Aerospace Science and Technology最新文献_第10页

Modeling and analysis of performance degradation in proton exchange membrane fuel cell system for aviation applications 航空用质子交换膜燃料电池系统性能退化建模与分析

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-25 DOI: 10.1016/j.ast.2025.110236

Le Kang , Shixuan Lin , Shengze Bao , Junkui Mao

{"title":"Modeling and analysis of performance degradation in proton exchange membrane fuel cell system for aviation applications","authors":"Le Kang , Shixuan Lin , Shengze Bao , Junkui Mao","doi":"10.1016/j.ast.2025.110236","DOIUrl":"10.1016/j.ast.2025.110236","url":null,"abstract":"<div><div>Proton Exchange Membrane Fuel Cell Systems (PEMFCS) are considered an ideal power source for addressing the aviation industry's decarbonization demands. However, their performance adaptability under aviation-specific operational conditions has not been thoroughly investigated or theoretically validated. This study aims to characterize the performance degradation of PEMFCS in aviation environments and explore corresponding regulation strategies to maintain their functionality. A performance degradation model for PEMFCS under aviation conditions was developed and validated through experimental data, demonstrating high simulation accuracy. The study systematically evaluated the impact of aviation environmental factors on PEMFCS performance and quantified its degradation across full-flight operating conditions. Results revealed that during the cruise phase, power decay in PEMFCS leads to insufficient thrust to meet operational demands. To address this issue, humidification and pressurization measures were implemented, reducing maximum performance degradation from 46.28 % to 29.12 % and 3 %, respectively, effectively mitigating power deficits at high altitudes. This research identifies the mechanisms of PEMFCS power insufficiency under aviation conditions and proposes control strategies to maintain performance. The findings provide feasible solutions and quantitative safety assessments, offering critical support for the practical application of PEMFCS in aviation.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110236"},"PeriodicalIF":5.0,"publicationDate":"2025-04-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143898400","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

Maneuvering target tracking based on a random motion model and integrated random interacting multiple model filtering 基于随机运动模型和集成随机交互多模型滤波的机动目标跟踪

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-25 DOI: 10.1016/j.ast.2025.110244

Fengqi Yang , Jinshan Zhong , Yingting Luo, Ying Zhang, Xiaojing Shen, Yunmin Zhu

{"title":"Maneuvering target tracking based on a random motion model and integrated random interacting multiple model filtering","authors":"Fengqi Yang , Jinshan Zhong , Yingting Luo, Ying Zhang, Xiaojing Shen, Yunmin Zhu","doi":"10.1016/j.ast.2025.110244","DOIUrl":"10.1016/j.ast.2025.110244","url":null,"abstract":"<div><div>Traditional maneuvering target tracking algorithms assume that the target motion model is either fixed or limited in number. For high-speed and highly maneuvering targets, the tracker's performance degrades rapidly when the model set fails to adequately encompass the maneuvering mode or when there is a substantial deviation. Therefore, we propose a novel maneuvering target tracking method based on a random motion model. This algorithm employs a random model to describe the target maneuver, which is more widely applicable than traditional algorithms and remains more stable when the target maneuver is not covered by the model set. Additionally, in cases where the model set of the Interacting Multiple Model algorithm (IMM) does not align with the actual maneuvering state, the new method exhibits a smaller tracking error compared to IMM and shows no divergence trend. Finally, we combine IMM and the random motion model to propose an Integrated Random Interacting Multiple Model algorithm (IRIMM). The performance of the IRIMM algorithm closely matches that of IMM when provided with a perfectly accurate model set and significantly improves tracking effectiveness and stability when the model is incorrect.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110244"},"PeriodicalIF":5.0,"publicationDate":"2025-04-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143882065","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

Air-breathing wide-range vehicle configuration concepts with double-sided inlet based on the waverider theory 基于乘波器理论的双面进气道吸气式大范围车辆配置概念

