Aerospace Science and Technology最新文献

An online learning framework for aero-engine sensor fault detection isolation and recovery 航空发动机传感器故障检测、隔离与恢复在线学习框架

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-26 DOI: 10.1016/j.ast.2025.110241

Kun Wang , Ai He , Jiashuai Liu , Qifan Zhou , Zhongzhi Hu

{"title":"An online learning framework for aero-engine sensor fault detection isolation and recovery","authors":"Kun Wang , Ai He , Jiashuai Liu , Qifan Zhou , Zhongzhi Hu","doi":"10.1016/j.ast.2025.110241","DOIUrl":"10.1016/j.ast.2025.110241","url":null,"abstract":"<div><div>Accurate and reliable sensor data are critical for the safe operation of modern aero-engine control systems. However, maintaining the accuracy and robustness of fault diagnosis models throughout the engine lifecycle is particularly challenging, especially under conditions of gradual degradation. To address these challenges, this paper proposes a novel Fault Detection, Isolation, and Recovery (FDIR) framework. The framework utilizes a Deep Denoising Autoencoder (DDAE) for fault detection, a multi-model strategy for fault isolation, and a dual-task learning framework for fault signal recovery, ensuring system integrity and continuous operation. Additionally, an online update mechanism based on distribution mean shifts is introduced, integrating parameter regularization and memory replay to prevent catastrophic forgetting and enhance adaptability. Experimental results demonstrate that the proposed framework achieves high-precision FDIR under both non-degraded and degraded conditions, exhibiting superior robustness and adaptability. By combining data-driven methods with adaptive online learning mechanisms, this work provides a scalable and reliable solution for aero-engine sensor fault diagnosis. It not only enhances the operational safety and efficiency of complex, data-intensive systems but also contributes to advancing the state of the art in this field.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110241"},"PeriodicalIF":5.0,"publicationDate":"2025-04-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143891858","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Combined flow control for corner separation in compressor cascades: A mechanistic and performance evaluation 压气机叶栅拐角分离的组合流动控制：机理与性能评价

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-25 DOI: 10.1016/j.ast.2025.110238

Xinyu Ren, Tongtong Meng, Lucheng Ji

{"title":"Combined flow control for corner separation in compressor cascades: A mechanistic and performance evaluation","authors":"Xinyu Ren, Tongtong Meng, Lucheng Ji","doi":"10.1016/j.ast.2025.110238","DOIUrl":"10.1016/j.ast.2025.110238","url":null,"abstract":"<div><div>Improving compressor performance requires precise control of high-loss flows in corner regions. This study proposes a combined passive control strategy that integrates a Blended Blade and EndWall (BBEW) profile with Vortex Generators (VGs) to address corner separation near the endwall. Numerical simulations conducted in a linear compressor cascade reveal the underlying mechanisms and effectiveness of this approach. The BBEW profile increases the blade-endwall dihedral angle, guiding low-energy fluid into the mainstream and weakening boundary layer interactions in the corner region, which helps delay the onset of separation. Concurrently, VGs generate streamwise vortices that enhance mixing between the mainstream and low-momentum fluid, reducing local vorticity and viscosity near the hub and further suppressing corner-related losses. VGs reduce losses below the 15% span, while BBEW counteracts losses introduced by VGs across the entire span. The combined control method achieves the most significant reduction in losses, decreasing them by 6.06%, surpassing the individual contributions of either VG or BBEW. This integrated approach effectively eliminates the Corner Vortex and reduces the Passage Vortex, resulting in a more stable flow. A quantitative evaluation model has also been developed to assess the influence of the combined control method on secondary flow suppression and boundary layer regulation. While the results are based on linear cascade simulations, the revealed mechanisms provide valuable guidance for future applications in real compressor stages.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110238"},"PeriodicalIF":5.0,"publicationDate":"2025-04-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143888063","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Maneuvering target tracking based on a random motion model and integrated random interacting multiple model filtering 基于随机运动模型和集成随机交互多模型滤波的机动目标跟踪

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-25 DOI: 10.1016/j.ast.2025.110244

Fengqi Yang , Jinshan Zhong , Yingting Luo, Ying Zhang, Xiaojing Shen, Yunmin Zhu

