How to plot the Tsiolkovsky rocket equation for a multi stage rocket

Hello! I am looking to plot the Tsiolkovsky rocket eqution as a funcion of time for a multi stage rocket. I found the total delta-V:

g0 = 9.81; % [m/s^2]

%Stage 1

Isp1 = 284; % Specific Impulse [sec]

bt1 = 56.5; % Burn Time [sec]

mp1 = 45400; % Propellant Mass [kg]

ms1 = 3600; % Structural Weight [kg]

Z1 = 0.93; % Prop mass fraction

C1 = Isp1*g0; %Exhaust Velocity

F1 = (mp1/bt1)*C1; % Thrust

%Stage 2

Isp2 = 308; % Specific Impulse [sec]

bt2 = 61; % Burn Time [sec]

mp2 = 24500; % Propellant Mass [kg]

ms2 = 3200; % Structural Weight [kg]

Z2 = 0.88; %Prop mass fraction

C2 = Isp2*g0;

F2 = (mp2/bt2)* C2;

%Stage 3

Isp3 = 300; % Specific Impulse [sec]

bt3 = 72; % Burn Time [sec]

mp3 = 7080; % Propellant Mass [kg]

ms3 = 650; % Structural Weight [kg]

Z3 = 0.92; %Prop mass fraction

C3 = Isp3*g0;

F3 = (mp3/bt3)* C3;

%Stage 4

Isp4 = 292; % Specific Impulse [sec]

bt4 = 84.1; % Burn Time [sec]

mp4 = 2010; % Propellant Mass [kg]

ms4 = 155; %Structural Weight [kg]

Z4 = 0.93; %Prop mass fraction

C4 = Isp4*g0

F4 = (mp4/bt4)* C4;

% Total

m_prop_0 = 78990; % kg

m_s_0 = 7605;

m_lift = 88432; % kg lift off mass

mpl = 1837; % kg

delta_V_1 = (g0*Isp1)*log(1/(1-Z1))

delta_V_2 = (g0*Isp2)*log(1/(1-Z2));

delta_V_3 = (g0*Isp3)*log(1/(1-Z3));

delta_V_4 = (g0*Isp4)*log(1/(1-Z4));

Delta_V_total = delta_V_1 + delta_V_2 + delta_V_3 + delta_V_4 % [m/s]

I am given the burn time for each sub-rocket, but I have no idea how to approach this next.

Answer 1

[Rohit Pappu]

Please refer top this link for reference

[Christina Reid]

Thank you!