Design of Electrified Propulsion Aircraft (2-Day Course) Manchester Grand Hyatt, San Diego, CA


In this course, participants learn about current developments in electrified propulsion, with an emphasis on hybrid electric aircraft. Participants will learn how to design electrified propulsion aircraft starting from the top-level aircraft requirements. Design examples will include electric and hybrid-electric aircraft of various sizes and missions. Various powertrains will be examined including pure electric, parallel hybrid, serial hybrid, and combinations with both combustion engines and fuel cells. It will be demonstrated which design variables are unique to electric and hybrid electric aircraft and how the sizing and performance process of the powertrain components can be executed. Historical and recent electric and hybrid electric aircraft system studies will be reviewed, and standard reporting parameters will be recommended.

Learning Objectives

  • Identify types of electric and hybrid aircraft configurations
  • Gain an up-to-date understanding of the latest developments in the field of (hybrid-) electric aircraft propulsion including fuel cell electric powertrains
  • Perform the preliminary sizing process of an electric or hybrid electric aircraft based on top-level aircraft requirements
  • Perform off-design mission performance analysis of sized hybrid electric aircraft, with appropriate considerations of reserve requirements and battery life and safety margins
  • Understand electrified propulsion drivetrain component fundamental design and performance parameters
  • Develop drivetrain system models and predict system weight and performance
  • Perform trade studies on the powertrain design variables to achieve a predefined design goal
  • Include aero-propulsive interaction effects into the preliminary sizing process by using results from experimental or numerical simulations
  • Review the results of existing electric and hybrid electric aircraft system studies and learn standard reporting parameters
  • [See full outline below]

Who Should Attend: This course intended for engineers with a background in aerospace engineering that are interested in learning about the unique design considerations for electric and hybrid electric aircraft.

Course Fees

AIAA Member Price(Early): $599 USD
AIAA Member Price(Standard): $699 USD
Non-Member Price: $799 USD 

AIAA CEUs are available for this course.


Please contact Lisa Le if you have questions about the course or group discounts (for 5+ participants).

Safety Protocols:
In-person Course and Workshop attendees will be required to present proof of full vaccination or a negative COVID-19 test. A third-party vendor will be used to collect all vaccination and testing information. Booster shots will not be necessary. Information will follow your registration with instructions on how to submit these documents closer to the event.


Course Outline

    1. Introduction (Bradley)

  • Summary of recent aircraft projects, Thin Haul, Commuter, Regional, and Airliners, On Demand Mobility & Air Taxi
  • Propulsion Integration Considerations
    • Taxonomy of propulsion and power architectures including hybrid architectures with turbines and fuel cells
    • Propulsion efficiency chains & examples
    • Aero-propulsive interaction, Distributed Propulsion, Wing Interactions
  • Electric Aircraft Conceptual Sizing
    • Range equation customized for electric aircraft
    • Range and weight sensitivities to battery technologies
    • Future battery chemistries and performance potentials
    • Simplified battery modeling including state of charge, depth of discharge, battery life, degradation, power C-rate, and reserves

    2. Hybrid Electric Aircraft Design Process (de Vries)

  • Aircraft design process: from conceptual to detailed design
  • Overview of different conceptual design approaches for hybrid-electric aircraft
  • Design requirements including airworthiness regulations
  • Flight-performance equations including aero-propulsive interaction
  • Constructing the performance constraints diagram
  • Simplified hybrid-electric powertrain modelling
  • Component sizing conditions: one-engine inoperative condition
  • Sizing for total energy requirements
  • Demonstration of sizing process with step-by-step example: sizing of an aircraft with leading-edge distributed propulsion
  • How to expand the sizing process towards alternative energy sources (e.g. hydrogen, fuel cells) and propulsor layouts (e.g. over-the-wing, tip-mounted, boundary-layer ingestion)


    3. Propulsion Components and Modeling (Lents)

  • Review of the electric and hybrid electric drivetrain and components
  • Simple reduced order modeling
  • Component characterization (sizing and performance)
    • Prime movers - gas turbines and other IC machines
    • Prime movers – batteries and fuel cells
    • Electric drivetrain components – generators, rectifiers, inverters, power distribution, motors
    • Mechanical conversion – shafts and gearboxes
    • Propulsors – ducted fans and propellers
  • Thermal management system design and performance
    • Heat acquisition – component cooling technologies and approaches; heat pumping systems
    • Heat transport – pumps, fans, ducts and pipes
    • Heat rejection - heat exchangers, phase change materials, skin coolers
  • Full system model examples and exercises


