MNV-0905 · FENGYUN 1C DEB
OG-2 Meridian-2 — in-track burn, executed
Delta-v0.31m/s
Propellant0.045kg
Axisin-track
Executed4d 0h ago
Statusexecuted
Burn performed. Post-burn state vector confirmed by tracking.
Effect on the event
Pc before6.7×10−4
Pc after1.4×10−7
- Conjunction
- CJ-4419 (cleared)
- Spacecraft
- OG-2 Meridian-2
- Secondary
- FENGYUN 1C DEB
- Operator
- A. Lindqvist
Propellant cost
This burn0.045kg
Remaining4.82kg
SK runway1.4yr
4.820 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 axis561.9m
Δ period0.696s
Δ eccentricity8.2e-5
Drift per orbit5.296km
Along-track at TCA (0.0h lead)0.00km
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.
Propulsion
Tsiolkovsky
Specific impulse220s
Thrust2.400N
Vehicle mass312.4kg
Propellant0.0449kg
Burn duration40s
Mass fraction1.4e-4
- System
- Hydrazine monopropellant, 4x0.6N
- Δv capability remaining
- 18.2 m/s
- Avoidance burns of this size left
- 58
Burn is short relative to the orbital period, so the impulsive approximation used above holds.
Downstream conjunctions
not modelled
No downstream screening on file for this burn. Historical burns retain their record but not the re-screening that followed.