Aerospace Science and Technology最新文献

英文中文

Deep learning based flow field reconstruction study in the isolator of rocket based combined cycle engine

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-18 DOI: 10.1016/j.ast.2025.110081

Shaohua ZHU, Huamin ZHANG, Yi GAO, Dequan XU, Fei QIN, Bin LIU

In a rocket based combined cycle engine, the incoming flow parameters change drastically during the wide range working process. Thus, the isolator is highly susceptible to overflow conditions resulting in engine performance degradation or even non-starting conditions. To broaden the stable working boundary, we design a deep learning-based flow field reconstruction method to obtain the flow field information within an isolator. The two-dimensional velocity field can be reconstructed rapidly by studying the one-dimensional wall pressure of the isolator. This method we proposed can realize the rapid sense of its own abnormal state, which provides the necessary conditions for timely engine regulation and the robustness improvement. To optimize the effectiveness of the method, we compare the reconstruction accuracy of the velocity field for four typical neural network models. The results show that the MPFC-CNN neural network has high reconstruction accuracy. In this way, the starting positions of the separation zone are accurately reconstructed, and the morphology of the center high-speed core flow shock train is obtained. It is indicated that the model can accurately identify the working state of the isolator, and provide accurate feedback for the efficient control of the engine. Therefore, this study has obviously high value in engineering application for the combustion stabilization and wide-range performance improvement of the combined cycle engine.

{"title":"Deep learning based flow field reconstruction study in the isolator of rocket based combined cycle engine","authors":"Shaohua ZHU, Huamin ZHANG, Yi GAO, Dequan XU, Fei QIN, Bin LIU","doi":"10.1016/j.ast.2025.110081","DOIUrl":"10.1016/j.ast.2025.110081","url":null,"abstract":"<div><div>In a rocket based combined cycle engine, the incoming flow parameters change drastically during the wide range working process. Thus, the isolator is highly susceptible to overflow conditions resulting in engine performance degradation or even non-starting conditions. To broaden the stable working boundary, we design a deep learning-based flow field reconstruction method to obtain the flow field information within an isolator. The two-dimensional velocity field can be reconstructed rapidly by studying the one-dimensional wall pressure of the isolator. This method we proposed can realize the rapid sense of its own abnormal state, which provides the necessary conditions for timely engine regulation and the robustness improvement. To optimize the effectiveness of the method, we compare the reconstruction accuracy of the velocity field for four typical neural network models. The results show that the MPFC-CNN neural network has high reconstruction accuracy. In this way, the starting positions of the separation zone are accurately reconstructed, and the morphology of the center high-speed core flow shock train is obtained. It is indicated that the model can accurately identify the working state of the isolator, and provide accurate feedback for the efficient control of the engine. Therefore, this study has obviously high value in engineering application for the combustion stabilization and wide-range performance improvement of the combined cycle engine.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110081"},"PeriodicalIF":5.0,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143474516","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

Extension of graph-accelerated non-intrusive polynomial chaos to high-dimensional uncertainty quantification through the active subspace method

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-18 DOI: 10.1016/j.ast.2025.110074

