基于STK的高超声速飞行器可视化仿真平台研究

 论证了利用STK软件建立高超声速飞行器可视化仿真平台的可行性,研究了创建高超声速飞行器结构模型以及模拟其所处空间地理环境的方法,提出了利用STK/Connect模块功能实现分布式实时可视化仿真的策略,仿真结果表明基于STK的仿真平台能够满足任务需求。     

空间天气模式集成可视化演示软件设计

空间天气模式集成是空间天气预报业务化的基础, 空间天气模式集成可视化演示软件系统是其中重要的研究内容之一. 空间天气模式种类繁多, 要素多样, 模型复杂, 且各模式可视化形式及方法具有差异性. 本文综合当前中国空间天气模式的特点, 构建了一套空间天气模式集成可视化演示系统. 该系统兼容性好、可扩展性高, 能够集成当前中国空间天气中大多数模式. 讨论了空间数据管理方法, 基于Visual C++ 软件平台和OpenGL可视化软件模块,以动态加载方式初步实现了多个空间天气模式的可视化集成.      

主矢量法在空间近距离拦截优化中的应用

重点研究了在固定时间内利用主矢量原理判断近距离冲量拦截轨道燃料消耗是否最优的问题, 并对非最优情况提出了优化策略. 根据轨道动力学理论, 建立了近距离空间拦截轨道的数学模型. 根据主矢量理论给出了判断冲量拦截是否最优的理论依据, 并给出了优化方法. 利用仿真算例证实了优化的有效性. 通过对不同时间的空间拦截燃料消耗进行仿真比较分析, 提出了燃料消耗最优的拦截策略.      

天文观测卫星动中探测机动测试系统设计

天文观测卫星普遍采用动中探测模式开展空间探测任务。为了实现动中探测姿态机动模式的地面有效验证，设计了整星机动集成测试方案。设计惯性空间基准的地面动力学仿真，满足惯性空间扫描仿真；设计整星各分系统间高精度时间统一系统，为整星机动测试提供统一基准；基于STK与Matlab接口模块，设计基于实时遥测数据的可视化判读系统，可提高测试判读实时性与准确度。整星测试结果表明，该方案有效验证了动中探测任务中姿态机动功能的正确性和指标符合情况，为开展整星地面测试和在轨应用提供了参考。     

天基激光移除空间碎片仿真平台研究与开发

为了从空间碎片和天基移除系统两方面分析激光驱动碎片变轨过程,优化移除任务规划和策略,基于真实的可观测空间碎片数据,设计并开发了一套天基激光移除空间碎片三维数值仿真平台。首先从总体设计出发,对三维数值仿真平台的需求分析、总体框架、模块功能进行了明确的描述。其次通过对激光驱动空间碎片变轨过程数学模型的分析,确定了各模块的具体实现方法。最后采用C++/Qt开发了三维数值仿真平台,通过仿真验证了设计平台的有效性。该仿真平台可用于不同天基平台和目标碎片的任务规划、碎片分布热点区域和航天器防护区域的方案设计及空间环境治理体系的优化设计。     

小天体探测自主绕飞智能规划建模

针对小天体探测存在显著通讯延迟、任务执行效率低等问题,梳理了小天体探测智能规划需求,面向自主绕飞任务开展了智能规划研究。首先将该问题分解为平台任务智能规划和载荷任务智能规划两部分。针对平台任务智能规划问题,基于PDDL语言设计了探测器自主管理知识模型,提出了基于状态时间线扩展的求解算法;针对任务智能规划问题,建立了基于CSP问题的智能规划数学模型,提出了基于遗传策略的求解算法。最后开发了仿真系统进行算法验证。仿真结果表明:该方法可综合平台与载荷需求,在存储、能源、通信等多种约束条件下,对绕飞探测任务进行统一的任务规划,并得到指令序列和动作序列,能够提高任务管控的智能化程度,降低任务操作的复杂性。     

分布式武器目标分配中的实时截止期分配

在分布式武器对目标的协同拦截中,作战任务往往被划分为多个子任务,为了保证任务的实时性,针对分布式武器对目标的协同拦截问题建立实时任务模型,运用分布式实时系统中的截止期分配技术,把全局作战任务的截止期转化为其包含的各子任务的截止期.建立了任务调度模型和仿真模型,对分配有截止期的子任务实施仿真调度,研究了在一定武器数量情况下,不同来袭目标数量和武器节点上本地负载所占不同比例时,各截止期分配方法保障任务实时性和完成率的能力,可为实时条件下的分布式任务协作研究提供参考.     

