Forecast of Conjunctions: 50 Latest Payloads vs. All (31718) 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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2026-09-30 22:05:25.206
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62556
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STARLINK-11515
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100769
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STARLINK-38388
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3.207
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-1.721, 2.173, 1.613
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9.1846
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2026-09-30 22:14:41.946
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66708
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FLOCK 4H 5
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100741
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TIANYI 51
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4.227
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-2.099, -3.083, -1.988
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8.2486
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2026-09-30 22:35:09.875
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47086
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SL-14 DEB *
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100689
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FLEX
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4.615
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-0.612, -0.486, -4.548
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14.7746
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2026-09-30 22:42:18.701
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40216
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SCOUT G-1 DEB
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100696
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QIANFAN-243
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2.151
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1.539, 0.454, 1.432
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14.0203
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2026-09-30 23:17:27.945
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45369
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STARLINK-1277
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100772
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STARLINK-38367
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2.553
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-2.329, 0.541, 0.894
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13.2116
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2026-09-30 23:53:43.460
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12087
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COSMOS 1225
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100695
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QIANFAN-242
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0.985
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0.983, -0.058, 0.017
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3.3848
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2026-10-01 00:22:48.101
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62556
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STARLINK-11515
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100769
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STARLINK-38388
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2.706
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1.495, -1.807, 1.350
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9.1987
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2026-10-01 00:28:36.570
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100534
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STARLINK-38244
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100773
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STARLINK-38386
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4.286
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-4.222, -0.708, -0.211
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4.4340
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2026-10-01 00:30:35.672
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2680
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DIADEME 2
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100693
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QIANFAN-240
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3.759
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-3.591, -1.081, 0.256
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6.7130
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2026-10-01 00:46:10.085
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14974
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SL-8 R/B
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100694
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QIANFAN-241
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3.687
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3.682, -0.096, -0.180
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13.1429
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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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