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Aerospace
Special Issues
Aerodynamic and Multidisciplinary Design Optimization
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Aerodynamic and Multidisciplinary Design Optimization

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (20 September 2024) | Viewed by 11920

Special Issue Editors

Dr. Zhonghua Han

E-Mail Website
Guest Editor
Professor, National Key Lab. of Science and Technology on Aerodynamic Design and Research, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Interests: surrogate modeling and efficient global optimization algorithm; aerodynamic and multidisciplinary design optimization of aircraft; multi-fidelity data fusion and aerodynamic modeling; sonic-boom prediction and low-boom design for supersonic aircraft; aerodynamic design optimization of wide-speed-range aircraft configuration; transition prediction and natural-laminar-flow airfoil/wing design
Dr. Jiangtao Huang

E-Mail Website
Guest Editor
Researcher, China Aerodynamics Research and Development Center, Mianyang 621000, China
Interests: aerodynamic design and multidisciplinary optimization of aircraft; flight dynamics and control

Special Issue Information

Dear Colleagues,

The aerodynamic shape optimization and multidisciplinary design optimization methods have received increasing attention in the area of aerospace engineering. They can improve the aerodynamic and overall performance of an aircraft or spacecraft and significantly improve the design efficiency when compared with the traditional “cut and try” method. However, they still suffer from the difficulties and challenges associated with (a) the design of complex configuration parameterized with many design variables, (b）expensive numerical simulations and sensitivity analysis of coupled disciplines, (c) complicated engineering constraints, (d) multiple objectives and multiple design points, and (e) uncertainties relevant to flight conditions and manufacture error, etc. This Special Issue aims to provide an overview of recent advances in the aerodynamic shape optimization and multidisciplinary design optimization of aircraft or spacecraft. Authors are invited to submit full-length research articles or review manuscripts addressing (but not limited to) the following topics:

  • Geometric parameterization and mesh-deformation method
  • Design-oriented multidisciplinary numerical simulations 
  • Innovation and application of efficient global optimization algorithm
  • Innovation and application of single-discipline or coupled adjoint method 
  • Machine learning in aerodynamic and multidisciplinary design optimization
  • Design application of new-concept airfoil/wing/aircraft configurations
  • Low-boom design of supersonic aircraft.

Dr. Zhonghua Han
Dr. Jiangtao Huang
Guest Editors

Manuscript Submission Information

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Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • aerodynamic shape optimization
  • multidisciplinary design optimization
  • coupled adjoint method
  • new-concept aircraft
  • machine learning

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Published Papers (7 papers)

