United Technologies Corporation

Gregory P Wright

Nicholas D Lappos

Don L Adams

James J Howlett

Mark A Johnston

Lorren Stiles

Charles W Evans

David H Sweet

Robert W Rice

An integrated time/limit exceedance cue system including a plurality of dedicated subsystem sensors, a processing unit, and a graphics generating/processing unit that is operative to generate an event dependent, time varying visual cue indicative of the exceedance of an established normal operating limit of a specific aircraft subsystem and operation thereof in a time critical exceedance condition. The time varying visual cue provides a relative indication of the elapsed time of operation of the specific subsystem in the time critical exceedance condition. The time varying visual cue is a symbolic image in the form of an outline, having a predetermined length, that defines a void region. The void region is proportionately opaqued or 'filled in' in correspondence with the elapsed time of operation of the specific subsystem in the time critical exceedance condition. The outline of the visual cue may be shaped and/or have a spatial orientation that is cognitively connected to the particular subsystem and/or to a symbolic image or display representing the specific generated status data provided by the dedicated subsystem sensors for monitoring the operation of the particular subsystem. The cue system may provide a corrective action cue in conjunction with the time varying visual cue that provides information as to the appropriate recovery procedure to restore the particular subsystem to operation within its established normal operating range.

Integrated time/limit exceedance cue system

Primary logic (116-128) for engine failure detection in a multi-engine aircraft is based on thresholds for engine torque (Q), gas generator speed (NG), power turbine inner stage temperature (T5), power turbine speed (NF), throttle setting (PLA), and throttle manipulation (PLADOT).

Detection of engine failure in a multi-engine aircraft

A bias actuator, such as an extensible link, in the longitudinal cyclic pitch channel of a helicopter is provided with inputs as a function of airspeed multiplied inversely with collective pitch, and as a function of the rate of change of collective pitch stick position, so as to enforce positive angle of attack and speed stability and positive static pitch trim gradient and to decouple collective pitch from the longitudinal cyclic pitch channel at cruise airspeeds, the invention compensates, inter alia, adverse control effects of tail stabilizer surfaces at cruise speeds. A pair of indicators display bias commands and actual bias responses.

Speed and collective pitch bias of helicopter longitudinal cyclic pitch

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Ansonia, CT, United States of America

Gregory P Wright