Speakers 2026
Keynote Speaker Ⅰ
Prof. Liu Cunliang
Northwestern Polytechnical University, China
Biography: Liu Cunliang, Professor, Humboldt Research Fellow. He currently serves as Dean of the School of Power and Energy at Northwestern Polytechnical University, Chairman of the Shaanxi Society of Engineering Thermophysics, Head of the Shaanxi Provincial Science and Technology Innovation Team, and Director of the Shaanxi Provincial Key Laboratory of Thermal Science for Aero-Propulsion Systems.
His research primarily focuses on advanced cooling technologies for aero-engines. He has led multiple major national research projects, published over 100 academic papers, and been granted more than 80 invention patents. Professor Liu has received numerous awards and honors, including the Special Prize for Higher Education Teaching Achievement in Shaanxi Province, the First Prize for Technical Invention from the Chinese Society of Aeronautics and Astronautics, the Second Prize for Natural Science in Shaanxi Province, the Wu Zhonghua Outstanding Young Scholar Award, and the Shaanxi Provincial Distinguished Young Scholar Fund. He also serves on the Heat Transfer Committee of the Gas Turbine Division of the American Society of Mechanical Engineers (ASME) and as Associate Editor of the journal Aeroengine.
Speech Title: TBD
Abstract: TBD
Keynote Speaker Ⅱ
Prof. Wang Dingxi
Northwestern Polytechnical University, China
Biography:TBD
Speech Title: TBD
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Keynote Speaker Ⅲ
Prof. Tang Haibin
Beihang University, China
Biography:TBD
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Keynote Speaker Ⅳ
Researcher Yang Yongqiang
Xi'an Aerospace Propulsion Institute, China
Biography:Yang Yongqiang currently serves as the Deputy Chief Designer for the CZ-6 series and CZ-12 rockets at the China Aerospace Science and Technology Corporation (CASC).During the flight missions of the reusable CZ-10 series rockets, he led his team to overcome a series of critical technical challenges. These included vacuum ignition for self-starting staged-combustion cycle engines, asynchronous start control for multi-engine parallel configurations, and structural reliability assessment under complex thermal and mechanical environments.His work ensured that the engine's full-process operational states remained controllable, with stable and reliable performance. The engine performed exceptionally well during flight tests, playing a pivotal role in securing the complete success of China's first orbital re-entry and recovery test for a launch vehicle. This achievement broke foreign technological monopolies and made outstanding contributions to advancing China's reusable launch vehicle technology and the construction of a space power.Mr. Yang has been honored with several prestigious titles, including the CASC "Aerospace Innovation Award" (2025), the "Xi'an May 4th Youth Medal" (2018), and the "Outstanding Contributor to the Maiden Flight of the Long March 5 Launch Vehicle" (2017).
Speech Title: Reusable Rocket Engine Technology
Abstract: To meet the engineering requirements of China’s next-generation reusable launch vehicles, high-pressure staged-combustion cycle LOX/kerosene engines have become a key direction for reusable launch vehicle propulsion, owing to their high specific impulse, high density, deep throttling capability, and strong reusability potential. This paper focuses on reusable high-pressure staged-combustion cycle LOX/kerosene engine technology, with emphasis on the overall architecture, reusability-adaptive design, and flight verification approach. In response to critical challenges encountered in reusable missions—such as multiple starts, off-design operation, vacuum ignition, asynchronous start of multi-engine parallel configurations, and adaptation to the recovery and re-entry environment—corresponding technical approaches and system-level solutions are proposed. Based on a typical flight recovery profile, the report discusses full-process engine state controllability, health monitoring capability, ground-based reuse maintenance strategies, and the development of a full-life-cycle reliability assurance system. The study indicates that improving reusability design criteria, strengthening durability design of key components, and establishing an integrated technical system covering flight missions, status monitoring, and reuse maintenance can effectively enhance engine reusability, mission adaptability, and flight safety, thereby providing propulsion support for the engineering application of China’s reusable launch vehicles.
