U.S. patent number 3,710,716 [Application Number 05/058,807] was granted by the patent office on 1973-01-16 for ram pressure standoff extension and safe/arm mechanism for self-arming munitions.
This patent grant is currently assigned to The Boeing Company. Invention is credited to Thomas L. Davis, Joseph D. Hansen.
United States Patent |
3,710,716 |
Davis , et al. |
January 16, 1973 |
RAM PRESSURE STANDOFF EXTENSION AND SAFE/ARM MECHANISM FOR
SELF-ARMING MUNITIONS
Abstract
A munition for flight through a fluid medium environment to a
target having an extendible standoff member normally carried within
the munition body for efficient packing density, an interior
diaphragm responsive to the differential between fluid ram pressure
and local low static pressure during flight to extend the standoff
member forwardly of the munition body, and a detonator carried by
the standoff member into an armed position wherein it is responsive
to the impact of the standoff member with the target to detonate
the munition at a predetermined standoff distance from the
target.
Inventors: |
Davis; Thomas L. (Huntsville,
AL), Hansen; Joseph D. (Huntsville, AL) |
Assignee: |
The Boeing Company (Seattle,
WA)
|
Family
ID: |
22019043 |
Appl.
No.: |
05/058,807 |
Filed: |
July 28, 1970 |
Current U.S.
Class: |
102/397;
102/223 |
Current CPC
Class: |
F42B
12/105 (20130101); F42C 15/29 (20130101); F42B
12/10 (20130101); F42C 1/14 (20130101) |
Current International
Class: |
F42C
1/00 (20060101); F42C 1/14 (20060101); F42C
15/29 (20060101); F42C 15/00 (20060101); F42B
12/10 (20060101); F42B 12/02 (20060101); F42c
001/14 () |
Field of
Search: |
;102/7.4,81,81.2,70 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Engle; Samuel W.
Claims
We claim:
1. In a munition for flight through a fluid medium environment to a
target, improved means for arming the munition and for detonating
the munition at a predetermined standoff distance from the target
comprising:
a. a housing for containing an explosive charge and having a
forward nose portion;
b. elongated standoff means longitudinally mounted in the nose
portion of said housing and adapted for movement from a first
position, wherein said standoff means is withdrawn into said
housing, to a second position, wherein said standoff means extends
forwardly beyond the nose portion of said housing;
c. differential pressure sensitive means connected to said standoff
means within said housing and responsive to the pressure
differential between the fluid ram pressure at the forward nose
portion and the fluid static pressure at a low pressure region
remote from the forward nose portion, said differential pressure
sensitive means including a deformable diaphragm means defining
fore and aft chambers within said housing, and further including
means for venting said fore chamber to the static fluid pressure at
a low pressure region remote from the forward nose portion of said
housing and means for applying the fluid ram pressure to the aft
chamber whereby the differential fluid pressure between the fore
and aft chambers during flight of the munition to the target
deforms said diaphragm means to move said standoff means from the
first to the second positions, and
d. detonator means connected to said standoff means for movement
thereby into operative relationship with the explosive charge as
said standoff means moves from the first to the second positions,
said detonating means adapted for detonation of the explosive
charge upon impact of said standoff means with the target when in
the second position.
2. The apparatus as claimed in claim 1 wherein said standoff means
comprises a hollow tube in fluid pressure communication with the
aft chamber for applying the fluid ram pressure to said diaphragm
means during flight to the target.
3. The apparatus as claimed in claim 2 further including orifice
defining means positioned within said hollow tube standoff means
for delaying the application of the fluid ram pressure to said
diaphragm means during flight to the target.
4. In a munition for flight through a fluid medium environment to a
target, improved means for arming the munition in response to the
flight environment and for detonating the munition at a
predetermined standoff distance from the target comprising:
a. a housing for containing an explosive charge and having a
forward nose portion;
b. elongated standoff means having a longitudinal axis and slidably
mounted in the forward nose portion of said housing, said standoff
means longitudinally movable from a first position, contained
essentially entirely within said housing for storage of the
munition, to a second position, extending substantially beyond the
forward nose portion of said housing, for impact with the target
prior to such impact of the forward nose portion;
c. detonator means having an impact actuation axis, a first end
containing a detonating charge, and a second end pivotally
connected to said standoff means;
d. spring bias means engaging said detonating means for biasing
said detonating means to a safe position wherein the impact
actuation axis is essentially normal to said standoff means
longitudinal axis when said standoff means is in the first
position;
e. camming means contained within said housing and having a first
surface engaging said detonating means for overcoming the bias of
said spring bias means and pivotally urging said detonating means
to an inclined armed position wherein the impact actuation axis has
a substantial component parallel to said standoff means
longitudinal axis as said standoff means is moved from the first to
the second positions; said camming means further having a second
surface receiving in abutting relationship the first end of said
detonating means when said detonating means is in the armed
position wherein the second surface presents a detonating cord
explosive train, connected to the explosive charge, in operative
relationship with the detonating charge; and
f. differential pressure sensitive means connected to said standoff
means within said housing responsive to the pressure differential
between the fluid ram pressure at the forward nose portion and the
fluid static pressure at a low pressure region remote from the
forward nose portion during flight of the munition to the target to
move said standoff means from the first position to the second
position.
