# Made by eph2tle, compiled May 1 2018 10:14:32 # Run at Wed May 23 07:57:10 2018 # # This object (the Queqiao lunar communations relay satellite) will # presumably be staying at the earth-moon L2 point. The following TLEs # are just for its ascent to the moon, so these TLEs won't be updated. # The following line should keep 'sat_id' from nagging you to update : # # No updates # # The following TLEs (Two-Line Elements) were generated by fitting # a numerically-integrated ephemeris, based on the orbit given below, # to the SDP4/SGP4 models. Each TLE is good for the interval between # its epoch and the epoch of the subsequent TLE (usually one day). # The maximum deviation between the numerically integrated ephemerides # and the TLE-based ephemeris, in kilometers, is given for each TLE # as the "worst residual". # # This fitting is done using the 'eph2tle' code packaged with Find_Orb. # The code has details on how the TLEs were computed : # # https://github.com/Bill-Gray/find_orb/eph2tle.cpp # # Be warned: the error given is that between the numerically # integrated ephems and the TLE model. There will usually be at # least some additional difference between the ephems and the actual # motion of the satellite, especially if the ephemerides are based # on a short arc. If the following orbital elements say something # like "[based on] 10 observations 2015 Jan. 1-13", and the TLEs # are for 2015 May, the extrapolation may be tenuous at best. If # your application requires a specific level of accuracy, you may # want to contact me; I can give you some idea as to the fit of the # underlying data (and possibly TLEs based on newer data). # # Queqiao just went in a simple Hohmann-like transfer from low-earth # orbit to a lunar flyby. These TLEs give its position over four # days; after that, it'll maneuver into an orbit behind the moon # at the earth-moon L2 point. So these are the only TLEs it'll have. # (At least, until it runs out of stationkeeping fuel and falls into # a geocentric orbit.) # # Also, if you use a TLE outside the "correct" time range (between # its epoch and that of the next epoch), all bets are off. It usually # seems to be a decent fit, at least for a while, but I don't # recommend doing it. # # Ephem range: 58259.000000 58263.000000 1.000000 # Created Wed May 23 07:56:32 2018 # Ephemeris start: 21 May 2018 0:00:00 # Ephemeris end: 25 May 2018 0:00:00 # Times are all TDT # Positions/velocities are in equatorial J2000 # Orbital elements: 2018-045A = NORAD 43470 = Queqiao # Perigee 2018 May 20.911901 +/- 0.000131 TT = 21:53:08 (JD 2458259.411901) # Epoch 2018 May 22.0 TT = JDT 2458260.5 Gray # M 39.60922 +/- 0.013 (J2000 equator) # n 36.40221537 +/- 0.013 Peri. 174.41284 +/- 0.0028 # a194618.877 +/- 46.5 Node 204.65259 +/- 0.00009 # e 0.9664106 +/- 6.47e-6 Incl. 29.01042 +/- 0.0006 # P 9.89d H 27.9 G 0.15 U 9.8 # q 6537.11322 +/- 2.18 Q 382700.641 +/- 91.2 # 12 of 16 observations 2018 May 21-22 (23.4 hr); mean residual 0".083 # # 1 NoradU COSPAR Epoch.epoch dn/dt/2 d2n/dt2/6 BSTAR T El# C # 2 NoradU Inclina RAAscNode Eccent ArgPeri MeanAno MeanMotion Rev# C # Worst residual: 86.03 km # MJD 58259.000000 (2018 May 21 0:00) 2018-045A = NORAD 43470 = Queqiao 1 43470U 18045A 18141.49919926 .00000000 00000-0 00000-0 0 1431 2 43470 028.6387 204.9593 9646218 173.6943 025.9019 00.10188824 03 # Worst residual: 13.70 km # MJD 58260.000000 (2018 May 22 0:00) 2018-045A = NORAD 43470 = Queqiao 1 43470U 18045A 18142.49919926 .00000000 00000-0 00000-0 0 1432 2 43470 029.0185 204.6370 9655144 173.9312 061.6563 00.10068563 03 # Worst residual: 49.47 km # MJD 58261.000000 (2018 May 23 0:00) 2018-045A = NORAD 43470 = Queqiao 1 43470U 18045A 18143.49919926 .00000000 00000-0 00000-0 0 1433 2 43470 030.0198 204.1279 9663393 174.2926 098.0263 00.10099998 09 # Worst residual: 220.93 km # MJD 58262.000000 (2018 May 24 0:00) 2018-045A = NORAD 43470 = Queqiao 1 43470U 18045A 18144.49919926 .00000000 00000-0 00000-0 0 1434 2 43470 035.3452 202.5371 9696628 175.4084 135.1331 00.10164195 01 Worst residual in entire run: 220.93 km on MJD 58262.0 1 3 10 30 100 300 1K 3K 10K km 0 0 0 1 2 1 0 0 0 0