JP3136060B2 - 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 solid rocket motor used for a spacecraft and the like, and more particularly, to a solid rocket motor provided with an insulation for protecting a motor case from heat generated when a propellant is burned.

[0002]

2. Description of the Related Art FIG. 3 is a diagram showing a head portion of a conventional solid rocket motor. This solid rocket motor 1
01, a propellant 105 having an inner hole 104 is loaded into a motor case 102 via an insulation 103, and an ignition motor 106 for the propellant is inserted into the inner hole 104 at the head of the motor case 102. And a propelling nozzle on the tail side (not shown).

[0003] At the end of the insulation 103, a propellant 10 is formed by directly casting it into the motor case 102.
5. The relief boot 10 has a structure in which the insulation 103 is divided into two layers in order to reduce the internal processing stress of
7 are formed. The ignition motor 106 is provided with an ignition nozzle (one or more) at the tip and an insulation 109 attached to the outer periphery, and is attached by fixing the base flange 110 to the motor case 102 with bolts. It is.

[0004] The solid rocket motor as described above is described in, for example, "Second Edition," published by Maruzen on September 30, 1992.
Aerospace Engineering Handbook ", pages 932 to 934.

[0005]

However, in the above-mentioned conventional solid rocket motor, the insulation 103 inside the motor case and the insulation 109 for the ignition motor must be separately prepared, and both the insulations 103 and 109 must be separately prepared. Since it is necessary to provide a filler for heat treatment between 103 and 109 (indicated by reference numeral 100 in FIG. 3), an improvement in reducing the number of manufacturing steps has been demanded.

[0006]

SUMMARY OF THE INVENTION It is an object of the present invention to provide a solid rocket motor capable of realizing a reduction in man-hours and the like by focusing on the above-mentioned conventional problems.

[0007]

According to a first aspect of the present invention, there is provided a solid rocket motor for covering an ignition motor for a propellant inserted in the motor case into an insulation attached to the inside of the motor case. Insulation is provided integrally, and as a second aspect, the propellant loaded in the motor case has a shape having an inner hole over the axle, and is inserted from the head of the motor case into the inner hole. An ignition motor is provided, and at the end of the insulation, the insulation is divided into two layers to form a relief boot on the propellant side, and the relief motor is connected to the ignition motor by the ignition motor insulation. And in a non-adhered state, and the above configuration is used as means for solving the problem.

[0008]

In the solid rocket motor according to the first aspect of the present invention, the ignition motor insulation covering the ignition motor is integrated with the insulation inside the motor case, so that both can be manufactured in a series of steps. Thus, there is no need to perform heat treatment between the two.

Further, in the solid rocket motor according to the second aspect of the present invention, in addition to the above operation, the solid state rocket motor is directly cast into the motor case by the ignition motor insulation in a non-adhered state to the relief boot and the ignition motor. Thus, it is possible to cope with the deformation of the end of the propellant formed when the propellant is cured.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a solid rocket motor according to the present invention will be described below with reference to the drawings.

A solid rocket motor 1 shown in FIGS. 1 and 2 has a propellant 5 having an inner hole 4 over a machine axis via an insulation 3 made of synthetic rubber or the like in a metal motor case 2. The motor case 2 has an opening 6 for mounting an ignition motor on the head thereof, and an ignition motor 7 for propellant is inserted into the opening 6 in the inner hole 4. Propulsion nozzle 13
It has.

At the end of the insulation 3, the insulation 3 is divided into two layers to reduce the internal working stress of the propellant 5 formed by directly casting into the motor case 2. A relief boot 8 on the side is formed, and an ignition motor insulation 9 covering the outer periphery of the ignition motor 7 is provided integrally with the relief boot 8 in a non-adhered state with respect to the ignition motor 7.

The ignition motor 7 has an ignition charge loaded therein (not shown), has an ignition nozzle 10 at the tip and a flange 11 at the base end, and has an edge of the opening 6 in the motor case 2. The attachment is made by fixing the flange 11 to the portion with a number of bolts 12.

