A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.

Flight control system

The invention provides a control device of a digital electric steering engine and a control method. The control method comprises the steps that a steering surface deflection angle given signal is subjected to voltage transformation, filtering and amplitude limiting processing by a signal conditioning circuit, and sent to a controller DSP (Digital Signal Processor) by AD (Analogue-to-Digital) conversion; the DSP outputs a digital control signal; the digital control signal is subjected to digital isolation and then sent to a driving circuit to be converted into a power control signal; a brushless DC (Direct Current) motor is controlled to operate by controlling a main power circuit, and drives a steering surface to deflect through a transmission gear set to follow the steering surface deflection angle given signal; the bus current of the brushless DC motor is sampled by a current sensor and fed back to the DSP; an angle sensor connected with the transmission gear set feeds back a current deflection angle of the steering surface in real time and sends the current deflection angle to the DPS. The control device and the control method effectively accelerate frequency response of a brushless DC electric steering engine, and improve the interference immunity of a system.

Control device of digital electric steering engine and control method

A system for controlling an aircraft control surface may include a control surface having at least two control surface elements mounted to rotate about an axis on a stabilizer element of the aircraft. An actuator with at least two actuating devices moves the control surface elements according to individual turn commands. Also, a first device determines a particular phase of flight of the aircraft. When the particular phase of flight is determined to exist by the first device, a second device generates differentiated individual turn commands for the actuating devices, according to an overall turn command received from a control unit, to provide prioritized control of the control surface element that generates the lowest force on the stabilizer element.

Method and system for controlling an aircraft control surface

The invention provides a control method for a double-Y-type brushless direct current electric steering engine and a driving device. The electric steering engine drives a controller to receive a control-surface position set signal and a control-surface position feedback signal so as to resolve through a sliding mode control method to drive a double-Y-type brushless direct current motor to operate, torque is applied on a controlled control surface through a driving gear group, and the controlled control surface can move according to the set control-surface position signal. The invention provides a sliding mode flow equalization control policy, two sets of winding currents of the motor are balanced, a force dissension problem is solved, and the reliability of a rudder system is simultaneously improved.

Control method for double-Y-type brushless direct current electric steering engine and driving device

An example method includes: determining a throttle command for a servomotor configured to control a position of a throttle lever, where the position of the throttle lever indicates a commanded thrust for the first engine of the aircraft; determining a trim command for the first engine to equalize the thrust of the first engine with the respective thrust of the second engine; determining that a magnitude of the throttle command is less than a magnitude of a threshold throttle command indicative of a dead zone of the servomotor, where the servomotor is irresponsive to a given throttle command within the dead zone; modifying the trim command based on the throttle command to generate a modified trim command that compensates for irresponsiveness of the servomotor to the throttle command; and changing the thrust generated by the first engine based on the modified trim command.

Low throttle rate command compensation via full authority engine trim

The present invention relates to an arrangement and a method in a mechanical control system of an aircraft. From the cockpit of the aircraft control surfaces (1) of the aircraft can be acted upon via the control system by means of at least one control element (3), for example a wheel, a control column or a pair of pedals operatively connected to the control system. A servomotor (5) together with sensors is also connected to the control system. The sensors are designed, when acted upon by the control element (3), to detect the torque exerted on the control element (3) by a force applied thereto, the trim angle of the control element and the angular velocity with which the action occurs. The arrangement comprises a control device (9) which, on the basis of the conditions detected by the sensors, is designed to control the servomotor (5) so that a ratio between the force applied to the control element (3) and the trim angle of the control element assumes a desired, essentially constant value.

Sjoequist Anders

Papers

Arrangement and method for regulating the steering force in a mechanical steering system for an aircraft