def getStateVector(fileName):
import orbitTools
from scipy.interpolate import UnivariateSpline
from scipy import interpolate
import orbitProp as op
import sys
sys.path.append('../PythonScripts')
import AtmosProfile as AP
import matplotlib.pyplot as plt
planetModel = 0
omegaE = 2.*np.pi/(86164.0906)
inputs = readInput(fileName)
[lon0,lat0,h0] = inputs[0]
thetag = inputs[10]
ispList = inputs[9]
[x0,y0,z0] = orbitTools.latlonalt2ECI(lat0,lon0,h0,thetag,planetModel)
#SEZ2ECI(lat,lon,hs,Vsouth,Veast,Vzenith,inertial,thetag,planetModel)
V0 = orbitTools.SEZ2ECI(lat0,lon0,h0,0,0,0,0,thetag,planetModel)
Vx0 = V0[0]
Vy0 = V0[1]
Vz0 = V0[2]
massList = inputs[1]
m0Vec = massList[0]
mfVec = massList[1]
SrefList = inputs[2]
MinfCDlist = inputs[3]
CDList = inputs[4]
atmosoption = inputs[5]
atmoFile = inputs[6]
timelist = inputs[7]
thrustList = inputs[8]
retTrajs = []
#atmosoption = 2
if atmosoption>0:
print 'using given atmo data'
altitudeList,densityMeanList,uMeanList,vMeanList,wMeanList,densitySDList,uSDList,vSDList,wSDList,nPoints= AP.readGramAtmos(atmoFile)
else:
altitudeList = [0]
densityMeanList = [0]
uMeanList = [0]
vMeanList = [0]
wMeanList = [0]
densitylist = densityMeanList
ulist = uMeanList
vlist = vMeanList
wlist = wMeanList
dtinterval = inputs[12]
cloption = 0
cl = [0]
loverd = 0
minfcl = [1]
geoptions = 1
fileGE = 'trajProp'
thrustoffangledeg =[0,0]
mass_time_alt_opt = 1
dtinterval = 0.01
stateVectors = []
for index in range(0,len(m0Vec)):
mass = m0Vec[index]
mf = mfVec[index]
initialstate = [x0,y0,z0,Vx0,Vy0,Vz0]
thrust = thrustList[index]
Tx = thrust[0]
Ty = thrust[1]
Tz = thrust[2]
timeVec = timelist[index]
'''
fTx = UnivariateSpline(timeVec,Tx)
fTy = UnivariateSpline(timeVec,Ty)
fTz = UnivariateSpline(timeVec,Tz)
timeVec = np.linspace(timeVec[0],timeVec[-1],1000)
Tx = fTx(timeVec)
Ty = fTy(timeVec)
Tz = fTz(timeVec)
'''
cd0 = CDList[index]
minfcd0 = MinfCDlist[index]
sref = SrefList[index]
fcd0 = UnivariateSpline(minfcd0,cd0)
isp = ispList[index]
minfcd = np.linspace(minfcd0[0],minfcd0[-1],100)
cd = fcd0(minfcd)
Tlist = np.array([Tx,Ty,Tz]).T#np.concatenate([[Tx],[Ty],[Tz]],axis=1)
ndtinterval = int(np.ceil(2*timeVec[-1]/dtinterval))
ntime = len(timeVec)
#finalconditions,derivVals = op.propagate(initialstate,mass,mf,sref,minfcd,cd,cloption,minfcl,cl,loverd,atmosoption,altitudeList,densitylist,ulist,vlist,wlist,Tlist,timeVec,isp,geoptions,fileGE,planetModel,dtinterval,ndtinterval,thetag,1,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudeList))
#finalconditions,finalderivs = propagate(initialstate,mass,mass_time_alt_final,sref,minfcd,cd,cloption,minfcl,cl,loverd,atmosoption,altitudelist,densitylist,ulist,vlist,wlist,tlist,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,mass_time_alt_opt,thrustoffangledeg,ncd=len(minfcd),ncl=len(minfcl),ntime=shape(tlist,0),nlist=len(altitudelist))
if index == len(m0Vec)-1:
mass_time_alt_opt = 2
fcond = timeVec[-1]
else:
fcond = mf
