Gust response analysis of supersonic aircraft based on three-dimensional piston theory

ifasd2024 Tracking Number 93

Though the influence of atmosphere disturbance (gust) on low-speed aircraft has been studied a lot since the disintegration of the Helios Prototype, the gust load on supersonic vehicles still needs further discussion, along with efficient analysis methods. On the other hand, with the development of hypersonic glide vehicles, the assembly of warhead and booster usually has a lower basic frequency than supersonic fighters and therefore, is more sensitive to atmosphere disturbance, which makes it necessary to analyze the gust response of supersonic aircraft. In this paper, first-order piston theory is applied in the local frame of 3-D aero mesh to calculate the unsteady aerodynamic force caused by elastic vibration and gust, which could be written into matrix form using modal coordinates and interface interpolation method, where and are aerodynamic damping and stiffness respectively. Integrate the aerodynamic model into the structural dynamics, and the aeroelastic dynamic equation could be formed, with the notation : where are the generalized mass, damping, and stiffness matrixes of the structure. In most research, the ODE is solved by numerical methods like Ruuge-Kutta methods though semi-analytical solution exists: , with . To justify the proposed method and semi-analytical solution, the dynamic response of a simple wing model under 1-cos gust is calculated by both the proposed method and ZAERO at Ma 3.0: (a) Fig. (a): Diagram of the wing model (b): Acceleration of monitor point (b) In conclusion, the gust response analysis based on three-dimensional piston theory has great consistency with commercial software, yet the proposed method could be applied to high-resolution 3-D mesh. The analytical solution gives almost identical results to Runge-Kutta with 1/20 of the time spent, which makes it practical to analyze complex objects.