JP2011064670A - Injection testing apparatus - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an injection testing apparatus can injecting a missile having a non-axisymmetric shape with its attitude maintained. <P>SOLUTION: The injection testing apparatus 1 includes: an acceleration tube 4 for housing a cylindrical sabot 3, which holds the missile 2, at its rear end in the direction of injection and accelerating the sabot 3 through the use of acceleration energy; a vacuum chamber 6 for housing the tip of the acceleration tube 4 in the direction of injection and housing the target 5 on which an accelerated missile 2 is made to impact in the acceleration tube 4; and a sabot stopper 7 provided for the inside of the vacuum chamber 6 for receiving an accelerated sabot 3, separating the missile 2 from the sabot 3, and making the missile 2 impact on the target 5. The injection testing apparatus 1 includes a rail 17 for rotation prevention provided along the inner circumferential surface of the acceleration tube 4 in the longitudinal direction; a groove 18 for rotation prevention formed in the outer circumferential surface of the sabot 3 to be engaged with the rail 17 for rotation prevention; and rotation prevention means 16 for preventing the rotation of the sabot 3 in the acceleration tube 4. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to an injection test apparatus for testing a high-speed collision phenomenon by causing a flying object to collide with a target at a high speed in order to study a high-speed collision phenomenon such as a bird strike to a jet engine.

  Since a jet engine or the like may be damaged by a bird strike or the like, it is necessary to test its impact resistance performance to confirm safety. For example, a sufficient impact resistance evaluation is required for a fan case of a jet engine. In the design of the fan case, according to FAA (Federal Aviation Administration: Federal Aviation Administration) regulations, to maintain the performance to suppress damage in the fan case even if the fan blades that have been subjected to foreign object collisions should break and scatter In the final stage of the development of a new engine, a test is carried out to intentionally break the root of a real fan blade in operation with explosives. Before the evaluation with the actual machine, the strength of the fan case material is evaluated by a small impact test. In this case, a flat flying object close to the shape of the fan blade is often used as the flying object driven into the fan case material. .

  The injection test apparatus used for this test is an apparatus that accelerates the flying object using the explosive energy of compressed gas or explosives and collides with the target at high speed.

  The injection test apparatus generally includes an acceleration energy supply system that supplies acceleration energy, an acceleration tube (straight tube portion) for accelerating the flying object, and a collision part between the flying object and the target. Since the shape and dimensions of the flying object differ depending on the target test, there is a method in which the flying object is put in a container called Sabo, accelerated, separated immediately before the collision with the target, and only the flying object collides with the target. It is general purpose.

  In consideration of the workability of the sabot, it is economical to use a cylindrical cross section (solid cylindrical shape) and use an acceleration tube with a circular cross section.

  However, as shown in FIGS. 8A and 8B, when a non-axisymmetric flying object 50 such as a flat plate is used, the acceleration tube 51 having a circular cross section accelerates as shown in FIG. 8C. The sabot 52 may rotate in the tube 51, and it is difficult to cause the flying object 50 to collide with the target in the intended posture. In particular, when an inexpensive metal tube is used as the accelerating tube 51, there is a risk that the rotation of the sabot 52 may be facilitated by a line scar formed on the inner peripheral surface of the accelerating tube 51 as the metal tube is manufactured.

  If the material of the fan case has anisotropy, the roll strength (tilt around the trajectory axis) of the collided flat projectile causes a difference in material strength, so an arbitrary roll angle is maintained. There is a need for an injection technique that can be injected in the finished state.

  However, as shown in FIG. 9, even when the flying object 50 is ejected at a predetermined roll angle (roll angle 0 ° in FIGS. 9B and 9C), the sabot 52 rotates in the same manner, It may not be possible to collide with the target at the roll angle.

  Therefore, as the simplest method for causing the non-axisymmetric flying object 50 to collide with the target without rotating, there is a method of injecting the flying object 50 using an acceleration tube having a cross section corresponding to the cross-sectional shape of the flying object 50. Used.

JP 2008-89265 A JP 2004-271216 A JP 2004-77323 A Japanese Patent Laid-Open No. 3-233300 JP-A-6-323951 Japanese Patent Laid-Open No. 6-11297

  However, in order to inject the non-axisymmetric flying object 50 having different cross-sectional dimensions without rotating, an accelerating tube suitable for these dimensions is required, and there is a problem that there is no versatility.

