Mission Description

Earth – Low Lunar Orbit (Earth Spiral Out from 100,000 km)

• Propulsion System SEP
• Launch Date 05/20/2003 (fixed)
• End Date 09/07/2003 (fixed)
• Flight Time 110 days (fixed)
• Solar Array TJGA
• Initial Mass 2,500 kg (fixed)
• P0 20 kW
• Isp 6000 sec
• Efficiency 70 %
• Duty Cycle 100%
• Initial States (EME2000) – fixed
  • a = 100,000 km
  • e = 0
  • i = 28.5 deg
• Final State (Moon Centered, plane free) – initial target a = 20,000 km
• Originally modeled using Mystic

Additional Mission Options

A.  LEO to Low Lunar Orbit

Same as (28), but final target is a 100 km altitude polar orbit (90 deg) around the moon.  Originally modeled using Mystic

B.  LEO to Low Lunar Orbit w/ Round-trip

Same as (28a), but with a Lunar science orbit and a return trip back to Earth.

• 20 days of science orbit at the Moon
• 50 kg mass drop at the Moon
• Originally modeled using Mys

C.  LEO to Earth-Moon Libration Points & Libration Points Halo Orbits

Same as (28), but targeting a Earth-Moon L1 Halo Orbit

• Time To Halo-Orbit-Insertion (HOI): 82.5751 days
• No Thrusting after HOI
• Total Flight Time: 118 days (fixed)
  • Halo Orbit Target:
  • Ax = 10,000 km
  • Ay = 30,000 km
  • Az = 10,000 km
• Propellant Mass: < 25 kg
• Originally modeled using Mysti

Input/Output files

Copernicus20060313.zip (download)

Mystic9_0_0.zip (download)

All Reference Case 28: Earth-Moon low thrust Files (download zip)