JP6165594B2 - Interceptor - Google Patents

Description

  The present invention relates to an interceptor for actively intercepting a vehicle or a facility, for example, in a conflict area or the like, effectively and while suppressing damage to the surroundings when the vehicle or facility is attacked by a rocket.

Conventionally, as a defense against threats such as portable rockets that fly toward vehicles or facilities, there is an active defense system that detects and responds to incoming threats, and among them, a hard kill type interceptor It is widely known that an explosive is loaded and a blast or a large number of metal fragments are dispersed to effectively damage the flying threat.
However, in an interceptor that sprays high energy metal debris, the debris for interception and debris generated from components such as the case, and the blast due to the explosion of explosives must be generated. However, operation may be restricted depending on the situation.

Therefore, as a method that can form a large defense range within a relatively short time without spraying high-energy debris by itself, a device that neutralizes the threat by deploying a net or airbag and colliding with the threat Researched and developed.
As a technique related to such an intercepting device, for example, a system for protecting a person who deploys and protects an air bag against a flying threat is known (see, for example, Patent Document 1).
Patent Document 1 discloses a method of detecting an incoming threat and deploying an air bag made of tough fibers such as Kevlar to protect personnel and facilities from threats.

In addition, a method for protecting a flying rocket by releasing a net is known (for example, see Patent Document 2).
Patent Document 2 discloses a method for releasing a net made of tough fibers such as Dyneema and associating it with a threat to destroy the threat firing mechanism or change the threat trajectory to protect it.
In addition, an apparatus for protecting a flying rocket by releasing a parachute is known (for example, see Patent Document 3).
Patent Document 3 discloses a method of protecting a parachute made of a fiber such as Kevlar or nylon.

US Pat. No. 6,029,558 US Pat. No. 8,141,470 US Pat. No. 6,957,602

However, in the personnel protection system of Patent Document 1, since the interceptor is deployed in the vicinity of the personnel to be protected or on the wall of the facility, the meeting position of the threat and the interceptor is close, and the jet is generated by the collision of the portable anti-tank rocket. And threats that generate debris.
Moreover, in the protection method of patent document 2, since the parachute and the net are immediately deployed by the force of an air bag or the like, the resistance at the time of flight is large, and the interceptor cannot fly far away.
Therefore, the interceptor cannot fly far away.

Moreover, in the protective device of patent document 3, since expansion | deployment is started when a parachute is pulled, resistance at the time of flight is large.
Therefore, the interceptor cannot fly far away.
Moreover, in the protective device of patent document 3, since the launched weight pulls the interceptor through the string-like structure, the mutual center of gravity and the center axis of the interceptor and the weight are not stable and deployed. It is also possible that the posture and the trajectory of the ball fluctuate greatly due to the impact of time, and as a result, the flight is not stable and the accuracy of hitting in the distance is reduced.

  The present invention has been made in order to solve such a conventional problem, and its purpose is to set the meeting distance with a threat such as a portable rocket to come away, so that a portable battle is possible. An object of the present invention is to provide an interceptor that can reliably cope with jets and debris generated by collisions such as car rockets.

The invention according to claim 1 is a flying aircraft body, an inflatable body provided in the flying aircraft body, which expands and expands with gas, and an inflator which is provided in the flying aircraft body and generates a gas for expanding and expanding the expanding body. An outer cylinder for storing the expansion body and the inflator provided in the flying machine body, a postponing device provided in the flying machine body for setting an operating time of the inflator, and provided in the flying machine body. and a firing mechanism for generating propulsion energy of flying the aircraft, the flight aircraft, support, comprises a front body and a bottom body, said supporting body, each connecting the front body and the bottom body The front body has a seat portion for attaching a head portion constituting an aerodynamically stable tip shape, and an inflator housing portion for housing the inflator, and the bottom portion. Includes actuating a postponement device accommodating portion for accommodating the postponement device, anda firing mechanism mounting portion for mounting said firing mechanism, the postponement device, the inflator to the operation time during flight of the flying body The expansion body expands and expands with the gas generated by the inflator and expands and expands, and the expansion body that expands and expands separates the outer cylinder from the flying aircraft body in flight and expands and expands from the flying aircraft body. It is characterized by damaging the rockets by colliding with rockets flying to the body.

The invention according to claim 2, in interceptor according to claim 1, wherein the expansion body, when flying at high speed until meeting position before that also generate debris and jet from threats the safety, the inflator It expands and expands with the gas which produces | generates .
The invention according to claim 3 is characterized in that, in the interceptor according to claim 1 or 2 , a traction member is provided between the expansion body and the flying aircraft body .

The invention according to claim 4, in interceptor according to any one of claims 1 to 3, wherein the expansion body is superposed two fabric pieces of the same shape having a hole in the center portion, respectively the outer peripheral edge portion is constituted by a bag member formed by combining a, after inserting the flying body in the hole two fabrics the expansion body has has the flying aircraft the hole at predetermined intervals in that respectively fixed via the concluding portion, wherein the center of the two fabric pieces are fastened to said support.

The invention according to claim 5, in interceptor according to any one of claims 1 to 3, wherein the expansion body is superposed two fabric pieces of the same shape having a hole in the center portion, respectively In order to control the shape at the time of expansion, the outer peripheral edge portion of the fabric is formed by a bag body that is fastened by a shape-holding member, and the two holes included in the expansion body have the holes in the holes . after inserting the flying body, said hole to be to each fixed via the concluded portion to the support at a predetermined distance, that the center of the two fabric pieces are fastened to said support Features.

According to a sixth aspect of the present invention, in the interceptor according to the fourth or fifth aspect , a ratio between a deployment diameter of the expansion body and a distance between fastening portions respectively provided in holes of the expansion body is (4 : 1) to (1: 1).
The invention according to claim 7 is the interceptor according to claim 5 , wherein the shape holding member is made of an aramid fiber or a polyamide fiber, and an interval between the fabrics is a fastening portion provided in each hole of the expansion body. It is the same as the interval.

Invention is the interceptor as claimed in any one of claims 7, wherein the outer cylinder has a cylindrical shape, both ends of a position equally divided into two cylinder vertically according to claim 8 And a main groove formed between the notches, and a sub-groove formed on a circumference between the notches and having a depth smaller than that of the main groove.

The invention according to claim 9 is the interceptor according to claim 8 , wherein the length of the notch on the head side is 5 to 20% of the total length of the outer cylinder, and the length on the tail side of the notch. Is 30 to 50% of the total length of the outer cylinder, the depth of the main groove is 30 to 60% of the wall thickness of the outer cylinder, and the depth of the sub-groove is the thickness of the outer cylinder. It is characterized by being 20 to 50% of the thickness.
According to a tenth aspect of the present invention, in the interceptor according to the eighth or ninth aspect, the cutout is filled by insertion of a cover body having a shape corresponding to the cutout.

According to the present invention, it is a shape with a small velocity attenuation that is casing by a flying aircraft body and an outer cylinder, and it flies at high speed up to a safe meeting position even if a threat debris such as a portable rocket or a jet is generated, When launching or when a preset time is reached, the postponing device energizes the inflator and deploys the inflatable body to complete the deployment of the effective protective range immediately before the meeting position, so the interceptor will fly far away It is possible to make it.
Further, according to the present invention, since the interceptor is stably deployed, the defense range and the hit accuracy can be maintained.
Further, according to the present invention, the interceptor after deployment flies stably, so that the defense range and the accuracy of hitting can be maintained.

