Task title: assessment of the state of the art of progressive damage analysis 1.0 introduction/background: the NASA advanced composites project (ACP) seeks to develop and transition technology that…

Task title: assessment of the state of the art of progressive damage analysis 1.0 introduction/background: the NASA advanced composites project (ACP) seeks to develop and transition technology that will enable reduction in the timeline required for development and certification of new aircraft structures that utilize advanced composite materials. High fidelity analysis methods that can reliably predict the onset of damage and damage progression in composite materials can contribute to this goal by replacing some of the testing requirements in the building block approach used for the design and certification of primary aircraft structure. Additionally, these analysis methods offer the potential for the development of more efficient structural concepts by enabling the exploration of the large design space of laminated composites, which is not possible with the current largely empirical approach for structural design and substantiation. With this goal in mind, NASA is seeking to develop, or mature, new or improved, physically accurate, verified and validated, high fidelity progressive damage analysis (PDA) tools for quasi-static, dynamic and fatigue loading conditions. These high fidelity tools need to be computationally rigorous, applicable to structural level simulations, and capture not only the global response of the component modeled, but also capture the correct failure modes and interactions, location, and progression of damage and the ultimate effect of damage progression on the component strength and life. The NASA ACP is focusing on three case studies for development and validation of analysis tools: (1) static case study: predictive capability for residual damage tolerance of low-velocity-impact damaged stringer-reinforced, post-buckled, thin-skin composite structure; (2) fatigue case study: predictive capability for fatigue life of dynamic rotor components and highly loaded bolted joints; and (3) dynamic case study: predictive capability for containment of engine fan blades subjected to high energy impacts. Case studies (1) and (2) will use a graphite epoxy pre-impregnated tape material architecture and case study (3) will use a dry woven resin-infused material architecture or and a graphite epoxy pre-impregnated tape material. 2.0 scope & objectives: 2.1 the scope of this task order is to assess the state of the art (SOA) in progressive damage analysis methodologies and tools for the case studies stated above. Of particular interest to NASA are the developments required to advance the down-selected methodologies and tools to a maturity level suitable for integration into an aircraft certification process. 2.2 the objectives of this task order are to: identify the most promising PDA methodologies and tools for predicting damage formation, growth, accumulation and the effect on strength and life for practical application. Identify the maturity of these methodologies and tools relative to their potential to be considered for use in a new product certification effort by 2019 and to have achieved a maturity level required for aircraft certification by 2024. Recommend the subset of methodologies and tools most promising for further investment by the NASA ACP. 3.0 description of the work/tasks to be performed: 3.1 PDA methodology and tool assessment the contractor shall perform an assessment that shall: - include a summary of candidate prediction methodologies relevant to each case study, and recommendations on the most promising methodologies to be potentially carried forward by the ACP for thorough quantitative evaluation and for future development. - address the theoretical foundations of the methodology, as well as the potential for practical application at the structural level, and shall include sufficient data on candidate codes to enable selection of analysis codes for future evaluat