Two sets of propagator controls are available: one set for use during estimation and simulation processes and another set which may be enabled for use in ephemeris prediction. When enabled, the predict controls are applied during ephemeris predictions generated at the end of processes (Filter, Smoother, Simulator, Least Squares) and during ephemeris predictions generated directly from satellite objects.
In the special case where a finite maneuver is modeled in the prediction interval and the GaussJackson integrator specified for use in prediction, the GaussJackson integrator is used up to the maneuver time, a maneuver integrator is used to cross the maneuver, then the GaussJackson integrator is restarted. If the maneuver has custom integrator setting, those settings are used during the maneuver time span, otherwise the nominal integrator settings are used to cross the maneuver.
The following Propagator Controls can be set for each satellite:
Propagator Controls  

Control  Description 
IntegrationMethod  BulirschStoer  Integration method based on Richardson extrapolation with automatic step size control. 
IntegrationMethod  RK4  RungeKutta integration method of 4th order with no error control for the integration step size. 
IntegrationMethod  RKF 7(8)  RungeKuttaFehlberg integration method of 7th order with 8th order error control for the integration step size. 
IntegrationMethod  RKV 8(9)  RungeKuttaVerner integration method of 8th order with 9th order error control for the integration step size. 
IntegrationMethod  GaussJackson* 
12th order GaussJackson integration method with no error control implemented for the integration step size. This option is restricted for use during ephemeris prediction since it must be restarted after measurement updates. Note: The GaussJackson integration method requires smaller time steps than most of the single step methods with a step of 30 seconds being appropriate for LEO. 
MinimumAltitude**  Limits propagation of ephemeris for a satellite when it is approaching the surface of its central body. The value is honored if drag is not being modeled. If drag is modeled and a variable step size is used, then the selected drag model will provide its minimum valid altitude. If drag is modeled and a fixed step size is used, then the minimum allowed altitude is 90 km. 
Enabled*  Boolean flag indicating if custom integrator settings are desired for use in ephemeris prediction. See description of where these settings would be used above. 
UseVOP  The UseVOP attribute is a boolean flag; if true, a variation of parameters in universal variables formulation of the equations of motion is used. If false, the Cowell formulation is used. Not available in combination with GaussJackson integration method. 
PredictorCorrectorScheme 

MaxCorrectorIterations  Maximum number of corrector iterations allowed in GaussJackson predictor/corrector integration scheme. Valid for the GaussJackson integration method only. 
StepSize  Select a StepControlMethod (below) and enter the appropriate parameters. 
The following step control methods and parameters are available for defining step size:
StepControlMethod Options  

StepControlMethod  Parameter  Description 
Fixed  Time  Enter the step size (in time) to be used during fixed time step integration. This step size will be used when the eccentricity is below the eccentricity threshold. Must be greater than 0. 
TrueAnomaly  Enter the step size (in true anomaly) to be used during fixed true anomaly step integration. This step size will be used when the eccentricity is above the eccentricity threshold. Must be greater than 0.  
EccentricityThreshold  Enter a value for the eccentricity of the orbit above which the propagator will take fixed steps (approximately) in true anomaly as opposed to fixed steps in time. Must be greater than 0.  
RelativeError***  ErrorTolerance  Nominally 1e13. 
MinStepSize  Nominally 1 sec.  
MaxStepSize  Nominally 86400 sec. 
* Only available in predict integrator settings.
** Not available for a GPS satellite.
*** Not available with the RK4 or GaussJackson integration methods.
ODTK 6.5