Surrogate-Assisted Reliability Optimisation of an Aircraft Wing with Static and Dynamic Aeroelastic Constraints

Wansaseub, Kittinan; Sleesongsom, Suwin; Panagant, Natee; Pholdee, Nantiwat; Bureerat, Sujin

doi:10.1007/s42405-019-00246-6

Cited by 18 publications

(10 citation statements)

References 37 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The method is coupled with the OMOPSO algorithm [26,36]. All the multi-point, multi-objective optimisations start with a design space exploration based on a Latin Hypercube Sampling (LHS) [37,38]. The process is driven with numerical simulations and the convergence criteria of the MOOs is based on the hypervolume indicator [39].…”

Section: Methodsmentioning

confidence: 99%

Towards the design and optimisation of future compact aero-engines: intake/fancowl trade-off investigation

Tejero

MacManus

García

et al. 2022

HFF

View full text Add to dashboard Cite

Purpose Relative to in-service aero-engines, the bypass ratio of future civil architectures may increase further. If traditional design rules are applied to these new configurations and the housing components are scaled, then it is expected that the overall weight, nacelle drag and the effects of aircraft integration will increase. For this reason, the next generation of civil turbofan engines may use compact nacelles to maximise the benefits from the new engine cycles. The purpose of this paper is to present a multi-level design and optimisation process for future civil aero-engines. Design/methodology/approach An initial set of multi-point, multi-objective optimisations for axisymmetric configurations are carried out to identify the trade-off between intake and fancowl bulk parameters of highlight radius and nacelle length on nacelle drag. Having identified the likely optimal part of the design space, a set of computationally expensive optimisations for three-dimensional non-axisymmetric configurations is performed. The process includes cruise- and windmilling-type operating conditions to ensure aerodynamic robustness of the downselected configurations. Findings Relative to a conventional aero-engine nacelle, the developed process yielded a compact aero-engine configuration with mid-cruise drag reduction of approximately 1.6% of the nominal standard net thrust. Originality/value The multi-point, multi-objective optimisation is carried out with a mixture of regression and classification functions to ensure aerodynamic robustness of the downselected configurations. The developed computational approach enables the optimisation of future civil aero-engine nacelles that target a reduction of the overall fuel consumption.

show abstract

Section: Methodsmentioning

confidence: 99%

Towards the design and optimisation of future compact aero-engines: intake/fancowl trade-off investigation

Tejero

MacManus

García

et al. 2022

HFF

View full text Add to dashboard Cite

show abstract

“…A response surface model was used to analyze the data and find behavioral equations on remolded clayey samples mixed with gasoil to evaluate their geotechnical properties [33]. A radial basis function model was employed for optimization of highway guardrails [34] while the Kriging model was used to quantify uncertainties in the design of an aircraft wing structure [35]. Such models are proven numerical tools for engineers.…”

Section: Cfd Simulationmentioning

confidence: 99%

Angle Design of Stator-Rotor Blades for VLH Axial Flow Turbine using Surrogate-based Optimization

et al. 2021

View full text Add to dashboard Cite

This paper demonstrates design of a Very Low Head axial flow turbine using surrogate-based optimization. The design variables were blade angles between guide vanes and runner blades, whereas the objective function was turbine efficiency. A Latin Hypercube Sampling method was initially used to design the experiment with thirty sampling points, and a Large Eddy Simulation was modeled to analyze the flow for all sampling points. A correlation between design variables and the turbine efficiency was then evaluated using the surrogate models while the optimal design variables were identified. Also, several optimizers were used to tackle the proposed problem and their performances were investigated. The optimal design of blade angles 18   being 10 o , 20 o , 30 o , 40 o , 25 o , 45 o , 55 o and 65 o respectively, increased the turbine efficiency up to 89.87 %. The approach of using surrogate modeling was proved to be very effective and simple for optimizing a design of blade angles of stator-rotor and it can be applied for designing any other new blades.

show abstract

“…From Equation (7), if y1 and y2 are known, x1 and x2 can be computed. In cases of the car turning right, the two circles traced by the steering arms and tie rods are intersected at two points B and B :…”

Section: Optimization Design Problem Formulationmentioning

confidence: 99%

“…This technique is straightforward but requires thousands of analyses for an optimization run, which is impractical in most cases. As a result, to improve computational burden, the surrogate models as mentioned in many research papers [2,7] have been used to estimate function evaluations. Meanwhile, research in the field of topology optimization has been presented in [8], which depends on uncertainty of material properties, external loads, and other parameters.…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective, Reliability-Based Design Optimization of a Steering Linkage

Sleesongsom

Bureerat

2020

Applied Sciences

View full text Add to dashboard Cite

Reliability-based design optimization (RBDO) of a mechanism is normally based on the non-probabilistic model, which is viewed as failure possibility constraints in each optimization loop. It leads to a double-loop nested problem that causes a computationally expensive evaluation. Several methods have been developed to solve the problem, which are expected to increase the realization of optimum results and computational efficiency. The purpose of this paper was to develop a new technique of RBDO that can reduce the complexity of the double-loop nested problem to a single-loop. This involves using a multi-objective evolutionary technique combined with the worst-case scenario and fuzzy sets, known as a multi-objective, reliability-based design optimization (MORBDO). The optimization test problem and a steering linkage design were used to validate the performance of the proposed technique. The proposed technique can reduce the complexity of the design problem, producing results that are more conservative and realizable.

show abstract

Surrogate-Assisted Reliability Optimisation of an Aircraft Wing with Static and Dynamic Aeroelastic Constraints

Cited by 18 publications

References 37 publications

Towards the design and optimisation of future compact aero-engines: intake/fancowl trade-off investigation

Towards the design and optimisation of future compact aero-engines: intake/fancowl trade-off investigation

Angle Design of Stator-Rotor Blades for VLH Axial Flow Turbine using Surrogate-based Optimization

Multi-Objective, Reliability-Based Design Optimization of a Steering Linkage

Contact Info

Product

Resources

About