Aircraft seat

1. An active vibration mitigation method for reducing vibrations of a seat onboard an aircraft, comprising:

determining, via a controller, an expected level of vibration for the seat based on command inputs from a pilot control device or autopilot servo;

receiving, via the controller, vibration data from one or more accelerometers located onboard the aircraft;

determining a vibration profile of the seat based on the vibration data;

determining whether vibration mitigation is warranted based on the expected level of vibration and the vibration profile; and

when vibration mitigation is warranted, determining control signals for damping vibration and transmitting the control signals to a plurality of linear actuators adapted to support the seat.

2. The active vibration mitigation method of claim 1 , wherein determining the vibration profile comprises filtering the vibration data to exclude low amplitude and low frequency vibrations.

3. The active vibration mitigation method of claim 1 , wherein determining the vibration profile comprises filtering the vibration data to exclude cutout frequencies.

4. The active vibration mitigation method of claim 1 , comprising:

receiving aircraft avionics data via the controller;

determining an aircraft phase of flight based on the aircraft avionics data; and

determining the expected level of vibration for the seat based on the aircraft phase of flight.

5. The active vibration mitigation method of claim 4 , comprising:

moving the seat via the plurality of linear actuators based on the aircraft phase of flight.

6. The active vibration mitigation method of claim 1 , comprising:

extending/retracting the plurality of linear actuators in a coordinated manner for counteracting expected aircraft motion based on the command inputs.

7. The active vibration mitigation method of claim 1 , comprising actively controlling vibration of the aircraft seat induced while taxiing, during landing, or from air turbulence during flight.

8. The active vibration mitigation method of claim 1 , comprising:

receiving first vibration data from a center-of-gravity accelerometer located at a center-of-gravity of the aircraft and second vibration data from a seat accelerometer located at a seat base; and

determining control signals for damping vibration of the seat base by reducing a difference between the first vibration data and the second vibration data.

9. The active vibration mitigation method of claim 1 , comprising providing height adjustability, inboard/outboard tracking and tilting, forward/aft tracking and tilting, and swiveling of the aircraft seat by coordinating extension/retraction of the plurality of linear actuators.

10. The active vibration mitigation method of claim 1 , comprising:

extending/retracting the plurality of linear actuators in a coordinated manner for adjusting position of the aircraft seat in six degrees-of-freedom based on inputs received from a user input device communicatively coupled with the controller.

11. The active vibration mitigation method of claim 1 , comprising initiating vibration of the seat by controlling an extension/retraction of the plurality of linear actuators at a predetermined frequency and amplitude for providing a notification to a user of the seat.

12. A vibration mitigation method for an aircraft seat, comprising:

receiving, via a controller, command inputs from a pilot control device or autopilot servo;

determining, via the controller, an expected level of vibration for the aircraft seat based on the command inputs;

receiving, via the controller, vibration data from an accelerometer mounted to the aircraft seat; and

damping vibration of the aircraft seat via a plurality of linear actuators based on the expected level of vibration and the vibration data.

13. The vibration mitigation method of claim 12 , comprising filtering the vibration data to remove low amplitude signals or low frequency signals.

14. The vibration mitigation method of claim 12 , comprising:

determining that the aircraft is banking a turn based on the command inputs; and

tilting the aircraft seat to partially or fully counteract a banked turn.

15. The vibration mitigation method of claim 12 , comprising:

determining a pitch of the aircraft based on the command inputs; and

tilting the aircraft seat to partially or fully counteract the pitch of the aircraft.

16. The vibration mitigation method of claim 12 , comprising:

selecting a mode of operation via a user interface;

actively damping vibrations in all directions while in a full stabilization mode; and

actively damping vibrations in a Z-axis while in a reduced stabilization mode.