| 摘要 |
<P>PROBLEM TO BE SOLVED: To improve a ratio of a propellant to be filled, while stably burning the propellant of a flying body. <P>SOLUTION: A rear opening part for releasing pressure generated by combustion of the inside propellant is arranged on one end in a combustion chamber. A first propellant is filled in the rear opening part side in the combustion chamber while forming a first cavity around the axis in the longitudinal direction of the combustion chamber. The propellant for a partition wall is filled in a predetermined thickness in the other end side of the combustion chamber from an end surface of the first propellant. A second propellant is filled up to the front of the combustion chamber from a boundary surface while forming a second cavity up to a boundary surface with the propellant for the partition wall around the axis in the longitudinal direction of the combustion chamber. A first igniter starts first stage combustion by igniting the first propellant. A second igniter is arranged inside the second cavity, and determines whether the second stage combustion start time has come based on the elapsed time from the first stage combustion start time, and starts second stage combustion by igniting the second propellant. <P>COPYRIGHT: (C)2012,JPO&INPIT |
