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Reaching Mars: Medical risks and potential surgical conditions in the Martian environment and during long-duration spaceflight 到达火星:火星环境和长时间航天飞行期间的医疗风险和潜在手术条件
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2024.09.002
Dora Babocs , Angela Preda , Rowena Christiansen
Compared to lunar missions, Mars missions will pose additional challenges. This includes a longer duration (currently anticipated to take around three years for a return mission), and a hazardous Martian environment with 0.38 Earth gravity, a thin atmosphere, and a weak magnetosphere. These factors contribute to extreme weather conditions, and significant exposure to space radiation. Evacuation to Earth for medical treatment will be impractical, rendering the capability to provide surgical interventions absolutely necessary. This paper is part of an ongoing scoping review of relevant published scientific literature to identify medical conditions that might require operative or non-operative surgical solutions during long-duration spaceflight. In the context of potential future Mars missions, onboard acute conditions, or newly developed chronic diseases (Type 1), and Mars surface/environment-related surgical conditions (Type 2), provide relevant considerations for future mission planning and crew safety. (Type 1) During long-duration spaceflight, exposure to space radiation and microgravity affects every organ system. This may result in a broad range of medical events requiring diverse operative or non-operative surgical interventions. The likelihood of acute life-threatening events (Type 1a.) is increased, and newly developed chronic diseases (Type 1b.) may also occur. If asymptomatic, but untreated, secondary sudden surgical emergencies may result. On reaching Mars (Type 2), reintroduction of partial gravity (0.38 G), flight-related reduced bone mineral density and potential changes in muscle mass, might lead to increased risk of lumbar disc herniations and traumatic injuries such as fractures. Without adequate space radiation shielding, surface conditions will likely increase the risk for development of malignancies and eye diseases such as cataracts. Communication delays (as long as 24 min each way) will require any immediate medical emergency to be managed in-situ by the expeditioners. Remotely operated robotic surgery is not currently feasible, as any communication lag >100 ms will cause a perceptible delay, potentially affecting surgical outcomes. The provision of healthcare for Mars missions will face unique challenges in terms of both a hostile and extreme environment, and a remote and isolated location without real-time Earth communication. The medical team will need to be equipped to manage a very wide range of health conditions, including low acuity, chronic, and high acuity life-threatening issues, with some potentially requiring surgical intervention. Issues for the treating team include appropriate skill sets and access to medical guidance, facilities, equipment and supplies, and available pharmaceuticals. These significant challenges underlie the importance of adequate anticipation, preparation and planning for the healthcare needs of Mars explorers.
与月球任务相比,火星任务将带来额外的挑战。这包括一个更长的持续时间(目前预计需要大约三年的返回任务),一个危险的火星环境,0.38地球引力,稀薄的大气层,弱磁层。这些因素造成了极端的天气条件和严重的空间辐射暴露。撤离到地球接受治疗将是不切实际的,因此提供外科手术干预的能力是绝对必要的。本文是正在进行的一项范围审查的一部分,该审查是对相关已发表的科学文献进行的,目的是确定在长时间航天飞行期间可能需要手术或非手术手术解决方案的医疗状况。在潜在的未来火星任务背景下,机载急性疾病或新发展的慢性病(第一类)以及火星表面/环境相关的外科手术条件(第二类)为未来的任务规划和机组人员安全提供了相关考虑因素。在长时间的太空飞行中,暴露在太空辐射和微重力下会影响每个器官系统。这可能导致广泛的医疗事件需要不同的手术或非手术手术干预。急性危及生命事件(1a型)的可能性增加,也可能发生新发展的慢性疾病(1b型)。如果无症状,但未经治疗,可能会导致继发性突发手术。到达火星(2型)后,部分重力(0.38 G)的重新引入,与飞行相关的骨密度降低和肌肉质量的潜在变化,可能导致腰椎间盘突出和骨折等创伤性损伤的风险增加。如果没有足够的空间辐射屏蔽,表面条件可能会增加恶性肿瘤和白内障等眼疾的发生风险。通信延迟(单程长达24分钟)将要求探险队在现场处理任何紧急医疗情况。远程操作的机器人手术目前还不可行,因为任何100毫秒的通信延迟都会造成可察觉的延迟,潜在地影响手术结果。在恶劣和极端的环境以及没有实时地球通信的偏远和孤立位置,为火星任务提供医疗保健将面临独特的挑战。医疗团队将需要装备来管理非常广泛的健康状况,包括低敏锐度,慢性和高敏锐度危及生命的问题,有些可能需要手术干预。治疗小组面临的问题包括适当的技能组合和获得医疗指导、设施、设备和用品以及现有药品的机会。这些重大挑战凸显了充分预测、准备和规划火星探险者保健需求的重要性。
