| 摘要 |
<p>An apparatus is disclosed for stage separation and thrust termination in a multi-stage missile having an upper stage (14) detachably connected to a lower stage rocket motor (12). The apparatus includes a piston (16) located at the forward end of the lower stage rocket motor (12) in fluid communication with the motor's combustion chamber (18). The piston (16) is configured with a plurality of venting passages (48), and capable of deployment from a stowed position, in which the venting passages (48) are sealed, to an extended position, in which the venting passages (48) are unsealed. The venting passages (48) are preferably configured to vent the combustion chamber (18) at an angle to the upper stage (14), providing the lower stage rocket motor (12) with a component of thrust away from the upper stage (14) after detachment, without damaging the upper stage (14).</p> |
