CN110723281B - 飞行器起落架组件 - Google Patents
飞行器起落架组件 Download PDFInfo
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- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
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- B60T17/18—Safety devices; Monitoring
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/17—Using electrical or electronic regulation means to control braking
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- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/17—Using electrical or electronic regulation means to control braking
- B60T8/171—Detecting parameters used in the regulation; Measuring values used in the regulation
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- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/32—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
- B60T8/52—Torque sensing, i.e. wherein the braking action is controlled by forces producing or tending to produce a twisting or rotating motion on a braked rotating member
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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
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D55/00—Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes
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Abstract
本发明涉及一种飞行器起落架组件,包括:轮轴,该轴具有轮轴线;轮,该轮可旋转地安装在轮轴上以绕轴线旋转;制动器,该制动器布置成在轮上围绕轴线选择性地施加制动扭矩;制动器锚固结构,该制动器锚固结构相对于轮轴具有大致固定的位置;制动器反作用连杆,该制动器反作用连杆将制动器机械地联接到制动器锚固结构;以及传感器,该传感器包括传感器元件,该传感器元件布置成检测制动器反作用连杆的部件的一个或多个物理性质的变化,从而确定由于制动扭矩引起的部件中的应力,其中,传感器元件不接触部件。
Description
技术领域
本发明涉及一种飞行器起落架组件。
背景技术
已知飞行器起落架遇到各种恶劣的环境条件。
已知提供盘式制动器组件以将制动扭矩施加到飞行器起落架的每个轮组件。一个或多个制动器盘相对于一个或多个轮盘转子以平行交错关系安装,形成制动器堆叠。可以致动活塞组件以迫使制动器盘轴向地抵靠轮盘转子,以将制动扭矩施加到轮组件。
本发明人已经确认,与已知的组件相比,飞行器起落架组件的重量可以减小和/或可靠性增加。
发明内容
根据本发明的第一方面,提供了一种根据权利要求1所述的飞行器组件。
本发明人已经确认,预定水平的制动致动可以产生取决于制动器的温度、飞行器速度和/或制动器磨损水平的不同水平的制动扭矩。特别是碳制动器会受此影响。因此,已知的起落架被设计从而承受超过降低飞行器速度所需的制动扭矩。根据第一方面的飞行器起落架提供了一种制动扭矩测量传感器,其能够可靠地测量施加到轮组件的制动扭矩的水平,这可以使起落架的部件尺寸和重量减小。传感器可以是轻质的并且布置成以非接触方式操作,以便提高长期可靠性。
不与部件接触的传感器元件可以意味着在传感器元件和部件之间没有力传递,并且传感器元件以对部件大致没有影响的方式观察部件。这与应变计不同,应变计必须通过由部件传递的力来弹性变形从而确定应力。总之,传感器元件不会由于部件的变形而变形。
此外,不同于应变计,由于传感器元件不需要与部件结合,传感器的坚固性和寿命得到改善,因为降低了粘接失效的风险。
传感器元件可以布置成将物理参数(诸如磁场强度或部件的偏转)转换为电信号。
传感器元件也可以是诸如光传感器之类的光学装置。
传感器可以布置在部件外部。
通过这种布置,提供了一种包括制动扭矩测量传感器的起落架组件,该制动扭矩测量传感器可以容易地实施在起落架上,包括改装到现役的起落架。
