JP2018159492A - Flying body ejecting device and method for fragment impact test using the same - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a flying body ejecting device for ejecting a flying body at a requested speed in a fragment impact test, reducing variations in ejection speed of flying bodies, and capable of substituting as the conventional guns which are more expensive.SOLUTION: A flying body ejection device of the present invention comprises: a cylindrical container 11 having a first end and a second end which open in the axial direction; a cover member 12 for covering a first end 11a; a bottom member 13 for covering a second end 11b; a gunpowder 15 loaded into the cylindrical container 11; a communication passage 14 which penetrates the bottom member 13 for communicating with the inside of the cylindrical container 11; a priming powder 16 loaded in the communication passage 14 for exploding the gunpowder 15; a primer 17 disposed in contact with the priming powder 16 for firing the priming powder 16; a loading hole 12b which penetrates the cover member 12 for housing a flying body; a stopper which projects from the inner peripheral surface of the loading hole for preventing a flying body from moving toward the cylindrical container.SELECTED DRAWING: Figure 1

Description

  The present invention relates to a flying object injection apparatus capable of injecting a flying object corresponding to debris generated from a debris-type warhead, and a debris sensitivity test method using the same.

  In recent years, artillery ammunition and firing charges are required to have sufficient safety in consideration of storage and operation. The safety evaluation method is standardized by, for example, ITOP (International Operations Procedure) and STANAG (Standardization Agreement, NATO standard) in the United States. Test items for evaluating handling during operation include a drop test, a cook-off test, a detonation test, a gun sensitivity test, and a debris sensitivity test.

  In the Fragment Impact Test, fragments generated from a fragment type warhead collide with an explosive target (bullet, warhead, propellant, propulsion device, etc.). For example, as shown in Non-Patent Document 1, an explosive target is fixed to a fixed base. Then, a flying object (simulated fragment) corresponding to a fragment generated from the fragment-type warhead is fired to hit the flying object to the target. The reaction of the target at this time is investigated to confirm the safety of the target. In this test, a flying object is ejected using a dedicated artillery called a fragment GUN.

Ballistics Study Group, “Firearm Ammunition Technology Handbook”, 2012 revised edition, published by Japan Defense Technology Association, pages 1018 and 1025, April 2012

  However, a dedicated artillery such as the fragment GUN is generally expensive and requires a large amount of money to perform the test. Moreover, in order to inject the flying object at a high speed of about 1700 to 2600 m / s, it is necessary to generate an ultrahigh pressure of 500 MPa or more with the propellant. For this reason, the progress of erosion (burnt) in the gun barrel is fast and the life is short. Therefore, artillery is expensive and frequently exchanged.

  Accordingly, an object of the present invention is to provide a flying object injection apparatus that emits a flying object at a speed required in the fragment sensitivity test, has little variation in the injection speed of the flying object, and can be replaced with a conventional expensive artillery. It is.

  In order to solve the above-mentioned problem, one feature of the present invention is a flying object injection apparatus for emitting a flying object corresponding to a fragment generated from a fragment type warhead. The flying object injection device includes a cylindrical container having an axial first end and a second end open, a lid member that closes the first end, and a bottom member that closes the second end. The glaze is loaded into the cylindrical container. The communication passage passes through the bottom member, and an explosive for initiating the glaze is loaded into the communication passage. A detonator for igniting the explosive is provided in contact with the explosive. A loading hole is provided through the lid member. A stopper is provided so as to protrude from the inner peripheral surface of the loading hole in order to restrict the flying object inserted into the loading hole from moving toward the cylindrical container.

  Therefore, the flying object can be reliably held at a predetermined position of the loading hole by the stopper. For example, the flying object may contact the glaze while being loaded in the loading hole. If there is no stopper and the glaze contracts, the flying object may be misaligned. The flying speed of the flying object changes as the position of the flying object shifts before the firing. When variations occur in the amount of displacement of the flying object, variations occur in the ejection speed of the flying object. On the other hand, in this feature, a stopper is provided on the inner peripheral surface of the loading hole of the lid member. For this reason, it is possible to prevent the position of the flying object from shifting before the injection, and to prevent variations in the injection speed of the flying object. Therefore, the flying object in the fragment sensitivity test can be ejected at a required speed, and variations in the ejection speed can be reduced. The stopper has a simple configuration of protruding from the inner peripheral surface of the loading hole. Therefore, the flying object injection device can be configured at low cost.

