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Meeting	ACGS Committee Meeting 114 - Cleveland, Ohio - October 2014
Agenda Location	4 GENERAL COMMITTEE TECHNICAL SESSION 4.1 Research Institutions, Industry, and University Summary Reports 4.1.3 Research Institutions and Companies 4.1.3.1 Systems Technology, Inc.
Title	Systems Technology, Inc.
Presenter	Dave Klyde
Available Downloads*	presentation
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Abstract	SAFE-Cue Warning Display A study conducted by The Boeing Company of world-wide commercial jet transport accidents found the most common events to be loss of control associated with an inability of pilots to recover from upsets and unusual attitudes. A key component in some of these events is pilot spatial disorientation (SD). Improved pilot training in these abnormal flight conditions, including the ability of training simulators to replicate spatial disorientation, is needed to reduce loss of control accidents. Traditional commercial pilot training is conducted with hexapod-based motion systems that are limited in their ability to replicate the motion cues associated with these events. Given these short-comings, how can air carriers and other stakeholders be certain that there is positive transfer of training regarding spatial disorientation from the simulator to flight? To address this question, Systems Technology, Inc. (STI) is developing SD training scenarios designed for Level D flight simulators and the Spatial Disorientation – Transfer of Training Assessment Library (SD-TOTAL) software application that will provide tools to quantify the ability of flight simulators to create SD for pilot training. Performance Adaptive Wing The following abstract was extracted from the NASA NRA proposal submitted by a team led by the University of Minnesota with Systems Technology, Inc., Virginia Tech, CMSoft, Schmidt and Associates, and Aurora Flight Sciences. This program will mature integrated multidisciplinary tools, techniques, technology, and processes to cultivate an innovative “research through development” approach to create a performance adaptive aeroelastic wing. This philosophy exploits valuable knowledge gained from prototype flight experiments to validate and drive advances in modeling, controls, optimization, effector/sensor selection and designprocesses. The wing structure, which will leverage Multi-Disciplinary Analysis and Optimization and curvilinear SpaRibs, will be designed with minimal weight to handle static loading. The design will optimally include many distributed control effectors and a large distributed sensor network enabling innovative control solutions for flutter suppression and alleviation of gust and turbulence loading, further decreasing the structural weight. Outer-loop control laws will optimally alter the wing shape and load distribution at varying conditions across the flight envelope adaptively minimizing drag and providing high lift for takeoff and landing. This research will accomplish NASA N+3 goals and will build upon work at Ames Research Center (ARC) in elastically shaped air vehicles and Armstrong Flight Research Center (AFRC) in the modeling of flexible vehicles, active flutter suppression, and optimal control algorithms. Interaction with ARC and AFRC is planned including flight testing on the X-56A over the course of a potential five year program.