The invention discloses a calibration method for a strapdown inertial navigation installation attitude of a photoelectric
tracking system. The calibration method comprises the following steps: establishing a coordinate
system n
system, a coordinate
system b system, a coordinate system t system and a coordinate system
s system; conducting the strapdown inertial navigation initial alignment for multiple times, obtaining the average value, and obtaining a strapdown inertial navigation initial attitude Euler angle; sequentially placing the
theodolite with the
azimuth reference at each measurementposition, completing alignment, recording an
azimuth angle and a
pitch angle of the
theodolite with the
azimuth reference and an azimuth angle and a
pitch angle of a photoelectric
tracking system, performing north-seeking for multiple times, recording a north-seeking result average value, and calculating a vertical disc index difference; establishing an attitude matrix vector r which is parallel to the
visual axis of the photoelectric
tracking system, takes a unit vector of which the starting point is the origin of the coordinate system, the coordinate of the vector r being vector r<s> in the
s system, calculating the attitude matrix C<s><t>, i of from the t system and the
s system, according to the vector r<s> and the C<s><t>, i, calculating the
coordinate vector r<t>of thevector r in the t system, calculating the
coordinate vector r<n>of the vector r in the n system, calculating the attitude matrix C<n> from the n system to the b system according to the Euler angle, calculating the
coordinate vector r of the vector r in the b system according to the vector r<n> and C<n>, establishing a linear equation (as shown in the description) according to the vector r<t> and the vector r, and solving C<t> by combining with the k linear equations. The the method can be used for indoor calibration.