Aerospace Systems最新文献_第6页

Modeling of the stress–strain responses and deformation patterns of superelastic NiTi tubes subjected to biaxial loadings 受双轴载荷作用的超弹性镍钛管的应力应变响应和变形模式建模

Aerospace Systems Pub Date : 2024-01-04 DOI: 10.1007/s42401-023-00266-x

Mingxun Wu, Dongjie Jiang

{"title":"Modeling of the stress–strain responses and deformation patterns of superelastic NiTi tubes subjected to biaxial loadings","authors":"Mingxun Wu, Dongjie Jiang","doi":"10.1007/s42401-023-00266-x","DOIUrl":"10.1007/s42401-023-00266-x","url":null,"abstract":"<div><p>Nearly equiatomic NiTi shape memory alloy exhibits superelasticity, i.e., it can be strained up to ~ 7% and recover completely upon unloading, and consequently, the stress–strain response forms a closed hysteresis. The mechanical behavior of superelastic NiTi is characterized by significant tension–compression asymmetry, which leads to complexity in the stress–strain responses and deformation patterns of thin-walled superelastic NiTi tubes loaded by axial force and internal pressure simultaneously. In the reported biaxial experiments, the NiTi tube exhibits hardening responses and essentially homogeneous deformation in a neighborhood of equibiaxiality. In other cases, its stress–strain responses trace stress plateaus associated with localized deformation patterns, and the level of plateaus, magnitude of transformation strains, and orientation of the localization bands are strongly dependent on the axial-to-hoop stress ratio. In this paper, finite element modeling is performed to analyze numerically the mechanical response of biaxially loaded superelastic NiTi tube. A numerical feedback control scheme is developed to maintain the stress ratio to follow the target value. The simulations reproduce successfully the observed phenomena in the experiments, such as the localization of helical bands, the variation of band angles with stress ratio, as well as the hardening and uniform deformation near the state of equibiaxial stress. In addition, the variation of axial and hoop stress–strain responses with different stress ratios are also studied, which are reasonably close to the experimental ones. The presented work demonstrates the validity of the developed finite element analysis framework and paves the way for analysis of superelastic shape memory alloy structures under multiaxial loading.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 3","pages":"599 - 615"},"PeriodicalIF":0.0,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139384667","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Hybrid optimization of curvature continuous stacking line on the highly loaded diffuser cascade 在高负荷扩散器级联上对曲率连续堆叠线进行混合优化

Aerospace Systems Pub Date : 2024-01-04 DOI: 10.1007/s42401-023-00265-y

Ke Yao, Xingyi Zhang, Xiaoqing Qiang

{"title":"Hybrid optimization of curvature continuous stacking line on the highly loaded diffuser cascade","authors":"Ke Yao, Xingyi Zhang, Xiaoqing Qiang","doi":"10.1007/s42401-023-00265-y","DOIUrl":"10.1007/s42401-023-00265-y","url":null,"abstract":"<div><p>The compressor is a critical component of aero-engines. In order to improve the performance, the compressor ratio of single-stage compressor is getting higher and higher, which will lead to high back pressure gradient and losses. To solve this problem, there are many techniques applied, such as cantilevered stator, tip clearance and slotted airfoils. However, traditional design methods are experience-dependent and time-consuming. This paper proposes a hybrid optimization method to optimize the stacking line of compressor cascade and reduce total pressure loss on both design and off-design conditions. The approach employs various surrogate models and a multi-infill strategy, outperforming traditional optimization methods using a single surrogate model and a single infilling strategy. The results show that compared to the original blade, the optimized blade has a 34.6<span>(%)</span> lower mass-averaged total pressure loss at the design point, while the static pressure ratio increases by 2.43<span>(%)</span>. This paper innovatively combines deep learning-based surrogate models, the hybrid optimization algorithm, and the curvature-based blade shaping method to optimize the blade shape, shorten the blade design time, and ultimately reduce the losses significantly.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 3","pages":"585 - 597"},"PeriodicalIF":0.0,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139386247","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Rocket-based versus solar wing-tail Martian UAVs: design, analysis, and trade studies 火箭与太阳能翼尾火星无人飞行器：设计、分析和贸易研究

Aerospace Systems Pub Date : 2024-01-04 DOI: 10.1007/s42401-023-00267-w

Elena Karpovich, Timur Kombaev, Djahid Gueraiche, Dmitriy Strelets

引用次数: 0

Theoretical analysis of decompression tolerance based on a simulated depressurisation model of an aircraft’s pressurised cabin 基于飞机增压舱模拟减压模型的减压耐受性理论分析

