Title:
HELICOPTER LANDING GEAR DAMPER
Document Type and Number:
WIPO Patent Application WO/2010/141628
Kind Code:
A3
Abstract:
A damper for a landing gear of a helicopter having a barrel, a piston defining a first hydraulic cavity between the piston and a bottom end of the barrel and a second hydraulic cavity between the piston and a top of the barrel, a stack of disc springs disposed within the first hydraulic cavity in a compressed state between the bottom end of the barrel and the piston. Each of the disc springs having a substantially concave side and an opposing substantially convex side, the disc springs stacked in an alternating pattern such that any two adjacent washers have their like sides positioned adjacent to each other. A spring disposed within the second hydraulic cavity such that the spring is compressed between the compression member and the top of the barrel when the piston is in an extended position. A hydraulic fluid is disposed inside at least a portion of the first hydraulic cavity and at least a portion of the second hydraulic cavity. At least one valve is disposed in the piston so as to establish fluid communication between the first hydraulic cavity and the second hydraulic cavity so as to allow bilateral fluid communication between the first hydraulic cavity and the second hydraulic cavity.
Inventors:
DUNN MARCUS L (US)
Application Number:
PCT/US2010/037124
Publication Date:
March 03, 2011
Filing Date:
June 02, 2010
Export Citation:
Assignee:
DUNN MARCUS L (US)
International Classes:
B64C25/58; B64C25/06; B64C25/52
Foreign References:
| US20060144993A1 | 2006-07-06 | |||
| US4337912A | 1982-07-06 | |||
| EP0212022A1 | 1987-03-04 |
Attorney, Agent or Firm:
ROUSE, Nicholas, D. (P.C.P.o. Box 1637, Oklahoma City OK, US)
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