5. In a munition for flight through a fluid medium environment to a
target, improved means for arming the munition in response to the
flight environment and for detonating the munition at a
predetermined standoff distance from the target comprising:
a. a housing for carrying an explosive charge;
b. said housing having a forward nose portion;
c. elongated standoff means slidably mounted in said forward nose
portion for movement from a first position within said nose portion
to a second position extending substantially beyond said forward
nose portion;
d. differential pressure sensitive means connected to said standoff
means within said housing responsive to differential pressure;
e. said differential pressure sensitive means including a
deformable diaphragm defining fore and aft chambers within said
housing, and means for venting said fore chamber to static fluid
pressure at a low pressure region remote from said forward nose
portion and means for applying said fluid ram pressure to said aft
chamber whereby the differential of fluid pressure between said
fore and aft chambers during flight of munition to the target
deforms said diaphragm for moving said standoff means from said
first to said second position, and
f. detonator means having an impact actuation axis, a first end
containing a detonator charge and a second end connected to said
standoff means for movement of said detonator means from an unarmed
to an armed position in response to movement of said standoff means
first position to said standoff means second position respectively,
so that said impact actuation axis of said detonator means moves
for a substantial component parallel to said standoff means
longitudinal axis in said second extended position and whereby said
first end detonator charge moves into cooperating relationship with
means interconnecting said detonating charge with said explosive
charge carried in said housing, thereby arming said munition.
6. The munition as claimed in claim 5 wherein said standoff means
comprises a hollow tube in fluid pressure communication with the
aft chamber for applying the fluid ram pressure to said diaphragm
means during flight to the target.
7. The munition as claimed in claim 6 further including orifice
defining means positioned within said hollow tube standoff means
for delaying the application of the fluid ram pressure to said
diaphragm means during flight to the target.
Description
BACKGROUND OF THE INVENTION
This invention relates to munitions designed for flight through a
fluid environment to a target and more particularly to means for
arming such munitions in response to a flight environment forcing
function and for detonating the munition at a predetermined
standoff distance from the target.
It has long been known that the armor penetration capability of a
munition can be increased by appropriately shaping the munition
charge geometry and by detonating the munition at a predetermined
distance, known as the standoff distance, from the charge to the
armor surface. For conventionally shaped charge geometries, maximum
armor penetration is achieved with a standoff distance of
approximately three to four charge diameters. Detonation of the
charge at the predetermined standoff distance has been provided in
the prior art by affixing to the nose of the munition an elongated
standoff member which impacts the target prior to the munition
proper, and triggers the detonation of the explosive charge upon
the impact of the standoff member with the target. However,
providing a standoff member of sufficient length to detonate the
munition at an optimum standoff distance seriously compromises the
packing density capability of the munition, resulting in handling
problems prior to launch and seriously limiting the number of
munitions that can be carried in a weapons delivery system. With
the development of submunitions designed to be clustered in the
warhead of a missile or other similar weapons delivery system, the
packing density of the particular submunition design becomes a
critical factor for effective weapon deployment. Thus the weapons
designer has been required to make a compromise between optimum
standoff distance and maximum packing density with the normal
compromise generally being for increased packing density and
reducing standoff distance to approximately to one charge
diameter.
In addition to the penalty of low packing density, prior art
standoff members have posed problems in prelaunch handling of the
munition. Since the munition must be sensitive to detonation by
impact force applied to the standoff member, the extension of this
member beyond the normal envelope of the munition has resulted in
increased exposure of the munition to accidental detonation. Thus
it is desirable to provide an arming sequence that is responsive to
a forcing function obtained only in the in-flight environment and
to provide a safe condition wherein the explosive train is
discontinuous so the accidental detonation of the initiator or
detonator will not result in detonation of the principal explosive
charge.
