公开(公告)号：US20210254997A1

公开(公告)日：2021-08-19

申请号：US16866257

申请日：2020-05-04

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Rajesh Chaubey ,  Akshay Sankeshwari ,  Sharanabasappa Advani ,  Bhalakrishnan Janardhanan ,  Roopa Niveditha Sundara Kulal ,  Ravish Udupa ,  Daniel E. Lewis

IPC: G01C23/00 ,  B64D43/02

Abstract: Methods and systems are provided for guiding or otherwise assisting energy management of an aircraft radar vectoring en route to a runway. A method involves determining a predicted lateral trajectory for the radar vectoring in accordance with interception criteria, wherein the lateral trajectory comprises a sequence of segments for satisfying the interception criteria from a current location of the aircraft and each navigational segment of the sequence is associated with an anticipated aircraft heading assignment. The method determines a reference vertical trajectory corresponding to the lateral trajectory, determines a target value for an energy state parameter of the aircraft at the current location on the lateral trajectory using the reference vertical trajectory, and provides indication of a recommended action to reduce a difference between a current value for the energy state parameter and the target value.

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

IPC: G08G5/02 ,  B64D45/08 ,  G08G5/00

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).

公开(公告)号：US20200273350A1

公开(公告)日：2020-08-27

申请号：US16286792

申请日：2019-02-27

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Monika Litvova ,  Zdenek Jancik ,  Dorothee De Villele ,  Rajesh Chaubey

IPC: G08G5/00 ,  B64D43/00

Abstract: An automatic diversion management system on-board an aircraft is provided. The diversion management system is configured to automatically detect a need for the aircraft to divert from a primary airport to a diversion airport; automatically initiate diversion planning to a suitable diversion airport responsive to detecting conditions that can cause a need for diversion; automatically create a diversion flight plan; automatically send a clearance request to air traffic control (ATC) for a first type of conditions causing a need for diversion and send a clearance request to ATC, responsive to flight crew action, for a second type of conditions causing a need for diversion; and automatically activate the diversion flight plan after receipt of ATC clearance for the first type of conditions causing a need for diversion and activate the diversion flight plan, responsive to flight crew action, for the second type of conditions causing a need for diversion.

公开(公告)号：US10600328B2

公开(公告)日：2020-03-24

申请号：US15791970

申请日：2017-10-24

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Dorothee De Villele ,  Sharanabasappa Advani ,  Rajesh Chaubey

IPC: G08G5/02 ,  G05D1/06 ,  B64D45/04 ,  G08G5/00 ,  G01C23/00

Abstract: An enhanced flight management system and flight management method directed to improved guidance in unstable approach scenarios. The method includes receiving and processing a published arrival procedure (PAP), a published glide path (PGP), landing parameters, and real-time aircraft sensor data to determine a an actual approach profile, and whether the aircraft is following the reference approach profile. Approach stabilization criterion are determined, including, (i) a wind corrected air mass flight path angle (WC FPA) at the IMC; (ii) a vertical speed at the wind corrected air mass flight path angle (VS IMC); (iii) a wind corrected air mass flight path (WC FPA) angle at the VMC; and (iv) a vertical speed at the wind corrected air mass flight path angle (VS VMC). The method also determines whether an IMC criterion profile and a VMC criterion profile stabilizes the actual approach.

公开(公告)号：US10528043B2

公开(公告)日：2020-01-07

申请号：US15658669

申请日：2017-07-25

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Brian O'Laughlin ,  Mike Jackson ,  Rajesh Chaubey

IPC: G05D1/00 ,  G08G5/00 ,  B64D37/00 ,  G01C23/00 ,  G06F3/0488

Abstract: A method for computing a required speed profile for an aircraft to meet a required time of arrival (RTA) for a waypoint of a current flight is provided. During flight, the method calculates a fuel-efficient speed profile for the aircraft to meet the RTA for the waypoint, by a processor of a computing device communicatively coupled to one or more avionics systems onboard the aircraft; activates the fuel-efficient speed profile to fly the aircraft to the waypoint, by the processor; determines a priority between fuel efficiency of the fuel-efficient speed profile and time reliability, by the processor; and when the priority is the time reliability, switches from the fuel-efficient speed profile to a guidance margin control strategy to fly the aircraft to the waypoint, wherein the guidance margin control strategy increases the time reliability by enabling the aircraft to satisfy constraints of the RTA.

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

IPC: G08G5/02 ,  B64D45/08 ,  G08G5/00

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).

