Landing gear shock absorber with variable viscosity fluid

Details Landing gear shock absorber with variable viscosity fluid Landing gear shock absorber with variable viscosity fluid

B - Operations, Transporting

64

C

B64C 25/58 (2006.01) B64C 25/60 (2006.01) F16F 9/53 (2006.01)

Patent

CA 2348270

An aircraft landing gear includes a sealed cylinder divided by a cylinder head to define an upper chamber and a lower chamber. The lower chamber is further divided by a piston having a piston rod passing in a sealed manner through the lower cylinder end. The cylinder head includes one or more orifices, the opening of each containing an electromagnetic coil configured to control the viscosity of the magneto- rheological oil passing therethrough. The electrical current through the electromagnetic coil is continually controlled by a microcomputer with attached sensors for piston position and pressure between the desired piston and the cylinder head, such that the pressure between the piston and the cylinder head decelerates the aircraft evenly throughout the desired piston stroke. The pressure also is limited to a desired maximum level so that, in a severe crash, the shock absorber will absorb significant energy before it fails structurally.

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