Aerospace Science and Technology最新文献

{"title":"Sun-Earth debris study, part 1: Preliminary investigation of debris propagation dynamics near the Sun-Earth collinear Lagrange points","authors":"Nicholas S. Reid,&nbsp;Robert A. Bettinger","doi":"10.1016/j.ast.2024.109866","DOIUrl":"10.1016/j.ast.2024.109866","url":null,"abstract":"<div><div>The Sun-Earth <span><math><msub><mrow><mi>L</mi></mrow><mrow><mn>1</mn></mrow></msub></math></span> and <span><math><msub><mrow><mi>L</mi></mrow><mrow><mn>2</mn></mrow></msub></math></span> Lagrange points offer a unique and advantageous location for missions related to heliophysics, astronomy, and the overall study of the Solar System. As interest in these points grows and becomes more populated, however, 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 debris propagation dynamics associated with a catastrophic spacecraft breakup occurring in currently used orbits about the Sun-Earth <span><math><msub><mrow><mi>L</mi></mrow><mrow><mn>1</mn></mrow></msub></math></span> and <span><math><msub><mrow><mi>L</mi></mrow><mrow><mn>2</mn></mrow></msub></math></span> points. The NASA Standard Breakup Model is used for debris generation along with an isotropic breakup model for comparison. Additionally, this research provides a cohesive and comprehensive overview of <span><math><msub><mrow><mi>L</mi></mrow><mrow><mn>1</mn></mrow></msub></math></span> and <span><math><msub><mrow><mi>L</mi></mrow><mrow><mn>2</mn></mrow></msub></math></span> point history spacecraft history. Past, present, and future missions are detailed, with each vehicle's respective nation, launch date, orbit type, orbital parameters, objective, and current mission status all simplified into four tables. Overall, this research found that for selected halo orbits, debris traverses throughout the system, including other Lagrange points, with 92% of debris exiting the system within one year of propagation.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109866"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134005","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":"Fault-tolerant control of nonlinear cluster system for fixed-wing UAV piston engine faults based on hierarchical architecture","authors":"Yiming Li,&nbsp;Aojie Li,&nbsp;Zhongchao Zhang,&nbsp;Guiqiu Song","doi":"10.1016/j.ast.2024.109804","DOIUrl":"10.1016/j.ast.2024.109804","url":null,"abstract":"<div><div>Due to the information exchange between fixed-wing UAV clusters, the fault and disturbance information generated when the actuator, including the engine, is transmitted from the faulty UAVs to the healthy UAVs. Given this situation, this paper proposes a cluster fault-tolerant control strategy based on hierarchical architecture. Firstly, this paper analyzes the influence of vibration caused by engine failure on fixed-wing UAVs and illustrates the necessity of considering this factor with simulation experiments. Secondly, this paper designs a hierarchical architecture, which divides the distributed control of the fixed-wing cluster system into consistency control of the upper layer and fault-tolerant tracking control of the lower layer, so that the fault information will only exist in the faulty UAVs, ensuring that the healthy UAVs will not be affected, thus avoiding the occurrence of fault propagation and improving the overall fault tolerance of the cluster. Finally, by analyzing the stability of the Lyapunov function, it is shown that this method can still follow the leader in systems with the followers' failures, and the effectiveness of this method is verified by comparing simulation results.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109804"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134050","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":"Improvement of the SST model for streamline curvature effect based on field inversion and symbolic regression","authors":"Boyang An,&nbsp;Zhenhua Jiang,&nbsp;Chen Yi,&nbsp;Mingze Han,&nbsp;Chao Yan","doi":"10.1016/j.ast.2024.109828","DOIUrl":"10.1016/j.ast.2024.109828","url":null,"abstract":"<div><div>Due to the coordinate-invariant nature of traditional eddy viscosity models, it is challenging to accurately predict flows with specific directional influences without modification. The rotation of reference frames or curved wall flows significantly increases the complexity of turbulence, making the accurate prediction of directional turbulent flows crucial, especially for aircrafts which have curved walls and wings. This paper improves the eddy viscosity coefficient by considering the mathematical principles of directional flow effects during model correction, using a data-driven framework of field inversion and symbolic regression. The development is oriented towards an SST-SC model suitable for flows with streamline curvature. The iterative Kalman filter algorithm is used to solve the inversion problem, and the inversion results serve as training data for the correction model, which is trained through symbolic regression. A series of representative cases are employed for model verification and validation. The findings indicate that the inversion process produces favorable results, and the enhanced model developed using the inversion data exhibits good generalizability.