TY - GEN
T1 - Defining the critical depth of impact damage for thermal protection systems
AU - Skolnik, Nathaniel L.
AU - Putnam, Zachary R.
N1 - Funding Information:
This work was supported by a NASA Space Technology Research Fellowship. The authors would like to thank MaireadStackpoole,MiladMahzari, andoJsh MonkoftheNASA AmesResearchCenter.
Publisher Copyright:
© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - Thermal protection systems for hypersonic vehicles are low- to zero-fault-tolerant. A self-healing capability for thermal protection systems is proposed to mitigate impact damage from micrometeoroids and orbital debris. An integrated self-healing system should be positioned within the thermal protection system at the critical depth, the minimum depth at which impact damage will cause mission failure. A method of calculating the critical depth is presented over mission and vehicle parameters of interest. The maximum allowable size and speed of impacting particles is determined as a function of critical depth. Results indicate that the critical depth is a strong function of the entry environment as well as the damage shape; changes in crater depth and width significantly affect bondline temperature.
AB - Thermal protection systems for hypersonic vehicles are low- to zero-fault-tolerant. A self-healing capability for thermal protection systems is proposed to mitigate impact damage from micrometeoroids and orbital debris. An integrated self-healing system should be positioned within the thermal protection system at the critical depth, the minimum depth at which impact damage will cause mission failure. A method of calculating the critical depth is presented over mission and vehicle parameters of interest. The maximum allowable size and speed of impacting particles is determined as a function of critical depth. Results indicate that the critical depth is a strong function of the entry environment as well as the damage shape; changes in crater depth and width significantly affect bondline temperature.
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U2 - 10.2514/6.2018-1481
DO - 10.2514/6.2018-1481
M3 - Conference contribution
AN - SCOPUS:85141563364
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -