Forecast of Conjunctions: 50 Latest Payloads vs. All (31338) 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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2026-09-25 21:17:09.591
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61898
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OBJECT E
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100614
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SPECTRUM
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4.893
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2.143, 4.397, -0.093
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0.9172
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2026-09-25 22:24:34.666
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40054
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AISAT
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100561
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STRIX-9
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3.674
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1.839, 1.914, 2.540
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12.1396
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2026-09-25 22:58:05.780
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53578
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STARLINK-4556
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100789
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ZK-1A / RB
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2.717
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-2.717, 0.024, 0.016
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13.3053
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2026-09-25 23:39:37.002
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13908
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SL-6 DEB
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100692
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QIANFAN-239
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1.497
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-1.407, -0.469, -0.199
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7.8235
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2026-09-25 23:54:01.789
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62204
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STARLINK-32664
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100619
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STARLINK-36683
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3.922
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-2.365, 2.799, 1.398
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6.8981
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2026-09-25 23:59:23.356
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29772
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FENGYUN 1C DEB
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100701
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QIANFAN-248
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4.725
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-0.378, -3.355, 3.306
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10.3909
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2026-09-26 00:18:44.629
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45728
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ELECTRON KICK STAGE R/B
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100742
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TIANYI 52
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3.774
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-2.566, 0.768, 2.659
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14.6209
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2026-09-26 00:27:53.420
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66538
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STARLINK-35577
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100789
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ZK-1A / RB
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3.945
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-1.399, -2.007, 3.095
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12.6845
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2026-09-26 01:25:07.903
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66769
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SPEQTRE
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100742
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TIANYI 52
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3.551
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-3.514, 0.461, 0.213
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6.3831
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2026-09-26 01:31:20.470
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30669
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FENGYUN 1C DEB
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100694
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QIANFAN-241
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1.529
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0.911, 0.090, -1.225
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14.6939
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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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