Aircraft simulation using MATLAB and Python

#aeronauticalengineering #aircraftsimulation #MATLAB #Python
This tutorial walks through the program to simulate the longitudinal equations of motion of an aircraft in MATLAB and Python.
Link to the aerodynamic and geometric data of the Convair aircraft: ntrs.nasa.gov/archive/nasa/ca...
MATLAB flight simulation script:
Python flight simulation script:

[@yashaswiniravi2801]

Very informative video! Do more such videos :)

[@bundeligeetsanrakshan3246]

We may not require any of these quantities, W, m, Iyy, S, MAC, Q, etc. as you are directly taking the values of Xa, Xu, Xw, Za, Zu, Zw, Ma, Mw, Mq, etc. These quantities are only required when you are using coefficients of the derivatives and converting them to the dimensional derivatives in this case your direct values.

[@fidgetrunner6251]

@avion dock where did you find the xalpha zalpha and malpha variables in the document? I could not find them.

[@madhavvenkatesh6782]

can you post the scripts in the description? They are not there.

[@gregbarnhouse8923]

The scripts links are blank?

[@bundeligeetsanrakshan3246]

You have chosen density rho = 1.225Kg/m^3 which is at sea level but your flying altitude is h = H = 23000*0.3048, which is incorrect. Density decreases with altitude.

[@bundeligeetsanrakshan3246]

I am solving for non-linear 6dof equations and I am getting all solutions straight lines for different initial conditions. Why?
I checked with function (aircraft_EOM()) values it has different values then it is given out. Why is that they must be same.
In a function I am solving 12 variables 12 non-linear equations for aircraft! Why I am getting the error could you please help me!
You video is very helpful! Thank you for the video.

[@universo_desconocido]

Hi mate, I would love to ask you some questions if you are still active on RUclips

[@bundeligeetsanrakshan3246]

@@universo_desconocido Thank you for your reply sir. The reason for the error is due to pitching angle goes near to 90degrees and cos term was on denominator. I implemented the solution by giving the condition, if theta = 90, change it to 89degrees or slightly more close to 90 degrees.
Other than aircraft nonlinear equations of motion, I have developed the similar code for Airship nonlinear equations of motion.
Thank you for your reply sir.

[@EM-xq9ts]

Great thanks? can you give sousce code&