KR101879944B1 - Concussion fuse that ensures alignment between armoring part and firing part - Google Patents

Abstract

Disclosed is a shock fuse wherein warping alignment between the entire length of the delay chamber and the sinker is ensured. The present invention relates to a mechanical shock tube for preventing ignition failure phenomenon in which an ignition alignment is changed due to an impact of a projectile upon impact of a projectile, thereby preventing the impact force of the sinking needle from being transmitted to the primer in the recharging rotor. (37) formed at the entrance of the detonation path and a sunken guide pipe (36) disposed behind the loading rotor and protruding forward at the time of impact and entering the guide pipe entrance hole, and coaxial with the sunken guide pipe, And a sunk needle (24) which is delayed after the impact and protrudes forward in the sunken guide pipe.
Fast and fast fitting engagement between the guide tube inlet and sunken guide tubes ensures that the sunken vessel will strike the priming tube 32 even under severe conditions, such as collapse of the loading base 16 and buckling of the loading rotor 30, It is possible to induce a definite ignition of the warhead (high explosive) regardless of the time when the sinking is released and the collapse of the entire length of the tunnel.

Description

[0001] The present invention relates to a collision fuze,

The present invention relates to a mechanical shock absorber, which prevents the ignition failure phenomenon, in which erroneous alignment is changed by the impact of the impact of the projectile when the target is hit by the impact of the projectile so that the impact force of the impactor is not properly transmitted to the primer in the recharging rotor.

The mechanical impact fuse is structured to trigger a primer by directly transmitting a collision impact applied to the fuse to the fuse or triggering the primer due to the reaction of the spring when the fixed state is released due to a collision impact.

Apart from the triggering of the sinkhole, there is a delayed load that safely protects the gunpowder from the attack of the sinkhole before launch.

The delayed loading part is a disassembled, independent modular part. It is also called safety loading device. It keeps a straight line of detonation path that connects the primer-connecting gunpowder-ignition charge before the launch of the projectile and keeps the time when the projectile leaves the certain safety distance (Delayed) rotation to align the detonation path so that it coincides with the declination.

With the delayed loading completed in the ignition alignment, the sinkhole is positioned so that it immediately strikes the primer at the same time as releasing (protruding).

If the target is a light glove target that can be penetrated and the internal explosion after the penetration is advantageous to freeing the target, then the impact sensing head is set not to retreat to a relatively small penetration impact, and instead a shock ) Causing the sensitive means to release the latch slightly later.

Accordingly, the projectile may penetrate the glove and cause a delayed explosion in the internal space of the target. However, as a precondition, the aligned detonation path of the delay device must be firmly maintained irrespective of the projecting point of the sinker.

Most of the artillery shells equipped with the mechanical shock tube are constructed of a front fuse-rearward warhead structure in which a new tube is mounted at the head of the projectile, and the triggering action of the impact detection head formed at the front of the new tube is synchronized with the triggering operation.

Since the shock tube for a steel wire rotary shell is vigorously rotated (spinned) after firing, it is equipped with a delayed loading device of a disk rotating structure using centrifugal force. Because of this, all of the delay elements in the housing of the new tube and the sinking part are made of a wide and flat laminated structure, so that they can respond stably to shocks at various angles and sizes, such as slanting.

On the other hand, projectiles with forward-rearward fuselage structures are widely used, such as locust-controlled rockets, rockets for large-scale naval ships, launchers equipped with all types of man-made gunships and anti- This is the case here.

The shock tube used in the wing stabilization projectile such as a rocket is equipped with a retarding device which is operated only by a setback force because the loading rotor can not be driven by the centrifugal force.

(1) Korean Unexamined Patent Application Publication No. 10-2016-0082027 Dual Safety Loading Device and Loading Method Thereof (2) US registered patent US 4242963 Delay fuse for spin-stabilized launch vehicle (3) US registered patent US 4535695 Spin-stabilized launch vehicle fuse (4) US registered patent US 8443728 New tube for spin-stabilized launch vehicle with self-expanding function

The retraction inertia-actuated retarding device mounted between the sinking portion of the main housing of the new pipe and the ignition charge is described in detail in the prior art documents (1) and FIG. The semi-moon-shaped loading rotor has eccentric center of gravity position on the rotating shaft, and the heavy part of the rotor is rotated by the backward inertia, and it rotates appropriately by the delay gear. In a straight line.

