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1. 发明授权

US07963484B2 Lift-augmenting flap, in particular for a leading edge flap, for an aerodynamically effective wing 有权
标题翻译：用于空气动力学有效的翼的提升增强翼，特别是用于前缘翼片
公开(公告)号：US07963484B2
公开(公告)日：2011-06-21
申请号：US11922068
申请日：2006-06-14
申请人： Morten Raudszus , Bernhard Schlipf , Luc Andreani , Xavier Hue , Mark Heintjes
发明人： Morten Raudszus , Bernhard Schlipf , Luc Andreani , Xavier Hue , Mark Heintjes
IPC分类号： B64C3/50
CPC分类号： B64C3/50 , Y02T50/14
摘要： A lift-augmenting leading edge flap for a carrying wing of an aircraft, wherein the flap comprises an essentially rigid main body which makes a transition from the first side to the second side of the wing the flap being adjustable by a retention- and actuation mechanism coupled between the flap and wing box, between a first, retracted, position and a second, extended, position, wherein the first transition region of the flap is slidable to rest in each position essentially free of any gap, against the first skin of the wing box or against the wing end cover, in relation to the wing end cover.
摘要翻译：一种用于飞行器的携带翼的提升增加的前缘翼片，其中所述翼片包括基本上刚性的主体，其从翼的第一侧向第二侧过渡，所述翼可通过保持和致动机构联接在所述翼片和翼盒之间，在第一缩回位置和第二延伸位置之间，其中所述翼片的第一过渡区域可滑动以在基本上没有任何间隙的每个位置中抵靠所述翼片的第一皮肤相对于机翼端盖，机翼盒或机翼端盖。

2. 发明申请

US20090272853A1 Lift-Augmenting Flap, in Particular for Leading Edge Flap, for an Aerodynamically Effective Wing 有权
标题翻译：升降翼，特别是前缘翼片，用于空气动力学有效的翼
公开(公告)号：US20090272853A1
公开(公告)日：2009-11-05
申请号：US11922068
申请日：2006-06-14
申请人： Morten Raudszus , Bernhard Schlipf , Luc Andreani , Xavier Hue , Mark Heintjes
发明人： Morten Raudszus , Bernhard Schlipf , Luc Andreani , Xavier Hue , Mark Heintjes
IPC分类号： B64C3/50 , B64C9/22
CPC分类号： B64C3/50 , Y02T50/14
摘要： A lift-augmenting leading edge flap for a carrying wing of an aircraft, wherein the flap comprises an essentially rigid main body which makes a transition from the first side to the second side of the wing the flap being adjustable by a retention- and actuation mechanism coupled between the flap and wing box, between a first, retracted, position and a second, extended, position, wherein the first transition region of the flap is slidable to rest in each position essentially free of any gap, against the first skin of the wing box or against the wing end cover, in relation to the wing end cover.
摘要翻译：一种用于飞行器的携带翼的提升增加的前缘翼片，其中所述翼片包括基本上刚性的主体，其从翼的第一侧向第二侧过渡，所述翼可通过保持和致动机构联接在所述翼片和翼盒之间，在第一缩回位置和第二延伸位置之间，其中所述翼片的第一过渡区域可滑动以在基本上没有任何间隙的每个位置中抵靠所述翼片的第一皮肤相对于机翼端盖，机翼盒或机翼端盖。