  According to another feature, the stopper is an annular shape formed over the entire circumference of the loading hole. Therefore, the stopper can hold | maintain the outer periphery of the bottom face of a flying body over a perimeter. Thereby, the position shift of a flying object can be prevented reliably.

  According to another feature, the flying object has a cylindrical main body and a conical tip that tapers from the front end of the main body. The inner diameter of the loading hole is larger than the diameter of the main body. The stopper protrudes from the inner peripheral surface of the loading hole so as to face the rear end of the main body. Therefore, the flying object can be inserted into the loading hole, and the rear end of the flying object can be supported by the stopper. Further, by making the flying object have the shape, the flying posture of the flying object is stabilized. Thereby, the variation degree of the injection speed of the flying object is also reduced.

  According to another feature, the flying object injection device can enable the flying object to be injected at a speed of 1700-2600 m / s. Therefore, the flying object can be ejected at the required high speed.

  According to another feature, a debris sensitivity test method using these flying object injection devices can be performed. As a result, the flying object can be injected at a speed required in the fragment sensitivity test, and variations in the injection speed can be reduced. A debris sensitivity test method can be performed using an inexpensive flying object injection device.

  In this specification, the “debris-type warhead” refers to a warhead in which a glaze is contained in a shell represented by a grenade, and fragments of the shell are scattered by the explosion of the glaze. Unless otherwise specified, “XX to XX” indicating a numerical range means “XX or more and XX or less”.

It is sectional drawing of a flying body injection device. It is sectional drawing of a cover member. FIG. 3 is an enlarged view of region III in FIG. 2. FIG. 3 is an enlarged front view of FIG. 2 for showing a loading hole. It is a perspective view of a flying body. It is sectional drawing of the flying object injection apparatus in the vicinity of the loading hole with which the flying object was loaded. It is a front view of the loading hole in other embodiments. It is a front view of the loading hole in other embodiments. It is a model top view which shows a fragment sensitivity test. It is a model side view which shows a fragment sensitivity test.

<Aircraft injection device>
Hereinafter, one embodiment of the present invention will be described. The flying object injection device of this embodiment is used in a fragment sensitivity test, and injects a flying object (simulated fragment) corresponding to a fragment generated from a fragment type warhead.

  As shown in FIG. 1, the flying object ejection apparatus 1 includes a cylindrical container 11, a lid member 12, and a bottom member 13. A glaze 15 is loaded in the cylindrical container 11. An explosive 16 and a detonator 17 are connected to the bottom member 13. The cylindrical container 11 is a main body of the flying object injection apparatus 1 and has a cylindrical shape in which the first end 11a and the second end 11b are open. The inner diameter D1 and the axial length L1 of the cylindrical container 11 are determined according to the shape of the glaze 15 described later that is loaded inside the cylindrical container 11.

  The material of the cylindrical container 11 is not particularly limited as long as it is a hard material and can maintain the shape of the glaze 15 described later during transportation or storage. When the material strength of the cylindrical container 11 is high, the expansion of the product gas generated after the glaze detonates is suppressed, and the detonation pressure acting on the flying object becomes high. For this reason, the amount of glaze to be used can be suppressed. For example, the material of the cylindrical container 11 is preferably a metal material such as iron, aluminum, or brass that has high material strength and is inexpensive.

  As shown in FIG. 2, the lid member 12 is cylindrical and has a front surface (left surface in the drawing) and a back surface (right surface in the drawing). An annular groove or step 12 a is formed on the outer peripheral edge of the back surface of the lid member 12. The lid member 12 has a disk having a diameter corresponding to the outer diameter of the cylindrical container 11 on the front surface side, and a disk having a diameter corresponding to the inner diameter of the cylindrical container 11 on the back surface side. These discs are positioned so that the central axes are aligned. An annular stepped portion 12a is formed between these discs. As shown in FIG. 1, the first end 11 a of the cylindrical container 11 is fitted into the stepped portion 12 a of the lid member 12. Thereby, the lid member 12 closes the opening of the first end 11 a of the cylindrical container 11. When the lid member 12 cannot be sufficiently connected to the cylindrical container 11 simply by fitting, the first end 11a of the cylindrical container 11 and the bottom member 13 may be fused.