However, considering the fact that the long, light and thin fuselage of shells compared to shells does not have enough structural strength of the area around the warhead and the new tube, it is considered that when the target is hit, the guiding element in front of the projectile, It is difficult to see that the detonating fuse will always maintain a stable aerodynamic alignment until the moment it penetrates the target, collapses after the penetration failure, or bounces back to the slope.

3E shows an actual model of a safety loading device, i.e., a delay loading device, for a rocket currently in use. This model is also referred to as SAD (Safety Armoring Device). The upper picture shows the state before the loading rotor is not rotated, and the lower picture shows the case where the loading rotor is destroyed after being rotated and aligned, And a large part of the structure collapsed.

If we examine the damage condition after the lower ignition test, the combination of the loading base for fixing the loading rotor and the delay gearbox for the side structure is not structurally strong. Therefore, the probability that the loading rotor will stay in a straight line state It is not so high.

In particular, a low-cost guided rocket that uses the above-mentioned delay loading device frequently buckles or collapses the fuselage during the collision, and thus the warhead and the fuselage shake momentarily. At this time, the impulsive force applied to the new pipe is not rapid in its action speed, and may not be uniform and may cause buckling or buckling of the loading base, causing the loading rotor to fall to the side There is a high possibility.

Such non-uniform and non-rapid impacts are more pronounced in post-penetration retarded situations where the sinking protrudes forward at least a few milliseconds later.

In other words, the delayed trigger condition, in which the sinkhole should protrude a little later, is more likely to cause unwanted buckling or breakage between the entire length of the delay chamber and the sinker, which can lead to failure and failure of the fuse.

This may be because the fuselage length of the projectile is long, the flight speed is not very fast, and the strength of the fuselage is also low. Basically, after the primary impact is applied from the front of the projectile, This is due to the time difference and the order of impact, the order in which the impact is coming in, and the direction in which the impactor goes out, which are opposite to each other. Unless the sinker retreats from the front impact and hits the primer in the rear loading rotor naturally, It is a source of instability that must be caused.

SUMMARY OF THE INVENTION It is an object of the present invention to provide a shock absorber capable of ensuring reliable ignition irrespective of a disengagement timing of a sinker in a new ship equipped with all of a retractable inertia actuated delay line having a high possibility of undesired buckling to be.

It has been found in this invention that the most effective method of solving the presented problems is to maintain a definite straight path between the sinkhole and the primer, even if some of the structures are tilted and tilted, rather than the overall structural reinforcement of the entire delay field, .

The high-explosive gunpowder is finally detonated by the explosion of the explosive charge (12). The explosive charge 12 disposed at the foremost position, that is, the topmost position, of the new pipe main housing 10 is filled with a relatively large and large volume as compared with the other explosive gases.

The coupling gun (33), which amplifies the initial explosive force of the primer (32) in the situation where the delay loading part begins to collapse due to the impact impact, is slightly different from the ignition charge, but once it explodes, It can be excited normally and stimulated.

The primer 32 and the coupling agent 33 are arranged in a proper alignment between the dimple 24 and the primer 32 in consideration of the fact that the loading rotor 30 in the form of a half disk is surely located on the coaxial line, Is the key to success.

In other words, in any sudden situation, it is a key factor to determine the reliability of overall explosive alignment, whether the pointed tip is able to beat accurately and precisely without deflecting a small primer.

In order to secure the above-described structural reliability, a sunk guide tube (36) sensitive and rapidly protruding from a low impact condition, a sunk needle (24) protruding from the sunk guide tube, And a charging rotor 30 having an induction tube receiving hole 37 for quickly bringing the sunk guide tube 36 and the sunk needle 24 into close contact with the primer tube 32, All the delay fields were constructed.

The sunken guide pipe 36, which is susceptible to rapid protrusion from a low impact condition, can be integrally formed with the sunken outer ring 20 to obtain the necessary inertia, And is initially retracted and fixed by an outer elastic contact spring 21 of appropriate elasticity so as not to protrude only to a minimum change in inertial force.

