Aerospace Science and Technology最新文献

英文中文

Research on inverse design method of pitching moment for the scramjet nozzle under strong geometric constraint

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-27 DOI: 10.1016/j.ast.2025.110107

Shuhong Tong , Maotao Yang , Ye Tian , Yue Ma , Jialing Le , Heng Wang

The traditional forward design method of the scramjet nozzle is difficult to obtain good performance under strong geometric constraints. Meanwhile, the existing optimal design methods rarely design from the perspective of the overall torque balance of the engine, and often only take into account the performance of the nozzle itself. This paper introduces an innovative inverse design method for the pitching moment of Single Expansion Ramp Nozzles (SERN). The core of this method integrates the Particle Swarm Optimization (PSO) algorithm with the Grey Wolf Optimization-based Kernel Extreme Learning Machine (GWO-KELM). A high-precision surrogate model of nozzle performance is constructed using a data-driven approach. Based on this surrogate model, performance constraints for PSO are established according to the desired moment. Nozzle design parameters are then iteratively optimized to achieve maximum thrust and minimum moment. The proposed method's effectiveness and accuracy are verified using Computational Fluid Dynamics (CFD). In twelve inverse design experiments, the average absolute percentage error between the designed and expected moment is 0.75 %. Compared to the reference nozzle profile, these designs achieve precise moment control while significantly improving thrust and reducing drag under strict geometric constraints. In conclusion, this paper presents an effective SERN design method, enhancing integration in hypersonic vehicles.

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引用次数: 0

Two-stage three-dimensional obstacle avoidance and impact angle control guidance law

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-27 DOI: 10.1016/j.ast.2025.110104

Rui Zhao , Xiang Yu , Dechuan Wang , Peng Yao

Aiming at the problems of avoiding obstacle and solving impact angle control in terminal guidance in three-dimensional scene, a two-stage guidance law which consists of three-dimensional softmax modified vector field guidance (SMVFG) and sliding mode impact angle control guidance (SMIACG) is proposed in this paper. In the first stage, the three-dimensional SMVFG law is designed to avoid static obstacles encountered in terminal guidance. In the second stage, the three-dimensional SMIACG law is designed to control the impact angle of the terminal under the premise of ensuring zero miss distance. Furthermore, the accessibility and safety of the whole guidance process are proved theoretically. Several numerical simulations are carried out to verify the accessibility and safety of the proposed guidance laws in different scenarios.

引用次数: 0

Three-dimensional cooperative guidance strategy for heterogeneous vehicles without prior communication topology establishment

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-26 DOI: 10.1016/j.ast.2025.110095

Yongcheng Xiong , Jianfeng Li , Changqing Hu , Liguo Tan

This study proposes a novel heterogeneous vehicle cooperative guidance law, named HKGG. This guidance law integrates the proportional navigation law (PNG) and the Hegselmann-Krause (HK) model, enabling multiple vehicles to self-organize and reach the target point in groups based on their own states. Firstly, a three-dimensional overload model for multiple flying-vehicles is established. Then, by deriving the combination form of the PNG term and the consensus algorithm through the vehicle-target model on a two-dimensional plane, normal and lateral guidance commands are derived based on the HK model and the estimation of the remaining flight time of the multi-vehicles. The proposed strategy does not require prior establishment of a communication topology, and the communication relationships between vehicles are time-varying. By employing the proposed strategy, the multi-vehicle system can significantly enhance its capability to strike high-defense/multi-interception facilities. Various simulation scenarios were considered to verify the effectiveness of the proposed control strategy.

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引用次数: 0

Recent advancements in morphing applications: Architecture, artificial intelligence integration, challenges, and future trends-a comprehensive survey

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-26 DOI: 10.1016/j.ast.2025.110102

Md. Najmul Mowla , Davood Asadi , Tahir Durhasan , Javad Rashid Jafari , Mohammadreza Amoozgar

This study provides a comprehensive review of recent advancements in aerospace morphing technologies, focusing on integrating artificial intelligence (AI) into morphing architectures. It emphasizes AI's pivotal role in optimizing these systems, particularly through machine learning (ML), deep learning (DL), and reinforcement learning (RL), to enhance real-time adaptability, performance, and efficiency. The review categorizes developments in smart materials, compliant mechanisms, and adaptive structures, offering a detailed analysis of their architectural foundations. It further examines AI-driven aerodynamic optimization and control systems, highlighting recent solutions to structural integrity, energy efficiency, and scalability challenges. Key contributions since 2020 are synthesized through a year-by-year analysis, offering a clear overview of the research landscape. The paper also addresses emerging challenges in aerospace morphing and proposes strategies to alleviate them. Recommendations for future advancements emphasize the integration of state-of-the-art technologies. By critically evaluating current capabilities and limitations, this review provides valuable insights for researchers and practitioners, identifying AI's transformative potential in morphing systems and outlining the technical challenges that must be addressed for future morphing aerospace applications.