When a munition is designed for multiple packing or clustering in a
warhead, problems of standoff member damage and premature
detonation have been encountered due to collisions between the
submunitions during the initial dispersal sequence. Thus it is
desirable to not only provide an arming sequence responsive to the
in-flight environmental conditions, but means must be provided to
protect the standoff member and delay the arming sequence for an
interval subsequent to warhead opening to prevent disarming of the
submunition and to insure against premature detonation.
SUMMARY OF THE INVENTION
It is an object of this invention to provide means for detonating a
munition at an optimum predetermined standoff distance from a
target without compromising packing density of the munition.
It is another object of this invention to provide means for arming
a munition designed for flight through a fluid environment to a
target, said means being responsive to a forcing function obtained
only in the in-flight environment.
It is yet another object of this invention to provide a munition
having minimum length for increased packing density and an
out-of-line explosive train for increased safety during prelaunch
handling and which is responsive to post launch in-flight
environment for arming and standoff extension.
It is a further object of this invention to provide a submunition
capable of delayed in-flight standoff extension and arming for
preventing premature detonation due to collisions between
submunitions during initial dispersal sequence.
These and other objects of the invention are provided by
incorporating within a munition designed for flight through a fluid
medium environment to a target, an extendible standoff member that
is carried within the body of the munition prior to launch and
which, in response to the flight environment, extends forwardly of
the munition body to a predetermined optimum standoff distance.
Forward movement of the standoff member is provided by a rearwardly
extending conical yieldable diaphragm attached to the standoff
member and defining a pair of chambers within the munition body;
one of said chambers being in communication with the fluid ram
pressure at the nose of the munition, and the other chamber being
in communication with the fluid static pressure at a point remote
from the nose of the munition. The differential fluid pressure
applied to the diaphragm deforms the conical diaphragm to a
forwardly extending position extending the standoff member
forwardly beyond the nose of the munition. Detonator means, carried
by the standoff member, are simultaneously moved from a safe
position, out of line with the explosive train with its impact
actuation axis normal to the longitudinal axis of the standoff
member, to an armed position, in operative relationship with the
munitions explosive charge with the impact actuation axis inclined
to and having a substantial component parallel with the
longitudinal axis of the standoff member. Upon impact of the
standoff member with the target, impact forces are transmitted to
the detonator causing detonation of the munition's charge at the
predetermined optimum standoff distance from the target.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is an isometric view, partly in section and with portions
broken away, of a munition incorporating the features of the
invention in the safe condition with the standoff member
withdrawn.
FIG. 2 is an isometric view, partly in section and with portions
broken away, of a munition incorporating the features of this
invention in the armed condition with the standoff member
extended.
FIG. 3 is a longitudinal cross sectional view of the forward
portion of the munition of FIG. 2 showing details of the detonator
and standoff extension apparatus.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring now to the drawings which illustrate a shaped charge
munition designed for flight through the atmosphere to a target
that incorporates the standoff extension and safe/arm features of
the invention, there is shown a housing 10 having fins 12 for
aerodynamic stability and containing a shaped explosive charge 14
with a shaped charge liner 16. While the standoff extension
features of this invention provide particular benefits when applied
to shaped charge munitions and will be described herein that
context, it is to be understood that the features of this invention
can be applied to other than shaped charge munitions. Similarly,
the application of this invention is not limited to munitions
designed for aerodynamic flight to a target, but may also be
applied to munitions designed for flight through environments other
than the atmosphere, such as torpedoes and other underwater
munitions.
Housing 10 has a nose cone 18 which is generally hollow and forming
an interior nose cavity defined by the interior surface 19 of nose
cone 18 and the shaped charge liner 16. A differential pressure
sensitive means, such as a conically shaped deformable diaphragm 20
is positioned within said nose cavity with the outer peripheral
edge 22 of the diaphragm sealed to the interior wall surface 19 of
nose cone 18 forming two separate pressure chambers within said
nose cavity: a fore or low pressure chamber 24 defined by diaphragm
20 and interior wall surfaces 19 of nose cone 18; and an aft or
high pressure chamber 26 defined by diaphragm 20 and shaped charge
liner 16. Attached to the central apex of conical diaphragm 20 and
sealed thereto is elongated standoff means 28 which may
conveniently be a hollow tubular member having longitudinal axis 30
and an interior bore 32 communicating with aft chamber 26. Standoff
means 28 extends forwardly of diaphragm 20 through fore chamber 24
and is slidably fitted to an aperture in forward nose portion 34 of
nose cone 18. It is normally desirable that standoff means 28 be
fitted to nose cone 18 such that its longitudinal axis 30 is
coincident with the longitudinal axis of the munition in order to
provide aerodynamic stability and to insure that the forward end of
standoff means 28 will be presented to the free stream total
pressure field during flight of the munition. A bore or aperture 36
is provided in the shoulder of nose cone 18 at a point remote from
forward nose portion 34 to vent fore chamber 24 to a low fluid
pressure region on the order of free stream static pressure during
the flight of the munition through a fluid medium environment.
