U.S. patent application number 16/547957 was filed with the patent office on 2021-02-25 for device to puncture wing environmental seals and reduce deployment force.
This patent application is currently assigned to BAE Systems Controls Inc.. The applicant listed for this patent is BAE Systems Controls Inc.. Invention is credited to Dan A. Snavely.
Application Number | 20210055085 16/547957 |
Document ID | / |
Family ID | 1000005225288 |
Filed Date | 2021-02-25 |
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United States Patent
Application |
20210055085 |
Kind Code |
A1 |
Snavely; Dan A. |
February 25, 2021 |
DEVICE TO PUNCTURE WING ENVIRONMENTAL SEALS AND REDUCE DEPLOYMENT
FORCE
Abstract
A puncturing feature is provided on the deployable wings of a
precision guidance kit of a rocket to facilitate breaking through
the wing slot seal that protecting the wings prior to deployment.
The puncturing feature may be a sharp region on the leading edge
near the wing tip that first contacts the wing slot seal. The
puncturing feature may be a sharp edge extended along the leading
edge of the wing to provide a cutting action as the wing passes
through the wing slot seal.
Inventors: |
Snavely; Dan A.;
(Binghamton, NY) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
BAE Systems Controls Inc. |
Endicott |
NY |
US |
|
|
Assignee: |
BAE Systems Controls Inc.
Endicott
NY
|
Family ID: |
1000005225288 |
Appl. No.: |
16/547957 |
Filed: |
August 22, 2019 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F42B 10/14 20130101 |
International
Class: |
F42B 10/14 20060101
F42B010/14 |
Claims
1. An aerial projectile, comprising: a fuselage; at least one wing
slot formed in the fuselage; a wing slot seal covering each of the
at least one wing slot; and a guidance wing being in a stowed
position within each of the at least one wing slot prior to
deployment of the wing, the guidance wing having a puncturing
feature formed on a leading edge of the wing, the puncturing
feature being configured to break through the wing slot seal during
deployment of the wing from the stowed position.
2. The aerial projectile of claim 1, wherein the puncturing feature
is formed proximate a tip of the wing.
3. The aerial projectile of claim 1, wherein the puncturing feature
is a sharp point.
4. The aerial projectile of claim 1, wherein the puncturing feature
is a sharp edge.
5. The aerial projectile of claim 4, wherein the sharp edge has
serrations.
6. The aerial projectile of claim 1, wherein the puncturing feature
is a machined feature of the wing.
7. The aerial projectile of claim 1, wherein the puncturing feature
is a separate part that is attached to the wing.
8. The aerial projectile of claim 1, wherein the puncturing feature
is comprised of a material selected from the group consisting of
steel, stainless steel and tungsten carbide.
9. The aerial projectile of claim 1, wherein the puncturing feature
is comprised of a material having fine grain properties.
10. The aerial projectile of claim 1, wherein the wing slot seal
includes a burst seam.
11. A precision guidance kit, comprising: a section of a fuselage
having connectors on either end that are configured to couple to a
projectile; at least one wing slot formed in the section; a wing
slot seal covering each of the at least one wing slot; and a
guidance wing being in a stowed position within each of the at
least one wing slot prior to deployment of the wing, the guidance
wing having a puncturing feature formed on a leading edge of the
wing, the puncturing feature being configured to break through the
wing slot seal during deployment of the wing from the stowed
position.
12. The precision guidance kit of claim 11, wherein the puncturing
feature is formed on a tip of the wing.
13. The precision guidance kit of claim 11, wherein the puncturing
feature is a sharp point.
14. The precision guidance kit of claim 11, wherein the puncturing
feature is a sharp edge.
15. The precision guidance kit of claim 14, wherein the sharp edge
has serrations.
16. The precision guidance kit of claim 11, wherein the puncturing
feature is a machined feature of the wing.
17. The precision guidance kit of claim 11, wherein the puncturing
feature is a separate part that is attached to the wing.
18. The precision guidance kit of claim 11, wherein the connectors
are configured to couple to the projectile.
19. The precision guidance kit of claim 11, wherein the wing slot
seal includes a burst seam.
Description
BACKGROUND
[0001] Aerial rockets and missiles which include folded, deployable
guidance wings, have been in use for many years. Some examples
include the Hydra 70 family of WAFAR (Wrap-Around Fin Aerial
Rocket) and APKWS.RTM. laser guided missile. For many such weapons,
the guidance wings are folded in a stowed configuration within the
main fuselage until the weapon is launched, at which point the
wings deploy outward through slots provided in the fuselage.