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引用次数: 0
Attitude estimation from photometric data using Gaussian process regression 利用高斯过程回归对光度数据进行姿态估计
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2025.02.008
Ryui Hara, Yasuhiro Yoshimura, Toshiya Hanada
The rapid growth of resident space objects in Earth’s orbit has intensified the need for advanced space situational awareness and space domain awareness to manage satellite traffic and prevent collisions. Attitude estimation is critical for accurate state propagation, as non-gravitational forces like solar radiation pressure and atmospheric drag depend on the object’s attitude. This study explores using light curves, time variation of an object’s brightness, to estimate a space object’s attitude. Light curve inversion, traditionally used in astronomy, faces challenges when applied to resident space objects due to their non-convex shapes and specular reflections. Conventional methods for attitude estimation often assume known shape and surface parameters, which are usually unknown for space debris generated by a collision or breakup. To address this issue, this study proposes the estimation method combining Gaussian process regression with the unscented Kalman filter. This study uses Gaussian process regression for a non-parametric observation model, enhancing robustness against unknown surface parameters. Numerical examples consider a box-wing object in a geosynchronous orbit and demonstrate that the proposed method has better estimation accuracy than a conventional unscented Kalman filter. The numerical simulation results also represent the attitude estimation robust against uncertainties in surface properties, contributing to practical scenarios in space situational awareness and space domain awareness where the object parameters are unknown.
地球轨道上驻留空间物体的快速增长,加强了对先进空间态势感知和空间域感知的需求,以管理卫星交通和防止碰撞。姿态估计对于精确的状态传播至关重要,因为太阳辐射压力和大气阻力等非引力取决于物体的姿态。这项研究探索了使用光曲线,即物体亮度的时间变化,来估计空间物体的姿态。传统上用于天文学的光曲线反演,由于其非凸形状和镜面反射,在应用于驻留空间物体时面临挑战。传统的姿态估计方法通常假定已知的形状和表面参数,而对于碰撞或破裂产生的空间碎片来说,这些参数通常是未知的。针对这一问题,本文提出了高斯过程回归与无气味卡尔曼滤波相结合的估计方法。本研究将高斯过程回归用于非参数观测模型,增强了对未知表面参数的鲁棒性。以地球同步轨道上的一个箱翼目标为例,数值算例表明,该方法比传统的无气味卡尔曼滤波具有更好的估计精度。数值模拟结果也表明姿态估计对表面特性的不确定性具有鲁棒性,有助于在物体参数未知的空间态势感知和空间域感知中实现实际场景。
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引用次数: 0
Iterating on a design – further developments in the evolution of the ballistic limit equations for the Mars Sample Return Project 设计的迭代——火星样本返回计划弹道极限方程演化的进一步发展
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2024.12.004
William P. Schonberg , Michael Squire
The goal of the Mars Sample Return–Capture, Containment, and Return System Project is to retrieve samples launched from the Martian surface and return them to Earth for detailed analysis. An important part of this project is the design of the system's micrometeoroid protection system, which protects the Earth Entry System and the collected samples during their journey back to Earth. As mission parameters and the micrometeoroid and orbital debris threat became better understood, the design of the micrometeoroid protection system evolved. A key element used in the shield development process is the ballistic limit equation, which is an equation that is used to determine whether or not a particular structural element or system will end up in a failed state as a result of a specified impact. As the design of the Earth Entry System and the micrometeoroid protection system evolved, a new set of ballistic limit equations was needed to better predict and assess the performance of developing shield system designs in anticipation of possible damage from micrometeoroid and orbital debris particle impacts. This paper provides a summary of how a set of initial BLEs were either extended or modified so that the resulting equations were better suited to new types of target configurations being considered, as well as how additional ballistic limit equations were developed where none previously existed.
