JPH1150911A - Solid rocket and its oscillating combustion restraining method - Google Patents

Abstract

PROBLEM TO BE SOLVED: To realize restraint of oscillating combustion without influencing upon characteristics of combustion speed, etc., of a solid propellant by providing a solid particle producing mechanism to produce solid particles to function as an oscillating combustion restrainer on the upstream side of the solid propellant. SOLUTION: A solid rocket 11 is constituted by providing an insulation 13 on the inner surface of a cylindrical pressure container 12 and loading a solid propellant 14 in the inside of this insulation 13. A nozzle 15 is provided on the downstream side of the solid propellant 14, and an igniter 16 is provided on the upstream side of the solid propellant 14. The igniter 16 contains an oscillating combustion restrainer and ZrC powder to function not to inhibit turning to be smokeless or lean-smoke, and this igniter 16 is structured to doubly work as a solid particle producing mechanism 17. Consequently, on the solid rocket 11, ZrC solid particles are supplied from the solid particle producing mechanism 17 doubly to use by the igniter 16 while the solid propellant 14 is ignited by the igniter 16 and burns and thrust is generated as combustion gas is blown out from the nozzle 15.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a solid rocket used as a propulsion source of a flying object, and more particularly to a method for suppressing vibration of a solid rocket which is suitable for suppressing vibration combustion of the solid rocket.

[0002]

2. Description of the Related Art Solid rockets have a very simple structure, can be stored for a long period of time with a solid propellant charged, can be fired immediately, can easily obtain a large initial acceleration, and have a small size. It has been selected and adopted based on a comparison with liquid rockets, and has achieved considerable results.

This solid rocket mainly comprises a solid propellant formed by mixing an oxidizer component containing a large amount of oxygen and a fuel component composed of a hydrocarbon polymer material, and a nitrate ester as a main component. As shown in FIG. 3, for example, a general solid rocket 31 is provided with an insulation 33 on the inner surface of a cylindrical pressure vessel 32, and the insulation 33
Is loaded with a solid propellant 34, and the solid propellant 34
A nozzle 35 is provided downstream of the solid propellant 34, and an igniter 36 as an igniter is provided upstream of the solid propellant 34.

The solid propellant 34 includes metal particles such as Al, Mg, Be, B, and Zr that function as a metal fuel, and Al, Zr, and Zr that function as a vibration combustion suppressant.
In some cases, solid particles such as C and solid particles such as ZrC that function so as not to inhibit smokelessness and rarefaction are included.

[0005]

In such a solid rocket, the solid particles are contained in a state of being uniformly dispersed in the solid propellant. However, when the solid particles contain Al as solid particles, Al is not sometimes added when there is a request for smokeless and rare smoke because it generates a bright flame, so that Al may not be added in some cases.

[0006] However, since this Al also functions as a vibration combustion suppressant, the Al is used for the purpose of smokeless and smoke reduction.
When no is added, the possibility of generating oscillating combustion increases.

For this reason, solid particles such as ZrC have been added in some cases to prevent vibration combustion and to satisfy the demand for smokeless and lean smoke. However, such solid particles such as ZrC have been added to a solid propellant. When mixed and dispersed in the solid propellant, the combustion characteristics of the solid propellant change, for example, affecting the burning speed of the solid propellant. Therefore, the composition of the solid propellant must be changed. Therefore, there was an issue to solve such a problem.

[0008]

SUMMARY OF THE INVENTION The present invention has been made in view of such conventional problems, and has been developed as a vibration-combustion inhibitor.
Even when using solid particles such as ZrC that can meet the demand for smokeless and lean smoke combustion gas, it is not necessary to change the composition of the solid propellant, and the burning speed of the solid propellant, etc. It is an object of the present invention to make it possible to set the characteristic of the initial setting to an initial one.

[0009]

A solid rocket according to the present invention includes a solid propellant inside a pressure vessel (combustion vessel) and a downstream side of the solid propellant. A solid rocket having a nozzle is characterized in that a solid particle generation mechanism for generating solid particles functioning as a vibration combustion suppressant is provided upstream of the solid propellant.

In the embodiment of the solid rocket according to the present invention, as described in claim 2, the solid particle generating mechanism is provided with an igniter provided upstream of the solid propellant. Alternatively, as described in claim 3, the solid particle generating mechanism is provided with an insulation (including a restrictor) provided upstream of the solid propellant. It is possible to

[0011] Similarly, in the embodiment of the solid rocket according to the present invention, as described in claim 4, solid particles that can function so as not to inhibit smokeless and lean smoke can be selected.

According to a fifth aspect of the present invention, there is provided a solid rocket having a solid propellant inside a pressure vessel and a nozzle having a nozzle downstream of the solid propellant. When suppressing the oscillating combustion in the rocket, solid particles functioning as an oscillating combustion inhibitor are generated upstream of the solid propellant.

