Journal of Spacecraft and Rockets最新文献

Deterministic Multistage Constellation Reconfiguration Using Integer Programming and Sequential Decision-Making Methods 使用整数编程和顺序决策方法进行确定性多级星座重构

Journal of Spacecraft and Rockets Pub Date : 2024-07-15 DOI: 10.2514/1.a35990

Hang Woon Lee, David O. Williams Rogers, Brycen D. Pearl, Hao Chen, Koki Ho

{"title":"Deterministic Multistage Constellation Reconfiguration Using Integer Programming and Sequential Decision-Making Methods","authors":"Hang Woon Lee, David O. Williams Rogers, Brycen D. Pearl, Hao Chen, Koki Ho","doi":"10.2514/1.a35990","DOIUrl":"https://doi.org/10.2514/1.a35990","url":null,"abstract":"This paper addresses the problem of reconfiguring Earth observation satellite constellation systems through multiple stages. The Multistage Constellation Reconfiguration Problem (MCRP) aims to maximize the total observation rewards obtained by covering a set of targets of interest through the active manipulation of the orbits and relative phasing of constituent satellites. This paper considers deterministic problem settings in which the targets of interest are known a priori. We propose a novel integer linear programming formulation for MCRP, capable of obtaining provably optimal solutions. To overcome computational intractability due to the combinatorial explosion in solving large-scale instances, we introduce two computationally efficient sequential decision-making methods based on the principles of a myopic policy and a rolling horizon procedure. The computational experiments demonstrate that the devised sequential decision-making approaches yield high-quality solutions with improved computational efficiency over the baseline MCRP. Finally, a case study using Hurricane Harvey data showcases the advantages of multistage constellation reconfiguration over single-stage and no-reconfiguration scenarios.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"11 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141648383","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

Low-Earth-Orbit Mega-Constellation Low-Redundancy Design: Rapid Performance Analysis and Adaptive Configuration Layering 低地轨道巨型星座低冗余设计：快速性能分析和自适应配置分层

Journal of Spacecraft and Rockets Pub Date : 2024-07-15 DOI: 10.2514/1.a35995

Yao Xiao, Shuai Guo, Yazhong Luo

{"title":"Low-Earth-Orbit Mega-Constellation Low-Redundancy Design: Rapid Performance Analysis and Adaptive Configuration Layering","authors":"Yao Xiao, Shuai Guo, Yazhong Luo","doi":"10.2514/1.a35995","DOIUrl":"https://doi.org/10.2514/1.a35995","url":null,"abstract":"Megaconstellations, which offer convenient communication and navigation services, are at the forefront of satellite application advancements. However, traditional constellations with a single uniform configuration fail to meet the various demands in different regions, thus leading to low utilization. In addition, satellite safety becomes a key consideration that megaconstellations cannot ignore. To address the aforementioned problems, this study proposes an adaptive method for designing layered megaconstellations under the assumptions of circular orbits, uniform distribution in each plane, and a pregiven altitude. Two novel methods are developed for evaluating the coverage performance and satellite safety. First, the longitude-coverage-ratio model is proposed based on the street of coverage theory, enhancing the constellation design for latitude-specific coverage needs. Next, a rapid method is derived for calculating the minimum angular distance between planes. Then, the study investigates the models to be used in subconstellation design techniques for assembling multilayer hybrid megaconstellations. Several hybrid megaconstellations are designed, demonstrating the applicability of the methodology for both nonuniform and global uniform coverage requirements. The results show that this method offers reduced redundancy and a lower number of satellites compared to a single Walker. The examples also suggest that low-Earth-orbit hybrid constellations can achieve global uniform coverage when reaching sufficient coverage folds.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"21 20","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141645851","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

Integrated Orbital Design Method for Manned Lunar Exploration with Relaxed Temporal Constraints 具有宽松时间约束条件的载人月球探测综合轨道设计方法

