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机载机电管理计算机双余度设计 总被引:1,自引:0,他引:1
机载机电管理计算机的任务可靠性对飞机飞行安全至关重要,而提高任务可靠性的一个有效途径就是进行余度设计.本文从研究两种常用的双余度容错模型出发,将桥联模型应用于机电管理计算机的双余度设计.通过对工作模型的故障容错机制的分析,证明该双余度设计可有效提高机电管理计算机的任务可靠性,具备一定的工程实用价值. 相似文献
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提高安全性和可靠性是机载设备的设计重点,余度技术是系统或设备获得高可靠性的设计方法之一。当系统发生故障时,余度系统能够自动完成系统重构,继续带故工作,从而提高系统的任务可靠性和安全性。从余度数目选择、余度结构、余度管理及策略设计、余度系统的单点故障影响分析和共模影响分析等几方面介绍了机载设备余度设计方法,同时分析了余度设计对设备的有利和不利影响,具有一定工程实用价值。 相似文献
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机载机电系统是支持飞机正常、安全飞行工作所必需的,对飞机发动机和航空电子等设备的正常执行起着保障作用.为了提高机载机电系统的可靠性,机电系统采用了双余度结构,以达到故障容错,进而实现整个飞机系统的高可靠性和安全性.重点介绍了机载机电控制与管理计算机的容错体系结构的设计方案和工作原理,分析了系统的容错管理策略,研究了支持双余度计算机实现的故障检测及重构等关键技术. 相似文献
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多余度飞控计算机通道故障逻辑技术研究 总被引:1,自引:0,他引:1
在航空电子系统中,飞控计算机系统用于控制飞机的飞行功能,要求具有极高的可靠性,必须采用容错技术来满足要求。容错的重要方法是冗余。目前的飞控计算机系统,大多采用双余度、三余度及四余度的容错计算机。在余度计算机中,每一余度称为一个通道,每个通道均具有输出控制能力,因此余度计算机输出控制权的确定和交接就变得至关重要。介绍了道故障逻辑的功能需求和结构,重点研究了一种3×2余度飞控计算机系统通道故障逻辑的设计。 相似文献
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本文阐述一种复合四余度机电作动系统,在分析双重绕组的电机控制系统的基础上对电机的功率损耗进行分析;并提出了系统可能的几种容错运行方式,分析了容错工作方式的运行性能;进而对功率电路部分在容错工作方式下的损耗进行分析。分析结果表明,采用复合余度结构的机电作动系统,具有系统控制要求的容错能力,提高了系统的任务可靠度,可作为未来飞机机电作动系统的余度方案之一。 相似文献
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航空电子设备对可靠性的要求越来越高,文章介绍了一种双主机冗余显示控制系统,并且详细介绍了系统的架构和冗余管理策略。本系统具有故障检测、自动切换控制的能力,可以保证系统稳定、连续的工作。双主机冗余设计增加了系统成本,但在一定程度上提高了系统的可靠性、稳定性,满足航空电子产品对可靠性的要求。 相似文献
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The Satellite Operation System (SOS) has been developed for a low earth orbiting remote sensing satellite, Korea Multipurpose Satellite‐I, to monitor and control the spacecraft as well as to perform the mission operation. SOS was designed to operate on UNIX in the HP workstations. In the design of SOS, flexibility, reliability, expandability and interoperability were the main objectives. In order to achieve these objectives, a CASE tool, a database management system, consultative committee for space data systems recommendation, and a real‐time distributed processing middle‐ware have been integrated into the system. A database driven structure was adopted as the baseline architecture for a generic machine‐independent, mission specific database. Also a logical address based inter‐process communication scheme was introduced for a distributed allocation of the network resources. Specifically, a hot‐standby redundancy scheme was highlighted in the design seeking for higher system reliability and uninterrupted service required in a real‐time fashion during the satellite passes. Through various tests, SOS had been verified its functional, performance, and interface requirements. Design, implementation, and testing of the SOS for KOMPSAT‐I is presented in this paper. 相似文献
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《Proceedings of the IEEE. Institute of Electrical and Electronics Engineers》1965,53(12):1969-1981
Various redundancy tradeoffs with respect to weight, power, reliability, and testing ability are discussed for the Vela spacecraft. The types of redundancy considered were complete circuit (such as quads), standby automatic switchable, standby command switchable, and fully automatic. Complete circuit redundancy was rejected because of weight and power limitations. Standby automatic switchable redundancy was rejected because of possible failure modes and complexity of the automatic detection circuits. Fully automatic redundancy was applied to those portions of the system where a failure would cause loss of the mission. Standby command switchable redundancy was applied to those portions of the system where a failure could be detected and corrected by command switching. The final redundant system is compared with a nonredundant system to indicate the additional weight and power required to accomplish the redundancy design. 相似文献
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大型相控阵雷达的天线阵面系统复杂,故障模式多样,各模式对雷达工作的影响程度也不同。针对这些特点,文中采用了基于任务可靠性的可靠性预计。同时,通过表决冗余及开展定期检修的方式,来确保天线阵面设备及系统的高任务可靠性。推导了各种典型任务剖面的可靠性数学模型,建立了任务可靠性模型,并对雷达天线阵面进行了可靠性预计,从而为大型相控阵雷达天线阵面的高任务可靠性设计提供了理论依据和技术方法。 相似文献
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M. Sakawa 《Microelectronics Reliability》1980,20(3):191-204
This paper deals with the reliability design of a standby redundancy system from a view point of large-scale multiobjective optimization. A large-scale multiobjective mathematical model is formulated and the problem considered is to optimize system reliability, cost, weight and volume, for a given mission time, subject to multiple constraints. A large-scale multiobjective optimization method is proposed by combined application of both surrogate worth trade-off method and dual decomposition method, and the preferred solution of the decision maker can effectively be obtained by using the proposed method. The method is illustrated by numerical examples. 相似文献
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An attempt is made to derive the closed-form mathematical expression of a phased mission system reliability. A system is considered, where failure probability of a component and number of added redundancy change during the mission time. Several performance measures are also suggested. 相似文献
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