Further, in the embodiment of the method for suppressing vibration and combustion of a solid rocket according to the present invention, as described in claim 6, the solid particles function so as not to inhibit smokeless / lean smoke. And so on.

A solid rocket according to the present invention and a method for suppressing vibration combustion thereof have the above-described configuration.
Among them, the pressure vessel generally has a cylindrical shape, but is not particularly limited.

A solid propellant is provided on the inner surface of the pressure vessel via a suitable insulation (or restrictor). However, the solid propellant is not particularly limited. Ammonium (AP), ammonium nitrate (AN), nitronium perchlorate (NP), cyclotrimethylenetrinitramine (RDX), cyclotetramethylenetetranitramine (HMX) and the like can be used. You can choose from among them.

Examples of high-carbon fuels include polysulfide (PS), polyvinyl chloride (PVC), polyurethane (PU), terminal carboxyl group polybutadiene (CTPB), and terminal hydroxyl group polybutadiene (HTP).
B) and the like can be used, but are not particularly limited.

Further, as a metal fuel, Al, Mg, B
e, B, Zr, etc., metal particles such as Al, Zr, ZrC, etc., can be used as a vibration-combustion inhibitor, and ZrC which functions so as not to inhibit smokeless / leaning. Solid particles such as the above can be used, and in addition, an appropriate curing agent, a crosslinking agent, a binder, a plasticizer, a stabilizer, a combustion catalyst, and the like can be used.

Further, as the insulation provided on the inner surface of the pressure vessel, a rubbery sheet material (for example,
Sheet material composed of EPDM, CTPB, HTPB, etc.)
Can be used, but it is not particularly limited, and it is also possible to adopt instead of the restrictor.

Further, as an igniter provided in the solid rocket according to the present invention, an igniter (Al / NH ₄ ClO) in which a mixture of a metal and an oxidizing agent is pelletized is used.
₄ , Al / KClO ₄ , B / KClO ₄ , B / KN
A pellet type igniter that ignites a solid propellant by a flame generated by combustion of O ₃ , Mg / C ₂ F ₂ (Teflon) and the like and a combustion product can be used. Not done.

In this case, solid particles can be generated while the solid propellant is burning.
The operation time of the igniter may be appropriately synchronized with the combustion time of the solid propellant.

In the solid rocket and the method for suppressing vibration combustion thereof according to the present invention, solid particles which function as a vibration combustion suppressant are generated on the upstream side opposite to the downstream side of the solid propellant having a nozzle. It is equipped with a solid particle generation mechanism.
Oscillating combustion is suppressed by feeding solid particles (having a particle diameter of about 1 to 3 μm) such as l, Zr, and ZrC into the combustion chamber.

The function of suppressing the oscillating combustion by the solid particles is as follows: when the solid particles pass through the combustion chamber and are discharged from the nozzle to the outside air, high-frequency vibrations such as lateral vibrations are generated. However, when the solid particles move in synchronization with the pressure vibration, they are released to the outside air while absorbing the energy of the vibration, which is considered to have an action of suppressing the excitation of the vibration. Is, for example, AIAA Paper No. 82-1
223 is also described.

In this case, the solid particle generating mechanism may be provided in an igniter provided on the upstream side of the solid propellant, or may be provided in an insulation provided on the upstream side of the solid propellant. In the case where the igniter is provided, for example, solid particles mixed in the pellet-shaped igniter are generated toward the solid propellant together with the combustion of the pellet-shaped igniter. In the case where the insulation is prepared for the insulation, when the insulation is decomposed or burned by the radiant heat of the combustion of the solid propellant, 2 to 20% of the solid particles mixed with the insulation are solidified. It can be generated toward the propellant. When the combustion speed of the insulation is insufficient, the combustion speed can be improved by, for example, mixing a small amount of an oxidizing agent or the like into the insulation.

Further, when the solid particles are made of smokeless ZrC or the like,
If it works so as not to inhibit the smoke reduction,
It becomes possible to make the combustion gas smokeless and rare.

[0025]

According to the solid rocket of the present invention, a solid propellant is provided inside a pressure vessel and a nozzle is provided downstream of the solid propellant. Because it has a structure that has a solid particle generation mechanism that generates solid particles that function as an inhibitor, it is similar to the case where solid particles that function as a vibration combustion inhibitor are uniformly dispersed in a solid propellant as in the past. It is possible to suppress vibration combustion without affecting characteristics such as the burning speed of the solid propellant, and there is no need to change the composition of the solid propellant to suppress vibration combustion. Significant effects are achieved.

And, as described in claim 2,
The solid particle generation mechanism is equipped with an igniter provided on the upstream side of the solid propellant, and suppresses oscillating combustion by generating solid particles toward the combustion chamber along with ignition charge combustion in the igniter In addition, as described in claim 3, the solid particle generation mechanism is provided with an insulation (restrictor) provided on the upstream side of the solid propellant, thereby achieving the insulation. By generating solid particles toward the solid propellant side together with the thermal decomposition or combustion of, a remarkably excellent effect that oscillation combustion can be suppressed is brought about.

