Uplock unlock electro-hydrostatic actuator
AssigneeGoodrich Corporation
InventorJason Bradley Allen
Life of this patent
Estimating the term…
Abstract
An electrohydrostatic actuator (EHA) for unlocking a uplock of an aircraft is provided, the EHA includes a solenoid, a plunger, a first manifold, and an unlock mechanism. The plunger is mechanically coupled to the solenoid. Responsive to the solenoid being energized, the solenoid is configured to translate the plunger in a first direction to push a hydraulic fluid into the first manifold that feeds the unlock mechanism. Responsive to a command to unlock the uplock of the aircraft, the hydraulic fluid is pushed to the unlock mechanism thereby causing the unlock mechanism to maneuver an over-centered mechanism over a centerline and unlock a uplocked landing gear.
Claims16
An electrohydrostatic actuator (EHA) for unlocking an uplock of an aircraft, the EHA comprising:
- a solenoid;
- a primary plunger positioned within the solenoid;
- a secondary plunger positioned within a first chamber separate from the solenoid, wherein the secondary plunger is mechanically coupled to the primary plunger within the solenoid via a shaft;
- a first manifold, wherein the first manifold is fluidly coupled to the first chamber;
- an extension, wherein:
- a first end of the extension is mechanically coupled to the secondary plunger,
- a second end of the extension is positioned within a second chamber, and
- the first manifold is fluidly coupled to the second chamber;
- and
- an unlock mechanism,
- wherein, responsive to the solenoid being energized, the solenoid is configured to translate the primary plunger in a first direction to push a hydraulic fluid within the first chamber, via the secondary plunger, into the first manifold, via a first check valve, that feeds the unlock mechanism and, at a same time, translate the extension in the first direction to push hydraulic fluid within the second chamber, via the extension, into the first manifold, via a second check valve, that feeds the unlock mechanism, and
- wherein, responsive to a command to unlock the uplock of the aircraft, the hydraulic fluid in the first manifold is pushed to the unlock mechanism, thereby causing the unlock mechanism to maneuver an over-centered mechanism over a centerline and unlock an uplocked landing gear.
An aircraft, the aircraft comprising:
- a landing gear;
- and
- an electrohydrostatic actuator (EHA) for unlocking the landing gear in an uplocked position, the EHA comprising:
- a solenoid;
- a primary plunger positioned within the solenoid;
- a secondary plunger positioned within a first chamber separate from the solenoid, the secondary plunger is mechanically coupled to the primary plunger within the solenoid via a shaft;
- a first manifold;
- an extension, wherein:
- a first end of the extension is mechanically coupled to the secondary plunger,
- a second end of the extension is positioned within a second chamber, and
- the first manifold is fluidly coupled to the second chamber;
- and
- an unlock mechanism,
- wherein, responsive to the solenoid being energized, the solenoid is configured to translate the primary plunger in a first direction to push first hydraulic fluid within the first chamber, via the secondary plunger, into the first manifold, via a first check valve, that feeds the unlock mechanism and, at a same time, translate the extension in the first direct direction to push a second hydraulic fluid within the second chamber, via the extension, into the first manifold, via a second check valve, that feeds the unlock mechanism, and
- wherein, responsive to a command to unlock an uplock of the aircraft, the first hydraulic fluid and the second hydraulic fluid are pushed to the unlock mechanism thereby causing the unlock mechanism to maneuver an over-centered mechanism over a centerline and unlock an uplocked landing gear.
Dependencies are inferred from the claim text.