  Further, even if the flying object 50 is directly injected using an acceleration tube having a cross section that matches the cross-sectional shape of the flying object 50, the flying object in an asymmetric posture (for example, a non-axisymmetric flying object 50 is trajected). An object that is arbitrarily tilted with respect to a plane perpendicular to the axis) cannot be ejected while maintaining its posture, and the acceleration efficiency is poor compared to the case of using a sabot.

  As shown in FIG. 10, a sabo 60 that can hold the flying object 50 in a state tilted at a predetermined angle is used for the injection of the flying object in such an asymmetric posture, and a sabo stopper 61 is provided around the front part thereof. The flying body 50 and the sabot 60 were separated from each other by colliding with a plate having a through-hole 62 (a size through which the flying body 50 can pass) so that the flying body 50 collides with the target 63.

  However, when the sabot 60 and the flying object 50 are separated, the periphery of the front part of the sabot 60 is caused to collide with the sabot stopper 61. Therefore, when the flying object 50 leaves the sabot 60, it is affected by deformation of the sabot 60 at the time of collision. There is a problem of losing posture.

  Accordingly, an object of the present invention is to provide an injection test apparatus capable of injecting a non-axisymmetric flying object while maintaining its posture.

  The present invention has been devised to achieve the above object, and the invention of claim 1 is characterized in that a cylindrical sabot holding a flying object is accommodated at the rear end in the injection direction, and the sabot is stored in a compressed gas or explosive. An accelerating tube for accelerating using explosive energy, a vacuum chamber containing a target for colliding the flying object accelerated in the accelerating tube, while accommodating a tip in the injection direction of the accelerating tube, and the vacuum An injection test apparatus comprising a sabo stopper provided in a chamber for receiving the accelerated sabo and separating the projectile from the sabo and causing the projectile to collide with the target. An anti-rotation rail provided along the longitudinal direction of the inner peripheral surface, and an anti-rotation groove formed on the outer peripheral surface of the sabot and engaged with the anti-rotation rail. An injection test apparatus comprising a rotation preventing means for preventing rotation in serial acceleration tube.

  According to a second aspect of the present invention, the sabot stopper has a through-hole that is smaller than the sabot and allows the flying object to pass therethrough, and the sabot fits into the inner peripheral surface of the acceleration tube and rotates on the outer peripheral surface. A cylindrical sabo body having the rotation prevention groove that engages with the prevention rail, and a cylindrical flying body having a diameter that is integrally formed at the tip of the sabo body in the injection direction and that passes through the through hole of the sabo stopper The injection test apparatus according to claim 1, comprising a holding unit.

  A third aspect of the invention is the injection test apparatus according to the second aspect, wherein the flying body holding part is provided with a detachable buffer, and the flying body is held by the buffer.

  According to a fourth aspect of the present invention, the flying body holding portion has a hollow portion having a non-circular cross-sectional shape in which the buffer body is detachably provided, and the buffer body is engaged with the hollow portion having a non-circular cross-sectional shape. The injection test apparatus according to claim 3, which is formed as described above.

  According to a fifth aspect of the present invention, the flying object holding portion is formed so as to hold the flying object at a predetermined roll angle, and is separated from the sabot at the tip end side in the injection direction of the through hole of the sabot stopper. The injection test apparatus according to claim 3, wherein a guide rail is provided for causing the flying object to collide with the target while maintaining the predetermined roll angle.

  According to the present invention, a non-axisymmetric flying object can be ejected while maintaining its posture.

It is the schematic of the injection test apparatus which shows one embodiment of this invention, (a) is a schematic side view, (b) is the schematic in a vacuum chamber. It is a figure which shows the mode of the sabot in an acceleration tube, (a) is sectional drawing, (b) is an A direction arrow directional view of (a). It is a figure which shows an example of the sabot used for this invention, (a) is a side view, (b) is a front view. It is a figure which shows the mode at the time of injecting a flying body with the injection test apparatus of FIG. It is a figure which shows the modification of a rotation prevention means. It is a figure which shows the other example of the sabot used for this invention, (a) is a side view, (b) is a front view. It is a figure which shows a mode at the time of injecting a flying body with the injection | emission test apparatus using the sabot of FIG. It is a figure which shows the mode of the sabot in the acceleration tube in the conventional injection test apparatus, (a) is sectional drawing, (b) is a B direction arrow view of (a), (c) is a sabot in (a). It is a B direction arrow view when it rotates. It is a figure which shows the mode of the sabot in the acceleration tube in the conventional injection | pouring test apparatus, (a) is sectional drawing, (b) is a C direction arrow directional view of (a), (c) is a sabot in (a). It is a C direction arrow line view when rotating. It is a figure which shows the mode at the time of injecting a flying body with the conventional injection test apparatus.

