Information
-
Patent Grant
-
6227119
-
Patent Number
6,227,119
-
Date Filed
Friday, October 30, 199826 years ago
-
Date Issued
Tuesday, May 8, 200123 years ago
-
Inventors
-
Original Assignees
-
Examiners
Agents
- Burns, Doane, Swecker & Mathis, LLP
-
CPC
-
US Classifications
Field of Search
US
- 102 501
- 102 473
- 102 529
-
International Classifications
-
Abstract
The present invention is devoted to providing projectiles which can be configured as relatively lightweight warhead assemblies that are comparable to heavier warhead assemblies in target-destruction effectiveness. In accordance with exemplary embodiments, the lightweight warhead assemblies can be more efficiently carried in greater numbers on, for example, aircraft platforms. Because these lightweight warhead assemblies can replace existing, larger warhead assemblies, a standard size warhead assembly can be used to attack different types of targets. In addition, various submunitions or unitary warheads can be incorporated into payload containers having a common external shape with common aerodynamic and mass properties, as well as common guidance, sensor, fuzing, and mechanical and electrical interfaces. A standardized, or modular approach improves the interchangeability of various warhead assemblies, reduces costs of configuring and operating the aircraft platform, and enables a reduction in the size of internal weapon bays of aircraft platforms.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
The invention generally relates to projectiles, and more particularly, to lighter warhead assemblies which achieve levels of performance that are comparable to much heavier warhead assemblies.
2. State of the Art
The design of an effective penetrating projectile, such as a warhead, often involves balancing between competing requirements. A warhead must have adequate penetration, blast, and fragmentation performance to effectively destroy the intended target. One important factor in the design of a warhead is its mass. The greater the mass of the warhead, the greater force imparted to the target upon impact. However, the greater the mass of the warhead, the more difficult it is to deliver the warhead to the target, particularly with munitions carried by aircraft platforms. Warheads of relatively large mass require more fuel to carry, reduce maneuverability of the aircraft, occupy more space on the aircraft platform, appear more prominently on radar signatures, and must be carried in fewer numbers.
Existing relatively lightweight warhead assemblies having a weight on the order of 1,000 lbs. lack sufficient performance capabilities and can be ineffective against certain targets. Therefore, it is common to carry different warhead assemblies of varying sizes and configurations on aircraft platforms to accommodate different types of targets. These warheads are different in their aerodynamics, their mass, and their mechanical and electrical interfaces with the aircraft. These differences limit the flexibility of the aircraft platform to accommodate different weapon configurations, increase the cost of configuring and operating the aircraft, and require larger weapon bays to accommodate the warhead assemblies.
Accordingly, it would be desirable to provide projectiles which can accommodate different types of targets, but which avoid the drawbacks associated with delivering different warhead assemblies designed to accommodate different types of targets.
SUMMARY OF THE INVENTION
The present invention is devoted to providing projectiles which can be configured as relatively lightweight warhead assemblies that are comparable to heavier warhead assemblies in target-destruction effectiveness. In accordance with exemplary embodiments, the lightweight warhead assemblies can be more efficiently carried in greater numbers on, for example, aircraft platforms. Because these lightweight warhead assemblies can replace existing, larger warhead assemblies, a standard size warhead assembly can be used to attack different types of targets. In addition, various submunitions or unitary warheads can be incorporated into payload containers having a common external shape with common aerodynamic and mass properties, as well as common guidance, sensor, fuzing, and mechanical and electrical interfaces. A standardized, or modular approach improves the interchangeability of various warhead assemblies, reduces costs of configuring and operating the aircraft platform, and enables a reduction in the size of internal weapon bays of aircraft platforms.
Generally speaking, exemplary embodiments are directed to warhead assemblies including a main body portion and a substantially ogive-shaped end portion, the substantially ogive-shaped end portion having an external surface with a first radius of curvature and an internal surface having a second radius of curvature, a ratio of the first radius of curvature to the second radius of curvature being approximately 1.27-1.40, and a substantially cylindrical body portion.
BRIEF DESCRIPTION OF THE DRAWING FIGURES
Other objects and advantages of the present invention will become more apparent to those skilled in the art from reading the following detailed description of preferred embodiments in conjunction with the accompanying drawings, wherein like elements have been designated with like reference numerals, and wherein:
FIG. 1
is a side view of a warhead assembly constructed according to an exemplary embodiment of the present invention;
FIG. 2
is a cross-sectional view of the
FIG. 1
warhead casing;
FIG. 3
is an enlarged partial cross-sectional view of the
FIG. 2
warhead casing;
FIG. 4
is an enlarged partial cross-sectional view of the
FIG. 2
warhead casing;
FIG. 5
is a cross-sectional view taken along line
5
—
5
of
FIG. 1
;
FIG. 6A
is an enlarged partial cross-sectional view of the
FIG. 1
area
6
—
6
;
FIG. 6B
is a top view of a warhead assembly including a guidance kit according to an exemplary embodiment of the present invention;
FIG. 7
is a partial, enlarged cross-sectional view of the
FIG. 1
area
7
—
7
.