finalconditions,finalderivs = op.propagate(initialstate,mass,fcond,sref,minfcd,cd,cloption,minfcl,cl,loverd,atmosoption,altitudeList,densitylist,ulist,vlist,wlist,Tlist,timeVec,isp,geoptions,fileGE+str(1+index),planetModel,dtinterval,ndtinterval,thetag,mass_time_alt_opt)
newIndex = finalconditions[:,10]>=0.0
newfinalConditions = finalconditions[newIndex,:]
stateVectors.append(newfinalConditions)
x0 = newfinalConditions[-1,0]
y0 = newfinalConditions[-1,1]
z0 = newfinalConditions[-1,2]
Vx0 = newfinalConditions[-1,3]
Vy0 = newfinalConditions[-1,4]
Vz0 = newfinalConditions[-1,5]
massCheck = newfinalConditions[-1,9]
timeCheck = newfinalConditions[-1,7]
thetag = thetag + omegaE*newfinalConditions[-1,10]
retTrajs.append(newfinalConditions)
def generateRandomMultiTrajMalFunc(missionList,tLaunchDesired,dt,timeMalfunc,deltatfail,TOffset,ThrustOffsetAngDegMalFunc,atmProfile):
# this function generates entire trajectories
import numpy as np
#calculating ECI coordinates for launch
import orbitTools # library for coordinate transformation
import orbitProp as op # trajectory propagation routine
import data2GE
import copy
if len(atmProfile)>0:
atmosoption =1
[altitudelist,densitylist,ulist,vlist,wlist] = atmProfile
else:
atmosoption = 0
densitylist = [0]
ulist = [0]
vlist = [0]
wlist = [0]
altitudelist = [0]
mission0 = missionList[0]# getting mission parameters for current mission
omegaE = getAngVelEarth(mission0)# planet's angular velocity
retList = []
latitude,longitude,height = latlonaltFromMission(mission0)
planetmodel = 0# 0 for Circ ...1 for ellipt
trajList,thetag0 = interpolateTrajectories(missionList,tLaunchDesired,dt)
r0 = orbitTools.latlonalt2ECI(latitude,longitude,height,thetag0,planetmodel)
Rearth = getRfromMission(mission0)
omega = getAngVelEarth(mission0)
nEvents = getNumberOfStages(mission0)
cloption = 1
cl = 0.
minfcl = [1]
loverd = 0.0
geoptions = 0
dtinterval = dt
ndtinterval = 20000
fileList = []
currentTime = 0.0
retList= []
malFuncBool = False
for indexEvent in range(nEvents):
ThrustOffsetAngDeg= [0,0]#ThrustOffsetAngDegMalFunc
if indexEvent ==0 : #first stage...setting initial conditions for rest of cases
[vS0,vE0,vZ0] = [0,0,0] # initial velocity in SEZ frame
inertial = 0
thetag = copy.deepcopy(thetag0)
# inertial = 1. input velocities are inertial velocities in SEZ frame
# inertial =0. input velocities are local velocities (earth rotation not accounted)
#Veci0 = orbitTools.SEZ2ECI(latitude,longitude,r0,vS0,vE0,vZ0,inertial,thetag)
Veci0 = orbitTools.SEZ2ECI(latitude,longitude,height,vS0,vE0,vZ0,inertial,thetag,planetmodel)
initialstate = np.array([r0[0],r0[1],r0[2],Veci0[0],Veci0[1],Veci0[2]])
m0,Fmax,isp,minfcd,cd,sref = vehicleParamFromMission(mission0,indexEvent)
massf = getFinalMassFromMission(mission0,indexEvent)# m0[-1]
Fmax = TOffset*Fmax
etaMin = getEtaMinFromMission(mission0,indexEvent)
filename = 'pTraj'+str(indexEvent)+'.txt'
fileList.append(filename)
if etaMin>=0:
propOption = 1
currTraj = trajList[indexEvent]
[indexEvent,tfit,uxFit,uyFit,uzFit,etaFit] = currTraj
# ensuring that unit vector is actually a unit vector (due to interpolation)
uMag = (uxFit**2 + uyFit**2 + uzFit**2)**.5
