Abstract
The first Mars Sample Return mission to be launched in 2005 presents significant challenges to the design of the Earth entry, descent, and landing system for the Martian sample. These challenges are driven by low vehicle mass, high entry velocity, and very high reliability, the latter being due the the unknown biohazard potential of the Martian material. The challenges include a passive landing system that maintains sample containment, and the qualification of a high-performance thermal protection system at entry velocities exceeding the Earth entry vehicle experience to date.
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