For uniform circular motion,centripetal force= mv2/r, where m is mass, v is velocity and r is radius of the circular path.
Also, gravitational force between 2 mass m1 and m2 is given by: Gm1*m2 /r2 , where G is universal gravitational constant, m1 and m2 are the masses and r is distance between them.
Let mass of planet be M and let mass of satellite be m.
Gravitational force provides the necessary centripetal force to the satellite. So,
So, GMm/r2 = mv2/r , where r is radius of the circular path of the satellite.
=>v2 = GM/r => v = (GM/r)1/2
Here,M=8*10^24 kg and r=7.5x10^6+ 3.0x10^7 m = 3.75*10^7 m
So, v=(GM/r)1/2 =[6.67*10-11*8*1024/(3.75*107)]1/2 = 3772.18 m/s
Now,period of orbit = distance/time = 2r/v = 2*3.75*107/( 3772.18) = 62462.41 seconds
= 626462.41/(60*60) hours = 17.35 hours.
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