19–22 August 2019
JW Marriott, Indianapolis, Indiana

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

7-8 July 2018
0800-1700 hrs

Member - Early (until 18 June) $500
Member - Standard $600
Conference Rate $700


Register Here

Synopsis

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 toward emerging liquid rocket engines. In addition to the popular rocket engine testing module, this year, the course will also include a module on combustion instability and a module on propellant management systems.

Key Topics 

  • Rocket Propulsion Fundamentals
  • Rocket Fuels & 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.

Outline

  • Rocket Propulsion Fundamentals
    • History of Propulsion/Overview of Components
    • Performance and Design Considerations
    • Rocket Classifications
    • Regeneratively Cooled Chambers
    • Combustion Instability
    • Propellant Management Systems and Propellant Dynamics
  • Rocket Fuels & Oxidizers Definition and Characterization
    • Definitions
    • Exposure & Handling Guidelines
    • Desirable Physical Properties
    • Survey of Potential Fuels & 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 & System Design Considerations
    • Green Propellant Storage Considerations
    • Common Green Options & Ionic Liquids
    • GRASP Program and REACH Regulation
  • Development and Flight Experience with Green Monopropellants
    • Rocket Grade Hydrogen Peroxide Properties & Experience
    • High Performance Green Propulsion Monopropellant and Thrusters
    • Microsat, Nanosat and Cubesat Propulsion & Micropropulsion TestingCourse Instructor

Instructors

Dr. 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 ongoing 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, including an altitude simulation test facility for chemical rocket engines, at the Maurice Zucrow Laboratories at Purdue University. Dr. Pourpoint is an Associate Fellow of AIAA.

Dr. Behurzi is a Senior Expert in Fluid Mechanics in the department of Vehicle Engineering at Airbus Safran Launchers in Bremen, Germany. He received his Ph.D. at Aachen University, Germany, in 2000. He also received his Diploma in Aerospace Engineering at Aachen University. After his Ph.D., he was employed 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 much experience in developing Propellant Management Devices (PMDs) for satellites, transfer vehicles, and upper stages. Examples are the Spacebus and Globalstar satellite tank families and 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 in 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.

Dr. Lineberry is a Research Engineer with the University of Alabama in Huntsville Propulsion Research Center (PRC). 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.

Dr. 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.

Dr. Mohammad Naraghi is a Professor of Mechanical Engineering at Manhattan College. He is active in research on thermal analysis of rocket engines, radiation heat transfer, and renewable energy. In collaboration with NASA Glenn Research Center, he developed a comprehensive Rocket Thermal Evaluation Code (RTE). Recognized for the code development, Dr. Naraghi was awarded the Certificate of Recognition by NASA for the creative development of technically significant software that has been accepted and approved for dissemination to the public by NASA. Since the first release of RTE through NASA's COSMIC Library, Dr. Naraghi has continued collaborating closely with NASA colleagues as well as a number of aerospace companies, thereby expanding the myriad capabilities of the code. 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 the U.S. Air Force. Dr. Naraghi is a Fellow of ASME and an Associate Fellow of AIAA.

Mr. David Ransom is a Manager in the Machinery Program at Southwest Research Institute (SwRI) in San Antonio, Texas. His areas of research include root cause failure analysis, wet-gas compression, machinery reliability, and liquid and air-breathing propulsion. Mr. Ransom is currently completing development of a pogo suppressor for a new commercial launch vehicle. Prior to joining SwRI, Mr. Ransom worked at Boeing, TurboCare, and Rocketdyne. At Boeing, Mr. Ransom worked in the Cargo Loads Group supporting the Space Shuttle Program by performing structural dynamic loads analysis of the Space Shuttle Payload Bay. In addition to the normal mission support work, Mr. Ransom supported the post-Columbia Return to Flight effort by performing extensive code verification and validation activities. At TurboCare, Mr. Ransom managed an engineering team designing bearings and seals for industrial machinery such as compressors, turbines, and pumps. At Rocketdyne, he was involved in the design of bearing and seal systems for liquid rocket engine turbopumps, as well as performing prototype testing of two novel turbopump devices under development at the time.

Course Materials

Course notes will be made available about one week prior to the course event. Course registrants 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.  

Contact

Please contact Jason Cole if you have any questions about courses and workshops at AIAA forums.

Dates to Remember

  • Abstract Deadline: 31 Jan 2019
  • Manuscript Deadline: 15 Jul 2019

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