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Question 5 (a) (i) Explain what is meant by impulse orbital manoeuvre. (ii) What types of rocket engine can be used for an impulse orbital manoeuvre? [2 marks] 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. 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 QS). [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] Total 14 marks