I need help with getting this MatLab program to work

The code I have so far: *Note* not sure what to do with "State" since it was given in the provided code from the school

clc close all

function stateDerivative = parachuteModel(time,state)

state0 = [0]; g=9.81; %Force of gravity rho=1.225; %define the density v0=0; %initial velocity s=0.65; %area S=47.78 cd=0.45; %coefficient of drag cd2=1.45; %coefficient of drag of open parachute m=80; %mass mp=8; %mass of parachute tSpan = [0 20]; %time span given

[Time,Yout] = ode45(@(t,v)(g-rho*v^2*s*cd/(2*m)),tSpan,state0); prev=Yout(1); TerminalVelocity=sqrt((m*g)/(rho/2)*s*cd); %Find terminal velocity

if(tSpan

plot(Time,Yout); xlabel("Time in Seconds"); ylabel("Velocity in Meters/Second"); end

The provided information:

This is a continuation of the discussion during module week 4: The same parachutist with a mass m of 80kg, a cross sectional area S of 0.65 m², a drag coefficient C_D = 0.45 at an atmospheric density at sea level = 1.225kg/m³ has an initial velocity of 0 m/s after dropping out of a balloon. Now, after falling for 15 seconds, he deploys the parachute. Which parameters change? Perform some research to find appropriate cross sectional areas and drag coefficients for civilian and military use. What is the main driver for sizing the parachute?

mV=mg2V2SCD

Update the following program in a way such that at time = 15 s the deployment of the parachute is being accounted for. An "if" statement in the parachute model function is suggested. Plot the velocity vs. time and discuss.

Main Program:

Function:

mV' state0[0 tSpan[0 201; % [m/s] Initial speed % [s] Simulation start and end times time, results] ode45 (@parachuteModel, tSpan, state0) function stateDerivative parachuteModel (time, state) % function to calculate the state derivative of a body exposed to % atmospheric drag and gravity. % state is the velocity in [m/s] 9.81 % % % [m/s^2] [kg] [kg/m^3] m2] Cross Earth's gravity Mass of the parachutist Density of the atmosphere 80; rho1.225: 0.65 ; 0.45: sectional area cd Drag coefficient acceleration -rho/2*s*cd" state*2/m + g; % Acceleration Derivative of the velocity = = stateDerivative[acceleration]; % State Derivative of the Velocity %(multi dimensions must be column vector) end mV' state0[0 tSpan[0 201; % [m/s] Initial speed % [s] Simulation start and end times time, results] ode45 (@parachuteModel, tSpan, state0) function stateDerivative parachuteModel (time, state) % function to calculate the state derivative of a body exposed to % atmospheric drag and gravity. % state is the velocity in [m/s] 9.81 % % % [m/s^2] [kg] [kg/m^3] m2] Cross Earth's gravity Mass of the parachutist Density of the atmosphere 80; rho1.225: 0.65 ; 0.45: sectional area cd Drag coefficient acceleration -rho/2*s*cd" state*2/m + g; % Acceleration Derivative of the velocity = = stateDerivative[acceleration]; % State Derivative of the Velocity %(multi dimensions must be column vector) end