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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2026-11-02 13:03:16.198
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61113
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CZ-6A DEB
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101193
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HULIANWANG DIGUI 231
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3.555
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0.814, 1.733, 2.996
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12.6494
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2026-11-02 13:24:41.802
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46384
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STARLINK-1771
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101174
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STARLINK-38273
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3.667
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-1.000, -1.742, 3.068
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13.4099
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2026-11-02 14:50:50.856
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61113
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CZ-6A DEB
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101191
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HULIANWANG DIGUI 229
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1.429
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1.086, -0.496, -0.786
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12.6369
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2026-11-02 14:55:43.624
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46384
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STARLINK-1771
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101174
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STARLINK-38273
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1.546
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-1.084, 0.543, -0.958
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13.4122
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2026-11-02 15:16:07.947
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4991
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THORAD AGENA D DEB
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101188
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HULIANWANG DIGUI 226
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0.959
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-0.167, -0.284, 0.900
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13.9703
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2026-11-02 15:17:59.947
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4843
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OPS 0100 DEB *
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101193
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HULIANWANG DIGUI 231
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4.485
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-4.345, 0.391, -1.043
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13.6740
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2026-11-02 15:56:58.559
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44571
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SCOUT G-1 DEB
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101190
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HULIANWANG DIGUI 228
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3.038
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-1.717, 1.538, 1.979
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11.6312
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2026-11-02 17:02:26.830
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4991
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THORAD AGENA D DEB
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101188
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HULIANWANG DIGUI 226
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3.736
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-0.282, 1.117, -3.555
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13.9765
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2026-11-02 18:43:19.702
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68028
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STARLINK-36253
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101201
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STARLINK-38230
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3.339
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3.157, -0.948, 0.537
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7.5335
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2026-11-02 19:31:10.224
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66515
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SZ-21 MODULE
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101206
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STARLINK-37986
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0.958
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-0.615, 0.670, -0.301
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6.3170
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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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