{"title":"Maneuvering target tracking based on a random motion model and integrated random interacting multiple model filtering","authors":"Fengqi Yang , Jinshan Zhong , Yingting Luo, Ying Zhang, Xiaojing Shen, Yunmin Zhu","doi":"10.1016/j.ast.2025.110244","DOIUrl":"10.1016/j.ast.2025.110244","url":null,"abstract":"<div><div>Traditional maneuvering target tracking algorithms assume that the target motion model is either fixed or limited in number. For high-speed and highly maneuvering targets, the tracker's performance degrades rapidly when the model set fails to adequately encompass the maneuvering mode or when there is a substantial deviation. Therefore, we propose a novel maneuvering target tracking method based on a random motion model. This algorithm employs a random model to describe the target maneuver, which is more widely applicable than traditional algorithms and remains more stable when the target maneuver is not covered by the model set. Additionally, in cases where the model set of the Interacting Multiple Model algorithm (IMM) does not align with the actual maneuvering state, the new method exhibits a smaller tracking error compared to IMM and shows no divergence trend. Finally, we combine IMM and the random motion model to propose an Integrated Random Interacting Multiple Model algorithm (IRIMM). The performance of the IRIMM algorithm closely matches that of IMM when provided with a perfectly accurate model set and significantly improves tracking effectiveness and stability when the model is incorrect.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110244"},"PeriodicalIF":5.0,"publicationDate":"2025-04-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143882065","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Air-breathing wide-range vehicle configuration concepts with double-sided inlet based on the waverider theory 基于乘波器理论的双面进气道吸气式大范围车辆配置概念

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-25 DOI: 10.1016/j.ast.2025.110259

Shibin Luo , Yuhang Sun , Jiaqi Tian , Jun Liu

{"title":"Air-breathing wide-range vehicle configuration concepts with double-sided inlet based on the waverider theory","authors":"Shibin Luo , Yuhang Sun , Jiaqi Tian , Jun Liu","doi":"10.1016/j.ast.2025.110259","DOIUrl":"10.1016/j.ast.2025.110259","url":null,"abstract":"<div><div>Air-breathing wide-range vehicles have garnered widespread attention for their long voyages, high specific impulse, and broad flight envelope. Such vehicles must operate in different airspace and speed environments. Based on the cone-derived waverider theory, this paper proposes two double-sided intake configurations suitable for wide-range flight: one with jettisonable fuel tanks and inlets, and the other as a full-waverider reversible double-sided intake. Both configurations have similar design processes. Subsequently, numerical methods are used to assess their feasibility. Pressure contours and aerodynamic coefficients at different Mach numbers show that both configurations exhibit excellent wave-riding characteristics during Mach 7 high-speed and Mach 5 low-speed cruises. The first vehicle changes from a double-sided intake to a dorsal intake configuration with full wave-riding characteristics on its lower surface by jettisoning one inlet and spent auxiliary fuel tank. This strategy not only addresses the weight issues caused by the double inlets but also achieves a maximum lift-to-drag ratio of over four at both cruising points. The second vehicle utilizes full-waverider theory for both upper and lower surfaces. This configuration allows simultaneous wave-riding of the airframe and inlet at both cruises and possesses higher positive lift than the like-rotating-body configuration. In particular, the newly refined configuration shows an improvement of over 6 % in the maximum lift-to-drag ratio during cruise compared to the like-rotating-body configuration. Moreover, the Mach 7 waverider surface has a larger wall compression angle than the Mach 5 surface, resulting in significantly better aerodynamic performance for both configurations at Mach 7 compared to Mach 5.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110259"},"PeriodicalIF":5.0,"publicationDate":"2025-04-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143891872","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Anti-saturation prescribed-time control for stochastic systems of free-flying space robots using a self-adapting non-monotonic approach 基于自适应非单调方法的自由飞行空间机器人随机系统抗饱和时间控制

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-24 DOI: 10.1016/j.ast.2025.110231

Yu Xia , Jun He , Kaixin Li , Feng Gao , Ramesh K. Agarwal

{"title":"Anti-saturation prescribed-time control for stochastic systems of free-flying space robots using a self-adapting non-monotonic approach","authors":"Yu Xia , Jun He , Kaixin Li , Feng Gao , Ramesh K. Agarwal","doi":"10.1016/j.ast.2025.110231","DOIUrl":"10.1016/j.ast.2025.110231","url":null,"abstract":"<div><div>This paper proposes an anti-saturation prescribed-time control scheme for free-flying space robots (FFSRs) subject to system uncertainties, external disturbances, input saturation, and output constraint. Initially, the control scheme is developed based on a newly constructed stochastic model, introducing stochastic neural networks (SNNs) to approximate the lumped stochastic factor that encompasses system uncertainties and external disturbances. Subsequently, a novel self-adapting non-monotonic prescribed-time function is proposed, integrating input saturation as an adaptive variable to dynamically adjust the constraint boundaries. This integration enables the constraint boundaries to adaptively expand in a non-monotonic manner in response to the occurrence of input saturation. Moreover, the constraint boundaries are designed as tunnel-shaped to prevent overshoot. The proposed control scheme ensures that all closed-loop signals are semi-globally uniformly ultimately bounded in probability, with the tracking error stabilized within a prescribed time. Finally, simulation results validate the effectiveness and superiority of the proposed scheme.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110231"},"PeriodicalIF":5.0,"publicationDate":"2025-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143879104","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Optimization strategy for ensemble learning models based on fusing resampling, adaptive dimensionality reduction, and Optuna in intelligent flight technology evaluation 智能飞行技术评估中基于融合重采样、自适应降维和Optuna的集成学习模型优化策略

