Write a MATLAB .m file that solves the equations below for the missile trajectory from a given set of initial conditions. Use t = 0.005 s. The function should have the following header: function [T, X, Y, Z, U, V, W] = missile(X0, Y0, Z0, m0, mf, Thmag0, theta, phi, Tburn) where the inputs are the initial position, initial and landing mass, initial thrust magnitude, launch angles and burn time of the missile. All inputs are scalars while all outputs are vectors. You need to simulate until the missile lands on the terrain. Use the MATLAB built-in function "interp2."

Equations:

Where the call format for mass is [m] = mass(t, m0, mf, Tburn), Thrust is [Th_x, Th_y, Th_z] = thrust(t, Thmag0, theta, phi, Tburn, u, v, w), and Drag Coefficient is [Cd] = drag_coeff(Vmag).

Th-an pA U2 V2 W V2 At Un Un din n+1 2mm man Th yn. pA V, U2 V2 W2 At din n+1 2m. man Th 2n pA g At W, d.ns n+1 2mn man At Xn U, n+1 n+1 At n+1 n-+1 Zn Zn Wnti At n+1 (2) where subscript n denotes variables at current time, subscript n variables at time that is At ahead. Note that Th-an, Th-yn and Th-zn on the right-hand-side are the three components of the thrust at the nth time step