JP4462735B2 - Load release device - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a payload release equipment that emits payload from projectile.
[0002]
[Prior art]
With reference to FIG. 21, an example of a case where the load is a child bullet will be described with respect to the load released from the conventional flying object. In the figure, reference numeral 101 denotes a flying body, and reference numeral 102 denotes a shell package in which a plurality of shells are packaged, that is, a parent bullet in which a plurality of shells are packed. Contained.
[0003]
First, the primary bullet 102 is released from the fuselage of the flying object 101 by the primary release A while the secondary bullets are packed, and then the secondary release B is performed in the air to spray the secondary bullets in the primary bullet 102. The C is the distribution range of the bullets at this time.
[0004]
The main bullet 102 emitted from the flying object 101 is disclosed in, for example, Japanese Patent Application Laid-Open No. 6-74698, and FIG. 22A shows a front view and FIG. As shown, a plurality of slave bullets 104 are arranged around the airbag 103 in a contracted state, and these slave bullets 104 are covered with a pack material 105. The airbag 103 is configured to expand in a substantially cylindrical shape when the gas generator 103a disposed therein is operated.
[0005]
After primary discharge of the main bullet 102 configured in this manner, when the gas generator 103 a is operated to inflate the airbag 103, the pack material 105 is destroyed and the secondary bullet 104 contained around the airbag 103. The secondary discharge is carried out by being pushed out and scattered.
[0006]
In addition, the primary discharge range in which the main bullet is released from the flying object is controlled by controlling the ignition timing of the primary emitter by the dispenser control computer in the flying direction of the flying object, and in the primary direction in the lateral direction. This is done by changing the amount of propellant in the discharger.
[Problems to be solved by the invention]
According to the base bullet 102 of JP-A-6-74698, the airbag 103 is inflated into a cylindrical shape, so that each base bullet 104 is given a radial release speed and can be sprayed.
[0008]
However, it is difficult to inflate the airbag 103 uniformly at a uniform speed in all directions by using the gas pressure generated by the gas generator 103a. There is a risk that it cannot be sprayed.
[0010]
Therefore, the objective of this invention made | formed in view of this point is to provide the load discharge | release apparatus which can obtain dispersion | distribution of a uniform load.
[0012]
[Means for Solving the Problems]
The invention of the mounted object discharge device according to claim 1, which achieves the above object, includes a plurality of mounted objects, wherein the mounted object discharging apparatus releases the plurality of mounted objects after being released from the flying object. A mounted object holder having a columnar mounted object supporting portion that extends on an axis passing through the center of gravity of the object discharge device and in which a plurality of mounted objects are arranged in a circle around the axis along the outer periphery; and the mounted object A lashing means comprising: a band-like body collectively surrounding a plurality of mounted objects arranged on the outer periphery of the support part; and a coupling means for joining between both ends of the belt-like body and being damaged by a predetermined load; And a rotation applying means for rotating the mounted object holder around the axis.
According to the first aspect of the present invention, the loaded object holder is rotated by the rotation applying means to stabilize the flying direction posture of the loaded object discharge device, and the centrifugal force is generated by the rotation so that each mounted object removes the securing means. When the rotation speed exceeds the predetermined value, the connecting means connecting the ends of the belt cannot withstand the centrifugal force from the load and breaks beyond the strength limit. Is released, and each load is released radially and uniformly by centrifugal force. Each of the released mounted objects maintains the rotational motion before the discharge, and can be landed in a stable dropping posture while rotating. Moreover, the dispersion | distribution range of the load by a centrifugal force is controllable by setting suitably the breaking strength of a coupling means.
[0016]
The invention according to claim 2, in mounted object emitting device of claim 1, further comprising a tubular body for accommodating a payload that is fastened to the mounting piece holder by lashing means, mounted on the tubular body The object holder and the loaded object are accommodated and mounted on the flying object, and the loading object holder protrudes from the cylindrical body in conjunction with the release from the flying object and flies together with the cylindrical object. The rotation applying means operates.
