Jovian Outpost Establishment Trajectory Design
- Paper number
IAC-05-A3.2.A.06
- Author
Mr. Ridanto Poetro, Kyushu University, Japan
- Year
2005
- Abstract
In the future, human is likely to turn their attention to establish an outpost in Jovian System. With the outpost, an ultimate exploration and exploitation of the Jovian system as replica of the solar system can be secured with potential to extend the exploration to further destination of the solar system or beyond. An international co-operation like ISS is expected with US, Russia, EU, Japan, China and India as the major contributors.
Use of current technology for the outpost establishment assessment is performed with outpost base location at low Callisto orbit. The orbit is chosen considering Jupiter radiation and access energy from/to Jupiter and water resource (Europa or Callisto itself). The base consists of propellant production facilities, nuclear power units, science equipment, communications equipment, rocket engines, spare parts, and so on with mass at least 300 ton (full configuration of ISS) up to 1000 ton as the optimistic number.
The base construction requires multiple launchs, distributed in 30 years (2030-2060) with various gravity assist paths involving Venus, Earth and Mars. Multiple gravity assist launch opportunities are enumeratively searched by means of “C3 matching”. Low energy (launch C3 < 16 km2/s2) trajectories are exist for almost every year with time of flight between 6-8 years. Use of bi-elliptic transfer to Callisto and Galilean moons gravity assist further reduces insertion energy which in turn enable reasonable number of required flight per year.
Examination of Japan’s capability to handle one supplier spacecraft in 2034 launch opportunity with H2A-222 launch vehicle and VEE-GA shows more than 5 metric ton dry mass can be delivered per single flight into low Callisto orbit. This figure includes payload docking with separately launched booster (ESC-B class) and bi-elliptic transfer to Callisto.
Development of nuclear- powered electric propulsion will reach maturity by 2030 and would replace multiple gravity assist option with more payload capability and less flight time. Double the payload capability with half flight time of the conventional way can achieve is estimated.
- Abstract document
- Manuscript document
IAC-05-A3.2.A.06.pdf (🔒 authorized access only).
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