JP2009097763A - Missile - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a missile facilitating loading into a launcher even when it is increased in size and weight. <P>SOLUTION: The missile 10 is launched from the launcher 3 by combustion of a propellant 1, and it is divided into a rear missile part 10a arranged in a launching direction rear side in the launcher 3, and a front missile part 10b arranged in a launching direction front side in the launcher 3. It has a joining structure, joining the rear missile part 10a and the front missile part 10b at launching from the launcher 3. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

  The present invention relates to a projectile that is launched from a launch tube by combustion of a propellant.

FIG. 7 shows an example of the flying object 40 and the launch tube 3. In the example of FIG. 7, the flying object 40 is a cannonball, and the launch tube 3 is a gun barrel for firing the flying object 40. The projectile 1 is also loaded in the launch tube 3 together with the flying object 40. When the propellant 1 is ignited, the propellant 1 burns. Due to the high-temperature and high-pressure gas generated by this combustion, the flying object 40 is thrust in the firing direction and fired from the launch tube 3. Such a flying body 40 and the launch tube 1 are described, for example, in Patent Document 1 below.
JP 2005-299959 A "mortar loading device"

Some recent flying objects are subject to guidance control during flight, and the guidance type flying object includes electronic components used for guidance control. A flying object including such an electronic component is increased in size and weight accordingly. For example, the weight of the non-guided flying object excluding the weight of the propellant is 10 to 15 kg, while the weight of the guiding flying object exceeds 25 kg. In addition, for example, the length of the non-guided flying object is 30 to 50 cm, whereas the length of the guiding flying object exceeds 1 m (for example, 1.5 m).
When the flying object becomes larger and heavier in this way, it becomes difficult to load the flying object into the launcher. For example, when a flying object is loaded into a launch tube manually by a human, the handling of the flying object becomes difficult due to the increase in size and weight, and the flying object loading operation becomes difficult. In particular, in the case of a preloading method in which the flying object is loaded into the firing cylinder from the front in the firing direction, the flying object loading operation becomes more difficult.
Further, even a flying object that is not a guidance system is large and heavy, and it is difficult to load the flying object.

  Accordingly, an object of the present invention is to provide a flying object that makes it easy to load a flying object into a launch tube even when the size and weight are increased.

In order to achieve the above object, according to the present invention, a projectile that is launched from a launcher by combustion of a propellant,
It is divided into a rear flying body portion arranged on the rear side in the firing direction in the launch tube, and a front flying body portion arranged on the front side in the firing direction in the launch tube,
There is provided a flying body characterized by having a coupling structure for coupling a rear flying body part and a front flying body part when launched from a launch tube.

In the above configuration, the flying object is divided into a rear flying object part disposed on the rear side in the firing direction in the firing cylinder and a front flying object part disposed on the front side in the firing direction in the firing cylinder. Because it has a coupling structure that connects the rear flying body part and the front flying body part when firing from the launch tube, the weight and dimensions of each of the rear flying body part and the front flying body part are larger than the entire flying object. Thus, the rear flying body part and the front flying body part thus reduced in weight and size can be loaded into the launcher one by one. Thereby, it becomes easy to load the projectile into the launcher.
In addition, even if the flying object is an induction type, since the flying object is divided, it can be expected that the restrictions on the weight and dimensions of the induction type flying object will be eased, and the design freedom and required performance of the induction type flying object The scope can be expected to be expanded.
In addition, since the flying object is divided into the rear flying object part and the front flying object part, the rear flying object part and the front flying object part can be separated and stored.

  According to a preferred embodiment of the present invention, a pyrotechnic product containing gunpowder is mounted on the rear flying body part, and an electronic component is mounted on the front flying body part without mounting gunpowder.