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-24 DOI: 10.1016/j.ast.2025.110251

Jinyi Mao , Jian Chen , Yaoji Deng

{"title":"Optimization strategy for ensemble learning models based on fusing resampling, adaptive dimensionality reduction, and Optuna in intelligent flight technology evaluation","authors":"Jinyi Mao , Jian Chen , Yaoji Deng","doi":"10.1016/j.ast.2025.110251","DOIUrl":"10.1016/j.ast.2025.110251","url":null,"abstract":"<div><div>The flight techniques of pilots directly impact flight safety and constitute the primary factors influencing aviation accidents. However, existing research is limited by several challenges, including overly subjective evaluation criteria, the inability to implement large-scale data-driven approaches, and suboptimal outcomes. In this paper, a novel dynamic assessment framework for flight technique is proposed based on QAR data. The framework employs multiple ensemble learning models as baselines, fusing a three-stage optimization strategy. First, resampling techniques are introduced to address data imbalance. Second, a Stepwise Feature Selection-Adaptive Dimensionality Reduction (SFS-ADR) method is developed to efficiently reduce flight parameter dimensionality. Finally, Optuna hyperparameter optimization is adopted to further enhance model precision. Experiments on four public datasets demonstrate that the optimization strategy achieves accuracy improvements of 8.45%, 7.51%, 7.37%, and 7.22% respectively, with consistent superiority over baseline models. Model interpretability is further validated through SHapley Additive exPlanation (SHAP) method. The framework provides a high-precision dynamic solution for flight technique evaluation, offering valuable insights for Human Factors (HF) research in aviation safety.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110251"},"PeriodicalIF":5.0,"publicationDate":"2025-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143891857","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Adjustability analysis and experiment for mesh antenna 网状天线的可调性分析与实验

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110250

Yongxiang Huang , Tuanjie Li , Xiang Xu , Zhiyang Shi , Xifan Xu

{"title":"Adjustability analysis and experiment for mesh antenna","authors":"Yongxiang Huang , Tuanjie Li , Xiang Xu , Zhiyang Shi , Xifan Xu","doi":"10.1016/j.ast.2025.110250","DOIUrl":"10.1016/j.ast.2025.110250","url":null,"abstract":"<div><div>Mesh antenna plays an important role in the field of space communication. Surface accuracy is the key factor to determine the electrical performance of mesh antenna, which needs to be ensured by surface adjustment. Because the mesh antenna has variable stiffness and great flexibility, the surface may be 'non-adjustable' within the limited range of the adjustment device, in the sense that it is not possible to further improve the surface accuracy by surface adjustment. In order to directly describe the adjustment state of the surface through the structure parameters of the mesh antenna, a method of calculating the surface adjustability is proposed to quantitatively describe the degree of further adjustment of the surface. Three parameters which affect the adjustability are put forward: the adjustment force margin parameter, the adjustment amount margin parameter and the accuracy adjustable parameter. The adjustment balance equations for mesh antenna surface are established, and the relationship between surface structure parameters and influence parameters is deduced. The method of calculating the adjustability of surface by influencing parameters is given. The experimental results show that the surface adjustability can not only accurately reflect the adjustment state of the surface, but also guide the selection of the adjustment configuration, which can effectively improve the surface accuracy compared with the traditional method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110250"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143882063","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Event-triggered three-dimensional adaptive anti-disturbance IGC method for a class of flight vehicles 一类飞行器的事件触发三维自适应抗干扰IGC方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110233