{"title":"Recent advancements in morphing applications: Architecture, artificial intelligence integration, challenges, and future trends-a comprehensive survey","authors":"Md. Najmul Mowla , Davood Asadi , Tahir Durhasan , Javad Rashid Jafari , Mohammadreza Amoozgar","doi":"10.1016/j.ast.2025.110102","DOIUrl":"10.1016/j.ast.2025.110102","url":null,"abstract":"<div><div>This study provides a comprehensive review of recent advancements in aerospace morphing technologies, focusing on integrating artificial intelligence (AI) into morphing architectures. It emphasizes AI's pivotal role in optimizing these systems, particularly through machine learning (ML), deep learning (DL), and reinforcement learning (RL), to enhance real-time adaptability, performance, and efficiency. The review categorizes developments in smart materials, compliant mechanisms, and adaptive structures, offering a detailed analysis of their architectural foundations. It further examines AI-driven aerodynamic optimization and control systems, highlighting recent solutions to structural integrity, energy efficiency, and scalability challenges. Key contributions since 2020 are synthesized through a year-by-year analysis, offering a clear overview of the research landscape. The paper also addresses emerging challenges in aerospace morphing and proposes strategies to alleviate them. Recommendations for future advancements emphasize the integration of state-of-the-art technologies. By critically evaluating current capabilities and limitations, this review provides valuable insights for researchers and practitioners, identifying AI's transformative potential in morphing systems and outlining the technical challenges that must be addressed for future morphing aerospace applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110102"},"PeriodicalIF":5.0,"publicationDate":"2025-02-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143535292","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

The correlations between the thermodynamic variables in hypersonic turbulent boundary layers of a lifting body

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-25 DOI: 10.1016/j.ast.2025.110087

Yuandong Chen , Xiaoning Wang , Dehao Xu , Jianchun Wang

The correlations between thermodynamic variables in hypersonic turbulent boundary layers around a lifting body are comprehensively investigated through direct numerical simulations. By utilizing the Kovasznay decomposition, the fluctuating density and temperature are decomposed into acoustic and entropic modes. The traveling-wavelike alternating positive and negative structures are identified for the fluctuating pressure and acoustic modes of density and temperature, whereas the streaky structures are observed in the fluctuating entropy and entropic modes of the density and temperature near the wall. Both the acoustic and entropic modes of density and temperature make a significant contribution to the correlations of these variables in the near-wall region, whereas the entropic modes play a predominant role in the far-wall region. The strong correlation between fluctuating entropy and fluctuating density and temperature in the far-wall region is primarily attributed to the dominance of the entropic modes in these variables. The statistical properties and correlations of thermodynamic variables in the windward vortex region exhibit noticeable variations along the streamwise direction, characterized by an increase in entropy modes and decrease in acoustic modes. By contrast, the windward cross-flow region demonstrates stronger isotropy than the windward vortex region, as evidenced by minimal variations in the fluctuations and correlation coefficients of thermodynamic variables along the streamwise direction.

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引用次数: 0

Full Infrared band shock layer radiation noise analysis of a high-speed vehicle at high altitude based on virtual detection array method

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-24 DOI: 10.1016/j.ast.2025.110070

Yutong Zhu, Mingdong Hou, Siyang Sheng, Zhihong He, Shikui Dong

In this study, an algorithm was developed for analyzing the infrared radiation noise of aircraft shock layer flow fields based on virtual detection arrays. The spatial-spectral characteristics and influencing factors of infrared radiation noise in the 1–25 μm range in shock layer flow fields at high altitudes (40–80 km) was investigated. By comparing two flight trajectories, the contribution of different molecules (air chemical components NO, NO₂, OH, and atmospheric trace components CO₂, H₂O, CO) as sources to radiation noise, the spatial distribution patterns of radiation noise, and the relationship between radiation noise and trajectory characteristics were analyzed. The results show that: (1) In terms of the spectral characteristics of radiation noise, the atmospheric trace component CO₂ is identified as the strongest contributor to spectral radiation noise in both trajectories, with concentrations in 2.0–2.2 μm, 2.6–3.0 μm, 4.15–4.5 μm and 15 μm, while the shock layer chemical component NO is recognized as the second strongest radiation source, primarily concentrated in the 5–6 μm range. (2) In terms of spatial distribution patterns, the band irradiance in different positions of the blunt cone region decays exponentially along the streamline direction. (3) In terms of the magnitude of radiation noise, the band irradiance in the 3–5 μm band can be three orders of magnitude higher than that in the 8–12 μm band. (4) The band irradiance in the 40 km-50 km airspace of the low trajectory is determined to be one order of magnitude higher than that in the 50 km-80 km airspace of the high trajectory, with atmospheric pressure being identified as the main contributing factor.

