U.S. patent number 3,818,833 [Application Number 05/281,904] was granted by the patent office on 1974-06-25 for independent multiple head forward firing system.
This patent grant is currently assigned to FMC Corporation. Invention is credited to Guy C. Throner, Jr..
United States Patent |
3,818,833 |
Throner, Jr. |
June 25, 1974 |
INDEPENDENT MULTIPLE HEAD FORWARD FIRING SYSTEM
Abstract
A missile carries a plurality of independent explosive heads
which when fired direct fragments only in a forward direction. The
missile releases all heads either in response to a timed delay from
drop or launch or in response to movement of the missile to a
predetermined position relative to the target. Upon release the
explosive heads are rotated to swing each head away from the other
heads while retaining orientation of each head so that firing of
the dispersed heads will cause fragments to discharge forwardly
toward the target without undue interference with the fragments
from other heads.
Inventors: |
Throner, Jr.; Guy C. (Saratoga,
CA) |
Assignee: |
FMC Corporation (San Jose,
CA)
|
Family
ID: |
23079261 |
Appl.
No.: |
05/281,904 |
Filed: |
August 18, 1972 |
Current U.S.
Class: |
102/389; 102/213;
102/214; 102/393 |
Current CPC
Class: |
F42B
12/58 (20130101); F42B 12/202 (20130101); F42B
10/56 (20130101); F42B 12/204 (20130101); F42B
12/208 (20130101) |
Current International
Class: |
F42B
10/00 (20060101); F42B 12/20 (20060101); F42B
12/58 (20060101); F42B 10/56 (20060101); F42B
12/02 (20060101); F42b 025/16 () |
Field of
Search: |
;89/1
;102/7.2,70.2,70.27,67,4 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Engle; Samuel W.
Attorney, Agent or Firm: Moore; A. J. Tripp; C. E.
Claims
I claim:
1. A forward firing system comprising a missile movable in a
forward direction toward a target area and including a tubular
body; a plurality of explosive heads in the form of discs
positioned in said body defining a stack of heads having a
longitudinal axis; each head including an explosive charge, a
fragmentation wall disposed only on the forward end of said
explosive charge, and a thin walled housing enclosing the remaining
portion of the head; means for rotating the stack of heads; means
for simultaneously releasing all heads in said stack of heads from
said body in response to the movement of the missile into range of
the target area; connecting means for releasably interconnecting
said heads in said stack and being responsive to rotation of said
stack and to the release of said stack from said body for
dispensing said heads from said stack and from each other in a
plurality of different directions while retaining directional
orientation of said heads relative to said target area; and means
for thereafter detonating the explosive charge in each of said
heads prior to the heads reaching the target area.
2. A forward firing system according to claim 1 wherein said
detonating means is a proximity fuze.
3. A forward firing system according to claim 2 wherein each of
said heads carries a signal wave generator and a signal reflector,
and means mounting at least a portion of said reflector for
movement from a compact stacked position against one end surface of
said head to an extended reflecting position spaced from said one
end of said head.
4. A forward firing system according to claim 3 wherein said one
end is the forward end of said head, and additionally comprising
forward expansible reflector supporting means movable between a
compact position encompassed within said associated head when said
head is in said stack, and an extended position forwardly of said
forward end of the head after the head has been swung away from
said stack.
5. A forward firing system according to claim 3 wherein said one
end is the rear end of said head and wherein said reflector is a
concave dish which contacts and conforms to the shape of the rear
wall of said head when the head is in said stack, and which is
spaced rearwardly of said rear wall in an operative reflecting
position when the head is released from said stack, and extendible
connecting means for connecting said reflector to said head when in
its operative reflecting position.
6. A forward firing head according to claim 3 wherein said tubular
body is a cylindrical housing having an axis of generation and
wherein said signal reflector includes a plurality of resiliently
stressed pie shaped leaves having their inner ends connected to the
forward end of said housing about said axis of generation and
having their outer ends free to move forwardly away from said
forward end, and means engaging the free ends of said pie shaped
leaves for bowing said leaves by moving the outer ends of said
leaves forwardly away from said fragmentation wall in position to
define a parabolic reflector for sending and collecting signals
reflected back from the target area.
7. A forward firing head according to claim 6 and additionally
comprising forwardly extendible resilient means movable between a
compact position encompassed by said housing and an extended
position projecting forwardly of said housing, said antenna being
mounted on the projectable end of said extendible resilient
means.
8. A forward firing head according to claim 1 wherein said
fragmentation wall is a planar wall.