  In the above configuration, pyrotechnics containing explosives are mounted on the rear flying body, and electronic components are mounted on the front flying body without being loaded with explosives, so maintenance of electronic components mounted on the flying body is performed. Becomes easier. That is, it is necessary to store the gunpowder loaded in the gunpowder, but in the above configuration, only the rear flying body part loaded with the gunpowder is stored in the gunpowder, and the electronic parts are mounted without the gunpowder mounted. The front flying body part can be stored in a place different from the powder storage. Therefore, the front flying body part can be stored under storage conditions that are more relaxed than in the case of explosives, whereby the front flying body part can be handled flexibly. Accordingly, maintenance such as periodic inspection of the electronic components of the front flying body portion and battery replacement is facilitated.

  Further, according to a preferred embodiment of the present invention, the glaze is mounted on the rear flying body portion, and the explosive device is mounted on the front flying body portion to explode the glaze without mounting the glaze.

  In the above configuration, glaze is loaded on the rear flying body, and no glaze is loaded on the front flying body, and a detonator is installed to explode the glaze. The glaze that releases can be stored separately from the detonator. As a result, even if the detonator operates or ignites unexpectedly, damage can be minimized.

According to a preferred embodiment of the present invention, the binding structure is:
A pressure contact portion formed at the front portion in the firing direction of the rear flying body portion;
A pressure contact part formed on the rear part in the firing direction of the front flying body part,
When the rear flying body part is pushed in the firing direction by the combustion of the propellant, the pressure contact part of the rear flying body part is brought into pressure contact with the pressure contact part of the front flying body part.

  In the said structure, the back flying body part is pushed by the firing direction by combustion of a propellant, and the said pressure contact part of a back flying body part is press-contacted to the said to-be-contacted contact part of a front flying body part. By adopting such means, it is possible to combine the divided rear flying body part and the front flying body part.

According to another embodiment of the invention, the binding structure is:
A front part formed in the front part in the firing direction of the rear flying body part;
A rear part formed at the rear part in the firing direction of the front flying body part,
One of the front part and the rear part is formed with a coupling hole into which the other of the front part and the rear part is inserted,
When the rear flying body part is pushed in the firing direction by the combustion of the propellant, the other is pressed into the coupling hole.

  In the above configuration, a coupling hole into which the other is inserted is formed in one of the front part of the rear flying body part and the rear part of the front flying body part, and the rear flying body part is pushed in the firing direction by combustion of the propellant. Thus, since the other is press-fitted into the coupling hole, the other is pushed into the coupling hole and firmly fixed to the one. By adopting such means, it is possible to firmly join the divided rear flying body part and front flying body part.

The direction from the other side toward the one side is a cross-sectional reduction direction,
The cross-sectional area perpendicular to the other firing direction is reduced as the cross-sectional reduction direction is shifted, and the cross-sectional area perpendicular to the firing direction of the coupling hole is also reduced as the cross-sectional reduction direction is shifted. Good.

  In the above configuration, the cross-sectional area perpendicular to the other firing direction becomes smaller as the cross-sectional reduction direction is shifted, and the cross-sectional area perpendicular to the firing direction of the coupling hole is also shifted toward the cross-sectional reduction direction. Since it is small, even if the rear flying body part and the front flying body part are displaced with respect to each other in the direction perpendicular to the launch direction, this misalignment can be corrected by inserting the other into the coupling hole.

The coupling hole is composed of a first hole on the opening side of the coupling hole and a second hole located on the back side opposite to the opening side,
The first hole and the second hole are both smaller as the cross-sectional area perpendicular to the firing direction shifts to the cross-sectional reduction direction,
The rate at which the cross-sectional area perpendicular to the firing direction of the first hole decreases in the cross-sectional reduction direction is the rate at which the cross-sectional area perpendicular to the firing direction of the second hole decreases in the cross-sectional reduction direction. It may be larger.