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Research

20 pages, 10248 KiB  
Article
The Design and Performance Analysis of a 15 g/mol Helium–Xenon Mixture Centrifugal Compressor
by Jinchao Zheng, Zhitao Tian, Adil Malik, Jianchi Xin and Huawei Lu
Aerospace 2024, 11(11), 869; https://doi.org/10.3390/aerospace11110869 - 23 Oct 2024
Viewed by 611
Abstract
One of the primary parts of a closed Brayton cycle that uses a helium–xenon mixture as the working medium is a centrifugal compressor. Nowadays, there has been minimal research on the theoretical underpinnings and design procedures of a helium–xenon mixture centrifugal compressors, and [...] Read more.
One of the primary parts of a closed Brayton cycle that uses a helium–xenon mixture as the working medium is a centrifugal compressor. Nowadays, there has been minimal research on the theoretical underpinnings and design procedures of a helium–xenon mixture centrifugal compressors, and the internal flow mechanisms remain poorly understood. In this study, we present a redesign of the 15 g/mol helium–xenon centrifugal compressor originally developed by Bruno M, utilizing a helium–xenon mixture as the working fluid to enhance compressor performance and facilitate an in-depth analysis of the internal flow dynamics. The findings indicate a significant expansion of the stable operating range of the redesigned compressor under identical outlet conditions, with a 33.27% increase in flow margin and substantial improvements in the pressure ratio. Furthermore, under consistent inlet conditions, at an operational flow rate of 0.8657 kg/s, the redesigned compressor exhibits a pressure ratio that is 2.11% greater than that of the original design, along with a variable efficiency increase of 1.1%. Full article
(This article belongs to the Special Issue Aerodynamic and Multidisciplinary Design Optimization)
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18 pages, 10893 KiB  
Article
Position Calculation for Front Fin of Rocket Forebody Using Variable Step Scheme
by Zeyang Zhou and Jun Huang
Aerospace 2024, 11(8), 617; https://doi.org/10.3390/aerospace11080617 - 27 Jul 2024
Viewed by 900
Abstract
In order to determine the installation position of the front fin on the example rocket forebody, an optimized method based on a comprehensive evaluation indicator and variable step search is presented. The comprehensive indicator consists of four weight coefficients, two lateral aerodynamic forces [...] Read more.
In order to determine the installation position of the front fin on the example rocket forebody, an optimized method based on a comprehensive evaluation indicator and variable step search is presented. The comprehensive indicator consists of four weight coefficients, two lateral aerodynamic forces and two aerodynamic moments. The computational fluid dynamics method based on a shear stress transport turbulence model is established to analyze the flow field characteristics of the forebody. The results indicate that under equal weight coefficients, the presented search algorithm can provide an optimized solution for the front fin to achieve the minimum value of the comprehensive evaluation indicator. When the range of the current wing movement changes or the weight coefficient distribution changes, this search algorithm can still provide the optimal solution and some feasible solutions. Under the given conditions, there is a difference between the optimal solution of the aerodynamic force priority and that of the aerodynamic moment priority. For the case of the aerodynamic moment priority, the mean level of the pressure coefficient corresponding to the optimal solution on the given observation plane is low. The presented method is effective in learning the appropriate installation position of the rocket’s front fins. Full article
(This article belongs to the Special Issue Aerodynamic and Multidisciplinary Design Optimization)
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28 pages, 5764 KiB  
Article
Optimization Study of Steady-State Aerial-Towed Cable Circling Strategy Based on BP Neural Network Prediction
by Luqi Feng, Xueqiang Liu and Zi Feng Nio
Aerospace 2024, 11(7), 594; https://doi.org/10.3390/aerospace11070594 - 21 Jul 2024
Cited by 4 | Viewed by 984
Abstract
This paper presents models for UAV aerial-towed cables in free-end and fixed-end configurations, crucial for tasks like communication and aerial charging. By establishing a quasi steady-state model, computational results on cable shapes are obtained. To accelerate computations, a backpropagation (BP) neural network prediction [...] Read more.
