The invention relates to an aircraft landing gear, at least: the axle (1), which is loaded in the bottom part of the landing gear; the wheel is equipped with a rim (2) and is mounted on the axle of the landing gear by bearing (3) to revolve around the axis of rotation; the brake part (100) is attached to the axle and includes a torque tube. (5) a friction member (4) and at least one brake actuator (7), which extends around the wheel shaft, which is mounted around the torque tube and extends between the torque tube and the wheel rim of the torque tube, and the at least one brake actuator (7) is designed to selectively apply the braking force to the friction member, which is caused by the brake. The actuator is loaded by the torque tube mounted on the actuator (6a, 6b); and the rotating drive device is used to drive the wheel rotation and first includes the actuator and then the drive member (20, 25, 27), which is used to drive the wheel rotation, and the drive member is used to rotate the rotation motion from rotation. The actuator is selectively transmitted to the rim of the wheel and extends between the wheel shaft and the torque tube. In the invention, the actuator bracket is directly meshing from the wheel shaft, and the transmission member is carried by the brake part and is driven to rotate by the bearing on the brake part.
【技术实现步骤摘要】
装配有制动轮的飞行器起落架
本专利技术涉及一种起落架,该起落架设有旋转驱动装置,该旋转驱动装置用于驱动由起落架承载的制动轮旋转。
技术介绍
文献FR3026717公开了一种飞行器起落架,该飞行器起落架设有与用于驱动旋转的装置相关联的制动轮,以使得该飞行器可在无需求助于飞行器的推进器的情形下在地面上运动。每个驱动装置均包括驱动致动器,该驱动致动器包括电动机,该电动机经由联接(或传动)构件以选择性的方式连接于机轮,该联接构件在承载机轮的轮轴和制动件的扭矩管之间延伸,且制动盘安装在该制动件上。具体地说,该联接构件包括管状驱动轴,该管状驱动轴围绕轮轴延伸,且同时由滚针轴承引导而在所述轮轴之上旋转。管状驱动轴通过承载制动件致动器的致动器托架的基部下方,以使得致动器托架经由滚针轴承并不直接地在轮轴上而是在驱动轴上对中。该布置意味着由于制动引起的并且经由致动器托架传递至轮轴的径向力须经由管状驱动轴及其轴承传递,这会导致所述构件加速疲劳。
技术实现思路
本专利技术的目的是提供一种新颖布置,该新颖布置避免径向制动力经由传动构件的驱动轴传递。为了实现该目的,本专利技术提供一种飞行器起落架,该飞行器起落架至少包括:·轮轴,该轮轴承载在起落架的底部部分中;·机轮,该机轮设有轮辋并且经由轴承安装在起落架的轮轴上,以绕旋转轴线旋转;·制动件,该制动件螺接在轮轴上并且包括扭矩管、摩擦构件以及至少一个制动件致动器,该扭矩管围绕轮轴延伸,这些摩擦构件围绕扭矩管安装并且在扭矩管和机轮的轮辋之间延伸,而该至少一个制动件致动器设计成将制动力选择性地施加在摩擦构件上,该制动件致动器由扭矩管固定于其上的 ...
【技术保护点】
1.飞行器起落架,至少包括:·轮轴(1),所述轮轴承载在所述起落架的底部部分中;·机轮,所述机轮设有轮辋(2)并且经由轴承(3)安装在所述起落架的轮轴上,以绕旋转轴线旋转;·制动件(100),所述制动件螺接在所述轮轴上并且包括扭矩管(5)、摩擦构件(4)以及至少一个制动件致动器(7),所述扭矩管围绕所述轮轴延伸,所述摩擦构件围绕所述扭矩管安装并且在所述扭矩管和所述机轮的轮辋之间延伸,而所述至少一个制动件致动器设计成将制动力选择性地施加在所述摩擦构件上,所述制动件致动器由所述扭矩管固定于其上的致动器托架(6a、6b)承载;·旋转驱动装置,所述旋转驱动装置用于驱动所述机轮旋转且首先包括致动器而其次包括传动构件(20、25、27),所述致动器用于驱动所述机轮旋转,而所述传动构件用于将旋转运动从所述旋转致动器选择性地传递至所述机轮的轮辋,且在所述轮轴和所述扭矩管之间延伸;所述起落架的特征在于,所述致动器托架由所述轮轴直接对中,且所述传动构件由所述制动件承载且由所述轴承在所述制动件上引导旋转。
【技术特征摘要】
2016.12.23 FR 16633351.飞行器起落架,至少包括:·轮轴(1),所述轮轴承载在所述起落架的底部部分中;·机轮,所述机轮设有轮辋(2)并且经由轴承(3)安装在所述起落架的轮轴上,以绕旋转轴线旋转;·制动件(100),所述制动件螺接在所述轮轴上并且包括扭矩管(5)、摩擦构件(4)以及至少一个制动件致动器(7),所述扭矩管围绕所述轮轴延伸,所述摩擦构件围绕所述扭矩管安装并且在所述扭矩管和所述机轮的轮辋之间延伸,而所述至少一个制动件致动器设计成将制动力选择性地施加在所述摩擦构件上,所述制动件致动器由所述扭矩管固定于其上的致动器托架(6a、6b)承载;·旋转驱动装置,所述旋转驱动装置用于驱动所述机轮旋转且首先包括致动器而其次包括传动构件(20、25、27),所述致动器用于驱动所述机轮旋转,而所述传动构件用于将旋转运动从所述旋转致动器选择性地传递至所述机轮的轮辋,且在所述轮轴和所述扭矩管之间延伸;所述起落架的特征在于,所述致动器托架由所述轮轴直接对中,且所述传动构件由所述制动件承载且由所述轴承在所述制动件上引导旋转。2....
【专利技术属性】
技术研发人员:M·达弗斯,N·达尔莱兰斯,
申请(专利权)人:赛峰起落架系统公司,
类型:发明
国别省市:法国,FR
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