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

  First, an injection test apparatus of the present invention suitable for injecting a flying object in a non-axisymmetric posture will be described.

  FIG. 1 is a schematic view showing an injection test apparatus according to the present embodiment of the present invention, (a) is a schematic side view, and (b) is a schematic view inside a vacuum chamber.

  As shown in FIG. 1, the injection test apparatus 1 accommodates a solid cylindrical sabot 3 holding a flying object 2 at the rear end (left side in the figure) in the ejection direction, and explodes the sabot 3 with compressed gas or explosives. The acceleration tube 4 for accelerating using energy (acceleration energy), and the target 5 that collides the flying object 2 accelerated in the acceleration tube 4 while accommodating the front end (right side in the drawing) of the acceleration tube 4 in the emission direction. , And a sabo stopper 7 for receiving the accelerated sabo 3 to separate the flying object 2 from the sabo 3 and causing only the flying object 2 to collide with the target 5. With. In this embodiment, a case where compressed 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 high-speed 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, equipment for capturing a high-speed collision phenomenon such as a laser or a high-speed camera is 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 passes only the flying object 2 is formed in the sabot stopper 7 that receives the accelerated sabot 3 and separates the flying object 2 from the 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. Needless to say, 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 injection test apparatus 1 according to the present embodiment uses a non-axisymmetric flying object 2 that is held by the sabot 3 in an asymmetric posture, and can collide with the target 5 while holding the posture. Is.

  Therefore, as shown in FIG. 2, the injection test apparatus 1 includes the rotation prevention means 16 that prevents the rotation of the sabot 3 within the acceleration tube 4 in the acceleration tube 4 and the sabot 3.

  The anti-rotation means 16 includes an anti-rotation rail 17 provided along the longitudinal direction of the inner peripheral surface of the acceleration tube 4 and an anti-rotation groove formed on the outer peripheral surface of the sabot 3 and engaged with the anti-rotation rail 17. 18 and.

  As the anti-rotation rail 17, a rail having a necessary strength with a sufficiently small cross-sectional area (for example, a cross-sectional area of about 1 to 5%) compared to the cross-sectional area of the inner peripheral surface of the acceleration tube 4 is attached. For example, a hole is formed in the outer periphery of the acceleration tube 4 along the longitudinal direction, the anti-rotation rail 17 is accommodated in the acceleration tube 4, and the anti-rotation rail 17 is then inserted through the hole of the acceleration tube 4. By screwing, the anti-rotation rail 17 can be attached in a straight line. This anti-rotation rail 17 may be provided over the entire length of the acceleration tube 4 or may be provided over a part thereof.

  The rotation-preventing groove 18 is formed by cutting the outer periphery of the sabot 3. Therefore, processing is easy.

  By these rotation preventing means 16, the rotation of the sabot-3 is restricted in the acceleration tube 4, and the flying object 2 can be ejected without rotation.

  The sabo 3 used in the injection test apparatus 1 includes a columnar (solid cylindrical) sabo body 19 that is formed with an anti-rotation groove 18 on the outer peripheral surface and is fitted to the inner peripheral surface of the acceleration tube 4. The sabo body 19 is formed integrally with the tip in the injection direction, and includes a solid cylindrical flying body holding portion 20 having a diameter passing through the through hole 15 of the sabo stopper 7.

  More specifically, as shown in FIG. 3, a mounting portion 21 for mounting the flying object 2 is formed on the leading end side in the emission direction of the flying object holding unit 20. The flying object 2 is placed and held on the surface.