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-25 DOI: 10.1016/j.ast.2025.110259

Shibin Luo , Yuhang Sun , Jiaqi Tian , Jun Liu

{"title":"Air-breathing wide-range vehicle configuration concepts with double-sided inlet based on the waverider theory","authors":"Shibin Luo , Yuhang Sun , Jiaqi Tian , Jun Liu","doi":"10.1016/j.ast.2025.110259","DOIUrl":"10.1016/j.ast.2025.110259","url":null,"abstract":"<div><div>Air-breathing wide-range vehicles have garnered widespread attention for their long voyages, high specific impulse, and broad flight envelope. Such vehicles must operate in different airspace and speed environments. Based on the cone-derived waverider theory, this paper proposes two double-sided intake configurations suitable for wide-range flight: one with jettisonable fuel tanks and inlets, and the other as a full-waverider reversible double-sided intake. Both configurations have similar design processes. Subsequently, numerical methods are used to assess their feasibility. Pressure contours and aerodynamic coefficients at different Mach numbers show that both configurations exhibit excellent wave-riding characteristics during Mach 7 high-speed and Mach 5 low-speed cruises. The first vehicle changes from a double-sided intake to a dorsal intake configuration with full wave-riding characteristics on its lower surface by jettisoning one inlet and spent auxiliary fuel tank. This strategy not only addresses the weight issues caused by the double inlets but also achieves a maximum lift-to-drag ratio of over four at both cruising points. The second vehicle utilizes full-waverider theory for both upper and lower surfaces. This configuration allows simultaneous wave-riding of the airframe and inlet at both cruises and possesses higher positive lift than the like-rotating-body configuration. In particular, the newly refined configuration shows an improvement of over 6 % in the maximum lift-to-drag ratio during cruise compared to the like-rotating-body configuration. Moreover, the Mach 7 waverider surface has a larger wall compression angle than the Mach 5 surface, resulting in significantly better aerodynamic performance for both configurations at Mach 7 compared to Mach 5.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110259"},"PeriodicalIF":5.0,"publicationDate":"2025-04-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143891872","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

Anti-saturation prescribed-time control for stochastic systems of free-flying space robots using a self-adapting non-monotonic approach 基于自适应非单调方法的自由飞行空间机器人随机系统抗饱和时间控制

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-24 DOI: 10.1016/j.ast.2025.110231

Yu Xia , Jun He , Kaixin Li , Feng Gao , Ramesh K. Agarwal

{"title":"Anti-saturation prescribed-time control for stochastic systems of free-flying space robots using a self-adapting non-monotonic approach","authors":"Yu Xia , Jun He , Kaixin Li , Feng Gao , Ramesh K. Agarwal","doi":"10.1016/j.ast.2025.110231","DOIUrl":"10.1016/j.ast.2025.110231","url":null,"abstract":"<div><div>This paper proposes an anti-saturation prescribed-time control scheme for free-flying space robots (FFSRs) subject to system uncertainties, external disturbances, input saturation, and output constraint. Initially, the control scheme is developed based on a newly constructed stochastic model, introducing stochastic neural networks (SNNs) to approximate the lumped stochastic factor that encompasses system uncertainties and external disturbances. Subsequently, a novel self-adapting non-monotonic prescribed-time function is proposed, integrating input saturation as an adaptive variable to dynamically adjust the constraint boundaries. This integration enables the constraint boundaries to adaptively expand in a non-monotonic manner in response to the occurrence of input saturation. Moreover, the constraint boundaries are designed as tunnel-shaped to prevent overshoot. The proposed control scheme ensures that all closed-loop signals are semi-globally uniformly ultimately bounded in probability, with the tracking error stabilized within a prescribed time. Finally, simulation results validate the effectiveness and superiority of the proposed scheme.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110231"},"PeriodicalIF":5.0,"publicationDate":"2025-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143879104","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

