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Aerodynamic Effects of Surface Protuberance Size on Slender-Bodied Supersonic Vehicle 超声速细长体飞行器表面凸起尺寸对气动性能的影响
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-10-18 DOI: 10.2514/1.a35714
Kazuki Nimura, Fumiya Tsutsui, Keiichi Kitamura, Satoshi Nonaka
The presence of protuberances can create an asymmetric flowfield, which contributes to side forces in slender-bodied launch vehicles. In this study, we conduct numerical calculations using a supercomputer at Japan Aerospace Exploration Agency (JAXA) on a slender body with a different-sized protuberance at Mach 1.5 to systematically determine the aerodynamic effects of the protuberance size. The protuberance size is varied in its height and width. According to the results, it is demonstrated that the side force significantly increases when the height of the protuberance increases. This is because, the higher the protuberance, the farther the wake vortex produced by the protuberance moved away from the body. Consequently, the flow asymmetry between the protuberance side and clean side is augmented, and the side force increases. In contrast, the side force is almost constant when only the width of the protuberance is changed. The results of this study indicate that when attaching the protuberance to the vehicles the height of the protuberance should be lowered, and the width of the protuberance should be increased to secure the volume of the protuberance and reduce the increase in side force.
凸起的存在可以产生不对称的流场,这有助于细长体运载火箭的侧力。在本研究中,我们使用日本宇宙航空研究开发机构(JAXA)的超级计算机对具有不同大小凸起的细长物体在1.5马赫下进行数值计算,以系统地确定凸起尺寸对空气动力学的影响。凸起的大小在高度和宽度上是不同的。结果表明,随着凸点高度的增加,侧力显著增大。这是因为,凸起越高,凸起产生的尾流离身体越远。因此,突出侧与干净侧之间的流动不对称性增强,侧力增大。相反,当仅改变突起的宽度时,侧力几乎是恒定的。研究结果表明,在将凸出物固定在车辆上时,应降低凸出物的高度,增大凸出物的宽度,以保证凸出物的体积,减小侧向力的增加。
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引用次数: 0
Scheduling an Agile Multipayload Earth-Observing Satellite 敏捷多载荷地球观测卫星调度
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-10-18 DOI: 10.2514/1.a35726
Wenyuan Zhang, Gangtie Zheng
A highly integrated Earth-observing satellite can possess several maneuverable payloads to perform different missions simultaneously, which brings some challenges to the method of task scheduling. This paper addresses the selection and scheduling problem of an agile satellite with several independently maneuverable optical payloads. Some differences compared to the traditional scheduling problem of agile satellites are presented and considered in a constrained optimization model. A two-stage method is proposed to accomplish the scheduling of the satellite and payloads in different stages. Clusters are generated from preprocessed tasks by a clique partition algorithm, and their centers are used to calculate the pointing direction of the satellite in the first stage. A multiobjective local search algorithm is introduced to schedule tasks in each selected cluster in the second stage. Considering the time-dependent property of the transition time, the problem of determining the start observation time is transformed into linear programming in a proposed insertion operator that guarantees the feasibility of generated solutions. Two types of instances are created and tested to demonstrate the effectiveness of the proposed method, and some analyses are conducted based on the experimental results.
