초록 ▼

There is provided a controller for aiding a pilot to control an airplane\s track over the ground. While the airplane is in the air, a lateral control subsystem is provided for automatically holding the aircraft aligned with a desired track angle. Control is initiated when the pilot places the airpla

There is provided a controller for aiding a pilot to control an airplane\s track over the ground. While the airplane is in the air, a lateral control subsystem is provided for automatically holding the aircraft aligned with a desired track angle. Control is initiated when the pilot places the airplane in a wings level condition and centers his roll axis controller (e.g., wheel or stick). An in-air track rate control subsystem is also provided. While the airplane is on the ground, a directional control subsystem is provided which enables the pilot to command track rate or heading rate with rudder pedal inputs. The track/heading rate commands are integrated to generate track/heading angle commands. Feedback control is used to position the rudder and nosewheel steering as required to make the airplane\s actual track/heading follow the track/heading commands. Provisions are made to initialize the in-air lateral and on-ground directional control subsystems to provide smooth transitions during takeoff and landing.

대표청구항 ▼

A control system for an aircraft, the control system comprising: a. roll input means, (i) which are movable by a pilot of the aircraft, for generating a first command signal which is a function of an input made by the pilot to the roll input means so as to control a roll angle of the aircraft and (i

A control system for an aircraft, the control system comprising: a. roll input means, (i) which are movable by a pilot of the aircraft, for generating a first command signal which is a function of an input made by the pilot to the roll input means so as to control a roll angle of the aircraft and (ii) which are movable in a manner that when the roll input means are in a neutral position there is no rolling moment applied to the aircraft in response to the first command signal; b. means for generating a second command signal, as a function of a selected navigation angle, for controlling a roll angle of the aircraft so as to maintain the selected navigation angle; c. aircraft rolling means for generating a rolling moment on the aircraft; and d. control means for causing the aircraft rolling means to respond to the first command signal from the roll input means, unless the roll input means is in the neutral position and the first command signal is within a calculated roll angle threshold value, in which case the aircraft rolling means is caused to respond to the second command signal so as to maintain the selected navigation angle.