一种新的飞航导弹飞行高度测量处理方法

针对飞航导弹掠海飞行试验测量和数据处理提出的高精度要求,通过对影响精度的各个环节的分析,在现有测量条件基础上,提出了航区等高参照物误差折算的飞航导弹海面高计算方法,设计了具体的测量和数据处理方案,建立了相应的精度评估模型,工程应用结果表明,由此得到的目标海面高更接近真实值,为掠海型飞航导弹海面高精确测量提供了一种新的方法。     

测试与校准实验室保密监督检查实践

根据新版保密资格标准中的保密检查要求,基于风险管理思想提出以风险分析为基础,以风险控制为核心的保密监督检查体系,形成基于主要风险的保密监督检查金字塔模型和各类保密检查的设计方法,指导测试与校准实验室保密监督检查工作的开展。     

谈风险管理在航天器研制中的应用

风险管理是航天计划/项目管理的重要组成部分。在航天型号研制中，国际上都十分重视风险的管理，在型号研制工作中都制定风险管理计划，并已有一套系统的做法。文章介绍了在航天项目中风险管理的内容、要求和过程，并介绍了一些国际上应用的情况。     

航天系统快速风险分析法

风险分析是大型工程,特别是具有高风险的航天系统可行性研究、案论证和方案评审等的主要内容之一。已经开发的对费用、进度、性能进行综合风险分析的计算机软件,如GERT,VERT,RISNET,SLAM 等,要求分析人员经过专门的培训,且工作量大,使用不便。文章给出了等风险轮廓线法、风险参数法和概率事件分析法三种快速、简便的风险分析方法,适合于一般工程技术人员,特别是管理人员在实际工作中应用。     

Procedure and methodologies for managing the risk of space object reentry

This paper proposes a procedure for managing the risk of reentering space objects and risk assessment methodologies used for the process. The proposed procedure comprises three phases encompassing the whole reentry stages of space objects. Mathematical models for assessing the impact risk of the reentering space objects by utilizing the information available during different risk management phases and the recommended risk analysis results for public communication are presented. The concept of the conditional casualty expectation is proposed as the metric representing the reentry risk and the method to compute its profile is introduced. A case study on the risk management procedure with the dataset on an actual reentry event is conducted to demonstrate the efficacy of the proposed procedure.     

Mars Sample Return: Do Australians trust NASA?

Mars Sample Return (MSR) represents an important scientific goal in space exploration. Any sample return mission will be extremely challenging from a scientific, economic and technical standpoint. But equally testing, will be communicating with a public that may have a very different perception of the mission. A MSR mission will generate international publicity and it is vital that NASA acknowledge the nature and extent of public concern about the mission risks and, perhaps equally importantly, the public’s confidence in NASA’s ability to prepare for and manage these risks. This study investigated the level of trust in NASA in an Australian population sample, and whether this trust was dependent on demographic variables. Participants completed an online survey that explored their attitudes towards NASA and a MSR mission. The results suggested that people believe NASA will complete the mission successfully but have doubts as to whether NASA will be honest when communicating with the public. The most significant finding to emerge from this study was that confidence in NASA was significantly (p < 0.05) related to the respondent’s level of knowledge regarding the risks and benefits of MSR. These results have important implications for risk management and communication.     

航天器微流星体及空间碎片环境与风险分析

微流星体及空间碎片的高速撞击威胁着长寿命、大尺寸航天器的安全运行 ,导致其严重的损伤和灾难性的失效。文章对低地球轨道微流星体及空间碎片环境进行了分析 ,给出了微流星体及空间碎片对航天器威胁方向的确定方法 ,得到了空间碎片撞击航天器相对撞击角的概率分布以及地球对微流星体遮挡的影响。编制了风险分析软件 ,以采用单防护屏防护结构的柱状低地球轨道航天器为例进行风险分析。     

考虑人及组织因素的航天工程项目风险分析模型

针对人及组织因素是造成航天工程项目风险的重要原因,在揭示了人及组织因素产生航天工程项目风险的机理基础上,构建了考虑人及组织因素的航天工程项目风险分析模型。模型首先评价人及组织因素对航天工程元器件建造工作质量的影响,接着测度工作质量与不同缺陷类型之间的一致性概率,并应用Poisson分布计算缺陷严重性,最后根据贝叶斯定理对元器件先验失效率进行修正,通过一个经过数据处理的航天工程项目对所构建的模型和方法进行了验证。     

