Mars Spacecraft Mission Trade Space & Delta-V Planner

Mission Configuration Electric Hybrid

Architecture Presets

Launch Vehicle Class C3 > 0: 2,500 kg

Spacecraft Propulsion Architecture

Instrument Payload Mass (kg) 450 kg

Specific Impulse Isp (seconds) 3,100 s

Target Mars Arrival Orbit

Delta-V Flight Reserve Allowance 15%

High-Isp solar electric propulsion minimizes propellant wet mass while extending transfer spiral duration. Ideal for cost-capped commercial smallsats challenging traditional monolithic exploration architectures.

Orbital Transfer Visualizer

Viable

Initial Wet Mass 2140.2 kg Payload: 450 kg

Propellant Mass 1690.2 kg Mass frac: 78.9%

Required Total ΔV 5.85 km/s TMI: 3.60 | MOI: 2.25

Transit Duration 310 days Low-thrust spiral

Margin of Error 14.5% Nominal buffer

Launch Margin +359.8 kg Under LV limit

Mission Phase	Maneuver Description	Delta-V (ΔV)	Mass Post-Burn