Aerospace Systems最新文献

{"title":"Research on real-time trajectory optimization methods for stratospheric airships based on deep learning","authors":"Tianshu Wang,&nbsp;Zhiqiang Peng,&nbsp;Quanbao Wang","doi":"10.1007/s42401-024-00315-z","DOIUrl":"10.1007/s42401-024-00315-z","url":null,"abstract":"<div><p>Stratospheric airships are a type of large aircraft capable of operating for extended periods in the stratosphere. This paper focuses on real-time trajectory planning for stratospheric airships. It constructs an optimization path dataset based on the Gauss pseudospectral method and utilizes deep learning neural networks to solve the real-time path planning problem for stratospheric airships. The article first establishes a six-degree-of-freedom airship spatial motion model. It uses the Gauss pseudospectral method to transform the original optimization problem into a parameter optimization problem, which is then solved using sequential quadratic programming. During the ascent phase, based on the airship's speed, yaw angle, and pitch angle when transitioning from the troposphere to the stratosphere, a total of 26,901 optimized paths are generated using the Gauss pseudospectral method, and the influence of different initial states on the optimized paths is analyzed. During the level flight phase, 3960 optimized paths are generated based on different initial speeds and yaw angles, and an analysis of the impact of the initial yaw angle on the optimized paths is conducted. Finally, the dataset generated by the Gauss pseudospectral method is divided into training and testing sets. Long short-term memory (LSTM) networks and Transformer networks are employed to learn and generate optimized paths from the dataset. Comparison results show that the neural network model is highly consistent with the optimized paths obtained using the Gauss pseudospectral method. Furthermore, the path generation time is reduced from hundreds of seconds to seconds, leading to a significant improvement in generation time stability.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 4","pages":"771 - 789"},"PeriodicalIF":0.0,"publicationDate":"2024-08-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142519120","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}

{"title":"Data-driven dynamic health index construction for diagnosis and prognosis of Engine Bleed Air system","authors":"Yilin Wang,&nbsp;Honghua Zhao,&nbsp;Wei Cheng,&nbsp;Yuxuan Zhang,&nbsp;Lei Jia,&nbsp;Yuanxiang Li","doi":"10.1007/s42401-024-00318-w","DOIUrl":"10.1007/s42401-024-00318-w","url":null,"abstract":"<div><p>The Engine Bleed Air system is a critical component in aircraft operations, providing necessary air supply for various onboard systems. Failures in the Engine Bleed Air (EBA) System can lead to flight delays, extended downtime, and safety risks. The current practice of using fixed pressure thresholds for EBA monitoring has limitations in terms of maintenance efficiency and aircraft safety. This paper presents a data-driven approach to dynamic thresholding and health index construction for the Airbus A330 EBA. A substantial EBA flight dataset is constructed using Quick Access Recorder (QAR) data, incorporating normal and faulty states. To explore the extensive QAR data of the EBA system, a data-driven baseline mining model is proposed in this study. To efficiently process high-dimensional feature data and model the pressure baseline, the LightGBM tree-based algorithm is employed. Additionally, this study proposes a health index (HI) construction method based on the baseline model, along with the EBA diagnosis and prognosis experiments based on the HI index. The Diagnosis and Prognosis methods, utilizing the proposed HI, demonstrate superior diagnostic effectiveness compared to fixed threshold methods and uncover a clearer trend of EBA health degradation. These contributions highlight the potential of data-driven approaches in managing aircraft EBA systems, emphasizing the advantages of dynamic thresholds and health index models for improved diagnosis and prognosis.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"149 - 161"},"PeriodicalIF":0.0,"publicationDate":"2024-08-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00318-w.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143581098","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}

{"title":"Liquid propellant sloshing characteristics and suppression in new-generation space vehicle","authors":"Peng-fei Guo,&nbsp;Zi-an Wang,&nbsp;Rui Shi,&nbsp;Yang Yang,&nbsp;Hui-fang Huo,&nbsp;Chengxi Zhang","doi":"10.1007/s42401-024-00317-x","DOIUrl":"10.1007/s42401-024-00317-x","url":null,"abstract":"<div><p>Given the complex flight mission and structural characteristics of special-shaped tanks in new-generation space vehicles, this study investigates the sloshing characteristics and suppression methods of liquid propellant. Initially, the numerical calculation and structural suppression approaches for liquid propellant periodic sloshing are introduced. Subsequently, a new equivalent dynamic analysis approach based on the Volume of Fluid (VOF) method is presented and validated to simulate liquid sloshing and determine dynamic characteristic parameters such as sloshing mass, frequency, and damping ratio. Furthermore, anti-sloshing baffles are designed for sloshing suppression, and the influence of baffle height on sloshing frequency and damping ratio is examined. These significant findings provide crucial references and foundations for enhancing the flight stability and reliability of the attitude control system in new-generation space vehicles.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 4","pages":"791 - 799"},"PeriodicalIF":0.0,"publicationDate":"2024-08-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00317-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142518384","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}

