JP2005171970A5 - - Google Patents

Claims (5)

Jetting nozzle 4 is disposed behind,
The first combustion chamber 1 and the second combustion chamber 2 are disposed in front of the injection nozzle 4 in such a state that the first combustion chamber 1 and the second combustion chamber 2 are coupled in series in this order or through the joint 3
A first propellant 6 having a hollow portion penetrating front and rear in the first combustion chamber and a second propellant 7 having a hollow portion penetrating front and rear in the second combustion chamber, respectively;
One or more through holes are provided in the wall surface of the position where the first propellant 6 is selectively ignited, and a mechanism for igniting the first igniter 10 is attached to the front end of the first ignition housing 12. A first ignition housing 12 having a first sealing body 14 and loaded with a first igniting agent 10 is disposed on a front and rear central axis in the first combustion chamber,
One or more through holes are provided in the wall surface at a position where the hollow wall surface of the second propellant 7 is directly ignited, and a mechanism for igniting the second igniter 11 is attached to the front end of the second ignition housing 13. A second ignition housing 13 having the second sealing body 15 and the second ignition powder 11 loaded therein is disposed in the hollow portion of the second propellant 7;
A diaphragm 9 having an outer peripheral end fixed on the entire circumference of the rocket motor body and an inner peripheral end fixed between the first ignition housing 12 and the second ignition housing 13 is a first propellant. 6 and the second propellant 7 are disposed to be isolated from each other,
The diaphragm 9 is not broken or lost by the gas generated from the first igniter 10 and the combustion gas from the first propellant 6, but is broken or lost by the combustion gas from the second propellant 7 and the gas generated from the second igniter 11. Two-stage thrust type rocket motor. The two-stage thrust rocket motor according to claim 1, wherein the diaphragm 9 is EPDM rubber, silicone rubber, EPDM rubber or silicone rubber containing organic fibers, or EPDM rubber or silicone rubber containing inorganic fibers . The two-stage thrust rocket motor according to any one of claims 1 to 2 , wherein the diaphragm 9 is bonded to the rear end face of the second propellant 7 or the hollow wall surface of the second propellant 7. . A mechanism for igniting the first igniting agent 10 penetrates all of the first initiator 26, the second sealing body 15, the second ignition housing 13 and the first sealing body 14 connected thereto, and the first ignition housing. body 12 internal and stretching out to, and according to any one of claims 1 to 3, characterized in that it consists of tube 23 having a JoSoyaku 24 therein for propagating ignition of the initiator 26 Two-stage thrust type rocket motor. And mechanism initiator 22 to ignite the second ignition charge 11, in the second sealed member 15, claim 1-4, characterized in that it consists of second JoSoyaku 21 for propagating the ignition of the initiator 22 The two-stage thrust type rocket motor according to any one of the above.