高度集成的对地观测卫星可以同时拥有多个机动载荷执行不同的任务,这给任务调度方法带来了挑战。研究了具有多个独立机动光载荷的敏捷卫星的选择与调度问题。在约束优化模型中,提出并考虑了敏捷卫星调度问题与传统调度问题的区别。提出了一种两阶段调度方法来完成不同阶段的卫星和有效载荷调度。通过团划分算法将预处理后的任务生成聚类,利用聚类中心计算第一级卫星的指向方向。在第二阶段,引入多目标局部搜索算法对所选集群中的任务进行调度。考虑到过渡时间的时变特性,将起始观测时间的确定问题转化为线性规划问题,提出了一种保证生成解的可行性的插入算子。创建了两类实例并进行了测试,验证了所提方法的有效性,并根据实验结果进行了分析。
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引用次数: 0
High Vacuum Capable Fused Filament Fabrication 3D Printer, Part I: Low-Temperature Polymers and Early Lessons Learned 高真空能够熔丝制造3D打印机,第一部分:低温聚合物和早期的经验教训
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-10-18 DOI: 10.2514/1.a35708
Randy Spicer, Fatima Miranda, Tom Cote, Tom Itchkawich, Jonathan Black
On-orbit manufacturing and assembly have become major research and development topics for government and commercial entities seeking the capability to build very large structures in space. Additive manufacturing is well suited to this paradigm since the process is highly automated, produces little material waste, and allows for a large degree of geometric freedom. This paper presents a design for a 3D printer that operates in high vacuum. The vacuum 3D printer has completed multiple thermal vacuum test campaigns, with dozens of parts printed to date using low-temperature thermoplastics. Testing of material coupons shows that samples printed in vacuum have strength properties generally within a standard deviation of samples printed at ambient pressure. The overall results from multiple successful tests of the vacuum 3D printer promote the feasibility of on-orbit additive manufacturing while exposed to the space environment. This paper is part one of a two-part series. Part I presents the results using a low-temperature hotend capable of printing hobby-grade materials and documents some initial findings and lessons learned for applying FFF in vacuum. Part II presents the results for a high-temperature hotend capable of printing engineering grade plastics that are suitable for on-orbit manufacturing. The combined results of the two papers in this series can be used to inform future on-orbit additive manufacturing applications as well as potential uses on future moon missions.
在轨制造和组装已经成为政府和商业实体寻求在太空中建造超大型结构的能力的主要研究和开发主题。增材制造非常适合这种模式,因为该过程高度自动化,产生很少的材料浪费,并且允许很大程度的几何自由度。本文介绍了一种在高真空环境下工作的3D打印机的设计。真空3D打印机已经完成了多次热真空测试,迄今为止使用低温热塑性塑料打印了数十个部件。材料样品的测试表明,在真空中印刷的样品的强度性能通常在环境压力下印刷的样品的标准偏差之内。真空3D打印机多次成功测试的总体结果,提高了空间环境下在轨增材制造的可行性。本文是由两部分组成的系列文章的第一部分。第一部分介绍了使用能够打印业余级材料的低温主机的结果,并记录了在真空中应用FFF的一些初步发现和经验教训。第二部分介绍了一种能够打印适合在轨制造的工程级塑料的高温加热器的结果。本系列中两篇论文的综合结果可用于为未来在轨增材制造应用以及未来月球任务的潜在用途提供信息。
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引用次数: 0
Risk Index for the Optimal Ranking of Active Debris Removal Targets 主动碎片清除目标最优排序的风险指数
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-10-11 DOI: 10.2514/1.a35752
Simone Servadio, Nihal Simha, Davide Gusmini, Daniel Jang, Theodore St. Francis, Andrea D’Ambrosio, Giovanni Lavezzi, Richard Linares
The first step of any active debris removal (ADR) mission is the selection of the target. The optimal choice is to find the most dangerous debris that can be removed considering the chaser spacecraft requirements and mission constraints. After creating a catalog of the current space population in low Earth orbit (LEO), the MIT Monte Carlo Orbital Capacity Assessment Tool (MOCAT-MC) is used to simulate and predict the future space environment and the interaction among the space population. A novel performance index to quantify the criticality of each debris and the risk that it presents to the space environment is proposed. The new risk index considers the proximity of the debris to highly populated regions, its persistence in orbit, its likelihood to collide, and the estimated number and mass of debris that it can generate. The risk index is then optimized to work either with the full space population or a subset of it, where the ranking of risk among debris is highlighted. Multiple risk analyses are proposed in the test cases, where the ranked list of optimal targets is provided.
