Stability of a Deployable Drag Device for Small Satellite Deorbit
Author(s)
Long, Alexandra C.
Spencer, David A.
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Abstract
Orbital debris has crossed a threshold of critical density in Low Earth Orbit where the
number of debris objects will grow exponentially due to collisions unless actively mitigated. Recent announcements of commercial small satellite constellations indicate interest
in deploying hundreds to thousands of micro-satellites into Low-Earth Orbit at altitudes
ranging from 1,000-1,200 km, in order to provide global internet service. These constellations create a great need for a standard system for deorbit to help mitigate the orbital
debris problem. This paper describes a deployable drag device that leverages recent advancements in thin membrane deployable structures to create a passive aerodynamically
stable drag sail that will ensure a satellite deorbits within 25 years regardless of its functionality. The aerodynamic stability of the drag device is evaluated for orbit altitudes
ranging from 400 to 600 km, while varying the apex half-angle of the square pyramid drag
sail from 65 to 85 deg. An apex half-angle of 80 or 85 deg provides passive stability for
most conditions at orbit altitudes of 500 km and lower. It is shown that transparent CP1
is preferable to aluminized sail material for aerodynamic stability, due to the reduced solar
torques.
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Date
2016-09
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