Advances in Astronautics Science and Technology最新文献

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

Multi-Satellite Capture Configuration with Continuous Thrust 带持续推力的多卫星捕获配置

Advances in Astronautics Science and Technology Pub Date : 2024-08-16 DOI: 10.1007/s42423-024-00161-3

Weike Wang, Hanjun Wang, Tian Liao, Shunli Li, Mengping Zhu

{"title":"Multi-Satellite Capture Configuration with Continuous Thrust","authors":"Weike Wang, Hanjun Wang, Tian Liao, Shunli Li, Mengping Zhu","doi":"10.1007/s42423-024-00161-3","DOIUrl":"10.1007/s42423-024-00161-3","url":null,"abstract":"<div><p>The pursuit-evasion game of orbital satellite is an important research problem in the field of space security. In this pursuit-evasion game, intercepting the target usually requires superior maneuvering capabilities. To address this issue, a method is proposed in this paper to use multiple small satellites with weaker maneuvering capabilities to encircle and capture larger targets with stronger maneuvering abilities. Firstly, based on Tsiolkovsky’s formula, the planar interception problem is derived and a one-on-one planar interception strategy is designed. Next, the existence of solutions for planar mission is analyzed, and a multi-satellite encirclement configuration is designed based on elliptical passive flyby theory. Finally, simulation analysis is conducted on the impact of various design parameters of the planar interception configuration on the encirclement task. The results indicate that the initial distance between interceptor and target significantly affects interception time. Simulation results validate that the proposed interception strategy and encirclement configuration can achieve rapid interception of close-range targets effectively.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"7 2","pages":"133 - 143"},"PeriodicalIF":0.0,"publicationDate":"2024-08-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142443274","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 Conflict-Priority-Based Variable Neighborhood Tabu Search Method for Multi-Satellite Scheduling 基于冲突优先级的多卫星调度变邻塔布搜索法

Advances in Astronautics Science and Technology Pub Date : 2024-07-26 DOI: 10.1007/s42423-024-00165-z

Xiaoyu Chen, Qi Gao, Shengren Peng, Shihui Song, Yufei Liu, Guangming Dai, Maocai Wang, Changxing Zhang

{"title":"A Conflict-Priority-Based Variable Neighborhood Tabu Search Method for Multi-Satellite Scheduling","authors":"Xiaoyu Chen, Qi Gao, Shengren Peng, Shihui Song, Yufei Liu, Guangming Dai, Maocai Wang, Changxing Zhang","doi":"10.1007/s42423-024-00165-z","DOIUrl":"10.1007/s42423-024-00165-z","url":null,"abstract":"<div><p>With the increasing number and capabilities of orbital satellites and their onboard sensors, satellites scheduling plays an important role in growing demands for Earth observation tasks. A conflict-priority-based variable neighborhood tabu search method is proposed in this paper. By analyzing the flexibility of resources, the conflict-priority of tasks, and the visible time window features, the indicators of the impact, the conflict, the flexibility, and the bad impact are first established. On this basis, a first-come first-served greedy algorithm and a minimum bad impact greedy algorithm are designed for the generation of the initial solution. some rule-based heuristic strategies are also adopted for optimizing. Additionally, the algorithm incorporates three types of neighborhood structures including insertion, swapping and rearrangement, and deletion, using a tabu list to avoid local optima. Experimental results indicate the validity and efficiency of the proposed method. All solutions are within 10% of the optimal solution, with some even within 5%.The proposed method is effective for obtaining optimum solutions or solutions with a very good quality in various multi-satellite scheduling scenarios of realistic planning.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"7 2","pages":"163 - 176"},"PeriodicalIF":0.0,"publicationDate":"2024-07-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141798799","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

Distributed Constrained Control Allocation for Attitude Takeover of Combined Spacecraft 组合航天器姿态接管的分布式受限控制分配

Advances in Astronautics Science and Technology Pub Date : 2024-07-17 DOI: 10.1007/s42423-024-00162-2

Yufeng Jiang, Jitang Guo, Fei Zong, Shunli Li, Xinlong Chen

引用次数: 0

Spacecraft Anti-Reconnaissance Game Based on Particle Swarm Optimization Algorithm 基于粒子群优化算法的航天器反侦察游戏

Advances in Astronautics Science and Technology Pub Date : 2024-07-11 DOI: 10.1007/s42423-024-00160-4

Caihong Dong, Mengping Zhu, Jitang Guo, Xinlong Chen

引用次数: 0

Research on Strategies of Multi-Spacecraft Interception Based on Matrix Game 基于矩阵博弈的多航天器拦截策略研究

Advances in Astronautics Science and Technology Pub Date : 2024-07-01 DOI: 10.1007/s42423-024-00159-x

Zhang Hanlong, Zhou Wenya, Zhu Mengping, Xie Zhengyou, Guo Jitang

引用次数: 0

Scientific Objectives and Suggestions on Landing Site Selection of Manned Lunar Exploration Engineering 载人月球探测工程着陆点选择的科学目标和建议

Advances in Astronautics Science and Technology Pub Date : 2024-06-27 DOI: 10.1007/s42423-024-00153-3

Ran Niu, Guang Zhang, Lingli Mu, Yang-ting Lin, Jianzhong Liu, Zheng Bo, Wei Dai, Zheng Qin, Peng Zhang

{"title":"Scientific Objectives and Suggestions on Landing Site Selection of Manned Lunar Exploration Engineering","authors":"Ran Niu, Guang Zhang, Lingli Mu, Yang-ting Lin, Jianzhong Liu, Zheng Bo, Wei Dai, Zheng Qin, Peng Zhang","doi":"10.1007/s42423-024-00153-3","DOIUrl":"10.1007/s42423-024-00153-3","url":null,"abstract":"<div><p>Focusing on cutting-edge scientific issues related to lunar exploration and applications, 9 overarching goals and 38 specific objectives for China's manned lunar exploration program have been proposed. Leveraging China's technical capabilities in manned spaceflight and lunar exploration, as well as its expertise in lunar and planetary science, the objectives center on scientific research, lunar-based scientific research, and resource exploration and utilization. Based on these scientific goals and trends in domestic and international manned lunar exploration landing site selection, China's basic principles and processes for selecting landing sites have been established. Thirty prime landing sites have been identified, including 11 low-latitude regions and 1 mid-latitude region, taking into account scientific value and engineering implementation conditions. These scientific objectives and landing site selection recommendations will serve as important guidance and top-level input for the design and implementation of China's manned lunar exploration program.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"7 1","pages":"37 - 50"},"PeriodicalIF":0.0,"publicationDate":"2024-06-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142414285","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