Performance Characterization of Supersonic Retropropulsion for Application to High-Mass Mars Entry, Descent, and Landing
Loading...
Author(s)
Korzun, Ashley M.
Braun, Robert D.
Advisor(s)
Editor(s)
Collections
Supplementary to:
Permanent Link
Abstract
Prior high-mass Mars EDL systems studies have neglected aerodynamic-propulsive
interactions and performance impacts during the supersonic phase of descent. The goal of
this investigation is to accurately evaluate the performance of supersonic retropropulsion
with increasing vehicle ballistic coefficient across a range of initiation conditions relevant for
future high-mass Mars landed systems. Past experimental work has established supersonic
retropropulsion trends in static aerodynamics as a function of retropropulsion
configuration, freestream conditions, and thrust. From this experimental database, an
aerodynamic-propulsive interactions model is created. EDL system performance results are
developed with the potential aerodynamic drag preservation included and excluded during
this phase of flight for comparison against prior studies. The results of this investigation
demonstrate the significance of aerodynamic drag preservation as a function of
retropropulsion initiation conditions, characterize mass optimal trajectories utilizing
supersonic retropropulsion, and compare propulsion system requirements with existing
propulsion systems and systems under development for future exploration missions.
Sponsor
Date
2009-08
Extent
Resource Type
Text
Resource Subtype
Paper
Rights Statement
Unless otherwise noted, all materials are protected under U.S. Copyright Law and all rights are reserved