TY - GEN
T1 - Electrothermal icing protection of aerosurfaces using conductive polymer nanocomposites
AU - Buschhorn, Samuel T.
AU - Lachman, Noa
AU - Gavin, Jennifer
AU - Wardle, Brian L.
AU - Kessler, Seth S.
AU - Thomas, Greg
N1 - Funding Information:
The authors would like to acknowledge financial support from NAVAIR SBIR contract N68335-11-C-0424, J. Gavin acknowledges support from the CMSE Research Experience for Undergraduates Program, as part of the MRSEC Program of the National Science Foundation under grant number DMR-0819762. Materials developed for use in this work were supported by Boeing, EADS, Embraer, Lockheed Martin, Saab AB, Composite Systems Technology, Hexcel, and TohoTenax through MIT’s Nano-Engineered Composite aerospace STructures (NECST) Consortium. The authors would like to thank Richard Li (MIT), Itai Y. Stein (MIT), and John Kane (MIT) and the entire necstlab at MIT for technical support and advice. This work made use of the core facilities at the Institute for Soldier Nanotechnologies at MIT, supported by the U.S. Army Research Office under contract W911NF-07-D-0004, the Undergraduate Teaching Laboratory in the Department of Materials Science and Engineering at MIT, and the Shared Experimental Facilities supported in part by the MRSEC Program of the National Science Foundation under award number DMR-0819762.
PY - 2013
Y1 - 2013
N2 - Ice protection systems (IPS) are critical components for many aerospace flight vehicles, including commercial transports and unmanned aerial systems (UAS), and can include anti-icing, de-icing, ice sensing, etc. Here, an IPS is created using nanomaterials to create a surface-modified external layer on an aerosurface based on observations that polymer nanocomposites have tailorable and attractive heating properties. The IPS uses Joule heating of aligned carbon nanotube (CNT) arrays to create highly efficient de-icing and anti-icing of aerosurfaces. An ice wind tunnel test of a CNT enhanced aerosurface is performed to demonstrate the system under a range of operating regimes (temperature, wind speed, water content in air) including operation down to -20.6°C (-5°F) at 55.9 m/s (125 mph) under heavy icing. Manufacturing, design considerations, and further improvements to the materials and systems are discussed.
AB - Ice protection systems (IPS) are critical components for many aerospace flight vehicles, including commercial transports and unmanned aerial systems (UAS), and can include anti-icing, de-icing, ice sensing, etc. Here, an IPS is created using nanomaterials to create a surface-modified external layer on an aerosurface based on observations that polymer nanocomposites have tailorable and attractive heating properties. The IPS uses Joule heating of aligned carbon nanotube (CNT) arrays to create highly efficient de-icing and anti-icing of aerosurfaces. An ice wind tunnel test of a CNT enhanced aerosurface is performed to demonstrate the system under a range of operating regimes (temperature, wind speed, water content in air) including operation down to -20.6°C (-5°F) at 55.9 m/s (125 mph) under heavy icing. Manufacturing, design considerations, and further improvements to the materials and systems are discussed.
UR - http://www.scopus.com/inward/record.url?scp=84880791526&partnerID=8YFLogxK
U2 - 10.2514/6.2013-1729
DO - 10.2514/6.2013-1729
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AN - SCOPUS:84880791526
SN - 9781624102233
T3 - 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
BT - 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
T2 - 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
Y2 - 8 April 2013 through 11 April 2013
ER -