It is sectional drawing of the interceptor which concerns on 1st embodiment of this invention. It is a side view of the interceptor which concerns on 1st embodiment of this invention. It is a side view which shows the flying body of FIG. It is an expanded sectional view which shows the tail part fastening part of the flying body of FIG. It is an expanded sectional view which shows the front part body (except a head) of the flying body of FIG. It is a decomposition | disassembly expanded sectional view which shows the state before connecting the upper surface fabric of an expansion body to a front part body. It is an expanded sectional view which shows the inflator of FIG. 8A is an exploded view of the inflator shown in FIG. 7, and FIG. 8B is an exploded sectional view of the inflator shown in FIG. It is sectional drawing of the ignition part of the inflator of FIG. It is a disassembled sectional view which shows the bottom part of the flying body of FIG. It is a bottom view of the bottom part of the flying body of FIG. FIG. 11 is an exploded cross-sectional view showing the firing mechanism assembly of the bottom body of FIG. 10. It is sectional drawing of the propellant chamber of the bottom body of FIG. 14A is an exploded view of the propellant chamber of FIG. 13, and FIG. 14B is an exploded sectional view of the propellant chamber of FIG. It is a perspective view of the case of the propellant chamber of FIG. It is sectional drawing of the ignition part of the propellant chamber of FIG. It is a perspective view which shows the expansion body of FIG. It is sectional drawing which shows the expansion body of FIG. It is an exploded view which shows the expansion body of FIG. It is sectional drawing which shows the state which the expansion body of FIG. 1 expand | deployed. It is explanatory drawing which shows the assembly | attachment of a traction member and a traction member coupling tool. It is a perspective view which shows a traction member coupling tool. It is a perspective view which shows the outer cylinder of FIG. It is a perspective view which shows the state which attaches a cover body to a notch in the outer cylinder of FIG. It is sectional drawing which decomposes | disassembles and shows the flying body of FIG. 1, an outer cylinder, a head body, a traction member coupling tool, an expansion body, a shaft body, and a base part. FIG. 26 is a cross-sectional view illustrating a state in which the expansion body is assembled to the head body in FIG. It is sectional drawing which shows the state which attaches a tail part fastening part to the shaft body in FIG. It is sectional drawing which shows the state which assembles a traction member coupling tool to the head body in FIG. It is a perspective view which shows the state which assembles a traction member coupling tool to the head body in FIG. It is a conceptual diagram which shows the state which loaded the interceptor which concerns on 1st embodiment of this invention in the launching device. It is a figure which shows the structure of the postponement apparatus of the interceptor which concerns on 1st embodiment of this invention. It is explanatory drawing which shows the state which isolate | separates an outer cylinder by the expansion | deployment expansion | deployment of the expansion body of the interceptor which concerns on 1st embodiment of this invention. It is a side view which shows the state which an outer cylinder isolate | separates from the interceptor in FIG. 32 by the expansion | deployment expansion | deployment of an expansion body. (A) Gas pressure acts from the notch on the front body side of the outer cylinder toward the main groove, (B) Cracking starts from the front side of the main groove, and (C) shows a state of separation by cracking of the main groove. It is explanatory drawing. It is explanatory drawing which shows a mode that the interceptor which concerns on 1st embodiment of this invention flies, and intercepts a portable anti-tank rocket. FIG. 6 is an explanatory view showing a comparative example 1; It is explanatory drawing which shows the comparative example 2. FIG. It is explanatory drawing which shows the comparative example 3. FIG. It is a side view which fractures | ruptures and shows the one side of the expansion body of the interceptor which concerns on 2nd embodiment of this invention. It is a side view which fractures | ruptures and shows the one side of the expansion body of the interceptor which concerns on 3rd embodiment of this invention. It is explanatory drawing which launches the interceptor which concerns on 1st embodiment of this invention from a launching device, and image | photographs the behavior with a high-speed camera. It is a figure which shows the protection range of the interceptor acquired from the image | video of the high-speed video camera by FIG. FIG. 43 is a schematic diagram of an oscilloscope waveform obtained during measurement according to FIG. 42. (A) The figure which suspended the interceptor which concerns on 1st embodiment of this invention on the mount frame, (B) The situation where the expansion body of the interceptor which concerns on 1st embodiment of this invention expand | swells and expands is image | photographed with a high-speed camera. (C) It is a figure which shows the condition which the expansion body of the interceptor which concerns on 1st embodiment of this invention expand | deployed.

Hereinafter, the present invention will be described based on embodiments shown in the drawings.
Next, the interceptor 1 which concerns on 1st embodiment of this invention is demonstrated based on FIGS. 1-35.
As shown in FIG. 1, the interceptor 1 according to the present embodiment includes a flying machine body 10, an expansion body 130 that expands and expands with gas, an inflator 30 that generates gas that expands and expands the expansion body 130, and An outer cylinder 150 that stores the inflating body 130 and the inflator 30, a postponing device 62 that sets the operating time of the inflator 30, and a launching mechanism 66 that causes the interceptor 1 to fly are provided.

As shown in FIGS. 1 and 3, the flying machine body 10 includes a support 10A, a front body 10B provided on the head side of the support 10A, and a bottom body 10C provided on the tail side of the support 10A. It consists of
As shown in FIGS. 1, 3, and 4, the support body 10 </ b> A includes a shaft body 11 made of, for example, an aluminum alloy, steel, engineering resin, or fiber reinforced plastic. As shown in FIGS. 1, 3, 6, and 10, the shaft 11 passes through the wiring 12 of the inflator 30, and is provided with a wiring hole 11 a that is also used for mass adjustment, and a hole in the lower surface fabric 132 of the expansion body 130. A male screw portion 11b that is screwed into a female screw portion 14g provided in the tail fastening portion 13b that fixes the periphery of 136, and a female screw provided on the tail portion side of the inflator storage portion 25 incorporated in the front body 10B. A male screw 11c screwed into the attachment hole 25b and a male screw 11d screwed into the female screw connection hole 55 provided on the head side of the bottom body 10C are provided.

As shown in FIG. 4, the tail fastening portion 13 b holds down the plug 14 attached to the shaft body 11 with the gasket 15 and the retaining ring 16 attached thereto, and the tail side of the expansion body 130 superimposed on the plug 14 from above. The slide ring 17 is fixed on the plug 14 with a plurality of bolts 18, and the press ring 19 presses the slide ring 17.
The plug 14 is, for example, a mushroom-shaped integrally formed product made of aluminum alloy or the like, and has a substantially triangular pyramid-shaped protruding portion 14a and a substantially triangular shape that is coaxially connected to the bottom surface side of the substantially triangular pyramid-shaped protruding portion 14a. A cylindrical portion 14b having a smaller diameter than the cone-shaped protruding portion 14a is provided, and a hole 14c through which the shaft body 11 is inserted is provided at the center of the substantially triangular-pyramidal protruding portion 14a and the small-diameter cylindrical portion 14b.
A wall surface corresponding to the bottom surface of the substantially triangular protrusion 14a includes an annular receiving portion 14d on which a gasket 15 is mounted at the base of the boundary portion with the small-diameter cylindrical portion 14b, and a retaining ring 16 on the outer periphery of the receiving portion 14d. And an annular stepped portion 14e for mounting. The small-diameter cylindrical portion 14b includes a male screw 14f on the outer surface on the tail side. The hole 14c is provided with a female screw 14g that is screwed to a male screw 11b provided at a substantially central position of the shaft body 11 over the axial length of the small diameter cylindrical portion 14b.

The gasket 15 is, for example, a ring-shaped molded product made of silicon rubber or the like, and is attached to the bottom of the receiving portion 14d.
The retaining ring 16 is a ring-shaped molded product made of, for example, an aluminum alloy, and is provided in a hole 16a substantially the same as the inner diameter of the annular step portion 14e and the outer periphery of the hole 16a, and the annular step portion 14e. And a ring portion 16b mounted on the top. The ring portion 16 b includes holes 16 c through which a plurality of bolts 18 screwed to the slide ring 17 are inserted. On the ring portion 16b, the hole 136 of the lower surface fabric 132 of the expansion body 130 passes through the shaft body 11, and a plurality of holes 136a provided on the outer periphery of the hole 136 are positioned coaxially with the hole 16c.

The slide ring 17 is a ring-shaped molded product made of, for example, an aluminum alloy, and is provided in a hole 17a through which the small-diameter cylindrical portion 14b of the plug 14 is inserted and an outer periphery of the hole 17a, and an annular receiving portion 14d. A ring portion 17b having an annular recess 17c that presses the gasket 15 attached to the step portion 14e and a retaining ring 16 attached to the step portion 14e; and a retaining portion 16 provided to the ring portion 17b and attached to the step portion 14e. Holes 17d through which a plurality of bolts 18 screwed into the screw holes 16a are respectively inserted are provided. The plurality of bolts 18 are respectively inserted into a plurality of holes 136 a provided on the outer periphery of the hole 136 of the lower surface fabric 132 of the inflatable body 130 sandwiched between the slide ring 17 and the retaining ring 16.
The holding ring 19 is a ring-shaped molded product made of, for example, an aluminum alloy, and is screwed into a hole 19a through which the shaft body 11 is inserted, and a male screw 14f provided in the small-diameter cylindrical portion 14b connected to the hole 19a. A female screw 19b to be attached and a pressing surface 19c that is provided on the outer periphery of the hole 19a and that presses the slide ring 17 fixed on the plug 14 with a bolt 18 are provided.

The front body 10B is made of, for example, polyacetal resin as shown in FIGS. 1 to 3 and 5 and is designed to match the inner diameter of the gun 201 of the launching device 200 as shown in FIG. An annular head mounting portion 20, a centering portion 21 made of, for example, polyacetal resin, a connection fitting 24 made of, for example, an aluminum alloy and assembled to the head mounting portion 20, and aluminum, for example An inflator housing portion 25 that is made of an alloy or the like and is assembled to the connection fitting 24 and an inflator 30 that is housed in the inflator housing portion 25 are provided.
As shown in FIGS. 1 to 3 and 5, the head mounting portion 20 includes a male screw 20 b on the outer side of the upper end portion 20 a for mounting the head 120. The head mounting portion 20 includes two stepped portions 20c and 20d connected to the lower side of the upper end portion 20a so as to protrude outwardly in order to attach the centering portion 21. The lower step portion 20 d includes a male screw 20 e that is screwed to the female screw 21 b of the fixed center portion 21.

