For a satellite revolving around the Earth in a circular orbit, it can be written that
rmv2=r2GMm...(1) (r=R+h is the distance from the centre of the Earth)
Simplify equation (1) to obtain the linear speed of the satellite.
v=rGM
Thus, the angular momentum of the satellite is given by
L===mvrmrrGMmGMr...(2)
Similarly, for distance r′ from the centre of the Earth, the angular momentum is given by
L′=mGMr′...(3)
Divide equation (3) by equation (2) to obtain the required angular momentum.
LL′==mGMrmGMr′rr′...(4)
Now, r′=r+8r=9r
Substitute the known values of the parameters into equation (4) to obtain the required angular momentum.
LL′=⇒9L′=3L