| 摘要 |
<p>A release mechanism between a projectile (1) and a rocket motor (10) in a missile is disclosed. The projectile (1) releases from the rocket motor (10) during the flight thereof when the rocket motor (10) is burned out and retardation occurs. The front end of the rocket motor (10) comprises a forward closure (7,7'), one in the forward closure (7,7') received and movable locking means retainer (2), at least one locking means (3), at least one spring means (6) that bias against the locking means retainer (2) in a direction opposite to the direction of motion for the missile. The rear end of the projectile (1) has a central boss (4) surrounded by said forward closure (7,7') of the rocket motor (10), where the boss (4) comprises recesses or a circumferential groove (14) in which the at least one locking means (3) is lying and keeps the forward closure (7,7') and boss (4) axially together.</p> |
