In multidisciplinary coupled calculations represented by aeroelastic calculations, structural deformation will lead to deformation of the fluid solution domain. It is necessary to develop a dynamic mesh deformation technology with good versatility, high computational efficiency and strong applicability to meet the calculation needs of aerodynamic forces. The dynamic mesh technology based on the Radial Basis Function (RBF) interpolation method has strong deformation ability and is applicable to the deformation calculation of any type of mesh. It is considered to be a dynamic mesh technology with good application prospects. This article introduces the basic theory of dynamic mesh technology based on RBF, and analyzes the selection scheme of basis function and compact radius of RBF. The research progress of acceleration algorithm and accuracy improvement method for mesh deformation technology based on RBF is summarized, and the hybrid dynamic mesh technology based on RBF is introduced. A brief summary of the current research status of RBF-based dynamic mesh technology in aeroelastic calculations is also made.

Hypersonic vehicle often uses a propulsion-airframe integrated design, and often has a slender body layout using thin-walled structure and lightweight materials. These factors cause serious coupling effects between propulsion system, aerodynamic force and structural deformation, then lead the ensuing special propulsion-aeroelastic coupling problems. Given these, integrated dynamic modeling and analysis methods were studied. Firstly, dynamic equations were established based on small-perturbation theory of flight dynamics. Then the sub-discipline models with both high accuracy and efficiency were employed, which were aerodynamic model based on local piston theory, structural deformation model based on modal method and quasi-one-dimensional scramjet model. Finally, a dynamic model of air-breathing hypersonic vehicle considering the coupling of propulsion system and structural deformation was established. The dynamic stability analysis of a X-43-liked two-dimensional model is carried out based on the dynamic model. The effects of propulsion and aeroelastic coupling on the dynamic characteristics of the aircraft model are analyzed, and variable parameter analysis of key coupling parameters are conducted. The results validated the feasibility of these dynamic modeling & analysis methods, and demonstrate the special influence of propulsion-aeroelastic coupling on the dynamic characteristics of the example aircraft model. The propulsion coupling can significantly reduce the Phugoid mode stability, the aeroelastic coupling can slightly increase the short period mode stability, and the elevator deflect vibration coupling can significantly reduce the short period mode stability.

The wingtip-hinged multi-body combined Unmanned Aerial Vehicle (UAV) represents a novel conceptual aircraft, comprising multiple individual unmanned aircraft interconnected through wingtip hinges and allowing for relative roll motion. It exhibits significant distinctions in layout parameters and flight dynamics characteristics compared to conventional aircraft, with the presence of aerodynamic coupling between individual unmanned aircraft. First, the state-space vortex lattice method is employed to derive the aerodynamic derivatives specific to this aircraft type. Then, utilizing the Newton-Euler equations, a flight dynamics model is established for trim calculation and stability analysis, elucidating its unstable compound motion flight modes dominated by relative roll motion. Lastly, an investigation is conducted on the influence of layout parameters on flight dynamics stability. The analysis shows that reducing the trim roll angle of individual unmanned aircraft and increasing the sweep angle can enhance flight stability, while an optimal distance between the wing and tail is found to improve flight stability. The research findings can provide guidance and reference for the design of wingtip-hinged multi-body combined UAVs.