The primer tube 32 in the loading rotor 30 should be placed deeper into the evacuation path as much as the protrusion amount of the priming induction tube and the proper gap between the priming induction tube and the primer should not be unnecessarily stimulated, The area of contact of the tube with the primer and the amount of impact applied to the primer should be adequately controlled.

Of course, the sinkhole 24 should protrude more than the sinkhole guiding tube in order to strike the primer strongly during the final impact trigger.

For reference, there is a document (4) that introduces a spin-mounted fuse having a plunger as a configuration that looks more like a sinking guide tube (36).

This is a structure that pulls out the sinking pin embedded in the loading rotor and loads it backward, but the projectile deviates from the target, and the spin of the body of the new body is eventually released, This is not a structure for fixing the loading rotor.

In the structure similar to that of the present invention, there is a guiding structure between the plunger and the inlet passage of the inner housing surrounding the plunger and the charging rotor. However, since the passage of the inner housing does not catch the rotation caused by the rotation or impact of the charging rotor, (4) is collided backwards from the rear explosive charge side, it is difficult to ensure a clear alignment of the primer and the primer in the loading rotor.

In the following, drawings and detailed explanations specifically supporting the problem solving means of the present invention, which is different from Document (4), are presented.

The shock fuse according to the present invention is based on the quick action of the inertia-sensitive ring connected to the sinking guide tube, assuring a reliable blow between the primer and the sinker even in a severe situation where collapse of the loading base upon buckling and buckling of the loading rotor is proceeding, It is possible to induce a definite ignition of the warhead (high explosive) irrespective of the timing of disengagement of the sinker.

Therefore, it is possible to maintain the entire length of the delay chamber and the main housing at a compact size and weight in a wing stabilized projectile with a light weight, and even in the case of a mechanical shock-absorbing mechanical fuse having a relatively weak delay- It is possible to maximize the delay detonation ability before and after penetration of the warhead without deterioration.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is an external perspective view of a shock crown of the present invention and a sectional view of a projectile to which the present invention is applied; FIG.
FIG. 2A is an overall perspective view showing a major part of the impact shock tube of the present invention in module units. FIG.
FIGS. 2B to 2D are perspective views illustrating an explosive alignment securing structure of all the delay elements according to operation steps.
Figs. 3A to 3B are overall exploded views of a shock fuse tube according to the present invention. Fig.
Figs. 3C to 3D are detailed exploded views of all the delay fields. Fig.
FIG. 3E is a photograph showing the state before and after the initiation of the entire conventional delay line. FIG.
Fig. 4 and Fig. 5 are overall cross-sectional views of the impact crown of the present invention. Fig.
FIG. 6 is a view showing a step-by-step example of the decanting operation of the present invention in a low-impact throughput situation.
FIG. 7 is a view showing a step-by-step view of the sinking operation of the present invention in a high-impact condition;
Figs. 8A to 8B are perspective views showing the pretreatment preventing structure of the entire length of the delay field in operation steps. Fig.
8C is a cross-sectional view that intuitively illustrates the sinking operation of the present invention in low shock and high impact conditions;

BRIEF DESCRIPTION OF THE DRAWINGS The above and other objects, features and advantages of the present invention will be more apparent from the following description taken in conjunction with the accompanying drawings, in which: FIG.

However, in the embodiments described below, the components expressed in the specific terminology and the combination structure thereof do not limit the technical idea that is included in the present invention in a comprehensive manner.

FIG. 1 shows a cross-sectional view of a 130 mm ground-based rocket to which the impact fuse of the present invention can be applied.

Rockettan is a representative weapon to fire firepower that is available to the enemy with the enemy.

Although there are large rockets that use the inertial induction method as in the MLRS, the rocket car in Fig. 1, to which the mechanical fuse is applied, is effective in the image-to-air active induction method using the infrared seeker. For this reason, the front part of the rocket is equipped with a video tracking sensor and a control wing guide mechanism, which are completely collapsed when the target is hit, and a central warhead containing high explosives penetrates directly into the target (in the case of light gloves) .

