JPH06221800A - Safety fuse for front part of gun barrel and shell equipped with the same - Google Patents

Abstract

PURPOSE: To simplify structure and reduce danger such as bad priming and a mistaken flying trajectory. CONSTITUTION: A guide element 32 disposed positionally fixedly in a cannonball, and an unlocking element 38 is disposed relatively with respect to the guide element 32, and the unlocking element 38 becomes movable in a flying direction upon passing through a region near the muzzle of a gun after the cannonball is shot from a shooting cylinder, whereby a through-hole 54 provided in the guide element 32 is released. In the through-hole 54, a safety locking element 52 is held for locking a priming actuation element 40 for priming a cannonball gunpowder 22 provided in the guide element 32. When the through-hole 54 is released, the safety locking element 52 is first advanced. As a result, the priming actuation element 40 is movable for actuate the cannonball gunpowder 22 upon arrival of the cannonball.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a low-turn or non-turn-type shell, particularly to a front fuselage safety fuse used for a subsonic range practice ammunition, and a bullet equipped with the front barrel safety fuse. .

[0002]

2. Description of the Related Art Such shells are fired from a projectile using a propellant charge. This shell is equipped with a fuse that causes the shell to detonate when it is loaded. Safety fuses are used during handling and in the vicinity of the front of the barrel, i.e. in the front of the barrel, so that the shell does not already detonate and endanger the operating personnel. When equipped with such a safety fuse, the ammunition is ready to fire only after exiting the front of the barrel.

Published German Patent Application No. 2119
The safety fuze disclosed in 574 can be used in low-turn or non-turn-type shells. This known safety fuse has a safety lock sleeve and a guide sleeve in a hollow chamber provided in the outer cylinder. These sleeves are fitted in and out of each other and are slidably arranged in the hollow chamber. A hammer with a firing pin is slidably guided inside the guide sleeve.
The hammer is fixed in position in the safety locking position by means of a first safety locking sphere with respect to the guide sleeve. The first safety locking sphere partially engages a constriction provided in the hammer and a through hole provided in the guide sleeve, respectively, so that a mechanical contact between the hammer and the guide sleeve is provided. It causes coupling. The guide sleeve, which has been preloaded by the compression coil spring in the direction opposite to the flight direction of the shell, is firmly held by the second safety lock sphere in the safety lock position. The second safety lock sphere is arranged in a through hole provided in the safety lock sleeve and partially engages a constriction provided in the guide sleeve. In this case, the second safety lock sphere is in contact with the wall of the hollow chamber. In the safety lock position, the safety lock sleeve
Since the through hole in which the first safety lock sphere is arranged is covered, the first safety lock sphere holds the hammer relatively to the guide sleeve. The safety lock sleeve is fixed in position by a safety lock pin before launching and in the launch barrel.

The above-mentioned German Patent Application Publication No. 21
In the configuration described in the 19574 specification, the safety fuze is ready for ignition in two stages. That is, in the first stage, the guide sleeve, the safety lock sleeve, and the hammer are combined to make relative movement to the shell in the hollow chamber based on the mass inertia, that is, the deceleration acting on the shell by the wind resistance. Move forward. In the first stage, the strength of this deceleration action must be high enough that the entire mass of the guide sleeve, the safety lock sleeve and the hammer, advanced in the flight direction in the shell, compresses the spring. At this stage, the second safety lock spheres arranged in the through hole provided in the safety lock sleeve and the constricted portion provided in the guide sleeve are in contact with the hollow chamber wall from the inside.
This is because the mechanical coupling between the safety lock sleeve and the guide sleeve is maintained. The forward movement of the entire mass of guide sleeve, safety locking sleeve and hammer is limited by the safety locking sleeve abutting the end of the hollow chamber located in the flight direction. In this position, the through hole provided in the safety lock sleeve faces the notch provided in the wall of the hollow chamber, and the second safety lock sphere enters into this notch. At this time, the second safety lock sphere advances from the constricted portion provided on the guide sleeve, and as a result,
The mechanical coupling between the safety lock sleeve and the guide sleeve is released. Due to the spring force of the compressed spring acting on the guide sleeve, the guide sleeve is returned with the hammer, which is subsequently mechanically coupled to the guide sleeve, in the direction opposite to the flight direction. However, for this purpose, it is a prerequisite that the deceleration force acting on the mass body composed of the guide sleeve and the hammer is smaller than the spring force. Certainly, the mass to be returned by the compressed spring is reduced by the amount of the safety lock sleeve, but in order to return the guide sleeve and hammer, the deceleration force acting on the shell has an appropriate value. Must have. If this deceleration force is too great, the guide sleeve and hammer will remain at the front end of the hollow chamber without the spring relaxing. After the spring is relaxed (second stage), the guide sleeve is moved backwards from the safety lock sleeve until the through hole provided in the guide sleeve is released. At this time, since the first safety lock sphere can advance from the through hole of the guide sleeve, the mechanical coupling between the hammer and the guide sleeve is released. The hammer, which is now free to move, is at the rear end of the hollow chamber and is located at the same position it had at the beginning of the first stage. From this stage, the shell or its fuse is ready to fire, so when the shell hits the target, the hammer moves forward based on its inertial force to detonate the charge. Subsequently, the guide sleeve and the safety lock sleeve are released from the coupling by unlocking the spherical body, and the guide sleeve moves rearward in the hollow chamber under the influence of the compression spring. In this case, the guide sleeve carries the hammer. Then, in the rear position of the guide sleeve, the opening of the safety locking sphere is freed so that the safety locking sphere is unlocked and releases the hammer. In this position, the hammer is free to move and the shell is ready to fire.

