Aerospace Systems最新文献_第2页

Solution separation-based fault detection and exclusion for reliable solid-state LiDAR localization 基于分离的固态激光雷达可靠定位故障检测与排除方法

Aerospace Systems Pub Date : 2026-04-15 DOI: 10.1007/s42401-026-00462-5

Tianqi Xu, Shizhuang Wang, Jiahui Liu, Chenzhang Ning, Yawei Zhai, Xingqun Zhan

{"title":"Solution separation-based fault detection and exclusion for reliable solid-state LiDAR localization","authors":"Tianqi Xu, Shizhuang Wang, Jiahui Liu, Chenzhang Ning, Yawei Zhai, Xingqun Zhan","doi":"10.1007/s42401-026-00462-5","DOIUrl":"10.1007/s42401-026-00462-5","url":null,"abstract":"<div><p>Solid-state Light Detection and Ranging (LiDAR) provides an accurate, robust, cost-effective, and lightweight localization solution for autonomous systems across aerial and ground domains operating in GNSS-challenging and GNSS-denied environments. With a pre-built map of landmarks, autonomous systems can estimate their positions using real-time LiDAR scans, a process commonly known as re-localization. However, LiDAR scans acquired in complex and dynamic environments may contain outliers, which could lead to hazardous localization errors and threaten system safety. Therefore, this paper develops an efficient Fault Detection and Exclusion (FDE) approach for solid-state LiDAR re-localization by employing Multiple Hypothesis Solution Separation (MHSS). We first analyze the fault sources for LiDAR re-localization and then develop an FDE approach to detect and exclude outliers from LiDAR scans in real time. In addition, a point cloud clustering strategy is introduced to reduce the computation complexity. Experiment results show that the proposed FDE approach mitigates the effect of outliers and enhances localization reliability.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"351 - 364"},"PeriodicalIF":0.0,"publicationDate":"2026-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261647","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Aero-engine gas-path fault diagnosis method based on multimodal feature fusion and knowledge distillation 基于多模态特征融合和知识蒸馏的航空发动机气路故障诊断方法

Aerospace Systems Pub Date : 2026-03-24 DOI: 10.1007/s42401-026-00461-6

Linhao Yang, Zhengyang Li, Yongkang Ma, Zhongyang Fei

{"title":"Aero-engine gas-path fault diagnosis method based on multimodal feature fusion and knowledge distillation","authors":"Linhao Yang, Zhengyang Li, Yongkang Ma, Zhongyang Fei","doi":"10.1007/s42401-026-00461-6","DOIUrl":"10.1007/s42401-026-00461-6","url":null,"abstract":"<div><p>This paper proposes a multimodal feature fusion approach for aero-engine gas-path fault diagnosis. By designing a multimodal feature fusion model, temporal fault data are transformed into Gramian Angular Summation Field (GASF) images and Recurrence Plot (RP) images. GASF images capture global trends, while RP images highlight local nonlinear characteristics, thereby enhancing fault recognition and overall algorithm performance. Experimental results demonstrate that this approach improves diagnostic accuracy compared with single-modality networks. Furthermore, a lightweight student model is constructed to substantially reduce model parameters and memory usage, while knowledge distillation (KD) ensures the diagnostic accuracy of the student model. By further integrating logit and feature distillation and employing reinforcement learning for automatic weight optimization, the student model achieves accuracy comparable to or even surpassing that of the teacher model. Compared with the independently trained teacher model, the parameter count is reduced by 93.78%; compared with the independently trained student model, accuracy increased by 11.09%. These results validate the effectiveness of the proposed method and provide a practical reference for aero-engine gas-path fault diagnosis.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"329 - 350"},"PeriodicalIF":0.0,"publicationDate":"2026-03-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-026-00461-6.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261626","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Machine learning-based fault diagnosis of control moment gyroscopes in spacecraft three-axis attitude control systems 基于机器学习的航天器三轴姿态控制系统控制力矩陀螺仪故障诊断

