The application discloses an aero-engine thrust fast response redundant control method and
system considering
combustion delay, and belongs to the technical field of aero-engine control. The method steps are as follows: an open-loop
transfer function L of main fuel flow and
tail nozzle throat area respectively controlling thrust is established based on a desired thrust closed-
loop bandwidth; a decoupling condition between the variable
tail nozzle throat area and the thrust is set to eliminate the
mutual influence between them; four undetermined RTM controller functions in the
transfer function L are solved; the
actuator transfer functions of the main fuel flow and the
tail nozzle throat area are set as first-order systems for solving;
system identification is carried out at an engine steady-state working point to obtain a
transfer function of a difference between the main fuel flow and the tail
nozzle throat area relative to a steady-state value to a difference between the thrust and the steady-state value; the transfer function L is solved, and then the RTM control is completed according to the transfer function L, so that the fast
response control of the thrust is realized. The application solves the key technical problems in the prior art.