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2015JAT/JAT/data/simulation/input/initialConditions_cev_e2m.txt
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# Simulator Input List | |
# Earth to Moon 3 Day from NG | |
# Mode: 0 = Trajectory Generation Only, 1 = Trajectory and Filter | |
init.mode 1 | |
init.runMonteCarlo true | |
MONTE.num_runs 3 | |
MONTE.r_error 1000 | |
MONTE.v_error 10 | |
MONTE.lm_error 100 | |
# To turn on plotting specify possible values jat, truth, geonsref, geonsboth, and measurements | |
# If omitted, will default to whatever the program specifies. If blank, nothing plotted. | |
output.plot | |
# output.plot jat,truth,measurements | |
# 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 57038 | |
#init.MJDF 57040 | |
init.TF 000 | |
#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 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 | |
#GEONS REFERENCE | |
#REF_STATE.0.X 7500 | |
#REF_STATE.0.Y 6600000 | |
#REF_STATE.0.Z 2000000 | |
#REF_STATE.0.VX -9000 | |
#REF_STATE.0.VY -1000 | |
#REF_STATE.0.VZ 4000 | |
#REF_STATE.0.X 7605.608 | |
#REF_STATE.0.Y 6361752.47 | |
#REF_STATE.0.Z 2337664.704 | |
#REF_STATE.0.VX -10062.402 | |
#REF_STATE.0.VY -1309.862 | |
#REF_STATE.0.VZ 3596.46 | |
REF_STATE.0.X 7705.608 | |
REF_STATE.0.Y 6361652.47 | |
REF_STATE.0.Z 2337564.704 | |
REF_STATE.0.VX -10061.402 | |
REF_STATE.0.VY -1308.862 | |
REF_STATE.0.VZ 3597.46 | |
#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 false | |
#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-8 | |
Q.0.Y 1e-8 | |
Q.0.Z 1e-8 | |
Q.0.VX 1e-4 | |
Q.0.VY 1e-4 | |
Q.0.VZ 1e-4 | |
#Q.0.X 1e-13 | |
#Q.0.Y 1e-13 | |
#Q.0.Z 1e-13 | |
#Q.0.VX 1e-8 | |
#Q.0.VY 1e-8 | |
#Q.0.VZ 1e-8 | |
#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 1e3 | |
P0.0.Y 1e3 | |
P0.0.Z 1e3 | |
P0.0.VX 3 | |
P0.0.VY 3 | |
P0.0.VZ 3 | |
#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 | |
#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 moon | |
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.R 4e-4 | |
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.vbody moon | |
MEAS.1.R 2.741556778080377e-007 | |
#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 | |
# |