The head mounting portion 20 includes a hole 20f penetrating from the center portion of the upper end portion 20a toward the center portion of the lower end portion of the stepped portion 20d. The hole 20f includes a first hole 20f1 having a depth corresponding to the height from the upper end portion 20a to the lower end of the step portion 20c, and a depth corresponding to a height from the lower end of the step portion 20c to the lower end of the step portion 20d. The second hole 20f2 is provided, and the diameter of the second hole 20f2 is set larger than the diameter of the first hole 20f1. The second hole 20f2 includes a female screw 20f21 for screwing a male screw 24a provided on the outer periphery of the connection fitting 24.
The head 120 is a molded product having a flat head shape made of, for example, aluminum alloy, iron, steel, resin, or the like. The outer diameter of the head 120 is substantially the same as the outer diameter of the centering part 21 assembled to the head mounting part 20. The head 120 includes a female screw portion 120b that is screwed to a male screw portion 20b provided on the outer periphery of the upper end portion 20a of the head mounting portion 20 on the inner peripheral surface 120a. The head 120 is not limited to a flat head, and may have a shape such as a hemisphere, a spheroid, a cone, a blunt cone, or a tangent ogive.

  The centering portion 21 is configured by a substantially cylindrical member having substantially the same height as the two step portions 20c and 20d of the head mounting portion 20, and is mounted on the step portion 20d of the head mounting portion 20 on the inner periphery. A substantially annular convex portion 21a, a female screw 21b to be screwed onto the male screw 20e of the step portion 20d of the head mounting portion 20, and a front portion during movement in the gun when shooting the interceptor 1 from the launching device 200 A substantially annular recessed portion 21c formed on the outer periphery for assembling the ring body 22 for relieving vibration of the body 10B and an annular recessed portion 21d for mounting the upper end portion of the outer cylinder 150 are provided. The ring body 22 is made of, for example, silicon rubber.

As shown in FIG. 6, the connection fitting 24 is made of, for example, an aluminum alloy, and is a substantially annular member for attaching the inflator storage portion 25 to the head attachment portion 20. The connection fitting 24 includes a male screw 24a for screwing into a female screw 20f21 provided in the second hole 20f2 of the head mounting portion 20 on the outer periphery of the upper end portion, and a pulling member 145 is attached to the lower side of the male screw 24a. A step portion 24b for attaching the traction member connector 148 is provided.
Further, the connection fitting 24 has a first annular portion 24d cut out from the upper end portion toward the lower end portion by a predetermined depth in the central through hole 24c, and a center line direction from the lower end portion of the first annular portion 24d. The first step portion 24e that protrudes, the second annular portion 24f that is cut out by a predetermined depth from the inner peripheral surface of the first step portion 24e toward the lower end portion, and the center from the lower end portion of the second annular portion 24f. A second stepped portion 24g protruding in the linear direction, a substantially annular third annular portion 24h cut out by a predetermined depth from the lower end of the second stepped portion 24g toward the outer portion of the connection fitting 24, A third step portion 24i that is recessed from the lower end portion of the tricyclic portion 24h toward the outer portion of the connection fitting 24, a female screw 24j provided in the third step portion 24i, and a lower end of the third step portion 24i. The fifth annular portion 24 is cut from the portion to a depth equivalent to the inner diameter of the first annular portion 24d. And an annular protrusion 24l provided so as to project between the outer portion of the fifth annular portion 24k and the outer portion of the connection fitting 24, and an axial center from the first step portion 24e toward the fifth annular portion 24k. And a plurality of holes 24m penetrating in parallel.

  Bolts 24o are inserted into the respective holes 24m, and the upper surface fabric 131 of the inflatable body 130 arranged on the fifth annular portion 24k side of the connection fitting 24 is sandwiched between the retaining rings 24p to stop the respective bolts 24o. It is fixed by screwing onto the ring 24p. At this time, as shown in FIG. 6, the connection portion 25 e of the inflator storage portion 25 is screwed to the third step portion 24 i of the connection fitting 24, and the hole 133 of the upper surface fabric 131 of the expansion body 130 is stored in the inflator. A plurality of holes 133a provided on the outer periphery of the hole 133 are positioned coaxially with the hole 24m and constitute a head fastening portion 13a that fixes the periphery of the hole 133 of the upper surface fabric 131 of the inflatable body 130. . The retaining ring 24p is, for example, a ring-shaped molded product made of aluminum alloy or the like, and a hole 24q that is substantially the same as the inner diameter of the notch 25h at the lower end of the annular connecting portion 25e of the inflator storage portion 25, and this hole The ring portion 24r is provided on the outer periphery of the 24q and mounted on the annular protrusion 24l. The ring portion 24r includes holes 24s through which the plurality of bolts 24o are respectively inserted.

  As shown in FIGS. 1, 3, 5, and 6, the inflator storage unit 25 is a cup-shaped molded product made of, for example, an aluminum alloy. The inflator storage portion 25 includes a substantially triangular pyramid-shaped boss portion 25a having a female-threaded connection hole 25b into which a male screw 11c provided at the distal end portion of the shaft body 11 of the support 10A is screwed, and the boss portion 25a. A cylindrical portion 25c provided with window holes 25d at equal intervals on a side portion thereof, an annular connection portion 25e provided on the upper end side of the cylindrical portion 25c, and the connection portion 25e An inflator fixing bolt hole 25f provided at the upper end, a connection male screw 25g provided outside the upper end of the connection portion 25e, and an annular notch 25h provided at the lower end of the male screw 25g; It has. The female threaded connection hole 25b includes an inflator fixing seat 25i that passes through the boss portion 25a, passes the wiring 12 of the inflator 30, and fixes the lower end of the inflator 30.

  As shown in FIGS. 1, 5, and 7 to 9, the inflator 30 is a fire tube body 38 that is mounted coaxially with the chamber 31 from a chamber 31 and a hole 32 provided at the bottom of the center of the chamber 31. And an ignition powder 41 made of boron nitrate loaded in the fire tube 38, an igniter 44 assembled to the fire tube 38, and a smokeless powder loaded between the chamber 31 and the fire tube 38. Gas generating agent 36, a lid 47 for sealing the opening of the chamber 31, and a flange portion 48 having a plurality of bolt holes 48 a provided around the lid 47. The lid 47 seals the opening of the chamber 31 by screwing a plurality of bolts 49 into the bolt holes 48a.

  The chamber 31 is made of, for example, stainless steel, is a cup-shaped container having an opening on the upper side, a hole 32 for inserting a fire tube in the center on the bottom side, and a large number of nozzles 32a on the side wall. A nozzle seal 33 made of, for example, an aluminum vapor-deposited polyester sheet is attached to the outer wall surface of the chamber 31. Further, on the inner surface side of the chamber 31, for example, a filter 34 made of a stainless steel mesh or the like is attached. A partition cylinder 35 made of, for example, cardboard is mounted on the bottom of the chamber 31 and the inner wall surface of the filter 34. A gas generating agent 36 composed of smokeless explosive in an amount corresponding to the specifications of the interceptor 1 to be deployed is loaded in the partition tube 35. A cushion 37 is placed on top of the gas generating agent 36.

The fire tube 38 is made of, for example, stainless steel and is a cup-shaped container having a number of nozzles 39 on the side wall. A nozzle seal 40 made of, for example, an aluminum vapor-deposited polyester sheet is attached to the outer wall surface of the fire tube 38.
A seal 42 and a rubber ring 43 are placed on the fire tube 38 after the ignition powder 41 is loaded, and an ignition unit 44 is assembled so as to contact the rubber ring 43.
As shown in FIG. 9, the ignition unit 44 is an ignition unit 45 made of stainless steel or the like, and an ignition agent 46c made of boron nitrate is attached to a bridge line 46b attached to a resin holder 46a. The bottom 46d of the ball 46 is attached with an adhesive, and an auxiliary agent 46e made of, for example, boron nitrate is loaded around the ignition ball 107 and sealed with a resin cap 46f. The resin holder 46a is connected to the wiring 12 having the connector 12a at the end.

As shown in FIGS. 1 to 3 and FIGS. 10 to 16, the bottom body 10 </ b> C is formed on the base member 50 having the same outer diameter as that of the front body 10 </ b> B and the bottom surface 57 of the base member 50. The postponing device storage portion 59 and a firing mechanism assembly 76 assembled to the base member 50 are provided.
As shown in FIGS. 1 to 3 and FIGS. 10 to 16, the base member 50 is configured by a disc body having the same outer diameter as that of the front body 10 </ b> B, such as an aluminum alloy. The base member 50 has a shaft body mounting portion 51 having a substantially triangular pyramidal projection 52 on the head side on the front body 10B side, and a substantially annular protrusion on the bottom side opposite to the front body 10B. 58, a recess-shaped postponing device storage portion 59 surrounded by a bottom surface 57 of the base member 50 and a substantially annular ridge 58, and on the back side of the shaft body mounting portion 51 so as to surround the postponing device storage portion 59 And a firing mechanism assembly 76 to be assembled.

As shown in FIG. 10, the substantially triangular pyramid-shaped protrusion 52 includes a cylindrical portion 53 at the top, and attaches an end portion of the shaft body 11 penetrating from the cylindrical portion 53 toward the wall surface of the postponement device storage portion 59. A hole 54 is provided. The hole 54 has a female screw 55 on the inner wall surface for screwing a male screw 11 d provided at the end of the shaft body 11. A substantially annular step 56 for attaching the outer cylinder 150 is provided on the outer peripheral portion of the shaft body attaching portion 51.
The shaft body 11 is mounted on the substantially triangular pyramid-shaped protrusion 52, and the outer cylinder 150 is locked to the substantially annular step 56 in the shaft body mounting portion 51.
The substantially annular ridge 58 is formed with a predetermined width outward from a position corresponding to the root of the substantially triangular pyramidal projection 52. Bolt holes 60 are provided in the bottom surface 57 inside the substantially annular protrusion 58. A male screw 58 a for assembling the firing mechanism assembly 76 is provided on the outer surface of the substantially annular protrusion 58.

