Aerospace最新文献_第6页

Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime 非线性状态下民用倾转旋翼复合材料机翼的虚拟全尺寸静态测试

Aerospace Pub Date : 2024-03-31 DOI: 10.3390/aerospace11040278

Antonio Chiariello, Gaetano Perillo, Mauro Linari, Raffaele Russo, S. Orlando, Pasquale Vitale, M. Belardo

{"title":"Virtual Full Scale Static Test of a Civil Tilt Rotor Composite Wing in Non-Linear Regime","authors":"Antonio Chiariello, Gaetano Perillo, Mauro Linari, Raffaele Russo, S. Orlando, Pasquale Vitale, M. Belardo","doi":"10.3390/aerospace11040278","DOIUrl":"https://doi.org/10.3390/aerospace11040278","url":null,"abstract":"This study addresses the crucial role of post-buckling behavior analysis in the structural design of composite aeronautical structures. Traditional engineering practices tend to result in oversized composite components, increasing structural weight. EASA AMC 20-29’s Building Block Approach suggests phased testing, but its time and cost challenges necessitate a shift to high-fidelity post-buckling analyses, exemplified by MSC NASTRAN SOL 400. This approach, showcased in the analysis of the Next Generation Civil Tilt Rotor Technology Demonstrator’s wing (NGTCTR-TD), effectively de-risks static tests, contributing to a more efficient certification process. The study demonstrates how advanced simulations provide detailed insights into local buckling phenomena, allowing precise stress distribution analysis. These analyses eliminate the risk of structural failure, paving the way for safer, more efficient, and cost-effective airframe structures. Future developments aim to validate numerical analyses with experimental data, further emphasizing the reliability and benefits of high-fidelity simulations.","PeriodicalId":505273,"journal":{"name":"Aerospace","volume":"97 8","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140360214","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

Multi-Electric Aero Engine Control and Hardware-in-the-Loop Verification with Starter Generator Coordination 多电航空发动机控制和硬件在环验证与起动发电机协调

Aerospace Pub Date : 2024-03-30 DOI: 10.3390/aerospace11040271

Jun Fang, Tianhong Zhang, Zhaohui Cen, Elias Tsoutsanis

{"title":"Multi-Electric Aero Engine Control and Hardware-in-the-Loop Verification with Starter Generator Coordination","authors":"Jun Fang, Tianhong Zhang, Zhaohui Cen, Elias Tsoutsanis","doi":"10.3390/aerospace11040271","DOIUrl":"https://doi.org/10.3390/aerospace11040271","url":null,"abstract":"The starter generator, characterized by controllable starting torque and disturbance in generator load torque, poses challenges for the multi-electric aero engine control. The key to addressing this issue lies in multi-electric aero engine control with the collaboration of a starter generator. Firstly, a multi-electric aero engine model is established, comprising a full-state turbofan engine model to enhance low-speed simulation capability and an external characteristic model of a starter generator to improve real-time simulation capability. Subsequently, the control methods for a multi-electric aero engine with starter generator coordination are proposed in three processes, including the starting process, acceleration/deceleration process, and steady-state process. During the starting process, the acceleration is controlled by coordinating the torque of the starter generator and the fuel of the aero engine. During the acceleration/deceleration process, the fuel limit value is adjusted based on the electrical load of the starter generator. During the steady-state process, the fuel is compensated based on the q-axis current of the starting generator in response to load torque disturbance. Finally, hardware-in-the-loop simulation experiments are conducted for the control of a multi-electric aero engine. The results show that the coordination reduces the oscillation of the acceleration during the startup of a multi-electric aero engine, enhancing its ability to resist disturbances from electrical load fluctuations during power generation.","PeriodicalId":505273,"journal":{"name":"Aerospace","volume":"25 10","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140361831","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

Wind Tunnel Investigation of Transient Propeller Loads for Non-Axial Inflow Conditions 非轴向内流条件下螺旋桨瞬态载荷的风洞研究

