Hand written solution required

Question 5 (a) (1) Explain what is meant by impulse orbital manoeuvre. (li) 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 05). 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. Earth 14 Figure 05 (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 05). [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] Total 14 marksStandard constants: Acceleration due to gravity at sea level, go = 9.81 m s-2 Radius of the Earth (at equator) , RE = 6378 km Earth's gravitational parameter, # = 398,600 km3 s-2 Atmospheric density at sea-level, po = 1.225 kgm- Scale height of the atmosphere, hA = 7.5 km Universal gas constant, R = 8314 J K-1kmol-1