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引用次数: 0

Development of the minimal biorobotic stealth distance and its role in optimizing direct-drive dragonfly-inspired aircraft design

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-24 DOI: 10.1016/j.ast.2025.110044

Minghao Zhang , Bifeng Song , Xiaojun Yang , Liang Wang , Xinyu Lang

Advancements in electronic technology and control algorithms have enabled precise flight control techniques, transforming bionic aircraft from principal imitation to comprehensive resemblance. This paper introduces the Minimal Biorobotic Stealth Distance (MBSD), a novel quantitative metric to evaluate the bionic resemblance of biorobotic aircraft. Current technological limitations prevent dragonfly-inspired aircraft from achieving optimal performance at biological scales. To address these challenges, we use the DDD-1 dragonfly-inspired aircraft, a hover-capable direct-drive aircraft, to explore the impact of the MBSD on aircraft design.

Key contributions of this research include (1) the establishment of the MBSD as a quantifiable and operable evaluation metric that influences aircraft design, integrating seamlessly with the overall design process and providing a new dimension for optimizing bionic aircraft, balancing mechanical attributes and bionic characteristics; (2) the creation and analysis of a typical aircraft in the following directions: its coupling relationship with existing performance metrics (Longest Hover Duration and Maximum Instantaneous Forward Flight Speed), multi-objective optimization, and application in a typical mission scenario; (3) the construction and validation of a full-system model for the direct-drive dragonfly-inspired aircraft, demonstrating the design model's effectiveness against existing aircraft data.

The findings highlight the MBSD's role in enhancing the operational capabilities of biorobotic aircraft and provide a systematic approach for optimizing design and performance in biomimetic aerial vehicles.

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引用次数: 0

Fixed-time adaptive fault-tolerant control with predefined tracking accuracy for satellite systems

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-24 DOI: 10.1016/j.ast.2025.110088

Guanyu Lai , Shizhuan Zou , Hanzhen Xiao , Zhaodong Su , Kai Huang , C.L. Philip Chen

The development of space technology put forward higher demands on the satellite position tracking control, i.e., the system steady states behavior and transient performance. However, due to the presence of unknown dynamics uncertainties and actuator failures, the control performance of traditional adaptive control schemes is unsatisfactory. In this work, we study the position tracking control problem of uncertain nonlinear satellite systems in the presence of unknown actuator failures, which is a challenging problem when a predefined tracking accuracy and a fixed convergence time are required simultaneously. To overcome the difficulties, a backstepping recursive design based on smooth functions is proposed, and well combined with adaptive actuator failure compensation approach, based on which a prescribed fixed-time adaptive fault-tolerant control scheme is developed. With our scheme, it can be rigorously proved that all closed-loop signals are bounded, and the position-related tracking errors converge to predefined intervals in a bounded settling time regardless of the occurrence of actuator failures. The effectiveness of the proposed scheme is verified by a simulation tests based on a practical geostationary earth orbit satellite.

{"title":"Fixed-time adaptive fault-tolerant control with predefined tracking accuracy for satellite systems","authors":"Guanyu Lai , Shizhuan Zou , Hanzhen Xiao , Zhaodong Su , Kai Huang , C.L. Philip Chen","doi":"10.1016/j.ast.2025.110088","DOIUrl":"10.1016/j.ast.2025.110088","url":null,"abstract":"<div><div>The development of space technology put forward higher demands on the satellite position tracking control, i.e., the system steady states behavior and transient performance. However, due to the presence of unknown dynamics uncertainties and actuator failures, the control performance of traditional adaptive control schemes is unsatisfactory. In this work, we study the position tracking control problem of uncertain nonlinear satellite systems in the presence of unknown actuator failures, which is a challenging problem when a predefined tracking accuracy and a fixed convergence time are required simultaneously. To overcome the difficulties, a backstepping recursive design based on smooth functions is proposed, and well combined with adaptive actuator failure compensation approach, based on which a prescribed fixed-time adaptive fault-tolerant control scheme is developed. With our scheme, it can be rigorously proved that all closed-loop signals are bounded, and the position-related tracking errors converge to predefined intervals in a bounded settling time regardless of the occurrence of actuator failures. The effectiveness of the proposed scheme is verified by a simulation tests based on a practical geostationary earth orbit satellite.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110088"},"PeriodicalIF":5.0,"publicationDate":"2025-02-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143509405","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

Adaptive wind direction strategy for neuro-network-based active disturbance rejection control of tandem twin-rotor aerial-aquatic vehicle

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-23 DOI: 10.1016/j.ast.2025.110089

Maosen Shao , Sihuan Wu , Lidong Wang , Sifan Wu , Hui Wang , Zhilin He , Mingpei Lin , Jinxiu Zhang