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109828"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134059","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":"Comparative analysis of flow field and thrust behaviour of plug nozzles in continuum vs. rarefied conditions","authors":"Arantza Jency,&nbsp;Aasheesh Bajpai ,&nbsp;Ahilan Appar,&nbsp;Rakesh Kumar","doi":"10.1016/j.ast.2024.109821","DOIUrl":"10.1016/j.ast.2024.109821","url":null,"abstract":"<div><div>Plug nozzle of a single-stage-to-orbit launch vehicle moves through continuum to rarefied regime, as it approaches high altitudes. Despite multiple studies on plug nozzle flows in the rarefied regime, there is significantly less work that compares continuum and rarefied flows through plug nozzles. Even the works that conducted such comparative analysis did not consider the effect of varying nozzle pressure ratios (NPR). The present work compares flow field and thrust performance of a plug nozzle in continuum and rarefied regimes over a range of NPR. In the continuum domain, the exhaust jet displays typical characteristics such as shocks, expansion fans and flow separation. However, the influence of viscosity becomes more noticeable in the rarefied regime. Furthermore, some consequences of flow expanding outside the boundaries of the nozzle walls are noted. The nozzle thrust coefficients exhibit a comparable pattern in both the continuum and rarefied regimes, but noticeable disparities in magnitude are seen. The significant disparity in the thrust coefficients can be attributed to two factors: low mass flow rates and elevated frictional losses. In an effort to eliminate the impact of low mass flow rates, the computed specific impulse values provide insight into the effect of frictional losses on thrust performance of a plug nozzle operating in a rarefied domain.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109821"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134330","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":"A multivariable adaptive control method for aeroengine with H∞ performance considering engine output limitation protection based on fully adjustable Neural Network","authors":"Shancheng Li,&nbsp;Yong Wang,&nbsp;Haibo Zhang","doi":"10.1016/j.ast.2024.109754","DOIUrl":"10.1016/j.ast.2024.109754","url":null,"abstract":"<div><div>Aeroengines, being highly nonlinear systems subject to external disturbances, present a challenge for conventional control methods in achieving satisfactory performance. The radial basis function neural networks possess the capability to effectively model highly approximate nonlinear functions, making them suitable for implementation in aeroengine control. However, the radial basis function (RBF) neural network is a local approximation model that inadequately incorporates historical information. Additionally, the tracking error of neural networks can also impact control effectiveness. To address this issue, this paper proposes a multivariable control method for aeroengines with H_∞ performance based on fully adjustable Long Short-term Memory-Radial Basis Function Neural Network (LSTM-RBFNN). Firstly, a factual mathematical model of an aeroengine is established based on the principles of aerodynamics and thermodynamics. Secondly, the paper proposed an LSTM-RBF neural network architecture to enhance prediction performance and proposed using a finite time perturbation estimator to gauge the approximate error of neural networks, thereby acquiring immeasurable approximative error information. Then, in order to mitigate the influence of neural network tracking error on the loop, the estimated errors are incorporated into the primary loop controller, and a static state disturbance full feedback H_∞ controller is proposed. Then, leveraging the LSTM-RBF architecture proposed in this study, we further employ Taylor expansion of nodes to derive the adaptive law of the neural network and propose a novel neural network adaptive law that incorporates tracking error estimated by the disturbance observer into the adjustment mechanism to enhance tracking performance. The stability of this adaptive law has been proven based on Lyapunov function analysis. And considering the output limitation protection problem of aeroengine, a virtual command value based limitation protection method is proposed for the above control method, and it is proved that this limitation method does not damage the stability and design process of the original control method. Finally, numerical simulation and hardware in loop simulation experiments were conducted, and the results showed that under the same adaptive gain of the neural network, the performance indicators (IAE, IATE, σ) could be reduced by more than 50% compared to other methods, which demonstrates superior tracking and disturbance rejection performance achieved by our proposed