Rocket projectile separating mechanism

The invention relates to a rocket projectile separating mechanism and belongs to the field of civil rocket projectiles. The separating mechanism comprises a separating main body, a locking pin, a separating rod and a fuel gas actuator, wherein one end of the locking pin is fixed to a connecting body, the other end of the locking pin penetrates through the separating main body to achieve axial location between the rear end of the separating main body and a rear connecting body through the axial location between the separating rod and the locking pin, the separating rod and the locking pin are in rotary connection with the separating main body, and the front end of the separating main body is fixed to a front connecting body in a threaded mode. In separation, the fuel gas actuator pushes the separating rod to rotate to enable the rear end of the separating main body to be axially unlocked away from the rear connecting body. The rocket projectile separating mechanism uses circumferential opening force, so that the effect on projectile body flying attitude is little. The opening force is damped by a rotating structure, so that other components of a projectile body cannot be damaged. Thus, the technical problem that a traditional separating mechanism has high requirements for the strength of separating parts and the separating explosive quantity is solved. In addition, the rocket projective separating mechanism has important popularization and application values.