U.S. patent number 3,888,175 [Application Number 04/588,279] was granted by the patent office on 1975-06-10 for mechanical stabilizer.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Army. Invention is credited to George D. Dusoe, Joseph R. Messineo.
United States Patent |
3,888,175 |
Dusoe , et al. |
June 10, 1975 |
Mechanical stabilizer
Abstract
1. In a munition having a body and a rear base, said rear base
having a fr and an outer flange defining a recess, The improvement
comprising, in combination therewith, a rear stabilizer for
controlling the trajectory of said munition, said rear stabilizer
comprising a helical coil spring having convolutions of gradually
increasing widths, said spring being attached at its innermost
convolution directly to the center region of said floor of said
recess, and a collapsible frustoconical covering for said spring
extending from the innermost to the outermost convolution of said
spring, Said spring and covering being normally confined in
compressed and collapsed condition in said recess and having the
portion of the covering which surrounds the outermost convolution
of said spring in engagement with the flange of said recess, and
said covering forming in the released position of said spring an
empty hollow elongated inverted frustoconical stabilizing surface
at the rear of said munition; Whereby when said munition is
launched, said spring will extend itself outwardly upon centrifugal
forces generated by in-flight movements of said munition.
Inventors: |
Dusoe; George D. (Patterson,
NJ), Messineo; Joseph R. (Patterson, NJ) |
Assignee: |
The United States of America as
represented by the Secretary of the Army (Washington,
DC)
|
Family
ID: |
24353220 |
Appl.
No.: |
04/588,279 |
Filed: |
October 18, 1966 |
Current U.S.
Class: |
102/386; 244/87;
244/130; 244/3.3 |
Current CPC
Class: |
F42B
10/146 (20130101) |
Current International
Class: |
F42B
10/00 (20060101); F42B 10/14 (20060101); F42b
013/32 (); F42b 025/00 () |
Field of
Search: |
;244/3.27,3.3
;102/4,56 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Pendegrass; Verlin R.
Attorney, Agent or Firm: Edelberg; Nathan Gibson; Robert P.
Erkkila; A. Victor
Claims
We claim:
1. In a munition having a body and a rear base, said rear base
having a floor and an outer flange defining a recess,
the improvement comprising, in combination therewith, a rear
stabilizer for controlling the trajectory of said munition, said
rear stabilizer comprising a helical coil spring having
convolutions of gradually increasing widths, said spring being
attached at its innermost convolution directly to the center region
of said floor of said recess, and a collapsible frustoconical
covering for said spring extending from the innermost to the
outermost convolution of said spring,
said spring and covering being normally confined in compressed and
collapsed condition in said recess and having the portion of the
covering which surrounds the outermost convolution of said spring
in engagement with the flange of said recess, and said covering
forming in the released position of said spring an empty hollow
elongated inverted frustoconical stabilizing surface at the rear of
said munition;
whereby when said munition is launched, said spring will extend
itself outwardly upon centrifugal forces generated by in-flight
movements of said munition.
2. The invention of claim 1, wherein said covering is fabric.
3. The invention of claim 1, wherein said covering is nylon.
Description
This invention relates to an apparatus for use in an air-to-ground
missile delivery system. More particular, this invention relates to
an apparatus for selectively controlling the orientation of a
gravitating airborne missile.
One of the conventional methods of delivering a disbursed pattern
of missiles to a specified target is from a gravitating airborne
carrier which is usually launched by means of artillery or from a
fast moving aircraft. As the carrier reaches a predetermined point
in its trajectory, a mass of missiles are deployed in somewhat of a
dispersed pattern in the air. However, as the missiles gravitate
towards the ground, some will oscillate, tumble or will become
otherwise disoriented in their flight. This becomes a problem in
the case of a missile activated by an impact functioning fuze.
These missiles must be properly oriented or the detonators thereof
will not be activated upon impact with the ground.
In the past, the orientation means for such missiles consisted in
metal vanes, extended lengths of ribbon or merely the specially
designed outer configuration of the missile itself. These devices
function to orient the missile upon ejection from the carrier.
However, in the case of mechanically operated vanes, there is a
varied time differential between the ejection of the missile and
the instant that the device reaches the fully operative state. As
is apparent, this factor not only affects the trajectory of the
missile but also varies the ultimate location of the impact area.
Also, the point of deployment of the missiles must be of sufficient
height to insure successful operation of these devices prior to
impact. It is also found that these devices are complicated and, in
many instances, defective or become defective in operation due to
damage sustained in the collision of the missiles immediately after
deployment. These devices are also comparatively heavy, difficult
to manufacture and expensive. As a result, the destruct
capabilities of the pay-load are adversely affected due to the
restricted weight-carrying capacity of the conventional
carriers.
As for the extended ribbon type devices, they are somewhat simple
to manufacture and light in weight. However, they have a tendency
to tangle or otherwise become disarranged in shape and knotted
during operation. They are also unreliable in heavy winds or under
other adverse weather conditions such as rain or snow. Also, in the
case of a missile with a specially designed configuration having
aerodynamic attributes, the device is usually difficult to
manufacture and quite expensive which limits its use in wide spread
field operations where exceedingly large quantities of missiles are
utilized in every day activities.