  In the above configuration, the coupling hole includes a first hole on the opening side of the coupling hole and a second hole located on the back side opposite to the opening side, and is perpendicular to the firing direction of the first hole. Since the cross-sectional area perpendicular to the firing direction of the second hole becomes smaller as the cross-sectional area shifts in the cross-sectional reduction direction, the rate of the smaller cross-sectional area becomes smaller as it moves in the cross-sectional reduction direction. The above-mentioned positional deviation can be corrected with the hole, and the other can be press-fitted and fixed in the second hole.

According to another embodiment of the present invention, the rear flying body part is swung in the launch tube during launch,
The bonding structure is
A screw portion formed at the front portion in the firing direction of the rear flying body portion;
A screw part formed on the rear part in the firing direction of the front flying body part, and
At the time of launching, the rear flying body part is pushed in the firing direction by the combustion of the propellant and is turned so that the screw part of the rear flying body part is screwed to the screw part of the front flying body part. .

  In the above configuration, at the time of launching, the rear flying body part is pushed in the firing direction by the combustion of the propellant and is turned so that the screw part of the rear flying body part becomes the screw part of the front flying body part. Screwed together. By adopting such means, it is possible to combine the divided rear flying body part and the front flying body part.

  According to the present invention described above, since the flying object can be divided into the front flying object part and the rear flying object part and loaded into the launcher one by one, it becomes easy to load the flying object into the launcher. In addition, even if the flying object is an induction type, since the flying object is divided, it can be expected that the restrictions on the weight and dimensions of the induction type flying object will be eased, and the design freedom and required performance of the induction type flying object The scope can be expected to be expanded. In addition, since the flying object is divided into the rear flying object part and the front flying object part, the rear flying object part and the front flying object part can be separated and stored.

  The best mode for carrying out the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

[First Embodiment]
FIG. 1 is a diagram showing a flying object 10 according to the first embodiment of the present invention. The flying object 10 is accelerated from the combustion of the propellant 1 and is launched from the launcher 3. In this example, the launch tube 3 is a gun barrel.
According to the first embodiment, the flying body 10 includes a rear flying body portion 10a disposed on the rear side in the firing direction within the launch tube 3, and a front flying body disposed on the front side in the firing direction within the launch tube 3. It is divided into a part 10b. Moreover, according to 1st Embodiment, it has the joint structure which couple | bonds the back flying body part 10a and the front flying body part 10b at the time of the launch from the launch tube 3. The propellant 1 may be separated from the flying object 10 or may be loaded or coupled to the rear end part in the firing direction of the rear flying object part 10a. In the example of FIG. 1, the outermost diameter of the rear flying body portion 10 a and the outermost diameter of the front flying body portion 10 b are the same, and these outermost diameters are substantially equal to the inner diameter of the launch tube 3. The same. Thereby, in a state where the rear flying body portion 10a and the front flying body portion 10b are loaded in the launch tube 3, the axis of the rear flying body portion 10a and the axis of the front flying body portion 10b are arranged on substantially the same line. Can do.

  A pyrotechnic product containing gunpowder is mounted on the rear flying body part 10a, and an electronic component is mounted on the front flying body part 10b without mounting gunpowder. The pyrotechnics of the rear flying body part 10a may include explosives for propulsive explosion, explosives for destructive explosion, or a combination thereof. The explosive explosive explosive is for detonating during the flight of the flying object 10 to obtain the propulsive force of the flying object 10. The explosive explosive explosive is targeted by the flying object 10 by the flight. Explosives that explode destructively (ie, glazes) when they reach or at a predetermined point in flight. On the other hand, an electronic component for performing guidance control of the flying object 10 during the flight is mounted on the front flying object unit 10b. Thereby, the rear flying body part 10a can be stored in the gunpowder depot, and the front flying body part 10b can be stored in a place different from the gunpowder depot.