According to the fourth aspect of the invention, the solid particles are selected so as to function so as not to inhibit smokelessness and smokelessness, so that a solid rocket with low recognition can be obtained. A remarkably excellent effect is achieved.

According to the method for suppressing vibration of a solid rocket according to the present invention, a solid propellant is provided inside the pressure vessel and a nozzle is provided downstream of the solid propellant. In suppressing the oscillating combustion in a solid rocket, since solid particles functioning as an oscillating combustion suppressor are generated on the upstream side of the solid propellant, oscillating combustion that may be caused by the combustion of the solid propellant is generated on the upstream side. It can be easily suppressed by solid particles generated from the side, and since these solid particles are not intended to be uniformly dispersed in the solid propellant, characteristics such as the burning speed of the solid propellant are affected by the solid particles. A remarkable excellent effect is obtained that it is possible to perform the operation.

Then, as described in claim 6,
By selecting the solid particles that function so as not to inhibit smokelessness / leaning, a remarkably excellent effect that a solid rocket with low recognition can be obtained is obtained.

[0030]

Embodiment 1 FIG. 1 shows an embodiment of a solid rocket according to the present invention. This solid rocket 11 has an insulation 13 on the inner surface of a cylindrical pressure vessel (combustion vessel) 12. The solid propellant 14 is loaded inside the insulation 13 and the solid propellant 1
A nozzle 15 is provided downstream of the solid propellant 4, and an igniter 16 as an igniter is provided upstream of the solid propellant 14.

The igniter 16 has a vibration combustion suppressant and a Z function that does not inhibit smokeless and lean smoke.
The igniter 16 includes rC powder and has a structure also serving as a solid particle generation mechanism (17).

Accordingly, in the solid rocket 11 according to this embodiment, the solid propellant 14 is ignited by the igniter 16 and burns, and the igniter 16 is also used while the combustion gas is ejected from the nozzle 15 to generate thrust. ZrC solid particles are supplied from the solid particle generation mechanism (17), and the ZrC solid particles function as a vibration combustion suppressor and also function so as not to inhibit smokeless / lean smoke.

Embodiment 2 FIG. 2 shows another embodiment of the solid rocket according to the present invention. This solid rocket 21 has an insulation 23 provided on the inner surface of a cylindrical pressure vessel 22. A solid propellant 24 is loaded inside the insulation 23, a nozzle 25 is provided downstream of the solid propellant 24, and an igniter as an igniter is provided upstream of the solid propellant 24. It has 26.

The insulation 23a on the upstream side of the solid propellant 24 in the insulation 23
Contains a vibration-combustion inhibitor and ZrC powder that functions so as not to inhibit smokelessness / leaning, and the upstream insulation 23a has a structure also serving as a solid particle generation mechanism (27).

Therefore, in the solid rocket 21 according to this embodiment, the solid propellant 24 is ignited by the igniter 26 and burns, and the combustion gas is ejected from the nozzle 25 to generate thrust, while the upstream insulation 23 is generated.
a is pyrolyzed and this upstream insulation 2
From the solid particle generation mechanism (27) shared with 3a, Zr
C solid particles are supplied, and the ZrC solid particles function as a vibration combustion suppressant and also function so as not to inhibit smokeless / lean smoke.

[Brief description of the drawings]

FIG. 1 is an explanatory sectional view showing an embodiment of a solid rocket according to the present invention.

FIG. 2 is an explanatory sectional view showing another embodiment of the solid rocket according to the present invention.

FIG. 3 is an explanatory sectional view showing a conventional solid rocket.

[Explanation of symbols]

 11,21 Solid rocket 12,22 Pressure vessel 13,23 Insulation 14,24 Solid propellant 15,25 Nozzle 16,26 Igniter 17,27 Solid particle generation mechanism 23a Insulation on upstream side

Claims (6)

[Claims] 1. A solid rocket having a solid propellant inside a pressure vessel and a nozzle on the downstream side of the solid propellant, wherein solid particles functioning as a vibration combustion suppressant are provided on the upstream side of the solid propellant. A solid rocket characterized by having a solid particle generation mechanism for generating rockets. 2. The solid rocket according to claim 1, wherein the solid particle generating mechanism is provided in an igniter provided upstream of the solid propellant. 3. The solid rocket according to claim 1, wherein the solid particle generating mechanism is provided in an insulation provided upstream of the solid propellant. 4. The solid rocket according to any one of claims 1 to 3, wherein the solid particles function so as not to inhibit smokeless / leaning. 5. A solid rocket having a solid propellant inside a pressure vessel and a nozzle provided on a downstream side of the solid propellant, for suppressing vibration combustion of the solid rocket. A method for suppressing vibration and combustion of a solid rocket, characterized by generating solid particles functioning as a solid. 6. The method for suppressing vibration and combustion of a solid rocket according to claim 5, wherein the solid particles function so as not to inhibit smokeless / leanning.