Title:
Small Probe Flight Testing of Thermal Protection Systems in Simulated Earth Entries
Small Probe Flight Testing of Thermal Protection Systems in Simulated Earth Entries
Author(s)
Sidor, Adam T.
Anderson, Tyler R.
Braun, Robert D.
Anderson, Tyler R.
Braun, Robert D.
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Abstract
Flight testing of thermal protection system materials, once common during the early
era of spaceflight, is used infrequently in modern materials development. Testing and qualification of these materials primarily occurs in ground-based facilities which can produce
a limited range of discrete test conditions. A small probe platform to test thermal protection system materials in flight can produce environmental conditions that more closely
approximate the transient nature of actual entry. A methodology for designing such a test
is presented. Test vehicles are designed to be recoverable and are based on the highly
stable 45 degree sphere-cone geometry of Mars Microprobe. The current investigation
determines the feasibility of simulating low and high energy Earth entries with such a test
vehicle launched suborbitally aboard a Black Brant X rocket. Vehicle parameters (mass
and maximum diameter) as well as launch and flight trajectories are varied to achieve a
range of heat rates and stagnation pressures. An envelope of achievable environmental
conditions is generated and compared to those of the reference trajectories. The current
design is able to generate peak heat rates on the order of 102 W/cm2 and peak stagnation
pressures of 101 - 102 kPa. Average ow enthalpies of around 4 MJ/kg to 16 MJ/kg can
be sustained for anywhere from 10 seconds to 2 minutes.
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Date Issued
2016-01
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Text
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Paper
Rights Statement
Unless otherwise noted, all materials are protected under U.S. Copyright Law and all rights are reserved