主动碎片清除(ADR)任务的第一步是目标的选择。考虑到追踪器的要求和任务限制,最优的选择是找到最危险的碎片。在创建当前近地轨道空间人口目录后,利用麻省理工学院蒙特卡罗轨道容量评估工具(MOCAT-MC)对未来空间环境和空间人口之间的相互作用进行模拟和预测。提出了一种新的性能指标来量化每个碎片的临界性及其对空间环境造成的风险。新的风险指数考虑了碎片与人口密集地区的接近程度、在轨道上的持久性、碰撞的可能性以及可能产生的碎片的估计数量和质量。然后对风险指数进行优化,以适用于整个空间人口或其中的一个子集,其中突出显示碎片之间的风险排名。在测试用例中提出了多个风险分析,并给出了最优目标的排序列表。
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引用次数: 1
Space Launch System Unsteady Forces Developed from Unsteady-Pressure-Sensitive-Paint–Based Corcos Model Parameters 基于非定常压力敏感涂料模型参数的航天发射系统非定常力研究
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-10-06 DOI: 10.2514/1.a35670
Francesco Soranna, Patrick S. Heaney, Martin K. Sekula, David J. Piatak, James M. Ramey
During atmospheric ascent, launch vehicles (LVs) experience large dynamic loads at transonic conditions where aerodynamic buffet is most critical. To estimate buffet loads, coupled loads analyses typically utilize suitable forcing functions, called buffet forcing functions (BFFs). One of the key buffet environment contributors is the turbulent boundary layer (TBL) acting on the LV outer skin. The cross-spectral density function of TBL-induced fluctuating pressures can be estimated using the widely accepted Corcos model. In the context of transonic buffet, the performance of this model is not well established, partly because of lack of data. To fill this gap, NASA recently acquired extremely high-spatial-density data for the Space Launch System vehicle using the unsteady-pressure-sensitive-paint (uPSP) optical measurement technique. A methodology is developed for extraction of the Corcos model parameters using these unique data, with a focus on the LV design application. The model hypotheses are verified, and the model parameters are empirically tuned. For selected panels on the vehicle, force coherence factors are derived based on the Corcos model, and the associated panel BFFs are compared to uPSP data. It is shown that the modeled BFFs are in agreement with direct integration of uPSP data, except for regions where pressure fluctuations are spatially nonuniform. In those regions, the Corcos-based BFFs exhibit inherent limitations of BFF estimation methods that rely on discrete pressure measurements. Lastly, extending the present implementation of the Corcos model to frequencies impacted by vortex-shedding phenomena can result in underconservative BFF estimates at the subharmonic of the vortex shedding.
在大气层上升过程中,运载火箭在跨声速条件下承受较大的动载荷,其中气动冲击最为关键。为了估计自助餐载荷,耦合载荷分析通常使用合适的强迫函数,称为自助餐强迫函数(BFFs)。作用于低压外皮的湍流边界层(TBL)是造成冲击环境的关键因素之一。tbl引起的波动压力的交叉谱密度函数可以使用广泛接受的Corcos模型来估计。在跨音速自助餐的情况下,由于缺乏数据,该模型的性能还没有很好地建立。为了填补这一空白,NASA最近使用非稳态压敏涂料(uPSP)光学测量技术为太空发射系统车辆获得了极高的空间密度数据。开发了一种利用这些独特数据提取Corcos模型参数的方法,重点是LV设计应用程序。对模型假设进行了验证,并对模型参数进行了经验调整。对于车辆上选定的面板,基于Corcos模型推导出力相干系数,并将相关面板bff与uPSP数据进行比较。结果表明,除了压力波动空间不均匀的区域外,模型bff与uPSP数据的直接积分一致。在这些地区,基于corcos的BFF表现出依赖于离散压力测量的BFF估计方法的固有局限性。最后,将Corcos模型的实现扩展到受涡脱落现象影响的频率,可以在涡脱落的次谐波处得到欠保守的BFF估计。
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引用次数: 0
Tether System in Martian-Moons-eXploration-Like Mission for Phobos Surface Exploration 火卫一表面探测类火星卫星探测任务中的系绳系统
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-10-06 DOI: 10.2514/1.a35777
Vladimir S. Aslanov
Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.
