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.