Control electronics, electromechanical actuator, aircraft and method for damping the movement of an electromechanical actuator

Abstract

The present invention relates to control electronics, preferably for an electromechanical actuator, preferably for use in a primary flight control system of an aircraft, wherein the control electronics can connect or connects an electric motor, preferably of the electromechanical actuator, to an electrical or electronic load and/or wherein the control electronics can deactivate or deactivates a DC/DC converter supplying electrical power to the electric motor, and to an electromechanical actuator and to a method for damping the movement of an electromechanical actuator.

Claims

1. A control electronics system, comprising a DC/DC converter (1), control electronics (4) coupled to the DC/DC converter (1), a power amplifier (5) coupled to the control electronics (4), an electric motor (3) having three phases coupled to the power amplifier (5), an electronic load (R), and a switch(S) arranged to connect the electronic load (R) to the power amplifier (5), wherein the control electronics (4) is configured to deactivate the DC/DC converter (1) in event of power failure and connect the electronic load (R) to the power amplifier (5) through the switch(S), ensuring required counter-torque.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Further advantages, features and effects of the present invention will be apparent from the following description of preferred embodiments with reference to the figures, in which the same or similar components are designated by the same reference characters. The Figures show in:

(2) FIG. 1: an embodiment of a circuit with control electronics according to the invention.

(3) FIG. 2: a further embodiment of a circuit with control electronics according to the invention.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

(4) FIG. 1 shows components with which a solution to the damping requirement can be implemented.

(5) FIG. 1 shows a DC/DC converter 1 supplied with a DC voltage of 28 V, for example from the on-board power supply of an aircraft, which supplies a motor controller 2 with a DC voltage of 45 to 70 V. The DC/DC converter 1 thus functions as a power supply unit.

(6) This increased voltage of 45 to 70 V allows the electric motor 3 to be dimensioned with increased counter voltage values.

(7) Preferably, a control electronics according to the invention is integrated in the motor controller 2.

(8) The motor controller 2 is connected to the preferably three phases of an electric motor 3 and controls the electric motor.

(9) The control electronics present in the motor controller 2 switches the electric motor 3 to an electric load when the electric motor generates a certain counter voltage.

(10) In normal operation, the DC/DC converter 1 or the power supply unit supplies the motor control electronics or the motor controller 2 of the drive or the electric motor 3. However, in the event of a failure or loss of supply voltage, damping should be activated.

(11) The control electronics preferably requires a minimum voltage to become operative. Due to the modified design, the electric motor 3 generates this minimum voltage at already low speeds.

(12) FIG. 2 shows a possible architectural concept of a circuit with control electronics according to the invention.

(13) FIG. 2 shows a DC/DC converter 1 electrically connected to a control electronics 4 and a power amplifier 5.

(14) The power amplifier 5 is connected to the three phases of the electric motor 3.

(15) In the event of a failure, the control electronics 4 deactivates the DC/DC converter 1 and connects the electronic load R to the power amplifier 5 through the switch S.

(16) Activated by the minimum speed of the electric motor 3, the control electronics 4 switches the motor phases or the power amplifier 5 to an electronic load R and thus ensures the required counter-torque. Preferably, a disconnection from the on-board power supply is also implemented by deactivating the DC/DC converter 1.