% Minimal LEO mission used by the gmat-sweep evaluation guide.
%
% One Spacecraft, a tiny point-mass force model, an RK89 propagator, one
% ReportFile, and a 60-second propagate. Designed to run in seconds
% against either R2025a or R2026a and to expose Sat.SMA as a tractable
% sweep parameter.

%----------------------------------------
%---------- Spacecraft
%----------------------------------------

Create Spacecraft Sat;
Sat.DateFormat       = UTCGregorian;
Sat.Epoch            = '01 Jan 2026 00:00:00.000';
Sat.CoordinateSystem = EarthMJ2000Eq;
Sat.DisplayStateType = Keplerian;
Sat.SMA              = 7000;
Sat.ECC              = 0.001;
Sat.INC              = 28.5;
Sat.RAAN             = 0;
Sat.AOP              = 0;
Sat.TA               = 0;

%----------------------------------------
%---------- ForceModel
%----------------------------------------

Create ForceModel FM;
FM.CentralBody               = Earth;
FM.PrimaryBodies             = {Earth};
FM.Drag.AtmosphereModel      = None;
FM.SRP                       = Off;
FM.GravityField.Earth.Degree = 0;
FM.GravityField.Earth.Order  = 0;

%----------------------------------------
%---------- Propagator
%----------------------------------------

Create Propagator Prop;
Prop.FM              = FM;
Prop.Type            = RungeKutta89;
Prop.InitialStepSize = 30;
Prop.Accuracy        = 1e-9;

%----------------------------------------
%---------- ReportFile
%----------------------------------------

Create ReportFile RF;
RF.Filename     = 'sat.report';
RF.WriteHeaders = On;
RF.Add          = {Sat.UTCGregorian, Sat.EarthMJ2000Eq.X, Sat.EarthMJ2000Eq.Y, Sat.EarthMJ2000Eq.Z, Sat.Earth.SMA, Sat.Earth.ECC};

%----------------------------------------
%---------- Mission Sequence
%----------------------------------------

BeginMissionSequence;
Propagate Prop(Sat) {Sat.ElapsedSecs = 60};