JPS598416B2 - Impact treatment equipment for condensed substances - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an improvement in an apparatus for impact treatment of condensed substances such as solids and liquids by using explosion of gunpowder or explosives.

Traditionally, explosive impact has been used to synthesize substances, solidify powders, and
Technologies such as crimping metals are known, and some of them have been industrialized, as exemplified by the synthesis of diamond from graphite.

In this case, it is known that a method of obtaining a high-speed flying object such as a metal plate driven by explosive gas and causing it to collide with the sample is advantageous because a higher impact pressure can be obtained.

In this case, by increasing the flight speed of the projectile caused by the explosion,
In order to enhance the processing effect, it is desirable to increase the impact pressure generated within the sample and to increase the impact duration.

This can be achieved by using a large amount of explosives with high detonation velocity and good performance, but such explosives are expensive and their use in large quantities poses a major economical problem.

It is an object of the present invention to provide an apparatus capable of effective impact compression at ultra-high pressures at low cost. A main explosive layer and a sub-explosive layer having a higher detonation speed than the main explosive layer are sequentially laminated on the opposite side of the flying member which is installed parallel to the main explosive layer with a gap therebetween, and a detonator is provided at one end of the sub-explosive layer. Provided is an impact treatment device for condensed substances characterized by:

The invention will now be explained in more detail with reference to the drawings.

FIG. 1 is an explanatory diagram showing an embodiment of the impact compression treatment apparatus according to the present invention in an elevational cross section, and in the figure, 1 is a sample of a liquid or solid condensed substance to be subjected to compression treatment. , is housed in a cylindrical metal container 2.

Reference numerals 3 and 4 indicate the stoppers of the container 2. A cylindrical flying member 5 is installed concentrically with the container 2 with a gap 6 therebetween.

A main explosive layer 9 is provided on the outer peripheral surface of the flying member 5,
Due to this explosive force, the flying member 5 flies toward the container at high speed and collides with it, causing impact compression of the sample 1 inside.

Reference numeral 28 denotes a sub-explosive layer provided on the outer circumferential surface of the main explosive layer 9, which has a detonation velocity greater than that of the main explosive layer 9.

The sub-explosive layer 28 is detonated by a detonator formed of the detonator 11 and the detonator layer 10 provided at the upper end, and explodes continuously from the upper end to the lower end.

Due to the explosion of the sub-explosive layer 28, the main explosive 9 is also detonated continuously from the upper end to the lower end.

In order to prevent the main explosive 9 from being directly triggered by the explosion of the priming layer 10, a separating plate 29 such as a wooden board is inserted between the main explosive layer 9 and the priming layer 10.

Reference numerals 21 to 26 are means for preventing damage to the container provided at both ends of the container 2, and their functions will be described later.

Note that this damage prevention means can also be omitted.

FIG. 2 is a conceptual diagram of the impact treatment in progress by the apparatus of FIG. 1, and the action of the sub-explosive layer 28 will be explained with reference to this diagram.

Now, the detonation speeds of the sub-explosive layer 28 and the main explosive layer 9 are respectively D.
1 and D2, the detonation wavefront Z due to the main explosive layer 9 is:
It advances at an angle θ with respect to the flying member 5.

At this time, θ is θ−s'n −' (D2/DI)
Since D1>D2, θ is smaller than 90°.

That is, in the case of the present invention, the detonation wavefront Z is 9
It is formed by configuring a constant angle smaller than 0°.

In general, the smaller the angle between the detonation wavefront and the object accelerated thereby, the better the efficiency of acceleration, and the faster the object can be flown.

The detonation velocity value of commonly used explosives is 2 to 9 km/sec, so from equation (1) above, θ is approximately 13° or more and 90°.
less than

In this manner, by providing the sub-explosive layer 28 which exhibits a detonation velocity higher than the detonation velocity of the main explosive layer 9, it becomes possible to efficiently convert the detonation energy of the main explosive layer 9 into the kinetic energy of the flying member 5.