  As shown in FIGS. 2 to 4, a loading hole 12 b is provided in the center of the lid member 12 along the central axis of the lid member 12. The loading hole 12b penetrates the lid member 12 in the thickness direction. A stopper 12c is provided on the inner peripheral surface of the loading hole 12b. The stopper 12c is located along the opening end of the back surface of the loading hole 12b or in the vicinity of the opening end of the back surface. The stopper 12c protrudes from the inner peripheral surface of the loading hole 12b toward the central axis of the loading hole 12b. The stopper 12c is formed over the entire circumference of the inner peripheral surface of the loading hole 12b and has an annular shape.

  As shown in FIG. 6, the flying object 2 is loaded into the loading hole 12b. The inner diameter of the loading hole 12 b is a size corresponding to the diameter of the flying object 2 and is slightly larger than the diameter of the flying object 2. Preferably, the inner diameter of the loading hole 12b is determined so that the gap between the loading hole 12b and the flying object 2 described later is as small as possible. By reducing the gap, the center axis of the loading hole 12b and the center axis of the flying object 2 are matched as much as possible, and the landing accuracy of the flying object 2 on the target is improved. It is preferable that the clearance between the loading hole 12b and the flying object 2 conforms to the “clearance fit” fitting state defined in JIS B 0401.

  The length of the loading hole 12b (thickness of the lid member 12) only needs to be longer than the length of the flying object 2, and can be longer than the length of the flying object 2 as shown in FIG. However, if the loading hole 12b is too long, the injection speed of the flying object 2 becomes too high. Therefore, the length of the loading hole 12b is appropriately set according to the required flying object speed. For example, when the flying object injection device 1 is used in the fragment sensitivity test, the length of the loading hole 12b is preferably 1 to 2 times the length of the flying object.

  As shown in FIG. 6, the amount of protrusion of the stopper 12c from the inner peripheral surface of the loading hole 12b is preferably 20% or less of the diameter of the loading hole 12b. When it becomes larger than 20%, the stopper 12c blocks more openings of the loading hole 12b. For this reason, the pressure action area to the flying object 2 decreases, and the flying object 2 cannot be accelerated sufficiently. The contact area between the flying object 2 and the glaze 15 is also reduced. For this reason, the contact | adhesion power of the flying body 2 and the glaze 15 falls. As a result, the flying object 2 may be displaced with respect to the loading hole 12b, resulting in variations in the injection speed of the flying object 2. Therefore, the variation in the injection speed of the flying object 2 can be suppressed by setting the protruding amount of the stopper 12c to 20% or less of the diameter of the loading hole 12b.

  As shown in FIG. 1, the bottom member 13 has a bottomed cylindrical shape, and includes a disk-shaped bottom portion 13 b and an annular wall portion 13 a that stands up from the outer peripheral edge of the bottom portion 13 b. The wall portion 13a protrudes in the axial direction from the entire circumference of the outer peripheral edge of the bottom portion 13b. The size of the inner diameter of the wall portion 13 a corresponds to the outer diameter of the cylindrical container 11. The second end 11b of the cylindrical container 11 is fitted inside the wall portion 13a, and the bottom member 13 closes the opening of the second end 11b of the cylindrical container 11. When the bottom member 13 cannot be sufficiently connected to the cylindrical container 11 simply by fitting, the second end 11b of the cylindrical container 11 and the bottom member 13 may be fused.

  As shown in FIG. 1, the communication path 14 is cylindrical and penetrates the bottom member 13 in the thickness direction. The communication path 14 is located at the center of the bottom member 13 along the central axis of the bottom member 13. One end of the communication path 14 protrudes from the surface of the bottom member 13 (the right side in the figure). The communication path 14 communicates the internal space of the cylindrical container 11 with the outside.

  The glaze 15 is filled in the cylindrical container 11. The glaze 15 is used to accelerate the flying object 2. As the glaze 15, conventionally used glaze used for warheads such as grenades is used. The injection speed of the flying object 2 is proportional to the detonation pressure and detonation speed of the glaze. Therefore, when using an explosive having a high detonation pressure and a high detonation speed, the amount of the glaze 15 can be reduced. Therefore, the glaze 15 is preferably PBX (Plastic Bonded Explosive) mainly composed of cyclotetramethylenetetranitramine, which is HMX (High Melting Point Explosive), from the viewpoint of safety during production. PBX includes an injection type PBX and an explosive which are mixed after explosives, a binder and a plasticizer are mixed and poured into a mold, and a compression type PBX which is granulated with a binder and then compressed. As the glaze 15, a casting type PBX is preferable. This is because the casting type PBX contains a thermosetting resin, so that it also serves to closely contact the flying object and the glaze and is advantageous in terms of fixing the flying object.