Aerospace Systems Pub Date : 2023-12-20 DOI: 10.1007/s42401-023-00262-1

Timofey Matyushev, Michael Dvornikov, Irina Maximova, Anastasia Rybina, Andrey Malyshev

{"title":"Theoretical analysis of decompression tolerance based on a simulated depressurisation model of an aircraft’s pressurised cabin","authors":"Timofey Matyushev, Michael Dvornikov, Irina Maximova, Anastasia Rybina, Andrey Malyshev","doi":"10.1007/s42401-023-00262-1","DOIUrl":"10.1007/s42401-023-00262-1","url":null,"abstract":"<div><p>The method presented in the article is based on a complex simulation model of gas-dynamic processes that take place in sectioned cabins during depressurization. This model allows the theoretical calculation of decompression parameters (decompression time, cabin pressure, gas leakage from the cabin) depending on flight parameters and design features of the aircraft pressurised cabin (height, cabin volume, defect area, etc.) and determine the interdependence of pressure control parameters in critical operating modes. In computational experiments simulating decompression during depressurisation, the rate of cabin pressure drop as a function of the defect area, residual overpressure, decompression time, values of drops between compartment sections and mass flow rate during pressure changes; safe descent height and other parameters were determined. On the basis of computational experiments, a methodology for assessing the portability of decompression was developed, taking into account different levels of impact tolerance, allowing for a rational choice of hermetic and gas dynamic parameters of the cabin, as well as flight performance characteristics, taking into account the possible decompression of the cabin in flight or, conversely, with the specified parameters of the cabin and flight data at the design stage of the aircraft to assess the degree of danger in case of depressurization and to provide in advance a set of security measures. The transition for decompression safety analysis along the Chadov V. I. curve has advantages since it is applicable for various types of aircraft from spacecraft to aircraft and for various atmospheres with different combinations of pressures and concentrations.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 3","pages":"575 - 584"},"PeriodicalIF":0.0,"publicationDate":"2023-12-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139168720","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Transition control of the blasius boundary layer using linear robust control theory 利用线性鲁棒控制理论对布拉修斯边界层进行过渡控制

Aerospace Systems Pub Date : 2023-12-13 DOI: 10.1007/s42401-023-00258-x

Christopher J. Damaren

{"title":"Transition control of the blasius boundary layer using linear robust control theory","authors":"Christopher J. Damaren","doi":"10.1007/s42401-023-00258-x","DOIUrl":"10.1007/s42401-023-00258-x","url":null,"abstract":"<div><p>The paper considers control system design for linearized three-dimensional perturbations about a nominal laminar boundary layer over a flat plate (the Blasius profile). The objective is prevention of the laminar to turbulent transition using appropriate inputs, outputs, and feedback controllers. They are synthesized with a view to reducing transient energy growth, a known precursor to important transition scenarios. The linearized Navier–Stokes equations are reduced to the Orr–Sommerfeld and Squire equations with wall-normal velocity actuation entering through the boundary conditions on the wall. The sensor output is taken to be the wall-normal derivative of the wall-normal vorticity measured on the plate. Several multivariable output controllers are examined, including simple constant gain output feedback, loop transfer recovery, and <span>(H_{infty })</span> loop shaping. Reduced order compensators are developed using balanced truncation and analyzed for robustness using the gap metric between reduced order models and full order models. It is demonstrated that the level of minimum transient energy growth that can be achieved is similar for these diverse controller methodologies but falls short of that which can be achieved using optimal state feedback.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 2","pages":"279 - 292"},"PeriodicalIF":0.0,"publicationDate":"2023-12-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42401-023-00258-x.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138976884","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Ku-band tracking, command and ranging antenna design for small satellites communications applications 用于小型卫星通信应用的 Ku 波段跟踪、指令和测距天线设计

Aerospace Systems Pub Date : 2023-12-12 DOI: 10.1007/s42401-023-00261-2

Zakarya Kourdi, Mohammed Amin Rabah, Ahmed-Ali Kanoun, Faiza Merad, Youcef Benabdellah

引用次数: 0

Robust control design for zero-sum differential games problem based on off-policy reinforcement learning technique 基于非策略强化学习技术的零和微分博弈问题鲁棒控制设计

Aerospace Systems Pub Date : 2023-12-12 DOI: 10.1007/s42401-023-00263-0

Hongji Zhuang, Hongxu Zhu, Shufan Wu, Xiaoliang Wang, Zhongcheng Mu, Qiang Shen

引用次数: 0

SESPnet: a lightweight network with attention mechanism for spacecraft pose estimation SESPnet：带有关注机制的轻量级航天器姿态估计网络

Aerospace Systems Pub Date : 2023-12-08 DOI: 10.1007/s42401-023-00259-w

Chao Chen, Zhongliang Jing, Han Pan, Xiangming Dun, Jianzhe Huang, Hailei Wu, Shuqing Cao

引用次数: 0

Developing a novel battery management algorithm with energy budget calculation for low Earth orbit (LEO) spacecraft 为低地球轨道（LEO）航天器开发一种具有能量预算计算功能的新型电池管理算法

Aerospace Systems Pub Date : 2023-12-08 DOI: 10.1007/s42401-023-00260-3

Mohamed Ahmed Mokhtar, H. Amer Fawzy ElTohamy, Z. Elhalwagy Yehia, E. Hanafy Mohamed

{"title":"Developing a novel battery management algorithm with energy budget calculation for low Earth orbit (LEO) spacecraft","authors":"Mohamed Ahmed Mokhtar, H. Amer Fawzy ElTohamy, Z. Elhalwagy Yehia, E. Hanafy Mohamed","doi":"10.1007/s42401-023-00260-3","DOIUrl":"10.1007/s42401-023-00260-3","url":null,"abstract":"<div><p>The electrical power system (EPS) of a spacecraft (SC) plays a crucial role in the mission's success. This system provides electrical power to all loads of SC until its end of life (EOL). The primary power source onboard for the SC is the solar array (SA), while the storage battery serves as the secondary power source. We have developed a software program called the SC Charging Analysis Tool with Battery Management Algorithm (BMA) to address the challenges associated with the SC battery's charging and discharging processes. This tool fulfills two main objectives: first, to develop a BMA that effectively controls the battery charging and discharging processes through all modes of SC operation; second, to create a battery management environment with SC energy budget calculation capabilities to simulate the dynamic behavior of the SC battery using the developed BMA, thereby ensuring battery health. The battery management environment is specifically designed to verify the proper performance of the battery throughout the SC's lifetime and to execute operations during nominal conditions and throughout worst-case scenarios. Moreover, through the SC energy budget calculation, we can optimize the requirements of the chosen scenario to fit with the selected battery. However, during worst-case scenarios, the battery's vital parameters, including state of charge (SOC), thermal emission, voltage, and pressure, are calculated to verify its proper operation under the developed BMA. The dynamic behavior of the battery, in conjunction with the developed algorithms, will be validated using real telemetry data. The key result of this paper is the invention of a BMA, which contributes to the advanced management of SC battery systems and, consequently, better durability during challenging operational scenarios.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 1","pages":"143 - 157"},"PeriodicalIF":0.0,"publicationDate":"2023-12-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138588999","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Study of wedge-shaped Jet tabs for effective Thrust vector control in Supersonic vehicles 研究楔形射流片以有效控制超音速飞行器的推力矢量

Aerospace Systems Pub Date : 2023-12-08 DOI: 10.1007/s42401-023-00257-y

V. M. Jyothy, G. Jims John Wessley, A. Brusly Solomon

{"title":"Study of wedge-shaped Jet tabs for effective Thrust vector control in Supersonic vehicles","authors":"V. M. Jyothy, G. Jims John Wessley, A. Brusly Solomon","doi":"10.1007/s42401-023-00257-y","DOIUrl":"10.1007/s42401-023-00257-y","url":null,"abstract":"<div><p>This work explores the thrust vector control in a 2D convergent divergent nozzle with wedge shaped jet tab. The Computational analysis has been carried out with different thickness and height of jet tabs. The flow topology analysis is carried out qualitatively and quantitatively. The wedge-shaped jet tabs with 10%, 20%, 30% and 40% of height and 10 mm, 12 mm, 14 mm, 16 mm thickness are considered for right isosceles, left isosceles and isosceles shapes. The deflection angle is calculated to identify the best effective thrust deflection configuration. Results indicate that, when thickness and height of jet tab increases the deflection angle reduces due to the formation of mixing layer and shock wave generation. Also, depending on the shape of jet tab the oblique shock formation and angle of shock varied. The thickness-based CFD optimization shows that a 4.66° deflection angle with 10 mm thickness and 40% height isosceles tab produces the best deflection. The right jet tab with 12 mm and 14 mm thickness with 30% and 20% height shows 4.75° and 4.14° deflection angle. In the case of 16 mm thickness tab, left isosceles jet tab with 10% height shows 4.14° of deflection angle. It is concluded form the study that, the highest rate of deflection was produced by the right isosceles tab with 12 mm thickness and 30% height. This can be used for thrust deflection in supersonic aircrafts and missiles.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 3","pages":"565 - 573"},"PeriodicalIF":0.0,"publicationDate":"2023-12-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138587460","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0