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RunModelForTesting.m
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RunModelForTesting.m
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%% Initialization of system model for testing purposes
tic;
Launch_Date = datetime(); %[UTC]
RunTime = 80; %[s]
TimeStep = 10; %[mesh size]
Sat_Starting_True_Anomaly = 0; %[rad]
%% Satellite Orbital Properties
Eccentricity = 0.0007373; %[unitless]
Inclination = 0.9013; %[rad]
Semimajor_Axis = 6775200; %[m]
RAAN = 2.1078; %[rad]
Arg_of_Perigee = 5.495; %[rad]
GMEarth = 3.986004418*10^14; %[m^3 s^-2]
SatOrbitalParameters = OrbitalParametersClass(Eccentricity, Inclination, Semimajor_Axis, RAAN, Arg_of_Perigee, GMEarth);
%% Structural Properties
Inertia_Tensor = [0.0267, 0.03, 0.1; 0.03, 0.1333, 0.01; 0.03, 0.01, 0.1333]; %[kg*m2]
Magnetic_Moment = [0.5, 0.1, 0.1];
Hysteresis_Rod1 = [0.0001, 0.0002, 0.0003];
Hysteresis_Rod2 = [0.0004, 0.0005, 0.0006];
SatStructuralParameters = SatelliteStructuralClass(Magnetic_Moment, Hysteresis_Rod1, Hysteresis_Rod2, Inertia_Tensor);
%% Satellite Attitude Properties
Attitude = [0, 0, 0];
Angular_Velocity = [0, 0, 0];
Angular_Momentum = [0, 0, 0];
SatAttitudeParameters = SatelliteAttitudeClass(Attitude, Angular_Velocity, Angular_Momentum);
%% Power Properties
%% Run System Model
Results = RunModel(Launch_Date, Sat_Starting_True_Anomaly, RunTime, TimeStep, SatOrbitalParameters, SatStructuralParameters, SatAttitudeParameters);
toc;