uxetaFit = np.array([etaFit*uxFit/uMag]).T
uyetaFit = np.array([etaFit*uyFit/uMag]).T
uzetaFit = np.array([etaFit*uzFit/uMag]).T
uetaMat = np.concatenate((uxetaFit,uyetaFit,uzetaFit),1)
Fmat = Fmax*uetaMat
timelist = tfit
propCond = massf
ntime = len(timelist)
finalconditions,finalderivs = op.propagate(initialstate, m0, propCond,sref,minfcd,cd,cloption, minfcl,cl,loverd,atmosoption, altitudelist,densitylist,ulist,vlist ,wlist,Fmat,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,propOption,ThrustOffsetAngDeg,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
tfTemp = fixPropagateResultsGetTime(finalconditions)
if timeMalfunc<=tfTemp[-1]:
geoptions=0
#print 'TOff',ThrustOffsetAngDegMalFunc
finalconditions,finalderivs = malFunc.propagate(initialstate,m0,propCond,sref,minfcd,cd,cloption,minfcl,cl,loverd,atmosoption,altitudelist,densitylist,ulist,vlist,wlist,Fmat,timeMalfunc,deltatfail,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,propOption,ThrustOffsetAngDegMalFunc)
malFuncBool = True
xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,newfinalConditions = fixPropagateResults(finalconditions)
#print 'FC',newfinalConditions[-1]
#print 'new',newfinalConditions[-1]
# print 'tc',tc,currentTime
tc = tc + currentTime
initialstate = np.array([xc[-1],yc[-1],zc[-1],Vxc[-1],Vyc[-1],Vzc[-1]])
mass0 = mc[-1]
currentTime = tc[-1] # updating time
thetagVector = omegaE*tc + thetag0
thetag = omegaE*currentTime + thetag0 # updating thetag for next event
elif etaMin<0:
propOption = 2
currTraj = trajList[indexEvent]
[indexEvent,tffit] = currTraj
dtlocal = tffit/5.
Tmax = 0.0
uetaMat = np.array([[1,1,1]])
Fmat = Fmax*uetaMat
timelist = [tffit]
propCond = tffit
ntime = len(timelist)
finalconditions,finalderivs = op.propagate(initialstate, mass0, propCond,sref,minfcd,cd,cloption, minfcl,cl,loverd,atmosoption, altitudelist,densitylist,ulist,vlist ,wlist,Fmat,timelist,isp,geoptions,filename,planetmodel,dtlocal,ndtinterval,thetag,propOption,ThrustOffsetAngDeg,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,newfinalConditions = fixPropagateResults(finalconditions)
tc = tc + currentTime
mass0 = mc[-1]
currentTime = tc[-1] # updating time
thetagVector = omegaE*tc + thetag0
thetag = omegaE*currentTime + thetag0# updating thetag for next event
retList.append([xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,thetagVector,indexEvent])
if malFuncBool==True:
break
return retList
def generateTraj(missionList,atmProfile,nProp):
#import sys
#sys.path.append('../../../safetyAssessmentTool/DebrisPropagation/SourceCode')
import numpy as np
import orbitProp as op
from scipy.io import loadmat
from scipy.interpolate import UnivariateSpline
from scipy import interpolate
import AtmosProfile as AP
import data2GoogleEarth as GE
import copy
#import
altitudelist,densityMeanList,uMeanList,vMeanList,wMeanList,densitySDList,uSDList,vSDList,wSDList,nlist = atmProfile
planetmodel = 0 # 0 for spherical planet
#missionList = loadmat(trajectoryFile)['missionList']
cloption = 1
cl = 0.
