Aerospace Systems最新文献_第3页

Distributed information fusion based trajectory tracking for USV and UAV clusters via multi-agent deep learning approach 通过多代理深度学习方法为 USV 和 UAV 集群进行基于分布式信息融合的轨迹跟踪

Aerospace Systems Pub Date : 2024-02-23 DOI: 10.1007/s42401-024-00275-4

Hongzhi Wu, Miao wang, Jingshi Wang, Guoqing wang

{"title":"Distributed information fusion based trajectory tracking for USV and UAV clusters via multi-agent deep learning approach","authors":"Hongzhi Wu, Miao wang, Jingshi Wang, Guoqing wang","doi":"10.1007/s42401-024-00275-4","DOIUrl":"10.1007/s42401-024-00275-4","url":null,"abstract":"<div><p>Considering the complexities of the modern maritime operational environment and aiming for effective safe navigation and communication maintenance, research into the collaborative trajectory tracking problem of unmanned surface vehicles (USVs) and unmanned aerial vehicles (UAVs) clusters during patrol and target tracking missions holds paramount significance. This paper proposes a multi-agent deep reinforcement learning (MADRL) approach, specifically the action-constrained multi-agent deep deterministic policy gradient (MADDPG), to efficiently solve the collaborative maritime-aerial distributed information fusion-based trajectory tracking problem. The proposed approach incorporates a constraint model based on the characteristics of maritime-aerial distributed information fusion mode and two designed reward functions—one global for target tracking and one local for cross-domain collaborative unmanned clusters. Simulation experiments under three different mission scenarios have been conducted, and results demonstrate that the proposed approach possesses excellent applicability to trajectory tracking tasks in collaborative maritime-aerial settings, exhibiting strong convergence and robustness in mobile target tracking. In a complex three-dimensional simulation environment, the improved algorithm demonstrated an 11.04% reduction in training time for convergence and an 8.03% increase in reward values compared to the original algorithm. This indicates that the introduction of attention mechanisms and the design of reward functions enable the algorithm to learn optimal strategies more quickly and effectively.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140435266","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-objective optimization design of labyrinth seal of shrouded stator cavity in a low-speed research compressor 低速研究型压缩机定子腔迷宫密封的多目标优化设计

Aerospace Systems Pub Date : 2024-02-23 DOI: 10.1007/s42401-024-00271-8

Biaojie Zheng, Runzhu Shao, Zhuanyun Yan, Lin Fan, Jinfang Teng, Mingmin Zhu, Xiaoqing Qiang

{"title":"Multi-objective optimization design of labyrinth seal of shrouded stator cavity in a low-speed research compressor","authors":"Biaojie Zheng, Runzhu Shao, Zhuanyun Yan, Lin Fan, Jinfang Teng, Mingmin Zhu, Xiaoqing Qiang","doi":"10.1007/s42401-024-00271-8","DOIUrl":"10.1007/s42401-024-00271-8","url":null,"abstract":"<div><p>The shrouded stator is widely used in aero-engines and the leakage flow from the cavity has a strong effect on the performance of the stator. Due to the high degree of geometric freedom of the tooth shape, it is difficult to find the optimal geometry directly through a large number of sample calculations. In this research, a multi-objective optimization design method was used for the structure of labyrinth seal teeth and the optimal shape was found. The effect of the optimal seal teeth on the stator was analyzed in a low-speed research compressor. It is found that two different optimized shapes of seal teeth meet the optimization requirements. There is a significant difference in the cavity depth, but they have similar intervals and angles of inclination of seal teeth. The total pressure loss coefficient below 20% span decreases by 9.18% and the outlet static pressure coefficient below 20% span increases by 1.76%. For both optimal results, the leakage flow becomes closer to the pressure side of the stator. The leakage flow climbs in the radial direction in the rear of the passage. The vortex near the suction side disappears. Instead, two vortexes with opposite rotating directions exist in the passage. The range of the vortex in the radial direction expands.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140437466","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

An introduction to electric thruster modeling for stratospheric airship 平流层飞艇电动推进器建模简介

Aerospace Systems Pub Date : 2024-02-16 DOI: 10.1007/s42401-024-00272-7

Pingfang Zhou, Qiming Lin, Yuhao Jing

{"title":"An introduction to electric thruster modeling for stratospheric airship","authors":"Pingfang Zhou, Qiming Lin, Yuhao Jing","doi":"10.1007/s42401-024-00272-7","DOIUrl":"10.1007/s42401-024-00272-7","url":null,"abstract":"<div><p>The stratospheric airship uses the electric thrusters composed of motors and large diameter propellers to generate the forward thrust and heading manipulation torque. As the actuators of flight control, electric thrusters have an important impact on the station-keeping and flight-control performance. Due to the high-altitude environment and low-speed flight of big volumetric stratospheric airships, the operating of electric thrusters is significantly different from that of electric aircraft, which makes the analysis and modeling of electric thrusters difficult. In this paper, the characteristics of motors and propellers for stratospheric airship is analyzed at first. Then, the propeller and motor model expressions are summarized respectively, mainly concentrating on the relationship between torque, thrust, advance speed and rotational speed. Benefited from the methods in the field of marine propellers, a quantitative characterization method for the interaction between propeller and airship hull is introduced. Through the mechanical motion equation of the motor, the dynamic matching model between the motor output electromagnetic torque and the propeller load torque is described. An example is used to illustrate the modeling process. Finally, some of the challenging issues in engineering practice are discussed.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139961510","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