Bingran Wang, Nicholas C. Orndorff, Mark Sperry, John T. Hwang

The recently introduced graph-accelerated non-intrusive polynomial chaos (NIPC) method has shown effectiveness in solving a broad range of uncertainty quantification (UQ) problems with multidisciplinary systems. It uses integration-based NIPC to solve the UQ problem and generates the quadrature rule in a desired tensor structure, so that the model evaluations can be efficiently accelerated through the computational graph transformation method, Accelerated Model evaluations on Tensor grids using Computational graph transformations (AMTC). This method is efficient when the model's computational graph possesses a certain type of sparsity which is commonly the case in multidisciplinary problems. However, it faces limitations in high-dimensional cases due to the curse of dimensionality. To broaden its applicability in high-dimensional UQ problems, we propose AS-AMTC, which integrates the AMTC approach with the active subspace (AS) method, a widely-used dimension reduction technique. In developing this new method, we have also developed AS-NIPC, linking integration-based NIPC with the AS method for solving high-dimensional UQ problems. AS-NIPC incorporates rigorous approaches to generate orthogonal polynomial basis functions for lower-dimensional active variables and efficient quadrature rules to estimate their coefficients. The AS-AMTC method extends AS-NIPC by generating a quadrature rule with a desired tensor structure. This allows the AMTC method to exploit the computational graph sparsity, leading to efficient model evaluations. In an 81-dimensional UQ problem derived from an air-taxi trajectory optimization scenario, AS-NIPC demonstrates a 30% decrease in relative error compared to the existing methods, while AS-AMTC achieves an 80% reduction.

{"title":"Extension of graph-accelerated non-intrusive polynomial chaos to high-dimensional uncertainty quantification through the active subspace method","authors":"Bingran Wang, Nicholas C. Orndorff, Mark Sperry, John T. Hwang","doi":"10.1016/j.ast.2025.110074","DOIUrl":"10.1016/j.ast.2025.110074","url":null,"abstract":"<div><div>The recently introduced graph-accelerated non-intrusive polynomial chaos (NIPC) method has shown effectiveness in solving a broad range of uncertainty quantification (UQ) problems with multidisciplinary systems. It uses integration-based NIPC to solve the UQ problem and generates the quadrature rule in a desired tensor structure, so that the model evaluations can be efficiently accelerated through the computational graph transformation method, Accelerated Model evaluations on Tensor grids using Computational graph transformations (AMTC). This method is efficient when the model's computational graph possesses a certain type of sparsity which is commonly the case in multidisciplinary problems. However, it faces limitations in high-dimensional cases due to the curse of dimensionality. To broaden its applicability in high-dimensional UQ problems, we propose AS-AMTC, which integrates the AMTC approach with the active subspace (AS) method, a widely-used dimension reduction technique. In developing this new method, we have also developed AS-NIPC, linking integration-based NIPC with the AS method for solving high-dimensional UQ problems. AS-NIPC incorporates rigorous approaches to generate orthogonal polynomial basis functions for lower-dimensional active variables and efficient quadrature rules to estimate their coefficients. The AS-AMTC method extends AS-NIPC by generating a quadrature rule with a desired tensor structure. This allows the AMTC method to exploit the computational graph sparsity, leading to efficient model evaluations. In an 81-dimensional UQ problem derived from an air-taxi trajectory optimization scenario, AS-NIPC demonstrates a 30% decrease in relative error compared to the existing methods, while AS-AMTC achieves an 80% reduction.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110074"},"PeriodicalIF":5.0,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143453823","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

A volume-ratio index for sensitivity analysis of time-dependent models with interval uncertainty inputs

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-17 DOI: 10.1016/j.ast.2025.110077

Rongyao Song , Changcong Zhou , Jing Rui , Hanghang Li , Jialu Li

In practical engineering, owing to the presence of physical imperfections, model inaccuracies, and structural complexities, almost all time-dependent systems have physical and geometrical uncertainties to some degree. Analyzing the effects of input uncertainties on the output of time-dependent systems is important. In this paper, we focus on sensitivity analysis for the time-dependent output with interval uncertainties. First, the interval process model is introduced to characterize the uncertainty of the time-dependent output under interval inputs. We develop an interval field model on the basis of an analysis of the interval process model. This model allows visualization of the uncertainty effect of the interval input within its interval range on the time-dependent output. Furthermore, we propose a novel sensitivity index defined by the volume ratio of the interval field model, which is designated the “volume-ratio index”. This index quantifies the contribution of interval variables to the uncertainty in the time-dependent output. Two computational strategies are developed to calculate the proposed index. At last, three examples are presented to show the validity and applicability of the developed method.

