Rockwell Collins, Inc.

Bradley R Mickelson

Dinesh Kumar Kushwaha

Mark Wayne Volner

Douglas A Bell

Collin D Ogden

Thomas M Scanlon

Kirk A Kolek

Stephen W Howard

Stephen M Kleckner

Jason M Vanderhorn

A system and method for computing and displaying a fuel optimal idle deceleration start point which minimizes the overall auto throttle movement keeping the throttle at idle detent throughout the maneuver thus minimizing the fuel burn and stress on engine. The need for speed brakes deployment is also reduced because the deceleration distance length is accordingly adjusted based on current parameters. The accurate solution takes into account the current condition such as aircraft weight, altitude and speed and environmental parameters such as wind and temperature. The computed deceleration start point is displayed on map/navigation and vertical display for enhanced flight crew awareness.

Optimum idle descent start point display based on current conditions

A system includes a processing circuit onboard an aircraft and configured to determine an optimum cruise profile for the aircraft based on a flight plan, a characteristic of the aircraft, and an environmental characteristic. The processing circuit is also configured to determine an optimized cruise vertical path based on the optimum cruise profile and air traffic information of at least one other aircraft, and control an autopilot system of the aircraft to cause the aircraft to follow the optimized cruise vertical path.

Systems and methods for optimized cruise vertical path

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.

Aircraft energy indicator generating system, device, and method

Present novel and non-trivial systems and methods for validating single-channel tactical flight data in a multi-channel architecture are disclosed. Three single-channel monitors are disclosed along with a fourth, external monitor that is accessible to the multiple channels. A system could be comprised of a navigation data source, two or more communications channels, and an external display unit ('DU'), where each channel may be comprised of a flight management system ('FMS'), a DU, and a flight director (&#x201c;FD&#x201d;) system. In addition to the FMS performing two standard functions of calculating a lateral deviation (&#x201c;LDEV&#x201d;) and a roll command (&#x201c;Roll Cmd&#x201d;), a second LDEV/Roll Command calculator and a Roll Command Calculator are employed in DU and FD of same channel, respectively, to determine data validity. In addition, the FD and the symbologies of LDEV and Roll Cmd generated by the DU are also employed in the determination of data validity.

Growing community of inventors

Cedar Rapids, IA, United States of America

Bradley R Mickelson