火星样本回收、捕获、遏制和返回系统项目的目标是从火星表面回收发射的样本,并将其返回地球进行详细分析。该项目的一个重要组成部分是系统的微流星体保护系统的设计,该系统在地球进入系统和收集的样本返回地球的过程中保护它们。随着任务参数以及对微流星体和轨道碎片威胁的进一步了解,微流星体防护系统的设计也在不断发展。在盾构开发过程中使用的一个关键要素是弹道极限方程,该方程用于确定特定结构元件或系统是否会由于特定的冲击而最终处于失效状态。随着地球入口系统和微流星体防护系统设计的不断发展,需要一套新的弹道极限方程来更好地预测和评估正在开发的防护系统设计的性能,以预测微流星体和轨道碎片粒子撞击可能造成的损害。本文概述了如何对一组初始极限方程进行扩展或修改,以使所得到的方程更适合所考虑的新型目标构型,以及如何在以前没有弹道极限方程的情况下开发额外的弹道极限方程。
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引用次数: 0
Developing the IAASS Space Safety Academy 建设航天安全研究院
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2024.12.001
Tommaso Sgobba
The International Association for the Advancement of Space Safety (IAASS) has identified safety education as a key enhancer of system safety. Space safety design criteria, methods and hazard analyses techniques are not generally taught in depth as part of typical university education; however, both manned and unmanned space programs require familiarity with modern risk-based design techniques and with hazard control approaches. The IAASS Space Safety Academy (ISSA) is being established as the center of excellence in space safety education and professional training. The ISSA mission is to make available basic multidisciplinary knowledge in the field of space safety to aerospace engineering postgraduate and undergraduate students. The key ISSA program is a 10-week in-class certificate program in space safety (1/2 Master) organized in cooperation with major academic institutions in Europe, Americas, and Asia. The ISSA will also provide remote undergraduate level courses in space safety as well as in-class and remote on site and web-based professional training courses in space safety. The article provides an overview of the certificate program and of its multidisciplinary structure.
国际空间安全促进协会(IAASS)已将安全教育确定为系统安全的关键增强器。空间安全设计标准、方法和危害分析技术一般不作为典型大学教育的一部分进行深入教授;然而,载人和无人航天计划都需要熟悉现代基于风险的设计技术和危险控制方法。建立国际航天科学院空间安全学院,作为空间安全教育和专业培训的卓越中心。ISSA的任务是向航空航天工程研究生和本科生提供空间安全领域的基本多学科知识。ISSA重点项目是与欧洲、美洲和亚洲的主要学术机构合作组织的为期10周的空间安全(1/2硕士)课堂证书项目。国际空间研究所还将提供空间安全方面的远程本科课程,以及空间安全方面的课堂和远程现场和网络专业培训课程。文章提供了一个概述的证书程序和它的多学科结构。
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引用次数: 0
Professional technical training: Educating the professional community on space safety best practices 专业技术培训:就空间安全最佳做法对专业社区进行教育
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2025.03.001
Paul Kirkpatrick
The International Association for the Advancement of Space Safety (IAASS) offers a myriad of courses to educate the space community on safety engineering concepts and accepted best practices. Space safety concepts and methodologies are critical for the safety of occupants and the uninvolved public, alike, yet are not standard contents in academic programs for space science. The IAASS considers the education of the workforce among its core goals and fulfills that mission through the IAASS training academy.
