MERLIN: Mars-Moon Exploration,Reconnaissance and Landed Investigation |
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| Institution: | 1. The Johns Hopkins University Applied Physics Laboratory, Laurel, MD, USA;2. Washington University in St. Louis, St. Louis, MO, USA;3. Jet Propulsion Laboratory, Pasadena, CA, USA;1. University of Basilicata, School of Engineering, 10, Ateneo Lucano Street, 85100 Potenza, Italy;2. National Research Council, Institute of Methodologies for Environmental Analysis (IMAA), c/da S.Loja, 85050 Tito Scalo (PZ), Italy;1. Solar System Missions Division, ESA/ESTEC, Noordwijk, Netherlands;2. Office for Support to New Member States, ESA/ESTEC, Netherlands;3. Science Payload Instrument Section, ESA/ESTEC, Netherlands;1. Science and Technology on Aerospace Flight Dynamics Laboratory, Beijing 100094, China;2. Beijing Aerospace Control Center, Beijing 100094, China;1. University of Naples Parthenope, Italy;2. University of Naples Federico II, Italy |
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| Abstract: | Mars' moons Phobos and Deimos are low-albedo, D-type bodies that may preserve samples of outer solar system material that contributed organics and volatiles to the accreting terrestrial planets. A Discovery-class mission concept described in this paper, the Mars-Moon Exploration, Reconnaissance and Landed Investigation (MERLIN), will obtain in situ measurements from Deimos to test models for the moon's origin. The measurement objectives of MERLIN are to determine Deimos' elemental and mineralogical composition, to investigate its volatile and organic content, and to characterize processes that have modified its surface. To achieve these objectives, a landed payload will provide stereo imaging and measurements of elemental and mineralogical composition and interior structure. An orbital payload will acquire global high-resolution and color imaging, putting the landing site in context by characterizing Deimos' geology. Following MOI the spacecraft flies in formation with Deimos, and uses small changes in its orbit around Mars to investigate Deimos from a range of altitudes and illuminations over 4 months. Data taken during 1- to 2-km altitude flyovers will certify a landing site. The spacecraft will be delivered to a point several kilometers above Deimos, and will navigate to landing on a fresh exposure of regolith using onboard imaging. 90 days of baseline landed operations will provide a complete set of measurements, with schedule reserve, and there is sufficient propellant to repeat the measurements at a second site. |
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