Optimization strategy for ensemble learning models based on fusing resampling, adaptive dimensionality reduction, and Optuna in intelligent flight technology evaluation 智能飞行技术评估中基于融合重采样、自适应降维和Optuna的集成学习模型优化策略

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-24 DOI: 10.1016/j.ast.2025.110251

Jinyi Mao , Jian Chen , Yaoji Deng

{"title":"Optimization strategy for ensemble learning models based on fusing resampling, adaptive dimensionality reduction, and Optuna in intelligent flight technology evaluation","authors":"Jinyi Mao , Jian Chen , Yaoji Deng","doi":"10.1016/j.ast.2025.110251","DOIUrl":"10.1016/j.ast.2025.110251","url":null,"abstract":"<div><div>The flight techniques of pilots directly impact flight safety and constitute the primary factors influencing aviation accidents. However, existing research is limited by several challenges, including overly subjective evaluation criteria, the inability to implement large-scale data-driven approaches, and suboptimal outcomes. In this paper, a novel dynamic assessment framework for flight technique is proposed based on QAR data. The framework employs multiple ensemble learning models as baselines, fusing a three-stage optimization strategy. First, resampling techniques are introduced to address data imbalance. Second, a Stepwise Feature Selection-Adaptive Dimensionality Reduction (SFS-ADR) method is developed to efficiently reduce flight parameter dimensionality. Finally, Optuna hyperparameter optimization is adopted to further enhance model precision. Experiments on four public datasets demonstrate that the optimization strategy achieves accuracy improvements of 8.45%, 7.51%, 7.37%, and 7.22% respectively, with consistent superiority over baseline models. Model interpretability is further validated through SHapley Additive exPlanation (SHAP) method. The framework provides a high-precision dynamic solution for flight technique evaluation, offering valuable insights for Human Factors (HF) research in aviation safety.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110251"},"PeriodicalIF":5.0,"publicationDate":"2025-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143891857","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

Self-adaptive turbulence eddy simulation of a dual-mode, multi-stage, and cavity-based scramjet combustor 双模多级空腔超燃冲压发动机燃烧室自适应湍流涡模拟

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-24 DOI: 10.1016/j.ast.2025.110228

Pengfei Xie , Zhaoyang Xia , Xingsi Han

{"title":"Self-adaptive turbulence eddy simulation of a dual-mode, multi-stage, and cavity-based scramjet combustor","authors":"Pengfei Xie , Zhaoyang Xia , Xingsi Han","doi":"10.1016/j.ast.2025.110228","DOIUrl":"10.1016/j.ast.2025.110228","url":null,"abstract":"<div><div>Efficient modeling of turbulence and combustion for high-fidelity numerical simulations of supersonic combustion remains a long-standing challenge, particularly with respect to balancing accuracy and computational resource demands. This study presents a novel unified turbulence modeling approach, termed Self-Adaptive Turbulence Eddy Simulation (SATES), which is coupled with the classical Eddy Dissipation Concept (EDC) model to investigate the HIFiRE-2 scramjet at a Mach 5.84 flight condition. The SATES-EDC results demonstrate good agreements with ground test experimental measurements and show insensitivity to current mesh resolutions. Notable features such as dual-mode characteristics, vorticity transport, and three-dimensional effects are identified within the combustor, which can be divided into three distinct regions: the primary combustion zone, the cavity region, and the secondary combustion zone. The primary combustion region is characterized by boundary layer separation and jet-wake transportation, while the cavity primarily facilitates species transport. The secondary combustion zone exhibits typical features of a transverse jet in cross-flow and releases more heat than the primary combustion region. Quantitative analysis indicates that heat release in both combustion zones is predominantly governed by the subsonic mode and diffusion flames, with significant combustion occurring within the thin reaction zone and fast chemistry region, characterized by a relatively high Damköhler number. These findings underscore the efficacy of the SATES method coupled with the EDC model for complex supersonic combustion scenarios and provide valuable insights for scramjet combustors.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110228"},"PeriodicalIF":5.0,"publicationDate":"2025-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143894873","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

