NDLI: Novel matrix resins for composites for aircraft primary structures, phase 1

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Novel matrix resins for composites for aircraft primary structures, phase 1

Content Provider	NASA Technical Reports Server (NTRS)
Author	Woo, Edmund P. Godschalx, J. P. Bruza, K. J. Maynard, S. Mullins, M. J. Bishop, M. T. Puckett, P. M.
Copyright Year	1992
Description	The objective of the contract is the development of matrix resins with improved processability and properties for composites for primarily aircraft structures. To this end, several resins/systems were identified for subsonic and supersonic applications. For subsonic aircraft, a series of epoxy resins suitable for RTM and powder prepreg was shown to give composites with about 40 ksi compressive strength after impact (CAI) and 200 F/wet mechanical performance. For supersonic applications, a thermoplastic toughened cyanate prepreg system has demonstrated excellent resistance to heat aging at 360 F for 4000 hours, 40 ksi CAI and useful mechanical properties at greater than or equal to 310 F. An AB-BCB-maleimide resin was identified as a leading candidate for the HSCT. Composite panels fabricated by RTM show CAI of approximately 50 ksi, 350 F/wet performance and excellent retention of mechanical properties after aging at 400 F for 4000 hours.
File Size	7932569
Page Count	166
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19950003906
Archival Resource Key	ark:/13960/t76t5kk69
Language	English
Publisher Date	1992-08-01
Access Restriction	Open
Subject Keyword	Nonmetallic Materials Panels Heat Treatment Cyanates Aircraft Construction Materials Compressive Strength Powder Particles Prepregs Epoxy Resins Aging Materials Composite Structures Thermoplasticity Aircraft Structures Matrix Materials Resin Matrix Composites Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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