Keynote Speaker Ⅴ
Prof. Oskar Josef Haidn
Technical University of Munich, Germany
Biography: Prof. Oskar Josef Haidn is a Fellow of the European Conference of Aerospace Sciences (EUCASS) and an Associate Fellow of AIAA. He received his Diploma in Chemical Engineering in 1984 and his Doctorate in Engineering in 1991, both from the University of Erlangen-Nürnberg, Germany. He subsequently held a series of positions at the Institute of Space Propulsion of the German Aerospace Center (DLR), serving as Project Manager in 1990, Group Leader for Energy Technology in 1993, Department Head of Combustion Technology in 1996, Department Head of Modeling and Simulation in 1998, Department Head of Technology in 1998, and Deputy Director for Research and Technology in 1999. In 2011, he became Professor of Space Propulsion at the Technical University of Munich.
For many years, Prof. Haidn has served as an instructor within the AIAA Professional Development Courses. Since 2003, he has taught aspects of rocket propulsion in a specific master’s course at the University of Rome (La Sapienza). Since 2017, he has also been a visiting professor at the Harbin Institute of Technology.
Prof. Haidn’s research interests cover all fields of liquid-propellant rocket engines, including injection, atomization, ignition, combustion, combustion modeling, heat transfer, and cyclic life analyses, with a particular focus on all types of dynamic processes. He holds several patents in the field and is the author or co-author of more than 450 conference papers, journal articles, and book chapters.
Speech Title: Direct Numerical Simulation of Hydrogen/Oxygen Combustion for Rocket Engine
Abstract: We report recent results of DNS studies of H2/O2 combustion applying shear coax injectors in rocket engines. Study focus, for which we have used the OpenFoam code EB-DNS originating from the Karlsruhe Institute of Technology, was on validity and limits of the gradient transport assumption frequently used in CFD. Great emphasis was put on bias-less artificial turbulence generation to ensure that at propellant entrance into computational domain. Detailed grid refinement studies revealed the necessary number computational cells to resolve Kolmogorov eddies and the required number of cells (10-20) across the flame. These are necessary to ensure reliable predictions of species concentration profiles and gradients. The predicted number of cells for a full-scale simulation exceeded available super-computer capabilities. Hence, down-scaling of geometries and velocities such that the flow in the domain remained turbulent. Anyway, the total number of cells still exceeded 31 billion.
Simulation results reveal three substantially different regimes: the lean core, the fuel-rich area, and the recirculation zones. Within the core, oxygen transport follows the gradient assumption but combustion products deviate significantly. In the fuel-rich zone, all species transport follows the gradient assumption. The recirculation regions resembles a fuel-rich well-stirred reactor configuration where oxygen burns in almost pre-mixed conditions and the gradient assumption fails for oxygen. Recess establishes Kelvin-Helmholtz instabilities and their breakup generates asymmetric effects on turbulent production and dissipation. Turbulent viscosity substantial increases but micro-scale mixing intensifies even more.
Keynote Speaker Ⅵ
Dr. Matthias Meinke
RWTH Aachen University, Germany
Biography: Dr. Matthias Meinke earned his Diploma in Aerospace Engineering from RWTH Aachen University, Germany. Following this, he joined the Institute of Aerodynamics at RWTH Aachen University as a research assistant under the guidance of Prof. E. Krause. In 1993, he completed his Ph.D., presenting a dissertation focused on the Numerical Solution of the Navier-Stokes Equations for Unsteady Flows using the Multigrid Method.
Afterward, Dr. Meinke took on the role of head of the CFD department at the Institute of Aerodynamics and began teaching Computational Fluid Dynamics in both Bachelor’s and Master’s programs at RWTH Aachen University. He has extensive experience in various fields including aerodynamics, turbulence, aeroacoustics, turbomachinery, multiphase flows, and the development of advanced numerical methods.
For many years, Dr. Meinke and his team have been developing a multiphysics software framework specifically designed for high-performance computing systems. This framework is utilized in numerous national and European projects. To date, he has published over 190 peer-reviewed journal articles.
Speech Title: TBD
Abstract: TBD
Keynote Speaker Ⅶ
Prof. Vitaly Gennadievich Smelov
Samara University, Russia
Biography: Vitaly Gennadievich Smelov is a Professor in the Department of Engines Manufacturing Technologies, Director of Institute of Engine and Power Plant Engineering, vice rector of Samara National Research University named after Academician S.P. Korolev (Samara University)
Speech Title: The Implementation of Additive Manufacturing in the Production of Gas Turbine Units and Engines
Abstract: The framework integrates digital design, numerical simulation, additive manufacturing, post-processing, quality assurance, and experimental validation into a unified engineering workflow for the development and production of critical gas turbine components. The approach is focused on the hot-section parts of gas turbine engines, including combustion chambers, burner devices, nozzle guide vane segments, turbine components, heat exchangers, and structurally complex casings.
