Aerospace Science and Technology最新文献_第2页

Dynamical modelling of NASA's ACS3 solar sail mission

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-18 DOI: 10.1016/j.ast.2025.110146

Andrea Minervino Amodio, Pieter Visser, Jeannette Heiligers

{"title":"Dynamical modelling of NASA's ACS3 solar sail mission","authors":"Andrea Minervino Amodio, Pieter Visser, Jeannette Heiligers","doi":"10.1016/j.ast.2025.110146","DOIUrl":"10.1016/j.ast.2025.110146","url":null,"abstract":"<div><div>NASA's ACS3 mission aims to be the first Earth-bound solar sail to execute calibration steering laws for in-orbit estimation of solar-sail acceleration parameters. To maximise the mission's scientific return, this study identifies the physical effects to include in the dynamical model, the solar-sail acceleration parameters observable from flight data, and the uncertainties to consider during the orbit determination process. The sensitivity of the solar-sail dynamics to perturbations, model uncertainties, and sail-attitude errors is investigated by 1) comparing a reference orbit with modified orbits, each altered in a single dynamical aspect, and 2) evaluating the accuracy of modified models in reconstructing the reference orbit through iterative initial state adjustments.</div><div>For the one-sigma 10-meter observation noise level of the ACS3 mission and a seven-day arc, results indicate that higher-order lunar perturbations, planetary third-body effects, and relativistic corrections can be omitted from the dynamical model. Additionally, the geopotential expansion may be limited to degree and order 32. In contrast, the dynamics should include the effects of solid Earth tides, account for the instantaneous Sun-sailcraft distance in the solar radiation pressure model, and assume imperfect reflection from the sail surface in the solar and planetary radiation pressure models. Furthermore, the analysis reveals varying levels of observability for the sail optical coefficients, with frontside reflectivity and specularity showing the strongest influence on the solar-sail dynamics. Finally, systematic attitude errors and uncertainties in atmospheric density and accommodation coefficients are the most challenging factors to absorb through initial state adjustment, potentially complicating the estimation of solar-sail acceleration parameters.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110146"},"PeriodicalIF":5.0,"publicationDate":"2025-03-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685458","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

Nonlinear bending of sandwich plates with deep learning inverse-designed 3D auxetic lattice core 采用深度学习逆向设计三维辅助晶格核心的夹层板非线性弯曲

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-17 DOI: 10.1016/j.ast.2025.110148

Xi Fang, Hui-Shen Shen, Hai Wang

{"title":"Nonlinear bending of sandwich plates with deep learning inverse-designed 3D auxetic lattice core","authors":"Xi Fang, Hui-Shen Shen, Hai Wang","doi":"10.1016/j.ast.2025.110148","DOIUrl":"10.1016/j.ast.2025.110148","url":null,"abstract":"<div><div>Based on generative deep learning (DL), this paper innovatively proposes a sandwich panel with inverse-designed 3D auxetic cores. Furthermore, we demonstrate that the bending performance of such data-driven sandwich structure is superior to existing design which consists of 3D lattice core evolved from the traditional 2D re-entrant honeycomb design. The deflection related to proposed DL-based sandwich plate is nearly one-third of that in existing studies. Through metal additive manufacturing techniques and finite element (FE) modeling, flexural behaviors of the inverse-designed 3D truss unit cell with different geometric factor is further examined. With different functionally graded core configurations and uniform distributed as comparison group, parametric studies are conducted to investigate the effect of various dimensional parameters, thermal environments and boundary conditions on the nonlinear bending behaviors and effective Poisson's ratio of sandwich plates subjected to a uniform pressure. This work provides a reference for the study of mechanical properties of novel auxetic sandwich structures and has potential guiding implications for accelerating the design process and performance optimization of sandwich plates.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110148"},"PeriodicalIF":5.0,"publicationDate":"2025-03-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685460","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 structural damage identification model with finite thermomechanical sensors of the re-entry module 带有限热机械传感器的返回舱结构损伤识别模型

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-17 DOI: 10.1016/j.ast.2025.110150

