Aerospace America最新文献_第9页

On the Potentials of the Integration of Pressure Gain Combustion with a Hybrid Electric Propulsion System 压力增益燃烧与混合动力推进系统集成的潜力

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-15 DOI: 10.3390/aerospace10080710

Dong-Seop Kim, M. Asli, K. Höschler

{"title":"On the Potentials of the Integration of Pressure Gain Combustion with a Hybrid Electric Propulsion System","authors":"Dong-Seop Kim, M. Asli, K. Höschler","doi":"10.3390/aerospace10080710","DOIUrl":"https://doi.org/10.3390/aerospace10080710","url":null,"abstract":"As the issue of pollutant emissions from aviation propulsion escalates, research into alternative powertrains is gaining momentum. Two promising technologies are the Hybrid Electric Propulsion System (HEPS) and Pressure Gain Combustion (PGC). HEPS is expected to reduce pollutant emissions by decreasing fuel consumption, whereas PGC uses detonation in the combustor to increase the thermal efficiency of engines by elevating the total pressure during combustion. This study extensively explores the integration of these two emerging technologies, thoroughly assessing the advantages that arise from their combination. First, the renowned turboprop engine PW127 is benchmarked and modeled using Gasturb software. The model is integrated into Simulink using the T-MATS tool, with HEPS and pressure gain components added to analyze the thermodynamics of various configurations under different pressure gain values and HEPS parameters. The analysis, conducted up to the cruise phase of the baseline aircraft, reveals that applying pressure gain combustion through Rotating Detonation Combustion (RDC) results in a more significant increase in efficiency and decrease in fuel consumption compared to HEPS with conventional gas turbines. However, HEPS helps maintain a more uniform combustor inlet condition and reduces the Turbine Inlet Temperature (TIT) at the takeoff phase, where the highest TIT otherwise occurs. The results suggest that integrating HEPS with PGC can be beneficial in maintaining optimal combustor conditions and mitigating turbine efficiency degradation.","PeriodicalId":50845,"journal":{"name":"Aerospace America","volume":"5 1","pages":""},"PeriodicalIF":0.1,"publicationDate":"2023-08-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82469796","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

Research on Unmanned Aerial Vehicle Cluster Collaborative Countermeasures Based on Dynamic Non-Zero-Sum Game under Asymmetric and Uncertain Information 信息不对称不确定下基于动态非零和博弈的无人机集群协同对策研究

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-15 DOI: 10.3390/aerospace10080711

Pengcheng Wu, Hongqiao Wang, Gaowei Liang, Peng Zhang

引用次数: 0

Influence of Variable-Geometry Adjustment on the Matching Characteristics of a Medium Variable Bypass Ratio Compression System 变几何调整对介质变涵道比压缩系统匹配特性的影响

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-14 DOI: 10.3390/aerospace10080707

Qiaodan Luo, Shengfeng Zhao, Shiji Zhou, Huafeng Xu, X.Q. Sheng

{"title":"Influence of Variable-Geometry Adjustment on the Matching Characteristics of a Medium Variable Bypass Ratio Compression System","authors":"Qiaodan Luo, Shengfeng Zhao, Shiji Zhou, Huafeng Xu, X.Q. Sheng","doi":"10.3390/aerospace10080707","DOIUrl":"https://doi.org/10.3390/aerospace10080707","url":null,"abstract":"The research is based on a full 3D model of a medium variable bypass ratio compression system. The effects of core-driven fan stage (CDFS) VIGV adjustment and forward variable area bypass injector (FVABI) adjustment on the internal flow and component matching characteristics of the compression system during the mode transition process are investigated. The findings of the study reveal that during the mode transition period, the adjustment of variable-geometry components has a negligible impact on the aerodynamic performance of the fan. The closure of the CDFS VIGV has a significant effect on reducing the pressure ratio of the CDFS but only a minor effect on its efficiency. Additionally, the efficiency and pressure ratio of the high-pressure compressor (HPC) increase with the closure of the CDFS VIGV, particularly the second stage of the HPC. When the CDFS VIGV is closed by 30°, the efficiency of the second stage of the HPC increases by 3.4%, while that of the first stage only increases by 3.1%. Under the high bypass mode, increasing the FVABI opening will move the matching point of the CDFS towards the choke boundary. When the FVABI opening increases from 0.30 to 0.58, the efficiency of the CDFS decreases by 3.6%, while the efficiency of the HPC only increases by 0.4%. In summary, closing the CDFS VIGV and increasing the opening of the FVABI will increase the bypass ratio of the compression system, and the former has a more significant impact. When the compression system transitions from the low bypass mode to the high bypass mode, opening of the FVABI should be appropriately reduced to prevent CDFS matching in the operating condition too closely to the choke boundary, thereby maintaining the efficiency of each component of the compression system at a relatively high level.","PeriodicalId":50845,"journal":{"name":"Aerospace America","volume":"1 1","pages":""},"PeriodicalIF":0.1,"publicationDate":"2023-08-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90367746","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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 Study on the Ignition Characteristics of Scramjet Combustor with Tandem Cavities Using Micro-Pulse Detonation Engine 基于微脉冲爆震发动机的串联式超燃冲压发动机燃烧室点火特性实验研究

