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1. 发明授权

US11254414B2 Aircraft wing droop leading edge apparatus and methods 有权
公开(公告)号：US11254414B2
公开(公告)日：2022-02-22
申请号：US16849096
申请日：2020-04-15
申请人： The Boeing Company
发明人： Arvin Shmilovich , Eric D. Dickey
IPC分类号： B64C9/00 , B64C3/18 , B64C13/02 , B64C13/30 , B64C3/26
摘要： Aircraft wing droop leading edge apparatus and methods are described. An example aircraft includes a wing having a front spar and an outer skin covering the front spar. The outer skin includes a forward portion located forward of the front spar. The forward portion of the outer skin includes a leading edge movable between a neutral position and a drooped position deflected downward relative to the neutral position. The forward portion of the outer skin has a continuous outer mold line when the leading edge is in the drooped position.

2. 发明授权

US10988240B2 Thermally controlled active flow control system 有权
公开(公告)号：US10988240B2
公开(公告)日：2021-04-27
申请号：US16102179
申请日：2018-08-13
申请人： The Boeing Company
发明人： Arvin Shmilovich , Edward Andrew Whalen
IPC分类号： B64C21/04 , F15B21/12 , F15B21/042 , F15D1/12 , F15D1/00 , F15C1/00 , B64D33/02
摘要： A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

3. 发明申请

US20180363491A1 METHODS AND APPARATUS FOR REDUCING FLOW DISTORTION AT ENGINE FANS OF NACELLES 审中-公开
公开(公告)号：US20180363491A1
公开(公告)日：2018-12-20
申请号：US15625664
申请日：2017-06-16
申请人： The Boeing Company
发明人： Arvin Shmilovich , Yoram Yadlin
IPC分类号： F01D17/10 , F01D25/24
摘要： Methods and apparatus for reducing flow distortion at engine fans of nacelles are disclosed. An example apparatus for reducing flow distortion at an engine fan of a nacelle includes a plurality of nozzles radially spaced about an inner wall of the nacelle. In some examples, respective ones of the nozzles are positioned to eject corresponding respective jets of fluid adjacent the inner wall in a downstream direction toward the engine fan. The example apparatus further includes a controller to selectively activate the respective ones of the nozzles according to a time-based sequence. In some examples, the time-based sequence corresponds to a directional sequence that moves in an arcuate direction along a circumference of the inner wall.

4. 发明申请

US20160375986A1 METHOD AND APPARATUS FOR ROBUST LIFT GENERATION 有权
标题翻译：用于稳健提升生成的方法和装置
公开(公告)号：US20160375986A1
公开(公告)日：2016-12-29
申请号：US14637288
申请日：2015-03-03
申请人： The Boeing Company
发明人： Arvin Shmilovich , Yoram Yadlin
IPC分类号： B64C21/04 , B64C21/08 , B64C9/38
CPC分类号： B64C21/04 , B64C9/38 , B64C21/08 , Y02T50/166
摘要： A system and method for robust lift generation through flow separation suppression are presented. A fluid flow is ejected over a lifting surface from a fluid ejection orifice, and a flow direction of the fluid flow over the lifting surface is directed using a plurality of vanes configured in the fluid ejection orifice. The flow direction is rotated in a span-wise direction over the lifting surface by swiveling the vanes.
摘要翻译：提出了一种通过流动分离抑制实现鲁棒提升生成的系统和方法。流体流从流体喷射孔喷射到提升表面上，并且使用构造在流体喷射孔中的多个叶片来引导在提升表面上的流体流动的流动方向。通过旋转叶片，流动方向在跨越提升表面的跨度方向上旋转。

5. 发明公开

US20230264806A1 HIGH EFFICIENCY AIRCRAFT FLOW CONTROL ACTUATORS 审中-公开
公开(公告)号：US20230264806A1
公开(公告)日：2023-08-24
申请号：US17652239
申请日：2022-02-23
申请人： The Boeing Company
发明人： Arvin Shmilovich , Yoram Yadlin
IPC分类号： B64C21/04
CPC分类号： B64C21/04 , B64C2230/18
摘要： A method, apparatus, and system for managing airflow comprising flow control actuators in an aircraft. The flow control actuators comprise channels having inlets and outlets, wherein the channels are located under a surface of the aircraft and the outlets are in communication with the surface of the aircraft. Pressurized air applied to the inlets causes steady air jets to be emitted at the outlets in which the steady air jets add a momentum to airflow over the surface on the aircraft.

