U.S. patent number 3,903,804 [Application Number 04/491,858] was granted by the patent office on 1975-09-09 for rocket-propelled cluster weapon.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to John L. Luttrell, William E. Preston, William B. Richardson.
United States Patent |
3,903,804 |
Luttrell , et al. |
September 9, 1975 |
Rocket-propelled cluster weapon
Abstract
A warhead for an aerial missile containing a plurality of
submissiles. The arhead is provided with an inertia responsive mass
which in response to acceleration forces overcomes the forward
urging of spring to maintain a pair of normally outwardly urged
detents seated in the annular groove on a centrally disposed axial
shaft thereby to maintain the slideable warhead nose forwardly
urged to seal the warhead against admission of ram air pressure
into the warhead cavity. Upon deceleration, the spring urges the
inertia mass forwardly enabling the detents to unseat and the
warhead nose to slide rearwardly thereby permitting admission of
ram air pressure into the warhead cavity which affects rupture of
the warhead fairing and release of the submissiles along an
intercept path to the target.
Inventors: |
Luttrell; John L. (Silver
Spring, MD), Preston; William E. (Silver Spring, MD),
Richardson; William B. (Silver Spring, MD) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (Washington,
DC)
|
Family
ID: |
23953958 |
Appl.
No.: |
04/491,858 |
Filed: |
September 27, 1965 |
Current U.S.
Class: |
102/489;
102/703 |
Current CPC
Class: |
F42B
12/64 (20130101); Y10S 102/703 (20130101) |
Current International
Class: |
F42B
12/64 (20060101); F42B 12/02 (20060101); F42B
013/50 () |
Field of
Search: |
;102/2-4,7.2,49S,69,34.4,35.6,37.6 ;89/1.817 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Pendegrass; Verlin R.
Attorney, Agent or Firm: Sciascia; R. S. Cooke; J. A.
Government Interests
The invention described herein may be manufactured and used by or
for the Government of the United States of America for governmental
purposes without the payment of any royalties thereon or therefor.
Claims
What is claimed is:
1. A missile warhead comprising
a frusto-conical warhead fairing having an axial bore extending
therethrough,
a base plate adapted to be mounted upon a missle and having the
base of the frusto-conical fairing secured thereto, said plate
closing one end of said axial bore,
a support shaft mounted upon said base plate and extending into
said axial bore,
said fairing having a counterbore formed therein adjacent said base
plate,
a plurality of submissiles positioned within said counterbore,
said fairing having an internal cavity formed therein adjacent the
open end of said axial bore and being in fluid communication with
said axial bore, the diameter of said cavity being greater than the
diameter of said bore,
a submissile release assembly slideably mounted upon said shaft for
movement from a first position wherein said assembly prevents air
flow into the cavity to a second position wherein said assembly
permits air to flow into said cavity, and
means for locking said release assembly in said first position and
for unlocking said release assembly in response to deceleration of
the warhead for movement to said second position,
whereby ram air pressure about the warhead may enter the cavity
upon deceleration of the warhead occurring at the termination of
thrust by a warhead propelling motor to tear away the fairing and
release the submissiles for a ballistic trajectory toward a
target.
2. The warhead of claim 1 wherein said plurality of submissiles are
packed in an annular cluster having an inner diameter greater than
the diameter of said axial bore.
3. The warhead of claim 2 wherein said submissiles are constructed
of an inert high density material.
4. The warhead of claim 3 wherein said submissiles have a pointed
nose portion and an elongated body portion and have fins mounted
thereon to stabilize the ballistic flight of the submissiles.
5. The warhead of claim 1 wherein said fairing is constructed of a
material which, when subjected to ram air pressure within said
cavity, will tear apart and open the fairing for release of the
submissiles.
6. The warhead of claim 1 wherein said fairing comprises an annular
body having spaced apart walls of thin metallic material,
a mass of lightweight filler material positioned within and filling
the space between said walls.
7. The warhead of claim 6 wherein said walls have stress
concentrating grooves formed therein and extending from the apex of
the fairing to the base of the fairing.
