Advances in Astronautics Science and Technology最新文献

Task Assignment Method of Geodesic Dome Phased Array Antenna Based on High-Dimensional Combinatorial Bayesian Optimization 基于高维组合贝叶斯优化的测地圆顶相控阵天线任务分配方法

Advances in Astronautics Science and Technology Pub Date : 2025-06-11 DOI: 10.1007/s42423-025-00178-2

Yi Zhang, Qinyu Fan, Qinyang Zou, Qie Liu, Yi Chai, Tian Liu

{"title":"Task Assignment Method of Geodesic Dome Phased Array Antenna Based on High-Dimensional Combinatorial Bayesian Optimization","authors":"Yi Zhang, Qinyu Fan, Qinyang Zou, Qie Liu, Yi Chai, Tian Liu","doi":"10.1007/s42423-025-00178-2","DOIUrl":"10.1007/s42423-025-00178-2","url":null,"abstract":"<div><p>This paper addresses the task assignment problem for a geodesic dome phased array antenna (GDPAA), which is described as an optimization problem to obtain the maximum measurement performance. Several critical challenges arise in this task allocation, including the high dimensionality of decision variables, multiple conflicting objectives, and the lack of an analytical expression for the objective function. To solve these challenges, this work proposes a high-dimensional combinatorial Bayesian optimization approach for this task scheduling. A random dimension reduction method is used to simplify the decision variables to handle large-scale tasks. With the consideration on the time complexity of the construction of the classical surrogate model for Bayesian optimization, a probabilistic surrogate model is built to describe the relationship between the measurement task and the GDPAA’s performance. The new strategy accelerates the algorithm convergence. An experiment is conducted to show the merit of effectiveness of the proposed method. Compared to reinforcement learning, particle swarm optimization, and other methods, the proposed approach achieves superior measurement performance with reduced computational time.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"8 1","pages":"35 - 46"},"PeriodicalIF":0.0,"publicationDate":"2025-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145143292","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

Torque Direction Constrained Singular Avoidance Steering Law for Five-Skewed SGCMG System 五斜SGCMG系统的力矩方向约束奇异回避转向律

Advances in Astronautics Science and Technology Pub Date : 2025-05-30 DOI: 10.1007/s42423-025-00176-4

Tao Nie, Zhijun Que, Tao Yi

引用次数: 0

Active Vibration Control of Beam-Pointing-Sensitive Modes in Large Space Deployable Antennas 大型空间可展开天线波束指向敏感模式的主动振动控制

Advances in Astronautics Science and Technology Pub Date : 2025-05-26 DOI: 10.1007/s42423-025-00174-6

Zhenglin Yang, Keda He, Lei Liu, Wei Li, Peng Su, Qing Li, Hui Wang

{"title":"Active Vibration Control of Beam-Pointing-Sensitive Modes in Large Space Deployable Antennas","authors":"Zhenglin Yang, Keda He, Lei Liu, Wei Li, Peng Su, Qing Li, Hui Wang","doi":"10.1007/s42423-025-00174-6","DOIUrl":"10.1007/s42423-025-00174-6","url":null,"abstract":"<div><p>Large space deployable antennas play a critical role in satellite microwave communications, remote sensing, and deep space exploration due to their high-precision, light weight, and reliability. However, their large size and extremely low stiffness and damping make them susceptible to vibrations, which degrade the stability of antenna beam pointing under continuous external excitation. To mitigate the effects of such vibrations on beam pointing stability, this paper proposes an active hybrid control method targeting beam-pointing-sensitive vibration modes which significantly degrade beam pointing accuracy. First, the dynamic model of the antenna is established, and finite element computing is used to solve the mode shapes and identify the sensitive modes. A model-independent hybrid control method, based on independent modal space control approach, is then designed to control the specific modes, with initial effectiveness verified through numerical simulations. To further validate the practical feasibility of the proposed control method, active vibration control experiments are conducted on a 10 m aperture antenna prototype for a specific beam pointing sensitive mode (approximately 4.6 Hz). Experimental results indicate that steady state vibration is achieved within 1.1 s after initiating active control, with root-mean-square acceleration suppression exceeding 77% at monitoring points. These results demonstrate that the active control method effectively suppresses vibrations in beam-pointing-sensitive modes.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"8 1","pages":"1 - 16"},"PeriodicalIF":0.0,"publicationDate":"2025-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145145062","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 Data-Driven Equivalent Modeling Approach for Large-Amplitude Liquid Sloshing Under Microgravity Environment 微重力环境下大振幅液体晃动的数据驱动等效建模方法

Advances in Astronautics Science and Technology Pub Date : 2025-05-09 DOI: 10.1007/s42423-025-00172-8

Jiawei Huo, Jing Lyu

引用次数: 0

Adaptive IMM Algorithm Based on Variational Inference for Multiple Maneuvering Extended Targets Tracking 基于变分推理的多机动扩展目标跟踪自适应IMM算法

