Aerospace Science and Technology最新文献

{"title":"Passive safety-constrained impulsive maneuvers for formation reconfiguration: An analytic solution","authors":"Jihe Wang, Chenglong Xu, Chengxi Zhang, Jinxiu Zhang","doi":"10.1016/j.ast.2024.109901","DOIUrl":"https://doi.org/10.1016/j.ast.2024.109901","url":null,"abstract":"This paper investigates the spacecraft formation reconfiguration with general passive safety constraints. The <ce:italic>general</ce:italic> signifies that this constraint is universally applicable to relative orbits with nonzero relative semi-major axes, facilitating a more flexible relative motion than traditional constraints permit. Using relative eccentricity/inclination (E/I) vector theory, optimal reconfigurations are classified into same-region type and cross-region type. For each type, we conduct a geometrically intuitive analysis to re-evaluate the existing optimal solution, showing that it cannot guarantee passively safe. Considering the general passive safety constraint, we provide innovative analytic solutions for each type of reconfiguration, based on the sufficient conditions for satisfaction of constraint, theoretically guaranteeing the passive safety. Simulations of same-region and cross-region reconfigurations show that the existing optimal solution violates the passive safety constraint. In contrast, the proposed solutions ensure passive safety throughout the reconfiguration process. Comparative results also show that the produced reconfiguration schemes are fuel-optimal.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"34 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2025-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142929274","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}

{"title":"Advanced aerodynamic analysis of the supersonic flow field of an aerospike engine","authors":"Luca Fadigati, Ernesto Sozio, Federico Rossi, Nabil Souhair, Fabrizio Ponti","doi":"10.1016/j.ast.2024.109908","DOIUrl":"https://doi.org/10.1016/j.ast.2024.109908","url":null,"abstract":"In the last decade, the aerospike has been reconsidered as an alternative of the traditional bell-shaped nozzle because with the improving of additive manufacturing technique it has been possible to enable the fabrication of complex features while drastically reduce production time and manufacturing costs. Nevertheless, there are still some issue that should be solved to realize reliable engines. During the ascent phase of a launcher, the aerospike could deliver more thrust than a bell-shaped nozzle with the same expansion ratio and exit section area due to the capability to adapt the expansion reaching the ambient pressure in a wide range of altitudes. This research has been focused on the improvement of the aerospike performance simulating a small engine with different spike shapes in order to identify sources of losses and to determine which is the most efficient one. The considered shapes have been obtained using the Angelino's method and cutting the spike to achieve the target base radius. The exit section has been kept constant in different designs. The study compares the simulations results with the ones obtained applying the isentropic nozzle theory, highlighting the different behaviours of the flow at throat section and over the spike in terms of pressure and velocity distribution. In particular, the influence of both the round connection between the throat section and the external wall, and the connection between flow inclination at the throat section and the thrust loss at the base has been analyzed. Finally, a rough estimation of the thrust-to-mass ratio has been obtained.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"25 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2024-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142929276","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}

{"title":"Orbital motion intention recognition for space non-cooperative targets based on incomplete time series data","authors":"Qinbo Sun, Liran Zhao, Shengyong Tang, Zhaohui Dang","doi":"10.1016/j.ast.2024.109912","DOIUrl":"https://doi.org/10.1016/j.ast.2024.109912","url":null,"abstract":"This study establishes a method for recognizing the intentions of non-cooperative targets in orbital dynamics using incomplete time series data. By leveraging a relative orbital dynamics model, 38 distinct motion intentions are delineated, representing the largest variety identified in current research. A neural network-based intention recognition method is developed, with a comprehensive comparative analysis focusing on network architecture and types of time series data. The network architectures explored include long short-term memory networks, gated recurrent unit networks, and self-attention structures, while the time series data encompass position, angular, and distance measurements. Experimental findings reveal that the combination of gated recurrent unit networks with attention mechanisms achieves the highest performance in intention recognition, reaching a maximum accuracy of 95%. Both position and angular measurement time series demonstrate exceptional performance, with recognition accuracies exceeding 93%, utilizing the least amount of information in current studies. The proposed method maintains accuracies of 89% and 94% under position measurement noise and nonlinear orbital dynamics disturbances, respectively, compared to only 17% and 43% for methods based on orbital dynamics condition matching. Additionally, an analysis of intention observability is conducted to enhance model interpretability. This approach holds significant promise for applications such as spacecraft collision avoidance and non-cooperative space target capture.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"20 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2024-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142929278","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}

