function[state_eq, obser_eq, Nx, Ny, Nu, NparSys, Nparam, NparID, dt, Ndata, Nzi, izhf, ...
             t, Z, Uinp, param, parFlag, x0, iArtifStab, StabMat] = mDefCase10(test_case)

% Definition of model, flight data, initial values etc. 
% test_case = 10 -- Unstable aircraft, short period, Equation decoupling method
% variables:       states  - w, q
%                  outputs - az, w, q
%                  inputs  - de
%
% test_case=10 is similar to the test_case = 8; except for multiplication of
% Z and Uinp with eigTransf=exp(-0.7*t);
%
% Inputs
%    test_case    test case number
%
% Outputs
%    state_eq     function to code right hand sides of state equations       
%    obser_eq     function to code right hand sides of observation equations
%    Nx           number of states 
%    Ny           number of observation variables
%    Nu           number of input (control) variables
%    NparSys      number of system parameters
%    Nparam       total number of system and bias parameters
%    NparID       total number of parameters to be estimated (free parameters)
%    dt           sampling time
%    Ndata        total number of data points for Nzi time segments
%    Nzi          number of time segments (maneuvers) to be analyzed simultaneously
%    izhf         cumulative index at which the maneuvers end when concatenated
%    t            time vector
%    Z            observation variables: Data array of measured outputs (Ndata,Ny)
%    Uinp         input variables: Data array of measured input (Ndata,Nu)
%    param        initial starting values for unknown parameters (aerodynamic derivatives) 
%    parFlag      flags for free and fixed parameters
%    x0           initial conditions on state variables
%    iArtifStab   integer flag to invoke artificial stabilization
%                 = 0: No artificial stabilization
%                 > 0: Artificial stabilization (needs definition of StabMat)
%    StabMat      artificial stabilization matrix; (Nx,Ny); nonzero only for iArtifStab>0           
%

% Constants
d2r   = pi/180;
r2d   = 180/pi;

%----------------------------------------------------------------------------------------
%Model definition
state_eq = 'xdot_TC10_uAC_EigT';       % function for state equations       
obser_eq = 'obs_TC08_uAC';             % function for observation equations
Nx       = 2;                          % Number of states 
Ny       = 3;                          % Number of observation variables
Nu       = 1;                          % Number of input (control) variables
NparSys  = 6;                          % number of system parameters
Nparam   = NparSys;                    % Total number of system and bias parameters
dt       = 0.05;                       % sampling time
iArtifStab= 0;                         % No artificial stabilization
disp(['Test Case = ', num2str(test_case)]);
disp('Unstable aircraft, short period, Eigenvalue Transformation')

%----------------------------------------------------------------------------------------
% Load flight data for Nzi time segments to ba anylzed and concatenate 
load -ascii ..\flt_data\unStabAC_sim.asc;
Nzi  = 1;
data = [unStabAC_sim];     

% Number of data points
Ndata1 = size(unStabAC_sim,1);
izhf   = [Ndata1];
Ndata  = size(data,1);

% Generate new time axis
t = [0:dt:Ndata*dt-dt]';


% Eigenvalue transformation method
sigmaT = 0.7;
eigTransf=exp(-sigmaT*t);

% Observation variables az, w q
Z = [data(:,6).*eigTransf data(:,3).*eigTransf data(:,4).*eigTransf];

% Input variables de
Uinp = [data(:,5).*eigTransf];


% Initial starting values for unknown parameters (aerodynamic derivatives) 
param = [-1.22871D+00; -1.47680;     -4.20491D+00; ... 
          1.16197D-01; -2.70670D+00; -1.87718D+01 ];
% param = [-1.4249D+00-0.7; -1.47680;     -4.20491D+00; ... 
%           1.16197D-01; -2.70670D+00; -1.87718D+01 ];
% Flag for free and fixed parameters
parFlag = [1;  0;  1; ...
           1;  1;  1];

% Total number of free parameters
NparID = size(find(parFlag~=0),1); 

% Initial conditions p0, r0
x0 = [ 0.0; 0.0];

% Artificial stabilization matrix
StabMat    = zeros(Nx,Ny);