▁after ▁each ▁hard ▁dock ing ▁event ▁( l un ar ▁miss ions ▁required ▁two ▁dock ings ). ▁ ▁Se par ation ▁An ▁automatic ▁extension ▁l atch ▁attached ▁to ▁the ▁pro be ▁cyl inder ▁body ▁engaged ▁and ▁retained ▁the ▁pro be ▁center ▁p ist on ▁in ▁the ▁ret ract ed ▁position . ▁Before ▁vehicle ▁separation ▁in ▁lun ar ▁orbit , ▁manual ▁co ck ing ▁of ▁the ▁twelve ▁ring ▁l atch es ▁was ▁accomplished . ▁The ▁separ ating ▁force ▁from ▁the ▁internal ▁pressure ▁in ▁the ▁tunnel ▁area ▁was ▁then ▁transm itted ▁from ▁the ▁ring ▁l atch es ▁to ▁the ▁pro be ▁and ▁dro gue . ▁In ▁und ock ing , ▁the ▁release ▁of ▁the ▁capture ▁l atch es ▁was ▁accomplished ▁by ▁elect r ically ▁energ izing ▁tan dem - mount ed ▁DC ▁rot ary ▁sol en oid s ▁located ▁in ▁the ▁center ▁p ist on . ▁In ▁a ▁temperature ▁de grad ed ▁condition , ▁a ▁single ▁motor ▁release ▁operation ▁was ▁done ▁manually ▁in ▁the ▁lun ar ▁module ▁by ▁de press ing ▁the ▁lock ing ▁sp ool ▁through ▁an ▁open ▁hole ▁in ▁the ▁pro be ▁heads , ▁while ▁release ▁from ▁the ▁C SM ▁was ▁done ▁by ▁rot ating ▁a ▁release ▁handle ▁at ▁the ▁back ▁of ▁the ▁pro be ▁to ▁rotate ▁the ▁motor ▁tor que ▁sh aft ▁manually . ▁When ▁the ▁command ▁and ▁lun ar ▁modules ▁separated ▁for ▁the ▁last ▁time ▁just ▁before ▁re entry , ▁the ▁pro be ▁and ▁forward ▁dock ing ▁ring ▁were ▁py rote chn ically ▁separated , ▁leaving ▁all ▁dock ing ▁equipment ▁attached