Answer Happy

A satellite with mass of 5,500 kg, which includes the propellant for manoeuvres, is in a circular LEO with the altitude of 380 km (orbit 1 in Figure Q5). It has to be transferred to an elliptic orbit with the perigee of 4000 km and the apogee of 23,622 km (orbit 2 in Figure Q5). The specific impulse of the rocket engine is 460 s. B Earth A D 3 Figure Q5 (b) Find the total delta-v for the generalized Hohmann transfer by an orbit 3 started at point A of orbit 1 and ended at the apogee of orbit 2 (point C) (see Figure Q5). [4 marks] (c) Find the total delta-v for the generalized Hohmann transfer by an orbit 4 started at point B of orbit 1 and ended at the perigee of orbit 2 (point D) (see Figure Q5). [4 marks] (d) Find the amount of propellent needed for the transfer through orbit 3 and amount of propellant needed for the transfer through orbit 4. [2 marks] (e) Calculate the semimajor axes and eccentricities for all four orbits. [2 marks]