双拦截弹拦截单目标边界型微分对策制导律研究

针对战术弹道导弹、高超声速巡航导弹和无人飞行器等新型具有高机动性能的防空目标,为提高成功拦截的概率,采用多枚拦截弹进行拦截。应用微分对策理论,将双拦截弹拦截单目标的末段制导问题建模为“二对一追踪-逃逸”对策模型。考虑最大加速度约束,研究了两枚拦截弹的拦截空间分解和对策空间分布,并通过仿真研究了制导律性能。结果表明：采用两枚拦截弹拦截时,脱靶量对目标机动方向的转变时间具有很好的鲁棒性。     

基于网格的电路功能可靠性仿真系统

功能可靠性仿真是建立系统功能与可靠性一体化分析的综合仿真技术,论述了电路功能可靠性仿真系统的体系结构、功能及其实现的故障建模、故障虚拟注入、仿真器集成、故障自动判别等主要技术方法.为解决电路功能可靠性仿真系统中长仿真时间和大数据量存储的难点,提出了基于网格计算技术的体系结构,研究了仿真服务、分析服务和数据管理服务的实现方法,建立了通过网格平台向电路功能可靠性仿真系统提供虚拟计算和存储的能力,减少了系统分析所需要的仿真时间,实现了大量仿真结果数据的分布式存储.基于上述技术思想,实现了以TyrensGrid为网格平台、PSpice为仿真内核的TG-CFRS软件原型,证明了基于网格的电路功能可靠性仿真技术的有效性.     

脉冲推力轨道拦截可达性描述及求解方法

针对航天器单脉冲轨道拦截可达性分析问题,基于共面变轨、逆轨拦截假设,考虑能量、时间和交会角约束,提出了拦截航天器可拦截区和可发射区的概念。在航天器单脉冲空间可达范围的基础上,进一步考虑了目标轨道的约束,建立了目标轨道命中区的计算策略,对异面轨道交叉点为燃料最省点做出了解释。把拦截可达性相关的问题归纳为8个基本拦截问题,通过这8个问题的组合,描述了考虑能量、时间和交会角约束下拦截问题的可拦截区和可发射区的计算方法。采用圆轨道共面变轨、逆轨拦截场景进行了仿真验证,结果表明该方法能够快速有效地计算出约束条件下航天器的拦截可达范围,能够用于分析特定任务情况下的拦截可达性。     

空间科学任务协同设计论证平台

空间科学任务协同设计论证存在设计方案耦合强,数据一致性差,数据变更难,数据与流程脱节等问题.为了解决上述问题,建立了典型空间科学任务的多层数字化模型;采用图形化方式对论证流程进行建模,并建立流程与数据的映射关系;通过共享数据池的方式为多岗位用户提供多方案数据协同机制;采用消息总线对数据变更进行及时提醒;利用方案依赖关系矩阵来判别方案耦合关系,最终自动合并任务总体设计方案.作为一个分布式平台,空间科学任务协同设计平台采用Eclipse RCP和Spring技术架构,整合了Hibernate、工作流Activiti5等中间件,提供统一门户,支持多岗位、多任务、多方案、多版本的管理能力,提供论证流程监控、数据协同交互等功能.结合某空间科学任务论证验证了该平台的有效性.      

月球立方星姿态控制系统的初步设计与测试

立方星是一种模块化的微小卫星,在科学探测与专业人才培养等方面具有重要意义。针对目前立方星任务逐渐从近地轨道向深空扩展的发展趋势,以立方星月球深空任务为背景,利用商业器件设计并实现了初步的立方星姿态控制系统,以及姿态控制系统所必需的结构、电源、计算机等立方星子系统,同时给出了姿态测试平台的设计方案及其硬件实现。在所搭建硬件平台上,通过测量飞轮控制器的阻尼系数,对控制模型进行参数辨识与标定,获得了与数值仿真一致的实物测试结果。针对姿态控制系统设计了PD控制律,并在控制实验中实现了至任意姿态角的机动控制。     

月球探测器可视化仿真系统的开发

基于软件平台OpenGL和Visual C++,开发了基于轨道动力学规律的月球探测器在轨运行实时视景仿真系统,用以动态仿真探测器、地球、月球和太阳的时空关系,实时地计算和显示探测器空间位置的变化,并利用三维可视化技术完成逼真的三维图形图像信息的显示.讨论了仿真系统软件结构,主要模块的设计,开发过程中所遇到的主要问题及其解决方法.实际应用表明,该可视化仿真系统可帮助用户更加直观地了解探月飞行任务的进行情况.      

