空间拦截中只测量视线角速度的跟踪滤波器的可观性分析

建立了空间拦截中导弹与目标的相对运动方程。论述了卡尔曼滤波器的可观性准则，研究了跟踪滤波器的可观性，并分析了影响跟踪滤波器可观性的因素。数字仿真证实了理论的正确性。     

碎裂开盖鱼雷发射箱内流场变化研究

利用计算流体力学的仿真软件FLUENT对鱼雷发射箱内流场变化情况进行仿真计算,通过仿真计算分析发射箱内的压强分布规律及其对易碎裂盖体的影响。仿真结果表明,后盖在助推器射流直接冲击下会受到极不均匀的压强作用,可能使后盖中心破裂而不碎;前盖受后盖反射的射流影响而开盖。研究结果对发射箱的碎裂开盖方案设计有一定的指导意义。     

载人航天任务测速雷达双通道数据融合方法

针对载人航天任务中高精度测速雷达在实时多主站外弹道融合时仅能采用单通道应答数据参与处理,获得的弹道精度较差,且测速雷达数据利用率仅有50%的问题,提出利用多普勒效应和应答机遥测参数两种方法对测速雷达跟踪模式进行实时准确识别,首先得到测速雷达双通道的应答数据,然后通过改进的非线性滤波+机动模型算法对火箭上升段外弹道测量数据进行高精度融合。最后采用仿真数据对传统方法和新方法的外弹道融合精度进行了比对分析。该方法的应用可有效提高测速雷达测元利用率和载人航天任务火箭上升段外弹道精度,具有较强的工程应用价值。     

深空机动对运载火箭发射火星探测轨道研究

为解决长征(LM)运载火箭发射火星探测器转移轨道时，因低温入轨级最长允许滑行时间及测控限制，有效发射日期窗口亟需拓展的问题，采用主矢量理论结合序列二次规划算法(SQP)，研究了探测器深空机动(DSM)对优化运载火箭发射火星转移轨道的作用。在发射直接转移火星探测轨道算法基础上，重点研究了包含引力影响球(SOI)内近地及近火飞行段后，采用主矢量获取深空机动最优猜测初值的分析算法，通过直接使用探测器近火点目标轨道参数优化运载火箭发射轨道，研究对比不同优化目标及设计约束下深空机动的分析结果，证实深空机动对降低转移轨道总发射能量需求、拓展发射日期窗口的高效性；该算法已应用于工程设计。     

基于QoS的面向消费者的服务发现

当前万维网服务发现机制并没有考虑消费者对服务质量的需求,消费者需要花很多时间来选择满足自己服务质量的服务.采取了一个QoS (Quality of Service)过滤器,采用服务质量属性量化方法和一个服务质量匹配算法来选取符合消费者服务质量要求的服务,并把服务存储在本地缓存中.这种方法考虑到消费者对服务质量的要求,减少访问远程发现服务器的次数,加快了服务发现速度.通过对本地服务添加标注和关键字来支持消费者服务的个性化.     

大型水陆两栖飞机特殊任务模式对总体设计的挑战

面向森林灭火和水上救援任务设计的大型水陆两栖飞机，由于其特殊的任务模式，给设计工作带来了许多全新的挑战。首先，分析了国内森林灭火和水上救援的需求，并介绍了对应的任务模式。然后，总结了在型号研制过程中不同于常规飞机的特殊设计和相应的解决方法，具体包括：以国内供应商为主体的构型管理体系的建立、气水动一体化设计、全新的起落架布局设计、任务系统集成和效能评估、驾驶舱集成设计、设备布置和腐蚀防护设计。最后，提出了在适航审定和集成应用方面仍需重点关注的4个研究方向。     

Analysis on coverage ability of BeiDou navigation satellite system for manned spacecraft

To investigate the service ability of the BeiDou Navigation Satellite System (BDS) for manned spacecraft, both the current regional and the future-planned global constellations of BDS are introduced and simulated. The orbital parameters of the International Space Station and China׳s Tiangong-1 spacelab are used to create the simulation scenario and evaluate the performance of the BDS constellations. The number of visible satellites and the position dilution (PDOP) of precision at the spacecraft-based receiver are evaluated. Simulation and analysis show quantitative results on the coverage ability and time percentages of both the current BDS regional and future global constellations for manned-space orbits which can be a guideline to the applications and mission design of BDS receivers on manned spacecraft.     

System design of the Hayabusa 2—Asteroid sample return mission to 1999 JU3

The Japan Aerospace Exploration Agency is currently developing the second asteroid sample return mission, designated as Hayabusa 2. Following the successful return of Hayabusa from the asteroid “Itokawa”, Hayabusa 2 is designed as a round-trip mission to the asteroid “1999 JU3”. The 1999 JU3 is a C-type asteroid, which is believed to contain organic matter and hydrated minerals. Thus, it is expected that successful sample collection will provide additional knowledge on the origin and evolution of the planets and, in particular, the origin of water and organic matter. The current mission scenario will enable the spacecraft to reach 1999 JU3 in the middle of 2018 and perform an asteroid proximity operation for 1.5 years. Three touch downs for sampling and one 2-m-class crater generation by means of a high-speed impact operation are planned during the asteroid proximity operation. The samples are to be brought back to the Earth by a re-entry capsule. The present paper describes the system design of Hayabusa 2, some key technical challenges of the mission, and the development status.     

攻击型航空综合体作战效能分析的基本问题

以作战过程最为复杂的攻击型航空综合体为例，给出了与攻击型航空综合体作战效能分析相关的基本概念，简述了攻击机机群的基本作战过程，对其在完成作战任务的整个战斗机飞行过程中进行战效评估时所涉及到的基本问题－作战“剧本”的描述和所需要建立的数学模型等进行了较详细的介绍，阐述了各数学模型间的关系及各自应具有主要功能，为从系统工程观战来研究对地攻击机的作战效能，建立战效评估的顶层数学模型提供参考。     

Cancer risk above 1 Gy and the impact for space radiation protection

Analyses of the epidemiological data on the Japanese A-bomb survivors, who were exposed to γ-rays and neutrons, provide most current information on the dose–response of radiation-induced cancer. Since the dose span of main interest is usually between 0 and 1 Gy, for radiation protection purposes, the analysis of the A-bomb survivors is often focused on this range. However, estimates of cancer risk for doses larger than 1 Gy are becoming more important for long-term manned space missions. Therefore in this work, emphasis is placed on doses larger than 1 Gy with respect to radiation-induced solid cancer and leukemia mortality. The present analysis of the A-bomb survivors data was extended by including two extra high-dose categories and applying organ-averaged dose instead of the colon-weighted dose. In addition, since there are some recent indications for a high neutron dose contribution, the data were fitted separately for three different values for the relative biological effectiveness (RBE) of the neutrons (10, 35 and 100) and a variable RBE as a function of dose. The data were fitted using a linear and a linear-exponential dose–response relationship using a dose and dose-rate effectiveness factor (DDREF) of both one and two. The work presented here implies that the use of organ-averaged dose, a dose-dependent neutron RBE and the bending-over of the dose–response relationship for radiation-induced cancer could result in a reduction of radiation risk by around 50% above 1 Gy. This could impact radiation risk estimates for space crews on long-term mission above 500 days who might be exposed to doses above 1 Gy. The consequence of using a DDREF of one instead of two increases cancer risk by about 40% and would therefore balance the risk decrease described above.