Aerospace Science and Technology最新文献_第7页

Optimal fault-tolerant control of reusable launch vehicle with actuator faults using zero-sum differential game theory

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-21 DOI: 10.1016/j.ast.2025.110080

Hao Ren , Yajie Ma , Bin Jiang

{"title":"Optimal fault-tolerant control of reusable launch vehicle with actuator faults using zero-sum differential game theory","authors":"Hao Ren , Yajie Ma , Bin Jiang","doi":"10.1016/j.ast.2025.110080","DOIUrl":"10.1016/j.ast.2025.110080","url":null,"abstract":"<div><div>Due to the harsh conditions and the potential for system faults and disturbances, ensuring the reliability and stability of reusable launch vehicles (RLVs) during reentry is critical. Traditional control strategies often struggle to maintain performance in the face of actuator faults and unpredictable external disturbances. In this paper, a novel approach for optimal fault-tolerant control in the attitude control system of reusable launch vehicle in reentry phase is introduced. This approach incorporates the zero-sum differential game theory to effectively address faults in actuators and external disturbance. We represent these actuator faults and external disturbance as an unpredictable bias in opposition to the control mechanism. By solving the Hamilton-Jacobi-Isaacs (HJI) equation and employing the Nash-Pontryagin minimax principle, we derive both the optimal control strategy and the maximum limit for the bias signal, thus attaining a Nash equilibrium saddle point. The estimation of the ideal cost function in real-time is executed via an adaptive critic neural-network, which utilizes adaptive dynamic programming method to formulate an adaptive control strategy. This method guarantees the stability and accuracy of the tracking performance, as well as the confinement of error margins within the attitude management system. Simulation results validate the efficacy of our proposed strategy for fault-tolerant control.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110080"},"PeriodicalIF":5.0,"publicationDate":"2025-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143477866","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

Single action control for oleo-pneumatic shock absorbers in CS-23 aircraft

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-20 DOI: 10.1016/j.ast.2025.110078

Felix Willich , Jadran Vrabec , Florian Holzapfel

{"title":"Single action control for oleo-pneumatic shock absorbers in CS-23 aircraft","authors":"Felix Willich , Jadran Vrabec , Florian Holzapfel","doi":"10.1016/j.ast.2025.110078","DOIUrl":"10.1016/j.ast.2025.110078","url":null,"abstract":"<div><div>A novel open-loop semi-passive control concept for oleo-pneumatic shock absorbers of CS-23 aircraft is presented. This concept enables the control of the damping characteristics in diverse impact scenarios with a single configuration before touchdown. This approach maintains low energy consumption and allows for the application of slower actuators. The damping properties are optimized to achieve the best possible uniform deceleration during compression in various impact scenarios. Integration of this concept is focused on a trailing arm suspension, where the controller takes the interaction between the wheel and the ground at the point of impact as well as the orientation change of the shock absorber during deflection into account. This approach shows minimal maximum load in systems with uniform deceleration curves. For uncontrolled systems, the guaranteed overshoot causes the restoring forces to amplify the tendency for a bounced landing, if the recoil is not effectively damped, especially when ground forces or lift are present. Therefore, the shock absorber is augmented with a coned metering pin to provide increased damping at low deflections. To ensure a comparable analysis of the system regarding rebound tendency, a decompression efficiency criterion is introduced, which can be determined via drop tests. The influence of the metering pin and the single configuration control (separate and combined) on the system's performance (minimal load and rebounce tendency) is examined under varying load conditions. It is shown that the semi-passive concepts improve overall performance across various load scenarios.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110078"},"PeriodicalIF":5.0,"publicationDate":"2025-02-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143487503","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

Game-based fault-tolerant formation containment control for fixed-wing UAVs under the fully actuated system framework

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-19 DOI: 10.1016/j.ast.2025.110052