  The injection speed of the flying object 2 is proportional to the amount of the glaze 15. Therefore, the filling amount of the glaze 15 is not particularly limited, but can be appropriately set according to the mass of the flying object 2 and the target injection speed of the flying object 2. The length (L2) and diameter (D2) of the columnar glaze 15 and the ratio of the length to the diameter (L2 / D2) can be set as appropriate. L2 / D2 is preferably 0.4 to 2.0, more preferably 1.5 to 1.9. If L2 / D2 is less than 0.4, the flying speed of the flying object is not sufficient, and if L2 / D2 is larger than 2.0, the flying speed of the flying object becomes too high.

  As shown in FIG. 1, the explosive 16 is filled in the communication path 14. The detonator 16 is used to detonate the glaze 15. As the explosive 16, it is possible to use a conventional one that is detonated with a detonator. For example, it is preferable to use PBX having high safety as the explosive 16.

  As shown in FIG. 1, the detonator 17 has an axial shape and is inserted into the explosive 16. The detonator 17 is not particularly limited as long as it can ignite the explosive 16. In consideration of availability and handleability, it is preferable to use the electric detonator used for the blasting operation as the detonator 17.

  As shown in FIG. 5, the flying object (simulated fragment) 2 loaded in the flying object injection apparatus 1 integrally has a columnar main body 21 and a tapered conical tip part 22. Since the distal end portion 22 is conical, air easily flows along the side surface from the distal end of the distal end portion 22, and air resistance is small. Therefore, air can flow smoothly from the front end portion 22 to the rear of the main body portion 21. Thus, the flying posture of the flying object 2 is stabilized, and the accuracy of hitting the flying object 2 to the target in the fragment sensitivity test is increased.

  The material of the flying object 2 can be a metal material generally used for warheads, and is not particularly limited. For example, high carbon steel is preferable from the viewpoint of availability. If it is a soft material that is not used for warheads, the flying object will be cracked or melted and cannot serve as a simulated piece. Since the mass of the flying object simulates a warhead fragment, it is preferably set to 10 to 100 g.

  As shown in FIG. 6, the flying object 2 is loaded into the loading hole 12 b of the flying object injection apparatus 1. The flying body 2 is restricted from moving toward the internal space of the cylindrical container 11 by the stopper 12c at the end of the loading hole 12b. The flying object 2 can be brought into close contact with the glaze 15 by being set in the loading hole 12b. For this reason, the flying object 2 is held in position by the glaze 15.

  With reference to FIG. 1, FIG. 6, operation | movement of the flying object injection apparatus 1 is demonstrated. First, the flying object 2 is loaded into the loading hole 12b. The detonator 16 is ignited by the detonator 17. The explosive 16 is detonated, and then the glaze 15 is detonated in the internal space of the cylindrical container 11. A pressure of several tens of Pa or more is generated in the inner space of the cylindrical container 11 by detonation of the glaze 15, and the flying object 2 is pushed out from the loading hole 12 b by the pressure. The flying object 2 is ejected along the loading hole 12b, and the flying object 2 is ejected from the loading hole 12b along the tangential direction of the inner peripheral surface of the loading hole 12b.

  As shown in FIG. 6, the glaze 15 is filled in the cylindrical container 11 so as to be in close contact with the flying object 2. The glaze 15 contracts over time, and the glaze 15 may pull the flying object 2 toward the internal space of the cylindrical container 11. When there is no stopper 12c, the flying object 2 moves toward the internal space of the cylindrical container 11, and the amount of movement varies depending on how the glaze 15 contracts. This may cause variations in the injection speed of the flying object. On the other hand, the flying object injection device 1 has a stopper 12c at the end of the loading hole 12b. For this reason, it is suppressed that the position shift before the injection of the flying object 2 occurs, and the variation in the injection speed of the flying object 2 is reduced.

  As shown in FIG. 4, the stopper 12c is formed in an annular shape. Therefore, the stopper 12c can hold the flying object 2 stably by facing the entire periphery of the outer periphery of the bottom surface of the flying object 2. Therefore, it is possible to reliably prevent the displacement of the flying object 2 with respect to the loading hole 12b.

