Controller for an aircraft assembly

1 . A controller for an aircraft assembly that includes a permanent magnet motor; the controller configured to:

control the permanent magnet motor according to a damping mode;

wherein in the damping mode the controller;

receives electrical energy from the permanent magnet motor, wherein the electrical energy is produced as a result of kinetic energy in the aircraft assembly; and

uses the electrical energy to send a first signal to control a transfer of electrical energy from the permanent magnet motor to a damping component to provide damping to the permanent magnet motor;

wherein the damping component comprises an energy storage device; wherein providing the first signal causes the transferred energy to be stored in the energy storage device;

wherein the damping component further comprises a resistive load and a third switch;

wherein the controller is further configured to:

in response to the energy storage device reaching a charge threshold, provide a third signal to the third switch, wherein the third signal configures the third switch to connect the resistive load to the circuit, such that energy can be transferred to and then dissipated in the resistive load.

2 . The controller of claim 1 , wherein the controller is further configured to:

monitor a power line used for powering the motor by sensing a voltage, a current and/or a power level on the power line to produce data; and

determine a state of the power line based on the data.

3 . The controller of claim 2 , wherein the permanent magnet motor receives electrical power from a circuit;

wherein in the damping mode the controller is further configured to:

provides the first signal to a first switch in order to connect or disconnect a part of the circuit.

4 . The controller of claim 3 , wherein the first switch is a Normally Open switch; wherein the first signal configures the first switch into a closed configuration which connects the damping component to the circuit, such that electrical energy can be transferred from the permanent magnet motor to the damping component.

5 . The controller of claim 4 , wherein the first signal is a Pulse Width Modulated signal, and the first switch is in the closed configuration for a period of time corresponding to a parameter of the PWM signal, such that the power transferred to the damping component is proportional to the parameter of the PWM signal.

6 . The controller of claim 5 , further comprising a brake controller;

wherein the brake controller is configured to implement a braking algorithm;

wherein the braking algorithm configures one or more of the parameters of the PWM signal based on the data.

7 . The controller of claim 6 , wherein the braking algorithm configures one or more of the parameters of the PWM signal by:

increasing a pulse width or a duty cycle of the PWM signal as the voltage, current and/or power level on the power line increases; and

decreasing a pulse width or a duty cycle of the PWM signal as the voltage, current and/or power level on the power line decreases.

8 . The controller of claim 1 , wherein the damping component comprises a resistive load; wherein providing the first signal causes the transferred energy to be dissipated in the resistive load.

9 . A DC-AC inverter circuit for damping a permanent magnet motor, the circuit comprising:

a controller according to claim 1 for controlling the circuit to provide the damping.

10 . An aircraft system comprising:

the circuit of claim 9 ;

the permanent magnet motor; and

a power source for powering the permanent magnet motor.

11 . The aircraft system of claim 10 , wherein the permanent magnet motor is for providing actuation to: an aircraft landing gear system; a control surface; a flap; a spoiler; an aircraft door or evacuation system.

12 . A method for controlling an aircraft assembly with the controller of claim 1 , the method comprising:

controlling the permanent magnet motor according to a damping mode;

wherein the damping mode comprises:

powering a controller by drawing electrical energy from the permanent magnet motor, wherein the electrical energy is produced as a result of kinetic energy in the aircraft assembly; and

using the electrical energy to send a first signal to control a transfer of electrical energy from the permanent magnet motor to a damping component to provide damping to the permanent magnet motor,

monitor a power line used for powering the motor by sensing a voltage, a current and/or a power level on the power line to produce data; and

determine a state of the power line based on the data.

13 . The method of claim 12 , further comprising:

monitoring a power line used for powering the motor by sensing a voltage, a current and/or a power level on the power line to produce data; and

determining a state of the power line based on the data.

14 . The method of claim 13 , wherein the permanent magnet motor receives electrical power from a circuit;

wherein in the damping mode the method further includes providing the first signal to a first switch in order to connect or disconnect a part of the circuit.

15 . The method of claim 14 , wherein the first switch is a Normally Open switch; wherein the first signal configures the first switch into a closed configuration which connects the damping component to the circuit, such that electrical energy can be transferred from the permanent magnet motor to the damping component.

16 . The method of claim 15 , wherein the first signal is a Pulse Width Modulated signal, and the first switch is in the closed configuration for a period of time corresponding to a parameter of the PWM signal, such that the power transferred to the damping component is proportional to the parameter of the PWM signal.

17 . The method of claim 16 , wherein the controller further comprises a brake controller;

wherein the brake controller is configured to implement a braking algorithm;

wherein the braking algorithm configures one or more of the parameters of the PWM signal based on the data.

18 . A controller for an aircraft assembly that includes a permanent magnet motor; the controller configured to:

control the permanent magnet motor according to a damping mode;

wherein in the damping mode the controller;

receives electrical energy from the permanent magnet motor, wherein the electrical energy is produced as a result of kinetic energy in the aircraft assembly; and

uses the electrical energy to send a first signal to control a transfer of electrical energy from the permanent magnet motor to a damping component to provide damping to the permanent magnet motor,

wherein the controller is further configured to:

monitor a power line used for powering the motor by sensing a voltage, a current and/or a power level on the power line to produce data; and

determine a state of the power line based on the data;

wherein the permanent magnet motor receives electrical power from a circuit;

wherein in the damping mode the controller is further configured to:

provide the first signal to a first switch in order to connect or disconnect a part of the circuit,

wherein the first switch is a Normally Open switch; wherein the first signal configures the first switch into a closed configuration which connects the damping component to the circuit, such that electrical energy can be transferred from the permanent magnet motor to the damping component,

wherein the first signal is a Pulse Width Modulated signal, and the first switch is in the closed configuration for a period of time corresponding to a parameter of the PWM signal, such that the power transferred to the damping component is proportional to the parameter of the PWM signal,

the controller further comprising a brake controller, wherein the brake controller is configured to implement a braking algorithm;

wherein the braking algorithm configures one or more of the parameters of the PWM signal based on the data;

wherein the braking algorithm configures one or more of the parameters of the PWM signal by:

increasing a pulse width or a duty cycle of the PWM signal as the voltage, current and/or power level on the power line increases; and

decreasing a pulse width or a duty cycle of the PWM signal as the voltage, current and/or power level on the power line decreases,

wherein the controller is further configured to:

provide a second signal to a second switch, wherein the second signal configures the second switch to connect or disconnect the damping component from the circuit.