Astrodynamics最新文献_第10页

Correction to: Missing Declaration of Competing Interest statements in previously published articles 更正:先前发表的文章中缺少竞争利益声明

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-02-11 DOI: 10.1007/s42064-022-0136-2

Astrodynamics Editorial Office

引用次数: 0

PHiFA—A tool for numerical propagation of high-fidelity astrodynamics 用于高保真天体动力学数值传播的工具

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-29 DOI: 10.1007/s42064-021-0113-1

Yang Yang, Erik Klein, Changyong He, Han Cai, Yan Zhang

引用次数: 1

Landing site positioning and descent trajectory reconstruction of Tianwen-1 on Mars “天文一号”火星着陆点定位与下降轨迹重建

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0121-1

Anran Wang, Li Wang, Yinuo Zhang, Baocheng Hua, Tao Li, Yang Liu, Dayong Lin

{"title":"Landing site positioning and descent trajectory reconstruction of Tianwen-1 on Mars","authors":"Anran Wang, Li Wang, Yinuo Zhang, Baocheng Hua, Tao Li, Yang Liu, Dayong Lin","doi":"10.1007/s42064-021-0121-1","DOIUrl":"10.1007/s42064-021-0121-1","url":null,"abstract":"<div><p>Tianwen-1 (TW-1) is the first Chinese interplanetary mission to have accomplished orbiting, landing, and patrolling in a single exploration of Mars. After safe landing, it is essential to reconstruct the descent trajectory and determine the landing site of the lander. For this purpose, we processed descent images of the TW-1 optical obstacle-avoidance sensor (OOAS) and digital orthophoto map (DOM) of the landing area using our proposed hybrid-matching method, in which the landing process is divided into two parts. In the first, crater matching is used to obtain the geometric transformations between the OOAS images and DOM to calculate the position of the lander. In the second, feature matching is applied to compute the position of the lander. We calculated the landing site of TW-1 to be 109.9259° E, 25.0659° N with a positional accuracy of 1.56 m and reconstructed the landing trajectory with a horizontal root mean squared error of 1.79 m. These results will facilitate the analyses of the obstacle-avoidance system and optimize the control strategy in the follow-up planetary-exploration missions.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 1","pages":"69 - 79"},"PeriodicalIF":6.1,"publicationDate":"2022-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-021-0121-1.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50007940","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

Aerodynamic design, analysis, and validation techniques for the Tianwen-1 entry module 天文一号进入模块的空气动力学设计、分析和验证技术

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0123-z

Qi Li, Wei Rao, Xiaoli Cheng, Haogong Wei, Chuang Wang, Jie Dong

{"title":"Aerodynamic design, analysis, and validation techniques for the Tianwen-1 entry module","authors":"Qi Li, Wei Rao, Xiaoli Cheng, Haogong Wei, Chuang Wang, Jie Dong","doi":"10.1007/s42064-021-0123-z","DOIUrl":"10.1007/s42064-021-0123-z","url":null,"abstract":"<div><p>The clear differences between the atmosphere of Mars and the Earth coupled with the lack of a domestic research basis were significant challenges for the aerodynamic prediction and verification of Tianwen-1. In addition, the Mars entry, descent, and landing (EDL) mission led to specific requirements for the accuracy of the aerodynamic deceleration performance, stability, aerothermal heating, and various complex aerodynamic coupling problems of the entry module. This study analyzes the key and difficult aerodynamic and aerothermodynamic problems related to the Mars EDL process. Then, the study process and results of the design and optimization of the entry module configuration are presented along with the calculations and experiments used to obtain the aerodynamic and aerothermodynamic characteristics in the Martian atmosphere. In addition, the simulation and verification of the low-frequency free oscillation characteristics under a large separation flow are described, and some special aerodynamic coupling problems such as the aeroelastic buffeting response of the trim tab are discussed. Finally, the atmospheric parameters and aerodynamic characteristics obtained from the flight data of the Tianwen-1 entry module are compared with the design data. The data obtained from the aerodynamic design, analysis, and verification of the Tianwen-1 entry module all meet the engineering requirements. In particular, the flight data results for the atmospheric parameters, trim angles of attack, and trim axial forces are within the envelopes of the prediction deviation zones.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 1","pages":"39 - 52"},"PeriodicalIF":6.1,"publicationDate":"2022-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-021-0123-z.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50007953","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 1

End-to-end Mars entry, descent, and landing modeling and simulations for Tianwen-1 guidance, navigation, and control system 天文一号制导、导航和控制系统的端到端火星进入、下降和着陆建模和仿真

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0115-z

Chao Xu, Xiangyu Huang, Minwen Guo, Maodeng Li, Jinchang Hu, Xiaolei Wang

引用次数: 4

Message from the Guest Editors of the Special Issue on Entry, Descent, and Landing of Tianwen-1—China’s First Mission to Mars 中国首次火星探测任务“天文一号”进入、下降和着陆特刊特约编辑寄语

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0129-6

Xiangyu Huang, Yu Jiang, Xiangyuan Zeng

引用次数: 0

Tianwen-1 Mars entry vehicle trajectory and atmosphere reconstruction preliminary analysis “天文一号”火星进入飞行器轨道和大气重建初步分析

