Aircraft attitude adjustment path optimization method based on rotation

[0114] For the sake of illustration, the relevant coordinate axes are defined first. In the present invention, the star sensor and the optical fiber inertial set are installed in strapdown, and the roll axis of the aircraft carrier is defined as y b axis, the pitch axis of the carrier is x b axis, the carrier heading axis is z b axis, x b 、y b ,z b The three axes conform to a right-handed coordinate system, and the x b 、y b ,z b Denote it as the b system; define the navigation system x n axis points due east, y n Axis points to true north, z n axis pointing towards the sky in the direction of gravity, the x n 、y n ,z n It is recorded as the n system, where the optical axis of the star sensor and the rolling axis of the aircraft carrier y b The axes point the same way. The present invention will be further described below in conjunction with the accompanying drawings, but it should be understood that the protection scope of the present invention is not limited theret