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NASA Langley Distributed Propulsion VTOL Tilt-Wing Aircraft Testing, Modeling, Simulation, Control, and Flight Test DevelopmentControl of complex Vertical Take-Off and Landing (VTOL) aircraft traversing from hovering to wing born flight mode and back poses notoriously difficult modeling, simulation, control, and flight-testing challenges. This paper provides an overview of the techniques and advances required to develop the GL-10 tilt-wing, tilt-tail, long endurance, VTOL aircraft control system. The GL-10 prototype's unusual and complex configuration requires application of state-of-the-art techniques and some significant advances in wind tunnel infrastructure automation, efficient Design Of Experiments (DOE) tunnel test techniques, modeling, multi-body equations of motion, multi-body actuator models, simulation, control algorithm design, and flight test avionics, testing, and analysis. The following compendium surveys key disciplines required to develop an effective control system for this challenging vehicle in this on-going effort.
Document ID
20140011413
Document Type
Conference Paper
Authors
Rothhaar, Paul M. (NASA Langley Research Center Hampton, VA, United States)
Murphy, Patrick C. (NASA Langley Research Center Hampton, VA, United States)
Bacon, Barton J. (NASA Langley Research Center Hampton, VA, United States)
Gregory, Irene M. (NASA Langley Research Center Hampton, VA, United States)
Grauer, Jared A. (NASA Langley Research Center Hampton, VA, United States)
Busan, Ronald C. (NASA Langley Research Center Hampton, VA, United States)
Croom, Mark A. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 8, 2014
Publication Date
June 16, 2014
Subject Category
Aircraft Stability and Control
Report/Patent Number
NF1676L-17842
AIAA Paper 2014-2999
Meeting Information
AIAA Aviation Technology, Integration and Operations (ATIO) Conference(Atlanta, GA)
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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