JP5375755B2 - Flying object injection device - Google Patents

Description

  The present invention relates to a flying object injection apparatus used in a collision test for an aircraft engine case and the like, and more particularly to a flying object injection apparatus capable of accurately separating a sabot and a flying object.

  A gas gun-type flying object injection device that uses a gas force to strike a flying object toward a target is used for a collision test at an impact speed of 100 to 300 m / s for an aircraft engine case or the like.

  In this flying object injection device, the cross-sectional shape of the acceleration tube (cannon) for accelerating the flying object is a shape having a constant inner diameter along the emission direction of the flying object. Therefore, in order to inject a flying object having an arbitrary shape, size, and posture, a cylindrical plastic container called a cylindrical sabot having an outer diameter equivalent to the inner diameter of the acceleration tube is used.

  Since the accuracy of the separation between the sabot and the flying object greatly affects the accuracy of the collision test and the running cost, the technique for separating the sabot and the flying object in the flying object ejecting apparatus is indispensable.

  Conventionally, for example, a board called a sabo stopper having a through hole smaller than the outer diameter of the sabo and larger than the flying body is used, and only the flying body is passed through the through hole to separate the sabo and the flying body.

  Further, a split-type sabot has been used to divide the sabot by air resistance during free flight after being emitted from the acceleration tube, and to separate the sabot from the flying object (see, for example, Patent Document 1). ).

  In addition, a separation part formed by bundling a plurality of strips with an annular member to form a cylinder and gradually reducing the inner diameter of the cylinder, the sabo is gradually decelerated in this separation part to separate it from the flying object There is also a way to make it. In this method, the sabot is finally stopped at the separation section.

JP 2004-271216 A Japanese Patent No. 3103861

  However, the method using the sabo stopper has a problem that the attitude of the flying object is disturbed because the sabo greatly deforms due to an impact when the sabo collides with the sabo stopper.

  Further, in the method using the split-type sabot, since air resistance is used, a long distance is required to separate the sabot and the flying object, and the flying object injection device becomes large. Furthermore, normally, in order to maintain the attitude of the flying object, the tip of the accelerating tube in the injection direction and the target are accommodated in a vacuum chamber with no air resistance, but air resistance is used to divide the sabot. There is also a problem that the inside of the vacuum chamber cannot be evacuated and the attitude of the flying object is disturbed by air resistance.

  In the method using the separation unit, a long distance (for example, about 2 m) for gradually reducing the inner diameter of the cylinder is required, and the flying object injection device becomes large. In addition, since the inner diameter of the cylinder is finally reduced considerably in order to stop the sabot in the separation part, the sabot is greatly deformed before the sabot stops. Therefore, there is a problem that a part of the sabot damaged by the deformation reaches the target, an accurate collision test cannot be performed, and the running cost is deteriorated.

  Accordingly, an object of the present invention is to provide a flying object ejection apparatus capable of accurately separating a sabot and a flying object.

This invention has been made in order to achieve the above object, a cylindrical Szabo holding the flying Shokarada housed in an injection direction rear end, accelerated the Szabo utilizes explosion energy of the gas and explosives An accelerating tube, a target that is provided at a front end side in the injection direction of the accelerating tube, and that collides with the flying object accelerated in the accelerating tube; In a flying object injection apparatus comprising a sabo stopper for causing collision, an inner diameter of the sabo is formed so as to form a deceleration section that is integrally attached to the tip of the accelerating tube in the injection direction and decelerates only the sabo. The flying object injection device includes a sabo separating muzzle having a reduced diameter portion that is reduced in diameter than an outer diameter, and an inner diameter of the deceleration section is 95 to 99% of an outer diameter of the sabot .
The injection direction length of the deceleration section may be the same as the injection direction length of the sabot.
A boundary portion between the inner peripheral surface of the deceleration section and the inner peripheral surface at the rear end in the injection direction may be formed as a tapered portion so that the diameter thereof gradually changes.

  According to the present invention, the sabot and the flying object can be accurately separated.

It is the schematic which shows the flying object injection apparatus of this invention, (a) is a schematic side view, (b) is the schematic in a vacuum chamber. It is a figure which shows the structure of the muzzle for sabo separation used for this invention, (a) is the figure seen from the injection | emission direction front end, (b) is the XX sectional drawing of (a). It is a figure which shows the structure of the sabot used for this invention. (A)-(c) is a figure explaining the separation process of the sabot and a flying body in the flying body injection apparatus of this invention.

  Preferred embodiments of the present invention will be described below with reference to the accompanying drawings.

  FIG. 1 is a view showing a flying object injection apparatus according to a preferred embodiment of the present invention, where (a) is a view seen from the front end side in the injection direction, and (b) is a cross section taken along line XX of (a). FIG.