The above-mentioned known safety fuse has the following drawbacks. That is, in order to get ready to fire,
Multiple individual components, which are time-consuming to process, can be advanced several times.
A retreat movement must be carried out. This creates a risk of detonation failure. In addition, there is a risk that the trajectory of the flight will be misaligned due to the mass movement caused by the movement of the individual components. In order to obtain the function of the above-mentioned known safety fuze, the whole mass body consisting of the guide sleeve, the safety lock sleeve and the hammer is precisely matched with the spring force, and the spring force is composed of the mass body consisting of the guide sleeve and the hammer. It is necessary to harmonize with. Such harmony is also relevant to the deceleration experienced by the (practical) shell, especially during the flight phase. Such harmonization poses a problem due to the relatively short pre-barrel safety zone for subsonic practice shells. In particular, exercise shells used in mortars are designed to draw only short flight trajectories of a relatively steep parabola, and in this case, the safety range in front of the barrel is several meters to several tens of meters (for example, maximum 30 It is only in meters.

[0006]

SUMMARY OF THE INVENTION An object of the present invention is to have a simple structure and reduce the risk of detonation failure and flight trajectory deviation, and especially for subsonic (practice) shells. To provide a safety fuze that can be used for.

A further object of the present invention is to provide a shell equipped with such a safety fuse.

[0008]

In order to solve this problem, in the structure of the safety fuze of the present invention, a guide element that is fixedly arranged in the shell is provided to detonate the charge of the shell. Is provided in the guide element, the notch provided in the initiation and detonation element, and the through hole provided in the guide element. A safety lock element is provided, and in a state where the safety lock element is held in the notch and the through hole, the detonation element is fixed in position on the guide element, A spring is provided, and the detonation element is movable against the spring force of the restraining spring for the purpose of detonating the charge. , A lock / release element is provided, the lock / release element is arranged so as to be freely movable in the longitudinal direction, and the safety lock element is held in the through hole and the notch in the safety lock position. In addition, the locking / releasing element releases the through hole to advance the safety locking element, and thus the position is fixed by such a movement amount as to release the coupling between the initiation / explosion element and the guide element. The movable guide element is freely movable relative to the guide element.

Further, in order to solve the above-mentioned problems, in the structure of the cannonball of the present invention, a hollow chamber for accommodating the safety fuse for the front region of the barrel is provided in the bullet head, and the charge is accommodated in the hollow chamber. The guide element is fixedly arranged in the hollow chamber provided in the warhead,
An initiation / detonation element for detonating the charge of the warhead is provided, the initiation / detonation element is arranged in the guide element so as to be movable in the longitudinal direction, and a notch provided in the initiation / detonation element. There is provided a safety lock element arranged in the through hole provided in the guide element, and in a state in which the safety lock element is held in the notch and the through hole, the initiation and explosion motion element is Positionally fixed to the guide element, a restraining spring is provided, and against the spring force of the restraining spring, the initiation and explosion motion element is
It is movable for the purpose of detonating the charge and is provided with a locking / unlocking element, which is arranged so as to be freely movable in the longitudinal direction in the hollow chamber and in the safe locking position the safety A lock element is held in the through hole and the notch, and further, the lock / release element releases the through hole to advance the safety lock element, and by extension, the initiation and explosion motion element and the guide element. The hollow chamber can be freely moved relative to the positionally fixed guide element by an amount of movement capable of releasing the coupling.

[0010]

The front fuselage safety fuse according to the present invention is a guide element which should be fixedly positioned in the hollow chamber of the shell for the purpose of guiding the detonation element provided for detonating the charge. have. The initiation and detonation element is guided by the guide element so as to be movable in the longitudinal direction. That is, the initiation / detonation element can be moved in the flight direction (and the direction opposite to the flight direction) relative to the guide element unless locked by the positionally fixed guide element. . The locking of the detonator element is provided by a safety locking element. In the locked state, this safety locking element is located at the same time in the notch provided in the initiation / detonation element and the through hole provided in the guide element. The safety locking element is advantageously a sphere. A lock / unlock element is arranged on the side of the guide element opposite to the blasting element. This locking / unlocking element is freely movable in the longitudinal direction inside the hollow chamber of the shell, that is to say in the direction of flight of the shell and in the direction opposite to the direction of flight of the shell. The lock / release element covers the through hole provided in the guide element for the purpose of locking the initiation / explosion element to the guide element,
The safety lock sphere is held in this through hole and a notch provided in the initiation / detonation element. The through hole can only be released after the locking and unlocking element has completely passed by the through hole. When the through hole is released, the safety locking element can be advanced through the through hole, and the lock between the initiation and detonation element and the guide element is released. In the front fuselage safety fuse according to the present invention, the restraining force of the restraining spring acts on the initiation / detonation element. The hold-down spring holds the blast element in its locked position. That is, in this locked position, the safety lock element is partially arranged in the notch of the initiation / explosion element and partially in the through hole of the guide element. Both the guide element and the locking and unlocking element are preferably sleeve bodies. In this case, the blast element is arranged in the guide sleeve with radial play, and the safety locking sleeve (locking / unlocking element) is arranged so as to surround the guide sleeve with a certain play. The detonation element is
Elements that collide with a (detonation) charge (for example, a hammer or a firing pin) or have a (detonation) charge that collides with a fixed-detonation detonation element (for example, a firing pin) when a shell hits the target. It is the element that

