Aerospace Science and Technology最新文献_第6页

Trajectory tracking control of a morphing UAV using radial basis function artificial neural network based fast terminal sliding mode: Theory and experimental 使用基于径向基函数人工神经网络的快速终端滑动模式对变形无人机进行轨迹跟踪控制：理论与实验

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-08 DOI: 10.1016/j.ast.2024.109719

Saddam Hocine Derrouaoui , Yasser Bouzid , Aymen Doula , Mohamed Amine Boufroua , Amina Belmouhoub , Mohamed Guiatni , Aicha Hamissi

{"title":"Trajectory tracking control of a morphing UAV using radial basis function artificial neural network based fast terminal sliding mode: Theory and experimental","authors":"Saddam Hocine Derrouaoui , Yasser Bouzid , Aymen Doula , Mohamed Amine Boufroua , Amina Belmouhoub , Mohamed Guiatni , Aicha Hamissi","doi":"10.1016/j.ast.2024.109719","DOIUrl":"10.1016/j.ast.2024.109719","url":null,"abstract":"<div><div>Lately, Morphing Aerial Systems (MASs) have seen a surge in demand due to their exceptional maneuverability, flexibility, and agility in navigating complex environments. Unlike conventional drones, MASs boast the ability to adapt and alter their morphology during flight. However, managing the control and stability of these innovative and unconventional vehicles poses a significant challenge, particularly during the aerial transformation phases. To solve this problem, this manuscript proposes a Radial Basis Function Artificial Neural Network-Based Fast Terminal Sliding Mode Control (RBFANN-FTSMC) method. This approach is designed to effectively manage morphology changes, ensure precise trajectory tracking, and mitigate the impact of external disturbances and parameter uncertainties. Accordingly, the RBFANN-FTSMC will be evaluated against Proportional Integral Derivative (PID), Sliding Mode (SM), and Fast Terminal Sliding Mode (FTSM) controllers through two flight simulation scenarios to validate its effectiveness. Additionally, the control parameters will be optimized using a recent metaheuristic algorithm known as the Whale Optimization Algorithm (WOA). A novel hardware control diagram is explained. Finally, the ability to alter morphologies and the results of experimental tests are discussed to highlight the performance and limitations of the mechanical structure and the implemented RBFANN-FTSMC.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109719"},"PeriodicalIF":5.0,"publicationDate":"2024-11-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664218","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

Application of causal analysis based on systems theory (CAST) to regulatory decision-making: A case study of the Sikorsky S92A 基于系统理论的因果分析（CAST）在监管决策中的应用：西科斯基 S92A 的案例研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-08 DOI: 10.1016/j.ast.2024.109708

Clementino R. Veras Neto , Rodrigo L. Rose , John Thomas

{"title":"Application of causal analysis based on systems theory (CAST) to regulatory decision-making: A case study of the Sikorsky S92A","authors":"Clementino R. Veras Neto , Rodrigo L. Rose , John Thomas","doi":"10.1016/j.ast.2024.109708","DOIUrl":"10.1016/j.ast.2024.109708","url":null,"abstract":"<div><div>Ensuring aviation safety requires maintaining the integrity of product design and operations. The Federal Aviation Administration (FAA) regulates Transport Category rotorcraft design through 14 CFR Part 29, establishing Categories A and B of certification for multiengine rotorcraft, and requires aircraft to be operated according to the certified procedures in flight manuals. This paper presents a case study of the Sikorsky S92A, a Transport Category rotorcraft that is not certified for elevated helideck operations according to Part 29, but operates primarily in the offshore market through FAA-authorized exemptions from applicable regulation. To understand how this discrepancy between the aircraft's certification and operation came to be, a relatively new accident analysis methodology called Casual Analysis based on Systems Theory (CAST) is applied to a hypothetical accident involving an S92A, strongly based on a real incident described in a service difficulty report. The CAST results identify unsafe decisions on the part of flight crews, air operators, the aircraft manufacturer, and the FAA that contribute to the accident. We explain these contributions by identifying several systemic factors generalizable to the entire offshore rotorcraft industry that underlie unsafe decisions, and we propose a set of recommendations to address them.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109708"},"PeriodicalIF":5.0,"publicationDate":"2024-11-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702120","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

Thermal deformation monitoring of large-scale composite honeycomb spaceborne antennas with limited strain measurements 利用有限应变测量对大型复合蜂窝状机载天线进行热变形监测

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-07 DOI: 10.1016/j.ast.2024.109665

