Object NameField NameData TypeWidget TypeDefault ValueRangeAccessDescriptionUnitsField CouplingsRequirementsInterfacesAdditional Tests
BarycenterBodyNamesStringListSelection ListEarth, LunaCelestial Body. You cannot add bodies to the built-in SolarySystemBarycenter object.SetThe list of celestial bodies included in the barycenter. A Celestial Body can only appear once in the BodyNames list.N/ANoneFRR-18.1G+SNone
CelestialBodyTextureMapFileName FileNameText box''../data/graphics/texture/GenericCelestialBody.jpg'Valid file of typeTexture map used in OrbitView graphics.N/ANoneFRR-16.2.4G+SNone
CelestialBodyEquatorialRadius RealText Box6378.1363Real > 0.The body's equatorial radius.kmNoneFRR-16.2.2G+SNone
CelestialBodyFlattening RealText Box0.0033527Real >= 0The body's polar flattening.N/ANoneFRR-16.2.3G+SNone
CelestialBodyMu RealText Box398600.4415Real > 0.The body's gravitational parameter.km^3/s^2NoneFRR-16.2.1G+SNone
CelestialBodyNutationUpdateInterval RealText box60Real >=0The interval between updates for Earth nutation matrix. If NutationUpdateInterval = 3600, then GMAT only updated nutation on an hourly basis.sec.NoneFRR-16.2.7G+S
CelestialBodyRotationConstant RealText box190.147RealThe body's spin angle at the orientation epoch.degOrientationEpoch FRR-16.7.5G+SNone
CelestialBodyRotationRate RealText box360.9856235RealThe body's spin rate.deg/dayNoneFRR-16.7.6G+SNone
CelestialBodySpinAxisDECConstant RealText box90RealThe declination of the body's spin axis at the orientation epoch.degOrientationEpoch FRR-16.7.3G+SNone
CelestialBodySpinAxisDECRate RealText box-0.5570RealThe rate of change of the body's declination.deg/dayNoneFRR-16.7.1G+SNone
CelestialBodySpinAxisRAConstant RealText box-0.641RealThe right ascension of the body's spin axis at the orientation epoch.degOrientationEpoch G+SNone
CelestialBodySpinAxisRARate RealText box-0.641RealThe rate of change of the body's right ascension.deg/dayNoneFRR-16.7.2G+SNone
CelestialBodyOrientationEpoch StringText box21545.06116.0 <= Epoch <= 58127.5The reference epoch for orientation dataA1 Mod Julian EpochRotationConstant, RotationRate, SpinAxisDECConstant, SpinAxisDECRate, SpinAxisRAConstant, SpinAxisRARate FRR-16.7.7G+SNone
CelestialBodyPosVelSource StringDrop Down Menu'''DE405' for build in bodies. 'SPICE' for user defined bodies.'SPICE'The model for the bodies orbit ephemeredes.N/ANoneFRR-16.3.0G+SNone
CelestialBodyRotationDataSource StringDrop Down MenuFor Earth default is 'FK5IAU1980', for Luna default is DE405, for selected build it bodies IAU2000, and for selected built in bodies and all user defined bodies, default is IAUSimplified.''IAUSimplified', 'DE405' 'FK5IAU1980', 'IAU2000'The model for the body's time dependent orientation.N/ACoupling is based on body. See Default description.FRR-16.4.0G+SNone
CelestialBodyOrbitSpiceKernelNameStringArrayListN/AValid SPK kernelList of SPK kernels.N/ANoneFRR-16.6.1
CelestialBodyCentralBody UserDefStringDrop Down MenuFor Comet, Planet, Asteroid, the default is Sun. For Moon, the default is Earth.Celestial Body. The central body of the celestial body. The central body field is used primarily by the GUI.N/ANoneFRR-16.8.10G+SNone
CelestialBodyNAIFId UserDefStringText Box-123456789IntegerNAIF Integer ID for body.N/APosVelSourceG+SNone
CoordinateSystemAxes StringDrop Down MenuMJ2000EqMJ2000Eq, MJ2000Ec, ICRF, ITRF, MODEq, MODEc, TODEq, TODEc, MOEEq, MOEEc, TOEEq, TOEEc, ObjectReferenced, Equator, BodyFixed, BodyInertial, GSE, GSM, TopocentricSetThe axes of the coordinate system.N/AEpoch, Primary, Secondary, XAxis, YAxis, ZAxisFRR-35.2.0G + SNone
CoordinateSystemEpochStringText Box21545See Epoch??SetThe reference epoch for the coordinate system. This field is only used for TOE amd MOE axis types.Modified Julian DateAxesFRR-35.2.3, FRR-35.2.4, FRR-35.2.5, FRR-35.2.6G+SNone
CoordinateSystemPrimaryStringDrop Down MenuEarthCelestialBody, Spacecraft, LibrationPoint, Barycenter, SolarSystemBarycenter, GroundStationSetThe primary body for an ObjectReferenced axis system. This field is only use if Axes = ObjectReferenced.N/AAxesFRR-35.2.13G+SNone
CoordinateSystemSecondaryStringDrop Down MenuLunaCelestialBody, Spacecraft, LibrationPoint, Barycenter, SolarSystemBarycenter, GroundStationSetThe secondary body for an ObjectReferenced axis system. This field is only use if Axes = ObjectReferenced.N/AAxesFRR-35.2.13G+SNone
CoordinateSystemXAxisStringDrop Down MenuRR,V, N, -R, -V, -N, or emptySetThe x-axis definition for an ObjectReferenced axis system. This field is only use if Axes = ObjectReferenced.N/AAxesFRR-35.2.13G+SNone
CoordinateSystemYAxisStringDrop Down MenuNo DefaultR,V, N, -R, -V, -N, or emptySetThe y-axis definition for an ObjectReferenced axis system. This field is only use if Axes = ObjectReferenced.N/AAxesFRR-35.2.13G+SNone
CoordinateSystemZaxisStringDrop Down MenuNR,V, N, -R, -V, -N, or emptySetThe z-axis for an ObjectReferenced axis system. This field is only use if Axes = ObjectReferenced.N/AAxesFRR-35.2.13G+SNone
CoordinateSystemOriginUserDefStringDrop Down MenuEarthCelestialBody, Spacecraft, LibrationPoint, Barycenter, SolarSystemBarycenter, GroundStationSetThe origin of the coordinate system.N/ANoneFRR-35.1.0G+SNone
DifferentialCorrectorReportFileFileNameDifferentialCorrectorDCName.data, where DCname is the name of the differential correctorFilename consistent with OS SetThe ReportFile field allows the user to specify the path and file name for the differential correction report.  The report is only generated if ShowProgress is set to true.  N/ANoneFRR-19.3G+SNone
DifferentialCorrectorMaximumIterationsInteger25Integer >= 1SetThe MaximumIterations field allows the user to set the maximum number of iterations the differential corrector is allowed during the attempt to find a solution. If the maximum iterations is reached, GMAT exits the target loop and continues to the next command in the mission sequence. In this case, the objects retain their states as of the last nominal pass through the targeting loop.N/ANoneFRR-19.1.1G+S-1
DifferentialCorrectorDerivativeMethodStringForwardDifferenceForwardDifference, BackwardDifference, CentralDifferenceSetThe DerivativeMethod field allows the user to choose between one-sided and central differencing for numerically determining the derivative.N/ANoneFRR-19.1.2.1-3G+SNone
DifferentialCorrectorReportStyleStringNormalNormal, Concise, Verbose, DebugSetThe ReportStyle field allows the user to control the amount and type of information written to the file defined in the ReportFile field. Currently, the Normal and Concise options contain the same information: the Jacobian, the inverse of the Jacobian, the current values of the control variables, and achieved and desired values of the constraints. Verbose contains values of the perturbation variables in addition to the data for Normal and Concise. Debug contains detailed script snippets at each iteration for objects that have control variables.N/ANoneFRR-19.3G+SNone
DifferentialCorrectorShowProgressStringtruetrue, falseSetWhen the ShowProgress field is set to true, then data illustrating the progress of the differential correction process are written to the message window and the ReportFile. The message window is updated with information on the current control variable values and the contraint variances.  When the ShowProgress field is set to false, no information on the progress of the differential correction process is displayed to the message window or written to the ReportFile. N/ANoneFRR.19.2.1-3G+SNone
EphemerisFileInterpolationOrderIntegerTextBox71 <= Integer Number <= 10SetThe InterpolationOrder field allows you to set the interpolation order for the available interpolator methods (Lagrange or Hermite) for either CCSDS-OEM or SPK file formats. N/ANoneFRR-31.4.4.1, FRR-31.5.4.1 G+SNone
EphemerisFileStepSizeRealTextBoxIntegratorStepsReal Number > 0.0 or equals 'IntegratorSteps'SetThe ephemeris file is generated at the step size that is specified for StepSize field. The user can generate ephemeris file at default Integration step size (using raw integrator steps) or by defining a Fixed step size provided by user.N/ANoneFRR-31.4.5G+SNone
EphemerisFileEpochFormatStringDropDownMenuUTCGregorianUTCGregorian, UTCModJulian, TAIGregorian, TAIModJulian, TTGregorian, TTModJulian A1Gregorian, A1ModJulian, TDBGregorian, TDBModJulianSetThe EpochFormat field allows the user to select format of the epoch.N/ANoneFRR-31.4.2, FRR-31.5.2 G+SNone
EphemerisFileFileFormatStringDropDownMenuCCSDS-OEMCCSDS-OEM, SPKSetThe FileFormat field allows the user to generate ephemeris file in two available file formats: CCSDS-OEM or SPK,N/AInterpolatorFRR-31.2.0G+SNone
EphemerisFileFileNameStringTextBox, FileBrowseButtonEphemerisFile1.ephValid File Path and NameSetThe FileName field allows the user to name the generated ephemeris file and save it in user-specified location.N/ANoneFRR-31.19 G+SNone
EphemerisFileFinalEpochStringTextBoxFinalSpacecraftEpochuser-defined final epoch or 'FinalSpacecraftEpoch'SetThe FinalEpoch field allows the user to specify the time span of an ephemeris file. Ephemeris file is generated up to final epoch that is specified in FinalEpoch field.N/ANoneFRR-31.7.0G+SNone
EphemerisFileInitialEpochStringTextBoxInitialSpacecraftEpochuser-defined initial epoch or 'InitialSpacecraftEpoch'SetThe InitialEpoch field allows the user to specify the starting epoch of the ephemeris file. Ephemeris file is generated starting from the epoch that is defined in InitialEpoch field.N/ANoneFRR-31.7.0G+SNone