As shown in FIG. 10, a postponement device 62 having a bolt hole 63 is assembled to the postponement device storage portion 59 with a bolt 64 via a cushion material 61. The cushion material 61 is made of, for example, silicon rubber, and has a hole 61a in the center. Connected to the postponement device 62 is a connector 12a that is pulled out from the bottom surface 57 of the postponement device storage portion 59 and passes through the hole 61a of the cushion material 61.
For example, as shown in FIG. 31, the postponing device 62 includes a capacitor 60 a for storing power for operating the ignition unit 44 of the inflator 30 and a control IC 60 b for controlling the energization time to the inflator 30. It consists of an ignition device.

Specifically, the postponement ignition device communicates with a safety key that prevents energization of the circuit, the inflator 30 and the firing mechanism 66 by a physical short circuit or disconnection of the circuit, a launch control system, and a launch detection mechanism. An arming circuit for controlling the arming state, a firing detection mechanism for sensing that the interceptor 1 has been fired, and a power storage unit (capacitor 60a) for storing electric power for operating the inflator 30 from the outside. And an energizing circuit for energizing the inflator 30 from the power storage unit (capacitor 60a) and a control IC 60b for controlling energization timing, arming state, and charging state by connecting to the launch control system.
It should be noted that the postponement ignition device may be configured by an explosive series as an auxiliary or alternative to the postponement ignition function.

As shown in FIG. 10, the firing mechanism 66 that causes the interceptor 1 to fly includes a firing mechanism assembly 76 that is assembled to the base member 50 and a propellant chamber 78.
As shown in FIGS. 10, 11, and 12, the firing mechanism unit assembly 76 is a substantially cylindrical molded product made of, for example, an aluminum alloy. The inner wall surface of the firing mechanism assembly 76 has a first female screw 68 that is screwed into a male screw 58a provided on the outer surface of the substantially annular ridge 58 from the head side toward the bottom side. An annular portion 67, a second annular portion 69 that is continuous with the first annular portion 67 and has a smaller diameter than the first annular portion 67, and a third annular portion that is continuous with the second annular portion 69 and has a smaller diameter than the second annular portion 69. , And a fourth annular portion 71 that is continuous with the third annular portion 70 and has a larger diameter than the third annular portion 70. The fourth annular portion 71 includes a female screw 71a.

In order to mount the ignition electrode holder 101 mounted with the ignition electrode 100 on the shelf 72 connecting the second annular portion 69 and the third annular portion 70 in parallel with the axis of the firing mechanism assembly 76. Ignition electrode hole 73 and a charging electrode hole 74 for mounting the charging electrode holder 103 mounted with the charging electrode 102 parallel to the axis of the firing mechanism assembly 76 are provided.
The third annular portion 70 includes a plurality of bolt insertion holes 72 a parallel to the axis of the firing mechanism assembly 76 on the axial center side from the ignition electrode hole 73 and the charging electrode hole 74.
An annular recess 76 a for mounting the gas stopper ring 99 is provided on the outer wall portion of the firing mechanism assembly 76.

For example, a spacer 65 made of polyacetal resin is attached to the second annular portion 69, and the postponing device 62 is placed on the spacer 65. On the postponing device 62, for example, a cushion material 61 made of silicon rubber is placed.
A propellant chamber 78 is assembled to the third annular portion 70 and the fourth annular portion 71. After the propellant chamber 78 is mounted from the fourth annular portion 71 toward the third annular portion 70, a plurality of bolts 80 are respectively inserted into bolt insertion holes from bolt holes 75 provided on the lid side of the propellant chamber 78. It is fixed to the third annular portion 70 and the fourth annular portion 71 by being screwed to 72a. On the bottom side of the propellant chamber 78, a sealing ring 98b is screwed through a sealing seal 98a.

  As shown in FIG. 13, the propellant chamber 78 includes a cup-shaped container 82 in which the igniter 81 is assembled, a cup-shaped igniter case 83 having a recess that covers the igniter 81, and the bottom of the igniter case 83. , A spacer 84 disposed between the inner surface of the container 82, an igniting agent 85 filled in the igniting agent case 83, a cap 86 for sealing the opening of the igniting agent case 83 filled with the igniting agent 85, and a cylinder A case 87 including a portion 88, a cylindrical portion 89 with a nozzle, and a bottom plate 91; a partition tube 92 that covers the periphery of the cylindrical portion 89 with a nozzle; a cushion 93 that is placed on the bottom plate 91 of the case 87 during assembly; A smokeless gunpowder 94 sometimes filled on the cushion 93, a cushion 95 placed on the smokeless gunpowder 94 during assembly, a rupture sheet 96 placed on the cushion 95 during assembly, And a lid 97 to seal the opening side of the. Here, the assembling work of the propellant chamber 78 is performed with the top and bottom of FIG. 13 turned upside down in order to fill with explosives and the like. FIG. 13 shows a state of the propellant chamber 78 that is inverted upside down from that during assembly work.

As shown in FIG. 15, the case 87 has a cylindrical portion 88 on the outer peripheral side and a cylindrical portion 89 with a nozzle on the inner peripheral side arranged concentrically, and a donut-shaped bottom plate 91 has a cylindrical portion 88 and a cylindrical with nozzle. The shape which connects the part 89 is comprised. The nozzle-equipped cylindrical portion 89 includes a large number of nozzles 90. In the propellant chamber 78 shown in FIG. 13, the cylindrical portion 88 covers the inner wall surface of the container 82, and the cylindrical portion 89 with the nozzle covers the periphery of the ignition powder case 83.
The ignition unit 81 includes a connector 105 connected to the ignition harness 104. The ignition harness 104 is connected to the ignition electrode 100, and the connector 105 is connected to the ignition electrode 100 via the ignition harness 104.
The ignition unit 81 includes a connector 105 that is connected to an ignition harness 104 that is connected to the ignition electrode 100.

As shown in FIG. 16, the ignition unit 81 includes an ignition unit holder 106 made of stainless steel or the like, and an ignition agent 107c made of rhodium lead attached to a bridge wire 107b attached to a resin holder 107a. The bottom 107d of the ball 107 is attached with an adhesive, and an auxiliary agent 108 made of, for example, boron nitrate is loaded around the ignition ball 107 and sealed with a resin cap 109. The resin holder 107a is connected to a wiring (leg line) 107c having a connector 105 at its end.
As shown in FIGS. 10, 11, and 12, the charging electrode 102 is connected to a charging harness 111, and the charging harness 111 is connected to a connector 12 a that is connected to the wiring 12 of the inflator 30.

  Next, as shown in FIGS. 17 to 19, the expansion body 130 is a cloth body made of tough fibers such as an aramid fiber and a polyamide fiber and having a substantially circular shape and a hole 133 at the center. The inflatable body 130 has an upper surface cloth 131 made of a cloth body having a substantially circular shape and having a hole 133 in the central part, and a lower surface cloth 132 made of a cloth body having a substantially circular shape and having a hole 136 in the central part. Each of the end portions 131a and 132a is formed by sewing on the circumference. A plurality of shape holding members 140 are sewn on the inner surface of the expansion body 130, and a plurality of pulling members 145 are sewn around the hole 133 of the upper surface fabric 131 of the expansion body 130. The expansion body 130 is assembled to the flying aircraft body 10 by fastening the hole 133 to the front body 10B and fastening the hole 136 to the support body 10A.

The upper fabric 131 includes a coating layer that is coated with silicon resin or the like and dried. A disk-shaped reinforcing fabric 134 is sewn on the outer surface of the hole 133, and a disk-shaped protective fabric 135 is sewn on the inner surface of the hole 133. In the vicinity of the hole 133, a plurality of holes 133a are provided concentrically for screwing the upper surface fabric 131 to the connection fitting 24 and the plurality of bolts 24o to the retaining ring 24p.
The lower surface fabric 132 includes a coating layer that is coated with silicon resin or the like and dried. A disc-shaped reinforcing fabric 137 is sewn on the outer surface of the hole 136, and a disc-shaped protective fabric 138 is sewn on the inner surface of the hole 136. In the vicinity of the hole 136, a plurality of holes 136 a for screwing the lower surface fabric 132 to the retaining ring 16 with a plurality of bolts 18 are provided concentrically.

