公开(公告)号：WO2006071263A2

公开(公告)日：2006-07-06

申请号：PCT/US2005/021633

申请日：2005-06-20

Applicant: GOODRICH CORPORATION ,  LAVIGNE, Paul J. ,  LEVOIR, Barry

Inventor： LAVIGNE, Paul J. ,  LEVOIR, Barry

CPC classification number: B64C25/34 ,  B64C25/12 ,  B64C2025/345

Abstract: A landing gear for an aircraft, characterized by upper and lower pintle frame members (38, 40) being connected to a telescoping shock strut (14) in a non-rigid manner that tolerates twisting when reacting to torsional loads applied to the landing gear, and/or by a pitch trim actuator (30) that positions a landing gear truck (16) proportionally to the retraction angle of a shock strut (14) during retraction and extension.

Abstract translation: 用于飞机的起落架，其特征在于上和下枢轴架构件（38,40）以非刚性方式连接到伸缩式冲击支柱（14），当对施加到起落架的扭转载荷作出反应时，该起重装置允许扭转， 和/或通过间距调节致动器（30），其将起落架卡车（16）与缩回和延伸期间的冲击支柱（14）的缩回角成比例地定位。

公开(公告)号：WO2006071263A3

公开(公告)日：2007-03-22

申请号：PCT/US2005021633

申请日：2005-06-20

Applicant: GOODRICH CORP ,  LAVIGNE PAUL J ,  LEVOIR BARRY

Inventor： LAVIGNE PAUL J ,  LEVOIR BARRY

IPC: B64C25/10 ,  B64C25/34 ,  B64C25/50 ,  B64C25/58

CPC classification number: B64C25/34 ,  B64C25/12 ,  B64C2025/345

Abstract: A landing gear for an aircraft, characterized by upper and lower pintle frame members (38, 40) being connected to a telescoping shock strut (14) in a non-rigid manner that tolerates twisting when reacting to torsional loads applied to the landing gear, and/or by a pitch trim actuator (30) that positions a landing gear truck (16) proportionally to the retraction angle of a shock strut (14) during retraction and extension.

Abstract translation: 用于飞机的起落架，其特征在于上和下枢轴架构件（38,40）以非刚性方式连接到伸缩式冲击支柱（14），当对施加到起落架的扭转载荷作出反应时，该起重装置允许扭转， 和/或通过间距调节致动器（30），其将起落架卡车（16）与缩回和延伸期间的冲击支柱（14）的缩回角成比例地定位。

公开(公告)号：WO2006071262A1

公开(公告)日：2006-07-06

申请号：PCT/US2005/021632

申请日：2005-06-20

Applicant: GOODRICH CORPORATION ,  COLES, John W. C. ,  LAVIGNE, Paul J.

Inventor： COLES, John W. C. ,  LAVIGNE, Paul J.

IPC: B64C25/34 ,  B64C25/50

CPC classification number: B64C25/50 ,  B64C25/34 ,  B64C2025/345

Abstract: A landing gear system for an aircraft comprises a truck beam (22); at least one steerable axle (42) mounted to the truck beam for pivotal steering movement; a steering actuator (46) connected to the steerable axle; and a locking mechanism (60) including a locking groove member (62) provided on the steerable axle for pivotal movement therewith, and a locking wedge member (64) engageable with the locking groove member to prevent pivotal movement of the steerable axle. The locking groove member includes a slot (63) having opposed sides converging towards one another, and the locking wedge member has correspondingly converging sides for mating engagement in the slot. The locking wedge member is resiliently biased (66, 69) into engagement with the locking groove member and the locking wedge member is mounted to the truck beam for pivotal movement (70).

Abstract translation: 用于飞机的起落架系统包括卡车梁（22）; 安装到所述卡车梁上的至少一个可操纵的轴（42）用于枢转转向运动; 连接到可转向轴的转向致动器（46） 以及锁定机构（60），其包括设置在可转向轴上的锁定槽构件（62），用于与其枢转运动;以及锁定楔构件（64），其可与锁定槽构件接合以防止可转向车轴的枢转运动。 锁定槽构件包括具有朝向彼此会聚的相对侧的槽（63），并且锁定楔形构件具有用于在槽中配合接合的相应的会聚侧。 锁定楔形构件被弹性偏置（66,69）与锁定槽构件接合，并且锁定楔形构件安装到卡车梁以进行枢转运动（70）。