Abstract: In view of the fact that the output of line of sight angular rate error was big in the test of certain laser seeker, it was pointed out that line of sight angular noise root in the detector noise together with bomb disturbing and friction moment. Then stable tracking loop model was built based on the control principle of the laser seeker, the influence of above-mentioned error on tracking performance and los angular rate of the laser seeker was quantificationally analyzed. The characteristic of los angular rate noise of the laser seeker was analyzed, the function relationship with distance between missile and target was deduced by experiment method. Finally, the los angular rate noise was joined into control and guidance model of the laser guided missile. Simulation result showed that roll angle of missile and rudder departure angle varied obviously, angular noise changed small gradually along with the close up of missile and target and the miss distance varied less, which was accordant with actual test phenomenon. When the angular instruction was situated in the peak value of the angular noise, deviation of missile couldn't be modified timely, which possibly affected attack area of missile along with close up of missile and target. The research provids reference for further actual test of laser seeker and tactical application of missile.