For this problem, earth’s orbit around the sun is elliptical, with a = 149.6 × 10⁶ km and e = 0.0167. on a date when the earth was 147.4 × 10⁶ km from the sun, a spacecraft parked in a 200- km altitude circular earth orbit was launched directly into an elliptical orbit around the sun with perihelion radius of 120 × 10⁶ km and aphelion radius equal to the earth’s distance from the sun on the launch date.
find v[infinity] required on the departure hyperbolic orbit at earth