Rockwell Collins, Inc.

Collin D Ogden

Michael James Krenz

Ellen L McGaughy

Bradley R Mickelson

Kirk A Kolek

David M Eckert

Ryan C Palmer

Jesse J Bliss

A system and method are provided for continuously monitoring manual flight inputs and updating a flight management system with those manual inputs. The flight management system recalculates and provides predictions based on the manual inputs. The flight management system may continuously monitor certain thresholds. The flight management system utilizes the crew entered speed schedule until a threshold is exceeded. When the flight management system is reengaged, it may utilize the manually entered speeds within the speed schedule for a current phase of the flight. The flight management system may analyze the manual input and corresponding predictions to determine if they are within or conform to certain predefined criteria before using them for automated flight.

Speed schedule tracking

A system and method are provided for selecting features from a digital chart, and entering corresponding flight plan amendments into a flight plan by direct transfer to an FMS. Based on the selection, the system may prompt the user for subsequent selections. Digital charts are generated in dynamically or in real-time according to a set of databases, including the databased used by the FMS. Elements within the databases are characterized so that the flight crew can select which elements are displayed. Features in the digital chart may be made selectable or unselectable based on a filtering process. The filtering process may be based on environmental variables, aircraft capabilities, safety tolerances, etc.

Flight planning through data driven charting

A system for assisting an aircraft in an emergency landing includes a processor with a non-transitory processor-readable medium storing processor-executable code. The processor-executable code causes the processor to detect an all engine failure of an aircraft. In response to the detected all engine failure, the processor-executable code further causes the processor to determine at least one of an aerodynamic and environmental attribute associated with the aircraft and a descent rate of the aircraft based on the at least one aerodynamic and environmental attribute, calculate a maximum distance the aircraft can travel without engine power based on at least one of the attribute and descent rate; calculate a range for the aircraft based on the maximum distance; and generate a display of the range and provide the display to a display system of the aircraft.

Visualization of glide distance for increased situational awareness

Present novel and non-trivial system, device, and method for generating an aircraft energy indicator(s) is disclosed. The energy indicator generating system is comprised of one or more sources of aircraft performance factors data, an image generator (IG), and a presentation system. The IG may be configured to receive the aircraft performance factors data representative of at least aircraft altitude and speed; determine descent path data as a function of at least the aircraft performance data; determine target aircraft energy data as a function of at least the descent path data; determine actual energy data as a function of at least the aircraft performance data; and generate presentation data as a function of the target energy data and the actual energy data, where the presentation data is representative of one or more images of an aircraft energy indicator presentable to a viewer.

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North Liberty, IA, United States of America

Collin D Ogden