No abstract

Розробка надійної системи визначення самоналаштовуваних параметрів регулятора в автоматичних системах керування газотурбінними двигунами (САК ГТД) принесе користь як військовій, так і цивільній авіації за рахунок підвищення надійності та ремонтопридатності повітряного судна. Представлена стохастична інформаційна система газотурбінного двигуна, яка об’єднує інформацію з різних сучасних методів аналізу керування для досягнення надійної поінформованості контуру самоналаштовування. У статті представлені обчислювальні методи ідентифікації точної послідовності параметрів регулятора за допомогою: по-перше, застосування функції Ляпунова з аналізатором характеристик для забезпечення стабільності процесів оптимізації; по-друге, застосування функції Вінера-Хопфа з генератором білого шуму (випадкові процеси) для визначення інтенсивності та імпульсної перехідної функції сигналу, як результат, точного налаштування блоку управління авіаційним двигуном. Основний контур керування представлений передавальною функцією об'єкта та регулятора, їх моделями самоналаштовування, критеріями встановлення параметрів регулятора та чутливою функцією. Важливою особливістю інформаційної системи газотурбінного двигуна є наявність неоднорідного апаратного та програмного забезпечення, яке часто пов'язане з тривалим періодом підтримування експлуатації системи, необхідно використовувати мобільний обслуговуючий пристрій і хост запиту для задоволення вимог правильної експлуатації двигуна.

The article is devoted to the formation of requirements for the accuracy of regulation of an aviation gas turbine engine, one of which is the maintenance of engine thrust at a given operating mode, regardless of the engine condition, within the gas temperature margin. Its value should not be significantly affected by turning on or off additional power and air consumers, as well as various regulatory influences on the part of the automatic control system (turning on or turning off the bypass in the compressor and blowing the housings, partial restriction of the supply of cooled air, changing the position of the guiding devices). Fulfilling the requirements for the accuracy of regulation is important for ensuring the reliability and safety of the operation of the power plant and the convenience of controlling the aircraft. In order to reduce operating costs, it is necessary that during operation, a minimum number of additional settings of the ACS in the acceleration mode, gas reset and start-up mode are required. The control program is implemented in the form of a automatic control system (ACS), which is a closed circuit of the main feedback. There is also a flexible local feedback loop in the circuit, which is designed to stabilize the ACS, which contributes to the fact that the ACS is quite stable. The presence of feedback in the ACS indicates that the system may be unstable, so the analysis of the ACS should include an assessment of its stability and, if necessary, the selection of measures and means for its stabilization. Changing the input signal at the first moment of time leads to a corresponding increase in deviation, since the links in front of the object and the object itself have inertia and therefore the rotation frequency cannot change instantly. The change in deviation, being an amplified amplifier, thyristor converter and generator, taking into account their inertia, leads to a gradual change in the control value, the voltage on the anchor, which smoothly changes the frequency of rotation of the shaft so that the tracking error, that is, the deviation, is directed to zero. Voltage feedback stabilizes the ACS and increases its speed. This is how tracking is done. The implementation of wireless technologies in the ACS of the gas station has been studied, which will allow to reduce the mass and dimensions of the nodes due to the reduction of the number of connectors and cables, increase the reliability and accuracy of the adjustment of the ACS, reduce maintenance costs and increase fire safety.

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.

The article is devoted to the solution of an important scientific and applied problem of improving the dynamic characteristics of an aviation engine and ensuring flight safety and the efficiency of aircraft operation, taking into account the properties of adaptive control of an aviation gas turbine engine: <structure><functioning><adaptation><development>. Based on the concept of creating perspective aviation engines with an increased level of control automation and with units operating at elevated temperatures and protected from high-energy electromagnetic radiation, the basic laws of controlling an aviation gas turbine engine in throttle modes, low-throttle mode, gas intake and discharge modes, and start-up mode are defined. To improve the working process of the engine, it is proposed to use the gas turbine engine control system as a mechatronic system based on the principle of adaptation. With the help of the Laplace transformation, the dynamic characteristics of the power plant were determined and the mathematical model of the power plant was investigated as a constructive aspect of the automatic control system. The gas turbine and the supersonic air manifold can to some extent be considered as independent control objects, replacing the connections between them with disturbing influences. For the control and limitation circuits, it is necessary to create control programs that calculate the values of the control parameters of the turbocharger rotor speed and gas temperature behind the turbine. Regulation of fuel consumption is carried out according to the derivative of the control parameters.