Aerospace Systems最新文献_第7页

AGD-YOLO: a forward-looking sonar target detection method with attention-guided denoising convolutional neural network AGD-YOLO：一种基于注意引导去噪卷积神经网络的前视声纳目标检测方法

Aerospace Systems Pub Date : 2025-03-06 DOI: 10.1007/s42401-025-00352-2

Shuangjie Fu, Han Pan, Jianzhe Huang, Xuyang Zhang, Zhongliang Jing

{"title":"AGD-YOLO: a forward-looking sonar target detection method with attention-guided denoising convolutional neural network","authors":"Shuangjie Fu, Han Pan, Jianzhe Huang, Xuyang Zhang, Zhongliang Jing","doi":"10.1007/s42401-025-00352-2","DOIUrl":"10.1007/s42401-025-00352-2","url":null,"abstract":"<div><p>Underwater target detection is a critical and rapidly evolving research area with significant applications in both military and civilian fields. Multi-Beam Forward-Looking Sonar (MFLS) operates reliably in low-visibility conditions and is one of the most widely used technologies for underwater detection. However, the complex and dynamic underwater environment, signal attenuation and distortion, along with the high cost of signal acquisition and transmission, make MFLS images detection one of the most challenging tasks in computer vision and image processing. To address these challenges, this paper proposes a target detection model based on MFLS, named AGD-YOLO. First, the ADNet attention mechanism is introduced to enhance performance by focusing on relevant features while suppressing unrelated noise. This denoising mechanism balances efficiency and further improves the model’s detection performance. Second, MPDIoU is adopted as the boundary regression loss, which considers the overlapping region, center point distance, and deviations in width and height, thereby enhancing the efficiency and accuracy of bounding box regression. Third, a new dataset based on MFLS is constructed to facilitate the detection of Unmanned Underwater Vehicle (UUV). Experimental results show that the proposed model improves <span>({mAP}_{0.5:0.95})</span> by 2.6% compared to the second-best detection algorithm, significantly enhancing detection performance on MFLS images.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 4","pages":"809 - 824"},"PeriodicalIF":0.0,"publicationDate":"2025-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145537769","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

Boundary criterion of vortex ring state for axially descending BO-105 rotor based on unsteady momentum source method 基于非定常动量源法的BO-105转子轴向下降涡环状态边界判据

Aerospace Systems Pub Date : 2025-02-27 DOI: 10.1007/s42401-024-00340-y

Yanqing Qi, Gaohua Li, Fuxin Wang

引用次数: 0

Choice of design solutions for separating the payload from the launch vehicle without using pyrotechnic elements 在不使用烟火元件的情况下将有效载荷与运载火箭分离的设计方案的选择

Aerospace Systems Pub Date : 2025-02-20 DOI: 10.1007/s42401-025-00348-y

Vladimir Yu. Ermakov, Ant Tufan, Sergey O. Firsyuk

{"title":"Choice of design solutions for separating the payload from the launch vehicle without using pyrotechnic elements","authors":"Vladimir Yu. Ermakov, Ant Tufan, Sergey O. Firsyuk","doi":"10.1007/s42401-025-00348-y","DOIUrl":"10.1007/s42401-025-00348-y","url":null,"abstract":"<div><p>The paper presents a selection of rational design solutions for payload separation devices from the last stage of the launch vehicle without using pyrotechnic elements (spring, bandage and pneumatic pin-based types). An overview and analysis of the applicability of various options for separation devices as part of existing disposable and reusable launch vehicles is presented, as a result of which the growing need for using separation devices without pyrotechnics is revealed due to the need to ensure shock-free separation and rescue of the payload in case of an emergency, as well as increased requirements for reducing the number of pyrotechnic elements due to possible risk fire or explosion during transportation, launch and separation of the payload. The methods of reducing the influence of disturbing factors leading to a deviation of the calculated parameters of the payload motion during launch into a given orbit are considered. It has been established that one of the effective methods to reduce these disturbances is to ensure a minimum time delay between the shutdown of the propulsion system of the last stage and the separation of the payload, which is selected from the after action pulse decline in order to reduce the loss of work of the separation device for its parrying. Mathematical modeling of the dynamics of separation of the payload from the last stage of the launch vehicle was carried out when the proposed separation devices were triggered, while docking rings were considered as dangerous points for collision of structural elements. An analysis of the results of mathematical modeling is presented, which shows that the angular velocity of the last stage of the launch vehicle has little effect on smooth separation of the payload, while the required work when the proposed separation devices are triggered should be determined based on the required relative velocity of the payload at the time of its separation from the last stage.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"511 - 520"},"PeriodicalIF":0.0,"publicationDate":"2025-02-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871567","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