  Moreover, even when it is a case where the electronic component used for guidance control is mounted in the front flying body part 10b as mentioned above, even when it is not so, when mounting a glaze on the rear flying body part 10a, It is preferable to mount a detonator (for example, a fuze) for exploding the glaze on the front flying body portion 10b. Thereby, even if the detonator unexpectedly operates or ignites to explode the glaze, damage can be minimized. In the example of FIG. 2, electronic parts used for guidance control are mounted on the front flying body part 10 b, glaze is mounted on the rear flying body part 10 a, and the rear end part of the rear flying body part 10 a is a rocket auxiliary propulsion part. It has become. The rocket auxiliary propulsion unit is loaded with explosives for obtaining a propulsive force during the flight of the flying object 10. Moreover, in the example of FIG. 2, the code | symbol 5 has shown the spacer (sabo), and the outermost diameter of the front flying body part 10b including the spacer 5 is attached by attaching the spacer 5 to the front flying body part 10b. The outermost diameter of the rear flying body portion 10a and the inner diameter of the launch tube 3 can be made the same.

According to 1st Embodiment, said joint structure has the press-contact part 7 formed in the firing direction front part of the back flying body part 10a, and the to-be-contacted part 9 formed in the firing direction back part of the front flying body part 10b. And consist of When the rear flying body part 10a is pushed in the firing direction by the combustion of the propellant 1, the pressure contact part 7 of the rear flying body part 10a is pressed against the pressure contact part 9 of the front flying body part 10b. For example, when the launch tube 3 is a gun barrel, the propellant 1 is ignited and burned, so that the rear projectile unit 10a has a firing direction of several thousand G to about 10,000 G (for example, several thousand G). The rear flying object 10a is pushed so as to be accelerated at an acceleration of ˜15,000 G). Thereby, the pressure contact part 7 of the rear flying body part 10a can be pressed against the pressure contact part 9 of the front flying body part 10b, and after the pressure welding, the rear flying body part 10a and the front flying body part 10b fly together. .
Immediately before this pressure contact, the air between the rear flying body portion 10a and the front flying body portion 10b passes from the gap between the front flying body portion 10b and the inner wall surface of the launcher 3 to the outside of the launcher 3. Get out. For this purpose, the outermost diameter of the front flying body portion 10b may be made somewhat smaller than the inner diameter of the launch tube 3. In this case, the spacers 5 may be provided at intervals in the circumferential direction of the front flying body portion 10b so that air escapes between the adjacent spacers 5. Such a point may be the same also in 2nd Embodiment and 3rd Embodiment mentioned later.

  FIG. 3 shows a configuration example in the case where the glaze is mounted on the rear flying body portion 10a and the initiation device 6 is mounted on the front flying body portion 10b. The detonator 6 is for exploding the glaze of the rear flying body portion 10a in the state where the rear flying body portion 10a and the front flying body portion 10b are pressure-bonded as described above. FIG. 3 shows a state in which no glaze is mounted on the front flying body portion 10b, and the rear flying body portion 10a and the front flying body portion 10b are pressure-bonded as described above. The detonator 6 includes a power source 6a, a circuit 6b, and a primary coil 6c. Corresponding to the initiation device 6 of the front flying body portion 10b, the rear flying body portion 10a is provided with a secondary coil 8a and a detonation detonator 8b. The detonator 6 is configured such that the circuit 6b receives electric power from the power source 6a and causes a current to flow through the primary coil 6c when receiving an operation signal from the outside or reaching a preset time point. Yes. When a current flows through the primary coil 6c, an electromotive force is generated in the secondary coil 8a due to electromagnetic induction, and a current flows through the detonator (electric detonator) 8b. By energizing such a detonator 8b, the detonator 8b explodes, and as a result, the glaze can also explode.

