initialConditions_cev_m2e.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 57044.00069  
#init.T0 21600.0		 
init.T0 0.0		 

#Final MJD and Seconds past MJDF for simulation end
#init.MJDF    57047.00069
init.MJDF    57044.01069
#init.TF      21600	 
init.TF      0	 

#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   2.675264403e8
#TRUE_STATE.0.Y   -2.039608462e8
#TRUE_STATE.0.Z   -0.6456322161e8
#TRUE_STATE.0.VX  -496.811
#TRUE_STATE.0.VY  460.144
#TRUE_STATE.0.VZ  -52.466
TRUE_STATE.0.X   282406920.7
TRUE_STATE.0.Y   -212684538.
TRUE_STATE.0.Z   -64186635.16
TRUE_STATE.0.VX  -1662.899
TRUE_STATE.0.VY  0639.598
TRUE_STATE.0.VZ  1214.703

#GEONS REFERENCE
#REF_STATE.0.X   264851175.897
#REF_STATE.0.Y   -201921237.738
#REF_STATE.0.Z   -63917589.3939
#REF_STATE.0.VX  -491.84289
#REF_STATE.0.VY  455.54256
#REF_STATE.0.VZ  -51.94134
#REF_STATE.0.X   282407715.3
#REF_STATE.0.Y   -212684885.1
#REF_STATE.0.Z   -64183163.7
#REF_STATE.0.VX  -1664.312505
#REF_STATE.0.VY  639.2041685
#REF_STATE.0.VZ  1214.517541
REF_STATE.0.X   282406920.7
REF_STATE.0.Y   -212684538.
REF_STATE.0.Z   -64186635.16
REF_STATE.0.VX  -1662.899
REF_STATE.0.VY  0639.598
REF_STATE.0.VZ  1214.703

#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-3   
Q.0.VY   1e-3
Q.0.VZ   1e-3

#Set the Initial Position and Velocity Covariance (m and m/s)
P0.0.X    1e7		 
P0.0.Y    1e7				
P0.0.Z    1e7			
P0.0.VX   3e1	
P0.0.VY   3e1			
P0.0.VZ   3e1
#P0.0.X    1		 
#P0.0.Y    1				
#P0.0.Z    1			
#P0.0.VX   0.01	
#P0.0.VY   0.01			
#P0.0.VZ   0.01

#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 1

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

#MEAS.2.desc OPT
#MEAS.2.satellite 0
#MEAS.2.frequency 10
#MEAS.2.t0 0
#MEAS.2.tf 259200
#MEAS.2.type y_angle_los
#MEAS.2.cbody earth
#MEAS.2.vbody moon
#MEAS.2.q.1 0
#MEAS.2.q.2 0
#MEAS.2.q.3 0
#MEAS.2.q.4 1
#MEAS.2.R 2.741556778080377e-007

#MEAS.3.desc OPT
#MEAS.3.satellite 0
#MEAS.3.frequency 60
#MEAS.3.t0 0
#MEAS.3.tf 259200
#MEAS.3.type range
#MEAS.3.cbody earth
#MEAS.3.vbody moon
#MEAS.3.R 2.741556778080377e-007