AIRCRAFT ENGINE AIRBORNE MONITORING SYSTEM WITH LIMITATION OF SPEED, FUEL PARAMETERS AND PRESSURE Russian patent published in 2005 - IPC

FIELD: instrumentation engineering.

SUBSTANCE: invention can be used for on-board control of aircraft engines, mainly, gas-turbine engines. For this purpose use is made of information getting from pickups of controlled parameters of engine to inputs of multiplexing unit and from output of said unit into airborne computer. Information from pickups of most important parameters of aircraft engine is supplied directly to input of command unit. In airborne computer and command unit, basing on calculating algorithms kept in memory and information from pickups on values of dangerous parameters of aircraft engine, namely, speed of high-pressure compressor rotor, fuel rate and pressure and gas pressure behind fan flaps, measured current values of signals from pickups are compared with calculated current values of limiting and emergency values and, if signal values come out of the limits of limiting and emergency values, limit and danger commands are formed and transmitted into airborne computer and into aircraft emergency information system for recording and warning the crew. In airborne computer, with account of received commands, actual engine operating time and residual service life of aircraft engine are determined and transmitted into airborne information system for indication and recording.

EFFECT: possibility of checking condition of aircraft engine at standard, abnormal and augmented duties.

2 dwg