For the problem of attitude oscillation during projectile low-speed rotating flight, the rotating speed and overload sensors are usually used to measure the flight quality. When the attitude oscillation occurs, the nutation can only be found based on the overload signal, but cannot be quantitatively analyzed. To solve this problem, the approach of the rocket attitude oscillation quantitative analysis is provided, and the flight nutation process is reconstructed by the frequency characteristic analysis of flight overload sensor signal in the body coordinates. The analysis result and analysis approach are verified by trajectory simulation. The analysis approaches can provide the judgment basis for the flight state and flight quality.