The invention provides an SINS / CNS integrated
navigation system based on comprehensive optimal correction and a navigation method thereof, and belongs to the technical field of integrated navigation. The integrated
navigation system comprises an astronavigation subsystem, an
inertia navigation subsystem and an
information fusion subsystem. The navigation method comprises the following steps: analyzing celestial fix based on
starlight refraction, building up
navigation system state equations, building up navigation
system measuring equations and performing
information fusion of an integrated navigation
system based on Kalman filtering. According to the invention, by utilizing the basic principle of
starlight refraction indirection sensitive
horizon and a large viewing field
star sensor, the characteristics of a plurality of
fixed stars can be observed at the same time, and the
starlight refraction indirection sensitive
horizon method is applied to aircrafts that do not fulfill track
kinetics, so that the problem of high-precision autonomous
horizon of the
celestial navigation system is solved. According to the invention, position and posture information of the
celestial navigation system are fully utilized to perform comprehensive optimal correction on the SINS deviation, so that the integrated navigation accuracy is significantly improved.