Numerical study on the internal flow mechanisms of variable geometry high-load low-pressure turbine cascade under wide operating conditions 宽工况下变几何高负荷低压涡轮叶栅内部流动机理的数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-24 DOI: 10.1016/j.ast.2025.110246

Mai Li , Jun Liu , Xiaodan Zhang , Hang Yuan , Wenying Ju , Xingen Lu

{"title":"Numerical study on the internal flow mechanisms of variable geometry high-load low-pressure turbine cascade under wide operating conditions","authors":"Mai Li , Jun Liu , Xiaodan Zhang , Hang Yuan , Wenying Ju , Xingen Lu","doi":"10.1016/j.ast.2025.110246","DOIUrl":"10.1016/j.ast.2025.110246","url":null,"abstract":"<div><div>Variable geometry turbines (VGTs) serve as critical components in adjustable aeroengines. In this work, validated numerical simulations are employed to systematically study the internal flow mechanisms of an adjustable high-load low-pressure turbine vane across varying installation angles, and the local clearance effects are analysed under practical operating conditions. The results reveal that high-load blades demonstrate enhanced flow adaptability compared with conventional designs, achieving a flow modulation range of 55.5 %-135.5 %. This improved adjustability stems from the amplified transverse pressure gradients within the blade passages, and these gradients intensify the endwall secondary flow losses (proportionally higher in total losses) and generate complex vortical structures, including passage vortices (PVs), trailing-edge vortices (TVs), and corner vortices (CVs). Extreme positive angles induce pressure‒surface separation vortices (SVs) with spanwise propagation; this increases the aerodynamic losses through channel blockage. Conversely, reduced angles primarily cause suction–surface separation near the leading edges, where the separation losses surpass the mid-chord flow detachment effects. Local clearance exhibits dual functionality: moderately expanding the inter-blade passage area to enhance the flow capacity while generating leakage vortices (LV) that interact with the endwall vortices. At reduced angles, the LV intensity inversely correlates with the flow rate, and the loss mechanisms are dominant in the low-flow regimes. The clearance-induced loss regions exhibit radial downwards migration across all angles, and the LV‒PV interactions intensify the secondary losses between 0.02<<em>z</em>/<em>h</em> < 0.04. These findings highlight the inherent compromise between the flow adaptability and loss accumulation in VGTs, particularly under off-design operating conditions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110246"},"PeriodicalIF":5.0,"publicationDate":"2025-04-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143898399","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 the structural design of fixed-wing airframes for next-generation electric aircraft 下一代电动飞机固定翼机身结构设计评估

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110224

Kathrin Schulte , Steven O’Keefe , Maksym Rybachuk , Sascha Stegen

{"title":"Assessing the structural design of fixed-wing airframes for next-generation electric aircraft","authors":"Kathrin Schulte , Steven O’Keefe , Maksym Rybachuk , Sascha Stegen","doi":"10.1016/j.ast.2025.110224","DOIUrl":"10.1016/j.ast.2025.110224","url":null,"abstract":"<div><div>The aviation industry faces a major push for a technology transformation to electric propulsion systems as current worldwide environmental requirements demand a shift from fossil fuels to sustainable energy. To achieve this, improved airframe and propulsion systems must be developed, while keeping the strict regulations and standards of the aviation safety authorities in mind. This paper focusses on the introduction of traction batteries and electric motors in the general and civil aviation industry by assessing the potential of proven airframe designs as well as unconventional concepts for electric aircraft. First, hybrid and all-electric propulsion system concepts are examined by evaluating the feasibility and integration challenges based on a comparative analysis of existing electric aircraft which provide insights into current industry practices. Also, general principles of aircraft design are explored, which can be tailored to electric propulsion systems, highlighting key structural modifications required for optimized performance. In this study, the impact of suitable State-of-the-Art as well as future battery and motor performances on the range, mass and aircraft structure are investigated. For this approach, two aircraft of different sizes and use are taken into consideration. The Cessna 172S for recreational purposes and the ATR72–600 for regional passenger transport. The findings of the investigation and calculations offer a holistic perspective on the design as well as operational considerations necessary for advancing electric aircraft. Thus, this paper provides a comprehensive current picture of the transition to sustainable aviation solutions and a guide for future innovations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"163 ","pages":"Article 110224"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143911840","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

