公开(公告)号：US20180305007A1

公开(公告)日：2018-10-25

申请号：US16020802

申请日：2018-06-27

申请人： JETOPTERA, INC.

发明人： Andrei Evulet

IPC分类号： B64C29/00 ,  B64C15/02 ,  B64C39/12 ,  B64C39/06 ,  B64D33/04 ,  B64D27/16 ,  B64C3/16

CPC分类号： B64C29/005 ,  B64C3/16 ,  B64C15/02 ,  B64C39/066 ,  B64C39/12 ,  B64D27/16 ,  B64D33/04

摘要： A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

公开(公告)号：US20180258880A1

公开(公告)日：2018-09-13

申请号：US15980476

申请日：2018-05-15

申请人： The Boeing Company

发明人： David Alan Bakken

IPC分类号： F02K1/12 ,  F02K1/80

CPC分类号： F02K1/1207 ,  B64C15/02 ,  F02K1/06 ,  F02K1/30 ,  F02K1/70 ,  F02K1/72 ,  F02K1/78 ,  F02K1/805 ,  F16J15/00 ,  F16J15/02 ,  Y02T50/671

摘要： Methods and apparatus for sealing variable area fan nozzles of jet engines are disclosed. An apparatus in accordance with the teachings of this disclosure includes a frame and a seal to be coupled to the frame. The seal to enclose petals of a variable area fan nozzle to substantially prevent airflow between the petals.

公开(公告)号：US20180162540A1

公开(公告)日：2018-06-14

申请号：US15576996

申请日：2016-05-27

申请人： BOMBARDIER INC.

发明人： Alexandros ILIOPOULOS ,  Laurent REGNAULT ,  Marcin KULCZYK ,  Alain RICHER

IPC分类号： B64D27/18 ,  B64F5/10 ,  G01M1/12

CPC分类号： B64D27/18 ,  B64C15/02 ,  B64F5/10 ,  G01M1/125

摘要： An aircraft (10) is described as including a reference axis extending along at least a portion of the aircraft, and a propulsion system having a thrust vector feature (43) defining generally a direction of thrust of the turbofan engine (18), the thrust vector feature (43) extending relative to a thrust vector axis, where the turbofan engine (18) is disposed on the aircraft with the thrust vector feature (43) oriented with respect to the reference axis of the aircraft.

公开(公告)号：US09944393B1

公开(公告)日：2018-04-17

申请号：US14941660

申请日：2015-11-16

申请人： FlyDive, Inc.

发明人： Ryan Lorence

IPC分类号： B64C39/02 ,  F16L41/02 ,  B64C15/02 ,  B63H11/107

CPC分类号： B64C39/026 ,  B63B35/7943 ,  B63H11/04 ,  B63H11/107 ,  B63H2011/006 ,  B64C15/02 ,  F16L41/02

摘要： A novel two-way splitter having reduced distance between outlets, while enabling smooth, efficient fluid flow (e.g., water flow) is provided. In a variant, the splitter includes a first pipe and a second pipe meeting at an interface near the inlet and extending away from the inlet, wherein portions of the first pipe and the second pipe proximal to the inlet are substantially helical and are intertwined with each other. In another variant, the first and second pipes have first portions proximal to the inlet which extend vertically side by side away from the inlet, such that the width of each first portion decreases and the depth of each first portion increases as a vertical distance from the inlet increases.

公开(公告)号：US09919792B2

公开(公告)日：2018-03-20

申请号：US14322752

申请日：2014-07-02

申请人： THE AEROSPACE CORPORATION

发明人： Kevin L Zondervan ,  Jerome K Fuller

IPC分类号： B64C15/02 ,  B64C17/00 ,  F02K1/00 ,  F02K9/90 ,  B64C19/00 ,  F02K9/80

CPC分类号： B64C15/02 ,  B64C17/00 ,  B64C19/00 ,  F02K1/002 ,  F02K9/80 ,  F02K9/90

摘要： Attitude and/or attitude rate of a vehicle may be controlled using jet paddles and/or movable masses. Thrust direction generally may also be controlled using jet paddles. The jet paddles may be moved into and/or sufficiently close to the exhaust flow, and out of the exhaust flow, to change the thrust direction. Movable masses may also be used in addition to, or in lieu of, jet paddles. Movement of the movable masses alters a center-of-mass of the vehicle, generating torque that changes vehicle attitude.

公开(公告)号：US20180002014A1

公开(公告)日：2018-01-04

申请号：US15200211

申请日：2016-07-01

申请人： Bell Helicopter Textron Inc.