Furthermore, when the flying member 5 collides with the container 2, an oblique shock wave is generated from the collision point through the container into the sample 1 toward its central axis, and collides at the central axis to generate a reflected shock wave with higher pressure. , proceeding outward from the central axis.

Since the downward traveling speed of the shock wave front Y is equal to the detonation velocity D1 of the sub-explosive layer in a steady state, if D1 is sufficiently large, even if the detonation velocity D2 of the main explosive layer 9 is small, the shock wave front P will be greater than the sound velocity of the container 2. It is possible to obtain a moving speed of

When θ is close to 90°, that is, when D2 is approximately equal to D1, the detonation wavefront Z becomes a spherical wave, making it difficult to perform uniform compression processing.

That is, as shown in FIG. 3, if OA and QS are the positions of the sub-explosive layer 28 and the flying member 5, respectively, and OQ is the top surface of the main explosive layer 9, then the main explosive detonated at six points While the explosion of 28 reaches point Q, the explosion of the secondary explosive 28 progresses to point A.

Here, the ratio of the lengths of line segments OA and OQ is explosive speed D, , D
Equal to the ratio of 2.

Obtain a circular arc with radius OQ centered at 0, draw a tangent AR from point A, and set the tangent point to R. Then, the straight line AR and the circular arc RQ
denotes the detonation wavefront in the main charge, and the angle OAR (which is equal to the angle ROQ).

When θ is θ, θ satisfies equation (1).

If we extend the straight line OR and let the intersection with the straight line QS be T, a circular (actually spherical) detonation wave will arrive between QT, and a detonation wave with an angle of θ will arrive below T. As a result,
The flying members below point T are uniformly accelerated.

The lateral thickness of the main explosive is denoted by OQ, so it ends up being QT.
is expressed by the following formula: QT=OQ−諭θ ・・・・・・(2
) Therefore, when θ approaches 90°, that is, when D1 takes the same value as D2, the proportion of spherical detonation waves colliding with the flying member increases, giving uniform acceleration to the flying member. This makes it difficult to perform uniform impact compression treatment.

In the apparatus shown in FIG. 1, as mentioned above, due to the limit of the explosive that can be obtained, the angle θ given by equation (l) is limited to about 13°.

The device shown in FIG. 4 is a device that can further reduce the angle θ formed between the detonation wave front and the flying member, and in some cases reduce it to 0. 1
The same reference numerals as in the figures indicate the same members and elements.

As can be easily determined from FIG. 4, in this embodiment, the main explosive layer 9 is the primary explosive layer 1 for detonating the main explosive layer 9.
The layer thickness is gradually and uniformly thinned from the zero end (that is, the upper end in the illustrated case) toward the opposite end (that is, the lower end).

A sub-explosive layer 28 formed around such a main explosive layer 9
The detonation velocity D1 is made larger than the detonation velocity of the main explosive layer 9, and if the inclination angle of the outer surface of the main explosive layer, that is, the sub-explosive layer 28 is δ, the detonation wavefront of the main explosive layer 9 and the flying member 5 are The angle θ is expressed by the following equation.

θ-δ-cos”-’ (D2/D1)
......(3) Therefore, the value of COS δ is D2/DI
When θ is equal to , θ becomes 0.

That is, for example, when using an explosive having twice the detonation velocity as the main explosive 9 as the secondary explosive 28, if δ is set to 60°, θ can be set to 0.

When extremely high pressure is generated in a sample, if the shock wave that initially enters the sample is made as strong as possible and the collision angle at the central axis is made as small as possible, Matsuha shock waves will not be generated and only reflected shock waves will be generated. Almost the entire sample can be compressed uniformly.

In the case of the present invention, this is made possible by making the angle of impact of the flying member 9 on the container 2 sufficiently small, and therefore by making the angle θ formed by the detonation wavefront of the main explosive and the flying member 9 sufficiently small. , especially when θ is zero, the sample undergoes impact compression that causes it to contract completely into a cylindrical shape.