Journal of Spacecraft and Rockets Pub Date : 2024-07-15 DOI: 10.2514/1.a36062

Zeyue Li, Zhen Yang, Haiyang Li, Wanmeng Zhou

{"title":"Integrated Orbital Design Method for Manned Lunar Exploration with Relaxed Temporal Constraints","authors":"Zeyue Li, Zhen Yang, Haiyang Li, Wanmeng Zhou","doi":"10.2514/1.a36062","DOIUrl":"https://doi.org/10.2514/1.a36062","url":null,"abstract":"An integrated orbital design method with relaxation of temporal constraints is presented, focusing on improving the efficiency of complex-flight-mission planning for manned lunar exploration. Crewed lunar exploration programs are characterized by a variety of spacecraft and multiple trajectory stages. The aim of integrated design is to realize automatic splicing of such multistage trajectories under coupled temporal and spatial constraints. Currently, integrated mission–orbital design is mainly achieved through decoupling and iterative methods, and the matching of boundary constraints usually requires human-in-the-loop intervention. In this paper, a novel integrated orbital splicing process is proposed from the viewpoint of the temporal dimension, considering the temporal relationships between orbital stages and the scheduling flow of the underlying dynamical models. Relaxation factors are introduced for weak temporal constraints to improve the overall convergence of orbital splicing calculations across different stages. A comprehensive temporal constraint model and subsequently an integrated orbital design model are constructed. The proposed method is validated by simulation of flight missions targeting the high-latitude regions of the moon.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"51 10","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141648613","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

Low-Energy Transfers to Lunar Distant Retrograde Orbits from Geostationary Transfer Orbits 从地球静止转移轨道向月球遥远逆行轨道的低能量转移

Journal of Spacecraft and Rockets Pub Date : 2024-07-09 DOI: 10.2514/1.a35623

Chao Peng, Yunong Shang, Shengmao He, Zhengfan Zhu, Changxuan Wen

引用次数: 0

Measurements of Natural Turbulence During the BOLT II Flight Experiment BOLT II 飞行实验期间的自然湍流测量结果

Journal of Spacecraft and Rockets Pub Date : 2024-07-09 DOI: 10.2514/1.a35868

John M. Wirth, R. Bowersox, Aaron T. Dufrene, T. Wadhams

{"title":"Measurements of Natural Turbulence During the BOLT II Flight Experiment","authors":"John M. Wirth, R. Bowersox, Aaron T. Dufrene, T. Wadhams","doi":"10.2514/1.a35868","DOIUrl":"https://doi.org/10.2514/1.a35868","url":null,"abstract":"A Mach 6.0 flight experiment was performed to characterize the turbulent skin friction and heat flux associated with natural transition for vehicle-length Reynolds numbers up to 45 million. This boundary-layer turbulence flight, termed BOLT II, was the second in a series coordinated by the Air Force Office of Scientific Research. Surface heat flux, skin friction, and pressure fluctuation spectra were acquired to characterize the transition process. The test geometry used concave curvature and swept leading edges to introduce a boundary layer with stationary laminar vortex streaks, competing transition mechanisms, and complex early turbulence. The analyses also showed that the spatial evolution of turbulence varied with respect to the location of the vortex heating streaks. Prominent overshoots were observed in the early turbulence within the streak. Turbulence data was collected for Reynolds numbers [Formula: see text] up to [Formula: see text]. A common [Formula: see text] was identified as the start of equilibrium turbulence for the data presented. Conjugate heat transfer simulations, both laminar and turbulent, agreed well with the experimental data, including the laminar leading edge. The Reynolds analogy ratios based on the curve fits to the data, including compressibility, were generally between 0.9 and 1.0. The observed variations were likely the result of the spatial separation of the sensors and different definitions of Stanton number normalization between flight and theory.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"97 11","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141664062","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

Effect of Reynolds Number and Aeroelastic Scaling Upon Launch-Vehicle Ground-Wind Loads 雷诺数和气弹缩放对运载火箭地面风载荷的影响

Journal of Spacecraft and Rockets Pub Date : 2024-07-09 DOI: 10.2514/1.a35930

Thomas G. Ivanco, Donald F. Keller, Jennifer L. Pinkerton

{"title":"Effect of Reynolds Number and Aeroelastic Scaling Upon Launch-Vehicle Ground-Wind Loads","authors":"Thomas G. Ivanco, Donald F. Keller, Jennifer L. Pinkerton","doi":"10.2514/1.a35930","DOIUrl":"https://doi.org/10.2514/1.a35930","url":null,"abstract":"NASA conducted a launch vehicle ground-wind-loads investigation at the NASA Langley Transonic Dynamics Tunnel to investigate wind-induced oscillations (WIOs) of a launch vehicle when exposed to ground winds before launch. Previous publications from this effort have documented the effects of an atmospheric-boundary-layer profile on WIO response and the correlation process between model-scale and full-scale wind characteristics and resulting structural loads. This paper will focus on the importance of aeroelastic scaling and the impact of Reynolds number on WIO response. As described in the literature and confirmed in the present investigation, aeroelastic effects can significantly increase the magnitude of measured loads. Additionally, vortex shedding is sensitive to nuances of the flow in the shear layer, which is governed by Reynolds number. Many wind-tunnel facilities are not capable of producing flight Reynolds numbers for the ground-wind-loads problem. At very low Reynolds numbers, laminar shear layers exhibit different behavior, resulting in different vortex frequencies, oscillating lift magnitudes, and motion sensitivities. This investigation demonstrated that low Reynolds number testing can yield substantially lower dynamic loads with less aeroelastic coupling than those acquired at flight-representative Reynolds numbers for a resonant WIO event. Additionally, a resonant response phenomenon present at flight Reynolds number was absent at low Reynolds number. Conversely, for nonresonant WIO response conditions, similar dynamic load coefficients were obtained for similar test velocities at either Reynolds number condition. These findings impact many large launch vehicles, including the NASA Space Launch System series of vehicles.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"21 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141663694","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

