Aerospace最新文献_第8页

Performance Improvement of Human Centrifuge Systems through Multi-Objective Configurational Design Optimisation 通过多目标配置优化设计提高人体离心机系统的性能

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-12-02 DOI: 10.3390/aerospace10121013

Asher Winter, N. Mohajer, D. Nahavandi, Shady Mohamed

{"title":"Performance Improvement of Human Centrifuge Systems through Multi-Objective Configurational Design Optimisation","authors":"Asher Winter, N. Mohajer, D. Nahavandi, Shady Mohamed","doi":"10.3390/aerospace10121013","DOIUrl":"https://doi.org/10.3390/aerospace10121013","url":null,"abstract":"Human Centrifuge Systems (HCSs) are an effective training tool to improve the G-acceleration and Spatial Disorientation (SD) tolerance of aircrew. Though highly capable HCSs are available, their structure and performance are yet to be fully optimised to efficiently recreate the G-vectors produced using Aircraft Combat Manoeuvres (ACMs). To achieve this improvement, the relationship between configurational design and HCS performance should be profoundly investigated. This work proposes a framework for identifying the optimal configurational design of an active four Degree-of-Freedom (DoF) HCS. The relationship between configurational design parameters and objective criteria is established using inverse kinematics and dynamics. Then, a multi-objective evolutionary optimiser is used to identify the optimum arm length and seat position, minimising the Coriolis effect, relative acceleration ratio, and cost. The results of the work show that the applied optimisation step can significantly contribute to (1) efficiently replicating the aircraft motion, (2) minimising the detrimental effects generated during HCS motion, and (3) reducing the overall cost of the system. The applied methodology can be adapted to HCSs with different structures and DoFs.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"75 11","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138606224","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

Initial Identification of Thrust and Orbit Elements for Continuous Thrust Spacecraft in Circular Orbit 初步确定圆形轨道上连续推力航天器的推力和轨道要素

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-12-01 DOI: 10.3390/aerospace10121012

Shuailong Zhao, Xuefeng Tao, Zhi Li

引用次数: 0

Dynamic Modeling and Vibration Suppression of a Rotating Flexible Beam with Segmented Active Constrained Layer Damping Treatment 采用分段式主动约束层阻尼处理的旋转柔性梁的动态建模与振动抑制

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-30 DOI: 10.3390/aerospace10121010

Yue Wang, Yiming Fang, Liang Li, Dingguo Zhang, W. Liao, Jianshi Fang

{"title":"Dynamic Modeling and Vibration Suppression of a Rotating Flexible Beam with Segmented Active Constrained Layer Damping Treatment","authors":"Yue Wang, Yiming Fang, Liang Li, Dingguo Zhang, W. Liao, Jianshi Fang","doi":"10.3390/aerospace10121010","DOIUrl":"https://doi.org/10.3390/aerospace10121010","url":null,"abstract":"This paper uses high-order approximate coupling (HOAC) dynamics equations for the hub–beam system with segmented active constrained layer damping treatment (SACLD). To improve the damping characteristics of traditional active constrained layer damping (ACLD), the viscoelastic damping layer, and the piezoelectric constraining layer are cut at the same position. The damping characteristics of the structure are enhanced by increasing the shear strain of the viscoelastic damping layer. The finite element method is used to discretize the SACLD beam. The discontinuity of the SACLD beam element-to-element displacement achieves the notch. Based on the theory of rigid–flexible coupling dynamics, the dynamic responses of the SACLD rotating beam under different cases are studied. The results show that the segmentation method is not always effective. A SACLD beam provides better vibration suppression than an ACLD beam only when appropriate material and dimensional parameters are used. The influences of base-layer thickness, piezoelectric constraining layer thickness, viscoelastic damping-layer thickness, angular velocity, the viscoelastic damping-layer loss factor, and control gains on the vibration of the rotating flexible beam with SACLD treatment are also discussed.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"334 ","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139204143","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

Modular Multifunctional Composite Structure for CubeSat Applications: Embedded Battery Prototype Modal Analysis 用于立方体卫星的模块化多功能复合结构：嵌入式电池原型模态分析

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-30 DOI: 10.3390/aerospace10121009

