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 ?

Answer

A, D

Explanation

The centripetal force required to move the spaceship in circular orbit is given by
`(mv^2)/(R+h)`, where R=radius of the earth
Here , `(mv^2)/(R+h)=mg` or `(mv^2)/R =mg (because R > h) therefore v^2=gR` or `v=sqrt((gR))`
We know that `v_"escape"=sqrt((2gR))`
Hence, additional velocity imparted to spaceship =`v_"escape"-v=sqrt((2gR))-sqrt((gR))`
`=sqrt((gR))[(sqrt2)-1]=0.41 sqrt(gR) therefore ` n=0.41