This paper aims to create a terminal area operations (TAO) analysis software that can accurately appreciate the nuances of hybrid electric distributed propulsion (HEDP), including unique failure modes and powered-lift effects.
The program was written in Visual Basic with a user interface in Microsoft Excel. It integrates newly defined force components over time using a fourth order Runge-Kutta scheme.
Powered-lift, HEDP failure modes and electrical component thermal limitations play significant roles on the performance of aircraft during TAO. Thoughtful design may yield better efficiency; however, care must be given to address negative implications. Reliability and performance can be improved during component failure scenarios.
This program has and will support the investigation of novel propulsion system architectures and aero-propulsive relationships through accurate TAO performance prediction.
Powered-lift and HEDP architectures can be employed to improve takeoff and climb performance, both during nominal and component failure scenarios, however, reliance on powered-lift may result in faster approach speeds. High-lift and system failure behavior may also allow new approaches to design and sizing requirements.
This program is unique in both the public and private sectors in its broad capabilities for TAO analysis of aircraft with HEDP systems and powered-lift.
This paper offers a condensed version of the contents of the conference paper presented by the authors at Aviation 2013 American Institute of Aeronautics and Astronautics (AIAA-2013-4265) for inclusion in the AEAT Journal’s special issue on hybrid-energy and distributed propulsion topics. The work summarized here was completed in August of 2013. This work is sponsored by Mr Craig Hange at the NASA Ames Research Center Subsonic Fixed Wing (SSFW) and Mr Cale Zeune at the Air Force Research Laboratory.
Schiltgen, B., Green, M., Freeman, J. and Gibson, A. (2014), "Terminal area operations for hybrid electric distributed propulsion", Aircraft Engineering and Aerospace Technology, Vol. 86 No. 6, pp. 584-590. https://doi.org/10.1108/AEAT-04-2014-0047Download as .RIS
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