FIG. 8
is a side view of the warhead assembly of
FIG. 1
including a tail section.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
FIG. 1
illustrates an exemplary warhead assembly
100
constructed according to the principles of the present invention. The warhead assembly
100
includes a warhead casing
200
having a longitudinal axis A, a hardback assembly
500
, a retaining member
600
, and a fuse assembly
700
.
Referring to
FIG. 2
, the warhead casing
200
comprises a generally cylindrical main body portion
201
, a first open-end portion
203
defining a bore
205
, and a second substantially ogive-shaped closed end portion
207
. The main body portion together with the first and second end portions define a substantially continuous exterior peripheral surface
211
and interior surface
213
.
The internal longitudinal dimension of the warhead casing
200
is indicated by reference numeral
219
, and is measured from a first substantially flat end surface
209
at first end portion
203
to a second substantially flat interior end surface
215
defined at second end portion
207
. The external longitudinal dimension of the warhead casing
200
is indicated by reference numeral
221
, and is measured from the first end surface
209
to a second exterior end surface
217
located at second end portion
207
.
The longitudinal distance between the second interior end surface
215
and the second exterior end surface
217
constitutes a solid section of the second end portion
207
which is indicated by reference numeral
220
, and which corresponds to the difference between the internal longitudinal dimension and external longitudinal dimension. The extent of this solid section of second end portion
207
is an important factor in defining the mass distribution and penetrability of the warhead casing
200
. In an exemplary embodiment, the ratio of the longitudinal extent
220
of this solid section over the external longitudinal dimension
221
is on the order of 0.084-0.086, but can be any other specified ratio depending upon desired performance characteristics.
Other features of the second substantially ogive-shaped end portion
207
are illustrated in
FIG. 3. A
first interior tangent point
323
and a first exterior tangent point
325
are defined along interior surface
213
, and exterior surface
211
, respectively, in an area of transition between the main generally cylindrical body portion
201
and the substantially ogive-shaped second end portion
207
. The first and second tangent points
323
and
325
are located at a predetermined longitudinal distance
327
from the second interior end surface
215
, and are spaced from the second exterior end surface
217
by a predetermined longitudinal distance
329
.
The location of tangent points
323
and
325
, as defined by longitudinal dimensions
327
and
329
, corresponds to the extent of longitudinal elongation of the ogive shape possessed by second end portion
207
. In one embodiment, the ratio of longitudinal dimension
329
to longitudinal dimension
221
of the warhead casing
200
is on the order of 0.38, but can be any specified ratio depending on desired performance characteristics. This relative dimensioning is indicative of the longitudinal dimensions or elongation of the ogive-shaped second end portion
207
relative to the overall longitudinal dimension of the warhead casing
200
, and has been shown to provide advantageous results.
The outer diameter of the warhead casing
200
, as measured at the
FIG. 3
tangent points
323
and
325
, is indicated by reference numeral
331
. As illustrated in
FIG. 3
, the warhead casing
201
curves inwardly or gradually converges, defining a radius of curvature
333
along exterior surface
211
, and a radius of curvature
335
along interior surface
213
. The radial thickness
337
(the radial direction being normal to the longitudinal axis A) of the warhead casing
200
gradually increases in a direction from the first and second tangent points
323
and
325
toward the second end portion
207
as a result of a predetermined difference in the radii of curvature
333
and
335
. In an exemplary embodiment, the ratio of the radius of curvature
333
over radius of curvature
335
is on the order of 1.27-1.40, but can be any other specified ratio depending on desired performance characteristics. These relative dimensions are indicative of the rate of increase in radial thickness of the warhead casing, and provide desirable thickness and mass distribution properties in accordance with an exemplary embodiment.
In a direction toward second end surface
217
of the second end portion
207
, second interior tangent points
339
and
339
′ are disposed along interior surface
213
and are located a predetermined longitudinal distance
343
from the second interior end surface
215
. Tangent point
339
is also a predetermined radial distance
340
from the portion of exterior surface
211
located at exterior tangent point
325
. Tangent points
339
and
339
′ are separated by a predetermined radial separation
341
.