    4. Performance Assessment of Hybrid Electric Aircraft (Gladin)

  • Assessment Process: Introduction and steps in the process
  • Baselining: Projecting the baseline forward, defining EIS and technology level (TRL considerations), defining propulsion technologies
  • Defining the EP concept: EP architecture conceptualization, morphological matrices, Modes of benefit and basic trades, defining a CONOPS – Examples, Pre-Design filtering and selection
  • Power system modeling and representation: Schematics, Powertrain modeling approaches, Available tools, Standard performance parameters and definitions, units, nomenclature, etc.
  • Vehicle modeling and representation: Energy storage modeling, Mission(s): Flight segments, Power management, Propulsion-Airframe Integration
  • Calculating metrics: Energy specific air range, Fuel burn, Energy, ICAO CO2, Life-cycle CO2, TOFL, energy, DOC, NOx, etc.
  • AIAA Standard reporting parameters for presentation of results;
  • Example Assessment Results


    5. Hybrid Electric Mission Performance Study Examples & Wrap Up (Bradley)

  • Summary of selected historical and recent system studies
  • Current challenges and future research and technology needs

Course notes will be made available a few days prior to the course event. You will receive an email with detailed instructions on how to access your course notes. Since course notes will not be distributed on site, AIAA and your course instructor highly recommend that you bring your computer with the course notes already downloaded to the course. 



Dr. Marty Bradley is an AIAA Fellow and a Technical Fellow for The Boeing Company, working in the Boeing Commercial Airplanes Advanced Concepts Group in Long Beach, California. He is the technology leader for a variety of projects related to electric and hybrid electric aircraft. Marty has 34-years of experience in vehicle design, propulsion integration, and technology studies for a wide variety of commercial and military aerospace applications. Marty was the Principal Investigator for the NASA funded SUGAR study looking at advanced technologies for future commercial aircraft, including the hybrid electric SUGAR Volt, and contributed to the National Academies report on Low Carbon Aviation. He is the Leader of the AIAA Aircraft Electric Propulsion and Power Working Group. He previously was Chair of the AIAA Green Engineering Program Committee and the High-Speed Airbreathing Propulsion Technical Committee. Marty has a B.S., M.S., and Ph.D. in Aerospace Engineering, all from the University of Southern California and teaches their aircraft design capstone course.


Mr. Reynard de Vries is a PhD researcher at the Faculty of Aerospace Engineering of Delft University of Technology. His research activities are part of the European Commission’s Clean Sky 2 research framework for Large Passenger Aircraft (LPA), and focus on conceptual design methods for hybrid-electric aircraft and experimental investigations of propeller-wing interaction for distributed-propulsion systems. Reynard obtained a BSc degree in Aerospace Engineering at the Technical University of Madrid in 2014, sponsored by a Scholarship for Academic Excellence. He subsequently pursued an MSc degree in Aerospace Engineering at Delft University of Technology, which he obtained cum laude in 2016. Since 2016 he has been actively involved in over a dozen wind-tunnel tests of various (distributed-) propeller configurations and has taught several lectures on hybrid/electric aircraft design. Reynard won two best-presentation awards at the AIAA/IEEE Electric Aircraft Technologies Symposium in 2018 and has (co-) authored numerous papers in the fields of hybrid-electric aircraft design and propeller-airframe interaction in novel propulsion systems.


Mr. Charles Lents, Associate Director at the United Technologies Research Center, has thirty years of experience in the conceptual design of integrated aircraft primary and secondary power and thermal management systems.  At UTRC, Chuck led a team in the development of an integrated modeling environment for the study of integrated total aircraft power systems and their impact on air vehicle performance.  He has led several studies investigating power and thermal management solutions for a range of commercial and military vehicles, and is the project lead for UTRC’s Innovative Propulsion project, studying and developing high altitude and alternative small engine propulsion systems. . He currently leads UTRCs NASA funded Parallel Hybrid Propulsion System Technology Development program. He has experience in a diverse set of technical areas, including thermodynamics, fluid dynamics, turbo-machinery, heat transfer, power electronics cooling, systems integration and aircraft secondary power systems, reliability, risk/uncertainty analysis and life-cycle cost modeling. Chuck received his B.S.M.E from the University of Illinois in 1982 and his M.S.M.E. from Purdue University in 1984.


Dr. Jonathan Gladin is a research engineer at the Aerospace Systems Design Lab at Georgia Tech where he performs research in the area of propulsion for aircraft applications, specifically for hybrid electric propulsion systems and also in the areas of propulsion/airframe integration.  He has contributed to four different NASA sponsored NRA’s in the area of hybrid electric propulsion and has many technical publications in that area.  He is the lead developer of Georgia Tech’s hybrid electric modeling environment, GT-HEAT, and is actively involved in teaching students the fundamentals of hybrid electric aircraft for research applications.  He also has technical experience in the areas of boundary layer ingestion systems, aircraft sub-systems, and thermal management. He received his undergraduate degree in Aerospace Engineering from the Georgia Institute of Technology in 2006 and worked as a structural analyst for Sikorsky Helicopters for three years on the Black Hawk program before returning to Georgia Tech to pursue his graduate studies in 2009. He received his Master’s degree in Aerospace Engineering in 2011 and Ph.D. in 2015. 



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