[0002] In one such example, the APKWS precision guidance kit is
added to a 2.75'' (70 mm) diameter rocket such as the Hydra-70
(MK66). The APKWS has wings that start in a stowed position thus
allowing the munition to fit inside existing launching tubes. When
the rocket is fired it begins to spin to improve stability. Firing
of the rocket awakens the APKWS system. Once the control system is
initiated and operational, the four control surfaces, known as
flaperons, are commanded to rotate to the zero position, thus
unlatching them from their stow latch. Once unlatched, the
centrifugal force of the spinning rocket causes the wings/control
surfaces to pivot about a fixed point near their root and deploy
outwards to approximately a 30.degree. angle from the munition
centerline.
[0003] In some cases, the wing slots are covered by frangible seals
which protect the interior of the missile from moisture and debris
during storage, transport, and handling. For example, the APKWS has
environmental seals covering the four wing slots to protect the
internal components. Examples of wing slot seals disposed on an
APKWS are disclosed in U.S. Pat. No. 8,895,908, assigned to the
same assignee as the present application, the entire disclosure of
which is hereby incorporated by reference. In these cases the
guidance wings must be deployed with sufficient initial force to
enable them to penetrate the seals.
[0004] However, there is a practical limit to how rapidly a missile
can be spun. In one example, the average centrifugal force on the
tip of a guidance wing at the beginning of deployment is only
approximately 7.7 pounds at the minimum spin rate. This amount of
centripetal energy may not be sufficient by itself to enable the
wings to burst through the frangible slot covers. As a result, some
weapons that include deployable folded guidance wings and frangible
wing slot covers have demonstrated a tendency for the guidance
system to fail due to a lack of proper guidance wing
deployment.
[0005] One approach to address this problem is the addition of a
wing deployment force initiator, which assists the deployment of
the guidance wings by providing an initial burst of energy to help
the wings break through the frangible covers. In one such design,
the wing deployment initiator uses explosives to push the wings
through the frangible covers. However, this approach can be
undesirable due to the violent forces produced by the explosives
and due to concerns about the safety and the long-term chemical
stability of the explosives during storage of the weapon.
[0006] Another approach is to provide a torsion spring wing
deployment initiator which provides additional force to push the
wings outward a small amount. One such torsion spring wing
deployment initiator is described in U.S. Pat. No. 8,868,329
assigned to the same assignee as the present application, the
entire disclosure of which is hereby incorporated by reference.
This approach avoids the problems of using explosives. An
alternative approach is a compression spring wing deployment
initiator. One such compression spring wing deployment initiator is
described in U.S. Pat. No. 8,754,352, assigned to the same assignee
as the present application, the entire disclosure of which is
hereby incorporated by reference.
[0007] However, there is only very limited space available for a
wing deployment initiator to occupy. Also, for some applications,
the weight of the deployment initiator should be as low as
possible. Therefore, it is desirable to provide a mechanical wing
deployment initiator which can provide sufficient force to enable
the guidance wings to break through the frangible covers while also
fitting within the available space and remaining sufficiently light
in weight.
[0008] For certain applications, a more compact and less complex
solution would be desirable, since the reduced complexity would
lower the cost of production and would decrease the likelihood of
failure if the mechanism did not perform as intended.
BRIEF SUMMARY
[0009] In one embodiment, an aerial projectile, such as a missile
or rocket, is disclosed having a fuselage, at least one wing slot
formed in the fuselage and a wing slot seal covering each of the at
least one wing slot. A guidance wing in a stowed position within
each of the at least one wing slot prior to deployment of the wing,
includes a puncturing feature formed on a leading edge of the wing.
The puncturing feature is configured to break through the wing slot
seal during deployment of the wing from the stowed position. In a
further embodiment a precision guidance kit is an assembly that is
configured to couple to a rocket, such as the Hydra rocket, and
comprises wings, slot seal, and related components.
[0010] In one embodiment, the puncturing feature is a small sharp
region on the leading edge near the wing tip that first contacts
the wing slot seal. In one embodiment, the small sharp feature is
formed by a sharp point.