The functional form of the front fuselage safety fuse according to the present invention will be described below.

If the shell is in the firing barrel,
The detonation element is locked to the guide element via the safety locking element. The lock / release element is located at the rear end of the movement path of the lock / release element when viewed in the flight direction of the shell. At this time, the lock / release element covers the through hole, and holds the safety lock element in the through hole and the notch provided in the initiation / detonation element. Upon exiting the launch tube, the shell is decelerated (negative acceleration) due to wind resistance. Due to the mass inertia of the locking / releasing element which is freely movable inside the hollow chamber, this locking / releasing element advances in the direction of flight of the shell in the hollow chamber. As in the case of the lock / unlock element, the detonation element also receives the kinetic force due to the deceleration received by the shell. However, due to the action of the restraining spring, the blast element remains in the locked position despite this kinetic force. This becomes extremely important. This is because when the initiation / explosion element moves forward in the flight stage in which the safety lock element is still located in the notch and the through hole, the safety lock element is released based on an appropriate configuration of the notch. This is because the lock may be released from the notch through the through hole. If the through-hole is still covered by a locking / unlocking element that also advances on the basis of kinematic forces, a safety locking element located in the through-hole is interposed between the initiation / detonation element and the locking / unlocking element. There is a risk of wedge stop. As a result, the locking / unlocking element cannot move forward any further.
When such a wedge stop occurs, the detonation element cannot move forward against the spring force of the restraining spring even when the shell hits the target. In order to prevent such a false function of the front fuselage safety fuse, if only the inertial kinetic force generated by the deceleration of the shell due to air resistance acts on the detonation element, set the restraint spring based on the setting. , The detonation element cannot move forward.

That is, in the vicinity of the muzzle of the launch barrel, that is, in the front region of the barrel, only the negative acceleration force generated by the braking of the shell by the air resistance as described above for the initiation and detonation element and the lock / release element If it only acts, the hold-down spring holds back the detonation element and only the locking and unlocking element is advanced. Lock·
As soon as the entire release element has passed by the through hole, the safety tube's front barrel safety lock is released immediately. Then, when the target is hit, the detonation element can move forward against the spring force of the restraining spring to detonate the charge of the cannon based on the inertial force generated by the powerful braking of the cannon that occurs at this time. On the other hand, when the locking / unlocking element has not yet advanced to the position where the through hole is released, for example, when the shell is hit on an obstacle located in the front area of the barrel, the firing / explosion motion is already started. When an extremely large force is applied to the element and the initiation / explosion element is advanced against the spring force of the restraining spring, as described above, when the element is advanced, Through the unlocked safety locking element, wedging is created between the blast element and the locking / unlocking element, which in turn locks the blast element. Therefore, the detonation of the shell charge is prevented.

As explained above, in the safety zone in which the front fuselage safety fuse according to the present invention prevents the firing of the charge of the shell, the lock / unlock element completely closes the side of the through hole. It is related to the time it takes to pass. This time is also related to the speed with which the locking and unlocking element moves in the hollow chamber of the shell relative to the guide element. Rock this time
The length of the release element (length in the flight direction of the shell) is also important. The speed with which the locking and unlocking element is moved during deceleration acting on the shell is again related to the braking strength of the shell, and thus the wind resistance of the shell and the mass of the locking and unlocking element. By appropriately setting the characteristic values of the influencing factors, it is possible to define the front region of the barrel, that is, the region in which the safety fuse according to the present invention prevents unintentional initiation of the ammunition charge.

In addition to the above-mentioned function when the restraining spring passes through the front region of the barrel, the following role is added over the entire flight time of the cannonball. That is, the hold-down spring must prevent movement of the detonation element, and thus detonation of the ammunition charge, when only a force acting by deceleration of the shell is applied to the detonation element. It also guarantees that the detonation element will not already advance before impact, even along the arc of the flight trajectory of the shell. When the shell moves along the downward arc of the flight trajectory, the lock / release element passes by the through hole in the flight direction because it has already exited the front region of the barrel.

On the basis of an appropriate structure of the notch provided in the blast element, at the time of hitting an obstacle in the front region of the barrel, at this time, via the safety lock element unlocked from the blast element, A strong wedge is created between the initiation and detonation element and the locking and unlocking element, thus providing safety during unexploded handling of this shell. That is, even if vibration or force is applied to the projectile when the projectile is subsequently processed, the projectile can no longer detonate the fuse.

