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公开(公告)号：US09527582B2
公开(公告)日：2016-12-27
申请号：US14447825
申请日：2014-07-31
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Thierry Blanpain , Edouard Campbell , Yann Simonneaux , Martial Monseu , Remi Finet
CPC classification number: B64C25/18 , B64C25/405 , Y02T50/823
Abstract: Aircraft undercarriage leg including an axle (3) that bears at least one wheel (4), the undercarriage leg being equipped with a unit (6) for driving rotation of the wheel, wherein the drive unit is rigidly fixed to the axle and a deformable support (12) extends between a cantilevered portion of the drive unit and a portion of the undercarriage leg not including the axle to support the cantilevered portion of the drive unit.
Abstract translation: 飞机起落架腿包括具有至少一个轮（4）的轴（3），起落架腿配备有用于驱动车轮旋转的单元（6），其中驱动单元刚性地固定到车轴上，并且可变形 支撑件（12）在驱动单元的悬臂部分和不包括轴的起落架腿部的一部分之间延伸，以支撑驱动单元的悬臂部分。
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公开(公告)号：US09981737B2
公开(公告)日：2018-05-29
申请号：US13975592
申请日：2013-08-26
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Sebastien Remond , Edouard Campbell , Thierry Blanpain , Alexis Tovar
CPC classification number: B64C25/405 , B64C25/36 , Y02T50/823 , Y10T29/49826 , Y10T29/49948
Abstract: The invention provides a method of mounting an aircraft wheel drive member (30) on an undercarriage having an axle (1) that carries the wheel and that is provided with a torque plate (3) having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support (10) that bears against an inside face of the torque plate opposite from its outside face against which a brake (2) is fitted, and of fitting the drive member on the support.
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公开(公告)号：US09802697B2
公开(公告)日：2017-10-31
申请号：US14877253
申请日：2015-10-07
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Pierre-Yves Liegeois , Thierry Blanpain , Edouard Campbell
CPC classification number: B64C25/505 , B64C25/34 , Y02T50/54
Abstract: The invention relates to an aircraft landing gear equipped with a steering device (7) for orienting the wheels (5), the steering device (7) comprising a body (8) in which is incorporated an electromechanical actuator (41) equipped with an electric motor (42). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel (5) to the rest of the landing gear (1) when the aircraft is on the ground. The body (8) of the steering device (7) is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body (8) of the steering device (7) and the strut assembly (2) of the landing gear to damp the vibration between the body (8) of the steering device (7) and the strut assembly (2).
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