JP3916285B2 - A perforated plate and a short rocket motor using the perforated plate - Google Patents

Description

【００３２】
【発明の効果】
固体火薬類の飛散を効率よく抑制できる多孔板の提供により、短秒時作動ロケットモータ等の粒状推進薬の飛散を抑制することができ、大きな推力を発生する短秒時作動ロケットモータを提供することが可能になった。
【図面の簡単な説明】
【図１】本発明の多孔板の一例を示す、（ａ）正面図と（ｂ）Ａ−Ａ断面図である。
【図２】本発明の多孔板の一例を示す、（ａ）正面図と（ｂ）Ｂ−Ｂ断面図である。
【図３】本発明の短秒時作動ロケットモータ用の推進薬の一例を示す正面説明図である。
【図４】本発明の短秒時作動ロケットモータの一例を示す断面説明図である。
【図５】本発明の飛散制御用多孔板を使用したロケットモータの一例を示す断面説明図である。
【図６】本発明の飛散制御用多孔板を使用した点火薬装置の一例を示す断面説明図である。
【図７】本発明の飛散制御用多孔板の重ね枚数と相対推力の関係を示すグラフ図である。
【図８】短秒時作動ロケットモータの推力測定方法を示す概要図である。
【図９】従来のストレーナを用いた短秒時作動ロケットモータの断面説明図である。
【符号の説明】
１ ガス流出孔
２ 支柱
３ 通過流路の面積
４ 貫通部
５ リブ
６ リブとガス流出孔内壁との間隙
７ 貫通する空隙
８ スリット
９ 棒状推進薬
１０ モーターケース
１１ ノズル
１２ ラプチャーディスク
１３ 点火薬装置
１４ 燃焼室
１５ 推進薬
１６ 飛散制御用多孔板
１７ 点火薬ケース
１８ 点火具
１９ 点火薬
２０ 短秒時作動ロケットモータ
２１ カウンターウェイト
２２ 推力計
２３ ベース
２４ ストレーナ[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a perforated plate for preventing scattering of solid explosives in a solid combustion apparatus, and a short-time operation rocket motor using the perforated plate.
[0002]
[Prior art]
Conventionally, in order to prevent scattering of solid explosives in a solid combustion device, a porous plate is used, and the size of solid explosive particles and the size of the hole of the porous plate are adjusted to balance pressure resistance and scattering suppression. Has been done. For example, a perforated plate of an igniter device.
In addition, in order to prevent scattering of solid explosives in a solid combustion apparatus, a strainer disclosed in Japanese Patent Application Laid-Open No. 7-279760 has been studied.
In the case of the igniting device, even if the scattering of unburned solid explosives cannot be completely suppressed, a rocket motor combustion chamber is provided outside the igniting device, so that a sufficient function can be obtained even with a conventional perforated plate.
[0003]
However, unlike the attitude control motor disclosed in Japanese Patent Laid-Open No. 7-279760, there is no combustion chamber outside, and granular powder is used to shorten the operation time of the rocket motor. If it is not fixed to the case, it will be discharged out of the combustion device due to the difference in combustion pressure. Therefore, it is proposed to use a strainer (hereinafter referred to as a strainer) as shown in 24 of FIG.
[0004]
However, in the case of a rocket motor operating at short seconds using granular explosives, it is difficult to completely suppress scattering even if a strainer is used. Even when the area of the flow path is smaller than the nozzle throat cross-sectional area and cannot be used in the design, or even when the area of the passage flow path is larger than the nozzle throat cross-sectional area, the granular explosive is A phenomenon was observed in which the pores were blocked and abnormal combustion occurred. Moreover, as a result of the release of unburned explosives out of the system, an apparent decrease in energy per unit was observed, which became a design problem.
[0005]
In addition, although investigations have been made to prevent the explosives from burning out by reducing the thickness of the explosives to be burned, increasing the combustion pressure, and shortening the combustion completion time, the size is increased. At the same time, phenomena such as detonations were observed, which obstructed enlargement.
When the combustion time is long, explosive fixing methods such as a case bond method and a dip adhesion method used in general rocket motors are mainly used.