In the safety fuse according to the present invention, the lock
The release element consists of only one component. This component must move (as it passes through the front barrel area), which shifts the safety fuse to the pre-fire position despite the front barrel safety lock. further,
Only one safety locking element is required to lock the detonator element to the guide element. Of course, more than one safety locking element can be used if more than one safety locking element and thus more through holes in the guide element are desired. However, only one safety locking element is sufficient.

In particular, the force acting on the lock / release element based on the earth's attractive force holds the lock / release element at its forward end in the direction of flight, as seen in the direction of flight, at which point the lock / release element passes through The hole is open. That is, once the lock / release element has passed by the side of the through hole, the lock / release element can no longer be retracted. Therefore, after the ammunition passes through the front of the barrel without unintentional landing, the fuze is ready to fire for the remaining trajectories of the flight trajectory.

As already mentioned, the pre-barrel safety fuse according to the invention is preferably used in low-rotation or non-rotation type shells, in particular for reaching subsonic velocities. Such ammunition is especially an ammunition ammunition, preferably an undercaliber ammunition ammunition with a dummy. A cylinder containing a propellant charge is inserted into this dummy. A warhead equipped with a front fuselage safety fuse according to the present invention is inserted into the cylinder opened in the flight direction. Such shells are fired in a parabolic flight trajectory and have a low flight speed.

At the beginning of the flight trajectory of such a shell, the shell is tilted with respect to the horizon in accordance with the firing angle of the firing barrel of about 30-80 °, preferably 45-75 °. During flight, the shell is decelerated due to air resistance.
Since the lock / release element is not exposed to this deceleration inside the shell, the lock / release element moves forward in the shell flight direction relative to the shell due to inertial forces. The detonation element is prevented from such forward movement by the restraining spring. The inertial force acting on the lock / release element is formed to be larger than the synthetic force based on the gravitational acceleration acting on the lock / release element in the direction opposite to the flight direction. In the front part of the barrel, first the end section of the locking / unlocking element on the side opposite to the charge covers the safety locking element, then after exiting the front part of the barrel, the end section closer to the charge is also safe Pass by the rock element. The hollow chamber and the locking / releasing element have appropriate dimensions so that the two end positions are surely taken. As soon as the safety locking element is free to move outwards, the safety fuse is ready for ignition.

When the shell moves along the arc of the parabolic flight trajectory, an earth attractive force acts on the lock / unlock element and the (explosive element) shell. Because the shell is based on aerodynamic drag and is not accelerated more strongly than the lock / unlock element (and detonator element) that does not experience this drag, the lock / unlock element is in the position it had previously taken, i.e. The side end section remains in contact with the front end of the hollow chamber.

The starting and explosive element is provided with a restraining spring,
Motion due to gravitational acceleration is blocked. That is, the kinetic energy imparted to the initiation and detonation element increases only after the impact of the cannonball. Moreover, this kinetic energy is much larger than the spring force of the restraining spring. Since the detonator element is unlocked (the safety locking element has already been unlocked from the detonator element through the through hole or is unlocked), the detonation of the shell charge takes place.

However, when the bullet is hit on the obstacle in the front region of the barrel, the measures already explained above are taken.

When the safety fuse is used in practice ammunition, especially in undercaliber practice ammunition for mortars, the fuming charge provided on such ammunition is placed at the rear or rear of the shell. It is desirable to be arranged. As a result, when the bullet hits the terrain where the bullet can partially enter the ground, the hitting of the bullet can be visually confirmed by smoke emission. In this case, the detonation element is advantageously an detonation element with detonation charges. When in motion, this detonation element moves in the direction of the fixed-position firing pin against the spring force of the restraining spring, which can ignite the detonation charge. The explosive element that advances in the flight direction when the shell is landed collides with a fixed firing pin, and this firing pin fires the explosive charge of the explosive element. Based on the detonation flame generated at this time, the fuming charge stored in the rear portion of the shell is detonated. That is, the detonating charge is located between the firing pin and the smoke-filling charge with the firing pin placed at the front end of the warhead and the smoke-filling charge at the rear end of the warhead. It is a translation.

If the shell with the safety fuse has not yet been fired, the locking and unlocking element is preferably prevented from unintentional movements which would cause the through hole to be released. For this purpose, in an advantageous embodiment of the invention, a safety locking element is provided which prevents the longitudinal displaceability of the locking and unlocking element when the detonator element is in the locked position. Such a safety locking member is advantageously a spring loaded safety locking pin. This safety lock pin jumps out of the shell due to spring preload when the shell exits the launch barrel or, in the case of undercaliber exercise ammunition, from the propellant barrel contained by the dummy . By such a safety locking member, it is advantageous if not only the locking and unlocking element is held in its safety locking position, but also the detonation element is held in its locking position. This prevents the motive / explosion element from moving longitudinally without the need for locking with a guide element as is provided via a safety locking element.