发明人： John Richard McCullough ,  Paul K. Oldroyd

IPC分类号： B64C29/02 ,  B64C11/46 ,  B64C15/02 ,  G05D1/00

CPC分类号： B64C29/02 ,  B64C11/46 ,  B64C15/02 ,  G05D1/0011 ,  G05D1/102

摘要： In some embodiments, an aircraft includes a flying frame having an airframe with first and second wing members having a plurality of pylons extending therebetween, a distributed propulsion system including a plurality of propulsion assemblies securably attached to the airframe and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode with the wing members disposed in generally the same horizontal plane and a forward flight mode with the wing members disposed in generally the same vertical plane. The flight control system is operable to command the propulsion assemblies responsive to at least one of remote flight control, autonomous flight control and combinations thereof

公开(公告)号：US20170210468A1

公开(公告)日：2017-07-27

申请号：US15129555

申请日：2015-03-27

申请人： THE BOARD OF REGENTS FOR OKLAHOMA STATE UNIVERSITY

发明人： JAMEY D. JACOB ,  WENG KHEONG LOH

IPC分类号： B64C37/00 ,  B64C1/30 ,  B64C15/02 ,  B64C39/02

CPC分类号： B64C37/00 ,  B62D57/00 ,  B64C1/30 ,  B64C15/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/126

摘要： An embodiment of the present disclosure relates to an unmanned flying robotic object that contains a wheeled mechanism that encircles its spherical exoskeleton. This feature allows the flying spherical vehicle to readily transform into a ground maneuverable vehicle. A robotic motor with differential speed capability is used to operate each wheel to provide effective ground maneuverability. There are examples provided herein of wheel configurations suitable for use with an embodiment. One is the straight-(or parallel) wheel design, and another is tilted-wheel design as are illustrated and discussed hereinafter. One embodiment of an unmanned flying robotic object taught herein is foldable.

公开(公告)号：US09561844B2

公开(公告)日：2017-02-07

申请号：US13552263

申请日：2012-07-18

申请人： Itzhak Yogev ,  Michael Shepshelovich ,  Danny Abramov

发明人： Itzhak Yogev ,  Michael Shepshelovich ,  Danny Abramov

IPC分类号： B64C9/12 ,  B64C9/32 ,  B64C15/02

CPC分类号： B64C9/12 ,  B64C9/323 ,  B64C9/326 ,  B64C15/02 ,  Y02T50/32

摘要： A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system.

摘要翻译： 一种用于向具有垂直稳定器装置的机动车辆提供可控侧力的方法包括：（a）选择性地使垂直稳定器装置在第一侧方向上产生第一侧力以提供可控的侧向力，第一侧向力 在第一偏转方向上相应的第一横摆力矩; 以及（b）选择性地向所述空中交通工具提供在第二偏转方向上的第二横摆力矩，所述第二横摆力矩由施加到所述空中车辆的辅助力的力分量感应，所述力分量处于 相对于第一侧方向不平行，并且力分量与空中交通工具的重心间隔开; 其中所述第二偏转方向与所述第一偏转方向相对。 还公开了相应的辅助偏航产生系统。

公开(公告)号：US20160129992A1

公开(公告)日：2016-05-12

申请号：US14922420

申请日：2015-10-26

申请人： Airbus Operations (SAS)

发明人： Marie-Claire Moune

IPC分类号： B64C15/02 ,  B64D25/00

CPC分类号： B64C15/02 ,  B64D25/00 ,  B64D31/06 ,  B64D31/10

摘要： An energy protection device comprising an activation unit for, in a low energy situation, automatically activating an energy protection function comprising automatically engaging an autothrust and automatically controlling the engines of the aircraft for the engines to supply a maximum thrust, an auxiliary monitoring unit configured to perform a monitoring to detect an absence of activation of a protection mode by at least one of the engines of the aircraft although an activation command has been transmitted, and a disconnection unit to automatically disconnect the autothrust in case of the detection of such a situation, a disconnection of the autothrust resulting in the triggering of the protection function being stopped.

摘要翻译： 一种能量保护​​装置，包括用于在低能量情况下自动启动能量保护功能的激活单元，所述能量保护功能包括自动地接合自相关并自动地控制用于发动机的飞机的发动机以提供最大推力;辅助监控单元， 执行监视以检测飞机的至少一个发动机的保护模式的激活，尽管已经发送了激活命令，以及断开单元，在检测到这种情况的情况下自动断开自动停止， 自动停止导致触发保护功能的断开被停止。

公开(公告)号：US20160075428A1

公开(公告)日：2016-03-17

申请号：US14746055

申请日：2015-06-22

申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

发明人： Fuminori FUJISAWA ,  Hiroyuki TANI ,  Daisuke HYUGA

IPC分类号： B64C15/02 ,  F42B15/01

CPC分类号： B64C15/02 ,  F42B10/665

摘要： The thrust vectoring apparatus has a nozzle, a jet tab arranged behind the nozzle, a rotation shaft 30 connected to the jet tab, and a gas seal member arranged on an outer circumferential surface of the rotation shaft. The rotation shaft is connected to the jet tab, and has the protrusion in the redial direction out of the rotation shaft on the rear side of the gas seal member. The protrusion restrains that the combustion gas exhausted from the nozzle flows toward the gas seal member.

摘要翻译： 推力矢量装置具有喷嘴，配置在喷嘴后方的喷嘴，与喷嘴连接的旋转轴30，以及设置在旋转轴的外周面上的气体密封部件。 旋转轴连接到喷射突出部，并且在气体密封构件的后侧具有从重心方向突出的旋转轴。 该突起限制从喷嘴排出的燃烧气体朝向气体密封构件流动。