EphemerisFileInterpolatorStringDropDownMenuLagrangeLagrange for CCSDS file, Hermite for SPK fileSetThe Interpolator field defines the available interpolator method that was used to generate ephemeris file. Available Interpolators are Lagrange or Hermite.N/ANoneFRR-31.4.4.1 N/ANone
EphemerisFileWriteEphemerisStringCheckBoxtruetrue,falseSetWriteEphemeris field allows the user to optionally calculate/write or not calculate/write an ephemeris that has been created and configured. N/ANoneFRR-31.10 G+SNone
EphemerisFileCoordinateSystemUserDefStringDropDownMenuEarthMJ2000EqAny default or user defined coordinate systemSet,GetCoordinateSystem field allows the user to generate ephemeris data in the coordinate system that is selected from CoordinateSystem field. The user can choose to also generate ephemeris data in user-defined coordinate system. N/ANoneFRR-31.4.3G+SNone
EphemerisFileSpacecraftUserDefStringDropDownMenuDefaultSCDefault spacecraft or any number of user-defined spacecrafts or formations Set,GetThe Spacecraft field allows the user to generate ephemeris data of spacecraft(s) that are defined in Spacecraft field.N/ANoneFRR-31.1.0G+SNone
EphemerisFileUpperLeftStringN/A[ 0 0 ]Any Real numberSetThe UpperLeft field allows the user to pan the generated ephemeris file display window in any direction. First value in [0 0] matrix helps to pan the window horizontally and second value helps to pan the window vertically.N/ANoneFRR-31.18SNone
EphemerisFileSizeStringN/A[ 0 0 ]Any Real numberSetThe Size field allows the user to control the display size of generated ephemeris file panel. First value in [0 0] matrix controls horizonal size and second value controls vertical size of ephemeris file display window.N/ANoneFRR-31.16SNone
EphemerisFileRelativeZOrderStringN/A0Any Real numberSetRelativeZOrder field allows the user to select which generated ephemeris file display window is to displayed first on the screen. The EphemerisFile object with lowest RelativeZOrder value will be displayed last while EphemerisFile object with highest RelativeZOrder value will be displayed first.N/ANoneFRR-31.17SNone
EphemerisFileMaximizedStringN/Afalsetrue,falseSetThe Maximized field allows the user to maximize the generated ephemeris file window.N/ANoneFRR-31.15SNone
FiniteBurnThrusterStringListNo DefaultAny thruster created by userSetThe Thruster field allows the selection of which thruster, from a list of previously created thrusters, to use when applying a finite burn. Currently, the user can only select  one thruster to attach to a finite burn.  N/ANoneFRR-12.1G+SNone
FminconOptimizerDiffMaxChange0.1Real Number > 0The DiffMaxChange parameter is the upper limit on the perturbation used in MATLAB's finite differencing algorithm. For fmincon, you don't specify a single perturbation value, but rather give MATLAB a range, and it uses an adaptive algorithm that attempts to find the optimal perturbation.NoneNoneFRR-20.1.6G+S
FminconOptimizerDiffMinChange1e-8Real Number > 0The DiffMinChange parameter is the lower limit on the perturbation used in MATLAB's finite differencing algorithm. For fmincon, you don't specify a single perturbation value, but rather give MATLAB a range, and it uses an adaptive algorithm that attempts to find the optimal perturbation.NoneNoneFRR-20.1.7G+S
FminconOptimizerMaxFunEvals1000Integer > 0The MaxFunEvals parameter allows the user to set the maximum number of cost function evaluations in an attempt to find an optimal solution. This is equivalent to setting the maximum number of passes through an optimization loop in a GMAT script. If a solution is not found before the maximum function evaluations, fmincon outputs an ExitFlag of zero, and GMAT continues. NoneNoneFRR-20.1.2G+S
FminconOptimizerMaximumIterations25Integer > 0The MaximumIterations field allows the user to set the maximum allowable number of passes through the optimizer.  Note that this is not the same as the number of optimizer iterations that is shown for the VF13AD optimzer.   NoneNoneFRR-20.1.1G+S
FminconOptimizerReportFileFminconOptimizerSQP1.dataAny user-defined file nameThe ReportFile field contains the path and file name of the report file.NoneShowProgess, ReportStyleFRR-20.3G+S
FminconOptimizerReportStyleNormalNormal, Concise, Verbose, DebugThe ReportStyle field determines the amount and type of data written to the message window and to the report specified by field ReportFile for each iteration of the solver (when ShowProgress is true).  Currently, the Normal, debug, and Concise options contain the same information: the values for the control variables, the constraints, and the objective function.  In addition to this information, the Verbose option also contains values of the optimizer-scaled control variables.  NoneShowProgress, ReportFileFRR-20.3G+S
FminconOptimizerShowProgressTRUEtrue, falseThe ShowProgress field determines whether data pertaining to iterations of the solver is both displayed in the message window and written to the report specified by the ReportFile field. When ShowProgress is true, the amount of information contained in the message window and written in the report is controlled by the ReportStyle field.NoneReportStyle, ReportFileFRR-20.2.1-4G+S
FminconOptimizerTolCon1e-4Real Number > 0The TolCon parameter is the convergence tolerance on the constraint functions.NoneNoneFRR-20.1.3G+S
FminconOptimizerTolFun1e-4Real Number > 0The TolFun parameter is the convergence tolerance on the cost function value.NoneNoneFRR-20.1.4G+S
FminconOptimizerTolX1e-4Real Number > 0The TolX parameter is the termination tolerance on the vector of indepen- dent variables, and is used only if the user sets a value for this field.  NoneNoneFRR-20.1.5G+S
ForceModelPrimaryBodiesCelestial BodyDrop Down MenuEarthCelestial BodySetA body modelled with a "complex" force model. A PrimaryBody can have an atmosphere and harmonic gravity model. A PrimaryBody can be any celestial body not included in the PointMasses field. Currently GMAT only supports one PrimaryBody per force model.N/APointMasses, CentralBodyFRR-13.1.1.0,FRR-13.1.1.2G+SNone
ForceModelPointMassesCelestial Body ListSelection ListEmpty ListCelestial BodySetA list of celestial bodies to be treated as point masses in the force model. A body cannot be both the PrimaryBody and in the PointMass list.N/ASRPFRR-13.1.5.0G+SNone
ForceModelDrag.AtmosphereModelEnumerationDrop Down Menu''None'None, JacchiaRoberts, MSISE86, MSISE90, NRLMSISE00SetSpecifies the atmosphere model used in the drag force. This field is only active if there is a PrimaryBody. N/APrimaryBodyFRR-13.1.2.0G+SNone
ForceModelErrorControlEnumerationDrop Down MenuRSSStepNone, RSSStep, RSSState, LargestState, LargestStepSetControls how error in the current integration step is estimated. The error in the current step is computed by the selection of ErrorControl and compared to the value set in the Accuracy field to determine if the step has an acceptable error or needs to be improved. All error measurements are relative error, however, the reference for the relative error changes depending upon the selection of ErrorControl. RSSStep is the Root Sum Square (RSS) relative error measured with respect to the current step. RSSState is the (RSS) relative error measured with respect to the current state. LargestStep is the state vector component with the largest relative error measured with respect to the current step. LargestState is the state vector component with the largest relative error measured with respect to the current state. For a more detailed discussion see the GMAT Mathematical Specification. Setting ErrorControl to None turns off error control and the integrator takes constant steps at the value defined by InitialStepSize on the numerical integrator.N/AAccuracyFRR-14.6.0G+SNone
ForceModelGravityField.Earth.EarthTideModelEnumerationN/A''None'None, SolidAndPoleSetFlag for type of Earth tide model. This field is always active but only used in the dynamics when there is a harmonic gravity model for Earth.N/APrimaryBody,GravityFieldFRR-13.1.6.1SNone
ForceModelRelativisticCorrectionEnumerationCheck BoxOffOn, OffSetSets relativistic correction on or off.N/ANoneFRR-13.1.7G+SNone
ForceModelSRPEnumerationDrop Down MenuOffOn, OffSetSets SRP force on or off.N/ANoneFRR-13.1.3.1G+SNone
ForceModelGravityField.PrimaryBodyName.PotentialFileGravity FileText Box''JGM2.cof'path and name of .cof OR .grv fileSetThe gravity potential file. This field is only active if there is a PrimaryBody. N/APrimaryBodyFRR-13.1.1.0G+SNone
ForceModelGravityField.PrimaryBodyName.Degree IntegerText Box40<Degree<Max Degree On FileSetThe degree of the harmonic gravity field. This field is only active if there is a PrimaryBody. N/APrimaryBodyFRR-13.1.1.0G+SNone
ForceModelGravityField.PrimaryBodyName.OrderIntegerText Box40<Order<Max Degree On File AND Degree <= OrderSetThe order of the harmonic gravity field. This field is only active if there is a PrimaryBody. N/APrimaryBodyFRR-13.1.1.0G+SNone
ForceModelModelModel TypeDrop Down Menu''JGM-2'JGM-2, JGM-3, EGM-96, Mars-50C, MGNP-180USetA GUI list of "configured' gravity files defined in the file gmat_startup_file.txt. Model allows you to quickly choose between gravity files distributed with GMAT. For example, if PrimaryBody is Earth, you can select among Earth gravity models provided with GMAT such as JGM-2 and EGM-96. If you select Other, you can provide the path and filename for a custom gravity file.N/APrimaryBodyFRR-13.1.1.0GNone
ForceModelCentralBodyObject TypeDrop Down MenuEarthCelestial BodySetThe central body of propagation. CentralBody must be a celestial body and cannot be a LibrationPoint, Barycenter, Spacecraft, or other special point.N/APointMasses, PrimaryBodyFRR-13.1.1.0,FRR-13.1.1.2G+SNone
