Conversion actuation systems and methods for tiltrotor aircraft
A method of displacing rotors of an aircraft between a hover mode and an aircraft mode includes rotating a spindle drivingly connected to the rotors about a spindle axis to displace the rotors between the hover and aircraft modes until a component displaceable with the spindle abuts against a downstop of the aircraft and applies a load against the downstop. The method includes passively maintaining the component against the downstop to maintain the load applied against the downstop. An aircraft is also disclosed.
1. An aircraft, comprising:
rotor ducts each having a rotor, the rotor ducts and the rotors being displaceable between a hover mode and an aircraft mode;
a spindle drivingly connected to one of the rotor ducts and rotatable about a spindle axis to displace the rotor duct between the hover and aircraft modes;
a downstop fixedly mounted within the aircraft and defining a contact surface;
a linking member mountable to the spindle and displaceable therewith about the spindle axis toward and away from the contact surface of the downstop; and
an actuator with a rod displaceable by a drive mechanism, the rod mounted to the linking member such that displacement of the rod causes the spindle to rotate about the spindle axis, the actuator having a passive friction device engaged with the rod to stop displacement thereof, the drive mechanism operable to displace the rod to abut the linking member against the contact surface and to apply a load with the linking member against the downstop, the drive mechanism disengageable from the rod upon the load being applied against the downstop, the passive friction device passively engaging the rod and stopping displacement thereof upon the load being applied against the downstop.
2. The aircraft of claim 1 , wherein the drive mechanism is deactivated upon the load being applied against the downstop.
3. The aircraft of claim 1 , wherein the passive friction device includes a no-back mounted about the rod.
4. The aircraft of claim 1 , comprising a spindle position sensor operable to output a spindle position signal indicative of a position of the spindle, and a rod position sensor operable to output a rod position signal indicative of a position of the rod of the actuator, the spindle and rod position sensors deactivating upon the load being applied against the downstop.
5. The aircraft of claim 1 , comprising a rod position sensor operable to output rod position signals indicative of a position of the rod of the actuator, the rod position signal upon the load being applied against the downstop being a reference position signal indicative of a reference position of the rod, the aircraft operable to compare the reference position signal to other rod positions signals to determine deviation of the rod from the reference position.
6. The aircraft of claim 1 , wherein the actuator includes a ball screw actuator pivotably mounted to the aircraft.
7. The aircraft of claim 1 , wherein the linking member includes a nut mounted about the rod and displaceable relative to the rod.
8. The aircraft of claim 1 , wherein the linking member includes a nut mounted about the rod and displaceable relative to the rod, and a spindle arm mounted at a first end to the nut and at a second end to the spindle.