SGP4: propagation initialization by state vector

Question

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")[1].split("\n")
t1=tle_data[1]
t2=tle_data[2]

tle = twoline2rv(t1, t2, wgs84)
print (tle.propagate(date.year,date.month, date.day, date.hour, date.minute, date.second)[0])

1. Is there a way to initialize the propagation by state vector (X,Y,Z,Vx,Vy,Vz) or Keplerian elements?
2. Is there a way to generate an appropriate TLE file from mentioned data?
3. 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.

Answer 1

Indeed, SGP4 is not made to allow you to compute maneuvers. You can get a TLE, propagate up to maneuver time to obtain propagated position and velocity, then assume this instant is the new epoch, and re-generate a new TLE, to do so:

1-Compute a new epoch in TLE format at the maneuver ending time

2-Compute the position and velocity after the maneuver (maybe just add the desired delta-V).

3-Re-generate the elements for the TLE such that the output of SGP4 at zero propagation matches the position and velocity after the maneuver.

There is no simple way I'm aware to perform step 3. But you may use any technique for numerical problem solving you like.