Reliability of computer structures of integrated modular avionics for hardware configurations

The problem of designing advanced computing systems in the class of structures of integrated modular avionics is considered. The unified topology of the internal network of the computer on the basis of Space Wire exchange channels and variants of its execution for various onboard applications is offered. Equivalent reliability schemes of each of the specific structures are introduced and the probabilities of trouble-free operation of each structure are analyzed. Families of graphic dependencies are given. The analysis of the existing principles and algorithms for testing multiprocessor multimodal onboard digital computer systems is given; the new testing algorithm for the multiprocessor systems which follows the software design standards for products of integrated modular avionics is offered. The structure of the unified automated workplace for checking the functional modules of integrated modular avionics is considered. Specific requirements inherent in the workplaces for testing integrated avionics are identified: an increased level of control of the hardware component of products; the ability to simulate the failure state of individual components of avionics to check the mode of reconfiguration of the computer system; modular construction of software with the division of verification tests into components performed at the level of each CPM and the computer as a whole in single-task and multitasking modes; openness of architecture of a workplace, which provides an ability to change the level of control complexity of a product and control of one class of complexity; intra-project unification of both hardware and software of the workstation of the inspection.

METHODS OF DEVELOPING INTEGRATED MODULAR AVIONICS SYSTEMS

The development of modern avionics systems makes the design of such systems impossible without the use of automation tools. Currently, the area of such tools is represented by patented tools developed by major aircraft manufacturers such as Boeing and Airbus, as well as a number of open or partially open international projects, differing in terms of validity, availability of source code and documentation. All tools are based on architectural models of the developed system. This article discusses the languages available for describing architectural models of avionics systems and shows which programming language is most appropriate due to its textual notation and embedded concepts that are well suited to represent most of the elements of embedded systems. The article then presents a set of tools for designing modern avionics systems. The toolbox provides both a general platform for designing and analyzing architectural models and a specialized solution for a specific area of avionics systems. It supports creating, editing and manipulating models in both text and graphic formats.

Research on typical fault classification method of DC-DC converter

DC-DC converter is the core component of power conversion module of integrated modular avionics. Condition monitoring and fault diagnosis of DC-DC converter can effectively improve the reliability of avionics equipment, reduce the maintenance cost and greatly improve the use efficiency of aircraft. In this paper, firstly, a typical DC-DC converter model based on SEPIC topology is designed in PSPICE environment, and the failure modes of DC-DC converter are analyzed. Secondly, the typical fault types of DC-DC converter are simulated, and the corresponding original data are obtained through simulation. Finally, the processing framework including data preprocessing, feature extraction and selection, and multi model fusion is used to do fault classification of the DC-DC converter. The fault diagnosis of the converter is simulated. Simulation results show the effectiveness of the proposed method.