涵盖航天器、战术和战略导弹系统的进展,包括子系统设计和应用、任务设计和分析、材料和结构、空间科学的发展、空间加工和制造、空间操作以及空间技术在其他领域的应用。
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引用次数: 1
Efficient Two-Way Coupled Analysis of Steady-State Particle-Laden Hypersonic Flows 满载粒子的高超声速稳态流动的高效双向耦合分析
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-10-04 DOI: 10.2514/1.a35731
Andrew Hinkle, Serhat Hosder, Christopher Johnston
A direct solution approach for surface erosion in particle-laden hypersonic flows is extended for use in low-cost two-way coupled solutions of dilute gas-particle flows. The trajectory control volume method, which uses a sparse set of probe particles to predict surface erosion distributions on general vehicles, is reformulated for the solution of source terms by mean trajectory subdivision and computing a flux differencing. The approach is verified successfully against a boundary-layer solution and shown to agree well with experimental measurements. A representative Mars entry case, with conditions and geometry based on the ExoMars Schiaparelli capsule, is solved with the approach to study the impact of two-way coupling on surface heating and erosion. Results indicate that, for realistic loading conditions, heating is largely unmodified compared to one-way coupled results at peak heating trajectory conditions, and no measureable difference is observed in the surface erosion rate. At exaggerated loading conditions high enough to observe coupling effects, the worst-case collisional heating can increase heating by up to 60%.
将载颗粒高超声速流中表面侵蚀的直接求解方法推广到稀气-颗粒流的低成本双向耦合求解中。利用稀疏的探测粒子集来预测一般车辆表面侵蚀分布的轨迹控制体积方法,通过平均轨迹细分和计算通量差分来求解源项。该方法在边界层解上得到了成功的验证,与实验测量结果吻合良好。基于ExoMars Schiaparelli太空舱的条件和几何结构,利用该方法研究了双向耦合对表面加热和侵蚀的影响,解决了具有代表性的火星进入案例。结果表明,在实际加载条件下,与加热轨迹峰值条件下的单向耦合结果相比,加热在很大程度上没有改变,并且表面侵蚀速率没有可测量的差异。在高到足以观察到耦合效应的夸张加载条件下,最坏情况下的碰撞加热可以使加热增加高达60%。
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引用次数: 0
Observed High-Altitude Surface Erosion During the Mars Science Laboratory and Mars 2020 Landings 在火星科学实验室和火星2020登陆期间观测到的高空表面侵蚀
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-09-27 DOI: 10.2514/1.a35748
Jason Rabinovitch, Soleil A. Santana, Christopher D. Karlgaard, Elizabeth T. Jens, Kathryn M. Stack, Daniel M. Turner, Wesley A. Chambers, Manish Mehta, Ashley M. Korzun
Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.
涵盖航天器、战术和战略导弹系统的进展,包括子系统设计和应用、任务设计和分析、材料和结构、空间科学的发展、空间加工和制造、空间操作以及空间技术在其他领域的应用。
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引用次数: 0
Tianwen-1 Entry, Descent, and Landing Guidance, Navigation, and Control System Design and Validation 天文一号进入、下降和着陆制导、导航和控制系统的设计和验证
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-09-25 DOI: 10.2514/1.a35673
Xiangyu Huang, Chao Xu, Minwen Guo, Maodeng Li, Jinchang Hu, Xiaolei Wang, Yu Zhao, Wangwang Liu
On 15 May 2021, the Tianwen-1 mission delivered a lander and the Zhurong rover to the Mars surface, which made China the second nation to successfully land and place a rover on that planet. The guidance, navigation, and control (GNC) system for the entry, descent, and landing (EDL) of the Tianwen-1 mission play keys role in guaranteeing a successful landing. In this paper, the Tianwen-1 EDL GNC system design is presented, including the GNC architecture, scheme, and algorithm; additionally, the system is validated through experimental tests, numerical simulations, and actual flight results from telemetry data.
