http://www.loc.gov/mods/v3 http://www.loc.gov/standards/mods/v3/mods-3-2.xsd
Structural design of a lunar lander spacecraft for the Texas space grant regolith oxygen production experiment
viii, 79 leaves : illustrations ; 28 cm.
$450,000 more expensive than an aluminum structure, it is
also 41% lighter. This weight savings made it possible to
and the oxygen plant operation constraints resulted in a
being developed by the Texas Space Grant Consortium to
burns, and lunar landing were the primary load cases that
configuration was selected since it offered the greatest
dynamic requirements. Numerous iteration cycles were
element models subjected to static and dynamic mission loads.
for the lander was a triangular truss structure constructed
lightweight structure. The required diameter and thickness
load-carrying propellant tanks, and a retractable ramp for
meet the weight requirements of the mission and increase the
obtained. A parametric cost analysis of this design showed
of each strut in the truss was determined with two finite
of graphite-epoxy struts and titanium ball joints. This
payload deployment. The structural configuration selected
performed with these loads before a converged solution was
sized the structure. Modal and random vibration analyses
Static loads arising from launch accelerations, main engine
stiffness per unit weight, resulting in an efficient and
structural design for the lunar lander spacecraft currently
surface of the moon. An analysis of the mission requirements
that while the graphite-epoxy structure is approximately
The focus of this research is the determination of a
transport a regolith oxygen production experiment to the
vehicle configuration featuring a tensile thrust structure,
were also performed to verify that the structure met all
"Major subject: Mechanical Engineering".
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