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公开(公告)号：US12129028B2
公开(公告)日：2024-10-29
申请号：US17742663
申请日：2022-05-12
发明人： Kai Backhaus , Jürgen Arnold , Holger Hennings , Lorenz Tichy
CPC分类号： B64C9/26 , B64C13/16 , B64C30/00 , B64D2045/0085
摘要： In a method of expanding a flight envelope of an aircraft comprising a pair of wing halves and extendable leading-edge flaps at leading wing edges of the wing halves towards higher transonic flight Mach numbers, at least one of the leading-edge flaps at one of the two wing halves is extended in flight direction, when approaching the flight envelope with increasing flight Mach number of the aircraft.
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公开(公告)号：US12116139B2
公开(公告)日：2024-10-15
申请号：US17885463
申请日：2022-08-10
申请人： REGENT Craft Inc.
CPC分类号： B64D27/357 , B64C3/16 , B64C13/16 , B63B1/24 , B63B79/00 , B64C35/007
摘要： A craft includes a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.
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公开(公告)号：US20240300662A1
公开(公告)日：2024-09-12
申请号：US18180381
申请日：2023-03-08
CPC分类号： B64D31/18 , B64D35/025 , H02P9/008 , B64C13/16
摘要： A hybrid gas turbine engine for use on an aircraft includes a motor/generator and gas turbine engine placed in parallel power communication with a rotating bladed component, such as an aircraft propeller, through a combining gear box. Power can be modulated with the propeller using the motor/generator. An aircraft having the aircraft propeller can also include several aircraft systems such as an air data computer, automatic flight control system (AFCS), a guidance and navigation system, a full authority digital engine controller/flight control computer (FADEC/FCC), and a fault detection and mitigation controller (FDMC). Data from each of these respective systems can be communicated over an aircraft data bus. In one form data from the AFCS and guidance and navigation system can be provided over the aircraft bus to the FDMC to modulate power to the propeller and in some forms act as a backup to the FADEC/FCC.
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公开(公告)号：US12032389B2
公开(公告)日：2024-07-09
申请号：US18182094
申请日：2023-03-10
发明人： Luis Melendez
CPC分类号： G05D1/0688 , B64C13/16 , G05D1/106 , G08G5/0021 , G08G5/0039
摘要： Disclosed are methods, systems, and non-transitory computer-readable medium for controlling an automatic descent of a vehicle. For instance, the method may include: determining whether a descent trigger condition is present; and in response to determining the descent trigger condition is present, performing an automatic descent process. The automatic descent process may include: obtaining clearance data from an on-board system of the vehicle; generating a descent plan based on the clearance data, the descent plan including a supersonic-to-subsonic transition and/or a supersonic-descent to a target altitude; and generating actuator instructions to a control the vehicle to descend to the target altitude based on the descent plan.
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公开(公告)号：US20240134387A1
公开(公告)日：2024-04-25
申请号：US18535604
申请日：2023-12-11
发明人： Jong-Yeob Shin , Gi-Yun Chung , Lakmal Kaviratna
摘要： Flight control systems, flight control laws, and aircraft are provided. An flight control system includes an input configured to receive a pitch rate command, a processor operative to receive the pitch angle command, to calculate a pitch angle saturation limit, to compare the sum of the pitch rate command, the scaled pitch rate, and the scaled pitch angle to the pitch angle saturation limit, to convert the pitch rate command system to the pitch angle command system in response to the sum exceeding the pitch angle saturation limit value to limit the pilot pitch-up pitch rate command, and to couple the pitch rate command to an aircraft control surface for the failure case of one of control surface, and the aircraft control surface configured to adjust an aircraft control surface setting in response to the pitch rate command and/or pitch angle command to protect an aircraft from being in stall condition.
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公开(公告)号：US20240124160A1
公开(公告)日：2024-04-18
申请号：US17966786
申请日：2022-10-15
申请人： BETA AIR, LLC
发明人： Chris Woodall , Timothy Gerard Richter , Mike Shaw
摘要： Disclosed herein is a system and method for effector reboot on an electric aircraft during flight. An effector controller may perform a power on built-in test on boot. An effector controller may selective perform an additional built-in test (ABIT) on boot based on instructions from a flight controller. The flight controller may use flags to indicate the necessity of an ABIT on boot. The effector controller may not perform an ABIT during flight. A backup controller may be used to send standard commands to an effector controller but may not sent an ABIT command.
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公开(公告)号：US11846953B2
公开(公告)日：2023-12-19
申请号：US18114828
申请日：2023-02-27
申请人： Electra Aero, Inc.
CPC分类号： G05D1/0825 , B64C13/16 , B64D31/10
摘要： An aircraft may include a tail having a rudder and a pair of wings. The pair of wings may include at least one flap and at least one roll control device. The aircraft may also include at least two thrust-producing devices. The aircraft may also include a differential thrust control system including a computing device having at least one processor. The at least one processer may be configured to control an attitude of the aircraft by selectively operating the at least two thrust-producing devices, the rudder, and the at least one roll control device based at least in part on a plurality of conditions provided by a plurality of sensors on the aircraft and a selected mode setting of a mode control panel. The computing device may be communicatively coupled to the at least two thrust-producing devices, the rudder, and the at least one roll control device.
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8.发明授权公开(公告)号：US11733715B2
公开(公告)日：2023-08-22
申请号：US17066183
申请日：2020-10-08
发明人： Xichen Shi , Patrick Spieler , Ellande Tang , Elena S. Lupu , Soon-Jo Chung
摘要： A fixed-wing vertical take-off and landing (VTOL) vehicle configured with a composite adaptive nonlinear tracking controller that utilizes a real-time accurate estimation of the complex aerodynamic forces surrounding the wing(s) and rotors in order to achieve a high performance flight. The method employs online adaptation of force models, and generates accurate estimation for wing and rotor forces in real-time based on information from a three-dimensional airflow sensor. The novel three-dimensional airflow sensor illustrates improved velocity tracking and force prediction during the transition stage from hover to forward flight.
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公开(公告)号：US11724797B2
公开(公告)日：2023-08-15
申请号：US17365655
申请日：2021-07-01
申请人： BETA AIR, LLC
CPC分类号： B64C13/505 , B64C13/042 , B64C13/16 , B64C13/503 , B64C13/506 , B64D27/24 , B64C29/0025
摘要： A system of fall back flight control configured for use in electric aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the electric aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.
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公开(公告)号：US11685516B2
公开(公告)日：2023-06-27
申请号：US17395747
申请日：2021-08-06
摘要： A passive gust load alleviation device for an aerodynamic panel includes a free-floating aerodynamic control surface connected to the panel via a revolute joint. A counterweight is connected to the control surface. Relative to a direction of ambient airflow, the counterweight has a center of gravity forward of the axis of rotation. The counterweight is configured to passively deflect the control surface about the axis to alleviate a gust load. A vehicle includes an aerodynamic panel connected to a body and extending into ambient airflow, and the control surface and counterweight. A method for alleviating the gust load on an aircraft panel includes connecting the control panel, via the revolute joint, along a trailing edge of the panel, and during a flight of an aircraft having the panel, passively deflecting the control panel about the axis in response to an incident wind gust.
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