A Lunar Lander Concept for Scientific and Robotic Exploration on the Lunar South Pole
- Paper number
IAC-08.A3.2.B7
- Author
Mr. Jeffrey Apeldoorn, OHB-System AG, Germany
- Coauthor
Mr. Hartmut Mueller, OHB-System, Germany
- Year
2008
- Abstract
Since 2002 and under own responsibility, OHB-System has performed intensive studies with regard to the development of a roadmap towards a European lunar exploration program, which were dubbed “MonaLisa”. Based on the experience resulting from these activities and the involvement in national and European initiatives regarding Exploration on, of and from the Moon, a new lander concept was developed serving for static and mobile exploration activities specifically near the lunar South Pole. This new concept was proposed for further investigation within the AURORA NEXT Lunar Lander Phase A Mission study. In the context of this study the OHB-System approach has been adapted to - demonstrate in a representative environment key capabilities and technologies for Mars Sample Return (MSR) and future exploration missions in general, and to - offer an opportunity for important scientific investigations respectively research. The mission scenario foresees a launch in the year 2016 with a Soyuz-2-1b-Fregat launcher. The Lander shall utilize a unique active landing control system with a cluster of thrusters to reach a safe landing site. Moreover the capability of recognizing obstacles and acting according to them requires a sophisticated correlation between sensors and thrusters. These are prerequisites to achieve a successful autonomous soft precision landing with hazard avoidance. The proposed NEXT Lunar Lander is equipped with different scientific payloads including a separate Rover. After touch-down on the lunar surface this Rover will egress the Lander via egress ramps and will commence with an excursion of minimally one year over the lunar surface. During this expedition the Rover will stop on a regular basis to perform various scientific experiments including soil investigation and seismic measurements. At the same time the Lander will perform scientific experiments on its own at the landing site. After the mission of one year it is envisaged to let the Lander perform a concluding hopping manoeuvre with the rest propellant to demonstrate restartability of the engines and an ascent from another celestial body. The paper will give an overview on - Science and technology objectives - Overall mission and system architecture plus concept - Operations
- Abstract document
- Manuscript document
IAC-08.A3.2.B7.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.