Title:
Development of an Earth SmallSat Flight Test to
Demonstrate Viability of Mars Aerocapture
Development of an Earth SmallSat Flight Test to
Demonstrate Viability of Mars Aerocapture
Author(s)
Werner, Michael S.
Advisor(s)
Braun, Robert D.
Editor(s)
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Abstract
A smallsat mission concept is developed to demonstrate the feasibility of an aerocapture
system at Earth. The proposed mission utilizes aerocapture to transfer from a GTO rideshare
trajectory to a LEO. Single-event drag modulation is used as a simple means of achieving the
control required during the maneuver. Low- and high-fidelity guidance algorithm choices are
considered. Numeric trajectory simulations and Monte Carlo uncertainty analyses are
performed to show the robustness of the system to day-of-flight environments and
uncertainties. Similar investigations are performed at Mars to show the relevance of the
proposed mission concept to potential future applications. The spacecraft design consists of a
24.9 kg vehicle with an attached rigid drag skirt, and features commercially-available
hardware to enable flight system construction at a university scale. Results indicate that the
proposed design is capable of targeting the desired final orbit, surviving the
aerothermodynamic and deceleration environments produced during aerocapture, and
downlinking relevant data following the maneuver
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Date Issued
2017-05-01
Extent
Resource Type
Text
Resource Subtype
Masters Project
Rights Statement
Unless otherwise noted, all materials are protected under U.S. Copyright Law and all rights are reserved