Giorgio Capovilla, Enrico Cestino, Leonardo Reyneri

{"title":"Modular Multifunctional Composite Structure for CubeSat Applications: Embedded Battery Prototype Modal Analysis","authors":"Giorgio Capovilla, Enrico Cestino, Leonardo Reyneri","doi":"10.3390/aerospace10121009","DOIUrl":"https://doi.org/10.3390/aerospace10121009","url":null,"abstract":"Current CubeSats usually exhibit a low structural mass efficiency and a low internal volume for their payloads. The present work aims to propose an advanced structural architecture for CubeSats that addresses the issues of low structural mass efficiency and payload volume. The starting concept is the smart tiles architecture for satellites developed for the ARAMIS (an Italian acronym for a highly modular architecture for satellite infrastructures) CubeSat project. By introducing multifunctional structures and lightweight, composite materials in the design of smart tiles, the volumetric and structural mass efficiency of the entire CubeSat are enhanced. The advantages of the chosen approach are preliminarily analyzed in terms of the volumetric efficiency and amplitude of the payload design space. A 1U battery tile design is then selected to investigate the multifunctional structures design aspects in the project of space structures. A battery tile prototype is designed, produced, and tested. The CubeSat volumetric increment and the payload volume gain with respect to the traditional architecture is shown to reach a maximum of 37%. The CubeSat structural mass ratio can be reduced to 16.7%.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"41 1","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139208629","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

Time-of-Flight Measurements in the Jet of a High-Current Vacuum Arc Thruster 大电流真空电弧推进器喷流中的飞行时间测量

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-30 DOI: 10.3390/aerospace10121011

Etienne Michaux, S. Mazouffre

引用次数: 0

An Intelligent Autonomous Morphing Decision Approach for Hypersonic Boost-Glide Vehicles Based on DNNs 基于 DNN 的高超音速助推滑翔飞行器智能自主变形决策方法

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-30 DOI: 10.3390/aerospace10121008

Linfei Hou, Honglin Liu, Ting Yang, Shuaibin An, Rui Wang

{"title":"An Intelligent Autonomous Morphing Decision Approach for Hypersonic Boost-Glide Vehicles Based on DNNs","authors":"Linfei Hou, Honglin Liu, Ting Yang, Shuaibin An, Rui Wang","doi":"10.3390/aerospace10121008","DOIUrl":"https://doi.org/10.3390/aerospace10121008","url":null,"abstract":"In addressing the morphing problem in vehicle flight, some scholars have primarily employed reinforcement learning methods to make morphing decisions based on task. However, they have not considered the constraints associated with the task process. The innovation of this article is that it proposes an intelligent morphing decision method based on deep neural networks (DNNs) for the autonomous morphing decision problem of hypersonic boost-glide morphing vehicles under process constraints. Firstly, we established a dynamic model of a hypersonic boost-glide morphing vehicle with a continuously variable sweep angle. Then, in order to address the decision optimality problem considering errors and the heat flux density constraint problem during the gliding process, interference was introduced to the datum trajectory in segments. Subsequently, re-optimization was performed to generate a trajectory sample library, which was used to train an intelligent decision-maker using a DNN. The simulation results demonstrated that, compared with the conventional programmatic morphing approach, the intelligent morphing decision maker could dynamically determine the sweep angle based on the current flight state, leading to improved range while still adhering to the heat flux density constraint. This validates the effectiveness and robustness of the proposed intelligent decision-maker.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":" 29","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139207057","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

Conceptual Design of an On-Axis 6 m Space Telescope at the Diffraction Limit: Characteristics, Performance and Advantages 衍射极限轴上 6 米太空望远镜的概念设计：特性、性能和优势

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-29 DOI: 10.3390/aerospace10121003

Ariadna Calcines Rosario

{"title":"Conceptual Design of an On-Axis 6 m Space Telescope at the Diffraction Limit: Characteristics, Performance and Advantages","authors":"Ariadna Calcines Rosario","doi":"10.3390/aerospace10121003","DOIUrl":"https://doi.org/10.3390/aerospace10121003","url":null,"abstract":"This paper presents the conceptual design of an on-axis 6 metre aperture space telescope designed to cover a field of view of ±0.2 degrees with an optical quality at the diffraction limit within a spectral range between 0.5 μm and 2.5 μm. The plate scale is 3 arcsec/mm, and the overall length is less than 12 m. A Korsch layout has been selected based on the superb aberration compensation offered by Three-Mirror Anastigmat systems. The proposed design presents some characteristics: an almost flat response in RMS wavefront error across the field and for the entire spectral range; a flat mirror has been included to reduce the overall volume, and this has been adjusted to be placed at an intermediate pupil position, acting as a baffle for stray light and as a Lyott to restrict background radiation. This mirror presents a central hole, defined to the aperture of the pupil, allowing the transmission of the beam towards the image focal plane, where it can be split for multiple payloads. It also allows the transmission of the central field, at 90 degrees with respect to the science beam, to be used for Active Optics monitoring and correction of the primary mirror in order to ensure optimum optical performance. This on-axis solution significantly reduces the technical complexity for manufacturing, metrology, integration, and tests and has an important impact in the cost of the telescope.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"15 1","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139211492","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