[0006]
However, when using a case-bonded rocket motor that adheres the propellant and motor case at the same time as the propellant cures, the explosive discharge from the rocket motor can be controlled, but reducing the drug thickness reduces the filling rate. Since it is extremely reduced, there is a problem in manufacturing, and it is difficult to obtain a propellant having a high burning rate for increasing the drug thickness, and it is difficult to apply it to a rocket motor operating at a short second.
[0007]
[Problems to be solved by the invention]
An object of the present invention is to provide a perforated plate for scattering control that efficiently suppresses the scattering of explosives without fixing granular explosives or the like in a solid combustion device, and to provide a short-time operating rocket motor using the same. And
[0008]
[Means for Solving the Problems]
As a result of intensive studies by the present inventors, a plurality of perforated plates having a plurality of gas outflow holes are stacked with the positions of the gas outflow holes shifted from each other. The present invention has been completed by finding that it is possible to efficiently suppress scattering of unburned propellant from the nozzle by disposing it between the nozzle inlets.
[0009]
That is, the present invention is as follows.
In a short-time operation rocket motor in which a plurality of explosive scattering control perforated plates having a plurality of gas outflow holes between a propellant and a nozzle are arranged , the positions of the gas outflow holes between the perforated plates are shifted. A short-time-operating rocket motor characterized in that the through-holes through which the gas outflow holes of the overlapped perforated plates penetrate are eliminated by overlapping .
[0010]
The present invention is described in detail below.
An example of the scattering control porous plate of the present invention is shown in FIG. In this example, two perforated plates having four gas outflow holes 1 are overlapped with the phase of the gas outflow holes shifted by 45 degrees and joined by a support column 2.
The sum of the passage passage areas of the gas outflow holes 1 formed in the perforated plate is preferably larger than the throat cross-sectional area of the nozzle 11, and the inner diameter of the gas outflow holes 1 is preferably smaller than the minor axis diameter of the explosive. When the inner diameter of the gas outflow hole 1 is larger than the short axis diameter of the explosive, the explosive is clogged in the gas outflow hole during combustion, and the sum of the passage passage areas of the gas outflow hole 1 becomes smaller than the throat cross-sectional area of the nozzle 11. May cause abnormal combustion.
[0011]
In order to make the sum of the passage passage areas of the gas outflow holes 1 larger than the throat cross-sectional area of the nozzle 11, inevitably the inner diameter of the gas outflow holes 1 is larger than the minor axis diameter of the explosive, as shown in FIG. Ribs 5 are formed so as to cross the gas outflow holes 1 in the first porous plate adjacent to the explosive (the right side in the BB cross-sectional view of FIG. 2). At this time, the gap 6 between the rib 5 and the inner wall of the gas outflow hole 1 may be made smaller than the minor axis diameter of the explosive.
[0012]
In the present invention, it is necessary that the positions of the gas outflow holes of the plurality of perforated plates are shifted and overlapped. It is difficult to superimpose so that the gas outflow holes 1 between the perforated plates are completely closed using two perforated plates having the same shape, size, and arrangement position of the gas outflow holes 1 formed in the perforated plate, When the penetration part 4 is generated, one perforated plate in which the gas outflow holes 1 are arranged is added so as to close the penetration part 4, or the shape of the gas outflow holes 1 formed in the perforated plate, It is necessary to eliminate the penetrating part 4 by using two perforated plates having different dimensions and arrangement positions so that the gas outflow holes 1 are closed .
[0013]
The shape of the gas outflow hole 1 formed in the perforated plate is not particularly limited to a circular shape, but a circular shape is preferable because it is difficult for the granular explosive to be clogged in the gas outflow hole. Further, the gas outflow holes 1 formed in the respective perforated plates to be superimposed are not limited to those having the same shape, size, and arrangement position, and the through portions 4 are eliminated when they are superimposed. It is necessary. Therefore, in order to increase the sum of the passage passage areas of the gas outflow holes 1, it is preferable to provide as many gas outflow holes 1 as possible within the range where the number of the gas outflow holes 1 satisfies the above condition.