[0017]
According to the second aspect of the present invention, the loaded object is more evenly dispersed and dispersed by rotating the loaded object holder from the cylindrical body in a state in which the orientation is stabilized in conjunction with the release from the flying object. can do.
[0022]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, it will be explained with reference to FIG. Embodiments of the payload release equipment according to the present invention.
[0023]
(First embodiment)
The first embodiment will be described with reference to FIGS. 1 to 15 by taking the case where the mounted object is a small bullet as an example.
[0024]
FIG. 1 is a schematic explanatory diagram of a load discharge system. Reference numeral 1 denotes a flying object, and a plurality of primary emitters 10 are arranged on the left and right sides of the body of the flying object 1, and the primary emitter 10 serves as a flying object discharging device for the secondary emitter 20. A plurality of small bullets 40 are further sprayed from the discharged secondary emitter 20 in a lateral direction substantially perpendicular to the flight direction of one.
[0025]
As shown in a cross-sectional view in FIG. 2, the primary discharger 10 includes a discharge cylinder 11 having a cylindrical opening extending in a lateral direction substantially orthogonal to the flight direction of the flying object 1 and having an open front end facing the body outer plate 2. The bottom wall 12 provided at the base end of the discharge cylinder 11 is provided with a gas generating part 14 for containing a propellant 13 such as explosive or gas generating agent, and the gas generating part 14 is provided with an igniter 14a. Yes.
[0026]
A disc-shaped first pusher plate 15 is fitted in the discharge cylinder 11 so as to be movable in the axial direction thereof. The first pusher plate 15 is formed with a flange 15b projecting annularly rearward along the outer periphery of the disc-shaped pusher plate main body 15a, and a hammer insertion hole 15c is formed in the center of the pusher plate main body 15a. The flange 15b is mounted in the discharge cylinder 11 with the rear end of the flange 15b in contact with the bottom wall 12.
[0027]
A disc-shaped second pusher plate 16 is slidably fitted in a state of being in contact with the bottom wall 12 and having a gap with the pusher plate main body 15a in a flange 15b formed in an annular shape. At the center portion of the second pusher plate 16, a firing needle 16a for a timed operation mechanism with a tip portion fitted into the firing needle insertion hole 15c is projected. Reference numeral 17 denotes a lid that covers the tip of the discharge cylinder 11.
[0028]
The secondary discharger 20 is accommodated in the discharge cylinder 11 of the primary discharger 10 formed in this manner while being held between the first pusher plate 15 and the fuselage outer plate 2 via the lid 17. ing.
[0029]
The secondary emitter 20 will be described with reference to FIGS. 3 and 4. 3 is a cross-sectional view of the secondary emitter 20, FIG. 4 (a) is a side view showing the operating state of the secondary emitter 20, and FIG. 3 (b) is a view as seen from the arrow A in FIG. c) is a B arrow view of (a).
[0030]
The secondary emitter 20 has a cylindrical body 21 slidably fitted into the discharge cylinder 11 of the primary emitter 10, and the proximal end and the distal end of the cylindrical body 21 are each along the edge. A proximal end flange 21a and a distal end flange 21b are bent inward.
[0031]
In the cylindrical body 21, a discharge holder for holding a bullet, that is, a bullet holder 22 is accommodated. The bullet holder 22 is a slidable support 24 supported on the cylindrical body 21 via an annular sleeve 23, a spin motor 25 serving as a rotation imparting means, and a child serving as a columnar load support. The bullet support portion 26 is integrally formed continuously on the same axis. A timed operation mechanism for operating the spin motor 25 after the set time has elapsed is accommodated in the timed operation mechanism storage unit 24, and the spin motor 25 stores a gas generator 25a and a gas generator 25a for storing a combustion gas generating agent such as an explosive or a gas generating agent. And a spin motor fusible tube 25c for igniting a combustion gas generating agent in the gas generator 25a.
