A spacecraft of mass 1000 kg is in an elliptical orbit about the earth. At point A the spacecraft is at a distance of 1.2 x 10^7 meters form the center of the earth and its velocity ( 7.1 x 10^3 m/s) is perpendicular to the line connecting the center of the earth to the spacecraft. Mass of the earth= 6.0 x 10^24 and radius= 6.4 x 10^4. I need to find the speed of the spacecraft if it is in a CIRCULAR orbit and the minimum speed of the craft at pt. A if it is to escape completely from the earth.
V at point B= 2400 m/s
The Attempt at a Solution
So far, ive figured that the mechanical energy is 8.1 x 10^9 J
Angular momentum= 8.52 x 10^13
and speed at a point directly across from A
V= 2.4 x 10^3