[0011] In one embodiment, the puncturing feature is a sharp edge
extended along the leading edge of the wing to provide a cutting
action as the wing passes through the wing slot seal. In one
embodiment, the extended sharp edge puncturing feature has
serrations to increase the cutting action.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] FIG. 1 is a perspective view of an aerial rocket or missile
shown with the wings deployed with one embodiment of the wing slot
seal puncturing feature of the present disclosure.
[0013] FIG. 2 is a cross sectional view of the wings of an aerial
rocket or missile in a stowed position within the fuselage.
[0014] FIG. 2A is a diagram of one embodiment of the wing slot seal
puncturing feature of the present disclosure.
[0015] FIG. 2B is a diagram of one embodiment of the wing slot seal
puncturing feature of the present disclosure.
[0016] FIG. 2C is a diagram of one embodiment of the wing slot seal
puncturing feature of the present disclosure.
[0017] FIG. 3 is an end view of a wing stowed within fuselage an
aerial rocket or missile showing the side profile of one embodiment
of the puncturing feature extending beyond the rounded edge of the
wing.
[0018] FIG. 4 is a perspective view of an aerial rocket or missile
showing one embodiment of the wing slot seal puncturing feature of
the present disclosure has broken through a burst seam the wing
slot seal.
[0019] Further features as well as the structure and operation of
various embodiments are described in detail below with reference to
the accompanying drawings. In the drawings, like reference numbers
indicate identical or functionally similar elements.
DETAILED DESCRIPTION
[0020] In one embodiment a puncturing feature is provided on the
wing of the rocket to facilitate breaking through the wing slot
seal. In one embodiment, the puncturing feature is small sharp
region on the leading edge near the wing tip. This is the region of
the wing that first contacts the wing slot seal. In one embodiment,
the small sharp feature has a sharp point that will puncture the
wing slot seal just like a bird's egg tooth.
[0021] In one embodiment, the puncturing feature is a sharp edge
extended along the leading edge of the wing to provide a cutting
action as the wing passes through the wing slot seal. In one
embodiment the additional length of the sharp edge would slice the
wing slot seal as the wing passes through just like a knife blade.
In one embodiment, the extended sharp edge puncturing feature has
serrations to increase the cutting action.
[0022] The puncturing feature is an improvement over the prior art
deployment initiators by reducing the amount of force required by
the wing to puncture the wing slot seal and improve wing deployment
reliability. In one embodiment, the puncturing feature reduces the
deployment force enough where the wings can deploy reliably without
the need for an additional mechanical deployment initiator, thereby
avoiding the increased weight and cost of the prior art
solutions.
[0023] The puncturing feature could be a machined feature of the
wing or it could be a separate part that is then attached to the
wing. The puncturing feature may to be made from a material with
structural hardening such as steel, stainless steel and tungsten
carbide. In one example, metal hardness may be specified by ASTM
E18, which is a standard that defines the Rockwell hardness test
method for metallic materials. In one embodiment, a metallic
material that has a Rockwell C-scale hardness of 35 or greater may
be specified. In one embodiment, the puncturing feature may be made
with fine grain properties that it can be sharpened to a keen edge,
such as those meeting the test detailed in ASTM standard E112.
However, other materials such as hard plastic, ceramic or glass
could serve as the puncture and/or cutting feature.
[0024] FIG. 1 is a perspective view of one embodiment of an aerial
rocket or missile 10 that include guidance wings 12 which are
typically folded within the main fuselage 14 in a stowed
configuration until the weapon is launched, at which point the
wings 12 are released and deployed through wing slots 16. FIG. 1
illustrates the missile 10 having just been launched with its
guidance wings 12 deployed. The wing slots 16 in these missiles 10
are covered by frangible environmental cover seals 18, which
protect the interior of the missile from dirt and debris before
missile launch. Deployment of the guidance wings 12 requires
sufficient initial force to enable the wings 12 to break through
the frangible cover seals 18. The wings 12 include puncturing
feature 20 on the leading edge near the wing tip to break through
the wing cover seals 18. The dashed line 17 shows where the wing 12
has broken through the wing slot seal 18.
[0025] According to one embodiment, the wings 12, wing slots 16,
and frangible cover seals 18 along with guidance and navigation
electronics are integrated into a precision guidance kit 25. The
precision guidance kit 25 in one example is contained within a
section of the fuselage 27 with connectors (not shown) such that
the precision guidance kit 25 is secured between the rocket section
and the warhead section. In one example the precision guidance kit
25 is screwed onto the rocket and the warhead. The precision
guidance kit 25 is coupled to a rocket in order to convert the
rocket into a precision guided projectile. One example of this is
the APKWS precision guidance kit.