The initial velocity of the rocket in Fig. 1 is usually more than 500m per second, and the acceleration of the launch is more than 40G. The acceleration variation is about 5G ~ 15G due to irregularities in propulsion and irregularity of air resistance during flight. Therefore, the new pipe mounted here should operate at 40G, and the sensitivity of the impact response structure should be insensitive to shocks of at least 20G.

Almost all rocket launchers, including Figure 1, have a wing-stable flight pattern that does not rotate. Therefore, the safety armoring device (SAD) usually has a loading rotor which is not driven by the centrifugal force due to the spin of the projectile but operates as a rearward inertia due to forward movement after the launch and rotates about a half turn.

FIGS. 2A to 2D are perspective views showing a main part of the shock-absorbing tube of the present invention in module units or only a partial cut-away view of the core structure of all of the delay elements.

Figs. 3A to 3B show the overall exploded view of the impact crown of the present invention, and Figs. 3C to 3D show detailed exploded views of the entirety of the delay field.

FIG. 3E is a photograph of a state before ignition alignment and a state after ignition (flared and collapsed) of all the conventional delay fields.

Fig. 4 shows an entire cross-section cut along the operation surface of the safety pin 14, and Fig. 5 shows the entire cross-section taken along the operating surface of the declination fixing ball 27 and the inner layer sensitive restraining ball 26. Fig.

FIGS. 8A to 8B show the structure for preventing the puncture and protrusion of the entire length of the delay line according to the operation steps.

Detailed operation and operation of the present invention will be described with reference to Figs. 2 to 4 as a whole.

By way of reference, the components directly coupled to the main housing 10, in particular the fastening structure, such as the housing and the base,

And components that enter the fusebox housing 18 are shown at 20. These are the components involved in the operation of the cockpit.

Also, the components involved in the erection alignment and prevention of erroneous firing between the sinking part and the loading rotor around the entire length of the delay line are shown by reference numeral 30. All components denoted by the reference numerals are organically coupled to implement the final technical idea of the present invention.

The explosive charge 12 is disposed at the top of the main housing 10, that is, at the forward end to receive the impact shock. The sinking portion and the delayed loading portion are configured to ignite the explosion charge 12 at a desired point.

The delayed loading part is a module disposed behind the explosion charging device 12 and keeps the detonation path leading to the primer 32, the connecting gunpowder 33 and the explosion charging device 12 before the launch of the projectile, (30) to align the detonation path in a straight line after a predetermined time.

The loading rotor 30 is a core configuration for performing ignition alignment with delayed rotation by a delay gear. Inside the charging rotor, an explosive path is formed in which the priming tube 32 is mounted on the inlet side and the connecting powder 33 is mounted and fixed on the outlet side.

The charging rotor 30 is fixed in an unrotated state by the rotor locking weight 34 before firing.

When the rotor lock weight 34 is lowered by the firing inertia, the load lock rotor 39 is freely rotatable and mechanically connected to the load lock rotor 30 so as to be eccentric, And is rotated counterclockwise on the basis of FIG. 8A.

In addition, the charging rotor 30 is further provided with a sunken blocking protrusion 31 for preventing the sunken guide pipe 36 or the sunken needle 24 from protruding in a state where the sunken rotor is not rotated.

The decoupling blocking projection 31 is formed as a part of the charging rotor next to the entrance of the detonating path to prevent the projection of the decentering induction pipe 36 or the declination needle 24 in a state without delayed rotation.

If the sinkhole is fixed very steadily, it may not be necessary to construct such a shutoff projection, but if it is a sinkhole that performs delayed triggering and instantaneous triggering of intelligent operation under low and high impact conditions, as shown in Figures 6 to 7 It is also necessary to use a small-sized guide tube that easily protrudes forward even with a small change in inertia. Under these conditions, the blocking protrusion effectively blocks the detachment of the detachment pipe and consequently prevents the unwanted protrusion of the detachment.

The outer surface of the sunk blocking rotor 31 abutting against the sunk guide pipe 36 is formed so as to coincide with the outer circumferential surface of the charging rotor 30. In order to minimize the reverse rotation inertia increase of the charging rotor 30, The inner surface toward the center can be formed by denting.

