Aerospace Science and Technology最新文献_第3页

Aerodynamic shape optimization of a Pterocarya stenoptera seed based biomimetic aircraft using neural network 利用神经网络优化基于翼手目种子的生物仿真飞行器的气动外形

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-15 DOI: 10.1016/j.ast.2024.109737

Chenxi Liu , Chao Feng , Liu Liu , Tianqi Wang , Lifang Zeng , Jun Li

{"title":"Aerodynamic shape optimization of a Pterocarya stenoptera seed based biomimetic aircraft using neural network","authors":"Chenxi Liu , Chao Feng , Liu Liu , Tianqi Wang , Lifang Zeng , Jun Li","doi":"10.1016/j.ast.2024.109737","DOIUrl":"10.1016/j.ast.2024.109737","url":null,"abstract":"<div><div>The wind-borne <em>Pterocarya stenoptera</em> seeds depend on their double wings to keep stable autorotation and long endurance in the wind. Their superior flight modes can be applied to biomimetic aircraft. For biomimetic aircraft, floating ability is one of the most important performances, which is mainly affected by the aerodynamic shape. Based on the shape of a natural <em>Pterocarya stenoptera</em> seed, aerodynamic optimization is carried out for biomimetic aircraft. To increase the optimization efficiency, machine learning method is used in the optimization framework. Firstly, an aerodynamic surrogate model based on the radial basis function neural network and numerical simulated dataset is developed for the biomimetic aircraft, which has an accuracy of 98.4% and 94.7% for lift and aerodynamic efficiency factor, respectively. Aerodynamic optimization based on the multi-island genetic algorithm is carried out, and an optimized shape is obtained for the biomimetic aircraft. Compared with the original shape, the aerodynamic efficiency factor of the optimized one has been increased by over 50%. The larger pressure difference between the windward side and leeward side of the wings and the larger leading-edge vertex contribute to a higher lift for optimized shape.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109737"},"PeriodicalIF":5.0,"publicationDate":"2024-11-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703112","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}

引用次数: 0

Tension-twist coupling morphing wing using a novel mechanical metamaterial 利用新型机械超材料实现张扭耦合变形翼

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-15 DOI: 10.1016/j.ast.2024.109745

Xueren Zhu , Jiaying Zhang , Wei Chen , Huaiyuan Gu

引用次数: 0

A tracking guidance method with funnel scheduling for Mars landing 用于火星着陆的漏斗调度跟踪制导方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-14 DOI: 10.1016/j.ast.2024.109738

Yunzhao Liu , Mingming Wang , Jianjun Luo , JiaKe Li , Xuebin Cheng , Jishiyu Ding , Kewu Sun

{"title":"A tracking guidance method with funnel scheduling for Mars landing","authors":"Yunzhao Liu , Mingming Wang , Jianjun Luo , JiaKe Li , Xuebin Cheng , Jishiyu Ding , Kewu Sun","doi":"10.1016/j.ast.2024.109738","DOIUrl":"10.1016/j.ast.2024.109738","url":null,"abstract":"<div><div>Powered descent guidance is an enabling technology for extraterrestrial soft landing and reusable rocket recovery. Although the focus of guidance research has tilted towards trajectory optimization recently, feedback tracking control is still necessary to suppress the effects of flight perturbations and uncertainties. In this paper, for the Mars landing mission, the behavior of the powered descent closed-loop system is considered and a guidance method based on funnel (finite-time invariant set) scheduling is proposed. Firstly, the basic model of the powered descent problem is given and its state feedback closed-loop system is constructed. Subsequently, considering the thrust uncertainty as well as saturation constraints, the powered descent funnel model is established, and a point-by-point computation method based on Sum of Squares Programming (SOSP) is presented. On this basis, multiple nominal trajectories and their nearby funnels are solved. The guidance scheme based on funnel scheduling is formulated, which utilizes the funnels to provide a good basis for tracking different nominal trajectories, enhancing the adaptability to the initial state dispersions. The simulation results show that for the thrust deviation considered, the states within the funnel inlet can ensure convergence. The similar level of performance on fuel consumption and terminal accuracy of funnel scheduling guidance with convex programming guidance implies the bottleneck in feedback control performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109738"},"PeriodicalIF":5.0,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703113","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}