Description
CROSS REFERENCE TO RELATED APPLICATIONS
The independent multiple head forward firing system of the present
invention is related to an application Ser. No. 281,878 by James F.
Cullinane et al filed on even date herewith and assigned to the
assignee of the present invention.
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention pertains to anti-personnel and anti-material weapons
and more particularly relates to a forward firing explosive head,
and a missile that carries a plurality of independent forward
firing explosive heads and means for dispersing the heads.
2. Description of the Prior Art
Fragmentary anti-personnel and anti-material explosive heads are
known which when exploded propel fragments at high velocity against
the target. However, the known fragmentation heads of this type not
only propel fragments at the target but also propel other fragments
away from the target. U.S. Pat. No. 3,500,714 which issued to
Cullinane on Mar. 17, 1970 and is assigned to the assignee of the
present invention discloses a system for spinning explosive heads
which is similar to that used in certain embodiments of the present
invention.
SUMMARY OF THE INVENTION
The multiple head forward firing system of the present invention
provides a fragmentary explosive head which when fired propels the
fragments only in a forward direction toward the target. A
plurality of these heads are preferably carried by a missile, such
as an aerial bomb, projectile, or guided missile; and the missile
releases each head either after a predetermined interval from
launching or when in range of the target for tangential separation
from each other while retaining their aimed orientation so that the
fragments of one head will not interfere with fragments fired from
other ones of the heads, and so that a wide target area will be
contacted by the fragments of these several heads.
It is, therefore, one object of the present invention to provide an
explosive head having a fragmentary wall only on the forward end of
the head for directional control of the fragment upon firing of the
head.
Another object is to provide a relatively light explosive head by
providing a fragmentation wall only on the forward end of the
head.
Another object is to provide a missile having a plurality of
forward firing heads therein with the heads retaining their
directional orientation and with each head being swung radially
outward from the missile when in the proximity of the target and
prior to firing the heads.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a perspective of a missile containing a plurality of
forward firing heads therein, the missile being illustrated as an
aerial bomb substantially as it would appear when on the bomb racks
of an aircraft.
FIG. 1A is a diagrammatic perspective with parts in section
illustrating the manner in which the forward firing heads are
stacked together.
FIG. 1B is a diagrammatic perspective of a missile illustrating
first means for rotating the missile for dispersing the explosive
heads, certain parts being cut away.
FIG. 1C is a diagrammatic side elevation illustrating second means
for rotating the missile, certain parts being cut away.
FIG. 1D is a side elevation similar to FIG. 1C illustrating third
means for rotating the missile, certain parts being cut away.
FIG. 2 is a diagrammatic perspective illustrating the missile after
a fuze has ignited cutting charges which have separated the nose
cone from the body of the missile and has longitudinally severed
the missile body into three sections, the plurality of forward
firing heads being shown as they appear after being spun out of the
open missile body.
FIG. 3 is a diagrammatic perspective illustrating the wide firing
pattern of the plurality of forward firing heads as the heads
approach the targets, the firing elevation being illustrated in
greatly foreshortened scale.
FIG. 4 is an enlarged diagrammatic central section taken through
one of the explosive heads.
FIG. 5 is a diagrammatic perspective similar to FIG. 2 but
illustrating a plurality of forward firing heads of a second
embodiment of the invention immediately after they have been
released from the missile, each head being fired by a proximity
fuze.
FIG. 6 is a diagrammatic perspective illustrating the firing
pattern of the heads of FIG. 5.
FIG. 7 is an enlarged diagrammatic central section taken through
one of the forward firing heads of FIG. 5 when the head is in its
compact position.
FIG. 8 is a section similar to FIG. 7 but illustrating the parts in
an expanded position.
FIG. 9 is a diagrammatic perspective similar to FIG. 2 but
illustrating a plurality of forward firing heads of a third
embodiment of the invention.
FIG. 10 is a diagrammatic perspective illustrating the firing
pattern of the heads of FIG. 9.
FIG. 11 is an enlarged diagrammatic central section taken through
one of the forward firing heads of FIG. 9 when the head is in its
compact position.
FIG. 12 is a section similar to FIG. 11 but illustrating the parts
in their expanded positions.
DESCRIPTION OF THE PREFERRED EMBODIMENT
The forward firing system 20 (FIGS. 1-4) of the first embodiment of
the invention is illustrated as a missile in the form of an aerial
bomb 22 having a plurality of independent forward firing heads 24
therein. It will be understood, however, that other types of
missiles, such as mortar shells, rockets, or anti-aircraft shells
may be used to transport or launch the forward firing heads toward
their targets.
