Aerospace最新文献_第10页

Design of In-Orbit Sample Container Transfer Mechanism for Chang’E-5 Lunar Sample Return Mission 为嫦娥五号月球样品返回任务设计在轨样品容器传输机制

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-25 DOI: 10.3390/aerospace10120992

Weijun Wang, Yuxin Cui, Chenkun Qi, Yanyan Cao, Yuhua Zhang, Chongfeng Zhang, Shigang Wang

引用次数: 0

Critical Sample-Size Analysis for Uncertainty Aerodynamic Evaluation of Compressor Blades with Stagger-Angle Errors 对具有错开角度误差的压缩机叶片进行不确定性空气动力学评估的临界样本大小分析

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-25 DOI: 10.3390/aerospace10120990

Haohao Wang, Limin Gao, Baohai Wu

{"title":"Critical Sample-Size Analysis for Uncertainty Aerodynamic Evaluation of Compressor Blades with Stagger-Angle Errors","authors":"Haohao Wang, Limin Gao, Baohai Wu","doi":"10.3390/aerospace10120990","DOIUrl":"https://doi.org/10.3390/aerospace10120990","url":null,"abstract":"Many probability-based uncertainty quantification (UQ) schemes require a large amount of sampled data to build credible probability density function (PDF) models for uncertain parameters. Unfortunately, the amounts of data collected as to compressor blades of aero-engines are mostly limited due to the expensive and time-consuming tests. In this paper, we develop a preconditioner-based data-driven polynomial chaos (PDDPC) method that can efficiently deal with uncertainty propagation of limited amounts of sampled data. The calculation accuracy of a PDDPC method is closely related to the sample size of collected data. Therefore, the influence of sample size on this PDDPC method is investigated using a nonlinear test function. Subsequently, we consider the real manufacturing errors in stagger angles for compressor blades. Under three different operating conditions, the PDDPC method is applied to investigate the effect of stagger-angle error on UQ results of multiple aerodynamic parameters of a two-dimensional compressor blade. The results show that as the sample-size of measured data increases, UQ results regarding aerodynamic performance obtained by the PDDPC method gradually converge. There exists a critical sample size that ensures accurate UQ analysis of compressor blades. The probability information contained in the machining error data is analyzed through Kullback–Leibler divergence, and the critical sample size is determined. The research results can serve as a valuable reference for the fast and cheap UQ analysis of compressor blades in practical engineering.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"15 1","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139236810","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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 Simulation on Primary Breakup Characteristics of Liquid Jet in Oscillation Crossflow 振荡横流中液体射流一次破裂特性的数值模拟

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-25 DOI: 10.3390/aerospace10120991

Tao Zhang, Xinyu Song, X. Kai, Yeguang He, Rundong Li

{"title":"Numerical Simulation on Primary Breakup Characteristics of Liquid Jet in Oscillation Crossflow","authors":"Tao Zhang, Xinyu Song, X. Kai, Yeguang He, Rundong Li","doi":"10.3390/aerospace10120991","DOIUrl":"https://doi.org/10.3390/aerospace10120991","url":null,"abstract":"In order to understand the breakup characteristics of a transverse liquid jet flow in an actual combustion chamber, a numerical study was conducted using the Volume of Fluid (VOF) method combined with grid adaptation technology. The study focused on the primary breakup characteristics of liquid jets under the conditions of a steady and oscillating air crossflow. The simulated mediums were set to water and air. The research findings revealed that fluctuations in the incoming gas velocity can influence the development speed of surface waves and the mode of jet breakup during the initial stage of jet development as compared to the steady condition. In both conditions, the surface waves were initially observed to appear within 1/4 T–2/4 T. The surface wave of the jet develops faster under steady conditions because the average velocity of the steady flow is higher than that of the oscillation flow during this stage. As a result, the fragmentation of the jet is primarily influenced by the surface wave. Under an oscillating flow, the rear of the jet begins to break up earlier due to the slower development of surface waves. The velocity of the oscillating air inflow increases over time, and the speed of surface wave development also increases, gradually leading to the dominance of surface-wave-induced jet breakup. In the second stage of air inflow oscillation, an “up and down slapping” phenomenon occurs at the tail of the jet. Additionally, increasing the air inflow velocity leads to a longer jet breakup length and a higher number of droplets near the jet column. Surface waves are observed on both the windward and leeward sides of the jet. The penetration depth of the jet fluctuates with changes in the crossflow velocity, and the response of the jet penetration depth to the velocity fluctuations in the transverse air is delayed by half a period.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"33 8","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139237969","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Suction Control of a Boundary Layer Ingestion Inlet 边界层进气口的吸力控制

