Project EREBUS

Satellite
End-of-Life
Disposal Checker

OCS-1 · IADC-02-01 · UN COPUOS

Design for orbit. Verify your disposal plan before launch.

SYSTEM ONLINE

IADC REF: 24-1977

v2.4.1

ORBITAL COMPLIANCE
VERIFICATION SYSTEM

End-of-Life Deorbit Assessment · IADC Space Debris Mitigation Guidelines

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Satellite Parameters

// ORBITAL PARAMETERS

Altitude km, 200–2000 (LEO)

Operational Lifespan years, 1–25

// MASS & PROPULSION

Satellite Mass kg, 1–2000

Fuel Mass kg, 0–500

Disposal Method

▶ ADVANCED PARAMETERS (Optional)

Drag Area m²

Delta-V Capability m/s

Propulsion Type

Custom Isp s (overrides propulsion type)

EOL Fuel Reserve Fraction 0–1 (fraction of total fuel held for deorbit)

// LOAD EXAMPLE PROFILE

✕ Please fill in all required fields: altitude, lifespan, satellite mass, and fuel mass.

REF: IADC-02-01 Rev. 4 · UN COPUOS Guidelines 2007
Rule: All LEO debris must deorbit within post-mission EOL.
GEO disposal: raise to graveyard orbit (+300 km above GEO arc).

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Compliance Report

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AWAITING SATELLITE INPUT DATA
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Enter parameters and run analysis
to generate compliance report

COMPLIANCE SCORE —

◈ Model Assumptions & Limits

Calibrated for Low Earth Orbit (200–2000 km).
Natural decay times are approximate — real values depend on atmospheric drag and solar activity cycle.
Propulsive deorbit check uses a simplified Tsiolkovsky rocket equation with assumed Isp; results are estimates, not flight-certified.
Tool is intended for early design checks, not operational flight dynamics or regulatory filing.

STATUS:STANDBY

CHECKS:0/4

RULE:IADC-02-01

IADC-02-01 · Rules

◈ Reference Document

IADC-02-01
Space Debris Mitigation

Core rules this tool is aligned with

// Core Mitigation Principles

RULE 01 · DEBRIS RELEASE

Limit the number of objects released during normal mission operations. Each piece intentionally ejected adds to the long-term debris population.

RULE 02 · BREAK-UP PREVENTION

Minimise the risk of accidental break-ups. This means passivating residual stored energy at end-of-life — venting propellants, discharging batteries, and relieving pressure vessels — so they cannot explode or fragment years later.

RULE 03 · POST-MISSION DISPOSAL · LEO

Spacecraft operating in Low Earth Orbit must be removed from the densely used LEO region within 25 years after end-of-mission. Removal is achieved either by direct atmospheric reentry or by lowering the orbit so natural drag causes reentry within the limit.

RULE 04 · POST-MISSION DISPOSAL · GEO

Geostationary spacecraft should be moved to a graveyard orbit at least 300 km above the GEO ring at end-of-life, and passivated, so the valuable GEO belt remains usable.

RULE 05 · COLLISION AVOIDANCE

Assess and, where feasible, reduce the risk of collision with trackable debris and other spacecraft during operations. Responsible constellation design accounts for conjunctions from the outset.

// How This Tool Maps to the Rules

CHK-01 · ALTITUDE CHECK → RULE 03

Flags orbits above ~600 km where natural drag alone cannot guarantee reentry within 25 years, making active disposal mandatory.

CHK-02/05 · FUEL CHECK → RULE 03

Verifies whether onboard propellant (accounting for an end-of-life reserve) is sufficient to execute the required deorbit burn using a simplified Tsiolkovsky rocket equation.

CHK-03 · LIFETIME CHECK → RULE 03

Confirms that mission duration plus natural post-mission orbital decay stays within the 25-year window mandated by the guideline.

CHK-04 · METHOD CHECK → RULES 03–04

Validates that the chosen disposal strategy (propulsive deorbit, drag sail, graveyard, or passive decay) is appropriate for the satellite's altitude class.