8. The warhead of claim 1 wherein said submissile release assembly
comprises
a hollow cylindrical housing coaxially mounted upon said shaft for
sliding movement thereon,
said cylindrical housing having a hemispherical end portion formed
thereon,
whereby when said submissile release assembly is in said first
position, the hemispherical end portion provides the fairing with a
smooth aerodynamic surface.
9. The warhead of claim 8 further comprising
a re-entrant annular flange formed on said fairing adjacent said
axial bore at the apex end of said fairing, and
an annular flange formed on the outer peripheral surface of said
housing and releasably interlocking said re-entrant flange when
said housing is in said first position.
10. The warhead of claim 8 wherein said means for locking said
submissile release assembly comprises
an annular inertial weight coaxially mounted upon said shaft and
being positioned within said cylindrical housing,
a spring for resiliently biasing said weight toward the apex of
said fairing,
at least one locking detect mounted upon said housing for locking
engagement with a groove formed in said shaft,
a shear pin for releasably holding said weight in a locking
position wherein said detents are engaged by said weight and held
in locking engagement with the groove in said shaft,
whereby acceleration of the warhead by a propelling motor will
sever the shear pin to permit the resilient biasing spring to move
the weight toward the apex of the fairing after termination of
thrust by the propelling motor, thus permitting the detent to be
disengaged from the groove in said shaft to free said housing for
movement along the shaft and thereby permit ram air pressure to
enter said cavity and remove said fairing and release
submissiles.
11. A missile warhead comprising
a tapered fairing having an opening at its apex and an internal
cavity formed therein
a plurality of submissiles positioned within said cavity,
an elongate shaft axially secured within said fairing and having a
groove formed therein,
an assembly slideably mounted on said shaft and having an end
portion of substantially the same size as said fairing opening and
at least one resiliently urged detent,
an inertia mass slideably mounted on said shaft,
resilient means normally urging said mass in a forwardly
direction,
said mass moving rearwardly on said shaft in response to
acceleration forces to effect seating of said detent in said groove
for securing said end portion in sealing engagement with said
opening thereby preventing admission of ram air pressure into said
cavity, said mass being urged forwardly by said resilient means in
response to deceleration forces to effect unseating of said detent
and release of said assembly for rearward movement thereby
unsecuring said end portion from sealing engagement with said
opening and enabling admission of ram air pressure into said cavity
for rupturing of said fairing and release of said submissiles.
12. A missile warhead according to claim 11 and including means for
maintaining said inertia mass in an initial position on said shaft
and for affecting release of said mass for movement in response to
a shearing force.
Description
The present invention relates to warheads and more particularly to
a warhead for a rocket or missile containing a cluster of
submissiles which are released from the warhead at the time of
burnout of the rocket propellant for impact with the target.
It has long been the practice to employ multiparticle warheads for
projectiles or rockets, the particles being formed by fragmentation
of the warhead casing upon the detonation of an explosive charge
within the warhead. Although such warheads work satisfactorily
under most conditions, the full potential of the warhead is not
utilized because the size of the particles produced by the
fragmentation of the warhead is unpredictable and is at best
dificult to control by scoring of the warhead casing. In the
conventional warheads, the fragments from the warhead casing
produced upon detonation of the explosive charge are usually
projected in all directions in a random manner, thus producing the
situation that the particular particles which hit the target may
strike the target at a tangential angle and therefore do not
inflict their full damage upon the target.
The general purpose of this invention is to provide a warhead for a
rocket which embraces all of the advantages of similarly employed
warheads and possesses none of the aforedescribed disadvantages. To
attain this objective, the warhead of the present invention
contains a cluster of submissiles having flight stabilizing fins
thereon and being positioned within a warhead fairing which is
caused to open upon the burnout of the rocket propellant whereby
the rocket and fairing decelerate and permit the submissiles to
continue their travel toward the target at hypervelocity speeds.
Upon release from the fairing, the flight stabilized submissiles
travel in an intercept path with the target along slightly
diverging paths to produce a shotgun-like pattern to assure impact
with the target by one or more of the submissiles at an angle
substantially normal to the target, thus enabling the submissile to
inflict its maximum destructive capability.
