A Nonlinear, 6 DOF Dynamic Model of an Aircraft: The Research Civil Aircraft Model (RCAM)

In this video we develop a dynamic model of an aircraft by describing forces and moments generated by aerodynamic, propulsion, and gravity that act on the aircraft. This video outlines the analytical models/equations used as well as provides some discussion on the features and phenomenon that are captured in the RCAM model. A separate video discusses how to implement this in Matlab/Simulink.

This model is based on the Research Civil Aircraft Model (RCAM) documented in the following reference:

-Group for Aeronautical Research and Technology in Europe, "Robust Flight Control Design Challenge Problem Formulation and Manual: the Research Civil Aircraft Model (RCAM)", GARTEUR/TP-0883. February 17, 1997 (https://garteur.org) (an older version of the document is located at https://garteur.org/wp-content/report...)

Topics and timestamps:
0:00 – Introduction to the RCAM model
6:48 – Step 1: Control limits/saturation
11:22 – Step 2: Intermediate variables
23:14 – Step 3: Nondimensional aerodynamic force coefficients in Fs
1:00:24 – Step 4: Aerodynamic force in Fb
1:03:31 – Step 5: Nondimensional aerodynamic moment coefficients about AC in Fb
1:14:12 – Step 6: Aerodynamic moment about AC in Fb
1:16:21 – Step 7: Aerodynamic moment about CG in Fb
1:22:41 – Step 8: Propulsion effects
1:31:08 – Step 9: Gravity effects
1:36:15 – Step 10: Explicit first order form

Lecture notes and code can be downloaded from https://github.com/clum/YouTube/tree/...

Errata/Corrections
38:45 – This is improperly written as +11.5 deg, it should be -11.5 deg
1:08:36 – There should be a term cbar/Va multiplying the entire matrix

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