ON-BOARD AIRCRAFT ENGINE MONITORING SYSTEM AT LIMITING ROTATIONAL SPEED, TEMPERATURE, FUEL PARAMETERS AND PRESSURE

FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines. ^ SUBSTANCE: proposed system uses information transmitted from respective sensors to inputs of multiplexing unit and to on-board computer from output of this unit. Information from sensors of important parameters of aircraft engine is delivered directly to command unit input. Present magnitudes measured in on-board computer and in command unit on basis of algorithms introduced in their storage and information on dangerous parameters of engine: rotational speed of high-pressure compressor rotor, turbine outlet temperature, consumption and pressure of fuel, pressure of gas after fan doors are compared with limiting dangerous magnitudes and limiting commands are formed and transmitted to on-board computer and to emergency information system for warning the crew. Actual operating time and residual service life of aircraft engine are determined in on-board computer with commands thus obtained taken into account and are transmitted to on-board information system for indication and recording. ^ EFFECT: possibility of monitoring engine in standard, off-standard and augmented power rating conditions. ^ 2 dwg