2021年5月15日,“天文一号”任务将着陆器和朱荣探测器送到火星表面,这使中国成为第二个成功在火星上着陆并放置探测器的国家。天文一号任务的进入、下降和着陆(EDL)的制导、导航和控制(GNC)系统在保证成功着陆中起关键作用。本文介绍了天文一号EDL GNC系统的设计,包括GNC体系结构、方案和算法;此外,该系统还通过实验测试、数值模拟和遥测数据的实际飞行结果进行了验证。
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引用次数: 0
Comparison of Corcos-Based and Experimentally Derived Coherence Factors for Buffet Forcing Functions 基于corcos的与实验推导的Buffet强迫函数相干系数的比较
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-09-25 DOI: 10.2514/1.a35671
Francesco Soranna, Patrick S. Heaney, Martin K. Sekula, David J. Piatak, James M. Ramey
In this paper, high-spatial-resolution unsteady pressure-sensitive paint (UPSP) data are utilized to compare two methods for panel buffet forcing function (BFF) estimation for the Space Launch System (SLS). Such methods are based on discrete pressure measurements within a panel but employ coherence factors to account for partially correlated fluctuating pressures across the whole panel. In one method, coherence factors are derived based on the Corcos model, whereas the second method utilizes experimentally derived coherence factors. To simulate discrete measurements using UPSP data, suitable subsets of the data are extracted. When full UPSP resolution is retained, UPSP data provide a benchmark to assess discrete-measurement-based methods. The analysis focuses on the peak SLS buffet environment located downstream of the forward attachment hardware (FAH) between the core stage and solid rocket boosters. Trends of the Corcos-based and experimentally derived coherence factors are in reasonable agreement with the benchmark. However, at certain frequencies, experimentally derived coherence factors are sensitive to the separation distance between pressure measurements utilized to compute coherence lengths. Such sensitivity originates from deviation of the experimentally based coherence function from an exponential decay assumption. On the other hand, the present implementation of the Corcos model fails to capture certain nonturbulent boundary-layer-related environments, such as a subharmonic of FAH vortex shedding. For all methods presented in this paper, at near-transonic conditions, increased pressure coherence and spatial nonuniformity lead to BFF overestimation and sensitivity to the pressure measurement location within the panel.
本文利用高空间分辨率非定常压敏喷漆(UPSP)数据,比较了两种估算航天发射系统(SLS)面板冲击强迫函数(BFF)的方法。这种方法基于面板内的离散压力测量,但采用相干因素来解释整个面板上部分相关的波动压力。其中一种方法是基于Corcos模型推导相干因子,而第二种方法是利用实验推导的相干因子。为了模拟使用UPSP数据的离散测量,提取了合适的数据子集。当保留完整的UPSP分辨率时,UPSP数据为评估基于离散测量的方法提供了基准。分析的重点是位于核心级和固体火箭助推器之间的前附体硬件(FAH)下游的峰值SLS冲击环境。基于corcos和实验推导的相干因子趋势与基准基本一致。然而,在某些频率下,实验推导的相干系数对用于计算相干长度的压力测量之间的分离距离敏感。这种灵敏度源于基于实验的相干函数与指数衰减假设的偏差。另一方面,目前的Corcos模型无法捕获某些与边界层相关的非湍流环境,例如FAH涡脱落的次谐波。对于本文提出的所有方法,在近跨音速条件下,压力相干性和空间非均匀性的增加导致BFF高估和对面板内压力测量位置的敏感性。
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引用次数: 0
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Journal of Spacecraft and Rockets
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