It is necessary to add an inertial mass to the forward rotation side of the charging rotor in order to cancel the reverse rotation inertia increase amount caused by the deceleration blocking projection. This can be solved by increasing the weight of the rotation lock pin 38. The rotation lock pin 38 is disposed on the opposite side of the declination blocking protrusion 31 with respect to the center of the charging rotor so as to increase the forward rotation inertia increase amount such as the reverse rotation inertia increase amount of the declining blocking protrusion, .

Figures 2c-2d and Figures 8a-8b will be discussed. An induction tube inlet hole 37 is formed at the evacuation path entrance of the charging rotor 30. [ This serves to prevent a gap between the ignition path and the dimple 24 during a collision impact by engaging with the introduced dimple induction pipe 36 and is formed at a depth equal to or greater than the projecting height of the dimple induction pipe 26.

A primer 32 is mounted and fixed in the induction tube inlet 37 in the detonation path and a connecting gun powder 33 is fixed to the opposite side of the induction tube inlet.

If the front of the warhead is designed to be less rigid, the incidence of puncture and delayed loading will increase when hit.

In the present invention, the auxiliary induction pipe (36) is additionally formed in the outer sensitive ring (20) in the recessed portion housing (18), so that the bypass guide pipe (36) It is possible to make a state in which it has been inserted into the body 37. Therefore, it is possible to delay the detonation more freely in a low shock impact situation, and it is less likely that the ignition alignment is changed even in a high impact impact situation.

8A, when the charging rotor 30 is in an unrotated state, the launcher detachment safety pin 14 is inserted into the guide tube inlet hole 37 to constrain the rotation of the charging rotor.

FIG. 6 is a cross-sectional view showing only the connecting portion housing 18 in FIG. 5, FIG. 6 is a cross-sectional view showing the state of the present invention in a low- In a step-by-step manner.

Fig. 8 reflects the operation of Figs. 6 and 7 in Fig. 5, intuitively showing the sinking operation of the present invention in low shock and high impact situations.

The internal structure of the sunken housing 18 will be described with reference to FIGS.

The only components that can come out of the fuselage housing 18 are the fuselage guide tube 36 and the fuselage 24, all of which are disposed within the housing. In the present invention, the direction in which the sunk guide tube 36 and the sunk needle 24, which are integrally formed as one part of the outer sensitive ring 20, protrude outward from the sunk housing part is defined as forward and the opposite direction is defined as the backward direction do.

The outer sensitive ring 20 is disposed in the interior of the sunken housing 18 so that when a collision impact (backward impact) from the front is applied, the outer sensitive ring 20 responds to a change in forward tilting acceleration and advances to inertia due to its own weight without the aid of spring elasticity do.

As a result, the sunk guide tube 36 formed integrally with the outer sensitive ring 20 protrudes toward the charging rotor 30 when it is seated, and is drawn into the guide tube inlet hole 37.

First, the sunk needle 24 is coaxially disposed with the sunk guide tube 36, and is projected toward the sunk guide tube immediately after an impact or delayed after the sunk.

Once the sinking needle 24 is restrained by the outer sensing ring 20 and is released according to the advancement, it is fixed to the inner sensing ring 22 and is released in accordance with the forward or retreat. The decelerating spring 25 is set to be very strong, and once it is in the unlocked state regardless of the magnitude of the impact impact force, the decelerating spring 25 is strongly advanced forward.

The inner sensitive ring 22 is restrained by the outer sensitive ring 20 and released as it advances to relatively advance or retreat between the inner surface of the intermediate housing 28 and the outer surface of the involute housing 29 .

Here, the reference of the relative advancement or retreat is the sunken housing 18. In other words, the movement of the inner sensitive ring 22 with respect to the outer sensitive ring 20 can be seen as if the inner sensitive ring only retracts or does not advance at least. However, when viewed from the sunken housing (18), the inner sensitive ring (22) slightly advances in a low impact condition and retreats within a short impact condition, and advances only in a high impact condition.

Specifically, the inner sensitive ring 22 is constrained to the outer sensitive ring 20 by the inner sensitive restraining ball 26, and also fixes the sunk needle 24 to the sunk fixing ball 27.

