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Benefits of Hybrid-Electric Propulsion to Achieve 4x Increase in Cruise Efficiency for a VTOL AircraftElectric propulsion enables radical new vehicle concepts, particularly for Vertical Takeoff and Landing (VTOL) aircraft because of their significant mismatch between takeoff and cruise power conditions. However, electric propulsion does not merely provide the ability to normalize the power required across the phases of flight, in the way that automobiles also use hybrid electric technologies. The ability to distribute the thrust across the airframe, without mechanical complexity and with a scale-free propulsion system, is a new degree of freedom for aircraft designers. Electric propulsion is scale-free in terms of being able to achieve highly similar levels of motor power to weight and efficiency across a dramatic scaling range. Applying these combined principles of electric propulsion across a VTOL aircraft permits an improvement in aerodynamic efficiency that is approximately four times the state of the art of conventional helicopter configurations. Helicopters typically achieve a lift to drag ratio (L/D) of between 4 and 5, while the VTOL aircraft designed and developed in this research were designed to achieve an L/D of approximately 20. Fundamentally, the ability to eliminate the problem of advancing and retreating rotor blades is shown, without resorting to unacceptable prior solutions such as tail-sitters. This combination of concept and technology also enables a four times increase in range and endurance while maintaining the full VTOL and hover capability provided by a helicopter. Also important is the ability to achieve low disc-loading for low ground impingement velocities, low noise and hover power minimization (thus reducing energy consumption in VTOL phases). This combination of low noise and electric propulsion (i.e. zero emissions) will produce a much more community-friendly class of vehicles. This research provides a review of the concept brainstorming, configuration aerodynamic and mission analysis, as well as subscale prototype construction and flight testing that verifies transition flight control. A final down-selected vehicle is also presented.
Document ID
20140001088
Document Type
Conference Paper
Authors
Fredericks, William J.
(NASA Langley Research Center Hampton, VA, United States)
Moore, Mark D.
(NASA Langley Research Center Hampton, VA, United States)
Busan, Ronald C.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
March 7, 2014
Publication Date
August 12, 2013
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NF1676L-16092
AIAA Paper 2012-4324
Meeting Information
AIAA Aviation Technology, Integration, and Operations (ATIO) Conference(Los Angeles, CA)
Funding Number(s)
WBS: WBS 031102.02.07.05.9937.13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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