3. 发明授权

US08336829B2 Advanced trailing edge control surface on the wing of an aircraft 有权
标题翻译：先进的后缘控制面在飞机的机翼上
公开(公告)号：US08336829B2
公开(公告)日：2012-12-25
申请号：US11992495
申请日：2006-09-18
申请人： Daniel Reckzeh , Bernhard Schlipf , Luc Andreani , Mark Sutcliffe
发明人： Daniel Reckzeh , Bernhard Schlipf , Luc Andreani , Mark Sutcliffe
IPC分类号： B64C9/16
CPC分类号： B64C9/14 , B64C9/18 , Y02T50/32 , Y02T50/44
摘要： An aircraft wing trailing edge control surface including a trailing edge flap adjustable to different positions, a sealing flap on the upper side between the wing and the flap, and a ventilation flap on the underside between the wing and the flap. The flap is adjustable downward through positive positions and upward through negative positions. The wing profile is closed on the upper side by the sealing flap and the underside by the ventilation flap when the flap is used as a control flap and adjusted between negative and low positive positions. The ventilation flap releases air flow from the wing underside to the upper side of the flap and the sealing flap is retracted to release an outflow of air from the upper side of the flap when the flap is used for increasing lift and the flap is adjusted between low and high positive positions.
摘要翻译：飞行器机翼后缘控制表面，包括可调节到不同位置的后缘翼片，翼和翼片之间的上侧上的密封翼片，以及翼和翼片之间的下侧上的通风翼。舌片可通过正位置向下调节，向上可调，通过负位置。当翼片用作控制挡板并在负和低位置之间进行调整时，机翼轮廓通过密封翼片和下侧由通风挡板封闭在上侧。通风翼释放从翼下侧到翼片上侧的空气流，并且当翼片用于增加升力时，密封翼缩回以释放空气从翼片的上侧流出，并且翼片在低和高的积极位置。

4. 发明申请

US20100006707A1 Advanced Trailing Edge Control Surface on the Wing of an Aircraft 有权
标题翻译：飞机翼上高级尾翼控制面
公开(公告)号：US20100006707A1
公开(公告)日：2010-01-14
申请号：US11992495
申请日：2006-09-18
申请人： Daniel Reckzeh , Bernhard Schlipf , Luc Andreani , Mark Sutcliffe
发明人： Daniel Reckzeh , Bernhard Schlipf , Luc Andreani , Mark Sutcliffe
IPC分类号： B64C9/16 , B64C9/20 , B64C21/02
CPC分类号： B64C9/14 , B64C9/18 , Y02T50/32 , Y02T50/44
摘要： An aircraft wing trailing edge control surface including a trailing edge flap adjustable to different positions, a sealing flap on the upper side between the wing and the flap, and a ventilation flap on the underside between the wing and the flap. The flap is adjustable downward through positive positions and upward through negative positions. The wing profile is closed on the upper side by the sealing flap and the underside by the ventilation flap when the flap is used as a control flap and adjusted between negative and low positive positions. The ventilation flap releases air flow from the wing underside to the upper side of the flap and the sealing flap is retracted to release an outflow of air from the upper side of the flap when the flap is used for increasing lift and the flap is adjusted between low and high positive positions.
摘要翻译：飞行器机翼后缘控制表面，包括可调节到不同位置的后缘翼片，翼和翼片之间的上侧上的密封翼片，以及翼和翼片之间的下侧上的通风翼。舌片可通过正位置向下调节，向上可调，通过负位置。当翼片用作控制挡板并在负和低位置之间进行调整时，机翼轮廓通过密封翼片和下侧由通风挡板封闭在上侧。通风翼释放从翼下侧到翼片上侧的空气流，并且当翼片用于增加升力时，密封翼缩回以释放空气从翼片的上侧流出，并且翼片在低和高的积极位置。

5. 发明授权

US09102394B2 Flow body with a base body and a leading edge 有权
标题翻译：流体与基体和前缘
公开(公告)号：US09102394B2
公开(公告)日：2015-08-11
申请号：US13559825
申请日：2012-07-27
申请人： Bernhard Schlipf , Xavier Hue
发明人： Bernhard Schlipf , Xavier Hue
IPC分类号： B64C3/28 , B64C3/14
CPC分类号： B64C3/28 , B64C2003/146
摘要： A flow body includes a flow body base body with a first shell element, a leading flow body edge with a second shell element and a clamping body, and a receiving space partially delimited by the clamping body. The flow body base body includes on a front end a projection, having a shape corresponding to that of the receiving space for engaging into the receiving space. The clamping body is internally arranged on the leading flow body edge spaced apart from a rear end of the second shell element. The rear end of the second shell element is flushly positioned on the first shell element when the projection engages into the receiving space. A smooth and harmonious transition that does not influence a laminar flow around the flow body can be achieved between the two components.
摘要翻译：流体包括具有第一壳单元的流体基体，具有第二壳单元的引导流体边缘和夹紧体，以及由夹紧体部分界定的容纳空间。流动体基体在前端具有突起，该突起具有与用于接合到接收空间的接收空间的形状相对应的形状。夹紧体内部布置在与第二壳体元件的后端间隔开的引导流动体边缘上。当突起部接合到接收空间中时，第二壳体元件的后端被平齐地定位在第一壳体元件上。可以在两个部件之间实现不影响流体周围的层流的平滑和谐的转变。