The notch provided in the blast element is preferably formed as a constriction with a circular cross section extending in the circumferential direction. In this case, the safety locking element is preferably designed as a sphere. The constricted portion surrounds the sphere over a part of the spherical outer surface. The other area of the sphere projects into the through hole of the guide element. Good mechanical coupling between the detonator element and the guide element through the safety locking sphere by partially surrounding the safety locking sphere, which is almost immovable with the locking and unlocking element covering the through hole Is obtained. When the shell hits an obstacle as it passes through the front of the barrel and thus the safety function of the safety fuse responds, the detonation element and the locking / unlocking element can be strongly wedged via the safety locking sphere. In another advantageous configuration of the invention,
In the direction opposite to the flight direction, the constriction is followed by the conical extent of the blast element. Through this conical ramp, the safety locking sphere is pressed against the locking and unlocking element more and more strongly as the forward movement of the detonation element proceeds. This results in a very strong wedge stop. The transition region between the waist and the conical region is preferably designed as a shoulder.
This amplifies the unlocking movement of the safety locking sphere due to the forward movement of the blast element.

[0027]

Embodiments of the present invention will now be described in detail with reference to the drawings.

A mortar 10 is shown in FIG. From the firing barrel 12 of the mortar 10, a cannonball 14 is fired along a parabolic flight trajectory 16.
The firing tube 12 is inclined with respect to the horizon by a firing angle of about 30-80 °, preferably 45-75 °. The cannonball 14 is a non-rotating type undercaliber practice cannonball equipped with a fin stabilizer, and is fired from a dummy provided with a propelling cartridge.

The shell 14 has a cylindrical hollow chamber 17 and a safety fuse 18 equipped with a safety device. This hollow chamber 17
Is located at the front end of the bullet head 20 when viewed in the flight direction (FIG. 2). The safety device has a guide sleeve 32 as a guide element. This guide sleeve 32
Comprises a safety locking element in the form of a sphere 52 arranged in the radial through hole 54 and a locking and unlocking element in the form of a safety locking sleeve 38. The safety locking sleeve 38 surrounds the guide sleeve 32 with a small radial spacing. The shell 14 has a smoke charge as the charge 22 to be detonated. This charge 22
Is located behind the safety fuse 18 and in the rear of the warhead 20 when viewed in the direction of flight. The front end of the charge 22 is a warhead 2.
It rushes into the 0 hollow chamber. The warhead 20 is a thick metal tube. The front end of this metal tube when viewed in the flight direction is
Shooting needle holder 2 formed as a fitting portion that can be press-fitted
It is closed by 4. The firing pin holder 24, which is also made of metal, has a rear end when viewed in the flight direction.
It has a cylindrical projecting portion 26 that is coaxially projected.
The protrusion 26 is press-fitted to the guide sleeve 32. As a result, the protruding portion 26 is attached to the guide sleeve 3
2, also serves as a bearing for the front end in the direction of flight. The guide sleeve 32 is a substantially smooth tube,
The rear end of this tube in the flight direction is in contact with the charge 22 or the holder 27 inserted into the hollow chamber 17.
The projection 26, which is arranged concentrically with the rest of the firing pin holder 24 and the warhead 20, thus centers the guide sleeve 32. The projecting portion 26 is formed with a hole 28 for the shooting needle 30 that has entered the guide sleeve 32. The thickness of the guide sleeve 32 is
The annular chamber 36 is set so as to remain between the inner peripheral surface 34 of the hollow chamber 17 and the guide sleeve 32. This annular chamber 3
6 has a small radial play with respect to the guide sleeve 32 and also has a radial play with respect to the inner peripheral surface 34 which limits the hollow chamber 17, so that the safety lock sleeve 3
8 has been inserted. The safety locking sleeve 38 has a length of about 1/3 of the axial length of the guide sleeve 32 and the annular chamber 36.

Inside the guide sleeve 32, a substantially cylindrical detonation element 40 is arranged for the purpose of detonation. The detonator element 40 is inserted in the guide sleeve 32 with play, and the detonator element 4 is
No. 0, the front side facing the flight direction, has a detonating charge.
The detonation element 40 has a constricted portion 42 that extends in the circumferential direction and has a circular cross-section, and the constricted portion 42 is followed by a region 44 that extends in a conical shape in the backward direction opposite to the flight direction. ing. This conical area 44 transitions to the outer peripheral surface 48 of the detonator element 40 via an outwardly curved, rounded portion 46. A shoulder 50 is formed in the detonator element 40 between the waist 42 and the conical area 44.

In order to safely lock the detonator element 40 in the rear (locked) position (FIG. 2), a sphere 52 is provided as a safety locking element. The sphere 52 is arranged in a through hole 54 provided in the guide sleeve 32. The diameter of the spherical body 52 is formed to be about twice the thickness of the guide sleeve 32. The radius of curvature of the spherical body 52 corresponds to the radius of curvature of the constricted portion 42.