  According to the flying object 10 of the first embodiment described above, the flying object 10 is disposed in the launch tube 3 on the rear side in the launch direction, and on the rear side in the launch direction within the launch tube 3. It is divided into the front projecting body part 10b to be arranged, and has a coupling structure that joins the rear projecting body part 10a and the front projecting body part 10b at the time of launching from the launch tube 3, so that the rear projecting body part 10a and The weight and dimensions of each of the front flying body portions 10b can be made significantly smaller than the entire flying body 10. Thus, the rear flying body portion 10a and the front flying body portion 10b that are reduced in weight and size as described above are provided. It can be loaded into the launch tube 3 one by one. This makes it easy to load the flying object 10 into the launch tube 3. Moreover, in 1st Embodiment, the back flying body part 10a is pushed by the firing direction by combustion of the propellant 1, and the press-contact part 7 of the back flying body part 10a press-contacts the to-be-contacted contact part 9 of the front flying body part 10b. Is done. By adopting such means, the divided rear flying body part 10a and front flying body part 10b can be combined.

Furthermore, since the flying object 10 is divided even if the flying object 10 is an induction type, it can be expected that the restrictions on the weight and dimensions of the induction type flying object 10 can be relaxed, and the design freedom of the induction type flying object 10 It can also be expected that the required performance range will be expanded.
In addition, since the flying object 10 is divided into the rear flying object part 10a and the front flying object part 10b, the rear flying object part 10a and the front flying object part 10b can be separated and stored.

Further, when a pyrotechnic product containing explosives is mounted on the rear flying body portion 10a and an electronic component is mounted on the front flying body portion 10b without mounting an explosive, the electronic component mounted on the flying body 10 is mounted. Maintenance becomes easier. That is, it is necessary to store the gunpowder loaded in the gunpowder, but in the above configuration, only the rear flying body part 10a loaded with gunpowder is stored in the gunpowder box, and no electronic gunpowder is loaded. The forward flying body portion 10b thus made can be stored in a place different from the powder storage. Therefore, the front flying body portion 10b can be stored under a storage condition that is more relaxed than in the case of explosives, whereby the front flying body portion 10b can be handled flexibly. Accordingly, maintenance such as periodic inspection of the electronic parts of the front flying body part 10b and battery replacement is facilitated.
When the rear flying body part 10a is loaded with glaze and the front flying body part 10b is not loaded with glaze but is equipped with a detonator for exploding the glaze, a large amount of energy is generated by the explosion. The glaze to be released can be stored separately from the detonator. As a result, even if the detonator is unexpectedly activated or ignited, damage can be minimized.

[Second Embodiment]
FIG. 4 is a diagram showing a flying object 20 according to the second embodiment of the present invention. In the second embodiment, similarly to the first embodiment, the flying body 20 includes a rear flying body portion 20a disposed on the rear side in the firing direction within the launch tube 3, and a front side in the firing direction within the launch tube 3. And the forward projecting body part 20b disposed at the front, and has a coupling structure that joins the rear projecting body part 20a and the front projecting body part 20b when firing from the launch tube 3. In the following, parts different from the first embodiment will be mainly described. In the second embodiment, other parts not described below may be the same as those in the first embodiment.

  According to the second embodiment, the coupling structure includes the front part 11 formed at the front part in the firing direction of the rear flying body part 20a, and the rear part 13 formed at the rear part in the firing direction of the front flying body part 20b. The other of the front part 11 and the rear part 13 (the front part 11 in the example of FIG. 4) is inserted into one of the front part 11 and the rear part 13 (the rear part 13 in the example of FIG. 4). A coupling hole 15 is formed. When the rear projectile body portion 20 a is pushed in the firing direction by the combustion of the propellant 1, the other is pressed into the coupling hole 15. In FIG. 4, the coupling hole 15 is indicated by a broken line.

  The direction from the other side toward the one side is a cross-sectional reduction direction (firing direction in FIG. 4), and the cross-sectional area perpendicular to the other firing direction becomes smaller as the cross-sectional reduction direction is shifted, and the coupling hole The cross-sectional area perpendicular to the firing direction of 15 is also reduced as the cross-sectional reduction direction is shifted. For example, the other (the rear portion 13 in FIG. 4) has a tapered shape with a tapered tip in the cross-sectional reduction direction, and the coupling hole 15 also has a tapered shape with a tapered tip in the cross-sectional reduction direction.