[0014]
In the cross-sectional view (A-A cross section of FIG. 1) of the perforated plate for preventing scattering, the area 3 of the passage channel formed between the perforated plates (in the A-A cross-sectional view of FIG. The area formed by the perforated plate and the support column) is preferably set so that the perforated plates are spaced apart from each other so as to be larger than the area of one passage channel of the gas outflow hole 1. When the size of the gas outflow hole 1 is different, it is preferable to make it larger than the largest one. In this case, it is preferable to increase the area of the perforated plates as much as possible and to reduce the distance between the perforated plates as much as possible. When the granular explosive becomes smaller than the inner diameter of the gas outflow hole 1 in the course of combustion and passes through the flow path of the gas outflow hole 1, the time that is retained in the space formed between the perforated plates becomes longer, and it is possible to suppress the explosive scattering. Because.
[0015]
In the scattering control porous plate of the present invention, it is only necessary to hold a plurality of porous plates at regular intervals, and they may be supported by columns, or fitted into a frame provided with regular intervals. You may make it. When the support is provided, the support may be provided at the center as shown in FIG. 1 or may be provided at three or more locations on the end of the perforated plate. Thus, when a support | pillar is provided in the perforated-plate edge part, the area of the passage flow path formed between mutual perforated plates is two perforated plates in the sectional view which passes along the center of a perforated plate for scattering prevention. One half of the area to be formed.
[0016]
As the number of stacked porous plates increases, the time for explosives to stay between the porous plates increases as the number increases, so theoretically, it is possible to suppress the explosive scattering more efficiently by stacking more sheets. Although it is possible, usually two sheets are sufficient, and three sheets are practical even in the case of a high pressure for a short second that requires a very small drug diameter.
The material of the perforated plate is made of a metal selected from materials such as steel and stainless steel, but the material used is not particularly limited, and it is destroyed by the flow of combustion gas under the conditions used. It is sufficient if it has a strength that does not occur.
[0017]
The thickness of the porous plate is not particularly limited as long as it has a thickness that does not break due to the flow of combustion gas under the conditions used, but a porous plate with a thickness of 1 to 3 mm is usually used. Used. Since the size of the perforated plate is arranged between the nozzle of the motor case and the propellant, a plate having the same size as the inner diameter of the motor case is used. If there is a gap larger than the explosive diameter between the motor case and the scattering control perforated plate, unburned explosives will be released out of the system, resulting in a decrease in apparent energy per unit.
As described above, in the scattering control porous plate of the present invention, the size and number of gas outflow holes, the overlapping interval and the number of overlapping porous plates, and the like can be selected depending on the explosives to be applied and the structure of the combustion container.
In the case of a rocket motor for a short time, this scattering control perforated plate can be disposed between the nozzle and the propellant to efficiently suppress propellant scattering.
[0018]
As the explosive in this case, a granular propellant, a rod-shaped propellant, a rod-shaped propellant having a gap penetrating in the long axis direction, a plurality of granular propellants, and the like can be used. From the viewpoint of improving the gas flow, a rod-shaped propellant having a void penetrating in the long axis direction is preferable. The inner diameter of the void portion of the rod-shaped propellant is preferably 0.3 mm or more and 2 mm or less, and more preferably 0.5 mm or more and 1.5 mm or less. When the inner diameter is less than 0.3 mm, the flame propagation in the voids becomes poor and the combustion becomes unstable, and when it exceeds 2 mm, the space volume increases and the bulk density decreases. The difference between the minor axis diameter and the inner diameter of the gap is preferably 0.5 mm to 4 mm, and more preferably 1 mm to 3 mm. When the difference is less than 0.5 mm, the manufacturability and the handleability deteriorate. When the difference exceeds 4 mm, it becomes difficult to obtain an operation time of 10 msec or less. From the viewpoint of easy loading of the propellant in the case of high filling and improving the gas flow, it is particularly preferable to use a plurality of rod-shaped propellants having a gap penetrating in the long axis direction.
[0019]
A rod-shaped propellant is a smokeless gunpowder used for launching or propelling cannonballs or rockets. After kneading prescribed raw materials with a solvent, the rod-shaped propellant is drawn into a rod shape through a die and then dried. The Details are described in documents such as the Industrial Explosives Handbook (Kyoritsu Publishing).
