Transactions of Nanjing University of Aeronautics & Astronautics
Special Issue for UAV
Flight Dynamic Analysis of a Hypersonic Vehicles Considering Liquid-Solid coupling
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Abstract:
With the liquid propellant making up 60%—70% of the takeoff weight of the hypersonic vehicle, the dynamic load caused by great propellant sloshing interacts with the flexible structure of the aircraft. Therefore, the dynamic model displays characteristics of strong coupling with structure/control and nonlinearity. Based on the sloshing mass dynamic simplified as a spring-mass-damping model, a rigid-flexible-sloshing model is constructed. Moreover, the effect on the dynamic performance of the coupled model is analyzed with changing frequency and damping. The results show that propellant sloshing dynamics significantly affects the rigid body motion modes, especially flexible mode and short mode. The right half plane pole (RHP) moves far from the imaginary axis with the consumption of the propellant. The flexible mode attenuates with the increase of the sloshing damping, and the coupling becomes stronger when sloshing frequency is close to the short mode frequency or the flexible frequency of the beam.
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Project Supported:
This work was supported by the Fundamental Research Funds for the Central Universities (No. NS2015097).
Clc Number:
CHINA AERO-SCIENCES
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