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1. 发明公开

US20240051655A1 SYSTEM AND METHOD FOR LIFT AUGMENTATION OF AIRCRAFT WINGS 审中-公开
公开(公告)号：US20240051655A1
公开(公告)日：2024-02-15
申请号：US18465375
申请日：2023-09-12
申请人： ELECTRA AERO, INC.
发明人： Christopher B. COURTIN , Mark DRELA , Robert John HANSMAN, JR. , John S. LANGFORD, III , Oliver MASEFIELD
IPC分类号： B64C9/28 , B64C11/00 , B64C9/18 , B64D27/24 , B64C3/58 , B64C9/24
CPC分类号： B64C9/28 , B64C11/00 , B64C9/18 , B64D27/24 , B64C3/58 , B64C9/24 , B64C2009/005
摘要： A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

2. 发明授权

US11826965B2 Method for making consolidated composite structures 有权
公开(公告)号：US11826965B2
公开(公告)日：2023-11-28
申请号：US17744386
申请日：2022-05-13
申请人： The Boeing Company
发明人： Christopher A. Howe , Angelo Koucoulis , Stuart Bateman
IPC分类号： B33Y10/00 , B29C69/02 , B33Y80/00 , B64C9/24 , B29C70/48 , B29K307/04 , B29K309/08 , B29L31/30
CPC分类号： B29C69/02 , B33Y10/00 , B33Y80/00 , B64C9/24 , B29C70/48 , B29K2307/04 , B29K2309/08 , B29L2031/3085
摘要： Disclosed herein are methods for fabricating a composite structure by forming, via additive manufacturing, a solid-phase component; positioning the solid-phase component and a reinforcement into a mold cavity; and consolidating, in the mold cavity, the solid-phase component, the reinforcement, and a liquid-phase component to form the composite structure.

3. 发明申请

US20180370614A1 KRUEGER FLAP APPARATUS AND METHODS INCORPORATING A BULLNOSE HAVING A CONTOUR VARIATION ALONG A SPANWISE DIRECTION 审中-公开
公开(公告)号：US20180370614A1
公开(公告)日：2018-12-27
申请号：US15629542
申请日：2017-06-21
申请人： The Boeing Company
发明人： Adam M. Clark , Kenneth J. Kaufmann , Paul M. Vijgen
IPC分类号： B64C9/24 , B64C9/34 , B64C13/28
CPC分类号： B64C9/24 , B64C9/22 , B64C23/06
摘要： Krueger flap apparatus and methods incorporating a bullnose having a contour variation along a spanwise direction are described. An example apparatus includes a Krueger flap having a bullnose extending in a spanwise direction. The bullnose includes a contour variation formed by a plurality of protuberances located along the bullnose. Respective ones of the protuberances are spaced along the spanwise direction.

4. 发明授权

US09994312B2 Vertical take-off and landing aircraft 有权
公开(公告)号：US09994312B2
公开(公告)日：2018-06-12
申请号：US14886481
申请日：2015-10-19
申请人： IHI CORPORATION
发明人： Masayoshi Tsunekawa , Tetsuya Tamura
IPC分类号： B64C29/00 , B64C3/38 , B64C27/00 , B64C9/24 , B64C11/00
CPC分类号： B64C29/0033 , B64C3/385 , B64C9/24 , B64C11/001 , B64C27/006
摘要： A vertical take-off and landing aircraft includes a propulsion mechanism that generates lift and thrust, a main frame that supports seating and a landing undercarriage, a sub-frame which supports the propulsion mechanism and is arranged so as to be swingable back and forth relative to the main frame, a motive power supply unit supported by the main frame and supplying motive power to the propulsion mechanism, a control stick connected to the sub-frame, and a main wing arranged on the propulsion mechanism, wherein the main wing is formed to be retracted to a position not interfering with an air flow of the propulsion mechanism in a normal time and to be movable to a position where lift is generated when thrust is lost. Gliding is made possible even if thrust is lost while increasing in size of a fuselage is avoided.