6. 发明申请

US20130026295A1 FLOW BODY WITH A BASE BODY AND A LEADING EDGE 有权
标题翻译：流动身体与身体和领先的边缘
公开(公告)号：US20130026295A1
公开(公告)日：2013-01-31
申请号：US13559825
申请日：2012-07-27
申请人： Bernhard Schlipf , Xavier Hue
发明人： Bernhard Schlipf , Xavier Hue
IPC分类号： B64C3/26 , B64C1/12
CPC分类号： B64C3/28 , B64C2003/146
摘要： A flow body includes a flow body base body with a first shell element, a leading flow body edge with a second shell element and a clamping body, and a receiving space partially delimited by the clamping body. The flow body base body includes on a front end a projection, having a shape corresponding to that of the receiving space for engaging into the receiving space. The clamping body is internally arranged on the leading flow body edge spaced apart from a rear end of the second shell element. The rear end of the second shell element is flushly positioned on the first shell element when the projection engages into the receiving space. A smooth and harmonious transition that does not influence a laminar flow around the flow body can be achieved between the two components.
摘要翻译：流体包括具有第一壳单元的流体基体，具有第二壳单元的引导流体边缘和夹紧体，以及由夹紧体部分界定的容纳空间。流体基体在前端具有突出部，该突起的形状与容纳空间接合的形状相对应。夹紧体内部布置在与第二壳体元件的后端间隔开的引导流动体边缘上。当突起部接合到接收空间中时，第二壳体元件的后端被平齐地定位在第一壳体元件上。可以在两个部件之间实现不影响流体周围的层流的平滑和谐的转变。

7. 发明授权

US08925871B2 Wing of an aircraft 有权
标题翻译：机翼
公开(公告)号：US08925871B2
公开(公告)日：2015-01-06
申请号：US13464960
申请日：2012-05-05
申请人： Xavier Hue , Bernhard Schlipf
发明人： Xavier Hue , Bernhard Schlipf
IPC分类号： B64C9/26 , B64C9/22
CPC分类号： B64C9/22
摘要： A wing of an aircraft provided with a main wing and an arrangement of leading edge lifting bodies, which as seen with reference to the incident flow direction are arranged on the leading edge, which are adjustably arranged on the main wing one behind another as seen in the spanwise direction of the main wing by means of respectively two positioning devices spaced apart from one another in the spanwise direction of the main wing. The wing has a connecting device, which is coupled to each of two adjacent leading edge lifting bodies, wherein the connecting device is configured such that in the event of a fracture of a positioning device of a positioning body external forces acting on the latter are transferred via the respective connecting device to the leading edge lifting bodies coupled up via the latter.
摘要翻译：具有主翼的飞机翼和前缘提升体的布置，其如参照入射流动方向所看到的那样布置在前缘上，前缘被可调节地布置在主翼上，如前所述通过分别在主翼的翼展方向上彼此间隔开的两个定位装置，主翼的翼展方向。机翼具有连接装置，其连接到两个相邻的前缘提升体中的每一个，其中连接装置被构造成使得在定位体的定位装置的断裂的情况下，作用在定位体上的外力被转移通过相应的连接装置连接到通过其连接的前缘提升体。

8. 发明申请

US20090013862A1 Dual linear actuator 有权
标题翻译：双线性执行器
公开(公告)号：US20090013862A1
公开(公告)日：2009-01-15
申请号：US12157934
申请日：2008-06-13
申请人： Bernhard Schlipf , Mark Heintjes
发明人： Bernhard Schlipf , Mark Heintjes
IPC分类号： F15B13/00
CPC分类号： F15B18/00 , F15B15/088 , Y10T74/18584
摘要： An actuator having two or more interconnected movement components, wherein the movement components are designed as linear actuators with substantially coaxial longitudinal axes or longitudinal axes that are parallel to each other and that are interconnected in longitudinal direction such that their linear movements are superimposed on one another, and such that at least one of the linear actuators can be stopped at one or several predetermined positions.
摘要翻译：具有两个或更多个互连的运动部件的致动器，其中所述运动部件被设计为线性致动器，所述致动器具有基本上同轴的纵向轴线或彼此平行的纵向轴线，并且在纵向方向上互连，使得它们的线性运动彼此重叠并且使得至少一个线性致动器可以停在一个或几个预定位置。

