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Crashworthy landing gear shock

  • US 5,944,283 A
  • Filed: 12/05/1997
  • Issued: 08/31/1999
  • Est. Priority Date: 12/05/1997
  • Status: Expired due to Term
First Claim
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1. A shock absorber for fitting to the landing gear of an aircraft, the shock absorber comprising:

  • a cylinder having a first end and a second end and containing a hydraulic fluid;

    a piston located in the cylinder, the piston having a rod extending outward from the second end of the cylinder;

    an orifice in the cylinder, through which the hydraulic fluid flows as the piston moves toward the first end due to a shock applied; and

    a valve mounted to the cylinder, having a first end adjacent the orifice and a second end exposed to atmospheric pressure, the valve being movable relative to the orifice from a less restrictive position to fluid flow through the orifice to a more restrictive position and being urged toward the more restrictive position by a spring, wherein if a shock applied to the shock absorber is of sufficient magnitude, a pressure differential between atmospheric pressure and pressure between the valve and the piston causes the valve to move toward the less restrictive position to allow a greater flow rate through the orifice.

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