Aerospace Science and Technology最新文献

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

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

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

IF 5 1区工程技术

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

{"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

Aerospace Science and Technology Pub Date : 2025-02-15 DOI: 10.1016/j.ast.2025.110069

Zhiyuan Wang , Chong Pan , Zepeng Cheng

{"title":"Assessment of prevalent vortex-center detection criteria for the compensation of wandering motion of wingtip vortices","authors":"Zhiyuan Wang , Chong Pan , Zepeng Cheng","doi":"10.1016/j.ast.2025.110069","DOIUrl":"10.1016/j.ast.2025.110069","url":null,"abstract":"<div><div>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.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110069"},"PeriodicalIF":5.0,"publicationDate":"2025-02-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143453822","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

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

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

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

{"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

Aerospace Science and Technology Pub Date : 2025-02-14 DOI: 10.1016/j.ast.2025.110067

Ning Sun, Haibin Duan, Mengzhen Huo

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

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

{"title":"Dynamic performance of composite laminate wing beam structures of aeronautical engineering with complex geometrical profiles","authors":"Chen-Guang Wang , Xu-Yuan Song , Jian Zang , Zhen Zhang , Ye-Wei Zhang , Li-Qun Chen","doi":"10.1016/j.ast.2025.110024","DOIUrl":"10.1016/j.ast.2025.110024","url":null,"abstract":"<div><div>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.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110024"},"PeriodicalIF":5.0,"publicationDate":"2025-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143453820","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