초록 ▼

An automatic flight control apparatus for a rotary wing aircraft for controlling the flight condition by utilizing a signal representing the air speed of the aircraft which is added to a bias signal corresponding to the attitude of the aircraft in hovering condition, which added signal is used as a

An automatic flight control apparatus for a rotary wing aircraft for controlling the flight condition by utilizing a signal representing the air speed of the aircraft which is added to a bias signal corresponding to the attitude of the aircraft in hovering condition, which added signal is used as a “trim value”signal representing the attitude of the aircraft in a balanced relation to air speed at every instance. A signal representing the difference between said trim value signal and the attitude signal is used as an attitude/speed error signal and is added with the signal representing the difference between the ground speed and the set speed for performing control of the aircraft condition. Also, in order to provide true air speed utilizing a detecting means of the Pitot tube type, when the flight speed is below a predetermined value, a ground speed signal is added with a stored signal representing the difference between the air and ground speeds and the added signal is used instead of the air speed signal to overcome the inaccuracy of the Pitot tube at low speeds.

대표청구항 ▼

Automatic flight control means for rotary wing aircraft comprising ground speed detecting means for detecting the ground speed of a rotary wing aircraft and difference signal generating means for generating a signal representing the difference between a set speed and the ground speed obtained from s

Automatic flight control means for rotary wing aircraft comprising ground speed detecting means for detecting the ground speed of a rotary wing aircraft and difference signal generating means for generating a signal representing the difference between a set speed and the ground speed obtained from said ground speed detecting means so that flight control is performed by the difference signal, characterized in that the control means comprises means for detecting the air speed of the aircraft and generating an air speed signal, biasing means for adding to said air speed signal, a bias signal corresponding to the attitude of the aircraft in a hovering condition and generating a trim value signal representing the attitude in a balanced relation to the air speed at every instance, means for generating an attitude signal, and means for generating an attitude/speed error signal from the difference between said trim value signal and said attitude signal, said attitude/speed error signal being utilized to control a flight condition.