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公开(公告)号：US10065735B2
公开(公告)日：2018-09-04
申请号：US15840979
申请日：2017-12-13
申请人： The Boeing Company
发明人： Steven D. Richardson
CPC分类号： B64C27/82 , B64C3/385 , B64C15/02 , B64C15/14 , B64C27/18 , B64C27/24 , B64C27/26 , Y02T50/14
摘要： A method of operating an aircraft having a rotor/wing assembly and a nozzle comprises vectoring the nozzle into a position for creating vertical thrust, and using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation.
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公开(公告)号：US20180170536A1
公开(公告)日：2018-06-21
申请号：US15840979
申请日：2017-12-13
申请人： The Boeing Company
发明人： Steven D. Richardson
CPC分类号： B64C27/82 , B64C3/385 , B64C15/02 , B64C15/14 , B64C27/18 , B64C27/24 , B64C27/26 , Y02T50/14
摘要： A method of operating an aircraft having a rotor/wing assembly and a nozzle comprises vectoring the nozzle into a position for creating vertical thrust, and using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation.
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公开(公告)号：US09932107B2
公开(公告)日：2018-04-03
申请号：US15007172
申请日：2016-01-26
申请人： The Boeing Company
发明人： Mark S. Good , Steven Paul Walker
IPC分类号： B64C3/56
摘要： Disclosed is a method of enhancing aerodynamic performance of an aircraft wing assembly including a fixed section and a foldable section. The foldable section is hinged to the fixed section at a hinge axis. The method includes turning a torque box extending from the foldable section to rotate the foldable section about the hinge axis from a stowed position to a deployed position.
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公开(公告)号：US20180065737A1
公开(公告)日：2018-03-08
申请号：US15811510
申请日：2017-11-13
发明人： Ilan Kroo
摘要： A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.
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公开(公告)号：US09908611B2
公开(公告)日：2018-03-06
申请号：US14905102
申请日：2014-07-10
发明人： Horst Haslach
摘要： This relates to changes in wing profiles. In order to provide an aerodynamic structure that can be variably adjusted and changed with respect to the wing profile, it is provided that an aerodynamic structure for a wing or rudder arrangement of an aircraft comprises a support structure and an outer skin. The support structure comprises an adaptive surface support structure in a longitudinal direction, which extends in a longitudinal direction from a root area to an outer end area, and is formed by a support surface, which comprises an adjustable periodic profiling that runs in the transverse direction, in which first flange areas and second flange areas are alternatingly formed, and joined together by web areas running in the direction of a profile height. Alternatingly aligned open profile segments running in the longitudinal direction are here formed.
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公开(公告)号：US09889920B2
公开(公告)日：2018-02-13
申请号：US15045318
申请日：2016-02-17
发明人： Matthew Harding , Stefan Napier , Nicola Marongiu , Robert Ian Thompson , Nick Livings , Stephen Paul Briancourt , Sylvain Boye
CPC分类号： B64C3/56 , B64C23/072 , Y02T50/14 , Y02T50/164
摘要： An aircraft wing comprises a fixed wing and a wing tip device at the tip thereof. The wing tip device is configurable between: a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce the span. The wing comprises an actuation assembly for moving the wing tip device. The actuation assembly is arranged to move the wing tip device in a two-stage movement comprising a first stage in which the wing tip device is translated away from the flight configuration in a linear movement only, and a second, subsequent stage, in which the wing tip device is rotated to the ground configuration.
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公开(公告)号：US20170369151A1
公开(公告)日：2017-12-28
申请号：US15629013
申请日：2017-06-21
摘要： A method of configuring a wing tip device (7) on an aircraft (1), including: undertaking ground-based operations at an airport with the wing tip device (7) in a ground configuration, in which the span of the aircraft is within an airport compatibility limit, moving the wing tip device (7) to a take-off configuration in which the wing tip device (7) is moved away from the ground configuration such that the span of the aircraft is increased and such that the wing tip device (7) has a first lift coefficient; taking-off with the wing tip device (7) in the take-off configuration; moving the wing tip device from the take-off configuration to a flight configuration, in which the wing tip device has a second lift coefficient, the second lift coefficient being lower than the first lift coefficient. The lift coefficient may be changed by adjusting the sweep of the wing tip device (7).
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公开(公告)号：US20170355443A1
公开(公告)日：2017-12-14
申请号：US15619126
申请日：2017-06-09
IPC分类号： B64C3/56
摘要： A latching device for a wing including a support structure (29), a latching bolt (35) having a longitudinal axis (36) and being slidably supported by the support structure (29) such that the latching bolt (35) is movable between a retracted position and an extended position. The latching device (27) includes a first hydraulic actuator (47a) and a first connector assembly (38a) adapted to be connected to a first hydraulic system of an aircraft (1), and at least one second hydraulic actuator (47b) and a second connector assembly (38b) connected to a second hydraulic system. The first hydraulic actuator (47a) and the second hydraulic actuator (47b) are adapted to effect movement of the latching bolt (35) from the extended position into the retracted position independent of the other one of the at least one first hydraulic actuator (47a) and the at least one second hydraulic actuator (47b).
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公开(公告)号：US09821909B2
公开(公告)日：2017-11-21
申请号：US15091456
申请日：2016-04-05
发明人： Jonathan Moshe
CPC分类号： B64C29/02 , B64C3/38 , B64C27/22 , B64C29/0033 , Y02T50/14
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：US09815345B2
公开(公告)日：2017-11-14
申请号：US15378121
申请日：2016-12-14
申请人： AeroMobil, S.R.O.
发明人： Stefan Klein
CPC分类号： B60F5/02 , B60F5/003 , B64C3/385 , B64C3/54 , B64C3/56 , B64C25/04 , B64C25/54 , B64C37/00 , B64C2025/003 , Y02T50/14
摘要： Transformation method of hybrid transportation vehicle for ground and air includes the following transformation and reciprocal steps: Tilting the compensation cover (7) on. Expansion of both whole wings (1) from the transportation vehicle longitudinal position around two vertical axes (2) into the flying position. Expansion of rear parts of wings (1) from the top front parts of wings (1) into the spread flying position by tilting the rear of each wing (1) around a horizontal axis (3). The take-off and landing tilting of wings (1) by an angle of attack alpha=0 to 40° of the wings onset. Front wheels track (5) is reduced by axially shifting the front wheels (5) towards the fuselage. Furthermore, a corresponding hybrid transportation vehicle for ground and air is described which contains reciprocal transformation mechanisms for transformation from a sterling double or four-track automobile into a sterling aircraft for take-off and landing on the ground or water, and vice versa.
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