Mission Description

Ballistic trajectory from LEO to an Exterior Ballistic Lunar Capture Trajectory, using an SEP engine to capture into a pre-specified circular lunar polar orbit.  Model includes only the gravity of the Earth, Moon, and Sun and these follow a realistic ephemeris.  This mission tests a program’s capability to target a multi-body gravitational lunar capture type trajectory with a combined SEP based insertion maneuver around the target body.

• Depature date Jan 1 2010 <= T0 <= March 1 2010
• Initial Orbit LEO 200 KM altitude, circular, 28.5 deg inclin (J2000), RAAN-free
• Total Transfer Time Arrive before May 1 2010
• Thrust 1 N (fixed)
• SEP Engine P0 5 kW
• Initial Injection Mass 1000 kg
• Launch C3 and direction free
• Engine Degradation None
• Coast Periods allowed if optimal
• Target Orbit Lunar Polar Orbit, Circular, Semi-Major Axis: 5000 km
• Final Mass Maximize
• Originally modeled using Copernicus

Additional Mission Options

A. Sun-Earth Sub-L1 Point
B. Above Earth's Poles (Sitting) Orbits
C. Saturn Ring Observer

Input/Output files

Copernicus20060313.zip (download)