Application of composite materials in aircraft power engineering and their optimized design

Abstract

Abstract The aeroelastic flutter characteristics of composite wall plate structures of aircraft are investigated, the equations of motion of the structures are established by Hamilton’s principle and assumed modal method, and the aerodynamic forces of the aircraft are simulated by using piston theory. Physical quantities such as the intrinsic frequency and damping ratio of the structure can be obtained by solving the eigenvalue problem. The variation curves of the dimensionless intrinsic frequency of the structure with the aerodynamic pressure are numerically calculated to determine the critical aerodynamic pressure for flutter vibration, and the time response history curves of the structure for forced vibration are computed to analyze and compare the effects of graphene and carbon nanotube materials on the aerodynamic-elastic stability of the composite wall plate structure. It is found that the critical aerodynamic pressure of the FGM wall plate composed of carbon nano-(Si3N4) and graphene (SUS304) composites is 762 KPa at the temperature of 0°C. The calculated results show that the critical flutter dynamic pressure of the composite wall plate is increased from 375.6 Kpa to 433.1 Kpa, with an improvement in performance of 57.5 Kpa. The results of this paper are useful for the application of composites in the flight vehicle. The results of this paper are of theoretical reference value for the application of composites in power engineering and the optimization of the aeroelastic stability of the wall plate structure of the aircraft.