please use matlab. only matlab. i have tried solving it and i am struggling

Question 2. A single-stage rocket (missile-type) is to be launched for a suborbital flight on a gravity turn trajectory. The rocket and the mission have the following parameters: mo = 21,000 kg Lift-off mass n = 10 Mass ratio T2W = 1.4 Thrust to weight ratio Isp = 2045 Specific impulse Cp = 0.5 Drag coefficient (assumed constant) d = 1.5 m Vehicle diameter 1.225 kg/m Sea level density of atmosphere hscale = 7.5 km Density scale height hrower = 60 m Tower height Po = (a) Prepare a Matlab code for integration of the differential equations (on the first page) describing the gravity turn launch in the curved-Earth model. Account for the atmospheric drag and gravity variation with the altitude. Pitch-over should commence once the rocket has passed the rocket tower at an altitude htower. Below this height hold the flight path angle constant at y = 90 which changes suddenly at h = hrower to the value y