Tianxiang Huang, Shenfang Yuan, Jian Chen, Tianyu Dong, Wenpeng Duan

{"title":"Thermal deformation monitoring of large-scale composite honeycomb spaceborne antennas with limited strain measurements","authors":"Tianxiang Huang, Shenfang Yuan, Jian Chen, Tianyu Dong, Wenpeng Duan","doi":"10.1016/j.ast.2024.109665","DOIUrl":"10.1016/j.ast.2024.109665","url":null,"abstract":"<div><div>Shape reconstruction of spaceborne antennas is essential for calibrating phase signals and ensuring structural safety, particularly in large-scale composite honeycomb structures subjected to thermal load. The inverse finite element method (iFEM) has emerged as a promising technique for shape reconstruction using surface-measured strains. However, due to the dense coverage of transmit/receive modules on one side of the structure and weight constraints, only a limited number of sensors can be attached to the surface without payloads. To overcome this limitation, this paper proposes a strain surrogate model-based inverse finite element method (SSM-iFEM) for real-time shape reconstruction using limited strain measurements from a single surface of the structure. The strain surrogate model employs a parallel multilayer perceptron (PMLP) neural network to establish the relationship between sparse strain measurements and strains on both surfaces. The PMLP consists of six parallel branches corresponding to the strain components in three directions on both surfaces. Furthermore, the displacement-curvature-strain relation is utilized for strain sample construction. In the iFEM formulation, an integral error function is applied to enhance the robustness of the algorithm. The proposed SSM-iFEM and strain sample construction method are validated using a numerical model of a large-scale composite structure under thermal load. Finally, the proposed method is applied to monitor the shape of the large-scale composite honeycomb structure during heating and cooling processes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109665"},"PeriodicalIF":5.0,"publicationDate":"2024-11-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702121","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

Robust control of Chat-PM: A switched singular system with mode-dependent bounded nonlinearity Chat-PM 的鲁棒控制：具有模式相关有界非线性的开关奇异系统

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-07 DOI: 10.1016/j.ast.2024.109718

Chengzhe Han, Lixian Zhang, Yihang Ding, Yifei Dong, Yimin Zhu, Tong Wu, Jianan Yang

{"title":"Robust control of Chat-PM: A switched singular system with mode-dependent bounded nonlinearity","authors":"Chengzhe Han, Lixian Zhang, Yihang Ding, Yifei Dong, Yimin Zhu, Tong Wu, Jianan Yang","doi":"10.1016/j.ast.2024.109718","DOIUrl":"10.1016/j.ast.2024.109718","url":null,"abstract":"<div><div>This paper is concerned with the robust control of the composite hybrid aerial-terrestrial precise manipulator (Chat-PM), a quadrotor-based robot with aerial/terrestrial movement and payload transportation capabilities. Given the distinct dynamics between aerial and terrestrial locomotion modes, Chat-PM is modeled as a type of switched singular system. A nonlinear term is contained in the system to model the coupling between translational and rotational movements of Chat-PM, which is proven to be norm-bounded and mode-dependent. Besides, the estimation error of the robotic arm's interaction force/torque is treated as the disturbance of the system. By means of the mixed <span><math><msub><mrow><mi>H</mi></mrow><mrow><mn>2</mn></mrow></msub></math></span>/<span><math><msub><mrow><mi>H</mi></mrow><mrow><mo>∞</mo></mrow></msub></math></span> approach, numerically testable stability criteria are obtained, based on which the existence conditions for controllers with satisfactory transient and disturbance attenuation performance are provided. Compared to traditional studies assuming the nonlinearity term to be mode-independent, the conservatism in the controller design is reduced. Experimental results are provided to demonstrate the effectiveness of the proposed approach.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109718"},"PeriodicalIF":5.0,"publicationDate":"2024-11-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664217","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

Unsteady aerodynamic modeling and flight trajectory simulation of dual-spin projectile based on DNN and transfer-learning 基于 DNN 和迁移学习的双旋弹丸非稳态气动建模和飞行轨迹仿真

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-06 DOI: 10.1016/j.ast.2024.109711