公开(公告)号：US20190122569A1

公开(公告)日：2019-04-25

申请号：US15791970

申请日：2017-10-24

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Dorothee De Villele ,  Sharanabasappa Advani ,  Rajesh Chaubey

IPC: G08G5/02

CPC classification number: G08G5/02 ,  B64D45/04 ,  G01C23/00 ,  G05D1/0676 ,  G08G5/0021 ,  G08G5/0026 ,  G08G5/025

Abstract: An enhanced flight management system and flight management method directed to improved guidance in unstable approach scenarios is provided. The method includes receiving a published arrival procedure (PAP), a published glide path (PGP), landing parameters, and real-time aircraft sensor data. These inputs are processed to determine a reference approach profile and an actual approach profile, and whether the aircraft is following the reference approach profile. Approach stabilization criterion are determined, including, (i) a wind corrected air mass flight path angle (WC FPA) at the IMC; (ii) a vertical speed at the wind corrected air mass flight path angle (VS IMC); (iii) a wind corrected air mass flight path (WC FPA) angle at the VMC; and (iv) a vertical speed at the wind corrected air mass flight path angle (VS VMC). The approach stabilization criterion is used to determine, whether (a) an IMC criterion profile stabilizes the actual approach and whether (b) a VMC criterion profile stabilizes the actual approach. A display system is commanded to display the approach stabilization criterion; and, when conditions (a) and (b) occur concurrently, user selections responsive to the displayed approach stabilization criterion are processed to update the actual approach profile.

公开(公告)号：US20180273200A1

公开(公告)日：2018-09-27

申请号：US15469763

申请日：2017-03-27

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Dorothee De Villele ,  Rajesh Chaubey ,  Sharanabasappa Advani ,  Veeralla Sai V Yashodhar ,  Ranju Thomas Pulikot ,  Abhishek Gupta

IPC: B64D45/08 ,  G08G5/00 ,  B64C9/32

CPC classification number: B64D45/08 ,  B64C9/32 ,  G08G5/0021 ,  G08G5/0091 ,  G08G5/025

Abstract: Avionic display systems and methods are provided for generating avionic displays including instability prediction and avoidance symbology, such as dynamically-adjusted drag device deployment cues. In one embodiment, the avionic display system includes a controller and an avionic display device, which is coupled to the controller and on which an avionic display, such as a Vertical Situation Display (VSD), is generated. The controller is configured to: (i) project whether an unstable aircraft state will occur during an approach flown by an aircraft; (ii) when an unstable aircraft state is projected to occur, determine whether implementation of an optimized drag device deployment scheme can prevent the projected occurrence of the unstable aircraft state; and (iii) if determining that the implementation of the optimized drag device deployment scheme can prevent occurrence of the projected unstable aircraft state, generating symbology on the avionic display indicative of the optimized drag device deployment scheme.

公开(公告)号：US20160229554A1

公开(公告)日：2016-08-11

申请号：US14619849

申请日：2015-02-11

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Amit Nishikant Kawalkar ,  Rajesh Chaubey ,  Rajeev Mohan

IPC: B64D45/08 ,  G08G5/00 ,  G01C23/00

CPC classification number: G08G5/0056 ,  G01C23/00 ,  G01C23/005 ,  G08G5/00 ,  G08G5/0021 ,  G08G5/0039 ,  G08G5/025

Abstract: Cockpit display systems and methods for generating navigation displays including landing diversion symbology are provided. In one embodiment, the cockpit display system includes a cockpit monitor and a controller coupled to the cockpit monitor. The controller is configured to assess the current feasibility of landing at one or more diversion airports in a range of an aircraft on which the cockpit display system is deployed. The controller is further configured to assign each diversion airport to one of a plurality of predetermined landing feasibility categories, and generate a horizontal navigation display on the cockpit monitor including symbology representative of the feasibility category assigned to one or more of the diversion airports.

Abstract translation: 提供了用于产生导航显示器的驾驶舱显示系统和方法，包括着陆转向符号系统。 在一个实施例中，驾驶舱显示系统包括驾驶舱监视器和耦合到驾驶舱监视器的控制器。 控制器被配置为评估在部署驾驶舱显示系统的飞机的范围内的一个或多个转向机场降落的当前可行性。 控制器还被配置为将每个引水机构分配到多个预定着陆可行性类别中的一个，并且在驾驶舱监视器上生成水平导航显示器，其包括代表分配给一个或多个转向机场的可行性类别的符号系统。