Tie rod lock

A stabilizer actuator having a first end for connecting to an aircraft support structure and a second end for connecting to a stabilizer, the actuator including a primary load path for transmittal of loads acting on the stabilizer to the aircraft support structure, and a secondary load path for transmittal of loads acting on the stabilizer to the aircraft support structure upon failure of the primary load path, the secondary load path comprising:

• a tie rod extending along a longitudinal axis;
• a load path locking mechanism coupled to the tie rod;
• a lock housing having a central bore for receiving the locking mechanism;
• and
• at least one radially movable segment that, upon failure of the primary load path, moves radially to lock the tie rod to the lock housing against axial and/or radial movement,
• wherein an inner surface defining the central bore includes the at least one protrusion extending radially inward from the inner surface,
• wherein the locking mechanism includes the at least one segment, and the at least one segment is configured to move radially outward from a standby position to a failsafe position to prevent relative movement of the tie rod with respect to the lock housing by interacting with the at least one protrusion, and
• wherein the at least one protrusion comprises at least one inwardly extending axial ridge and wherein the at least one segment comprises a lock segment having an outward extending axial flange configured to prevent relative radial movement between the tie rod and the lock housing by interacting with the at least one ridge.

A stabilizer actuator having a first end for connecting to an aircraft support structure and a second end for connecting to a stabilizer, the actuator including a primary load path for transmittal of loads acting on the stabilizer to the aircraft support structure, and a secondary load path for transmittal of loads acting on the stabilizer to the aircraft su ort structure u on failure of the primary load path, the secondary load path comprising:

• a tie rod extending along a longitudinal axis;
• a load path locking mechanism coupled to the tie rod;
• a lock housing having a central bore for receiving the locking mechanism;
• and
• at least one radian movable segment that, upon failure of the primary load path, moves radially to lock the tie rod to the lock housing against axial and/or radial movement,
• wherein the locking mechanism further comprises a spring pack for radially moving the segment outward from the standby position to the failsafe position, and
• wherein the spring pack includes an inner spring having a first twist direction and a coaxial outer spring having a second twist direction opposite the first twist direction.

A stabilizer actuator having a first end for connecting to an aircraft support structure and a second end for connecting to a stabilizer, the actuator including primary load path for transmittal of loads acting on the stabilizer to the aircraft support structure, and a secondary load path for transmittal of loads acting on the stabilizer to the aircraft support structure upon failure of the primary load path, the secondary load path comprising:

• a tie rod extending along a longitudinal axis;
• a load path locking mechanism coupled to the tie rod;
• a lock housing having a central bore for receiving the locking mechanism;
• and
• at least one radially movable segment that, upon failure of the primary load path, moves radially to lock the tie rod to the lock housing against axial and/or radial movement,
• wherein the locking mechanism further comprises a trigger mechanism configured to trigger movement of the segment to the failsafe position when the a load path fails, and
• wherein the trigger mechanism is axially slidable with respect to the segment.

A stabilizer actuator having a first end for connecting to an aircraft support structure and a second end for connecting to a stabilizer, the actuator including a primary load path for transmittal of loads acting on the stabilizer to the aircraft support structure, and a secondary load path for transmittal of loads acting on the stabilizer to the aircraft support structure upon failure of the primary load path, the secondary load path comprising:

• a tie rod extending along a longitudinal axis;
• a load path locking mechanism coupled to the tie rod at an end of the tie rod;
• a lock housing having a central bore for receiving the locking mechanism;
• and
• at least one radially movable segment that, upon failure of the primary load path, moves radially to lock the tie rod to the lock housing against axial and/or radial movement.

A stabilizer actuator having a first end for connecting to an aircraft support structure and a second end for connecting to a stabilizer, the actuator including a primary load path for transmittal of loads acting on the stabilizer to the aircraft support structure, and a secondary load path for transmittal of loads acting on the stabilizer to the aircraft support structure upon failure of the primary load path, the secondary load path comprising:

• a tie rod extending along a longitudinal axis;
• a load path locking mechanism coupled to the tie rod;
• a lock housing having a central bore for receiving the locking mechanism;
• and
• at least one radially movable segment that, upon failure of the primary load path, moves radially to lock the tie rod to the lock housing against axial and/or radial movement,
• wherein an inner surface defining the central bore includes the at least one protrusion extending radially inward from the inner surface,
• wherein the locking mechanism includes the at least one segment, and the at least one segment is configured to move radially outward from a standby position to a failsafe position to prevent relative movement of the tie rod with respect to the lock housing by interacting with the at least one protrusion, and
• wherein the lock housing further comprises one or more radial ports adjacent to the protrusion thereby allowing access to reset the locking mechanism from the failsafe position to the standby position.

An actuator comprising:

• a drive motor and gear assembly;
• a ballscrew driven by the motor;
• a support gimbal for coupling the ballscrew to a support structure;
• a ball nut driven by the ballscrew;
• a tie rod extending along a longitudinal axis and rigidly coupled to the ballscrew;
• a locking mechanism coupled to the tie rod at an end of the tie rod;
• a lock housing having a central bore for receiving the locking mechanism;
• and
• at least one radially movable segment that, upon structural failure of the drive motor and gear assembly, the ballscrew, and/or the support gimbal, moves radially to lock the tie rod to the lock housing against axial and/or radial movement.