(Other embodiments)
As described above, an annular stopper 12c is provided in the loading hole 12b (see FIG. 4). The loading hole 12b may be provided with a stopper 12d shown in FIG. 7 instead of the stopper 12c. The stopper 12d has a shape in which one or more annular portions are cut out. Alternatively, the loading hole 12b may be provided with a plurality of stoppers 12f shown in FIG. 8 instead of the stopper 12c. The stoppers 12f are claw-shaped and are arranged at predetermined intervals along the inner periphery of the loading hole 12b.

  As described above, the flying object injection apparatus 1 is configured by assembling the cylindrical container 11, the lid member 12, the bottom member 13, and the communication path 14 which are separate members. Instead of this, the flying object injection apparatus 1 may include the cylindrical container 11 and the lid member 12 as a single member. Or you may have the cylindrical container 11 and the bottom member 13 as one member, the bottom member 13 and the communicating path 14 as one member, or these three parts or more as one member.

  As described above, the flying object ejection apparatus 1 uses the flying object 2 shown in FIG. Instead of this, the flying object injection apparatus 1 may use a flying object of another shape.

<Debris sensitivity test method>
A typical fragment sensitivity test method using the flying object injection apparatus 1 will be described with reference to FIGS. In the fragment sensitivity test, two stopper plates 4 are installed between the flying object injection device 1 and the target 3. A debris passage conduit 5 is installed between the two stopper plates 4, and two measuring devices 6 are installed between the stopper plate 4 and the target 3.

  The target 3 is a target for hitting the simulated debris. Specifically, ammunition having ignitability or explosive properties such as a bullet, a warhead, a propellant, a propulsion device or the like to be tested. The target 3 is fixed on the gantry 31.

  As shown in FIGS. 9 and 10, the stopper plate 4 is a plate for protecting the equipment, the measuring device, and the like. A through hole 4 a is provided at the contact point between the injection line of the flying object 2 emitted from the flying object injection apparatus 1 and the stopper plate 4. From the flying object injection device 1, not only the flying object 2, but also the fragments of the cylindrical container 11 and the lid member 12 in the flying object injection device 1 may explode and scatter. The stopper plate 4 can protect the equipment and the measuring device from debris that explode and fly by allowing only the flying object 2 to pass through the through hole 4a and not passing other objects. 9 and 10, the stopper plates 4 are arranged one by one before and after the debris passage conduit 5, but only one of them may be arranged. However, it is preferable to arrange at least one piece before and after the debris passage conduit 5. This is because the equipment and measuring device can be protected more reliably.

  As shown in FIGS. 9 and 10, the debris passage conduit 5 is cylindrical and is installed along the emission line of the flying object 2 launched from the flying object injection apparatus 1. Since the ejected flying object 2 goes straight, it is necessary to adjust the arrangement and direction of the fragment passage conduit 5 so that the flying object 2 does not touch the inner wall. Therefore, it is preferable to install the debris passage conduit 5 so as to penetrate the protective sand pile 7 formed by stacking the sandbags 7a, for example. This is because the sand pile can be easily repaired even if a part thereof is damaged by a fragment of the flying object injection device 1 or the like, and fine adjustment in the installation of the fragment passage conduit 5 can be facilitated.

  The measuring device 6 measures the flying object speed. As the measuring device 6, for example, a flash X-ray device or a speed calculating means based on time measurement using a sensor can be used. The measuring device 6 is preferably speed calculation means using a sensor in consideration of cost. The speed calculation means using the sensor prepares a pair of sensors, obtains the elapsed time of the flying object passing between the sensors (section), and calculates the average of the flying objects passing the section from the “distance distance / elapsed time”. Calculate the speed. Examples of this type of sensor include a high-speed video camera using a foil type or linear type using a contact system, or an optical system.

  In the fragment sensitivity test method, first, the flying object 2 is injected from the flying object injection apparatus 1. The flying object 2 passes through the through hole 4a of the stopper plate 4 and the inside of the cylindrical fragment passage conduit 5, and is hit by the target 3. By observing the mode of reaction of the target 3 at this time, it is possible to confirm the safety when the target 3 having explosive properties hits a debris due to shelling or the like. The flying object speed can be measured by the measuring device 6. The flying object speed needs to be set according to the ITOP standard or the STANAG standard, and is required to be 1700-2600 m / s in the fragment sensitivity test.

  The mode of reaction when the flying object 2 hits the target 3 can be measured by using photographing devices such as cameras provided at one place or several places around the target 3. Various cameras such as a high-speed video camera, a range camera, and an infrared camera can be used as the photographing device.

