Automatic Control of Aircraft Engine in Conditions of Stand Test

The general principles of automatic control of aircraft engines and functionally related systems in the conditions of their stand tests are suggested. These principles are prospectively reduced to six sequentially implemented procedures or steps. In accordance with these principles, the control of aircraft engine parameters is carried out by a computer-aided test equipment (CTE) based on a computer complex that implements algorithms based on Boolean algebra and the algebra of events and states. These algorithms allow control procedures to be carried out in dynamic mode in accordance with the schedule of testing an aircraft engine. With this control, the specified sequence of operating modes of the aircraft engine undergoing testing is observed without fixing them in time and with the possibility of skipping or repeating individual modes. Parameters are monitored at each of the next aircraft engine operating modes only after all parameters are checked in the previous mode and the value of the main determining parameter reaches the value determined for this mode. During the period of transient processes, parameters are controlled only at the points of extremum of the values of the main determining parameter with fixing the time of transient processes and determining that. "In the tolerance" or "not in the tolerance" is the checked parameter and the fixed time interval. Upon arrival of the signals from the monitoring object, the time of occurrence of which is unknown, and only the time interval during which they can appear is known, any of the CTE operation modes are terminated, tolerance control of the parameters provided by the program is performed, and the previously interrupted mode is restored. Simultaneously with the tolerance control of the parameters, the time of arrival of the above signals is recorded. The group of emergency parameters is monitored continuously throughout the entire period of stand test.