Review on guidance and control of aerospace vehicles: recent progress and prospect 航空航天飞行器制导与控制回顾：最新进展与前景

Aerospace Systems Pub Date : 2024-02-15 DOI: 10.1007/s42401-024-00273-6

Zian Wang, Pengcheng Cai, Zheng Gong, Chengxi Zhang, Shunyi Zhao, Jin Wu, Peng Dong

引用次数: 0

Finite state machine and ultrasonic ranging-based approach for automatic grasping by aerial manipulator 基于有限状态机和超声波测距的空中机械手自动抓取方法

Aerospace Systems Pub Date : 2024-01-13 DOI: 10.1007/s42401-023-00264-z

Dingcheng Pu, Xiangming Dun, Zhongliang Jing

引用次数: 0

Hysteresis of oscillatory airflow in a supersonic intake model 超音速进气模型中振荡气流的滞后现象

Aerospace Systems Pub Date : 2024-01-13 DOI: 10.1007/s42401-023-00268-9

Alexander Kuzmin

引用次数: 0

Finite-time error convergent trajectory generation with field-of-view and angle constraints 有限时间误差收敛轨迹生成，带视场和角度约束

Aerospace Systems Pub Date : 2024-01-12 DOI: 10.1007/s42401-023-00269-8

Ye Chen, Shufan Wu, Xiaoliang Wang, Di Zhang, Jun Jia, Quan Li

引用次数: 0

Determining the applicability limits of different accuracy models when analyzing the loads on the landing gear during landing 在分析着陆时起落架上的载荷时，确定不同精度模型的适用极限

Aerospace Systems Pub Date : 2024-01-05 DOI: 10.1007/s42401-023-00253-2

Roman Trifonov, Kirill Shelkov, Sergey Perepechaev, Andrey Boykov

引用次数: 0

Modeling of the stress–strain responses and deformation patterns of superelastic NiTi tubes subjected to biaxial loadings 受双轴载荷作用的超弹性镍钛管的应力应变响应和变形模式建模

Aerospace Systems Pub Date : 2024-01-04 DOI: 10.1007/s42401-023-00266-x

Mingxun Wu, Dongjie Jiang

{"title":"Modeling of the stress–strain responses and deformation patterns of superelastic NiTi tubes subjected to biaxial loadings","authors":"Mingxun Wu, Dongjie Jiang","doi":"10.1007/s42401-023-00266-x","DOIUrl":"10.1007/s42401-023-00266-x","url":null,"abstract":"<div><p>Nearly equiatomic NiTi shape memory alloy exhibits superelasticity, i.e., it can be strained up to ~ 7% and recover completely upon unloading, and consequently, the stress–strain response forms a closed hysteresis. The mechanical behavior of superelastic NiTi is characterized by significant tension–compression asymmetry, which leads to complexity in the stress–strain responses and deformation patterns of thin-walled superelastic NiTi tubes loaded by axial force and internal pressure simultaneously. In the reported biaxial experiments, the NiTi tube exhibits hardening responses and essentially homogeneous deformation in a neighborhood of equibiaxiality. In other cases, its stress–strain responses trace stress plateaus associated with localized deformation patterns, and the level of plateaus, magnitude of transformation strains, and orientation of the localization bands are strongly dependent on the axial-to-hoop stress ratio. In this paper, finite element modeling is performed to analyze numerically the mechanical response of biaxially loaded superelastic NiTi tube. A numerical feedback control scheme is developed to maintain the stress ratio to follow the target value. The simulations reproduce successfully the observed phenomena in the experiments, such as the localization of helical bands, the variation of band angles with stress ratio, as well as the hardening and uniform deformation near the state of equibiaxial stress. In addition, the variation of axial and hoop stress–strain responses with different stress ratios are also studied, which are reasonably close to the experimental ones. The presented work demonstrates the validity of the developed finite element analysis framework and paves the way for analysis of superelastic shape memory alloy structures under multiaxial loading.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139384667","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

Hybrid optimization of curvature continuous stacking line on the highly loaded diffuser cascade 在高负荷扩散器级联上对曲率连续堆叠线进行混合优化

Aerospace Systems Pub Date : 2024-01-04 DOI: 10.1007/s42401-023-00265-y

Ke Yao, Xingyi Zhang, Xiaoqing Qiang

{"title":"Hybrid optimization of curvature continuous stacking line on the highly loaded diffuser cascade","authors":"Ke Yao, Xingyi Zhang, Xiaoqing Qiang","doi":"10.1007/s42401-023-00265-y","DOIUrl":"10.1007/s42401-023-00265-y","url":null,"abstract":"<div><p>The compressor is a critical component of aero-engines. In order to improve the performance, the compressor ratio of single-stage compressor is getting higher and higher, which will lead to high back pressure gradient and losses. To solve this problem, there are many techniques applied, such as cantilevered stator, tip clearance and slotted airfoils. However, traditional design methods are experience-dependent and time-consuming. This paper proposes a hybrid optimization method to optimize the stacking line of compressor cascade and reduce total pressure loss on both design and off-design conditions. The approach employs various surrogate models and a multi-infill strategy, outperforming traditional optimization methods using a single surrogate model and a single infilling strategy. The results show that compared to the original blade, the optimized blade has a 34.6<span>(%)</span> lower mass-averaged total pressure loss at the design point, while the static pressure ratio increases by 2.43<span>(%)</span>. This paper innovatively combines deep learning-based surrogate models, the hybrid optimization algorithm, and the curvature-based blade shaping method to optimize the blade shape, shorten the blade design time, and ultimately reduce the losses significantly.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139386247","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