[0032]
A plurality of submunitions 40 are arranged so as to surround the submunition support part 26, and in this embodiment, seven submunition groups surrounding the submunition support part 26 are arranged by seven submunitions 40, for a total of 21 submunitions 40. Are arranged in a circle around the central axis passing through the center of gravity of the secondary emitter 20, and the outer peripheries of these bullets 40 are collectively secured by the securing means 30.
[0033]
The lashing means 30 includes a plate-like restraining holder 31 spanned between the outer peripheries of the respective bullets 40, a belt-like body 32 that collectively surrounds and restrains the bullets 40 from the outer circumference of the restraining holder 31, and The two ends of the belt-like body 32 are coupled to each other, and the shear pin 33 is a coupling means that is broken by a predetermined load.
[0034]
As shown in FIG. 3, the bullet holder 22 to which the bullet 40 is mounted in this manner is compressed by a spring 27 that is compressed and applied between the proximal flange 21 a of the cylindrical body 21 and the sleeve 23. The cylindrical body 21 is mounted by being pressed against a plate-like holding member 28 locked to the front end flange 21b.
[0035]
Next, the dispersion of the load by the flying object 1 configured as described above will be described with reference to FIG. 2 and FIGS. 5 to 15 which are operation explanatory diagrams.
[0036]
As shown in FIG. 2, in the flying state of the flying object 1 in which the secondary emitter 20 having the bullet 40 mounted thereon is set in each primary emitter 10, the control device (not shown) removes each primary emitter 10 from the primary emitter 10. The igniters 14a of the primary emitters 10 are sequentially energized while controlling the discharge interval. In the primary emitter 10 energized by the igniter 14a, the propellant accommodated in the gas generator 14 starts to burn, and the gas pressure in the combustion gas generator 14 rises, and the gas pressure increases the second pusher plate. 16 is pushed from the state shown in FIG. 5 as shown in FIG. 6, and the tip of the shooting needle 16 a protruding from the second pusher plate 16 protrudes from the shooting hole insertion hole 15 c of the first pusher plate 15. The timed operation mechanism in the timed operation mechanism storage part 24 of the discharger 20 is operated.
[0037]
Further, as shown in FIGS. 7A and 7B, the first pusher plate 15 is pushed by the increase of the gas pressure in the combustion gas generation unit 14 to push the secondary discharger 20. When the gas pressure reaches a critical point, the secondary discharger 20 breaks through the lid 17 of the primary discharger 10 and the airframe outer plate 2 of the flying object 1 and is discharged in the lateral direction of the flying object 1.
[0038]
Here, considering the relationship between the lateral flight distance of the secondary emitter 20 and the flying speed of the flying object 1, the flying speed V1 of the secondary emitter 20 is the flying speed of the flying object 1, as shown in FIG. It is determined by the vector sum of the speed V2 and the primary discharge speed V3, that is, the horizontal discharge speed of the secondary emitter 20.
[0039]
The primary release speed V3 is determined by the amount of the propellant 13 in the gas generator 14 of the primary emitter 10. When the primary discharge speed V3 is constant, if the flying speed V2 of the flying object 1 is large as shown in FIG. 9A, the flying speed V1 of the secondary emitter 20 increases. That is, when the flying speed V2 of the flying object 1 is large, the flying speed V1 of the secondary emitter 20 is also large, so that the air resistance acting on the secondary emitter 20 is also large. As a result, as shown in FIG. 9B, the flight distance L1 of the secondary emitter 20 is reduced, and the lateral flight distance L3 is reduced.
[0040]
On the other hand, when the flying speed V2 of the flying object 1 is small as shown in FIG. 10A, the flying speed V1 of the secondary emitter 20 becomes small, and when the primary emitting speed V3 is constant, the flying object. When the flying speed V2 of 1 is small, the flying speed V1 of the secondary emitter 20 is also small, so the air resistance of the secondary emitter 20 is also small, and the flying of the secondary emitter 20 is shown in FIG. 10 (b). The distance L1 increases and the flight distance L3 in the lateral direction increases.
