Design and Analysis of the Deorbit and Earth Entry
Trajectories for SPORE
Author(s)
Nehrenz, Matthew
Advisor(s)
Spencer, David A.
Editor(s)
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Abstract
Small Probes for Orbital Return of Experiments (SPORE) provides on-orbit operation
and recovery of small payloads. The flight system architecture consists of a service module
for on-orbit operations and deorbit maneuvering, and an entry vehicle for atmospheric
entry, descent, and landing. Prior to approximating a landing footprint with a Monte Carlo
analysis on the entry trajectory, the entry state uncertainties must be characterized. These
uncertainties arise from errors induced by the guidance system and thruster pointing
control during the deorbit maneuver. In order to capture the effect that these errors have on
the entry state uncertainty, the service module’s attitude determination and control system
(ADCS) and guidance system were both modeled in Matlab. By incorporating the ADCS
loop into the guidance loop, the effect of pointing errors during the deorbit trajectory
combined with errors in the guidance system can be assessed. A Monte Carlo analysis is
performed on this 3+3 DOF deorbit simulation (which terminates at entry interface),
resulting in an entry state covariance. The analysis is performed on the three orbits under
consideration for SPORE: ISS, LEO, and GTO. Finally, the resulting entry state covariance
from the deorbit simulation is used as input for an entry, descent, and landing trajectory
Monte Carlo analysis. Landing footprint, heating, and g-loading are considered for
trajectories targeting Woomera Test Range in Australia
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Date
2012-05-02
Extent
Resource Type
Text
Resource Subtype
Masters Project
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