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高分七号卫星GPS接收系统作为整星高精度立体测绘目标实现的重要手段之一,具有为整星提供高精度时统、辅助有效载荷指标实现、协助高速数据传输天线准确指向及实现高精度事后精密定轨的功能。针对其稳定运行和持续服务的要求,基于故障预测与健康管理(PHM)技术,提出了GPS接收系统多层级健壮设计方案,从单机/分系统级、整星级和星地级为GPS接收系统在轨健壮运行提供支撑,通过层级内部形成独立PHM系统实现自主、直接的健壮运行管理,同时借助低层级向高层级的状态信息传递实现全面、及时的故障补充处置和故障隔离。高分七号卫星在轨运行结果表明:该多层级健壮设计降低了故障处置对接收系统功能实现的影响,保障了GPS接收系统在轨提供服务的连续性。 相似文献
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高分三号卫星自主健康管理系统设计与实现 总被引:1,自引:0,他引:1
《航天器工程》2017,(6):40-46
在分析遥感卫星自主健康管理需求和目标的基础上,对自主健康管理进行分级,提出高分三号(GF-3)卫星自主健康管理系统架构,设计可重配置的遥测在轨实时监测与量化管理系统,实现了标准化遥测监视表设计、可量化故障事件包设计、可量化统计事件包设计、故障和统计事件包自主生成条件、曲线比对功能等共性关键技术。GF-3卫星在轨运行结果表明:卫星能够在非地面干预的情况下自主对整星健康状态进行实时监测,并在故障发生时实施自主诊断、隔离和恢复,最大限度地保证卫星安全,有效提高卫星在轨自主运行的可靠性。 相似文献
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敏捷光学卫星自主任务管理系统关键技术分析 总被引:1,自引:1,他引:0
《航天器工程》2016,(4):54-59
针对敏捷光学卫星单轨任务数多,成像模式复杂,应急任务响应速度要求快的特点,提出了一种自主任务管理系统分层架构设计,采用分层递进、逐步细化的方式,便于系统模块化设计和有效降低软件实现的复杂度。文章研究了任务规划与应急重规划、积分时间实时计算、任务执行自主监控3项关键技术,基于此研究成果设计的自主任务管理系统已应用于某敏捷遥感卫星平台,试验结果表明:星上使用自主任务管理系统后,支持成像任务数量提升了5倍,可以有效满足我国后续新型遥感卫星的任务需求。 相似文献
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为了提高小卫星星务软件的自主化、智能化水平,提出一种基于模糊神经网络的小卫星任务自主调度的设计方法。该方法根据小卫星有效载荷和任务的需求,将小卫星的星务软件分解为若干个任务模块。同时,考虑到一些任务执行的紧前关系要求,将若干有紧前关系的任务模块划分为一个任务流程。以任务流程为单位,利用模糊神经网络构建任务流程自主调度决策系统。仿真实验结果表明,该决策系统能够根据小卫星的监测数据,以任务流程的自主调度为基础,最终实现对任务模块的动态自主调度。 相似文献
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针对分离模块航天器对于灵活构建和组织多个卫星协同工作,实现自主运行的需求,提出基于"Agent容器程序"管理的多Agent自主运行系统结构。以多个规划Agent的组织为基础,综合使用多种类型的通用及专用Agent,实现了自主运行系统的适用性、灵活性和健壮性,为多卫星协同工作的仿真和实际应用提供可行的方法。 相似文献
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本文提出了一种基于姿态敏感器的地球同步轨道卫星自主导航方法,作为解决未来高轨道卫星自主运行的先决条件。在整个系统中,以包含摄动项的HILL 方程作为状态方程,根据由姿态敏感器给出的卫星本体相对于地球和另外两个空间天体的方位,推导出测量方程,进而用简化的推广 Kalman 滤波算法进行状态估计。仿真表明,该方法收敛速度快,精度较高,是一种可行的地球同步轨道卫星自主导航方法。 相似文献
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The French Space Agency (CNES) is currently operating thirteen satellites among which five remote sensing satellites. This fleet is composed of two civilian (SPOT) and three military (HELIOS) satellites and it has been recently completed by the first PLEIADES satellite which is devoted to both civil and military purposes. The CNES operation board decided to appoint a Working Group (WG) in order to anticipate and tackle issues related to the emergency End Of Life (EOL) operations due to unexpected on-board events affecting the satellite. This is of particular interest in the context of the French Law on Space Operations (LSO), entered in force on Dec. 2010, which states that any satellite operator must demonstrate its capability to control the space vehicle whatever the mission phase from the launch up to the EOL. Indeed, after several years in orbit the satellites may be affected by on-board anomalies which could damage the implementation of EOL operations, i.e. orbital manoeuvres or platform disposal. Even if automatic recovery actions ensure autonomous reconfigurations on redundant equipment, i.e. setting for instance the satellite into a safe mode, it is crucial to anticipate the consequences of failures of every equipment and functions necessary for the EOL operations. For this purpose, the WG has focused on each potential anomaly by analysing: its emergency level, as well as the EOL operations potentially inhibited by the failure and the needs of on-board software workarounds… The main contribution of the WG consisted in identifying a particular satellite configuration called “minimal Withdrawal From Service (WFS) configuration”. This configuration corresponds to an operational status which involves a redundancy necessary for the EOL operations. Therefore as soon as a satellite reaches this state, a dedicated steering committee is activated and decides of the future of the satellite with respect to three options: a/. the satellite is considered safe and can continue its mission using the redundancy, b/. the EOL operations must be planned within a mid-term period, or c/. the EOL operations must be implemented as soon as possible by the operational teams. The paper describes this management and operational process illustrated with study cases of failures on SPOT and PLEIADES satellites corresponding to various emergency situations. 相似文献
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Seung-woo Baek Sun-mi Han Kyeum-rae Cho Dae-woo Lee Jang-sik Yang Peter M. Bainum Hae-dong Kim 《Acta Astronautica》2011,68(7-8):1396-1402
In this paper, a scheduling optimization algorithm is developed and verified for autonomous satellite mission operations. As satellite control and operational techniques continue to develop, satellite missions become more complicated and the overall quantity of tasks within the missions also increases. These changes require more specific consideration and a huge amount of computational resources, for scheduling the satellite missions. In addition, there is a certain level of repetition in satellite mission scheduling activities, and hence it is highly recommended that the operation manager carefully considers and builds some appropriate strategy for performing the operations autonomously. A good strategy to adopt is to develop scheduling optimization algorithms, because it is difficult for humans to consider the many mission parameters and constraints simultaneously. In this paper, a new genetic algorithm is applied to simulations of an actual satellite mission scheduling problem, and an appropriate GUI design is considered for an autonomous satellite mission operation. It is expected that the scheduling optimization algorithm and the GUI can improve the overall efficiency in practical satellite mission operations. 相似文献
