Forecast of Conjunctions: 50 Latest Payloads vs. All (32067) 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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2026-10-16 00:42:38.264
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67099
↓
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STARLINK-36193
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100955
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NEONSAT-02
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2.204
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1.988, -0.229, 0.922
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14.6970
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2026-10-16 00:47:22.301
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100123
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STARLINK-38134
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100878
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STARLINK-40076
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4.226
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-4.207, -0.256, -0.307
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11.7765
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2026-10-16 02:14:38.433
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55297
↓
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STARLINK-5284
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100963
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NEONSAT-05
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4.476
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-1.534, -0.737, 4.139
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14.9172
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2026-10-16 02:16:19.649
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56810
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STARLINK-6031
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100955
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NEONSAT-02
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4.626
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-4.283, -0.824, 1.543
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13.3858
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2026-10-16 02:44:43.856
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58507
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JIELONG 3 R/B
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100968
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NEONSAT-06
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4.686
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1.521, 0.429, 4.411
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14.9800
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2026-10-16 03:22:06.044
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33410
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CZ-4B R/B
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100917
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ION SCV-026
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4.171
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-3.912, -1.303, -0.631
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0.3857
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2026-10-16 03:35:25.643
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52500
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STARLINK-3866
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100889
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ICEYE-X83
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0.456
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-0.437, -0.062, 0.113
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13.4239
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2026-10-16 03:46:18.739
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62881
↑
↺
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STARLINK-11382
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100875
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STARLINK-40103
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4.311
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-2.470, 3.238, 1.413
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6.1669
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2026-10-16 04:55:56.778
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68461
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IRIDE-MS1-EAG2-12
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100941
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RADIX-A
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3.854
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3.852, -0.054, -0.081
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12.5427
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2026-10-16 05:13:08.108
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53925
↓
→
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STARLINK-5011
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100889
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ICEYE-X83
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2.959
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2.833, -0.739, 0.433
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7.6691
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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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