The novel slender aerial-aquatic vehicle (AAV) with slender fuselages enhances underwater maneuverability compared to traditional AAVs, which prioritize aerodynamic efficiency. However, these novel vehicles face challenges in positioning accuracy and energy consumption due to rotor control coupling and the significant differences in frontal and lateral surface areas, especially under crosswind and wave interference in open sea areas. This paper proposes an adaptive wind direction (AWD) strategy, combined with the active disturbance rejection control (ADRC) based on a radial basis function (RBF) neural network to enhance positioning accuracy and reduce energy consumption. Firstly, the mathematical models of the slender AAV, varying wind fields and waves are established. Subsequently, an ADRC law is designed for the attitude and position control of the AAV, where an RBF-based Extended State Observer (ESO) is used for disturbance observation instead of the traditional ESO. Then, the adaptive wind direction strategy is employed. This strategy utilizes wind disturbance characteristics, disturbance observations and body surface area parameters to calculate the wind field angle. Based on this angle, the attitude is adjusted to minimize interference. Finally, simulations validated the effectiveness and robustness of the designed ADRC control law based on the RBF ESO. After applying the adaptive wind disturbance strategy, positioning accuracy improved by 2 to 10 times, and energy consumption decreased by 20 % to 80 %, compared to the neural network-based active disturbance rejection control that does not utilize adaptive wind direction strategy.

{"title":"Adaptive wind direction strategy for neuro-network-based active disturbance rejection control of tandem twin-rotor aerial-aquatic vehicle","authors":"Maosen Shao , Sihuan Wu , Lidong Wang , Sifan Wu , Hui Wang , Zhilin He , Mingpei Lin , Jinxiu Zhang","doi":"10.1016/j.ast.2025.110089","DOIUrl":"10.1016/j.ast.2025.110089","url":null,"abstract":"<div><div>The novel slender aerial-aquatic vehicle (AAV) with slender fuselages enhances underwater maneuverability compared to traditional AAVs, which prioritize aerodynamic efficiency. However, these novel vehicles face challenges in positioning accuracy and energy consumption due to rotor control coupling and the significant differences in frontal and lateral surface areas, especially under crosswind and wave interference in open sea areas. This paper proposes an adaptive wind direction (AWD) strategy, combined with the active disturbance rejection control (ADRC) based on a radial basis function (RBF) neural network to enhance positioning accuracy and reduce energy consumption. Firstly, the mathematical models of the slender AAV, varying wind fields and waves are established. Subsequently, an ADRC law is designed for the attitude and position control of the AAV, where an RBF-based Extended State Observer (ESO) is used for disturbance observation instead of the traditional ESO. Then, the adaptive wind direction strategy is employed. This strategy utilizes wind disturbance characteristics, disturbance observations and body surface area parameters to calculate the wind field angle. Based on this angle, the attitude is adjusted to minimize interference. Finally, simulations validated the effectiveness and robustness of the designed ADRC control law based on the RBF ESO. After applying the adaptive wind disturbance strategy, positioning accuracy improved by 2 to 10 times, and energy consumption decreased by 20 % to 80 %, compared to the neural network-based active disturbance rejection control that does not utilize adaptive wind direction strategy.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110089"},"PeriodicalIF":5.0,"publicationDate":"2025-02-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143519343","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

Mechanism of the isolator compression constraint on the operating boundary of a dual-mode scramjet engine

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-23 DOI: 10.1016/j.ast.2025.110086

Xinwei Chen, Miaosheng He, Yuan Ji, Bin Yu, Wei Wang, Hong Liu

To uncover the mechanism by which the isolator length instigates the high- and low-speed performance conflict of the dual-mode scramjet (DMSJ) engine, a comprehensive thermodynamic cycle analysis of the DMSJ engine has been conducted, and two basic design perspectives for isolator length selection are considered. Results show that, aiming to optimize the specific impulse at the upper operating Mach number (UOM) under design perspective I yields an isolator length (L/H) as short as 0.65, which leads to significantly inadequate specific thrust at the lower operating Mach number (LOM), highlighting challenges in extending the DMSJ engine's lower operating boundary. Conversely, aiming to optimize the specific thrust at the LOM under design perspective II necessitates an isolator length as long as 16.7, resulting in a 60 % reduction of the specific impulse compared to the optimized specific impulse at the UOM. This underscores the challenges in extending the DMSJ engine's upper operating boundary. Comparative analysis further reveals that reducing the UOM proves far more effective than increasing the LOM to mitigate the conflict. Additionally, the adverse effect of low-dynamic-pressure combustion on the DMSJ engine's high- and low-speed performance conflict calls attention to the strong coupling effect between low-dynamic-pressure combustion and isolator pressurization, encouraging further study on the mechanism.

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