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| Bin Li | |||
| Academy of Aerospace Propulsion Technology, China | |||
| Brief Biography: Bin Li, research fellow and doctoral supervisor, member of the "National Ten Thousand Talents Program" (for Science and Technology Innovation Leaders), is currently the Director of the Science and Technology Commission of The China Academy of Aerospace Propulsion Technology. He has been engaged in the technical research of advanced liquid rocket engines for a long time, and led the team successfully developed the 120-ton high-pressure staged-combustion LOX-kerosene engine, which are employed as the main propulsion system for the new generation Long March launch vehicles. At present, Bin Li is committed to tackling key technologies for propulsion system of manned lunar missions and heavy launch vehicles. He has won a first prize of National Science and Technology Progress Award and 15 National Defense Science and Technology Progress Awards, published more than 50 papers and 3 monographs, and was granted with 35 invention patents. He was honored the 4th Aerospace Laureate Awards, the Qian Xuesen Outstanding Contribution Award from China Aerospace Foundation, and other awards. |
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| Speech Title: Key Technologies of Advanced Liquid Rocket Engines |
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| Abstract: The liquid rocket engine is the core component of launch vehicles and determines the ability to enter space. With the rapid development of large-scale space infrastructure and the aerospace industry, higher requirements are imposed on liquid propulsion technology. This lecture provides a systematic overview of the major research directions of advanced liquid rocket engines. Beginning with an overview of Chinese liquid rocket engines, the speech addresses representative technical characteristics of advanced liquid rocket engines, including rapid dynamic processes, extreme operating environments, high requirements on manufacturing, and difficulties in fault diagnosis. To overcome these challenges, several research directions have been identified. The speech introduces the latest progress in detail and outlines prospects for future advancement, covering the control of system dynamic characteristics, the design of lightweight structures, the control of combustion stability, the design of high-power-density turbopumps, technologies of reusable engines, as well as fault diagnosis and health management. |
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| Keynote Speaker Ⅱ | |||
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| Wenhui Ling | |||
| Beijing Power Machinery Institute, China | |||
| Keynote Speaker Ⅲ | |||
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| Zonglin Jiang | |||
| Institute of Mechanics, Chinese Academy of Sciences, China | |||
| Brief Biography: Zonglin Jiang is a professor from the Institute of Mechanics, Chinese Academy of Sciences and graduated from the Department of Mechanics, Peking University, and has engaged in gas dynamics research since then. Zonglin Jiang has won the AIAA 2016 Ground Test Award, received the a Distinguished Fellow of the International Shock Wave Institute in 2021, authored about 300 refereed papers and published two academic monographs, including "Gaseous Detonation Physics and Its Universal Framework Theory" by Springer and "Theories and Technologies of Hypersonic Shock Tunnels" by Cambridge University Press. |
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| Speech Title: Critical Condition for Stable Oblique Detonation for Hypersonic Propulsion |
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| Abstract: Standing oblique detonation is a unique pressure-gain combustion phenomenon for hypersonic ramjet propulsion, and its research has been related with supersonic combustion in scramjet engines since its births, for example, absent treatment in its early stage and re-consideration in recent decades. Standing oblique detonations and supersonic combustion share the same features of supersonic chemically-reacting flows, and can be considered as different flow stages in its development. Combustion instability in a chemically-reacting flow is reviewed first to identify its fundamental mechanisms, and the upstream-propagating shock wave is identified as one of the most important intrinsic characteristics and taken as the key problem for developing hypersonic ramjet propulsion. Three critical conditions for the standing oblique detonation are proposed as a theoretical base for standing oblique detonation ramjet engines. The first critical condition is the maximum heat that can drive local flow states from supersonic to sonic after combustion. The second one is the critical inflow Mach number of combustors, at which supersonic combustion will transform from instable to stable at full equivalent ratio. The last is the critical wedge angle above which a standing oblique detonation can be initiated. The three critical conditions are discussed in detail and verified with numerical simulations and wind tunnel experiments. In conclusion, the stable operation of hypersonic ramjet propulsion is a critical issue to approach its engineering application, and the standing oblique detonation ramjet engine is recommended as a promising candidate, deserving more attention in the future. |
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| Keynote Speaker Ⅳ | |||
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| Jinglei Xu | |||
| Nanjing University of Aeronautics and Astronautics, China | |||
| Keynote Speaker Ⅴ | |||
