A Damage Resistance Comparison Between Candidate Polymer Matrix Composite Feedline Materials

NASA/TM-210482, Nettles, A.T., A Damage Resistance Comparison Between Candidate Polymer Matrix Composite Feedline Materials, George C. Marshall Space Flight Center Marshall Space Flight Center, Alabama 35812, National Aeronautics and Space Administration Washington, DC 20546-0001, Prepared by the Materials, Manufacturing and Processes Department, Engineering Directorate, September 2000, pp. 32, Format(s): PDF 19105k

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As part of NASA's focused technology programs for future reusable launch vehicles, a task is underway to study the feasibility of using the polymer matrix composite feedlines instead of metal ones on propulsion systems. This is desirable to reduce weight and manufacturing costs. The task consists of comparing several prototype composite feedlines made by various methods. These methods are electron-beam curing, standard hand lay-up and autoclave cure, solvent assisted resin transfer molding, and thermoplastic tape laying. One of the critical technology drivers for composite components is resistance to foreign objects damage. This paper presents results of an experimental study of the damage resistance of the candidate materials that the prototype feedlines are manufactured from. The materials examined all have a 5-harness weave of IM7 as the fiber constituent (except for the thermoplastic, which is unidirectional tape laid up in a bi-directional configuration). The resin tested were 977-6, PR 520, SE-SA-1, RS-E3 (e-beam curable), Cycom 823 and PEEK. The results showed that the 977-6 and PEEK were the most damage resistant in all tested cases

Keywords:	composite materials, impacts, microcracking
Subjects:	Chemistry and Materials: Composite Materials: Composite Materials
ID Code:	538
Deposited On:	25 July 2002