  Therefore, the mounting portion 21 of the sabo 3 is formed into various shapes according to the shape of the flying object 2 that collides with the target 5. In FIG. 3, since the flying object 2 is an inclined flat plate, the mounting portion 21 has an inclined surface 22 and a positioning groove 23 so that the flat plate can be held in an inclined posture. An anti-slip portion 24 that supports the flying body 2 so that it does not slide down is formed at the lower portion of 23. A clearance of about 0.2 mm is provided between the groove width of the positioning groove 23 and the flying object 2. Depending on the angle at which the flying object 2 is placed, the flying object 2 may fall due to its own weight. Therefore, in order to place the flying object 2 on the placing part 21 in the posture shown in FIG. You may make it assist mounting using an adhesive tape.

  The length of the flying object holding portion 20 (projection length from the sabot body 19) is longer than the depth of the bottom portion that houses the flying object 2 (for example, about 10 to 20 mm).

  An injection test using this injection test 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. The rotation prevention groove 18 is accommodated and installed so as to engage with the rotation prevention rail 17 of the acceleration tube 4.

  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, the valve 11 is opened at once, and is stored in the rear end of the acceleration tube 4 in the injection direction with the filled compressed gas. Accelerate Sabo 3 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. 4, the sabo 3 accelerated in the accelerating tube 4 is sabo-stopped so that the sabo body 19 collides with the outer peripheral surface of the through-hole 15 and the flying object holder 20 passes through the through-hole 15. 7 and the flying object 2 is separated from the sabot 3. At this time, immediately after the sabo 3 collides with the sabo stopper 7, the sabo body 19 that collides with the sabo stopper 7 is deformed, but the flying object holder 20 is hardly deformed because it passes through the through hole 15 of the sabo stopper 7. . The flying object 2 is separated from the flying object holding part 20 immediately after the sabot body 19 collides with the sabot stopper 7. Thereafter, the deformation of the sabo body 19 is transmitted to the flying object holder 20. Therefore, the flying object 2 is separated from the sabot 3 before the deformation of the sabot body 19 is transmitted to itself.

  The flying object 2 separated from the sabo 3 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. The sabot 3 holding the flying object 2 is accommodated so that the rotation preventing groove 18 engages with the rotation preventing rail 17 of the accelerating tube 4, and then the test is performed.

  Thus, according to the injection test apparatus 1 according to the present embodiment, since the acceleration tube 4 and the sabot 3 are provided with the rotation preventing means 16 for preventing the rotation of the sabot 3 within the acceleration tube 4, the acceleration tube 4 The sabo-3 is prevented from rotating around the central axis of the accelerating tube 4, and even the non-axisymmetric flying object 2 such as a flat plate can collide with the target 5 in the intended posture.

  Further, the rotation preventing means 16 is a rotation preventing rail 17 provided along the longitudinal direction of the inner peripheral surface of the accelerating tube 4 and a rotation preventing rail formed on the outer peripheral surface of the sabot 3 and engaged with the rotation preventing rail 17. Since the groove 18 is used, the rotation of the sabo 3 in the acceleration tube 4 can be prevented with a simple structure.

  Further, since the rotation of the sabo 3 in the accelerating tube 4 can be prevented, an inexpensive metal tube in which linear streaks are formed can be used as the accelerating tube 4, and each flying object 2 having various shapes can be used. In addition, since it is not necessary to prepare the acceleration tube 4, the cost required for the injection test apparatus 1 can be reduced.

  In addition to this, in the injection test apparatus 1, the sabo 3 is formed integrally with the cylindrical sabo body 19 fitted to the inner peripheral surface of the accelerating tube 4 and the sabo stopper 7 formed integrally with the tip of the sabo body 19 in the injection direction. Since it has a solid cylindrical projectile holding part 20 having a diameter passing through the hole 15, the deformation of the sabot 3 when it collides with the sabot stopper 7 is transmitted to the projectile 2 before the sabot 3 and the projectile. 2 can be separated, and the flying object 2 in an asymmetric posture inclined at an arbitrary angle can be ejected while maintaining the posture.

  In the present embodiment, the case where the anti-rotation means 17 is provided with the anti-rotation rail 17 and the anti-rotation groove 18 at one place has been described. However, the present invention is not limited to this. For example, as shown in FIG. Further, the anti-rotation rail 17 and the anti-rotation groove 18 may be provided at three positions at intervals of 120 °.

  Next, an injection test apparatus according to the present invention suitable for injecting a flying object while maintaining the roll angle will be described.

