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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2026-11-08 07:18:26.524
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55677
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STARLINK-5324
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101257
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QPS-SAR-20
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3.202
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-0.522, 2.847, 1.371
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6.5755
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2026-11-08 07:49:37.314
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100610
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OBJECT B
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101257
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QPS-SAR-20
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2.034
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-0.376, 0.706, 1.870
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14.1742
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2026-11-08 07:50:18.682
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45676
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STARLINK-1460
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101221
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STARLINK-38491
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3.607
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0.860, 1.688, -3.070
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13.4842
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2026-11-08 08:22:30.107
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63054
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STARLINK-11347
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101218
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STARLINK-38153
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2.391
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2.021, -0.730, -1.049
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12.6436
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2026-11-08 09:08:34.842
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101163
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STARLINK-38392
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101215
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STARLINK-38337
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1.629
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1.610, -0.113, 0.219
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13.7055
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2026-11-08 10:00:46.329
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63548
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STARLINK-11669
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101211
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STARLINK-38340
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4.442
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0.525, 3.868, 2.122
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7.3991
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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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