When the safety fuse 18 is locked, the end portion 5 of the safety lock sleeve 38, which is rearward in the flight direction, is seen.
5 is in contact with the rear end of the annular chamber 36 in the flying direction, that is, the holding body 27. In this case, the end section 68 of the safety lock sleeve 38 facing the flight direction on the side opposite to the charge 22 and the holding body 27 has the through hole 54.
And the sphere 52 located in this through hole (FIG. 2). As a result, the sphere 52 becomes the detonation element 4
Since the ignition element 40 is fixed at the position in contact with 0, the detonator element 40 cannot move and is locked (locked position). For reasons of shell handling and transport safety, in order to hold the safety locking sleeve 38 in this locked position prior to firing, at least one radial through hole 58 in the bullet head 20 is provided. A safety lock pin 56 is provided. In this case, the safety lock pin 56 is preloaded outward by the compression coil spring 60. Since the length of the safety lock pin 56 is formed to be larger than the wall thickness of the warhead 20, the safety lock pin 56 projects into the annular chamber 36 of the safety fuse 18 in the safety locked state, and The end of the sleeve 38 on the side opposite to the charge 22 is in contact with the protruding safety lock pin 56.

The preparation of the function of the safety fuse 18 is automatically performed when the cannonball 14 is fired. In this case, before exiting the dummy, the safety fuse 18 is locked by the safety lock pin 56 holding the safety lock sleeve 38 in the safety lock position shown in FIG. Safety lock sleeve 38
It itself locks the sphere 52 in a locked position which locks the detonator element 40.

After the shell 14 leaves the dummy and the firing barrel 12, the safety lock pin 56 is ejected in the direction away from the bullet head 20 by the spring action of the compression coil spring 60, so that the safety lock sleeve 38 moves freely. It will be possible.
The shell 14 is braked due to air resistance. However, this braking does not act on the safety lock sleeve 38. Due to the inertial force based on the mass, the safety lock sleeve 38 moves forward in the flight direction A relative to the warhead 20. The length and mass of the safety locking sleeve 38, the air resistance, the weight and speed of the shell 14 and the firing angle are coordinated with one another, in this case the safety locking sleeve 3
It is designed that the ball 8 is completely moved by the side of the through hole 54 only after leaving the front area of the barrel to release the sphere 52. That is, since the safety lock sleeve 38 receives a kinetic force based on the braking applied to the shell 14, the safety lock sleeve 38 exits from the muzzle of the firing barrel 12 in the front region of the barrel (range B in FIG. 1). It is possible to move forward in the flight direction A over a length of about 15 m. In order to prevent the ball 52 from being wedged by the detonator element 40 and the safety locking sleeve 38, a compression coil spring 62 is provided between the detonator element 40 and the projecting portion 26 of the firing pin holder 24 inside the guide sleeve 32. Are arranged. This compression coil spring 62
Is supported by the detonator element 40 at one end,
The other end is supported by the circumferential shoulder 66 of the protrusion 26. The compression coil spring 62 blocks the relative movement of the detonation element 40 relative to the warhead 20 based on the inertial force generated when the shell 14 is decelerated during flight. As a result, no pushing force is applied from the detonation element 40 to the sphere 52, so the sphere 52 is located loosely in the constricted portion 42. Therefore, the detonation element 40 and the safety lock sleeve 38 are not wedged via the sphere 52, and the safety lock sleeve 38 can move freely beside the sphere 52 outside.

After the safety locking sleeve 38 has moved past the sphere 52, the safety fuse 18 is ready for firing. In this case, the individual components of the safety fuse 18 are shown in FIG.
Take the position shown in. The detonation element 40 can move toward the firing pin 30 with a force (for example, when landing) that exceeds the spring force of the compression coil spring 62. This is because the sphere 52 is released automatically or is pushed radially outward through the constriction 42 and the conical area 44 of the detonator element 40, thus releasing the detonator element 40.

When the shell 14 is loaded (FIG. 5), the detonator element 40 collides with the firing pin 30 with high kinetic energy due to its mass inertia, so that the firing pin 30 is placed in the detonation device 40. Ignite the medicine. The detonation flame generated at this time detonates the charge 22 arranged at the rear portion of the cannonball 14.

If the shell is inadvertently landed in the front region of the gun barrel (range B; the position of the safety lock sleeve 38 before being mounted as shown in FIG. 3), for example, in a cover or an obstacle, the safety lock is applied. Although the sleeve 38 has already been advanced (to some extent), the safety fuse 18 is not ready to fire. In this case, the arrangement shown in FIG. 6 results. Due to the impact, the detonation element 40 is moved forward in the flight direction A due to its high inertial force (due to the high relative acceleration of the warhead 20 with respect to the detonation element 40). The sphere 52 in contact with the partially circular constriction 42 is based on the motion of the detonation element 40,
It is extruded outwardly through the constriction 42 and the conical area 44 and is frictionally applied to the safety locking sleeve 38. The constriction portion 42 and the shoulder portion 50 are formed in the spherical body 5 by the initiation element 40 performing only a slight axial forward movement.
2, a large unlocking speed directed radially outward is produced. Front of the barrel safety and reliable function is an immovable guide sleeve 3
It is obtained by quick unlocking of the sphere 52 which is in contact with the inner peripheral surface section of the through hole 54 provided in 2. During the unlocking movement, the sphere 52 is pressed outwardly against the safety locking sleeve 38. Thus, the detonator element 40 is wedged with the safety lock sleeve 38 via the sphere 52. This wedge stop is so powerful that once the front barrel safety feature is introduced, it provides the safety of unexploded shells. Also, the sphere 52 is “embedded” on the one hand in the constriction 42 and the conical region 44 and on the other hand in the safety locking sleeve 38 on the basis of the large pushing force.

