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Replicator-2

In orbit NORAD 69927 VCDK-6912-2495-5415-3885 Poland

Time in UTC

11.10 05:44

Scheduled · JHR

132

Observations over 30 days

61%

Successful observations

2k

Frames, latest 2026-10-10 10:23 UTC

Mission information
Spacecraft name
Replicator-2
Other names
Replicator 2
Status
Active
The satellite is in orbit
Launch and timeline
Carrier rocket
Falcon 9 Block 5
Spaceport
Space Launch Complex 4E
Launch time
2026-07-07 07:12:00
Separation time
2026-07-07 08:13:01
Last observers
Observer
Time of receipt
2026-10-10 10:23:36 UTC
2026-10-10 08:52:25 UTC
2026-10-10 07:14:50 UTC
2026-10-09 21:54:25 UTC
2026-10-09 00:51:48 UTC
Satellite appearance
Data for the last 30 days
Orbital parameters of the satellite
Perigee
582.32 km
Apogee
593.03 km
Inclination
97.7°
Period
96.5 min
Semi-major axis
6965.8 km
Velocity
7.56 km/s
Orbital elements
TLE source
Celestrak
TLE updated
2026-10-10 04:46:21 UTC
Two-line elements (TLE)
1 69927U 26156BL  26282.68665929  .00000847  00000-0  88354-4 0  9995
2 69927 97.7435 181.6174 0007688 196.9920 163.1043 14.92334736 13906
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Orbit history, past year

Mean elements of every TLE set over the past 365 days, plotted against the epoch of the set. Each source is its own line; click it in the legend to hide it. A jump in altitude is a manoeuvre or a bad set; lines drifting apart are a disagreement between sources. “TLE age” is how many hours have passed since the epoch of the source's freshest set, plotted against when the set reached us, on a logarithmic scale. A set the source repeats unchanged does not reset the age.

Prediction divergence

Each TLE set is propagated with SGP4 to the epoch of the next set from the same source and compared with it, plotted against the epoch of the next set; the tooltip shows how many hours ahead the prediction ran. The logarithmic scale shows the size of the divergence and the tooltip its sign: plus along-track means the prediction is ahead of the satellite. This is how well the sets agree, not the true error: the reference is a TLE too, off by about a kilometre. An outlier is a manoeuvre between sets. Sets more than a week apart are not compared.

Time of closest approach, UTC Object 1 Object 2 Distance, km Speed, km/s Max. probability
2026-10-11 16:22:09 REPLICATOR 2
NORAD 69927
UNKNOWN
NORAD 85151
2.765 1.77 5.7e-07
2026-10-12 05:20:06 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
3.693 14.33 1.4e-07
2026-10-12 06:08:24 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
4.013 14.36 1.2e-07
2026-10-12 06:56:40 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
1.390 14.33 1.0e-06
2026-10-12 07:44:57 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
2.165 14.36 4.2e-07
2026-10-12 08:33:13 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
0.943 14.33 2.2e-06
2026-10-12 09:21:31 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
2.005 14.36 4.9e-07
2026-10-12 10:09:47 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
3.241 14.33 1.9e-07
2026-10-12 10:58:05 YAM-10
NORAD 64580
REPLICATOR 2
NORAD 69927
3.755 14.36 1.4e-07
2026-10-12 23:38:11 REPLICATOR 2
NORAD 69927
THOR ABLESTAR DEB
NORAD 15783
3.213 12.52 2.7e-07
2026-10-13 01:20:01 OBJECT B
NORAD 66651
REPLICATOR 2
NORAD 69927
0.812 3.70 6.5e-06
2026-10-13 02:01:36 ICEYE-X77
NORAD 69892
REPLICATOR 2
NORAD 69927
2.426 0.00 6.8e-07
2026-10-13 08:33:43 REPLICATOR 2
NORAD 69927
THOR BURNER 2A DEB
NORAD 37584
3.161 3.59 4.3e-07
2026-10-13 16:38:30 LEMUR-2-ALEX-FULTON
NORAD 69905
REPLICATOR 2
NORAD 69927
4.371 0.02 2.3e-07
2026-10-13 17:26:19 LEMUR-2-ALEX-FULTON
NORAD 69905
REPLICATOR 2
NORAD 69927
1.107 0.02 3.6e-06
2026-10-13 23:02:20 REPLICATOR 2
NORAD 69927
CESARIO
NORAD 100642
3.127 0.19 4.5e-07
2026-10-13 23:50:39 REPLICATOR 2
NORAD 69927
CESARIO
NORAD 100642
4.207 0.19 2.5e-07
2026-10-14 06:17:54 HYPERION GR-1
NORAD 69883
REPLICATOR 2
NORAD 69927
3.847 0.02 3.0e-07
2026-10-15 04:53:29 REPLICATOR 2
NORAD 69927
FENGYUN 1C DEB
NORAD 37042
4.565 12.42 1.3e-07
2026-10-15 06:26:36 FOSSASAT-2E26
NORAD 69899
REPLICATOR 2
NORAD 69927
4.510 0.02 2.2e-07

Data: CelesTrak SOCRATES Plus, computed from TLEs of the public catalog. This is an estimate, not grounds for a manoeuvre: TLEs carry no covariance, and the maximum probability assumes a position error.

All conjunctions of this satellite