Satellite: Astrogator Maneuver Ephemeris Block History: Target Vector

Data for incoming and outgoing asymptotes as well as C3 energy.

Name Dimension Type Description
Time DateFormat Real Number Time.
C3_Energy Rate Squared Real Number An energy defined as -(mu/semi-major-axis). The Calc Object allows a choice of a central body. The default is Earth.
Incoming_Asymptote_Dec AngleUnit Real Number Declination of incoming asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Incoming_Asymptote_RA AngleUnit Real Number Right Ascension of incoming asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Incoming_Vel_Az_at_Periapsis AngleUnit Real Number Velocity azimuth at periapsis for incoming trajectory. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Outgoing_Asymptote_Dec AngleUnit Real Number Declination of outgoing asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Outgoing_Asymptote_RA AngleUnit Real Number Right Ascension of outgoing asymptote or apsides. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.
Outgoing_Vel_Az_at_Periapsis AngleUnit Real Number Velocity azimuth at periapsis for outgoing trajectory. The Calc Object allows a choice of coordinate systems. The default is Earth Centered Inertial.

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