Patent ID: 6652233
Filing Date: 2003-11-25
Classification: B64D,F02D,Y02T

Abstract:
A control system for a turbo-charged diesel aircraft engine comprising:a controllable pitch propeller connected to and driven by the turbo-charged diesel aircraft engine; governor means for controlling the rotational speed of the propeller to a set speed by adjusting the pitch of the propeller; speed setting means for changing the set speed of the governor means; throttle means for changing a set amount of fuel supplied to the engine; fuel supply means for supplying fuel to the engine by an amount determined in accordance with the set amount; control means for controlling the speed setting means and the throttle means so that the set speed and the set amount of fuel change simultaneously in accordance with the stroke of a single control lever, the control means comprising delay control means for restricting the rate of change in the set amount of fuel to smaller than a predetermined value when the set amount of fuel supplied to the engine is increased; and wherein the control means controls the throttle means according to the stroke of the control lever in such a manner that the set amount of fuel is always smaller than a maximum limit determined in accordance with the set speed of the propeller.