In the illustrated first embodiment of the invention, the missile
or bomb 22 (FIG. 1) comprises a thin walled tubular body 26, a nose
cone 28 on one end of the body with a time fuze or proximity fuze
29 therein, and a tail assembly 30 on the other end with direction
controlling fins 32 pivotally mounted thereon all as is well known
in the art.
The forward firing heads 24 are in the shape of circular discs each
having a cylindrical wall 34 (FIG. 4) of plastic or thin metal with
a lower flange 36 and a rear flat wall 38. A lower or forward
fragmentation wall 40 made up of one or more layers 42 and 44 of
metal fragments 46 such as steel, is supported by the lower flange
36. A fragmenting plate may be substituted for the precut
fragmentation wall 40 if desired. The fragments 46 are normally
interconnected with sufficient strength to define the wall 40 but
separate into individual fragments 46 upon firing of an explosive
charge 48. The explosive charge 48 is illustrated as including a
wave shaper 50, and is fired by a fuze 52 such as a time delay
sub-missile fuze.
The plurality of heads 24 are concentrically stacked in the tubular
body 26 in abutting contact with each other as illustrated in FIG.
1B, 1C and 1D, and with the fragmentation wall 40 of each head
facing the nose cone 28 (FIG. 1). The fuze 29 is provided in order
to open the body 26 at a predetermined time from launch or at the
desired distance from the target. If the fuze is a proximity fuze,
it may be adjusted to fire when the missile is at any one of a
plurality of predetermined distances from the target. The fuze 29
(FIG. 1) is connected to an annular cutting charge 54 on the
internal surface of the body adjacent the nose cone 28, and is also
connected to three linear cutting charges 56 (only one being
illustrated in FIG. 1) placed at even intervals on the inner or
outer surface of the body 26 and extending longitudinally thereof
for substantially the full length of the body. Activation of the
fuze 29 fires the cutting charges 54 and 56 thus severing the nose
cone 28 from the body 26 and longitudinally cutting the body into
three pieces 58 (only two being shown in FIG. 2). The wind
resistance immediately strips the nose cone from the missile and
peels the three body strips 58 therefrom as indicated in FIG. 2
leaving the stack of forward firing heads 24 exposed for
substantial tangential dispersal.
In order to disperse the several forward firing heads 24, and
retain orientation of each head with its fragmentation wall 40
directed toward the target, each missile is first spun as a unit
thus imparting rotation to each forward firing head about its
longitudinal axis prior to activation of the cutting charges 54 and
56.
FIGS. 1B, 1C and 1D illustrate three separate ways of rotating at
least the load carrying portions of the missiles about their
longitudinal axes. In FIG. 1B, the tail assembly 30b is rigid with
the body 26b of the missile 22b and has its fins 32b angled
relative to the missiles longitudinal axis thus causing air
resistance to spin the entire missile. In FIG. 1C, the tail
assembly 30c is rigid with the body 26c of the missile 22c is spun
by a rotating motor 60c which is illustrated as a rocket propelled
device having several substantially tangential rocket motors 61c
which communicate with openings (not shown) in the missile body 26c
thus rotating the entire missile when activated. FIG. 1D
illustrates a missile spinning system that is similar to the
missile 22c except that the tail assembly 30d is journaled on the
body 26d and accordingly does not spin with the body when the motor
60d is activated.
As best illustrated in FIGS. 1A and 1D, the forward firing heads
24,24d in the missile are interconnected to each other and to the
head rotating motor 60,60d by pins 62,62d. The heads 24,24d are
releasably connected to the next adjacent head or to the motor
60,60d by one of the pins 62,62d, (FIG. 1A). Each pin 62,62d is
secured to one of the heads 24,24d (or the motor 60) adjacent its
periphery and is slidably received in a radial edge slot 64,64d in
the adjacent wall of the next adjacent head in a manner similar to
that disclosed in the aforementioned Cullinane patent. Thus, the
motor 60,60d causes all of the heads to rotate as a unit with the
end head or heads of the stack of heads being the first to be spun
from the stack of heads. The remaining plurality of heads will each
progressively peel off the ends of the stack of heads and will be
tangentially dispersed as indicated in FIG. 2. The gyroscopic
affect of each spinning head will maintain orientation of the head
with the fragmentation wall 40 facing the target.
