The invention relates to a shock absorber of the landing gear of the aircraft, comprising a casing (11) and a rod - piston (12) sliding in said casing, said rod - piston (12), delimiting with the chamber (11) a main chamber (14) of hydraulic fluid and an annular chamber (15) of hydraulic fluid, and internally provided with two adjacent chambers (23, 24) isolated from one another by a separator piston (21), an upper chamber (23) of hydraulic fluid and a lower chamber (24) of gas under pression.conformément to the invention, the rod - piston (12) is extended to the - beyond the lower chamber (24) of gas under pressure, by a sheath (50) in which slides telescopically a hollow piston rod - terminal (51) forming a lower chamber (57) of hydraulic fluid, said piston rod - terminal (51), delimiting with the sheath (50) a lower annular chamber (58) of hydraulic fluid which is connected to an associated control circuit (59, 60, 75), thus making it possible to lengthen or shorten the total length of the shock absorber (10).
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