The above-mentioned insulation 3 is formed, for example, by laminating sheet-like materials while laminating them. Further, the relief boot 8 is formed by sandwiching a release film between predetermined layers during the laminating step, and bringing the layers into a non-adhered state.

In the solid rocket motor 1, when producing the above-mentioned insulation 3, a core having the outer shape of the ignition motor 7 is previously attached to the opening 6 of the motor case 2, and the insulation inside the motor case 2 is provided. The insulation 3, the relief boot 8 and the ignition motor insulation 9 are prepared by a series of operations.

At this time, a release film is pasted on the surface of the core so that the ignition motor 7 and the ignition motor insulation 9 to be attached later are in a non-adhesive state. As the release film to be attached to the core, it is also possible to use a film integral with the release film forming the relief boot 8.

After the above-mentioned insulation is prepared, a core for forming the inner hole 4 of the propellant 5 is provided from the tail side in the motor case 2 and the slurry propellant is filled and hardened. Attachment of the ignition motor 7 and the propulsion nozzle 13 is performed. It should be noted that, at the stage of filling the slurry propellant, the relief boot 8 is in contact with the insulation 3 unlike the state of FIG.

Further, the propellant 5 is deformed during curing so that its end is bent toward the inner hole 4. At this time, in the rocket motor 1, the ignition motor insulation 9 which is not adhered to the relief boot 8 and the ignition motor follows the deformation, and the relief boot 8 and the ignition motor insulation 9 as shown in FIG. 3 and the propellant 5 away from the ignition motor 7.
Alleviates internal processing stress.

As described above, in the solid rocket motor 1, the ignition motor insulation 9 that covers the ignition motor 7 is integrated with the insulation 3 inside the motor case 2, so that both are produced in a series of steps. There is no need to perform heat treatment between the two, and the relief boot 8 is provided with the ignition motor insulation 9 which is not adhered to the ignition motor 7, so that the ignition motor 7 is mounted. In this case, a large deformation of the end of the propellant 5 can be handled.

[0020]

As described above, according to the solid rocket motor according to the first aspect of the present invention, the insulation inside the motor case and the ignition motor insulation can be formed in a series of steps. Since there is no need to perform heat treatment during the process, the number of manufacturing steps can be reduced, the manufacturing time can be shortened, and the cost can be reduced. , Heat resistance can be significantly improved.

According to the solid rocket motor of the second aspect of the present invention, in addition to the above effects, the relief boot is provided integrally with the ignition motor insulation in a non-adhered state to the ignition motor. Thereby, it is possible to sufficiently follow a large deformation of the end of the propellant which is generated when the propellant formed by directly casting into the motor case is hardened, and the degree of freedom for the deformation is increased even when the ignition motor is attached. Obtainable.

[Brief description of the drawings]

FIG. 1 is a sectional view of a head portion illustrating an embodiment of a solid rocket motor according to the present invention.

FIG. 2 is a cross-sectional view showing the entire solid rocket motor in a partially broken state.

FIG. 3 is a sectional view of a head portion illustrating a conventional solid rocket motor.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Solid rocket motor 2 Motor case 3 Insulation 4 Inner hole 5 Propellant 7 Ignition motor 8 Relief boot 9 Ignition motor insulation

──────────────────────────────────────────────────続 き Continued on front page (58) Field surveyed (Int.Cl. ⁷ , DB name) F02K 9/32 F02K 9/36 F02K 9/95

Claims (2)

(57) [Claims] 1. A solid rocket motor characterized in that an insulation attached to the inside of a motor case is integrally provided with an ignition motor insulation covering a propellant ignition motor inserted into the motor case. 2. A propellant charged in a motor case has a shape having an inner hole over an axle, and an ignition motor is inserted from the head of the motor case into the inner hole. At the end, the insulation is divided into two layers to form a relief boot on the propellant side, and the relief boot is provided with an ignition motor insulation in a non-adhered state with respect to the ignition motor. The solid rocket motor according to claim 1.