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-11 DOI: 10.3390/aerospace10080706

Min-Su Kim, In-Hoi Koo, Keon-Hyeong Lee, E. Lee, Hyung-seok Han, Seungmin Jeong, Ho-Chung Kim, Jeong-Yeol Choi

{"title":"Experimental Study on the Ignition Characteristics of Scramjet Combustor with Tandem Cavities Using Micro-Pulse Detonation Engine","authors":"Min-Su Kim, In-Hoi Koo, Keon-Hyeong Lee, E. Lee, Hyung-seok Han, Seungmin Jeong, Ho-Chung Kim, Jeong-Yeol Choi","doi":"10.3390/aerospace10080706","DOIUrl":"https://doi.org/10.3390/aerospace10080706","url":null,"abstract":"This experimental investigation focused on the ignition and combustion characteristics of a tandem cavity-based scramjet combustor with side-by-side identical cavities. This study utilized the Pusan National University-direct connect scramjet combustor (PNU-DCSC), which was capable of simulating flight conditions at Mach number 4.0–5.0 and altitudes of 20–25 km using the vitiated air heater (VAH). The combustion tests were conducted under off-design point conditions corresponding to low inlet enthalpy. It is a condition in which self-ignition does not occur, and a micro pulse detonation engine (μPDE) ignitor is used. The results revealed that as the injection pressure of the gaseous hydrogen fuel (GH2) and the corresponding equivalence ratio increased, the combustion mode transitioned from the cavity-shear layer flame to the jet-wake flame. Furthermore, the measured wall static pressure profiles along the isolator and scramjet combustor indicated that the region of elevated pressure distribution caused by the shock train expanded upstream with higher equivalence ratios. When ignited from the secondary cavity, the combustion area did not extend to the primary cavity at lower equivalence ratios, while it expanded upstream faster with higher equivalence ratios. Therefore, the combustion characteristics of the tandem cavity were found to vary based on the overall equivalence ratio of the main fuel (GH2) and ignition position.","PeriodicalId":50845,"journal":{"name":"Aerospace America","volume":"2 4 1","pages":""},"PeriodicalIF":0.1,"publicationDate":"2023-08-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83667794","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

Trajectory Optimization for the Nonholonomic Space Rover in Cluttered Environments Using Safe Convex Corridors 基于安全凸通道的非完整漫游车在混乱环境下的轨迹优化

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-11 DOI: 10.3390/aerospace10080705

Yiqun Li, Shaoqiang Liang, Jiahui Gao, Zong Chen, Siyuan Qiao, Zhoupin Yin

{"title":"Trajectory Optimization for the Nonholonomic Space Rover in Cluttered Environments Using Safe Convex Corridors","authors":"Yiqun Li, Shaoqiang Liang, Jiahui Gao, Zong Chen, Siyuan Qiao, Zhoupin Yin","doi":"10.3390/aerospace10080705","DOIUrl":"https://doi.org/10.3390/aerospace10080705","url":null,"abstract":"Due to the limitation of space rover onboard computing resources and energy, there is an urgent need for high-quality drive trajectories in complex environments, which can be provided by delicately designed motion optimization methods. The nonconvexity of the collision avoidance constraints poses a significant challenge to the optimization-based motion planning of nonholonomic vehicles, especially in unstructured cluttered environments. In this paper, a novel obstacle decomposition approach, which swiftly decomposes nonconvex obstacles into their constituent convex substructures while concurrently minimizing the proliferation of resultant subobstacles, is proposed. A safe convex corridor construction method is introduced to formulate the collision avoidance constraints. The numerical approximation methods are applied to transfer the resulting continuous motion optimization problem to a nonlinear programming problem (NLP). Simulation experiments are conducted to illustrate the feasibility and superiority of the proposed methods over the rectangle safe corridor method and the area method.","PeriodicalId":50845,"journal":{"name":"Aerospace America","volume":"123 1","pages":""},"PeriodicalIF":0.1,"publicationDate":"2023-08-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83715970","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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: 1

Modeling Airport Choice Using a Latent Class Logit Model 使用潜在类Logit模型建模机场选择

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-10 DOI: 10.3390/aerospace10080703