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| Guang Pan | |||
| Northwestern Polytechnical University, China | |||
| Keynote Speaker Ⅵ | |||
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| Bing Wang | |||
| Tsinghua University, China | |||
| Brief Biography: Professor Wang, Humboldt Scholar, Associate Dean of the Institute for Aero Engine, Tsinghua University, Director of the Spray Combustion and Propulsion Laboratory. Professor Wang has a long experience in basic and engineering application researches in two-phase flows and reactive flows under extreme conditions. As either the principle investigator or a major participant, he has completed more than 40 major national engineering projects. He has published more than 160 papers in SCI indexed journals such as Progress of Aerospace Sciences, Journal of Fluid Mechanics, Combustion and Flame, Physics of Fluids, more than 70 conference papers, and is the co-inventor of more than 15 Chinese and international patents. He is the winner of multiple golden awards at world-class international invention exhibitions as the Beijing Municipal Award for Scientific Progress. He is currently an Associate Fellow of the AIAA. In 2019, he was awarded as the "TUM Ambassador" by the Technical University of Munich. |
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| Speech Title: Modeling Compressible Multiphase Interfacial and Reactive Flows in Aerospace Engineering |
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| Abstract: Recent advancements in aerospace technology have significantly increased the demand for hypersonic propulsion systems. In scramjets and detonation-based engines, the intricate interactions between fuel droplets and intense shock waves are critical for enhancing combustor thermal efficiency. This underscores the importance of understanding compressible multiphase interfacial and reactive flows to advance next-generation high-speed propulsion technologies. In recent years, we have developed and implemented a comprehensive suite of high-fidelity numerical strategies—incorporating adaptive mesh refinement, immersed boundary methods, high-order reconstruction schemes, interface-tracking techniques, as well as detailed chemistry and phase transition models—to accurately resolve the coupled evolution phenomena and mechanisms associated with shock waves and detonation dynamics involving Eulerian droplets. Through systematic simulations of both planar and curved shock impacts, along with cellular detonation environments, we elucidate the evolution of transient wave configurations, quantify the onset and growth of interface instabilities, and characterize regimes related to droplet flattening, ligament formation, and fragmentation. Our findings reveal that multidimensional shock structures not only modulate the local thermochemical state surrounding each droplet but also generate complex vortex-driven shear due to surface pit formations that accelerate droplet breakup far beyond classical Weber-number predictions. These insights provide a robust mechanistic foundation for designing next-generation hypersonic vehicles with enhanced atomization capabilities, improved mixing efficiency, and superior ignition performance. |
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| Keynote Speaker Ⅶ | |||
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| Shuguang Chen | |||
| Shanghai Cosmoleap Technology Co., Ltd., China | |||
| Keynote Speaker Ⅷ | |||
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| Shipeng Li | |||
| Beijing Institute of Technology, China | |||
| Keynote Speaker Ⅸ | |||
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| Ping'an Liu | |||
| Harbin Engineering University, China | |||
| Brief Biography: Ping'an Liu is a professor at the College of Aerospace and Civil Engineering at the Harbin Engineering University (HEU). He received his PhD in mechanics in 2012 at Harbin Engineering University, China. His research is primarily focused on combustion and flow processes in solid rocket motors and water ramjet engines, metal fuel technology, underwater supercavitating vehicles and transmedia technology. He is an Associate Editor of Journal of Energy Science and Technology. Currently, he is also the deputy director of the Key Laboratory of Vehicle Transmedia Technology of the Ministry of Industry and Information Technology. He has published around 80 peer reviewed journal papers. He serves as the co-chair of the organizing committee of the 2025 International Conference of Mechanical Engineering on Aerospace (CoMEA). |
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| Speech Title: Progress in Metal-Fueled Transmedia Engine Research and Future Emerging Power Systems |
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| Abstract: The metal-fueled engine is attractive in aerospace and underwater propulsion because of its rather successful combination of such characteristics as high combustion heat, density, safety of powder handling, non-toxic combustion products, and price. However, to realize these advantages, metal-fueled propellants are required to have good delivery characteristics and stable, efficient combustion. These key technologies remain a major challenge in the development of metal-fueled engines. This presentation focuses on the present development of metal-fueled engine technology and its application in transmedia vehicle, specifically covering numerical modeling of the flow field in the engine and recent experimental studies. Finally, several novel power systems with high potential for future applications in launch and transmedia vehicles are introduced. |
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