Aerospace Systems最新文献

{"title":"Nonlinear modeling and vibration modal analysis of Fin-actuator system with freeplay","authors":"Yanshen Ren,&nbsp;Zhiwei Xu,&nbsp;Dejia Tang,&nbsp;Ruoyu Liu,&nbsp;Li Fang,&nbsp;Wei Wang","doi":"10.1007/s42401-025-00385-7","DOIUrl":"10.1007/s42401-025-00385-7","url":null,"abstract":"<div><p>Electromechanical actuators (EMAs) are extensively employed in small aircraft. However, inherent structural nonlinearities such as freeplay, arising from limitations in production and manufacturing processes, can adversely affect the dynamic behavior of fin-actuator systems. This paper studies the correlation between modal frequencies and freeplay through the developed simulation model of the fin-actuator, and the modal frequencies are obtained by the impact hammer test. Both freeplay and friction effects are incorporated into the model to evaluate the influence of freeplay gap length and external loads on the frequency response function (FRF). Comparative analyses reveal that, under consistent impact load, significant differences exist in the vibration frequency responses for a fin with/without an external weight load. These results suggest a positive correlation between the frequency discrepancy and the magnitude of the freeplay, offering a reference for the detection of freeplay in fin-actuator systems.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 4","pages":"747 - 762"},"PeriodicalIF":0.0,"publicationDate":"2025-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145537767","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":"Enhancements to star identification algorithms utilizing singular value decomposition","authors":"Mona Zahednamazi,&nbsp;Alireza Toloei,&nbsp;Mohammad Hossein Toloei","doi":"10.1007/s42401-025-00383-9","DOIUrl":"10.1007/s42401-025-00383-9","url":null,"abstract":"<div><p>The star sensor is recognized as the most precise attitude determination sensor for space applications. This sensor establishes attitude by capturing images of stars within its field of view. The calculation of attitude via the star sensor involves several algorithms, among which star identification is the most critical. Incorrect star identification can result in erroneous attitude determinations. One of the lesser-explored star identification algorithms employs singular value decomposition (SVD) of a matrix formed by the directional vectors of a star cluster. This paper provides a survey of various star identification techniques based on this concept, along with simulations, analyses, and enhancements of these methods. Additionally, the impact of varying star cluster sizes and different field of view dimensions on the algorithm's performance has been examined across multiple methodologies. The identification process is framed as a two-step procedure utilizing singular values and singular vectors. Furthermore, the prevalence of duplicate sets within the databases of different methods has been investigated. In the concluding section of this paper, novel approaches for eliminating dimmer stars from images and selecting brightest stars based on the characteristics of singular value decomposition are proposed.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"607 - 620"},"PeriodicalIF":0.0,"publicationDate":"2025-07-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871590","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 deformation and failure of jet engine case during blade-out","authors":"Yu N. Shmotin,&nbsp;A. A. Ryabov,&nbsp;K. Yu Mokhov,&nbsp;S. S. Kukanov,&nbsp;S. O. Ptitsyn","doi":"10.1007/s42401-025-00384-8","DOIUrl":"10.1007/s42401-025-00384-8","url":null,"abstract":"<div><p>The present paper discusses issues related to dynamic deformation and failure of the jet engine case impacted by released blade of rotating rotor. It is shown that due to a local area of deformation of the jet engine case impacted by the released blade acceptable failure criterion for the case can be obtained on the base of model tests and corresponding numerical simulations. The equation of motion based on the variation principle of balance of virtual powers of work. The plasticity models of the materials are based on the von Mises yield surface with associated flow rule and isotropic hardening low depends on the strain rate. Numerical solutions of the problem are implemented by the finite element method and explicit scheme of numerical integration in time, realized in the code LOGOS. The uncoupled ductile fracture model is applied with the equivalent plastic strain as failure criterion. Validity of computer simulations is supported by proximity of numerical and experimental data for the depth of cutting of the targets at the impact sides and perforation and perforation time of the targets. Analysis of the principal strains and equivalent plastic strains as well as stress triaxiality parameters during the deformation process up to the failure of the targets is also presented. It is shown that destruction of the plane model of the jet engine case is initiated on the impact side when the equivalent plastic strain normalized by the elongation reaches the level <span>({overline{varepsilon }}_{pl1}^{f}=2.5)</span> with triaxial compression and perforation of the plate takes place if <span>({overline{varepsilon }}_{pl2}^{f}=1.2)</span> on the opposite side of the target plate with biaxial tension.