In operation of the first embodiment of the invention, an aerial
bomb or missile 22 loaded with a stack of forward firing heads 24
therein is dropped from an aircraft. The fuze 29 is activated in
response to the bomb reaching a predetermined elevation above the
target; or alternately, in response to a predetermined interval of
time elasping from the time of drop, depends upon what type of fuze
is being used. The activation of the fuze 29 preferably occurs when
the bomb is within between about 5,000 to 200 feet from the target
area. If the bomb is of the type illustrated in FIGS. 1C or 1D,
activation of the fuze 29 first fires the motor 60c, 60d for a
period of about 1/10 to 2 seconds thereby spinning the missile.
After a delay of about 1/100 to 2 seconds, a delayed signal from
the fuze ignites the cutting charges 54 and 56 allowing air
resistance to peel the nose cone 28 and body strips 58 from the
stack of forward firing heads 24. The rotating heads 24 then
disperse outwardly as indicated in FIG. 2 before the time delay
sub-missile fuzes 52 (FIG. 4) fire their respective heads 24. The
fuses 52 fire after a preset delay after dispersion of about 1/100
to 10 seconds. The fired explosives 48 and 50 in each head breaks
the fragmentation wall 40 into a plurality of separate fragments
46. Subsequently all of the fragments 46 are thus propelled in a
generally conical pattern toward the target as illustrated in FIG.
3.
Although the size of the missile is not controlling, an effective
missile size may be within the range of about 4 to 60 inches in
diameter, and an effective fragment size may be about 10-1,000
grains.
The forward firing system 20' of the second embodiment of the
invention illustrated in FIGS. 5-8 is fired, and the heads 24' are
dispensed in a manner substantially the same as that of the first
embodiment of the invention. The system 20' differs only in the
particular type and shape of forward firing head 24' being used.
Accordingly, only the heads 24' will be described in detail and
parts which are similar to those described in the first embodiment
of the invention will be assigned the same numerals followed by a
prime (').
When the heads 24' are stacked in the bomb 22' they are in their
compacted positions as illustrated in FIG. 7, and after the heads
24' have been rotated and dispersed from the bomb they expand to
the position illustrated in FIGS. 5 and 8. A jet motor or angled
vanes 32' in the tail assembly 30' may be used to spin the head as
in the first embodiment of the invention and serve to disperse the
several forward firing heads as diagrammatically illustrated in
FIGS. 5 and 6.
Each forward firing head 24' comprises a relatively thin plastic or
metal, generally disc shaped shell 86 (FIGS. 7 and 8). The shell 86
includes a cylindrical side wall 88 having an outwardly bowed
concave lower wall 90 and an outwardly bowed concave upper wall 92.
A concave fragmentation wall 94 made up of fragments 96 within the
shell 86 bears against the lower wall and has an explosive charge
98 and a wave shaper 100 thereabove. It is to be understood that
the wave shaper is optional. A proximity fuze 102 which includes a
primary reflector or antenna 106, a booster 103, and a wave
generator is provided for each head 24'. The reflector or antenna
106 is mounted on the free end of an expandible helical leaf spring
108 (FIG. 8) which fits within a housing 109 secured in a small
cavity in the lower wall 90 when compacted as illustrated in FIG.
7. The antenna 106 is projected outwardly a substantial distance
from the forward wall 90 as illustrated in FIG. 8 in response to
the next forward head 24' moving away from the wall 90. The leaf
spring 108 may be of the type disclosed in U.S. Pat. No. 3,587,658
which issued to Charles M. Giltner on June 28, 1971.
As indicated in FIG. 8, the antenna or reflector 106 directs
electrical wave signals against a multi-leafed parabolic secondary
reflector 110 for reflection to the target area. The reflector 110
thereafter collects waves reflected off the target and target area,
and focuses all such return signals at the apex of the concave
reflector or antenna until the set distance is ascertained by the
fuze which then detonates the explosive 98.
The secondary reflector 110 is composed of a plurality of resilient
pie shaped leafs 112 having their inner ends secured to the outer
periphery of the housing 109 and having their outer ends engaging a
ring 114 slidably received on the outer periphery of the side wall
88 of the shell 86. A helical spring 116 is disposed between the
slidable ring 114 and a stationary ring 118 that is rigidly secured
to the cylindrical side wall 88. As indicated in FIG. 7, each pin
62' of the spinning mechanism is secured to a hub 119 on the ring
114 of one head 24' and is slidably received in an edge slot 120 in
the stationary ring 118 of the next adjacent head 24'. When the
pins 62' have been removed from their associated slots 120 by
swinging the heads 24' in the stack away from their stacked
position as previously described, the reflector 106 and the
secondary reflector 110 of the next above head 24' are free to
extend under the influence of the helical leaf spring 108 and the
helical spring 116, respectively.
