Patent ID: 8070095

Claim:
A shrinking shock strut system for an aircraft landing gear having a retract actuator that is moveable in length to deploy or retract the landing gear, comprising: a shrink strut that is moveable between an extended length and a shrunk length, the shrink strut including a strut cylinder and a strut piston mounted coaxially, wherein a variable length strut shrink chamber is formed between the strut cylinder and the strut piston, and wherein an increase in the length of the strut shrink chamber causes a decrease in the length of the shrink strut; a transfer device configured to transfer hydraulic fluid to the strut shrink chamber independent of movement of the retract actuator; a control device configured to cause the transfer device to transfer hydraulic fluid to the strut shrink chamber; and a pressure compensator and wherein the strut shrink chamber, the transfer device, and the pressure compensator are in communication with a closed hydraulic system, wherein the pressure compensator is configured to maintain a minimum pressure in the closed hydraulic system.