Publication Date:
2019-07-13
Description:
A finite element computational fluids dynamics-based aeroservoelastic analysis methodology is presented in this paper, in which both structural and fluids discretization are achieved by the finite element method, and their interaction is modeled by the transpiration boundary condition technique. In the fluids discipline either inviscid or viscous flow may be accounted for, usually employing unstructured grids.Adescription of a novel viscous flow solver employing unstructured grids is given in detail. Provisions are made for digital as well as analog controllers. These new aeroservoelastic analysis techniques are next applied for the solution of a number of example problems including the novel Hyper-X launch vehicle. Experimental and actual flight test data are also compared with analysis results that signify to the efficacy and accuracy of the newly developed solution procedures.
Keywords:
Launch Vehicles and Launch Operations
Type:
Paper 884
,
AIAA Aerospace Science Conference and Exhibit; Jan 05, 2004 - Jan 09, 2004; Reno, NV; United States|AIAA Journal; 45; 7; 1459-1471
Format:
text
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