MNV-0912 · COSMOS 2251 DEB

OG-2 Meridian-2 — in-track burn, proposed

All maneuvers

Delta-v0.34m/s

Propellant0.049kg

Axisin-track

Scheduledin 3h 00m

Statusproposed

Solution generated. No operator has committed it.

Effect on the event

Pc before4.7×10⁻⁴

Pc after8.2×10⁻⁸

Conjunction: CJ-4471
Spacecraft: OG-2 Meridian-2
Secondary: COSMOS 2251 DEB
Operator: —
Burn time: 2026-08-01 17:32:00Z
Upload pass: Svalbard (SG-1)
Duration: 44 s

Propellant cost

This burn0.049kg

Remaining4.82kg

SK runway1.4yr

4.771 kg after burnreserve 2.2 · capacity 12.4 kg

Orbit response

Gauss variational · Clohessy–Wiltshire

Δ semi-major axis616.3m

Δ period0.764s

Δ eccentricity8.9e-5

Drift per orbit5.808km

Along-track at TCA (6.2h lead)22.88km

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 projection19.5%

Only the component of that displacement perpendicular to the 14.81 km/s relative velocity lies in the encounter plane and changes miss distance; the rest changes arrival time. At 11.2° off the relative-velocity vector, 22.9 km of drift becomes 4.46 km of additional separation.

Propulsion

Tsiolkovsky

Specific impulse220s

Thrust2.400N

Vehicle mass312.4kg

Propellant0.0492kg

Burn duration44s

Mass fraction1.6e-4

System: Hydrazine monopropellant, 4x0.6N
Δv capability remaining: 18.2 m/s
Avoidance burns of this size left: 53

Burn is short relative to the orbital period, so the impulsive approximation used above holds.

Downstream conjunctions

4 affected

Event	Secondary	TCA	Pc before	Pc after	Effect
CJ-4471	COSMOS 2251 DEB34454	T+9.2h	4.7×10⁻⁴	8.2×10⁻⁸	resolved
CJ-4489	SL-16 R/B DEB23705	T+34.1h	—	3.3×10⁻⁶	created
CJ-4491	FENGYUN 1C DEB29275	T+51.2h	—	1.1×10⁻⁶	created
CJ-4463	COSMOS 2251 DEB34871	T+61.4h	5.2×10⁻⁶	1.1×10⁻⁷	improved