Here, the term "restraint" means a state that can be slightly moved forward and backward but not completely released. Of course, the meaning of fixed is the opposite of disarming. In other words, only the sunk needles 24 are fixed and releasable (triggered), but the inner sensitive ring 22 is in a state in which it can slightly move back and forth even if it is restrained by the inner sensitive restraining ball 26.

This very subtle part is that the inner sensing ring 22 of the present invention ensures a long delay time from the short advance-retreat to the detonation, or the outer sensing ring is advanced before releasing the restraint, This is the reason why it is possible to show a short delay time which can be triggered (middle diagram in Fig. 6, middle diagram in Fig. 7).

The outer contact spring 21 is disposed in a compressed state between the outer contact ring 20 and the dimple housing 18 and the inner contact spring 23 is disposed between the outer contact ring 20 ) And the inner sensitive ring (22).

In this case, if the outer contact spring 21 is disposed in a weakly compressed state so as to support only irregular small inertia acting during flight of the projectile, the inner contact spring 23 overcomes the collision impact force at the delay triggering and retreats the inner contact ring 22 It is necessary to be arranged in a strongly compressed state so that the two sensitive rings can be pushed out immediately without oscillation in the event of a severe impact.

However, since the inner urging spring 23 is stronger in the initial compression state than the outer urging spring 21, the absolute urging force by the spring does not have to be stronger.

7, the inner contact spring 23 is not completely relaxed by the inertia of the inner contact ring 22, and the three structures of the outer contact ring-inner contact spring-inner contact ring are formed as one integral type You have to move forward as if it were a configuration. It is the outer contact spring 21 that receives this inertia when the one integral configuration advances. If the outer contact spring is compressed too rapidly, advance action can not take place in advance of the inner contact ring (until the outer contact ring is released), which makes it difficult to instantly trigger the contact without delay in a high impact condition.

Therefore, the outer contact spring 21 is set to a lower spring constant and a higher spring capacity than the inner contact spring 23, and the outer contact ring 20 is connected to the inner contact ring 20 in order to act as a softer spring than the inner contact spring. (22). ≪ / RTI >

The core operation of FIG. 6 will be reviewed again.

The inner sensitive ring 22 is retracted relative to the outer sensitive ring 20 or the retracted position relative to the facing housing 18 when the outer sensitive spring 21 is compressed and the inner sensitive spring 23 is relaxed in the low impact condition, And then set back to advance.

Thus, the inner sensitive ring 22 can be freely detached for a fairly long time (at least 6 milliseconds) without releasing the immobilizing pin 27.

To this end, the advance distance of the outer sensitive ring 20 for restraining the inner sensitive ring 22 is set shorter than the advance distance of the inner sensitive ring 22 for releasing the sunk 24, so that the inner sensitive ring releases the sunk The outer sensitive ring must first unfasten the inner sensitive ring before doing so.

The sinkhole 24 is disposed coaxially with the sinkhole guide pipe 36 and protrudes forward from the sinkhole guide tube immediately after the collision or after the collision.

As a result, the dimple 24 is fixed to the inner sensitive ring 22 and is released in accordance with its advancement or retraction. At this time, the forward distance of the dimple 24 needs to be set longer than the advanceable distance of the outer sensitive ring 20 .

The core operation of FIG. 7 will be reviewed again.

Fig. 7 shows the state in which the outer contact spring 21 is in compression and the inner contact spring 23 is in an unstressed state in a high impact condition. In this state, the advance distance of the inner sensitive ring (22) for releasing the sunk needles (24) should be set shorter than the total advanceable distance of the outer sensitive ring (20).

Accordingly, the three components described above move for a moment during the moment as if they are a unitary structure, and then the inner sensing ring 22 releases the dimple fixing ball 27 so that it can be released for a short time (2 to 3 milliseconds Within a few seconds).

The operation of Figures 6 and 7 is shown more intuitively in Figure 8c.

It should be noted that the outer and inner sensing rings 20 and 22 are disposed between the outer sensing spring 21 and the inner sensing constrained ball 26 It is preferable to maintain a state in which they are in close contact with each other before the impact. This helps to more reliably move the three components together in a high impact condition and to prevent the bad situation in which the outer sensing ring 20 moves due to irregular inertial changes during flight.

