A satellite is launched into a circular orbit close to the earth's surface. What additional velocity has new to be imparted to the satellite in the orbit to overcome the gravitational pull ?

Explanation

Since, orbital velocity near earth's surface, `v_(o) = sqrt(gR_(e))`
Escape velocity, `v_(e)=sqrt(2gR_(e))=1.414 sqrt(gR_(e))`
Therefore, additional velocity required
`=v_(e)-v_(o)=(1.414-1)sqrt(gR_(e))`
`=0.414sqrt(9.8xx6400xx10^(3))`
`=3.278xx10^(3) "ms"^(-1)`
`=3.378 "kms"^(-1)`.