Reduced-dimensional MPC controller for direct thrust control

With the development of aircraft gas turbine engine, a control system should be able to achieve effective thrust gain better operability. The main contribution this paper is develop novel direct approach based on an improved model predictive method through strategy that reduces dimension sequence. It can not only normal tasks but also maximize level within safe operation boundaries. Only action switching objective functions required switch these two modes while there no modification structure. Besides, shorter sequence defined for multivariable by updating one variable at every simulation time instant. Therefore, requirement solving process optimal reduced. proposed controller implemented twin-spool engine. Simulations are conducted in wide flight envelope, and results show average time-consumption reduced up 65% comparison with standard control, increased significantly when maximum mode using engine limit margins.