Abstract
The subject of the research is the application of the method of parrying sensor failures - one of the modern progressive approaches to ensuring the smooth and efficient operation of complex automatic control systems. This article is devoted to the application of this method in the control of a small-sized aircraft engine, which is an actual solution for the development of the aviation industry. The purpose of this study is to choose the optimal method for parrying sensor failures of a small-sized aircraft engine by analyzing existing methods and choosing engine parameters that should be used for parrying. Tasks. Consider the main methods of countering sensor failure and justify the choice of the most effective one. To state the main principles of the method of replacing the parameter value at all stages of the development of the control unit for the operation of a small-sized aircraft engine and to carry out an analysis of the disadvantages and advantages of such an approach. Consider algorithms for identifying and countering sensor failures for the engine management system. Analyze the simulation of individual parameters of a small-sized aircraft engine and propose parameters that should be replaced in the event of sensor failure. Research methods. Comparative analysis of methods of parrying sensor failures and models for simulating the parameters of small-sized aircraft engines with adjacent ones. The results. The method for replacing the parameter value with an adjacent one, switching to a backup value, redundancy, and the use of backup data sources are analyzed. Among the parrying methods, the two most optimal ones are selected (the method of replacing the value of the failed sensor parameter with an adjacent parameter and the method of switching to a backup value) and their work algorithms are described. The advantages are increased reliability and efficiency of engine operation, prevention of information loss, adaptability, and improved diagnostics. Among the shortcomings, the existence of risks of erroneous measurements, complex settings, accuracy limitations, dependence on other parameters, cost and complexity of the system are highlighted. Using the example of the ECU-35 unit developed by JSC "Element", the model of replacing the engine rotor speed parameter using the current temperature of the gases behind the turbine, taking into account the calibration of the measurement channel, was described. Conclusions (scientific and practical novelty). It was found that the application of the method of identification and parrying of sensor failures ensured the smooth operation of the control system when individual sensors failed. Thanks to the method for parrying sensor failures, it was possible to achieve a significant improvement in the performance of a small-sized aircraft engine.
Keywords
sensor failures parrying; parameter simulation; substitution method; conversion function; parameter reconstruction; transition to a reserve value; redundancy; backup parameter; the condition of a small aircraft engine
References
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Shahmatov, E. V. & Shorin, V. P. Sistemy avtomaticheskogo regulirovaniya aviatsionnykh GTD [Automatic control systems for aircraft gas turbine engines]. Kuibyshev, Kuibysh. aviats. in-t, 1990. 122 p.
Gol'berg, F. D., Gurevich, O. S. & Petuhov, A. A. Primenenie programmnogo obespecheniya «virtual'nyi dvigatel'» v sisteme avtomaticheskogo upravleniya gazoturbinnogo dvigatelya [Application of software "virtual engine" in the automatic control system of a gas turbine engine]. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroenie – Vestnik of Samara University. Aerospace and Mechanical, 2016, vol. 15, no. 4, pp. 47-56.
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