{"title":"An implicit coupling framework for numerical simulations between hypersonic nonequilibrium flows and thermal responses of charring materials in the presence of ablation","authors":"Jingchao Zhang, Chunsheng Nie, Jinsheng Cai, Shucheng Pan","doi":"10.1016/j.ast.2024.109915","DOIUrl":"https://doi.org/10.1016/j.ast.2024.109915","url":null,"abstract":"An implicit coupling framework for hypersonic nonequilibrium flows and material thermal responses is proposed for numerical simulations of ablative thermal protection materials during flight trajectories. When subjected to aerodynamic heating from hypersonic flows, charring ablative materials undergo complex processes such as ablation and pyrolysis, which involve heterogeneous and homogeneous chemical reactions. These multiphysical phenomena are simulated using a multicomponent material thermal response (MTR) solver that accounts for the complexity of the components of pyrolysis gases. The species concentrations are calculated to enhance the accuracy of the transport and thermophysical parameters of pyrolysis gases. The efficiency of the MTR solver is improved by 92% through implicit time integration in the test cases. The numerical solutions of hypersonic flows and material thermal response are coupled through a gas-surface interaction (GSI) interface, which is based on the surface mass and energy balance on the ablating surface. An explicit coupling method and an implicit coupling mechanism are developed depending on when the GSI interface is updated. The explicit coupling method updates the interfacial quantities at physical time steps, which improves computational efficiency by 40%, but introduces time discretization errors and numerical oscillations in wall properties. In contrast, the implicit coupling mechanism updates the interfacial quantities at pseudo time steps, reducing temporal discretization errors by up to 5.8% and suppressing numerical oscillations. Additionally, a simplified ablation boundary based on a steady-state ablation assumption is proposed to approximate the MTR solution, providing quasi-steady flow solutions in the presence of ablation.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"48 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2024-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142929275","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}

{"title":"Sun-Earth debris study, Part 2: Preliminary investigation of debris-induced spacecraft survivability risks near the Sun-Earth collinear Lagrange points","authors":"Nicholas S. Reid, Robert A. Bettinger","doi":"10.1016/j.ast.2024.109865","DOIUrl":"https://doi.org/10.1016/j.ast.2024.109865","url":null,"abstract":"In the past two years of 2023-2024, two space vehicles were inserted into orbits about Sun-Earth Lagrange points, joining eight other spacecraft about the <mml:math altimg=\"si1.svg\"><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>1</mml:mn></mml:mrow></mml:msub></mml:math> and <mml:math altimg=\"si2.svg\"><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>2</mml:mn></mml:mrow></mml:msub></mml:math> points. As interest in these points grows and become more populated, the chance for artificial space debris to inflict hazard on the region increases. The Circular Restricted Three-Body Problem (CR3BP) may be used to propagate the motion of debris in the region, and this paper investigates the risks associated with a catastrophic spacecraft breakup occurring in currently used or planned orbits about the Sun-Earth <mml:math altimg=\"si1.svg\"><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>1</mml:mn></mml:mrow></mml:msub></mml:math> and <mml:math altimg=\"si2.svg\"><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>2</mml:mn></mml:mrow></mml:msub></mml:math> points. The NASA Standard Breakup Model is used for debris generation, and a survivability model is used to calculate the debris related probability of hazard for a spacecraft with respect to a catastrophic breakup in the system. Additionally, a Monte Carlo simulation architecture enables a comprehensive sampling of initial conditions associated with potential breakup scenarios in the Sun-Earth <mml:math altimg=\"si1.svg\"><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>1</mml:mn></mml:mrow></mml:msub></mml:math> and <mml:math altimg=\"si2.svg\"><mml:msub><mml:mrow><mml:mi>L</mml:mi></mml:mrow><mml:mrow><mml:mn>2</mml:mn></mml:mrow></mml:msub></mml:math> regions. Overall, this research finds that the maximum probability of hazard for a bystander spacecraft varies greatly on the order of <mml:math altimg=\"si3.svg\"><mml:msup><mml:mrow><mml:mn>10</mml:mn></mml:mrow><mml:mrow><mml:mo linebreak=\"badbreak\" linebreakstyle=\"after\">−</mml:mo><mml:mn>8</mml:mn></mml:mrow></mml:msup></mml:math> to <mml:math altimg=\"si4.svg\"><mml:msup><mml:mrow><mml:mn>10</mml:mn></mml:mrow><mml:mrow><mml:mo linebreak=\"badbreak\" linebreakstyle=\"after\">−</mml:mo><mml:mn>12</mml:mn></mml:mrow></mml:msup></mml:math>, based on different initial angular positions between the bystander and breakup spacecraft.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"23 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2024-12-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142825351","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}