引用次数: 0

Multisource data fusion for defect detection in composite additive manufacturing using explainable deep neural network 利用可解释深度神经网络融合多源数据检测复合材料增材制造中的缺陷

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-14 DOI: 10.1016/j.ast.2024.109729

Deepak Kumar , Nicholas A. Phillips , Yongxin Liu , Sirish Namilae

{"title":"Multisource data fusion for defect detection in composite additive manufacturing using explainable deep neural network","authors":"Deepak Kumar , Nicholas A. Phillips , Yongxin Liu , Sirish Namilae","doi":"10.1016/j.ast.2024.109729","DOIUrl":"10.1016/j.ast.2024.109729","url":null,"abstract":"<div><div>Composite additive manufacturing has the potential to replace traditional composite manufacturing for aerospace applications. Additive manufacturing provides greater adaptability to complex designs, reduce material waste, and streamline the production process. However, in comparison to conventional composite manufacturing methods, additive manufacturing is inherently more susceptible to processing anomalies and defects, primarily due to the novelty of the process and the absence of applied pressure. To effectively capitalize on the benefits of additive manufacturing, a quality and reliability assurance system is critical. In this study, we have generated multisource data to analyze the inner layer thermography and surface quality, employing a multi-camera system including thermal and charge-coupled device cameras. This multisource data is utilized in an explainable zero bias deep neural network framework to detect manufacturing defects. This deep learning algorithm introduces a new zero bias layer following the regular dense layer. After being trained on normal (defect-free) samples of each data stream, the trained model is transformed into an anomaly detector by extracting low dimension features from the zero-bias layer. This allowed identification various anomalies without having to train the model on any defective inputs. As a result, the model's accuracy to detect multiple types of anomalies is higher with multisource data compared to models based on single data source. Anomaly detection accuracy was 99.72% when using data from multiple sources, 98.28% when using only CCD images, and 95% when using only thermal camera data.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109729"},"PeriodicalIF":5.0,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702119","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}

引用次数: 0

Nonlinear guided waves in improved silicon solar cells using mathematical modeling and a bio-inspired artificial intelligence algorithm 利用数学建模和生物启发人工智能算法实现改进型硅太阳能电池中的非线性导波

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-14 DOI: 10.1016/j.ast.2024.109726

Lei Chang , Wenqing Yang , Mohammed El-Meligy , Khalil El Hindi

{"title":"Nonlinear guided waves in improved silicon solar cells using mathematical modeling and a bio-inspired artificial intelligence algorithm","authors":"Lei Chang , Wenqing Yang , Mohammed El-Meligy , Khalil El Hindi","doi":"10.1016/j.ast.2024.109726","DOIUrl":"10.1016/j.ast.2024.109726","url":null,"abstract":"<div><div>Solar cells are crucial in aerospace industries as they provide a reliable and sustainable power source for spacecraft and satellites, enabling long-duration missions without relying on conventional fuel. This study investigates the propagation of nonlinear guided waves in improved silicon solar cells reinforced by graphene platelet (GPL) nanocomposites. The microplate model of the solar cells is developed using the modified couple stress theory (MCST) to capture size-dependent effects, and the sinusoidal shear deformation theory (SSDT) is applied to account for realistic shear deformation behavior. Nonlinear governing equations describing the dynamic response of the system are derived using Hamilton's principle. The equations are then solved numerically using the Runge–Kutta method to analyze the phase velocity and wave characteristics under varying parameters. The effects of GPL weight fraction, length scale parameter, and wavenumber on wave propagation are thoroughly examined. In this investigation, an intelligent model based on deep neural networks as an artificial intelligent algorithm combined with a genetic algorithm (DNN-GA) as a bio-inspired optimization approach, is employed to predict nonlinear phenomena in guided waves within the solar cell, using datasets generated from mathematical simulations. The results demonstrate that the inclusion of GPL nanocomposites enhances the mechanical properties of the silicon solar cells, leading to higher phase velocities and improved wave propagation efficiency. Additionally, the influence of the length scale parameter on phase velocity is found to be significant, particularly for low wavenumbers. This study provides valuable insights into the optimization of advanced nanocomposite-reinforced silicon solar cells for applications requiring efficient guided wave propagation. The findings offer a promising approach for the design and enhancement of next-generation solar cells.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109726"},"PeriodicalIF":5.0,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142721124","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}