An informer approach to civil aviation hard landing prediction considering learning assurance and explainability 考虑学习保证和可解释性的民航硬着陆预测方法

Aerospace Systems Pub Date : 2025-02-20 DOI: 10.1007/s42401-024-00335-9

Lei Dong, Xinqi Peng, Xi Chen, Jiachen Liu

{"title":"An informer approach to civil aviation hard landing prediction considering learning assurance and explainability","authors":"Lei Dong, Xinqi Peng, Xi Chen, Jiachen Liu","doi":"10.1007/s42401-024-00335-9","DOIUrl":"10.1007/s42401-024-00335-9","url":null,"abstract":"<div><p>Predicting hard landings is crucial for aiding pilots’ decisions and ensuring flight safety. This paper addresses the limitations of current hard landing prediction models, specifically in terms of long-term forecasting accuracy and explainability. To overcome these challenges, it introduces the Informer hard landing prediction model, developed using QAR data, and performs an in-depth explainability analysis of the model’s output. Following the principles of learning assurance, the data processing and model training phases are standardized. This involves the application of forward–backward filtering and Granger causality testing to refine the QAR data, thus creating a dataset that aligns with essential prediction standards. The Informer model addresses the challenges of multivariate time series discontinuities by localizing its network to enhance data adaptability. During model training and testing, hyperparameters are finely tuned to maximize prediction accuracy and generalizability. To improve transparency, the model employs an attention weight matrix and a feature reset-based explainability method. Tests show that models trained on datasets developed through a defined data management process deliver favorable predictive performance. The localized enhanced network improved prediction accuracy by 23.5% and increased its capacity to learn from discontinuous multivariate time series. Compared to the LSTM network, the Informer network achieved an 18.83% improvement in prediction accuracy and demonstrated superior long-time series prediction capabilities.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 4","pages":"789 - 807"},"PeriodicalIF":0.0,"publicationDate":"2025-02-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145537812","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 status assessment of electrical measuring equipment for aircraft based on Analytical Hierarchy Process 基于层次分析法的飞机电气测量设备健康状态评价

Aerospace Systems Pub Date : 2025-02-18 DOI: 10.1007/s42401-025-00349-x

Qifan Yin, Sheng Cheng, Youbing Chu, Zhongliang Jing

{"title":"Health status assessment of electrical measuring equipment for aircraft based on Analytical Hierarchy Process","authors":"Qifan Yin, Sheng Cheng, Youbing Chu, Zhongliang Jing","doi":"10.1007/s42401-025-00349-x","DOIUrl":"10.1007/s42401-025-00349-x","url":null,"abstract":"<div><p>There are about 1,900 electrical measuring equipment in the aircraft assembly workshop and aircraft production line, which is directly related to the manufacturing quality of the aircraft. This paper evaluates the health status of electrical measuring equipment based on Analytical Hierarchy Process. The bottom-up health status evaluation system of electrical measuring equipment is established by selecting an appropriate number of health indicators. According to the failure mode summary of electrical measuring equipment, the evaluation indexes at all levels are determined, the health assessment and judgment matrix of electrical measuring equipment is constructed. The 1–9 scale method is used for quantitative analysis of the indexes of electrical measuring equipment. The health level of the electrical measuring equipment is divided into 5 levels, and the corresponding relationship between the score of the measuring equipment and the health status is formulated. The 0–1 method and fuzzy distribution method are used to score each quantitative index. The historical data of a company electrical measuring equipment is used for example analysis, and the example results show that the calculation results of the health status score of the general measuring equipment is 0.951. The health status of the general measuring equipment is health. The health status score of the special measurement equipment is 0.877. The health status of the aviation specific measuring equipment is available.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 4","pages":"775 - 787"},"PeriodicalIF":0.0,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145537835","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