ForceModelDrag.F107RealText Box15050 <= Drag.F107 <= 400SetThe instantaneous value of solar flux at wavelength of 10.7 cm. This field is only active if there is a PrimaryBody. W/m^2/HzPrimaryBodyFRR-13.1.2.1.1,FRR-13.1.2.2.1,FRR-13.1.2.4.1,FRR-13.1.2.6.1G+S-1
ForceModelDrag.F107ARealText Box15050 <= Draft.F107A <= 400SetThe average (monthly) value of solar flux at wavelength of 10.7 cm. This field is only active in the script if there is a PrimaryBody. This field is only active if there is a PrimaryBody. W/m^2/HzPrimaryBodyFRR-13.1.2.1.2,FRR-13.1.2.2.2,FRR-13.1.2.4.2,FRR-13.1.2.6.2G+S-1
ForceModelDrag.MagneticIndexRealText Box30 <= Real Number <= 9SetThe geomagnetic index (Kp) used in density calculations. Kp is a planetary 3-hour-average, geomagnetic index that measures magnetic effects of solar radiation. This field is only active if there is a PrimaryBody. N/APrimaryBodyFRR-13.1.2.1.3,FRR-13.1.2.2.3,FRR-13.1.2.4.3,FRR-13.1.2.6.3G+S-1
ForceModelSRP.FluxRealN/A13671300 < Flux < 1450SetThe value of SRP flux at 1 AU. This field is only active in the script if SRP is on. W/m^2SRPFRR-13 Missing Req.S-1
ForceModelSRP.Flux_PressureRealN/A4.55982118135874e-006 4.33e-6 < Flux_Pressure < 4.84e-6SetThe solar flux at 1 AU divided by the speed of light. This field is only active in the script if SRP is on. W *s/m^3SRPFRR-13 Missing Req.S
ForceModelSRP.Nominal_SunRealN/A149597870.691135e6<Nominal_Sun<165e6SetThe value of one Astronomical Unit in AU used in scaling SRP.Flux, which is flux at 1 AU, to the flux at spacecraft distance from sun. This field is only active in the script if SRP is on. kmSRPFRR-13 Missing Req.S-1
ForceModelDrag (Deprecated)See AtmosphereModelSee AtmosphereModelSee AtmosphereModelSee AtmosphereModelSetSee AtmosphereModel.N/APrimaryBodyFRR-13.1.2.0SNone
ForceModelUserDefined
FormationAddUserDefStringListNone
FuelTankAllowNegativeFuelMass Boolean_TypeFALSEtrue, falsesetThis field allows the fuel tank to have negative fuel mass which can be useful in optimization and targeting sequences before convergence has occurred.N/ANoneFRR-8.3.3G+SNone
FuelTankPressureModel EnumerationPressureRegulatedPressureRegulated, BlowDownsetThe pressure model describes how pressure in the tank changes as fuel is depleted.N/ANoneFRR-8.3.1,FRR-8.3.2G+SNone
FuelTankFuelDensity Real1260Real > 0set, getThe density of the fuel.  kg/m^3NoneFRR-8.2.4G+S0 -1
FuelTankFuelMass Real756Real > 0set, getThe mass of fuel in the tank.  kgNoneFRR-8.2.1G+S-1
FuelTankPressureReal1500Real > 0set, getThe pressure in the tank.kPaNoneFRR-8.2.2G+S-1
FuelTankRefTemperatureReal20Real > -273.15, |Real| > 0.01set, getThe temperature of the tank when fuel was loaded.CNoneFRR-8.2.5G+SNone
FuelTankTemperature Real20Real > -273.15set, getThe temperature of the fuel and ullage in the tank. GMAT currently assumes ullage and fuel are always at the same temperature.CNoneFRR-8.2.3G+SNone
FuelTankVolume Real0.75Real > 0 such that calculated fuel volume is < input tank Volume.set, getThe volume of the tank. GMAT checks to ensure that the input volume of the tank is larger than the calculated volume of fuel loaded in the tank and throws an exception in the case that the calculated fuel volume is larger than the input tank volume.m^3NoneFRR-8.2.6G+S0 -1
GroundStationAltitudeRealNone
GroundStationLatitudeRealNone
GroundStationLongitudeRealNone
GroundStationXRealNone
GroundStationYRealNone
GroundStationZRealNone
GroundStationHorizonReferenceStringNone
GroundStationStateTypeStringNone
GroundStationCentralBodyString None
GroundStationIdUserDefNameNone
GroundTrackPlotTextureMapFileNameTextBox, FileBrowseButton../data/graphics/texture/ModifiedBlueMarble.jpgValid File Path and NamesetThe TextureMap field allows you to enter or select any user-defined texture map image for the central bodyNoneCentralBodyFRR-42.7.0G+SNone
GroundTrackPlotDataCollectFrequencyIntegerTextBox1integer >= 1setThe number of integration steps to skip between plot pointNoneNoneFRR-42.5.1G+SNone
GroundTrackPlotNumPointsToRedrawIntegerTextBox0integer >= 0setThe number of plot points to retain and redraw during propagation and animation. 0 indicates to redraw all.NoneNoneFRR-42.5.3G+SNone
GroundTrackPlotUpdatePlotFrequencyIntegerTextBox50integer > 1setThe number of plot points to collect before updating a ground track plot.NoneNoneFRR-42.5.2G+SNone
GroundTrackPlotCentralBodyStringDrop Down MenuEarthSun, Mercury, Venus, Earth, Luna, Mars,Jupiter, Saturn, Uranus, Neptune, PlutosetThe central body of the Ground track plotNoneTextureMapFRR-42.1.0G+SNone
GroundTrackPlotMaximizedStringN/Afalsetrue,falsesetThe Maximized field allows the user to maximize the GroundTrackPlot window.NoneNoneFRR-42.17SNone
GroundTrackPlotRelativeZOrderStringN/A0Any Real numberSetRelativeZOrder field allows the user to select which GroundTrackPlot window to display first on the screen. The GroundTrackPlot with lowest RelativeZOrder value will be displayed last while GroundTrackPlot with highest RelativeZOrder value will be displayed first.N/ANoneFRR-42.18SNone
GroundTrackPlotShowPlotStringCheckboxTrueTrue,FalsesetThe ShowPlot field specifies whether to show ground track plot during a mission run.NoneNoneFRR-42.8G+SNone
GroundTrackPlotSizeStringN/A[ 0 0 ]Any Real numberSetThe Size field allows the user to control the display size of GroundTrackPlot window. First value in [0 0] matrix controls horizonal size and second value controls vertical size of GroundTrackPlot display window.N/ANoneFRR-42.15 SNone
GroundTrackPlotSolverIterationsStringDrop Down MenuCurrentAll, Current,NonesetThe SolverIterations field determines whether or not ground track data associated with perturbed trajectories during a solver (Targeter, Optimize) sequence is displayed in the GroundTrackPlot. When SolverIterations is set to All, all perturbations/iterations are plotted in the GroundTrackPlot. When SolverIterations is set to Current, only the current solution or perturbation is plotted in GroundTrackPlot. When SolverIterations is set to None, only the final nominal run is plotted on the GroundTrackPlot.NoneNoneFRR-42.6.0G+SNone
GroundTrackPlotUpperLeftStringN/A[0 0]Any Real numberSetThe UpperLeft field allows the user to pan the GroundTrackPlot display window in any direction. First value in [0 0] matrix helps to pan the GroundTrackPlot window horizontally and second value helps to pan the window vertically.N/ANoneFRR-42.16 SNone
GroundTrackPlotAddUserDefStringListCheckListBoxDefaultSCSelected Objects like Spacecraft(s) or GroundStation(s)setThe Add field allows the user to pick selected objects such as Spacecraft(s) or GroundStation(s) whose ground track is drawn in GroundTrackPlot. To select multiple Spacecrafts or GroundStations, seperate the list by comma and enclose the list in curly brackets. For Example: DefaultGroundTrackPlot.Add = {aSat, bSat, aGroundStaton, bGroundStation};NoneNoneFRR-42.2.1G+SNone
ImpulsiveBurnElement1 Real1Realset, getX-component of the applied impulsive burn (Delta-V)NoneNoneFRR-11.2.1G+SNone
ImpulsiveBurnElement2Real0Realset, getY-component of the applied impulsive burn (Delta-V)NoneNoneFRR-11.2.1G+SNone
ImpulsiveBurnElement3 Real0Realset, getZ-component of the applied impulsive burn (Delta-V)NoneNoneFRR-11.2.1G+SNone
ImpulsiveBurnGravitationalAccel Real9.81Real > 0set, getValue of the gravitational acceleration used to calculate fuel depletion.   m/s^2NoneFRR-11.4.1G+S0 -1
ImpulsiveBurnIsp Real300Realset, getValue of the specific impulse of the fuelsThe Isp field is only active if the DecrementMass field is set to true.FRR-11.4.2G+S0 -1
ImpulsiveBurnAxes StringVNBVNB, LVLH, MJ2000Eq, SpacecraftBodysetThe Axes field allows the user to define a spacecraft centered set of axes for the impulsive burn.  N/AThe Axes field is only active if the CoordinateSystem field is set to Local.  FRR-11.1.2.1-3. FRR-11.1.3G+SNone
ImpulsiveBurnDecrementMass StringFALSEtrue, falsesetFlag which determines if the FuelMass is to be decremented as it used.    N/ANoneFRR-11.3G+SNone
ImpulsiveBurnCoordinateSystemUserDefStringLocalLocal, EarthMJ2000Eq, EarthMJ2000Ec, EarthFixed, or any user defined systemsetThe CoordinateSystem field for an impulsive burn determines what coordinate system the orientation parameters, Element1, Element2, and Element3 refer to.  N/ANoneFRR-11.1.1G+SNone
ImpulsiveBurnOrigin UserDefStringEarthSun, Mercury, Venus, Earth, Luna, Mars,Jupiter, Saturn, Uranus, Neptune, PlutosetThe Origin field, used in conjunction with the Axes field, allows the user to define a spacecraft centered set of axes for the impulsive burn.  N/AThe Origin field is only active if the CoordinateSystem field is set to Local.  FRR-11.1.2.1-2G+SNone
ImpulsiveBurnTankUserDefStringListN/AUser defined list of FuelTankssetTank from which the thruster draws propellant from.N/AThe Tank field is only active if the DecrementMass field is set to true.FRR-11.4.3G+SNone
LibrationPointPoint StringDrop Down MenuL1L1, L2, L3, L4, L5setThe libration point index.N/ANoneFRR-17.1.0G+SNone
LibrationPointPrimary UserDefStringDrop Down MenuSunCelestialBody or Barycenter. Primary cannot be SolarSystemBarycenter and Primary cannot be the same as Secondary.setThe primary body or barycenter.N/ASecondaryFRR-17.2.0G+SNone
LibrationPointSecondaryUserDefStringDrop Down MenuEarthCelestialBody or Barycenter. Secondary cannot be SolarSystemBarycenter and Primary cannot be the same as Secondary.setThe secondary body or barycenter.N/APrimaryFRR-17.3.0G+SNone
MatlabFunctionFunctionPathFileNameTextBox, FileBrowseButtonMATLAB_FUNCTION_PATH from the gmat_startup_fileValid file pathSet,GetThe location in a file system that contains MATLAB function.