The proposed implementation model combines selective laser melting (SLM) for high-precision complex components and direct laser deposition (DLD) for large-scale parts, repair operations, and functional restoration. Additive manufacturing is embedded at the design stage through topology optimization, design-for-additive-manufacturing principles, process simulation, and the development of digital twins. This enables the creation of lightweight and functionally integrated components with internal cooling channels, reduced part counts, improved heat-transfer surfaces, and optimized aerodynamic and thermal characteristics.
The Samara University approach is based on an end-to-end digital production chain: requirements definition, parametric CAD modelling, thermodynamic and gas-dynamic calculations, strength analysis, manufacturing-process planning, powder-material qualification, additive fabrication, heat treatment, machining, non-destructive testing, metrological control, and bench testing. Particular attention is given to domestic metal powders, nickel-based heat-resistant alloys, process parameter optimization, residual-stress reduction, dimensional accuracy, surface quality, and repeatability of mechanical properties.
The technology platform supports the transition from laboratory development to industrial production in cooperation with engine manufacturers. It can be applied to the production of industrial gas turbine units, small gas turbine engines, auxiliary power units, distributed-energy systems, and prospective aircraft propulsion systems.
Keynote Speaker Ⅷ
Prof. Daniel Nélias
INSA Lyon, France
Biography: Daniel Nélias is professor of Mechanical Engineering at INSA Lyon in France since 2003 and director of the LaMCoS laboratory since 2016. He is a specialist of contact mechanics, mostly developing numerical models for a wide range of academic and engineering applications. He has been the supervisor of 70 PhD students, among them 60 already graduated including 10 from China.
Speech Title: Modelling of Multiple Coupled Normal and Tangential Contacts, Application to the Simulation of Blade/Disk Attachments
Abstract: A blade root, due to its specific geometry, involves multiple simultaneous contacts between disk teeth and blade root teeth. This configuration requires the simultaneous resolution of multiple contact problems between two bodies, one for each contact zone. The proposed approach separates the global structural deformation of the assembly from the local contact deformation at each contact zone.
An initial equilibrium is established between the local variables used to control the various contacts calculated upstream and the contact pressures, shear and slip vectors obtained using a semi-analytical method. The resulting local contact reactions are then balanced against the applied external loads in the global reference frame using an iterative numerical method until global equilibrium is reached. This numerical method enables the simultaneous solution of both normal and tangential multiple contact problems.
Several loading configurations are performed to assess the influence of different parameters such as the skew angle, the contact inclination angle, and friction coefficient on both the pressure field and the load distribution across different contact areas. The ability to perform rapid sensitivity studies is one of the key benefits of the proposed design tool.
Keynote Speaker Ⅸ
Prof. Daniele Botto
Politecnico di Torino, Italy
Biography: Daniele Botto has been a Full Professor at Politecnico di Torino since 2022. He received his PhD in Machine Design in 1994, and his research focuses on mechanical and aerospace engineering, with particular emphasis on structural dynamics, tribology, and optical methods for experimental dynamics. He teaches undergraduate and graduate courses and supervises MSc and PhD students in structural dynamics, aerospace engineering, and experimental mechanics. He is Head of the AERMEC Laboratory at Politecnico di Torino and coordinates national and international research projects.
Speech Title: Digital Image Correlation for Rotating Disks: From Decorrelation to Full-Field Dynamic Measurements
Abstract: Digital Image Correlation (DIC) has become a powerful tool for the dynamic characterization of structures, combining non-contact operation with full-field displacement measurements. Extending DIC to rotating components is particularly attractive because it can reveal their operational deformation without adding sensors, cables, or telemetry to the rotating assembly.
However, rotation also exposes one of the fundamental limitations of conventional correlation procedures. Once the angular displacement becomes too large, approximately 7°, the image subsets can no longer be matched reliably and decorrelation interrupts point tracking. This keynote examines the principal strategies developed to overcome this barrier. Incremental DIC preserves compatibility with standard software by periodically updating the reference image before the trackable rotation limit is reached. Although this extends the measurable angular range, successive reference updates accumulate correlation errors and may produce substantial displacement drift.
