Table 2
Simulation environment for demonstration using Lunar Prospector tracking data

Property		Value
Dynamic model (GMAT)	Force model	GRAIL165 (GL0660B) 100 100
		3rd body effect of Sun, Earth, Jupiter, Saturn
		Solar Radiation Pressure
		Relativistic correction
	Propagator	Runge-Kutta 89
Estimation	Convergence Criteria	ΔCost/Cost < 10-3
	Parameters	Position and velocity vectors of spacecraft, range and Doppler
		biases of tracking stations
Measurement weight	Range (m)	2
	Doppler (mm/s)	1
A priori uncertainty (covariance matrix)	Position (km)	1
	Velocity (km/s)	0.001