This component is passed as the lone argument for the Evaluate() method of the IAgGatorPluginEngineModel plugin component.  This component contains functions that allow the plugin component to access inputs and set outputs.

Date	DEPRECATED. Use DateElements instead. Current epoch in requested time scale expressed in date format.
Date_Array	DEPRECATED. Use DateElements_Array instead. Current epoch in requested time scale expressed in date format returned as an array representing year [yyyy], dayOfYear, month [0-11], hour [0-23], minute [0-59], seconds. Useful for scripting clients.
DateElements	Current epoch in requested time scale expressed in date format. Year [yyyy], DayOfYear [1-366], Month [1-12], DayOfMonth [1-31], Hour [0-23], Minute [0-59], Seconds [0-60].
DateElements_Array	Current epoch in requested time scale expressed in date format returned as the array: Year [yyyy], DayOfYear [1-366], Month [1-12], DayOfMonth [1-31], Hour [0-23], Minute [0-59], Seconds [0-60]. Useful for scripting clients.
DateString	Current epoch expressed using the date format abbreviation specified.
DayCount	Current epoch in requested time scale expressed in day count format.
DayCount_Array	Current epoch in requested time scale expressed in day count format returned as an array representing wholeDays, secsIntoDay. Useful for scripting clients.
LatLonAlt	Current detic latitude, detic longitude, and altitude.
LatLonAlt_Array	Current detic latitude, detic longitude, and altitude(in internal units) returned as an array representing lat, lon, alt. Useful for scripting clients.
PosVel	Current position and velocity in the requested frame.
PosVel_Array	Current position and velocity in the requested frame (in internal units) returned as an array representing x, y, z, vx, vy, vz. Useful for scripting clients.
SetIspAndMassFlowRate	Sets the current isp and mass flow rate. Computes the thrust using the rocket equation. Returns false on an error.
SetThrustAndIsp	Sets the current thrust (N) and isp (secs). Computes the mass flow rate using the rocket equation. Returns false on an error.
SetThrustAndMassFlowRate	Sets the current thrust(N) and mass flow rate (kg/sec). Computes the isp using the rocket equation. Returns false on an error.
StopPropagation	Stops propagation. For fatal errors.
SunPosition	Position of the sun wrt the current satellite position, in the requested frame, computed in the requested manner.
SunPosition_Array	Position of the sun wrt the current satellite position, in the requested frame, computed in the requested manner, (in internal units) returned as an array representing x, y, z. Useful for scripting clients.
Trace	Set this interface to trace the next numCalls by outputting a message to the message viewer.
TransformVector	Transforms a vector from the input frame to the output frame.
TransformVector_Array	Transforms a vector from the input frame to the output frame (in internal units) returned as an array representing x, y, z. Useful for scripting clients.

Altitude	Current altitude.
CbName	Name of the central body used as reference frame origin.
Cd	Drag Coefficient.
Cr	SRP Coefficient.
DragArea	Drag Area.
DryMass	Dry Mass.
FuelMass	Fuel Mass.
Isp	Current Isp (secs).
Mass	Total Mass.
MassFlowRate	Current mass flow rate (kg/sec).
Mu	Gravitational constant of the state central body
SRPArea	SRP Area.
Thrust	Current thrust (N).
TimeSinceIgnition	Time since ignition (secs).

Name
AgGatorPluginResultEvalEngineModel