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Meeting	ACGS Committee Meeting 106 - La Jolla - October 2010
Agenda Location	9 SUBCOMMITTEE B – MISSILES AND SPACE 9.1 Draper Space System Integrated Design Tool
Title	Draper Space System Integrated Design Tool
Presenter	John West
Affiliation	Draper Laboratory
Available Downloads*	presentation
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Abstract	Integrated Modeling for Analysis and Design of Robust, Fault-Tolerant Systems By Nick Borer, nborer@draper.com System reliability is a metric that is necessarily quantified after the system design has been established – the failure rates are dependent on component operation and selection, and the failure effects of an individual component need to be propagated through the entire system to capture any cascading effects. However, the design freedom available to build a high-reliability system is greatest prior to definition of the system architecture. Draper Laboratory has introduced behavioral-Markov modeling over three decades of research as an early integrated modeling approach to identify system loss drivers when this design freedom is greatest. This latest approach, using an in-house tool dubbed PARADyM (Performance and Reliability Analysis via Dynamic Modeling), has been applied to a variety of space and terrestrial systems since its introduction in late 2006. Selected space systems includes the Commercial Orbital Transportation System (COTS) avionics architecture for two customers, the avionics architecture of NASA’s Ares I rocket, an independent estimate of the Orion avionics fault-tolerance, and the avionics architecture of the proposed NASA Lunar Surface Systems (LSS) habitat and pressurized rover. The results from the LSS analysis will be presented in this talk (the full results are available in a 2010 paper presented at the IEEE Aerospace Conference). In addition, this presentation will introduce multi-state system design, the latest logical outgrowth of behavioral-Markov modeling. Multi-state system design is an approach that not only identifies the system loss drivers, but also finds those design parameters that impact the overall design’s robustness to off-nominal events. Its utility is demonstrated on a simple aircraft example, and the full results are available in a conference paper (at the 2010 AIAA MDO Specialist’s Conference) and submitted for publication as a journal article. References for these articles are available upon request.