{"title":"Rotor-force controller for multirotors under aerodynamic interferences","authors":"Antonio Gonzalez-Morgado, Pedro J. Sanchez-Cuevas, Guillermo Heredia, Anibal Ollero","doi":"10.1016/j.ast.2024.109861","DOIUrl":"https://doi.org/10.1016/j.ast.2024.109861","url":null,"abstract":"The use of multirotors for inspection tasks requires the ability to perform high-precision flights close to the environment, where aerodynamic effects appear and make control of the platform difficult. This paper presents a control solution for multirotors to deal with aerodynamic effects and other disturbances produced at a motor level. It combines the inclusion of a mechatronic system embedded in the multirotor power plant and a new control architecture focused on enabling a Rotor-Force Controller (RFC) at a motor level. Unlike model-based solutions developed in recent years, our solution can be used with any type of motor perturbation, such as ground and ceiling aerodynamic effects, wind effects, battery discharge and rotor damage effects. The implementation of both parts, the mechatronics system and the Rotor-Force Controller, are presented in this paper and experimentally validated in a custom testbench. The experiment shows that the proposed Rotor-Force Controller reduces the impact of aerodynamic effects on platform attitude approximately 80% compared with the results without the Rotor-Force Controller.","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"43 1","pages":""},"PeriodicalIF":5.6,"publicationDate":"2024-12-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142825352","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}

{"title":"Uncertainty analysis of rudder shaft thermal conditions on the flutter characteristics of the hypersonic control surface","authors":"Kun Ye ,&nbsp;Liuzhen Qin ,&nbsp;Zhengyin Ye ,&nbsp;Dangguo Yang ,&nbsp;Bin Dong","doi":"10.1016/j.ast.2024.109721","DOIUrl":"10.1016/j.ast.2024.109721","url":null,"abstract":"<div><div>The thermal conditions in hypersonic aerothermoelastic systems exert a significant influence on the flutter characteristics of the system. Nevertheless, in previous investigations on aeroelastic uncertainty analysis, the influence of thermal uncertainty has frequently been neglected. In this study, an uncertainty analysis framework based on Monte Carlo simulation and surrogate model is conducted for addressing the thermal uncertainty and its implications on the flutter characteristics. Initially, the all-moving control surface of a hypersonic vehicle is selected as the investigated model. A parametric method is then developed to represent the temperature distribution along the control rudder shaft, taking into account the temperature conditions calculated by CFD. Based on the approach, the impact of temperature uncertainty is designed to perform the uncertainty quantification of temperature uncertainty on flutter characteristics of the control surface. Sensitivity indices are computed to evaluate the impact of temperature uncertainty in different regions of the shaft on flutter characteristics. This implies BPNN always provides accurate models. This is not always true and even if it is, showing that in a general sense is not within the scope of this study. Furthermore, the temperature uncertainty on the shaft surface induces uncertainty in the modal frequencies of the control surface, thereby resulting in uncertain flutter characteristics. Notably, the leading-edge region of the shaft exhibits the most pronounced effect on flutter characteristics, followed by the midsection region. These results could offer valuable insights for the refined design of control surfaces in hypersonic vehicles, contributing to the advancement of this field of research.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109721"},"PeriodicalIF":5.0,"publicationDate":"2024-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142747056","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}

