| 摘要 |
FIELD: aircraft industry. ^ SUBSTANCE: proposed method comes to control of gas-turbine engine by main electronic channel, control of actuating elements of main electronic channel providing control of gas-turbine engine, switching off of main electronic channel in case of its failure or failure of actuating elements with subsequent changing over to standby hydromechanical channel by means of channel selector at measuring, in main control channel, of at least speed of rotation nnpc of high-pressure compressor, and fuel delivery Gf to combustion chamber. According to invention, when engine is controlled by main electronic channel preset speed of rotation is additionally set, and measured speed of rotation nnpc is compared with preset value and at first logic signal I1 is formed and presence of ENGINE STOP signal is determined and if signal I1 and ENGINE STOP signal are present, second logic signal I2 is formed, and at presence of signal I2, test action is set which provides short-time successive sensing of signal to switch on selector from main to stand by channel and sensing of signal I4 to actuating element of main channel to increase flow rate of fuel Gf, and preset value of fuel flow into combustion chamber is provided and measured value Gf is compared with preset value in process of sending of signal I4 and at fifth logic signal I5 is formed, and at simultaneous presence of signals I4, I5, sixth logic signal I6 if formed indicating that channel selector of automatic control system is faulty. Signal to change over selector from main to stand by channel is sent for period of 1 s, and signal I4 is sent 0.5 sec later than selector change-over signal for time equal to 0.5 s. ^ EFFECT: improved reliability of operation of two-channel automatic control system owing to functional control of channel selector in process of engine switching off at end of flight. ^ 2 cl, 1 dwg |
