Description

Object Model

Public Methods

Propagate

Propagates the launch vehicle's path using the specified time interval.

Public Properties

EphemerisInterval	The propagator's ephemeris interval.
InitialState	Get the initial state.
StartTime	This property is deprecated. Use EphemerisInterval to configure the propagation interval. Start time. Uses DateFormat Dimension.
Step	Step size. Uses Time Dimension.
StopTime	This property is deprecated. Use EphemerisInterval to configure the propagation interval. Stop time. Uses DateFormat Dimension.
UseScenarioAnalysisTime	This property is deprecated. Use the new Timeline API components to configure the propagator's analysis time. Whether the scenario analysis start/stop times shall be used.

Interfaces

Example

Configure the Simple Ascent propagator

[C#]

Copy Code

// Configure time period  propagator.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2 Jan 2012 12:00:00.000");  propagator.Step = 60.0;    // Set the initial state  propagator.InitialState.Launch.AssignGeodetic(38.3721, -77.6402, 25.0);  propagator.InitialState.Burnout.AssignGeodetic(48.1395, -82.5145, 25.0);  propagator.InitialState.BurnoutVel = 7.7258;    // Propagate  propagator.Propagate();

Configure the Simple Ascent propagator

[Visual Basic .NET]	Copy Code
' Configure time period propagator.EphemerisInterval.SetExplicitInterval("1 Jan 2012 12:00:00.000", "2 Jan 2012 12:00:00.000") propagator.[Step] = 60 ' Set the initial state propagator.InitialState.Launch.AssignGeodetic(38.3721, -77.6402, 25) propagator.InitialState.Burnout.AssignGeodetic(48.1395, -82.5145, 25) propagator.InitialState.BurnoutVel = 7.7258 ' Propagate propagator.Propagate()

CoClasses that Implement IAgVePropagatorSimpleAscent