As shown in FIG. 3, the rod-shaped propellant 9 is provided with a gap 7 penetrating in the long axis direction. If there is no through-hole 7, the explosive combustion becomes unstable. Further, when it is necessary to facilitate the propagation of the flame, a slit 8 having a width of about 0.1 to 0.5 mm with one end opened in a vertical direction partially or over the entire length with respect to the gap 7 penetrating in the long axis direction. It is also possible to provide. The movement is restricted so that the long axis direction of the rod-shaped propellant and the long axis direction of the attitude control motor are oriented in the same direction.
[0020]
The perforated plate for scattering control of the present invention can be used without limitation as long as it is not only a posture control motor but also a combination of explosives combustion container and perforated plate. For example, a short second in which nozzles are arranged in the axial direction as shown in FIG. The present invention is applicable to a system having a problem with scattering of solid explosives from a combustion container, such as a time-operating rocket motor, an ignition powder device as shown in FIG.
[0021]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, the present invention will be described in more detail based on examples and comparative examples.
[0022]
[Example 1]
FIG. 4 shows an embodiment of a short-time operating rocket motor using the scattering control porous plate of the present invention. In the structure, a combustion chamber 14 is formed inside the motor case 10, and a nozzle 11 having a throat diameter of φ6.5 mm is formed on one side surface (left side in FIG. 4) of the combustion chamber 14. In addition, the propellant 15 is filled in the combustion chamber 14 at a position biased to the opposite side of the nozzle 11, and the igniting device 13 is disposed in the vicinity of the propellant 15. Further, a rupture disk 12 is attached to the outlet side of the nozzle 11, and a scattering control porous plate 16 is disposed between the nozzle 11 and the propellant 15.
[0023]
The propellant composition is a single-base (S / B) rod-shaped propellant with a short axis diameter of about 3 mm, a through-hole diameter of about 0.6 mm, a long axis of about 65 mm, and a slit width of about 0.3 mm. . As shown in FIG. 3, the rod-shaped propellant is provided with a gap 7 penetrating in the major axis direction, and has a slit 8 whose one end is opened in the vertical direction over the entire length with respect to the major axis direction. .
The thing of the structure shown in FIG. 2 was used for the perforated plate for scattering control. The perforated plate has a circular shape with an outer diameter of about 17 mm, a piece with a thickness of about 2 mm, and an inner diameter of the gas outflow hole of about 4.5 mm, and a phase interval of 45 degrees so that the overlap interval is about 4 mm. The two pieces were overlapped. The material was made of S25C. The diameter of the column was about 6.5 mm, and the diameter of the rib was 11.5 mm. In this embodiment, the gas flow holes between the perforated plates are completely deviated and there are no through portions.
[0024]
[Example 2]
This is an example in which three perforated plates are superposed as a perforated plate for scattering control in the short-time operating rocket motor of the first embodiment. The scattering control perforated plate was used in which the same perforated plate was overlapped with a spacing of about 4 mm and the phase was shifted by 45 degrees on the scattering control perforated plate used in Example 1.
[0025]
[Example 3]
In the same short-time operating rocket motor as in Example 1 except that the throat diameter φ of the nozzle 11 is 5.5 mm, the propellant 15 penetrates the short axis diameter of about 5.4 mm and the long axis of about 5.6 mm. This is an example in which a granular propellant having a void diameter of about 0.5 mm and a number of penetrating voids of seven, that is, a seven-hole tubular drug is used.
[0026]
[Comparative Example 1]
This is an example in which a conventional strainer is used in place of the scattering control perforated plate 16 in the short-time operating rocket motor of the third embodiment.
[0027]
[Comparative Example 2]
This is an example in which a conventional porous plate is used in place of the scattering control porous plate 16 in the short-time operating rocket motor of the third embodiment.
[0028]
[Comparative Example 3]
This is an example in which a conventional porous plate is used in place of the scattering control porous plate 16 in the short-time operating rocket motor of the first embodiment.