引用次数: 0

Experimental and numerical investigation on the ballistic impact performance of sandwich panels with additively manufactured honeycomb cores 带添加型蜂窝芯的夹芯板弹道冲击性能的实验和数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-14 DOI: 10.1016/j.ast.2024.109733

Ahsan Ul Haq, Suresh Kumar Reddy Narala

{"title":"Experimental and numerical investigation on the ballistic impact performance of sandwich panels with additively manufactured honeycomb cores","authors":"Ahsan Ul Haq, Suresh Kumar Reddy Narala","doi":"10.1016/j.ast.2024.109733","DOIUrl":"10.1016/j.ast.2024.109733","url":null,"abstract":"<div><div>The pursuance of lightweight yet robust materials and structures has led to the rapid evolution of protective technologies. Additive Manufacturing (AM) has emerged as a transformative tool, enabling the fabrication of intricate cellular structures with tailored properties. The use of additively manufactured honeycombs in the field of ballistic protection has not been explored extensively. In this view, the current work presents a comprehensive investigation involving experimental and numerical procedures, to understand the impact response of sandwich panels embedded with additively manufactured honeycomb cores against ogive and conical projectile impacts. Three different honeycomb cores, namely Hexagonal, Star, and AuxHex are additively manufactured using AlSi10Mg powder via selective laser melting technique. Each core is bonded to a pair of 1 mm thick SS 316 sheets. The projectiles are launched at velocities varying between 180 m/s and 260 m/s. Finite element models are created in ABAQUS/Explicit to simulate ballistic impact scenarios. A strong consistency between the predicted results and experimental outcomes in terms of deformation, damage modes and residual velocities was obtained. The results revealed that the sandwich panel featuring an AuxHex core exhibits a superior energy absorption capacity, absorbing 15 % and 12 % more energy than hexagonal and star cores, respectively. Additionally, it was observed that, when compared to a conical projectile, an ogive projectile requires 14 % more energy to perforate the same sandwich panel. Furthermore, the ballistic limit of star and AuxHex panels is found to be increased by 5 % and 9 %, respectively compared to panels with hexagonal honeycomb cores. This work contributes valuable insights into the application of additively manufactured honeycomb cores, offering potential scope for the development of lightweight and resilient structures crucial in aerospace and defense industries.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109733"},"PeriodicalIF":5.0,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702118","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}

引用次数: 0

Effect of injection location on mixing characteristics with pylon downstream of cavity 注入位置对空腔下游塔架混合特性的影响

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-14 DOI: 10.1016/j.ast.2024.109741

