Consider a 200 kg spacecraft orbiting the Earth. The vehicle’sposition at a given time (lets call it time zero), relative to anon-rotating reference frame with origin at Earth’s centre, is r =−5310i + 5040j km. Its velocity vector at time zero is v = −4.85i −6.37j km/s.
Calculate the distance from Earth’s centre to the spacecraft,the speed of the spacecraft, and the specific angular momentum(magnitude and direction) relative to Earth’s centre at timezero.
Calculate the length of the orbit’s semi-major axis, and theorbital period, τ.
Calculate the orbit’s eccentricity, the altitude of the spacecraft at its point of closest approach,
and the angle of the space craft from periapsis at timezero.