OrbitViewDataCollectFrequencyIntegerTextBox1Integer ≥ 1SetThe DataCollectFrequency field allows the user to define how data is collected for plotting. It is often inefficient to draw every ephemeris point associated with a trajectory. Often, drawing a smaller subset of the data still results in smooth trajectory plots, while executing more quickly. The DataCollectFrequency is an integer that represents how often to collect data and store for plotting. If DataCollectFrequency is set to 10, then Data is collected every 10 integration steps.Integration StepsNoneFRR-28.6.1G+SNone
OrbitViewNumPointsToRedraw IntegerTextBox0Integer ≥ 1SetWhen NumPointsToRedraw is set to zero, all ephemeris points are drawn. When NumPointsToRedraw is set to a positive integer, say 10 for example, only the last 10 collected data points are drawn. See DataCollectFrequency for explanation of how data is collected for an OrbitView plot.N/ANoneFRR-28.6.3G+SNone
OrbitViewStarCount IntegerTextBox7000Integer ≥ 1SetThe StarCount field allows the user to enter the number of stars that need to be displayed in an OrbitView plot.N/AN/AFRR-28.12G+SNone
OrbitViewUpdatePlotFrequency IntegerTextBox50Integer ≥ 1SetThe UpdatePlotFrequency field allows the user to specify how often to update an OpenGL plot is updated with new data collected during the process of propagating spacecraft and running a mission. Data is collected for a plot according the value defined by DataCollectFrequency. An OpenGL plot is updated with the new data, according to the value set in UpdatePlotFrequency. If UpdatePlotFrequency is set to 10 and DataCollectFrequency is set to 2, then the plot is updated with new data every 20 (10*2) integration steps.N/AN/AFRR-28.6.2G+SNone
OrbitViewAxes StringCheckBoxOnOn, OffSetThe Axis flag allows the user to tell GMAT to draw the Cartesian axis system associated with the coordinate system selected under the CoordinateSystem field of an OrbitView plot.N/ANoneFRR-28.4.1G+SNone
OrbitViewCelestialPlane StringCheckBoxOffOn, OffSetThe CelestialPlane field allows the user to tell GMAT to draw a grid representing the ecliptic plane in an OrbitView plot. N/ANoneFRR-28.4.7G+SNone
OrbitViewDrawObjectStringCheckBox[true true]true, falseSetThe DrawObject field allows the user to option of displaying Spacecraft or Celestial objects on the OrbitView plot.N/ANoneFRR-28.4.9 G+SNone
OrbitViewEnableConstellations StringCheckBoxOnOn,OffSetThe EnableConstellations field allows the user the option of displaying star constellations on the OrbitView Plot.N/ANoneFRR-28.4.6G+SNone
OrbitViewEnableStars StringCheckBoxOnOn,OffSetThe EnableStars field allows the user the option of displaying stars on the OrbitView Plot. When the EnableStars field is turned off, then EnableConstellations field is automatically diabled.N/AEnableConstellations and StarCount fieldsFRR-28.4.5G+SNone
OrbitViewGrid StringCheckBoxOffOn,OffSetThe Grid flag allows the user to tell GMAT to draw a grid representing the longitude and latitude lines celestial bodies added to an OrbitView plot.N/ANoneFRR-28.4.4G+SNone
OrbitViewMaximizedStringN/AfalseTrue, FalseSetThe Maximized field allows the user to maximize the OrbitView Plot window.N/ANoneFRR-28.15SNone
OrbitViewOrbitColorStringSelectBox[ 255 32768 ]Any color available from the Orbit Color selectboxSetThe OrbitColor field allows the user to be able to select colors for both spacecraft and celestial body trajectories. N/AN/AFRR-28.16G+SNone
OrbitViewRelativeZOrderStringN/A0Any real numberSetRelativeZOrder field allows the user to select which OrbitView window to display first on the screen. The OrbitViewPlot with lowest RelativeZOrder value will be displayed last while OrbitViewPlot with highest RelativeZOrder value will be displayed first.N/AN/AFRR-28.17SNone
OrbitViewShowPlot StringCheckBoxTrueTrue,FalseSetThe ShowPlot field allows the user to turn off a plot for a particular run, without deleting the plot object, or removing it from the script. If you select true, then the plot will be shown. If you select false, then the plot will not be shown.N/ANoneFRR-28.8G+SNone
OrbitViewSizeStringN/A[0 0]Any Real numberSetThe Size field allows the user to control the display size of OrbitViewPlot window. First value in [0 0] matrix controls horizonal size and second value controls vertical size of OrbitViewPlot display window.N/ANoneFRR-28.13SNone
OrbitViewSolverIterations StringDrop Down MenuCurrentAll,Current,NoneSetThe SolverIterations field determines whether or not data associated with perturbed trajectories during a solver (Targeter, Optimize) sequence is plotted to OrbitView. When SolverIterations is set to All, all perturbations/iterations are plotted to an OrbitView plot. When SolverIterations is set to Current, only current solution is plotted to an OrbitView. When SolverIterations is set to None, this shows only final solution after the end of an iterative process and draws only final trajectory to an OrbitView plot.N/ANoneFRR-28.7.0G+SNone
OrbitViewSunLine StringCheckBoxOffOff,OnSetThe SunLines allows the user to tell GMAT to draw a line that starts at the center of central body and points towards the Sun.N.AN/AFRR-28.4.8G+SNone
OrbitViewTargetColorStringSelectBox[ 8421440 0 ]Any color available from Target Color select boxSetThe TargetColor field allows the user to select any available color for perturbing trajectories during iterative processes such as Differential Correction or Optimization.N/AN/AFRR-28.18G+SNone
OrbitViewUpperLeftStringN/A[0 0]Any Real numberSetThe UpperLeft field allows the user to pan the OrbitViewPlot display window in any direction. First value in [0 0] matrix helps to pan the OrbitView window horizontally and second value helps to pan the window vertically.N/ANoneFRR-28.14 SNone
OrbitViewUseInitialView StringCheckBoxOnOn,OffSetThe UseInitialView field allows the user to control the view of an OrbitView plot between multiple runs of a mission sequence. The first time a specific OrbitView plot is created, GMAT will automatically use the view as defined by the fields associated with View Definition, View Up Direction, and Field of View. However, if the user changes the view using the mouse, GMAT will retain this view upon rerunning the mission if UseInitialView is set to false. If UseInitialView is set to true, the view for an OrbitView plot will be returned to the view defined by the initial settings.N/AN/AFRR-28.8G+SNone
OrbitViewViewDirection StringDrop Down MenuEarthSpacecraftName, CelestialBodyName, LibrationPointName, BarycenterName, or a 3-vector of numerical valuesSetThe ViewDirection field allows the user to select the direction of view in an OrbitView plot. The user can specify the view direction by choosing an object to point at such as a spacecraft,celestial body, libration point,or barycenter. Alternatively, the user can specify a vector of the form [x y z]. If the user specification of ViewDirection, ViewPointReference, and ViewPointVector, results in a zero vector, GMAT uses [0 0 10000] for ViewDirection.km or N/AN/AFRR-28.2.5G+SNone
OrbitViewViewPointReference StringDrop Down MenuEarthSpacecraftName, CelestialBodyName, LibrationPointName, BarycenterName, or a 3-vector of numerical valuesSetThe ViewPointReference field is an optional field that allows the user to change the reference point from which ViewPointVector is measured. ViewPointReference} defaults to the origin of the coordinate system for the plot. A ViewPointReference can be any spacecraft, celestial body, libration point, or barycenter.km or N/AN/AFRR-28.2.2G+SNone
OrbitViewViewPointVector StringDrop Down Menu[30000 0 0]SpacecraftName, CelestialBodyName, LibrationPointName, BarycenterName, or a 3-vector of numerical valuesSetThe product of ViewScaleFactor and ViewPointVector field determines the view point location with respect to ViewPointReference. ViewPointVector can be a vector, or any of the following objects: spacecraft,celestial body, libration point,or barycenter. The location of the Viewpoint in three-space is defined as the vector addition of ViewPointReference, and the vector defined by product of ViewScaleFactor and ViewPointVector in the coordinate system chosen by the user.km or N/AN/AFRR-28.2.5G+SNone
OrbitViewViewScaleFactor StringTextBox1Real Number ≥ 0SetThe ViewScaleFactor field scales ViewPointVector before adding it to ViewPointReference. The ViewScaleFactor allows the user to back away from an object to fit in the field of view.N/AN/AFRR-28.2.4G+SNone
OrbitViewViewUpAxis StringDrop Down MenuZX , -X , Y , -Y , Z , -ZSetThe ViewUpAxis allows the user to define which axis of the ViewUpCoordinateSystem that will appear as the up direction in an Orbitview plot. See the comments under ViewUpCoordinateSystem for more details of fields used to determine the up direction in an Orbitview plot.N/AN/AFRR-28.2.6G+SNone
OrbitViewViewUpCoordinateSystem StringDrop Down MenuEarthMJ2000EqAny default or user defined coordinate systemSetThe ViewUpCoordinateSystem and ViewUpAxis fields are used to determine which direction appears as up in an Orbitview plot and together with the fields associated the the View Direction, uniquely define the view. The fields associated with the View Definition allow the user to define the point of view in 3-space, and the direction of the line of sight. However, this information alone is not enough to uniquely define the view. We also must provide how the view is oriented about the line of sight. This is accomplished by defining what direction should appear as the up direction in the plot and is configured using the ViewUpCoordinateSystem field and the ViewUpAxis field. The ViewUpCoordinateSystem allows the user to select a coordinate system to define the up direction. Most of the time this system will be the same as the coordinate system chosen under the CoordinateSystem field.N/AN/AFRR-28.2.6G+SNone
OrbitViewWireFrame StringCheckBoxOffOff,OnSetWhen the WireFrame field is set to On, celestial bodies are drawn using a wireframe model. When the WireFrame field is set to Off, then celestial bodies are drawn using a full mapN/AN/AFRR-28.4.3G+SNone
OrbitViewXYPlane StringCheckBoxOnOn,OffSetThe XYPlane flag allows the user to tell GMAT to draw a grid representing the XY-plane of the coordinate system selected under the CoordinateSystem field of the OrbitView plot.N/AN/AFRR-28.4.2G+SNone
OrbitViewAdd StringLIstListBoxDefaultSC, EarthSpacecraftName CelestialBodyName LibrationPointName BarycenterNameSetThe Add subfield adds a spacecraft,celestial body, libration point,or barycenter to a plot. When creating a plot the Earth is added as a default body and may be removed by the user. The user can add a spacecraft, celestial body, libration point, or barycenter to a plot by using the name used to create the object. The GUI's Selected field is the equivalent of the script's Add field. In the event of no Add command or no objects in the Selected field, GMAT should run without the OrbitView plot and a warning message displayed in the message window. The following warning message is sufficient: The OrbitView named "DefaultOrbitView" will be turned off. No SpacePoints were added to plot.N/ANoneFRR-28.1.0G+SNone