L. dell’Olio, Andrés Rodríguez, S. Sipone

引用次数: 0

Passive Damping of Solar Array Vibrations Using Hyperelastic Shape Memory Alloy with Multilayered Viscous Lamina 多层粘层超弹性形状记忆合金对太阳能电池阵振动的被动阻尼

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-10 DOI: 10.3390/aerospace10080704

Jae-Hyeon Park, Sung-Woo Park, Jong-Pil Kim, Hyun-Ung Oh

引用次数: 0

Study on Aerodynamic Design of the Front Auxiliary Inlet 前辅助进气道气动设计研究

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-09 DOI: 10.3390/aerospace10080700

Junyao Zhang, H. Zhan, Bai-gang Mi

{"title":"Study on Aerodynamic Design of the Front Auxiliary Inlet","authors":"Junyao Zhang, H. Zhan, Bai-gang Mi","doi":"10.3390/aerospace10080700","DOIUrl":"https://doi.org/10.3390/aerospace10080700","url":null,"abstract":"Submerged inlets have been widely used in advanced aircraft due to their excellent stealth characteristics, but they also suffer from poor aerodynamic performance. To improve the aerodynamic efficiency while maintaining stealth capabilities, this paper proposes a design scheme for a front auxiliary inlet with an inlet grille. The front auxiliary inlet is connected to the main inlet to form a composite inlet system. The low-energy upstream airflow that accumulates at the inlet is guided by the front auxiliary inlet to flow into the mainstream, resulting in a stable and high-quality airflow. A certain type of cruise missile was used as the research subject, and intake systems with and without front auxiliary inlets were constructed to compare the inlet performance of the two configurations using the CFD method. Additionally, a sensitivity analysis of the main design parameters of the front auxiliary inlet was carried out. The study reveals that a reasonable design of the front auxiliary inlet can prevent low-energy airflow, which accumulates on the missile body surface, from directly entering the inlet. Moreover, the front auxiliary inlet can inject additional mechanical energy into the low-energy airflow, inhibit airflow separation, and improve the uniformity of the flow field. Under cruise conditions, the total pressure recovery coefficient of the front auxiliary inlet configuration increased by 12.39% compared to the model without a front auxiliary inlet configuration. Furthermore, the total pressure distortion index was reduced by 47.24%.","PeriodicalId":50845,"journal":{"name":"Aerospace America","volume":"58 1","pages":""},"PeriodicalIF":0.1,"publicationDate":"2023-08-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89144921","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

Recent Developments in the Aerodynamic Heat Transfer and Cooling Technology of Gas Turbines Endwalls 燃气轮机端壁气动传热与冷却技术的最新进展

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-09 DOI: 10.3390/aerospace10080702

Rongdi Zhang, Peng Liu, Xirui Zhang, Wen-xiong Xi, Jian Liu

引用次数: 0

Experimental Investigation of Helicopter Noise While Approaching an Elevated Helipad 直升机接近高架停机坪时噪声的实验研究

IF 0.1 4区工程技术

Aerospace America Pub Date : 2023-08-09 DOI: 10.3390/aerospace10080701

G. Gibertini, Silvano Rezzonico, Marco Rossetti, A. Zanotti

{"title":"Experimental Investigation of Helicopter Noise While Approaching an Elevated Helipad","authors":"G. Gibertini, Silvano Rezzonico, Marco Rossetti, A. Zanotti","doi":"10.3390/aerospace10080701","DOIUrl":"https://doi.org/10.3390/aerospace10080701","url":null,"abstract":"The present paper describes a test campaign performed to investigate the noise footprint emitted by a helicopter in an idealised urban context, reproducing the approach to an elevated helipad. The test campaign was performed in Politecnico di Milano’s anechoic chamber and was finalised to investigate the effects produced only by helicopter noise. The set up consisted of a two-blade main rotor helicopter model and an aluminium rectangular prism model reproducing the landing building. Ground observer perceptions were recorded by means of a surface microphone and a realistic landing trajectory was approximated as a succession of fixed point measurements. Collected data were analysed through acoustic spectra and sound maps. Spectra were used to comprehend physical phenomena, such as reflection, diffraction and shielding, and to analyse the different contributions of helicopter noise. A sound map analysis enabled us to obtain a global perspective of the involved phenomena and to understand th extent to which people close to a building are stressed by a helicopter approaching an elevated urban helipad. Moreover, the experimental database, obtained over a free geometry, can be considered a useful tool for the validation of aeroacoustic solvers with different levels of fidelity.","PeriodicalId":50845,"journal":{"name":"Aerospace America","volume":"4 1","pages":""},"PeriodicalIF":0.1,"publicationDate":"2023-08-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73304207","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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