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"31 - 38"},"PeriodicalIF":0.0,"publicationDate":"2025-07-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375190","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":"Research on theory and method of multiple fault diagnosis for airborne systems","authors":"Zhiyu She,&nbsp;Cunbao Ma,&nbsp;Haotian Niu,&nbsp;Jin Zhao","doi":"10.1007/s42401-025-00380-y","DOIUrl":"10.1007/s42401-025-00380-y","url":null,"abstract":"<div><p>An aircraft is composed of several complicated systems interacting with each other at different levels to ensure safe flight. Faults originating from one airborne system may propagate to others, potentially leading to a series of faults and even severe consequences. To enhance flight safety, minimize false alarms and reduce maintenance costs, it is essential to develop efficient and precise fault diagnosis techniques. This paper investigates the theory and methodology of multiple fault diagnosis in airborne systems. Fault diagnosis logic equations are adopted to model the cause-effect relationship between fault modes and fault symptoms. In addition, the existence of solutions to fault diagnosis logic equations is theoretically proved. Fault diagnosis logic equations may have a unique solution, more than one solution or no solutions under different conditions. Regarding the problem that fault diagnosis logic equations may have more than one solution or no solutions, an algorithm for solving fault diagnosis logic equations is proposed. The algorithm ensures that, for any given combination of fault symptoms, fault diagnosis logic equations will have a unique solution, enabling precise fault reasoning and isolation. Finally, a case study is carried out to verify the proposed method and results demonstrate that fault diagnosis logic equations-based approach achieves high diagnostic accuracy.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 2","pages":"225 - 233"},"PeriodicalIF":0.0,"publicationDate":"2025-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148261638","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":"Landing trajectories improvement of a vertical takeoff and landing aircraft systems considering linear quadratic regulator strategy","authors":"Nader M. Moustafa,&nbsp;Katea L. Hamid,&nbsp;Ehsan S. Al -Ameen","doi":"10.1007/s42401-025-00381-x","DOIUrl":"10.1007/s42401-025-00381-x","url":null,"abstract":"<div><p>Controlling the landing path trajectories of a vertical takeoff and landing aircraft is a challenge that requires an accurate design algorithm. This study introduces an innovative approach to investigate the dynamic of such vehicles and implement an automatic controller such that the aircraft follows a desired landing path trajectory. By linearizing the governing equations of the aircraft around a specific reference path, the linear model of the aircraft system is established. The bank angle is used as the primary control input to adjust landing profile and ballistic paths, while landing speed is treated as an independent state variable. This design algorithm involves creating a linear quadratic regulator controller gain that minimizes the cost function of the aircraft system, establishing dynamic state equations. The Hamiltonian function is employed to generate and solve both state and co-state equations under specific boundary conditions, culminating in the solution of the Riccati matrix. Finally, the controller's performance is tested with different initial state values. Results reveal significant improvements in stability and performance considering the landing path. However, challenges such as conflicts between system states, control gain saturation, and abrupt state changes remain key design hinders. This study offers a sufficient method for controlling such an aircraft using linear control algorithms, which can be more efficient and cost-effective than complex nonlinear algorithms. By simplifying control systems, this approach ensures stable and effective flight operations, making it a valuable advancement in the field of vertical takeoff and landing aircraft technology.