该部件可以是扭矩管,并且该传感器可以布置成观察扭矩管的径向内表面或径向外表面。利用这种布置,传感器可以监控扭矩管而不用在扭矩管内部成为一体。换句话说,传感器被施加到扭矩管的现有外表面,而不需要为传感器的操作而提供诸如凹部之类的部件传感器特定特征。因此,当部件是扭矩管时,参考传感器位于部件“外部”,术语“外部”旨在区分传感器是否在部件内部成为一体。术语“外部”包括由管封围的区域以及径向地在管外部的区域。它不包括位于专用通道中的传感器,例如钻入到管中的传感器。
当传感器布置在扭矩管的径向外表面上时,由扭矩管可以容纳更大的轮轴。
该部件可以是凸缘适配件,其布置成将起落架的制动器外壳机械地联接到轮轴。利用这种布置,可以精确地测量制动扭矩。
凸缘适配件可以是带辐条的凸缘适配件。利用这种布置,凸缘适配件可针对给定的扭矩进一步变形,使其更适合与诸如光学传感器之类的测量偏转的传感器一起使用。
应当理解,在制动时,部件将制动扭矩传递到制动器外壳和起落架结构。因此,该部件将承受诸如扭转应力之类的应力。通过测量由于应力而改变的部件的任何物理特性,将可能确定由于施加制动而发生的扭矩。在部件内部观察到的物理特性可以是磁性的变化或取决于部件的刚度的各种量级的偏转。
附图说明
现将参照附图描述本发明的实施例,附图中:
图1是根据本发明实施例的飞行器的示图;
图2是根据本发明的实施例的制动组件的示意性剖视图;
图3是根据本发明的实施例的替代制动组件的示意性剖视图;
图4a至图4c是不同凸缘适配件的视图;以及
图5是根据本发明的实施例的另外的替代制动组件的外部视图。
具体实施方式
图1是飞行器10的示意图。飞行器10包括诸如前起落架12、主起落架14以及发动机16之类的组件。其它飞行器组件对于技术人员来说是显然的。飞行器组件可以是一组互连的部件,这些部件布置成作为单元配装到一个或多个其它飞行器组件。这里使用的术语“飞行器”包括飞机、直升机、无人机以及类似物。
图2示出了起落架制动器组件100。制动器组件100安装在起落架的轮轴102上并且可操作以在安装在轮轴102上的轮104上施加制动扭矩。在图2所示的布置中,轮轴102不旋转,并且轮104经由轴承(未标记)安装在轮轴上使得其可相对于轮轴102旋转。
制动器组件100由布置在制动器外壳112内部的致动缸操作。致动缸用于将一叠制动器盘压在一起。该叠制动器盘由一组制动器定子盘108形成,这组制动器定子盘安装在扭矩管110上,以交错的方式地与一组轮转子盘106交替,轮转子盘106连接到轮104。
当致动制动器时,定子盘108与转子盘106接合。盘之间的摩擦力意味着扭矩施加在轮104上,这减慢了轮104的旋转。
经由转子盘106施加在轮104上的制动扭矩的相等且相反的反作用是在定子盘108上的沿轮104的运动方向的扭矩。定子盘108锚固在扭矩管110中。扭矩管110刚性地连接到轮轴102和制动器外壳112。在一些布置中,施加在扭矩管110上的扭矩可以通过制动器杆来平衡(参见图5)。
受制动扭矩影响的上述部件可以被称为处于制动扭矩的“负载路径”中。应当理解,负载路径中的每个部件可以由于施加的扭矩而弹性变形。响应于特定制动扭矩的负载路径中的任何一个部件中的应力与制动扭矩成比例。
因此,为了确定制动扭矩,非接触式传感器116用来确定扭矩管110中的扭转应力。特别地,非接触式传感器116确定扭矩管110靠近制动器外壳112的一端处的扭转应力,因为扭矩管110的这一端将受到完全制动扭矩,无论定子盘108或转子盘106中的哪一个正在施加成什么比例的制动扭矩。非接触式传感器116可以布置成使得没有定子盘108连接到由非接触式传感器116观察到的扭矩管110上的点与制动器壳体112之间的扭矩管110。
当要测量扭矩管110中的扭转应力时,非接触传感器116可以布置成观察扭矩管110的外表面或扭矩管110的内表面。通过将非接触式传感器116放置在扭矩管110的外表面上,存在允许更大的轮轴的更大的空间。
在任一种情况下,由于非接触式传感器116在扭矩管的外部,非接触式传感器可以包括在制动器组件中且具有最小的结构干涉。
非接触式传感器116可以安装在支架(未示出)上,该支架与扭矩管110邻接并且连接到制动器外壳112和/或凸缘适配件114。
替代地,如图3所示,扭矩管110可以刚性连接到凸缘适配件214,凸缘适配件214连接到轮轴102和制动器外壳112。负载路径可以经由凸缘适配件214从扭矩管110通达到轮轴102。
非接触式传感器216可以布置成确定凸缘适配件214中的扭转应力,凸缘适配件214连接到制动器外壳112和扭矩管110。
可以使用诸如图4a中所示的实心凸缘适配件,从而为制动器组件提供结构刚度。
当要测量凸缘适配件214中的应力时,可能有利的是使用将会响应于施加的扭矩而偏转显著量的凸缘适配件214。这种凸缘适配件214可以称为辐条适配件。图4b示出了辐条适配件,其中辐条将凸缘适配件的内环连接到凸缘适配件的外环,凸缘适配件的内环可以连接到轮轴102,凸缘适配件的外环可以连接到制动器外壳和扭矩管。
还可以使用在凸缘的外周界与内毂之间具有中间环的辐条适配件,中间环通过辐条连接到外周界和内毂,辐条不连续地横跨内环。这种适配件将被称为弹簧凸缘适配件。图4c中示出辐条适配件。