6. 发明申请

US20200182080A1 METHODS AND APPARATUS FOR REDUCING FLOW DISTORTION AT ENGINE FANS OF NACELLES 审中-公开
公开(公告)号：US20200182080A1
公开(公告)日：2020-06-11
申请号：US16793716
申请日：2020-02-18
申请人： The Boeing Company
发明人： Arvin Shmilovich , Yoram Yadlin
IPC分类号： F01D17/10 , F01D25/24 , F02C7/04 , F02C7/057
摘要： Methods and apparatus for reducing flow distortion at engine fans of nacelles are disclosed. An example apparatus for reducing flow distortion at an engine fan of a nacelle includes a plurality of nozzles radially spaced about an inner wall of the nacelle. In some examples, respective ones of the nozzles are positioned to eject corresponding respective jets of fluid adjacent the inner wall in a downstream direction toward the engine fan. The example apparatus further includes a controller to selectively activate the respective ones of the nozzles according to a time-based sequence. In some examples, the time-based sequence corresponds to a directional sequence that moves in an arcuate direction along a circumference of the inner wall.

7. 发明申请

US20190248475A1 ACTIVE FLOW CONTROL SYSTEMS AND METHODS FOR AIRCRAFT 审中-公开
公开(公告)号：US20190248475A1
公开(公告)日：2019-08-15
申请号：US16396177
申请日：2019-04-26
申请人： The Boeing Company
发明人： Arvin Shmilovich , Yoram Yadlin , Paul Vijgen
IPC分类号： B64C23/06 , B64C21/04 , B64C9/38 , B64C21/08 , G05D7/06
CPC分类号： B64C23/065 , B64C9/38 , B64C21/04 , B64C21/08 , B64C2230/04 , B64C2230/06 , G05D7/0664
摘要： Example active flow control systems and methods for aircraft are described herein. An example active flow control system includes a plurality of nozzles arranged in an array across a surface of an aircraft. The nozzles are oriented to eject air across the surface to reduce airflow separation. The active flow control system also includes an air source coupled to the nozzles and a controller to activate the nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a wave of air moving from outboard to inboard and then from inboard to outboard across the surface.

8. 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.

9. 发明申请

US20160375987A1 SYSTEM AND METHOD FOR ENHANCING THE HIGH-LIFT PERFORMANCE OF AN AIRCRAFT 有权
标题翻译：提高飞机高性能的系统和方法
公开(公告)号：US20160375987A1
公开(公告)日：2016-12-29
申请号：US14690377
申请日：2015-04-18
申请人： The Boeing Company
发明人： Arvin Shmilovich , Yoram Yadlin
IPC分类号： B64C21/04 , B64C3/18 , B64C9/16
CPC分类号： B64C21/04 , B64C3/185 , B64C9/16 , B64C9/38 , B64C2009/005 , B64C2230/04 , B64C2230/06 , Y02T50/166 , Y02T50/32
摘要： A drag reduction system for an aircraft may include an air ejector having an ejection port located between an aft portion of an airfoil main element and a forward portion of a trailing edge device. The air ejector may be configured to discharge an air jet from the ejection port in such a manner that the air jet passes over the upper surface of the trailing edge device.
摘要翻译：用于飞机的减阻系统可以包括具有位于翼型主元件的后部与后缘装置的前部之间的排出口的空气喷射器。空气喷射器可以被配置为以这样的方式从喷射口排出空气射流，使得空气喷射通过后缘装置的上表面。

10. 发明授权

US09371132B2 Systems and methods for attenuation of noise and wakes produced by aircraft 有权
标题翻译：用于衰减飞机产生的噪声和唤醒的系统和方法
公开(公告)号：US09371132B2
公开(公告)日：2016-06-21
申请号：US14099400
申请日：2013-12-06
申请人： The Boeing Company
发明人： Arvin Shmilovich , Abdollah Khodadoust
IPC分类号： B64C21/04 , B64C21/08 , B64C9/38 , B64C23/06
CPC分类号： B64C21/04 , B64C9/38 , B64C21/08 , B64C23/06 , B64C2230/04 , B64C2230/06 , Y02T50/162
摘要： Systems and methods for reducing the trailing vortices and lowering the noise produced by the side edges of aircraft flight control surfaces, tips of wings and winglets, and tips of rotor blades. A noise-reducing, wake-alleviating device is disclosed which incorporates an actuator and one or more air-ejecting slot-shaped openings coupled to that actuator and located on the upper and/or lower surfaces and/or the side edges of an aircraft flight control surface or the tip of a wing, winglet or blade. The actuation mechanism produces sets of small and fast-moving air jets that traverse the openings in the general streamwise direction. The actuation destabilizes the flap vortex structure, resulting in reduced intensity of trailing vortices and lower airplane noise.
摘要翻译：用于减少尾部涡流并降低由飞行器飞行控制表面的侧缘，翼和小翼的尖端以及转子叶片的尖端产生的噪声的系统和方法。公开了一种降噪的尾流缓冲装置，其包括致动器和联接到该致动器并且位于飞行器飞行器的上和/或下表面和/或侧边缘上的一个或多个空气喷射槽形开口控制面或翼，小翼或叶片的尖端。致动机构产生一组在一般流向方向上穿过开口的小而快速移动的空气射流。该致动使翼片涡旋结构变得不稳定，导致后退涡流的强度降低，飞机噪音降低。

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