Patent ID: 8727273

Claim:
A shrink shock strut assembly for retractable aircraft landing gear, comprising: a) an elongated strut cylinder; b) an elongated strut piston coaxially mounted for reciprocal movement within the strut cylinder between a shrunk condition when the landing gear is retracted into a wheel well of an aircraft and a fully extended condition when the landing gear is deployed from the wheel well for landing the aircraft; and c) a blocking mechanism operatively associated with the strut cylinder and mounted for movement into a blocking position with respect to the strut piston, when the landing gear is retracted within the wheel well, to prevent axial movement of the strut piston into the fully extended condition within the wheel well, wherein, a capture notch is associated with the strut piston to engage the blocking mechanism in the event that the strut piston moves toward the fully extended condition within the wheel well, and wherein the blocking mechanism comprises a plunger mounted for movement from a retracted position spaced from the strut piston to the blocking position relative to the capture notch; and d) a dynamic abutment structure for moving the plunger into the blocking position when the landing gear is retracted into the wheel well.