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公开(公告)号：US20240400197A1
公开(公告)日：2024-12-05
申请号：US18802403
申请日：2024-08-13
Applicant: Beta Air, LLC
Inventor： Herman Wiegman
Abstract: A system for automated flight correction in an electric aircraft includes an input control configured to generate a control datum, at least a sensor connected to the electric aircraft, wherein the at least a sensor is configured to detect a status datum, and a flight controller communicatively connected to the input control and the at least a sensor, wherein the flight controller is configured to determine a command datum as a function of the control datum and the status datum, wherein determining the command datum comprises comparing the control datum to a limitation set based on the status datum, and calculating a modified control datum based on a flight plan of the electric aircraft through a remote device.
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公开(公告)号：US12071223B2
公开(公告)日：2024-08-27
申请号：US18094043
申请日：2023-01-06
Applicant: BETA AIR, LLC
Inventor： Herman Wiegman
CPC classification number: B64C13/506 , B64C13/18 , B64C13/20 , B64C29/0025 , B64C39/024 , G05D1/0061 , G05D1/102 , B64C13/22
Abstract: A system for automated flight correction in an electric aircraft includes an input control configured to generate a control datum, at least a sensor connected to the electric aircraft, wherein the at least a sensor is configured to detect a status datum, and a flight controller communicatively connected to the input control and the at least a sensor, wherein the flight controller is configured to determine a command datum as a function of the control datum and the status datum, wherein determining the command datum comprises comparing the control datum to a limitation set based on the status datum, and calculating a modified control datum based on a flight plan of the electric aircraft through a remote device.
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公开(公告)号：US11530028B1
公开(公告)日：2022-12-20
申请号：US17406978
申请日：2021-08-19
Applicant: BETA AIR, LLC
Inventor： Herman Wiegman
Abstract: A system for autonomous flight of an electric vertical takeoff and landing (eVTOL) aircraft. The system may include a fuselage, a plurality of laterally extending elements, a plurality of propulsors, a flight controller, and a pilot override switch. The plurality of laterally extending elements are attached to the fuselage. The plurality of propulsors is attached to the plurality of laterally extending elements. The flight controller is communicatively connected to the pilot override switch. The flight controller is configured to identify a flight transition point, initiate rotation about an axis of the fuselage a as function of the flight transition point, and terminate rotation once the desired flight angle is reached.
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公开(公告)号：US20220073188A1
公开(公告)日：2022-03-10
申请号：US17416346
申请日：2019-12-19
Applicant: SAFRAN ELECTRONICS & DEFENSE
Inventor： Alexandre GUYAMIER , Julien FARJON , Nicolas CADALEN
Abstract: A piloting device arranged to be integrated in a pre-existing aircraft that includes original systems comprising both a flight control system and an autopilot system is distinct from and autonomous relative to the original systems and includes a positioning unit and a control unit. The positioning unit is arranged to produce positioning data for the pre-existing aircraft. The control unit is arranged to perform a geofencing function from the positioning data produced by the positioning unit and to produce an alternative piloting setpoint for the pre-existing aircraft. The alternative piloting setpoint is adapted to supplement both a manual piloting setpoint produced by a pilot of the pre-existing aircraft via the flight control system and also an autopilot setpoint produced by the autopilot system.
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公开(公告)号：US10926866B2
公开(公告)日：2021-02-23
申请号：US15616005
申请日：2017-06-07
Applicant: Ratier-Figeac SAS
Inventor： Pierre-Jacques Labry , Benoit Mazars
IPC: H01H9/00 , B64C13/22 , B64C13/04 , G05G5/04 , H01H50/20 , H01H50/44 , B64C13/16 , B64D31/04 , B64D31/06
Abstract: A positioning and position maintaining device comprises a solenoid having an armature and an electromagnetic holder. The solenoid is arranged to effect positioning of an object upon translation of the armature and the electromagnetic holder is arranged to effect position maintaining in order to maintain the object in the position effected by the solenoid. An apparatus for aircraft autopilot and manual control feel-force control switching comprises an autopilot mechanism and the positioning and position maintaining device. The positioning and position maintaining device is arranged to engage the autopilot mechanism and maintain the engagement thereof. A method of switching between autopilot and manual control in an aircraft is also envisaged.
