I'm using the SGP4 model to propagate the orbit, initialized by TLE from celestrak.com
noradId = '40053' date="2018/3/10 07:48:00" from sgp4.earth_gravity import wgs84 from sgp4.io import twoline2rv import requests import datetime date = datetime.datetime.strptime(date, "%Y/%m/%d %H:%M:%S") response = requests.get("https://www.celestrak.com/cgi-bin/TLE.pl?CATNR="+noradId) tle_data = response.text.split("<PRE>\n").split("\n") t1=tle_data t2=tle_data tle = twoline2rv(t1, t2, wgs84) print (tle.propagate(date.year,date.month, date.day, date.hour, date.minute, date.second))
- Is there a way to initialize the propagation by state vector (X,Y,Z,Vx,Vy,Vz) or Keplerian elements?
- Is there a way to generate an appropriate TLE file from mentioned data?
- Is there any other appropriate, accurate model to propagate using mentioned data?
What I need, is to be able to apply maneuvers. However, SGP4 with TLE doesn't allow that.