Question

Question #5ba10

Answer 1

please see below

Explanation:

If we apply Newton's law, the force due to gravity will be
`F=(GMm)/r^2`

The satellite moves in a circular orbit, and the centripetal force must be provided by the gravitational force. So for a stable orbit
`F=(mv^2)/r=(GMm)/r^2`

So if the velocity is too high, then

`(mv^2)/r>(GMm)/r^2`

The force of gravity is insufficient to maintain the satellite in a circular orbit and the satellite will "fly off into space" unless it can be directed into an orbit of lower radius.

Or seen another way, rearranging the above equations gives:
`GM=r*v^2`
Since `GM` is constant, if `v` is too high, `r` must be reduced (or the satellite will not maintain its orbit).

If velocity is too low:
`(mv^2)/r<(GMm)/r^2`
The force gravity exceeds the centripetal force required. Unless the orbit can be moved to a larger radius (reducing the force of gravity until the above are in equilibrium), the satellite will spiral in towards the earth.