Several image-based compensation methods are considered to control this drift. Point Cloud Overlapping (PCO) estimates the rigid-body motion from locations assumed to have negligible vibration. Excitation-free PIctures (EPI) instead compares each test image with a baseline image acquired without excitation at the same angular position, thereby removing the rigid-body contribution. A hybrid strategy combines the two concepts to reduce cumulative error, limit the required number of reference images, and improve robustness to angular mismatch.
A complementary hardware-based solution uses encoder-synchronized acquisition to record images at prescribed angular positions over successive revolutions, allowing correlation between equivalent rotor position. By critically comparing these approaches in terms of accuracy, experimental complexity, data requirements, and applicability, the keynote highlights their respective strengths and limitations. The objective is to provide a practical framework for selecting an appropriate measurement strategy and to identify the remaining challenges on the path toward reliable full-field dynamic measurements of rotating disks.
Keynote Speaker Ⅹ
Dr. Khurram Nisar
Institute of Space Technology (IST), Pakistan
Biography: Dr. Khurram Nisar is an aerospace engineer. Presently, he is Associate Professor at the Institute of Space Technology (IST), Islamabad, Pakistan. He did MSc & Ph.d in Rocket propulsion from Beihang (Beijing) University of Aeronautics & Astronautics, China. He has vast experience in Rocket Propulsion and has been involved in various R&D projects.
Speech Title: TBD
Abstract: TBD
Keynote Speaker XI
Dr. Cen Zhaohui
Technology Innovation Institute, UAE
Biography: Dr. Zhaohui Cen is a Principal Researcher and Director at the Propulsion and Space Research Center of the Technology Innovation Institute (TII) in Abu Dhabi, United Arab Emirates (UAE). He specializes in intelligent automation for aerospace and renewable energy systems. Dr. Cen brings nearly two decades of experience in the field of intelligent automation and control for complex industrial systems, including aerospace propulsion systems (turbojet engines and rockets), UAVs, and satellites, lithium-ion battery energy storage systems, solar photovoltaic (PV) systems, as well as robotics and autonomous systems for solar PV applications. Dr. Cen received his B.A., M.S., and Ph.D. degrees in Electronics and Information Engineering from Huazhong University of Science and Technology (HUST) in 2005, 2007, and 2011, respectively. Following his Ph.D., he has held academic and research positions at the University of Sheffield, University of Lincoln, United Arab Emirates University, Qatar Foundation, and TII, spanning the United Kingdom, Qatar, and the United Arab Emirates. Prior to joining TII, he served as a Scientist and Group Head of Robotics and Autonomous Systems at the Qatar Environment and Energy Research Institute (QEERI). As a Principal Investigator and Project Leader, Dr. Cen has successfully secured and managed approximately USD 5 million in research funding and led a multi-institutional consortium of 10 organizations, including Texas A&M University, Carnegie Mellon University, TotalEnergies, and Midea. His research has been published in numerous high-impact journals and international conferences, and his work has also been featured in mainstream media. Dr. Cen serves on the Editorial Board of the Elsevier journal 《Energy Nexus》 (Impact Factor: 9.5, since 2022) and the 《International Journal of Applied Mathematics and Computer Science》(since 2019). He has also been invited as Lead Guest Editor for 《Frontiers in Energy Research》 and 《Aerospace》.
Speech Title: Research on Turbojet Engine Control and Diagnostics Development
Abstract: As the primary power source for UAVs and aircraft, aeroengines—such as micro turbojet engines—play a crucial role in propulsion and overall flight performance. These engines exhibit complex aerothermodynamic behaviors and integrate multiple actuators and sensors within their control systems. As the “brain” of the engine, the engine control unit (ECU) is responsible for acquiring sensor data, processing command inputs, and coordinating actuator responses to ensure successful ignition, stable operation, and attainment of the desired speed. In this talk, research on the development of a micro-turbojet ECU will be presented, along with related theoretical work on engine diagnostics. The discussion will also cover key challenges in extreme hot-weather conditions and outline future research directions in this field.