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US 11,814,160 B2Granted
Landing gear percolation
AssigneeGoodrich Corporation
InventorsBasavaraj Bodki, Hemanth Nagaraja, Steve Healey
Life of this patent
Estimating the term…
Abstract
A shock strut is disclosed. The shock strut may include a shock strut cylinder, a shock strut piston that is slidably disposed within the shock strut cylinder, a metering pin, and a percolation seal configured to restrict a flow of liquid between the shock strut cylinder and the shock strut piston.
Claims19
A shock strut, comprising:
- a shock strut cylinder;
- a shock strut piston that is slidably disposed within the shock strut cylinder;
- a metering pin coupled to the shock strut piston;
- a conduit disposed through the metering pin;
- a seal orifice extending through a wall of the metering pin and in fluid communication with the conduit;
- a fluid source coupled to the conduit and in fluid communication with the conduit, the metering pin, and the seal orifice;
- and
- an annular seal in fluid communication with the fluid source through the conduit, the metering pin, and the seal orifice, the annular seal configured to inflate and deflate, the annular seal restricting a flow of liquid between the shock strut cylinder and the shock strut piston when the annular seal is in an inflated state, wherein the fluid is configured to flow through the conduit, completely through the metering pin via the seal orifice, and into the annular seal.
5 more elements
A landing gear system, comprising:
- a shock strut cylinder;
- a shock strut piston that is slidably disposed within the shock strut cylinder;
- a metering pin;
- a conduit disposed through the metering pin;
- a seal orifice extending through a wall of the metering pin and in fluid communication with the conduit;
- an annular seal in fluid communication with the seal orifice, the annular seal configured to inflate and deflate, the annular seal restricting a flow of liquid between the shock strut cylinder and the shock strut piston when the annular seal is in an inflated state;
- and
- a fluid source in fluid communication with the conduit, the seal orifice, and the annular seal, the fluid source configured to pressurize a fluid causing the fluid to flow through the conduit, the seal orifice, and into the annular seal in order to inflate the annular seal to the inflated state.
5 more elements
A method for restricting fluid flow within a landing gear assembly via an annular seal, comprising:
- sensing whether the landing gear assembly is being retracted or extended, wherein the landing gear assembly includes a conduit extending through a metering pin and a fluid source in fluid communication with the conduit;
- inflating the annular seal if the landing gear assembly is being retracted to seal a liquid chamber from a mixed fluid chamber, wherein inflating the annular seal includes pressurizing a fluid in the conduit by the fluid source, the fluid being configured to flow through the conduit, through the metering pin via a seal orifice, and into the annular seal, wherein a retainer plate separates the liquid chamber and the mixed fluid chamber, the annular seal disposed adjacent the retainer plate when the landing gear assembly is being retracted;
- and
- deflating the annular seal if the landing gear assembly is being extended, wherein the fluid is configured to flow out of the annular seal, through the conduit, and into the fluid source in response to a decrease in pressure.
1 more element
Dependencies are inferred from the claim text.