| 摘要 |
PURPOSE:To keep the combustion chamber pressure constant at a time when a rocket is detached from a nozzle closure by connecting the rear periphery of a rocket nozzle to the nozzle closure by a fixing means, by which fixing can be released, when the combustion pressure reaches the prescribed level. CONSTITUTION:A nozzle closure 17 is fixed to a rocket motor 11 via a shear pin 18. the total shear strength of these shear pins 18 is set at a value larger than the maximum ignition pressure P1, which is idicated by the high speed, high tempeature combustion gas in an ignited ignitor when it escapes through as exhaust nozzle 17a after is passes through a combustion chamber 20 and is reversed in its course at a forward part 14a. The said shear strength is also set in such a manner that the shear pins 18 are sheared when the combustion pressure reaches the prescribed pressure P2 after all the propellant is ignited. With these contrivances, the pressure in the combustion chamber 20 at the time when a rocket is detached from a nozzle 17 does not fluctuate much so that a rocket motor with high performance can be obtained. |
