Forecast of Conjunctions: 50 Latest Payloads vs. All (31204) Objects
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Time of Closest Approach (TCA), UTC
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NORAD ID 1
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Object Name 1
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NORAD ID 2
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Object Name 2
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Distance at TCA, km
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RIC Distance, km
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Rel.Speed
km/s
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2026-09-26 08:24:48.704
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100538
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STARLINK-36331
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100621
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STARLINK-38347
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2.937
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-2.009, -1.457, 1.571
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11.2828
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2026-09-26 08:31:08.750
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66691
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OBJECT AB
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100742
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TIANYI 52
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0.641
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-0.108, -0.571, 0.269
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6.4886
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2026-09-26 08:36:27.630
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39767
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UNIFORM 1
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100611
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PLATFORM-6
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4.730
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-1.346, 4.449, -0.874
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2.9422
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2026-09-26 09:02:52.819
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100076
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PRAETORIAN SDA_518
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100693
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QIANFAN-240
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2.544
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2.421, -0.354, -0.696
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13.1843
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2026-09-26 09:23:33.968
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46955
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DRAGRACER 2(AUGURY)
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100625
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STARLINK-38311
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4.470
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4.349, 0.608, 0.835
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12.4501
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2026-09-26 09:35:51.767
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49160
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STARLINK-3095
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100611
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PLATFORM-6
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2.584
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0.023, 0.440, 2.547
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14.9044
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2026-09-26 09:42:34.710
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66637
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STARLINK-35953
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100789
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ZK-1A / RB
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0.654
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-0.023, 0.526, -0.387
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8.9483
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2026-09-26 09:44:16.004
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69915
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MISR-D-2
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100611
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PLATFORM-6
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0.650
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-0.650, -0.001, -0.001
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14.9636
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2026-09-26 09:47:30.287
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100512
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STARLINK-38362
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100637
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STARLINK-38422
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1.967
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0.014, 1.188, -1.568
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12.2696
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2026-09-26 10:11:28.545
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100690
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SENTINEL-3C
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270405
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TBA - TO BE ASSIGNED
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4.872
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-1.647, -3.135, -3.346
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10.8751
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Our orbit propagation model is based on SGP4/SDP4 and uses data sourced from space-track.org. Object 1 and Object 2 are arranged by their NORAD ID (NORAD_CAT_ID).
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The "Within ellipsoid" option allows you to check if the predicted miss distance is within the RIC (Radial, In-track, Cross-track) ellipsoid, centered on either Object 1 or Object 2 at TCA, with specified semi-axis lengths.
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To exclude long-lasting conjunctions of ride-sharing satellites, you can use the "Relative Speed > 0.01 km/s" filter. Additionally, connected modules of ISS and CSS are not included in the forecast. Some ride-sharing satellites may also be temporarily excluded from the forecast.
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Gray background indicates a >1 km difference between the latest published position of a conjunction object and the position propagated from the TLE used for conjunction detection, indicating that the record may no longer be current.
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If comparison of the velocity vector and Keplerian orbital parameters from the latest published TLE with the corresponding values propagated from the TLE used for conjunction detection shows a deviation exceeding ±3× the background RMSE, indicating probable maneuvering, the following symbols identify the orbital parameter and direction of the probable change:
↑ ↓ - semimajor axis increase/decrease
↺ ↻ - inclination increase/decrease
→ ← - RAAN increase/decrease
↗ - probable maneuvering detected based on a propagated-versus-published velocity-vector difference exceeding 3× the background RMSE, while the semimajor axis, inclination, and RAAN deviations each remain within ±3× their respective background RMSEs.
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Please note that the "Selected Objects vs. All" option and Email Notifications are only available for registered users, with registration currently being free of charge.
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