Advances in Astronautics Science and Technology Pub Date : 2025-04-27 DOI: 10.1007/s42423-025-00173-7

Shenghua Wang, Renxian Li, Chenkai Men, Yunhe Cao, Tat-Soon Yeo

{"title":"Adaptive IMM Algorithm Based on Variational Inference for Multiple Maneuvering Extended Targets Tracking","authors":"Shenghua Wang, Renxian Li, Chenkai Men, Yunhe Cao, Tat-Soon Yeo","doi":"10.1007/s42423-025-00173-7","DOIUrl":"10.1007/s42423-025-00173-7","url":null,"abstract":"<div><p>In order to track multiple maneuvering extended targets accurately, an adaptive interacting multiple model algorithm based on variational inference (AIMM-VI) is proposed. An augmented state is constructed to cater for time-varying orientation angle and track realistic shape changes, resulting in better elliptical shape estimation and tracking accuracy. Multiple measurements from multiple extended targets are effectively assigned to corresponding targets through the marginal association probability distribution criterion, and the variational inference is used to accurately estimate the augmented state and shape information, which greatly improves the parameters estimation performance. The residual and likelihood functions are updated in real-time according to the results of variational inference, allowing for the updating of the model probability in real-time. The Markov probability transfer matrix is subsequently adaptively updated by the compression ratio, which makes the algorithm more adaptable to maneuvering target and significantly improves the adaptability and robustness of the algorithm. The final simulation and experiment results show that the proposed algorithm can effectively improve the tracking performance of multiple maneuvering extended targets.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"8 1","pages":"73 - 87"},"PeriodicalIF":0.0,"publicationDate":"2025-04-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145145228","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

Online Uncertainty Evaluation on the Launch Vehicle Mission Re-planning Under Thrust Faults 推力故障下运载火箭任务重规划的在线不确定性评估

Advances in Astronautics Science and Technology Pub Date : 2025-03-20 DOI: 10.1007/s42423-025-00169-3

Keshu Li, Ying Ma, Wanqing Zhang, Xiqiang Lin, Yuanjun He

{"title":"Online Uncertainty Evaluation on the Launch Vehicle Mission Re-planning Under Thrust Faults","authors":"Keshu Li, Ying Ma, Wanqing Zhang, Xiqiang Lin, Yuanjun He","doi":"10.1007/s42423-025-00169-3","DOIUrl":"10.1007/s42423-025-00169-3","url":null,"abstract":"<div><p>The propulsion system failure is statistically acknowledged as the most fatal factor of launch vehicles, which has received extensive attention. In this paper, mission re-planning is conducted to address typical thrust faults when they exceed the adaptability of the guidance system. This is achieved by generating degraded orbits according to the residual capacity of the launch vehicle using successive convex optimization. Since the uncertainties of some critical parameters provided by the fault diagnosis system are not considered in the re-planning process, their influence is then analyzed by the polynomial chaos expansion (PCE) method. Considering the non-coincident engine cut-off phenomenon, an additional coasting phase is introduced to enable the evaluation of the stochastic distribution of the final orbit by PCE. Moreover, a deep neural network (DNN) is trained to reduce the time consumption of the uncertainty evaluation process. By implementing the DNN, the terminal states can be predicted directly from the fault information, enabling the online application. Simulation results verify the effectiveness and the accuracy of the PCE-based uncertainty evaluation. Besides, the DNN-assisted PCE is confirmed to greatly improve the computational efficiency while maintaining comparable accuracy to Monte-Carlo simulation and conventional PCE. Since the computational time of the DNN-assisted PCE is on the order of hundreds of milliseconds, it can be applied in real-time to support making appropriate and reliable mission re-planning decisions based on probability.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"8 1","pages":"17 - 34"},"PeriodicalIF":0.0,"publicationDate":"2025-03-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145144482","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

Research on Overload Characteristics of Projectile Penetrating Layered Protective Structures with High-Velocity 弹丸高速侵彻层状防护结构过载特性研究

Advances in Astronautics Science and Technology Pub Date : 2024-12-18 DOI: 10.1007/s42423-024-00168-w

