Forecast of Conjunctions: 50 Latest Payloads vs. All (31369) 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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2026-09-20 22:40:51.084
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2828
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GGSE 4
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100700
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QIANFAN-247
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4.856
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0.441, -1.341, 4.646
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14.2068
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2026-09-20 23:30:28.041
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54251
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OBJECT A
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100620
↑
↻
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STARLINK-38278
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3.461
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-3.402, 0.071, 0.630
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15.3165
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2026-09-20 23:33:46.886
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59224
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STRIX-3
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100741
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TIANYI 51
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3.817
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0.993, -2.406, -2.792
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11.5461
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2026-09-20 23:47:20.472
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12212
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DELTA 1 DEB
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100694
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QIANFAN-241
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2.823
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2.812, -0.184, -0.165
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10.0656
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2026-09-21 00:17:14.628
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6788
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THOR BURNER 2 R/B
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100689
↻
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SENTINEL-3C
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0.810
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-0.037, -0.189, -0.787
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14.4374
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2026-09-21 00:23:54.726
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2828
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GGSE 4
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100701
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QIANFAN-248
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1.670
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0.604, -0.430, 1.497
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14.2105
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2026-09-21 00:23:55.140
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2828
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GGSE 4
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100700
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QIANFAN-247
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2.783
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0.455, -0.759, 2.639
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14.2107
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2026-09-21 01:45:54.929
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55010
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MENUT
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100632
↑
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STARLINK-38403
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2.769
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2.767, -0.070, 0.088
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11.9535
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2026-09-21 02:06:58.779
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2828
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GGSE 4
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100701
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QIANFAN-248
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0.836
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0.605, 0.159, -0.556
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14.2144
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2026-09-21 02:06:59.195
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2828
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GGSE 4
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100700
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QIANFAN-247
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0.767
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0.456, -0.170, 0.593
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14.2146
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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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