%
%   EphemPropagator_Code500_Validation_CentralBody_NoEffect
%
%   Use the Code500 Propagator type with an Earth-centered ephemeris file. Set
%   the propagator CentralBody to Moon and verify that the setting has no effect
%   on the output vectors.
%
%   08/30/2016 SES Initial version.
%

SolarSystem.EphemerisSource = 'DE421';

%
%   Spacecraft
%

Create Spacecraft Code500Sat;

Code500Sat.DateFormat    = UTCGregorian;
Code500Sat.Epoch         = '09 May 2016 00:00:00.000';
Code500Sat.Id            = 'Code500Sat';
Code500Sat.EphemerisName = '../data/navdata/otherinputfiles/terra.ephem.pc';

%
%   Propagator
%

Create Propagator Code500Prop;

Code500Prop.Type        = 'Code500';
Code500Prop.StepSize    = 60;
Code500Prop.StartEpoch  = 'FromSpacecraft';
Code500Prop.CentralBody = Luna;

%
%   Output report.
%

Create ReportFile PropReport

PropReport.Filename     = 'EphemPropagator_Code500_Validation_CentralBody_NoEffect.txt';
PropReport.WriteHeaders = False;

%
%	Miscellaneous variables.
%

Create String initialEpoch finalEpoch;
Create Array initialState[6,1] finalState[6,1];

%
%   Mission Sequence
%

BeginMissionSequence

[initialEpoch, initialState, finalEpoch, finalState] = ...
	GetEphemStates('Code500', Code500Sat, 'UTCGregorian', EarthMJ2000Eq);

Code500Sat.Epoch = initialEpoch;
Code500Sat.X     = initialState(1,1);
Code500Sat.Y     = initialState(2,1);
Code500Sat.Z     = initialState(3,1);
Code500Sat.VX    = initialState(4,1);
Code500Sat.VY    = initialState(5,1);
Code500Sat.VZ    = initialState(6,1);

While Code500Sat.ElapsedDays <= 1.5

   Report PropReport Code500Sat.TAIModJulian ...
        Code500Sat.X Code500Sat.Y Code500Sat.Z ...
        Code500Sat.VX Code500Sat.VY Code500Sat.VZ;
		
	Propagate Code500Prop(Code500Sat);

EndWhile