JP2904409B2 - Thrust suspension device for solid rocket motor - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a capsule for accommodating a payload, and a thrust suspension device for a solid rocket motor in a separation device for a flying object provided with a solid rocket motor for applying thrust to the capsule.

[0002]

2. Description of the Related Art As shown in FIG. 3, in a flying object constituted by connecting a capsule 6 containing a payload and a rocket motor chamber 8, when the capsule 6 is separated from the rocket motor chamber 8, the capsule 6 is separated by a rocket motor. And the rocket motor is operated so as to interrupt the thrust by reverse injection.

FIG. 4 shows a conventional example of such a rocket motor thrust interruption device. FIG. 4 is an enlarged sectional view of a portion A in FIG. In FIG. 4, the rocket motor chamber 8 accommodates an ignition device 1 having a main ignition charge 2 at an axial center thereof.

The periphery of the igniter 1 is filled with a propellant 9, and the propellant 9 is formed with a flame passage 13 extending obliquely forward from an axis. The end of the flame passage 13 is covered with a lid 11. The rocket motor chamber 8 and the capsule 6 are connected by a band 7 with a plate 5 interposed therebetween.

[0005] A conventional method of separating the capsule 6 and the solid rocket motor chamber 8 connected in this manner is as follows. First, the band 7 is cut by a pyrotechnic while the propellant 9 is burning. When the band 7 is cut, the igniter 1 moves to the position of the stopper 12 due to the combustion pressure in the solid rocket motor chamber 8, and pushes the capsule 6 through the plate 5 in the propulsion direction.

When the capsule 6 is extruded, the plate 5
The plurality of lids 11 provided on the outer skin of the solid rocket motor chamber 8 come off, and the flame passes through the flame passage 13 provided in the propellant 9, and the flame is released from the plurality of flame passages 13 with the lid 11 removed. The rocket motor acts as a reverse injection force larger than the thrust in the traveling direction, and interrupts the rocket motor thrust.

[0007]

As described above, the conventional thrust suspending device forms the flame passage 13 in the propellant in the rocket motor chamber 8, and the rocket motor chamber 8, which contacts the outside of the flame passage 13. And the structure is complicated.

As described above, the conventional thrust interruption device has a large number of parts and is complicated to assemble in order to prevent the flame of the reverse injection generated after the interruption of the thrust from affecting the payload. In addition, in the conventional apparatus, similarly, the molding of the solid propellant requires an additional step and is expensive.

According to the present invention, a capsule including a payload and a flying object separating apparatus provided with a solid rocket motor for applying thrust to the capsule have a small number of parts.
An object of the present invention is to provide a separating device for a solid propellant which is easy to mold and assemble.

[0010]

SUMMARY OF THE INVENTION In order to solve the above-mentioned problems in a capsule containing a payload and a flying object separating device provided with a solid rocket motor for applying thrust to the capsule, the present invention provides a capsule and a solid rocket motor. Has an igniter equipped with a base part which is protruded by the combustion pressure in the solid rocket motor and pushes the capsule in the propulsion direction when the solid rocket motor is disconnected. The present invention provides a thrust suspension device for a solid rocket motor having a configuration in which a plurality of flame injection nozzles for performing reverse injection are provided.

In the thrust interruption device according to the present invention, it is preferable that the flame injection nozzle is provided at a protruding portion of the base portion. Further, it is preferable that the flame injection nozzle is provided in an outward direction so as not to thermally affect the payload by the flame ejected from the nozzle.

In the thrust interruption device of the present invention having the above-described structure, immediately after the interruption of the thrust, only the central portion of the ignition device is pushed forward by the internal pressure due to the combustion in the rocket motor. As a result, the capsule containing the payload is pushed out in the traveling direction, and a distance that does not interfere with the rocket motor after the interruption is secured.

When the center of the ignition device is advanced by a certain stroke, it is restrained, and the flame of the reverse injection comes out from the flame injection nozzle in the base portion, and generates a reverse thrust. Here, the flame injection nozzle is formed, for example, obliquely from the advancing direction so as not to have a thermal effect on the payload, and the flame injection does not affect the payload.

[0014]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a thrust suspending device for a solid rocket motor according to the present invention will be described in detail with reference to the embodiments shown in FIGS. Note that, in the following embodiments, the same components as those of the conventional device shown in FIG.
A duplicate description of them will be omitted.

In FIG. 1, the rocket motor chamber 8
An outer cylinder 4 is provided at a tip end of the outer cylinder 4.
Stopper 1 for restricting protrusion of ignition device 1 as described later
Steps 2 are formed. The basic portion 3 of the ignition device 1 is fitted into the outer cylinder 4 and has a plurality of obliquely forward flame injection nozzles 14 formed therein.

