Device for measuring the roll rate or roll attitude of a missile

A rate gyro (10) is arranged in a seeker head of a missile and is stimulated to nutate with its natural nutation frequency in inertial space for the purpose of scanning a field of view. The rotational frequency and the nutation frequency of the rate gyro (10) relative to the missile are determined. The roll rate or roll angle is achieved by subtraction of these frequencies multiplied by suitable factors depending on the gyro in a roll measuring circuit (32).