Prasanth P Nair, Vinod Narayanan

{"title":"Effect of injection location on mixing characteristics with pylon downstream of cavity","authors":"Prasanth P Nair, Vinod Narayanan","doi":"10.1016/j.ast.2024.109741","DOIUrl":"10.1016/j.ast.2024.109741","url":null,"abstract":"<div><div>Scramjet propulsion holds promise for high-speed travel and reusable satellite launches, but fuel combustion at supersonic speeds presents a challenge. Limited retention time hinders proper air-fuel mixing. While placing a pylon upstream improves mixing, its impact downstream remains unexplored. This study investigates the effects of different fuel injection locations within the cavity on mixing performance. Numerical simulations with the Improved Delayed Detached-Eddy Simulation (IDDES) turbulence model are used to examine various injection locations. The study found that placing the pylon downstream significantly altered flow patterns. This led to the formation of additional vortices and better mixing downstream and within the cavity. The penetration height is also augmented due to the presence of a pylon. Different injection locations varied in mixing efficiency, penetration height, and total pressure loss, with normal-flow injection close to the cavity's aft showing better overall mixing performance. Dynamic Mode Decomposition (DMD) analysis provided insights into mixing improvement mechanisms, highlighting the effect of injection strategies on flow dynamics and relation with pressure spectra. DMD modes showed distinct dominant frequencies for each injection case, influencing lateral mass and momentum exchange within the cavity and affecting shock interactions. The findings underscore the significance of judiciously selecting injection positions, accounting for mixing efficiency, penetration height, and total pressure loss.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109741"},"PeriodicalIF":5.0,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703115","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}

引用次数: 0

Single-mode flutter analysis of drag reduction spike by parameterized eigenvalue method and energy method 用参数化特征值法和能量法对减阻尖峰进行单模扑动分析

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-14 DOI: 10.1016/j.ast.2024.109736

Chengde Huang , Xiangyan Chen , Xueyuan Nie , Guannan Zheng , Guowei Yang

{"title":"Single-mode flutter analysis of drag reduction spike by parameterized eigenvalue method and energy method","authors":"Chengde Huang , Xiangyan Chen , Xueyuan Nie , Guannan Zheng , Guowei Yang","doi":"10.1016/j.ast.2024.109736","DOIUrl":"10.1016/j.ast.2024.109736","url":null,"abstract":"<div><div>Attaching a spike to the blunt nose of a vehicle is one of the simplest ways to reduce drag in supersonic and hypersonic conditions. However, the spike can encounter aeroelastic instability which remains a challenging topic and limits applications in practical engineering. Computational fluid dynamics/computational structural dynamics coupling method is used and the results show the spike can experience flutter at low structural stiffness ratios and the flutter is dominated by a single mode. To evaluate the effects of structural parameters efficiently, this paper proposes a parameterized eigenvalue method by deriving the parameterized reduced structural equation which is coupled with an aerodynamic reduced order model. Results show both the critical flutter frequency and the critical natural frequency decrease with the increase of structural damping ratio and the flutter frequency is close to the natural frequency only for large mass ratios. It is found that the critical flutter frequency does not change with the mass ratio for zero structural damping, but this is not true for non-zero structural damping. This paper also proposes an energy method based on the work-energy principle and the aerodynamic frequency response function. The energy method can also obtain the critical flutter frequency and can explain how the structural parameters influence the flutter characteristics.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109736"},"PeriodicalIF":5.0,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703111","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}

引用次数: 0

Passive control of flow separation with blade-end slots for a three-stage compressor at different Reynolds numbers 在不同雷诺数条件下利用叶片末端槽对三级压缩机的气流分离进行被动控制

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-14 DOI: 10.1016/j.ast.2024.109742

