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 19:04:44.205
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12646
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SL-3 R/B
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101268
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QIANFAN-253
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4.380
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1.230, 0.677, 4.149
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14.7151
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2026-11-08 19:04:45.445
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12646
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SL-3 R/B
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101267
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QIANFAN-252
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1.778
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1.307, 0.197, 1.189
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14.7150
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2026-11-08 19:04:47.003
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12646
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SL-3 R/B
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101266
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QIANFAN-251
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2.885
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1.406, -0.403, -2.487
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14.7150
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2026-11-08 19:04:47.099
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12646
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SL-3 R/B
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101265
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QIANFAN-250
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3.118
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1.374, -0.448, -2.762
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14.7150
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2026-11-08 19:13:21.960
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60536
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LEMUR 2 MARHISYAM
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101291
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OBJECT A
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4.694
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4.508, -1.015, -0.830
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9.6031
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2026-11-08 19:41:58.716
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41354
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NOAA 16 DEB
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101264
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QIANFAN-249
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3.886
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-0.658, 3.622, -1.245
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4.8375
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2026-11-08 20:01:49.682
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64650
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CZ-6A DEB
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101292
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OBJECT B
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3.873
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3.698, -0.928, -0.686
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9.1406
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2026-11-08 20:51:51.567
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68198
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OBJECT A
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101286
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CZ-2C ROCKET BODY
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4.610
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4.128, 0.691, -1.933
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14.2825
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2026-11-08 21:47:55.680
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101265
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QIANFAN-250
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101281
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QIANFAN-266
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3.211
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-0.017, 3.211, 0.026
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0.0034
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2026-11-08 22:12:05.011
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22568
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SL-18 DEB
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101264
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QIANFAN-249
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2.544
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1.508, 0.828, -1.874
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13.5594
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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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