Journal of Spacecraft and Rockets最新文献_第2页

Durability of Passive Thermal Control Materials Exposed to Low-Earth-Orbital Environment 暴露在低地球轨道环境中的被动热控材料的耐久性

Journal of Spacecraft and Rockets Pub Date : 2024-07-01 DOI: 10.2514/1.a36021

M. Finckenor, Meghan Carrico

引用次数: 0

Acquisition of Objects in Cislunar Space with Small Spaceborne Telescope 用小型星载望远镜获取太阳系空间的天体

Journal of Spacecraft and Rockets Pub Date : 2024-07-01 DOI: 10.2514/1.a35951

William Priedhorsky, Yancey H. Sechrest, Marion Vance, Christian Ward, Przemek Wozniak

引用次数: 0

Microscale Thermal–Structural Modeling for Carbon Fibers Subjected to a Hypersonic Boundary Layer 受高超音速边界层影响的碳纤维的微尺度热结构建模

Journal of Spacecraft and Rockets Pub Date : 2024-05-17 DOI: 10.2514/1.a35916

Rui Fu, Alexandre Martin, Sahadeo Ramjatan, Michael Kroells, Thomas E. Schwartzentruber

{"title":"Microscale Thermal–Structural Modeling for Carbon Fibers Subjected to a Hypersonic Boundary Layer","authors":"Rui Fu, Alexandre Martin, Sahadeo Ramjatan, Michael Kroells, Thomas E. Schwartzentruber","doi":"10.2514/1.a35916","DOIUrl":"https://doi.org/10.2514/1.a35916","url":null,"abstract":"With regard to the thermal protection system, the thermal–structural responses of modern ablative materials are of primary importance in many aspects, including material selection and sizing. Due to the intricate nature of their porous structure and complicated thermal conditions they are subjected to, ablative materials may exhibit unexpected behavior, which can potentially lead to material failure. In this study, two solvers—a direct simulation Monte Carlo solver and a finite-volume-based material response solver—are coupled together to predict the microscale thermal–structural performance of a thermal protection system material like phenolic impregnated carbon ablator. In this approach, individual fibers are modeled at the microscale, which provides valuable knowledge of porous media behavior. Nonuniform boundary conditions, including the heat flux and external force, are captured by the direct simulation Monte Carlo solver, and the detailed thermal and structural performance of the fiber is captured by the material response solver. The results show that individual fibers do not fail based on the temperature gradient and applied aerodynamic forces. However, it is shown that the attachment points of the fibers are the most vulnerable. This vulnerability can potentially lead to a breakdown of the binders, which would separate fibers and cause material failure.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"45 13","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140966053","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

Numerical Study of Supersonic Jet Characteristics of Underwater Solid Rocket Engine 水下固体火箭发动机超音速喷流特性的数值研究

Journal of Spacecraft and Rockets Pub Date : 2024-05-17 DOI: 10.2514/1.a36056

Yiqing Li, Ranhui Liang, Pin Lv, Zhitan Zhou, Dehua Cao

{"title":"Numerical Study of Supersonic Jet Characteristics of Underwater Solid Rocket Engine","authors":"Yiqing Li, Ranhui Liang, Pin Lv, Zhitan Zhou, Dehua Cao","doi":"10.2514/1.a36056","DOIUrl":"https://doi.org/10.2514/1.a36056","url":null,"abstract":"The structure of the rocket supersonic jet changes periodically when the solid rocket engines are ignited underwater. To investigate the flowfield structure and thrust characteristics of underwater gas jets emanating from solid rocket engines, this study establishes a numerical model for the multiphase flow of underwater jets based on the volume of fluid and realizable [Formula: see text] models. The effectiveness of the model is validated through comparison with experimental data. Subsequently, numerical simulations of tail jets from solid rocket engines are conducted at different water depths. The results indicate that during the underwater operation of solid rocket engines, the tail jet undergoes periodic processes such as expansion, constriction, rupture, and recoil. At larger depths, the environmental pressure exerts a more significant effect on the gas jet, thus resulting in a slower axial development of gas bubbles but more significant periodic evolution processes. Unlike the case in air, the thrust of solid rocket engines oscillates significantly when ignited underwater. In deeper water environments, the engine thrust presents a smaller oscillation amplitude. The findings of this study provide a theoretical basis for the design of solid rocket engines ignited underwater.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"47 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140965951","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 Protuberances on Surface Loads on the Vega-C Launch Vehicle 凸起对织女星-C 运载火箭表面载荷的影响

Journal of Spacecraft and Rockets Pub Date : 2024-05-17 DOI: 10.2514/1.a35908

Mirko Leopardi, R. Paciorri, A. Assonitis, Agostino Neri, Daniele Barbagallo

{"title":"Effects of Protuberances on Surface Loads on the Vega-C Launch Vehicle","authors":"Mirko Leopardi, R. Paciorri, A. Assonitis, Agostino Neri, Daniele Barbagallo","doi":"10.2514/1.a35908","DOIUrl":"https://doi.org/10.2514/1.a35908","url":null,"abstract":"The need to meet the demands of the aerospace market in terms of payload capability, mission flexibility, and cost reduction has led the European Space Agency to develop Vega-C as an evolution of the original Vega launcher. The design of a modern launch vehicle like the Vega-C requires accurate evaluation of the thermal and mechanical loads on its surface under conditions as close as possible to real flight conditions. Despite its apparently simple aeroshape, the Vega-C surface is characterized by the presence of antennas, wiring ducts, flanges, and retrorockets. These protuberances interact with the external supersonic stream during the launcher’s flight, giving rise to locally complex flows that can impose stresses on the launcher structure through the generation of severe mechanical and thermal loads. The present work focuses on an in-depth aerothermal analysis of Vega-C protuberances under specific flight conditions. Numerical computations are carried out using the commercial solver [Formula: see text] on multiblock structured Chimera grids to assess which protuberances are subject to the most severe surface loads. Particular emphasis is placed on the role of boundary-layer thickness in the heat flux and pressure peaks that occur on the protuberances.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"3 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140963033","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

Small Solid-Model Rocket Design and Soft Landing Trajectory Planning 小型固体模型火箭设计与软着陆轨迹规划

Journal of Spacecraft and Rockets Pub Date : 2024-05-13 DOI: 10.2514/1.a35919

Nuo Chen, Shang Liu, Xiang Zhou, Hong-bo Zhang

引用次数: 0

Commissioning of Upgrades to T6 to Study Giant Planet Entry 为研究巨行星进入而对 T6 进行的升级投入使用

Journal of Spacecraft and Rockets Pub Date : 2024-05-13 DOI: 10.2514/1.a35893

J. Steer, P. Collen, Alex B. Glenn, Chris Hambidge, L. Doherty, Matthew McGilvray, T. Sopek, Stefan Loehle, Louis Walpot

{"title":"Commissioning of Upgrades to T6 to Study Giant Planet Entry","authors":"J. Steer, P. Collen, Alex B. Glenn, Chris Hambidge, L. Doherty, Matthew McGilvray, T. Sopek, Stefan Loehle, Louis Walpot","doi":"10.2514/1.a35893","DOIUrl":"https://doi.org/10.2514/1.a35893","url":null,"abstract":"The scientific potential of a mission to the ice giants is well recognized and has been identified by NASA and ESA as a high priority on several occasions, most recently in the 2023–2032 Decadal Survey. The payload capacity of such a spacecraft is limited by the heat shield thickness, which must be sized conservatively due to a lack of reliable data for convective and radiative heat flux along the proposed entry trajectories. Major upgrades to the Oxford T6 Stalker Tunnel have been commissioned that allow study of giant planet entry trajectories, including a flammable gas handling system, a Mach 10 expansion nozzle, and a steel shock tube with optical access. Initial testing has been completed in shock tube and expansion tunnel modes, with peak shock speeds of 18.9 km/s achieved. Convective heat flux and surface pressure were measured at several locations on a 45° sphere cone model in expansion tunnel mode. Measurements of the radiating shock layer were made in shock tube mode to assess the effect of [Formula: see text] concentration. This work establishes the first high-enthalpy giant planet entry test bed in Europe.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"2 3","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140982576","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

