Temperature compensated landing gear shock strut
AssigneeGoodrich Corporation
InventorsHemanth M N, Basavaraj Bodki
Life of this patent
Estimating the term…
Abstract
A landing gear assembly is provided. The landing gear assembly includes a shock strut. The shock strut includes a shock strut cylinder and a shock strut piston slidably disposed within the shock strut cylinder. The landing gear assembly further includes a temperature control unit assembly disposed within the shock strut cylinder. The temperature control unit assembly is configured to, responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, circulate heated fluid into a chamber of the shock strut cylinder to heat gas within the shock strut cylinder.
Claims18
A landing gear assembly, comprising:
- a shock strut comprising:
- a shock strut cylinder;
- and
- a shock strut piston slidably disposed within the shock strut cylinder;
- and
- a temperature control unit assembly disposed within the shock strut cylinder, wherein the temperature control unit assembly is configured to:
- responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, circulate heated fluid into a chamber of the shock strut cylinder to heat gas within the shock strut cylinder;
- and
- responsive to the temperature within the shock strut cylinder rising up to or above the predetermined temperature, stop the circulation of the heated fluid into the chamber of the shock strut cylinder to heat the gas within the shock strut cylinder.
An aircraft, comprising:
- a landing gear assembly, the landing gear assembly comprising:
- a shock strut comprising:
- a shock strut cylinder;
- and
- a shock strut piston slidably disposed within the shock strut cylinder;
- and
- a temperature control unit assembly disposed within the shock strut cylinder, wherein the temperature control unit assembly is configured to:
- responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, circulate heated fluid into a chamber of the shock strut cylinder to heat gas within the shock strut cylinder;
- and
- responsive to the temperature within the shock strut cylinder rising up to or above the predetermined temperature, stop the circulation of the heated fluid into the chamber of the shock strut cylinder to heat the gas within the shock strut cylinder.
A method of maintaining a compressibility factor of gas in a shock strut of a landing gear assembly of an aircraft, comprising:
- receiving, by a temperature regulator, a temperature sensed by a temperature sensor;
- and
- responsive to the temperature sensed by the temperature sensor being below a predetermined temperature, circulating, by the temperature regulator, heated fluid from a heated fluid chamber into a heat exchanger within a chamber of a shock strut cylinder to heat gas within the shock strut cylinder.
Dependencies are inferred from the claim text.