{"title":"A volume-ratio index for sensitivity analysis of time-dependent models with interval uncertainty inputs","authors":"Rongyao Song , Changcong Zhou , Jing Rui , Hanghang Li , Jialu Li","doi":"10.1016/j.ast.2025.110077","DOIUrl":"10.1016/j.ast.2025.110077","url":null,"abstract":"<div><div>In practical engineering, owing to the presence of physical imperfections, model inaccuracies, and structural complexities, almost all time-dependent systems have physical and geometrical uncertainties to some degree. Analyzing the effects of input uncertainties on the output of time-dependent systems is important. In this paper, we focus on sensitivity analysis for the time-dependent output with interval uncertainties. First, the interval process model is introduced to characterize the uncertainty of the time-dependent output under interval inputs. We develop an interval field model on the basis of an analysis of the interval process model. This model allows visualization of the uncertainty effect of the interval input within its interval range on the time-dependent output. Furthermore, we propose a novel sensitivity index defined by the volume ratio of the interval field model, which is designated the “volume-ratio index”. This index quantifies the contribution of interval variables to the uncertainty in the time-dependent output. Two computational strategies are developed to calculate the proposed index. At last, three examples are presented to show the validity and applicability of the developed method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110077"},"PeriodicalIF":5.0,"publicationDate":"2025-02-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143471299","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

Cooling characteristics of opposing jet-transpiration cooling combined system with variable mass flow rate distribution

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-16 DOI: 10.1016/j.ast.2025.110073

Yunan Wang, Lin Wang, Zhenbing Luo, Yan Zhou, Qiang Liu, Wenqiang Peng, Wei Xie, Mingjie Du

To address the extreme thermal load challenges faced by aerospace vehicles, one of the promising solutions is the integration of multiple cooling techniques through combined cooling technology. To further enhance the efficiency of this combined cooling approach, this study employs numerical simulations to analyze the effect of multi-chamber injection strategies on the efficiency of opposing jet (OJ) - transpiration cooling (TC) combined cooling. The research reveals that the multi-chamber injection strategy exhibits a significant advantage compared to the baseline injection method in terms of thermal protection at the leading edge. Specifically, when the coolant distribution is optimized to 10 g/s for TC and 15 g/s for OJ, the peak and average temperatures at the leading edge are reduced by 17.47 % and 10.22 %, respectively. This strategy optimizes coolant distribution along the vehicle's leading edge, significantly modulating the interaction between the coolant and the mainstream, and utilizes the convective heat transfer characteristics of the porous matrix more effectively. The study further demonstrates that dynamically adjusting OJ and TC injection rates based on the thermal load distribution can achieve more effective thermal protection. For regions of high thermal load, like the stagnation point on the leading edge, increasing the coolant mass flow rate on the OJ side can achieve more effective thermal protection, whereas for low thermal load areas, a high-efficiency TC injection strategy is more appropriate. These findings provide a valuable theoretical basis and technical guidance for the design and optimization of thermal protection systems in aerospace vehicles.

{"title":"Cooling characteristics of opposing jet-transpiration cooling combined system with variable mass flow rate distribution","authors":"Yunan Wang, Lin Wang, Zhenbing Luo, Yan Zhou, Qiang Liu, Wenqiang Peng, Wei Xie, Mingjie Du","doi":"10.1016/j.ast.2025.110073","DOIUrl":"10.1016/j.ast.2025.110073","url":null,"abstract":"<div><div>To address the extreme thermal load challenges faced by aerospace vehicles, one of the promising solutions is the integration of multiple cooling techniques through combined cooling technology. To further enhance the efficiency of this combined cooling approach, this study employs numerical simulations to analyze the effect of multi-chamber injection strategies on the efficiency of opposing jet (OJ) - transpiration cooling (TC) combined cooling. The research reveals that the multi-chamber injection strategy exhibits a significant advantage compared to the baseline injection method in terms of thermal protection at the leading edge. Specifically, when the coolant distribution is optimized to 10 g/s for TC and 15 g/s for OJ, the peak and average temperatures at the leading edge are reduced by 17.47 % and 10.22 %, respectively. This strategy optimizes coolant distribution along the vehicle's leading edge, significantly modulating the interaction between the coolant and the mainstream, and utilizes the convective heat transfer characteristics of the porous matrix more effectively. The study further demonstrates that dynamically adjusting OJ and TC injection rates based on the thermal load distribution can achieve more effective thermal protection. For regions of high thermal load, like the stagnation point on the leading edge, increasing the coolant mass flow rate on the OJ side can achieve more effective thermal protection, whereas for low thermal load areas, a high-efficiency TC injection strategy is more appropriate. These findings provide a valuable theoretical basis and technical guidance for the design and optimization of thermal protection systems in aerospace vehicles.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110073"},"PeriodicalIF":5.0,"publicationDate":"2025-02-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143445580","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