  As shown in FIGS. 1 (a) and 1 (b), the flying object ejection device 1 accommodates a solid cylindrical sabot 3 holding a projecting body 2 at the rear end (left side in the figure) in the ejection direction. Acceleration tube 4 for accelerating 3 using the explosive energy (acceleration energy) of gas and explosive, and the injection direction tip (right side in the figure) of acceleration tube 4 are accommodated, and flight accelerated in acceleration tube 4 A vacuum chamber 6 in which a target 5 that causes the body 2 to collide is accommodated, and a sabo stopper 7 that is provided in the vacuum chamber 6 and receives the accelerated sabo 3 to cause only the flying object 2 to collide with the target 5. . In this embodiment, a case where gas is used as acceleration energy will be described.

  The target 5 to be tested is, for example, a material that requires impact resistance design such as a fan case of a jet engine. As the flying object 2, various things such as a bird, gelatin imitating it, or a metal piece are used. As a test of a collision phenomenon using these, for example, there is a test for confirming impact resistance when a bird is sucked into a jet engine.

  The sabot 3 is made of a polymer material such as polyethylene. Since the polymeric material has a large elongation at break and is not easily broken even when it collides with the sabo stopper 7, it is possible to prevent the sabo 3 from being broken and the fragments from being scattered. The shape of the sabot 3 will be described later.

  The acceleration tube 4 is supported by a plurality (three in FIG. 1) of support pillars S along the longitudinal direction thereof, and the center thereof is made to be substantially in a straight line. An acceleration energy supply system 8 is connected to the rear end of the acceleration tube 4 in the injection direction. The acceleration energy supply system 8 includes a pressure accumulation container 9 for accumulating gas, a gas cylinder 10 for supplying gas to the pressure accumulation container 9, and a valve 11 connected to the rear end of the acceleration pipe 4 in the injection direction.

For example, helium (He) or nitrogen (N ₂ ) is used as the gas supplied to the pressure accumulating vessel 9. As an inert gas, helium having a small molecular weight is preferable because it is most easily accelerated.

  The valve 11 is composed of, for example, an electromagnetic valve. After accumulating gas in the pressure accumulating container 9, the sabo 3 accommodated at the rear end of the accelerating tube 4 in the injection direction is accelerated by opening the electromagnetic valve all at once.

  The acceleration energy supply system 8 and the acceleration tube 4 are connected via a flange portion 12. When the sabot 3 holding the flying object 2 is installed at the rear end of the acceleration tube 4 in the injection direction, the acceleration energy supply system 8 and the acceleration tube 4 are separated from each other with the flange portion 12 as a boundary, and the injection direction of the acceleration tube 4 The sabot 3 is installed in the flying object installation unit 13 at the rear end. Therefore, the acceleration energy supply system 8 is movable in the left-right direction in the figure.

  A target 5 that collides with the flying object 2 accelerated in the acceleration tube 4 is accommodated in a vacuum chamber 6 connected to the tip of the acceleration tube 4 in the emission direction. On the outside of the vacuum chamber 6, devices for capturing a collision phenomenon such as a laser and a high-speed camera are installed. Further, an observation window W is provided on the side wall of the vacuum chamber 6.

  In addition, a seal flange 14 having a seal portion (for example, packing) is formed at the distal end portion of the acceleration tube 4 in the injection direction. The tip of the acceleration tube 4 in the injection direction is inserted into an insertion hole formed in the side wall of the vacuum chamber 6 and the seal flange 14 is screwed to the side wall, whereby the tip of the acceleration tube 4 in the injection direction is sealed in the vacuum chamber 6. To be accommodated. Thereby, the inside of the acceleration tube 4 is also evacuated, and the sabo 3 holding the flying object 2 in the acceleration tube 4 is sufficiently accelerated.

  A through hole 15 that is smaller than the sabot 3 and allows only the flying object 2 to pass through is formed in the sabot stopper 7 that receives the accelerated sabot 3. Therefore, the accelerated sabot 3 is stopped by colliding with the outer peripheral portion of the through hole 15, and only the flying object 2 collides with the target 5. The sabot stopper 7 is formed of a material and a design that have soundness against the impact force of the sabot 3.

  Now, the flying object injection device 1 according to the present embodiment can accurately separate the sabot 3 and the flying object 2 by separately decelerating and stopping the sabot 3.

  Therefore, as shown in FIGS. 2A and 2B, the flying object injection apparatus 1 is integrally attached to the tip of the acceleration tube 4 in the injection direction, and a muddy 16 for sabo separation for decelerating the sabo 3. Is provided.