A combustion test was performed using the short-time operating rocket motors of the above examples and comparative examples, and thrust was measured.
As shown in FIG. 8, the thrust is measured by connecting the counterweight 21 so that the nozzle of the short-time-operating rocket motor 20 is oriented vertically and the center of gravity of the rocket motor is exactly at the nozzle center axis position. The center axis was fixed on the base 23 so that the center axis of the thrust meter 22 coincided. The thrust meter used was a crystal type load washer manufactured by Nippon Kisler.
[0029]
Table 1 shows the results of the thrust measurement, and FIG. 7 shows the relationship between the number of stacked perforated plates and the relative thrust. As can be seen from a comparison between Example 1 and Comparative Example 1, the short-time operating rocket motor using the perforated plate for scattering control of the present invention has the effect of suppressing the explosive scattering by the perforated plate for scattering control compared to the conventional strainer system. It was confirmed that a thrust of 1.16 times could be obtained by increasing the bulk density (increasing the amount of explosive loaded) due to the use of a rod-shaped propellant.
[0030]
Further, as can be seen from Example 3, when the perforated plate for scattering control of the present invention is used, even when granular propellant is used as the propellant, 1.1 times the thrust is obtained as compared with the conventional strainer system. Further, it was confirmed that a sufficient scattering suppression effect can be obtained even with a granular explosive system. From the graph showing the relationship between the number of stacked perforated plates in FIG. 7 and the relative thrust in FIG. 7 where the number of perforated plates in Examples 1 and 2 and Comparative Example 3 is plotted on the horizontal axis and the relative thrust on the vertical axis, the rod-shaped propellant is used. It was found that there was almost no difference in relative thrust between the double perforated plate and the triple perforated plate in the short rocket motor of the present invention. Therefore, it was confirmed that a sufficient number of the explosives scattering suppression effect can be obtained when two porous plates are stacked.
[0031]
[Table 1]

[0032]
【The invention's effect】
Providing a perforated plate that can efficiently suppress the scattering of solid explosives, providing a short-time-operating rocket motor that can suppress the scattering of granular propellants such as short-time-operating rocket motors and generate large thrust It became possible.
[Brief description of the drawings]
FIG. 1A is a front view and FIG. 1B is a cross-sectional view taken along line AA, showing an example of a porous plate of the present invention.
2A is a front view and FIG. 2B is a cross-sectional view taken along the line BB showing an example of the porous plate of the present invention.
FIG. 3 is a front explanatory view showing an example of a propellant for a short second operating rocket motor of the present invention.
FIG. 4 is an explanatory cross-sectional view showing an example of a short second operating rocket motor of the present invention.
FIG. 5 is an explanatory cross-sectional view showing an example of a rocket motor using a perforated plate for scattering control according to the present invention.
FIG. 6 is a cross-sectional explanatory view showing an example of an igniter device using the scattering control porous plate of the present invention.
FIG. 7 is a graph showing the relationship between the number of stacked perforated plates for scattering control according to the present invention and the relative thrust.
FIG. 8 is a schematic diagram showing a method for measuring thrust of a rocket motor operating in a short second.
FIG. 9 is a cross-sectional explanatory view of a short-time operating rocket motor using a conventional strainer.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Gas outflow hole 2 Support | pillar 3 Area of passage channel 4 Through part 5 Rib 6 Gap between rib and inner wall of gas outflow hole 7 Penetration space 8 Slit 9 Rod-shaped propellant 10 Motor case 11 Nozzle 12 Rupture disk 13 Ignition device 14 Combustion chamber 15 Propellant 16 Spatter control perforated plate 17 Igniter case 18 Igniter 19 Igniter 20 Short-time operation rocket motor 21 Counterweight 22 Thrust meter 23 Base 24 Strainer

Claims (1)

In a short-time operation rocket motor in which a plurality of explosive scattering control perforated plates having a plurality of gas outflow holes between a propellant and a nozzle are arranged , the positions of the gas outflow holes between the perforated plates are shifted. A short-time-operating rocket motor characterized in that the through-holes through which the gas outflow holes of the overlapped perforated plates penetrate are eliminated by overlapping .

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