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1. 发明申请

WO2012171034A1 THE SPLIT SPIROID 审中-公开
标题翻译： SPLIT SPIROID
公开(公告)号：WO2012171034A1
公开(公告)日：2012-12-13
申请号：PCT/US2012/041961
申请日：2012-06-11
申请人： AVIATION PARTNERS, INC. , GRATZER, Louis, B.
发明人： GRATZER, Louis, B.
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： The spiroid wing tip according to embodiments of the invention including a continuous segmental assembly having a closed loop frontal profile comprising a lower near vertical segment, a horizontal segment, a vertical segment, a second horizontal upper segment, and a near vertical segment. Accordingly to some embodiments of the invention, the spiroid profile is lowered with respect to the wing chord plane, such that a portion of the spiroid wing tip extends below the wing chord plane.
摘要翻译：根据本发明的实施例的螺旋翼尖包括具有闭环正面轮廓的连续节段组件，该连续节段组件包括下近近垂直段，水平段，垂直段，第二水平上段和近垂直段。因此，根据本发明的一些实施例，螺旋体轮廓相对于翼弦平面降低，使得一部分螺旋翼尖延伸到翼弦平面的下方。

2. 发明申请

WO2009155584A1 CURVED WING TIP 审中-公开
公开(公告)号：WO2009155584A1
公开(公告)日：2009-12-23
申请号：PCT/US2009/048065
申请日：2009-06-19
申请人： AVIATION PARTNERS, INC. , GRATZER, Louis, B.
发明人： GRATZER, Louis, B.
IPC分类号： B64C3/10
CPC分类号： B64C23/069 , B64C3/10 , B64C11/18 , B64C27/463 , Y02T50/164
摘要： A wing incorporating a wing tip with a curved leading edge and a curved trailing edge to minimize induced drag for a given wing form is disclosed. The curve of the leading and trailing edges of the wing tip may be described generally as parabolic, elliptic, or super elliptic. A finite tip segment may be included with a sweep angle between the end of the curved leading edge and the end of the curved trailing edge. The wing tip may also include a spanwise camber.
摘要翻译：公开了一种具有弯曲前缘和弯曲后缘的翼尖的翼，以最小化给定翼形式的诱发阻力。翼尖的前缘和后缘的曲线可以被概括地描述为抛物线形，椭圆形或超椭圆形。有限的尖端段可以包括在弯曲前缘的端部与弯曲后缘的端部之间的扫掠角度。翼尖还可以包括翼展向外倾角。

3. 发明申请

WO2020146399A1 HIGH-PERFORMANCE WINGLET 审中-公开
公开(公告)号：WO2020146399A1
公开(公告)日：2020-07-16
申请号：PCT/US2020/012597
申请日：2020-01-07
申请人： AVIATION PARTNERS, INC.
发明人： SIKAVI, Danny A.
IPC分类号： B64C23/06
摘要： High-performance winglets are provided for attachment to an airplane wing. A split blended winglet includes a blended or upper winglet smoothly extending from the wing tip above a chord plane of the wing and a lower winglet including a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet includes a blade section that projects vertically along a reverse curve before transitioning to a linear upper blade portion. Upper and lower surfaces of the upper winglet are bound by leading and trailing edges that are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Upper and lower surfaces of the lower winglet are bound by leading and trailing edges that curve toward the airstream direction and terminate at a point distal of the wing tip.

4. 发明申请

WO2016022692A1 SPLIT BLENDED WINGLET 审中-公开
标题翻译：分散混合WINGLET
公开(公告)号：WO2016022692A1
公开(公告)日：2016-02-11
申请号：PCT/US2015/043819
申请日：2015-08-05
申请人： AVIATION PARTNERS, INC.
发明人： GRATZER, Louis, B.
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： A split winglet configured for attachment to a wing of an airplane. The split winglet may include an upper winglet smoothly extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet may include a transition section which curves upward from the wing tip into a substantially planar section. Upper and lower surfaces of the upper winglet may be bounded by leading and trailing edges which are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Similarly, upper and lower surfaces of the ventral fin may be bounded by leading and trailing edges which curve toward the airstream direction and terminate at a point distal of the wing tip.
摘要翻译：构造成附接到飞机机翼的分裂小翼。分裂的小翼可以包括从机翼尖端平滑地延伸到机翼的弦平面上方的上小翼和从上小翼的下表面突出到弦平面下方的腹鳍。上小翼可以包括从翼尖向上弯曲成基本平坦的部分的过渡部分。上小翼的上表面和下表面可以被前缘和后缘限定，前缘和后缘平行于和弦平面扫过气流方向，并且在端翼远端终止之前朝向气流方向弯曲。类似地，腹鳍的上表面和下表面可以由朝向气流方向弯曲的前缘和后缘界定，并终止在翼尖的远端。

5. 发明申请

WO2012171023A1 THE SPLIT BLENDED WINGLET 审中-公开
标题翻译：分开混合的WINGLET
公开(公告)号：WO2012171023A1
公开(公告)日：2012-12-13
申请号：PCT/US2012/041936
申请日：2012-06-11
申请人： AVIATION PARTNERS, INC. , GRATZER, Louis, B.
发明人： GRATZER, Louis, B.
IPC分类号： B64C23/06
CPC分类号： B64C23/069 , Y02T50/164
摘要： A split winglet is disclosed having a first generally upward projecting wing end, and a second generally downward projecting wing end. The second generally downward projecting wing end may be integrally formed with the first generally upward projecting wing end to form a winglet assembly or may be separately attached onto an existing upwardly curved winglet.
摘要翻译：公开了一种具有第一大致向上突出的翼端和第二大致向下突出的翼端的分裂小翼。第二个大致向下突出的翼端可以与第一大致向上突出的翼端一体地形成，以形成小翼组件，或者可以单独地附接到现有的向上弯曲的小翼上。

6. 发明申请

WO2017176583A1 ACTUATOR FOR ADAPTIVE AIRFOIL 审中-公开
标题翻译：适应性翼的执行器
公开(公告)号：WO2017176583A1
公开(公告)日：2017-10-12
申请号：PCT/US2017/025375
申请日：2017-03-31
申请人： AVIATION PARTNERS, INC.
发明人： DAVIS, Edward
IPC分类号： B64C3/46 , B64C3/44
CPC分类号： B64C9/18 , B64C3/50 , B64C9/02 , B64C9/16 , B64C13/30 , B64C2003/445
摘要： An apparatus and method for an actuator system to modify an adaptive flap of an aircraft wing. The system may include a drive rod extending from a nose portion of the flap to an interior thereof. A bell crank may be attached to the interior and configured to receive an end of the drive rod. A pivot disposed opposite of the drive rod may couple the bell crank to a mount fixed to a lower surface of a trailing edge portion of the flap. A skin overlap may be configured to allow the lower surface of the trailing edge portion to slide adjacent to a lower surface of a remaining portion of the flap under the action of the drive rod. A bumper may be disposed within the aircraft wing and configured to exert a continuous force on the drive rod when the flap is moved to a retracted state.
摘要翻译：用于致动器系统修改飞机机翼的自适应襟翼的装置和方法。该系统可以包括从护翼的鼻部延伸到其内部的驱动杆。钟形曲柄可以连接到内部并构造成接收驱动杆的一端。布置在驱动杆对面的枢轴可将钟形曲柄连接到固定到翼片的后缘部分的下表面的支架。表皮重叠可以被配置为允许后缘部分的下表面在驱动杆的作用下邻近瓣的其余部分的下表面滑动。保险杠可以设置在飞机机翼内并且被配置成当翼片移动到缩回状态时在驱动杆上施加连续的力。

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