| 摘要 |
FIELD: aircraft industry. ^ SUBSTANCE: invention relates to aircraft instruments and it can be used for in-flight monitoring of aircraft engine, mainly, gas-turbine engine, using on-board computer and command unit. According method, limit and critical parameters are revealed from controllable parameters of aircraft engine and limit and critical values of said parameters are found, parameter settings are introduced into memory of on-board computer through command unit for calculating limit and critical values and also time of tolerable operation of aircraft engine at afterburning and algorithms of calculations of current values of limit and critical values as function of current values of parameters of aircraft engine and algorithms of calculation of effective, forced and actual running times and residual service life of aircraft engine, and current values of limit and critical values are calculated in on-board computer and results are delivered into command unit, current values of controllable parameters are supplied to input of on-board computer, and current values of limit and critical parameters of aircraft engine are supplied to input of command unit, and current values of said parameters are compared in command unit with current values of limit and critical values, and if parameter values comes out of limits of limit or critical values, corresponding commands are formed and transmitted into aircraft emergency system and into on-board computer, and said computer calculates actual values of running time and residual service life of aircraft engine using said commands and measured time of operation of engine at afterburning and transmits them into interacting on -board information systems, measured time of operation of aircraft engine at afterburning is compared with tolerable time and if tolerable time value is exceeded, corresponding command is formed which is transmitted through command unit into aircraft emergency system. ^ EFFECT: possibility of checking condition of aircraft engine at standard, emergency and afterburning operation. ^ 2 dwg |
