Mercurial > octave-nkf
view scripts/control/system/jet707.m @ 7017:a1dbe9d80eee
[project @ 2007-10-12 21:27:11 by jwe]
author | jwe |
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date | Fri, 12 Oct 2007 21:27:37 +0000 |
parents | 93c65f2a5668 |
children | 59dcf01bb3e3 |
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## Copyright (C) 1997, 2000, 2004, 2005, 2006, 2007 Kai P. Mueller ## ## This file is part of Octave. ## ## Octave 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. ## ## Octave 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 Octave; see the file COPYING. If not, see ## <http://www.gnu.org/licenses/>. ## -*- texinfo -*- ## @deftypefn {Function File} {@var{sys} =} jet707 () ## 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 ## @ifinfo ## (@var{M} = 0.26, @var{Ga0} = -3 deg, @var{alpha0} = 4 deg, @var{kappa} = 50 deg). ## @end ifinfo ## ## 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. ## @seealso{ord2} ## @end deftypefn ## Author: Kai P. Mueller <mueller@ifr.ing.tu-bs.de> ## Created: September 28, 1997 function outsys = jet707 () if (nargin != 0) print_usage (); endif if (nargin > 1) 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, 0.0, 4, 0, snam, inam, onam); endfunction