9. 发明授权

US09422050B2 Fore flap disposed on the wing of an aircraft 有权
标题翻译：飞机前翼设在飞机机翼上
公开(公告)号：US09422050B2
公开(公告)日：2016-08-23
申请号：US13122733
申请日：2009-10-06
申请人： Bernhard Schlipf , Xavier Hue
发明人： Bernhard Schlipf , Xavier Hue
IPC分类号： B64C3/48 , B64C3/50 , B64C9/24 , B64C9/14
CPC分类号： B64C9/24 , B64C3/50 , B64C2009/143
摘要： A leading edge slat arranged on the aerofoil of an aircraft. The leading edge slat is provided on the front of the main wing. The leading edge slat has a partially extended setting, with its trailing edge flat against the wing, and a further extended setting, with its trailing edge spaced apart from the nose of the wing to open a gap feeding high-energy air from the lower surface of the slat to the upper surface of the wing. The leading edge slat includes a body and a trailing edge facing the main wing, which can be bent around the spanwise direction of the slat relative to the body, and on which the trailing edge of the slat is provided, and which by means of a device generating a contact force is loaded for making contact between the trailing edge of the slat and the profile nose of the wing.
摘要翻译：一架安排在飞机机翼上的前沿板条。前缘板条设置在主翼的前部。前缘板条具有部分延伸的设置，其后缘平坦地抵靠机翼，并且进一步延伸设置，其后缘与机翼的鼻部间隔开以打开从下表面供给高能量空气的间隙的板条到机翼的上表面。前缘板条包括主体和面向主翼的后缘，其可相对于主体围绕板条的翼展方向弯曲，并且在其上设置板条的后缘，并且借助于加载产生接触力的装置用于使板条的后缘与机翼的轮廓鼻之间接触。

10. 发明申请

US20120061524A1 AEROFOIL COMPRISING A HIGH LIFT FLAP 有权
标题翻译： AEROFOIL包含一个高提升片
公开(公告)号：US20120061524A1
公开(公告)日：2012-03-15
申请号：US13255276
申请日：2010-03-29
申请人： Bernhard Schlipf , Xavier Hue
发明人： Bernhard Schlipf , Xavier Hue
IPC分类号： B64C3/50
CPC分类号： B64C9/22 , B64C9/02 , B64C9/16
摘要： A wing is provided, including a high-lift flap arranged on the wing such that it is movable by means of at least two adjustment mechanisms arranged side-by-side in the spanwise direction of the wing and adjustable by means of a drive device. Each adjustment mechanism includes a first adjustment lever, articulated on a main wing surface via a first pivotal articulation, with the formation of a first rotation axis; a second adjustment lever, articulated on the high-lift flap via a second pivotal articulation, with the formation of a second rotation axis; and a central articulation, linking together the first and the second adjustment levers, with the formation of a third rotation axis. An intermediate articulated part is arranged on at least one of the adjustment mechanisms for coupling the first adjustment lever and the main wing surface, or for coupling the second adjustment lever and the high-lift flap.
摘要翻译：设置有一个机翼，包括一个设置在机翼上的高升降挡板，使其能够通过在机翼的翼展方向上并排设置并通过驱动装置可调节的至少两个调节机构来移动。每个调节机构包括第一调节杆，通过第一枢转关节铰接在主翼表面上，形成第一旋转轴线; 第二调节杆，通过第二枢转关节铰接在高升降翼上，形成第二旋转轴; 以及将第一和第二调节杆连接在一起的中心关节，形成第三旋转轴线。在至少一个用于联接第一调节杆和主翼面的调节机构中，或用于联接第二调节杆和高升降挡板的中间铰接部件。

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