Assessment of prevalent vortex-center detection criteria for the compensation of wandering motion of wingtip vortices

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-15 DOI: 10.1016/j.ast.2025.110069

Zhiyuan Wang , Chong Pan , Zepeng Cheng

Vortex wandering, characterized as low-frequency displacements of vortex core locations, significantly affects the quantification of vortex statistics. To mitigate this impact, re-centering correction is a commonly employed method for post-processing velocity-field datasets being measured by particle image velocimetry (PIV). One of the key problems in this method is how to precisely detect instantaneous vortex centers. In this paper, eight prevalent vortex-center detection criteria are empirically evaluated, with the purpose of finding the most practical criterion for the compensation of vortex wandering. Cross-stream velocity fields in the near-wake and middle-wake regions of either an isolated vortex or a counter-rotating vortex pair, being measured by time-resolved stereoscopic PIV, are post-processed by re-centering correction with various vortex-center detection criteria, which are categorized as local or non-local methods with velocity-based or velocity-gradient-based measures. The yielded instantaneous vortex centers and vortex kinematical statistics, including mean velocity profiles and turbulent statistics, are compared in detail. It is found that the pseudo-circulation criterion, which is a velocity-based non-local method, outperforms all the other tested criteria. Once applying the pseudo-circulation criterion to decompose the instantaneous velocity field into triple components, i.e., mean component, large-scale motion and small-scale turbulent fluctuation, the pseudo-fluctuation from vortex wandering can be effectively peeled off from small-scale turbulent fluctuation, resulting in the most compact vortex profile, as well as the lowest level of small-scale turbulent kinetic energy and Reynolds shear stress in the vortex core region. Such an advance makes it an ideal vortex-center detection criterion to study either wingtip vortex instability or energy transfer characteristics associated with the vortex wandering motion.

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引用次数: 0

Adaptive reset control for group-bipartite formation of multi-UAVs subject to transmission delays

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-15 DOI: 10.1016/j.ast.2025.110068

Zhen Tang , Xinhua Wang , Ziyang Zhen , Zhengen Zhao , Teng Cao , Geert Deconinck

Existing multi-UAV formation control methods face challenges in achieving stable and fast tracking under transmission delays and inaccessible information, particularly when addressing the design of various formation configurations and optimizing transient performance. To address these challenges, this paper proposes an adaptive reset control technique that integrates virtual leaders and state observers to achieve fast and accurate time-varying group-bipartite formation tracking in multi-UAV systems. Firstly, a state observer is designed to accurately estimate the position and velocity of each UAV. Then, a distributed adaptive group-bipartite time-varying formation tracking controller with a reset component is introduced. This controller enables each UAV to adjust its position and velocity according to neighboring UAVs, thus achieving the desired group-bipartite formation. The inclusion of reset component significantly enhances the transient performance of formation. Moreover, the sufficient conditions were derived for group-bipartite formation control by employing a novel Lyapunov-Krasovskii functional, which constructed with the matrix-valued polynomial, the Bessel-Legendre inequality, and the reciprocally convex matrix inequality. Finally, the effectiveness and advantages of the proposed control strategy are demonstrated through comprehensive simulations involving multiple fixed-wing UAVs.

