Two-pulse rocket motor

Abstract

In the two-pulse rocket motor in accordance with the present invention, the second propellant is set outside of the first propellant in a motor case, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case. Therefore, the initial burning area can be secured without deteriorating the performance. Also, by providing a weak part by bonding the barrier membranes or shaping slits on the barrier membrane, the breaking portion of barrier membrane and the behavior of barrier membrane after breakage can be controlled. Further, by setting an igniter charge having higher ignitability and a higher burning rate than the second propellant between the inner surface of the second propellant and the inner barrier membrane, the detachment of barrier membrane and the ignition of the second propellant can be assisted.

1 . A two-pulse rocket motor having a motor case, comprising:
 a first propellant;   a second propellant;   a second igniter set on an end surface of the second propellant;   a barrier membrane that covers an initial burning surface of the second propellant entirely and the second igniter; and wherein   the first propellant is loaded so as to cover the barrier membrane entirely, and wherein   the first propellant and the second propellant each has an internal burning type or an internal and end burning type of propellant grain design, and   wherein the barrier membrane has notches on it.   
     
     
         2 . The two-pulse rocket motor according to  claim 1 , wherein the second igniter is set on an aft end surface of the second propellant. 
     
     
         3 . The two-pulse rocket motor according to  claim 1 , wherein an igniter charge having higher ignitability and a higher burning rate than the second propellant is set on an inner surface of the second propellant. 
     
     
         4 . The two-pulse rocket motor according to  claim 3 , wherein an igniter charge is set in plural slots, which are shaped on the inner surface of the second propellant in the axial direction around the longitudinal axis.