The shape holding member 140 is formed of a belt-like cloth body made of tough fibers such as aramid fiber and polyamide fiber, for example, and includes T-shaped sewing portions 141a and 141b at both ends. The sewing parts 141a and 141b are respectively sewn to the inner side of the upper surface fabric 131 and the inner side of the lower surface fabric 132.
In the shape holding member 140, the interval and position of sewing between the upper fabric 131 and the lower fabric 132 are determined according to the size and shape of the inflatable body 130, and the axial interval is the upper fabric 131 of the front body 10B. Is set at the same height as the distance from the front fastening portion 13a to the tail fastening portion 13b with the lower surface fabric 132 of the shaft body 11, but preferably the front fastening with the upper surface fabric 131 of the front body 10B. The length is set to be about 5 to 20% smaller than the interval of the tail fastening portion 13 from the portion 13a to the lower surface fabric 132 of the shaft body 11.

  The shape holding member 140 can be provided with a plurality of arrangement diameters in the radial direction of the expansion body 130. At that time, it is desirable to sew at many positions in order to control the shape well. As shown in FIG. 20, an efficient interval when sewing the shape-retaining member 140 is obtained by setting the ratio of the axial length L to the diameter φ of the inflating body 130 as an integer (the axial length). : Diameter) = (1: N), it is set to have (N-1) to (N-2) arrangement circles in the radial direction, and the number of shape holding members 140 in one arrangement circle is , When the order of the arrangement circles counted from the central axis is represented by an integer A, {(A) × 4} or four arrangement circles closest to the central axis are used, and the number of successive multiples (4, 8, 16, 32,...・ Set to a level. At this time, the distance between each arrangement circle and the outer end from the central axis may be basically {radius / (N)}, but is adjusted so that the distance decreases from the central axis toward the end. It is desirable that For example, when the radius is 450, (X: Y: Z) = (150: 150: 150) may be used, but (X: Y: Z) = (170: 150: 130) is desirable.

Here, the axial length L of the expansion body 130 means a distance from the front fastening portion 13a with the upper surface fabric 131 of the front body 10B to the tail fastening portion 13b with the lower surface fabric 132 of the shaft body 11. .
The length L of the shape retaining member 140 is 5 to 20% with respect to the distance from the front fastening portion 13a with the upper surface fabric 131 of the front body 10B to the tail fastening portion 13b with the lower surface fabric 132 of the shaft body 11. A small length is desirable.
Further, in the upper surface fabric 131 of the inflatable body 130, a pulling member 145 is provided at a position on the arrangement circle where the one or more shape holding members 140 are disposed and at a circumferential portion of the upper surface fabric 131.

As shown in FIGS. 21 to 24, the pulling member 145 is configured by a belt-like cloth body made of tough fibers such as aramid fiber and polyamide fiber, and has an annular connection portion 146 at one end and the other end. Is provided with a connecting portion 147. The connecting portion 146 is connected to a pulling member connecting tool 148 attached to the step portion 24 b of the connecting member 24. Further, the connecting portion 147 is sewn to the upper surface fabric 131.
The sewing positions of the pulling member 145 and the upper surface fabric 131 are on the same arrangement circle as the shape holding member 140 arranged in an arrangement circle with a constant interval in the radial direction and on the circumferential portion of the upper surface fabric 131.

The number of traction members 145 arranged on the expansion body 130 is preferably the same as the number of shape holding members 140 on the same arrangement circle on the arrangement circle, and the circumference of the upper surface fabric 131 in the developed shape of the expansion body 130. When the number of the shape holding members 140 of the outermost shape holding member arrangement circle is represented by an integer B, the range of {B to (2 × B)} is desirable.
The pulling member 145 is provided on a circle where the one or more shape holding members 140 are arranged and a circumferential portion of the upper surface fabric 131 of the inflatable body 130.

  As shown in FIGS. 21 and 22, the traction member coupler 148 is configured by, for example, connecting semi-circular and half-divided members 149 a and 149 b with a bolt 149 f formed of an aluminum alloy. . The split members 149a and 149b are provided with two notches 149c to which the annular connecting portion 146 is attached, a bolt insertion hole 149d provided at one end, and a bolt 149f inserted from the bolt insertion hole 149d. Are provided with screw holes 149e at the end of each.

As shown in FIGS. 23 and 24, the outer cylinder 150 is formed in a cylindrical shape made of a lightweight member such as ABS resin, for example, and notches 151 and 152 are formed at both ends of the position where the cylinder is vertically divided into two. Is done. The notch 151 on the front body 10B side is a notch having a length of 5 to 20% of the entire length of the outer cylinder 150, and the notch 152 on the bottom body 10C side is a notch having a length of 30 to 50% of the entire length of the outer cylinder 150.
A main groove 153 having a depth of 30 to 60% of the thickness of the outer cylinder 150 is formed in a line connecting the tips of the notches 151 and 152 at both ends. The groove shape of the main groove 153 is a mountain shape, a U shape, a V shape, or the like.
The cutouts 151 and 152 are filled by inserting a cover body 154 having a shape corresponding to the cutouts 151 and 152.

A sub-groove 155 having a depth of 20 to 50% of the thickness of the outer cylinder 150 and a depth smaller than the main groove 153 is formed on the circumference between the two notches 151 and 152. The groove shape of the sub-groove 155 is a mountain shape, a U shape, a V shape, or the like.
The sub-groove 155 is desirably formed on the circumference between the two notches 151 and 152 by about 1 to 5 at equal angular intervals.
As a result, due to the force received from the expansion body 130 that is expanded by the introduction of gas, the outer cylinder 150 is inserted into the main groove 153 provided inside or outside from the notch 151 on the inflator 30 side as shown in FIG. The fracture progresses along, reaches the notch 152 on the opposite side, is divided into equal parts, and the divided outer cylinders 150 are, for example, sub-grooves 155 cut at equal angular intervals as shown in FIG. Smoothly deforms or breaks. Thereby, the outer cylinder 150 does not hinder the expansion of the expansion body 130, and can stably expand the expansion body 130.

Next, the assembly of the expansion body 130 and the outer cylinder 150 to the flying aircraft body 10 will be described with reference to FIGS. 4 and 25 to 28. A screw lock agent is applied to all screw parts before screwing.
FIG. 25 shows the positional relationship between the flying aircraft body 10, the expansion body 130, and the outer cylinder 150.
Next, a procedure for attaching the expansion body 130 and the outer cylinder 150 to the flying aircraft body 10 will be described.
First, as shown in FIG. 26, the male screw 25 g of the connection portion 25 e of the inflator storage portion 25 is connected to the female screw 24 j of the third step portion 24 i of the connection fitting 24 to be integrated.
Next, as shown in FIG. 26, the boss portion 25 a of the inflator storage portion 25 includes a hole 133 of the upper surface fabric 131 of the inflatable body 130, and a hole 24 q of the retaining ring 24 p previously arranged inside the inflatable body 130. To be inserted. Next, the bolt 24o is passed through the hole 24m of the connection fitting 24, and the bolt 24o and the retaining ring 24p are screwed.

Next, as shown in FIG. 27, the shaft body 11 to which the plug 14 is screwed is passed through the expansion body 130, and the male screw 11 c is screwed into the female screw hole 25 b of the boss portion 25 a of the inflator storage portion 25. Next, the gasket 15 and the retaining ring 16 are put inside the expansion body 130 and attached to the plug 14 respectively.
Next, as shown in FIG. 4, the lower surface fabric 132 of the inflatable body 130 is placed on the retaining ring 16 and the positions of the bolt holes are adjusted. Similarly, the slide ring 17 is placed on the lower surface fabric 132 of the expansion body 130, and the position of the bolt hole is adjusted. Then, the bolt 18 is passed through the hole 17 d of the slide ring 17, the retaining ring 16 is screwed with the plurality of bolts 18, and the lower surface fabric 132 of the expansion body 130 is fixed. Next, the female screw 19 b of the holding ring 19 is screwed onto the male screw 14 f of the plug 14, and the slide ring 17 is pressed.

Next, as shown in FIGS. 21, 27, and 28, among the four traction members 145 attached to the expansion body 130, the split members 149 a and 149 b are divided into the connection portions 146 of the two adjacent traction members 145. Through each. Then, in each of the split members 149a and 149b, the connecting portions 146 are fitted into the respective step portions 149c. Next, the split member 149a, 149b is coupled by the bolt 149f to form the traction member connector 148.
Next, as shown in FIGS. 28 and 29, the traction member coupler 148 is attached to the step portion 24 b of the connection fitting 24. Next, the head mounting portion 20 is screwed to the connection fitting 24.
Next, the base member 50 is screwed to the lower end portion of the shaft body 11.
Next, after the internal air of the expansion body 130 is discharged with a suction machine and folded, two places with appropriate heights are bound with Velcro (registered trademark).

Next, a sealing agent (for example, silicone rubber) is applied to the lower end of the outer cylinder 150 and attached to the step portion 56 of the base member 50.
Next, the ring body 22 is fitted into the centering portion 21.
Next, a sealing agent (for example, silicone rubber) is applied to the upper end of the outer cylinder 150, and the upper end of the outer cylinder 150 is annularly recessed 21 d of the centering part 21 while screwing the centering part 21 to the connection fitting. Attach to.
As described above, the expansion body 130 and the outer cylinder 150 can be attached to the flight assembly 10.