Jiao Hu, Yuhang Xu, Bin Jiang

引用次数: 0

Non-overshooting Fixed Time Control of Free-Flying Space Robotic Manipulators with output constraints: An Inverse Optimal Approach

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-19 DOI: 10.1016/j.ast.2025.110079

Zhicheng Xie, Xianliang Chen, Jiashu Wu, Xiaofeng Wu

{"title":"Non-overshooting Fixed Time Control of Free-Flying Space Robotic Manipulators with output constraints: An Inverse Optimal Approach","authors":"Zhicheng Xie, Xianliang Chen, Jiashu Wu, Xiaofeng Wu","doi":"10.1016/j.ast.2025.110079","DOIUrl":"10.1016/j.ast.2025.110079","url":null,"abstract":"<div><div>Inverse Optimal Control (IOC) features addressing optimal control problem without the need to solve the complex Hamilton-Jacobi-Bellman (HJB) equation. Although IOC has been extensively studied over the recent years, the state of the art lacks the results of achieving a fixed time non-overshooting response with constrained outputs on IOC schemes. In this paper, an adaptive inverse optimal control scheme is proposed to address the tracking problem of free-flying space robotic manipulators subject to system uncertainties and unknown disturbances, which achieves the practical fixed time non-overshooting response with the constrained tracking errors. More precisely, a novel practical fixed time non-singular virtual controller is designed to define the desired dynamics of tracking errors, which features the non-singular <span><math><msup><mrow><mi>n</mi></mrow><mrow><mi>t</mi><mi>h</mi></mrow></msup></math></span> derivative where <span><math><mi>n</mi></math></span> is any positive integers defined by users. Then, an auxiliary variable is designed to work with the virtual controller to guarantee the absence of overshoot even the system is subject to uncertainties and disturbances. After that, a Fixed Time Disturbance Observer (FTDO) based inverse optimal control scheme is finally constructed to achieve a practical fixed time non-overshooting response with the satisfied output constraints. To the best of author's knowledge, this is the first work of simultaneously achieving non-overshooting response, practical fixed time stability, inverse optimality, and constrained output. The stability of the proposed controller is proven by Lyapunov theory, and the effectiveness is verified by numerical simulations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110079"},"PeriodicalIF":5.0,"publicationDate":"2025-02-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143643556","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

Hierarchical reinforcement learning method for long-horizon path planning of stratospheric airship

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-18 DOI: 10.1016/j.ast.2025.110075

Chao Lv , Ming Zhu , Xiao Guo , Jiajun Ou , Wenjie Lou

{"title":"Hierarchical reinforcement learning method for long-horizon path planning of stratospheric airship","authors":"Chao Lv , Ming Zhu , Xiao Guo , Jiajun Ou , Wenjie Lou","doi":"10.1016/j.ast.2025.110075","DOIUrl":"10.1016/j.ast.2025.110075","url":null,"abstract":"<div><div>The rapid development of stratospheric airships has shown excellent application prospects, such as meteorological research, remote sensing, communication, and so on. The path planning of stratospheric airships has become the focus of research. Traditional methods have already implemented the path planning problem for simple scenarios. However, long-horizon path planning in a dynamic environment, causing problems like state explosion and time abstraction, is difficult to solve by traditional algorithms. This paper presents a hierarchical TD3 algorithm (H-TD3), a long-horizon path planning with a hierarchical framework operating on different temporal scales. It consists of two layers: the high-level controller and the low-level controller. The high-level controller decomposes the long-horizon path planning task into short-horizon navigation tasks, completed by the low-level controller for short-horizon path planning. In addition, we introduce an execution reward to promote cooperation between the high-level controller and the low-level controller to complete the task. Finally, the model is trained and tested in forecast wind fields and compared with other algorithms based on deep reinforcement learning. The effectiveness of the proposed method in long-horizon path planning is verified.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110075"},"PeriodicalIF":5.0,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143445577","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