OrbitViewCoordinateSystem UserDefStringDrop Down MenuEarthMJ2000EqAny default or user defined coordinate systemSetThe CoordinateSystem field on an OrbitView plot allows the user to select which coordinate system to use to draw the plot data. A coordinate system is defined as an origin and an axis system, and the CoordinateSystem field allows the user to determine the origin and axis system of an OrbitView plot. See the CoordinateSystem object fields for information of defining different types of coordinate systems.N/ANoneFRR-28.2.1G+SNone
PropagatorStopIfAccuracyIsViolatedBOOLEAN_TYPECheckboxtruetrue, falseSetFlag to stop propagation if integration error value defined by Accuracy is not satisfied.N/ANoneFRR-14.6.6G+S
PropagatorMaximumReductionDEFERREDN/A1e-005Real > 0.0 AND 0.0 < MaximumReduction < MinimumReductionSetLargest factor by which the step size will be reduced, such that the new step H_new = (MaximumReduction * H_old). Applies only to BulirshStoer Integrator.N/ATypeFRR-14.2S
PropagatorMinimumReductionDEFERREDN/A0.7Real > 0.0 AND 0.0 < MaximumReduction < MinimumReductionSetSmallest factor by which the step size will be reduced, such that the new step H_new = (MinimumReduction * H_old). Applies only to BulirshStoer Integrator.N/ATypeFRR-14.2S
PropagatorMinimumTolerancedeprecated- ignored with warningdeprecateddeprecateddeprecatedN/AdeprecatedN/AdeprecateddeprecatedN/A
PropagatorMaxStepAttemptsINTEGER_TYPEText Box50Integer > 1SetThe number of attempts the integrator takes to meet the tolerance defined by the Accuracy field.N/ATypeFRR-14.4.5G+S
PropagatorFMOBJECT_TYPEN/AN/AValid force model. Script only, SetIdentifies the force model used by an integrator. If no force model is provided, GMAT uses an Earth centered 4x4 gravity model only.N/ANone
PropagatorTypeOBJECT_TYPEDrop Down MenuRungeKutta89PrinceDormand78, PrinceDormand45, RungeKutta89,RungeKutta68, RungeKutta56, BulirschStoer, AdamsBashforthMoultonSetSpecifies the integrator or analytic propagator used to model time evolution of spacecraft motion. N/ASelecting a numerical integrator results in fields associated with numeri-integrator type propagators to be active. Selecting SPK causes fields associated with an SPK propagator.FRR-14.1.0, FRR-14.2, FRR-14.3S
PropagatorAccuracyREAL_TYPEText Box1e-11 except for ABM integrator which is 1e-10Real > 0, < 1 SetThe desired accuracy for an integration step. GMAT uses the method selected in the ErrorControl field on the Force Model to determine a metric of the integration accuracy. For each step, the integrator ensures that the error in accuracy is smaller than the value defined by the ErrorControl metric.N/ATypeFRR-14.4.2G+SCheck This
PropagatorInitialStepSizeREAL_TYPEText Box60Real > 0.0001SetThe size of the first step attempted by the integrator. secTypeFRR-14.4.1G+S
PropagatorLowerErrorREAL_TYPEText Box1e-13Real > 0 AND 0 < LowerError < TargetError < AccuracySetThe lower bound on integration error, used to determine when to make step size larger. Applies only to AdamsBashforthMoultonIntegratorN/AType, Accuracy, TargetErrorFRR-14.5.1G+S
PropagatorMaxStepREAL_TYPEText Box2700Real > 0 AND MinStep <= MaxStepSetThe maximum allowable step size.secType, MinStepFRR-14.4.4G+S
PropagatorMinStepREAL_TYPEText Box0.001Real >= 0 AND MinStep <= MaxStepSetThe minimum allowable step size.secType, MaxStepFRR-14.4.3G+S
PropagatorTargetErrorREAL_TYPEText Box1e-11Real > 0 AND 0 < LowerError < TargetError < AccuracySetThe nominal bound on integration error, used to set the target integration accuracy when adjusting step size. Applies only to AdamsBashforthMoultonIntegratorN/AType, Accuracy, LowerErrorFRR-14.5.2G+S
PropagatorCentralBodyDrop Down MenuEarthValid Celestial body.The central body of propagation.N/AOnly used when Type is set to SPK
PropagatorEpochFormatDrop Down MenuA1ModJulianA1ModJulian, TAIModJulian, UTCModJulian, TTModJulian, TDBModJulian, A1Gregorian, TAIGregorian, TTGregorian, UTCGregorian, TDBGregorianThe format of the epoch contained in the StartEpoch field.N/AOnly used when Type is set to SPKFRR-27.3.3.1G+S
PropagatorStart EpochText Box21545Gregorian: 04 Oct 1957 12:00:00.000 <= Epoch <= 28 Feb 2100 00:00:00.000 Modified Julian: 6116.0 <= Epoch <= 58127.5 or "FromSpacecraft"The initial epoch of propagation. When an epoch is provided that epoch is used as the initial epoch. When the keyword "FromSpacecraft" is provided, the start epoch is inherited from the spacecraft.See Description.Only used when Type is set to SPKFRR-27.3.3.2, FRR-27.3.3.1G+S
PropagatorStepSizeText Box300Real > 0The step size for an SPK PropagatorsecOnly used when Type is set to SPKFRR-27.3.1G+S
ReportFileFilenameFileNameText BoxReportFile1.txtValid File Path and NameSetThe FileName field allows the user to define the file path and file name for a report.NoneNoneFRR-30.1G+SNone
ReportFileColumnWidthIntegerText Box20integer > 1SetThe ColumnWidth field is used to define the width of the datacolumns in a report file. The value for ColumnWidth is appliedto all columns of data. For example, if ColumnWidth is set to20, then each data column will be 20 white-spaces wide.CharactersNoneFRR-30.3.1G+SNone
ReportFilePrecisionIntegerText Box16integer > 1SetThe Precision field allows the user to set the number of digits of the data written to a report.Same as variable being reported.NoneFRR-30.3.2G+SNone
ReportFileLeftJustifyStringCheckboxOnOn, OffSetWhen the LeftJustify field is set to On, then the data isleft justified and appears at the left most side of the column. Ifthe LeftJustify field is set to Off, then the data iscentered in the column.NoneNoneFRR-30.4.2G+SNone
ReportFileSolverIterationsStringDrop Down MenuCurrentAll, Current, NoneSetThe SolverIterations field determines whether or not data associated with perturbed trajectories during a solver (Targeter, Optimize) sequence is written to a report file. When SolverIterations is set to All, all perturbations/iterations are written to a reportfile. When SolverIterations is set to Current, only current solution is written to a reportfile. When SolverIterations is set to None, this shows only final solution after the end of an iterative process and reports only final solution to a report file.NoneNoneFRR-30.6.0G+SNone
ReportFileWriteHeadersStringCheckboxTrueTrue,FalseSetThe WriteHeaders field specifies whether to includeheaders that describe the variables in a report.NoneNoneFRR-30.5G+SNone
ReportFileWriteReportStringCheckboxTrueTrue,FalseSetThe WriteReport field specifies whether to write data to the report FileName.NoneNoneFRR-30.7G+SNone
ReportFileZeroFillStringCheckboxOffOn,OffSetThe ZeroFill allows zeros to be placed in data written to a report to match set precision NoneNoneFRR-30.3.3G+SNone
ReportFileAddUserDefStringList{DefaultSC.A1ModJulian, DefaultSC.EarthMJ2000Eq.X}Any user-defined parameter. Ex.Variables, Arrays, S/C parametersSetThe {Add} field allows a user to add user-defined variables to a report file. To add multiple user-defined variables, enclose the variables with curly brackets.Ex. MyReportName.Add ={Sat.X, Sat.Y, Var1, Array(1,1)}; TheGUI's Selected field is the equivalent of the script's Add field.In the event of no Add command or no objects in the Selected field, GMATshould run without the Report output and a warning message displayed in the message window. Thefollowing warning message is sufficient: Report plot will be turned off. No object has beenselected for reporting. NoneNoneFRR-30.2.0G+SNone
SolarSystemDEFilenameFileNameTextBox and Brower Button../data/planetary_ephem/de/leDE1941.405Valid DE fileSetThe path and name of the DE file.N/ANoneG+SNone
SolarSystemEphemerisSourceFileNameDrop Down MenuDE405DE405, DE421, DE424, or SPICESetThe ephemeris model for built-in celestial bodies.N/ANoneFRR-16.3.0G+SNone
SolarSystemLSKFilenameFileNameTextBox and Brower Button../data/time/naif0010.tlsValid SPK leapsecond kernelSetThe path and name of the SPK leap second kernel.N/ANoneFRR-16.3.2G+SNone
SolarSystemSPKFilenameFileNameTextBox and Brower Button../data/planetary_ephem/spk/DE421AllPlanets.bspValis SPK ephemeris kernel (.bsp)SetThe path and name of the SPK orbit ephemeris kernel.N/ANoneFRR-16.3.2G+SNone
SolarSystemEphemerisUpdateIntervalRealTextBox0Real >= 0SetThe time between updates for celetial body ephemeris. For example, if EphemerisUpdateInterval = 60, if an ephemeris call is made at time t = 1200, and a subsequent call is made at time t = 1210, the same ephemeris will be returned for the second call. This option is for high speed, low fidelity modelling or for use when modelling orbits far from third body perturbation sources.sNoneFRR-16.2.5G+SNone
SolarSystemUseTTForEphemerisStringCheckboxfalsetrue,falseSetFlag to use TerrestrialTime as input to the orbital ephemeris routines. When set to False TDB is used.N/ANoneFRR-16.2.6G+SNone
SpacecraftDateFormatEnumerationDrop Down MenuTAIModJulianA1ModJulian, TAIModJulian, UTCModJulian, TTModJulian, TDBModJulian, A1Gregorian, TAIGregorian, TTGregorian, UTCGregorian, TDBGregoriansetThe time system and format of the Epoch field. In the GUI, this field is called Epoch Format.N/AEpochFRR-2G+STCBGregorian TCBModJulian
SpacecraftModelFile FileNameTextBox, FileBrowseButton../data/vehicle/models/aura.3ds 3DS or POV model formatsSet The ModelFile field allows you to upload spacecraft models that are either in 3DS or POV format.N/A None FRR-5.1.0G+S None
SpacecraftAOPRealText Box314.1905515359921-Inf<AOP<Inf where Inf is defined by compiler's definition of a real.set,getThe orbital argument of periapsis expressed in the coordinate system chosen in the CoordinateSystem field.deg.CoordinateSystemFRR-1.1.1G+SNone
SpacecraftAZIRealText Box82.37742168155043-Inf<AZI<Inf where Inf is defined by compiler's definition of a real.set/getThe orbital velocity azimuth expressed in the coordinate system chosen in the CoordinateSystem field. CoordinateSystemFRR-1.2.2G+SNone
SpacecraftCdRealText Box2.2Cd >= 0setThe coefficent of drag used to compute the acceleration due to drag.N/ANoneFRR-4.3.1, FRR-4.4.3G+S-1
SpacecraftCrRealText Box1.80 <= CR <= 2.0setThe coefficent of reflectivity used to compute the acceleration due toSRP.N/ANoneFRR-4.3.1, FRR-4.4.2G+S-1 4
