Accession Number:

ADA540143

Title:

Sizing Analysis for Aircraft Utilizing Hybrid-Electric Propulsion Systems

Descriptive Note:

Master's thesis Sep 2009-Mar 2011

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT

Personal Author(s):

Report Date:

2011-03-18

Pagination or Media Count:

148.0

Abstract:

Current conceptual aircraft design methods use historical data to predict and evaluate the size and weight of new aircraft. These traditional design methods have been ineffective to accurately predict the weight or physical dimensions of aircraft utilizing unique propulsion systems. The mild hybrid-electric propulsion system represents a unique design that has potential to improve fuel efficiency and reduce harmful emissions. Hybrid-electric systems take advantage of both reliable electric power and the long rangeendurance capabilities of internal combustion engines. Desirable applications include general aviation single-engine aircraft and remotely-piloted aircraft. To demonstrate the advantages of mild hybrid-electric propulsion, a conceptual design code was created that modified conventional methods. Using several case studies, the mild hybrid conceptual design tool verified potential fuel savings for general aviation aircraft and expanded mission capability for remotely-piloted aircraft.

Subject Categories:

  • Combustion and Ignition
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE