Aerospace Science and Technology最新文献

{"title":"Static and structural dynamic analysis of thick panel kirigami deployable structures","authors":"Junlan Li ,&nbsp;Cheng Wang ,&nbsp;Yucheng Yan ,&nbsp;Peng Wang ,&nbsp;Jieliang Zhao ,&nbsp;Dawei Zhang","doi":"10.1016/j.ast.2024.109753","DOIUrl":"10.1016/j.ast.2024.109753","url":null,"abstract":"<div><div>Thick panel origami and kirigami concepts have been wildly used to design novel deployable structures in various engineering applications. However, these novel folding methods usually involve complex connected topologies, which may lead to unclear and intricate characterized relationships between system properties and structural parameters, e.g., the position of cutting creases, design parameters and hinge stiffness arrangement, etc. In this paper, we propose theoretical models to describe the static and dynamic properties of thick panel kirigami structure in the fully deployed configuration. Firstly, the connected topology of the origami and kirigami structure is analysed, and the internal coupling topology of the structure is obtained. Based on the compliant matrix method, the static model of the structure is presented, and the different crease cutting modes of origami and kirigami arrays are discussed. Then, the motion modes of slight oscillation of structure are discussed and the structural dynamic model is obtained based on the Lagrange equation and validated by simulation. On this basis, the sensitivity analysis of the parameters is carried out, and the optimization model is given based on the comprehensive performance evaluation function. A physical prototype is optimized and tested, which indicates that our model is valid. This paper provides models for the structural static and dynamic properties of thick panel kirigami structures with complex connected topology, and the findings have a potential to be developed in other thick panel structures with origami and kirigami folding concepts.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109753"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142696829","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":"Aerodynamics coupling study on the tail cone electrical ducted fan integrated with fuselage","authors":"Hanru Liu ,&nbsp;Jiahui Li ,&nbsp;Yuyao Feng ,&nbsp;Yangang Wang ,&nbsp;Xuewei Sun","doi":"10.1016/j.ast.2024.109749","DOIUrl":"10.1016/j.ast.2024.109749","url":null,"abstract":"<div><div>The tail cone thruster configuration is an important layout to realize the hybrid electric propulsion technology. This study carries out numerical simulation on the scaling tail-cone electrical ducted fan integrated with fuselage. The performance change of the ducted fan under the boundary layer ingestion and the overall benefit in the tail cone thruster layout are investigated. The results show that compared with the isolated fan, the thrust of the tail cone thruster layout increases by 2%. The fan isentropic efficiency is decreased by 1.03%, but the fan propulsive efficiency is increased by 15.48%. The influence of the axial installation position of the fan on the aerodynamic performance is analyzed. The results show that as the axial installation position increases, the propulsive efficiency first increases and then decreases. When the axial installation position increases to 1.71D, the propulsive efficiency is increased by 0.26% compared with 1.58D. The investigation of angle of attack shows that the aerodynamic performance of the tail cone thruster layout has no obvious change in the range of 0° to 5° angle of attack. However, when the angle of attack increases from 10° to 15°, the overall thrust is decreased significantly by 42.60%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109749"},"PeriodicalIF":5.0,"publicationDate":"2024-11-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702116","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 aluminum agglomeration model based on realistic pocket distribution via microcomputed tomography","authors":"Yanfeng Jiang,&nbsp;Zilong Zhao,&nbsp;Zhan Wen,&nbsp;Wenchao Zhang,&nbsp;Songchen Yue,&nbsp;Peijin Liu,&nbsp;Wen Ao","doi":"10.1016/j.ast.2024.109727","DOIUrl":"10.1016/j.ast.2024.109727","url":null,"abstract":"<div><div>The condensed combustion products (CCPs) resulted from aluminum agglomeration significantly affect the operation and safety of solid rocket motor, so it is essential to create a precise agglomeration model to predict the size of the CCPs of aluminized solid propellant. To accomplish this, high-precision microcomputed tomography (micro-CT) scanning was employed to obtain the quasi-three-dimensional structure of the propellant. The distribution of the ammonium perchlorate (AP) pockets was recognized via artificial intelligence (AI) method. The results revealed that the pocket size was mainly influenced by the AP grade. As the fraction of the coarse AP fraction declined from 43.1 % to 23.1 %, the average pocket diameter reduced from 388.91 to 68.23 μm. Size distribution predictions were subsequently performed for the agglomerations based on the pocket model theory. The equation relationship between agglomeration coefficient and propellant formulation was presented and corrected through mathematical fitting. The proposed agglomeration model was validated using the CCPs collection experiments of six aluminized propellants at 7 MPa. The agglomeration model produced an average particle size prediction error of &lt;9.8 %, and the goodness of fit of the agglomerate distribution was &gt;0.85. Subsequent analysis indicated that the agglomerate size mainly depended on the percentage of coarse AP, the burn rate, and the size distribution of raw aluminum particles. The present model is expected to offer a new way to achieve the accurate prediction of solid propellant agglomeration behaviors.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109727"},"PeriodicalIF":5.0,"publicationDate":"2024-11-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703108","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":"Wall temperature effects in high-enthalpy supersonic turbulent channel flows considering air dissociation","authors":"Xiaoping Chen,&nbsp;Shuo Zhao","doi":"10.1016/j.ast.2024.109750","DOIUrl":"10.1016/j.ast.2024.109750","url":null,"abstract":"<div><div>Direct numerical simulations of temporally evolving high-enthalpy supersonic turbulent channel flows are performed at a Mach number of 3.0 and Reynolds number of 4880. The high-enthalpy air is assumed to behave as a chemical and thermal equilibrium of five-species mixture. The wall temperatures in the range of 1733.2 K to 4100.0 K to study the influence of wall temperature on the chemical activity, turbulent statistics and aerodynamic characteristics. The results show that the chemical activity is remarkable because the air is relatively sufficient dissociated. When the wall temperature higher than 2300 K, an extreme value can be observed in the distributions of mean and fluctuating mass fraction of atomic nitrogen close to the wall. Many of the influence of wall temperature on the turbulent statistics which hold for low-enthalpy conditions also hold for high-enthalpy conditions, including mean and fluctuating velocity, recovery enthalpy, and strong Reynolds analogy. As the wall temperature increases, the turbulent momentum flux and turbulent heat flux decrease, the turbulent mass flux mainly depends on species mass fractions fluctuations. The integral formulas of decomposing the aerodynamic characteristics are proposed, and the predicted heat flux and skin friction are all in good agreement with those direct estimation. The wall temperature does not change the primarily contributions of aerodynamic characteristics. Although the turbulent heat flux term is approximately 6%, its part of turbulent transport of enthalpy significantly increases with increasing wall temperature. The turbulent Schmidt number is insensitive to wall temperature.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109750"},"PeriodicalIF":5.0,"publicationDate":"2024-11-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702117","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":"Accelerated inverse design of vibration isolators with customizable low dynamic stiffness characteristics via deep neural network","authors":"Changzhi Hu,&nbsp;Zonghan Li,&nbsp;Ximing Tan,&nbsp;Mingji Chen","doi":"10.1016/j.ast.2024.109735","DOIUrl":"10.1016/j.ast.2024.109735","url":null,"abstract":"<div><div>The quasi-zero stiffness (QZS) isolator composed of curved beams is considered to be an effective way to address the contradiction between high load-bearing capacity and low-frequency vibration isolation. However, finding geometries with target QZS characteristics is not simple. In this study, we present a framework for designing customizable QZS isolators. We employ a deep neural network to accurately learn the relationship between the geometry of the curved beam and its nonlinear mechanical response. Furthermore, we combine the network with genetic algorithm to inverse-design isolators that exhibit the targeted QZS characteristics, thereby achieving a two-order-of-magnitude improvement in speed compared to traditional method. Static experiments demonstrate the reliability and customizability of the proposed design strategy for QZS isolators. Dynamic analysis shows that the isolator has a low resonant frequency, enabling ultra-low-frequency vibration isolation. Notably, series-parallel arrangements can significantly improve the load-bearing capacity or vibration isolation performance of the isolator. Our design framework addresses efficiency issues in traditional QZS designs, enabling faster iterations and calculations. It has broad applicability and potential in systems requiring customized nonlinear mechanical responses.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109735"},"PeriodicalIF":5.0,"publicationDate":"2024-11-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703110","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":"Aerodynamic and aeroacoustics investigation of tandem propellers in hover for eVTOL configurations","authors":"Daniele Granata,&nbsp;Alberto Savino,&nbsp;Donato Grassi,&nbsp;Luca Riccobene,&nbsp;Alex Zanotti","doi":"10.1016/j.ast.2024.109740","DOIUrl":"10.1016/j.ast.2024.109740","url":null,"abstract":"<div><div>The present study investigates the aerodynamic interactions and the aeroacoustic footprint of a tandem propellers configuration typical of a multi-rotor eVTOL aircraft in hover conditions. In particular, an experimental campaign was conducted to collect a comprehensive aerodynamic and aeroacoustic database over two scaled propellers models in tandem. Aerodynamic loads and acoustic measurements were performed in an anechoic test chamber. Measurements also included flow field surveys using stereoscopic PIV technique. The configurations tested included twin propellers in side-by-side and staggered configurations with partial overlap between rotor disks. The activity was completed by numerical simulations performed with the mid-fidelity aerodynamic solver DUST. The analysis of experimental and numerical results enabled to provide a robust comprehension of the different flow mechanisms that characterise aerodynamic interaction between propellers wakes by changing longitudinal and lateral distances as well as blades sense of rotation. In particular, the effects of these interactions on both the aerodynamic performance and aeroacoustic footprint was investigated. Specifically, the partial overlap between propellers disks leads to a conspicuous reduction of aerodynamic performance of the propeller invested by front propeller slipstream as well as an increase of the acoustic emission of the dual propeller system.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109740"},"PeriodicalIF":5.0,"publicationDate":"2024-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703114","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Multi-objective optimization of the design parameters in longitudinal corrugated tubes to improve crashworthiness performance","authors":"Mehrdad Koloushani ,&nbsp;Mohammad Reza Forouzan ,&nbsp;Mohammad Reza Niroomand","doi":"10.1016/j.ast.2024.109728","DOIUrl":"10.1016/j.ast.2024.109728","url":null,"abstract":"<div><div>Longitudinal corrugated tubes (LCTs) are among the structures of interest to designers, because of their ability to improve the weaknesses of conventional simple tubes by reducing the maximum crushing force (<em>F_max</em>) and providing a controllable and predictable force-displacement curve during energy absorption. In this study using finite element (FE) simulations, the effect of design parameters of LCTs, i.e., amplitude and number of folds on the crashworthiness criteria, in different deformation modes has been investigated. Crushing parameters of some simple and corrugated tubes have been examined experimentally to validate the FE simulations. Results of 400 FE models, revealed some geometries in LCTs that, in addition to reducing <em>F_max</em>, can increase the specific energy absorption (<em>SEA)</em> compared to the simple tubes. Most of these geometries deform under compressive axial loading in the N-mode region. Using multi-objective optimization, specification of the optimal LCT, including number of folds and their amplitudes were determined. Then the optimal LCT was made by the ring-forming method and compared with the simple tube experimentally. The optimized LCT was experimentally evaluated and results showed that it can reduce <em>F_max</em> by 27.2% and increase <em>SEA</em> by 21.6% compared to the simple tube. The lower <em>SEA</em> of the LCTs is usually considered as a disadvantage for the LCTs compared to the simple tubes, which is violated in this research. Optimized LCT may be a new idea for aerospace applications as crash-resistant structures.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109728"},"PeriodicalIF":5.0,"publicationDate":"2024-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703109","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 body-fitted structured grid approach to simulate breathing mode oscillations during parachute deployment","authors":"Guru P. Guruswamy","doi":"10.1016/j.ast.2024.109747","DOIUrl":"10.1016/j.ast.2024.109747","url":null,"abstract":"<div><div>A new grid topology approach suitable for body-fitted structured grids is presented to time-accurately simulate the deployment of parachutes from start. The goal is to provide an alternative efficient body-fitted structured grids to Cartesian/unstructured grids for more accurate modeling of turbulent flows. Time-accuracy essential for deployment is maintained, unlike in the quasi-steady loose coupling methods used elsewhere with Cartesian/unstructured grids. Prediction of breathing mode during deployment is demonstrated. The current paper establishes a new approach for accurately simulating deployments from the start.