|
3432
|
1 ## Copyright (C) 1997 Kai P. Mueller |
|
|
2 ## |
|
|
3 ## This file is part of Octave. |
|
|
4 ## |
|
|
5 ## Octave is free software; you can redistribute it and/or modify it |
|
|
6 ## under the terms of the GNU General Public License as published by the |
|
|
7 ## Free Software Foundation; either version 2, or (at your option) any |
|
|
8 ## later version. |
|
|
9 ## |
|
|
10 ## Octave is distributed in the hope that it will be useful, but WITHOUT |
|
|
11 ## ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or |
|
|
12 ## FITNESS FOR A PARTICULAR PURPOSE. See the GNU General Public License |
|
|
13 ## for more details. |
|
|
14 ## |
|
|
15 ## You should have received a copy of the GNU General Public License |
|
|
16 ## along with Octave; see the file COPYING. If not, write to the Free |
|
|
17 ## Software Foundation, 59 Temple Place, Suite 330, Boston, MA 02111 USA. |
|
|
18 |
|
|
19 ## -*- texinfo -*- |
|
3500
|
20 ## @deftypefn {Function File} {} jet707 () |
|
3432
|
21 ## Creates linearized state space model of a Boeing 707-321 aircraft |
|
|
22 ## at v=80m/s. (M = 0.26, Ga0 = -3 deg, alpha0 = 4 deg, kappa = 50 deg) |
|
|
23 ## System inputs: (1) thrust and (2) elevator angle |
|
|
24 ## System outputs: (1) airspeed and (2) pitch angle |
|
|
25 ## Ref: R. Brockhaus: Flugregelung (Flight Control), Springer, 1994 |
|
|
26 ## @end deftypefn |
|
|
27 ## @seealso{ord2} |
|
|
28 |
|
|
29 ## Author: Kai P. Mueller <mueller@ifr.ing.tu-bs.de> |
|
|
30 ## Created: September 28, 1997 |
|
|
31 |
|
|
32 function outsys = jet707 () |
|
|
33 |
|
|
34 if (nargin != 0) |
|
|
35 usage("outsys = jet707()") |
|
|
36 endif |
|
|
37 if (nargin > 1) |
|
|
38 usage("outsys = jet707()") |
|
|
39 endif |
|
|
40 |
|
|
41 a = [ -0.46E-01, 0.10681415316, 0.0, -0.17121680433; |
|
|
42 -0.1675901504661613, -0.515, 1.0, 0.6420630320636088E-02; |
|
|
43 0.1543104215347786, -0.547945, -0.906, -0.1521689385990753E-02; |
|
|
44 0.0, 0.0, 1.0, 0.0 ]; |
|
|
45 b = [ 0.1602300107479095, 0.2111848453E-02; |
|
|
46 0.8196877780963616E-02, -0.3025E-01; |
|
|
47 0.9173594317692437E-01, -0.75283075; |
|
|
48 0.0, 0.0 ]; |
|
|
49 c = [ 1.0, 0.0, 0.0, 0.0; |
|
|
50 0.0, 0.0, 0.0, 1.0 ]; |
|
|
51 d=zeros(2,2); |
|
|
52 inam = ["thrust"; "rudder"]; |
|
|
53 onam = ["speed"; "pitch"]; |
|
|
54 snam = ["x1"; "x2"; "x3"; "x4"]; |
|
4771
|
55 outsys = ss(a, b, c, d, 0.0, 4, 0, snam, inam, onam); |
|
3432
|
56 |
|
|
57 endfunction |