Reconstructed Performance of Mars 2020 Parachute Decelerator System 火星 2020 降落伞减速器系统的重建性能

Journal of Spacecraft and Rockets Pub Date : 2024-07-09 DOI: 10.2514/1.a35976

Clara O’Farrell, Ian G. Clark

引用次数: 0

Three-Dimensional Radiation Analysis of the Hypersonic Jules Verne Reentry Spectra 高超音速儒勒-凡尔纳再入光谱的三维辐射分析

Journal of Spacecraft and Rockets Pub Date : 2024-07-02 DOI: 10.2514/1.a35959

Sara J. Swenson, B. Argrow, Craig P. Turansky

引用次数: 0

Coupled Spacecraft Charging Due to Continuous Electron Beam Emission and Impact 连续电子束发射和撞击导致的航天器耦合充电

Journal of Spacecraft and Rockets Pub Date : 2024-07-02 DOI: 10.2514/1.a36010

Julian Hammerl, Hanspeter Schaub

{"title":"Coupled Spacecraft Charging Due to Continuous Electron Beam Emission and Impact","authors":"Julian Hammerl, Hanspeter Schaub","doi":"10.2514/1.a36010","DOIUrl":"https://doi.org/10.2514/1.a36010","url":null,"abstract":"Spacecraft charge naturally in orbit due to the plasma environment and the electromagnetic radiation from the sun. By emitting an electron beam, a servicer spacecraft can control its electric potential and also the potential of a neighboring target if the electron beam is aimed at the target spacecraft. In addition, the impacting electron beam excites secondary electrons and x-rays, providing a way to touchlessly sense the potential of the target. Because of the electron beam, the charging dynamics of the two spacecraft are coupled. This paper studies the effects of the beam on the electric potentials using a numerical charging model. It is found that multiple equilibria may exist due to the electron beam. Jumps between equilibrium configurations are possible when the electron beam energy is quickly reduced or when current fluctuations are present. Being aware of multiple equilibrium configurations is important for feedback-based charge control but also enables a new open-loop charge control around one of the equilibria. The effect of the electron beam on the spacecraft potentials is studied for geostationary Earth orbit and cislunar space. It is found that the current applied by the beam to the target may influence remote electric potential sensing methods.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"19 8","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141687007","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

Simultaneously Adjusting Deployment Strategies for Mega-Constellations Using Low-Thrust Maneuvers 利用低推力机动同时调整巨型恒星的部署策略

Journal of Spacecraft and Rockets Pub Date : 2024-07-01 DOI: 10.2514/1.a36007

Huang Pu, Guangwei Wen, Zhaokui Wang

{"title":"Simultaneously Adjusting Deployment Strategies for Mega-Constellations Using Low-Thrust Maneuvers","authors":"Huang Pu, Guangwei Wen, Zhaokui Wang","doi":"10.2514/1.a36007","DOIUrl":"https://doi.org/10.2514/1.a36007","url":null,"abstract":"Deploying a constellation can be costly and inefficient. The ultimate goal is to position multiple satellites into designated orbital slots with the fewest launches and lowest energy consumption. This paper presents a method for simultaneous right ascension of the ascending node (RAAN) and argument of latitude (AOL) adjustments using continuous low thrust. Firstly, how changes in the semimajor axis and inclination affect the RAAN and the AOL is analyzed. A control method is proposed, and all satellites are sequentially placed from the injection orbit to the working orbit at specific time intervals. Because the RAAN and AOL are coupled with each other, a priority control strategy is introduced. This strategy ensures that the AOL is accurately satisfied within the time between each maneuver. Next, equations that correlate the RAAN and the AOL with the orbit inclination deviation and maneuver interval time are established. By studying the maneuver time intervals and inclination compensations, a highly accurate synchronized deployment scheme can be obtained. A simulation experiment based on the OneWeb constellation is carried out. In the simulation, 80 satellites are launched by just one rocket. By employing the proposed method, the constellation is successfully deployed. Results from the simulation verified the effectiveness of the proposed algorithm, which may be employed for rapid deployment of a mega-constellation in the future.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"119 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141712861","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