AIRCRAFT MISSION AND SYSTEM FAILURE CONSIDERATIONS FOR FUNCTIONAL INDUCTION BASED CONCEPTUAL ARCHITECTURE DESIGN

With current advances in system-level technologies, changes in system level aircraft requirements, and outsourcing of technology development, architecture innovation and integration have become driving differentiators between competing aircraft concepts. Revolutionary conceptual vehicle systems architectures promise additional benefits over incremental improvements achieved through technology insertion and system adaptation or evolution. However, exploration of the complex vehicle systems architecture design space introduces unique challenges in the definition and allocation of sizing critical unit and platform level requirements. Sizing critical performance requirements are infrequently derived from normal operating conditions but rather emerge from responses to system failures. This paper explores means for the identification and allocation of architecture specific offnominal operating mode requirements through the extension of traditional hazard assessment tools, performance degradation optimization, and the propagation of function/criticality requirements through structured functional dependencies.