This paper presents models for UAV aerial-towed cables in free-end and fixed-end configurations, crucial for tasks like communication and aerial charging. By establishing a quasi steady-state model, computational results on cable shapes are obtained. To accelerate computations, a backpropagation (BP) neural network prediction model is trained, significantly reducing the computation time. An evaluation function has been developed that integrates both aircraft performance and cable shape considerations to evaluate circling parameters across various states. This function integrates techniques such as BP neural networks and particle swarm optimization (PSO) to refine parameters such as velocities and bank angles for both free-end and fixed-end cables. The results show that the BP neural network accurately predicts cable shapes, achieving a maximum error of 5% in towing force and verticality. Additionally, PSO efficiently optimizes circling parameters, thereby enhancing the effectiveness of the evaluation function in identifying optimal solutions. This approach significantly improves the efficiency of determining optimal circling parameters for UAV aerial-towed cables, thereby contributing to their operational efficacy. Full article
(This article belongs to the Special Issue Aerodynamic and Multidisciplinary Design Optimization)
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19 pages, 9101 KiB  
Article
Discrete Adjoint Optimization Method for Low-Boom Aircraft Design Using Equivalent Area Distribution
by Chuang Ma, Jiangtao Huang, Daochun Li, Jun Deng, Gang Liu, Lin Zhou and Cheng Chen
Aerospace 2024, 11(7), 545; https://doi.org/10.3390/aerospace11070545 - 3 Jul 2024
Viewed by 812
Abstract
This paper introduces a low-boom aircraft optimization design method guided by equivalent area distribution, which effectively improves the intuitiveness and refinement of inverse design. A gradient optimization method based on discrete adjoint equations is proposed to achieve the fast solution of the gradient [...] Read more.
This paper introduces a low-boom aircraft optimization design method guided by equivalent area distribution, which effectively improves the intuitiveness and refinement of inverse design. A gradient optimization method based on discrete adjoint equations is proposed to achieve the fast solution of the gradient information of target equivalent area distribution relative to design variables and to drive the aerodynamic shape update to the optimal solution. An optimization experiment is carried out based on a self-developed supersonic civil aircraft configuration with engines. The results show that the equivalent area distribution adjoint equation can accurately solve the gradient information. After optimization, the sonic boom level of the aircraft was reduced by 13.2 PLdB, and the drag coefficient was reduced by 60.75 counts. Moreover, the equivalent area distribution adjoint optimization method has outstanding advantages, such as high sensitivity and fast convergence speed, and can take both the low sonic boom and the low drag force of the aircraft into account, providing a powerful tool for the comprehensive optimization design of supersonic civil aircraft by considering sonic boom and aerodynamic force. Full article
(This article belongs to the Special Issue Aerodynamic and Multidisciplinary Design Optimization)
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32 pages, 7213 KiB  
Article
Extended Hierarchical Kriging Method for Aerodynamic Model Generation Incorporating Multiple Low-Fidelity Datasets
by Vinh Pham, Maxim Tyan, Tuan Anh Nguyen and Jae-Woo Lee
Aerospace 2024, 11(1), 6; https://doi.org/10.3390/aerospace11010006 - 20 Dec 2023
Cited by 2 | Viewed by 1830
Abstract
Multi-fidelity surrogate modeling (MFSM) methods are gaining recognition for their effectiveness in addressing simulation-based design challenges. Prior approaches have typically relied on recursive techniques, combining a limited number of high-fidelity (HF) samples with multiple low-fidelity (LF) datasets structured in hierarchical levels to generate [...] Read more.
Multi-fidelity surrogate modeling (MFSM) methods are gaining recognition for their effectiveness in addressing simulation-based design challenges. Prior approaches have typically relied on recursive techniques, combining a limited number of high-fidelity (HF) samples with multiple low-fidelity (LF) datasets structured in hierarchical levels to generate a precise HF approximation model. However, challenges arise when dealing with non-level LF datasets, where the fidelity levels of LF models are indistinguishable across the design space. In such cases, conventional methods employing recursive frameworks may lead to inefficient LF dataset utilization and substantial computational costs. To address these challenges, this work proposes the extended hierarchical Kriging (EHK) method, designed to simultaneously incorporate multiple non-level LF datasets for improved HF model construction, regardless of minor differences in fidelity levels. This method leverages a unique Bayesian-based MFSM framework, simultaneously combining non-level LF models using scaling factors to construct a global trend model. During model processing, unknown scaling factors are implicitly estimated through hyperparameter optimization, resulting in minimal computational costs during model processing, regardless of the number of LF datasets integrated, while maintaining the necessary accuracy in the resulting HF model. The advantages of the proposed EHK method are validated against state-of-the-art MFSM methods through various analytical examples and an engineering case study involving the construction of an aerodynamic database for the KP-2 eVTOL aircraft under various flying conditions. The results demonstrated the superiority of the proposed method in terms of computational cost and accuracy when generating aerodynamic models from the given multi-fidelity datasets. Full article
