Advances in Astronautics Science and Technology最新文献_第4页

Research on Space Electrostatic Discharge Detection Technology Based on Optical Fiber Sensing 基于光纤传感的空间静电放电检测技术研究

Advances in Astronautics Science and Technology Pub Date : 2022-11-12 DOI: 10.1007/s42423-022-00134-4

Xiaoqi Huang, Li Wang, Qiang Guo, Feiyang Xie

引用次数: 0

Analysis on Efficient Global Data Transmission and Timeliness of FY-3E Satellite FY-3E卫星全球数据高效传输与时效性分析

Advances in Astronautics Science and Technology Pub Date : 2022-09-19 DOI: 10.1007/s42423-022-00132-6

Heng Zhang, Sikang Deng, Xudong Gao, Yong Yang, Shengping Zhang

引用次数: 0

Review of Angles-Only Navigation Technique for Spacecraft Autonomous Rendezvous and Docking 航天器自主交会对接全角度导航技术研究进展

Advances in Astronautics Science and Technology Pub Date : 2022-09-13 DOI: 10.1007/s42423-022-00131-7

Ronghua Du, Wenhe Liao, Xiang Zhang

引用次数: 0

Carbon Fiber Composite Honeycomb Structures and the Application for Satellite Antenna Reflector with High Precision 碳纤维复合蜂窝结构及其在高精度卫星天线反射器中的应用

Advances in Astronautics Science and Technology Pub Date : 2022-09-05 DOI: 10.1007/s42423-022-00133-5

Xingyu Wei, Yan Wang, Pengcheng Xue, Taotao Zhang, Abir Rouis, Wei Xiao, Jian Xiong

引用次数: 2

Research Status of Deployment and Folding Technology of Large-Scale Membrane Sunshield in Space Mission 空间任务中大型膜式遮阳板展开与折叠技术研究现状

Advances in Astronautics Science and Technology Pub Date : 2022-08-24 DOI: 10.1007/s42423-022-00118-4

Lin Qiuhong, Peng Tao, Su Zhou, Qiu Hui, Li Xiao, Cong Qiang

引用次数: 0

Lightweight Thermal Protection System for the Mars Probe 火星探测器的轻型热防护系统

Advances in Astronautics Science and Technology Pub Date : 2022-08-05 DOI: 10.1007/s42423-022-00130-8

Cui Zhang, Changhao Yang, Bin Ma, Wenxuan Huang, Xiuzhu Han, Yanzhi Dong

引用次数: 0

System Design and Technical Characteristics of Fengyun-3E Meteorological Satellite 风云三号E气象卫星系统设计与技术特点

Advances in Astronautics Science and Technology Pub Date : 2022-08-04 DOI: 10.1007/s42423-022-00128-2

Yikai Shao, Jinhua Wang, Xiuqing Hu, Yong Yang, Pengfei Miao, Xiaofei Chen, Jinhuan Li, Sikang Deng, Yefei Li, Haisheng Li

{"title":"System Design and Technical Characteristics of Fengyun-3E Meteorological Satellite","authors":"Yikai Shao, Jinhua Wang, Xiuqing Hu, Yong Yang, Pengfei Miao, Xiaofei Chen, Jinhuan Li, Sikang Deng, Yefei Li, Haisheng Li","doi":"10.1007/s42423-022-00128-2","DOIUrl":"10.1007/s42423-022-00128-2","url":null,"abstract":"<div><p>Fengyun-3E(FY-3E) satellite is the first early morning orbit meteorological satellite for civil use in the world. It operates in the sun-synchronous orbit whose nominal altitude is 836 km and local time of descending node is 05:30–05:50. It is equipped with eleven payloads, which can realize comprehensive detection of various spectral bands from extreme ultraviolet, ultraviolet, visible, infrared to microwave. All-band absolute radiometric calibration in orbit has been realized on FY-3E satellite, with the calibration error of infrared band up to 0.4 K, microwave band up to 0.8 K, and visible near-infrared band up to 5%. FY-3E satellite can provide images, clouds and radiation, atmospheric parameters, sea and land surface, space weather and other products, which are important supporting data for weather forecast, climate monitoring and environmental disaster monitoring. This paper introduces the system design scheme of FY-3E satellite, summarizes the main technical features of the satellite, and looks forward to the application prospect of the satellite.</p><p>Chinese library classification number: V411.8; TP391.9</p><p>Document identification code: A</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 4","pages":"363 - 374"},"PeriodicalIF":0.0,"publicationDate":"2022-08-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50447931","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 Pressurized Structure Based on Lattice Truss Sandwich 基于格构特拉斯夹层的受压结构研究

Advances in Astronautics Science and Technology Pub Date : 2022-07-24 DOI: 10.1007/s42423-022-00129-1

Shi Liming, Li Linling, Wang Heyuan, Xian Yuhua, Zhang Xiaoyu

引用次数: 0

Research on Impact Location Method of Complex Spacecraft Pressure Vessel Structure 复杂航天器压力容器结构碰撞定位方法研究

Advances in Astronautics Science and Technology Pub Date : 2022-07-13 DOI: 10.1007/s42423-022-00125-5

Wang Lei, Zhou Hao, Wen Nan

引用次数: 0

For the 71st IAC A Novel Deployable Redundant Unit for Spacecraft Causality Analysis: Modelled With Existing Technology 一种用于航天器因果分析的新型可部署冗余单元：用现有技术建模

Advances in Astronautics Science and Technology Pub Date : 2022-07-13 DOI: 10.1007/s42423-022-00127-3

Chiranthan Krishnappa, Suraj Ravichandra, Ananda Mukesh Tamilselvan , Pruthvi Jagadeesh Gavirangapura Krishnamurthy, Sushmith Thuluva, Rohith Soma

{"title":"For the 71st IAC A Novel Deployable Redundant Unit for Spacecraft Causality Analysis: Modelled With Existing Technology","authors":"Chiranthan Krishnappa, Suraj\u0000 Ravichandra, Ananda Mukesh Tamilselvan \u0000, Pruthvi Jagadeesh Gavirangapura Krishnamurthy, Sushmith Thuluva, Rohith Soma","doi":"10.1007/s42423-022-00127-3","DOIUrl":"10.1007/s42423-022-00127-3","url":null,"abstract":"<div><p>This abstract proposes a design that helps analyze the causalities experienced by a spacecraft during communication loss or any unpredicted event. The idea is to build a mini backup box akin deployable spacecraft unit, also called a Redundant Unit that gets deployed under the command of the central unit on the occurrence of any possible danger to the spacecraft. This deployed unit ensures to picture and measure the spacecraft parameters at the time of deployment and store the data within it. This unit also serves the purpose of storing the backup payload data of a spacecraft under an uncompromisable fate. This helps in learning the potential dangers for a spacecraft alongside preventing the complete loss of mission data during any causality. This paper propounds the overall design of the structure and internal architecture of the Redundant unit with all the required subsystems, and technologies involved. The deploying mechanisms, payloads of the redundant unit, and methods employed will be presented on the basis of the most common possible fates for spacecraft.</p></div>","PeriodicalId":100039,"journal":{"name":"Advances in Astronautics Science and Technology","volume":"5 4","pages":"407 - 414"},"PeriodicalIF":0.0,"publicationDate":"2022-07-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50477189","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