Surrogate Model Considering Trim Condition for Design Optimization of High-Aspect-Ratio Flexible Wing
An improved, bilevel surrogate model to optimize aerodynamic/nonlinear structural coupled problems, considering trim conditions, is proposed in this paper. The proposed model is applied to a high-aspect-ratio flexible wing. Computational fluid and structural dynamic codes are loosely coupled and int...
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| Published in | International journal of aeronautical and space sciences Vol. 23; no. 2; pp. 288 - 302 |
|---|---|
| Main Authors | , , , , , |
| Format | Journal Article |
| Language | English |
| Published |
Seoul
The Korean Society for Aeronautical & Space Sciences (KSAS)
01.04.2022
한국항공우주학회 |
| Subjects | |
| Online Access | Get full text |
| ISSN | 2093-274X 2093-2480 |
| DOI | 10.1007/s42405-021-00438-z |
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| Abstract | An improved, bilevel surrogate model to optimize aerodynamic/nonlinear structural coupled problems, considering trim conditions, is proposed in this paper. The proposed model is applied to a high-aspect-ratio flexible wing. Computational fluid and structural dynamic codes are loosely coupled and interact with the coupling variables of pressure and displacement. Level 1 reduces the coupling variables, using proper orthogonal decomposition, enabling the expansion of any data field as a linear combination of several modes. Level 2 builds the surrogate model, considering proper orthogonal displacement coefficients and the angle of attack as input parameters and the pressure coefficients as output parameters. Unlike the conventional bilevel surrogate model, the improved bilevel surrogate model includes the angle of attack as an input parameter to facilitate the immediate calculation of the trim angle of attack. The wing model of Global Hawk is optimized using the improved bilevel surrogate model, and the conventional bilevel surrogate model was used to compare the results of design optimization under two conditions: including and excluding the trim condition. |
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| AbstractList | An improved, bilevel surrogate model to optimize aerodynamic/nonlinear structural coupled problems, considering trim conditions, is proposed in this paper. The proposed model is applied to a high-aspect-ratio flexible wing. Computational fluid and structural dynamic codes are loosely coupled and interact with the coupling variables of pressure and displacement. Level 1 reduces the coupling variables, using proper orthogonal decomposition, enabling the expansion of any data field as a linear combination of several modes. Level 2 builds the surrogate model, considering proper orthogonal displacement coefficients and the angle of attack as input parameters and the pressure coefficients as output parameters. Unlike the conventional bilevel surrogate model, the improved bilevel surrogate model includes the angle of attack as an input parameter to facilitate the immediate calculation of the trim angle of attack. The wing model of Global Hawk is optimized using the improved bilevel surrogate model, and the conventional bilevel surrogate model was used to compare the results of design optimization under two conditions: including and excluding the trim condition. KCI Citation Count: 2 An improved, bilevel surrogate model to optimize aerodynamic/nonlinear structural coupled problems, considering trim conditions, is proposed in this paper. The proposed model is applied to a high-aspect-ratio flexible wing. Computational fluid and structural dynamic codes are loosely coupled and interact with the coupling variables of pressure and displacement. Level 1 reduces the coupling variables, using proper orthogonal decomposition, enabling the expansion of any data field as a linear combination of several modes. Level 2 builds the surrogate model, considering proper orthogonal displacement coefficients and the angle of attack as input parameters and the pressure coefficients as output parameters. Unlike the conventional bilevel surrogate model, the improved bilevel surrogate model includes the angle of attack as an input parameter to facilitate the immediate calculation of the trim angle of attack. The wing model of Global Hawk is optimized using the improved bilevel surrogate model, and the conventional bilevel surrogate model was used to compare the results of design optimization under two conditions: including and excluding the trim condition. |
| Author | Park, Kyunghyun Lee, Dong-Ho Cho, Maenghyo Kim, Euiyoung Chang, Seongmin Im, Sunyoung |
