Propulsion Policy

Overall: PASS

• Released orbit: 600.0 km circular SSO at 97.8 deg
• Mission duration basis: 5.0 years
• Architecture: blowdown green-monopropellant orbit-maintenance and disposal system
• Wet mass sizing basis: 4500.000 kg

Hardware complement

• aft_thruster_quad: monopropellant_thruster, 4 unit(s), 4.0 W total, 12.0 kg total
• central_diaphragm_tank: diaphragm_tank, 1 unit(s), 1.0 W total, 18.0 kg total
• pressurant_regulator_module: pressurant_regulation_module, 1 unit(s), 2.0 W total, 8.0 kg total
• latch_valve_feed_manifold: feed_isolation_valve_manifold, 1 unit(s), 5.0 W total, 10.0 kg total

Propellant and subsystem budget

• Propellant: AF-M315E
• Loaded propellant mass: 150.000 kg
• Usable propellant mass after residuals: 145.500 kg
• Propellant loaded volume: 102.041 L
• Tank usable fill volume: 105.800 L
• Dry hardware mass: 48.000 kg
• Total propulsion-system mass: 198.000 kg against 210.000 kg allocation
• Total propulsion-system power: 12.000 W against 12.000 W allocation

Delta-v closure

• Drag make-up delta-v with margin: 24.786 m/s
• Momentum-management delta-v: 0.000 m/s
• Disposal delta-v with margin: 49.403 m/s to a 450.0 km perigee target
• Required total delta-v: 74.188 m/s
• Available total delta-v: 82.192 m/s
• Effective burn duration: 3878.484 s against 5400.000 s limit
• Momentum-management approach: magnetorquer-based

Disposal concept

• Retrograde disposal burn at 600 km apogee lowers perigee into a drag-decay corridor, with the detailed post-disposal lifetime verification tracked separately under the orbit-environment backlog item.

Checks