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# Simulator Input List
# Low Lunar Orbit
# Mode: 0 = Trajectory Generation Only, 1 = Trajectory and Filter
init.mode 1
init.runMonteCarlo false
MONTE.num_runs 3
MONTE.r_error 1000
MONTE.v_error 10
MONTE.lm_error 100
# 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 58232
init.T0 0.0
#Final MJD and Seconds past MJDF for simulation end
init.MJDF 58234
init.TF 0
#The step size in the propagation step.
#NOTE: This number should be smaller than the desired measurement period
init.dt 60
FILTER.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
#lci [km]
#1.7232607076253737e+002 1.6379287856614317e+003 -8.1592709137349675e+002 1.3836671664810035e-001 7.1393322649210633e-001 1.4624051437086556e+000
#seleno [km]
#-7.0653447440413493e+002 9.2387238910403778e+002 -1.4232051310790273e+003 -7.6578459477044203e-001 1.0064446005845396e+000 1.0334979559135251e+000
TRUE_STATE.0.X -7.0653447440413493e+002
TRUE_STATE.0.Y 9.2387238910403778e+002
TRUE_STATE.0.Z -1.4232051310790273e+003
TRUE_STATE.0.VX -7.6578459477044203e-001
TRUE_STATE.0.VY 1.0064446005845396e+000
TRUE_STATE.0.VZ 1.0334979559135251e+000
# exact
#REF_STATE.0.X -7.0653447440413493e+002
#REF_STATE.0.Y 9.2387238910403778e+002
#REF_STATE.0.Z -1.4232051310790273e+003
#REF_STATE.0.VX -7.6578459477044203e-001
#REF_STATE.0.VY 1.0064446005845396e+000
#REF_STATE.0.VZ 1.0334979559135251e+000
# skew 99.9%
REF_STATE.0.X -7.0582793993e+002
REF_STATE.0.Y 9.22948516715e+002
REF_STATE.0.Z -1.42178192595e+003
REF_STATE.0.VX -7.6501810176e-001
REF_STATE.0.VY 1.00543815598e000
REF_STATE.0.VZ 1.03246445796e+000
# skew - 99% and 1.01% alternate
#REF_STATE.0.X -6.9946912966e+002
#REF_STATE.0.Y 9.33111112995e+002
#REF_STATE.0.Z -1.40897307977e+003
#REF_STATE.0.VX -7.73442440718e-001
#REF_STATE.0.VY 9.96380154579e-001
#REF_STATE.0.VZ 1.04383293547e+000
# skew - 100 m and 1 m/s error
#REF_STATE.0.X -7.0643447440413493e+002
#REF_STATE.0.Y 9.2397238910403778e+002
#REF_STATE.0.Z -1.4231051310790273e+003
#REF_STATE.0.VX -7.6678459477044203e-001
#REF_STATE.0.VY 1.0054446005845396e+000
#REF_STATE.0.VZ 1.0344979559135251e+000
#-668428.2069244173 874267.8019608951 -1344570.5796060965
#REF_STATE.0.LX -668428.2069244173
#REF_STATE.0.LY 874267.8019608951
#REF_STATE.0.LZ -1344570.5796060965
#above is actual
#skew 99% 101% 99%
#REF_STATE.0.LX -661743.924855
#REF_STATE.0.LY 883010.479981
#REF_STATE.0.LZ -1331124.87381
#skew 100 m
REF_STATE.0.LX -668528.2069244173
REF_STATE.0.LY 874247.8019608951
REF_STATE.0.LZ -1344670.5796060965
#MEAS.0.0.latitude -50.7
#MEAS.0.0.longitude 127.4
#MEAS.0.0.altitude 0
#MEAS.0.0.bounding_diameter 20
