Cure Evaluation of Two Critical Composite Hybrid Flat Panels for use in a High-Dimensional Stability Satellite Application
Abstract
Two large composite panels critical to a composite structure were recently fabricated. The panels consist of a complex hybrid of different fibers along with an ultra-low-moisture absorption siloxane-modified polycyanurate resin. After fabrication, the contractor noticed that the panels exhibited signs of partial cure by performing an acetone solvent wipe test. We were asked by the program office to assist the contractor in determining the extent of the contamination and whether the parts could be salvaged. Numerous composite tag samples were machined from the periphery of the part as well as moving inward from the edges. Dynamic mechanical analysis was performed on all samples to determine the extent of contamination. Our data suggested that severe carbamate formation had occurred in one of the panels. The suspected areas of the panel appeared compromised, as evidenced by a multimode loss modulus curve indicating several depressed glass-transition temperatures for the first panel. The second panel exhibited only minimal degradation. The contamination was primarily observed in the outer inch of the panel. The majority of the panel appeared well consolidated and cured. Machining the outer portions of the part salvaged the second panel. The other panel was too greatly compromised.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 20, 2003
- Accession Number
- ADA418488
Entities
People
- R. Casteneda
- R. J. Zaldivar
Organizations
- The Aerospace Corporation