Stability analysis of elastic launch vehicles with fuel sloshing in planar flight using a BEM-FEM model

A numerical model is developed for investigation of coupled dynamics of fuel contained elastic launch vehicles in planar atmospheric flight. Finite element method along with the linear quasi-steady piston aerodynamic theory is used for developing an aeroelastic model. A reduced order boundary elemen...

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Bibliographic Details
Published in:Aerospace science and technology 2016-06, Vol.53, p.74-84
Main Authors: Noorian, M.A., Haddadpour, H., Ebrahimian, M.
Format: Article
Language:English
Subjects:
Aeroelasticity
BEM-FEM model
Damping
Elastic launch vehicle
Fluid-solid interaction
Launch vehicles
Mathematical analysis
Mathematical models
Rigid-body dynamics
Sloshing
Stability analysis
Tanks
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Summary:A numerical model is developed for investigation of coupled dynamics of fuel contained elastic launch vehicles in planar atmospheric flight. Finite element method along with the linear quasi-steady piston aerodynamic theory is used for developing an aeroelastic model. A reduced order boundary element model is used for modeling the liquid sloshing in tanks. The interaction of sloshing and aeroelasticity is studied using stability analysis of the coupled system. Results show that the slosh–aeroelastic coupling in an elastic launch vehicle occurs for low tank filling ratios and may lead to decreasing the system damping. Due to more interactions between the slosh and rigid body modes, larger damping values of the rigid body mode and lower slosh frequencies are found for an elastic vehicle compared with a rigid vehicle. It is also shown that the slosh–aeroelastic interaction is increased as the slosh inherent damping decreases.
ISSN:1270-9638
1626-3219
DOI:10.1016/j.ast.2016.02.028