Yangwei Liu , Pengli Zhang , Yumeng Tang , Xindi Wei , Jiashou Yang , Guofeng Ji

{"title":"Passive control of flow separation with blade-end slots for a three-stage compressor at different Reynolds numbers","authors":"Yangwei Liu , Pengli Zhang , Yumeng Tang , Xindi Wei , Jiashou Yang , Guofeng Ji","doi":"10.1016/j.ast.2024.109742","DOIUrl":"10.1016/j.ast.2024.109742","url":null,"abstract":"<div><div>The unmanned aerial vehicles (UAVs) operate at flight altitudes exceeding 20 kilometers, where the effect of low Reynolds number (<span><math><mtext>Re</mtext></math></span>) on the aero-engine of UAVs is significant. The blade-end slots technique is proved to be an effective method to control the corner separation flow in the blade end regions under conventional Reynolds number. To verify the effectiveness of this technique under low <span><math><mtext>Re</mtext></math></span> conditions, the blade-end slots technique is applied to a three-stage compressor under high flight altitude conditions. The control effect and mechanism of the blade-end slots under different <span><math><mtext>Re</mtext></math></span> are revealed to lay a foundation for the subsequent experiments of the three-stage compressor at low <span><math><mtext>Re</mtext></math></span> condition. Results show that the loss near the blade-end region under 20 km (low <span><math><mtext>Re</mtext></math></span>) condition is larger than that under 0 km (high <span><math><mtext>Re</mtext></math></span>) condition. The employment of the blade-end slots technique can significantly suppress the corner separation and widen the stall margin of the three-stage compressor without reducing the efficiency. The self-adaptive jet generated by blade-end slots effectively displaces low-momentum fluid near the suction surface and restricts its spanwise migration along the blade. Furthermore, the single blade-end slotted scheme for the third-stage stator and the combined blade-end slotted scheme for each stator can increase the stall margin by 3.52% and 6.81% under 20 km condition, respectively. These findings underscore the potential of blade-end slots as a control mechanism to optimize compressor performance under low <span><math><mtext>Re</mtext></math></span> conditions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109742"},"PeriodicalIF":5.0,"publicationDate":"2024-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703116","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}

引用次数: 0

Deep learning-based prediction of initiation jet momentum ratio in jet-induced oblique detonations 基于深度学习的射流诱发斜向爆轰中起爆射流动量比预测

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-13 DOI: 10.1016/j.ast.2024.109724

Yue Bao (鲍越), Ruofan Qiu (邱若凡), Jinhua Lou (楼锦华), Xin Han (韩信), Yancheng You (尤延铖)

{"title":"Deep learning-based prediction of initiation jet momentum ratio in jet-induced oblique detonations","authors":"Yue Bao (鲍越), Ruofan Qiu (邱若凡), Jinhua Lou (楼锦华), Xin Han (韩信), Yancheng You (尤延铖)","doi":"10.1016/j.ast.2024.109724","DOIUrl":"10.1016/j.ast.2024.109724","url":null,"abstract":"<div><div>Oblique detonation, with its attributes of self-ignition, rapid heat release, and high thermal cycle efficiency, has garnered significant attention. It is crucial to explore methods that actively control the detonation at a shorter distance under less compressive conditions, and wall jets for active control stands out. However, when the jet momentum ratio excessively exceeds the critical value, it not only leads to resource wastage but may also compromise the outlet thrust performance. Thus, this paper presents a novel deep learning-based method for predicting the jet momentum ratio to ensure detonation with a sufficient margin while minimizing its value across various flight conditions. Firstly, the proposed methodology utilizes a deep neural network (DNN) to classify detonation status under different operating conditions. Building upon the concept of incremental learning, knowledge acquired by the classification network is repurposed to identify the transition point between detonation initiation failure and success. To address potential initiation failure issues in practical applications when seeking the critical jet momentum ratio, we elevate the threshold for the probability of successful initiation, defining such the ratio as the \"robust jet momentum ratio\". The framework developed in this study enables rapid identification of the robust jet momentum ratio within 0.07 s. To improve the model's inadequate learning of the discontinuous features associated with initiation/initiation failure transitions, data augmentation techniques are employed. The improved model demonstrates efficient determination under two-dimensional variables of flight altitude and Mach number. This study addresses a key challenge in jet prediction by devising an adaptive strategy for tuning jet momentum ratios according to varying flight conditions. This work bears significant engineering application value in the realm of hypersonic propulsion technology.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109724"},"PeriodicalIF":5.0,"publicationDate":"2024-11-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142703107","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}

引用次数: 0