[Brief description of drawings]

FIG. 1 is a schematic diagram showing the flight trajectory of an exercise shell for an undercaliber mortar.

FIG. 2 is a vertical cross-sectional view showing the safety fuse for the front barrel region according to the present invention in the state of the starting stage II of the flight trajectory shown in FIG.

FIG. 3 is a longitudinal sectional view showing the safety fuse for the front barrel region according to the present invention in a range near the muzzle, that is, in a stage III state of the flight trajectory shown in FIG. 1 when passing through the front region of the barrel.

FIG. 4 is a longitudinal sectional view showing the front fuselage safety fuse according to the present invention in the stage IV state of the flight trajectory shown in FIG. 1 in the ignition preparation position after passing through the front barrel area.

FIG. 5 is a vertical cross-sectional view showing the front fuselage safety fuse according to the present invention in a final stage V state of the flight trajectory shown in FIG. 1 at the time of impact.

FIG. 6 is a longitudinal sectional view showing the safety fuse for the front barrel region according to the present invention in a state of the final stage VI of the flight trajectory shown in FIG. 1 after the voluntary landing in the front barrel region.

[Explanation of symbols]

10 mortars, 12 firing barrels, 14 shells, 17
Hollow chamber, 18 safety fuse, 20 bullet head, 22
Charge, 24 Shooting needle holder, 26 Projection part, 27
Holder, 28 holes, 30 firing pin, 32 guide sleeve, 34 inner peripheral surface, 36 annular chamber, 38
Safety lock sleeve, 40 detonator element, 42
Constricted portion, 44 range, 46 portion, 48 outer peripheral surface, 50 shoulder portion, 52 spherical body, 54 through hole,
56 safety lock pin, 58 through hole, 60, 62
Compression coil spring, 66 circumferential shoulder

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Alfred Hel Zirndorf Ai Benstraße 41 Germany Wiesenstrasse 56

Claims (29)