  When the flying object is held at a predetermined roll angle by using a conventional injection test apparatus and the flying object is injected while maintaining the roll angle, the following problems occur. (1) When a test is performed with a plurality of types of roll angles, a sabo 3 having a shape corresponding to the roll angles is required, resulting in high costs. (2) Since the flying object is directly restrained by a hard sabot, there is only a slight tilt or deviation in the attitude or trajectory of the sabot when it collides with the sabot stopper. I often lose my posture.

  The injection test apparatus according to another embodiment of the present invention that solves these problems is mainly different from the above-described injection test apparatus 1 in the configuration of the sabot and the configuration around the sabot stopper.

  As shown in FIGS. 6A and 6B, in the sabot 30 used in the injection test apparatus according to another embodiment, a buffer 33 is detachably provided in the hollow part 32 of the flying object holding part 31. The flying object 2 is held by the buffer 33. That is, in the sabot 30, the part holding the flying object 2 is formed of a separate member.

  The hollow part 32 of the flying object holding part 31 is formed in a non-circular cross-sectional shape, and the buffer 33 is similar to the hollow part 32 so that the non-circular cross-sectional shape hollow part 32 is engaged with almost no gap. The non-circular cross-sectional shape is formed. Thereby, rotation of the buffer 33 in the hollow part 32 is prevented.

  The buffer 33 is made of, for example, a foamed resin body such as expanded polystyrene or expanded polystyrene. Moreover, as the buffer 33, what has moderate hardness is preferable so that the flying body 2 can be firmly hold | maintained with exact roll angle (theta).

  In order to hold the flying object 2 on the buffer 33, a groove corresponding to an arbitrary roll angle θ is processed in the buffer 33, and the flying object 2 is fitted into the groove. Since the cushioning body 33 is formed by processing a foamed resin body by heat rays or grinding, a cushioning body corresponding to an arbitrary roll angle θ can be easily and inexpensively manufactured.

  Moreover, in the injection test apparatus according to another embodiment, as shown in FIG. 7A, the flying object 2 separated from the sabot 30 is disposed at a predetermined position on the front end side in the injection direction of the through hole 15 of the sabot stopper 7. A guide rail 34 for colliding with the target 5 while maintaining the roll angle θ is provided.

  As shown in FIG. 7B, the guide rail 34 is configured by assembling a plurality (six in the figure) of round bars 35 so as to surround the flying object 2, and restrains the trajectory of the flying object 2. is there. Thus, by constituting the guide rail 34 with the round bar 35, the contact area between the guide rail 34 and the flying object 2 can be reduced, and the acceleration efficiency is reduced due to the contact between the guide rail 34 and the flying object 2. Can be prevented.

  In addition, the guide rail 34 is not limited to what is comprised with the multiple round bar 35, For example, you may make it restrain the trajectory of the flying body 2 with a multiple square bar. In this case, if the flying object 2 is restrained by the corner portion of the square bar, the contact area between the guide rail 34 and the flying object 2 can be reduced. That is, the guide rail 34 may be anything as long as it does not reduce the acceleration efficiency of the flying object 2.

  Moreover, since the one where the distance from the front-end | tip of the injection direction of the guide rail 34 to the target 5 is short can restrain the flying body 2 just before a collision, the one where this distance is as small as possible is preferable. However, if the tip of the guide rail 34 in the injection direction is too close to the target 5, the flying object 2 may bounce back to the guide rail 34 after the collision, and the guide rail 34 may be damaged, or it may be difficult to capture the situation at the time of the collision. Therefore, the arrangement of the guide rails 34 needs to be adjusted as appropriate according to the test environment.

  Between the sabot stopper 7 and the guide rail 34, there is a guide hole 36 that guides the flying object 2 separated from the sabot 30 to the guide rail 34, and receives the buffer 33 and separates the flying object 2 from the buffer 33. A buffer stopper 37 is provided.

  The guide hole 36 is formed so as to be gradually reduced in diameter toward the front end side in the injection direction, and guides the flying object 2 to the guide rail 34 even when the attitude of the flying object 2 is slightly inclined when separated. Configured. Further, in order to receive the buffer body 33 and separate the flying body 2 from the buffer body 33, the diameter of the guide hole 36 on the rear end side in the injection direction is smaller than the outer diameter of the buffer body 33 of the sabot 30 and the flying body 2. It is formed larger than.