国际促进空间安全协会(IAASS)提供了许多课程,向空间界传授安全工程概念和公认的最佳做法。空间安全概念和方法对居住者和未参与的公众的安全至关重要,但在空间科学学术课程中却不是标准内容。IAASS将劳动力教育视为其核心目标之一,并通过IAASS培训学院实现这一使命。
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引用次数: 0
Application of Re-entry survivability analysis tool to mars planetary protection 再入生存能力分析工具在火星行星保护中的应用
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2025.02.005
Kenichi Sato , Tsutomu Matsumoto , Takashi Ozawa , Toru Yoshihara , Kazuko Hagiwara , Satoshi Kobayashi
JAXA develops the Object Re-entry Survival Analysis Tool - Japan (ORSAT-J), which is a tool to assess the survivability and risk to the ground of objects re-entering from low Earth orbit. This tool is derived from NASA's ORSAT ver. 4.
ORSAT-J can calculate the temperature of an entering object during its entry into a celestial body with respect to the elapsed time. Therefore, in terms of planetary protection, it could be used to evaluate whether aerodynamic heating during celestial entry is sufficient for sterilization in the event of an Earth-derived spacecraft entering into a celestial body due to an accidental event. JAXA plans some Martian biosphere exploration missions such as the MMX mission, and is aiming to build a tool that can easily analyse the aerodynamic heating during Mars entry.
In this paper, we collected and evaluated the information such as celestial geometry, gravity model, atmospheric model, radiative heating, etc. necessary to perform a Mars entry heating analysis with ORSAT-J. These were applied to the code and compared with the measured data of Schiaparelli of the ExoMars Program. The novelty of this paper is that it introduces a comprehensive analysis method for Mars entry, including trajectory and heating simulations, into a simplified survivability analysis tool for the on-ground risk of re-entry into Earth.
JAXA开发了物体再入生存分析工具-日本(ORSAT-J),该工具用于评估从低地球轨道再入的物体的生存能力和对地面的风险。这个工具来自美国宇航局的ORSAT卫星。4.ORSAT-J可以计算进入天体的物体在进入天体期间的温度与经过的时间的关系。因此,在行星保护方面,可以用来评估在地球源航天器因意外事件进入天体时,进入天体时的气动加热是否足以进行灭菌。JAXA计划一些火星生物圈探测任务,如MMX任务,并旨在建立一个工具,可以很容易地分析进入火星时的空气动力学加热。本文利用ORSAT-J收集并评估了进行火星入口加热分析所需的天体几何、重力模型、大气模型、辐射加热等信息。将这些数据应用于代码中,并与ExoMars计划的Schiaparelli测量数据进行了比较。本文的新颖之处在于,将一种综合的火星进入分析方法,包括轨道和加热模拟,引入到一个简化的再入地球地面风险的生存能力分析工具中。
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引用次数: 0
Master of Science in Astronautical Engineering degree at the University of Southern California for the space industry 南加州大学航天工程硕士学位
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2024.07.007
Mike Gruntman
The Department of Astronautical Engineering at the University of Southern California (USC) focuses on space engineering education. It is a unique space-engineering program in the United States where such studies usually constitute parts of aerospace departments. In addition to full-time on-campus students, its flagship Master of Science in Astronautical Engineering degree program reaches working professionals online through distance education. The growth of this space-focused graduate degree program led to the establishment of a new independent department at USC twenty years ago in 2004. Since its founding, this Department of Astronautical Engineering awarded nearly one thousand Master's degrees to students from across the United States, Canada, and selected locations abroad. The article describes the origin, rationale, focus, structure, coursework, and reach of USC's Master of Science in Astronautical Engineering program. It concludes with the lessons learned in program development which contributed to its success.
