Control System of the Aircraft’s Propulsion Device at Take-off with the Derated Thrust

The nonlinear control system of the aircraft propulsion system at take-off with the derated thrust at a running start stage on the runway (R) is considered. The mathematical model of rise of an object taking into account the different perturbing influences, such as starting mass, status of a surface of the runway, wind perturbation, real value of the engine’s thrust is analyzed. The settlement trajectory of running start based on of a priori the set model parameters of an object and the environment is defined. For the solution of a task of thrust control, at a deviation of model parameters of an object and the environment from rated values, the nonlinear control law draft is under construction. In work, the scheme of synthesis of a thrust control system, which is implemented based on a method of linearization of nonlinear model by feedback on an output, is offered. This method comes down to creation of nonlinear differentiable conversion of initial coordinates. With use of an assumptions the robust nonlinear control law providing forming a controlt signal with engine’s thrust for deviation compensation between rated and real running start trajectories in the absence of complete a priori information about take-off parameters was constructed. Conditions of respect for technical stability of running start of the aircraft, taking into account restrictions on the maximum value of draft of the propulsion system and the maximum length of running start on the runway were investigated. And the criterion of the emergency termination of take-off of the aircraft, when resources of the propulsion system do not allow to compensate the having mismatch between settlement and real trajectories of running start is offered. The received criterion allows to form a signal for take-off stopping and passing to the mode of the emergency termination of running start on the runway.