Next, a procedure for assembling the postponing device 62 and the firing mechanism assembly 76 to the base member 50 will be described.
First, the cushion 61 is affixed to the bottom surface 57 of the postponement device storage part 59 of the base member 50 using a double-sided tape.
Next, the connector 12 a of the inflator 30 is connected to a connector (not shown) at the center of the postponing device 62.
Next, the postponing device 62 is put into the postponing device storage portion 59 of the base member 50 while adjusting the screw position.
Next, the bolt 64 is passed through the hole 63 of the postponing device 62, and the screw hole 60 and the bolt 64 of the base member 50 are screwed together.

Next, the spacer 65 is inserted into the firing mechanism assembly 76.
Next, the firing mechanism assembly 76 is screwed to the base member 50.
Next, the charging harness 111 of the firing mechanism assembly 76 is connected to the postponing device 62.
Next, the connector 105 of the propellant chamber 78 is connected to the connector 104 of the firing mechanism assembly 76.
Next, the propellant chamber 78 is placed inside the firing mechanism assembly 76 while aligning the screw positions.

Next, the bolt 80 is passed through the hole 75 of the propellant chamber 78, and the hole 72a of the firing mechanism assembly 76 and the bolt 80 are screwed.
Next, an epoxy adhesive is applied to the hermetic seal 98a to adhere to the hermetic ring 98b and is dried.
Next, the sealing ring 98 b is screwed to the bottom of the firing mechanism assembly 76.
As described above, the postponing device 62 and the firing mechanism assembly 76 can be assembled to the base member 50.

Next, the operation of the interceptor 1 according to this embodiment will be described.
The interceptor 1 according to the present embodiment is set, for example, in order to cope with a threat from a portable anti-tank rocket when a vehicle or a facility is attacked by a portable anti-tank rocket in a conflict area or the like. It is used by flying near the meeting position.
First, the postponement time of the postponing device 62 is set in a vehicle or facility, and then, as shown in FIG. 31, the external power source device 205 is connected to the charging device 206 and the charging electrode 102 to connect the postponing device 62. Charge the battery.
Next, for example, as shown in FIG. 30, the interceptor 1 is loaded into the gun 201 of the launching device 200. As a result, the ignition signal electrode 202 of the launcher 200 and the ignition electrode 100 of the interceptor 1 come into contact with each other.

Next, the switch 204 of the ignition signal device 203 is closed to energize the ignition electrode 100 with an ignition signal.
Next, the ignition signal is energized from the connector 105 of the propellant chamber 78 through the ignition electrode 100 and the ignition harness 104 to the ignition unit 81.
Next, the bridge 107b of the ignition unit 81 is heated by energization. The igniting agent 107 is ignited by the heat of the electric bridge line 107b.
Next, the auxiliary agent 108 is ignited by the ignition of the igniting agent 107. The cap 109 of the ignition unit 81 and the upper part of the ignition powder case 83 are destroyed by the ignition of the auxiliary powder 108, and the ignition powder 85 is burned.

Next, the ignition powder case 83 and the partition tube 92 that block the nozzle 90 of the case 87 are destroyed by the combustion of the ignition powder 85, and the smokeless powder 94 is burned.
Next, the cushions 93 and 95, the rupture sheet 96, and the sealing seal 98 a are broken by the combustion of the smokeless explosive 94, and the combustion gas is released from the bottom body 10 </ b> C of the interceptor 1.
Next, the interceptor 1 is launched from the launching device 200 by the released combustion gas and flies.
Next, when the set postponement time is reached, the ignition unit 44 of the inflator 30 is energized through the wiring 12 that passes through the wiring hole 11a of the shaft body 11 from the postponing device 62.

Next, the electric bridge wire 46b of the ignition part 44 of the inflator 30 is heated by energization. The ignition powder 46c is ignited by the heat of the electric bridge line 46b.
Next, the auxiliary agent 46e is ignited by the ignition of the ignition agent 46c. The cap 46f and the seal 42 of the ignition unit 44 are destroyed by the ignition of the auxiliary agent 46e, and the ignition agent 41 is burned.
Next, the nozzle seal 40 and the partition cylinder 35 are destroyed by the combustion of the ignition powder 41, and the gas generating agent 36 made of smokeless powder is burned.
Next, the nozzle seal 33 is broken by the combustion of the gas generating agent 36, and gas is released from the nozzle 32 a through the filter 34.

Next, the expansion body 130 is expanded by the gas. For example, as shown in FIGS. 32 and 33, the outer cylinder 150 is separated from the notches 151 and 152 and the main groove 153 by the force with which the expansion body 130 expands. The expansion body 130 is developed into a required developed shape by the supplied gas, for example, as shown in FIG.
Next, as shown in FIG. 35, at the meeting position, the interceptor 1 can collide with the portable anti-tank rocket 3 to damage the portable anti-tank rocket 3.

  As described above, the interceptor 1 according to the present embodiment has a shape with small velocity attenuation that is casing by the outer cylinder 150 and the head 120, and is high in speed before the meeting position that is safe even if threat fragments and jets are generated. Fly in. When the interceptor 1 is fired or when a preset time is reached, the postponement ignition circuit of the postponing device 62 energizes the inflator 30 so that the effective protection range is expanded just before the meeting position. Since the expansion body 130 is deployed, it is possible to fly the interceptor 1 far away.

  Further, in the interceptor 1 according to the present embodiment, as shown in FIG. 33, the outer cylinder 150 has an internal portion with the notch 151 on the front body 10 </ b> B side as a base point due to the force received from the expansion body 130 that expands due to the introduction of gas. Alternatively, the breakage proceeds along the main groove 153 and the sub-groove 155 provided inside and outside. Then, the outer cylinder 150 reaches the notch 152 on the rear body 10C side and the outer cylinder 150 is divided into equal parts, and the divided outer cylinders 150 are smoothly deformed or broken by the sub-grooves 155 formed at equal angular intervals. . Thereby, the outer cylinder 150 can expand | deploy the expansion body 130 stably, without inhibiting expansion | deployment of the expansion body 130. FIG.

  Moreover, in the interceptor 1 which concerns on this embodiment, since the center of the upper surface fabric 131 and the lower surface fabric 132 of the expansion body 130 is fastened by the support body 10A, the center of gravity and the center axis of the expansion body 130 are the center of gravity of the interceptor 1 and In addition to the above-described effects, the pulling member 145 connects the expansion body 130 and the support body 10A to suppress the vibration even after the expansion of the expansion body 130 is completed. . As a result, the interceptor 1 can fly while maintaining a state in which the posture, the trajectory, and the deployed diameter of the expanding body 130 are stable, and therefore, it is possible to suppress a decrease in hit accuracy even at a distance.

Further, in the interceptor 1 according to the present embodiment, the expander 130 has the expander shaft core height fixed by the head fastening portion 13a and the bottom fastening portion 13b, and the top fabric 131 and the bottom surface by the shape holding member 140. Since the movement of the fabric 132 in the axial direction is limited, as shown in FIG. 20, the vibration in the axial direction during deployment can be suppressed.
FIG. 36 shows Comparative Example 1 in which only the head fastening portion 13a is fixed to the expanding body 130 and the bottom fastening portion 13b is not fixed to the interceptor 1 according to the present embodiment.
In Comparative Example 1, since the movement of the lower surface fabric 132 in the axial direction is not limited, the expandable body 130 may vibrate greatly in the axial direction when deployed.

FIG. 37 shows Comparative Example 2 in which the shape holding member 140 is not used for the interceptor 1 according to the present embodiment.
In Comparative Example 2, the axial movement of the upper surface fabric 131 and the lower surface fabric 132 is not limited, and thus the expansion body 130 may vibrate greatly in the axial direction or the width direction when deployed.
FIG. 38 shows a third comparative example in which the shape retaining member 140 is not used for the interceptor 1 according to the present embodiment.
In Comparative Example 3, since the movement of the upper surface fabric 131 and the lower surface fabric 132 in the axial direction is not limited, the expandable body 130 may vibrate greatly in the axial direction or the width direction when deployed.

FIG. 39 shows an interceptor 1A according to the second embodiment of the present invention.
The interceptor 1A according to the present embodiment is shown as a state in which the expansion body 130 is inflated and deployed. The form before the expansion body 130 is inflated and deployed is the same as the interceptor 1 shown in FIG.
The interceptor 1A according to the present embodiment is different from the interceptor 1 according to the first embodiment in that the shape maintaining member 140 and the pulling member 145 are not used and the tail fastening portion 13b is located in the bottom body 10C.

The interceptor 1A according to the present embodiment has a spherical shape when the expansion body 130 is inflated and deployed. The reason for the spherical shape is that the distribution of the bullets of the interceptor 1A has a circular normal distribution, and the spherical shape is a generally assumed shape when following this.
Also in the present embodiment, as shown in FIG. 35, the inflatable body 130 expands to such a size that it can collide with the portable anti-tank rocket 3 and damage the portable anti-tank rocket 3 at the meeting position. If it can be deployed, it is possible to achieve the same effects as the interceptor 1 according to the first embodiment.

