Energy Conservation in Elliptical Orbits
A 400 kg satellite is in an elliptical orbit around a planet. The satellite has a total mechanical energy of -4.0×10^9 J and an angular momentum of 2.4×10^11 kg·m²/s. What is the change in the satellite’s kinetic energy as it moves from perigee to apogee?
A
Zero, as mechanical energy is conserved
B
Equal to the change in potential energy but opposite in sign
C
Dependent only on the change in orbital radius
D
Equal to the change in potential energy
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