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-24 DOI: 10.3390/aerospace10120989

Lei Liu, Guozhan Li, Ban Wang, Shaofeng Wu

{"title":"Suction Control of a Boundary Layer Ingestion Inlet","authors":"Lei Liu, Guozhan Li, Ban Wang, Shaofeng Wu","doi":"10.3390/aerospace10120989","DOIUrl":"https://doi.org/10.3390/aerospace10120989","url":null,"abstract":"This study presents a numerical investigation of suction control in an aggressive S-shaped air intake with large boundary ingestion. The results show that the variation of suction control parameters such as suction location, suction pipe diameter, and suction angle all have an impact on the effectiveness of the flow control. In general, further upstream suction, such as near the throat, is favorable for the decrease of the second flow intensity and the area of the low-energy fluid region at the exit of the S-shaped inlet. However, it is bad for the total pressure recovery and the circumferential total pressure uniform distribution. From the perspective of the uniformity of the total pressure distribution at the air intake exit, there is an optimal location for suction between the throat and the separation start point. A bigger suction pipe diameter brings better effects as the suction location and suction angle keep constant, due to more low-energy fluid being sucked out. But this doesn’t mean the largest mass flow suction results in the biggest improvement. Overall, sucking at the 1st bend, with suction angle and suction pipe diameter equaling 15 degrees and 12 mm, respectively, is the optimal suction scheme here. Since the change rule of the cross-section area along the centerline has not changed during suction control, the second flow and complex surface streamline at the air intake exit cannot be eliminated, though they can be decreased a lot with reasonable suction control. Similarly, owing to large boundary ingestion, the remarkable low-energy fluid region always exists despite the significant reduction of the separation and second flow, which is very different from the results of this kind of micro-suction executed in the non-BLI S-duct. To pursue a higher improvement, suction combined with vortex generator vanes has been further studied. Corresponding results analysis shows that the hybrid flow control method has great potential and should be investigated in detail in the future.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"31 1","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139240881","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

The Influence of Gas Models on Numerical Simulations of Cryogenic Flow 气体模型对低温流动数值模拟的影响

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-23 DOI: 10.3390/aerospace10120986

Ruifan Hu, Yongliang Chen, Jifei Wu, Shuling Tian

引用次数: 0

The Large Imaging Spectrometer for Solar Accelerated Nuclei (LISSAN): A Next-Generation Solar γ-ray Spectroscopic Imaging Instrument Concept 太阳加速核大型成像光谱仪（LISSAN）：下一代太阳γ射线光谱成像仪器概念

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-23 DOI: 10.3390/aerospace10120985

D. Ryan, Sophie Musset, H. Reid, Säm Krucker, A. Battaglia, Eric Bréelle, Claude Chapron, H. Collier, J. Dahlin, C. Denker, E. Dickson, Peter T. Gallagher, I. Hannah, N. Jeffrey, J. Kašparová, E. Kontar, P. Laurent, S. Maloney, P. Massa, A. Massone, Tomasz Mrozek, D. Pailot, M. Pallu, M. Pesce-Rollins, Michele Piana, Illya Plotnikov, A. Rouillard, Albert Y. Shih, David Smith, M. Stȩślicki, Muriel Z. Stiefel, A. Warmuth, Meetu Verma, Astrid M. Veronig, N. Vilmer, C. Vocks, A. Volpara

