MNV-0911 · SL-16 R/B DEB
OG-1 Meridian-1 — in-track burn, expired
Delta-v0.15m/s
Propellant0.022kg
Axisin-track
Executed1h 36m ago
Statusexpired
The decision deadline passed before anyone committed.
Effect on the event
Pc before3.2×10−5
Pc after4.4×10−8
- Conjunction
- CJ-4474
- Spacecraft
- OG-1 Meridian-1
- Secondary
- SL-16 R/B DEB
- Operator
- —
- Burn time
- 2026-08-01 12:56:00Z
- Upload pass
- Fairbanks (KSAT)
- Duration
- 20 s
Propellant cost
This burn0.022kg
Remaining6.14kg
SK runway2.1yr
6.140 kg after burnreserve 2.2 · capacity 12.4 kg
Already drawn down — the remaining figure above is post-burn.
Orbit response
Gauss variational · Clohessy–Wiltshire
Δ semi-major axis271.8m
Δ period0.337s
Δ eccentricity3.9e-5
Drift per orbit2.561km
Along-track at TCA (6.7h lead)10.85km
An in-track burn separates by changing the orbital period, so displacement grows as Δx = 3·Δv·t. Lead time, not delta-v, is what buys miss distance — the same burn an hour later is worth proportionally less.
B-plane projection37.1%
Only the component of that displacement perpendicular to the 13.42 km/s relative velocity lies in the encounter plane and changes miss distance; the rest changes arrival time. At 21.8° off the relative-velocity vector, 10.9 km of drift becomes 4.03 km of additional separation.
Propulsion
Tsiolkovsky
Specific impulse220s
Thrust2.400N
Vehicle mass313.7kg
Propellant0.0218kg
Burn duration20s
Mass fraction7.0e-5
- System
- Hydrazine monopropellant, 4x0.6N
- Δv capability remaining
- 27.3 m/s
- Avoidance burns of this size left
- 180
Burn is short relative to the orbital period, so the impulsive approximation used above holds.
Downstream conjunctions
2 affected
| Event | Secondary | TCA | Pc before | Pc after | Effect |
|---|---|---|---|---|---|
| CJ-4474 | SL-16 R/B DEB23705 | T+5.1h | 3.2×10−5 | 4.4×10−8 | resolved |
| CJ-4487 | DELTA 1 DEB12445 | T+58.2h | — | 1.6×10−6 | created |