minfcl = [1]
loverd = 0.0
atmosoption = 2
geoptions = 0
dtinterval = 1 # [sec]
indval = 0
stages = getNumberOfStages(missionList[0])
# iterating through each optimal trajectory
retTrajs = [[0]*stages for i in range(len(missionList)*nProp)]
#exit()
for index in range(len(missionList)):
filename = 'debrisTrash'+str(index)
mission = missionList[index]# getting mission parameters for current mission
omegaE = getAngVelEarth(mission)
for randindex in range(nProp):
stateVectors = []
densitylist, ulist,vlist,wlist = AP.generateAtmosProfile(densityMeanList,uMeanList,vMeanList,wMeanList,densitySDList,uSDList,vSDList,wSDList)
fileNameGE = 'TrajProp'+str(indval) + '.kml'
indval = indval + 1
for staging in range(stages):
# setting initial condition
if staging ==0: # working with first stage
xM,yM,zM,VxM,VyM,VzM,ux,uy,uz,timeM,mc,eta,thetag = nominalTrajFromMission(mission,staging)
initialstate = np.array([xM[0],yM[0],zM[0],VxM[0],VyM[0],VzM[0]])
offset = 1.0*np.random.uniform(.95,1.05)
else :
xM,yM,zM,VxM,VyM,VzM,ux,uy,uz,timeM,mc,eta,thetag = nominalTrajFromMission(mission,staging)
thetag = thetag + omegaE*t[-1]
offset = 1.0*np.random.uniform(.95,1.05)
initialstate = np.array([x[-1],y[-1],z[-1],Vx[-1],Vy[-1],Vz[-1]])
mf = mc[-1]
m0,Fmax,isp,minfcd,cd,sref = vehicleParamFromMission(mission,eventIndex)
Fmax = Fmax*offset
time = time - time[0] # shifting time
timeVec = np.linspace(time0[0],time0[-1],1000)
fcd = UnivariateSpline(minfcd,cd)
f*x = interpolate.interp1d(time,ux)
fuy = interpolate.interp1d(time,uy)
fuz = interpolate.interp1d(time,uz)
feta = interpolate.interp1d(time,eta)
uxN = f*x(timeVec)
uyN = fuy(timeVec)
uzN = fuz(timeVec)
etaN = feta(timeVec)
minfcdN = np.linspace(minfcd[0],minfcd[-1],100)
cdN = fcd(minfcdN)
Fx = np.array([Fmax*etaN*uxN]).T
Fy = np.array([Fmax*etaN*uyN]).T
Fz = np.array([Fmax*etaN*uzN]).T
Farray = np.concatenate([Fx,Fy,Fz],axis=1)
ndtinterval = int(np.ceil(2.*timelist[-1]/dtinterval))
ntime = len(timelist)
finalconditions,derivVals = op.propagate(initialstate,m0,mf,sref,minfcdN,cdN,cloption,minfcl,cl,loverd,atmosoption,altitudelist,densitylist,ulist,vlist,wlist,Farray,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,1,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
x,y,z,Vx,Vy,Vz,m,t,newfinalConditions = fixPropagateResults(finalconditions)
stateVectors.append(newfinalConditions)
retTrajs[indval-1][staging] = newfinalConditions
return retTrajs
def generateRandomMultiTrajMalFunc(missionList,tLaunchDesired,dt,timeMalfunc,deltatfail,TOffset,ThrustOffsetAngDegMalFunc,atmProfile):
# this function generates entire trajectories
import numpy as np
#calculating ECI coordinates for launch
import orbitTools # library for coordinate transformation
import orbitProp as op # trajectory propagation routine
import data2GE
import copy
if len(atmProfile)>0:
atmosoption =1
[altitudelist,densitylist,ulist,vlist,wlist] = atmProfile
else:
atmosoption = 0
densitylist = [0]
ulist = [0]
vlist = [0]
wlist = [0]
altitudelist = [0]
mission0 = missionList[0]# getting mission parameters for current mission
omegaE = getAngVelEarth(mission0)# planet's angular velocity
retList = []
latitude,longitude,height = latlonaltFromMission(mission0)
planetmodel = 0# 0 for Circ ...1 for ellipt
trajList,thetag0 = interpolateTrajectories(missionList,tLaunchDesired,dt)
r0 = orbitTools.latlonalt2ECI(latitude,longitude,height,thetag0,planetmodel)
Rearth = getRfromMission(mission0)
omega = getAngVelEarth(mission0)
nEvents = getNumberOfStages(mission0)
cloption = 1
cl = 0.