Aerospace Pub Date : 2024-03-30 DOI: 10.3390/aerospace11040274

Catharina Moreira, N. Herzog, Christian Breitsamter

{"title":"Wind Tunnel Investigation of Transient Propeller Loads for Non-Axial Inflow Conditions","authors":"Catharina Moreira, N. Herzog, Christian Breitsamter","doi":"10.3390/aerospace11040274","DOIUrl":"https://doi.org/10.3390/aerospace11040274","url":null,"abstract":"Recent developments in electrical Vertical Take-off and Landing (eVTOL) vehicles show the need for a better understanding of transient aero-mechanical propeller loads for non-axial inflow conditions. The variety of vehicle configurations conceptualized with different propellers in terms of blade geometry, number of blades, and their general integration concept results in aerodynamic loads on the propellers which are different from those on conventional fixed-wing aircraft propellers or helicopter rotors. Such varying aerodynamic loads have to be considered in the vehicle design as a whole and also in the detailed design of their respective electric propulsion systems. Therefore, an experimental approach is conducted on two different propeller blade geometries and a varying number of blades with the objective to explore the characteristics at non-axial inflow conditions. Experimental data are compared with calculated results of a low-fidelity Blade Element Momentum Theory (BEMT) approach. Average thrust and side force coefficients are shown to increase with inflow angle, and this trend is captured by the implemented numerical method. Measured thrust and in-plane forces are shown to oscillate at the blade passing frequency and its harmonics, with higher amplitudes at higher angles of inflow or lower number of blades.","PeriodicalId":505273,"journal":{"name":"Aerospace","volume":"52 19","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140361817","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

Investigations on Hot Air Anti-Icing Characteristics with Internal Jet-Induced Swirling Flow 内部喷射漩涡流热空气防结冰特性研究

Aerospace Pub Date : 2024-03-30 DOI: 10.3390/aerospace11040270

Yuyang Liu, Xian Yi

{"title":"Investigations on Hot Air Anti-Icing Characteristics with Internal Jet-Induced Swirling Flow","authors":"Yuyang Liu, Xian Yi","doi":"10.3390/aerospace11040270","DOIUrl":"https://doi.org/10.3390/aerospace11040270","url":null,"abstract":"The tangential jet-induced swirling flow is a highly efficient technology for enhancing heat transfer. This paper explores the application of swirling flow of an airfoil/aero-engine in a hot air anti-icing chamber, aiming to improve the anti-icing performance and achieve a more uniform temperature on the surface. A series of numerical computations adopting the SST k − ω turbulent model was carried out to obtain the internal flow and heat transfer characteristics, as well as the surface temperature distributions, considering water evaporation and solid heat conduction. Three jet arrangements, including impingement jets, offset jets, and swirl jets, were studied and compared, which evidently showed that the swirling effect was helpful to elevate the internal heat transfer. Compared to the impingement jets at the Reynolds number of 40,000, the Nusselt number with the offset jets is increased by 19.5%, while the corresponding Nusselt number of the swirl jets is augmented by 44.3%. The swirling flow significantly elevates the swirl number within the internal chamber, intensifying the vortex strength near the wall and increasing the circumferential velocity, which also results in an augmentation of internal pressure loss. By adopting the swirling internal flow, the temperature distribution on the anti-icing surface is more uniform and is increased by up to about 4.1 K in the leading edge when the internal-to-external temperature difference is 80 K. Simultaneously, the heat absorption of water evaporation and the matches between the internal heat transfer and external icing load are of particular importance to determine the anti-icing performance, and this has been discussed in this paper.","PeriodicalId":505273,"journal":{"name":"Aerospace","volume":"25 11","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140361830","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

A Review of Novel Heat Transfer Materials and Fluids for Aerospace Applications 航空航天应用中的新型传热材料和流体综述

Aerospace Pub Date : 2024-03-30 DOI: 10.3390/aerospace11040275

Glauco Nobrega, Beatriz Cardoso, Reinaldo Souza, José Pereira, Pedro Pontes, S. Catarino, Diana Pinho, Rui Lima, Ana Moita