The subject invention fulfills the needs of the art, as described
above, by being effective at low elevations, inexpensive, light in
weight, simpler in construction and use, and totally reliable under
adverse conditions.
It is an object of this invention to provide an apparatus of
improved construction for use in an air-to-ground missile delivery
system.
Another object is to provide an improved apparatus for use in
controlling the orientation, stabilization, deceleration, and
trajectory of a gravitating airborne missile.
A further object is to provide an apparatus for use in selective
orientation of an airborne missile.
Other objects and many of the attendant advantages of this
invention will be readily appreciated as the same become better
understood by reference to the following detailed description when
considered in connection with the accompanying drawing wherein:
FIG. 1 is a side view, partially in section, of the device of this
invention adapted in distended form to an impact activated
missile.
FIG. 2 is a side view, partially in section, of another embodiment
of the device.
FIG. 3 is a cross-sectional view showing the device in the
compressed form in the accommodating space of the missile.
Similar numerals refer to similar parts throughout the several
views.
Referring to FIGS. 1 and 2, the device is in the form of a surface
covered, helical shaped distensible orientation means 11 such as a
spring and the like which is adapted to be attached, in a
conventional manner, to the rear base of a missile 12 at a point
opposed in direction to the desired site of impact with the ground.
As shown, the circumvolution of the peripheral circuit of the
helically shaped device along the longitudinal axis may be
gradually increasing in value with respect to its diameter, as in
FIG. 1, or it may be substantially constant in value as in FIG. 2.
In either case, the outer circumscribing area of the device may be
covered with lightweight cloth or nylon 13 and, in each case, the
device is adapted to take the form of a helicoid 14 in the
compacted or compressed state without, in any way, disrupting its
inherent ability to become distended or expanded in shape.
As shown in FIG. 3, the nylon covered helically shaped orientation
device may be secured, in the helicoid form 13 in the accommodating
space of the impact activated missile 12 during manufacture of the
missile or at any time prior to storage in the carrier, by directly
attaching the innermost convolution of spring 11 to the center
region of the recess 14 defined by the floor and a surrounding
outer flange of the rear base, so that the portion of the covering
which surrounds the outermost convolution of spring 11 engages said
flange. Due to the volumetric characteristics of the described
device, in the helicoid form, comparatively less space is required
to store the missile in the carrier than is required with the
conventionally available orientation devices. As a result, the
missiles adapted with the present device may be placed in nestable
alignment in a conventional carrier due to the construction of the
device. In this way, the destruct capabilities or payload of a
conventional carrier, having restricted capacity in weight and
volumetric size, may be substantially increased due to the fact
that the light-weight device of this invention may be incorporated
in the structure or accommodating space of the missile itself.
In operation, the carrier of the missiles will be launched from
artillery or from a high speed aircraft. At a predetermined point
in the trajectory of the gravitating airborne missile, the
plurality of missiles will be deployed in somewhat of a dispersed
pattern in the air. As soon as the pressure upon the helicoid,
incident to nesting, is released, the helicoid shaped device will
immediately expand to its full distended length. As a result, the
nylon covered peripheral area of the distended helically shaped
device will produce an empty hollow inverted frustoconical surface
which, when exposed to the airstreams, will tend to orient the
gravitating missile in the desired, upright, stabilizing position
accompanied by a drag, which will decelerate the missile and
positively control the trajectory of the missile. It has been found
that if a missile is adapted with the device of this invention, in
the manner described and shown, such gravitating airborne missile
will orient itself in all cases in an upright position in the air
so that the site of impact will be substantially in the detonating
area of the impact activated pin of the fuze.
It has also been found that at lower levels of elevation in the
order of 50 feet, a missile adapted with the present device will
stabilize in substantially less time thereby orienting the missile
in the desired manner prior to impact. Due to the inherent nature
of a helical shaped device such as a compression spring, it will
expand to its full length in less than about 1 second and will
maintain the center of gravity of the missile in the upright state
to achieve aerodynamic stability. However, the spring should be
made of light-weight material so that the orientation of the
missile does not vary from the desired attitude in space. We have
found that, in typical device for use with the most common impact
oriented missiles, the weight of the device should be between 0.10
to about 0.5 ounce and the length of the expanded device should be
between 0.5 to 1 foot long. The compressive strength of such device
is preferable between 0.5 and 2 pounds per square inch and the
thickness of the body should be between 0.03 and 0.125 inch
depending on the material the spring consists of.
The advantages accompanying the use of the device of this invention
include the fact that it is inexpensive to manufacture due to its
construction. A missile adapted with the present device may be
nestably aligned in the carrier increasing the destruct
capabilities of the entire system. As a grenade or missile is
deployed from a carrier, there are several components of force
acting on the missile itself. These include centrifugal force,
gravity and a forward component of force due to the velocity of the
item. It has been found that, notwithstanding these forces, the
present device will orient the missile in the most favorable
position for impact. It also provides accuracy of delivery to a
specified target area by inducing a constant drag on the missile
throughout the trajectory thereof.
Obviously, many modifications and variations of the present
invention are possible in the light of the above teaching. It is
therefore to be understood that within the scope of the appended
claims, the invention may be practiced otherwise than as
specifically described.
* * * * *