Xiao-Bing Ma , Rui Guo , Hua Su , Chun-Lin Gong , Jian-Jun Gou

{"title":"A structural damage identification model with finite thermomechanical sensors of the re-entry module","authors":"Xiao-Bing Ma , Rui Guo , Hua Su , Chun-Lin Gong , Jian-Jun Gou","doi":"10.1016/j.ast.2025.110150","DOIUrl":"10.1016/j.ast.2025.110150","url":null,"abstract":"<div><div>The re-entry module encounters extremely harsh aerodynamic pressure and heating conditions, and the high-precision identification of the structural damage state is crucial to the flight and reuse performance evaluation. The current techniques are mainly based on complex numerical simulations or indirect sensor measurements of finite nodes in time or space dimensions, respectively. This work developed a damage identification model that included numerical simulations, sensor measurements, and additional machine learnings to obtain the structural damage state of the module. First, the primary damage database was established by thermomechanical numerical simulations and a structural damage model, which was proposed based on the strain-equivalent-based stiffness reduction method with certain structural partition rules. Second, a database expansion method with higher accuracy based on the Kriging agent model was proposed, the damage database was expanded by 10 times with 7 % error. Third, the damage identification model was developed with inputs of the finite nodal temperature and stress and output of structural damage value based on the back propagation neural network, and a structural damage grade evaluation equation was finally formulated. The result shows that the model overfitting is fully suppressed and the identification error is reduced by 60 % compared with the original data without expansion, and great identification accuracy of 92.6 % with error threshold of 0.03 and good anti-interference ability of 1 % sensor noise are exhibited for the model. The model holds higher recognition efficiency and accuracy of structural residual capacity and indicates potentials for real-time safety assessment of re-entry module.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110150"},"PeriodicalIF":5.0,"publicationDate":"2025-03-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685409","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

Near-asteroid spacecraft formation control with prescribed-performance: A dynamic event-triggered reinforcement learning control approach

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-17 DOI: 10.1016/j.ast.2025.110138

Ran Sun , Choon Ki Ahn , Deyun Liu , Wei Wang , Chengxi Zhang

{"title":"Near-asteroid spacecraft formation control with prescribed-performance: A dynamic event-triggered reinforcement learning control approach","authors":"Ran Sun , Choon Ki Ahn , Deyun Liu , Wei Wang , Chengxi Zhang","doi":"10.1016/j.ast.2025.110138","DOIUrl":"10.1016/j.ast.2025.110138","url":null,"abstract":"<div><div>This paper presents an event-triggered approximate optimal tracking control method for near-asteroid spacecraft formation flying systems. Compared with the traditional open-loop optimal control, the proposed solution optimizes the trade-off between tracking performance and online energy consumption by combining prescribed performance control and reinforcement learning. Specifically, a state transformation approach is employed to convert the relative error systems into a form with adjustable performance metrics. Then, a policy iteration algorithm is developed to derive the optimal control policy for the transformed system, which leverages historical data to relax the persistence of excitation conditions. Furthermore, a new Lipschitz-assumption-free dynamic event-triggered mechanism is incorporated to activate the approximate optimal controller only under specific conditions, further reducing the control update frequency. Finally, simulation results show that the update numbers can be lower by 40% compared to the static event-triggered scheme.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110138"},"PeriodicalIF":5.0,"publicationDate":"2025-03-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143643555","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 theory of functional connections-based method for orbital pursuit-evasion games with analytic satisfaction of rendezvous constraints

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-17 DOI: 10.1016/j.ast.2025.110142

Chengming Zhang, Yanwei Zhu, Leping Yang

{"title":"A theory of functional connections-based method for orbital pursuit-evasion games with analytic satisfaction of rendezvous constraints","authors":"Chengming Zhang, Yanwei Zhu, Leping Yang","doi":"10.1016/j.ast.2025.110142","DOIUrl":"10.1016/j.ast.2025.110142","url":null,"abstract":"<div><div>This study proposed an efficient approach to address the boundary constraints in the context of rendezvous with the noncooperative target within the vicinity of elliptical orbits. The problem was transformed into a two-point boundary value problem (TPBVP) constituted by series of boundary constraints and differential equation constraints by deriving the necessary conditions for the saddle-point strategy. The switching functions embedded with the boundary constraints equations were derived through the Theory of Functional Connections (TFC) to deal with the boundary constraints. Subsequently, the nested function structure with two levels was applied to be the free functions, which was involved in the constrainted expressions together with switching functions to treate the differential equation constraints. Simulation outcomes confirmed the superior computational efficiency of this method when compared to previous studies. Furthermore, a comprehensive analysis was undertaken to explore the impact of orbital eccentricity and true anomaly on the game's results, offering critical insights for enhancing spacecraft safety during on-orbit operations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110142"},"PeriodicalIF":5.0,"publicationDate":"2025-03-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143643557","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

