| 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 inputs and to on-board computer from output of this unit. Information received from sensors of very important parameters of engine is transmitted directly to command unit input. Present limiting and dangerous magnitudes are compared with preset magnitudes in on-board computer and in command unit on bases of algorithms and information of sensors introduced in their storage. 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 hours 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 |
