Partition optimization in the flight envelope for control design of aero-engines

According to the optimization theory and linear system theory,the method of flight-envelop optimization partition for aero-engines is researched.First,linear state variable mode (LSVM) was used to describe aero-engine’s dynamic characteristic of small perturbation on steady operating point,and the perturbation between LSVMs was denoted by the perturbation of coefficient matrix eigenvalues and low-frequency gains of the LSVMs.Then,a general distance based on the perturbation of eigenvalues and low-frequency gains of the LSVMs was put forward.And the problem of dividing the flight envelope and selecting the nominal points in a flight envelope was translated into a most overlay problem.Thus,based on the general distance,a set of least number of nominal points could be found to divide the flight envelope by using optimizing method.Last,a flight envelope area of a turbofan engine was divided by using this method,and the results indicated that this method was proper.