Development of a separation device as part of a promising launch vehicle without using pyrotechnics 一种分离装置的发展，作为一个有前途的运载火箭的一部分，不使用烟火

Aerospace Systems Pub Date : 2025-02-18 DOI: 10.1007/s42401-025-00347-z

Sergey O. Firsyuk, Vladimir Yu. Ermakov, Ant Tufan, Denis V. Vasikov

{"title":"Development of a separation device as part of a promising launch vehicle without using pyrotechnics","authors":"Sergey O. Firsyuk, Vladimir Yu. Ermakov, Ant Tufan, Denis V. Vasikov","doi":"10.1007/s42401-025-00347-z","DOIUrl":"10.1007/s42401-025-00347-z","url":null,"abstract":"<div><p>The paper develops and investigates various options for separating the first and second stages of a promising launch vehicle without using pyrotechnic elements (such as the “Clamp Band” type, “petal” and “ball” types). A review and analysis of the applicability of pyrotechnic elements as part of separation devices of existing and promising launch vehicles was carried out, as a result, it was revealed that their use is difficult for technological reasons related to the need for specialized devices and equipment for accurate control of the detonation process and the likelihood of a large number of fragments and shock loads during operation, which negatively affects the provision of specified structural and operational characteristics of launch vehicles. The basic requirements for ensuring the rational operation of the proposed separation devices, taking into account the possibility of their multiple use, are considered. Experimental and mathematical modeling of relative motion of the stages separating according to the “cold” scheme under the influence of static and dynamic loads has been carried out, and rational technical solutions and design and technological approaches for the proposed separation devices have been selected. The results of the research on assessment of the stress–strain state of structural elements of the proposed separation devices without using pyrotechnic elements in various configurations, as well as their novelty, are presented.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 4","pages":"763 - 774"},"PeriodicalIF":0.0,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145537768","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

Sound field reconstruction of aero-engine fans using hierarchical Bayesian algorithms 基于层次贝叶斯算法的航空发动机风扇声场重建

Aerospace Systems Pub Date : 2025-02-07 DOI: 10.1007/s42401-025-00345-1

Bohan Ma, Meng Wang, Mingsui Yang, Wei Ma

{"title":"Sound field reconstruction of aero-engine fans using hierarchical Bayesian algorithms","authors":"Bohan Ma, Meng Wang, Mingsui Yang, Wei Ma","doi":"10.1007/s42401-025-00345-1","DOIUrl":"10.1007/s42401-025-00345-1","url":null,"abstract":"<div><p>Acoustic field reconstruction for aircraft engine fans is essential for effective noise reduction. However, the use of a limited number of far-field measurement points in the reconstruction process exacerbates the ill-posedness issues, which necessitates the adoption of regularization techniques. The hierarchical Bayesian-based regularisation method has recently been applied to solve the equivalent source intensity distribution and reconstruct the sound field. However, previous methods have failed to accurately obtain the acoustic modal coefficients of the sound source, which are essential for determining the radiation type and directivity. This paper proposes a sound field reconstruction method that applies the hierarchical Bayesian algorithm to the source modal coefficient solution. Firstly, the deconvolution beamforming method obtains the sound source position. Subsequently, the hierarchical Bayesian algorithm is employed to obtain the source modal coefficients of the sound field, thereby completing the reconstruction of the sound field in the far-field region. Experimental results indicate that the proposed algorithm is highly effective in reconstructing far-field sound fields. Under free-field conditions and in mid-high frequency ranges, the average reconstruction error can be significantly reduced by using a few far-field microphones compared to traditional methods.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 2","pages":"257 - 274"},"PeriodicalIF":0.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145142589","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

A conceptual approach to ensure the reliability of separation devices for promising launch vehicles without using pyrotechnics 在不使用烟火的情况下保证有前途运载火箭分离装置可靠性的概念方法

Aerospace Systems Pub Date : 2025-02-03 DOI: 10.1007/s42401-025-00346-0

Sergey O. Firsyuk, Vladimir Yu. Ermakov, Ant Tufan, Aleksey V. Kurguzov

引用次数: 0

An intelligent energy management system for enhanced performance in electric UAVs 一种用于增强电动无人机性能的智能能源管理系统

