% Orbital Settings
ID = 33500;                             % [int] TLE object identifier. See ./utils/getSatelliteTLE.m to add different orbits.
dtUTC = datetime('now', 'TimeZone','Z');% dtUTC = datetime(2023, 5, 25, 12, 0, 0, 'TimeZone', 'Z'). The date influences position in orbit and sun vector calculation.

number_orbits = 1;                      % [double]  Number of orbits to simulate
sunV_ECI = approxECISunPosition(dtUTC); % Sun Vector Settings [x,y,z] unit vector. NOTE: KHI project special request sun vector can be found in section "Obtain sun vector" (~line 200)
sunV_ECI = sunV_ECI/norm(sunV_ECI);     % Or enter your own vector. Example: sunV = [1,0,0];

% Tumble Motion Settings
Q_import = false;                       % [boolean] If importing tumble motion data set to true
% If importing tumble data (Q_import = true)
import_filename = 'gravity_gradient_motion_array.mat'; % File path of the data to be imported
import_time_step = 1;                   % [s] The imported data has a timestep that may be different than our requested timestep
% If generating tumble data (Q_import = false)
q_initial = [1,0,0,0]';                 % Initial attitude quaternion [qw, qx, qy, qz]' 
w_initial = [0,0,0,pi()/180]';          % [0, wx, wy, wz]' [rad/s] initial relative rotation
dt = 0.1;                               % [s] simulation timestep (4th order Runge-Kutta) <--- NOTE: time_step >= dt
sim_plot = true;                        % [boolean] whether to show the energy and angular velocity plots
sim_viewer = false;                     % [boolean] whether to show the orientation viewer (NOTE: the program will not continue while the viewer is running)
I = [27548.8, 0,       0;               % [kgm2] object inertia matrix
     0,       27675.3, 0; 
     0,       0,       6808.8];