Patent ID: 6352223
Filing Date: 2002-03-05
Classification: B64C,G05D

Abstract:
A system for yaw control of an aircraft fitted with a plurality of engines, said system comprising:at least one control facility, for the yaw control, capable of being actuated by a pilot of the aircraft; first means delivering electrical signals representative respectively of the controlled roll attitude &PHgr;c, of the roll rate p, of the effective roll attitude &PHgr;, of the yaw rate and r and of the sideslip &bgr; of said aircraft; a computation unit formulating an electrical command dr for yaw control, on the basis of the relation: dr=Ka.&PHgr;c+Kb.p+Kc.&PHgr;+Kd.r+Ke.&bgr;â€ƒin which: &PHgr;c, p, &PHgr;, r and &bgr; are the values delivered by said first means, and Ka, Kb, Kc, Kd, and Ke are gains, the values of which are capable of being fixed by second means at nominal values; and a transmission device making it possible to combine said electrical command dr for yaw control and a mechanical command which originates directly from the control facility by way of a mechanical transmission and which is representative of the position of said control facility, so as to deliver a single combined command for yaw control which is intended to control a rudder of the aircraft, which moreover comprises third means for detecting any fault with one of said engines of the aircraft, and wherein said second means are formed in such a way as to increase the value of the gain Kd relating to the yaw rate r and to modify the values of the gains Ka and Ke relating respectively to the controlled rolled attitude &PHgr;c and to the sideslip &bgr;, upon the detection by said third means of a fault with one of said engines of the aircraft.