It is an object of this invention to provide a simple and reliable
yet highly effective weapon for projecting a plurality of inert
projectiles at a target.
Another object of the invention is to provide a warhead for
launching a cluster of projectiles along an intercept path with a
target at hypervelocity speeds.
Another object of the invention is to provide a rocket warhead for
releasing a cluster of projectiles in such a manner that each of
the projectiles takes an intercept path with a target.
Other objects and many of the attendant advantages of this
invention will be readily appreciated as the same becomes better
understood by reference to the following detailed description when
considered in connection with the accompanying drawing wherein:
The FIGURE shows a longitudinal view of the weapon with the warhead
of the weapon shown in section.
Referring now to the drawing, there is shown a warhead 10 adapted
to be attached to the forward portion of a rocket 11 by any
suitable means, the details of the rocket not being significant for
the purposes of this invention since the warhead may be delivered
by any one of a plurality of conventional rockets. The body of the
warhead is defined by a substantially frusto-conical fairing 12
having an axial bore 13 extending therethrough to receive the nose
element for triggering the cluster release system. The fairing is
further provided with a counterbore 14 to define a chamber for
receiving a cluster of inert submissiles 15. Each of the
submissiles is formed from an inert high density material and is
provided with an elongated configuration having a low aerodynamic
drag and being provided with fins 16 on the tail portion thereof to
stabilize the flight of the submissile during its travel toward the
target upon release from the warhead. The submissiles are packed in
annular cluster around an annular submissile support block 17 which
is secured to a axial shaft 18 mounted upon a support base 19. The
support base 19 is secured to the forward portion of a rocket motor
casing 11 by any suitable means and has formed therein slots 21 to
receive the tail fins 16 of the submissiles to hold the submissiles
in their stacked array.
The warhead is so constructed as to release the cluster of
submissiles 15 upon sensing the condition of deceleration caused by
burnout of the rocket propellant. The interior of the warhead is
provided with an enlarged inner diameter portion 22 to define a
cavity to receive ram air pressure after the rocket propellant has
been consumed. The warhead fairing is so constructed as to be torn
apart by the entrance of ram air pressure into the cavity 22 in
such a manner as to provide an uninterrupted path for the
submissiles as the fairing and rocket motor further decelerate and
the submissiles are permitted to continue on their path toward
their target. To permit an easy and effective separation for
removal of the fairing assembly, the fairing is constructed of a
thin metallic skin and is packed with a lightweight rigid filler
material to give it regidity and strength, the metallic skin of the
fairing being provided with a plurality of grooves extending from
the apex to the base of the frusto-conical fairing to provide
weakened portions in the fairing skin. Upon entrance of the ram air
pressure into the cavity 22, the ram air pressure acts upon the
tapered cavity wall 24 to produce forces on the fairing in a
radially outwardly direction, thus causing the fairing to tear
along the weakened grooves formed in the fairing skin and
consequently be removed from its obstructing position in the path
of the submissiles. Entrance of ram air pressure into the cavity 22
is prevented prior to propellant burnout by means of a cluster
release assembly 23 which seals the entrance to the cavity and is
withdrawn from its sealing position upon the deceleration of the
warhead.
The cluster release assembly 23 has a cylindrical body portion
having a diameter substantially equal to the inner diameter of the
entrance to the apex of the frusto-conical fairing. The cluster
release assembly is provided with a hemispherical end portion 25
which, when the cluster release assembly is in its sealing
position, provides the fairing with a continuous smooth aerodynamic
surface at the forward end thereof. The cluster release assembly is
mounted upon a shaft 26 which is connected to the base 19 by the
axial shaft 18. The cluster release assembly is adapted to be moved
by ram air pressure acting upon the hemispherical surface 25 from
its sealing position shown in the drawing to an open position
rearwardly along shaft 26. The release assembly is locked in the
position shown by means of a pair of spring fingers 27 having
detents 28 integrally formed on the ends thereof, the detents 28
being received within an annular recess 29 formed in the shaft 26.
