Redundant load path for a tiltable aircraft component
A tilting apparatus for an aircraft, comprising: a tiltable aircraft component which tilts between a first and second position, at least one actuator for adjusting a tilt angle of the tiltable aircraft component, and at least one passive damper connected to the tiltable aircraft component and configured to limit a rate of change of the tilt angle of the tiltable aircraft component. The at least one passive damper is on a load path separate from a load path of the at least one actuator.
1 . A tilting apparatus for an aircraft, comprising:
a tiltable aircraft component which tilts between a first and second position;
at least one actuator for adjusting a tilt angle of the tiltable aircraft component; and
at least one passive damper connected to the tiltable aircraft component and configured to limit a rate of change of the tilt angle of the tiltable aircraft component, and
wherein the at least one passive damper is connected to the tiltable aircraft component on a first load path and the at least one actuator is connected to the tiltable aircraft component on a second load path separate from the first load path of the at least one passive damper.
2 . The tilting apparatus of claim 1 , wherein the tiltable aircraft component comprises a proprotor.
3 . The tilting apparatus of claim 1 , wherein the tiltable aircraft component comprises a proprotor frame.
4 . The tilting apparatus of claim 1 , wherein the at least one passive damper is configured to limit the rate of change of the tilt angle of the tiltable aircraft component in both tilt directions.
5 . The tilting apparatus of claim 1 , wherein the at least one passive damper comprises a hydraulic or pneumatic cylinder.
6 . The tilting apparatus of claim 5 , wherein the hydraulic or pneumatic cylinder is a balanced uncharged cylinder or an unbalanced cylinder.
7 . The tilting apparatus of claim 1 , wherein the at least one actuator comprises a linear actuator or a rotary actuator.
8 . The tilting apparatus of claim 1 , wherein the tiltable aircraft component is configured to be tiltably mounted to a boom.
9 . The tilting apparatus of claim 1 , wherein the at least one passive damper is at least partially housed within an outer shell.
10 . The tilting apparatus of claim 1 , wherein the at least one actuator and the at least one passive damper are configured to be positioned on opposite sides of a rib of an aircraft.
11 . The tilting apparatus of claim 1 , wherein the tiltable aircraft component is configured to tilt in an upward direction from a forward flight position to a lift position, and a force vector of the at least one passive damper extends beneath a tilt axis of the tiltable aircraft component.
12 . The tilting apparatus of claim 1 , wherein a range of the tilt angle of the tiltable aircraft component is at least 90 degrees.
13 . The tilting apparatus of claim 1 , further comprising a single actuator for adjusting the tilt angle of the tiltable aircraft component.
14 . The tilting apparatus of claim 1 , wherein the at least one passive damper is configured to limit the rate of change of the tilt angle to a predetermined threshold value in an event in which the tiltable aircraft component is disconnected from the at least one actuator during forward flight.
15 . The tilting apparatus of claim 1 , wherein the first position is a lift position for providing lift to the aircraft; and wherein the second position is a forward thrust position for providing forward thrust to the aircraft.
16 . The tilting apparatus of claim 1 , wherein the tiltable aircraft component is electrically powered.
17 . An aircraft, comprising:
a wing;
a boom mounted to the wing;
at least one tiltable aircraft component mounted to the boom, which tilts between a first and second position;
at least one actuator for adjusting a tilt angle of the at least one tiltable aircraft component; and
at least one passive damper connected to the at least one tiltable-aircraft component and configured to limit a rate of change of the tilt angle of the at least one tiltable aircraft component, and
wherein the at least one passive damper is on a load path separate from a load path of the at least one actuator.
18 . The aircraft of claim 17 , wherein the at least one tiltable aircraft component is mounted to a forward end of the boom.
19 . The aircraft of claim 17 , wherein the boom is mounted inward of the end of the wing.
20 . The aircraft of claim 17 , wherein the at least one tiltable component comprises a plurality of tiltable components; and
wherein the at least one passive damper comprises a plurality of dampers.
21 . The aircraft of claim 17 , wherein the aircraft is a passenger aircraft.
22 . A method for controlling a tiltable component of an aircraft, comprising:
receiving a command at a controller to adjust a tilt angle of a tiltable aircraft component between a first and second position;
controlling at least one actuator to adjust the tilt angle of the tiltable aircraft component; and
wherein at least one passive damper is connected to the tiltable aircraft component and limits a rate of change of the tilt angle of the tiltable aircraft component, and
wherein the at least one passive damper is connected to the tiltable aircraft component on a first load path and the at least one actuator is connected to the tiltable aircraft component on a second load path separate from the first load path of the at least one passive damper.
23 . The method of claim 22 , wherein the tiltable aircraft component comprises a proprotor.
24 . The method of claim 22 , wherein the at least one passive damper is configured to limit the rate of change of the tilt angle of the tiltable aircraft component in both tilt directions.
25 . The method of claim 22 , wherein the at least one passive damper comprises a hydraulic or pneumatic cylinder.
26 . The method of claim 22 , wherein the at least one actuator and the at least one passive damper are configured to be positioned on opposite sides of a rib of an aircraft.
27 . The method of claim 22 , wherein the tiltable aircraft component is configured to tilt in an upward direction from a forward flight position to a lift position, and a force vector of the at least one passive damper extends beneath a tilt axis of the tiltable aircraft component.
28 . The method of claim 22 , wherein a range of the tilt angle of the tiltable aircraft component is at least 90 degrees.
29 . The method of claim 22 , wherein the at least one passive damper is configured to limit the rate of change of the tilt angle to a predetermined threshold value in an event in which the tiltable aircraft component is disconnected from the at least one actuator during forward flight.
30 . The method of claim 22 , wherein the first position is a lift position for providing lift to the aircraft; and wherein the second position is a forward thrust position for providing forward thrust to the aircraft.