Closed Environment Module – Modularization and extension of the Virtual Habitat

The Virtual Habitat (V-HAB), is a Life Support System (LSS) simulation, created to perform dynamic simulation of LSS’s for future human spaceflight missions. It allows the testing of LSS robustness by means of computer simulations, e.g. of worst case scenarios.     

The fundamental physics explorer: An ESA technology reference study

ESA technology reference studies are used as a process to identify key technologies and technical challenges of potential future missions not yet in the science programme. This paper reports on the study of the Fundamental Physics Explorer (FPE), a re-usable platform targeted to small missions testing fundamental laws of physics in space. The study addresses three specific areas of interest: special and general relativity tests based on atomic clocks, experiments on the Weak Equivalence Principle (WEP), and studies of Bose–Einstein condensates under microgravity conditions. Starting from preliminary science objectives and payload requirements, three reference missions in the small/medium class range are discussed, based on a re-adaptation of the LISA Pathfinder spacecraft. A 700/3600 km elliptic orbit has been selected to conduct clock tests of special and general relativity, a 700 km circular orbit to perform experiments on the Weak Equivalence Principle and to study Bose–Einstein condensates, each mission being based on a three-axis stabilised spacecraft. It was determined that adaptation of LISA Pathfinder would be required in order to meet the demands of the FPE missions. Moreover it was established that specific payload and spacecraft technology development would be required to realise such a programme.     

CELSS transportation analysis

Regenerative life support systems based on the use of biological material have been considered for inclusion in manned spacecraft since the early days of the United States space program. These biological life support systems are currently being developed by NASA in the Controlled Ecological Life Support System (CELSS) program. Because of the progress being achieved in the CELSS program, it is time to determine which space missions may profit from use of the developing technology. This paper presents the results of a study that was conducted to estimate where potential transportation cost savings could be anticipated by using CELSS technology for selected future manned space missions.

Six representative missions were selected for study from those included in NASA planning studies. The selected missions ranged from a low Earth orbit mission to those associated with asteroids and a Mars sortie. The crew sizes considered varied from four persons to five thousand. Other study parameters included mission duration and life support closure percentages, with the latter ranging from complete resupply of consumable life support materials to 97% closure of the life support system. The paper presents the analytical study approach and describes the missions and systems considered, together with the benefits derived from CELSS when applicable.     

Implementing new strategic plans for NASA long duration scientific balloons

Over that past twelve years, global long duration balloon (LDB) missions have provided scientists an observation platform that offers tremendous opportunity for accomplishing monumental science. The precedence of several years of highly successful LDB missions and the capability to recover and re-fly such instruments within a relatively short period of time has created even greater demands for serving science missions in 2004 and beyond. To address NASA’s strategic plans for more missions and longer durations, new concepts are being explored and some are currently being developed, in order to enhance the current LDB mission concept.     

A new approach based on crater detection and matching for visual navigation in planetary landing

This paper provides an approach of crater detection and matching to visual navigation in planetary landing missions. The approach aims to detect craters on the planetary surface and match them to a landmark database during the descent phase of a planetary landing mission. Firstly an image region pairing method is proposed to detect the crater by using an image region feature detector. Then a WTA-rule is adopted to match the detected crater to the crater in database. To further reduce the false matching rate, an efficient method for reducing false matches using parameters of crater in 3-D database is proposed. Real images of planetary terrain and a semi-physical planetary landing simulation platform are utilized to test the performance of the approach, simulation results show the proposed approach is able to match the required number of craters to the database for pin-point planetary landing with a low rate of false detection and false matching, which will lead to an improved planetary landing precision.     

Global approach to simulation: a gateway to long-term human presence in space.

The establishment of an autonomous European manned space capability is an objective set up by the ESA Council Meeting at the ministerial level, in 1985/1987. ESA's Long-Term Programme Office (LTPO), charged of the preparation of the programme for a European Manned Space Infrastructure (EMSI), started during 1988 to build up an intellectual framework in the domain of long-duration manned space missions. EMSI scope was eventually extended to embrace Moon/Mars missions and bases. Several exploratory studies on problems related to human factors in long-duration space missions were initiated by LTPO. The work of an ad-hoc group of experts (SIMIS Group) has been focused during 1989/1990 on the planning for simulation of such missions with a broad mandate, covering the physiological, psychological and operational aspects of long-duration exposure to microgravity and isolation/confinement. Preliminary results of SIMIS activities are reported. The HYDREMSI experiment, carried out in a terrestrial, analogous environment for 72 days during 1989, is described as an example of the envisaged simulations.