Translates the position vector from this system into the output system.

Public Function Transform( _
   ByVal Epoch As System.Object, _
   ByVal OutputSystem As IAgCrdnSystem, _
   ByVal PositionInMySystem As IAgCartesian3Vector _
) As IAgCrdnSystemTransformResult

public IAgCrdnSystemTransformResult Transform(
   System.Object Epoch, 
   IAgCrdnSystem OutputSystem, 
   IAgCartesian3Vector PositionInMySystem
);

public: IAgCrdnSystemTransformResult^ Transform(
   VARIANT Epoch, 
   IAgCrdnSystem ^ OutputSystem, 
   IAgCartesian3Vector ^ PositionInMySystem
);

public IAgCrdnSystemTransformResult transform(
   Variant Epoch, 
   IAgCrdnSystem OutputSystem, 
   IAgCartesian3Vector PositionInMySystem
);

public: HRESULT Transform(
   VARIANT Epoch, 
   IAgCrdnSystem * OutputSystem, 
   IAgCartesian3Vector * PositionInMySystem, 
   IAgCrdnSystemTransformResult ** ReturnValue
);

Consider a point moving along its trajectory in space. The point's position and velocity can be given at some specified time using Cartesian coordinates in one of VGT coordinate systems. The same point at the same time will have different Cartesian coordinates with respect to a different VGT coordinate system. One set of coordinates can be obtained from the other using Transform methods defined for VGT coordinate systems: given time and coordinates with respect to one VGT coordinate system, these methods output coordinates with respect to another system. For example, consider a center point of a satellite. Its location in low Earth orbit can be given using Cartesian coordinates with respect to the ECEF coordinate system ("ECEF" means "Earth Centered Earth Fixed"). The same location is significantly farther away from the center of the Moon so its Cartesian coordinates in the Moon Centered Moon Fixed coordinate system will reflect a much greater distance from the Moon center.