To disassemble the docking mechanism the locks on the bushing opened, and the mechanism was stored like an umbrella; the remaining supports left the attachment sockets of the docking frame. Before the first undocking the pilot of the command module executed the following manual operations: installed the receiving cone in the tunnel of the lunar module; linked the head of the docking mechanism with the receiving cone; using a winch (which required about 20 turns by hand with an effort of up to 260 N) separated the remaining supports until they entered the attachment sockets on the docking frame; created a preliminary tension of the rod of the docking mechanism, sufficient to maintain the docked state while there was pressure in the tunnel; consecutively opened the 12 locks of the docking frame (the locks were raised for the next docking); opened the hatch, relieving the pressure in the tunnel, and verified the hermeticity of the hatch. Undocking was done on command from the astronaut's control panel. First the electromagnets were switched on, which released the rod latches and then (at a certain length of the rod) automatically turned on electromagnets which released the latches of the head. The final undocking was done by firing the active docking assembly from the command module on command from the astronaut's control panel using a pyrotechnic fuse (see Figure 1.21). The docking mechanism is a complex multi-functional structure weighing about 40 kg (Figure 1.22). To align with the socket when the rod is in an elevated position relative to the axis of the cone, the head is equipped with a two-stage hinge and is centered by a spring. The shock absorption system consists of a centra! spring, which in a compressed state creates a thrust of 600 N, three pneumo-hydraulic shock absorbers, spring cables under the limiting levers, and three support spring cables. The kinematics of the lever mechanism is such that when the rod settles it compresses the pneumo-hydraulic shock absorbers (the nominal static force at full compression is 1.8 kN). The shock absorbers and spring cables are also compressed with direct compression of the limiting levers during shock absorption of the relative rotations of the spacecraft after linkage. For lateral impacts the support spring cables are deformed, and the head of the rod deviates laterally.
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