The portion of interior surface
213
extending between tangent points
339
and
339
′ to second interior flat surface
215
constitutes a substantially curved surface having a radius of curvature
345
. The second interior end surface
215
is defined by radial dimension
347
. The extent of radial dimension
347
helps define the interior shape and the mass distribution properties of warhead casing
200
.
The second exterior end surface
217
is defined by a predetermined radial dimension
349
. The extent of radial dimension
349
helps define the exterior shape and the mass distribution properties of warhead casing
200
.
In an exemplary embodiment, the warhead casing
200
further comprises a threaded nose portion
351
extending longitudinally from the second exterior end surface
217
.
Certain details of the first open end portion
203
, of warhead casing
200
will now be described by reference to FIG.
4
. As the main body portion
201
extends toward the first end surface
209
, a transition portion having a predetermined radius of curvature
453
is defined along exterior surface
211
. A sloped surface
455
connects the transition portion defined by radius of curvature
453
with a second transition point
459
. Sloped surface
455
defines a predetermined angle
457
relative to the longitudinal direction. A substantially flat surface
461
extends from second transition point
459
to the second flat end surface
209
.
The first end portion
203
defines a bore
205
having an inner diameter
463
. Similarly, substantially flat surface
461
defines an outer diameter
465
. By this construction, first end portion
203
is strengthened thereby permitting connection of various accessories, such as a booster section, to the warhead casing
200
.
Warhead casing
200
can be constructed of any suitable high strength material. For example, the warhead casing can be constructed of a heat treatable alloy steel. In an exemplary embodiment, the heat treatment is carried out to military specification MIL-H-6875, CL A. A suitable heat treated alloy steel will have a yield strength of approximately 170,000 psi or more, an ultimate strength of approximately 180,000 to 200,000 psi, or more, Charpy V-notch impact resistance at −40°(+/−) 2° Farenheight of approximately 20 ft.-lb. on 3 per section, with a 15 ft.-lb. minimum, or more, and a Brinnel hardness number (BHN) of approximately 375 to 415, or more. By way of example, one suitable heat treatable alloy is AISI 4335 steel.
The overall shape and dimensions of the warhead casing
200
are an important factor in achieving the desired objectives of the present invention. The following dimensions and ratios are given as an illustration of one exemplary embodiment of a warhead casing constructed according to the principles of the present invention.
|
Value (in inches, unless otherwise
|
Dimension
indicated)
|
|
219
64.52-64.64
|
220
5.94-6.06
|
221
70.52-70.64
|
327
21.011-21.031
|
329
27.011-27.031
|
331
11.50-11.70
|
333
80.99-81.01
|
335
58.0-64.0
|
337
0.94-1.06
|
340
4.02-4.18
|
341
3.38-3.44
|
343
1.97-2.03
|
345
0.45-1.05
|
347
1.984-2.004
|
349
2.310-2.330
|
457
2.5 0 6.5 degrees
|
463
9.57-9.63
|
465
12.97-13.03
|
|
Ratio
Value
|
|
333/335
1.27-1.40
|
220/221
0.084-0.086
|
329/221
0.382-0.383
|
|
A warhead assembly incorporating a warhead casing constructed in accordance with exemplary embodiments of the present invention provides numerous advantages. For example, by controlling the forward exterior and interior shape of the warhead casing, the particular thicknesses and variations in thicknesses of the warhead casing, and mass distribution, a warhead can be provided with exceptional structural strength, enabling survival of the warhead upon impact with hardened structures. The shape of the warhead casing enables penetration of hard materials such as rock or concrete to a greater depth than other warheads weighing on the order of 2,000 pounds, and to a depth that exceeds certain existing 1,000 pound class warheads.
FIG. 5
illustrates details of an exemplary hardback assembly
500
which can be mounted to the warhead casing
200
. Hardback assembly
500
includes a hardback plate
501
. The hardback plate
501
can be constructed of any suitable material, such as high strength aluminum alloy material. Hardback plate
501
is connected to an adaptor lug
503
by a suitable fastener member, such as a threaded bolt
505
. Adaptor lug
503
can also be constructed of any suitable material, such as a heat-treated alloy steel. Adaptor lug
503
is connected to the warhead casing by a suitable threaded fastener member, such as threaded bolt member
507
. Adapter lug member
503
defines an opening having a counter bore
509
disposed therein.
Hardback assembly
500
facilitates mounting of the warhead assembly
100
to a suitable launch platform, such as an aircraft, as known in the art.