南加州大学(USC)的航天工程系专注于空间工程教育。在美国,这是一个独特的空间工程项目,这类研究通常是航空航天部门的一部分。除了全日制在校学生外,其旗舰的航天工程理学硕士学位课程通过远程教育在线为工作专业人员提供服务。这个以太空为重点的研究生学位项目的发展,促使南加州大学在20年前的2004年建立了一个新的独立部门。自成立以来,航天工程系向来自美国、加拿大和国外选定地区的学生颁发了近1000个硕士学位。本文描述了南加州大学航天工程硕士项目的起源、基本原理、重点、结构、课程和范围。它总结了在程序开发中吸取的经验教训,这些教训有助于它的成功。
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引用次数: 0
Autonomous flight termination system: A proposal for an international regulatory frame and set of requirements 自主飞行终端系统:国际监管框架和一套要求的建议
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2025.02.003
F. Pasciuti, G. Acampa, M. Cinque, W. Dai, G.T. Kuthukallumkal, A. Scolaro, R. Armellini
Current trends in the Space Industry show that launcher providers are moving towards the automatization of Flight Termination Systems (AFTS). Nevertheless, nowadays a problem arises when trying to conceive an AFTS which can be compliant with all the relevant international safety regulations.
A previous study [12], starting from differences existing among those legislations that more explicitly refer to Flight Termination Systems, has identified and highlighted the key needs and concepts an AFTS should fulfill.
Therefore, starting from the proposed regulatory guideline, a further step is moved hereinafter for building up a set of generic (not mission dependent) requirements matching with the above-mentioned needs and concepts.
The resulting requirements here proposed are meant to be set as a starting point for the agreement, among industries and safety authorities, on a common specification for developing an AFTS suitable to all launch sites, with greater range of mission trajectories and cadences allowed.
航天工业目前的趋势表明,发射装置供应商正朝着飞行终端系统(AFTS)的自动化方向发展。然而,如今,当试图构思一个符合所有相关国际安全法规的AFTS时,出现了一个问题。先前的一项研究[12],从那些更明确地提到飞行终止系统的立法之间存在的差异开始,已经确定并强调了AFTS应该满足的关键需求和概念。因此,从拟议的监管指南开始,下文将进一步建立一套与上述需求和概念相匹配的通用(非任务相关)要求。这里提出的最终要求旨在作为工业界和安全当局之间协议的起点,就开发适用于所有发射场的AFTS的共同规范,允许更大范围的任务轨迹和节奏。
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引用次数: 0
Ionospheric GPS-VTEC forecasting using hybrid deep learning model (LSTM-CNN) 基于LSTM-CNN混合深度学习模型的电离层GPS-VTEC预测
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2024.11.004
Kenneth Iluore , Jianyong Lu , Kesyton Oyamenda Ozegin
Predictions of the ionosphere are essential for detecting anomalies in space weather conditions. Deep learning technologies applied to ionospheric forecasting have emerged as an exciting field of focus for researchers. This paper presents the forecasting of GPS-VTEC using multilayer perceptron (MLP) and the deep learning model: long short-term memory (LSTM), gated recurrent unit (GRU), and a hybrid model composed of LSTM and a convolutional neural network (CNN). The MLP and the deep learning model are constructed with the GPS-vertical total electron content (GPS-VTEC) time series data estimated over a mid-latitude HUGE Station (47.834oN,7.596oE) located in Germany. Factors that influence the variations of GPS-VTEC are identified and used as the input parameters for the deep learning model. The factors are seasonal variation, diurnal variation, magnetic activity, and solar activity. The training is carried out using the data obtained from the years 2010–2014, while the prediction performance of the model is evaluated using the data from the year 2015 (high solar activity). The hybrid LSTM-CNN model performs better than the MLP and the other deep learning model, with a root mean square error (RMSE) of 3.046 total electron content unit (TECU) and a correlation coefficient (R) of 0.896 and is able to capture the diurnal variations of the GPS-VTEC. In addition, the prediction performance of the MLP and the deep learning model is compared with that of IRI-Plas 2017 and NeQuick-2 in capturing the seasonal variation of GPS-VTEC, and it is observed that the IRI-Plas 2017 model provides more accurate predictions than the MLP, the deep learning model, and the NeQuick-2 model during March 2015. However, on average, the deep learning model, the MLP, and the NeQuick-2 model capture the seasonal variations more accurately than the IRI-Plas 2017 at this GPS station.