Aerospace Systems Pub Date : 2026-03-23 DOI: 10.1007/s42401-025-00438-x

T. S. Abdel Aziz, S. Hussein, M. S. Mohamed, G. I. Salama

{"title":"Machine learning-based fault diagnosis of control moment gyroscopes in spacecraft three-axis attitude control systems","authors":"T. S. Abdel Aziz, S. Hussein, M. S. Mohamed, G. I. Salama","doi":"10.1007/s42401-025-00438-x","DOIUrl":"10.1007/s42401-025-00438-x","url":null,"abstract":"<div>\u0000 \u0000 <p>“Control Moment Gyroscopes (CMGs) are integral components of a spacecraft’s Attitude Determination and Control System (ADCS), the subsystem responsible for determining the spacecraft’s orientation in space and executing precise attitude maneuvers. Owing to their high torque efficiency, CMGs are widely used in modern spacecraft; however, faults in these actuators can critically degrade mission performance. These vulnerabilities highlight the urgent need for advanced Fault Detection, Isolation, and Identification (FDII) techniques. Existing FDII methods often detect only the presence of a fault without identifying its specific type, limiting the effectiveness of corrective actions. This paper presents a two-stage machine learning-based FDII framework. In the first stage, the framework detects and isolates the faulty CMG with high accuracy, while the second stage classifies fault types such as voltage-related, current-related, and compound anomalies. The framework was evaluated using two high-fidelity simulation datasets comprising 640 multivariate time-series samples, each containing 10,001 time steps per CMG operating condition. The proposed methods achieved fault detection and isolation (FDI) accuracies of 85.0–94.4<span>(%)</span>, compared to 62.0–93.5<span>(%)</span> for state-of-the-art techniques, and FDII accuracies of 91.0–95.7<span>(%)</span>, demonstrating superior reliability and diagnostic depth. This detailed diagnosis enables faster and more targeted fault-tolerant control, supporting mission continuity, extending spacecraft operational lifespan, and enhancing onboard autonomy.”</p>\u0000 </div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"213 - 223"},"PeriodicalIF":0.0,"publicationDate":"2026-03-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261953","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Health monitoring of carbon fiber structural batteries based on resistive networks 基于电阻网络的碳纤维结构电池健康监测

Aerospace Systems Pub Date : 2026-03-13 DOI: 10.1007/s42401-026-00448-3

Jiangman Ma, Haitao Zhao, Mingqing Yuan, Yukui Wang, Xiaochu Gao, Yufan Wang, Ji’an Chen

{"title":"Health monitoring of carbon fiber structural batteries based on resistive networks","authors":"Jiangman Ma, Haitao Zhao, Mingqing Yuan, Yukui Wang, Xiaochu Gao, Yufan Wang, Ji’an Chen","doi":"10.1007/s42401-026-00448-3","DOIUrl":"10.1007/s42401-026-00448-3","url":null,"abstract":"<div>\u0000 \u0000 <p>Carbon fiber structural batteries, as multifunctional composites integrating mechanical load-bearing, energy storage, and self-sensing capabilities, enable energy storage while maintaining load-bearing performance. By utilizing solid-state systems, they enhance operational safety, significantly improve lightweighting and space utilization, and demonstrate broad application prospects in aerospace and electric vehicles. However, these materials endure coupled effects of mechanical loading and electrochemical reactions during service. Damage not only reduces structural load-bearing capacity but may also compromise energy storage safety. Therefore, real-time, in-situ health monitoring is crucial for reliability assessment and lifespan prediction. This paper proposes an electrical resistivity tomography (ERT) method based on the intrinsic conductivity of the material, enabling structural health monitoring of carbon fiber structural batteries during energy storage. The forward problem constructs control equations by modeling the battery as an equivalent resistive network, with finite element simulation verifying its convergence. The inverse problem employs the Levenberg–Marquardt algorithm for iterative inversion. Experimental results demonstrate the method’s ability to accurately identify damaged regions under battery energy storage conditions, validating its feasibility and effectiveness. This research provides a novel approach for integrated load-bearing, energy storage, and self-monitoring applications in carbon fiber structural batteries, offering significant reference value for their engineering implementation and service safety assurance.</p>\u0000 </div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"317 - 328"},"PeriodicalIF":0.0,"publicationDate":"2026-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261644","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Resilient attitude control under sensor-actuator faults via varying-self-learning observers 基于可变自学习观测器的传感器-执行器故障下的弹性姿态控制

