|
7017
|
1 ## Copyright (C) 1997, 2000, 2004, 2005, 2006, 2007 Kai P. Mueller |
|
3432
|
2 ## |
|
|
3 ## This file is part of Octave. |
|
|
4 ## |
|
|
5 ## Octave is free software; you can redistribute it and/or modify it |
|
7016
|
6 ## under the terms of the GNU General Public License as published by |
|
|
7 ## the Free Software Foundation; either version 3 of the License, or (at |
|
|
8 ## your option) any later version. |
|
3432
|
9 ## |
|
7016
|
10 ## Octave is distributed in the hope that it will be useful, but |
|
|
11 ## WITHOUT ANY WARRANTY; without even the implied warranty of |
|
|
12 ## MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU |
|
|
13 ## General Public License for more details. |
|
3432
|
14 ## |
|
|
15 ## You should have received a copy of the GNU General Public License |
|
7016
|
16 ## along with Octave; see the file COPYING. If not, see |
|
|
17 ## <http://www.gnu.org/licenses/>. |
|
3432
|
18 |
|
|
19 ## -*- texinfo -*- |
|
5016
|
20 ## @deftypefn {Function File} {@var{sys} =} jet707 () |
|
|
21 ## Creates a linearized state-space model of a Boeing 707-321 aircraft |
|
|
22 ## at @var{v}=80 m/s |
|
|
23 ## @iftex |
|
|
24 ## @tex |
|
|
25 ## ($M = 0.26$, $G_{a0} = -3^{\circ}$, ${\alpha}_0 = 4^{\circ}$, ${\kappa}= 50^{\circ}$). |
|
|
26 ## @end tex |
|
|
27 ## @end iftex |
|
|
28 ## @ifinfo |
|
|
29 ## (@var{M} = 0.26, @var{Ga0} = -3 deg, @var{alpha0} = 4 deg, @var{kappa} = 50 deg). |
|
|
30 ## @end ifinfo |
|
|
31 ## |
|
|
32 ## System inputs: (1) thrust and (2) elevator angle. |
|
|
33 ## |
|
|
34 ## System outputs: (1) airspeed and (2) pitch angle. |
|
|
35 ## |
|
7136
|
36 ## @strong{Reference}: R. Brockhaus: @cite{Flugregelung} (Flight |
|
|
37 ## Control), Springer, 1994. |
|
5642
|
38 ## @seealso{ord2} |
|
3432
|
39 ## @end deftypefn |
|
|
40 |
|
|
41 ## Author: Kai P. Mueller <mueller@ifr.ing.tu-bs.de> |
|
|
42 ## Created: September 28, 1997 |
|
|
43 |
|
|
44 function outsys = jet707 () |
|
|
45 |
|
|
46 if (nargin != 0) |
|
6046
|
47 print_usage (); |
|
3432
|
48 endif |
|
7136
|
49 |
|
|
50 a = [-0.46E-01, 0.10681415316, 0.0, -0.17121680433; |
|
|
51 -0.1675901504661613, -0.515, 1.0, 0.6420630320636088E-02; |
|
|
52 0.1543104215347786, -0.547945, -0.906, -0.1521689385990753E-02; |
|
|
53 0.0, 0.0, 1.0, 0.0]; |
|
|
54 |
|
|
55 b = [0.1602300107479095, 0.2111848453E-02; |
|
|
56 0.8196877780963616E-02, -0.3025E-01; |
|
|
57 0.9173594317692437E-01, -0.75283075; |
|
|
58 0.0, 0.0]; |
|
3432
|
59 |
|
7136
|
60 c = [1.0, 0.0, 0.0, 0.0; |
|
|
61 0.0, 0.0, 0.0, 1.0]; |
|
|
62 |
|
|
63 d = zeros(2,2); |
|
|
64 |
|
|
65 inam = {"thrust"; "rudder"}; |
|
|
66 onam = {"speed"; "pitch"}; |
|
|
67 snam = {"x1"; "x2"; "x3"; "x4"}; |
|
|
68 |
|
|
69 outsys = ss (a, b, c, d, 0.0, 4, 0, snam, inam, onam); |
|
3432
|
70 |
|
|
71 endfunction |
