function [state_eq, obser_eq, Nx, Ny, Nu, NparSys, Nparam, NparID, dt, Ndata, ...
                   t, Z, Uinp, param, parFlag, x0, iSD, SDyError, output_file] = mDefCase04cm(test_case, target_log)

% Definition of model, flight data, initial values etc. 
% test_case = 4 -- Longitudinal motion: HFB-320 Aircraft
% Nonlinear model in terms of non-dimensional derivatives as function of
% variables in the stability axes (V, alfa):   
%                  states  - V, alpha, theta, q
%                  outputs - V, alpha, theta, q, qdot, ax, az
%                  inputs  - de, thrust  
%
% 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
%    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
%    iSD          Flag to specify optionally initial R (default; 0) 
%    SDyError     standard-deviations of output errors to compute initial covariance
%                 matrix R (required only for iSD ~= 0)

if (nargin < 1), target_log = 0; end

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

%----------------------------------------------------------------------------------------
% Model definition
state_eq   = 'xdot_TC04b_hfb_lon';       % Function for state equations       
obser_eq   = 'obs_TC04c_hfb_lon';        % Function for observation equations
Nx         = 4;                          % Number of states 
Ny         = 6;                          % Number of observation variables
Nu         = 1;                          % Number of input (control) variables
NparSys    = 10;                         % Number of system parameters
Nparam     = NparSys + Nx;               % Total number of parameters to be estimated
dt         = 0.02;                       % Sampling time
iSD        = 0;                          % Initial R option (default; 0) 

disp(['Test Case = ', num2str(test_case)]);
disp('Longitudinal motion, nonlinear model -- Business Jet R/C without dt: Nx=4, Ny=6, Nu=1')

%----------------------------------------------------------------------------------------
% Load flight data for Nzi time segments to be analyzed and concatenate 
log_file = sprintf('../CVS_IGNORE/flight_log_true.csv');
output_file = sprintf('../CVS_IGNORE/FEM_out_true_%d.csv', test_case);
if target_log > 0,
  log_file = sprintf('../CVS_IGNORE/flight_log_%03d.csv', target_log - 1);
  output_file = sprintf('../CVS_IGNORE/FEM_out_%03d_%d.csv', target_log - 1, test_case);
end

disp(['Target file = ', log_file]); 
data = load(log_file);

% Number of data points
Ndata = size(data,1);
izhf  = Ndata;

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

% Observation variables V, alpha, theta, q, axcg, azcg
Z = [data(:,3),data(:,4),data(:,5),data(:,6),data(:,8),data(:,9)];

% Input variables de
Uinp = [data(:,2)];

% Initial starting values for unknown parameters (aerodynamic derivatives) 
% Xu, Xa, Zu, Za, Zq, Zde, Mu, Ma, Mq, Mde, f11, f22, f33, f44                                                 
param = [-3.00000D-01; 2.00000D+00; ...
         -1.00000D-00; -1.00000D+02; -3.00000D-00; -9.00000D-00; ...
          0.00000D-00; -4.00000D+01; -8.00000D-00; -1.00000D+02; ...
          1.00000D-04;  1.00000D-08;  1.00000D-08;  1.00000D-06]; % 真値の場合
if target_log > 0,
  param = [-1.00000D+00; 1.00000D+01; ...
           -1.00000D+01; -1.00000D+02; -1.00000D+01; -1.00000D+01; ...
            1.00000D-02; -1.00000D+02; -1.00000D+01; -1.00000D+02; ...
            1.00000D+00;  1.00000D-02;  1.00000D-02;  1.00000D+00];
end

% Flags for free and fixed parameters
parFlag = [1; 1; ...
           1; 1; 1; 1; ...
           1; 1; 1; 1; ...
           0; 0; 0; 0]; % 真値の場合
if target_log > 0,
  parFlag = [1; 1; ...
             1; 1; 1; 1; ...
             1; 1; 1; 1; ...
             1; 1; 1; 1];
end
       
% Total number of free parameters
NparID = size(find(parFlag~=0),1); 

% Initial conditions on state variables u, alpha, theta, q
x0 = [3; 1*d2r; 1*d2r; 1*d2r];

% Initial R: Default (iSD=0) or specified as standard-deviations of output errors 
SDyError = [];
% SDyError = zeros(Ny,1);
% iSD = 1;
% SDyError = [.....]';     % if iSD=1, specify SD for Ny outputs

% トリム状態における対気速度[m/s], 下方向速度[m/s], ピッチ角(安定軸), ピトー管オフセット
global stables;
stables = [17.0; 0; 0 * d2r; 0];