{"title":"Adaptive reset control for group-bipartite formation of multi-UAVs subject to transmission delays","authors":"Zhen Tang , Xinhua Wang , Ziyang Zhen , Zhengen Zhao , Teng Cao , Geert Deconinck","doi":"10.1016/j.ast.2025.110068","DOIUrl":"10.1016/j.ast.2025.110068","url":null,"abstract":"<div><div>Existing multi-UAV formation control methods face challenges in achieving stable and fast tracking under transmission delays and inaccessible information, particularly when addressing the design of various formation configurations and optimizing transient performance. To address these challenges, this paper proposes an adaptive reset control technique that integrates virtual leaders and state observers to achieve fast and accurate time-varying group-bipartite formation tracking in multi-UAV systems. Firstly, a state observer is designed to accurately estimate the position and velocity of each UAV. Then, a distributed adaptive group-bipartite time-varying formation tracking controller with a reset component is introduced. This controller enables each UAV to adjust its position and velocity according to neighboring UAVs, thus achieving the desired group-bipartite formation. The inclusion of reset component significantly enhances the transient performance of formation. Moreover, the sufficient conditions were derived for group-bipartite formation control by employing a novel Lyapunov-Krasovskii functional, which constructed with the matrix-valued polynomial, the Bessel-Legendre inequality, and the reciprocally convex matrix inequality. Finally, the effectiveness and advantages of the proposed control strategy are demonstrated through comprehensive simulations involving multiple fixed-wing UAVs.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110068"},"PeriodicalIF":5.0,"publicationDate":"2025-02-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143474517","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

A hybrid discretization strategy for successive convex programming in skip entry trajectory optimization

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-15 DOI: 10.1016/j.ast.2025.110056

Nuo Chen , Hong-Bo Zhang , Xiang Zhou , Lei Xie , Guo-Jian Tang

When applying successive convex programming to solve the skip entry trajectory optimization problem, it is challenging for a single discretization method to ensure both convergence accuracy and stability simultaneously. To address this issue, a hybrid discretization strategy is proposed. First, from the perspective of whether state propagation is utilized, discretization methods can be categorized into two types, and the properties of both are analyzed theoretically. Second, the strategy begins to iterate using discretization without state propagation. Once the designed switch condition is satisfied, the method transitions to discretization with state propagation to continue iterating until convergence. The precision and stability of the proposed strategy are verified through simulations involving various discretization combinations and different discrete switching criteria.

引用次数: 0

Adaptive robust fault-tolerant control for a small size unmanned helicopter: Theory and experimental implementation

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-14 DOI: 10.1016/j.ast.2025.110059

Aochen Ma , Bin Xian , Mohan Liu , Baokun Yuan , Xin Jin

This paper investigates the control design problem of small-size unmanned helicopter which is subject to unknown actuator faults. After an actuator failure occurs, the unmanned helicopter may become unstable and even lead to a fatal crash. Due to the complexity of the unmanned helicopter's mechanical structure and dynamics, there has been very few research work in the fault tolerant control design for unmanned helicopters, and only numerical simulation verification are provided. To address the power loss caused by tail rotor damage, a new sliding mode surface is proposed based on geometric control. And by combined with the adaptive control, a robust adaptive fault-tolerant control law is developed. It utilizes adaptive terms to approximate uncertain actuator's faults, and the robust components are used to improve the control law's robustness. This enables the small-size unmanned helicopter to complete normal flight missions even in the event of power loss failures. The proposed control algorithm's stability is proven using Lyapunov based analysis. To further demonstrate the control performance of this algorithm, validating experiments are conducted on a small-size unmanned helicopter control experimental platform, and good control performance is achieved under tail actuator faults.

