Composite guidance method for maneuvering target

The invention discloses a composite guidance method for a maneuvering target, which comprises the following steps of: respectively calculating required overload in real time by optimizing a guidance law and a proportional guidance law, adjusting the weight of the required overload through a fuzzy control switching function to obtain composite required overload, and finally transmitting the composite required overload to a steering engine system enabling the steering engine system to perform steering work according to the composite required overload and control the flight attitude of the aircraft, wherein the normal acceleration of a target is obtained in real time through a specially arranged target observer, and the required overload is adjusted by setting a reasonable fuzzy control switching function, so that the flight attitude is stable, the energy loss is small, and the hit rate is high; the normal acceleration of the target is obtained in real time through the specially-arranged target observer, so that