minfcl = [1]
loverd = 0.0
geoptions = 0
dtinterval = dt
ndtinterval = 20000
fileList = []
currentTime = 0.0
retList= []
malFuncBool = False
for indexEvent in range(nEvents):
ThrustOffsetAngDeg= [0,0]#ThrustOffsetAngDegMalFunc
if indexEvent ==0 : #first stage...setting initial conditions for rest of cases
[vS0,vE0,vZ0] = [0,0,0] # initial velocity in SEZ frame
inertial = 0
thetag = copy.deepcopy(thetag0)
# inertial = 1. input velocities are inertial velocities in SEZ frame
# inertial =0. input velocities are local velocities (earth rotation not accounted)
#Veci0 = orbitTools.SEZ2ECI(latitude,longitude,r0,vS0,vE0,vZ0,inertial,thetag)
Veci0 = orbitTools.SEZ2ECI(latitude,longitude,height,vS0,vE0,vZ0,inertial,thetag,planetmodel)
initialstate = np.array([r0[0],r0[1],r0[2],Veci0[0],Veci0[1],Veci0[2]])
m0,Fmax,isp,minfcd,cd,sref = vehicleParamFromMission(mission0,indexEvent)
massf = getFinalMassFromMission(mission0,indexEvent)# m0[-1]
Fmax = TOffset*Fmax
etaMin = getEtaMinFromMission(mission0,indexEvent)
filename = 'pTraj'+str(indexEvent)+'.txt'
fileList.append(filename)
if etaMin>=0:
propOption = 1
currTraj = trajList[indexEvent]
[indexEvent,tfit,uxFit,uyFit,uzFit,etaFit] = currTraj
# ensuring that unit vector is actually a unit vector (due to interpolation)
uMag = (uxFit**2 + uyFit**2 + uzFit**2)**.5
uxetaFit = np.array([etaFit*uxFit/uMag]).T
uyetaFit = np.array([etaFit*uyFit/uMag]).T
uzetaFit = np.array([etaFit*uzFit/uMag]).T
uetaMat = np.concatenate((uxetaFit,uyetaFit,uzetaFit),1)
Fmat = Fmax*uetaMat
timelist = tfit
propCond = massf
ntime = len(timelist)
# letting vehicle propagate until propOption is reached (final mass from input parameter from SPOT!! not from propagated trajectory or desired time).