非接触式传感器216可以布置在凸缘适配件214的垂直于轮轴102且用于连接到制动器外壳112的表面上,或者布置在凸缘适配件214的平行于轮轴102且用于经由花键或螺栓连接来连接到轮轴的表面上。
图5示出了制动器组件的一部分的外部视图。在图5所示的布置中,制动扭矩由制动器杆322平衡,制动器杆322经由杠杆臂320联接到制动器外壳112。
在图5所示的布置中,制动扭矩的大小可以通过布置在传感器外壳324内部的非接触式传感器测量。布置在传感器外壳324内部的非接触式传感器布置成测量凸缘适配件214的变形。
替代地,非接触式负载传感器可以在将制动器外壳112连接到制动器杆322的扭矩销(未示出)内形成一体。这可以通过测量在受到诸如磁性或偏转的力时发生变化的销的物理特性来实现。
本发明的实施例可以包括各种非接触式传感器,安装在相对于待监控的部件的外部或者安装在诸如孔之类的传感器专用安装形式内部。
例如,非接触式传感器可以包括被布置成检测部件内部的涡电流的传感器。涡电流可以通过它们的相关联的磁场来检测。可以通过称为傅科电流(Foucault current)传感器的设备检测磁场。通过检测涡电流的强度,可以确定传感器与部件之间的距离。因此,可以确定部件的变形。
替代地,非接触式传感器可以包括被布置成检测部件内部的磁场的传感器。可以通过称为磁通门(flux-gate)传感器的设备检测磁场。扭转应力的变化将产生磁场强度方向和幅度的变化。
在另一个示例中,传感器可以包括传感器元件,该传感器元件可以使用反射光检测部件内部的偏转并且评估发送和接收的光之间的变化。
在另一个示例中,传感器可以包括基于视觉的系统,该系统布置成观察部件的外表面以确定部件的变形。该系统可以例如布置成监控由于部件的变形而在外表面上的诸如点之类的特征的移动。
应注意的是,上述实施例说明而非限制本发明,并且本领域技术人员将能够设计许多替代实施例,而不会偏离由所附权利要求所限定的本发明范围。在权利要求书中,不应将放置在括号中的任何附图标记理解为限制这些权利要求。词语“包括”并不排除除了作为整体在任何权利要求或说明书中列举的那些构件或步骤以外的构件或步骤的存在。构件的单数引用并不排除对这些构件的复数引用,且反之亦然。本发明的各部件可借助包括若干不同构件的硬件来实施。在列举若干部件的装置权利要求中,这些部件中的几个可以由一项或同一项硬件来实施。在相互不同的从属权利要求中描述了特定措施的事实并不意味着这些措施的组合不能用于产生良好效果。
Claims (15)
1.一种飞行器起落架组件,包括:
轮轴,所述轮轴具有轴线;
轮,所述轮可旋转地安装在所述轮轴上以绕所述轴线旋转;
制动器,所述制动器布置成在所述轮上围绕所述轴线施加制动扭矩;
制动器锚固结构,所述制动器锚固结构相对于所述轮轴具有固定的位置;
制动器反作用连杆,所述制动器反作用连杆将所述制动器机械地联接到所述制动器锚固结构;以及
传感器,所述传感器包括传感器元件,所述传感器元件布置成检测所述制动器反作用连杆的部件的一个或多个物理特性的变化,从而确定由于所述制动扭矩引起的所述部件中的应力,其中,所述传感器元件布置成观察所述部件,并且所述传感器元件不接触所述部件。
2.根据权利要求1所述的起落架组件,其特征在于,所述传感器元件布置成将电磁特性转换为电信号。
3.根据权利要求2所述的起落架组件,其特征在于,所述传感器元件是光换能器。
4.根据权利要求2所述的起落架组件,其特征在于,所述传感器元件布置成检测磁场。
5.根据权利要求1所述的起落架组件,其特征在于,所述传感器是干涉仪。
6.根据权利要求1所述的起落架组件,其特征在于,所述部件是扭矩管,其围绕所述轮轴并沿所述轮轴延伸,并且固定的制动器盘联接到所述扭矩管。
7.根据权利要求6所述的起落架组件,其特征在于,所述传感器布置在所述扭矩管的径向内表面或径向外表面上。
8.根据权利要求6所述的起落架组件,其特征在于,所述传感器布置成靠近所述扭矩管的一端,其中所述扭矩管连接到制动器外壳。
9.根据权利要求6所述的起落架组件,其特征在于,所述传感器布置在被布置成邻接所述扭矩管的支架上。
10.根据权利要求1所述的起落架组件,其特征在于,所述部件是布置成将所述起落架的制动器外壳机械地联接到所述轮轴的凸缘适配件,所述凸缘适配件围绕所述轮轴延伸并且具有环形形状,所述凸缘适配件的横截面为L形。
11.根据权利要求10所述的起落架组件,其特征在于,所述凸缘适配件是带辐条的凸缘适配件,其具有在所述轮轴与所述制动器外壳之间径向延伸的多个辐条。
12.根据权利要求1所述的起落架组件,其特征在于,还包括成叠的制动器盘。
13.根据权利要求12所述的起落架组件,其特征在于,所述制动器盘由碳制成。
14.根据权利要求1所述的起落架组件,其特征在于,所述传感器元件布置成观察所述制动器反作用连杆的部件,从而检测所述部件的一个或多个物理特性的变化。
15.一种包括一个或多个如权利要求1至14中任一项所述的起落架组件的飞行器。
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EP18183607.3A EP3597496B1 (en) | 2018-07-16 | 2018-07-16 | Aircraft landing gear assembly |
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