Numerical Simulation of Folding Tail Aeroelasticity Based on the CFD/CSD Coupling Method
Di Zhou,
Weitao Lu,
Jiangpeng Wu,
Tongqing Guo,
Binbin Lv,
Hongtao Guo,
Hongya Xia
Affiliations
Di Zhou
Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Weitao Lu
Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Jiangpeng Wu
AVIC Shenyang Aircraft Design and Research Institute, Shenyang 110035, China
Tongqing Guo
Key Laboratory of Unsteady Aerodynamics and Flow Control, Ministry of Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Binbin Lv
Institute of High Speed Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China
Hongtao Guo
Institute of High Speed Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China
Hongya Xia
Institute of High Speed Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China
This paper presents a CFD/CSD coupling method for aeroelastic simulation of folding tail morphing aircraft. The unsteady aerodynamic analysis is based on an in-house computational fluid dynamics (CFD) solver for the Euler equations, and emphasis is made on developing an efficient dynamic mesh method for the tail’s hybrid fold motion/elastic vibration deformation. The structural dynamic analysis is based on the computational structural dynamics (CSD) technique for solving the structural equation of motion in modal space. The aeroelastic coupling was achieved through successive iterations of CFD and CSD computations in the time domain. An adaptive multi-functional morphing aircraft allowing tail fold motion was selected to be studied. By using the developed method, aeroelastic simulation and mechanism analysis for fixed configurations at different folding angles and for variable configurations during the folding process were performed. The influence of folding rate on tail aeroelasticity and its influence mechanism were also analyzed.