Wen Ji , Chunlin Gong , Xuyi Jia , Chunna Li , Gang Wang

{"title":"Unsteady aerodynamic modeling and flight trajectory simulation of dual-spin projectile based on DNN and transfer-learning","authors":"Wen Ji , Chunlin Gong , Xuyi Jia , Chunna Li , Gang Wang","doi":"10.1016/j.ast.2024.109711","DOIUrl":"10.1016/j.ast.2024.109711","url":null,"abstract":"<div><div>To evaluate flight performance and aerodynamic characteristics of a dual-spin projectile, the coupled computational fluid dynamics and rigid body dynamics (CFD/RBD) method is commonly used, which can simultaneously solve the flight mechanics and flow field. However, the efficiency is compromised by the large number of CFD calculations required. This paper develops an unsteady aerodynamic modeling method that combines deep neural networks and transfer learning, which can accurately predict unsteady aerodynamics of dual-spin projectiles under varying initial conditions. Considering the influence of flight state and aerodynamic data from short-term historical moments, we integrate them as input features of the aerodynamic model to reduce the impact of long-term historical data. To enhance the model generalization under varying initial conditions, we fine-tune the built aerodynamic model using small amounts of data under new conditions by transfer learning. The proposed method is validated through interpolated and extrapolated prediction cases, respectively. The results indicate that the proposed method can achieve better accuracy and generalizability than long short-term memory neural networks and autoregressive moving average method in unsteady aerodynamic modeling of the dual-spin projectile. By coupling the flight dynamics equations with the aerodynamic model in the time domain, the flight simulation only takes a few seconds, which can reduce computing time by three orders of magnitude compared to the coupled CFD/RBD method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109711"},"PeriodicalIF":5.0,"publicationDate":"2024-11-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664238","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

Investigation of the aerodynamic performance of the dragonfly-inspired tandem wings considering the coupling between the stroke plane and phase difference 考虑冲程平面与相位差耦合的蜻蜓启发式串联翼气动性能研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-06 DOI: 10.1016/j.ast.2024.109717

Xiaojun Yang , Yang Luo , Xinyu Lang , Wei Wang

{"title":"Investigation of the aerodynamic performance of the dragonfly-inspired tandem wings considering the coupling between the stroke plane and phase difference","authors":"Xiaojun Yang , Yang Luo , Xinyu Lang , Wei Wang","doi":"10.1016/j.ast.2024.109717","DOIUrl":"10.1016/j.ast.2024.109717","url":null,"abstract":"<div><div>The dragonfly's tandem wings can make full use of the interference of various spatial vortices to obtain efficient flight capability. The complex coupling among multiple motion parameters will have an important influence on the interference between the forewing (FW) and hindwing (HW). In this paper, the aerodynamic performance of the dragonfly-inspired tandem wings is analyzed using the Computational Fluid Dynamics (CFD) method considering the coupling effect of the stroke plane and phase difference. The variation of the force coefficient, vortex structure and aerodynamic efficiency of the tandem wings in forward flight are analyzed, respectively. The results show that the stroke plane angle affects the distribution of the leading edge vortex (LEV) and trailing edge vortex (TEV), which primarily controls the trend of horizontal force variation. The phase difference of tandem wings will change the fluctuation of the horizontal force coefficient curve by affecting the meeting time of the forewing and hindwing. However, with the increase of stroke plane angle, the fluctuation of aerodynamic coefficient caused by phase difference will decrease. The propulsion efficiency(<em>η</em>) and power loading(<em>PL</em>) can be improved through increasing the stroke plane angle and selecting a reasonable phase difference. The conclusion can provide theoretical guidance for the design of the dragonfly-inspired tandem flapping wing aircraft (DTFWA) and the choice of motion parameters.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109717"},"PeriodicalIF":5.0,"publicationDate":"2024-11-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664235","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 local concave non-axisymmetric endwall profiling on endwall secondary flows of a highly-loaded turbine cascade 局部凹面非轴对称端壁剖面对高负荷涡轮级联端壁二次流的影响

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-05 DOI: 10.1016/j.ast.2024.109716

Zhiyuan Cao, Xinyu Hao, Xi Gao, Wei Guo

{"title":"Effect of local concave non-axisymmetric endwall profiling on endwall secondary flows of a highly-loaded turbine cascade","authors":"Zhiyuan Cao, Xinyu Hao, Xi Gao, Wei Guo","doi":"10.1016/j.ast.2024.109716","DOIUrl":"10.1016/j.ast.2024.109716","url":null,"abstract":"<div><div>Non-axisymmetric endwall profiling (NAEP) has been widely utilized in reducing secondary flow loss of turbines. However, most of NAEP are designed for the endwall of the entire blade passage, which presents challenges to the design of cooling structures of turbine endwall. This study aims to explore the local concave non-axisymmetric endwall profiling (LCNP) method with the same effect as whole passage NAEP, and reveal the influence mechanism of LCNP on endwall secondary flow structures of a highly-loaded turbine cascade. Under the condition that the maximum depth of LCNP is unchanged, the axial length effect and pitchwise location effect of LCNP are studied, the influence mechanism of LCNP on the secondary flow loss is analyzed, and the genetic algorithm is utilized to optimize LCNP at the optimal position. Results show that as the axial length of the LCNP increases and the pitchwise location gets closer to the suction surface, the intensity and range of the passage vortex are decreased, and the total pressure loss coefficient (loss coefficient) of the turbine cascade is decreased. When LCNP is 100% axial chord in length and at the position of 2/9 pitch, the loss coefficient is reduced by 5.49%. LCNP was optimized at the optimal position, and the optimal LCNP reduced the loss coefficient of the turbine cascade by 6.73%. After the local concave endwall profiling, the loading in the middle of the endwall of the turbine cascade is reduced, and the intensity of the passage vortex is effectively inhibited, which is the mechanism that the loss coefficient of the turbine cascade is reduced. However, after the local concave endwall profiling, the loading in the trailing of the endwall of the turbine cascade is increased, the transverse migration of the new boundary layer in the endwall is accelerated, and the loss coefficient of the near endwall is increased.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109716"},"PeriodicalIF":5.0,"publicationDate":"2024-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664236","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