Designing a variable camber wing trailing edge with initially curved beams 设计带有初始弯曲梁的可变外倾角机翼后缘

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-16 DOI: 10.1016/j.ast.2025.110151

Haoyang Huang , Yitong Fan , Zhiqiang Ke , Ding Tang , Weiming Wang , Dayong Li

{"title":"Designing a variable camber wing trailing edge with initially curved beams","authors":"Haoyang Huang , Yitong Fan , Zhiqiang Ke , Ding Tang , Weiming Wang , Dayong Li","doi":"10.1016/j.ast.2025.110151","DOIUrl":"10.1016/j.ast.2025.110151","url":null,"abstract":"<div><div>In recent years, variable camber wings (VCWs) have gained significant attention worldwide because of their advantages in improving fuel efficiency, reducing turbulence, and providing an adjustable lift-to-drag ratio for future aircraft. Although many attempts have been made to design the structure of VCWs, the design of VCWs with large deformations and high loading capacities remains lacking. This study proposes a novel method for designing VCWs by applying initially curved beams (ICBs). Through a compliance analysis of ICBs versus straight beams, it is evident that ICBs provide a more comprehensive compliance range than straight beams. Utilizing the compliance properties of ICBs, a VCW trailing edge (TE) structure was proposed and parameterized. To minimize deformation errors and post-deformation stress, finite element models were established, and a genetic algorithm was employed to optimize the cross-sectional geometry and dimensions. An optimized cross-sectional TE prototype was fabricated. Subsequently, experiments on the variable camber, digital image correlation (DIC), and load bearing were conducted to validate the function of the variable camber, measure the stress level, and assess the load-bearing capacity. The experimental results were consistent with those of the simulations. The 5 cm-wide TE prototype achieved the variable camber range of ±25° with a maximum stress of 243 MPa along with notable deformation accuracy. It has a static load capacity of 10 kg. These results confirmed the feasibility of designing VCWs capable of large deformations and high loading capacities, utilizing ICBs.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110151"},"PeriodicalIF":5.0,"publicationDate":"2025-03-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685407","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

Robust parameter design for rocket boosters using deep Gaussian process 利用深度高斯过程进行火箭助推器的稳健参数设计

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-16 DOI: 10.1016/j.ast.2025.110143

Chunfeng Ding , Jianjun Wang , Xiaoying Chen , Zebiao Feng , Yan Ma

{"title":"Robust parameter design for rocket boosters using deep Gaussian process","authors":"Chunfeng Ding , Jianjun Wang , Xiaoying Chen , Zebiao Feng , Yan Ma","doi":"10.1016/j.ast.2025.110143","DOIUrl":"10.1016/j.ast.2025.110143","url":null,"abstract":"<div><div>In aerospace engineering optimization, multiple correlated non-stationary responses (NSRs) are often produced. Ignoring the non-stationary characteristic of data may impact the prediction accuracy of response surface models and the reliability of optimization solutions. Traditional stationary Gaussian process model struggles to handle non-stationary data with limited samples. Recently, deep Gaussian process (DGP) has gained popularity in non-stationary models due to its ability to handle rapidly changing data. However, efficiently inferring the posterior distribution of DGP remains a significant challenge. This paper uses DGP surrogate model based on Bayesian inference to simulate non-stationary response surfaces and proposes the Chain Rule Hamiltonian Monte Carlo (CRHMC) algorithm to efficiently and accurately sample the posterior distribution. Additionally, a new multivariate quality loss function (MQLF) is introduced to optimize multiple correlated non-stationary responses and ensure the robustness of optimal design parameters. Numerical examples and a real rocket booster engineering case demonstrate the superiority of the proposed method in fast computation and robust optimization against other competing methods.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110143"},"PeriodicalIF":5.0,"publicationDate":"2025-03-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685408","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 mesh reflector design method with triangle-quadrangle mixture based on electromagnetic performance

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-16 DOI: 10.1016/j.ast.2025.110149

Xiang Xu, Tuanjie Li

引用次数: 0

Thermal non-equilibrium nonlinear coupled constitutive relations for hypersonic rarefied diatomic gas flows

