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1 ## Copyright (C) 1997, 2000, 2004, 2005, 2006, 2007 Kai P. Mueller |
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2 ## |
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3 ## This file is part of Octave. |
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4 ## |
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5 ## Octave is free software; you can redistribute it and/or modify it |
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6 ## under the terms of the GNU General Public License as published by |
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7 ## the Free Software Foundation; either version 3 of the License, or (at |
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8 ## your option) any later version. |
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9 ## |
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10 ## Octave is distributed in the hope that it will be useful, but |
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11 ## WITHOUT ANY WARRANTY; without even the implied warranty of |
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12 ## MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
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13 ## General Public License for more details. |
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14 ## |
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15 ## You should have received a copy of the GNU General Public License |
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16 ## along with Octave; see the file COPYING. If not, see |
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17 ## <http://www.gnu.org/licenses/>. |
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18 |
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19 ## -*- texinfo -*- |
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20 ## @deftypefn {Function File} {@var{sys} =} jet707 () |
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21 ## Creates a linearized state-space model of a Boeing 707-321 aircraft |
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22 ## at @var{v}=80 m/s |
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23 ## @iftex |
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24 ## @tex |
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25 ## ($M = 0.26$, $G_{a0} = -3^{\circ}$, ${\alpha}_0 = 4^{\circ}$, ${\kappa}= 50^{\circ}$). |
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26 ## @end tex |
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27 ## @end iftex |
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28 ## @ifinfo |
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29 ## (@var{M} = 0.26, @var{Ga0} = -3 deg, @var{alpha0} = 4 deg, @var{kappa} = 50 deg). |
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30 ## @end ifinfo |
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31 ## |
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32 ## System inputs: (1) thrust and (2) elevator angle. |
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33 ## |
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34 ## System outputs: (1) airspeed and (2) pitch angle. |
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35 ## |
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36 ## @strong{Reference}: R. Brockhaus: @cite{Flugregelung} (Flight Control), Springer, 1994. |
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37 ## @seealso{ord2} |
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38 ## @end deftypefn |
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39 |
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40 ## Author: Kai P. Mueller <mueller@ifr.ing.tu-bs.de> |
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41 ## Created: September 28, 1997 |
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42 |
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43 function outsys = jet707 () |
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44 |
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45 if (nargin != 0) |
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46 print_usage (); |
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47 endif |
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48 if (nargin > 1) |
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49 print_usage (); |
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50 endif |
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51 |
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52 a = [ -0.46E-01, 0.10681415316, 0.0, -0.17121680433; |
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53 -0.1675901504661613, -0.515, 1.0, 0.6420630320636088E-02; |
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54 0.1543104215347786, -0.547945, -0.906, -0.1521689385990753E-02; |
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55 0.0, 0.0, 1.0, 0.0 ]; |
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56 b = [ 0.1602300107479095, 0.2111848453E-02; |
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57 0.8196877780963616E-02, -0.3025E-01; |
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58 0.9173594317692437E-01, -0.75283075; |
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59 0.0, 0.0 ]; |
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60 c = [ 1.0, 0.0, 0.0, 0.0; |
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61 0.0, 0.0, 0.0, 1.0 ]; |
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62 d=zeros(2,2); |
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63 inam = ["thrust"; "rudder"]; |
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64 onam = ["speed"; "pitch"]; |
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65 snam = ["x1"; "x2"; "x3"; "x4"]; |
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66 outsys = ss(a, b, c, d, 0.0, 4, 0, snam, inam, onam); |
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67 |
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68 endfunction |