{"title":"Effectiveness evaluation of shipboard manned/unmanned aerial vehicle synergy based on CFP-miner","authors":"Gechen Wang,&nbsp;Ling Peng,&nbsp;Miao Wang,&nbsp;Guoqing Wang","doi":"10.1007/s42401-024-00310-4","DOIUrl":"10.1007/s42401-024-00310-4","url":null,"abstract":"<div><p>With the development of artificial intelligence and information technology, drones working in tandem with manned aerial vehicle have become the new normal. Current paper focuses on the following theme: how to assess the effectiveness of manned/unmanned aerial vehicle systems under different formations. However, the analysis of the effectiveness of manned/unmanned aircraft cooperation faces the problem of unclear mechanisms and difficulty in tracing the key influencing factors. Therefore, in this paper, a closed frequent pattern mining method is used to analyze and design a new data structure based on cross-linked table improvement. In this paper, the units and capabilities in the manned/unmanned aerial vehicle system are mined and analyzed in a time-series manner to obtain the effectiveness of the patterns of manned/unmanned aircraft utilization in tandem under different formations. Finally, a typical maritime application scenario is used as an example to effectively compare the effectiveness of different manned/unmanned aircraft cooperative modes and to provide guidance for the subsequent development of manned/unmanned aircraft cooperative applications.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"191 - 205"},"PeriodicalIF":0.0,"publicationDate":"2024-07-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00310-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141658302","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}

{"title":"Application of digital image correlation in aerospace engineering: structural health monitoring of aircraft components","authors":"Ravindra Mallya,&nbsp;Amol Kiran Uchil,&nbsp;Satish B. Shenoy,&nbsp;Anand Pai","doi":"10.1007/s42401-024-00309-x","DOIUrl":"10.1007/s42401-024-00309-x","url":null,"abstract":"<div><p>Digital Image Correlation (DIC) is a vital optical measurement technique that finds diverse applications in the domain of mechanics of materials. In aerospace applications, DIC has excellent scope in structural health monitoring of aircraft components. Aircraft wings, one of the critical components are subjected to different loads during flight. Ground testing and In-flight testing of wings can benefit substantially by DIC monitoring. DIC can be utilized to analyze the time-based variation in the speckle pattern or grid, applied to the wing’s surface. High-resolution images processed through a suitable correlation software helps decipher the data into stress and strain contours. Thus, any potential material failure or component defects can be identified. DIC also finds a role in flutter analysis, enabling the scrutiny of wing vibrations and deformations. In this review, the applications of DIC in analysis of aircraft components has been taken up, as in-flight structural health monitoring is a critical activity for a safe flight.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 4","pages":"663 - 675"},"PeriodicalIF":0.0,"publicationDate":"2024-07-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00309-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141686411","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}

{"title":"Modeling and PIL-based design for AGV flight control system","authors":"Mohamed Ibrahim Mohamed,&nbsp;Ehab Safwat,&nbsp;Yehia Z. Elhalwagy","doi":"10.1007/s42401-024-00306-0","DOIUrl":"10.1007/s42401-024-00306-0","url":null,"abstract":"<div><p>Aerial Gliding Vehicles (AGVs) play a crucial role in military operations owing to their versatile and multipurpose capabilities. Achieving accurate modeling of AGVs is paramount for understanding their behavior and optimizing performance. While nonlinear models excel in capturing intricate phenomena, their complexity and computational demands make them less suitable for control system design. Hence, the utilization of linear models becomes imperative, offering a more comprehensible depiction of AGV dynamics and facilitating effective control system analysis and design. This study aims to develop a precise linear model for AGVs, providing a clear and interpretable framework for analysis and control system development. The constructed linear model serves as the foundation for devising various control strategies, significantly enhancing our comprehension of AGV behavior. Moreover, a comprehensive investigation into the AGV’s actuation system is conducted, employing advanced system identification techniques to establish an accurate actuation model. This phase is critical for ensuring the precise and efficient operation of the control system. The research encompasses the design and evaluation of two distinct AGV control strategies. Firstly, the Modified Proportional-Integral-Derivative (PI-D) controller, a conventional approach widely employed in control systems, serves as a stable benchmark for comparison. Secondly, the innovative Fuzzy-PI-D (F-PI-D) controller is introduced, harnessing fuzzy logic to augment control accuracy and responsiveness, particularly advantageous for complex systems like AGVs. To validate the performance of these control strategies, the study adopts the robust Processor in the Loop (PIL) methodology, integrating LabVIEW and an embedded device to conduct reliable testing and verification of control systems in a simulated environment. PIL offers the distinct advantage of evaluating control strategies under diverse conditions without the necessity of costly and hazardous real-world flight tests. Simulation outcomes furnish valuable insights into the efficacy of these control strategies. Significantly, the F-PI-D controller emerges as the preferred choice for enhancing AGV flight stability, precision, and responsiveness, thus contributing to the advancement of AGV control systems and their utility in military operations.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"45 - 60"},"PeriodicalIF":0.0,"publicationDate":"2024-07-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00306-0.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141685391","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}