{"title":"A Review of Novel Heat Transfer Materials and Fluids for Aerospace Applications","authors":"Glauco Nobrega, Beatriz Cardoso, Reinaldo Souza, José Pereira, Pedro Pontes, S. Catarino, Diana Pinho, Rui Lima, Ana Moita","doi":"10.3390/aerospace11040275","DOIUrl":"https://doi.org/10.3390/aerospace11040275","url":null,"abstract":"The issue of thermal control for space missions has been critical since the early space missions in the late 1950s. The demands in such environments are heightened, characterized by significant temperature variations and the need to manage substantial densities of heat. The current work offers a comprehensive survey of the innovative materials and thermal fluids employed in the aerospace technological area. In this scope, the materials should exhibit enhanced reliability for facing maintenance and raw materials scarcity. The improved thermophysical properties of the nanofluids increase the efficiency of the systems, allowing the mass/volume reduction in satellites, rovers, and spacecraft. Herein are summarized the main findings from a literature review of more than one hundred works on aerospace thermal management. In this sense, relevant issues in aerospace convection cooling were reported and discussed, using heat pipes and heat exchangers, and with heat transfer ability at high velocity, low pressure, and microgravity. Among the main findings, it could be highlighted the fact that these novel materials and fluids provide enhanced thermal conductivity, stability, and insulation, enhancing the heat transfer capability and preventing the malfunctioning, overheating, and degradation over time of the systems. The resulting indicators will contribute to strategic mapping knowledge and further competence. Also, this work will identify the main scientific and technological gaps and possible challenges for integrating the materials and fluids into existing systems and for maturation and large-scale feasibility for aerospace valorization and technology transfer enhancement.","PeriodicalId":505273,"journal":{"name":"Aerospace","volume":"24 26","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140364719","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

A Framework for Aircraft Conceptual Design and Multidisciplinary Optimization 飞机概念设计和多学科优化框架

Aerospace Pub Date : 2024-03-30 DOI: 10.3390/aerospace11040273

Saeed Hosseini, Mohammad Ali Vaziry-Zanjany, H. Ovesy

引用次数: 0

Design and Experimental Study of a Drilling Tool for Mars Rock Sampling 火星岩石取样钻探工具的设计与实验研究

Aerospace Pub Date : 2024-03-30 DOI: 10.3390/aerospace11040272

Yafang Liu, Lu Zhang, Ye Tian, Weiwei Zhang, Junyue Tang, Jiahang Zhang, Zhangqing Duan, Jie Ji

引用次数: 0

Flight Simulation of Fire-Fighting Aircraft Based on Multi-Factor Coupling Modeling of Forest Fire 基于林火多因素耦合建模的灭火飞机飞行模拟

Aerospace Pub Date : 2024-03-29 DOI: 10.3390/aerospace11040267

Hu Liu, Siliang Liu, Yongliang Tian

引用次数: 0

Precision Landing of Unmanned Aerial Vehicle under Wind Disturbance Using Derivative Sliding Mode Nonlinear Disturbance Observer-Based Control Method 利用基于衍生滑模非线性扰动观测器的控制方法实现风扰动下无人飞行器的精确着陆

Aerospace Pub Date : 2024-03-29 DOI: 10.3390/aerospace11040265

Sunghun Jung

{"title":"Precision Landing of Unmanned Aerial Vehicle under Wind Disturbance Using Derivative Sliding Mode Nonlinear Disturbance Observer-Based Control Method","authors":"Sunghun Jung","doi":"10.3390/aerospace11040265","DOIUrl":"https://doi.org/10.3390/aerospace11040265","url":null,"abstract":"Unmanned aerial vehicles (UAVs) are extensively employed in civilian and military applications because of their excellent maneuverability. Achieving fully autonomous quadrotor flight and precision landing on a wireless charging station in the presence of wind disturbance has become a crucial research topic. This paper presents a composite control technique for UAV altitude and attitude tracking in harsh environments, i.e., wind disturbance. A composite controller was developed based on nonlinear disturbance observer (NDOB) control theory to allow the UAV to land in the presence of random external wind disturbances and ground effects. The NDOB estimated the unknown wind disturbance, and the estimation was fed into the derivative sliding mode nonlinear disturbance observer-based control (DSMNDOBC), allowing the UAV to perform autonomous precision landing. Two loop designs were applied: the inner loop for stabilization and the outer loop for altitude tracking. The quadrotor model dynamics and the proposed controller, DSMNDOBC, were simulated employing MATLAB/Simulink®, and the results were compared with the one obtained by the proportional derivative (PD) controller and the sliding mode controller (SMC). The simulation results indicated that the DSMNDOBC has superior altitude and attitude control compared to the PD and SMC controllers and better disturbance estimation and attenuation performance.","PeriodicalId":505273,"journal":{"name":"Aerospace","volume":"20 10","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140368192","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

Invariant Kalman Filter Design for Securing Robust Performance of Magnetic–Inertial Integrated Navigation System under Measurement Uncertainty 在测量不确定性条件下确保磁惯性综合导航系统稳健性能的不变卡尔曼滤波器设计

Aerospace Pub Date : 2024-03-29 DOI: 10.3390/aerospace11040268

Taehoon Lee, Byungjin Lee, Sangkyung Sung

引用次数: 0