公开(公告)号：US20030164423A1

公开(公告)日：2003-09-04

申请号：US10360638

申请日：2003-02-10

Applicant: MESSIER-DOWTY SA

Inventor： Maud Courtois ,  Dominique Ducos

IPC: B64C025/10

CPC classification number: B64C25/16 ,  B64C7/00 ,  B64C2025/003

Abstract: The invention relates to an aircraft landing gear having a retractable leg, in which the leg comprises a strut with a telescopic rod, the strut being hinged to a structure of the aircraft in order to pivot between a gear-up position and a gear-down position, said strut also being connected to the structure of the aircraft via hinged brace elements. According to an essential aspect of the invention, the landing gear includes an independent low-noise fairing system that serves, when the leg is in the gear-down position, to cover the front of at least a portion of the hinge between the brace elements, said low-noise fairing system comprising a hinged fairing of two complementary portions connected to each other via a hinge whose axis is parallel to the axis of the corresponding hinge portion of said brace elements.

Abstract translation: 本发明涉及一种具有可伸缩腿部的飞机起落架，其中腿部包括具有伸缩杆的支柱，该支柱铰接到飞行器的结构上，以便在起落位置和减档之间枢转 所述支柱还通过铰链支架元件连接到飞行器的结构。 根据本发明的一个重要方面，起落架包括一个独立的低噪声整流装置系统，当腿部处于减速位置时，其用于覆盖支架元件之间铰链的至少一部分的前部 所述低噪声整流罩系统包括通过铰链彼此连接的两个互补部分的铰接整流罩，所述铰链的轴线平行于所述支撑元件的相应铰链部分的轴线。

公开(公告)号：US20040111891A1

公开(公告)日：2004-06-17

申请号：US10730984

申请日：2003-12-10

Applicant: MESSIER-DOWTY SA

Inventor： Florian Serouart ,  Christophe De Kermadec

IPC: B21K001/76

CPC classification number: F16C23/041 ,  B64C25/62 ,  F16C33/14 ,  F16C2220/60 ,  F16C2326/43 ,  Y10T29/49636 ,  Y10T29/49668

Abstract: The invention relates to a method of forming the inside wall of a support bearing of given height H and suitable for receiving a cylindrical portion of a cylindrical element for co-operating with the inside wall, said method comprising the steps of estimating a deflection f taken up by the cylindrical element between the center and one of the ends of the support bearing, estimating a nominal radius R using the relationship RnullH2/8f, determining an inside wall for the support bearing that occupies a toroidal surface having a throat diameter equal to a diameter of the cylindrical element, ignoring predetermined clearance, and having a meridian radius lying in a range of null15% about the nominal radius R, and machining the support bearing in such a manner that its inside wall occupies the toroidal surface as determined in this way.

Abstract translation: 本发明涉及一种形成给定高度H的支撑轴承的内壁的方法，该方法适于接收与内壁协同工作的圆柱形元件的圆柱形部分，所述方法包括以下步骤： 通过圆柱形元件在支撑轴承的中心和一个端部之间，通过使用关系R = H 2 / 8f来估计标称半径R，确定用于支撑轴承的内壁，该支撑轴承占据具有 喉部直径等于圆柱形元件的直径，忽略预定间隙，并且子午线半径约在标称半径R的±15％的范围内，并且以这样的方式加工支撑轴承，使得其内壁占据环形 表面以这种方式确定。

公开(公告)号：US20040262452A1

公开(公告)日：2004-12-30

申请号：US10899766

申请日：2004-07-27

Applicant: MESSIER-DOWTY SA

Inventor： Michel Derrien ,  Benjamin Parzy

IPC: B64C025/10

CPC classification number: B64C25/10 ,  B64C2025/345

Abstract: The invention relates to aircraft landing gear of the type comprising a leg constituted by a strut receiving a telescopic rod to slide on a sliding axis, said strut being hinged to an aircraft structure and being capable of pivoting about a pivot axis that is highly offset from the sliding axis. In accordance with the invention, the landing gear includes a connection structure essentially constituted by two panels connecting two axially separate points of the strut to a common axis structure extending along the strut pivot axis. In the gear-down position, the panels are one above the other, the top panel being connected to the strut via a high attachment which is rigid in twisting, while the bottom panel is connected to the strut via a low attachment which tolerates twisting, thereby enabling the strut to warp to some extent when the aircraft is turning while taxiing.

Abstract translation: 本发明涉及这种类型的飞机起落架，该起落架包括由支撑件构成的支腿，所述支柱接收伸缩杆以在滑动轴线上滑动，所述支柱铰接到飞行器结构并且能够围绕枢转轴线枢转， 滑动轴。 根据本发明，起落架包括基本上由将支柱的两个轴向分离的点连接到沿着支柱枢转轴线延伸的公共轴线结构的两个板构成的连接结构。 在减速位置中，面板是彼此之一的，顶板通过刚性扭转的高附件连接到支柱，而底板通过低附件连接到支柱，该附件允许扭转， 从而使得当飞机在滑行时转弯时，支柱能够在某种程度上翘曲。