8.7 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 of 120(106) km and aphelion equal to the earth’s distance from the sun on the launch date. Calculate the delta-v required and v[infinity] of the departure hyperbola. {Ans.: Δv 1⁄4 3.34 km/s, v[infinity] 1⁄4 1.579 km/s}