  In one example, the coupling hole 15 includes a first hole 15a on the opening side of the coupling hole 15 and a second hole 15b located on the back side opposite to the opening side. Both the first hole 15a and the second hole 15b become smaller as the cross-sectional area perpendicular to the firing direction shifts in the cross-sectional reduction direction. The rate at which the cross-sectional area perpendicular to the firing direction of the first hole 15a decreases as the cross-sectional reduction direction shifts is the rate at which the cross-sectional area perpendicular to the firing direction of the second hole 15b decreases as the cross-sectional reduction direction. Is bigger than. In other words, in this example, as shown in FIG. 5, the angle α formed by the inner wall surface of the front projecting body portion 20b that defines the first hole 15a and the axial direction of the front projecting body portion 20b is the second hole 15b. Is larger than the angle β formed by the inner wall surface of the front flying body portion 20b and the axial direction of the front flying body portion 20b.

  According to the flying object 20 of the second embodiment described above, since the flying object 20 is divided as in the first embodiment, it becomes easy to load the flying object 20 into the launch tube 3. Moreover, according to 2nd Embodiment, the joint hole 15 in which the other is inserted is formed in one of the front part 11 of the rear flying body part 20a and the rear part 13 of the front flying body part 20b, and combustion of the propellant 1 is carried out. By pushing the rear projecting body portion 20a in the firing direction, the other is pressed into the coupling hole 15, so that the other is pushed into the coupling hole 15 and firmly fixed to the rear portion 13. By adopting such means, the divided rear flying body part 20a and front flying body part 20b can be firmly coupled. Therefore, according to the second embodiment, the above-described press-fitting can be performed in place of or in addition to the press-contact of the first embodiment.

  In addition, the cross-sectional area perpendicular to the other firing direction is reduced as the cross-sectional reduction direction is shifted, and the cross-sectional area perpendicular to the firing direction of the coupling hole 15 is also decreased as the cross-sectional reduction direction is shifted. Therefore, even if the rear flying unit 20a and the front flying unit 10b are displaced from each other in the direction perpendicular to the launch direction, the other is inserted into the coupling hole 15 to correct this positional deviation. it can.

  Further, the coupling hole 15 includes a first hole 15a on the opening side of the coupling hole 15 and a second hole 15b located on the back side opposite to the opening side, and the firing direction of the first hole 15a. The rate of decreasing the cross-sectional area perpendicular to the cross-sectional reduction direction is larger than the rate of decreasing the cross-sectional area perpendicular to the firing direction of the second hole 15b as the cross-sectional reduction direction. The above-described misalignment can be corrected by the first hole 15a, and the other can be press-fitted and fixed in the second hole 15b.

  In the second embodiment, as shown in FIG. 3, the glaze may be mounted on the rear flying body portion 20a and the detonator 6 may be mounted on the front flying body portion 20b as in the first embodiment. . The detonator 6 is for exploding the glaze of the rear flying body portion 20a in a state where the rear flying body portion 20a and the front flying body portion 20b are coupled as described above. In this case, for example, the primary coil 6c described above may be disposed so that the axis thereof is wound around the coupling hole 15 with the axis thereof facing the axial direction of the front flying body portion 20b (the left-right direction in FIG. 3).

[Third Embodiment]
FIG. 6 is a diagram showing a flying object 30 according to the third embodiment of the present invention. In the third embodiment, similarly to the first embodiment, the flying object 30 includes a rear projecting body portion 30a disposed on the rear side in the launching direction in the launcher 3, and a launching direction in the launcher 3. It is divided into a front projecting body portion 30b disposed on the front side, and has a coupling structure that joins the rear projecting body portion 30a and the front projecting body portion 30b when firing from the launch tube 3. In the following, parts different from the first embodiment will be mainly described. In the third embodiment, other parts not described below may be the same as those in the first embodiment.