The pressure of the shock wave that contracts in the same cylindrical shape increases as it contracts,
At the center, there is an extremely high pressure that is close to infinity.

The strength of the contraction shock wave can be measured using Somon's method (physics), for example.
of High Energy Density (published by Academic Press, 1971), it can be estimated, but the radius is 〆.

If the pressure is below, the pressure increases several times in condensed materials, so in this case, if compression is required as uniformly as possible in the lateral direction, as shown in Figure 5, the pressure between the sample and the impact impedance increases. A rod 31 made of a similar material may be placed in the center.

In this case, it is preferable that the diameter of the rod be at least about % of the sample diameter.

On the other hand, extremely high pressure is achieved near the center, so on the other hand, ultra-high pressure treatment is performed by placing the sample at the bar 31 in Figure 5 and a substance with similar impact impedance to the sample at sample 1. be able to.

Each part of the apparatus of the present invention described above will be explained next.

A disk-shaped explosive is usually used as the explosive in the primer layer 10, and there are no particular restrictions on its type, but it is preferable to use one with a small explosive propagation limit as much as possible because the amount of explosive can be reduced. .

The thickness of the sub-explosive layer 28 is usually preferably 10 mm or less, and it is preferable to use a type of charge that has a detonation speed of 5.5 km/7 seconds or more and a small charge thickness that limits explosion propagation.

Examples of such things include silicone rubber, fine powder of high explosives such as vent lift or hexogen, etc.
Mixed with polymeric plastic resins such as urethane rubber,
Examples include molded products.

It is also possible to use liquid explosives.

The thickness of the main explosive layer 9 is usually 1071 m or more (in the case of the embodiment shown in Fig. 4, the thickness at the lower thin layer side), and the type of the main explosive layer 9 is determined by the detonation speed of the secondary explosive used. Any small explosive can be used, and general industrial explosives such as ampho explosives, dynamites, and hydrous explosives can also be used.

As the isolation member 29, other than wood, plastic, plaster, sand, paper, etc. can be used.

The material of the flying member 5 is not particularly limited, but steel or brass is preferable from the viewpoint of economy and workability.G).

Further, the wall thickness of the flying member 5 is a factor that determines the flying speed of the flying member 5 due to an explosion, and in practical terms, it is at least 0.
It is preferable to set it to 5 mm or more.

The sample container 2 and its plugs 3 and 4 are preferably made of a metal with as high strength as possible, and in practice, high-tensile steel such as stainless steel is desirable.

It is preferable that the wall thickness of the container 2 is thicker from the viewpoint of preventing breakage, but this increases the impact energy consumed in deforming the container.
From this point of view, it is preferable that the container be thin, since the processing effect of the sample will be reduced accordingly, but in the case of a stainless steel container in the present invention, a wall thickness of about 1 to 10'/n71 L is sufficient.

It is more effective to prevent the container from breaking if the metal stopper has a convex or concave shape, as shown in Figure 1, rather than a flat one, as shown in Figure 1. It is preferable to use a screw-in structure in which as many parts as possible are in contact with the

The width of the gap 6 between the flying member 5 and the container 2 in the lateral direction (direction perpendicular to the axial direction of the sample) is preferably at least % of the lateral thickness of the main explosive 9.

In FIGS. 1 and 4, reference numerals 21 to 26 indicate container breakage prevention means provided at both ends of the container 2.

In other words, when a compression process is performed by colliding a flying object with a sample due to an explosion, the upper part of the container 2 tends to move upward due to the impact of the projectile, and the rest of the container 2 as a whole tries to move downward, and as a result, the container 2 There is a problem in that the container is likely to break at the upper and lower parts of the container, particularly in the vicinity where the sample 1 and the stoppers 3 and 4 come into contact, resulting in loss of the sample due to dissipation.

When carrying out ultra-high-pressure impact compression as in the present invention, it is particularly desirable to prevent the container from rupturing. This can be achieved by providing a layer to reduce the speed of movement of the container toward the other end side due to the collision of the flying member.