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Patent Agency Ranking
公开(公告)号：US20200331587A1
公开(公告)日：2020-10-22
申请号：US16851766
申请日：2020-04-17
Applicant: Airbus Operations Limited
Inventor： Paul Gordon L'ALLIER
Abstract: A retractable landing gear on an aircraft is operated by a landing gear control system 20 having a manually operable lever 26 movable from a first, e.g. gear-down, position to a second, e.g. gear-up position, in response to which a signal (e.g. a gear-up command) is outputted causing the landing gear to move to an up position. The landing gear control system 20 also includes a motor 40 configured to move the lever 26 in dependence on a signal, for example a signal received by a landing gear lever control unit 42 from a take-off detection system 46 which indicates that the aircraft has taken-off. Thus, the lever 26 may be considered as being configured both to be operated by a pilot of the aircraft manually and to be operated by the motor automatically.
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公开(公告)号：US10589845B2
公开(公告)日：2020-03-17
申请号：US15520788
申请日：2015-10-14
Applicant: Tzafrir Sheffer , Yarden Sheffer
Inventor： Tzafrir Sheffer , Yarden Sheffer
Abstract: A device for releasably mounting an autopilot control circuit to a flight control component of an aircraft, includes a frame that holds a component of an autopilot control circuit; a first coupler releasably fastened to the frame and operable to releasably mount the frame to the airframe of an aircraft; and a second coupler releasably fastened to the frame and operable to releasably mount the frame to a flight control component of the aircraft. When the device is releasably mounted in an aircraft's cabin and the autopilot control circuit is engaged, the autopilot control circuit controls an aspect of the aircraft's flight by moving the second coupler relative to the first coupler. With the device one can releasably mount an autopilot control circuit to an aircraft that does not have one and use the autopilot control circuit and device to control one or more aspects of the aircraft's flight.
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公开(公告)号：US20170240268A1
公开(公告)日：2017-08-24
申请号：US15591110
申请日：2017-05-10
Applicant: Merlin Technology, Inc.
Inventor： Carlos E. Golborne , Ray E. Debs , Mark Marvin , John E. Mercer
CPC classification number: B64C13/22 , B64C13/04 , B64C13/18 , B64C27/04 , B64C27/56 , B64C27/57 , B64D43/00 , G01C23/00 , G01C23/005 , G05G9/047 , G05G2009/04774
Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.
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公开(公告)号：US09665097B2
公开(公告)日：2017-05-30
申请号：US14896983
申请日：2014-06-11
Applicant: Bombardier Inc.
Inventor： Antoine Letang , Florian Chedaleux , Vincent Poudou , Lawrence Oberfeld , Eric Palmer
CPC classification number: G05D1/0061 , B64C13/12 , B64C13/22 , B64C13/503
Abstract: A flight control system for an aircraft includes at least one flight control computer that carries out a ground lift dump function that selectively extends a spoiler located on a wing of the aircraft into an airflow passing over the wing. The at least one flight control computer includes arming logic that is responsive to an input signal indicative of an aircraft parameter to automatically arm the ground lift dump function during certain phases of operation of the aircraft. The at least one flight control computer includes spoiler deployment logic that is responsive to an arming signal from the aiming logic which indicates that the ground lift function is armed to deploy the spoiler into its extended position within the airflow passing over the wing of the aircraft to assist in stopping the aircraft while the aircraft is on the ground.
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公开(公告)号：US09604718B2
公开(公告)日：2017-03-28
申请号：US14740023
申请日：2015-06-15
Applicant: THALES
Inventor： Sylvain Lissajoux , Eric Guillouet , Thibaut Debard
CPC classification number: B64C13/22 , B64C13/04 , B64C13/18 , B64D31/00 , B64D31/04 , B64D31/06 , G05D1/0061
Abstract: A method and device for generating at least one set point from a flight control set point, a motor control set point and an aircraft guidance set point, a related computer program product and an aircraft are disclosed. In one aspect, the method includes acquiring a mechanical property relative to at least one corresponding primary control member and computing at least one set point from among one or more primary set points and one or more secondary set points. The method also includes generating at least one of the computed set point(s) and switching, based on the mechanical property acquired for the corresponding primary control member, between a first mode in which one or more primary set points are generated and a second mode in which one or more secondary set points are generated.
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