FIG. 40 shows an interceptor 1B according to the third embodiment of the present invention.
The interceptor 1B according to the present embodiment is different from the interceptor 1 according to the first embodiment in that the expansion body 130 is configured by a bag body in which a rectangular upper surface fabric 131 and a lower surface fabric 132 are sewn.
In the interceptor 1B according to the present embodiment, the shape holding member 140 is fastened to the upper surface fabric 131 and the lower surface fabric 132 at the same height as the support 10A, but the arrangement is equally spaced parallel to the rectangular sides. Provided on the line. Further, the expansion body 130 is accommodated so that the developed shape is symmetrical with respect to the separation position of the outer cylinder 150.
According to the interceptor 1B according to the present embodiment, for example, when protecting a vehicle or the like, it is possible to fire one or more interceptors 1B to protect the rectangular range including the vicinity of the ground surface.
The interceptor 1B according to the present embodiment can also exhibit the same operational effects as the interceptor 1 according to the first embodiment.

In each of the above-described embodiments, the launch mechanism 66 adopts a propellant method using a propellant as a method for generating the propulsion energy, but the present invention is not limited to this, and a rocket method using a propellant. May be adopted.
If it is a rocket system, a simple conceivable configuration includes an ignition part that ignites by energization and burns propellant, a propellant that burns to generate gas and energy for propulsion, and an ignition part and propellant. It is conceivable to configure a case having a nozzle for storing and ejecting gas to the outside.

Next, in the present invention, the results of the test for stabilizing the protection range of the interceptor 1 that deploys the spherical or ellipsoidal expansion body 130 and the protection by the configuration of the shape holding member 140, the pulling member 145, and the support 10A. The reason for stabilizing the range will be described.
First, the reason for stabilizing the protection range of the interceptor 1 will be described.
In order to hit the interceptor 1 with a threat from the portable anti-tank rocket 3 flying in the distance, (1) the detection accuracy of the threat by the portable anti-rocket 3 is high, (2) the interceptor 1 It is conceivable that the ballistic error is small (including the time factor), and (3) the protection range of the interceptor 1 is large.

(1) is related to the configuration of the interceptor system, and (2) is related to the launcher and launch conditions, and it is conceivable that the size of the protection range of (3) is determined based on these conditions.
The interceptor 1 needs to form and maintain a protection range within the time range that is expected to be hit by the portable anti-tank rocket bullet 3, but if this protection range changes every moment, It is conceivable to use the minimum value of the fluctuation range for a successful hit.
If this fluctuation range is large, the inflating body 130 must be made large in order to raise the minimum value, leading to an increase in the configuration of the intercepting system as well as the intercepting body 1, causing problems in practical use.
Therefore, stably forming and maintaining this protection range leads to a reduction in size and weight of the interceptor system and the interceptor 1 and can be expected to improve the practicality of operation.

Next, an outline of the verification test will be described.
The fluctuation range of the protection range at the time of flight by the configuration of the interceptor 1 (shape holding member 140, traction member 145, support 10A) was measured, and the effect of the configuration and the range thereof were verified.
The interceptor 1 was fired from the launching device 200 shown in FIG. 30 and the behavior was photographed by the high-speed video camera 212.
Firing conditions ・ Launch at an initial speed of 120 m / s ・ Launch horizontally ・ No wind

Expansion body conditions ・ Use a deployment diameter of about 800 to 820 mm when deployed in a stationary state ・ Design of an ultimate internal pressure of about 40 kPaG ・ Acquire the width while flying 5 m from deployment ・ The outer cylinder 150 is made of rigid PVC (t = 0.0 mm). 2) was used (in order to reduce the influence of the outer cylinder 150).
The protection range at the time of flight assuming that the width perpendicular to the flight direction is the protection range is optimally the same as the deployment diameter (about 800 to 820 mm) at the time of stationary deployment.

Next, a result of shooting the interceptor 1 according to the first embodiment of the present invention from the launching device 200 and photographing its behavior with the high-speed video camera 212 will be described based on FIG.
First, the program of the control IC 60b of the postponing device 62 of the interceptor 1 is adjusted so that the expandable body 130 is deployed after the interceptor 1 passes through the speed detector 213.
Next, as shown in FIG. 31, the external power supply device 205 is connected to the charging device 206 and the charging electrode 102 to charge the postponing device 62.
Next, for example, as shown in FIG. As a result, the ignition signal electrode 202 of the launcher 200 and the ignition electrode 100 of the interceptor 1 come into contact with each other.

The following operation is the same as that of the interceptor 1 according to the first embodiment of the present invention. When the interceptor 1 passes the speed detector 213, initial speed data is obtained.
Next, the ignition unit 44 of the inflator 30 is energized from the postponing device 62 through the wiring 12 that passes through the wiring hole 11 a of the shaft body 11.
The following operation is the same as that of the interceptor 1 according to the first embodiment of the present invention, and the expansion body 130 is expanded by the gas supplied from the inflator 30 as shown in FIGS. 20 and 33, for example. When expanded into a shape, the protection range of the interceptor 1 shown in FIG. 42 is acquired from the image of the high-speed video camera 212.
Here, the interceptor 1 is loaded into the launching apparatus 200 shown in FIG. 30, the passing speed of the interceptor 1 launched from the launching apparatus 200 is measured by the speed detector, and the interceptor 1 is protected by the high-speed video camera 212. Acquired the range.

The obtained results were stable with small fluctuations in the developed diameter. Further, as shown in FIG. 42, the fluctuation (+ α or −α) of the deflection angle α with respect to the longitudinal axis β corresponding to the protection range of the expansion body 130 was also small and stable.
As shown in FIG. 41, the speed detecting device 213 is provided with two sets of speed detecting lasers 214 on an aluminum base 213a. The two sets of detection lasers 214 are devices that detect the passage of an object. When the laser light output from the light emitting device 214a is blocked by the passage of the object, the light receiving device 214b cannot receive the light, so that the output voltage to the oscilloscope drops. Is set to The distance between the two sets of detection lasers 214 is about 0.5 m. The height of the gantry 213a is about 2 m.
As shown in FIG. 43, the velocity is calculated from the obtained oscilloscope waveform according to the following equation.
Speed = (detection laser 214 installation distance) ÷ (time required for passing the detection laser 214 installation distance)

Next, in the expansion body 130, (1) the presence / absence of the shape holding member 145 (the interval is the same as the interval between the fastening portions of the support), (2) the presence / absence of the pulling member 145, and (3) the shaft 11 of the support 10A. Existence and spacing, and (4) the number of arrangement circles of the shape holding member 140 are examined.
It should be noted that four traction members 145 are provided on the arrangement circle closest to the central axis (engraved at intervals of 90 °), and eight are provided on the circumferential portion (engraved at intervals of 45 °).
The result of having performed the verification test on the conditions which used the design parameter of (1)-(4) is shown.
The results for spheres (1: 1) are shown in Table 1.
In the case of a sphere, by providing the support 10A and fastening the expansion body 130, the fluctuation range of the protection range could be made the same as the deployment width during stationary deployment.

Table 2 shows the results of ellipsoids (2: 1), (4: 1), and (8: 1).
When the expansion body 130 to be developed is an ellipsoid, the support body 10A, the shape holding member 140, and the pulling member 145 are configured in the above ranges in (2: 1) (4: 1) (8: 1). Thus, the protection range can be maintained the same as that at the time of stationary deployment, but in the case of considering the operation in the situation where the launch speed or the deployment diameter is large, the stability is taken into consideration (2: 1) to (4: 1). ) Is preferable.

In Table 2, no. 6, the shape holding member 140 is provided in (N ÷ 2) or more arrangement circles in the radial direction when fastened by the support 10 </ b> A and expressed as (deployed diameter: fastening portion interval) = (N: 1). .
In Table 2, no. 13, the level where the four pulling members 145 are provided in the arrangement circle closest to the central axis and the eight pulling members 145 are provided in the circumferential portion can make the fluctuation range of the protection range the same as the deployment width during stationary deployment. It was.
In Table 2, no. 22, the level where the four pulling members 145 are provided in the arrangement circle closest to the central axis and the eight pulling members 145 are provided in the circumferential portion can make the fluctuation range of the protection range the same as the deployment width at the time of stationary deployment. It was.

Next, in the present invention, the result of the test that confirms that the reaction at the time of deploying the interceptor can be reduced by the configuration of the outer cylinder 150 and the reason for the reaction reduction will be described.
First, the reason for reducing the recoil when the interceptor 1 is deployed will be described.
When the interceptor 1 separates or destroys the outer cylinder 150 and deploys the expansion body 130, except for fine points such as gas movement, the interceptor 1 is largely subjected to reaction in the expansion body deployment direction due to the following factors.
(1) Reaction caused by expansion of the expansion body 130, (2) Reaction when the outer cylinder 150 is separated, and (3) Reaction when the expansion body 130 pushes the separated outer cylinder 150.
When these reactions occur asymmetrically with respect to the axis with respect to the flight direction of the interceptor 1, the interceptor 1 has a velocity in that direction, so that it deviates from the trajectory predicted before deployment. , The accuracy of the threat will be reduced.

