Question

To transfer a satellite from an elliptical orbit into a circular orbit having a radius equal to the apogee distance of the elliptical orbit, then the speed of the satellite should be

• A. increased at the apogee
• B. decreased at the apogee
• C. increased at the perigee
• D. decreased at the perigee

Hint:

Hohmann transfer orbits involve burns at perigee and apogee to adjust orbit shapes.

Answer 1

The Correct Option is A

To circularize an elliptical orbit at apogee, a tangential velocity increment (delta-V) is applied there.