| 摘要 |
FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines. ^ SUBSTANCE: proposed system employs information transmitted from aircraft engine parameter sensors to multiplexing unit input and to on-board computer from output of this unit. Information transmitted from sensors of important parameters of engine is transmitted directly to command unit input. Present measured magnitudes are compared with limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and information received from sensors: rotational speed of high-pressure compressor, consumption and pressure of fuel, pressure of gas after fan doors and thrust. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for recording and 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 the aircraft engine in standard, off-standard and augmented power rating conditions. ^ 2 dwg |
