please solve in matlab code preferably with ODE code like picture hints at

2. You are the propulsion system team lead and need to safely de-orbit a spacecraft from LEO in a 500km circular equatorial orbit. See Figure 2 for the initial orbit and possible impact sites. Assume the trajectory for an impact at Point B would rely on atmospheric burn up to disintegrate the spacecraft, but a portion of the trajectory is over a populated area. A trajectory targeting an impact at Point C would put the spacecraft safely in the ocean, posing no risk should the spacecraft not entirely burn up during ZRT - AE2713 - B20 reentry. Calculate the total propellant expenditure and delta- V for each impact location using finite burn maneuvers. The initial spacecraft mass is 200kg. The onboard propulsion system (OPS) has a thrust of 0.5kN and specific impulse of 280sec. Do you have enough propellant to execute either option? Which impact location is safer, and why? Hint: Remember the thrust is along the velocity vector and this is a burn to decelerate. \{ Partial Ans.: Point B,m=13.5kg. v=0.1914km/s ) \%... Integrate the equations of motion over the burn time: [t,y]=ode45(@finiteburn,[t0t_burn],y); \%... Compute the state vector and mass after the burn: r=[y( end, 1),y(end,2),y( end, 3)]; v=[y(end,4),y( end, 5), y( end, 6)]; m=y(end,7); rne - nrhital olemantc (n v mil)