Patent ID: 6732521
Filing Date: 2004-05-11
Classification: B64C,B64D,F02C,F02D,F05D,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; a propeller governor 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 propeller governor; accelerator 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 accelerator means so that the set speed and the set amount of fuel change simultaneously in accordance with the stroke of a single control lever; wherein the control means controls the speed setting means and the accelerator means in such a manner that the set speed and the set amount of fuel maintain a predetermined fixed relationship in which the set amount of fuel always becomes smaller than a smoke limit value at the maximum design altitude of the aircraft and is determined by the set speed; and wherein the control means further comprises an altitude compensator that replaces the set amount of fuel determined by the fixed relationship with an altitude fuel limit determined by the present altitude of the aircraft when the set amount of fuel determined by the fixed relationship is larger than the altitude fuel limit.