Numerical research on flow field structure and droplets distribution of kerosene-fueled rotating detonation ramjet engine 煤油燃料旋转爆破冲压式喷气发动机流场结构和液滴分布的数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-05 DOI: 10.1016/j.ast.2024.109713

Zheng Yushan, Liu Yu, Wang Chao, Wang Yitian

{"title":"Numerical research on flow field structure and droplets distribution of kerosene-fueled rotating detonation ramjet engine","authors":"Zheng Yushan, Liu Yu, Wang Chao, Wang Yitian","doi":"10.1016/j.ast.2024.109713","DOIUrl":"10.1016/j.ast.2024.109713","url":null,"abstract":"<div><div>In order to reveal the multiphase flow field structure and fuel droplets distribution under rotating detonation ramjet engine fueled by liquid kerosene, non-premixed simulations coupled with an Euler-Lagrangian approach is adopted. Supersonic air is used as oxidizer and the total pressure and total temperature at the entrance of isolation are set as 1.2 MPa and 1100 K, respectively, with a Mach number of 1.9. It is shown that a single-wave is formed and typical rotating detonation wave structures are established under two different orifice spacing conditions, namely 2 mm and 6mm. A \"rich oil and poor oxygen band\" is formed and attributed to the inconsistent supply of fuel and air after the passage of the detonation wave. When the orifices spacing is increased from 2 mm to 6 mm, both obvious strips after the detonation wave and “<strong><em>n</em></strong>-type” deflagration structures near the contact surface are observed. Besides, the detonation wave front becomes discontinuous, as well as from the deflagration heat release distribution. Despite of the effect of the circumferential propagation of detonation wave, kerosene droplets still propagate mainly along the downstream direction. However, Kerosene droplets distribution shows obvious difference along the detonation wave propagation direction.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109713"},"PeriodicalIF":5.0,"publicationDate":"2024-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664181","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 vibration characteristics and damage detection method of blade with breathing fatigue crack 带呼吸疲劳裂纹叶片的非线性振动特性和损伤检测方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-04 DOI: 10.1016/j.ast.2024.109715

Yue Liu , Weifeng Long , Yugang Chen , Haifeng Hu

{"title":"Nonlinear vibration characteristics and damage detection method of blade with breathing fatigue crack","authors":"Yue Liu , Weifeng Long , Yugang Chen , Haifeng Hu","doi":"10.1016/j.ast.2024.109715","DOIUrl":"10.1016/j.ast.2024.109715","url":null,"abstract":"<div><div>In aero-engine, blades operate under harsh conditions for extended periods, which makes them highly susceptible to fatigue cracks. The localized and nonlinear structural changes caused by blade crack lead to complex vibration characteristics that are not well understood, posing challenges to the identification of these cracks. This paper proposes an approach for identifying breathing fatigue crack in compressor blade, leveraging the nonlinear features induced by the cracks. Crucial sensitive characteristics are extracted and a crack indicator for accurate crack detection is defined. Initially addressing the typical morphology of fatigue breathing cracks, a dynamic model of blade with cracks is developed to analyze their impact on the natural frequencies. Nonlinear contact forces are introduced to characterize the \"breathing\" effect of the fatigue crack, allowing for the determination of the harmonic distribution patterns in the blade's vibration response under various excitation conditions. A finite element model is then established considering the crack morphology, by adopting the contact element. Based on that, the nonlinear response characteristics associated with the blade's primary, sub-harmonic, and super-harmonic resonances are explored. A crack-sensitive parameter is defined and extracted from the nonlinear responses, under different crack propagation stages. At last, effectiveness and reliability of the defined parameter for identifying cracks is validated through a vibration fatigue test.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109715"},"PeriodicalIF":5.0,"publicationDate":"2024-11-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664179","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

Effects of additional transmission chamber on flow dynamics of a pulsed jet in crossflow 附加传输室对横流脉冲射流流动动力学的影响

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-02 DOI: 10.1016/j.ast.2024.109712

Weimei Quan, Wenjing Sun, Jingzhou Zhang, Xiaoming Tan, Yuanhao Li

引用次数: 0