Journal of Spacecraft and Rockets最新文献_第6页

Onboard Cryogenic Liquid-Propellant Subcooler Based on Thermodynamic Vent for Upper-Stage Propulsion System 基于热动力通风口的机载低温液体推进剂过冷却器，用于末级推进系统

Journal of Spacecraft and Rockets Pub Date : 2024-01-30 DOI: 10.2514/1.a35888

Yuya Banno, K. Kinefuchi

{"title":"Onboard Cryogenic Liquid-Propellant Subcooler Based on Thermodynamic Vent for Upper-Stage Propulsion System","authors":"Yuya Banno, K. Kinefuchi","doi":"10.2514/1.a35888","DOIUrl":"https://doi.org/10.2514/1.a35888","url":null,"abstract":"Subcooling of cryogenic liquid propellants offers significant advantages for launch vehicles. Liquid subcooling can reduce the extent of cavitation generation in turbopumps, which provides advantages for upper-stage engine reignition in orbit. Additionally, liquid-propellant subcooling densifies the liquid, which can reduce the propellant tank volume and increase launch capability when it is applied during the propellant-filling phase on the ground. Here, a cryogenic propellant subcooling system derived from thermodynamic vent system (TVS) concepts is proposed. In contrast to prior approaches with TVS, the proposed method only focuses on the liquid subcooling and only requires the installation of a heat exchanger at the tank bottom, making it easily applicable to conventional upper stages and enhancing launch capability. First, ground tests were conducted using liquid nitrogen. We introduced energy efficiency to evaluate the subcooler performance, and an optimum point was found for the coolant supply pressure and Joule–Thomson orifice diameter. To investigate the advantages of the proposed method, a theoretical model for the subcooling process before engine reignition in orbit was developed based on experimental observation. The model assuming liquid hydrogen demonstrated an improved weight penalty in the proposed method compared to the conventional vent/pressurization method. A study that quantitatively addresses the enhancement of launch capability through TVS-induced liquid subcooling is unprecedented, paving the way for a new cryogenic propulsion system.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"192 ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-01-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140483947","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

Lambert Property-Based Swarm Search Algorithm for the Multiple-Rendezvous Trajectory Optimization 基于兰伯特属性的蜂群搜索算法用于多交会轨迹优化

Journal of Spacecraft and Rockets Pub Date : 2024-01-30 DOI: 10.2514/1.a35816

Hang Xu, Bin Song, Yanning Guo, Guangfu Ma, Xinglong Li, Lujiang Liu

{"title":"Lambert Property-Based Swarm Search Algorithm for the Multiple-Rendezvous Trajectory Optimization","authors":"Hang Xu, Bin Song, Yanning Guo, Guangfu Ma, Xinglong Li, Lujiang Liu","doi":"10.2514/1.a35816","DOIUrl":"https://doi.org/10.2514/1.a35816","url":null,"abstract":"In this paper, the multiple-rendezvous trajectory optimization problem is studied, which refers to optimizing rendezvous epochs for a single spacecraft to service multiple targets. It is found that the problem has multiple properties, such as a predictable trough number in each dimension. A novel Lambert property-based swarm search algorithm (LPSSA) that incorporates this problem-specific knowledge is proposed to improve efficiency. The design aims to improve the global search capability in the prophase and the local search capability in the anaphase. The algorithm has two different branches and is switched by a proposed complexity index. When the index is relatively large, the initial variables are distributed in some priority trough regions, and the update mechanism is divided into three stages. When the index is relatively small, the initial variables are first distributed to all trough regions and then selected. Multiple subpopulations search independently in the iterative process, and an annexation mechanism is introduced. An improved method for handling boundary conditions is applied in both branches. Besides, the improved mechanisms can also be combined with other swarm search algorithms. Numerical simulations show that the proposed method has a more stable convergence performance and a more optimal solution than the conventional algorithms.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"117 ","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-01-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140481955","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

Patch Antenna Dielectrics Reduction by Topology Optimization and Radio Wave Characteristics 通过拓扑优化和无线电波特性减少贴片天线电介质