Aerospace Systems Pub Date : 2026-03-02 DOI: 10.1007/s42401-025-00443-0

Chengxi Zhang, Ruiqiu Lu, Tianle Yin, Zhijian He, Lining Tan, Bing Huang, Dezhi Xu

引用次数: 0

Command filter based active fault tolerant control of missiles intercepting maneuvering target 基于命令滤波的导弹拦截机动目标主动容错控制

Aerospace Systems Pub Date : 2026-02-26 DOI: 10.1007/s42401-026-00447-4

Abdulrazaq Nafiu Abubakar, Ali Nasir, Abdul-Wahid A. Saif

{"title":"Command filter based active fault tolerant control of missiles intercepting maneuvering target","authors":"Abdulrazaq Nafiu Abubakar, Ali Nasir, Abdul-Wahid A. Saif","doi":"10.1007/s42401-026-00447-4","DOIUrl":"10.1007/s42401-026-00447-4","url":null,"abstract":"<div>\u0000 \u0000 <p>This paper presents a command filtered based active fault-detection and correction scheme for integrated guidance and control (IGC) of a supersonic skid-to-turn interceptor. It utilizes global terminal sliding mode (GTSMC), command filter, backstepping control, and extended state observer (ESO). The IGC technique accounts for the delay dynamics of the actuator subsystem and addresses constraints related to the impact angle. A strict-feedback IGC model is developed, including delayed rudder dynamics. Fault detection and estimation observers are designed to detect the presence and magnitude of faults in the rudder subsystem. The backstepping-based guidance and fault-tolerant control system comprises guidance, attitude, normal overload, and rudder subsystem. The guiding subsystem uses GTSMC to facilitate rapid convergence of the impact angle. The ESO effectively measures and compensates for lumped disturbances with target maneuver, external disturbances, and aerodynamic parameters. The stability of the IGC system is proven, and simulation results show superior performance compared to existing methods.</p>\u0000 </div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"285 - 299"},"PeriodicalIF":0.0,"publicationDate":"2026-02-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261740","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Research on a surrogate model and sensitivity analysis for aircraft icing under intermittent maximum icing conditions based on random forest 基于随机森林的间歇最大结冰条件下飞机结冰替代模型及敏感性分析

Aerospace Systems Pub Date : 2026-02-04 DOI: 10.1007/s42401-025-00432-3

Chao Xi, Tingting Cheng, Shumin Pu, Xiaoliang Wang

{"title":"Research on a surrogate model and sensitivity analysis for aircraft icing under intermittent maximum icing conditions based on random forest","authors":"Chao Xi, Tingting Cheng, Shumin Pu, Xiaoliang Wang","doi":"10.1007/s42401-025-00432-3","DOIUrl":"10.1007/s42401-025-00432-3","url":null,"abstract":"<div><p>Aircraft icing can significantly degrade aerodynamic performance and compromise flight safety, highlighting the need for efficient prediction of icing characteristics and critical influencing factors. In this study, a structured set of icing simulation parameters was defined by identifying key variables and constraining their ranges in accordance with airworthiness requirements of intermittent maximum icing conditions. According to the simulation results, it concludes that heavier ice accretion leads to increased surface roughness and consequently more severe aerodynamic degradation under the intermittent maximum icing conditions. Within this admissible domain, representative samples were generated and applied to FENSAP-ICE to simulate ice accretion on the reference aircraft airfoil, thereby constructing a comprehensive icing dataset with the iced mass as the output response. Based on this dataset, a surrogate model employing the Random Forest algorithm was developed, enabling rapid and reliable prediction of icing outcomes. Furthermore, sensitivity analysis was conducted to identify the dominant parameters governing the icing process, offering valuable insights into the core factors that critically influence aircraft icing behavior.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"199 - 211"},"PeriodicalIF":0.0,"publicationDate":"2026-02-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375189","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Robust state estimation for radar localization systems based on sensitivity penalization 基于灵敏度惩罚的雷达定位系统鲁棒状态估计

Aerospace Systems Pub Date : 2026-01-14 DOI: 10.1007/s42401-025-00439-w

Yuhao Cui, Huabo Liu

引用次数: 0

Mach number effect on the high-amplitude Richtmyer–Meshkov instability using the DSMC method 马赫数对高振幅richmyer - meshkov不稳定性的影响