  In the third embodiment, the rear flying body portion 30a is turned in the launch tube 3 at the time of launch. That is, on the inner wall surface of the launch tube 3, a rifle (cavity line) 4 for turning the rear flying body portion 30a is engraved in a spiral shape. On the other hand, an annular bullet band 17 is formed on the outer periphery of the rear flying body portion 30 a, and a protrusion 17 a that meshes with the rifle 4 is formed on the bullet band 17. When the projectile 30 is launched, when the propellant 1 is ignited and combusted, a high-temperature and high-pressure gas is generated, and the rear projectile unit 30a is pushed and moved in the firing direction by the high-temperature and high-pressure gas. At this time, the rear flying body part 30a turns along the rifle 4 by the protrusion 17a. Reference numeral 4 a indicates a mountain of the rifle 4, and reference numeral 4 b indicates a valley of the rifle 4. Moreover, in order to make the rear flying body part 30a turn in the launch tube 3 at the time of launch, the projection 17a may not be provided, and the rifle 4 may be formed on the inner wall surface of the launch tube 3.

  Moreover, in 3rd Embodiment, the connection structure has the screw part 19 formed in the firing direction front part of the rear flying body part 30a, the screw part 21 formed at the firing direction rear part of the front flying body part 30b, and Consists of. At the time of launching, the rear flying body part 30a is pushed in the firing direction by the combustion of the propellant 1 and is turned so that the screw part 19 of the rear flying body part 30a becomes the screw part of the front flying body part 30b. 21 is screwed. In FIG. 6, the screw portion 19 of the rear flying body portion 30a is a male screw, and the screw portion 21 of the front flying body portion 30b is a female screw. However, the screw portion 19 of the rear flying body portion 30a may be a female screw, and the screw portion 21 of the front flying body portion 30b may be a male screw.

  The screw portion 19 of the rear flying body portion 30a and the screw portion 21 of the front flying body portion 30b may be of a screw type (intermittent screw type). That is, the screw portions 19 and 21 may be formed with screw grooves only at a plurality of portions spaced in the outer circumferential direction or the inner circumferential direction. Thereby, the screw part 19 of the rear flying body part 30a moved while turning in the firing direction at the time of launching can be easily inserted into the screw hole in which the screw part 21 of the front flying body part 30b is formed. Thereby, the screw part 19 of the rear flying body part 30a is more reliably screwed to the screw part 21 of the front flying body part 30b.

  According to the flying object 30 of the third embodiment described above, since the flying object 30 is divided as in the first embodiment, it becomes easy to load the flying object 30 into the launch tube 3. Further, according to the third embodiment, at the time of launching, the rear flying body part 30a is pushed in the firing direction by the combustion of the propellant 1 and is swung so that the screw part 19 of the rear flying body part 30a is It is screwed to the screw part 21 of the front flying body part 30b. By adopting such means, it is possible to combine the divided rear flying body part 30a and the front flying body part 30b.

  In the third embodiment, as shown in FIG. 3, the glaze can be mounted on the rear flying body 30a and the detonator 6 can be mounted on the front flying body 30b, as in the first embodiment. . The detonator 6 is for exploding the glaze of the rear flying body 30a in a state where the rear flying body 30a and the front flying body 30b are coupled as described above. In this case, for example, the primary coil 6c described above may be arranged so that the axis thereof is wound around the screw portion 21 with the axis facing the axial direction of the front flying body portion 30b (the left-right direction in FIG. 3).

The present invention is not limited to the above-described embodiment, and various changes can be made without departing from the scope of the present invention.
For example, in the first embodiment or the second embodiment, the flying bodies 10 and 20 do not swivel at the time of launching, but the rifle 4 of the launcher 3 and the rear flying body portion 30a bullets as in the third embodiment. You may turn at the time of discharge by the protrusion 17a of the belt | band | zone 17, etc.

