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公开(公告)号：US12077281B2
公开(公告)日：2024-09-03
申请号：US17855572
申请日：2022-06-30
申请人： BETA AIR LLC
发明人： Herman Wiegman
摘要： A system for flight control for managing actuators for an electric aircraft is provided. The system includes a controller, wherein the controller is designed and configured to receive a sensor datum from at least a sensor, generate an actuator performance model as a function of the sensor datum, identify a defunct actuator of the electric aircraft as a function of the sensor datum and the actuator performance model, generate an actuator allocation command datum as a function of at least the actuator performance model and at least the identification of the defunct actuator, and perform a torque allocation as a function of the actuator allocation command datum.
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公开(公告)号：US20240278930A1
公开(公告)日：2024-08-22
申请号：US18574434
申请日：2022-06-27
发明人： Andreas FLEDDERMAN , Jan Arend VAN BRUGGEN , Christian KOHLÖFFEL , Tobias HARTMANN , Elko VAN BALEN
CPC分类号： B64D45/00 , B64C13/38 , B64F5/60 , B64D2045/0085
摘要： A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: blocking movement of the transmission device with a brake device, commanding the control surface drive device to apply a load on the blocked transmission device, and determining whether a load sensor output signal of the load sensor is within a predetermined range. Also, a flight control surface drive apparatus, a flight control system and an aircraft.
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公开(公告)号：US20240278905A1
公开(公告)日：2024-08-22
申请号：US18172569
申请日：2023-02-22
申请人： The Boeing Company
发明人： Samuel L. Block , Kevin R. Tsai
摘要： A linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. The rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. The rib frame of the flap mechanism defines a width with a first and second web. A linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. The linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. As a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.
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公开(公告)号：US20240035551A1
公开(公告)日：2024-02-01
申请号：US18351662
申请日：2023-07-13
申请人： Ratier-Figeac SAS
发明人： Etienne Pluchon
CPC分类号： F16H25/205 , F16H25/2204 , F16H25/2472 , B64C13/38
摘要： A screw actuator includes a primary ball nut, a secondary nut, and a ball screw. The primary ball nut and secondary nut are both in threaded engagement with the ball screw, in which the inner functional plays of the screw actuator are configured such that in normal operation the threads of the secondary nut are in contact with the ball screw threads.
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65.发明授权公开(公告)号：US11884380B2
公开(公告)日：2024-01-30
申请号：US17522734
申请日：2021-11-09
申请人： The Boeing Company
发明人： Ira Mitchell, III
摘要： Flight control surface actuation systems including skew detection systems and associated methods. A flight control surface actuation system includes a skew detection system configured to generate a skew detection signal that represents a skew condition of a flight control surface. In some examples, the skew detection system includes a skew lanyard and a detection mechanism assembly (DMA) configured to detect a lanyard displacement of the skew lanyard and to generate an analog lanyard displacement signal. In some examples, the skew detection system includes a hybrid sensing actuator that includes an actuator output and an actuator output position sensor directly coupled to the actuator output. Methods of utilizing a flight control surface actuation system include detecting a skew condition in the flight control surface utilizing DMAs and/or hybrid sensing actuators.
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公开(公告)号：US11866155B2
公开(公告)日：2024-01-09
申请号：US17615069
申请日：2020-09-14
发明人： Bernhard Schlipf , Norbert Geyer
摘要： An actuator arrangement for a fixed leading edge member of an aircraft wing. The fixed leading edge member has an inner cavity defined by the outer skin and ribs. The actuator arrangement comprises at least one geared rotary actuator which moves relative to the other parts along a circular arc section during extending and retracting of the high-lift device between a fully retracted position and a fully extended position. In the fully retracted position, the actuator is predominantly accommodated within the inner cavity and in the extended position the actuator is predominantly positioned outside the inner cavity, preferably protruding through a D-nose cut-out.
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公开(公告)号：US11845536B2
公开(公告)日：2023-12-19
申请号：US17385603
申请日：2021-07-26
申请人： THE BOEING COMPANY
摘要： Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.
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公开(公告)号：US20230382516A1
公开(公告)日：2023-11-30
申请号：US18325944
申请日：2023-05-30
发明人： Luc ANDREANI , Florian LORENZ
IPC分类号： B64C13/38
CPC分类号： B64C13/38
摘要： A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.
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公开(公告)号：US20230366454A1
公开(公告)日：2023-11-16
申请号：US18315167
申请日：2023-05-10
CPC分类号： F16H19/02 , F16H37/065 , F16D13/24 , F16D41/16 , B64C13/38
摘要： A drive system for an actuator comprises first and second motors, and first and second input shafts connected to be driven by the respective first and second motors. Each of the first and second input shafts comprises a first overrunning clutch configured to rotate with the input shaft in a first direction, and a second overrunning clutch configured to rotate with the input shaft in a second direction. A first drive gear is configured to be driven by either one of the first overrunning clutches, and a second drive gear is configured to be driven by either one of the second overrunning clutches, and an output clutch and an output shaft are arranged to be driven by the first drive gear in a first mode of operation of the drive system and be driven by the second drive gear in a second mode of operation of the drive system.
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公开(公告)号：US20230286642A1
公开(公告)日：2023-09-14
申请号：US17992601
申请日：2022-11-22
申请人： AeroVironment, Inc.
发明人： Pavel Belik , John Peter Zwaan
IPC分类号： B64C9/16 , B64F5/10 , B64C39/02 , B64C13/38 , B64C29/02 , B64D45/00 , B64C9/02 , B64C3/24 , B64C3/36 , B64F5/00
CPC分类号： B64C9/16 , B64F5/10 , B64C39/024 , B64C13/38 , B64C29/02 , B64D45/00 , B64C9/02 , B64C3/24 , B64C3/36 , B64F5/00 , B64U10/25
摘要： Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.
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