The problem concerns a spacecraft in a circular Earth orbit of altitude 630km. The Gravitatational constant 6.673 x 10^-11. Mass of the earth 5.972x10^24. Radius of the earth 6738km. Eccentricity 0.0867.
A delta-V of +320 m/s is applied in the prograde direction.
What are the altitude of periapsis and altitude of apoapsis after the burn?