Tbe main purpose of this work was to find a way of placing a meaningful scientific payload
within the upper atmosphere of Mars such that certain scientific measurements become possible.
So the altitude range covered and the possible dweIl time are relevant design drivers and will
be explored in greater detail within this thesis. Either concept of flying on Mars however be
it heavier or lighter than air (read: heavier or lighter than carbon dioxide) is restricted to
altitodes weil below 10 km. Since any sustained !light at that altitode or higher in such a
thin atmosphere is teehnically impractical so is ascending to that altitode with - sounding
rocket. Therefore - team of scientists from several research institutes around Europe fonned a
scientific committec. Together with engineers and scientists from tbe Mars Society Germany and
tbe University ofthe Federal Armed Forces of Germany in Munich (UBW) the committee drafted a
reference scientific mission scenario [1] to :find ways to da exactly that: providing an
instrument suite with access to a large altitu. de range and. meaningful dwell time (see 10. 3.
1 starting onp. ge 208). Tbc most practical approach was found in an inflatable entry vehicle
that can provide the largest and lightest possible configuration. Since 00 such attempts have
yet been m. ade the work described herein focuses mostly on the mathematical thcory and the
technical peculiarities of such a system but also treats mission design and testing aspects.
1.