5. 发明授权

US09878790B2 Method and device for fitting out an aircraft nose compartment in an avionics bay 有权
公开(公告)号：US09878790B2
公开(公告)日：2018-01-30
申请号：US14620021
申请日：2015-02-11
申请人： Airbus Operations (S.A.S.)
发明人： Samuel Burgunder , Bernard Guering
IPC分类号： B64C1/20 , B64D11/00 , B64C1/06 , B64C9/14 , B64C9/24 , B64C25/02
CPC分类号： B64D11/00 , B64C1/061 , B64C1/20 , B64C9/14 , B64C9/24 , B64C25/02 , Y02T50/46
摘要： Method of device for installation of avionics cabinets, electrical master boxes and IFE bays includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, systems cabinets are used which incorporate a structural function. The use of such system cabinet designs thus allows a reduction in the aerodynamic drag and mass of the aircraft, thereby positively impacting fuel consumption and performance of the aircraft.

6. 发明授权

US09868511B2 High lift system for an aircraft and aircraft having such a high lift system 有权
公开(公告)号：US09868511B2
公开(公告)日：2018-01-16
申请号：US14608271
申请日：2015-01-29
申请人： Airbus Operations GmbH
发明人： Frieder Henning , Tanno Zantz , Michael Brady
IPC分类号： B64C9/22 , B64C9/24 , B64C13/50 , F03D1/06 , B64C9/14
CPC分类号： B64C9/22 , B64C9/24 , B64C13/50 , B64C2009/143 , F03D1/0641 , Y02E10/721
摘要： A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.

7. 发明申请

US20170259909A1 AIRCRAFT WING STRUCTURE AND ASSOCIATED METHOD FOR ADDRESSING LIFT AND DRAG 审中-公开
公开(公告)号：US20170259909A1
公开(公告)日：2017-09-14
申请号：US15069117
申请日：2016-03-14
申请人： The Boeing Company
发明人： Arvin Shmilovich , Yoram Yadlin
IPC分类号： B64C9/24 , B64C21/04
CPC分类号： B64C9/24 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , B64C2230/18
摘要： An aircraft, an aircraft wing structure and a method are provided in order to address lift and drag, such as by increasing lift and reducing drag. In the context of an aircraft wing structure, the aircraft wing structure includes a wing extending outboard from a fuselage of an aircraft. The wing also extends from a leading edge to a trailing edge. The aircraft wing structure also includes one or more actuators carried by the wing and causing fluid to be directed through one or more respective orifices defined by the wing so as to alter flow over a lower surface of the wing. The one or more orifices that are defined by the wing are closer to the leading edge than to the trailing edge. Thus, the fluid introduced through the one or more orifices may increase lift and reduce drag of the associated aircraft.

8. 发明申请

US20170190410A1 CONTROLLING AIRLOADS ON AIRCRAFT FOLDING WING TIPS 有权
公开(公告)号：US20170190410A1
公开(公告)日：2017-07-06
申请号：US14988202
申请日：2016-01-05
申请人： The Boeing Company
发明人： Mark Steven Good , Jonathan J. Paul
IPC分类号： B64C3/56 , B64C9/24
CPC分类号： B64C3/56 , B64C9/24 , B64C2009/005 , Y02T50/14
摘要： Example apparatus and methods are disclosed herein for moving control surfaces on an aircraft wing to control airloads during a wing tip folding operation (from a folded position to an extended position or from an extended position to a folded position). An example method includes determining a position of a control surface on a wing of an aircraft. In the example method, the wing has a fixed wing portion and a wing tip moveably coupled to the fixed wing portion. The example method includes determining a change in the position of the control surface from a first position to second position for facilitating movement of the wing tip while the aircraft is not in flight. The example method also includes moving the control surface to the second position and moving the wing tip between an extended position and a folded position.

9. 发明授权

US09598167B2 Morphing airfoil leading edge 有权
公开(公告)号：US09598167B2
公开(公告)日：2017-03-21
申请号：US14196461
申请日：2014-03-04
申请人： The Boeing Company
发明人： Robert E. Grip , John J. Brown , Neal A. Harrison , Blaine K. Rawdon , John C. Vassberg
IPC分类号： B64C9/24 , B64C3/26 , B64C3/28 , B64C3/48 , B64C3/38 , B64C3/44
CPC分类号： B64C9/24 , B64C3/26 , B64C3/28 , B64C3/38 , B64C3/48 , B64C3/50 , B64C2003/445 , Y02T50/14
摘要： An airfoil may include a leading edge and a shape control mechanism. The leading edge may include a flexible leading edge skin having a first end, a second end, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations and may transition the flexible leading edge skin from a first shape having a first curvature profile to a second shape having a second curvature profile different than the first curvature profile without a change in the arc length.

10. 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。

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