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公开(公告)号：USRE49013E1
公开(公告)日：2022-04-05
申请号：US16930695
申请日：2020-07-16
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Rajesh Chaubey , Daniel Corbel , Marek Batelka , Pavel Ptacek
Abstract: Systems and methods, and non-transitory computer readable mediums directed to generating an adaptive glide slope angle and allowing a pilot to interact with the generated glide slope angle are provided. The systems and methods, and non-transitory computer readable mediums retrieve, from a navigation database (NDB), a designated approach procedure for the aircraft, and identify a designated glide slope angle (D_GSA) based thereon. The systems and methods, and non-transitory computer readable mediums receive sensed actual weather data and sensed aircraft status data and generate an adaptive glide slope angle A_GSA based thereon. The systems and methods, and non-transitory computer readable mediums allow modification of and modify, or prevent modification of, the designated approach procedure with the A_GSA based on the determination of whether or not the A_GSA is compatible with the designated approach procedure.
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公开(公告)号：US11113978B2
公开(公告)日：2021-09-07
申请号：US15265330
申请日：2016-09-14
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Erwan Paricaud , Daniel Corbel , Michal Polansky , Zdenek Jancik
Abstract: A system and method of displaying optimized aircraft energy level to a flight crew includes processing flight plan data, in a processor, to determine the optimized aircraft energy level along a descent profile of the aircraft from cruise altitude down to aircraft destination, and continuously processing aircraft data, in the processor, to continuously determine, in real-time, an actual aircraft energy level. The actual aircraft energy level of the aircraft is continuously compared, in the processor, to the optimized aircraft energy level. The processor is use to command a display device to render an image that indicates: (i) the optimized aircraft energy level, (ii) how the actual aircraft energy level differs from the optimized aircraft energy level, and (iii) how the actual aircraft energy level is trending relative to the optimized aircraft energy level.
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公开(公告)号：US10922985B2
公开(公告)日：2021-02-16
申请号：US15970225
申请日：2018-05-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Daniel Corbel , Rajesh Chaubey , Marek Batelka , Pavel Ptacek
Abstract: Systems and methods directed to evaluating and enabling enhanced glide slope angles are provided. The method includes, in a control module, identifying a designated glide slope angle (D_GSA) based on a designated approach procedure; receiving and processing sensor data and navigation data; and, generating an adaptive glide slope angle (A_GSA) and an associated final capture altitude (FCA) based thereon. The method includes determining whether (a) an altitude constraint applies at the FCA, and determining whether (b) a level segment exists at the FCA. When (a) and (b) are concurrent, the method enables modification of the designated approach procedure with the A_GSA; and, the method prevents modification of the designated approach procedure with the A_GSA when there is no concurrence of (a) and (b).
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Patent Agency Ranking
4.发明申请公开(公告)号：US20190340941A1
公开(公告)日：2019-11-07
申请号：US15970225
申请日：2018-05-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Daniel Corbel , Rajesh Chaubey , Marek Batelka , Pavel Ptacek
Abstract: Systems and methods directed to evaluating and enabling enhanced glide slope angles are provided. The method includes, in a control module, identifying a designated glide slope angle (D_GSA) based on a designated approach procedure; receiving and processing sensor data and navigation data; and, generating an adaptive glide slope angle (A_GSA) and an associated final capture altitude (FCA) based thereon. The method includes determining whether (a) an altitude constraint applies at the FCA, and determining whether (b) a level segment exists at the FCA. When (a) and (b) are concurrent, the method enables modification of the designated approach procedure with the A_GSA; and, the method prevents modification of the designated approach procedure with the A_GSA when there is no concurrence of (a) and (b).
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公开(公告)号：US11043131B2
公开(公告)日：2021-06-22
申请号：US16285367
申请日：2019-02-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Marek Batelka , Rajesh Chaubey , Jim Rumbo , Kiran Mancheiah Venkataramana , Daniel Corbel , Zdenek Moravek , Ivan Lacko , Zdenek Jancik
Abstract: Provided are enhanced flight guidance systems and methods for an aircraft. The method includes recognizing when the aircraft is in manual operation and an active flight path is different than the planned flight path. An interrupt is received and categorized as one of (i) obstacle, (ii) equipment/fuel, or (iii) pilot health monitor. A managed mode begins, including identifying a rejoining leg of the planned flight path at which to rejoin and a location on the rejoining leg at which to rejoin. A recapture path strategy is selected from (i) lateral, (ii) vertical, and (iii) mixed lateral and vertical. A recapture path to the location on the rejoining leg is computed. The computed recapture path includes speed targets and configuration requirements at dedicated points along the recapture path. Aircraft state data along the recapture path is predicted and guidance controls for the aircraft along the recapture path are generated.
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公开(公告)号：US20200273349A1
公开(公告)日：2020-08-27
申请号：US16285367
申请日：2019-02-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Marek Batelka , Rajesh Chaubey , Jim Rumbo , Kiran Mancheiah Venkataramana , Daniel Corbel , Zdenek Moravek , Ivan Lacko , Zdenek Jancik
Abstract: Provided are enhanced flight guidance systems and methods for an aircraft. The method includes recognizing when the aircraft is in manual operation and an active flight path is different than the planned flight path. An interrupt is received and categorized as one of (i) obstacle, (ii) equipment/fuel, or (iii) pilot health monitor. A managed mode begins, including identifying a rejoining leg of the planned flight path at which to rejoin and a location on the rejoining leg at which to rejoin. A recapture path strategy is selected from (i) lateral, (ii) vertical, and (iii) mixed lateral and vertical. A recapture path to the location on the rejoining leg is computed. The computed recapture path includes speed targets and configuration requirements at dedicated points along the recapture path. Aircraft state data along the recapture path is predicted and guidance controls for the aircraft along the recapture path are generated.
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公开(公告)号：US10026326B1
公开(公告)日：2018-07-17
申请号：US15641525
申请日：2017-07-05
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Rajesh Chaubey , Daniel Corbel , Marek Batelka , Pavel Ptacek
Abstract: Systems and methods directed to generating an adaptive glide slope angle and allowing a pilot to interact with the generated glide slope angle are provided. The systems and methods retrieve, from a navigation database (NDB), a designated approach procedure for the aircraft, and identify a designated glide slope angle (D_GSA) based thereon. The systems and methods receive sensed actual weather data and sensed aircraft status data and generate an adaptive glide slope angle A_GSA based thereon. The systems and methods allow modification of and modify, or prevent modification of, the designated approach procedure with the A_GSA based on the determination of whether or not the A_GSA is compatible with the designated approach procedure.
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公开(公告)号：US20180075761A1
公开(公告)日：2018-03-15
申请号：US15265330
申请日：2016-09-14
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Dorothee De Villele , Erwan Paricaud , Daniel Corbel , Michal Polansky , Zdenek Jancik
CPC classification number: G08G5/02 , B64D43/02 , B64D45/08 , G01C23/00 , G01C23/005 , G08G5/0021 , G08G5/025
Abstract: A system and method of displaying optimized aircraft energy level to a flight crew includes processing flight plan data, in a processor, to determine the optimized aircraft energy level along a descent profile of the aircraft from cruise altitude down to aircraft destination, and continuously processing aircraft data, in the processor, to continuously determine, in real-time, an actual aircraft energy level. The actual aircraft energy level of the aircraft is continuously compared, in the processor, to the optimized aircraft energy level. The processor is use to command a display device to render an image that indicates: (i) the optimized aircraft energy level, (ii) how the actual aircraft energy level differs from the optimized aircraft energy level, and (iii) how the actual aircraft energy level is trending relative to the optimized aircraft energy level.
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