Since the gyroscopic affect imparted to each head 24' as it is
rotated and swung from the stack of heads may not be sufficient to
compensate for the affect of air resistance acting upon the
elongated head when in the expanded position indicated in FIG. 8, a
retarding device 128 is provided. The drag or retarding device is
attached to the center of the upper wall 92 by a swivel mounted
plurality of flexible lines 132 such as wires or cords.
The operation of the second embodiment of the invention is
substantially the same as that of the first embodiment except that
firing of each forward firing head 24' is controlled by the
proximity fuze 102. The booster 103 of the fuze 102 fires when
sufficiently radiated wave signal energy which energy was
previously generated by the wave generator of the fuze and sent to
the target, is collected from the target area and reflected back to
the firing system by the reflector 110. The retarding device 128
serves to maintain the heads 24' aimed at the target. As indicated
in FIG. 6, when the heads are fired, the fragmentation wall 94
breaks into its individual fragments 96 which first destroys the
parts of the head 24' therebelow and then covers the target area
with a conical pattern of fragments moving toward the target at
very high speeds. It will also be noted that all fragments are
directed toward the target as opposed to having some of the
fragments being wasted by being directed outwardly to the sides or
in a direction away from the target.
The forward firing system 20" of the third embodiment of the
invention is illustrated in FIGS. 9-12. The system 20" differs from
the first and second embodiments only in that the forward firing
heads 24" differ somewhat from the previously described heads.
Accordingly, only the heads 24" will be described in detail and
parts which are similar to those described in the first embodiment
of the invention will be assigned the same numerals followed by a
double prime (").
As indicated in FIGS. 11 and 12, each forward firing head 24"
includes a shell 140 having a cylindrical side wall 142 with a
flange 144 on its lower end and with a concave upper wall 146
provided with a cavity for receiving a proximity fuze 148 which
includes a detonator and a wave generator. A fragmentation wall 150
made up of a plurality of interconnected fragments 152 closes the
lower end of the shell 140 and has an explosive charge 154 and a
wave shaper 156 thereabove. It is to be understood that the wave
shaper is optional. A combination reflector and retarding device
158 is shaped as a perforated dish 159 and is connected to the
center of the proximity fuze 148 by swiveled and flexible
connectors 160 as cables or the like.
As in the first embodiment of the invention, when the plurality of
forward firing heads 24" are stacked in the bomb 22", they are
interconnected by pins 62" which are secured to ears 162 in the
forward firing heads 24' and project into radial edge slots 164 in
the next adjacent head. The bomb 22" may be rotated about its
longitudinal axis either by a rocket motor or by angled fins 32" on
the tail assembly 30" as in the other two forms of the
invention.
In operation of the third embodiment of the invention, after the
stack of forward firing heads have been spun they are released from
their missile 22" (FIG. 9). The heads then swing outwardly from the
stack of heads and eventually assume the positions illustrated in
FIG. 9 with the combined retarding devices and reflectors 158 in
their extended positions. Each head 24 then moves toward the target
until the signals from the wave generator that was previously
reflected to the target area by the dished reflector 159 are
reflected back to the fuze mechanism 148 by the target and
reflector 159. At the set altitude the proximity fuze 148 initiates
the explosive train. The explosive charge 154 projects the
fragmentation wall 150 onto the target area at high speed in
conical patterns as indicated in FIG. 10.
From the foregoing description it is apparent that the forward
firing heads of the present invention are stacked in the missile
and the missile is spun about its longitudinal axis either by
angled tail fins or a rocket motor to induce spin. The heads are
released from the missile in response to the firing of a first time
delay or proximity fuze in the nose cone of the missile. The
rotated heads then independently disperse over a relatively wide
area and gyroscopically retain their directional control with their
fragmentation walls directed toward the target. The explosive
charge in each head is then fired either in response to a time
delay fuze or in response to an adjustable proximity fuze as in the
other embodiments of the invention. A retarding device is provided
on certain of the heads to retain orientation of the heads and to
provide for more effective control of the firing of the heads.
Since only one wall of each forward firing head is a fragmentation
wall, and since that wall is directed toward the target, all
fragments are propelled against the target area upon explosion of
the head and are not wasted by flying away from the target in other
directions.
Although the best mode contemplated for carrying out the present
invention has been herein shown and described, it will be apparent
that modification and variation may be made without departing from
what is regarded to be the subject matter of the invention.
* * * * *