Aerospace Systems Pub Date : 2025-01-26 DOI: 10.1007/s42401-025-00343-3

Mohamed S. Elkerdany, Ibrahim M. Safwat, Ahmed Medhat M. Youssef, Mohamed M. Elkhatib

{"title":"An intelligent energy management system for enhanced performance in electric UAVs","authors":"Mohamed S. Elkerdany, Ibrahim M. Safwat, Ahmed Medhat M. Youssef, Mohamed M. Elkhatib","doi":"10.1007/s42401-025-00343-3","DOIUrl":"10.1007/s42401-025-00343-3","url":null,"abstract":"<div><p>Unmanned aerial vehicles (UAVs) propelled by electricity have emerged as a prominent concept in aviation due to their eco-friendly and stealth characteristics. To address the limitations of Polymer Membrane Fuel Cell (PMFC), which serve as the primary power source but exhibit sluggish responses to sudden load changes, this research proposes a novel hybrid power system incorporating a Li-Ion battery. This hybrid setup ensures superior dynamic response while maintaining high power-to-weight efficiency. This paper presents an intelligent energy management system (EMS), which effectively regulates power flow between the PMFC and Li-Ion battery through a multi-input multi-output (MIMO) control framework. The uniqueness of this study lies in the comparative evaluation of two advanced EMS control strategies: Fuzzy Logic Control and the Adaptive Neuro-Fuzzy Inference System (ANFIS), under multiple flight modes. By thoroughly analyzing system transients and dynamic behaviors using MATLAB/SIMULINK, this work provides a detailed insight into optimizing UAV power efficiency. Unlike previous studies, this research highlights the distinct advantages and limitations of each control strategy for different flight phases, providing a comprehensive benchmark for future EMS designs in UAV applications.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 3","pages":"701 - 716"},"PeriodicalIF":0.0,"publicationDate":"2025-01-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145057677","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

Systematic computational probe of Fish Bone Morphing geometry for optimal airfoil performance 鱼骨变形几何优化翼型性能的系统计算探针

Aerospace Systems Pub Date : 2025-01-23 DOI: 10.1007/s42401-024-00339-5

Ritesh Mane, Mansi Sharma, Yash Mahore, Rinku, Rohit Kumar Prasad, Challa Parvathi Rudesh

{"title":"Systematic computational probe of Fish Bone Morphing geometry for optimal airfoil performance","authors":"Ritesh Mane, Mansi Sharma, Yash Mahore,  Rinku, Rohit Kumar Prasad, Challa Parvathi Rudesh","doi":"10.1007/s42401-024-00339-5","DOIUrl":"10.1007/s42401-024-00339-5","url":null,"abstract":"<div><p>This study investigates the potential of Fish Bone Morphing (FBM) technology for enhancing the aerodynamic performance of aerofoils. FBM is a bio-inspired concept that incorporates flexible structural elements to facilitate morphing of the aerofoil shape in response to varying flight conditions. The NACA 2412 aerofoil is chosen for its camber adaptability, and CFD simulations are employed to assess the efficacy of FBM integration. The k–ω SST turbulence model is adopted for its ability to combine the strengths of the k–ω and k–ε models. The investigation encompasses a systematic exploration of geometric configurations, including trailing edge deflection at various chord lengths (0.6c, 0.65c, 0.70c, 0.75c, and 0.80c) and deflection angles (4°, 8°, and 12°). The results reveal that FBM aerofoils exhibit a consistent increase in maximum lift coefficient compared to conventional aerofoils across all deflection points and angles. Additionally, improvements in lift-to-drag ratio are observed. Furthermore, the stalling angle remains unaffected by deflection point variations, while deflection angle increments lead to corresponding increases in maximum lift coefficient. The morphing aerofoil with a 0.60c deflection point demonstrates the most significant enhancement in maximum lift coefficient, achieving a 13% increase at a 12° deflection angle. These findings establish the aerodynamic efficiency of FBM aerofoils, characterized by superior lift-to-drag ratios and increased maximum lift coefficients.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 3","pages":"683 - 699"},"PeriodicalIF":0.0,"publicationDate":"2025-01-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145057725","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