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    Ultra-light aircraft with freely rotating rigid wing
    1.
    发明授权
    Ultra-light aircraft with freely rotating rigid wing 失效
    超轻型飞机具有自由旋转的刚性翼

    公开(公告)号：US4568043A

    公开(公告)日：1986-02-04

    申请号：US588079

    申请日：1984-03-09

    申请人： Hugh J. Schmittle

    发明人： Hugh J. Schmittle

    IPC分类号： B64C31/028 ,  B64C3/38

    CPC分类号： B64C31/028 ,  Y10S244/90

    摘要： An ultra-light aircraft of light-weight minimal construction includes a rigid wing from which a hang cage is suspended by a main hinge assembly. Rotation of the wing without pilot intervention induced by positive or negative wind gusts striking the wing causes the angle of pitch between the wing and hang cage to vary via the hinge so that the wing presents a relatively constant angle of attack to relative wind enabling the aircraft to be essentially stall free during flight. Twist and/or dihedral of the wing is maintained by first and second sets of tensioned cables or landing wires connecting leading and trailing wing edges to a kingpost projecting upward from the wing, and by first and second sets of flying wires connecting the wing to the hang cage. Each first and second set of flying wires is a stress distributing arrangement including a pair of tubes respectively connected at upper ends thereof to leading and trailing wing edges and at lower ends to a plate suspended between the wing and hang cage. A pair of tensioned cables in each set connect the plate to the hang cage. The point of attachment of the cables to the plate establishes a pivot point located collinear with the hinge axis. The tubes are free to rotate about the pivot point during co-rotation of the wing while maintaining proper dihedral and wing twist as well as tension transmitting bending stress acting on the wing to the hang cage.

    摘要翻译： 一种重量轻的最小结构的超轻型飞机包括刚性翼，悬挂笼由主铰链组件悬挂。 机翼的旋转没有由正或负的阵风引起的飞行员干扰引起机翼，导致机翼和吊架之间的俯仰角度通过铰链变化，使得机翼相对于相对风能够相对稳定地迎风， 在飞行过程中基本上失速。 机翼的扭转和/或二面体由第一组和第二组拉伸的电缆或着陆线保持，前者和后缘翼缘连接到从机翼向上突出的凸柱，以及通过将机翼连接到机翼的第一组和第二组飞行线 挂笼 每个第一组和第二组飞行线是应力分布装置，其包括分别在其上端连接到前翼缘和后翼缘的一对管，并且在下端分别连接到悬挂在翼与吊笼之间的板上。 每组中的一对张紧的电缆将板连接到吊架。 电缆连接到板上的点建立了一个与铰链轴线共线的枢轴点。 在翼的共同旋转期间，管可以围绕枢转点自由旋转，同时保持适当的二面和翼部扭转以及作用在机翼上的弯曲应力到吊架。

    Ultralight aircraft with freely rotating wing
    2.
    发明授权
    Ultralight aircraft with freely rotating wing 失效
    超轻型飞机具有自由旋转的翼

    公开(公告)号：US4596368A

    公开(公告)日：1986-06-24

    申请号：US544261

    申请日：1983-10-21

    申请人： Hugh J. Schmittle

    发明人： Hugh J. Schmittle

    IPC分类号： B64C3/38 ,  B64C31/028

    CPC分类号： B64C31/028 ,  B64C3/385 ,  Y10S244/903

    摘要： An ultralight aircraft of lightweight minimal construction includes a collapsible Rogallo type wing from which a hang cage is suspended by a main hinge assembly. The wing includes a longitudinal keel of lightweight tubular construction, leading edge members and a cross brace. A flexible lifting panel is secured along and between the wing members to define a lifting surface. The hinge includes a pitch hinge bracket having an upper longitudinal sleeve in which the keel is clamped. A ball joint connection secured to the bracket is connected to upwardly extending hang cage struts by means of hinge connecting plates to permit free rotation of the wing about a spanwise axis extending longitudinally through the cross brace. Rotation of the wing without pilot intervention induced by positive or negative wind gusts striking the flexible wing panel causes the angle of incidence between the wing and hang cage to vary so that the wing presents a relatively constant angle of attack to relative wind enabling the aircraft to be essentially stall free during flight. A cable and spreader tube arrangement interconnecting forward and trailing ends of the keel to the cross brace undergoes tension and compression loading to distribute bending stress acting on the keel during excessive wind loading to other parts of the aircraft.

    摘要翻译： 轻型最小结构的超轻型飞机包括可折叠的Rogallo型翼，悬挂笼由主铰链组件悬挂。 机翼包括轻质管状结构的纵向龙骨，前缘构件和十字架。 柔性提升面板固定在翼构件之间并且在翼构件之间，以限定提升表面。 铰链包括具有上纵向套筒的俯仰铰链支架，其中龙骨被夹紧。 通过铰链连接板将固定到托架上的球形接头连接件连接到向上延伸的悬挂支架上，以允许机翼围绕纵向延伸穿过横梁的翼展方向轴自由旋转。 没有由正或负阵风引起的飞行员干涉的机翼的旋转撞击柔性翼板导致机翼和吊架之间的入射角度发生变化，使得机翼相对于相对风力具有相对恒定的迎角，使得飞机能够 在飞行中基本上是空闲的。 将龙骨的前端和后端相互连接到横梁的电缆和扩张管布置经受张力和压缩载荷，以在过度的风载入飞行器的其它部分期间分布作用在龙骨上的弯曲应力。