Reference numerals 21 and 22 are deceleration explosive layers for preventing damage to the container, and as shown in the figure, shock wave attenuating plates 23 . 24 and 25, 2
It is preferable to use them by sandwiching them between 6 and 6 in the form of a sandwich.

There are no particular restrictions on the type of explosive used in the explosive layer 2L22, but it is best to avoid using explosives that detonate at low speed, are likely to exhibit a dead pressure phenomenon, or whose explosive properties are likely to change rapidly due to impact. It is preferable to use high-performance explosives such as vent lift, hexogen tetrile, etc., a mixture of these high-performance explosives, or powders of these high-performance explosives in paraffin. , beeswax, silicone rubber, butadiene rubber, etc., as well as liquid explosives such as nitromethane, nitric acid, and solutions made of flammable substances soluble in these.

In the case of a liquid moderator explosive, it is used in a thin-walled container, but in the case of a solid one, it may also be used by surrounding the sides with a vinyl chloride pipe or the like instead of using a naked charge.

The shape of the explosive layers 21 and 22 is usually plate-like.
It is preferable that the planar shape is approximately the same as that of the sample container 2.

The thickness should be at least the explosive limit thickness.

As the shock wave attenuating plates 23, 24, 25, and 26, it is preferable to use materials whose impact impedance is as similar as that of deceleration explosives; for example, plastics such as methacrylic, or water, an aqueous solution of inorganic or organic salts, etc. are used. be done.

When a liquid substance is used for shock wave attenuation, it is used by sealing it in a thin-walled container.

The shape of the shock wave attenuating plates 23, 24, 25, 26 is as follows:
Preferably, it has approximately the same planar shape and the same thickness as the sandwiching explosive layers 21, 22.

Next, the function of the moderating explosive layer 21, 22 according to the present invention will be explained.

Now deceleration explosive layer 21. 22, the impact of the flying object 5 on the damping plates 23, 24, 25, 26 and the sample container 2 would cause the upper part of the container to move upwards and the rest to move downwards as a whole.

In particular, at the bottom of the container 2, there is a plastic disc 2 under the damping plate.
7, and if the lower part is made into a free space, dilution waves are generated upward from the free surface, further increasing the downward movement speed of the entire container.

In addition, since the sample generally has a much lower impact resistance than the container 2 and the metal plugs 3 and 4, secondary dilution waves are likely to occur at the interface with the sample, and due to complex mutual interference between the dilution waves, a strong tensile force is generated in this vicinity. Force is generated and the container is likely to break.

Roughly the same effect occurs in the upper part of the container, which tends to break near the interface between the sample and the container stopper.

On the other hand, explosive layers 21 and 22 are provided, and the flying object 5
If the container is detonated from the side by colliding with it, the explosive force will reduce the speed of movement of the container in the upper and lower directions.

Therefore, breakage of the container can be prevented. In addition, when the amount of the explosive layer 10 is sufficiently large, the deceleration explosive layer 22 provided on the upper part
can be omitted.

In the above embodiments of the present invention, the sample to be compressed has a circular planar cross section, but the present invention is not limited to this. It will be understood by those skilled in the art that the present invention can also be applied to sample processing, and in that case, the shapes of the sample container, flying member, etc. should be changed as appropriate in accordance with the shape of the sample.

The present invention is applicable to material synthesis using impact such as the conversion reaction of graphite 1 to diamond, or when granular high melting point materials such as tungsten and silicon carbide are subjected to dense impact.
Or impact treatment of solid or liquid condensed substances for various purposes, such as impact hardening of metal materials such as steel, or pulverizing ceramic powder such as silicon carbide and activating it by applying strain. Applies to cases.

The present invention will now be explained in more detail with reference to Examples.

Example 1 Green silicon carbide powder (bulk specific gravity approximately 1.9) was compressed using the impact compression apparatus shown in FIG.