{"title":"Investigation of pitching frequency impact on stability criteria for supersonic fin stabilized missile","authors":"Fatouh Ibrahim,&nbsp;Mostafa Khalil,&nbsp;Mahmoud Y. M. Ahmed,&nbsp;M. Youssef","doi":"10.1007/s42401-024-00307-z","DOIUrl":"10.1007/s42401-024-00307-z","url":null,"abstract":"<div><p>The stability criteria of any fin-stabilized flying object are a decisive metric in evaluating its overall performance and results in mission success. Flight stability depends on many parameters such as body configuration, the center of gravity location, atmospheric conditions, and flight manoeuvres. These manoeuvres are needed for better target interception especially for moving targets located at short ranges, resulting in high frequencies either in pitch or yaw directions. This study examines the impact of body pitch frequency on the stability of a supersonic fin-stabilized object. Time-dependent numerical simulations are implemented to model the unsteady flow field induced by a simple harmonic motion in the case study missile. The missile’s tail section dominates the lift force generated compared to the forebody, resulting in a downstream shift of the missile’s center of pressure and, consequently, an increase in the static stability margin as the pitching frequency increases. However, pitch-damp aerodynamic derivatives remain unchanged at various pitching frequencies, indicating frequency independence. The validity of the results is confirmed compared with wind tunnel data.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 4","pages":"763 - 770"},"PeriodicalIF":0.0,"publicationDate":"2024-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142518658","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}

{"title":"Dynamic output feedback control strategy for a satellite orbital model within negative-imaginary systems theory framework","authors":"Santosh Kumar Choudhary,&nbsp;Shreesha Chokkadi","doi":"10.1007/s42401-024-00304-2","DOIUrl":"10.1007/s42401-024-00304-2","url":null,"abstract":"<div><p>This article presents the synthesis of a dynamic output feedback controller for a satellite orbital system confronted with uncertainties. The investigated method transforms the closed-loop system, synthesized by the controller, into an <span>(alpha )</span>-strictly negative-imaginary system. It utilizes the DC-loop gain condition associated with negative-imaginary systems theory to demonstrate robust stability of the satellite orbital system in the presence of uncertainties. Furthermore, the synthesized negative-imaginary closed-loop system exhibits notable time-domain performance. The numerical simulation outcomes presented in this article validate the investigated synthesis method.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 4","pages":"747 - 761"},"PeriodicalIF":0.0,"publicationDate":"2024-06-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00304-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141346782","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}

{"title":"Trajectory prediction for fighter aircraft ground collision avoidance based on the model predictive control technique","authors":"Shiyi Yuan,&nbsp;Qifu Li,&nbsp;Bei Lu,&nbsp;Xingjie Niu,&nbsp;Yishu Liu,&nbsp;Wei Gao","doi":"10.1007/s42401-024-00300-6","DOIUrl":"10.1007/s42401-024-00300-6","url":null,"abstract":"<div><p>Controlled flight into terrain accidents pose a significant threat to aviation safety, emphasizing the need for effective automatic ground collision avoidance system (Auto GCAS). However, the diversity and complexity of missions present considerable challenges to aircraft collision avoidance control. This paper proposes an approach for trajectory prediction based on the model predictive control (MPC) technique. Different from previous methods that rely on predefined fixed trajectories, the proposed approach incorporates constraints of aircraft state and actual terrain to generate an optimal trajectory. The safety and effectiveness of the method are demonstrated through integrating the trajectory prediction algorithm into the Auto GCAS system. The simulation results show that the MPC-based Auto GCAS can achieve optimal collision avoidance outcomes aligned with the aircraft's performance and mission needs.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"61 - 70"},"PeriodicalIF":0.0,"publicationDate":"2024-05-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00300-6.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140972781","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}

{"title":"Initial gap modeling for wing assembly analysis","authors":"Nadezhda Zaitseva,&nbsp;Sergey Lupuleac,&nbsp;Julia Shinder","doi":"10.1007/s42401-024-00302-4","DOIUrl":"10.1007/s42401-024-00302-4","url":null,"abstract":"<div><p>The aircraft wing is a complex structure consisting of many joined components. Because of the inevitable variability of the component shapes, different deviations may occur in the joining process including unreduced gaps between parts which can negatively affect the quality of further assembly. When developing the assembly process, the influence of these variations can be taken into account by considering the initial gap between the parts. For the variation analysis of the aircraft assembly process, a large set of random initial gaps between the parts is needed. To get this set without initial gap measurements it is proposed to use the method of modeling the initial gap based on the mode shape decomposition. The initial gap is represented as a sum of orthonormal mode shapes with random coefficients. This paper describes the method for estimating parameters and generating initial gap samples for such cases without initial gap measurements. The application of this method is illustrated for the wing assembly process. The effectiveness of the initial gap modeling based on residual gap measurements is studied and the application of this initial gap model for fastening pattern optimization is performed.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 1","pages":"163 - 169"},"PeriodicalIF":0.0,"publicationDate":"2024-05-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-024-00302-4.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140976006","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}