Aerospace Science and Technology最新文献_第9页

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

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

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

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-15 DOI: 10.1016/j.ast.2025.110068

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

{"title":"Adaptive reset control for group-bipartite formation of multi-UAVs subject to transmission delays","authors":"Zhen Tang , Xinhua Wang , Ziyang Zhen , Zhengen Zhao , Teng Cao , Geert Deconinck","doi":"10.1016/j.ast.2025.110068","DOIUrl":"10.1016/j.ast.2025.110068","url":null,"abstract":"<div><div>Existing multi-UAV formation control methods face challenges in achieving stable and fast tracking under transmission delays and inaccessible information, particularly when addressing the design of various formation configurations and optimizing transient performance. To address these challenges, this paper proposes an adaptive reset control technique that integrates virtual leaders and state observers to achieve fast and accurate time-varying group-bipartite formation tracking in multi-UAV systems. Firstly, a state observer is designed to accurately estimate the position and velocity of each UAV. Then, a distributed adaptive group-bipartite time-varying formation tracking controller with a reset component is introduced. This controller enables each UAV to adjust its position and velocity according to neighboring UAVs, thus achieving the desired group-bipartite formation. The inclusion of reset component significantly enhances the transient performance of formation. Moreover, the sufficient conditions were derived for group-bipartite formation control by employing a novel Lyapunov-Krasovskii functional, which constructed with the matrix-valued polynomial, the Bessel-Legendre inequality, and the reciprocally convex matrix inequality. Finally, the effectiveness and advantages of the proposed control strategy are demonstrated through comprehensive simulations involving multiple fixed-wing UAVs.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110068"},"PeriodicalIF":5.0,"publicationDate":"2025-02-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143474517","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

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

IF 5 1区工程技术

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

Design exploration of UAM vehicles

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-13 DOI: 10.1016/j.ast.2025.110058

Sen Wang, Lourenço Tércio Lima Pereira, Daniele Ragni

{"title":"Design exploration of UAM vehicles","authors":"Sen Wang, Lourenço Tércio Lima Pereira, Daniele Ragni","doi":"10.1016/j.ast.2025.110058","DOIUrl":"10.1016/j.ast.2025.110058","url":null,"abstract":"<div><div>This study describes a design exploration of Urban Air Mobility (UAM) vehicles, based on top-level aircraft requirements. The exploration focuses on a fully electric vertical takeoff and landing (eVTOL) vehicle that employs an architecture of conventional airframe coupled with tilted rotors, aimed to carry four passengers. Using a low-fidelity design framework, a variety of configurations are investigated by altering design variables such as wing area, number of propellers, operating speed, and range. The influence of these variables on the design is explored from the environmental, societal and, economical perspectives for a 2050 time horizon. The findings suggest that configurations with a small wing area and a large number of small propellers emerges as preferable for minimizing energy consumption (per pax-km) and operating expenses (per pax-km). However, in terms of noise emissions, configurations with fewer but larger propellers are favoured, marking a departure from the design choices that prioritize energy efficiency and cost. Additionally, the study underscores that operations prioritizing commercial viability require high-speed cruising and reduced flight hours, diverging from those that prioritize energy efficiency, thereby emphasizing the necessity of multidisciplinary optimization. Finally, a noise-estimation model is developed to enable quick assessment of the vehicle's sound power level. The model necessitates only fundamental powertrain information as inputs and provides insights into the impact of design choices on noise emission, which is beneficial at preliminary design stage.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110058"},"PeriodicalIF":5.0,"publicationDate":"2025-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143419235","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

Operation characteristics of miniature gas turbine with a pulse combustor

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-02-13 DOI: 10.1016/j.ast.2025.110046

Takashi Sakurai, Takehiro Sekiguchi, Sora Inoue, Asuka Sato

{"title":"Operation characteristics of miniature gas turbine with a pulse combustor","authors":"Takashi Sakurai, Takehiro Sekiguchi, Sora Inoue, Asuka Sato","doi":"10.1016/j.ast.2025.110046","DOIUrl":"10.1016/j.ast.2025.110046","url":null,"abstract":"<div><div>To clarify the operation characteristics of a gas turbine using pressure gain combustion, a miniature gas turbine with a pulse combustor was constructed, with an operation experiment conducted. The combustor has two combustion chambers, each operating in either a pulse or constant-pressure combustion state. In the normal combustion mode, wherein the two combustion chambers are in a constant-pressure combustion state, the gas turbine operates as a Brayton cycle. In addition, the gas turbine is operated in the pulse combustion mode, with one combustion chamber operated in the pulse combustion state and the other in the constant-pressure combustion state. In the pulse combustion state, the timing of hydrogen injection and ignition was actively controlled, with regular pulse combustion of 40 cycles per second achieved under gas-turbine operating conditions. The combustion chamber and turbine inlet pressures achieved peak pressures twice as high as the outlet pressure of the compressor. However, as the combustor was connected to the turbine and compressor without valves at the inlet and outlet, the flow pulsation generated by pulse combustion considerably fluctuated the turbine rotation and stagnated the air discharge from the compressor, making its operation unstable. The thermal efficiency of the pulse combustion mode did not show a clear advantage over that of the normal combustion mode, owing to the lower adiabatic efficiency of the turbine and compressor. However, owing to the large pressure fluctuations in the combustor, the hydrogen mass flow rates in both combustion modes were different, highlighting a future research direction to make the heat input the same for performance comparison.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110046"},"PeriodicalIF":5.0,"publicationDate":"2025-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143488539","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