However, the explosive layer 22 for preventing upper part breakage and the methacrylic plate 25
．． 26 was not used.

The flying object 5 has an inner diameter of 70 mm and a wall thickness of 1. 5mvt,
A brass tube with a length of 170 mm is used, and an inner diameter of 1
5 A hard vinyl chloride pipe with a diameter of 4 mm, a wall thickness of 5.5 mrn, and a length of 190 mm was installed.

At the bottom end of this hard PVC pipe is a plastic disc 2.
7 was attached, and a sub-explosive layer 28 with a thickness of 3 mm was provided along the inner wall circumferential surface.

The sub-explosive layer 28 has an average particle size of 0. Bent soft powder of 5 mm or less was mixed and stirred with uncured silicone resin (KE-10, manufactured by Shin-Etsu Chemical) at a weight ratio of 70:30, and the mixture was molded and then cured.

The sub-explosive layer is 6. It showed an explosive speed of 7 krn/sec.

Next, the annular space between the sub-explosive layer 28 and the brass tube 5 was filled with ampho explosive to form the main explosive layer 9.

The amount of Anho explosive used is approximately 2. At 1 kg, the loading specific gravity was approximately 0.8.

The detonation velocity of this main explosive layer is approximately 3. 1. km/sec.

The above sample has an inner diameter of 301It11L1 and a wall thickness of 2 mrn.
, length 1 4. Made of stainless steel (SUS
-3 04) Filled in a container 2 formed of a cylindrical tube (porosity about 40%), made of steel with convex shapes at both ends (SS-41)
The plugs 3 and 4 were screwed together.

The length of the screw part of plugs 3 and 4 is 5 mm, and the length of the lid part is 5 m.
It was m.

Container 2 has an inner diameter of 34.1 mm and a wall thickness of 3. It is surrounded and reinforced with a steel (SS-41) tube 9 mm long and 150 mm long, and at the bottom end of the container is a disc-shaped rubber explosive 41.5 mm in diameter and 5 mm thick that has the same composition as the sub-explosive layer 28. layer 21
Diameter 4 1. After fixing the sandwich between 5 mm and 5 mr/L Mekkrylic discs 23 and 24, the whole was concentrically inserted into the flying brass tube 5.

A plywood board 29 with a diameter of 1427'+712 and a wall thickness of 20vtyn is installed on the top, and on top of that a plywood board 29 with a diameter of 150mm and a wall thickness of 5
A 7n71L disc-shaped detonator 10 was attached.

As the detonator 10, a rubber disk made of equal weight parts of the vent lit and silicone resin was used.

The shock compression device constructed in this way was installed in the center of a large explosion chamber, and detonated with a No. 6 electric detonator.

After the explosion, the sample container was recovered and observed. Although the threaded part of the top stopper was torn, no damage to the bottom part was observed, and the sample recovery rate was recognized as 90%.

Table 1 shows the bulk specific gravity and chemical analysis of the collected samples.

In addition, when the sample was ground with a vibration mill, the particle size was 44
FIG. 6 shows the results of plotting the rate of generation of particles smaller than μ versus the vibration time.

Table 2 also shows the diffraction intensity and half-width C) of the collected sample by powder X-ray diffraction method.

Example 2 In Example 1, the wall thickness of the brass tube 5 for flight was set to 1.5 m.
Change the thickness of the lower explosive layer 21 from m to 3 mm, and increase the thickness of the lower explosive layer 21 to 5 mm.
In addition, the upper end of the container 2 is made of the same type of explosive as the explosive layer 21, with a diameter of 415 mm and a wall thickness of 5 mm.
The explosive layer 22 of the acrylic plate 25 of the same size. 2
A compression treatment was carried out using the same apparatus as in Example 1, except for the provision of a sandwich-shaped device in step 6.

No breakage of container 2 was observed, and the sample recovery rate was recognized as 100%.

When the sample was cut into rings along with the container and the cut surfaces were observed, the silicon carbide had changed color from its initial green color to black and had become hard and dense.

