Nicholas D. Lappos

TL;DR: In this article, a fuel control for an aircraft engine employs super contingency logic (76) in response to low rotor speed of a helicopter engine failure or entry into an avoid region of a flight regime following engine failure.

TL;DR: In this paper, the power required for a helicopter to hover is generated as the ratio of current operating power in forward flight to power required to hover for the aircraft, and the viability of the indication is indicated by a "ready" indication.

TL;DR: An integrated time/limit exceedance cue system including a plurality of dedicated subsystem sensors, a processing unit, and a graphics generating/processing unit 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.

TL;DR: In this paper, the authors compared the free turbine speed of a helicopter engine with that of a fixed-wing single-rotor with the speed of the helicopter rotor and found that the deceleration of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is used to increase fuel flow.

TL;DR: In this article, a helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108), and the reference speed is faded up at a rather rapid rate to 107% of rated speed (114).