SpacecraftDCM11RealText Box1-1 <= DCM11 <=1set,getComponent (1,1) of the Direction Cosine Matrix. DCM11 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM12RealText Box0-1 <= DCM12 <=1set,getComponent (1,2) of the Direction Cosine Matrix. DCM12 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM13RealText Box0-1 <= DCM13 <=1set,getComponent (1,3) of the Direction Cosine Matrix. DCM13 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM21RealText Box0-1 <= DCM21 <=1set,getComponent (2,1) of the Direction Cosine Matrix. DCM21 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM22RealText Box1-1 <= DCM22 <=1set,getComponent (2,2) of the Direction Cosine Matrix. DCM22 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM23RealText Box0-1 <= DCM23 <=1set,getComponent (2,3) of the Direction Cosine Matrix. DCM23 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM31RealText Box0-1 <= DCM31 <=1set,getComponent (3,1) of the Direction Cosine Matrix. DCM31 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM32RealText Box0-1 <= DCM32 <=1set,getComponent (3,2) of the Direction Cosine Matrix. DCM32 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDCM33RealText Box1-1 <= DCM33 <=1set,getComponent (3,3) of the Direction Cosine Matrix. DCM33 is used for the following Attitude models: Spinner.dimless.AttitudeFRR-3.1.2G+S-1 1
SpacecraftDECRealText Box10.37584492005105-90 <= DEC <= 90set,getThe declination of the orbital position expressed in the coordinate system chosen in the CoordinateSystem field. deg.CoordinateSystemFRR-1.2.2 FRR-1.2.3G+SNone
SpacecraftDECVRealText Box7.747772036108118-90 <= DECV <= 90set,getThe declination of orbital velocity expressed in the coordinate system chosen in the CoordinateSystem field. deg.CoordinateSystemFRR-1.2.3G+SNone
SpacecraftDragAreaRealText Box15DragArea > = 0setThe area used to compute acceleration due to atmospheric drag.m^2NoneFRR-4.3.1, FRR-4.4.3G+S-1
SpacecraftDryMassRealText Box850DryMass >=0setThe dry mass of the spacecraft, which does not include fuel mass.KgNoneFRR-4.3.1, FRR-4.1G+S0 -1
SpacecraftECCRealText Box0.02454974900598137ECC < 0.9999999 or ECC > 1.0000001. If ECC > 1, SMA must be < 0set,getThe orbital eccentricity expressed in the coordinate system chosen in the CoordinateSystem field.N/ASMA, CoordinateSystemFRR-1.1.1G+S-1
SpacecraftEquinoctialHRealText Box-0.02423431419337062-0.99999 < EquinoctialH < 0.99999, AND sqrt(EquinoctialH^2 + EquinoctialK^2) < 0.99999 set, getA measure of the orbital eccentricity and argument of periapsis. EquinoctialH and EquinoctialK together govern how eliiptic an orbit is and where the periapsis is located. EquinotialH = ECC * sin(AOP)dimlessCoordinateSystemFRR-1.1.3G+S-1 1
SpacecraftEquinoctialKRealText Box-0.003922778585859663-0.99999 < EquinoctialK < 0.99999, AND sqrt(EquinoctialH^2 + EquinoctialK^2) < 0.99999set, getA measure of the orbital eccentricity and argument of periapsis. EquinoctialH and EquinoctialK together govern how elliptic an orbit is and where the periapsis is located. EquinotialK = ECC * cos(AOP)dimlessCoordinateSystemFRR-1.1.3G+S-1 1
SpacecraftEquinoctialPRealText Box-0.09038834725719359-Inf <= EquinoctialP <= Infset, getA measure of the orientation of the orbit. EquinoctialP and EquinoctialQ together govern how an orbit is oriented. EquinotialP = tan(INC/2)*sin(RAAN).dimlessCoordinateSystemFRR-1.1.3G+S-1 1
SpacecraftEquinoctialQRealText Box0.06716454898232072-Inf <= EquinoctialQ <= Infset, getA measure of the orientation of the orbit. EquinoctialP and EquinoctialQ together govern how an orbit is oriented. EquinotialQ = tan(INC/2)*cos(RAAN).dimlessCoordinateSystemFRR-1.1.3G+S-1 1
SpacecraftEulerAngle1RealText Box0-Inf <= EulerAngle1 <= Infset,getThe value of the first Euler angle. EulerAngle1 is used for the following Attitude models: Spinner.Deg.AttitudeFRR-3.1.3G+SNone
SpacecraftEulerAngle2RealText Box0-Inf <= EulerAngle2 <= Infset,getThe value of the second Euler angle. EulerAngle2 is used for the following Attitude models: Spinner.Deg.AttitudeFRR-3.1.3G+SNone
SpacecraftEulerAngle3RealText Box0-Inf <= EulerAngle3 <= Infset,getThe value of the third Euler angle. EulerAngle3 is used for the following Attitude models: Spinner.Deg.AttitudeFRR-3.1.3G+SNone
SpacecraftEulerAngleRate1RealText Box0-Inf <= EulerAngleRate1 <= Infset,getThe value of the first Euler angle rate. EulerAngleRate1 is used for the following Attitude models: Spinner.Deg./sAttitudeFRR-3.2.2G+SNone
SpacecraftEulerAngleRate2RealText Box0-Inf <= EulerAngleRate2 <= Infset,getThe value of the second Euler angle rate. EulerAngleRate2 is used for the following Attitude models: Spinner.Deg./sAttitudeFRR-3.2.2G+SNone
SpacecraftEulerAngleRate3RealText Box0-Inf <= EulerAngleRate3 <= Infset,getThe value of the third Euler angle rate. EulerAngleRate3 is used for the following Attitude models: Spinner.Deg./sAttitudeFRR-3.2.2G+SNone
SpacecraftFPARealText Box88.608703653704480<= INC <= 180set, getThe orbital flight path angle expressed in the coordinate system chosen in the CoordinateSystem field. Deg.CoordinateSystemFRR-1.2.2G+SNone
SpacecraftINCRealText Box12.850080056580970<= INC <= 180set,getThe orbital inclination expressed in the coordinate system chosen in the CoordinateSystem field.deg.CoordinateSystemFRR-1.1.1G+SNone
SpacecraftMLONGRealText Box357.9131803707105-360 <= MLONG <=360set,getA measure of the location of the spacecraft in it's orbit. MLONG = AOP + RAAN + MA.deg.CoordinateSystemFRR-1.1.3G+SNone
SpacecraftModelOffsetX RealSlider, TextBox0.000000-3.5 <= Real <= 3.5Set The ModelOffsetX field lets you translate Spacecraft in +X or -X axis of central body's coordinate system.N/ANone FRR-5.2G+S None
SpacecraftModelOffsetY RealSlider, TextBox0.000000-3.5 <= Real <= 3.5Set The ModelOffsetY field lets you translate Spacecraft in +Y or -Y axis of central body's coordinate system.N/ANone FRR-5.2G+S None
SpacecraftModelOffsetZ RealSlider, TextBox0.000000-3.5 <= Real <= 3.5Set The ModelOffsetZ field lets you translate Spacecraft in +Z or -Z axis of central body's coordinate system.N/ANone FRR-5.2G+S None
SpacecraftModelRotationX RealSlider, TextBox0.000000-180 <= Real <= 180Set The ModelRotationX field lets you do a fixed rotation of spacecraft's attitude w.r.t X-axis of central body's coordinate system.Deg.None FRR-5.3G+S None
SpacecraftModelRotationY RealSlider, TextBox0.000000-180 <= Real <= 180Set The ModelRotationY field lets you do a fixed rotation of spacecraft's attitude w.r.t Y-axis of central body's coordinate system.Deg.None FRR-5.3G+S None
SpacecraftModelRotationZ RealSlider, TextBox0.000000-180 <= Real <= 180Set The ModelRotationZ field lets you do a fixed rotation of spacecraft's attitude w.r.t Z-axis of central body's coordinate system.Deg.None FRR-5.3G+S None
SpacecraftModelScale RealSlider, TextBox3.0000000.001 <= Real <= 1000Set The ModelScale field lets you apply a scale factor to the spacecraft model's size.N/ANone FRR-5.4G+S None
Spacecraft ModelFileFileNameTextBox and Brower Button../data/vehicle/models/aura.3ds3DS or POV model formatsSetThe ModelFile field allows you to upload any spacecraft model that is in 3DS or POV model format.N/ANoneFRR-5.1.0G+SNone
SpacecraftQ1RealText Box0-Inf <= Q1 <= Infset,getFirst component of quaternion. GMAT’s quaternion representation includes the three “vector” components as the first three elements in the quaternion and the “rotation” component as the last element in the quaternion. Q1 is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.1G+S None
SpacecraftQ2RealText Box0-Inf <= Q2 <= Infset,getSecond component of quaternion. GMAT’s quaternion representation includes the three “vector” components as the first three elements in the quaternion and the “rotation” component as the last element in the quaternion. Q2 is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.1G+S None
SpacecraftQ3RealText Box0-Inf <= Q3 <= Infset,getThird component of quaternion. GMAT’s quaternion representation includes the three “vector” components as the first three elements in the quaternion and the “rotation” component as the last element in the quaternion. Q3 is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.1G+S None
SpacecraftQ4RealText Box1-Inf <= Q4 <= Infset,getFourth component of quaternion. GMAT’s quaternion representation includes the three “vector” components as the first three elements in the quaternion and the “rotation” component as the last element in the quaternion. Q4 is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.1G+S None
SpacecraftRARealText Box0Input: -Inf<= RA <= Inf Output -180<= RA <= 180set,getThe right ascension of the orbital position expressed in the coordinate system chosen in the CoordinateSystem field. deg.CoordinateSystemFRR-1.2.2 FRR-1.2.3G+SNone
SpacecraftRAANRealText Box306.6148021947984-Inf<RAAN<Inf where Inf is defined by compiler's definition of a real.set,getThe orbital right ascension of the ascending node expressed in the coordinate system chosen in the CoordinateSystem field.deg.CoordinateSystemFRR-1.1.1G+SNone
SpacecraftRadApoRealText Box7368.49911046818abs(RadApo) >= 1 meter.set,getThe orbital radius of apoapsisexpressed in the coordinate system chosen in the CoordinateSystem field. The radius of apoapsis is the maximum distance (osculating) between the spacecraft and celestial body at the origin of CoordinateSystem.kmCoordinateSystemFRR-1.1.2G+S0
SpacecraftRadPerRealText Box7015.378524789846abs(RadPer) >= 1 meter.set,getThe orbital radius of periapsis expressed in the coordinate system chosen in the CoordinateSystem field. The radius of periapsis is the minimum distance (osculating) between the spacecraft and celestial body at the origin of CoordinateSystem.kmCoordinateSystemFRR-1.1.2G+S0 -1
SpacecraftRAVRealText Box90Input: -Inf<= RA <= Inf Output -180<= RA <= 180The right ascension of orbital velocity expressed in the coordinate system chosen in the CoordinateSystem field. deg.CoordinateSystemFRR-1.2.3G+SNone
SpacecraftRMAGRealText Box7218.032973047435RMAG >= 1e-10set,getThe magnitude of the orbital position vector expressed in the coordinate system chosen in the CoordinateSystem field.kmCoordinateSystemFRR-1.2.2 FRR-1.2.3 G+S-1
SpacecraftSMARealText Box7191.938817629013SMA < -0.001 m or SMA > 0.001 meter. If SMA < 0, then ECC must be > 1 set,getThe orbital semi-major axis expressed in the coordinate system chosen in the CoordinateSystem field.kmECC, CoordinateSystemFRR-1.1.1G+S0
SpacecraftSRPAreaRealText Box1SRPArea >= 0 setThe area used to compute acceleration due to solar radiation pressure.m/s^2NoneFRR-4.3.1,FRR-4.4.4G+S-1
SpacecraftTARealText Box99.8877493320488-Inf<TA<Inf where Inf is defined by compiler's definition of a real.set,getThe orbital true anomaly expressed in the coordinate system chosen in the CoordinateSystem field.deg.CoordinateSystemFRR-1.1.1G+SNone
SpacecraftVMAGRealText Box7.417715281675348VMAG >= 1e-10set, getThe magnitude of the orbital velocity vector expressed in the coordinate system chosen in the CoordinateSystem field.km/sCoordinateSystemFRR-1.2.2 FRR-1.2.3 -1
SpacecraftVXRealText Box0-Inf<Y<Inf where Inf is defined by compiler's definition of a real.set,getThe x-component of the spacecraft velocity with respect to the coordinate system chosen in the spacecraft's CoordinateSystem field.km/sCoordinateSystemFRR-1.2.1G+SNone
