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公开(公告)号：US20190217937A1
公开(公告)日：2019-07-18
申请号：US16256374
申请日：2019-01-24
申请人： Lilium GmbH
发明人： Daniel Wiegand
CPC分类号： B64C1/0009 , B64C3/385 , B64C3/48 , B64C29/0025 , B64C29/0033 , B64D27/02 , B64D27/12 , Y02T50/12 , Y02T50/14 , Y02T50/44
摘要： An aircraft includes a fuselage and first and second pairs of aerofoils, the aerofoils of each pair extend from opposing sides of the fuselage. Each aerofoil includes a first lift body and a second lift body which is arranged behind the first lift body in a direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil. At least one engine is arranged on the second lift body of at least one of the first and second pairs of aerofoils.
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公开(公告)号：US10351226B2
公开(公告)日：2019-07-16
申请号：US15921826
申请日：2018-03-15
发明人： Donald Freund
IPC分类号： B64C23/00 , B64C3/18 , B64C3/20 , B64C3/38 , B64C3/42 , B64C9/00 , B64C17/10 , B64C30/00 , B64D37/00
摘要： A method of controlling a magnitude of a sonic boom caused by off-design-condition operation of a supersonic aircraft at supersonic speeds includes, but is not limited to the step of operating the supersonic aircraft at supersonic speeds and at an off-design-condition. The supersonic aircraft has a pair of swept wings having a plurality of composite plies oriented at an angle such that an axis of greatest stiffness is non-parallel with respect to a rear spar of each wing of the pair of swept wings. The method further includes, but is not limited to the step of reducing wing twist caused by operation of the supersonic aircraft at supersonic speeds at the off-design condition with the composite plies. The method still further includes, but is not limited to, minimizing the magnitude of the sonic boom through reduction of wing twist.
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公开(公告)号：US10308346B2
公开(公告)日：2019-06-04
申请号：US15134938
申请日：2016-04-21
摘要： The present invention is directed to a solar-powered aircraft comprising a fixed wing panel, a motor driven propeller, a plurality of secondary wing panels, and a tail assembly having a first tail panel and a second tail panel. Each secondary wing panel being configured to rotate about a first longitudinal pivot axis extending from a distal end of the fixed wing panel through a central transverse portion of the secondary wing panel. The secondary wing panels may comprise an array of solar panels on its surface. The first tail panel comprises a second array of solar panels located on a surface of the first tail panel, the first tail panel being configured to rotate about a second longitudinal pivot axis through a central transverse portion of the first tail panel.
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公开(公告)号：US10293933B2
公开(公告)日：2019-05-21
申请号：US15801833
申请日：2017-11-02
发明人： Jonathan Moshe
摘要： A tailsitter aircraft includes one or more rotatable wings. The tailsitter aircraft optionally includes a fuselage from which wing supports extend. Each rotatable wing optionally includes a rotatable wing section having an inboard portion proximate to the fuselage, and an outboard portion distal from the fuselage. The rotatable wing section may be rotatably attached to the wing support and configured to rotate between a vertical flight configuration in which the inboard portion is positioned on an opposing side of the wing support relative to the outboard portion, and a horizontal flight configuration different from the vertical flight configuration. The wings may be rotated during flight to transition between horizontal and vertical flight configurations, and they may be rotated about multiple axes.
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公开(公告)号：US20190135423A1
公开(公告)日：2019-05-09
申请号：US15808801
申请日：2017-11-09
摘要： In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.
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公开(公告)号：US10279891B2
公开(公告)日：2019-05-07
申请号：US15171279
申请日：2016-06-02
申请人： Google Inc.
摘要： Systems and methods for operating control surfaces of an aircraft. The method involves receiving, by an aircraft control system from one or more sensors, deflection information related to a shape and motion of an aircraft, and decomposing, by the aircraft control system, the deflection information into a detected modal state including a first known mode having a first mode strength. The method may further involve determining, by the aircraft control system, a first modal compensation based on the first mode strength, and identifying, by the aircraft control system, a desired control corresponding to a second known mode. The method may yet further involve determining a first control response for a control surface having a first modal weight and a second modal weight, based on the first modal compensation and the first modal weight, and determining a second control response for the control surface based on the desired control and the second modal weight. The method may still further involve generating a control command for the control surface based on the first control response and the second control response.
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公开(公告)号：US10252798B2
公开(公告)日：2019-04-09
申请号：US15848705
申请日：2017-12-20
申请人： Val Petrov
发明人： Val Petrov
摘要： Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.
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公开(公告)号：US20190061909A1
公开(公告)日：2019-02-28
申请号：US16035317
申请日：2018-07-13
申请人： SUBARU CORPORATION
摘要： An aircraft wing load alleviation device is to be provided to an aircraft having a body, a main wing, and an elongated supporting member with an end fixed to the body and another end fixed to the main wing to support the main wing. The aircraft wing load alleviation device alleviates a load acting on the main wing, and includes a load detector, an actuator, and a controller. The load detector detects the load acting on the main wing. The actuator is provided to the supporting member and applies a load in a longitudinal direction of the supporting member. The controller controls, when the load acting on the main wing is detected, operation of the actuator to make the actuator apply the load to the supporting member in a direction opposite to a direction of a load applied on the supporting member as a result of the detected load.
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公开(公告)号：US20190047719A1
公开(公告)日：2019-02-14
申请号：US16042522
申请日：2018-07-23
摘要： An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust propulsor driven by the power source; and a wing extending from the fuselage, the vertical thrust propulsor positioned on or at least partially within the wing, the wing including a diffusion assembly, the diffusion assembly including at least one diffusion member fixed in position and located downstream of the vertical thrust propulsor for diffusing an airflow from the vertical thrust propulsor.
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公开(公告)号：US10131426B2
公开(公告)日：2018-11-20
申请号：US14915101
申请日：2014-08-29
发明人： Michael Judas , Friederike Stratenberg , Jan Van Toor , Werner Scholz , Berthold Karrais , Wolfgang Stangl
IPC分类号： B64C27/08 , B64C29/00 , B64C3/38 , B64C5/08 , B64C27/473 , B64C39/02 , B64C39/08 , B64D27/02 , B64D27/24
摘要： The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive.
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