Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM Scheme
Current technology in evaluating the aeroelastic behavior of aerospace structures is based on the staggered coupling between structural and low fidelity linearized aerodynamic solvers, which has inherent limitations, although tried and trusted outside the transonic region. These limitations arise fr...
| Main Authors: | , |
|---|---|
| Format: | Article |
| Language: | English |
| Published: |
MDPI AG
2020-11-01
|
| Series: | Aerospace |
| Subjects: | |
| Online Access: | https://www.mdpi.com/2226-4310/7/11/164 |
| _version_ | 1797547670764519424 |
|---|---|
| author | Angelos Kafkas George Lampeas |
| author_facet | Angelos Kafkas George Lampeas |
| author_sort | Angelos Kafkas |
| collection | DOAJ |
| description | Current technology in evaluating the aeroelastic behavior of aerospace structures is based on the staggered coupling between structural and low fidelity linearized aerodynamic solvers, which has inherent limitations, although tried and trusted outside the transonic region. These limitations arise from the assumptions in the formulation of linearized aerodynamics and the lower fidelity in the description of the flowfield surrounding the structure. The validity of low fidelity aerodynamics also degrades fast with the deviation from a typical aerodynamic shape due to the inclusion of various control devices, gaps, or discontinuities. As innovative wings tend to become more flexible and also include a variety of morphing devices, it is expected that using low fidelity linearized aerodynamics in aeroelastic analysis will tend to induce higher levels of uncertainty in the results. An obvious solution to these issues is to use high fidelity aerodynamics. However, using high fidelity aerodynamics incurs a very high computational cost. Various formulations of reduced order models have shown promising results in reducing the computational cost. In the present work, the static aeroelastic behavior of three characteristic aeroelastic problems is obtained using both a full three-dimensional staggered coupled scheme and a time domain Volterra series based reduced order model (ROM). The reduced order model’s ability to remain valid for a wide range of dynamic pressures around a specific Mach number (and Reynolds number regime if viscous flow is considered) and the capability to modify structural parameters such as damping ratios and natural frequencies are highlighted. |
| first_indexed | 2024-03-10T14:47:23Z |
| format | Article |
| id | doaj.art-09154de4682348f0b302a88f86b79ceb |
| institution | Directory Open Access Journal |
| issn | 2226-4310 |
| language | English |
| last_indexed | 2024-03-10T14:47:23Z |
| publishDate | 2020-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Aerospace |
| spelling | doaj.art-09154de4682348f0b302a88f86b79ceb2023-11-20T21:12:02ZengMDPI AGAerospace2226-43102020-11-0171116410.3390/aerospace7110164Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM SchemeAngelos Kafkas0George Lampeas1Department of Mechanical Engineering & Aeronautics, University of Patras, 26504 Patras, GreeceDepartment of Mechanical Engineering & Aeronautics, University of Patras, 26504 Patras, GreeceCurrent technology in evaluating the aeroelastic behavior of aerospace structures is based on the staggered coupling between structural and low fidelity linearized aerodynamic solvers, which has inherent limitations, although tried and trusted outside the transonic region. These limitations arise from the assumptions in the formulation of linearized aerodynamics and the lower fidelity in the description of the flowfield surrounding the structure. The validity of low fidelity aerodynamics also degrades fast with the deviation from a typical aerodynamic shape due to the inclusion of various control devices, gaps, or discontinuities. As innovative wings tend to become more flexible and also include a variety of morphing devices, it is expected that using low fidelity linearized aerodynamics in aeroelastic analysis will tend to induce higher levels of uncertainty in the results. An obvious solution to these issues is to use high fidelity aerodynamics. However, using high fidelity aerodynamics incurs a very high computational cost. Various formulations of reduced order models have shown promising results in reducing the computational cost. In the present work, the static aeroelastic behavior of three characteristic aeroelastic problems is obtained using both a full three-dimensional staggered coupled scheme and a time domain Volterra series based reduced order model (ROM). The reduced order model’s ability to remain valid for a wide range of dynamic pressures around a specific Mach number (and Reynolds number regime if viscous flow is considered) and the capability to modify structural parameters such as damping ratios and natural frequencies are highlighted.https://www.mdpi.com/2226-4310/7/11/164computational aeroelasticityreduced order modelVolterra seriesstatic aeroelasticityROM |
| spellingShingle | Angelos Kafkas George Lampeas Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM Scheme Aerospace computational aeroelasticity reduced order model Volterra series static aeroelasticity ROM |
| title | Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM Scheme |
| title_full | Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM Scheme |
| title_fullStr | Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM Scheme |
| title_full_unstemmed | Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM Scheme |
| title_short | Static Aeroelasticity Using High Fidelity Aerodynamics in a Staggered Coupled and ROM Scheme |
| title_sort | static aeroelasticity using high fidelity aerodynamics in a staggered coupled and rom scheme |
| topic | computational aeroelasticity reduced order model Volterra series static aeroelasticity ROM |
| url | https://www.mdpi.com/2226-4310/7/11/164 |
| work_keys_str_mv | AT angeloskafkas staticaeroelasticityusinghighfidelityaerodynamicsinastaggeredcoupledandromscheme AT georgelampeas staticaeroelasticityusinghighfidelityaerodynamicsinastaggeredcoupledandromscheme |