Collar 38 fixedly attached to standoff means 28 within chamber 24
has pivotally attached thereto a detonator means 39 having a first
end comprising a piston 40 pivotally connected to collar 38 by pin
42; and a second end comprising a cylindrical sleeve 44 containing
a detonating charge 46. As is more clearly shown in FIG. 3, sleeve
44 is crimped about an annular groove in piston 40 and the end of
piston 40 opposite to that pinned to collar 42 is formed into a
firing pin 48 placed adjacent to detonating charge 46. Impact or
accelerating force applied to detonator means 39 along impact
actuation axis 50, which is generally the symmetrical axis of
detonator means 39 and extends through pin 42, will cause firing
pin 48 to penetrate and detonate detonator charge 46.
During storage or while contained within a warhead or other weapons
delivery system, and at all times prior to launch through the
atmosphere or other fluid medium to a target, the munition
embodying the apparatus of this invention is in the configuration
as shown in FIG. 1, wherein standoff means 28 is in a first
position contained essentially entirely within nose cone 18 and
does not extend forwardly beyond forward nose portion 34 of nose
cone 18. Diaphragm 20 is in its relaxed position with the apex
thereof, to which is attached standoff means 28, extending
rearwardly toward shaped charge liner 16 and impact actuation axis
50 of detonator means 39 is essentially normal to longitudinal axis
30 of standoff means 28 in a safe or unarmed position. This
orientation of impact actuation axis 50 and longitudinal axis 30 is
maintained by compression springs bias means 52 which may be either
a metallic compression spring or a resilient nonmetallic
compression member. In this condition the overall length of the
munition is at a minimum enabling increased packing density to be
obtained in a warhead or other weapons delivery system. In
addition, any impact force accidentally applied to forward nose
portion 34 of nose cone 18 will not be transferred to detonator
means 39 and cause the detonation thereof because of the
perpendicular orientation of impact actuation axis 50 and standoff
longitudinal axis 30; and even if detonator means 39 should be
accidentally detonated, since it is not in operative relationship
with shaped explosive charge 14 and is shielded therefrom by
diaphragm 20 and shaped charge liner 16, a detonation of the shaped
charge would not result.
Upon warhead opening or other launch of the munition from its
delivery system into the atmosphere or other fluid medium
environment for flight to a target, fins 12 stabilize the flight
path of the munition and forward nose portion 34 of nose cone 18
experiences the ram fluid pressure. During the flight of the
munition to the target, the fluid ram pressure is conducted to aft
chamber 26 through interior bore 32 of standoff means 28 while
simultaneously fore chamber 24 is vented to a low static pressure
region remote from forward nose portion 34 causing a buildup of
pressure in the aft side of diaphragm 20 and a drop in pressure in
the fore side of diaphragm 20. This results in a differential
pressure applied across diaphragm 20 producing a resultant pressure
acting on the aft side of diaphragm 20 deforming it in a forward
direction, as shown in FIG. 2, to move standoff means 28 to a
second position wherein standoff means 28 extends forwardly beyond
forward nose portion 34 of nose cone 18.
As standoff means 28 moves forwardly to the second position during
flight, it carries detonator means 39 along with it into operative
relationship with shaped explosive charge 14 in a manner to be now
described. Positioned on interior surface 19 of nose cone 18 is
camming means 54 having a first surface 56 engaging sleeve 44 of
the second end of detonator means 39 during movement of standoff
means 28 from the first to the second position. During this
engagement of detonator means 39 with first surface 56 of camming
means 54, the bias of spring bias means 52 is overcome and
detonator means 39 is pivotally urged about pin 42 from the safe
position, wherein its impact actuation axis 50 is normal to
standoff means axis 30, to an inclined armed position, wherein
impact actuation axis 50 has a substantial component parallel to
longitudinal axis 30, as is shown more clearly in FIG. 3. As sleeve
44 of the second end of detonator means 39 travels along first
surface 56 of camming means 54 and reaches the forward end thereof,
spring bias means 52 urges detonator means 39 upwardly, as shown in
FIG. 3, locking the second end of detonator means 39 into abutting
relationship with second surface 58 of camming means 54. Mild
detonating cord 62 connected to booster charge 64 in a well or bore
66 within shaped explosive charge 14 has an end 60 contained within
a bore in camming means 54 and presented to second surface 58
thereof. In this manner, forward movement of standoff means 28 from
the first position to the second position by the differential
pressure applied to diaphragm 20 during flight of the munition to a
target, moves detonator means 39 from a safe or unarmed position,
wherein its impact actuation axis 50 is essentially normal to
standoff means axis 30, to an armed position, wherein detonator
charge 46 is locked into operative relationship with shaped
explosive charge 14 and wherein impact actuation axis 50 has a
substantial component parallel to longitudinal axis 30. Upon impact
with the target, a component of the impact force received by
standoff means 28 is transferred through pin 42 and piston 40,
causing firing pin 48 to penetrate detonator charge 46 producing a
detonation thereof. This explosive energy is then transferred by
mild detonator cord 62 to booster charge 64 which detonates
explosive charge 14 in a very short interval subsequent to the
impact of standoff means 28 with the target.