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 4","pages":"953 - 961"},"PeriodicalIF":0.0,"publicationDate":"2025-06-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145537814","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":"Effect of amplitude and wavelength of tubercles on propeller performance","authors":"Mayuri R. Gore,&nbsp;Ganapati N. Joshi","doi":"10.1007/s42401-025-00365-x","DOIUrl":"10.1007/s42401-025-00365-x","url":null,"abstract":"<div><p>In the aviation industry, drones are increasingly used for different purposes. They come in various types, shapes, and sizes based on their motive, ranging from small quadcopters to larger drones for cargo transport. Drones are generally prioritized due to their superior and safe performance, easy accessibility, and adaptable capabilities. Their efficiency depends on the speed at which the operation is carried out, which affects overall performance. The performance device that is most affected by increased speed is the drone’s propeller. On one hand, high speed can enhance lift and performance, whereas on the other hand, it imposes aerodynamic, mechanical, and power-related challenges. Thus, by focusing on the aerodynamic factor, speed balancing can be achieved by designing an efficient propeller to attain optimal performance while maintaining efficiency and stability in high-speed drones. Previous researchers have introduced the concept of variable pitch propellers (VPP), which adjust the blade angle to maintain optimal lift and efficiency at high speeds. However, VPPs still have not fully addressed challenges such as increased drag, potential stall, and tip-speed effects, ultimately affecting efficiency. To overcome these drawbacks, researchers have explored the idea of tubercles, which help improve propeller performance at high angles of attack and higher RPMs. However, tubercles also present certain performance drawbacks, such as a potential reduction in maximum efficiency, increased surface area, and added weight, which contribute to an increased drag coefficient and mixed performance across speeds. This study focuses on improving overall aerodynamic efficiency by addressing factors such as an increase in overall efficiency, thrust force, and power. By concentrating on these factors, the aim is to develop different propeller designs by modifying tubercle parameters such as amplitude, wavelength, and position. Many studies have been conducted on propellers to enhance drone operations, and experts continue to explore ways to improve efficiency. One effective approach is incorporating leading-edge (LE) tubercles on propellers, which enhance the overall efficiency of drones. To fulfil the purpose of this study, a numerical investigation is carried out by comparing the baseline model with a propeller featuring tubercles. Based on previous literature, the improved performance and increased overall efficiency of tubercle-equipped propellers demonstrate superior performance compared to baseline propellers.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"15 - 29"},"PeriodicalIF":0.0,"publicationDate":"2025-06-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375336","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":"Design optimization and computational validation of dual bell nozzle using ANN algorithm","authors":"Taranjit Singh,&nbsp;Balaji Ravi","doi":"10.1007/s42401-025-00367-9","DOIUrl":"10.1007/s42401-025-00367-9","url":null,"abstract":"<div><p>Modern space exploration requires superior Propelling systems and dual bell nozzles present a promising solution for enhancing rocket propulsion system performance across varied flight regimes. This study offers a comprehensive optimization and analysis of dual bell nozzle design for advanced rockets. By employing Machine Learning with an Artificial Neural Network model, we developed a novel approach to rapidly optimize dual bell nozzle geometry for a specified exit Mach number, addressing the complex calculations typically associated with nozzle design. The algorithm generated a nozzle configuration capable of efficient operation in both low and high-altitude conditions. To validate results, we conducted detailed computational simulations using ANSYS Fluent. The analysis corroborated the model predictions, revealing key performance characteristics including a maximum exhaust velocity of approximately 2200 m/s and an exit Mach number of 5.8, aligning closely with the optimization. Our study contributes to the advancement of space propulsion technology by demonstrating the potential of AI-driven optimization in nozzle design.