It is a figure which shows the flying body by 1st Embodiment of this invention. It is a figure which shows an example of the flying body by 1st Embodiment. It is a figure which shows the structural example in the case of mounting a glaze on a back flying body part, and mounting a detonator on a front flying body part. It is a figure which shows the flying body by 2nd Embodiment of this invention. It is an enlarged view of the front flying body part of FIG. It is a figure which shows the flying body by 3rd Embodiment of this invention. It is a figure which shows the conventional flying body.

Explanation of symbols

1 gunpowder, 3 launcher, 4 rifle,
5 spacer, 6 detonator, 6a power supply, 6b circuit,
6c primary coil, 7 pressure contact part, 8a secondary coil,
8b Detonator, 9 pressure contact, 10 projectile,
10a backward flying body part, 10b forward flying body part,
11 front part, 13 rear part, 15 coupling hole,
15a 1st hole, 15b 2nd hole, 17 band,
17a protrusion, 19 screw part, 20 flying object,
20a rear flying body part, 20b front flying body part, 21 screw part,
30 flying object, 30a rear flying object part, 30b forward flying object part

Claims (8)

A projectile fired from a launcher by burning propellant,
It is divided into a rear flying body portion arranged on the rear side in the firing direction in the launch tube, and a front flying body portion arranged on the front side in the firing direction in the launch tube,
A flying object characterized in that it has a coupling structure for joining a rear flying object part and a forward flying object part at the time of launching from a launch tube.   The flying object according to claim 1, wherein a pyrotechnic product containing explosives is mounted on the rear flying body part, and an electronic component is mounted on the front flying body part without mounting the explosive.   The flying object according to claim 1, wherein glaze is mounted on the rear flying body part, and no explosive is mounted on the front flying body part, and an initiation device for exploding the glaze is mounted on the flying object part. . The bonding structure is
A pressure contact portion formed at the front portion in the firing direction of the rear flying body portion;
A pressure contact part formed on the rear part in the firing direction of the front flying body part,
When the rear flying body part is pushed in the firing direction by combustion of the propellant, the pressure contact part of the rear flying body part is brought into pressure contact with the pressure contact part of the front flying body part. The flying object according to any one of claims 1 to 3. The bonding structure is
A front part formed in the front part in the firing direction of the rear flying body part;
A rear part formed at the rear part in the firing direction of the front flying body part,
One of the front part and the rear part is formed with a coupling hole into which the other of the front part and the rear part is inserted,
The flying object according to any one of claims 1 to 3, wherein the other projecting part is press-fitted into the coupling hole when the rear projecting part is pushed in the firing direction by combustion of the propellant. The direction from the other side toward the one side is a cross-sectional reduction direction,
The cross-sectional area perpendicular to the other firing direction is reduced as the cross-sectional reduction direction is shifted, and the cross-sectional area perpendicular to the firing direction of the coupling hole is also reduced as the cross-sectional reduction direction is shifted. The flying object according to claim 5. The coupling hole is composed of a first hole on the opening side of the coupling hole and a second hole located on the back side opposite to the opening side,
The first hole and the second hole are both smaller as the cross-sectional area perpendicular to the firing direction shifts to the cross-sectional reduction direction,
The rate at which the cross-sectional area perpendicular to the firing direction of the first hole decreases in the cross-sectional reduction direction is the rate at which the cross-sectional area perpendicular to the firing direction of the second hole decreases in the cross-sectional reduction direction. The flying object according to claim 6, wherein the flying object is larger. The rear flying body part is swung in the launch tube at the time of launch,
The bonding structure is
A screw portion formed at the front portion in the firing direction of the rear flying body portion;
A screw part formed on the rear part in the firing direction of the front flying body part, and
At the time of launching, the rear flying body part is pushed in the firing direction by the combustion of the propellant and is turned so that the screw part of the rear flying body part is screwed to the screw part of the front flying body part. The flying object according to any one of claims 1 to 3.

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