Abstract: Controlling an in-flight spin-rate of a spin-stabilized guided projectile is disclosed. In various embodiments, the projectile includes a despun control portion configured for despinning relative to a projectile chassis and for directional control of the projectile. In various embodiments, controlling the in-flight spin-rate includes determining a gyroscopic stability factor for the guided projectile using the in-flight spin rate and a forward velocity of the guided projectile, determining that the gyroscopic stability factor exceeds a stability threshold, and spin-braking the guided projectile, in response to determining that the gyroscopic stability factor exceeds a threshold value, by braking rotation of the despun control portion by which the gyroscopic stability factor of the guided projectile is reduced to a second gyroscopic stability factor.