method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109754"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134981","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":"Prediction of aerial refueling docking results by flying-wing UAV bow wave model established on CNN","authors":"Shilong Yin,&nbsp;Jianyang Yu,&nbsp;Yanping Song,&nbsp;Fu Chen,&nbsp;Jiaping Ma","doi":"10.1016/j.ast.2024.109760","DOIUrl":"10.1016/j.ast.2024.109760","url":null,"abstract":"<div><div>Soft air refueling has become the most widely used unmanned autonomous refueling method for air forces in various countries due to its simple, reliable, and convenient advantages. The bow wave effect generated by the oil receiver is the main reason for docking failure. Establishing a bow wave model and accurately predicting the docking effect under its influence has become a key focus of research in this field. Traditional modeling methods have many problems, such as the semi-Rankine body model or vortex lattice method not being suitable for wing layout, and numerical simulation methods cannot cover a large number of flight conditions and are time-consuming. This study proposes a convolutional neural network (CNN) with transposed convolutional structures, which utilizes its ability to extract deep features from data to establish a flow field regression model from flight conditions to velocity distribution. And based on multi-rigid body dynamics, a finite element model was constructed to solve for the equilibrium position of the hose-drogue assembly (HDA). Subsequently, the Kriging interpolation method was used to train the drogue position offset model under different docking positions, thereby determining the range within which the oil receiver can successfully complete docking. This process uses flow field calculations obtained from CNN prediction and computational fluid dynamics (CFD) calculation respectively, and the results show that these two methods are very close, verifying the effectiveness of CNN method in constructing bow wave models and the feasibility of obtaining soft aerial refueling docking effects based on this model.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109760"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134144","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":"Experimental investigation into the influence of strut and pulsed injection on flame stabilization in a kerosene-fueled scramjet","authors":"Guo-xiong Liu ,&nbsp;Lang Li ,&nbsp;Bin Jia","doi":"10.1016/j.ast.2024.109820","DOIUrl":"10.1016/j.ast.2024.109820","url":null,"abstract":"<div><div>To study the influence of strut and pulsed injection on flame stabilization in a kerosene-fueled scramjet, experiments have been carried out at the China Aerodynamics Research and Development Center. Wall pressure measurements, high-speed photography, and CH* luminosity imaging have been used to investigate the flow structure and flame development under different injection modes. The results of the experiments indicate that pilot hydrogen plays a significant role in igniting and stabilizing the kerosene flame for the configuration and incoming conditions considered in this paper. Withdrawal of the pilot hydrogen leads to the pressure of the monitoring point decreasing by more than 0.07 MPa at the combustion stage in all cases. Under pulsed injection, the flame oscillates due to the instability of the kerosene pulse pressure, the concentration upstream of the shear layer is significantly reduced, the CH* luminosity distribution becomes wider, and the pressure in the isolator is reduced by about 0.035 MPa. Strut injection increases combustor pressure by about 0.016 MPa, which is conducive to kerosene ignition and flame stabilization. Combining struts with pulsed injection results in a maximum combustor pressure of up to 0.2 MPa during the flame stabilization stage, which is significantly higher than with other injection modes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109820"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134329","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":"Stability enhancement of an axial fan by foam metal casing treatment subjected to circumferential inlet distortion","authors":"Chunwang Geng ,&nbsp;Jinfei Yang ,&nbsp;Jia Li ,&nbsp;Yuqing Wang ,&nbsp;Xu Dong ,&nbsp;Dakun Sun ,&nbsp;Xiaofeng Sun","doi":"10.1016/j.ast.2024.109778","DOIUrl":"10.1016/j.ast.2024.109778","url":null,"abstract":"<div><div>Circumferential distortion has been a concern since the early development of aeroengines, typically leading to a decrease in stability and efficiency. This paper experimentally investigates the effect of circumferential distortion on a low-speed axial fan and evaluates the potential of foam metal casing treatment (FMCT) to improve the stall margin. Distortions with different intensities were modeled by covering variable areas with wire mesh sectors. Under different distortions, the stall margin with solid casing drops significantly from 38.6% to -7.4%, while FMCT achieves a notable improvement ranging from 14% to 20%. Unsteady measurements were conducted to analyze the pre-stall behavior and the variation in the tip blade loading. The evolution of disturbance energy is presented to discuss the effects of distortion and FMCT on fan stability. It is observed that the proportion of low-frequency disturbance energy amplifies gradually when the rotor is leaving the distorted region. As the distortion angle increases, the maximum amplitude of proportion intensifies. The comparison of the disturbance energy at near stall point between solid casing and FMCT shows that the broadband disturbance energy is suppressed by FMCT. Additionally, the enhancement of stability under inlet distortion is also attributed to the redistribution of tip blade loading.