In addition, multiple spiral cracks were observed, and a molten condensation part with a diameter of 2 to 3 TL11L was observed in the center.

Table 1 shows the results of one measurement/test similar to Example 1.
It is shown in Table 2 and Figure 6.

Example 3 In Example 2, the wall thickness of the container reinforcing tube was set to 3. g mm
The main explosive 9 was paulownia dynamite (approximately 3
5kg was used and the detonation speed was approximately 6km/sec), the upper and lower explosive layers 2L22 were removed, and the methacrylic plate 23
, 24, 25.26 as diameter 48TfLTL1 wall thickness 5
The compression process was carried out using an apparatus that was exactly the same as in Example 2, except that two sheets of TL71L were used.

The container was torn off near the screws on both ends, and the sample recovery rate was approximately 5.
It was accepted as 0%.

When the sample was cut into rings along with the container and the cut surface was observed, it was found that there was a hole extending approximately 5 to 10 mm in the center.

It is thought that this part was formed due to melting and scattering of the sample.

The results of one measurement test similar to Example 1 are shown in Table 1, Table 2, and FIG. 6.

As is clear from the results shown in Table 2 and Figure 6,
The compression treatments shown in Examples 1 to 3 yield very fine ceramic particles with crystal strain.

Furthermore, as seen from Table 1 and the observation results, Examples 2 and 3 can generate temperatures high enough to cause melting and decomposition of silicon carbide (silicon carbide decomposes and sublimes from 2500°C at normal pressure). This proves that the melting point is believed to be approximately 2800°).

[Brief explanation of the drawing]

FIG. 1 is an explanatory diagram showing the impact compression processing apparatus according to the present invention in vertical section, FIG. 2 is an explanatory diagram showing the state in progress of processing by the apparatus of FIG. 1, and FIG. FIG. 4 is an explanatory diagram showing another embodiment of the present invention, FIG. 5 is a diagram showing the construction inside the container of FIG. 1 or 4, and FIG. The figure shows the crushing effect of a vibrating mill on a sample after impact treatment and before impact, and the broken line a =
d are graphs for Examples 1, 2 and 3 and unimpacted samples, respectively. In the figure, 1...sample, 2...container, 3,
4... Plug, 5... Flying member, 6...
...Gap, 9...Main explosive layer, 10...
- Explosive layer, 11... Detonator, 21, 22...
... Moderation explosive layer, 23, 24, 25.26...
・Shock wave attenuation plate, 27...Plastic plate, 2
8... Sub-explosive layer, 29... Separation plate, 3
1... Shock wave conducting rod, Y... Shock wave front, Z... Detonation wave front.

Claims (1)

[Claims] 1. A main explosive layer and a sub-explosive layer having a higher detonation speed than the main explosive are sequentially laminated on the opposite surface of a flying member installed parallel to the condensed substance extending in the axial direction with a gap, and
An impact treatment device for condensed substances, characterized in that a detonator is provided at one end of the sub-explosive layer. 2. The device according to claim 1, wherein the thickness of the main explosive layer is gradually and uniformly thinned from the one end side to the other end side. 3. The apparatus according to claim 1 or 2, wherein the condensed substance is housed in a metal container. 4. The device according to claim 3, wherein a rod made of a material having approximately the same impact impedance as the condensed material is provided on the central axis of the metal container. 5 positioning the condensed substance on the central axis of the metal container;
4. The device according to claim 3, wherein an object having substantially the same impact impedance as the condensed substance is installed in the space within the container surrounding the condensed substance. 6. A main explosive layer and a sub-explosive layer having a higher detonation speed than the main explosive layer are sequentially laminated on the opposite side of the flying member, which is installed parallel to and with a gap from the metal container containing the condensed substance extending in the axial direction, and A detonating part is provided at one end of the secondary explosive, and a deceleration explosive layer that explodes upon collision with the flying member is provided at both ends of the container or at the end opposite to the end on the side of the detonating part. Shock compression treatment equipment for condensed substances.