Honeywell International Inc.

Luis Melendez

John Koenig

Philip Sin

Ivan Sandy Wyatt

Jary Engels

Michael Mast

Zdenek Padera

Jan Frank

Systems and methods for an energy managed autoflight function that enables maneuvers previously done by the speed-on-elevator modes to be achieved while maintaining the autoflight function in speed-on-throttle mode. An autoflight guidance algorithm and strategy replaces speed-on-elevator modes with an automatic flight path angle (Auto-FPA) mode that can control speed-controlled climbs and descents. The autoflight guidance algorithm and strategy provide (i) autothrust and autoflight coordination during speed-on-throttle modes, (ii) and Auto-FPA control law or mode, (iii) the Auto-FPA control law being configurable for fixed thrust modes, and (iv) a speed protection monitoring scheme.

Systems and methods for energy managed autoflight guidance using potential flight path angle

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.

Methods and systems for automatic descent mode

Methods and systems are provided for autonomous vehicle operation for collision avoidance. One method involves identifying an autonomous operating mode and one or more settings associated with the autonomous operating mode prior to entering an autonomous collision avoidance mode in response to an output from a collision avoidance system, and after entering the autonomous collision avoidance mode, automatically restoring autonomous operation upon deactivation of the autonomous collision avoidance mode. For example, the autonomous operating mode may be automatically reinitiated based on the current vehicle status using the one or more settings in response to deactivation of the autonomous collision avoidance mode when it is determined that the autonomous operating mode is viable based on a relationship between a current vehicle status and the one or more settings associated with the autonomous operating mode.

Automated collision avoidance methods and systems

Disclosed are methods, systems, and non-transitory computer-readable medium for supersonic flight entry/exit management. For instance, the method may include determining whether a transition between supersonic and subsonic flight is approaching; and in response to determining the transition between subsonic and supersonic flight is approaching, performing a supersonic flight entry/exit process. The supersonic flight entry/exit process may include: obtaining center of gravity (CG) information for the vehicle, drag information for the vehicle, and a planned trajectory of the vehicle (trajectory data); performing an analysis of the trajectory data to determine whether the planned trajectory is safe and consistent; based on a result of the analysis, adjusting the planned trajectory or confirming the planned trajectory of the vehicle; and based on the adjusted planned trajectory or the confirmed planned trajectory of the vehicle, generating actuator instructions to execute the adjusted planned trajectory or the confirmed planned trajectory.

Methods and systems for controlling supersonic flight entry/exit of a vehicle

Technologically improved vehicle control systems and methods are described. The provided vehicle control systems and methods embody an inner loop auto-throttle control for causing delta-throttle changes, i.e., servo changes, to achieve desired acceleration targets. The system generates an error on a potential flight path angle using a received thrust acceleration command. The error on the potential flight path angle is converted into an equivalent acceleration. A throttle rate command TLA_rateis generated by converting the equivalent acceleration into the throttle rate command TLA_rate.

Systems and methods for providing throttle guidance as a function of flight path acceleration

Technologically improved flight guidance systems and methods that generate thrust guidance related to a potential flight path angle are provided. The thrust guidance is provided as acceleration commands that may be communicated to the pilot in an intuitive manner, such as with an acceleration cue on a primary flight display (PFD) system. The provided acceleration cues are uniform across the flight envelope and present consistently for two basic thrust guidance modes.

Systems and methods for providing thrust guidance related to flight path angle

An aircraft flight control system and method are provided. The system provides a control module that receives inertial data, sensor data, and a target airspeed. The control module processes the received data with aircraft thrust and drag models to evaluate the aircraft energy state. Based on the aircraft energy state, the control module determines (i) a maximum predicted potential flight path 'max PPFP', defined by a maximum thrust at the target airspeed, and (ii) an idle predicted potential flight path, 'idle PPFP,' defined by an idle thrust at the target airspeed. The control module generates display commands for a display system to display (i) the flight path angle, (ii) the max PPFP and (iii) the idle PPFP. In addition, the control module generates and displays a predicted flight path speed indicator (PFPS) when the FPA is above the max PPFP or below the idle PPFP.

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Scottsdale, AZ, United States of America

Luis Melendez