Self-tuning Process of the Control Laws of the Aviation Gas Turbine Engine

Abstract

The article is devoted to the selection of parameters and evaluation of the efficiency of an aviation engine based on a system approach, when the engine and power plant are considered as subsystems of a higher-level aircraft complex. To solve the problems of multiparameter optimization, complex mathematical models of the entire system, consisting of the aircraft and control systems, taking into account the properties of the used fuels, are developed. The integration of the aircraft engine and the aircraft is carried out on the basis of the conditions for ensuring mass balance, the volume layout of the starting thrust-mass ratio. In combined power plants, it is possible to consider engines of different types, for example, TPrE with parallel or sequential (tandem) arrangement of circuits, TRBEaf and ramjet and steam hydrogen rocket-turbine engines of several types, the parameters of the working process of which are optimized according to the conditions of a typical program flights The adaptation task can be solved by changing both control programs and parameters of intellectual regulators of individual subsystems, as well as the structure of individual subsystems and connections between them. The higher level determines which strategy and which adaptation algorithm to choose in this situation. The optimal behavior model of the system in the current situation is also determined here. At the next level (the level of the technological complex), a strategy for the integration of the control and planning systems of the gas station, technological equipment and information system is formed, depending on the modes of operation of the gas station and the fulfillment of the tasks set before it. The construction of the ACS GTE model in the VisSim modeling software package was completed, measures were taken to stabilize the system. The transfer functions of the main elements of the electronic automatic control system of the GTE were obtained: a speed sensor, a thermocouple, and a pressure sensor. sensor of the angular position, the actuator mechanism of the nozzle-valve, the movement of the aircraft by the pitch angle.