As illustrated in
FIG. 6A
, a retaining member
600
is threadably received about the threaded nose portion
351
of warhead casing
200
. Retaining
600
includes a threaded internal bore
601
which mates with the exterior threading of nose member
351
of the warhead casing
200
. Once threaded over nose member
351
, a set screw
602
acts to fix the position of retaining member
600
relative to the warhead casing
200
. Retaining member
600
further includes an external threaded surface
603
and upstanding flange member
605
. Retaining member
600
can be formed of any suitable material, such as an alloy steel.
By this construction a retaining bolt member
600
permits attachment of various accessories to the second end portion
207
of the warhead casing
200
. As illustrated in
FIG. 6B
one such accessory is a guidance kit
607
. Guidance kit
607
includes means to generate signals which guide the flight path warhead assembly
100
. Any suitable guidance system can be used in conjunction with the present invention. Suitable guidance systems include active or semi-active laser guided systems, such as those used in a guided bomb unit (GBU-24) and (GBU-27), produced by Raytheon Corporation. Other guidance systems which can be used include a combined global positioning system/inertial navigation system (GPS/INS), which is known in the art.
Guidance kit member
607
may be attached to the warhead casing
200
via retaining member
600
in any suitable fashion. For example, a rear section of guidance kit member
607
can be threadably received over external threaded surface
603
of retaining member
600
. Guidance kit member
607
can further include one or more stabilizing and/or steering air vane members
609
.
At the opposite first end
203
of the
FIG. 2
warhead casing
200
, a fuse assembly
700
of the exemplary
FIG. 7
embodiment is at least partially received within bore
205
of the first end
203
. In the exemplary embodiment shown in
FIG. 7
, an aft closure retaining ring
701
is received within threaded counter bore
464
thereby retaining the fuse assembly
700
in its proper position.
Aft closure
703
is positively engaged by the aft closure retaining ring
701
. An opposite side of the aft closure is engaged by a shoulder
704
formed along bore
205
. By this construction, the aft closure
703
is positively located and retained in its proper position. Aft closure
703
is provided with one or more openings
705
which are closed by a threaded plug member
706
. A fuse liner
707
is received within the aft closure
703
. A fuse liner retaining flange
711
is provided at one end of the fuse liner
707
and is received upon a shoulder
713
formed along the interior of aft closure
703
. A fuse liner retaining ring
709
is threadably received within aft closure
703
and is threadably driven into positive engagement with fuse liner retaining flange
711
. In this manner, fuse liner
707
is positively retained within aft closure
703
.
In an embodiment of the present invention in which warhead casing
200
carries a payload material, fuse assembly
700
is provided to activate the payload material. Any suitable payload material can be carried within warhead casing
200
, such as conventional or nuclear explosives, as well as agent-defeating materials such as incendiaries, chemicals or submunitions. The components of fuse assembly
700
can be constructed of any suitable material. A high strength, heat treated alloy steel is one such suitable material.
End surface
209
can be further provided with a plurality of blind bores
715
. Bores
715
can serve as a means for attachment of an exemplary
FIG. 8
tail section
800
to the warhead casing
200
. As illustrated in
FIG. 8
, tail section
800
can be attached to the end surface
209
. The tail section
800
can include a suitable booster device. For example, a rocket booster motor can be incorporated in the tail section
800
. Tail section
800
can further include stabilizing and/or control vanes
801
. In an alternate embodiment, an appropriate guidance system can be mounted within tail section
800
, rather than through the
FIG. 3
threaded nose member
351
.
According to the principles of the present invention, the exemplary warhead assembly
100
can have a total weight on the order of 900-1,000 lbs. (with approximately 250 lbs. of payload materials), or any specified weight for a given payload, and still possess the penetration and destructive capabilities comparable with warhead assemblies of greater weight. For example, the warhead having a weight on the order of 900-1,000 lbs. can have performance characteristics comparable to a warhead weighing on the order of 2,000 pounds. Such relatively lightweight warhead assemblies can be carried more efficiently and in greater numbers on launch platforms. These relatively lightweight warhead assemblies can be used to replace existing heavier warhead assemblies without significant sacrifice in effectiveness. This standardization or modular approach provides significant cost savings benefits over existing systems, and enables a reduction in the space occupied by the warhead assemblies on launch platforms.
Although the present invention has been described by reference to particular embodiments, it is in no way limited thereby. To the contrary, modifications and variants will be apparent to those skilled in the art in the context of the following claims.
Claims
- 1. A warhead assembly comprising:a main body portion and a substantially ogive-shaped end portion, said substantially ogive-shaped end portion having an external surface with a first radius of curvature and an internal surface having a second radius of curvature, a ratio of the first radius of curvature to the second radius of curvature being approximately 1.27-1.40; and a substantially cylindrical body portion.