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Earth remote sensing (alongside communications) is one of the key application of Earth-orbiting satellites. Civilian satellites in the LANDSAT and SPOT series provide Earth images which have been used for a vast spectrum of applications in agriculture, meteorology, hydrology, urban planning and geology, to name but a few. In the defence sector, satellite remote sensing systems are a critical tool in strategic and tactical planning – for the countries which can afford them. To date, remote sensing satellites have fallen into one of these two categories: military missions driven by the requirement for very high resolution and orbital agility; and multipurpose civil satellites using general purpose sensors to serve a diverse community of end users. For military-style missions, the drive to high resolution sets the requirements for optics, attitude control and downlink data bandwidth. For civil missions, the requirement to satisfy multiple, diverse user applications forces compromises on spectral band and orbit selection. Although there are exceptions, many small satellite remote sensing missions carry on in this tradition, concentrating on ultra high resolution products for multiple user communities. This results in satellites costing on the order of US $100 M, not optimised for any particular application. This paper explores an alternative path to satellite remote sensing, aiming simultaneously to reduce cost and to optimise imaging products for specific applications. By decreasing the cost of the remote sensing satellite system to a critical point, it becomes appropriate to optimise the sensor's spectral and temporal characteristics to fit the requirements of a small, specialised user base. The critical engineering trade-off faced in a cost driven mission is how to reduce mission cost while still delivering a useful product to the selected user. At the Surrey Space Centre, we have pursued an engineering path using two dimensional CCD array sensors, commercial off-the-shelf lenses and gravity-gradient stabilised microsatellites. In spite of the inherent limitations of such systems, recent successes with the Thai Microsatellite Company's Thai-Phutt satellite show that a system costing in the region of US $3 million, can approach the spectral and spatial characteristics of LANDSAT. Surrey's UoSAT-12 minisatellite (to be launched April, 1999) will further develop this cost-driven approach to provide 10 m panchromatic resolution and 30 m multi-spectral resolution. This paper describes the Thai-Phutt and UoSAT-12 imaging systems, explaining the engineering methods and trade-offs. Although Surrey is presently the only centre presently pursuing such implementations, our paper shows that they deserve wider consideration. 相似文献
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《Acta Astronautica》2009,64(11-12):1299-1304
Miniaturization techniques enable the realization of very small satellites with interesting capabilities in space science. The University of Würzburg contributed in the scope of the cubesat program with its own pico satellite UWE-1, which is in orbit since October 2005. Despite reliable and stable operation of the on-board data handling (OBDH) system during the UWE-1 mission, the successor UWE-2 will be equipped with a more sophisticated, modular and extensible OBDH system, which was designed to facilitate the further development of the UWE satellite platform. The OBDH system was designed for high reliability and stability, but with an easier extension capability. The modular structure of the new system thus supports potential transfer to other satellite platforms. 相似文献
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Miniaturization techniques enable the realization of very small satellites with interesting capabilities in space science. The University of Würzburg contributed in the scope of the cubesat program with its own pico satellite UWE-1, which is in orbit since October 2005. Despite reliable and stable operation of the on-board data handling (OBDH) system during the UWE-1 mission, the successor UWE-2 will be equipped with a more sophisticated, modular and extensible OBDH system, which was designed to facilitate the further development of the UWE satellite platform. The OBDH system was designed for high reliability and stability, but with an easier extension capability. The modular structure of the new system thus supports potential transfer to other satellite platforms. 相似文献