Problem with extracting STK object reports using MATLAB

[odegreeangle]

Dear everybody,
I am struggling with a problem that I have with extracting STK data. I developed a walker satellite constellation by using MATLAB but i am unable to extract objects data and report from STK. I can extract base satellite (that I defined primarily) data by using Dataproviders command. but there is no way to gain access to other satellites reports. I am attaching MATLAB code here. Please help me out if you can. I am working on it for a week.
Thank you in advance

%% initialization
clc; clear;

%% system parameters
stk_scenario_name = 'walker';
start_time = '2 Oct 2021 12:00:00.000';
stop_time = '3 Oct 2021 12:00:00.000';

main_satellite_name = 'LeoSat';

%% Create a New Instance of STK from Inside MATLAB
app = actxserver('STK11.application'); % Create a new instance of STK11
app.UserControl = 1; % Create a new instance of STK11
root = app.Personality2; % Grab a handle on the STK application root

%% Create a New STK Scenario and configure its properties
scenario = root.Children.New('eScenario',stk_scenario_name); % Create a new scenario
scenario.SetTimePeriod(start_time,stop_time); % Configure your STK scenario's properties
scenario.StartTime = start_time;
scenario.StopTime = stop_time;
root.ExecuteCommand('Animate * Reset');

%% Add a satellite and configure its properties
satellite = scenario.Children.New('eSatellite',main_satellite_name);
% IAgSatellite satellite: Satellite object
keplerian = satellite.Propagator.InitialState.Representation.ConvertTo('eOrbitStateClassical'); % Use the Classical Element interface
keplerian.SizeShapeType = 'eSizeShapeAltitude';  % Changes from Ecc/Inc to Perigee/Apogee Altitude
keplerian.LocationType = 'eLocationTrueAnomaly'; % Makes sure True Anomaly is being used
keplerian.Orientation.AscNodeType = 'eAscNodeLAN'; % Use LAN instead of RAAN for data entry

% Assign the perigee and apogee altitude values:
keplerian.SizeShape.PerigeeAltitude = 500;      % km
keplerian.SizeShape.ApogeeAltitude = 600;       % km

% Assign the other desired orbital parameters:
keplerian.Orientation.Inclination = 90;         % deg
keplerian.Orientation.ArgOfPerigee = 12;        % deg
keplerian.Orientation.AscNode.Value = 24;       % deg
keplerian.Location.Value = 180;                 % deg

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

% IAgSatellite satellite: Satellite object
basic = satellite.Attitude.Basic;
basic.SetProfileType('eProfileSpinning')
basic.Profile.Body.AssignXYZ(0,0,1)
basic.Profile.Inertial.AssignXYZ(0,1,0);
basic.Profile.Rate = 6;  % rev/sec

%% Create walker constellation based on LeoSat
walker_constellation = root.ExecuteCommand('Walker  */Satellite/LeoSat  Type  Delta  NumPlanes  1  NumSatsPerPlane  10  InterPlanePhaseIncrement 0 ColorByPlane Yes ConstellationName walker_system SetUniqueNames Yes');
% satellite.Unload();



%% Extract data
root.UnitPreferences.Item('DateFormat').SetCurrentUnit('EpSec');
satPosDP = satellite.DataProviders.Item('Cartesian Position').Group.Item('ICRF').Exec(scenario.StartTime,scenario.StopTime,60);
satx = cell2mat(satPosDP.DataSets.GetDataSetByName('x').GetValues);
saty = cell2mat(satPosDP.DataSets.GetDataSetByName('y').GetValues);
satz = cell2mat(satPosDP.DataSets.GetDataSetByName('z').GetValues);