finalconditions,finalderivs = op.propagate(initialstate, m0, propCond,sref,minfcd,cd,cloption, minfcl,cl,loverd,atmosoption, altitudelist,densitylist,ulist,vlist ,wlist,Fmat,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,propOption,ThrustOffsetAngDeg,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
tfTemp = fixPropagateResultsGetTime(finalconditions)
if (timeMalfunc - currentTime )<=tfTemp[-1]:
geoptions=0
#print 'TOff',ThrustOffsetAngDegMalFunc
timeMalfuncLocal = timeMalfunc -currentTime
finalconditions,finalderivs = malFunc.propagate(initialstate,m0,propCond,sref,minfcd,cd,cloption,minfcl,cl,loverd,atmosoption,altitudelist,densitylist,ulist,vlist,wlist,Fmat,timeMalfuncLocal,deltatfail,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,propOption,ThrustOffsetAngDegMalFunc)
malFuncBool = True
xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,newfinalConditions = fixPropagateResults(finalconditions)
#print 'FC',newfinalConditions[-1]
#print 'new',newfinalConditions[-1]
# print 'tc',tc,currentTime
#print 'tc',tc[0],tc[-1]
tc = tc + currentTime
initialstate = np.array([xc[-1],yc[-1],zc[-1],Vxc[-1],Vyc[-1],Vzc[-1]])
mass0 = mc[-1]
currentTime = tc[-1] # updating time
#print 'Current',currentTime,tc[-1]
thetagVector = omegaE*tc + thetag0
thetag = omegaE*currentTime + thetag0 # updating thetag for next event
elif etaMin<0:
propOption = 2
currTraj = trajList[indexEvent]
[indexEvent,tffit] = currTraj
dtlocal = tffit/5.
Tmax = 0.0
uetaMat = np.array([[1,1,1]])
Fmat = Fmax*uetaMat
timelist = [tffit]
propCond = tffit
ntime = len(timelist)
finalconditions,finalderivs = op.propagate(initialstate, mass0, propCond,sref,minfcd,cd,cloption, minfcl,cl,loverd,atmosoption, altitudelist,densitylist,ulist,vlist ,wlist,Fmat,timelist,isp,geoptions,filename,planetmodel,dtlocal,ndtinterval,thetag,propOption,ThrustOffsetAngDeg,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,newfinalConditions = fixPropagateResults(finalconditions)
tc = tc + currentTime
mass0 = mc[-1]
currentTime = tc[-1] # updating time
thetagVector = omegaE*tc + thetag0
thetag = omegaE*currentTime + thetag0# updating thetag for next event
retList.append([xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,thetagVector,indexEvent])
if malFuncBool==True:
break
#print 'tt', timelist[-1],currentTime,timeMalfunc
if (timelist[-1] + currentTime - tc[-1])< timeMalfunc:
print 'Warning when propagating malfunction turns. Failure time seems to be greater than thrust profile time bounds'
return retList
def generateRandomMultiTraj(missionList,tLaunchDesired,dt,atmProfile=[],TOffset = 1.0,ThrustOffsetAngDeg=[0,0]):
# this function generates entire trajectories
import numpy as np
#calculating ECI coordinates for launch
import orbitTools # library for coordinate transformation
import orbitProp as op # trajectory propagation routine
import data2GE
import copy
if len(atmProfile)>0:
atmosoption =2
[altitudelist,densitylist,ulist,vlist,wlist] = atmProfile
else:
atmosoption = 0
densitylist = [0]
ulist = [0]
vlist = [0]
wlist = [0]
altitudelist = [0]
mission0 = missionList[0]# getting mission parameters for current mission
omegaE = getAngVelEarth(mission0)# planet's angular velocity
retList = []
latitude,longitude,height = latlonaltFromMission(mission0)
planetmodel = 0# 0 for Circ ...1 for ellipt
trajList,thetag0 = interpolateTrajectories(missionList,tLaunchDesired,dt)
r0 = orbitTools.latlonalt2ECI(latitude,longitude,height,thetag0,planetmodel)
Rearth = getRfromMission(mission0)
omega = getAngVelEarth(mission0)
nEvents = getNumberOfStages(mission0)
cloption = 1
cl = 0.