#TRUE_STATE.0.X 1.7232607076253737e+002
#TRUE_STATE.0.Y 1.6379287856614317e+003
#TRUE_STATE.0.Z -8.1592709137349675e+002
#TRUE_STATE.0.VX 1.3836671664810035e-001
#TRUE_STATE.0.VY 7.1393322649210633e-001
#TRUE_STATE.0.VZ 1.4624051437086556e+000
#REF_STATE.0.X 1.7232607076253737e+002
#REF_STATE.0.Y 1.6379287856614317e+003
#REF_STATE.0.Z -8.1592709137349675e+002
#REF_STATE.0.VX 1.3836671664810035e-001
#REF_STATE.0.VY 7.1393322649210633e-001
#REF_STATE.0.VZ 1.4624051437086556e+000
#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 false
#Include Lunar Gravity Acceleration
jat.0.lunar true
jat.0.lunarHarmonic true
jat.0.lunar_n.filter 20
jat.0.lunar_n.jat 20
jat.0.lunar.monte 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 1 #see above
FILTER.states 9
#Set the process model used
FILTER.pm Lunar
#PROCESS NOISE
#Set the process noise for each of the states
#Q.0.X 1e-11
#Q.0.Y 1e-11
#Q.0.Z 1e-11
#Q.0.VX 1e-13
#Q.0.VY 1e-13
#Q.0.VZ 1e-13
#*** ***
#Q.0.X 1e0
#Q.0.Y 1e0
#Q.0.Z 1e0
#Q.0.VX 1e-4
#Q.0.VY 1e-4
#Q.0.VZ 1e-4
Q.0.X 2e0
Q.0.Y 2e0
Q.0.Z 2e0
Q.0.VX 5e-4
Q.0.VY 5e-4
Q.0.VZ 5e-4
#***
#Q.0.X 1e-9
#Q.0.Y 1e-9
#Q.0.Z 1e-9
#Q.0.VX 1e-11
#Q.0.VY 1e-11
#Q.0.VZ 1e-11
#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
Q.0.LX 1e-15
Q.0.LY 1e-15
Q.0.LZ 1e-15
#Set the Initial Position and Velocity Covariance (m and m/s)
P0.0.X 2e3
P0.0.Y 2e3
P0.0.Z 2e3
P0.0.VX 1e0
P0.0.VY 1e0
P0.0.VZ 1e0
#*** ***
#P0.0.X 3e3
#P0.0.Y 3e3
#P0.0.Z 3e3
#P0.0.VX 2e0
#P0.0.VY 2e0
#P0.0.VZ 2e0
#P0.0.X 1
#P0.0.Y 1
#P0.0.Z 1
#P0.0.VX 0.1
#P0.0.VY 0.1
#P0.0.VZ 0.1
#P0.0.LX 1e9
#P0.0.LY 1e9
#P0.0.LZ 1e9
P0.0.LX 2e4
P0.0.LY 2e4
P0.0.LZ 2e4
#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 2
#Measurement type position. Assumed an ECI absolute position can
#be measured or provided by a ground station. The associated
#measurement noise is also provided
#units for altitude & diameter = km
MEAS.0.desc OPT
MEAS.0.satellite 0
MEAS.0.frequency 60
MEAS.0.t0 0
MEAS.0.tf 604800
MEAS.0.type landmark
MEAS.0.cbody moon
MEAS.0.vbody moon
#MEAS.0.R 2.741556778080377e-007
#MEAS.0.R 0.001221730476
#MEAS.0.Rdeg 0.07
#MEAS.0.R 1.492625356955e-6
MEAS.0.Rdeg 0.001
MEAS.0.R 3.046174197867e-10
#MEAS.0.Rdeg 0.01
#MEAS.0.R 3.046174197867e-8
#MEAS.0.Rdeg 0.1
#MEAS.0.R 3.046174197867e-6
MEAS.0.datacount 1
MEAS.0.0.known unknown
MEAS.0.0.latitude -50.7
MEAS.0.0.longitude 127.4
MEAS.0.0.altitude 0
MEAS.0.0.bounding_diameter 20
MEAS.1.desc OPT
MEAS.1.satellite 0
MEAS.1.frequency 60
MEAS.1.t0 0
MEAS.1.tf 604800
MEAS.1.type range
MEAS.1.cbody moon
MEAS.1.vbody moon
# 4.5 deg
#MEAS.1.R 0.006168502751
# 0.45 deg
MEAS.1.R 0.00006168502751
#MEAS.1.R 4e-4