  The sabo separating muzzle 16 has an inner diameter equal to that of the accelerating tube 4, and the inner diameter is outside the sabo 3 so as to form a deceleration section A for decelerating the sabo 3 on a part of its inner peripheral surface. It has the reduced diameter part 17 diameter-reduced rather than the diameter.

  The deceleration section A is for decelerating the sabot 3 by separating the sabot 3 and the flying object 2 by applying resistance (that is, frictional force) to the sabot 3 passing through this portion. That is, the deceleration section A is intended only for the deceleration of the sabo 3 and the separation of the flying object 2 using the sabo 3, and the sabo stopper 7 described above is used to stop the sabo 3.

  In order to decelerate only the sabot 3, the inner diameter of the deceleration section A needs to be larger than that of the flying object 2.

  Further, the resistance applied to the sabot 3 can be increased as the inner diameter of the deceleration section A is reduced. As a result, the sabot 3 can be greatly decelerated and the sabot 3 and the flying object 2 can be separated with a sufficient distance.

  However, if the inner diameter of the deceleration section A is made too small, the deformation of the sabot 3 when it passes through the deceleration section A becomes too large, and the sabot 3 may be damaged and adversely affect the collision test. There is a risk of disturbing the posture.

  Therefore, it is necessary to design the sabo 3 so that it does not deform excessively or break with it. For example, it is conceivable that the inner diameter of the deceleration section A is set to about 95 to 99% of the outer diameter of the sabot 3 in consideration of the compressive strength of the sabot 3. The length of the deceleration section A in the injection direction is, for example, approximately the same as the length of the sabot 3 in the injection direction.

  A boundary portion between the inner peripheral surface of the deceleration section A and the inner peripheral surface at the rear end in the injection direction is preferably formed as a tapered portion 18 so that the diameter thereof changes gradually. Thereby, it becomes possible to relieve the impact when the sabot 3 enters the deceleration zone A.

  A flange portion 20 for connecting to a flange portion 19 formed at the front end in the injection direction of the accelerating tube 4 is formed at the rear end in the injection direction of the sabot separating muzzle 16. By connecting these flange portions 19 and 20 using bolts or nuts, the sabot separating muzzle 16 is integrally attached to the tip of the acceleration tube 4 in the injection direction.

  Further, as shown in FIG. 3, the sabo 3 used in the flying object ejection apparatus 1 includes a columnar (solid cylindrical) sabo body 21 fitted to the inner peripheral surface of the acceleration tube 4, and a sabo body 21. It is preferable to include a solid cylindrical flying body holding portion 22 that is integrally formed at the tip in the injection direction and holds the flying body 2.

  The flying object holding part 22 is formed so that its outer diameter is smaller than the inner diameter of the deceleration zone A. The outer diameter of the flying object holding part 22 is formed to be smaller than the inner diameter of the deceleration zone A so that the flying object holding part 22 does not come into contact with the deceleration zone A and deform when the sabot 3 enters the deceleration zone A. It is to make it.

  The flying object holding unit 22 is formed into various shapes according to the shape of the flying object 2 that collides with the target 5. Depending on the angle at which the flying object 2 is placed, the flying object 2 may fall due to its own weight. Therefore, the placing may be assisted by using an adhesive tape or the like that does not have a strong adhesive force.

  The length of the flying object holding part 22 (projection length from the sabo body 21) is longer than the depth of the bottom part that houses the flying object 2 (for example, about 10 to 20 mm).

  An injection test using the flying object injection apparatus 1 will be described.

  First, before the test, the sabo 3 holding the flying object 2 on the flying object installation part 13 at the rear end in the injection direction of the accelerating pipe 4 is separated from the acceleration pipe 4 and the acceleration energy supply system 8 with the flange part 12 as a boundary. Contain and install.

  Thereafter, the inside of the vacuum chamber 6 is evacuated to a desired degree of vacuum, and gas is supplied from the gas cylinder 10 to the pressure accumulating vessel 9. By vacuuming, the inside of the vacuum chamber 6 and the inside of the acceleration tube 4 to the valve 11 are evacuated. When the accumulator 9 is filled with sufficient gas for accelerating the sabot 3 at a desired speed, as shown in FIG. 4 (a), the valve 11 is opened at once, and the accelerator tube is filled with the filled gas. The sabo 3 accommodated at the rear end in the injection direction 4 is accelerated. That is, the sabo 3 is accelerated at a desired speed by appropriately adjusting the pressure in the pressure accumulating vessel 9 and the degree of vacuum in the accelerating tube 4 to the valve 11 according to the test environment. Can do.