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 2","pages":"467 - 481"},"PeriodicalIF":0.0,"publicationDate":"2025-06-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145161232","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":"Model-based remote sensing satellite parameter design and importance analysis","authors":"Renfei Li,&nbsp;Tao Meng,&nbsp;Zhaohui Wang,&nbsp;Zhihong Zhao","doi":"10.1007/s42401-025-00362-0","DOIUrl":"10.1007/s42401-025-00362-0","url":null,"abstract":"<div><p>In traditional satellite system engineering, when the system designer decomposes indicators, it is difficult to quantify the impact of indicator parameters between systems and components, and thus it is impossible to effectively optimize and evaluate the parameters of the entire system. Based on the Model-Based Systems Engineering (MBSE) concept, this paper takes remote sensing satellites as the research object, conducts top-down forward design, establishes a parametric model of system-subsystem-component, and embeds the mechanism relationship between parameters. By analyzing the System Modeling Language (SysML) parameter model, a parameter association tree is generated. The parameter association tree is further combined with the PageRank method to locate key parameters. Through the above methods, the association relationship between complex parameters of remote sensing satellites is constructed, and the parameter impact between indicators can be quantitatively analyzed, which provides an effective tool for satellite design. Case analysis shows that this method can effectively analyze important parameters in the satellite design process, which will aid in the evaluation and optimization of satellite parameters.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 3","pages":"639 - 659"},"PeriodicalIF":0.0,"publicationDate":"2025-05-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"148871745","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":"Surrogate-based aerodynamic shape design of a multi-element airfoil with a VLCS leading-edge","authors":"Yifeng Liao,&nbsp;Guoyu Zheng,&nbsp;Weipeng Li","doi":"10.1007/s42401-025-00364-y","DOIUrl":"10.1007/s42401-025-00364-y","url":null,"abstract":"<div><p>The Very Long Chord Slat (VLCS) has emerged as a promising high-lift device configuration for commercial jetliners. This study focuses on the parametric shape design of two-dimensional high-lift devices incorporating VLCS, with particular emphasis on slat contour and position modifications. A surrogate-based optimization (SBO) framework, integrating Kriging metamodeling and the Non-dominated Sorting Genetic Algorithm, was employed to enhance the lift and drag performance at targeted angles of attack (AOA). The results reveal distinct Pareto fronts, demonstrating that a 25% slat chord extension yields a 7% improvement in lift-drag ratio at take-off AOA and a 4% increase in lift coefficient at landing AOA. The study also underscores the efficacy of the SBO method in preliminary aerodynamic design exploration for high-lift devices.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"9 1","pages":"1 - 13"},"PeriodicalIF":0.0,"publicationDate":"2025-05-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"147375335","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":"A comprehensive fault propagation analysis method for software and hardware loosely coupled systems from time and space dimensions","authors":"Jingli Yang,&nbsp;Yuxiang Huang,&nbsp;Tianyu Gao,&nbsp;XiaoTong Fang","doi":"10.1007/s42401-025-00359-9","DOIUrl":"10.1007/s42401-025-00359-9","url":null,"abstract":"<div><p>Software and hardware loosely coupled systems, characterized by their critical role in various high-reliability applications, require robust fault tolerance mechanisms due to their complexity and the intertwined nature of software and hardware components. However, the tight integration of diverse functions within the system-wide computing environment, coupled with the unclear mechanism of fault propagation, presents significant challenges in enhancing system reliability. Modern avionics systems, as a prominent example, are also inherently software-hardware loosely coupled systems, and they face similar challenges in ensuring fault tolerance. In response to these challenges, this paper proposes a fault propagation analysis method that comprehensively considers both temporal and spatial dimensions. Through in-depth analysis of dependency, fault probability, and fault propagation capability, the paper constructs a fault propagation model for software and hardware loosely coupled systems, providing a precise description of fault information. In the spatial dimension, the efficiency of fault propagation analysis is enhanced using the ant colony algorithm, while in the temporal dimension, task modeling is performed using the directed acyclic graph (DAG) model to improve the adaptability of fault propagation methods to real-time task requirements. The experimental results validate the effectiveness and efficiency of the proposed fault propagation method, demonstrating that the temporal dimension of fault propagation can effectively complement the shortcomings of spatial dimension fault propagation in meeting real-time task requirements.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"8 4","pages":"933 - 952"},"PeriodicalIF":0.0,"publicationDate":"2025-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145537837","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}