[0041]
Therefore, as shown in FIG. 15, the secondary emission in the flight direction of the flying object 1 is controlled by controlling the interval of primary emission from the flying object 1, that is, the emission interval of the secondary emitter 20 by each primary emitter 10. The distance a between the landing points of the emitter 20 can be set, and when the primary release speed V3 is constant, the flight of the secondary emitter 20 from the flying body 1 in the lateral direction is caused by the flying speed V2 of the flying body 1. Even when the distance b is set, the primary discharge interval and the flying speed V2 of the flying object 1 can be easily changed because of the computer program, and the amount of the propellant in each primary discharger 10 is constant. Accordingly, the discharge range of the secondary emitter 20 can be changed.
[0042]
The secondary discharger 20 discharged from the primary discharger 10 is as shown in FIGS. 4 and 11A by a spring 27 elastically mounted between the proximal end flange 21a of the cylindrical body 21 and the sleeve 32. The shell holder 22 is pushed out from the tip of the cylindrical body 21, and the sleeve 23 is brought into contact with the tip flange 21 b of the cylindrical body 21 with the tip of the spin motor nozzle 25 b of the spin motor 25 protruding from the tip of the cylindrical body 21. It flies while being maintained in a state where the center of gravity is unevenly distributed on the front end side where the cylindrical body 21 is connected to the rear end of the shell holder 22.
[0043]
Thereafter, the spin motor fuze 25c is operated by the timing mechanism, and the combustion gas generating agent in the gas generator 25a is ignited by the spin motor fuze 25c. The gas pressure in the gas generator 25a is increased by the combustion of the combustion gas generating agent. As shown in FIG. 11B, the combustion gas is ejected from the tip of the spin motor nozzle 25b, and the secondary emitter 20 starts to rotate. .
[0044]
This rotation stabilizes the orientation and orientation of the secondary emitter 20 as shown in FIG. 12 (a), and centrifugal force due to the rotation of the secondary emitter 20 is generated in each secondary bullet 40, and each secondary bullet 40. As shown in FIG. 12B, the belt-like body 32 is pushed outward.
[0045]
When the rotational speed of the secondary emitter 20 exceeds a specified value, the shear pin 33 connecting both ends of the belt-like body 32 cannot withstand the centrifugal force from the shell 40, and the strength as shown in FIG. Break beyond limits.
[0046]
As shown in FIG. 13, each bullet 40 released from the strip 32 by the breakage of the shear pin 33 is released radially and uniformly dispersed from the secondary emitter 20 by centrifugal force. . Each released bullet 40 retains its rotational movement before being released, and each bullet 40 falls while rotating as shown in FIG. 14, so that the falling posture is stabilized and the fuse of the bullet 40 is operated correctly. You can land in a posture to do.
[0047]
The dispersion range of each bullet 40 from the secondary emitter 20 is, as shown in FIG. 15A, the distance La from the landing point of the secondary emitter 20 to the landing point of each bullet 40 is 2 By adjusting the amount of combustion gas generating agent accommodated in the gas generator 25a of the spin motor 25, controlled by the rotational force of the secondary emitter 20 and the strength of the shear pin 33 connecting both ends of the strip 32, or It can be controlled by appropriately setting the strength of the shear pin 33.
[0048]
Therefore, according to the present embodiment described above, the flight of the secondary emitter 20 from the flying body 1 in the lateral direction is controlled by the control of the primary discharge interval by each primary emitter 10 and the control of the flying speed V2 of the flying body 1. The distance is set, and the discharge range of the secondary emitter 20 can be changed by the computer program according to the situation of the primary discharge interval and the flying speed V2 of the flying object 1 according to the situation.
[0049]
Further, since the secondary bullets 20 are discharged from the secondary emitter 20 by centrifugal force, the distribution direction of each bullet 40 is uniform. The falling posture can be stabilized, and the rotation of the secondary emitter 20 is rotated by the combustion gas of the combustion gas generating agent such as explosive accommodated in the gas generator 25a of the spin motor 25. The discharge distance of the bullet 40 from the secondary emitter 20 and the rotation speed of the bullet 40 can be increased.