Minimum-Energy Transfer Optimization between Near-Circular Orbits Using an Approximate Closed-Form Solution 利用近似闭式解法优化近圆轨道间的最小能量传递

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-29 DOI: 10.3390/aerospace10121002

K. Suslov, Maksim Shirobokov, A. Tselousova

引用次数: 0

Training Sample Pattern Optimization Based on a Swarm Intelligence Algorithm for Tiltrotor Flight Dynamics Model Approximation 基于蜂群智能算法的训练样本模式优化，用于倾转旋翼机飞行动力学模型逼近

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-29 DOI: 10.3390/aerospace10121006

Jiayu Wen, Yanguo Song, Huanjin Wang, Dong Han, Changfa Yang

{"title":"Training Sample Pattern Optimization Based on a Swarm Intelligence Algorithm for Tiltrotor Flight Dynamics Model Approximation","authors":"Jiayu Wen, Yanguo Song, Huanjin Wang, Dong Han, Changfa Yang","doi":"10.3390/aerospace10121006","DOIUrl":"https://doi.org/10.3390/aerospace10121006","url":null,"abstract":"Neural networks have been widely used as compensational models for aircraft control designs and as surrogate models for other optimizations. In the case of tiltrotor aircraft, the total number of aircraft states and controls is much greater than that of both traditional fixed-wings and helicopters. This requires, in general, a huge amount of training data for the network to reach a satisfactory approximation precision and makes the network size rise considerably. To solve the practical problem of reducing the size of the approximating network, efforts have to be made in the efficient utilization of the limited amount of training data. This work presents the methodology of optimizing the sample pattern of the training data set by adopting the metaheuristic algorithm of the particle swarm optimizer improved by the fourth-order Runge–Kutta algorithm. A 6-degree-of-freedom nonlinear flight dynamics model of the tiltrotor aircraft is derived, along with its approximation radial basis function neural network. An example case of approximating a highly nonlinear function is studied to illustrate the principle and main parameters of the optimizer, and the approximation performance of the time-domain response of the unstable nonlinear system is revealed by the study of a Van der Pol oscillator. Then, the presented method is applied to the modeled tiltrotor aircraft for its early and late conversion modes. The optimization scheme shows great improvement in both cases, as the function approximation error is reduced significantly.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"17 1","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139214726","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

Effect of Engine Design Parameters on the Climate Impact of Aircraft: A Case Study Based on Short-Medium Range Mission 发动机设计参数对飞机气候影响的影响：基于中短程飞行任务的案例研究

IF 2.6 3区工程技术

Aerospace Pub Date : 2023-11-29 DOI: 10.3390/aerospace10121004

Harjot Singh Saluja, F. Yin, A. Gangoli Rao, Volker Grewe

{"title":"Effect of Engine Design Parameters on the Climate Impact of Aircraft: A Case Study Based on Short-Medium Range Mission","authors":"Harjot Singh Saluja, F. Yin, A. Gangoli Rao, Volker Grewe","doi":"10.3390/aerospace10121004","DOIUrl":"https://doi.org/10.3390/aerospace10121004","url":null,"abstract":"The climate impact of aviation is considerably different from that of other transport modes. The turbofan engine’s efficiency can be increased by increasing the Operating Pressure Ratio (OPR), bypass ratio (BPR) and Turbine Inlet Temperature (TIT), thereby reducing CO2 and H2O emissions. However, this may have an adverse effect on the secondary emissions, such as NOx, soot, etc. Taking a holistic view in evaluating the climate impact of engine development trends considering all the climate forcers is imperative for design trends in the future. This research investigates the impact of some key engine design parameters on climate. The emission changes due to design variations in the CFM56-5B are estimated using in-house engine performance and emission prediction tools. Accordingly, the changes in the species’ Average Temperature Response for 100 years (ATR100) are analyzed using a climate assessment tool, AirClim. The results show that the overall climate impact increases by 40% when increasing OPR from 25 to 40. Meanwhile, the Twin Annular Premixed Swirler (TAPS-II) combustor reduces the total ATR100 drastically, in the range of 52–58%, due to lean combustion.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":"15 1","pages":""},"PeriodicalIF":2.6,"publicationDate":"2023-11-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139212050","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