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公开(公告)号：US11257387B2
公开(公告)日：2022-02-22
申请号：US16825687
申请日：2020-03-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Ondrej Karas , Jakub Cisar , Zdenek Padera , Jiri Gazarek
Abstract: Methods and systems for automatic sequencing of an ownship aircraft behind a lead aircraft on an approach to a runway. The method determines that the ownship aircraft is in an instrument approach. A pilot selection of the lead aircraft is confirmed as matching the lead aircraft identified in an air traffic control (ATC) command. The method includes calculating, an arrival time of the lead aircraft at the runway; processing the arrival time of the lead aircraft at the runway with a desired separation time to determine a target point for the ownship aircraft to merge onto a centerline of the runway; and automatically, and without further human input, generate lateral guidance, vertical guidance, and speed targets for the ownship aircraft to join the runway centerline at the target point at the desired separation time after the lead aircraft.
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公开(公告)号：US20240262512A1
公开(公告)日：2024-08-08
申请号：US18191579
申请日：2023-03-28
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Mohan Kanathu , Sivaprakash Pasupathi , Ondrej Karas
IPC: B64D15/20
CPC classification number: B64D15/20
Abstract: A system for detecting ice accretion on a rotor of an aircraft includes a processing system that is configured to: receive torque data indicative of actual torque supplied from an electric motor to the rotor; implement a model of the electric motor and the rotor that determines an estimated torque that should be supplied from the electric motor to the rotor; compute a load on the rotor from the actual torque and the estimated torque; compare the computed load to a predetermined magnitude; and when the computed load exceeds the predetermined magnitude, generate an alert that indicates ice is accreting on the rotor.
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公开(公告)号：US20240059409A1
公开(公告)日：2024-02-22
申请号：US17820302
申请日：2022-08-17
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Pedro Alexandre Tonet Fleig , Ondrej Karas
CPC classification number: B64C29/0008 , B64C27/26 , G05D1/102 , B64C39/024
Abstract: Aircraft and methods of operating the aircraft to provide for increased descent angles. The aircraft includes a fuselage having fixed wings, a horizontal thrust source coupled to the fuselage and configured to selectively generate and supply horizontal thrust to the aircraft, a vertical thrust source coupled to the fuselage and configured to selectively generate and supply vertical thrust to the aircraft, the vertical thrust source including a vertical thrust rotor that is configured to selectively operate in a locked mode, in which the vertical thrust rotor cannot rotate freely in response to contact of airflow therewith, and an unlocked mode, in which the vertical thrust rotor can rotate freely in response to contact of airflow therewith, and a controller configured to selectively supply a command to the vertical thrust source that causes the vertical thrust rotor to operate in the unlocked mode.
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Patent Agency Ranking
公开(公告)号：US20210295721A1
公开(公告)日：2021-09-23
申请号：US16825687
申请日：2020-03-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Ondrej Karas , Jakub Cisar , Zdenek Padera , Jiri Gazarek
Abstract: Methods and systems for automatic sequencing of an ownship aircraft behind a lead aircraft on an approach to a runway. The method determines that the ownship aircraft is in an instrument approach. A pilot selection of the lead aircraft is confirmed as matching the lead aircraft identified in an air traffic control (ATC) command. The method includes calculating, an arrival time of the lead aircraft at the runway; processing the arrival time of the lead aircraft at the runway with a desired separation time to determine a target point for the ownship aircraft to merge onto a centerline of the runway; and automatically, and without further human input, generate lateral guidance, vertical guidance, and speed targets for the ownship aircraft to join the runway centerline at the target point at the desired separation time after the lead aircraft.
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公开(公告)号：US20250121949A1
公开(公告)日：2025-04-17
申请号：US18487394
申请日：2023-10-16
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Ondrej Karas , Juraj Holaza
Abstract: Vehicle systems and methods are provided for assisting operation by providing indication of remaining control margin with respect to actuation of a user input device to adjust an inertial rate of a vehicle. An exemplary method involves identifying one or more effector limits for one or more effectors associated with an aircraft based at least in part on current aircraft state information and current actuation state information for the one or more effectors using a flight dynamics model associated with the aircraft, determining a range of potential effective input commands for a user input device associated with the one or more effectors to adjust one or more inertial rates of the aircraft based on the one or more effector limits, the current aircraft state information and the current actuation state information, and providing a user indication of the range of potential effective input commands.
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公开(公告)号：US12151808B2
公开(公告)日：2024-11-26
申请号：US17820302
申请日：2022-08-17
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Pedro Alexandre Tonet Fleig , Ondrej Karas
Abstract: Aircraft and methods of operating the aircraft to provide for increased descent angles. The aircraft includes a fuselage having fixed wings, a horizontal thrust source coupled to the fuselage and configured to selectively generate and supply horizontal thrust to the aircraft, a vertical thrust source coupled to the fuselage and configured to selectively generate and supply vertical thrust to the aircraft, the vertical thrust source including a vertical thrust rotor that is configured to selectively operate in a locked mode, in which the vertical thrust rotor cannot rotate freely in response to contact of airflow therewith, and an unlocked mode, in which the vertical thrust rotor can rotate freely in response to contact of airflow therewith, and a controller configured to selectively supply a command to the vertical thrust source that causes the vertical thrust rotor to operate in the unlocked mode.
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公开(公告)号：US11679865B2
公开(公告)日：2023-06-20
申请号：US17353482
申请日：2021-06-21
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Ondrej Karas
CPC classification number: B64C13/0423 , B64C9/00 , B64C13/18 , G05D1/101
Abstract: A system and method for detecting yoke interference for an aircraft having an auto pitch trim function is provided. The system includes a source of elevator load data, a source of aircraft speed data, and a processing system. The processing system is coupled to receive the elevator load data, the aircraft speed data, and initial condition center-of-gravity (CG) data that is representative of at least an estimated initial position of the CG of the aircraft. The processing system is configured to process at least the speed data and the initial condition CG data to: (i) determine an expected elevator load on the elevator flight control surface, (ii) determine if the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, and (iii) when the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, generate a disconnect signal that will disable the auto pitch trim function.
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公开(公告)号：US20220402596A1
公开(公告)日：2022-12-22
申请号：US17353482
申请日：2021-06-21
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Ondrej Karas
Abstract: A system and method for detecting yoke interference for an aircraft having an auto pitch trim function is provided. The system includes a source of elevator load data, a source of aircraft speed data, and a processing system. The processing system is coupled to receive the elevator load data, the aircraft speed data, and initial condition center-of-gravity (CG) data that is representative of at least an estimated initial position of the CG of the aircraft. The processing system is configured to process at least the speed data and the initial condition CG data to: (i) determine an expected elevator load on the elevator flight control surface, (ii) determine if the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, and (iii) when the expected elevator load exceeds the sensed elevator load by a predetermined magnitude, generate a disconnect signal that will disable the auto pitch trim function.
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