Patent ID: 11858650
Assignee: HAMILTON SUNDSTRAND CORPORATION
Field: Mechanical elements (Mechanical engineering)
Classification: CPC B  F | IPC B  F

Claim 0:
1. A ram air turbine (RAT) restow system comprising:
an actuator assembly including a piston interposed between an upper fluid compartment and a lower fluid compartment, the actuator assembly configured to selectively move the piston between a deployed position and a stowed position; and
a hydraulic restow circuit configured to receive fluid, the hydraulic restow circuit including a manually actuated restow valve configured to operate in a first position that establishes a first fluid path to deliver the fluid to the upper fluid compartment to effect the deployed position and a second position that establishes a second fluid path to deliver the fluid to the lower fluid compartment to transition from the deployed position to the stowed position,
wherein the manually actuated restow valve rotates about a center axis in a first direction in response to receiving a rotational force manually applied to the manually actuated restow valve, and rotates about the center axis in a second direction opposite the first direction in response to manually removing the rotational force,
wherein the hydraulic restow circuit further comprises:
an actuator supply line including a first end in fluid communication with the actuator assembly and a second end in fluid communication with a third fluid path of the restow valve;
a aircraft return line including a first end in fluid communication with the third fluid path;
an aircraft supply line in fluid communication with the restow valve; and
an actuator return line including a first end in fluid communication with the actuator assembly and a second end in fluid communication with one of a first valve fluid path of the restow valve when the restow valve is in the first position or a second valve fluid path of the restow valve when the restow valve is in the second position,
wherein the actuator return line is in fluid communication with both the actuator supply line and the aircraft return line via the first valve fluid path when the restow valve operates in the first position, and
wherein the actuator return line is disconnected from the both the actuator supply line and the aircraft supply line, and is in fluid communication with the aircraft return line via the second valve fluid path when the restow valve is in the second position.