초록 ▼

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°glideslope). T

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°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.

대표청구항 ▼

In an aircraft maneuver command electronic flight control system wherein a continuing pitch axis control signal is produced by a continuing steady input applied to a pilot-operated pitch axis control device, the improvement comprising: altimeter means for determining the height of the aircraft above

In an aircraft maneuver command electronic flight control system wherein a continuing pitch axis control signal is produced by a continuing steady input applied to a pilot-operated pitch axis control device, the improvement comprising: altimeter means for determining the height of the aircraft above the ground and producing a related altimeter signal; and command modification means responsively connected to said pilot-operated pitch axis control device and to said altimeter means for receiving said pitch axis control signal and said altimeter signal and producing an incremental flight path angle command above a reference value based on the continuing steady input applied to said pilot-operated pitch axis control device, when the aircraft descends below a predetermined height above the ground during a landing maneuver. A method of controlling, during the flare portion of a landing maneuver, the pitch axis movement of an aircraft controlled by an aircraft maneuver command electronic flight control system, said method comprising the steps of: determining the height of the aircraft above the ground during a landing maneuver; and controlling an incremental flight path angle command relative to a reference value in response to the deflection of a pilot-operated pitch axis control device when the aircraft descends below a predetermined altitude above the ground during a landing maneuver.