While the optimum standoff distance yielding maximum armor
penetration for a shaped charge munition depends upon many design
factors, including charge cone angle, liner material and the type
of explosive, there is generally an increase in armor penetration
with increased standoff distance up to a certain point for all
types of shaped charge munitions. In the case of a munition
employing a charge cone angle of 60.degree., maximum armor
penetration is obtained at a standoff distance of approximately
three to four charge diameters. In order to obtain acceptable
packing densities, munitions employing conventional fixed geometry
standoff means are limited to standoff distances of approximately
one charge diameter thus compromising the armor penetration
capability of the munition. By employing the apparatus of this
invention, standoff means 28 may be readily sized to provide
standoff distances on the order of 1 1/2 - 3 charge diameters thus
providing increased armor penetration capability without
compromising the packing density of the munition. Increased length
of standoff means 28 yielding standoff distances in the order of 4
charge diameters may also be employed subject to the flight
stability characteristics of the specific munition design and its
intended application.
Differential pressure sensitive means of configurations other than
diaphragm 20, such as a bellows, may be employed in the practice of
this invention. However, diaphragm 20 is considerably less
complicated than a bellows arrangement and provides increased
economy of manufacture and reliability of operation. In addition,
diaphragm 20 has the capability of long excursions in response to
the fluid ram and static pressure differential making possible
standoff distances of up to three charge diameters without
sacrificing packing density. In certain applications, when such
large standoff distances are not required and the increased
complexity so warrants, a bellows arrangement may be used to
replace diaphragm 20. Diaphragm 20 is preferably made of a
deformable material such as nylon, Mylar, or other types of plastic
films or membranes. Diaphragm 20 must possess sufficient
yieldability to deform from the stored position, as shown in FIG.
1, to the inverted position, as shown in FIG. 2, in order to move
standoff means 28 from the first to the second position. Diaphragm
20 should also be sufficiently inert to retain its yieldability
over long durations of storage and, in this regard, vacuum formed
nylon materials have been found to be particularly suitable.
While the apparatus of this invention has been described as applied
to a munition, it is also particularly suitable as applied to a
plurality of submunitions, packed into a warhead or other weapons
delivery system. In this application, it is generally desirable to
delay the application of the full differential pressure to
diaphragm 20 for a duration subsequent to the initial submunition
dispersal sequence to prevent damage of standoff means 28 or
premature detonation of the submunition due to collisions between
the submunitions. This operational delay can be achieved by
metering the high fluid ram pressure flow through an orifice
restricting interior bore 32 of standoff means 28. In FIGS. 1 and
2, such metering is provided by rolling over the forward end of
tubular standoff means 28 to form an orifice of a diameter less
than interior bore 32. Increased flexibility in providing various
operational delays may be obtained by the alternate configuration
shown in FIG. 3, wherein a separate orifice defining plug 68 is
inserted into interior bore 32 and fixed therein prior to launch of
the munitions.
What is provided, then, by this invention is an improved means for
arming a munition during flight to a target responsive to a forcing
function obtained only in the flight environment and for detonating
the munition at optimum preselected standoff distances from the
target. These advantages are obtained without sacrificing packing
density capability of the munition and out-of-line safety of the
explosive train is maintained to prevent accidental detonation
prior to in-flight arming. The features of this invention may be
applied to a plurality of submunitions clustered in a warhead, or
the like, wherein delayed in-flight arming and standoff extension
can be provided to prevent premature detonation of the submunition
during the initial dispersal sequence due to collisions between the
submunitions. Various modifications of the features of this
invention may be resorted to by those skilled in the art without
departing from the spirit and scope of the invention as hereinafter
defined by the appended claims.
* * * * *