The operation of the thus-configured thrust interruption device of FIG. 1 will be described. As the ignition signal, the battery in the capsule ignites the main igniter 2 and ignites the propellant 9, whereby the solid rocket motor of the flying object is activated. When the solid rocket motor operates and the detached flying object reaches the target position, an ignition signal is sent to the pyrotechnic 15 attached to the band 7 to cut the band 7, and the capsule 6 and the solid rocket motor chamber 8 are separated. Is done. When separated, the plate 5 fixed by the base part 3 becomes free.

At this time, the base portion 3 is moved forward (propulsion direction side) by the combustion pressure 16 in the solid rocket motor chamber 8.
The capsule 6 moves to the position of the stopper 12 of the outer cylinder 4 (the moving state is shown in FIG. 2). At this time, the capsule 6 is accelerated and pushed forward through the plate 5, and the capsule 6 and the solid rocket motor chamber 8 are moved. Is a distance that does not have a thermal effect on the capsule 6 even when the flame 10 is jetted.

The base portion 3 includes a stopper 12 provided on the outer cylinder 4.
At this time, the flame 10 generated by the burning of the propellant 9 from the plurality of flame injection nozzles 14 provided on the base portion 3 is extruded obliquely from the traveling direction by the combustion pressure and released. . At this time, the basic part 3
Needless to say, the shapes and dimensions of the plurality of flame injection nozzles 14 provided in the above must be set so as to generate a reverse thrust that overcomes the thrust generated at the rear end of the solid rocket motor. A counter thrust is generated by the flame 10 extruded by the combustion pressure 16, the output of the solid rocket motor chamber 8 is reduced, and the thrust can be interrupted.

[0019]

As described above, in the thrust suspension device for a solid rocket motor according to the present invention, when the capsule and the solid rocket motor are separated, the capsule is protruded by the combustion pressure in the solid rocket motor and pushes the capsule in the propulsion direction. The basic part has an ignition device that has a plurality of flame injection nozzles that injects the flame in the solid rocket motor in the reverse direction with respect to the propulsion direction by the combustion pressure. Is formed.

Therefore, the thrust interruption device according to the present invention can greatly simplify the manufacturing process and reduce the cost by simplifying the structure. Specifically, the molding of the solid propellant becomes easy, and the number of parts can be reduced. Thus, according to the present invention, assembling of a rocket and the like becomes easy.

[Brief description of the drawings]

FIG. 1 is an explanatory diagram of a structure of a thrust interruption device according to an embodiment of the present invention.

FIG. 2 is an explanatory diagram of an operation procedure of the thrust interruption device shown in FIG.

FIG. 3 is an overall view of a flying object employing a conventional thrust suspending device.

FIG. 4 is an enlarged sectional view of a portion A in FIG. 3;

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Ignition device 2 Main igniter 3 Base part 4 Outer cylinder 5 Plate 6 Capsule 7 Band 8 Rocket motor chamber 9 Propellant 10 Flame 12 Stopper 14 Flame injection nozzle 15 Pyrotechnic 16 Combustion pressure

──────────────────────────────────────────────────続 き Continuation of the front page (56) References JP-A-4-108100 (JP, A) JP-A-63-207800 (JP, A) JP-A-10-111100 (JP, A) 190795 (JP, U) Japanese Utility Model Showa 48-93600 (JP, U) U.S. Pat. No. 3,830,303 (US, A) (58) Fields investigated (Int. Cl. ⁶ , DB name) F02K 9/92 B64G 1/64 F02K 9/32 F42B 15/36

Claims (3)

(57) [Claims] An apparatus for separating a flying object provided with a capsule containing a payload and a solid rocket motor for applying thrust to the capsule, wherein when the capsule and the solid rocket motor are separated, combustion in the solid rocket motor is performed. An ignition device having a base portion which is protruded by pressure and pushes the capsule in a propulsion direction, wherein the base portion has a plurality of flames for injecting a flame in the solid rocket motor in a direction opposite to the propulsion direction by a combustion pressure; A thrust suspending device for a solid rocket motor, comprising an injection nozzle. 2. The solid rocket motor thrust suspension device according to claim 1, wherein said flame injection nozzle is provided at a protruding portion of said base portion. 3. The solid rocket motor thrust suspension device according to claim 1, wherein the flame injection nozzle is provided so as to face outward so as not to thermally affect the payload by a flame ejected from the nozzle.