  As shown in FIG. 4B, when the savo 3 accelerated in the accelerating tube 4 passes through the deceleration section A, the sabo body 21 is gradually decelerated due to resistance from the deceleration section A. At this time, the sabo body 21 that has received resistance from the deceleration section A is deformed, but the flying object holding part 22 is not connected to the deceleration part A because the outer diameter of the flying object holding part 22 is smaller than the inner diameter of the deceleration part A. Almost no deformation due to resistance.

  Further, immediately after the sabot 3 enters the deceleration zone A, the speed of the flying object 2 is maintained by inertia, so the distance between the flying object 2 and the sabot 3 gradually increases, and the flying object 2 is in its posture. It is separated from the sabot 3 while maintaining

  Then, as shown in FIG.4 (c), the sabot 3 collides with the outer peripheral surface of the through-hole 15 of the sabot stopper 7, and the sabot 3 is stopped. On the other hand, the flying object 2 passes through the through-hole 15 of the sabo stopper 7 and collides with the target 5 previously stored in the vacuum chamber 6. The impact resistance performance of the target 5 is evaluated based on the information obtained from the target 5 after the collision and various devices such as a laser and a high-speed camera.

  When the repeated test is performed, the sabot 3 remaining in the vacuum chamber 6 is removed, the acceleration tube 4 and the acceleration energy supply system 8 are separated again, and the flying object installation unit 13 at the rear end in the emission direction of the acceleration tube 4. After the sabo 3 holding the flying object 2 is accommodated, the test is performed.

  As described above, according to the flying object ejection apparatus 1 according to the present embodiment, the sabot 3 is decelerated by the sabo separating muzzle 16, and the sabot 3 is stopped by the sabo stopper 7. Since the stop and the acceleration and deformation applied to the sabo 3 can be reduced, the sabo 3 and the flying object 2 can be accurately separated without affecting the attitude of the flying object 2.

  Further, since the sabo 3 is restrained in the sabo separating muzzle 16 during deceleration, the sabo 3 can be separated more stably than the method in which the sabo is simply collided with the sabo stopper and the sabo is separated and stopped simultaneously.

  Furthermore, the separation section of the sabot and the flying object can be shortened compared to the separation method using air resistance and the method of stopping the sabot at the separation portion formed by a strip, and the apparatus can be miniaturized.

  In addition, in the flying object injection apparatus 1, the sabo 3 includes a sabo body 21 that fits on the inner peripheral surface of the acceleration tube 4, and a flying object holding part 22 that has an outer diameter smaller than the inner diameter of the deceleration section A. Therefore, the sabot 3 and the flying object 2 can be separated before the flying object holding part 22 is deformed by deformation when the sabot 3 enters the deceleration section A, and the flying object 2 is maintained in its posture. Can be injected.

  The deceleration section A is not limited to the above-described configuration, and may be any configuration that can decelerate only the sabot 3. For example, a slow taper-shaped deceleration section that gradually decreases the inner diameter of the sabo separating muzzle 16 or a deceleration section having a large friction coefficient by providing a protrusion on the inner peripheral surface of the sabo separating muzzle 16 is provided. Or may be configured.

  In the present embodiment, the sabo 3 including the sabo body 21 and the flying object holding unit 22 is used. However, the shape of the sabo 3 is not limited to this, and is a solid that is normally used. A cylindrical sabot may be used.

DESCRIPTION OF SYMBOLS 1 Flying object injection apparatus 2 Flying object 3 Sabo 4 Acceleration pipe 5 Target 7 Sabo stopper 16 Sabo separation muzzle 17 Reduced diameter part A Deceleration section

Claims (3)

A cylindrical sabo holding a flying object is accommodated at the rear end of the injection direction, and an acceleration tube for accelerating the sabo using the explosive energy of gas or explosive, and provided at the front end side of the acceleration tube in the injection direction. A flying object injection apparatus comprising: a target for colliding the flying object accelerated in the accelerating tube; and a sabot stopper for receiving the accelerated sabot and causing the flying object to collide with the target.
For sabo separation, which is integrally attached to the tip of the accelerating tube in the injection direction and has a reduced diameter portion whose inner diameter is smaller than the outer diameter of the sabo to form a deceleration section for decelerating only the sabo With muzzle ,
The flying object injection apparatus according to claim 1, wherein an inner diameter of the deceleration section is 95 to 99% of an outer diameter of the sabot . The flying object injection apparatus according to claim 1, wherein an injection direction length of the deceleration section is the same as an injection direction length of the sabot. The flying object injection according to claim 1 or 2, wherein a boundary portion between the inner peripheral surface of the deceleration section and the inner peripheral surface at the rear end in the injection direction is formed as a tapered portion so that the diameter thereof changes gradually. apparatus.

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