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-15 DOI: 10.1016/j.ast.2025.110147

Shuhua Zeng , Junyuan Yang , Wenwen Zhao , Jiaqi An , Wanshu Li , Weifang Chen

{"title":"Thermal non-equilibrium nonlinear coupled constitutive relations for hypersonic rarefied diatomic gas flows","authors":"Shuhua Zeng , Junyuan Yang , Wenwen Zhao , Jiaqi An , Wanshu Li , Weifang Chen","doi":"10.1016/j.ast.2025.110147","DOIUrl":"10.1016/j.ast.2025.110147","url":null,"abstract":"<div><div>The generalized hydrodynamic theory and its derived nonlinear coupled constitutive relations (NCCR) model have proven effective in simulating a range of typical hypersonic rarefied non-equilibrium flows, particularly in regimes where traditional Navier-Stokes (NS) equations are inadequate. However, the treatment of bulk viscosity has been limited, serving primarily as an approximation for rotational non-equilibrium effects, and lacking an explicit framework for energy exchange between different modes within the NCCR model. To address this limitation, this study introduces a thermal non-equilibrium NCCR model that operates without bulk viscosity, incorporating the Landau-Teller-Jeans relaxation model to facilitate explicit energy exchange between translational and rotational modes. The model's accuracy has been rigorously validated through a series of classical numerical cases, including analyzing nitrogen shock structures, supersonic flow over a flat plate, and hypersonic flows past blunt and flat-headed cylinders. The results demonstrate a significant improvement in alignment with experimental data and direct simulation Monte Carlo (DSMC) solutions compared to those derived from the NS equations and the original NCCR model lacking bulk viscosity. Furthermore, the proposed model enhances the predictive capability over the original NCCR framework and elucidates the mechanisms of non-equilibrium energy exchange between modes. These findings underscore the potential of the thermal non-equilibrium NCCR model as a robust and accurate tool for the simulation of hypersonic rarefied diatomic gas flows.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110147"},"PeriodicalIF":5.0,"publicationDate":"2025-03-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685455","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

Assessing turbulence model budgets in supersonic rectangular jets using large Eddy simulations

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-03-13 DOI: 10.1016/j.ast.2025.110141

Kalyani R. Bhide , Daniel R. Cuppoletti

{"title":"Assessing turbulence model budgets in supersonic rectangular jets using large Eddy simulations","authors":"Kalyani R. Bhide , Daniel R. Cuppoletti","doi":"10.1016/j.ast.2025.110141","DOIUrl":"10.1016/j.ast.2025.110141","url":null,"abstract":"<div><div>This work aims to identify the sources of inaccuracies in Reynolds Averaged Navier-Stokes (RANS) and discuss the areas of improvements to enhance the predictions rectangular supersonic jets using LES, particularly for potential core lengths, jet mixing, and turbulence anisotropy. Budgets are analyzed for Turbulent kinetic energy (TKE) and Reynolds stress in various RANS models for a non-axisymmetric supersonic jet using well-validated Large Eddy Simulations (LES) as reference database. Examined RANS closures include Boussinesq (BSQ) <span><math><mrow><mi>k</mi><mo>−</mo><mi>ω</mi></mrow></math></span> Shear Stress Transport (SST), quadratic <span><math><mrow><mi>k</mi><mo>−</mo><mi>ω</mi></mrow></math></span> SST (QCR), and Reynolds stress model (RSM). A term-to-term comparison of Turbulent Kinetic Energy (TKE) and Reynolds stress budgets between RANS and LES is presented. In two-equation RANS, production in the shear layer is balanced by dissipation, with minimal diffusion. Thus, the diffusion along the jet centerline in RANS is delayed, resulting in slower mixing and longer potential cores. Although QCR accounts for the Reynolds stress anisotropy, it does not bring significant improvement to the TKE budget, suggesting that TKE transport remains minimally affected by the constitutive relation. RSM reproduces Reynolds stress budget trends, for production and pressure strain acting as source and sink respectively. However, the reduction in pressure strain correlation with increasing convective Mach number, is not predicted well. Primary areas for RANS improvement are identified, emphasizing the need to move beyond linear RANS, towards directly capturing the stress-strain relationship.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110141"},"PeriodicalIF":5.0,"publicationDate":"2025-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685456","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