Introduction to Aircraft Aeroelasticity and Loads

I

MATLAB/SIMULINK Programs for Flight/Ground Manoeuvres and Gust/Turbulence Encounters

In this appendix, some sample programs for calculation of equilibrium and dynamic manoeuvres, gusts and turbulence, and taxiing and landing are presented.

I.1 RIGID AIRCRAFT DATA

Before proceeding with calculation of results from different manoeuvres and gust/turbulence encounters, the basic aircraft data need to be entered for the rigid or flexible aircraft as appropriate. To save space, the aircraft data will simply be specified for a sample case; clearly, in a normal programme, the reader may choose to enter some parameters via a dialogue and to introduce loops to cover multiple cases (e.g. of air speed). Note that units used throughout for defining data are in N, kg, m, s and rad. Wherever possible, the symbols used in the code below aim to match those used in the main text, with the use of the underscore symbol _ indicating a subscript to follow; therefore, for example, m_W in MATLAB is equivalent to m_W in the text.

% Data for Symmetric Aircraft close all; clear all % Mass and Dimensions m = 10000; W = m * 9.81; m_F = 0.15 * m; m_W = 0.3 * m; m_C = 0.4 *m; m_T = 0.15 * m; S_W = 30.0; S_T = 7.5; s = 7.5; c = 2.0; s_tp = 3.0; c_tp = 1.25; l_W = 0.3*c; l_T = 3.5 * c; l_A = 0.125 * c; l_E = 0.125 * c; l_WM = l_W - l_A - l_E; l_M = 0.375 * c; l_F = (m_T * l_T- m_W * l_WM) / m_F; l_WT = l_W + l_T; l_N = l_F; l_M = 0.375 * c ; mu = m_W / 2 / s; % Moments of Inertia I_y_fuse = m_F * l_F^2 + m_T ...