|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 9 인용 특허 : 11|
The present invention relates to a system for the yaw control of an aircraft fitted with a plurality of engines, the system (SC) comprising in particular a computation unit (16) formulating a command dr for yaw control, dr=Ka..PHI.c+Kb.p+Kc..PHI.+Kd.r+Ke..beta., on the basis of the controlled roll attitude .PHI.c, of the roll rate p, of the effective roll attitude .PHI., of the yaw rate r, of the sideslip .beta. and of gains Ka, Kb, Kc, Kd and Ke which are fixed by a device (28). According to the invention, the system (SC) comprises a a device (30) for d...
1. 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 .PHI.c, of the roll rate p, of the effective roll attitude .PHI., of the yaw rate and r and of the sideslip .beta. of said aircraft; a computation unit formulating an electrical command dr for yaw control, on the basis of the relation: dr=Ka..PHI.c+K...