ABSTRACT

Metal Matrix Composites (MMCs) are potential high temperature materials for high performance propulsion and airframe systems. National Aero Space Plane (NASP) and IHPTET programs have helped develop a wealth of data in the understanding, characterization and life prediction of MMCs. This investigation provides simple approaches to predict the response characteristics of quasi-isotropic SCS-6/Ti-15-3 composites with 33% fiber volume fraction. Both micro and macro mechanics models are used to predict the ply properties and laminate properties. Bearing strength predictions are made by using BBJ[1], BJSFM[2] and ASCA[3]. The input data for these computations is given in reference [4]. In micro-mechanics computations the difference between the rule of mixture (ROM) and n-directional stress and strength (NDSANDS) models on effective laminate properties is within the experimental properties scatter. This research work is a part of the in-house effort of AFRL/VASM, and specific plans for conducting the tests for validation of predictions are in place. A boundary value problem representing a single lap bolted joint is solved using BBJ[1]. Pin loaded hole laminate specimens were tested with geometric parameters shown in Figure 4. A preliminary testing of a set of specimens shows a good agreement between experimental and predicted results. Both the load of failure and the mode of failure are accurately predicted.