Operant responding following exposure to HZE particles and its relationship to particle energy and linear energy transfer

On exploratory class missions astronauts will be exposed to a variety of heavy particles (HZE particles) which differ in terms of particle energy and particle linear energy transfer. The present experiments were designed to evaluate how these physical characteristics of different particles affect cognitive performance, specifically operant responding. Following exposure to ²⁸Si, ⁴⁸Ti, ¹²C and ¹⁶O particles at the NASA Space Radiation Laboratory rats were tested for their ability to respond appropriately to changes in reinforcement schedules using an operant task. The results showed that the effectiveness of different particles in disrupting cognitive performance, defined as the lowest dose that produced a performance decrement, varied as a function of the energy of the specific particle: for comparisons between different energies of the same particle (e.g., ⁵⁶Fe) the effectiveness of the particle was directly proportional to particle linear energy transfer, whereas for comparisons between different particles (e.g., ⁵⁶Fe and ¹⁶O) effectiveness was inversely proportional to particle linear energy transfer. The results are discussed in terms of the mechanisms that influence the effectiveness of different particles and energies and in terms of their implications for analyzing the possible risks to astronauts of decrements in cognitive performance following exposure to HZE particles on long-duration exploratory class missions.     

基于知识本体的资源管理平台框架设计与实现

针对大量领域信息资源缺乏有效内容分析这一问题,设计、开发了通过构建领域本体来充分发掘信息资源之间内在关系,实现信息资源增值服务的原型系统.首先构造了服装知识本体CO(Costume Ontology)用来表示服装领域知识.利用CO对被管信息资源进行语义描述,在描述数据库的基础上,实现基于语义的信息检索.讨论了服装知识本体的建模过程,本体的形式化表示以及存储方式.实验系统采用J2EE架构,开发了存储组件、语义查询接口组件、语义分析组件和语义推理组件.通过使用资源描述框架RDF,实现被管信息资源到知识本体层的映射.通过语义分析和语义推理,可以充分利用信息资源之间的关系实现相关信息资源检索与语义融合.     

The ratio of hazardous meteoroids to orbital debris in near-Earth space

Orbital debris is known to pose a substantial threat to Earth-orbiting spacecraft at certain altitudes. For instance, the orbital debris flux near Sun-synchronous altitudes of 600–800 km is particularly high due in part to the 2007 Fengyun-1C anti-satellite test and the 2009 Iridium-Kosmos collision. At other altitudes, however, the orbital debris population is minimal and the primary impactor population is not man-made debris particles but naturally occurring meteoroids. While the spacecraft community has some awareness of the risk posed by debris, there is a common misconception that orbital debris impacts dominate the risk at all locations. In this paper, we present a damage-limited comparison between meteoroids and orbital debris near the Earth for a range of orbital altitude and inclination, using NASA’s latest models for each environment. Overall, orbital debris dominates the impact risk between altitudes of 600 and 1300 km, while meteoroids dominate below 270 km and above 4800 km.     

On the effect of considering more realistic particle shape and mass parameters in MMOD risk assessments

One of the primary mission risks tracked in the development of all spacecraft is that due to micro-meteoroids and orbital debris (MMOD). Both types of particles, especially those larger than 0.1 mm in diameter, contain sufficient kinetic energy due to their combined mass and velocities to cause serious damage to crew members and spacecraft. The process used to assess MMOD risk consists of three elements: environment, damage prediction, and damage tolerance. Orbital debris risk assessments for the Orion vehicle, as well as the Shuttle, Space Station and other satellites use ballistic limit equations (BLEs) that have been developed using high speed impact test data and results from numerical simulations that have used spherical projectiles. However, spheres are not expected to be a common shape for orbital debris; rather, orbital debris fragments might be better represented by other regular or irregular solids. In this paper we examine the general construction of NASA’s current orbital debris (OD) model, explore the potential variations in orbital debris mass and shape that are possible when using particle characteristic length to define particle size (instead of assuming spherical particles), and, considering specifically the Orion vehicle, perform an orbital debris risk sensitivity study taking into account variations in particle mass and shape as noted above. While the results of the work performed for this study are preliminary, they do show that continuing to use aluminum spheres in spacecraft risk assessments could result in an over-design of its MMOD protection systems. In such a case, the spacecraft could be heavier than needed, could cost more than needed, and could cost more to put into orbit than needed. The results obtained in this study also show the need to incorporate effects of mass and shape in mission risk assessment prior to first flight of any spacecraft as well as the need to continue to develop/refine BLEs so that they more accurately reflect the shape and material density variations inherent to the actual debris environment.     