[Claims] 1. A front fuselage safety fuse used for low-rotation or non-rotation type shells, wherein a guide element (32) fixedly positioned in the shell (14) is provided, A detonation element (40) for detonating the charge (22) of the shell (14) is provided, and the detonation element (40) is arranged on the guide element (32), There is provided a safety lock element (52) arranged in a notch (42) provided in the actuating element (40) and a through hole (54) provided in the guide element (32). The safety locking element (52) has the notch (42) and the through hole (54).
In the state where it is held at, the initiation and detonation element (40) is positionally fixed to the guide element (32), and the restraining spring (62) is provided to resist the spring force of the restraining spring. The detonation element (40) is movable for the purpose of detonating the charge (22), and the lock / release element (38) is provided, and the lock / release element (38) can be freely moved. It is arranged so as to be movable in the longitudinal direction and holds the safety lock element (52) in the through hole (54) and the notch (42) in the safety lock position, and further, the lock / release element (38). ) Releases the through hole (54) to advance the safety lock element (52), and thus the initiation / detonation element (40) and the guide element (32). Movement amount as the coupling may releasing the position fixed the guide element (32)
A front fuselage safety fuse used for low-rotation or non-rotation type ammunition, characterized by being able to move freely relative to. 2. The locking and unlocking element (38)
2. The front fuselage safety fuse according to claim 1, wherein is formed as a safety locking sleeve surrounding the guide element (32). 3. A front fuselage safety fuse according to claim 1 or 2, characterized in that the guide element (32) is formed as a guide sleeve surrounding the initiation and detonation element (40). 4. The detonation element (40) is formed as detonation element with detonation charge,
4. The detonation element is movable in the direction of the fixed firing pin (30) against the spring force of the restraining spring (62) during movement in order to ignite the detonation charge. The safety fuse for the front of the barrel according to any one of the items above. 5. The locking and unlocking element (38)
Are held in a safety locking position by at least one safety locking member (56), whereby the safety locking element (52) is provided in the guide element (32) with the through hole (54), The notch (4) provided in the initiation and explosion element (40).
2) The safety fuse for the front barrel region according to any one of claims 1 to 4, which is held in 6. The safety locking member (56) limits longitudinal movement of the locking and unlocking element (38) while the locking and unlocking element (38) is in the safety locking position. And the safety locking member (56) is spring-elastically preloaded to automatically release the locking and unlocking element (38) on the basis of spring tension, whereby the guide element (32). 6. The front fuselage safety fuse of claim 5, which is adapted to provide a relatively free longitudinal movement relative to the. 7. The barrel according to claim 1, wherein the initiation and detonation element (40) has, as a cutout (42), a constriction of a circular transverse section extending in the circumferential direction. Safety fuse for the front area. 8. The front barrel region according to claim 7, wherein an expanded conical area (44) follows behind the constriction in the direction of application of the restraining force of the restraining spring (62). Safety fuze. 9. The outer peripheral surface (4) of the detonation element (40) is defined by the conical area (44) via an outwardly curved, rounded portion (46).
The safety fuse for the front barrel region according to claim 8, which has been moved to 8). 10. Front fuselage safety fuse according to claim 8 or 9, characterized in that a shoulder (50) is arranged between the waist (42) and the conical area (44). 11. The front fuselage safety fuse according to claim 1, wherein the safety locking element (52) is provided in the form of a sphere. 12. The front fuselage safety fuse according to claim 1, wherein only one safety locking element is arranged. 13. The detonation element (40) comprises:
13. A front fuselage safety fuse according to any one of claims 2 to 12, which is inserted into the guide sleeve with radial play. 14. Front barrel region according to any one of claims 2 to 13, wherein the safety locking sleeve is arranged to surround the guide sleeve (32) with radial play. Safety fuze. 15. A low-rotation or non-rotation type ammunition equipped with a front fuselage safety fuse is provided with a hollow chamber for accommodating the front fuselage safety fuse in the bullet head. A charge (22) is housed in the cartridge, and a guide element (32) fixedly positioned in the hollow chamber provided in the warhead is provided to detonate the charge (22) in the warhead. Is provided in the guide element (32) so as to be movable in the longitudinal direction, and the initiation and explosion element (40) is provided in the initiation and explosion element (40). There is a safety lock element (52) arranged in the cutout (42) and the through hole (54) provided in the guide element (32). While There held in said notch (42) the through-hole (54), the initiation trigger element (4
0) is fixed to the guide element (32) in position, and a restraining spring (62) is provided.
Against the spring force of 2), the initiation and explosion motion element (4
0) is movable for the purpose of detonating the charge (22) and is provided with a locking / unlocking element (38) which is free to move longitudinally in the hollow chamber. And the safety locking element (52) is retained in the through hole (54) and the notch (42) in the safety locking position, and the locking and unlocking element (38) is The safety lock element (52) is opened by releasing the through hole (54).
And then the explosive motion element (40).
And the guide element (32) can be freely moved in the hollow chamber relative to the position-fixed guide element (32) by a movement amount capable of releasing the coupling between the guide element (32) and the guide element (32). A low-turn type or non-turn type shell equipped with a safety fuse for the front of the barrel. 16. The locking and unlocking element (38).
Ammunition according to claim 15, wherein is formed as a safety locking sleeve surrounding the guide element (32). 17. A shell according to claim 15 or 16, wherein the guide element (32) is formed as a guide sleeve surrounding the detonation element (40). 18. The detonation element (40) comprises:
Formed as a detonating element with detonating charge, said detonating element resisting the spring force of said restraining spring (62) during movement in order to ignite the detonating charge,
A shell according to any one of claims 15 to 17, which is movable in the direction of the fixed firing pin (30). 19. The locking and unlocking element (38).
Are held in a safety locking position by at least one safety locking member (56), whereby the safety locking element (52) is provided in the guide element (32) with the through hole (54), The notch (4) provided in the initiation and explosion element (40).
A shell according to any one of claims 15 to 18, which is held in 2) and. 20. The safety locking member (56) projects into the hollow chamber to provide the locking and unlocking element (3).
8) limiting the longitudinal displaceability, said safety locking member (56) being spring-elastically preloaded to automatically release said locking and unlocking element (38) on the basis of spring tension. 20. The shell according to claim 19, which is thereby adapted to give a free longitudinal movement relative to the guide element (32). 21. A shell according to any one of claims 15 to 20, characterized in that the detonation element (40) has, as a notch (42), a circumferentially extending cross-section circular constriction. . 22. Ammunition according to claim 21, characterized in that an expanded cone-shaped area (44) follows behind the waist in the direction of application of the restraining force of the restraining spring (62). 23. The outer peripheral surface (4) of the detonation element (40) is defined by the conical area (44) via an outwardly curved, rounded portion (46).
23. A shell according to claim 22, which has been transferred to 8). 24. A shell according to claim 22 or 23, wherein a shoulder (50) is arranged between the waist (42) and the conical area (44). 25. A shell according to any one of claims 15 to 24, wherein the safety locking element (52) is provided in the form of a sphere. 26. A shell according to any one of claims 15 to 25, wherein only one safety locking element (52) is arranged. 27. The detonation element (40) comprises:
27. A shell according to any one of claims 16 to 26, which is inserted in the guide sleeve with radial play. 28. A shell according to any one of claims 16 to 27, wherein the safety locking sleeve is arranged to surround the guide sleeve (32) with radial play. 29. The restraining spring (62) is embodied as a compression coil spring, the compression coil spring being supported at one end thereof on the detonation element (40) and at the other end. 29. A shell as claimed in any one of claims 15 to 28, which is supported on the inner surface of a wall which bounds the hollow chamber of the head of the bullet.