{"title":"Asymmetric full-state constrained attitude control for a flexible agile satellite with multiple disturbances and uncertainties","authors":"Youxue Zhao ,&nbsp;Zhenxin Feng ,&nbsp;Jun Zhou ,&nbsp;He Huang","doi":"10.1016/j.ast.2024.109767","DOIUrl":"10.1016/j.ast.2024.109767","url":null,"abstract":"<div><div>In this paper, an asymmetric full-state constrained attitude control method for a flexible agile satellite with multiple disturbances and uncertainties is proposed. Both the attitudes and angular velocities of the flexible agile satellite are guaranteed in the asymmetric/symmetric bounds by utilizing the time-varying integral barrier Lyapunov function (TVIBLF) and constant integral barrier Lyapunov function (IBLF) respectively. Compared with the existing error-based barrier Lyapunov functions, the asymmetric TVIBLF does not need error transformation, relaxes the conservation of the initial requirements, and has more compatibility. Furthermore, the proposed asymmetric TVIBLF can deal with the asymmetric time-varying constraints without loss of generality. In addition, the high-frequency flexible vibrations, inertial uncertainties, and unknown external disturbance torques affected on the agile satellite are considered respectively. On one hand, a modal observer is utilized to suppress the high-frequency flexible vibration effects on the attitudes. On the other hand, the inertial uncertainties and unknown external disturbance torques are estimated with a multi-variable nonlinear disturbance observer. Therefore, both the asymmetric full-state constrained performances and robustness of the attitude control system for the flexible agile satellite are achieved. The stability of the closed-loop system is proved and numerical simulations have validated the effectiveness of the proposed method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109767"},"PeriodicalIF":5.0,"publicationDate":"2024-11-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142748145","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}

{"title":"Deep learning-enhanced aerodynamics design of high-load compressor cascade at low Reynolds numbers","authors":"Hua-feng Xu ,&nbsp;Sheng-feng Zhao ,&nbsp;Ming-yang Wang ,&nbsp;Ge Han ,&nbsp;Xin-gen Lu ,&nbsp;Jun-qiang Zhu","doi":"10.1016/j.ast.2024.109775","DOIUrl":"10.1016/j.ast.2024.109775","url":null,"abstract":"<div><div>This study addresses the challenges of designing high-efficiency compressors for long-endurance, high-altitude unmanned aerial vehicles (UAVs) under low Reynolds number (<em>Re</em>) and high load conditions, exploring the aerodynamic performance limits of compressor blades under extreme conditions. The research integrates advanced numerical simulations, experimental methods, and deep learning technologies to minimize profile losses and deviation angle on compressor blades. An orthogonal experimental design systematically explored the impact of key geometric factors on aerodynamic performance. A deep learning model incorporating neural networks with spatial attention mechanisms was developed to significantly enhance the accuracy of aerodynamic predictions. This model adeptly captured the complex nonlinear interactions between aerodynamic and geometric parameters. Sobol sensitivity analysis revealed that the dimensionless maximum thickness is the most critical factor, accounting for 44 % of the total variance in total pressure loss and deviation angle. The position of maximum thickness and the aspect ratio of the elliptical leading edge also significantly influenced performance. The optimized high-load compressor blade profile was validated through experimental data and detailed computational fluid dynamics analysis using large eddy simulation methods. This analysis revealed flow separation and reattachment mechanisms, shedding light on turbulence and vortex dynamics critical to performance. This research deepens the theoretical understanding of compressor cascade fluid dynamics and provides practical insights for designing more efficient compressors, especially for micro axial compressors in high-altitude UAVs.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109775"},"PeriodicalIF":5.0,"publicationDate":"2024-11-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142748141","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}

{"title":"Enhancement of flying wing aerodynamics in crossflow at high angle of attack using dual synthetic jets","authors":"Hao Wang,&nbsp;Zhenbing Luo,&nbsp;Xiong Deng,&nbsp;Yan Zhou,&nbsp;Jianyu Gong","doi":"10.1016/j.ast.2024.109773","DOIUrl":"10.1016/j.ast.2024.109773","url":null,"abstract":"<div><div>To address the asymmetric flow field of the flying wing under cross-flow conditions at high angles of attack, dual synthetic jet actuators (DSJAs) are positioned at the leading edge of the windward side. DSJ control effectively affects the flow separation structure on the windward side, thereby enhancing leading-edge suction. This leads to both lift enhancement and drag reduction. Furthermore, it strengthens the stabilizing roll moment and improves lateral static stability. Additionally, the effective suppression of the separation zone significantly reduces the aerodynamic load fluctuations of the flying wing after control. In terms of excitation frequency, low-frequency excitation more effectively generates lift, transfers energy downstream, promotes momentum transfer, and results in an 8.2% increase in lift. Moreover, the DSJ excitation exhibits fast response characteristics, with the entire flow establishment process taking only 190 ms. Therefore, through DSJ control, the asymmetric flow under lateral conditions can be effectively corrected, expanding the flight envelope and enhancing the maneuverability and reliability of the aircraft.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109773"},"PeriodicalIF":5.0,"publicationDate":"2024-11-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142757587","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}