The Boeing Company

Scott L Pelton

Mithra M Sankrithi

Terry Lee Davis

Brian D Kelly

Methods and systems for transmitting power and digital communication are provided. The method includes communicatively coupling a broadband over power line interface unit to a power conductor of a temporary power cable, communicatively coupling the broadband over power line interface unit to a network access point, electrically coupling the power conductor to a vehicle power receptacle, and transmitting network data between the network and the vehicle, and powering the vehicle simultaneously through the power conductor.

Methods and systems for high speed data communication

This invention provides a flare control modification for pilot-in-the-loop aircraft maneuver command electronic flight control systems. During flare, pilot pitch control inputs are interpreted as incremental pitch attitude commands. The flare control modification allows conventional piloting technique (i.e., pitch controller pull-and-hold) to be used during flare, while retaining the benefits of maneuver command system masking effects of gusts, winds, wind shear, and variations in airplane weight, balance, and aerodynamic configuration.

Pitch attitude command flight control system for landing flare

A flight path angle symbol is positioned on an aircraft attitude display indicator as a function of either a measured flight path angle or a flight path angle commanded by the pilot. When the aircraft is operating within a selected airspeed, angle of attack, pitch attitude or load factor range, or the difference between measured flight path angle and commanded flight path angle is within a selected range, the symbol is positioned on the display as a function of commanded flight path angle. However when the aircraft is operating outside any of these ranges, the symbols is positioned on the display as a function of the measured flight path angle. To avoid a rapid jump in symbol position when transitioning between measured and commanded flight path angle displays, a phase lag filter is used to attenuate and lag the symbol positioning signal.

Apparatus and method for displaying aircraft flight path angle on an

This invention provides a flare control modification for pilot-in-the-loop aircraft maneuver command electronic flight control systems. During flare pilot pitch control inputs are interpreted as incremental flight path angle commands above a reference flight path angle (nominally a -3.degree. glideslope). The flare control modification allows conventional piloting technique (i.e., pitch controller pull-and-hold) to be used during flare, while retaining the benefits of the maneuver command system masking effects of gusts, winds, windshear, and variations in airplane weight, balance, and aerodynamic configuration.

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Renton, WA, United States of America

Scott L Pelton