initialConditions_cev_e2m_high_freq.txt

# Simulator Input List
# Earth to Moon 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 57037   
init.T0 0.0		 

#Final MJD and Seconds past MJDF for simulation end
init.MJDF    57040
#init.MJDF    57040
init.TF      0000
	 

#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)        
TRUE_STATE.0.X   7705.608
TRUE_STATE.0.Y   6361652.47
TRUE_STATE.0.Z   2337564.704
TRUE_STATE.0.VX  -10061.402
TRUE_STATE.0.VY  -1308.862
TRUE_STATE.0.VZ  3597.46

#REF_STATE.0.X   0.00778266408000e6
#REF_STATE.0.Y   6.42526899470000e6
#REF_STATE.0.Z   2.36094035104000e6
#REF_STATE.0.VX  -0.01016201602000e6
#REF_STATE.0.VY  -0.00132195062000e6
#REF_STATE.0.VZ  0.00363343460000e6

REF_STATE.0.X   7715.608
REF_STATE.0.Y   6361662.47
REF_STATE.0.Z   2337574.704
REF_STATE.0.VX  -10061.412
REF_STATE.0.VY  -1308.872
REF_STATE.0.VZ  3597.56



#RUE_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

#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 7
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-8
Q.0.Y   1e-8
Q.0.Z   1e-8
Q.0.VX   1e-10  
Q.0.VY   1e-10
Q.0.VZ   1e-10

#Q.0.X   1e-55
#Q.0.Y   1e-55
#Q.0.Z   1e-55
#Q.0.VX   1e-55 
#Q.0.VY   1e-55
#Q.0.VZ   1e-55

Q.0.E1bias 5e-9
Q.0.M1bias 5e-9


#Q.0.X   1e-20 
#Q.0.Y   1e-20
#Q.0.Z   1e-20
#Q.0.VX   1e-26   
#Q.0.VY   1e-26
#Q.0.VZ   1e-26


#Set the Initial Position and Velocity Covariance (m and m/s)
#P0.0.X    1e5		 
#P0.0.Y    1e5				
#P0.0.Z    1e5			
#P0.0.VX   1e3		
#P0.0.VY   1e3			
#P0.0.VZ   1e3
P0.0.X    10	 
P0.0.Y    10			
P0.0.Z    10			
P0.0.VX   1	
P0.0.VY   1		
P0.0.VZ   1
 
#P0.0.E1bias 100
#P0.0.M1bias 100
P0.0.E1bias 1.0E-2
P0.0.M1bias 1.0E-2


#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-003

MEAS.0.desc OPT
MEAS.0.satellite 0
MEAS.0.frequency 60
MEAS.0.t0 0
MEAS.0.tf 241200
MEAS.0.type y_angle_los
MEAS.0.cbody earth
MEAS.0.vbody moon
MEAS.0.q.1 0
MEAS.0.q.2 0
MEAS.0.q.3 0
MEAS.0.q.4 1
MEAS.0.R 3.6e-3

#MEAS.0.R 4e-4

#MEAS.0.desc OPT
#MEAS.0.satellite 0
#MEAS.0.frequency 60
#MEAS.0.t0 0
#MEAS.0.tf 259200
#MEAS.0.tf  2e11
#MEAS.0.type range
#MEAS.0.cbody earth
#MEAS.0.vbody moon
#MEAS.0.R 2.741556778080377e-3

#MEAS.1.desc OPT
#MEAS.1.satellite 0
#MEAS.1.frequency 60
#MEAS.1.t0 0
#MEAS.1.tf 259200
#MEAS.1.tf  2e11
#MEAS.1.type range
#MEAS.1.cbody earth
#MEAS.1.vbody moon
#MEAS.1.R 2.741556778080377e-2




#MEAS.2.desc OPT
#MEAS.2.satellite 0
#MEAS.2.frequency 60
#MEAS.2.t0 1e5
#MEAS.2.tf 259200
#MEAS.2.tf  259200
#MEAS.2.type range
#MEAS.2.cbody earth
#MEAS.2.vbody earth
#MEAS.2.R 2.741556778080377e-9

#MEAS.3.desc OPT
#MEAS.3.satellite 0
#MEAS.3.frequency 60
#MEAS.3.t0 1e5
#MEAS.1.tf 259200
#MEAS.3.tf  259200
#MEAS.3.type y_angle_los
#MEAS.3.cbody earth
#MEAS.3.vbody earth
#MEAS.3.q.1 0
#MEAS.3.q.2 0
#MEAS.3.q.3 0
#MEAS.3.q.4 1
#MEAS.3.R 2.741556778080377e-9

#MEAS.1.R 4e-4

#MEAS.2.desc OPT
#MEAS.2.satellite 0
#MEAS.2.frequency 60
#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
#