The spring fingers 27 are resiliently baised outwardly out of
locking engagement with the annular recess 29 but are held in the
locked position by means of a peripheral engagement with a
cylindrical inertial weight 31. The inertial weight is mounted upon
the shaft 26 for longitudinal sliding movement thereon and is
resiliently baised in a forward direction for contact with a stop
plate 32 by means of a helical compression spring 33 positioned
within the cylindrical release assembly. The inertial weight is
held in the position shown by means of a shear pin 34 positioned
within and extending through complimentary apertures formed in the
inertial weight and the shaft 26. When the cluster release assembly
is in its sealing position shown in the FIGURE, an annular flange
35 mounted upon the release assembly 23 and spaced therefrom is in
locking engagement with an inwardly directed reentrant flange 36
formed at the apex of the frusto-conical fairing.
In operation, the rocket 11 is aimed at the target and ignited, the
setback forces of acceleration act upon the inertial weight 31 to
sever the shear pin 34 and permit the inertial weight to fully
compress the helical spring 33. During the acceleration of the
rocket throughout the burning time of the rocket propellant, the
inertial weight holds the helical spring 33 in its fully compressed
condition and continues to lock the detents 28 within the annular
recess 29 to maintain the cluster release mechanism 23 in its
locked sealing position. Upon the consumption of the rocket fuel,
the rocket begins to decelerate, thus causing the inertial weight
31 to move forward under the force of deceleration and as assisted
by the compression spring 33 so that the inertial weight reaches an
abutting contact with the stop plate 32. When the inertial weight
is in this position, the locking detents 28 on the spring fingers
27 are permitted to be urged radially outwardly out of engagement
with the annular recess 29 in the shaft thereby freeing the cluster
release mechanism 23 for longitudinal movement along the shaft 26.
The ram air pressure acting upon the hemispherical end portion 25
of the cluster release assembly forces the cluster release assembly
23 into abutment with annular wall 37 formed on the shaft 26. The
cylindrical cluster release mechanism having been moved into
contact with wall 37, the locking engagement of annular flanges 35
and 36 is uncoupled and the ram air pressure is permitted to enter
the cavity 22. As the ram air pressure acts upon the tapered cavity
wall 24, moments of force are developed perpendicular to the axis
of the warhead to tear the fairing 12 along its weakened groove
portions and remove the fairing from the warhead, thus further
decelerating the rocket motor and warhead and permitting the
cluster of submissles 15 to continue forwardly along an intercept
path toward the target. The aerodynamic pressure acting upon the
cluster of submissiles causes the submissiles to be deployed in a
shotgun-like pattern while the fins 16 on the tail sections of the
submissiles maintain the submissiles in a trajectory substantially
identical to that of the trajectory of the warhead prior to burnout
of the rocket propellant.
The warhead of this invention is adapted for use with any suitable
rocket motor and it has been found that known rocket motors will
accelerate the warhead through a velocity of 7,000 to 8,000 feet
per second during the propellant burning time of approximately 1
second. By constructing the submissiles of a high density material
such as tungsten or depleted uranium and by shaping the submissiles
to have a length to diameter ratio of about 5 to 1, the submissiles
will continue on their intercept paths to the target at an initial
velocity of about 8,000 feet per second upon release from the
warhead and, due to their low aerodynamic drag, will have very high
kinetic energy and momentum upon impact with the target. Upon
striking a target, hypervelocity projectiles do not simply
perforate the target, but fragment explosively, thus greatly
amplifying the destructive effects of the projectiles. The
launching rocket motor may be an unguided rocket, thus reducing the
expense and eliminating the intricacies of the guidance control
system, while the design of the warhead enables the submissiles to
intercept the target at angles substantially normal to the target
and also maximizes the kinetic energy and momentum of the
submissiles to thereby provide a weapon having high destructive
capability. When the weapon is used against ground personnel the
warhead may be provided with a larger number of submissiles of
smaller size than when the weapon is used against material or
aerial targets. It is apparent therefore that the present invention
provides an inexpensive weapon which is simple in construction and
yet very reliable and having a high destructive capability.
Obviously many modifications and variations of the present
invention are possible in light of the above teachings. It is
therefore to be understood, that within the scope of the appended
claims, the invention may be practiced otherwise than as
specifically described.
* * * * *