Как записать данные в файл .dat Python новая строка несколько списков Satellite Orbit

Я создал функцию для генерации и распространения спутниковой орбиты. Теперь я хочу сохранить все свои данные в файле .dat. Я не уверен, сколько циклов for мне нужно или как это сделать.

Я хочу, чтобы время, широта, долгота и высота были в одной строке для каждого шага распространения.

Код для данных:

myOrbitJ2000Time = [1085.0, 2170.0, 3255.0, 4340.1, 5425.1]

lat = [48.5, 26.5, -28.8, -48.1, 0.1]

lon = [-144.1, -50.4, -1.6, 91.5, 152.8]

alt = [264779.5, 262446.1, 319661.8, 355717.3, 306129.0]

Желаемый результат в файле .dat:

J2000 Время, Широта, Долгота, Альт.

1085.0, 48.6, -144.2, 264779.5

2170.0, 26.5, -50.4, 262446.1

3255.0, -28.7, -1.6, 319661.8

4340.1, -48.0, 91.5, 355717.2

5425.1, 0.1, 152.8, 06129.0

Полный код:

import orbital
from orbital import earth, KeplerianElements, plot
import matplotlib.pyplot as plt
import numpy as np
from astropy import time
from astropy.time import TimeDelta, Time
from astropy import units as u
from astropy import coordinates as coord


#def orbitPropandcoordTrans(orbitPineapple_J2000time, _ecc, _inc, _raan, _arg_pe, _meananom, meanMotion):
def orbitPropandcoordTrans(propNum, orbitPineapple_J2000time, _ecc, _inc, _raan, _arg_pe, _meananom, meanMotion):
        '''
        Create original orbit and run for 100 propagations (in total one whole orbit)
        in order to get xyz and time for each propagation step.
        The end goal is to plot the lat, lon, & alt data to see if it matches ISS groundtrace.
        '''
    import orbital
    from orbital import earth, KeplerianElements, plot
    import matplotlib.pyplot as plt
    import numpy as np
    from astropy import time
    from astropy.time import TimeDelta, Time
    from astropy import units as u
    from astropy import coordinates as coord

    'Calculate Avg. Period from Mean Motion'
    _avgPeriod = 86400 / meanMotion
    #print('_avgPeriod', _avgPeriod)

    ######
    #propNum = int(_avgPeriod)

    'Generate Orbit'
    #orbitPineapple = KeplerianElements.with_period(5560, body=earth, e=0.0004525, i=(np.deg2rad(51.6414)), raan=(np.deg2rad(247.1662)))
    orbitPineapple = KeplerianElements.with_period(_avgPeriod, body=earth, e=_ecc, i=(np.deg2rad(_inc)), raan=(np.deg2rad(_raan)), arg_pe=(np.deg2rad(_arg_pe)), M0=(np.deg2rad(_meananom))) #ref_epoch=   
    #plot(orbitPineapple)
    #plt.show()
    #print('')
    #print('')

    'Propagate Orbit and retrieve xyz'
    myOrbitX = []         #X Coordinate for propagated orbit step
    myOrbitY = []         #Y Coordinate for propagated orbit step
    myOrbitZ = []         #Z Coordinate for propagated orbit step
    myOrbitTime = []      #Time for each propagated orbit step
    myOrbitJ2000Time = [] #J2000 times
    #propNum = 100        #Number of propagations and Mean Anomaly size (one orbit 2pi/propNum)

    for i in range(propNum):
        orbitPineapple.propagate_anomaly_by(M=(2.0*np.pi/propNum)) #Propagate the orbit by the Mean Anomaly
        myOrbitX.append(orbitPineapple.r.x)                        #x vals
        myOrbitY.append(orbitPineapple.r.y)                        #y vals
        myOrbitZ.append(orbitPineapple.r.z)                        #z vals
        myOrbitTime.append(orbitPineapple_J2000time)               #J2000 time vals
        myOrbitJ2000Time.append(orbitPineapple.t)

        #plot(orbitPineapple)
    #print('X:', 'Length:', len(myOrbitX))
    #print(myOrbitX)
    #print('Y:', 'Length:',len(myOrbitY))
    #print(myOrbitY)
    #print('Z:', 'Length:', len(myOrbitZ))
    #print(myOrbitZ)
    #print('J2000 Time:', 'Length:',len(myOrbitTime))
    #print(myOrbitTime)


    '''Because the myOrbitTime is only the time between each step to be the sum of itself plus
    all the previous times. And then I need to convert that time from seconds after J2000 to UTC.'''
    myT = [] #UTC time list

    for i in range(propNum):
        myT.append((Time(2000, format='jyear') + TimeDelta(myOrbitTime[i]*u.s)).iso) #Convert time from J2000 to UTC
    #print('UTC Time List Length:', len(myT))
    #print('UTC Times:', myT)

    '''Now I have xyz and time for each propagation step and need to convert the coordinates from
    ECI to Lat, Lon, & Alt'''
    now = []     #UTC time at each propagation step
    xyz =[]      #Xyz coordinates from OrbitalPy initial orbit propagation
    cartrep = [] #Cartesian Representation
    gcrs = []    #Geocentric Celestial Reference System/Geocentric Equatorial Inertial, the default coord system of OrbitalPy
    itrs =[]     #International Terrestrial Reference System coordinates
    lat = []     #Longitude of the location, for the default ellipsoid
    lon = []     #Longitude of the location, for the default ellipsoid
    alt = []     #Height of the location, for the default ellipsoid


    for i in range(propNum):
        xyz = (myOrbitX[i], myOrbitY[i], myOrbitZ[i])                   #Xyz coord for each prop. step
        now = time.Time(myT[i])                                         #UTC time at each propagation step
        cartrep = coord.CartesianRepresentation(*xyz, unit=u.m)         #Add units of [m] to xyz
        gcrs = coord.GCRS(cartrep, obstime=time.Time(myT[i]))           #Let AstroPy know xyz is in GCRS
        itrs = gcrs.transform_to(coord.ITRS(obstime=time.Time(myT[i]))) #Convert GCRS to ITRS
        loc = coord.EarthLocation(*itrs.cartesian.xyz)                  #Get lat/lon/height from ITRS
        lat.append(loc.lat.value)                                       #Create latitude list
        lon.append(loc.lon.value)                                       #Create longitude list
        alt.append(loc.height.value)           

    #print('Current Time:', now)
    #print('')
    #print('UTC Time:')
    #print(myT)
    print('myOrbitJ2000Time', myOrbitJ2000Time)
    print('')
    print('Lat:')
    print('')
    print(lat)
    print('')
    print('Lon:')
    print(lon)
    print('')
    print('Alt:')
    print(alt)

орбитаPropandcoordTrans(5, -34963095, 0,0073662, 51,5946, 154,8079, 103,6176, 257,3038, 15,92610159)