无线电计量微机辅助管理系统

介绍了用于无线电计量室的“无线电计量微机辅助管理系统”的设计思路和主要功能模块。实践表明：该系统功能强、使用方便，缩短了数据处理时间，使信息质量大大提高。     

规范计量管理与监督 提升航天计量技术保障能力

阐述了规范计量管理与监督的意义和目的,详细说明了计量管理与监督的实施途径,描述了航天计量保证工作的内容、特点和一般要求,通过规范计量管理与监督,不断改进和完善计量保证体系,以进一步提升航天计量技术保障能力。     

一种航天器防护与遮挡的几何描述算法研究

文中提出了一种航天器部件在任意威胁攻击方向上的投影面积和重叠面积的计算方法及部件间遮挡关系的确定方法。采用“几何拼接法”或借助有限元软件来建立航天器及其部件模型。将航天器各个部件向投影坐标系进行投影获得部件投影边界图形。利用垂直扫描线对各个部件的投影多边形进行扫描并进行求交运算 ,形成多个分散的四边形 ,在每个四边形内产生射击线 ,累加求出航天器易损性评估中所需的部件投影面积、重叠面积及遮挡关系。算例对三个正方体形状的部件进行了几何描述 ,当扫描线步长取 2cm时 ,投影面积及重叠面积计算值与理论值的最大相对误差为 5 0 6% ;当扫描线步长取 0 5cm时 ,最大相对误差为 1 2 5 %。结果表明算法通用性强 ,易于实现     

专用计量测试设备信息化管理模式研究

分析了当前企业专用计量测试设备管理模式中存在的问题。阐述了专用计量测试设备全生命周期管理模式的优越性,指出实行专用计量测试设备全生命周期管理是解决现存问题,进一步提升设备管理水平的一种有效途径。并提出一种以微软的应用技术开发平台（ASP.NET）框架下的浏览器/服务器（B/S）结构的信息系统用于实现专用计量测试设备全生命周期管理。     

分层远程网络管理

针对远程网络管理存在的问题,实现了一个具有层次结构的管理体系结构,在各个被管的远程网段设置次管理站,中心管理站使用网络管理过程NMP(Network Management Procedure),将管理任务委托给次管理站执行,次管理站将执行的结果返回主管理站,从而减少了管理信息流量,降低了管理费用,也减轻了中心管理站的负担.     

计量校准测试实验室综合管理系统的设计与实现

针对计量校准测试实验室存在管控力不强、工作效率低等问题,开发了符合计量校准测试实验室业务工作模式的计量综合管理系统,实现了检定校准测试工作基于过程控制的网络化运行,实现测量标准档案、计量资源以及图书资料等各种资料档案的信息化管控,促进了质量管理体系运行模式的进一步优化,达到了“过程控得住,文件管得好,工作效率高”的目标,具有较大的应用推广价值。给出了系统总体设计和采用的一些关键技术。     

信息安全绩效测量体系研究

绩效管理是指组织内各级管理者和员工为了达到组织目标共同参与的绩效计划制定、绩效辅导沟通、绩效考核评价、绩效结果应用、绩效目标提升的持续循环过程,绩效管理的目的是持续提升个人、部门和组织的绩效。良好的绩效管理体系能够激发管理者和员工的工作积极性、创造性,自发改进组织目标的实现过程,提高目标实现的效率和效果。相反,糟糕的绩效管理体系给组织带来的负面影响也是巨大的。信息安全管理是组织管理的重要组成部分。本文立足组织信息安全管理,重点研究信息安全绩效测量体系制定环节,结合国际国内相关标准,剖析信息安全绩效测量体系的设计方法,分享设计思路。