Shock absorber for an aircraft landing gear leg

A shock absorber for an aircraft landing gear leg, the shock absorber comprising a cylinder and a rod sliding in said cylinder, together with a disk defining a lower hydraulic fluid chamber which communicates via a diaphragm with an upper hydraulic fluid chamber adjacent to a pressurized gas chamber provided in the upper portion of the cylinder, wherein the sliding rod is implemented in telescopic form, having an outer rod sliding in the cylinder, an intermediate partition which constitutes the above-mentioned disk, and an inner rod sliding in the outer rod on the other side of said partition from the lower hydraulic fluid chamber, bearing directly against said partition when the shock absorber is relaxed or under static load, and wherein the shock absorber further includes a linear actuator received inside the inner rod and suitable, when switched on, for extending the landing gear while the airplane is stationary or moving slowly on the ground, and at least one external scissors linkage for conveying the structural twisting forces to which the telescopic sliding rod is subjected.