  From the viewpoint of ensuring safety, in preparation for the case where the flying object 2 penetrates the target 3, the flying object 2 has landed behind the target 3 (the direction opposite to the installation direction of the flying object injection device 1 when viewed from the target 3). It is also possible to provide a stop where it can be stopped.

  Hereinafter, the embodiment will be described more specifically with reference to examples and comparative examples.

(Examples 1-4 and Comparative Examples 1-4)
In Examples and Comparative Examples, experiments were performed using the flying object injection apparatus 1 shown in FIG. An annular stopper 12c shown in FIGS. 3 and 4 was provided in the loading hole 12b of the flying object injection apparatus 1 of Examples 1 to 4. The protrusion amount of the stopper 12c was set to 0.1 mm. On the other hand, in Comparative Examples 1-4, the cylindrical loading hole 12b was formed without providing the stopper 12c in the loading hole 12b. In Examples 1 to 4 and Comparative Examples 1 to 4, the inner diameter (container inner diameter) D1 and the axial length (container length) L1 of the cylindrical container 11 were adjusted under the conditions shown in Tables 1 and 2.

  As the glaze 15 (explosive glaze), PBXN-101, which is an HMX PBX composed of 82% by mass of HMX and 18% by mass of polystyrene, was used. PBXN-101 was vacuum cast into a cylindrical container, cured at 60 ° C. for 6 days, formed into a cylindrical shape, and loaded into the cylindrical container 11. The outer diameter (glaze diameter) D2 and the axial length (glaze length) L2 of the cylindrical glaze 15 were adjusted under the conditions shown in Tables 1 and 2.

  As the detonator 16 (detonation glaze), RDX PBX composed of 75% by mass of RDX and 25% by mass of binder was used. The RDX PBX was vacuum-cast into a vinyl chloride pipe having an inner diameter of 31 mm and an axial length of 30 mm, cured at 60 ° C. for 6 days, formed into a cylindrical shape, and loaded into the communication path 14.

  The injection tests of the flying object injection devices of Examples 1 to 4 and Comparative Examples 1 to 4 were performed. The test was performed in the same manner as the fragment sensitivity test method shown in FIGS.

(Measurement of flying object speed)
A pair of lines were installed as the measuring device 6 with an interval of 1 m, and the flying object speed was measured. As for the flying object speed, three launch tests were performed under the same conditions, and the average of two shots with similar flying object speeds was taken as the flying object speed.

(Evaluation of flying speed variation)
In the measurement of the flying object speed, the difference between the maximum value and the minimum value of the flying object speed was calculated and used as the flying object speed variation degree.

  As shown in Table 1, in Examples 1 to 4, since the stopper was provided, the flying object speed variation was small.

  As shown in Table 2, since Comparative Examples 1 to 4 were not provided with a stopper, the flying object speed variation was large.

1 Flying object injection device 2 Flying object (simulated debris)
11 cylindrical container 11a first end 11b second end 12 lid member 12c, 12d, 12f stopper 12b loading hole 13 bottom member 14 communication path 15 glaze 16 explosive 17 detonator 21 main body 22 tip

Claims (5)

A flying object injection apparatus for injecting a flying object corresponding to a fragment generated from a fragment type warhead,
A cylindrical container having first and second axial ends open;
A lid member for closing the first end;
A bottom member for closing the second end;
A glaze loaded into the cylindrical container;
A communication passage penetrating the bottom member;
An explosive loaded in the communication path to detonate the glaze;
A detonator in contact with the initiator to ignite the initiator;
A loading hole penetrating the lid member;
A flying object injection apparatus comprising: a stopper projecting from an inner peripheral surface of the loading hole to restrict the flying object inserted into the loading hole from moving toward the cylindrical container. The flying object injection apparatus according to claim 1,
The said stopper is a flying body injection apparatus which is the annular | circular shape formed over the perimeter of the said loading hole. It is a flying object injection device according to claim 1 or 2,
The flying body has a cylindrical main body portion, and a conical tip portion that is tapered from the front end of the main body portion,
The inner diameter of the loading hole is larger than the diameter of the main body,
The said stopper is a flying object injection apparatus which protrudes so that it may face the rear end of the said main-body part of the said flying object from the internal peripheral surface of the said loading hole. It is a flying object injection device as described in any one of Claims 1-3, The flying object injection device which can inject the said flying object at the speed of 1700-2600 m / s. The debris sensitivity test method using the said flying object injection device as described in any one of Claims 1-4.

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