SpacecraftVYRealText Box7.35-Inf<Y<Inf where Inf is defined by compiler's definition of a real.set,getThe y-component of the spacecraft velocity with respect to the coordinate system chosen in the spacecraft's CoordinateSystem field.km/sCoordinateSystemFRR-1.2.1G+SNone
SpacecraftVZRealText Box1-Inf<Y<Inf where Inf is defined by compiler's definition of a real.set,getThe z-component of the spacecraft velocity with respect to the coordinate system chosen in the spacecraft's CoordinateSystem field.km/sCoordinateSystemFRR-1.2.1G+SNone
SpacecraftXRealText Box7100-Inf<X<Inf where Inf is defined by compiler's definition of a real.set,getThe x-component of the spacecraft position with respect to the coordinate system chosen in the spacecraft's CoordinateSystem field.kmCoordinateSystemFRR-1.2.1G+SNone
SpacecraftYRealText Box0-Inf<Y<Inf where Inf is defined by compiler's definition of a real.set,getThe y-component of the spacecraft position with respect to the coordinate system chosen in the spacecraft's CoordinateSystem field.kmCoordinateSystemFRR-1.2.1G+SNone
SpacecraftZRealText Box1300-Inf<X<Inf where Inf is defined by compiler's definition of a real.set,getThe z-component of the spacecraft position with respect to the coordinate system chosen in the spacecraft's CoordinateSystem field.kmCoordinateSystemFRR-1.2.1G+SNone
SpacecraftA1GregorianSee A1ModJulianSee A1ModJulian01 Jan 2000 12:00:00.034See Epochset, get (mission sequence only)The spacecraft orbit epoch in the A.1 system and the Gregorian format.N/ASee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftTAIGregorianSee A1ModJulianSee A1ModJulian01 Jan 2000 12:00:00.000See Epochset, get (mission sequence only)The spacecraft orbit epoch in the TAI system and the Gregorian format.See A1GregorianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftTAIModJulianSee A1ModJulianSee A1ModJulian21545See Epochset, get (mission sequence only)The spacecraft orbit epoch in the TAI system and the Modified Julian format.See A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftTDBGregorianSee A1ModJulianSee A1ModJulian01 Jan 2000 12:00:32.184See Epochset, get (mission sequence only)The spacecraft orbit epoch in the TDB system and the Gregorian format.See A1GregorianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftTDBModJulianSee A1ModJulianSee A1ModJulian21545.00037249916See Epochset, get (mission sequence only)The spacecraft orbit epoch in the TDB system and the Modified Julian format.See A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftTTGregorianSee A1ModJulianSee A1ModJulian01 Jan 2000 12:00:32.184See Epochset, get (mission sequence only)The spacecraft orbit epoch in the TT system and the Gregorian format.See A1GregorianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftTTModJulianSee A1ModJulianSee A1ModJulian21545.0003725See Epochset, get (mission sequence only)The spacecraft orbit epoch in the TT system and the Modified Julian format.See A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftUTCGregorianSee A1ModJulianSee A1ModJulian01 Jan 2000 11:59:28.000See Epochset, get (mission sequence only)The spacecraft orbit epoch in the UTC system and the Gregorian format.See A1GregorianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftUTCModJulianSee A1ModJulianSee A1ModJulian21544.99962962963See Epochset, get (mission sequence only)The spacecraft orbit epoch in the UTC system and the Modified Julian format.See A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulianSee A1ModJulian
SpacecraftEpoch.A1GregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulian01 Jan 2000 12:00:00.034See Epochset, getThe spacecraft orbit epoch in the A.1 system and the Gregorian format.N/ASee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.TAIGregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulian01 Jan 2000 12:00:00.000See Epochset, getThe spacecraft orbit epoch in the TAI system and the Gregorian format.See Epoch.A1GregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.TAIModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian21545See Epochset, getThe spacecraft orbit epoch in the TAI system and the Modified Julian format.See Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.TDBGregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulian01 Jan 2000 12:00:32.184See Epochset, getThe spacecraft orbit epoch in the TDB system and the Gregorian format.See Epoch.A1GregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.TDBModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian21545.00037249916See Epochset, getThe spacecraft orbit epoch in the TDB system and the Modified Julian format.See Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.TTGregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulian01 Jan 2000 12:00:32.184See Epochset, getThe spacecraft orbit epoch in the TT system and the Gregorian format.See Epoch.A1GregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.TTModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian21545.0003725See Epochset, getThe spacecraft orbit epoch in the TT system and the Modified Julian format.See Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.UTCGregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulian01 Jan 2000 11:59:28.000See Epochset, getThe spacecraft orbit epoch in the UTC system and the Gregorian format.See Epoch.A1GregorianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftEpoch.UTCModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian21544.99962962963See Epochset, getThe spacecraft orbit epoch in the UTC system and the Modified Julian format.See Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulianSee Epoch.A1ModJulian
SpacecraftAttitudeStringDrop Down MenuCoordinateSystemFixedCoordinateSystemFixed, Spinner, SpiceAttitudesetThe attitude mode for the spacecraft.N/AThe activity of various fields are effected by the selection of Attitude field. See Remarks section for further details.FRR-7.1.0G+SNone
SpacecraftAttitudeDisplayTypeStringDrop Down MenuQuaternionQuaternion, EulerAngles, DirectionCosineMatrix,MRPssetThe attitude representation to display in the GUI and script file. AttitudeDisplayType is used for the following Attitude models: Spinner.N/AAttitudeFRR-3.1.0G+SNone
SpacecraftAttitudeRateDisplayStateTypeStringDrop Down MenuAngularVelocityAngularVelocity, EulerAngleRatessetThe attitude rate representation to display in the GUI and script file. AttitudeRateDisplayType is used for the following Attitude models: Spinner.N/AAttitudeFRR-3.2.0G+SNone
SpacecraftDisplayStateTypeStringTextBoxCartesian'Cartesian', 'Keplerian', 'ModifiedKeplerian', 'SphericalAZFPA', 'SphericalRADEC', 'Equinoctial'set The orbital state type displayed in the GUI. Allowed state types are dependent upon the selection of CoordinateSystem. For example, if the coordinate system does not have a celestial body at the origin, Keplerian, ModifiedKeplerian, and Equinoctial are not allowed options for StateType.N/ACoordinateSystemFRR-1.1.0G+SNone
SpacecraftA1ModJulianTimeN/A21545.00000039794See Epochset, get (mission sequence only)The spacecraft orbit epoch in the A.1 system and the Modified Julian format.DaysNoneFRR-2SNone
SpacecraftCurrA1MJDTimeN/A21545.00000039794See Epochset, get (mission sequence only)[Deprecated] The current epoch in the A1ModJulian format.DaysNoneFRR-2SNone
SpacecraftEpochTimeText Box21545Gregorian: 04 Oct 1957 12:00:00.000 <= Epoch <= 28 Feb 2100 00:00:00.000 Modified Julian: 6116.0 <= Epoch <= 58127.5setThe time and date corresponding to the specified orbit state. It defines the start time for propagation using the Propagate command.N/A (Gregorian) Days (ModJulian)DateFormatFRR-2G+SNone
SpacecraftEpoch.A1ModJulianTimeN/A21545.00000039794See Epochset, getThe spacecraft orbit epoch in the A.1 system and the Modified Julian format.DaysNoneFRR-2NoneNone
SpacecraftAttitudeCoordinateSystemUserDefStringDrop Down MenuEarthMJ2000EqValid CoordinateSystem Resource.setThe CoordinateSystem used in attitude computations. CoordinateSystem field is only used for the following attitude models: CoordinateSystemFixed.N/AAttitudeFRR-7.1.2G+SNone
SpacecraftCoordinateSystemUserDefStringDrop Down MenuEarthMJ2000EqCoordinateSystemsetThe coordinate system with respect to which the orbital state is defined. The CoordinateSystem field is dependent upon the StateType field. If the coordinate system chosen by the user does not have a gravitational body at the origin, then the state types Keplerian, ModifiedKeplerian, and Equinoctial are not permitted. N/AStateTypeFRR-1.3G+SNone
SpacecraftAngularVelocityXText Box0Real numberset,getThe x-component of spacecraft body angular velocity expressed in the inertial frame. AngularVelocityX is used for the following Attitude models: Spinner.deg./sAttitude.FRR-3.2.1G+S
SpacecraftAngularVelocityY Text Box0Real numberset,getThe y-component of spacecraft body angular velocity expressed in the inertial frame. AngularVelocityY is used for the following Attitude models: Spinner.deg./sAttitude.FRR-3.2.1G+S
SpacecraftAngularVelocityZText Box0Real numberset,getThe z-component of spacecraft body angular velocity expressed in the inertial frame. AngularVelocityZ is used for the following Attitude models: Spinner.deg./sAttitude.FRR-3.2.1G+S
SpacecraftEulerAngleSequenceDrop Down Menu321123,231,312,132,321,213,121,232,313,131,323,212setThe EulerAngleSequence used for EulerAngle input and output..N/AEulerAngle1,EulerAngle2,EulerAngle3,EulerAngleRate1,EulerAngleRate2,EulerAngleRate3FRR-3.1.3G+S
SpacecraftMRP1TextBox0-Inf <= MRP1 <= Infset,getThe value of the first modified Rodrigues parameter. MRP1 is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.4G+S
SpacecraftMRP2TextBox0-Inf <= MRP2 <= Infset,getThe value of the second modified Rodrigues parameter. MRP2 is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.4G+S
SpacecraftMRP3TextBox0-Inf <= MRP3 <= Infset,getThe value of the third modified Rodrigues parameter. MRP3 is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.4G+S
SpacecraftNAIFIdTextBox-123456789IntegersetThe spacecraft Id used in SPICE kernels.N/AAttitudeFRR-7.1.3,FRR-27.1.1G+S
SpacecraftNAIFIdReferenceFrameTextBox-123456789IntegersetThe id of the spacecraft body frame used in SPICE kernels.N/AAttitudeFRR-7.1.3G+S
SpacecraftIdNot in GUI.SatIdStringsetThe spacecraft Id used in tracking data files. This field is only used for EstimationPlugin protype functionality.N/ANoneS
SpacecraftFrameSpiceKernelNameSelection BoxNo Default. The field is emtpy.List of path and filenames.setSPK Kernels for spacecraft body frame. SPK Frame kernels have extension ".TF".N/AAttitudeFRR-7.1.3G+S
SpacecraftSCClockSpiceKernelNameSelection BoxNo Default. The field is emtpy.List of path and filenames.setSPK Kernels for spacecraft clock. SPK clock kernels have extension ".TSC".N/AAttitudeFRR-7.1.3G+S