[0050]
(Second Embodiment)
The second embodiment will be described with reference to FIGS. 16 to 20 by taking the case where the mounted object is a large child bullet as an example. Note that parts corresponding to those in FIGS. 1 to 15 are denoted by the same reference numerals, detailed description of the outside is omitted, and different parts are mainly described.
[0051]
FIG. 16 is a schematic explanatory diagram of the load discharge system according to the present embodiment. Like the first embodiment, the primary discharge devices 10 are arranged in a plurality of rows on the left and right sides of the fuselage of the flying object 1, respectively. Large primary bullets 50 are sprayed by the primary emitter 10.
[0052]
As shown in FIG. 17, in the flying body of the flying body 1 in which the primary bullets 10 are set in the respective primary emitters 10, while controlling the discharge interval from each primary emitter 10 by a control device (not shown). The igniter 14a of each primary emitter 10 is energized sequentially. In the primary emitter 10 energized by the igniter 14a, the propellant contained in the gas generator 14 starts to burn, and the gas pressure in the combustion gas generator 14 rises, and the gas pressure is shown in FIG. When the second pusher plate 16 is pushed from the state as shown in FIG. 18, the tip of the firing needle 16 protruding from the second pusher plate 16 protrudes from the firing hole 15 c of the first pusher plate 15 to move the bullet 50. Activate the timed activation mechanism.
[0053]
Further, as the gas pressure in the combustion gas generation unit 14 increases, the first pusher plate 15 is pushed as shown in FIG. When the gas pressure reaches a critical point, the bullet 50 is released in the lateral direction of the flying object 1 through the lid 17 of the primary emitter 10 and the airframe outer plate 2 of the flying object 1.
[0054]
Here, the relationship between the lateral flight distance of the bullet 50 and the flying speed of the flying object 1 is as follows. The flying speed of the bullet 50 is as follows: the flying speed of the flying object 1 and the primary emission speed, that is, the child. It is determined by the vector sum of the release speeds of the bullets 50 in the lateral direction.
[0055]
That is, when the primary discharge speed is constant, if the flying speed of the flying object 1 is large, the lateral flight distance of the bullet 50 becomes small, and if the flying speed of the flying object 1 is small, the bullet 50 The flight distance in the horizontal direction increases.
[0056]
Therefore, as shown in FIG. 20, by controlling the primary discharge interval from the flying object 1, that is, the discharge interval of the bullet 50 by each primary emitter 10, the landing of the bullet 50 in the flying direction of the flying object 1. The distance a between points can be set, and the flying distance b in the lateral direction of the bullet 50 from the flying object 1 is set according to the flying speed of the flying object 1. The primary emission interval and the flying speed of the flying object 1 are as follows. Since it is based on a computer program, it can be easily changed, and the discharge range of the secondary emitter 20 can be changed according to the situation.
[0057]
Therefore, according to the present embodiment, the horizontal flight distance of the bullet 50 from the flying object 1 is set by controlling the primary discharge interval by each primary emitter 10 and the flying speed of the flying object 1. The discharge range of the bullet 50 can be changed according to the situation by the computer program with respect to the interval of the next discharge and the flying speed of the flying object 1.
[0058]
In each of the above-described embodiments, the case where the load is a child bullet has been described as an example. However, the present invention can be applied to other loads, and the present invention is not limited to the above-described embodiment. Various modifications can be made without departing from the spirit of the invention.
[0059]
【The invention's effect】
According to the loaded object discharging apparatus of the present invention described above, the loaded object is rotated by the rotation applying means to stabilize the flying posture of the loaded object discharging apparatus, and the loaded object is caused by the centrifugal force generated by the rotation of the loaded object holder. By urging the lashing means outwardly, releasing the lashing by the lashing means almost instantaneously and causing each load to radiate by centrifugal force, it is possible to uniformly release each load. Furthermore, each released load can be landed in a stable dropping posture while rotating.
