Mission Description

Earth Launch to Sun-Earth L1 Point to Low Lunar Orbit

• Propulsion System SEP
• Launch Date 05/20/2003 (fixed)
• Time to SE-L1 50 days (free)
• End Date 10/17/2003 (fixed)
• Flight Time 150 days (fixed)
• Solar Array TJGA
• Initial Mass 2,500 kg (fixed)
• P0 30 kW
• Engine NSTAR Engine Q-mod (1 engine)
• Duty Cycle 100%
• Launch Conditions
• C3 = 0 (free)
• rp = 185 km altitude (fixed)
• i = 28.5 deg
• Final State (Moon Centered, plane free) – initial target a = 25,000 km
• Originally modeled using Mystic

Additional Mission Options

A. Earth-Moon Libration Point/halo orbit to other Sun-Earth Libr. Pt Orbit/halo:
Constant Power Variable Specific Impulse Trajectory from the Earth-Moon interior libration (EML1) point to small amplitude quasi-periodic orbit about the interior Earth/Moon-Sun libration point (ESL1). Model includes only the gravity of the Earth, Moon, and Sun and these follow a realistic ephemeris.

• Depature date Jan 1 2010 <= T0 <= March 1 2010
• Total Transfer Time <= 360 days
• System Power 100 Kw
• Efficiency 75% (constant)
• Initial Mass 2000 kg
• Thrust variable
• ISP variable
• Engine Degradation None
• Coast Periods allowed if optimal
• Target Orbit Planar Lyapunov at L1 y-axis amplitude = 100,000 km.
• Final Mass Maximize
• Originally modeled using Copernicus

Input/Output files

Copernicus20060313.zip (download)

Mystic9_0_0.zip (download)

All Reference Case 31: Earth/Sun/Moon, 4-body/n-body Files (download zip)