To support the coming decade of Mars exploration, NASA is establishing a telecommunications relay and navigation infrastructure in Mars orbit, supporting increased science data return, providing energy-efficient relays for small scout-class mission concepts, gathering engineering telemetry during critical mission events, and providing in situ radiobased navigation. A key element of this vision is the Electra Proximity Payload, a telecommunications and navigation payload that will fly on each Mars orbiter, beginning with the 2005 Mars Reconnaissance Orbiter (MRO) and with subsequent flight on the 2009 Mars Telecommunications Orbiter (MTO). We present here the functional requirements, design characteristics, and implementation status of the Electra Payload and its role as a telecommunications node in an evolving Mars orbital infrastructure.

the Curiosity rover successfully touched down on the Martian surface setting off the most ambitious surface exploration of this planetary body. Preceding this significant step were years of design, development, and testing of the Curiosity Entry, Descent, and Landing system to prepare for the most complex landing endeavor ever attempted at Mars. To address the numerous challenges, the approach and implementation of the overall Entry, Descent, and Landing verification and validation program relied on its decomposition into three distinct domains: flight dynamics, flight system and subsystem verification and validation. The test and analysis scope, the venues, and the processes utilized were tailored to each of these domains, and are discussed in greater detail. The overall lessons learned and conclusions described herein can serve as a pathfinder for the Entry, Descent, and Landing system testing approach and implementation of future Mars landed missions.

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