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0116-y

Haogong Wei, Wei Rao, Guangqiang Chen, Guidong Wang, Xin Zou, Qi Li, Yanqi Hu

{"title":"Tianwen-1 Mars entry vehicle trajectory and atmosphere reconstruction preliminary analysis","authors":"Haogong Wei, Wei Rao, Guangqiang Chen, Guidong Wang, Xin Zou, Qi Li, Yanqi Hu","doi":"10.1007/s42064-021-0116-y","DOIUrl":"10.1007/s42064-021-0116-y","url":null,"abstract":"<div><p>The Tianwen-1 Mars entry vehicle successfully landed on the surface of Mars in southern Utopia Planitia on May 15, 2021, at 7:18 (UTC+8). To acquire valuable Martian flight data, a scientific instrumentation package consisting of a flush air data system and a multilayer temperature-sensing system was installed aboard the entry vehicle. A combined approach was applied in the entry, descent, and landing trajectory reconstruction using all available data obtained by the inertial measurement unit and the flush air data system. An aerodynamic database covering the entire flight regime was generated using computational fluid dynamics methods to assist in the reconstruction process. A preliminary analysis of the trajectory reconstruction result, along with the atmosphere reconstruction and aerodynamic performance, was conducted. The results show that the trajectory agrees closely with the nominal trajectory and the wind-relative attitude. Suspected wind occurred at the end of the trajectory.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 1","pages":"81 - 91"},"PeriodicalIF":6.1,"publicationDate":"2022-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-021-0116-y.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50007955","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

Adaptive entry guidance for the Tianwen-1 mission 天文-1任务的自适应进入制导

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0120-2

Minwen Guo, Xiangyu Huang, Maodeng Li, Jinchang Hu, Chao Xu

{"title":"Adaptive entry guidance for the Tianwen-1 mission","authors":"Minwen Guo, Xiangyu Huang, Maodeng Li, Jinchang Hu, Chao Xu","doi":"10.1007/s42064-021-0120-2","DOIUrl":"10.1007/s42064-021-0120-2","url":null,"abstract":"<div><p>To meet the requirements of the Tianwen-1 mission, adaptive entry guidance for entry vehicles, with low lift-to-drag ratios, limited control authority, and large initial state bias, was presented. Typically, the entry guidance law is divided into four distinct phases: trim angle-of-attack phase, range control phase, heading alignment phase, and trim-wing deployment phase. In the range control phase, the predictor—corrector guidance algorithm is improved by planning an on-board trajectory based on the Mars Science Laboratory (MSL) entry guidance algorithm. The nominal trajectory was designed and described using a combination of the downrange value and other states, such as drag acceleration and altitude rate. For a large initial state bias, the nominal downrange value was modified onboard by weighing the landing accuracy, control authority, and parachute deployment altitude. The biggest advantage of this approach is that it allows the successful correction of altitude errors and the avoidance of control saturation. An overview of the optimal trajectory design process, including a discussion of the design of the initial flight path angle, relevant event trigger, and transition conditions between the four phases, was also presented. Finally, telemetry data analysis and post-flight assessment results were used to illustrate the adaptive guidance law, create good conditions for subsequent parachute reduction and power reduction processes, and gauge the success of the mission.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 1","pages":"17 - 26"},"PeriodicalIF":6.1,"publicationDate":"2022-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-021-0120-2.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50007954","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 4

Entry vehicle control system design for the Tianwen-1 mission 天文一号任务的进入飞行器控制系统设计

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0124-y

Jinchang Hu, Xiangyu Huang, Maodeng Li, Minwen Guo, Chao Xu, Yu Zhao, Wangwang Liu, Xiaolei Wang

引用次数: 2

Powered-descent landing GNC system design and flight results for Tianwen-1 mission “天文一号”动力下降着陆GNC系统设计及飞行结果

IF 6.1 1区物理与天体物理

Astrodynamics Pub Date : 2022-01-04 DOI: 10.1007/s42064-021-0118-9

Xiangyu Huang, Chao Xu, Jinchang Hu, Maodeng Li, Minwen Guo, Xiaolei Wang, Yu Zhao, Baocheng Hua, Yunpeng Wang

{"title":"Powered-descent landing GNC system design and flight results for Tianwen-1 mission","authors":"Xiangyu Huang, Chao Xu, Jinchang Hu, Maodeng Li, Minwen Guo, Xiaolei Wang, Yu Zhao, Baocheng Hua, Yunpeng Wang","doi":"10.1007/s42064-021-0118-9","DOIUrl":"10.1007/s42064-021-0118-9","url":null,"abstract":"<div><p>The powered-descent landing (PDL) phase of the Tianwen-1 mission began with composite backshell—parachute (CBP) separation and ended with landing-rover touchdown. The main tasks of this phase were to reduce the velocity of the lander, perform the avoidance maneuver, and guarantee a soft touchdown. The PDL phase overcame many challenges: performing the divert maneuver to avoid collision with the CBP while simultaneously avoiding large-scale hazards; slowing the descent from approximately 95 to 0 m/s; performing the precise hazard-avoidance maneuver; and placing the lander gently and safely on the surface of Mars. The architecture and algorithms of the guidance, navigation, and control system for the PDL phase were designed; its execution resulted in Tianwen-1’s successful touchdown in the morning of 15 May 2021. Consequently, the Tianwen-1 mission achieved a historic autonomous landing with simultaneous hazard and CBP avoidance.</p><div><figure><div><div><picture><source><img></source></picture></div></div></figure></div></div>","PeriodicalId":52291,"journal":{"name":"Astrodynamics","volume":"6 1","pages":"3 - 16"},"PeriodicalIF":6.1,"publicationDate":"2022-01-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://link.springer.com/content/pdf/10.1007/s42064-021-0118-9.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"50013560","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 6