9–11 July 2018
Duke Energy Convention Center, Cincinnati, Ohio

Liquid Rocket Engines: Fundamentals, Green Propellants, and Emerging Technologies

[NOTE as of 30 June: The Liquid Rocket Engines: Fundamentals, Green Propellants, and Emerging Technologies course is SOLD OUT. If you would like to be contacted if space in the course becomes available, please contact Megan Scheidt.] 

8-9 July 2017 0800-1700 hrs


Liquid propulsion systems are critical to launch vehicle and spacecraft performance, and mission success. This two-day course, taught by a team of government, industry and international experts, will cover propulsion fundamentals and topics of interest in launch vehicle and spacecraft propulsion; propulsion system design and performance; green bipropellants and monopropellants and advances in additive manufacturing and their implications towards emerging liquid rocket engines.

Key Topics

  • Rocket Propulsion Fundamentals
  • Rocket Fuels and Oxidizers Definition and Characterization
  • Structural Considerations in Rocket Engine Design, including Additive Manufacturing
  • Rocket Engine Testing
  • Development, Characterization and Flight Experience with Green Propellants
  • Microsat, Nanosat and Cubesat Propulsion

Who Should Attend

This course is intended for students, engineers, and managers involved in liquid propulsion component and system design, development, testing, analysis, program management, contracts or certification for flight.

Course Outline

  • Rocket Propulsion Fundamentals
    • History of Propulsion/Overview of Components
    • Performance and Design Considerations
    • Rocket Classifications
    • Regeneratively cooled chambers
  • Rocket Fuels and Oxidizers Definition and Characterization
    • Definitions
    • Exposure and Handling Guidelines
    • Desirable Physical Properties
    • Survey of Potential Fuels and Additives
  • Structural Considerations in Rocket Engine Design
    • Failure Modes of Structures
    • Rocket Engine Design Drivers and Reliability
    • Material Characterization
    • Development and Qualification Testing
    • Additive Manufacturing in Liquid Rocket Engines
  • Rocket Engine Testing:
    • Test Facility Description
    • Testing Operational Aspects (Pre-Test/Test Day/Post-Test)
  • Green BiPropellants for LRE:
    • Why green?
    • Applications and System Design Considerations
    • Green propellant storage considerations
    • Common Green Options and Ionic Liquids
    • GRASP program and REACH regulation
    • Development and Flight Experience with Green Monopropellants
      • Rocket Grade Hydrogen Peroxide Properties and Experience
      • ADN in Liquid Monopropellants
      • High Performance Green Propulsion Monopropellant and Thrusters
      • HPGP System Design and Flight Experience Microsat, Nanosat and Cubesat Propulsion
      • Microsat, Nanosat and Cubesat Propulsion and Micropropulsion Testing


    Timothee Pourpoint is an Associate Professor in the School of Aeronautics and Astronautics at Purdue University. He is an expert in chemical propulsion and energy management. Specifically, his on-going research focuses on the understanding of storable propellant ignition and combustion through system level testing and advanced diagnostic techniques with an emphasis on novel propellant combinations. As part of his work, Dr. Pourpoint has been involved in designing, implementing, and operating several testing facilities at the Maurice Zucrow Laboratories at Purdue University. Dr. Pourpoint is an Associate Fellow of AIAA.

    Philipp Behurzi is Senior Expert in Fluid Mechanics in the department Vehicle Engineering at Airbus Safran Launchers in Bremen, Germany. He received his PhD at Aachen University, Germany, in 2000. He also received his Diploma in Aerospace Engineering at Aachen University. After his PhD, he signed up at Airbus Safran Launchers. Dr. Behruzi has 17 years of working experience concerning fluid mechanics in propellant tanks and is the focal point for the development and functional layout of cryogenic as well as non-cryogenic storage tanks. He worked on the functional layout of the next generation of restartable European cryogenic upper stages, especially for ballistic phase management. He has long experiences in developing Propellant Management Devices (PMDs) for satellites, transfer vehicles and upper stages. Examples are the Spacebus and Globalstar satellite tank families, ATV as well as all Ariane 5 upper stages (EPS, ESC-A, A5ME). Dr. Behruzi developed PMDs and Phase Separation Technologies for cryogenic upper stages based on his own patents. He participated to sounding rocket missions as Principal Engineer (Maser 11 & 12, TEXUS 48). Presently he is responsible for the functional layout of the Orion ESM propellant tanks. Dr. Behruzi is the focal point concerning collaborating activities with Universities and Institutes in his field.

    David Lineberry is a Research Engineer with the University of Alabama in Huntsville Propulsion Research Center. He is responsible for overseeing the daily operations of the PRC test facilities at the Johnson Research Center as well as PRC laboratory safety and leading funded propulsion related research efforts. While at the PRC, Dr. Lineberry led design and fabrication efforts for several test facilities including the PRC high pressure spray facility, test stand cryogenic propellant feed systems, a high flow rate Cryogenic component test rig, and a 2000 lbf hot-fire test stand. He has experience with cold flow experimentation, injector spray characterization, optical diagnostics, experimental uncertainty analysis, hot fire testing for solid, gaseous, gel, and liquid rocket engines, ultrasonic evaluation of solid propellants, and liquid rocket combustion instability.

    Joerg Riccius is the head of the Structures group inside the Rocket propulsion department of the DLR-institute of Space Propulsion in Lampoldshausen, Germany. His main subject is the development and (TMF panel test based) validation of structural analysis methods for components of high performance, high thrust liquid rocket engines such as hot gas walls (combustion chamber, nozzle), turbo pump components (impeller) and injector heads. Additionally to his structural activities, he contributed to a series of European projects like ATLLAS I and II, the Green Propellants project, GRASP, ISP1 and ORPHEE.

    Mohammad Naraghi is a Professor Mechanical Engineering at Manhattan College, and an adjunct Professor of Mechanical Engineering at Columbia University. Prior to joining Manhattan College, he was a Visiting Assistant Professor of Mechanical Engineering at University of Akron where he received his Ph.D. in Mechanical Engineering. Dr. Naraghi in collaboration with NASA Glenn Research Center developed a comprehensive Rocket Thermal Evaluation code (RTE), which is used by NASA research centers and aerospace companies. Dr. Naraghi's research is in Thermal/Fluids area and he has published more than eighty articles in ASME, AIAA and international journals and conferences. He is recipient of a number of research grants from NASA and Air Force. Dr. Naraghi is a Fellow of ASME, Associate Fellow of AIAA, and a member of AIAA’s Liquid Propulsion Technical Committee.

    Course Materials

    Course notes will be made available about one week prior to the course event. You will receive an email with detailed instructions on how to access your course notes. Since these 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.

    Course Registration

    Registration options include course only and course and forum together as well as undergraduate and graduates rates. Please click here to register.


    Please contact Megan Scheidt  if you have any questions about courses and workshops at AIAA forums.

    Dates to Remember

    • Abstract Deadline: 04 Jan 2018
    • Manuscript Deadline: 13 Jun 2018
    • Early Bird Reg Deadline: 18 Jun 2018
    • Cancellation Deadline: 25 Jun 2018

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