{"title":"Adaptive robust fault-tolerant control for a small size unmanned helicopter: Theory and experimental implementation","authors":"Aochen Ma , Bin Xian , Mohan Liu , Baokun Yuan , Xin Jin","doi":"10.1016/j.ast.2025.110059","DOIUrl":"10.1016/j.ast.2025.110059","url":null,"abstract":"<div><div>This paper investigates the control design problem of small-size unmanned helicopter which is subject to unknown actuator faults. After an actuator failure occurs, the unmanned helicopter may become unstable and even lead to a fatal crash. Due to the complexity of the unmanned helicopter's mechanical structure and dynamics, there has been very few research work in the fault tolerant control design for unmanned helicopters, and only numerical simulation verification are provided. To address the power loss caused by tail rotor damage, a new sliding mode surface is proposed based on geometric control. And by combined with the adaptive control, a robust adaptive fault-tolerant control law is developed. It utilizes adaptive terms to approximate uncertain actuator's faults, and the robust components are used to improve the control law's robustness. This enables the small-size unmanned helicopter to complete normal flight missions even in the event of power loss failures. The proposed control algorithm's stability is proven using Lyapunov based analysis. To further demonstrate the control performance of this algorithm, validating experiments are conducted on a small-size unmanned helicopter control experimental platform, and good control performance is achieved under tail actuator faults.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110059"},"PeriodicalIF":5.0,"publicationDate":"2025-02-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143430272","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

Automatic carrier landing control of carrier-based UAV under actuator failure condition

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-14 DOI: 10.1016/j.ast.2025.110067

Ning Sun, Haibin Duan, Mengzhen Huo

An automatic carrier landing system for carrier-based unmanned aerial vehicle (UAV) is developed in this paper, where external disturbance and actuator failure are considered. The landing area error caused by deck motion is introduced into the reference glide trajectory design to compensate for stochastic and unpredictable wave-induced carrier motion. Moreover, through the passive fault-tolerant control method, a model predictive control structure based on a nonlinear extended state observer with a designed fal function is proposed to address the landing control problem when actuator failure occurs on a carrier-based UAV. Within a fixed time, the observed error converges to the residual. In addition, the control vector reference curve is designed to ensure a fast and smooth control process during the landing process through the model predictive controller. Furthermore, numerical simulations are performed to demonstrate the system's superiority and reliability.

引用次数: 0

Dynamic performance of composite laminate wing beam structures of aeronautical engineering with complex geometrical profiles

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-13 DOI: 10.1016/j.ast.2025.110024

Chen-Guang Wang , Xu-Yuan Song , Jian Zang , Zhen Zhang , Ye-Wei Zhang , Li-Qun Chen

Critical aerostructures, such as wings, spars, and propellers, can be considered beam structures with complex geometrical profiles and varying stiffness along the axial direction, complicating their dynamic performance analysis. Therefore, this paper proposes a novel method for the dynamic modeling of composite laminate beams with complex geometrical profiles (CLBCGP). To overcome the difficulty of analytic geometry integration introduced by complex geometrical profiles and the heterogeneous stiffness of laminate composites, the CLBCGP is assumed to be divided into a series of discrete data points uniformly distributed along the axial direction. Meanwhile, a discrete displacement function with variable thickness weighting for CLBCGP is constructed for the first time, and Composite Simpson's numerical integration is imported to calculate the kinetic and potential energies of CLBCGP with arbitrary support in a hygrothermal environment. The governing equation is derived via the Lagrange equation, and then experimental investigations are carried out to confirm the validity of the proposed method. Finally, the stress distribution and dynamic properties of CLBCGP under basic excitation, elastic boundaries, and hygrothermal conditions are systematically investigated. The methodology resolves the numerical divergence of conventional approaches, enabling 2,000th-order calculations with an accuracy of approximately 1e-10, providing a high-precision solution for the dynamics of composite variable-section beams. Concurrently, the methodology is equally efficacious for beams exhibiting markedly nonlinear axial stiffness.

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