Mission Description

• Earth departure orbit is circular at an altitude of 1,000km
• Spiral escape to C3=0
• Depart from Earth sphere of influence (SOI) on Julian date 2457382.5 (Dec 26, 2015) – fixed at optimal
• Arrive at Neptune SOI on Julian date 2461765.5 (Dec 26, 2027) -- fixed
• Spiral descent to circular Neptune parking orbit at an altitude of 330,136 km (~ Triton altitude)
• Initial mass:  9679.0 kg (fixed)
• Propulsion and power system mass (alpha) = 50 kg/kW
• Tankage fraction = 0.1,  (Tank mass/propellant mass)
• Propulsion Model:  simple electric engine,
  • Isp 6600 sec, (optimal +/- 100sec)
  • 0.65 efficiency
• Power Model: constant power (nuclear), optimized to 54.83 kW
• Objective function:  final mass
• Originally modeled using CHEBYTOP

Input/Output files

CHEBYTOPv6.zip (download)

MALTO4_3_3.zip (download)

Mystic9_0_0.zip (download)

All Reference Case 20: 12-years to Neptune/Triton Orbiter Files (download zip)