Impact of atmospheric turbulence on typical shaped booms

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-18 DOI: 10.1016/j.ast.2025.110076

Di Wang , Zhonghua Han , Zhansen Qian , Jianling Qiao , Liangjie Gao , Yan Leng

{"title":"Impact of atmospheric turbulence on typical shaped booms","authors":"Di Wang , Zhonghua Han , Zhansen Qian , Jianling Qiao , Liangjie Gao , Yan Leng","doi":"10.1016/j.ast.2025.110076","DOIUrl":"10.1016/j.ast.2025.110076","url":null,"abstract":"<div><div>Accurate sonic boom prediction is crucial for low-boom supersonic civil transports (SST). In the real atmospheric environment, atmospheric turbulence randomly distorts the shape and energy distribution of sonic booms, posing significant challenges in assessing their intensity. Previous studies have focused primarily on N-waves, revealing that atmospheric turbulence can transform N-type waves into P-type and R-type waves. Facing the practical applications in the future, supersonic civil transports must be designed with low-boom methods to minimize their impact on the ground. Additionally, the focused sonic boom generated during supersonic maneuvering flight is another critical consideration. At this time, sonic boom signals warrant attention not only classical N-type wave, but also low-boom waveform such as flattop-wave and ramp-wave, as well as focused waveform such as U-wave. However, the impact of atmospheric turbulence on these shaped booms is not clear. The present work investigates the influence of atmospheric turbulence on shaped booms. Using high-order finite difference time domain methods and high-performance computing, we employed a three-dimensional augmented KZK sonic boom propagation model coupled with an atmospheric turbulence model to simulate the propagation and evolution of shaped booms in the atmospheric boundary layer (ABL). Flight experimental data from D-SEND#1 project was used to validate the present models and numerical methods. Results indicate that atmospheric turbulence has a relatively small distortion on both ramp-wave and U-wave, which is more conducive to low-boom design for supersonic civil transports. Conversely, the atmospheric turbulence has a relatively large impact on distortion of both N-wave and flattop-wave.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110076"},"PeriodicalIF":5.0,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143445578","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

An improved approach for aerodynamic optimization considering WIG effect and height static stability

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-18 DOI: 10.1016/j.ast.2025.110071

Yang Zhang , Yang Zhang , Song Chen , Jiakuan Xu , Junlin Li

{"title":"An improved approach for aerodynamic optimization considering WIG effect and height static stability","authors":"Yang Zhang , Yang Zhang , Song Chen , Jiakuan Xu , Junlin Li","doi":"10.1016/j.ast.2025.110071","DOIUrl":"10.1016/j.ast.2025.110071","url":null,"abstract":"<div><div>To address the issue of inadequate height static stability of the airfoil under ground-effects, an aerodynamic optimization was conducted on the NACA4412 airfoil, targeting static height stability and adhering to a lift to-drag ratio constraint. This article adopted the class function/shape function transformation (CST) method to parameterize the airfoil and reduced the number of design variables by using a layered dimensionality reduction method. Firstly, the proper orthogonal decomposition (POD) was used to decrease the dimensionality of CST weight coefficients. Subsequently, the extracted modes were subjected to sensitivity analysis, and the final design variables were selected from those with a higher sensitivity. Combined with surrogate model, a data-driven design platform for airfoil in ground-effect aerodynamic optimization was established. The camber line of the optimized airfoil exhibits a wavy pattern that resembles S-curve. The optimization of the airfoil resulted in a forward shift the locations of the aerodynamic center of altitude and a backward shift in the locations of the aerodynamic center of pitch. This improvement increased the static height stability by 16.38%, with the change range of the lift-to-drag ratio is only 0.2425%, meeting the constraint requirements. The method has certain significance for the optimization of airfoils in ground effect area.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110071"},"PeriodicalIF":5.0,"publicationDate":"2025-02-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143437904","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

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

IF 5 1区工程技术

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

{"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

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

{"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

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

{"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