Zheng Wang , Yanghong Qiu , Yuting Hao , Yunfei Bai , Likuan Qiu , Gaopeng Zhang

{"title":"Event-triggered three-dimensional adaptive anti-disturbance IGC method for a class of flight vehicles","authors":"Zheng Wang , Yanghong Qiu , Yuting Hao , Yunfei Bai , Likuan Qiu , Gaopeng Zhang","doi":"10.1016/j.ast.2025.110233","DOIUrl":"10.1016/j.ast.2025.110233","url":null,"abstract":"<div><div>This paper presents a novel event-triggered three-dimensional integrated guidance and control (IGC) methodology for flight vehicles, designed to address unmodeled dynamic disturbances and stringent state constraints. A hyperbolic tangent function is used to estimate the bounds of unmodeled disturbances, effectively managing time-varying and multi-source uncertainties. To enforce state constraints, the IGC model is augmented with a defined set of admissible states and incorporates a nonlinear transformation function, thus establishing a state-constrained integrated guidance and control (SCIGC) model. Event-triggered criteria are then developed to reduce the update rate of control commands, and the stability of the proposed event-triggered guidance and control methodology is rigorously analyzed. Additionally, it is demonstrated that the proposed event-triggered method avoids Zeno behavior. To prevent instability and numerical issues arising from the differentiation of virtual controllers, a low-pass filter is introduced. Finally, the efficacy of the proposed method is validated through Lyapunov functions and its capability to intercept tactical ballistic targets is confirmed by numerical simulations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110233"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143879103","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Low computational sequential optimization for large-scale satellite formation reconfiguration 大规模卫星编队重构的低计算顺序优化

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110232

Jihe Wang , Qiaoling Zeng , Chenglong Xu , Chengxi Zhang , Jinxiu Zhang

{"title":"Low computational sequential optimization for large-scale satellite formation reconfiguration","authors":"Jihe Wang , Qiaoling Zeng , Chenglong Xu , Chengxi Zhang , Jinxiu Zhang","doi":"10.1016/j.ast.2025.110232","DOIUrl":"10.1016/j.ast.2025.110232","url":null,"abstract":"<div><div>Large-scale satellite formations enhance mission flexibility and redundancy but also increase challenges in coordination, computational load and collision risks. This paper develops a low computational sequential optimization method for fuel-efficient and passively-safe reconfiguration. We propose using an optimal three-impulse analytical solution to identify passively unsafe satellites, thereby reducing the number of satellites that require further optimization. This analytical solution also serves as an initial guess, shrinking the search space for the optimization. The problem is then decomposed into multiple single-satellite reconfiguration subproblems, which are optimized in parallel to improve computational efficiency. Two optimization strategies for subproblems are proposed: fuel-optimal and fuel-suboptimal optimization. When passive safety requirements are not met in certain iterations, the optimization relaxes fuel constraints to prioritize safety. The sequential constraint management process dynamically adjusts the trade-off between fuel costs and passive safety based on the current scenarios. This flexibility allows the method to adapt the varying reconfiguration scenarios, since not all scenarios can meet the passive safety requirements under fuel-optimal conditions. This method provides a more scalable and flexible solution to large-scale satellite formation reconfiguration optimization over traditional centralized methods. It is particularly beneficial for medium to large satellite formations (≥100 satellites). Finally, a numerical simulation is given to verify the computational efficiency and passive safety improvements of the proposed method. The algorithm is tested on a 100-satellite formation. The passive safety parameter improved from 0.0189 to 21.1165 m, and runtime was reduced by 67% compared to centralized optimization result.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110232"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143879102","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A new distributionally robust optimization method and its application to rotor-stator clearance 一种新的分布鲁棒优化方法及其在转子-定子间隙中的应用

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110248

Xiao-Le Guan , Zhen-Xing Zeng , Hong-Shuang Li , Yuan-Zhuo Ma

{"title":"A new distributionally robust optimization method and its application to rotor-stator clearance","authors":"Xiao-Le Guan , Zhen-Xing Zeng , Hong-Shuang Li , Yuan-Zhuo Ma","doi":"10.1016/j.ast.2025.110248","DOIUrl":"10.1016/j.ast.2025.110248","url":null,"abstract":"<div><div>Robust design optimization is crucial for ensuring the normal and stable operational performance of engineering structures by considering the effects of uncertainties inherent in the production and manufacturing processes of structural components. However, current robust design optimization methods are still relatively conservative, time-consuming, and often necessitate significant sacrifice in structural performance to achieve robustness. In response to these issues, the present study proposes a novel distributionally robust optimization (DRO) method based on a two-level Kriging surrogate model. The first-level Kriging model is constructed to replace the relationship between design variables and structural response, thereby enabling the construction of ambiguity sets based on the Euclidean norm and Kullback–Leibler (KL) divergence. This transforms the inner maximization problem into a deterministic optimization. Subsequently, the second-level Kriging model is constructed to approximate the relationship between design variables and the maximum expected value so that the outer minimization problem is also degenerated into a deterministic optimization, which is then solved by subset simulation optimization. The performance of the proposed method is preliminarily validated through a numerical examples, after which its engineering practicability is demonstrated by comparing the results of DRO with those of deterministic optimization for the variation in rotor-stator clearance in a small turbine engine.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110248"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143888062","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0