电离层的预测对于探测太空天气条件的异常是必不可少的。应用于电离层预测的深度学习技术已经成为研究人员关注的一个令人兴奋的领域。本文利用多层感知器(MLP)和深度学习模型:长短期记忆(LSTM)、门控循环单元(GRU)以及LSTM和卷积神经网络(CNN)组成的混合模型对GPS-VTEC进行预测。MLP和深度学习模型是利用德国一个中纬度HUGE站(47.834oN,7.596oE)的gps -垂直总电子含量(GPS-VTEC)时间序列数据构建的。确定了影响GPS-VTEC变化的因素,并将其用作深度学习模型的输入参数。这些因素包括季节变化、日变化、地磁活动和太阳活动。使用2010-2014年的数据进行训练,使用2015年(太阳活动高)的数据评估模型的预测性能。LSTM-CNN混合模型表现优于MLP和其他深度学习模型,其均方根误差(RMSE)为3.046总电子含量单位(TECU),相关系数(R)为0.896,能够捕捉GPS-VTEC的日变化。此外,将MLP和深度学习模型与IRI-Plas 2017和nequick2模型在捕获GPS-VTEC季节变化方面的预测性能进行了比较,发现IRI-Plas 2017模型在2015年3月期间的预测精度高于MLP、深度学习模型和nequick2模型。然而,平均而言,深度学习模型、MLP和NeQuick-2模型比该GPS站的IRI-Plas 2017更准确地捕捉到季节变化。
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引用次数: 0
LiDAR-Based navigation strategies for a non-cooperative target considering rendezvous trajectory 考虑交会轨迹的非合作目标激光雷达导航策略
IF 1 Q3 ENGINEERING, AEROSPACE Pub Date : 2025-03-01 DOI: 10.1016/j.jsse.2025.02.010
Taisei Nishishita, Yu Nakajima, Takahiro Sasaki, Hiroyuki Okamoto, Ryo Nakamura
The grave danger posed by space debris is attracting increasing attention, and many countries are actively researching active debris removal (ADR). One of the most important challenges to an ADR mission is the need for a highly accurate, robust navigation technology for docking with non-cooperative targets. This paper proposes a LiDAR-based navigation system, in particular a point cloud processing architecture that is robust against point cloud outliers that may occur in real environments. This study selected the upper stage of an H2A rocket as an example for ADR target. The proposed method addresses technical issues specific to ADR missions, such as point cloud loss at the target’s mirror surface and LiDAR’s Field of View (FOV) limitations. The results of dynamic and static measurement testing using actual hardware showed that the proposed method is capable of stable estimation in close proximity operation.
空间碎片的严重危害日益引起人们的重视,许多国家都在积极研究空间碎片主动清除技术。ADR任务中最重要的挑战之一是需要一种高度精确、强大的导航技术来与非合作目标对接。本文提出了一种基于激光雷达的导航系统,特别是一种对现实环境中可能出现的点云异常值具有鲁棒性的点云处理架构。本文以H2A火箭上部为例,对ADR目标进行了研究。提出的方法解决了ADR任务特有的技术问题,例如目标镜面的点云损失和激光雷达的视场(FOV)限制。在实际硬件上进行的动态和静态测量测试结果表明,该方法在近距离操作下具有稳定的估计能力。
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引用次数: 0
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Journal of Space Safety Engineering
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