initialConditions.txt

# Simulator Input List
# Moon to Earth 3 Day from NG

# Mode: 0 = Trajectory Generation Only, 1 = Trajectory and Filter
init.mode    1

# Flag indicating whether to read observations from a file or generate them
init.fromfile false

#Initial MJD and Seconds past MJD0 for simulation start
init.MJD0 57044   
init.T0 0.0		 

#Final MJD and Seconds past MJDF for simulation end
init.MJDF    57044
init.TF      259200		 

#The step size in the propagation step.
#NOTE:  This number should be smaller than the desired measurement period
init.dt      60     
				


# Space Craft Properties/Initial Conditions (start numbering from 0)
# Each satellite needs a true state and a reference state
prop.NumSpacecraft  1

#ECI position and velocity (m and m/s)        
#GEONS TRUE
TRUE_STATE.0.X   2.82505882900000e+008 
TRUE_STATE.0.Y   2.82505882900000e+008
TRUE_STATE.0.Z   -0.64261622210000e+008 
TRUE_STATE.0.VX  -0.00000795264000e+008
TRUE_STATE.0.VY  0.00000721616000e+008
TRUE_STATE.0.VZ   0.00000922000000e+008

#GEONS REFERENCE
REF_STATE.0.X   2.79680824071000E+08
REF_STATE.0.Y   -2.10596670900000E+08
REF_STATE.0.Z   -0.63619005987900E+08
REF_STATE.0.VX  -0.00000787311360E+08
REF_STATE.0.VY  0.00000714399840E+08
REF_STATE.0.VZ   0.00000912780000E+08

#Initial Clock Bias Term 
jat.0.clockBias  0.0
jat.0.clockDrift 0.0

#Solar Radiation Pressure Coefficient and Drag Doefficient
#Area (m^2) and mass (kg)
jat.0.Cr    0.0        
jat.0.Cd    0.0
jat.0.area  10.0  
jat.0.mass  1000    

#Orbital Force Parameters (for each spacecraft)

#Use Gravitational Gradient (not currently implimented)
jat.0.GravGrad false 

#Use only 2-body force models
jat.0.2body false     

#Include Solar Gravity Acceleration
jat.0.solar true

#Include Lunar Gravity Acceleration
jat.0.lunar true

#Include Drag Acceleration      
jat.0.drag false      

#Include Solar Radiation Pressure Acceleration
jat.0.srp false       

#Include only jgm2 gravity model (False = JGM3)
jat.0.jgm2 false    

#Estimator Properties

#Set the number of states the filter will have
#X Y Z Vx Vy Vz B Bdot Srp
FILTER.dt    60	
FILTER.states 6
FILTER.clock 6
FILTER.bias 7

#Set the process model used
FILTER.pm Simple

#PROCESS NOISE
#Set the process noise for each of the states
Q.0.X   1e-13 
Q.0.Y   1e-13
Q.0.Z   1e-13
Q.0.VX   1e-13   
Q.0.VY   1e-13
Q.0.VZ   1e-13
Q.0.clockBias  .12
Q.0.clockDrift 1e-4  

#Set the Initial Position and Velocity Covariance (m and m/s)
P0.0.X    1e12		 
P0.0.Y    1e12				
P0.0.Z    1e12			
P0.0.VX   10		
P0.0.VY   10			
P0.0.VZ   10

#Set thhe Initial Clock Offset and Drift Covariance (m and m/s)		
#P0.0.clockBias 10000	
#P0.0.clockDrift 10
#P0.0.clockBias 10000	
#P0.0.clockDrift 10


#Set the Initial Solar Radiation Pressure and Drag Coefficient Covariances	
#P0.0.Cr   .12	
#P0.0.Cd  1e-30	



#MEASUREMENTS

#Set the number of types of measurements
MEAS.types 3

#Measurement type position.  Assumed an ECI absolute position can 
#be measured or provided by a ground station.  The associated
#measurement noise is also provided 

MEAS.0.desc OPT
MEAS.0.satellite 0
MEAS.0.frequency 60
MEAS.0.t0 0
MEAS.0.tf 259200
MEAS.0.type y_angle_star
MEAS.0.ustar.1 1.0
MEAS.0.ustar.2 0.0
MEAS.0.ustar.3 0.0
MEAS.0.cbody earth
MEAS.0.R 2.741556778080377e-007

MEAS.0.desc OPT
MEAS.0.satellite 0
MEAS.0.frequency 60
MEAS.0.t0 0
MEAS.0.tf 259200
MEAS.0.type y_angle_los
MEAS.0.cbody earth
MEAS.0.q.1 0
MEAS.0.q.2 0
MEAS.0.q.3 0
MEAS.0.q.4 1
MEAS.0.R 2.741556778080377e-007

MEAS.1.desc OPT
MEAS.1.satellite 0
MEAS.1.frequency 60
MEAS.1.t0 0
MEAS.1.tf 259200
MEAS.1.type range
MEAS.1.cbody earth
MEAS.1.R 2.741556778080377e-007