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109747"},"PeriodicalIF":5.0,"publicationDate":"2024-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702005","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":"Nonlinear phase velocities in tri-directional functionally graded nanoplates coupled with NEMS patch using multi-physics simulation","authors":"Shaoyong Han ,&nbsp;Qianqian Ye ,&nbsp;Haitham A. Mahmoud ,&nbsp;Ahmed Elbarbary","doi":"10.1016/j.ast.2024.109714","DOIUrl":"10.1016/j.ast.2024.109714","url":null,"abstract":"<div><div>The nonlinear phase velocities analysis of tri-directional functionally graded (FG) nanoplates is crucial for optimizing their performance as nano-electro-mechanical systems (NEMS). By understanding the nonlinear phase velocities of various wave modes within the nanoplate, engineers can accurately predict and enhance the efficiency of NEMS. This analysis allows for the precise tuning of the piezoelectric patches to capture vibrational energy more effectively, ensuring maximum energy conversion efficiency. Moreover, it helps in identifying the optimal placement and orientation of the piezoelectric patches, minimizing energy loss and enhancing the reliability and durability of the NEMS. Ultimately, this leads to more efficient utilization of ambient vibrations in airplanes, providing a sustainable power source for various onboard sensors and monitoring systems, contributing to reduced reliance on external power sources, and improved overall energy management. For this issue, for the first time, nonlinear phase velocity in the tri-directional functionally graded nanoplate coupled with a piezoelectric patch via COMSOL multi-physics simulation, physics-informed deep neural networks (PIDNNs), and mathematics simulation are presented. In the mathematics simulation domain, nonlocal strain gradient theory for modeling both the hardening and softening behavior of the current nanoplate is presented. The electromechanical coupling effect and the abrupt change in material properties at the interfaces will have a major influence on the mechanical performance of tri-directional functionally graded (TD-FG) nanoplate coupled with a piezoelectric patch if transverse shear deformations cannot be well modeled. Thereby, in the current simulation, a quasi-3D refined theory with 10 variables is presented. Also, for coupling the composite structure with the piezoelectric patch, compatibility conditions are considered. An analytical solution procedure is presented for solving the nonlinear partial differential equations of the current electrical system.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109714"},"PeriodicalIF":5.0,"publicationDate":"2024-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142721492","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 evaluation strategy of control method for corner separation/stall in compressor cascades","authors":"Jianhui Wu,&nbsp;Jiabin Li,&nbsp;Teng Fei,&nbsp;Lucheng Ji","doi":"10.1016/j.ast.2024.109743","DOIUrl":"10.1016/j.ast.2024.109743","url":null,"abstract":"<div><div>The modern design of turbomachinery tends to use a combination of the sweep, dihedral and endwall treatment methods to prevent the corner flow from separating. However, there are few rules for selecting the most effective endwall treatment methods and evaluating their efficiencies. In this paper, an evaluation method for the two phenomena that affect the endwall flow field is presented based on the diffusion parameter DJ. The method contains two models: the first is for the phenomenon of the boundary layer intersection in the corner (<em>B</em>), and the second is for the endwall secondary cross flow (<em>E</em>). The BE rule is presented by taking both B and E into account. The corner stall occurs when <span><math><mrow><mi>B</mi><mo>·</mo><mi>E</mi><mo>&gt;</mo><mn>1</mn></mrow></math></span>, and the value of B and E can be used to evaluate the severity of the two flow phenomena. The control efficiencies of the four kinds of endwall treatment methods are compared with one another using the BE rules. The four kinds of endwall treatment methods are end dihedral, blended blade and endwall, endwall grooves, and endwall vortex generators. The severity of the endwall secondary cross flow in the test case is more serious than the severity of the boundary layer intersection. The numerical results show that the control efficiency of the end dihedral, blended blade and endwall, endwall grooves, and endwall vortex generators are 23%, 50%, 34.6%, and 67.3%, respectively.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109743"},"PeriodicalIF":5.0,"publicationDate":"2024-11-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703117","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}