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发明公开
EP2450277A2 Vertically retracting side articulating landing gear for aircraft 审中-公开
VertikalzurückziehendesSeitengelenk-Fahrwerkfürein Luftfahrgzeug

  • 专利标题： Vertically retracting side articulating landing gear for aircraft
  • 专利标题（中）： VertikalzurückziehendesSeitengelenk-Fahrwerkfürein Luftfahrgzeug
  • 申请号： EP11250883.3
    申请日： 2011-11-04
  • 公开(公告)号： EP2450277A2
    公开(公告)日： 2012-05-09
  • 发明人: Acks, James P. , Martin, Dennis
  • 申请人： Goodrich Corporation
  • 申请人地址： Four Coliseum Centre 2730 West Tyvola Road Charlotte, NC 28217 US
  • 专利权人： Goodrich Corporation
  • 当前专利权人： Goodrich Corporation
  • 当前专利权人地址： Four Coliseum Centre 2730 West Tyvola Road Charlotte, NC 28217 US
  • 代理机构： Hargreaves, Timothy Edward
  • 优先权： US410654P 20101105
  • 主分类号： B64C25/12
  • IPC分类号： B64C25/12
Vertically retracting side articulating landing gear for aircraft
摘要：
A side articulating main landing gear assembly (100) for an aircraft (10) is disclosed which includes a wheel axle fitting (150) oriented in a horizontal plane when the landing gear is in an extended condition deployed from a landing gear bay (12) of the aircraft, a tire supported on the wheel axle fitting (150) and oriented in a vertical plane when the landing gear is in the extended condition, a shock absorber (120) adapted to stroke between an extended state and a compressed state upon landing the aircraft, a set of articulating links connected to the wheel axle fitting (150), the shock absorber (120) and the aircraft (10), and configured to maintain the tire (160) in a vertical plane as the shock absorber (120) strokes between the extended state and the compressed state, a set of tire planing links connected to the wheel axle fitting (150) and the articulating links (140,142,144), and configured to maintain the wheel axle fitting (150) in a horizontal plane as the shock absorber (120) strokes between the extended state and the compressed state, and a drive crank (130) connected to the shock absorber (120), the tire planing links, the articulating links (140,142,144) and the aircraft (10), for moving the landing gear assembly (100) between the extended condition and an inverted retracted condition stowed in the landing gear bay (12).
摘要（中）：

公开了一种用于飞机（10）的侧面关节式主起落架组件（100），其包括当起落架处于从起落架舱（12）展开的延伸状态时在水平面中定向的轮轴配件（150） ，当起落架处于伸展状态时，支撑在所述轮轴配件（150）上并且在垂直平面中定向的轮胎，适于在着陆时在延伸状态和压缩状态之间行进的减震器（120） 飞行器，连接到车轮轴配件（150），减震器（120）和飞行器（10）的一组铰接连杆，并且构造成将轮胎（160）保持在垂直平面中作为减震器（120 ）在延伸状态和压缩状态之间的冲程，连接到轮轴配件（150）和铰接连杆（140,142,144）的一组轮胎平整链接，并且被配置为将轮轴配件（150）保持在水平面中， 减震器（1 20）在延伸状态和压缩状态之间的行程，以及连接到减震器（120）的驱动曲柄（130），轮胎平整连杆，铰接连杆（140,142,144）和飞行器（10），用于移动着陆 齿轮组件（100）处于延伸状态和收起在起落架舱（12）中的倒置收缩状态之间。

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