Add a useful package (from Source forge) for octave

[CreaPhase.git] / octave_packages / control-2.3.52 / Boeing707.m

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+## Copyright (C) 1997, 2000, 2004, 2005, 2006, 2007 Kai P. Mueller
+##
+##
+## This program is free software; you can redistribute it and/or modify it
+## under the terms of the GNU General Public License as published by
+## the Free Software Foundation; either version 3 of the License, or (at
+## your option) any later version.
+##
+## This program is distributed in the hope that it will be useful, but
+## WITHOUT ANY WARRANTY; without even the implied warranty of
+## MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the GNU
+## General Public License for more details.
+##
+## You should have received a copy of the GNU General Public License
+## along with this program; see the file COPYING.  If not, see
+## <http://www.gnu.org/licenses/>.
+
+## -*- texinfo -*-
+## @deftypefn {Function File} {@var{sys} =} Boeing707 ()
+## Creates a linearized state-space model of a Boeing 707-321 aircraft
+## at @var{v}=80 m/s 
+## @iftex
+## @tex
+## ($M = 0.26$, $G_{a0} = -3^{\\circ}$, ${\\alpha}_0 = 4^{\\circ}$, ${\\kappa}= 50^{\\circ}$).
+## @end tex
+## @end iftex
+## @ifnottex
+## (@var{M} = 0.26, @var{Ga0} = -3 deg, @var{alpha0} = 4 deg, @var{kappa} = 50 deg).
+## @end ifnottex
+##
+## System inputs: (1) thrust and (2) elevator angle.
+##
+## System outputs:  (1) airspeed and (2) pitch angle.
+##
+## @strong{Reference}: R. Brockhaus: @cite{Flugregelung} (Flight
+## Control), Springer, 1994.
+## @end deftypefn
+
+## Author: Kai P. Mueller <mueller@ifr.ing.tu-bs.de>
+## Created: September 28, 1997
+
+function outsys = Boeing707 ()
+
+  if (nargin != 0)
+    print_usage ();
+  endif
+
+  a = [-0.46E-01,            0.10681415316, 0.0,   -0.17121680433;
+       -0.1675901504661613, -0.515,         1.0,    0.6420630320636088E-02;
+        0.1543104215347786, -0.547945,     -0.906, -0.1521689385990753E-02;
+        0.0,                 0.0,           1.0,    0.0];
+
+  b = [0.1602300107479095,      0.2111848453E-02;
+       0.8196877780963616E-02, -0.3025E-01;
+       0.9173594317692437E-01, -0.75283075;
+       0.0,                     0.0];
+
+  c = [1.0, 0.0, 0.0, 0.0;
+       0.0, 0.0, 0.0, 1.0];
+
+  d = zeros (2, 2);
+
+  inam = {"thrust"; "rudder"};
+  onam = {"speed"; "pitch"};
+  ## snam = {"x1"; "x2"; "x3"; "x4"};
+
+  outsys = ss (a, b, c, d, "inname", inam, "outname", onam);
+
+endfunction