[0060]
In addition, the securing means can be easily configured by a joining means for joining the strip and the both ends of the strip, and by appropriately setting the breaking strength of the joining means, the dispersion range of the load due to centrifugal force can be set. Can be controlled.
[Brief description of the drawings]
1 is a payload release system overview diagram illustrating an outline of a first embodiment of the payload release equipment according to the present invention.
FIG. 2 is also a cross-sectional view of a primary emitter.
FIG. 3 is a sectional view of the secondary emitter, similarly.
FIG. 4 is also an explanatory view of the operating state of the secondary emitter, in which (a) is a side view, (b) is a view from arrow A in (a), and (c) is a view from arrow B in (a). It is.
FIG. 5 is also an operation explanatory diagram for carrying a load.
FIG. 6 is also an operation explanatory diagram for carrying a load.
FIG. 7 is also an operation explanatory diagram for carrying a load.
FIG. 8 is also an operation explanatory diagram of the load distribution.
FIG. 9 is also an operation explanatory diagram of the load distribution.
FIG. 10 is also an operation explanatory diagram of the load distribution.
FIG. 11 is also an operation explanatory diagram for carrying a load.
FIG. 12 is also an operation explanatory diagram for carrying a load.
FIG. 13 is also an operation explanatory diagram for carrying a load.
FIG. 14 is also an operation explanatory diagram of the load distribution.
FIG. 15 is also an explanatory diagram of a load distribution range.
16 is a payload release system overview diagram illustrating an outline of a second embodiment of the payload release equipment according to the present invention.
FIG. 17 is a cross-sectional view showing a state in which a secondary bullet is housed in the primary emitter, similarly.
FIG. 18 is also an operation explanatory diagram of the load distribution.
FIG. 19 is also an operation explanatory diagram of the load distribution.
FIG. 20 is also an explanatory diagram of a load distribution range.
FIG. 21 is a schematic explanatory diagram of a conventional load distribution system.
FIG. 22 is also a schematic explanatory view of a conventional mounted object, in which (a) is a front view of a main bullet, and (b) is a cross-sectional view taken along line II.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Flying body 2 Airframe outer plate 10 Primary discharge device 11 Discharge cylinder 14 Gas generation part 15 1st pusher plate 16 2nd pusher plate 16a Firing needle 17 Lid 20 Secondary discharge device 21 Cylindrical body 21a Base end flange 21b End flange 22 Slave bullet holder 23 Sleeve 24 Timed actuation mechanism storage 25 Spin motor 26 Slave bullet support 27 Spring 30 Locking means 31 Restraint holder 32 Band 33 Shear pin (coupling means)
40 Submunition V1 Flight speed V2 of secondary emitter V2 Flight speed V3 Primary emission speed (secondary emitter lateral velocity)
L3 Flight distance in the horizontal direction of the secondary emitter La Distance from the landing point of the secondary emitter to the landing point of each bullet 50

Claims (2)

In the mounted object discharge device which mounts a plurality of mounted objects and releases the plurality of mounted objects after being released from the flying object,
A mounted object holder having a columnar mounted object supporting portion that extends on an axis passing through the center of gravity of the mounted object discharge device and in which a plurality of mounted objects are arranged in a circle around the axis along the outer periphery;
A band-shaped body that collectively surrounds a plurality of loads mounted on the outer periphery of the load-supporting part from the outside, and a coupling means that bonds between both ends of the band-shaped body and is damaged by a predetermined load. Binding means,
And a load imparting device for rotating the load holder around the axis. Furthermore, it has a cylindrical body that accommodates the loaded object that is secured to the loaded object holder by the securing means, and the loaded object holder and the loaded object are accommodated in the cylindrical body and mounted on the flying object. 2. The rotation applying means operates according to claim 1 , wherein the load holder protrudes from the tubular body in conjunction with the release of the flying object and flies together with the tubular body, and the rotation applying means is activated after a predetermined time has elapsed from the flying body. Load release device.

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