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statesetup2.m
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Copyright (C) 1999, 2007 Tomas Melin
%
% This file is part of Tornado
%
% Tornado 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 2, or (at your option) any later version.
%
% Tornado 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 Tornado; see the file GNU GENERAL
% PUBLIC LICENSE.TXT. If not, write to the Free Software
% Foundation, 59 Temple Place -Suite 330, Boston, MA
% 02111-1307, USA.
%
% usage: [STATE]=statesetup(STATE)
%
% Enables a user to manipulate the STATE structure.
%
% Example:
%
% [state]=statesetup(state);
%
% Calls:
% questions Contain user interface queries in string format.
% terror Displays various Error messages.
% isinptok Checks format of imput.
% ISAtmosphere Table inter polation of standard atmosphere.
%
% Author: Tomas Melin <[email protected]>
% Keywords: Tornado text based user interface
%
% Revision History:
% Bristol, 2007-06-27: Addition of new header. TM
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
function [state]=statesetup(state);
settings=config('startup');
q2=questions(4);
if isempty(q2)
q2=0;
terror(9)
end
switch q2
%% Load file
case 2
ok=0;
while ok==0;
try
cd(settings.sdir)
disp(' ')
ls
fname=input('Load file: ','s');
load(fname);
cd(settings.hdir)
ok=1;
catch
cd(settings.hdir)
terror(4)
ok=1;
end
end
%% Create State
case 1
disp(' ')
disp(' ')
stepper=0;
while stepper<99
switch stepper
case -1
stepper=1;
case 0
data=input('Alpha [deg]: ','s');
if isinptok(data)==1;
state.alpha=str2num(data)*pi/180;
end
case 1
data=input('Beta [deg]: ','s');
if isinptok(data)==1;
state.betha=str2num(data)*pi/180;
end
case 2
data=input('Roll angular velocity [deg/s]: ','s');
if isinptok(data)==1;
state.P=str2num(data)*pi/180;
end
case 3
data=input('Pitch angular velocity [deg/s]: ','s');
if isinptok(data)==1;
state.Q=str2num(data)*pi/180;
end
case 4
data=input('Yaw angular velocity [deg/s]: ','s');
if isinptok(data)==1;
state.R=str2num(data)*pi/180;
end
case 5
data=input('Angle of attack time derivative, (Alpha_dot), [deg/s]:','s');
if isinptok(data)==1;
state.adot=str2num(data)*pi/180;
end
case 6
data=input('Angle of sideslip time derivative, (Beta_dot), [deg/s]:','s');
if isinptok(data)==1;
state.bdot=str2num(data)*pi/180;
end
case 7
speedtype=questions(11);
disp(' ')
%% Different speedtypes
switch speedtype
%International units
case 1
data=input('True airspeed [m/s]: ','s');
if isinptok(data)==1;
state.AS=str2num(data);
state.rho=1.225;
state.ALT=0;
end
case 2
data=input('True airspeed [m/s]: ','s');
if isinptok(data)==1;
state.AS=str2num(data);
end
data2=input('Altitude [m]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2);
state.rho=ISAtmosphere(state.ALT);
end
disp(' ')
case 3
data=input('Equivalent airspeed [m/s]: ','s');
if isinptok(data)==1;
groundspeed=str2num(data);
end
data2=input('Altitude [m]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2);
state.rho=ISAtmosphere(state.ALT);
end
state.AS=sqrt(ISAtmosphere(0)*groundspeed^2/state.rho);
case 4
data=input('Calibrated airspeed [m/s]: ','s');
gamma=1.4;
if isinptok(data)==1;
speed=str2num(data);
end
data2=input('Altitude [m]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2);
[state.rho a p_1]=ISAtmosphere(state.ALT);
end
p_0=p_1+(101300)*(((((speed^2*(gamma-1))/(2*340.3^2))+1)^((gamma)/(gamma-1)))-1);%Stagnation pressure
state.AS=sqrt(2*a^2/(gamma-1)*((p_0/p_1)^((gamma-1)/(gamma))-1)); %True airspeed
case 5
data=input('Mach number [-]: ','s');
if isinptok(data)==1;
speed=str2num(data);
end
if speed>0.3
terror(15)
end
data2=input('Altitude [m]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2);
[state.rho a]=ISAtmosphere(state.ALT);
end
state.AS=speed*a;
disp(' ')
%%Imperial
case 6
data=input('True airspeed [kts]: ','s');
if isinptok(data)==1;
state.AS=str2num(data)*1852/3600;
end
data2=input('Altitude [ft]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2)*0.3048;
state.rho=ISAtmosphere(state.ALT);
end
disp(' ')
case 7
data=input('Equivalent airspeed [kts]: ','s');
if isinptok(data)==1;
groundspeed=str2num(data)*1852/3600;
end
data2=input('Altitude [ft]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2)*0.3048;
state.rho=ISAtmosphere(state.ALT);
end
state.AS=sqrt(ISAtmosphere(0)*groundspeed^2/state.rho);
case 8
data=input('Calibrated airspeed [kts]: ','s');
gamma=1.4;
if isinptok(data)==1;
speed=str2num(data)*1852/3600;
end
data2=input('Altitude [ft]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2)*0.3048;
[state.rho a p_1]=ISAtmosphere(state.ALT);
end
p_0=p_1+(101300)*(((((speed^2*(gamma-1))/(2*340.3^2))+1)^((gamma)/(gamma-1)))-1);%Stagnation pressure
state.AS=sqrt(2*a^2/(gamma-1)*((p_0/p_1)^((gamma-1)/(gamma))-1)); %True airspeed
case 9
data=input('Mach number [-]: ','s');
if isinptok(data)==1;
speed=str2num(data);
end
if speed>0.3
terror(15)
end
data2=input('Altitude [ft]: ','s');
if isinptok(data2)==1;
state.ALT=str2num(data2)*0.3048;
[state.rho a]=ISAtmosphere(state.ALT);
end
state.AS=speed*a;
end
%% Back to ordinary state
case 8
disp(' ')
disp('Caution, only use this option if you are sure, really sure, what you are doing.')
data=input('Apply Prandtl-Glauert Correction [0 1]: ','s');
if isinptok(data)==1;
state.pgcorr=str2num(data);
stepper=100;
end
disp(' ')
end%caseblock
if isinptok(data)==1
stepper=stepper+1;
elseif isinptok(data)==-1
stepper=stepper-1;
elseif isinptok(data)==-2
stepper=99;
else
end
end %whileblock
%state.rho=config('rho'); %standard sealevel density
%% Save State
case 3
disp(' ');
disp(' ');
disp(' ');
cd(settings.sdir)
sfname=input('Save state as file: ','s');
if isempty(sfname)==1;
disp('+++ no name, not saved +++')
cd(settings.hdir)
else
save(sfname,'state');
cd(settings.hdir)
disp(' ');
disp('*** File Saved. ****');
end
%% CHANGE ALPHA
case(4)
disp(' ');
disp(' ');
disp('Changing alpha ');
disp(strcat('Current alpha is: ',num2str(state.alpha*180/pi),' degrees.'))
state.alpha=input('New alpha [deg]: ')*pi/180;
%% exiting menu
case 0
stat=1;
return
otherwise
terror(9);
stat=1;
return
end
stat=0;