The technical idea of the present invention has been described above with reference to specific embodiments. It should be understood that the technical idea of the present invention should be construed on the basis of the contents described in the following claims rather than the technical interpretation category of the embodiment.

For reference, the present invention is best suited for a mechanical shock tube having a percussion structure in which a new tube is arranged behind the shell and has a percussion structure by advancing the shell in the direction of impact, but is not necessarily limited thereto, It can be effectively applied to most electronic fuses containing the possibility of collapse of the structure.

10: main housing 11: main base
12: Explosive charge 13: Safety pin cap
14: Release launcher safety pin 15: Firing pin
16: loading base 17: fingertip gap regulating pin
18: sunken housing 19: bottom plate
20: outer sensing ring 21: outer sensing spring
22: inner contact ring 23: inner contact spring
24: declination 25: declination spring
26: inner side restraining ball 27:
28: intermediate housing 29: sunken housing
30: Loading rotor 31: Decoupling protrusion
32: Primer 33: Connective Powder
34: rotor lock weight 35: delay gear
36: Light guide tube 37: Induction tube inlet tube
38: Rotation lock pin

Claims (7)

An ignition charge placed at the forward front subjected to impact impact (12);
A loading rotor (30) disposed behind the explosive charge (12) and performing ignition alignment with delayed rotation due to firing inertia;
An induction tube inlet hole 37 formed at the evacuation path entrance of the loading rotor 30;
A sunken guide pipe 36 disposed at the rear of the loading rotor 30 and protruding forward immediately after being thrust and drawn into the guide tube inlet hole 37;
And a sunk needle (24) disposed coaxially with the sunk guide tube (36) and projecting forward of the sunk guide tube,
The induction pipe inlet hole 37 is formed at a depth greater than the protrusion height of the light guide pipe 36,
A primer (32) is mounted and fixed inside the induction tube inlet in the detonation path,
A connection gun (33) is mounted and fixed on the opposite side of the induction tube inlet in the detonation path,
An outer sensing ring 20 disposed in the interior of the sinker housing 18 and advanced by a collision impact from the front;
Further comprising an inner sensing ring (22) restrained by the outer sensing ring (20) and released from restraint upon advancement thereof and relatively advanced or retracted relative to the facing housing (18)
The sunken guide pipe (36) is formed integrally with the outer sensitive ring (20)
The sunk needle (24) is fixed to the inner sensitive ring (22) and is released as it is advanced or retracted. delete delete The method according to claim 1,
The advanceable distance of the sunk needle 24 is set longer than the advanceable distance of the outer sensitive ring 20,
An inner sensitive spring (23) is arranged in a compressed state between the outer sensitive ring (20) and the inner sensitive ring (22) to act to push them against each other,
An outer contact spring 21 set to a lower spring constant and a higher spring capacity than the inner contact spring 23 is disposed between the outer contact ring 20 and the lock housing 18, . 5. The method of claim 4,
The inner sensitive ring 22 is restrained by the inner sensitive restraining ball 26 to the outer sensitive ring 20 and is fixed to the sunk fixing ball 27 by the sunk fixing ball 27,
The advance distance of the outer sensitive ring 20 for restraining the inner sensitive ring 22 is set shorter than the advance distance of the inner sensitive ring 22 for releasing the sunk 24,
The inner sensitive ring 22 may be retracted relative to the outer sensitive ring 20 or may be retracted relative to the facing housing 18 when the outer sensitive spring 21 is compressed and the inner sensitive spring 23 is relaxed. And then,
The advancing distance of the inner sensing ring 22 for releasing the declination needle 24 when the outer sensing spring 21 is in compression and the inner sensing spring 23 is in an un-relaxed state, 20). ≪ / RTI > The method according to claim 1,
Wherein the launcher detachment safety pin (14) is fitted into the induction pipe inlet hole (37) when the charging rotor (30) is in an unrotatable state, thereby restricting the rotation of the charging rotor. 5. The method of claim 4,
Wherein the charging rotor (30) is further provided with a deceleration blocking projection (31) for preventing the projection of the deceleration induction pipe (36) or the deceleration needle (24) from being delayed and rotated.

Images