Journal of Spacecraft and Rockets Pub Date : 2024-01-30 DOI: 10.2514/1.a35601

A. Torisaka

引用次数: 0

Aerodynamic Characterization of a Generic High-Speed Projectile Configuration 通用高速弹丸配置的气动特性分析

Journal of Spacecraft and Rockets Pub Date : 2024-01-09 DOI: 10.2514/1.a35784

Royce C. Pokela, Rajan Kumar, Joseph D Vasile, J. Despirito

{"title":"Aerodynamic Characterization of a Generic High-Speed Projectile Configuration","authors":"Royce C. Pokela, Rajan Kumar, Joseph D Vasile, J. Despirito","doi":"10.2514/1.a35784","DOIUrl":"https://doi.org/10.2514/1.a35784","url":null,"abstract":"A combined experimental and numerical study was conducted on a generic projectile configuration with low-aspect-ratio fins. The main objectives of this study were to characterize the aerodynamic behavior and validate numerical simulations for a range of Mach numbers (0.4–4) to facilitate an understanding of major flow features such as forebody and fin-generated shock waves, crossflow shear layer vortex, and fin vortex interactions. Measurements included forces and moments, surface oil flow visualization, and high-speed shadowgraph imaging. Numerical simulations were performed using the CFD++ solver. The results showed an excellent match between the experimental and numerical force and moment data. Pressure contours obtained using numerical simulations were integrated to obtain the contributions of individual components toward the total normal force on the body. Flow visualization results show a few complex and interesting flow features, such as shear layer roll-up, crossflow and fin tip vortex interactions, and shock-wave–boundary-layer interactions. The effects of vortex strength and location were analyzed to determine their contributions to the overall forces on the model. The database generated will be very useful for further validation of the numerical tool and a better understanding of vortex-dominated supersonic flows.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"26 4","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-01-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139443489","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

Effects of Orbit Raising and Deorbiting in Source-Sink Evolutionary Models 源汇进化模型中轨道提升和脱轨的影响

Journal of Spacecraft and Rockets Pub Date : 2024-01-07 DOI: 10.2514/1.a35849

Davide Gusmini, Andrea D’Ambrosio, Simone Servadio, P. M. Siew, Pierluigi Di Lizia, Richard Linares

引用次数: 0

Multisensor Integrated Autonomous Navigation Based on Intelligent Information Fusion 基于智能信息融合的多传感器集成自主导航

Journal of Spacecraft and Rockets Pub Date : 2024-01-02 DOI: 10.2514/1.a35585

Ying Yuan, Feng Yu, Hua Zong

{"title":"Multisensor Integrated Autonomous Navigation Based on Intelligent Information Fusion","authors":"Ying Yuan, Feng Yu, Hua Zong","doi":"10.2514/1.a35585","DOIUrl":"https://doi.org/10.2514/1.a35585","url":null,"abstract":"A major inadequacy of the Kalman filter is the necessity of accurate measurement models, which may not be possible in the case of complicated disturbances. A new solution to multisensor integrated autonomous navigation based on intelligent information fusion technology for launch vehicles is proposed in this paper, which can improve navigation performance based on the existing measurement models. Artificial neural networks (ANNs) are designed to discover the hidden relationship between the available data and trajectory parameters. The tracking, telemetry, and control system can provide centimeter-level accuracy of the launch vehicle after every flight. While postprocessing data is irrelevant to real-time navigation using traditional methods, it is crucial for ANNs to learn the rules of information fusion and identify the inaccuracy of the input variables. In this way, artificial-intelligence-modified trajectory parameters are expected to be closer to the truth value. The experimental results indicate that the proposed method can significantly improve navigation performance compared with the unscented Kalman filter, and ANNs can achieve good performance in various situations.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"132 24","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-01-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139453303","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

Editorial 2024 编辑 2024

Journal of Spacecraft and Rockets Pub Date : 2024-01-01 DOI: 10.2514/1.a35970

引用次数: 0