Heng Ye, Yuanchao Wang, Xiaoming Chen, Yuxuan Zheng, Chun Cheng

{"title":"Research on Overload Characteristics of Projectile Penetrating Layered Protective Structures with High-Velocity","authors":"Heng Ye, Yuanchao Wang, Xiaoming Chen, Yuxuan Zheng, Chun Cheng","doi":"10.1007/s42423-024-00168-w","DOIUrl":"10.1007/s42423-024-00168-w","url":null,"abstract":"<div><p>The LS-DYNA simulation software was used to study the overload characteristics of a projectile penetrating a layered protective structure at high velocity. Firstly, the simulation data were compared with experimental data to verify the accuracy of the finite element model. The process of projectiles penetrating two different protective structures was analyzed, and the overload characteristics of the projectile under different working conditions were studied. Results show that the peak overload of the projectile penetrating the light protective structure at 1200 m/s and 1700 m/s can exceed 80,000 g and 130,000 g, respectively, and the peak overload of the projectile penetrating the heavy protective structure at 1200 m/s and 1700 m/s can exceed 40,000 g and 70,000 g, respectively. When the projectile penetrates a lightweight protective structure with different material shielding layers at the same velocity, the overload peak value of penetrating the shielding layer material of reinforced concrete is greater than that of penetrating the shielding layer material of granite. The deceleration peak value of the projectile penetrating a light protective structure is larger than that of a projectile penetrating a heavy protective structure at the same velocity mainly due to the good buffering effect of the thick soil layer of the heavy protective structure.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"7 3-4","pages":"177 - 195"},"PeriodicalIF":0.0,"publicationDate":"2024-12-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142963106","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

Video Information-Based Liquid Rocket Engine Fault Simulation Test Method under Complex Environment 基于视频信息的复杂环境下液体火箭发动机故障模拟试验方法

Advances in Astronautics Science and Technology Pub Date : 2024-09-24 DOI: 10.1007/s42423-024-00167-x

Yang Zhang, Meng Ma, Zhirong Zhong, Xuanhao Hua, Zhi Zhai

{"title":"Video Information-Based Liquid Rocket Engine Fault Simulation Test Method under Complex Environment","authors":"Yang Zhang, Meng Ma, Zhirong Zhong, Xuanhao Hua, Zhi Zhai","doi":"10.1007/s42423-024-00167-x","DOIUrl":"10.1007/s42423-024-00167-x","url":null,"abstract":"<div><p>Liquid rocket engines are fault-prone parts on launch vehicles. Due to its complex working environment and strict performance requirements, liquid rocket engines often face many kinds of failure risks during actual commissioning and operation. In view of the high risk of liquid rocket engine failure and the scarcity of abnormal video data in the actual commissioning process, the traditional fault monitoring methods are faced with many challenges. In response, this paper proposes a fault simulation testing methodology specifically for liquid rocket engines under complex interference conditions. A semi-physical model has been developed to mimic the abnormal states that liquid rocket engines may experience during debugging or operational activities. This model enables the collection and generation of a series of video data that closely resemble real-life fault scenarios, enhancing the effectiveness of fault monitoring and analysis. Finally, by comparing with the data of the actual test run, the simulation test data achieved a high degree of similarity, indicating that the designed simulation test can effectively simulate the actual physical process during the actual test run. Through the innovative fault simulation test method, this study successfully solved the problem of abnormal video data scarcity, and provided support for the research of liquid rocket engine video anomaly monitoring.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"7 3-4","pages":"197 - 208"},"PeriodicalIF":0.0,"publicationDate":"2024-09-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142962960","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

Game Strategies Against High Orbit Surveillance Satellites 对抗高轨道监视卫星的博弈策略

Advances in Astronautics Science and Technology Pub Date : 2024-09-15 DOI: 10.1007/s42423-024-00163-1

Fei Zong, Mengping Zhu, Xinlong Chen

引用次数: 0

Orbital Rendezvous Guidance Strategy for Time-Sensitive Missions 时间敏感型飞行任务的轨道会合制导战略

Advances in Astronautics Science and Technology Pub Date : 2024-08-17 DOI: 10.1007/s42423-024-00164-0

Tian Liao, Xinlong Chen, Jitang Guo, Shunli Li

{"title":"Orbital Rendezvous Guidance Strategy for Time-Sensitive Missions","authors":"Tian Liao, Xinlong Chen, Jitang Guo, Shunli Li","doi":"10.1007/s42423-024-00164-0","DOIUrl":"10.1007/s42423-024-00164-0","url":null,"abstract":"<div><p>A fixed-time orbital rendezvous guidance strategy was proposed to meet the requirements of the time-sensitive pursuit-capture game mission. A key problem of fixed-time orbit rendezvous is the design of deceleration guidance strategy and the choice of transfer time. In order to solve the deceleration guidance problem under limited thrust, a displacement formula under constant rocket thrust is proposed. Basing on the formula, a deceleration guidance strategy of \"pulse correction, deceleration condition, inverse-relative-velocity deceleration\" was designed so that the spacecraft can meet the terminal position constraint. Basing on the formula, a deceleration guidance strategy of \"pulse correction, deceleration condition, inverse-relative-velocity deceleration\" was designed so that the spacecraft can meet the terminal position constraint. For the mission time delay caused by deceleration process, a differential correction method was designed based on the displacement formula, which can obtain the Lambert transfer time corresponding to a given mission time. With the proposed method, the mission time error is reduced less than 1 s.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"7 2","pages":"89 - 100"},"PeriodicalIF":0.0,"publicationDate":"2024-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142443366","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