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PE of satellite at altitude 2 R  =  - G M m / 3 R
KE of satellite in orbit of radius 3R =  1/2 m v²

m v² / R  = centripetal force = G m M / R²
v² = G M / R

Total Energy of satellite in orbit =  - GM m / 3R + 1/2 m G M /R
                                             =  - 2 G M m / 3 R
This is the minimum energy required to launch the satellite

1 5 1
There is 1 correction..
-GMm/3R-GMm/2R-_ -5GMm/6R..dis is r8 ans...but thanx 4 ur dirction..
total energy on surface of Planet M: KE - GMm/R. PE of m in orbit: -GMm/3R. KE in orbit +GMm/6R. Total Energy in orbit = 1/2 PE. Energy required: GMm/R(1-1/6) = 5/6 GMm/R