Forecast of Conjunctions: 50 Latest Payloads vs. All (32410) 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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2026-10-30 16:53:19.805
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100086
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RASSVET-3 20
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101144
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HAWK 16C
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4.886
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1.535, -4.412, 1.430
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4.6945
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2026-10-30 17:31:51.716
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60540
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HAWK-10A
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101117
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FRG-100D4
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4.976
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4.861, -0.669, -0.831
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11.7683
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2026-10-30 18:08:34.272
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37179
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SHIJIAN 6 04A (SJ-6 04A)
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101146
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HAWK 16A
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1.912
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1.814, -0.079, -0.600
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15.0716
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2026-10-30 19:55:15.972
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56583
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CZ-6A DEB
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101142
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XIGUANG-4 01
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1.673
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-1.626, 0.343, 0.196
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7.7342
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2026-10-30 20:58:26.781
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46141
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STARLINK-1596
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101159
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STARLINK-38479
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2.904
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0.695, -2.225, 1.732
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9.4901
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2026-10-30 21:12:08.694
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61776
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OBJECT AT
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101172
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STARLINK-38462
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2.871
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-1.756, -1.189, 1.936
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13.1616
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2026-10-30 21:14:47.712
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35249
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CZ-4C DEB
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101128
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PELICAN-12 3013
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4.784
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4.222, -0.605, -2.166
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14.6651
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2026-10-30 21:37:47.600
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68293
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ELECTRON KICK STAGE R/B
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101166
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STARLINK-38401
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4.185
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-3.998, 0.954, -0.791
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9.9965
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2026-10-30 21:56:50.904
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58672
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STARLINK-31104
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101165
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STARLINK-38456
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4.004
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-1.278, 3.300, 1.873
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7.6087
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2026-10-30 22:19:39.968
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64869
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LIDE
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101128
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PELICAN-12 3013
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2.744
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-0.026, 1.890, 1.989
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10.9555
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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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