  In the injection test using the injection test apparatus according to another embodiment, as shown in FIG. 7A, when the sabo 30 accelerated by the accelerating tube 2 collides with the sabo stopper 7, The buffer 33 is separated from the hollow portion 32 together with the flying object 2. Thus, when the sabo 30 collides with the sabo stopper 7, the flying object 2 is ejected integrally with the buffer 33, so that the flying object 2 is slightly misaligned or misaligned when the sabo 30 collides. Difficult to be affected by

  Thereafter, the flying object 2 is separated from the buffer 33 by the buffer stopper 37. At this time, even if the shock absorber 33 is sheared by the shock absorber stopper 37 and flies to some extent with the flying object 2, the density is extremely small, so that the injection of the flying object 2 is hardly affected.

  The separated flying object 2 is guided to the guide rail 34 through the guide hole 36 of the buffer stopper 37 and flies while being constrained by the guide rail 34. Due to this restraint, the roll angle θ of the flying object 2 is maintained even after the guide rail 34 has escaped, and it collides with the target 5 in this state.

  When testing with a plurality of types of roll angles θ, the flying object 2 is held by the buffer 33 with an arbitrary roll angle θ, and the guide rail 34 is rotated so as to match the roll angle θ, and the flying object 2 The body 2 is injected and tested.

  As described above, in the injection test apparatus according to another embodiment, since the flying object 2 is held by the buffer 33, the action due to the collision posture or the axis deviation when the sabot 30 collides with the sabot stopper 7 is achieved. The flying object 2 is not easily received, and is restrained by the guide rail 34 until immediately before the flying object 2 collides with the target 5, so that the flying object 2 can be ejected while maintaining a predetermined roll angle θ. That is, according to the injection test apparatus according to another embodiment, the flying object 2 can collide with the target 5 in the intended posture, and an accurate injection test can be performed.

  Moreover, since the part holding the flying body 2 of the sabo 30 is formed as a separate member, the shape of parts other than the buffer 33 that can be easily and inexpensively manufactured can be made common, and the processing cost of the sabo 30 can be reduced. it can.

DESCRIPTION OF SYMBOLS 1 Injection test apparatus 2 Flying object 3 Sabo 4 Acceleration tube 5 Target 6 Vacuum chamber 7 Sabo stopper 16 Anti-rotation means 17 Anti-rotation rail 18 Anti-rotation groove

Claims (5)

A cylindrical sabo holding a flying object is accommodated at the rear end of the injection direction, an acceleration tube for accelerating the sabo using the explosive energy of compressed gas or explosive, and the injection direction front end of the acceleration tube are accommodated And a vacuum chamber in which a target that collides the flying object accelerated in the accelerating tube is accommodated, and the flying object is provided in the vacuum chamber, receives the accelerated sabot and separates the projectile from the sabot. In an injection test apparatus comprising a sabot stopper for causing the flying object to collide with the target,
An anti-rotation rail provided along the longitudinal direction of the inner peripheral surface of the acceleration tube, and an anti-rotation groove formed on the outer peripheral surface of the sabot and engaged with the anti-rotation rail. An injection test apparatus comprising a rotation preventing means for preventing rotation in the acceleration tube. The sabot stopper has a through hole that allows the flying object to pass through smaller than the sabot,
The sabot is fitted to the inner peripheral surface of the accelerating tube and has a columnar sabot body having the rotation preventing groove on the outer peripheral surface to be engaged with the rotation preventing rail, and an injection direction front end of the sabot body. The injection test apparatus according to claim 1, comprising: a cylindrical flying object holding portion formed integrally and passing through the through hole of the sabot stopper.   The injection test apparatus according to claim 2, wherein the flying body holding unit is detachably provided with a buffer, and the flying body is held by the buffer. The flying body holding part has a hollow part having a non-circular cross-sectional shape in which the buffer body is detachably provided,
The injection test apparatus according to claim 3, wherein the buffer body is formed so as to engage with the hollow portion having a noncircular cross-sectional shape. The flying object holding part is formed to hold the flying object at a predetermined roll angle,
The guide rail for making the said flying body separated from the said sabot collide with the said target is provided in the injection direction front end side of the said through hole of the said sabot stopper, maintaining the said predetermined roll angle | corner. Or the injection test apparatus of 4.

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