minfcl = [1]
loverd = 0.0
geoptions = 0
dtinterval = dt
ndtinterval = 20000
fileList = []
currentTime = 0.0
retList= []
for indexEvent in range(nEvents):
if indexEvent ==0 : #first stage...setting initial conditions for rest of cases
[vS0,vE0,vZ0] = [0,0,0] # initial velocity in SEZ frame
inertial = 0
thetag = copy.deepcopy(thetag0)
# inertial = 1. input velocities are inertial velocities in SEZ frame
# inertial =0. input velocities are local velocities (earth rotation not accounted)
#Veci0 = orbitTools.SEZ2ECI(latitude,longitude,r0,vS0,vE0,vZ0,inertial,thetag)
Veci0 = orbitTools.SEZ2ECI(latitude,longitude,height,vS0,vE0,vZ0,inertial,thetag,planetmodel)
initialstate = np.array([r0[0],r0[1],r0[2],Veci0[0],Veci0[1],Veci0[2]])
m0,Fmax,isp,minfcd,cd,sref = vehicleParamFromMission(mission0,indexEvent)
massf = getFinalMassFromMission(mission0,indexEvent)# m0[-1]
Fmax = TOffset*Fmax
etaMin = getEtaMinFromMission(mission0,indexEvent)
filename = 'pTraj'+str(indexEvent)+'.txt'
fileList.append(filename)
if etaMin>=0:
propOption = 1
currTraj = trajList[indexEvent]
[indexEvent,tfit,uxFit,uyFit,uzFit,etaFit] = currTraj
# ensuring that unit vector is actually a unit vector (due to interpolation)
uMag = (uxFit**2 + uyFit**2 + uzFit**2)**.5
uxetaFit = np.array([etaFit*uxFit/uMag]).T
uyetaFit = np.array([etaFit*uyFit/uMag]).T
uzetaFit = np.array([etaFit*uzFit/uMag]).T
uetaMat = np.concatenate((uxetaFit,uyetaFit,uzetaFit),1)
Fmat = Fmax*uetaMat
timelist = tfit
propCond = massf
ntime = len(timelist)
finalconditions,finalderivs = op.propagate(initialstate, m0, propCond,sref,minfcd,cd,cloption, minfcl,cl,loverd,atmosoption, altitudelist,densitylist,ulist,vlist ,wlist,Fmat,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,propOption,ThrustOffsetAngDeg,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
newIndex = finalconditions[:,10]>=0.0
newfinalConditions = finalconditions[newIndex,:]
# updating parameters for propagation in next stage
xc = newfinalConditions[:,0]
yc = newfinalConditions[:,1]
zc = newfinalConditions[:,2]
Vxc = newfinalConditions[:,3]
Vyc = newfinalConditions[:,4]
Vzc = newfinalConditions[:,5]
mc = newfinalConditions[:,9]
tc = newfinalConditions[:,10] + currentTime
initialstate = np.array([xc[-1],yc[-1],zc[-1],Vxc[-1],Vyc[-1],Vzc[-1]])
mass0 = mc[-1]
currentTime = tc[-1] # updating time
thetagVector = omegaE*tc + thetag0
thetag = omegaE*currentTime + thetag0 # updating thetag for next event
elif etaMin<0:
propOption = 2
currTraj = trajList[indexEvent]
[indexEvent,tffit] = currTraj
dtlocal = tffit/5.
Tmax = 0.0
uetaMat = np.array([[1,1,1]])
Fmat = Fmax*uetaMat
timelist = [tffit]
propCond = tffit
ntime = len(timelist)
finalconditions,finalderivs = op.propagate(initialstate, mass0, propCond,sref,minfcd,cd,cloption, minfcl,cl,loverd,atmosoption, altitudelist,densitylist,ulist,vlist ,wlist,Fmat,timelist,isp,geoptions,filename,planetmodel,dtlocal,ndtinterval,thetag,propOption,ThrustOffsetAngDeg,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,newfinalConditions = fixPropagateResults(finalconditions)
tc = tc + currentTime
mass0 = mc[-1]
currentTime = tc[-1] # updating time
thetagVector = omegaE*tc + thetag0
thetag = omegaE*currentTime + thetag0# updating thetag for next event
retList.append([xc,yc,zc,Vxc,Vyc,Vzc,mc,tc,thetagVector,indexEvent])
return retList
def generateTraj(missionList,atmProfile,nProp):
#import sys
#sys.path.append('../../../safetyAssessmentTool/DebrisPropagation/SourceCode')
import numpy as np
import orbitProp as op
from scipy.io import loadmat
from scipy.interpolate import UnivariateSpline
from scipy import interpolate
import AtmosProfile as AP
import data2GoogleEarth as GE
import copy
#import
altitudelist,densityMeanList,uMeanList,vMeanList,wMeanList,densitySDList,uSDList,vSDList,wSDList,nlist = atmProfile
planetmodel = 0 # 0 for spherical planet
#missionList = loadmat(trajectoryFile)['missionList']
cloption = 1
cl = 0.