[0026] FIG. 2 is a cross sectional view of the wings 12 in a stowed
position within the fuselage 14. The wings 12 include the
puncturing feature 20 on the leading edge near the wing tip. FIG.
2A shows one embodiment of the puncturing feature 20 being
configured as a sharp point 22 on the leading edge of the wing 12.
FIG. 2B shows one embodiment of the puncturing feature 20
configured as a sharp edge 24 extending along the leading edge of
the wing 12. FIG. 2C shows one embodiment of the puncturing feature
20 configured as a sharp edge with serrations 26. In the stowed
position, the puncturing feature 20 is below the wing slot seal
18.
[0027] FIG. 3 is an end view of a wing 12 stowed within fuselage 14
showing the side profile of the puncturing feature 20 extending
beyond the rounded edge of the wing.
[0028] FIG. 4 is a perspective view of one embodiment in which the
wing slot seal 18 includes a burst seam 30. The burst seam 30 is
configured be aligned with the puncturing feature 20 so as to allow
the guidance wing 12 to separate and pass through the burst seam 30
during deployment of the guidance wing 12. In one embodiment, the
wing slot seal 18 is formed of a barrier sheet and an adhesive
layer on inner surface of the barrier sheet. The adhesive layer is
configured to secure the barrier sheet to the region of fuselage 14
surrounding the wing slot 16. In one embodiment, the adhesive layer
provides an adhesive strength which is sufficient to maintain the
barrier sheet in position over the wing slot 16 while the guidance
wing 12 breaks through the barrier sheet at the burst seam 30
facilitated by the puncturing feature 20 during deployment of the
guidance wing 12. The burst seam 30 is configured to close and
resist penetration when a force is applied to the barrier layer
from outside of the rocket or missile 10.
[0029] In one embodiment, the wing slot seal provides a frangible
barrier against exposure of internal components of a rocket or
missile to external contaminants, while enabling deployment of a
wing stored within the rocket or missile simply by bursting of the
wing through the frangible seal. The seal is strong enough to
resist rupture or dislodgement from the exterior due to normal
transport and handling of the missile, while at the same time
presenting minimum resistance to penetration from the interior when
the guidance wings are deployed by bursting through the seal.
[0030] In one embodiment, the wing slot seal is a thin, flexible
sheet which can be adhered to a surface of the fuselage of the
rocket or missile so as to cover a wing slot. In embodiments, the
seal is sufficiently thin so as not to exceed the diameter of "bore
riders" of the missile which define the maximum diameter of the
missile, and which support the missile when resting within a
cylindrical launching or transporting tube.
[0031] In one embodiment, the thin, flexible sheet includes an
outer layer and an inner layer. Both of the layers may be made of a
nickel alloy, and in some of these embodiments one layer is made of
half-hard nickel sulfamate, while the other layer is made of fully
hard nickel sulfamate. The inner layer includes at least one burst
seam which assists the wing in breaking through the seal for
deployment. The flexible sheet may be curved according to the
cylindrical shape of the rocket or missile, and the two layers are
stiff, although flexible, so that inward deformation due to
pressure applied from outside the rocket or missile tends to force
the edges of the burst seam together, thereby resisting the applied
force, while outward deformation caused by the wing pressing
against the seal from within the rocket or missile tends to force
the edges of the burst seam apart, so that the wing passes through
the cut or cuts in the inner layer and is only required to break
through the outer layer.
[0032] In one embodiment, the flexible sheet is resilient or
"springy," so that once the wing is deployed, portions of the
flexible sheet which lie against the deployed wing remain
substantially flush against the wing, while portions of the
flexible sheet which are not adjacent to the deployed wing tend to
spring back into place and close the opening made in the frangible
seal. The effect of the frangible seal on the aerodynamics of the
rocket or missile is thereby minimized.
[0033] While the present invention has been particularly shown and
described with respect to preferred embodiments thereof, it will be
understood by those skilled in the art that the foregoing and other
changes in forms and details may be made without departing from the
spirit and scope of the present invention. It is therefore intended
that the present invention not be limited to the exact forms and
details described and illustrated, but fall within the scope of the
appended claims.
* * * * *