{"title":"The Large Imaging Spectrometer for Solar Accelerated Nuclei (LISSAN): A Next-Generation Solar γ-ray Spectroscopic Imaging Instrument Concept","authors":"D. Ryan, Sophie Musset, H. Reid, Säm Krucker, A. Battaglia, Eric Bréelle, Claude Chapron, H. Collier, J. Dahlin, C. Denker, E. Dickson, Peter T. Gallagher, I. Hannah, N. Jeffrey, J. Kašparová, E. Kontar, P. Laurent, S. Maloney, P. Massa, A. Massone, Tomasz Mrozek, D. Pailot, M. Pallu, M. Pesce-Rollins, Michele Piana, Illya Plotnikov, A. Rouillard, Albert Y. Shih, David Smith, M. Stȩślicki, Muriel Z. Stiefel, A. Warmuth, Meetu Verma, Astrid M. Veronig, N. Vilmer, C. Vocks, A. Volpara","doi":"10.3390/aerospace10120985","DOIUrl":"https://doi.org/10.3390/aerospace10120985","url":null,"abstract":"Models of particle acceleration in solar eruptive events suggest that roughly equal energy may go into accelerating electrons and ions. However, while previous solar X-ray spectroscopic imagers have transformed our understanding of electron acceleration, only one resolved image of γ-ray emission from solar accelerated ions has ever been produced. This paper outlines a new satellite instrument concept—the large imaging spectrometer for solar accelerated nuclei (LISSAN)—with the capability not only to observe hundreds of events over its lifetime, but also to capture multiple images per event, thereby imaging the dynamics of solar accelerated ions for the first time. LISSAN provides spectroscopic imaging at photon energies of 40 keV–100 MeV on timescales of ≲10 s with greater sensitivity and imaging capability than its predecessors. This is achieved by deploying high-resolution scintillator detectors and indirect Fourier imaging techniques. LISSAN is suitable for inclusion in a multi-instrument platform such as an ESA M-class mission or as a smaller standalone mission. Without the observations that LISSAN can provide, our understanding of solar particle acceleration, and hence the space weather events with which it is often associated, cannot be complete.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"47 6","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139246248","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Mild Detonation Initiation in Rotating Detonation Engines: An Experimental Study of the Deflagration-to-Detonation Transition in a Semiconfined Flat Slit Combustor with Separate Supplies of Fuel and Oxidizer 旋转式爆燃发动机中的轻度爆燃起爆：在燃料和氧化剂分开供应的半封闭扁平狭缝燃烧器中从爆燃到引爆过渡的实验研究

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-23 DOI: 10.3390/aerospace10120988

I. O. Shamshin, Vladislav S. Ivanov, V. S. Aksenov, Pavel A. Gusev, K. A. Avdeev, Sergey M. Frolov

{"title":"Mild Detonation Initiation in Rotating Detonation Engines: An Experimental Study of the Deflagration-to-Detonation Transition in a Semiconfined Flat Slit Combustor with Separate Supplies of Fuel and Oxidizer","authors":"I. O. Shamshin, Vladislav S. Ivanov, V. S. Aksenov, Pavel A. Gusev, K. A. Avdeev, Sergey M. Frolov","doi":"10.3390/aerospace10120988","DOIUrl":"https://doi.org/10.3390/aerospace10120988","url":null,"abstract":"Rotating detonation engines (RDEs) are considered to be promising thrusters for aerospace propulsion. Detonation initiation in RDEs can be accompanied by a destructive explosion of an excess volume of the fuel mixture in the combustor. To exclude this phenomenon, a “mild” rather than “strong” initiation of detonation is required. For the mild initiation of detonation in RDEs, it is necessary to ignite a mixture of a certain minimum volume sufficient for deflagration-to-detonation transition (DDT). In this study, the critical conditions for detonation initiation through DDT in a semiconfined slit combustor simulating the RDE combustor with a separate supply of ethylene and oxygen diluted with nitrogen (from 0 to 40%) were obtained experimentally. It turned out that for the mild initiation of detonation, it is necessary to ignite the mixture upon reaching the critical (minimum) height of the combustible mixture layer. Thus, for the mild initiation of detonation in the undiluted C2H4 + 3O2 mixture filling such a slit combustor, the height of the mixture layer must exceed the slit width by approximately a factor of 12. In terms of the transverse size of the detonation cell λ the minimum layer height of such mixtures in experiments is ~150λ. Compared to the experiments with the premixed composition, the critical height of the layer is 20% larger, which is explained by the finite rate of mixing. As the degree of oxygen dilution with nitrogen increases, the critical height of the layer increases, and the role of finite rate mixing decreases: the results no longer depend on the method of combustible mixture formation.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"128 ","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139245611","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation 基于压力的推力矢量角优化估算法

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-22 DOI: 10.3390/aerospace10120978