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109778"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134071","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":"Design and stability study of a distortion-tolerant axial compressor based on an alternating stator layout","authors":"Wenguang Fu ,&nbsp;Junyang Yu ,&nbsp;Rui Zuo ,&nbsp;Peng Sun ,&nbsp;Wei Wang","doi":"10.1016/j.ast.2024.109810","DOIUrl":"10.1016/j.ast.2024.109810","url":null,"abstract":"<div><div>To effectively suppress flow separation in the corner regions of a compressor, improve aerodynamic performance, and enhance distortion tolerance, this study focuses on a single-stage high-load transonic axial flow compressor and introduces a novel and effective unconventional stator design known as an alternating stator (AS) vane layout. This study examines the relationship between the AS layout and the flow separation in the corner regions from a fluid dynamics perspective and investigates the enhancement effects of different AS designs on the compressor's aerodynamic performance and stability margin (SM). Numerical investigations indicate that the alternating layout scheme, which is developed by locally adjusting the inlet geometric angle of the stator vanes, can effectively improve the aerodynamic performance and stability of the compressor. Compared to the original compressor design, the scheme with a 12° adjustment in the blade tip's geometric angle significantly increases both the total pressure ratio and efficiency. This scheme also enhances the SM by 34.69 %. With this alternating layout, the novel stator arrangement induces differentiation in the flow field structure among adjacent passages. Internally, an alternating separation forms at the top and root corner regions of the adjacent stator passages, effectively preventing extensive flow separation from occurring at the top or root corner regions of the compressor and thereby delaying a compressor stall. When this design is applied to the compressor stage with inlet distortion conditions, the AS scheme with a 12° adjustment in the blade tip's geometric angle effectively improves the compressor's aerodynamic performance and distortion tolerance and holds significant potential for expanding the stable operating range of the compressor with inlet distortion conditions. Relative to the original design, the SM of the AS compressor can be increased by 83.09 %.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109810"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134223","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":"Screech modes in underexpanded hot free jets","authors":"Yitao Wang ,&nbsp;Xiangru Li ,&nbsp;Juan Sheng ,&nbsp;Feng He ,&nbsp;Pengfei Hao ,&nbsp;Xiwen Zhang","doi":"10.1016/j.ast.2024.109855","DOIUrl":"10.1016/j.ast.2024.109855","url":null,"abstract":"<div><div>High-speed thermal jets are widely applied in aerospace and other engineering fields. Compared with cold jets, screech tones in hot jets have higher frequencies and lower intensities. However, there are fewer studies on the screech modes of hot jets. In this paper, large eddy simulations are carried out on underexpanded free jets with different nozzle temperature ratios (NTRs) and nozzle pressure ratios (NPRs). The time-averaged shock cells and screech frequencies obtained from numerical simulations agree with the corresponding experimental results well. The screech modes of the NPR=2.4 jets at various NTRs are compared and analyzed. It is found that the screech mode changes with the NTR, which is not accidental after testing hot jets at other NPRs. Via Spectral Proper Orthogonal Decomposition, the features of different screech modes are analyzed in detail. To explain the mode change, the acoustic feedback mechanism of screech tones is studied by combining the neutral acoustic mode and the interaction between the shock cells and the K-H wavepackets. For hot jets, the wavenumber criterion of acoustic resonance in axisymmetric screech mode cannot be satisfied. Thus, the screech tones in axisymmetric mode cannot exist stably in underexpanded jets with NPR = 2.4 at high NTRs.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"157 ","pages":"Article 109855"},"PeriodicalIF":5.0,"publicationDate":"2025-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143134229","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}