Need help on parts a to c, and part c requires MATLAB to do the computation(best to provide both the plot and the code)

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Need help on parts a to c, and part c requires
MATLAB to do the computation(best to provide
both the plot and the code)...

Need Help On Parts A To C And Part C Requires Matlab To Do The Computation Best To Provide Both The Plot And The Code 1 (177.81 KiB) Viewed 26 times

We want to know the maximum height attained by the rocket. Newton's second law applied to this situation gives the following initial value problem: m(t)x"(t) = Fropellant - Fgravity - Fdrag = Fpropellant - 9.81m(t) - 0.5CapAz"(t) sign(x'(t)) (0) - 0 20-0 where Cd is the drag cocfficient of the rocket (0.75), p is the density of air (1.225 kg/m), and A is the cross sectional area of the rocket ( A = Tir ). The radius of the rocket is 0.0208 meters. The function m(l) is the mass of the rocket, which changes in time as the fuel burns up. The sign function is a MATLAB built-in function. (a) Write this second order differential equation as a system of 2 first order differential equations. Include initial conditions for the two dependent variables. (b) The solution to the system of differential equations is a set of functions. In the original context, we have a single differential equation which has a single function as its solution. Which function in your system of equations corresponds to the solution of the original higher-order differential equation? (c) The force from the fuel combustion is modeled: Propellant 601 0<t<0.26 15 0.26 <t<1.65 0 t>1.65 The mass of the rocket m(I) is a function of time since the fuel is consumed during the flight. The function satisfies the following differential equation: m'(t) = ,-0.01515 0<t< 1.65 I > 1.65 The initial mass of the rocket is 0.1536 kg. Note that we now have a system of 3 differential equations. Solve this system with ode45 on a time range from 0 st 15. You will want to write the system of equations as a separate function file since it will involve various if statements. Plot the height of the rocket as a function of time from t = 0 tot = 15. Turn in this plot. Use markers plot(t,y,'-o') to show the points used to make the plot.