In order to assist this reduction in accuracy, a vicious cycle occurs in which the expansion body 130 is further configured.
Since the expansion body 130 is folded and accommodated on the center axis and is supplied uniformly, if the gas is supplied evenly, the expansion body 130 is basically expanded evenly. Therefore, it is necessary to consider the outer cylinder 150. As the function of the outer cylinder 150, (1) the side shape of the interceptor 1 when flying is held on an aerodynamically stable cylinder until deployment, and (2) the internal parts are protected during handling and storage. Therefore, it is conceivable to be composed of a material having a certain degree of strength and environmental resistance and a wall thickness.
An outline of the verification test will be described.
Measure the amount of movement in the radial direction during suspension deployment by the configuration of the outer cylinder 150 (the length of the notches 151, 152, the depth of the main groove 153, the number of sub-grooves 155), and verify the effect and range of the configuration Went.

In this test, the inflator was operated in a state suspended from the gantry 210 shown in FIG. 44, and the behavior was photographed by the high-speed video camera 212.
Installation condition ・ Hanging with a single wire Expansion body condition ・ Fabric design with a deployment diameter of about 800 to 820 mm when deployed in a stationary state ・ Design of an ultimate internal pressure of about 40 kPaG ・ A ratio of (deployment diameter: fastening portion interval) (2: 1 ), A circle having one shape holding member 140 is used.

Outer cylinder conditions-The outer cylinder 150 was an ABS resin cylinder having a thickness of 5 mm.
-The outer cylinder 150 has an outer diameter of about 100 mm and a height of about 400 mm.
The position of the inflator 30 is 10% from the top with respect to the length of the outer cylinder 130.
Outer cylinder separation state ・ The outer cylinder 150 is divided into two parts. Interceptor radial movement amount. ・ It is desirable that the distance of movement of the interceptor 1 in the radial direction is small.

Next, regarding the outer cylinder 150, (1) presence / absence of the notch 151 (front body side) and length with respect to the entire length of the outer cylinder, (2) depth of cut of the main groove 153 (the shape is fixed to a triangular groove), workability is considered. (3) The length of the notch 152 (rear body side) and the length relative to the overall length of the outer cylinder, and (4) the number of sub-grooves 155 (the depth% of the main groove with respect to the wall thickness-10) % Round groove fixing).
Table 3 shows the results of the verification test performed under the conditions using the design parameters (1) to (4).

  As a result of the test, the range of the structure in which the outer cylinder 150 is equally divided into two is that the length of the notch 151 (front body side) is 5 to 20%, and the length of the notch 152 (rear body side) is 30 to 50%. The depth of the main groove 153 may be 30 to 60% of the wall thickness, and the outer cylinder 150 is divided by the main groove 153 to further reduce the amount of radial movement of the interceptor 1 that occurs during deployment. When considered as a semi-cylinder, it has been found that it is preferable to uniformly engrave the above-mentioned sub-grooves 155 (per place / per semi-cylinder).

Next, based on FIG. 44, the result of having performed the deployment test of the interceptor 1 according to the first embodiment of the present invention will be described. 44A is a diagram before deployment, FIG. 44B is a diagram during deployment, and FIG. 44C is a diagram during deployment as viewed from the front.
The inflatable body 130 has a fabric design with a deployment diameter of about 800 mm to 820 mm during stationary deployment. The ultimate internal pressure is designed to be about 40 kPaG. The outer cylinder 150 was a resin cylinder having a wall thickness of 1 mm or less.
As shown in FIG. 44A, the interceptor 1 is suspended from a 2m × 2m × 2m aluminum alloy mount 210 with a dyneema hanging thread 211, and a high-speed video camera 212 is mounted on the front side of the interceptor 1. After the installation, the inflator 30 was energized and operated, and the developed diameter was read from the video of the high-speed video camera 212. In the high-speed video camera 212, a value between 50 msec and 100 msec after energization was acquired.

The barycentric point is analyzed from the video of the high-speed video camera 212, and the barycentric point coordinates at the time of deployment are acquired.
In this test, since it was suspended, the fluctuation in the lower axial direction could not be obtained accurately, so only the upper direction was evaluated. It was confirmed that the fluctuation range of the coordinates of the center of gravity was small, and the vibration during deployment was small and stable.

In each of the above embodiments, the case where the inflator 30 is provided in the front body 10B has been described. However, the present invention is not limited thereto, and may be provided in the shaft body 11 of the support 10A, for example. In this case, the outer cylinder 150 preferably adjusts the length of the notch 151 according to the gas outlet of the inflator 30.
Moreover, in each said embodiment, although the outer cylinder 150 was comprised by one cylinder, this invention is not limited to this, For example, it is also possible to join and use split members, such as a split part.

DESCRIPTION OF SYMBOLS 1 Interceptor 3 Portable anti-tank rocket 10 Flying aircraft body 10A Support body 10B Front body 10C Bottom body 11 Shaft body 12 Wiring 13a Head fastening part 13b Tail fastening part 20 Head attachment part 21 Centering part 22 Ring body 24 Connection fitting 25 Inflator storage section 30 Inflator 38 Fire tube body 44 Ignition section 50 Base member 51 Shaft body mounting section 59 Postponing apparatus storage section 62 Postponing apparatus 66 Firing mechanism section 76 Firing mechanism section assembly 78 Propellant chamber 99 Gas stop ring 100 Ignition electrode 101 Ignition electrode holder 102 Charging electrode 103 Charging electrode holder 104 Ignition harness 105 Connector 120 Head 130 Expanding body 131 Upper surface fabric 132 Lower surface fabric 140 Shape holding member 145 Towing members 146 and 147 Connecting portion 148 Towing member Connector 150 Outer cylinder 151, 152 Notch 153 Main groove 155 Sub groove 00 launcher

Claims (10)

The flying aircraft,
An inflatable body that is provided in the flying machine body and expands and expands with gas;
An inflator that is provided in the flying machine body and generates a gas for expanding and expanding the expanding body;
An outer cylinder that is provided in the flying machine body and stores the inflating body and the inflator;
A postponement device provided in the flying body for setting an operating time of the inflator;
A launching mechanism provided on the flying aircraft for generating propulsion energy to fly the flying aircraft ; and
With
The flying aircraft includes a support, a front body, and a bottom body,
The support has a connecting portion for connecting the front body and the bottom body,
The front body has an inflator storage portion for storing the inflator and a seat portion for attaching a head that forms an aerodynamically stable tip shape.
The bottom body includes a postponement device storage portion that stores the postponement device, and a launch mechanism portion mounting portion that attaches the launch mechanism portion,
The postponing device operates the inflator during the operation time during the flight of the flying aircraft body, expands and expands the expansion body with the gas generated by the inflator, and expands and expands the flight during flight by the expansion body that expands and expands. Separating the outer cylinder from the fuselage,
An interceptor characterized by colliding a rocket projecting from the flying body to the expanding body that expands and deploys to damage the rocket. The interceptor according to claim 1,
The inflatable body, when flying at high speed until meeting position before that also generate debris and jet from threats the safety, inflated with gas the inflator generates, interceptor, characterized in that the deployment. In the interceptor according to claim 1 or claim 2,
An interceptor comprising a pulling member between the expansion body and the flying aircraft body. The interceptor according to any one of claims 1 to 3 ,
The inflatable body is composed of a bag body formed by superposing two sheets of the same shape having a hole in the central portion and connecting the respective outer peripheral edge portions, and the two cloths included in the inflatable body have the above-mentioned After the flying machine body is inserted into the hole, the holes are fixed to the support body through a fastening portion at a predetermined interval, whereby the centers of the two fabrics are fastened to the support body. Interceptor characterized by that. The interceptor according to any one of claims 1 to 3,
The inflatable body is formed by overlapping two identically shaped fabrics having a hole in the center portion, joining the respective outer peripheral edge portions, and fastening between the fabrics with a shape holding member in order to control the shape at the time of expansion. consists of a bag made Te, said after said flying body is inserted into the hole, through the concluded portion the hole in the support at prescribed intervals two fabrics the expansion body has has An interceptor characterized in that the centers of the two fabrics are fastened to the support by fixing each of them . In the interceptor according to claim 4 or claim 5 ,
Wherein the expansion diameter of the expansion member, the ratio of the respective spacing of the fastening portion provided in the hole of the expansion body, (4: 1) to (1: 1) interceptor, which is a. The interceptor according to claim 5 ,
Interceptor said shape retaining member is made of aramid fibers or polyamide fibers, the spacing between the fabric, characterized in that the bore of the expandable body is the same as the spacing of the fastening portions provided respectively. The interceptor according to any one of claims 1 to 7 ,
The outer cylinder has a cylindrical shape,
A notch formed at both ends of the position where the cylinder is equally divided into two vertically;
A main groove formed between the notches;
A sub-groove formed on a circumference between the notches and having a depth smaller than the main groove;
An interceptor characterized by comprising : The interceptor according to claim 8 ,
The length of the cutout on the head side is 5 to 20% of the total length of the outer cylinder,
The length of the notch tail side is 30-50% of the total length of the outer cylinder,
The depth of the main groove is 30 to 60% of the wall thickness of the outer cylinder,
The interceptor is characterized in that a depth of the sub-groove is 20 to 50% of a thickness of the outer cylinder . In the interceptor according to claim 8 or 9,
The cut-out, interceptor, characterized in that it is filling by the insertion of the cover body of shape corresponding to the cutout.

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