Numerical and experimental investigation of multifunctional high-efficiency anti-icing nickel-plated carbon fiber heating elements for wing-shaped composite airfoils 翼型复合材料翼型多功能高效防冰镀镍碳纤维加热元件的数值与实验研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110249

Won Tae Lee , Dong Jun Hong , Young Woo Nam , Rho Shin Myong

{"title":"Numerical and experimental investigation of multifunctional high-efficiency anti-icing nickel-plated carbon fiber heating elements for wing-shaped composite airfoils","authors":"Won Tae Lee , Dong Jun Hong , Young Woo Nam , Rho Shin Myong","doi":"10.1016/j.ast.2025.110249","DOIUrl":"10.1016/j.ast.2025.110249","url":null,"abstract":"<div><div>This study introduces wing-shaped composite airfoils integrated with high-efficiency, multifunctional anti-icing heating elements composed of nickel-plated carbon fiber. The anti-icing performance of these airfoils was evaluated through experiments conducted in an Icing Research Tunnel (IRT) under representative glaze icing conditions. These results indicate that the nickel-plated carbon fiber exhibits an electrothermal conversion efficiency of 0.1 W/℃ and a heating rate of 0.64 ℃/s. In particular, icing wind tunnel tests conducted at a power density of 9.0 kW/m² demonstrated that the heating zone remained above the freezing point, thereby preventing ice accretion, while runback ice formed in the region c orresponding to X/<em>C</em> ≈ 24–32 % during a 300 s accretion period. The experimental results demonstrated high reliability and accuracy, showing a temperature difference of <0.5 °C compared to the surface temperature predicted by the multiphysics anti-icing simulation under identical conditions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110249"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143894887","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

Adjustability analysis and experiment for mesh antenna 网状天线的可调性分析与实验

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-04-23 DOI: 10.1016/j.ast.2025.110250

Yongxiang Huang , Tuanjie Li , Xiang Xu , Zhiyang Shi , Xifan Xu

{"title":"Adjustability analysis and experiment for mesh antenna","authors":"Yongxiang Huang , Tuanjie Li , Xiang Xu , Zhiyang Shi , Xifan Xu","doi":"10.1016/j.ast.2025.110250","DOIUrl":"10.1016/j.ast.2025.110250","url":null,"abstract":"<div><div>Mesh antenna plays an important role in the field of space communication. Surface accuracy is the key factor to determine the electrical performance of mesh antenna, which needs to be ensured by surface adjustment. Because the mesh antenna has variable stiffness and great flexibility, the surface may be 'non-adjustable' within the limited range of the adjustment device, in the sense that it is not possible to further improve the surface accuracy by surface adjustment. In order to directly describe the adjustment state of the surface through the structure parameters of the mesh antenna, a method of calculating the surface adjustability is proposed to quantitatively describe the degree of further adjustment of the surface. Three parameters which affect the adjustability are put forward: the adjustment force margin parameter, the adjustment amount margin parameter and the accuracy adjustable parameter. The adjustment balance equations for mesh antenna surface are established, and the relationship between surface structure parameters and influence parameters is deduced. The method of calculating the adjustability of surface by influencing parameters is given. The experimental results show that the surface adjustability can not only accurately reflect the adjustment state of the surface, but also guide the selection of the adjustment configuration, which can effectively improve the surface accuracy compared with the traditional method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110250"},"PeriodicalIF":5.0,"publicationDate":"2025-04-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143882063","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