明所属领域中的普通技术人员的一般理解相同的意义。还应该理解的是，诸如通用字典中定义的那些术语应该被理解为具有与现有技术的上下文中的意义一致的意义，并且除非像这里一样定义，不会用理想化或过于正式的含义来解释。It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as generally understood by those skilled in the art in the field to which the present invention belongs. It should also be understood that terms such as those defined in common dictionaries should be understood to have meanings consistent with the meanings in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as herein.
以上所述的具体实施方式，对本发明的目的、技术方案和有益效果进行了进一步详细说明，所应理解的是，以上所述仅为本发明的具体实施方式而已，并不用于限制本发明，凡在本发明的精神和原则之内，所做的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204271879U (en) * | 2014-12-12 | 2015-04-15 | 廖新春 | Sharp angle magnetic damper |
| CN113757292A (en) * | 2021-09-16 | 2021-12-07 | 昆明理工大学 | Multi-channel aircraft landing gear magnetorheological damper, control method, system and application |
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| GB765588A (en) * | 1954-08-10 | 1957-01-09 | Selectra Ltd | Improvements relating to heteropolar inductor alternators |
| FR2895046B1 (en) * | 2005-12-21 | 2009-05-29 | Thales Sa | DAMPING DEVICE |
| DE102012020434B4 (en) * | 2012-10-18 | 2016-09-08 | Audi Ag | Electric damper for a motor vehicle |
| FR3032686B1 (en) * | 2015-02-18 | 2017-03-10 | Messier Bugatti Dowty | AIRCRAFT AIRCRAFT COMPRISING A TELESCOPIC LINEAR ROD |
| US9732818B2 (en) * | 2015-10-13 | 2017-08-15 | Goodrich Corporation | Axial engagement-controlled variable damper systems and methods |
| WO2020245392A1 (en) * | 2019-06-05 | 2020-12-10 | Universiteit Gent | An electrical machine comprising an integrated magnetic torsion spring |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN204271879U (en) * | 2014-12-12 | 2015-04-15 | 廖新春 | Sharp angle magnetic damper |
| CN113757292A (en) * | 2021-09-16 | 2021-12-07 | 昆明理工大学 | Multi-channel aircraft landing gear magnetorheological damper, control method, system and application |
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