Aerospace Systems Pub Date : 2026-01-07 DOI: 10.1007/s42401-025-00434-1

Yan Liu, Hao Chen

{"title":"Mach number effect on the high-amplitude Richtmyer–Meshkov instability using the DSMC method","authors":"Yan Liu, Hao Chen","doi":"10.1007/s42401-025-00434-1","DOIUrl":"10.1007/s42401-025-00434-1","url":null,"abstract":"<div>\u0000 \u0000 <p>This study conducts a numerical investigation of the Richtmyer–Meshkov instability (RMI) at microscale Helium/Argon interfaces using the Direct Simulation Monte Carlo (DSMC) method. The hydrodynamic behaviour and evolutionary mechanisms governing the single-mode RMI with high-amplitude are discussed, with the consideration of different Mach numbers (<i>Ma</i>) ranging from 1.5 to 6.0. Key findings reveal two distinct evolutionary pathways. In the high-Mach regime (<i>Ma</i> ≥ 3), complex shock configurations form through the establishment of Mach stem, accompanied by sustained positive vorticity deposition along the slipstream. This persistent process drives cavity initiation at spike apices. In the low-Mach regime (<i>Ma</i> ≤ 2), gradual degradation of Mach stem to regular reflection configurations occurs, wherein viscous dissipation extinguishes the vorticity accumulation and suppresses cavity formation. Quantitative comparison with DSMC data demonstrates that the Zhang and Guo (ZG) theoretical model has a prediction error of less than 20% for the overall amplitude growth of RMI across different <i>Ma</i> numbers, yet overestimates the bubble amplitude growth with a prediction error of approximately 50%, particularly in the late nonlinear stage. A dedicated discussion on gas species is also presented, revealing that the ZG theoretical model aligns well with the DSMC-calculated overall amplitude growth at high <i>Ma</i> numbers, with relative errors below 20%. Furthermore, the influence of <i>Ma</i> on the discrepancy between ZG model predictions and DSMC data diminishes as the Atwood number increases.</p>\u0000 </div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"185 - 198"},"PeriodicalIF":0.0,"publicationDate":"2026-01-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375188","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Orbit maintenance of LEO satellites with Hall-effect thrusters subjected to loss of effectiveness using robusst model predictive control 基于鲁棒模型预测控制的低轨道霍尔效应推进器失效卫星的轨道维护

Aerospace Systems Pub Date : 2026-01-07 DOI: 10.1007/s42401-025-00426-1

Hosna Rahimi, Fatemeh Jahangiri, Mostafa Abedi

{"title":"Orbit maintenance of LEO satellites with Hall-effect thrusters subjected to loss of effectiveness using robusst model predictive control","authors":"Hosna Rahimi, Fatemeh Jahangiri, Mostafa Abedi","doi":"10.1007/s42401-025-00426-1","DOIUrl":"10.1007/s42401-025-00426-1","url":null,"abstract":"<div><p>In this paper, a Robust Model Predictive Control (RMPC) method for orbit maintenance of low earth orbit (LEO) satellites with Hall-effect thrusters (HET) is developed. Due to the ability to produce continuous time thrust by the Hall effect thruster, continuous control commands which are updated online are applied to the satellite for the mission. The proposed RMPC method also accounts for loss of thruster effectiveness to enhance system performance despite the potential unknown efficiency decreases. This approach ensures the robust stability and H-infinity performance despite various unknown external disturbances like the Earth’s non-spherical gravitational field, atmospheric drag, solar and lunar gravity, and solar radiation pressure perturbations. Furthermore, uncertainties are incorporated to capture variable flight parameters and the osculating behavior of orbital elements. The cost function is defined to minimize fuel consumption and counteract disturbance effects. Multiple constraints, such as limited HET force production and orbit maintenance within an allowable window, are included in the optimization problem. The control design also addresses misalignments, and errors from thrusters. Furthermore, we will demonstrate in the paper that the proposed RMPC method achieves a reduction of approximately 65% in monthly fuel consumption and a 58–93% decrease in the RMS of orbital elements errors compared with the LQR controller. Through numerical simulations, the effectiveness and validity of this control method are confirmed.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"257 - 272"},"PeriodicalIF":0.0,"publicationDate":"2026-01-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-025-00426-1.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261841","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0