| Author_xml | – sequence: 1 givenname: Sunyoung surname: Im fullname: Im, Sunyoung organization: Multiscale Mechanical Design Division, School of Mechanical and Aerospace Engineering, Seoul National University – sequence: 2 givenname: Euiyoung surname: Kim fullname: Kim, Euiyoung organization: Korea Institute of Machinery and Materials – sequence: 3 givenname: Kyunghyun surname: Park fullname: Park, Kyunghyun organization: Aircraft Program Department, Defense Acquisition Program Administration – sequence: 4 givenname: Dong-Ho surname: Lee fullname: Lee, Dong-Ho organization: Multiscale Mechanical Design Division, School of Mechanical and Aerospace Engineering, Seoul National University – sequence: 5 givenname: Seongmin surname: Chang fullname: Chang, Seongmin email: schang@kumoh.ac.kr organization: Mechanical Design Engineering, Kumoh National Institute of Technology – sequence: 6 givenname: Maenghyo orcidid: 0000-0003-3942-9261 surname: Cho fullname: Cho, Maenghyo email: mhcho@snu.ac.kr organization: Multiscale Mechanical Design Division, School of Mechanical and Aerospace Engineering, Seoul National University |
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| Keywords | Multidisciplinary optimization Structural design optimization Surrogate model Proper orthogonal decomposition (POD) Angle of attack (AOA) |
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MaisonneuveMultidisciplinary design optimisation and robust design approaches applied to concurrent designStruct Multidiscip Optim200428535637110.1007/s00158-004-0417-9 Anindya C (2000) An introduction to the proper orthogonal decomposition. Curr Sci 808–817 ParkKHJunSOBaekSMChoMHYeeKJLeeDHReduced-order model with an artificial neural network for aerostructural design optimizationJ Aircraft20135041106111610.2514/1.C032062 Blazek J, Kroll N, Radespiel R, Rossow C-C (1991) Upwind implicit residual smoothing method for multi-stage schemes. 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| References_xml | – reference: Manoj B et al (1997) A CFD/CSD interaction methodology for aircraft wings. In: 7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization (p. 4783). https://doi.org/10.2514/6.1998-4783 – reference: BraunRDKrooIMAlexandrovNHussainiMYDevelopment and application of the collaborative optimization architecture in a multidisciplinary design environmentMultidisciplinary design optimization: state-of-the-art1995PhiladelphiaSIAM98116 – reference: FreitagSCaoBTNinićJMeschkeGRecurrent neural networks and proper orthogonal decomposition with interval data for real-time predictions of mechanised tunnelling processesComput Struct201820725827310.1016/j.compstruc.2017.03.020 – reference: PatilMJHodgesDHCesnikCESLimit-cycle oscillations in high-aspect-ratio wingsJ Fluids Struct200115110713210.1006/jfls.2000.0329 – reference: CoelhoRFBreitkopfPKnopf-LenoirCModel reduction for multidisciplinary optimization-application to a 2D wingStruct Multidiscip Optim2008371294810.1007/s00158-007-0212-5 – reference: JamesonASolution of the Euler equations for two dimensional transonic flow by a multigrid methodAppl Math Comput1983133–43273557266400545.76065 – reference: LeeJChoMEfficient design optimization strategy for structural dynamic systems using a reduced basis method combined with an equivalent static loadStruct Multidiscip Optim201858414891504385179810.1007/s00158-018-1976-5 – reference: KimEKimH-gBaekSChoMEffective structural optimization based on equivalent static loads combined with system reduction methodStruct Multidiscip Optim201450577578610.1007/s00158-014-1080-4 – reference: ImSKimEChoMReduction process based on proper orthogonal decomposition for dual formulation of dynamic substructuresComput Mech201964512371257401920510.1007/s00466-019-01702-61466.74054 – reference: CramerEJDennisJEJrFrankPDLewisRMShubinGRProblem formulation for multidisciplinary optimizationSIAM J Optim199444754776130085010.1137/08040440818.65055 – reference: ImSLeeJChoMSurrogate modeling of elasto-plastic problems via long short-term memory neural networks and proper orthogonal decompositionComput Methods Appl Mech Eng2021385429696910.1016/j.cma.2021.11403007415676 – reference: Anindya C (2000) An introduction to the proper orthogonal decomposition. Curr Sci 808–817 – reference: GottliebSShuC-WTotal variation diminishing Runge-Kutta schemesMath Comput1998672217385144311810.1090/S0025-5718-98-00913-20897.65058 – reference: Agostino De M, Eugene D, Jon B (2007) A general solution to the aircraft trim problem. 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| Snippet | An improved, bilevel surrogate model to optimize aerodynamic/nonlinear structural coupled problems, considering trim conditions, is proposed in this paper. The... |
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| SubjectTerms | Aerospace Technology and Astronautics Engineering Fluid- and Aerodynamics Original Paper 항공우주공학 |
| Title | Surrogate Model Considering Trim Condition for Design Optimization of High-Aspect-Ratio Flexible Wing |
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