(This article belongs to the Special Issue Aerodynamic and Multidisciplinary Design Optimization)
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18 pages, 7192 KiB  
Article
Efficient Global Aerodynamic Shape Optimization of a Full Aircraft Configuration Considering Trimming
by Kai Wang, Zhonghua Han, Keshi Zhang and Wenping Song
Aerospace 2023, 10(8), 734; https://doi.org/10.3390/aerospace10080734 - 21 Aug 2023
Cited by 4 | Viewed by 2146
Abstract
Most existing aerodynamic shape optimization (ASO) studies do not take the balanced pitching moment into account and thus the optimized configuration has to be trimmed to ensure zero pitching moment, which causes additional drag and reduces the benefit of ASO remarkably. This article [...] Read more.
Most existing aerodynamic shape optimization (ASO) studies do not take the balanced pitching moment into account and thus the optimized configuration has to be trimmed to ensure zero pitching moment, which causes additional drag and reduces the benefit of ASO remarkably. This article proposes an efficient global ASO method that directly enforces a zero pitching moment constraint. A free-form deformation (FFD) parameterization combing Laplacian smoothing method is implemented to parameterize a full aircraft configuration and ensure sufficiently smooth aerodynamic shapes. Reynolds-averaged Navier–Stokes (RANS) equations are solved to simulate transonic viscous flows. A surrogate-based multi-round optimization strategy is used to drive ASO towards the global optimum. To verify the effectiveness of the proposed method, we adopt two design optimization strategies for the NASA Common Research Model (CRM) wing–body–tail configuration. The first strategy is to optimize the configuration without considering balance of pitching moment, and then manually trim the optimized configuration by deflecting the horizontal tail. The second one is to directly enforce the zero pitching moment constraint in the optimization model and take the deflection angle of the horizontal tail as an additional design variable. Results show that: (1) for the first strategy, about 4-count drag-reducing benefits would be lost when manually trimming the optimal configuration; (2) the second strategy can achieve 3.2-count more drag-reducing benefits than the first strategy; (3) compared with gradient-based optimization (GBO), surrogate-based optimization (SBO) is more efficient than GBO for ASO problems with around 80 design variables, and the benefit of ASO achieved by SBO is comparable to that obtained by GBO. Full article
(This article belongs to the Special Issue Aerodynamic and Multidisciplinary Design Optimization)
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28 pages, 4735 KiB  
Article
Aero-Engine Preliminary Design Optimization and Operability Studies Supported by a Compressor Mean-Line Design Module
by Alexios Alexiou, Ioannis Kolias, Nikolaos Aretakis and Konstantinos Mathioudakis
Aerospace 2023, 10(8), 726; https://doi.org/10.3390/aerospace10080726 - 20 Aug 2023
Viewed by 3080
Abstract
An approach for preliminary aero-engine design, incorporating a mean-line code for the design of axial-flow, multi-stage compressors, is presented. The compressor mean-line code is developed and integrated within a framework for the preliminary design and assessment of aero-engine concepts. It is then combined [...] Read more.
An approach for preliminary aero-engine design, incorporating a mean-line code for the design of axial-flow, multi-stage compressors, is presented. The compressor mean-line code is developed and integrated within a framework for the preliminary design and assessment of aero-engine concepts. It is then combined with modules for compressor map generation, multi-point engine design, steady-state and transient engine off-design performance and aircraft mission analysis. Implementation examples are presented, demonstrating the determination of the optimal combination of compressor and engine design parameters for achieving minimum fuel burn over a specific aircraft mission, while obeying constraints that guarantee operability over the entire flight envelope. Constraints related to compressor stability during transient maneuvers between idle and static take-off conditions and engine temperature limits at maximum take-off are respected by the final design. The results demonstrate the potential for design trade-offs between engine performance at the aircraft mission level and compressor aerodynamic stability. Full article
(This article belongs to the Special Issue Aerodynamic and Multidisciplinary Design Optimization)
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