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2015JAT/JAT/data/simulation/input/initialConditions_cev_llo_1ULMwD.txt
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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 |