The invention relates to a single-actuating type
magneto-rheological
shock absorber used for an
aircraft landing gear. The single-actuating type
magneto-rheological
shock absorber comprises an outer cylinder
barrel, an inner cylinder
barrel, a
piston rod, a
piston assembly and an aircraft wheel axle base, wherein an end cover is installed on the top of the outer cylinder
barrel coaxially in a sealed mode; the inner cylinder barrel is coaxially installed in the lower end of the outer cylinder barrel in a sliding mode; the aircraft wheel axle base is installed at the lower end of the inner cylinder barrel in a threaded mode; the inner and outer cylinder barrels are coaxially provided with the
piston rod, the upper end of the
piston rod is fixedly installed on the end cover, and the piston
assembly is installed at the lower end of the
piston rod; the outer edge of the piston
assembly makes friction contact with the inner wall of the inner cylinder barrel. Based on an existing
aircraft landing gear buffer structure, the piston assembly capable of applying the
magneto-rheological fluid technology is added, so that the
shock absorber is simple in structure, low in
energy consumption, small in size and fast in response, and damping
force output by the shock absorber continuously changes, is adjustable and is reversible. Closed-loop semi-
active control is achieved by being combined with a computer, an optimization
control algorithm, a sensor, a controller and a power source, and the buffering efficiency and shock
absorption effect of the shock absorber are improved.