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EMISAR

In orbit NORAD 68427 DOFN-8999-9141-5844-0576 Romania

Falcon 9 Block 5

Carrier rocket

Space Launch Complex 4E

Spaceport

37

Observations all time

Mission information
Spacecraft name
EMISAR
Status
Active
The satellite is in orbit
The network has not received data from this satellite for a long time
Launch and timeline
Carrier rocket
Falcon 9 Block 5
Spaceport
Space Launch Complex 4E
Launch time
2026-03-30 11:02:00
Separation time
Last observers
Observer
Time of receipt
2026-06-20 11:27:47 UTC
2026-05-14 01:43:37 UTC
2026-04-22 10:44:29 UTC
2026-04-06 01:08:51 UTC
Satellite appearance
Data for the last 30 days
Orbital parameters of the satellite
Perigee
498.86 km
Apogee
500.42 km
Inclination
97.5°
Period
94.7 min
Semi-major axis
6877.8 km
Velocity
7.6 km/s
Orbital elements
TLE source
Celestrak
TLE updated
2026-10-11 04:56:40 UTC
Two-line elements (TLE)
1 68427U 26067M   26283.95302729  .00013237  00000-0  59864-3 0  9997
2 68427 97.4695 241.2615 0001130 44.8211 315.3116 15.21049075 29538
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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
2026-10-13 03:59:42 STARLINK-1451
NORAD 45668
EMISAR
NORAD 68427
4.547 10.93 4.7e-06
2026-10-13 04:47:06 STARLINK-1451
NORAD 45668
EMISAR
NORAD 68427
1.845 10.96 2.9e-05
2026-10-13 09:33:14 SUPERVIEW NEO-1 03
NORAD 63125
EMISAR
NORAD 68427
2.845 14.73 2.2e-07
2026-10-13 11:07:57 SUPERVIEW NEO-1 03
NORAD 63125
EMISAR
NORAD 68427
2.240 14.73 3.6e-07
2026-10-13 11:55:18 SUPERVIEW NEO-1 03
NORAD 63125
EMISAR
NORAD 68427
4.513 14.70 8.9e-08
2026-10-13 12:42:40 SUPERVIEW NEO-1 03
NORAD 63125
EMISAR
NORAD 68427
4.955 14.73 7.4e-08
2026-10-13 13:30:01 SUPERVIEW NEO-1 03
NORAD 63125
EMISAR
NORAD 68427
1.397 14.70 9.3e-07
2026-10-13 15:04:44 SUPERVIEW NEO-1 03
NORAD 63125
EMISAR
NORAD 68427
2.427 14.70 3.1e-07
2026-10-13 18:36:54 EMISAR
NORAD 68427
BREEZE-M DEB
NORAD 39010
4.137 15.63 1.2e-07
2026-10-13 22:18:40 EMISAR
NORAD 68427
MARS-1
NORAD 68830
0.853 0.03 6.1e-06
2026-10-14 14:38:29 FGN-100-D2
NORAD 66299
EMISAR
NORAD 68427
3.032 8.25 4.1e-07
2026-10-14 16:25:11 MICE-1
NORAD 66684
EMISAR
NORAD 68427
3.032 12.66 3.0e-07
2026-10-15 08:55:00 SUPERVIEW NEO-1 04
NORAD 63126
EMISAR
NORAD 68427
4.924 14.73 7.5e-08
2026-10-15 10:29:43 SUPERVIEW NEO-1 04
NORAD 63126
EMISAR
NORAD 68427
1.990 14.73 4.6e-07
2026-10-15 12:04:25 SUPERVIEW NEO-1 04
NORAD 63126
EMISAR
NORAD 68427
2.404 14.73 3.1e-07
2026-10-15 12:51:47 SUPERVIEW NEO-1 04
NORAD 63126
EMISAR
NORAD 68427
3.352 14.70 1.6e-07
2026-10-15 13:00:45 EMISAR
NORAD 68427
QUBE-II
NORAD 69023
2.618 7.71 5.7e-07
2026-10-15 14:26:29 SUPERVIEW NEO-1 04
NORAD 63126
EMISAR
NORAD 68427
1.322 14.70 1.0e-06
2026-10-15 16:01:12 SUPERVIEW NEO-1 04
NORAD 63126
EMISAR
NORAD 68427
3.755 14.70 1.3e-07
2026-10-15 17:42:03 SDGSAT 1
NORAD 49387
EMISAR
NORAD 68427
3.628 10.18 2.6e-07
2026-10-17 07:26:43 STARLINK-5862
NORAD 55920
EMISAR
NORAD 68427
3.261 14.96 4.7e-06

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