Article 11316

Title of the article

MONITORING THE OPERATION CONDITION OF PLATFORM FAILURE SAFETY

Authors

Avakyan Aleksandr Anushavanovich, doctor of technical sciences, senior research manager, Scientific Research Institute of Aircraft Equipment (140180, 18 Tupolev street, Zhukovskiy, Moscow region, Russia), avakyan@niiao.com
Kopnenkova Marina Vladimirovna, еngineer, Scientific Research Institute of Aircraft Equipment (140180, 18 Tupolev street, Zhukovskiy, Moscow region, Russia), info@niifi.ru
Maksimov Anatoliy Konstantinovich, leading еngineer, Scientific Research Institute of Aircraft Equipment (140180, 18 Tupolev street, Zhukovskiy, Moscow region, Russia), info@niifi.ru

Index UDK

62.192

DOI

10.21685/2307-4205-2016-3-11

Abstract

The modern element base of electronics allows the dimensions and masses of the functional blocks commonly used in avionics, focus powerful interfacecomputing resources. These resources are sufficient to ensure that the work of many hardware and software applications that implement many features aircraft (LA). System modules, including basic software that controls the resources in such a way as to ensure that the work of many applications in integrated modular avionics (IMA) [1] was called "IMA" platform. Platform, operating with a multitude of applications, integrated modular avionics (IMA), was called "IMA" System. Modern architecture complexes of the onboard equipment (BWC) avionics, from the Federation of multiple functional units, the number of which in the main air boats to one hundred or more optimizirovalos′ in architecture, consisting of a small number of systems. Realization of multiple functions LA IMA systems, including critical, demanded the execution of IMA systems airworthiness [2] and flight regularity [3]. Airworthiness standards for systems that implement functions, malfunction, IMA, which lead to catastrophic situations, impose requirements to likelihood of failure was less than 10-9 failure per hour flown. Flight regularity requirements require restore failed CCD during not more than 15 minutes with a probability equal readiness 0.998. To meet these requirements with a minimum cost of development and maintenance of the CCD, CCD systems platform should be as unified and have a high fault tolerance. Fault tolerance, ensure that the above norms of airworthiness and flight regularity, perhaps, if implemented in the IMA redundancy of key components and redundant management system (MIS). The article is devoted to consideration of the principles and methods of monitoring system platform for IMA, which is the main component of the IMS. This article discusses issues such as monitoring methods of control: the necessary completeness and accuracy control, depth control sufficient for carrying out reconfiguration system when Parry discovered failures and failures, as well as limiting the duration of controls that enable you to fend off critical situations.

Key words

monitoring, control, redundancy, failure, failure, System reconfiguration, regression filter.

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Дата создания: 28.09.2016 15:20
Дата обновления: 29.09.2016 15:38