SpacecraftAttitudeSpiceKernelNameSelection BoxNo Default. The field is emtpy.List of path and filenames.setSPK Kernels for spacecraft attitude. SPK atttitude kernels have extension ".BC".N/AAttitudeFRR-7.1.3G+S
SpacecraftOrbitSpiceKernelNameSelection BoxNo Default. The field is emtpy.List of path and filenames.setSPK Kernels for spacecraft orbit. SPK orbit kernels have extension ".BSP".N/APropagator.TypeFRR-27.1.1G+S
SpacecraftQuaternionNot in GUI.[0 0 0 1];Four Vector.The quaternion vector. GMAT’s quaternion representation includes the three “vector” components as the first three elements in the quaternion and the “rotation” component as the last element in the quaternion. Quaternion is used for the following Attitude models: Spinner.dimlessAttitudeFRR-3.1.1S
ThrusterDecrementMass BooleanFALSEtrue, falsesetFlag which determines if the FuelMass is to be decremented as it used.    N/ANoneFRR-9.5G+SNone
ThrusterC1Real10Realset, getThrust coefficient.NNoneFRR-9.4.6G+SNone
ThrusterC10Real0Realset, getThrust coefficient.N/kPa^C11NoneFRR-9.4.6G+SNone
ThrusterC11Real0Realset, getThrust coefficient.NoneNoneFRR-9.4.6G+SNone
ThrusterC12Real0Realset, getThrust coefficient.NNoneFRR-9.4.6G+SNone
ThrusterC13Real0Realset, getThrust coefficient.NoneNoneFRR-9.4.6G+SNone
ThrusterC14Real0Realset, getThrust coefficient.1/kPaNoneFRR-9.4.6G+SNone
ThrusterC15Real0Realset, getThrust coefficient.NoneNoneFRR-9.4.6G+SNone
ThrusterC16Real0Realset, getThrust coefficient.1/kPaNoneFRR-9.4.6G+SNone
ThrusterC2Real0Realset, getThrust coefficient.N/kPaNoneFRR-9.4.6G+SNone
ThrusterC3Real0Realset, getThrust coefficient.NNoneFRR-9.4.6G+SNone
ThrusterC4Real0Realset, getThrust coefficient.N/kPaNoneFRR-9.4.6G+SNone
ThrusterC5Real0Realset, getThrust coefficient.N/kPa^2NoneFRR-9.4.6G+SNone
ThrusterC6Real0Realset, getThrust coefficient.N/kPa^C7NoneFRR-9.4.6G+SNone
ThrusterC7Real0Realset, getThrust coefficient.NoneNoneFRR-9.4.6G+SNone
ThrusterC8Real0Realset, getThrust coefficient.N/kPa^C9NoneFRR-9.4.6G+SNone
ThrusterC9Real0Realset, getThrust coefficient.NoneNoneFRR-9.4.6G+SNone
ThrusterDutyCycleReal10 <= Real <= 1set, getFraction of time that the thrusters are on during a maneuver.  The thrust applied to the spacecraft is scaled by this amount.  Note that this scale factor also affects mass flow rate.  NoneNoneFRR-9.4.1G+S-1
ThrusterGravitationalAccel Real9.81Real > 0set, getValue of the gravitational acceleration used for the FuelTank/Thruster calculations.  m/s^2NoneFRR-9.4.3G+S0 -1
ThrusterK1Real300Realset, getIsp coefficientsNoneFRR-9.4.5G+SNone
ThrusterK10Real0Realset, getIsp coefficients/kPa^C11NoneFRR-9.4.5G+SNone
ThrusterK11Real0Realset, getIsp coefficientNoneNoneFRR-9.4.5G+SNone
ThrusterK12Real0Realset, getIsp coefficientsNoneFRR-9.4.5G+SNone
ThrusterK13Real0Realset, getIsp coefficientNoneNoneFRR-9.4.5G+SNone
ThrusterK14Real0Realset, getIsp coefficient1/kPaNoneFRR-9.4.5G+SNone
ThrusterK15Real0Realset, getIsp coefficientNoneNoneFRR-9.4.5G+SNone
ThrusterK16Real0Realset, getIsp coefficient1/kPaNoneFRR-9.4.5G+SNone
ThrusterK2Real0Realset, getIsp coefficients/kPaNoneFRR-9.4.5G+SNone
ThrusterK3Real0Realset, getIsp coefficientsNoneFRR-9.4.5G+SNone
ThrusterK4Real0Realset, getIsp coefficients/kPaNoneFRR-9.4.5G+SNone
ThrusterK5Real0Realset, getIsp coefficients/kPa^2NoneFRR-9.4.5G+SNone
ThrusterK6Real0Realset, getIsp coefficients/kPa^C7NoneFRR-9.4.5G+SNone
ThrusterK7Real0Realset, getIsp coefficientNoneNoneFRR-9.4.5G+SNone
ThrusterK8Real0Realset, getIsp coefficients/kPa^C9NoneFRR-9.4.5G+SNone
ThrusterK9Real0Realset, getIsp coefficientNoneNoneFRR-9.4.5G+SNone
ThrusterThrustDirection1Real1Realset, getThrustDirection1, divided by the RSS of the three direction components, forms the x component of the spacecraft thrust vector direction. NoneNoneFRR-9.3.1G+SNone
ThrusterThrustDirection2Real0Realset, getThrustDirection2, divided by the RSS of the three direction components, forms the y component of the spacecraft thrust vector direction. NoneNoneFRR-9.3.1G+SNone
ThrusterThrustDirection3Real0Realset, getThrustDirection3, divided by the RSS of the three direction components, forms the z component of the spacecraft thrust vector direction. NoneNoneFRR-9.3.1G+SNone
ThrusterThrustScaleFactorReal1Real >= 0set, getThrustScaleFactor is a scale factor that is multiplied by the thrust vector, for a given thruster, before the thrust vector is added into the total acceleration.  Note that the value of this scale factor does not affect the mass flow rate.   NoneNoneFRR-9.4.1G+S-1
ThrusterAxes StringVNBVNB, LVLH, MJ2000Eq, SpacecraftBodysetThe Axes field allows the user to define a spacecraft centered set of axes for the thruster.  N/AThe Axes field is only active if the CoordinateSystem field is set to Local.  FRR-9.2.1-3G+SNone
ThrusterCoordinateSystemUserDefStringLocalLocal, EarthMJ2000Eq, EarthMJ2000Ec, EarthFixed, or any user defined systemsetThe CoordinateSystem field for a thruster determines what coordinate system the orientation parameters, ThrustDirection1, ThrustDirection2, and ThrustDirection3 refer to.  N/ANoneFRR-9.2.1-3G+SNone
ThrusterOrigin UserDefStringEarthSun, Mercury, Venus, Earth, Luna, Mars,Jupiter, Saturn, Uranus, Neptune, PlutosetThe Origin field, used in conjunction with the Axes field, allows the user to define a spacecraft centered set of axes for the thruster.  Origin has no affect when a Local coordinate system is used and the Axes are set to MJ2000Eq or SpacecraftBody.N/AThe Origin field is only active if the CoordinateSystem field is set to Local.  FRR-9.2.1-3G+SNone
ThrusterTankUserDefStringN/AUser defined list of FuelTanks.  setTank from which the thruster draws propellant from.N/AThe Tank field is only active if the DecrementMass field is set to true.FRR-9.4.4G+S0 -1
VF13adReportFileFileNameVF13adVFname.data, where VFname is the name of the VF13ad resource.  Any user-defined file namesetThe ReportFile field contains the path and file name of the report file.NoneShowProgess, ReportStyleFRR-21.3G+SNone
VF13adMaximumIterationsInteger200Integer > 0setThe MaximumIterations field allows the user to set the maximum allowable number of optimizer iterations. NoneNoneFRR-21.1.1G+SNone
VF13adFeasibilityToleranceReal1e-3Real > 0setThe FeasibilityTolerance field specifies the accuracy with which the user desires a constraint to be satisfied.NoneNoneFRR-21.1.3.4G+S-1 0
VF13adToleranceReal1e-5Real > 0setThe Tolerance field specifies the measure the optimizer will use to determine when an optimal solution has been found.  been foundNoneNoneFRR-21.1.2G+SNone
VF13adReportStyleStringNormalNormal, Concise, Verbose, DebugsetThe ReportStyle field determines the amount and type of data written to the message window and to the report specified by field ReportFile for each iteration of the solver (When ShowProgress is true).  Currently, the Normal, debug, and Concise options contain the same information: the values for the control variables, the constraints, and the objective function.  In addition to this information, the Verbose option also contains values of the optimizer-scaled control variables.  NoneShowProgress, ReportFileFRR-21.3G+SNone
VF13adShowProgressStringTRUEtrue, falsesetThe ShowProgress field determines whether data pertaining to iterations of the solver is both displayed in the message window and written to the report specified by the ReportFile field. When ShowProgress is true, the amount of information contained in the message window and written in the report is controlled by the ReportStyle field.NoneReportStyle, ReportFileFRR-21.2.1-4G+SNone
VF13adUseCentralDifferencesStringfalsetrue, falsesetThe UseCentralDifferences field allows the user to choose whether or not to use central differencing for numerically determining the derivative. For the default, 'false' value of this field, forward differencing is used to calculate the derivative.  NoneNoneFRR-21.1.3.1-2G+SNone
XYPlotMaximizedStringN/Afalsetrue,falsesetThe Maximized field allows the user to maximize the XYPlot window.NoneNoneFRR-29.12SNone
XYPlotUpperLeftStringN/A[0 0]Any Real numberSetThe UpperLeft field allows the user to pan the XYPlot display window in any direction. First value in [0 0] matrix helps to pan the XYPlot window horizontally and second value helps to pan the window vertically.N/ANoneFRR-29.11 SNone
XYPlotRelativeZOrderStringN/A0Any Real numberSetRelativeZOrder field allows the user to select which XYPlot window to display first on the screen. The XYPlot with lowest RelativeZOrder value will be displayed last while XYPlot with highest RelativeZOrder value will be displayed first.N/ANoneFRR-29.13SNone
XYPlotShowGridStringCheckBoxTrueTrue,FalseSetWhen the ShowGrid field is set to True, then a grid is drawn on an xy-plot. When the ShowGrid field is set to False, then a grid is not drawn.NoneNoneFRR-29.4G+SNone
XYPlotShowPlotStringCheckBoxTrueTrue,FalseSetThe ShowPlot field allows the user to turn off a plot for a particular run, without deleting the plot object, or removing it from the script. If you select true, then the plot will be shown. If you select false, then the plot will not be shown.NoneNoneFRR-29.6G+SNone
XYPlotSizeStringN/A[ 0 0 ]Any Real numberSetThe Size field allows the user to control the display size of XYPlot window. First value in [0 0] matrix controls horizonal size and second value controls vertical size of XYPlot display window.N/ANoneFRR-29.10 SNone
XYPlotSolverIterationsStringDrop Down MenuCurrentCurrent, All, NoneSetThe SolverIterations field determines whether or not data associated with perturbed trajectories during a solver (Targeter, Optimize) sequence is displayed in the XY plot. When SolverIterations is set to All, all perturbations/iterations are plotted in the XY Plot. When SolverIterations is set to Current, only the current solution or perturbation is plotted in XY Plot. When SolverIterations is set to None, only the final nominal run is plotted on the XYPlot.NoneNoneFRR-29.5.0G+SNone
XYPlotXVariableUserDefStringButtonDefaultSC.A1ModJulianAny user variable, array element, or spacecraft parameter that evaluates to a real numberSet,getThe XVariable field allows the user to define the independent variable for an xy-plot. Only one variable can be defined as an independent variable. For example, the line MyXYPlot.XVariable = DefaultSC.A1ModJulian sets the independent variable to be the epoch of DefaultSC in the A1 time system and modified Julian format.NoneFRR-29.2.0G+SNone
XYPlotYVariablesUserDefStringListButtonDefaultSC.EarthMJ2000Eq.XAny user variable, array element, or spacecraft parameter that evaluates to a real numberSet,getThe YVariables field allows the user to add dependent variables to an xy-plot. All dependent variables are plotted on the y-axis vs the independent variable defined by XVariable. The dependent variable(s) should always be included in curly braces. For example, MyXYPlot.YVariables = {DefaultSC.EarthMJ2000Eq.Y, DefaultSC.EarthMJ2000Eq.Z}. NoneNoneFRR-29.2.0 & FRR-29.3G+SNone