/a, where is the gravity constant of
the central body and a is the semimajor axis. Enter a
value in the selected distance unit squared per selected time unit
squared.
in the
illustration). Enter a value in the selected
angle unit.This attribute retrieves the values for Target Vector Incoming Asymptote elements used to define the spacecraft's Initial State.
Astrogator_RM <Satellite Object Path> GetValue <Astrogator Object Path>.Target_Vector_Incoming_Asymptote.{Element}
If you select Target Vector Incoming Asymptote as the Coordinate Type, the following six elements need to be specified:
| Element | Connect Name | Description |
|---|---|---|
| Radius of Periapsis | rp | Distance from the center of mass of the central body to the periapsis of the hyperbolic orbit (rp in the illustration). Enter a value in the selected distance unit. |
| C3 Energy | C3 | The energy of the orbit, computed as -/a, where is the gravity constant of
the central body and a is the semimajor axis. Enter a
value in the selected distance unit squared per selected time unit
squared. |
| Right Ascension of Incoming Asymptote | AsymRA | The right ascension of the hyperbolic incoming asymptote in the selected coordinate system. Enter a value in the selected angle unit. |
| Declination of Incoming Asymptote | AsymDec | The declination of the incoming asymptote in the selected coordinate system. Enter a value in the selected angle unit. |
| Velocity Azimuth at Periapsis | AzVp | The inertial flight path azimuth of the trajectory measured at periapsis. Enter a value in the selected angle unit. |
| True Anomaly | TA | The angle from the periapsis of the orbit to the spacecraft's
position vector, measured in the direction of spacecraft motion
(the angle in the
illustration). Enter a value in the selected
angle unit. |
In the drawing below, 
and 
represent the incoming
and outgoing asymptotes, respectively:
Initial State Segment
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Initial_State.InitialState.Target_Vector_Incoming_Asymptote
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Initial_State.InitialState.Target_Vector_Incoming_Asymptote.rp
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Initial_State.FinalState.Target_Vector_Incoming_Asymptote
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Initial_State.FinalState.Target_Vector_Incoming_Asymptote.rp
Propagate Segment
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Propagate.InitialState.Target_Vector_Incoming_Asymptote
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Propagate.InitialState.Target_Vector_Incoming_Asymptote.rp
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Propagate.FinalState.Target_Vector_Incoming_Asymptote
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Propagate.FinalState.Target_Vector_Incoming_Asymptote.rp
Maneuver Segment
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Maneuver.InitialState.Target_Vector_Incoming_Asymptote
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Maneuver.InitialState.Target_Vector_Incoming_Asymptote.rp
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Maneuver.FinalState.Target_Vector_Incoming_Asymptote
Astrogator_RM */Satellite/Satellite1 GetValue MainSequence.SegmentList.Maneuver.FinalState.Target_Vector_Incoming_Asymptote.rp
STK Programming Interface 11.0.1