STK_and_MATLAB.m

clear; clc;

%% Open STK and create a new scenario
%Create an instance of STK
app = actxserver('STK11.application');
app.Visible = 1;

%% Get our IAgStkObjectRoot interface
root = app.Personality2;

%% Create new Scenario
root.NewScenario('Matlab_Training_Scenario');
sc = root.CurrentScenario;

%% Set Scenario Analysis Interval
sc.SetTimePeriod('10 Jun 2016 04:00:00', '11 Jun 2016 04:00:00');
root.Rewind();

%% Insert Facility and set its position
fac = sc.Children.New('eFacility', 'codeFacility');
fac.Position.AssignGeodetic(38.9943,-76.8489,0);

%% Insert Satellite and set its orbital elements
sat = sc.Children.New('eSatellite', 'codeSat');

sat.Propagator.InitialState.Epoch = '08 Jun 2016 15:14:26';
satProp = sat.Propagator.InitialState.Representation.ConvertTo('eOrbitStateClassical'); % Use the Classical Element interface
satProp.SizeShapeType = 'eSizeShapeMeanMotion';  % Changes from SMA/Ecc to MeanMotion/Ecc
satProp.LocationType = 'eLocationMeanAnomaly'; % Makes sure Mean Anomaly is being used
satProp.Orientation.AscNodeType = 'eAscNodeRAAN'; % Use RAAN instead of LAN for data entry

%Set unit preferences for revs/day
root.UnitPreferences.Item('Angle').SetCurrentUnit('revs');
root.UnitPreferences.Item('Time').SetCurrentUnit('day');

% Assign the perigee and apogee altitude values:
satProp.SizeShape.MeanMotion = 15.08385840;   % revs/day
satProp.SizeShape.Eccentricity = 0.0002947;   % unitless

%Return unit preferences for degrees and seconds
root.UnitPreferences.Item('Angle').SetCurrentUnit('deg');
root.UnitPreferences.Item('Time').SetCurrentUnit('sec');

% Assign the other desired orbital parameters:
satProp.Orientation.Inclination = 28.4703;    % deg
satProp.Orientation.ArgOfPerigee = 114.7239;  % deg
satProp.Orientation.AscNode.Value = 315.1965; % deg
satProp.Location.Value = 332.9096;            % deg

% Apply the changes made to the satellite's state and propagate:
sat.Propagator.InitialState.Representation.Assign(satProp);
sat.Propagator.Propagate;

%% Output LLA of sat using access times
dp = sat.DataProviders.Item('Cartesian Velocity').Group.Item('J2000');
res = dp.ExecElements(sc.StartTime, sc.StopTime, 60, {'Time'; 'x'; 'y'; 'z';});
time = res.DataSets.GetDataSetByName('Time').GetValues;
x = res.DataSets.GetDataSetByName('x').GetValues;
y = res.DataSets.GetDataSetByName('y').GetValues;
z = res.DataSets.GetDataSetByName('z').GetValues;

%