Preflight and Postflight Thermal/Structural Analysis of BOLT-2: The Holden Mission BOLT-2：霍尔登飞行任务的飞行前和飞行后热能/结构分析

Journal of Spacecraft and Rockets Pub Date : 2024-05-12 DOI: 10.2514/1.a35978

Bradley M. Wheaton, Aaron T. Dufrene

{"title":"Preflight and Postflight Thermal/Structural Analysis of BOLT-2: The Holden Mission","authors":"Bradley M. Wheaton, Aaron T. Dufrene","doi":"10.2514/1.a35978","DOIUrl":"https://doi.org/10.2514/1.a35978","url":null,"abstract":"BOLT-2: The Holden Mission, a follow-on to the BOLT experiment, was designed to measure the characteristics of turbulent flow in the hypersonic flight regime. This paper summarizes preflight transient thermal and structural analyses for the predicted flight trajectories that led to the selection of suitable materials for the flight experiment. Following the successful flight in March 2022, the preflight analysis methods, along with temperature measurements from the flight, were used to conduct a postflight thermal analysis based on the as-flown trajectory that attempted to match the flight data. Conservatism in the preflight design analysis was compared to the flight measurements. Databases of computed laminar and turbulent heating were generated as part of this effort that can aid in future analysis of the experimental data. The effects of modeling transitional heating during ascent were quantified when compared to a fully turbulent heating assumption. A set of estimated three-dimensional surface temperature distributions have been computed and were found to be a good match to the available flight data. Postflight structural modeling was used to estimate the differential thermal expansion at the nosetip/frustum joint interface.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"123 46","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140986334","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

Parameters Influencing the Effectiveness of Reaction Control Jets on the Basic Finner 影响基本芬纳喷气机反作用力控制效果的参数

Journal of Spacecraft and Rockets Pub Date : 2024-05-12 DOI: 10.2514/1.a35911

Phillip M. Munday, Kevin C. Massey

{"title":"Parameters Influencing the Effectiveness of Reaction Control Jets on the Basic Finner","authors":"Phillip M. Munday, Kevin C. Massey","doi":"10.2514/1.a35911","DOIUrl":"https://doi.org/10.2514/1.a35911","url":null,"abstract":"Reaction control jets provide a practical option to increase the acceleration rates of high-performance aerodynamic vehicles. Unfortunately, a designer or system engineer incorporating reaction control jets into a design cannot simply add the jet as a point force because it does not account for the change in force due to the modifications of the flowfield caused by the jet. The changes made to the flowfield can impact the forces and moments, enhancing, mitigating, or even reversing the desired force or moment, depending on a complex set of factors. This study examines the influence of different jet configurations, modifications to freestream parameters, and the presence of control surfaces on the body. It is shown that the proximity of the jet to the control surfaces has the most significant impact on the resulting force amplification. The emphasis is placed on differentiating between how the jet interacts with the body and fins. Ultimately, this shows that the interaction with the fuselage is consistent and self-similar, whereas the fins are primarily influenced by the jet blocking the flow and generating a shock that imparts high pressure on the control surface, increasing the force in the direction of the jet.","PeriodicalId":508266,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"123 26","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140986233","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

Study on Parameters Influencing Heat Dissipation Performance of Body-Mounted Fluid Tube Radiators 影响体装式流体管散热器散热性能的参数研究

Journal of Spacecraft and Rockets Pub Date : 2024-05-12 DOI: 10.2514/1.a35961

Bangxiang Che, Haiying Han, Xianlin Wu, Lei Huang, Hongyang Zheng

引用次数: 0