- 2. The warhead assembly of claim 1, further comprising:an open end portion defining a bore and a first end surface; a second external end surface and a second internal end surface defined by said substantially ogive-shaped end portion; a first longitudinal dimension extending between said second internal end surface and said second external end surface; and a second longitudinal dimension extending between said first end surface and said second external end surface, a ratio of said first longitudinal dimension over said second longitudinal dimension being approximately 0.084-0.086.
- 3. The warhead assembly of claim 2, wherein said second internal end surface is a substantially flat surface having a second radial dimension, said second radial dimension being approximately 1.984-2.004 inches.
- 4. The warhead assembly of claim 2, wherein said second external end surface is a substantially flat surface having a third radial dimension, said third radial dimension being approximately 1.984-2.004 inches.
- 5. The warhead assembly of claim 2, further comprising:a threaded nose member extending longitudinally from said second external end surface.
- 6. The warhead assembly of claim 5, further comprising:a retainer bolt threadably received about said threaded nose member.
- 7. The warhead assembly of claim 6, further comprising:a guidance kit connected to said retainer bolt.
- 8. The warhead assembly of claim 7, wherein said guidance kit further includes:a guidance system chosen from the group consisting of: an active laser-based system, a semi-active laser-based system, and a GPS/INS-based system.
- 9. The warhead assembly of claim 2, wherein said open end portion further includes:a first transition portion having a predetermined radius of curvature, a sloped surface extending from said first transition portion to a second transition point, and a substantially flat surface extending from said second transition point to said first end surface.
- 10. The warhead assembly of claim 2, further comprising:a fuse assembly, said fuse assembly being at least partially received within said bore of said open end portion.
- 11. The warhead assembly of claim 10, wherein said fuse assembly further includes:a fuse liner, said fuse liner being received within an aft closure ring; a fuse liner retaining ring engaged with said fuse liner to retain said fuse liner in position; and an aft closure ring threadably received within said bore and in engagement with said aft closure ring to retain said aft closure ring in position.
- 12. The warhead assembly of claim 2, further comprising:a tail section attached to said first end surface, said tail section including a booster for powering said warhead assembly.
- 13. The warhead assembly of claim 19, wherein said tail section further comprises: a guidance system, said guidance system being chosen from the group consisting of: an active laser-based system, a semi-active laser-based system, and a GPS/INS-based system.
- 14. The warhead assembly of claim 1, further comprising:a first internal tangent point along said internal surface, and a first external tangent point along said external surface, each of said first tangent points being located at an area of transition between said substantially cylindrical body portion and said substantially ogive-shaped end portion; and a third longitudinal dimension defined between said first tangent points and said second external end surface, a ratio of said third longitudinal dimension over said second longitudinal dimension is approximately 0.382-0.383.
- 15. The warhead assembly of claim 14, further comprising:a radial thickness measured at said first internal and external tangent points of approximately 0.94-1.06 inches, said radial thickness gradually increasing in a direction toward said second external end surface.
- 16. The warhead assembly of claim 14, further comprising: an outer diameter measured at said first internal and external tangent points, said outer diameter being approximately 11.50-11.70 inches.
- 17. The warhead assembly of claim 16, further comprising:a plurality of blind bores disposed in said first end surface.
- 18. The warhead assembly of claim 1, wherein said main body portion is formed from a heat-treated steel material and has a yield strength of approximately 170,000 psi or more, an ultimate strength of approximately 180,000 psi or more, a Charpy V-notch impact strength of approximately 20 ft.-lb. or more, and a Brinnel hardness number of approximately 375-415, or more.
- 19. The warhead assembly of claim 1, wherein said warhead assembly has a total weight of approximately 1,000 lbs. or less.
- 20. The warhead assembly of claim 1, further comprising:a hardback assembly having a hardback plate and an adapter lug, said hardback plate being attached to said adapter lug, and said adapter lug being attached to said main body portion.
- 21. A warhead casing comprising:a main body portion and a substantially ogive-shaped end portion, said substantially ogive-shaped end portion having an external surface with a first radius of curvature and an internal surface having a second radius of curvature, a ratio of the first radius of curvature to the second radius of curvature being approximately 1.27-1.40; and a substantially cylindrical body portion.
- 22. The warhead casing of claim 21, further comprising:an open end portion defining a bore and a first end surface; a second external end surface and a second internal end surface defined by said substantially ogive-shaped end portion; a first longitudinal dimension extending between said second internal end surface and said second external end surface; and a second longitudinal dimension extending between said first end surface and said second external end surface, a ratio of said first longitudinal dimension over said second longitudinal dimension being approximately 0.084-0.086.
US Referenced Citations (8)