▁ ▁square ▁reflect or . ▁During ▁launch ▁it ▁was ▁fol ded ▁down ▁parallel ▁to ▁the ▁main ▁engine ▁to ▁fit ▁inside ▁the ▁Space craft - to - LM ▁Ad apter ▁( S LA ). ▁After ▁C SM ▁separation ▁from ▁the ▁S LA , ▁it ▁deployed ▁at ▁a ▁right ▁angle ▁to ▁the ▁SM . ▁ ▁Four ▁om n id irection al ▁S - band ▁anten nas ▁on ▁the ▁C M ▁were ▁used ▁when ▁the ▁attitude ▁of ▁the ▁C SM ▁kept ▁the ▁high - g ain ▁anten na ▁from ▁being ▁pointed ▁at ▁Earth . ▁These ▁anten nas ▁were ▁also ▁used ▁between ▁SM ▁j ett ison ▁and ▁landing . ▁ ▁Spec ifications ▁ ▁L ength : ▁▁ ▁Diam eter : ▁▁ ▁Mass : ▁▁ ▁Str ucture ▁mass : ▁▁ ▁Elect rical ▁equipment ▁mass : ▁▁ ▁Service ▁Prop ulsion ▁( SP S ) ▁engine ▁mass : ▁▁ ▁S PS ▁engine ▁prop ell ants : ▁▁ ▁R CS ▁thrust : ▁two ▁or ▁four ▁x ▁▁ ▁R CS ▁Prop ell ants : ▁MM H / N 2 O 4 ▁ ▁S PS ▁engine ▁thrust : ▁▁ ▁S PS ▁engine ▁prop ell ants : ▁( UD M H / N 2 H 4 )/ N 2 O 4 ▁ ▁S PS ▁I SP : ▁ 3 1 4 ▁s ▁( 3 , 1 0 0 ▁N · s / kg ) ▁ ▁Space craft ▁delta ▁v : ▁▁ ▁Elect rical ▁System : ▁three ▁ 1 . 4   k W ▁ 3 0 ▁V ▁DC ▁fuel ▁cells ▁ ▁Mod ifications ▁for