High Autonomy Lunar Surface Mobility Systems

Paper number

IAC-06-A3.6.08

Author

Prof. Ernesto Vallerani, International Space Pioneers, Italy

Coauthor

Msc Alberto Della Torre, Carlo Gavazzi Space, Italy

Coauthor

Dr. Gian Paolo Guizzo, Italy

Coauthor

Dr. Igor Vukman, Carlo Gavazzi Space, Italy

Year

2006

Abstract

Mobility Systems operating on the Lunar Surface represent the most challenging Element of Future Architectures which will support the Moon Exploration and Development. Initially, they will be used for Robotic Systems, and subsequently to support Human presence.
The results of activities carried out in preparation of Studies to be performed in the frame of Future ESA and/or ASI Initiatives are reported.
Particular attention has been given to the Mobility Subsystem (MSS) which enables the transfers of the vehicles across the Lunar Surface.
Demanding requirements have been considered; the main mobility-related ones are: maximum autonomy during transfers, independence from the nature of the lunar terrain, "precise" close-range mobility, avoidance of the interference that the MSS operations could have on the scientific measurements, minimum consumption of the consumables.
The categories of MSS design solutions that will be compared in a trade-off analysis are: propulsion systems, surface mobility systems, non-propelled jumping systems, (e.g. with springs or gas pistons) combined systems (using two or more of the previous categories).
The Lunar Surface Mobility Systems (LSMS) comprise Fixed Moon Robotic Bases (FMRB), and a potential variety of Mobile Systems (MS) which carry the MSS. The resulting LSMS Architecture is based on a Very Large Flexibility and possesses a high degree of Growth Potential; it takes account of the crucial role of In Situ Resource Utilisation during all the exploration phases.
The Architecture identified and recommended for further analysis is based on Reusable and Highly Integrated Elements. In particular the Elements of the Deorbit and Landing System are largely integrated with the MS. Commonality is extensively utilized at System, Subsystem and Component levels.
A preliminary conceptual design of a "basic" Robotic LSMS will be shown. It is composed of a FMRB and a MS (with a chosen MSS solution), and starts its operation in Low Lunar Orbit (LLO), with an initial mass of 1500 kg. One of its main scientific tasks is the exploration of the permanently shadowed areas in the Shackleton crater. The results of the preliminary design will show that even with such a limited mass budget in LLO, scientific investigations of considerable importance can be performed with a payload mass of about 100 kg.

Abstract document

IAC-06-A3.6.08.pdf

Manuscript document

IAC-06-A3.6.08.pdf (🔒 authorized access only).

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