Nanxing Shi, Yunsong Gu, Tingting Wu, Yuhang Zhou, Yi Wang, Shuai Deng

{"title":"An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation","authors":"Nanxing Shi, Yunsong Gu, Tingting Wu, Yuhang Zhou, Yi Wang, Shuai Deng","doi":"10.3390/aerospace10120978","DOIUrl":"https://doi.org/10.3390/aerospace10120978","url":null,"abstract":"This research developed a pressure-based thrust vectoring angle estimation method for fluidic thrust vectoring nozzles. This method can accurately estimate the real-time in-flight thrust vectoring angle using only wall pressure information on the inner surface of the nozzle. We proposed an algorithm to calculate the thrust vectoring angle from the wall pressure inside the nozzle. Non-dominated sorting genetic algorithm II was applied to find the optimal sensor arrays and reduce the wall pressure sensor quantity. Synchronous force and wall pressure measurement experiments were carried out to verify the accuracy and real-time response of the pressure-based thrust vectoring angle estimation method. The results showed that accurate estimation of the thrust vectoring angle can be achieved with a minimum of three pressure sensors. The pressure-based thrust vectoring angle estimation method proposed in this study has a good prospect for engineering applications; it is capable of accurate real-time in-flight monitoring of the thrust vectoring angle. This method is important and indispensable for the closed-loop feedback control and aircraft attitude control of fluidic thrust vectoring control technology.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"301 ","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139249353","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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 Proton Flux Prediction Method Based on an Attention Mechanism and Long Short-Term Memory Network 基于注意力机制和长短期记忆网络的质子通量预测方法

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-22 DOI: 10.3390/aerospace10120982

Zhiqian Zhang, Lei Liu, Lin Quan, Guohong Shen, Rui Zhang, Yuqi Jiang, Yuxiong Xue, Xianghua Zeng

{"title":"A Proton Flux Prediction Method Based on an Attention Mechanism and Long Short-Term Memory Network","authors":"Zhiqian Zhang, Lei Liu, Lin Quan, Guohong Shen, Rui Zhang, Yuqi Jiang, Yuxiong Xue, Xianghua Zeng","doi":"10.3390/aerospace10120982","DOIUrl":"https://doi.org/10.3390/aerospace10120982","url":null,"abstract":"Accurately predicting proton flux in the space radiation environment is crucial for satellite in-orbit management and space science research. This paper proposes a proton flux prediction method based on a hybrid neural network. This method is a predictive approach for measuring proton flux profiles via a satellite during its operation, including crossings through the SAA region. In the data preprocessing stage, a moving average wavelet transform was employed to retain the trend information of the original data and perform noise reduction. For the model design, the TPA-LSTM model was introduced, which combines the Temporal Pattern Attention mechanism with a Long Short-Term Memory network (LSTM). The model was trained and validated using 4,174,202 proton flux data points over a span of 12 months. The experimental results indicate that the prediction accuracy of the TPA-LSTM model is higher than that of the AP-8 model, with a logarithmic root mean square error (logRMSE) of 3.71 between predicted and actual values. In particular, an improved accuracy was observed when predicting values within the South Atlantic Anomaly (SAA) region, with a logRMSE of 3.09.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"117 ","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139249291","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Multiple UAS Traffic Planning Based on Deep Q-Network with Hindsight Experience Replay and Economic Considerations 基于深度 Q 网络的多无人机系统交通规划，并考虑后见之明的经验回放和经济因素

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-22 DOI: 10.3390/aerospace10120980

Shao Xuan Seah, S. Srigrarom

{"title":"Multiple UAS Traffic Planning Based on Deep Q-Network with Hindsight Experience Replay and Economic Considerations","authors":"Shao Xuan Seah, S. Srigrarom","doi":"10.3390/aerospace10120980","DOIUrl":"https://doi.org/10.3390/aerospace10120980","url":null,"abstract":"This paper explores the use of deep reinforcement learning in solving the multi-agent aircraft traffic planning (individual paths) and collision avoidance problem for a multiple UAS, such as that for a cargo drone network. Specifically, the Deep Q-Network (DQN) with Hindsight Experience Replay framework is adopted and trained on a three-dimensional state space that represents a congested urban environment with dynamic obstacles. Through formalising a Markov decision process (MDP), various flight and control parameters are varied between training simulations to study their effects on agent performance. Both fully observable MDPs (FOMDPs) and partially observable MDPs (POMDPs) are formulated to understand the role of shaping reward signals on training performance. While conventional traffic planning and optimisation techniques are evaluated based on path length or time, this paper aims to incorporate economic analysis by considering tangible and intangible sources of cost, such as the cost of energy, the value of time (VOT) and the value of reliability (VOR). By comparing outcomes from an integration of multiple cost sources, this paper is better able to gauge the impact of various parameters on efficiency. To further explore the feasibility of multiple UAS traffic planning, such as cargo drone networks, the trained agents are also subjected to multi-agent point-to-point and hub-and-spoke network environments. In these simulations, delivery orders are generated using a discrete event simulator with an arrival rate, which is varied to investigate the effect of travel demand on economic costs. Simulation results point to the importance of signal engineering, as reward signals play a crucial role in shaping reinforcements. The results also reflect an increase in costs for environments where congestion and arrival time uncertainty arise because of the presence of other agents in the network.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"30 4","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139249333","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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