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Laser ablation based on-orbit debris removal
Karampudi, Prathyusha
Karampudi, Prathyusha
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Thesis
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2019-07
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Electronic dissertation
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Electronic dissertations
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Abstract
Space debris are defunct man-made satellites orbiting in the low-earth orbit (LEO)
and Geo-synchronous orbit (GEO) orbiting around earth with high velocities posing a serious
threat for current and future missions. Controlling the growth of debris is of great importance
for sustained space operations. This has led researchers to investigate a wide variety of active
debris removal missions basing on their characteristics: contact less, contact, capturing and
drag augmentation methods.
This thesis discusses space debris removal using ground based lasers. The effect of
laser ablation on de-orbiting process was investigated using Sims-Flanagan model, where
change in momentum translates in gradual change in the debris trajectory. A 5 cm spherical
shaped debris of mass 0.1 kg was modeled using a series of change in velocities ( Δv's)
due to multiple laser engagements to achieve the target orbit of 120 km altitude. The
translational dynamics of the debris was determined assuming laser propagation vector non-tangential
to its surface under the influence of atmospheric drag. It was observed that the
total de-orbit time decreases with the increase in laser coupling coefficient and decrease in
laser pulse duration. The model estimated hours to reach the target perigee radius with laser
engagement of each 30 seconds, for the coupling coefficient of 6 units, and the correspondingly
seconds and engagements for the 6ns laser pulse duration. The model also observed that
the atmospheric drag influenced the de-orbit time exponentially accelerating the process as
it approaching the earth atmosphere.
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Thesis (M.S.)-- Wichita State University, College of Engineering, Dept. of Aerospace Engineering
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Wichita State University
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Copyright 2019 by Prathyusha Karampudi
All Rights Reserved