minfcl = [1]
loverd = 0.0
atmosoption = 2
geoptions = 0
dtinterval = 1 # [sec]
indval = 0
stages = getNumberOfStages(missionList[0])
# iterating through each optimal trajectory
retTrajs = [[0]*stages for i in range(len(missionList)*nProp)]
#exit()
for index in range(len(missionList)):
filename = 'debrisTrash'+str(index)
mission = missionList[index]# getting mission parameters for current mission
omegaE = getAngVelEarth(mission)
for randindex in range(nProp):
stateVectors = []
densitylist, ulist,vlist,wlist = AP.generateAtmosProfile(densityMeanList,uMeanList,vMeanList,wMeanList,densitySDList,uSDList,vSDList,wSDList)
fileNameGE = 'TrajProp'+str(indval) + '.kml'
indval = indval + 1
for staging in range(stages):
# setting initial condition
if staging ==0: # working with first stage
xM,yM,zM,VxM,VyM,VzM,ux,uy,uz,timeM,mc,eta,thetag = nominalTrajFromMission(mission,staging)
initialstate = np.array([xM[0],yM[0],zM[0],VxM[0],VyM[0],VzM[0]])
offset = 1.0*np.random.uniform(.95,1.05)
else :
xM,yM,zM,VxM,VyM,VzM,ux,uy,uz,timeM,mc,eta,thetag = nominalTrajFromMission(mission,staging)
thetag = thetag + omegaE*t[-1]
offset = 1.0*np.random.uniform(.95,1.05)
initialstate = np.array([x[-1],y[-1],z[-1],Vx[-1],Vy[-1],Vz[-1]])
mf = mc[-1]
m0,Fmax,isp,minfcd,cd,sref = vehicleParamFromMission(mission,eventIndex)
Fmax = Fmax*offset
time = time - time[0] # shifting time
timeVec = np.linspace(time0[0],time0[-1],1000)
fcd = UnivariateSpline(minfcd,cd)
f*x = interpolate.interp1d(time,ux)
fuy = interpolate.interp1d(time,uy)
fuz = interpolate.interp1d(time,uz)
feta = interpolate.interp1d(time,eta)
uxN = f*x(timeVec)
uyN = fuy(timeVec)
uzN = fuz(timeVec)
etaN = feta(timeVec)
minfcdN = np.linspace(minfcd[0],minfcd[-1],100)
cdN = fcd(minfcdN)
Fx = np.array([Fmax*etaN*uxN]).T
Fy = np.array([Fmax*etaN*uyN]).T
Fz = np.array([Fmax*etaN*uzN]).T
Farray = np.concatenate([Fx,Fy,Fz],axis=1)
ndtinterval = int(np.ceil(2.*timelist[-1]/dtinterval))
ntime = len(timelist)
finalconditions,derivVals = op.propagate(initialstate,m0,mf,sref,minfcdN,cdN,cloption,minfcl,cl,loverd,atmosoption,altitudelist,densitylist,ulist,vlist,wlist,Farray,timelist,isp,geoptions,filename,planetmodel,dtinterval,ndtinterval,thetag,1,ncd=len(minfcd),ncl=len(minfcl),ntime=ntime,nlist=len(altitudelist))
x,y,z,Vx,Vy,Vz,m,t,newfinalConditions = fixPropagateResults(finalconditions)
stateVectors.append(newfinalConditions)
retTrajs[indval-1][staging] = newfinalConditions
return retTrajs