U.S. patent number 3,684,214 [Application Number 05/008,241] was granted by the patent office on 1972-08-15 for flying body having extensible fins.
This patent grant is currently assigned to Messerschmitt-Bolkow-Blohm Gesellschaft mit beschrankter Haftung. Invention is credited to Helmut Kloss.
United States Patent |
3,684,214 |
Kloss |
August 15, 1972 |
FLYING BODY HAVING EXTENSIBLE FINS
Abstract
A flying body, in particular a projectile of a type which is
adapted to be jected from a tube includes a tubular outer casing
and a plurality of tail fins conforming to the configuration of the
casing and arranged at spaced circumferential locations therearound
which are held by extension means under tension when the fins are
retracted in position within the tube. When the projectile is
directed out of the tube the extension means move in a direction to
cause outward movement of the tail fins into an operative
position.
Inventors: |
Kloss; Helmut (Munchen,
DT) |
Assignee: |
Messerschmitt-Bolkow-Blohm
Gesellschaft mit beschrankter Haftung (Munich,
DT)
|
Family
ID: |
5724558 |
Appl.
No.: |
05/008,241 |
Filed: |
February 3, 1970 |
Foreign Application Priority Data
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Feb 7, 1969 [DT] |
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P 19 06 028.7 |
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Current U.S.
Class: |
244/3.27 |
Current CPC
Class: |
F42B
10/18 (20130101) |
Current International
Class: |
F42B
10/00 (20060101); F42B 10/18 (20060101); F42b
013/32 () |
Field of
Search: |
;244/3.27,3.28,3.29 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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147,200 |
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Oct 1954 |
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SW |
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556,302 |
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Apr 1923 |
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FR |
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Primary Examiner: Pendegrass; Verlin R.
Claims
What is claimed is:
1. A guide fin assembly for a flying body or projectile which is
adapted to be ejected from a tube or receptacle, comprising a guide
fin of a configuration which is adapted to conform to the
peripheral surfaces of the projectile with which it is associated
so that it can be held in juxtaposition therewith by a surrounding
tube, a radially extending web connected to said guide fin for
supporting said guide fin and for moving it outwardly from the
projectile and for supporting it in an extended position spaced
outwardly from the projectile, an oblique guide surface adapted to
be located within the projectile and extending longitudinally and
radially outwardly toward the rear end of the projectile, said web
having an inner end engaged on the oblique surface and being
movable along said surface in a radial direction during extension
so as to be guided outwardly by said surface into an extended
position, a thrust collar arranged around said oblique surface and
engaged with said web in a manner permitting radial moving of said
web with respect to said thrust collar, and biasing means acting on
said thrust collar and urging it toward the rear of said missile in
a direction to move said webs with said collar rearwardly and
radially outwardly.
2. A flying body construction including a tubular outer casing, a
guide fin of the same configuration as said casing adapted to
overlie and conform to the casing, said casing including a slot
defined therein extending substantially longitudinally, a
supporting web connected to said guide fin and having an inner end
extending through said slot into said casing, a guide surface in
said casing extending longitudinally and radially outwardly toward
the rear of said casing and engaged with the inner end of said web
for deflecting said web outwardly with said guide fin during
rearward movement of said web, a thrust collar surrounding said
guide surface and connected with said guide fin web in a manner
permitting radial movement of said web, and means to move said
thrust collar in a direction to cause said guide fin to move
rearwardly over said guide service and radially outwardly to cause
the extension of said guide fin from outer surface of said casing
whenever the guide fin is not held in juxtaposition with such
casing.
3. A flying body construction, according to claim 2, wherein said
means to move said thrust collar in a direction to cause the guide
fin to move outwardly from the casing includes a compression
spring, said guide surface comprising a hollow conical member
arranged within the casing of said projectile, said web including a
portion riding over the surfaces of said conical member and being
deflectable outwardly when said web is moved in a direction to
extend said guide fin, said compression spring being compressed
when said guide fin is held in a position in juxtaposition with the
casing of said flying body.
4. A flying body construction, according to claim 2, wherein said
guide surface is of conical configuration, said web having a
portion in contact with said conical portion and being movable
outwardly thereby when said guide fin is not held in juxtaposition
with said casing, said means to move said web comprising a
compression spring which is compressed when said guide fin is held
in a juxtaposition with said casing.
5. A flying body construction, according to claim 4, wherein said a
thrust ring extending around said conical guiding means, said
compression spring comprising a coil spring at one end held by said
thrust ring, said thrust ring defining an abutment for said web,
said compression spring being compresseible within said casing to
permit forward movement of the thrust ring with said web along the
conical portion of said guinding means, said spring being
expansible to move said thrust ring rearwardly to move said web
along said conical portion of said guiding means to cause it to
move radially outwardly, and menas engageable with said ring in an
extended position to hold said ring with said web and said guide
fin in an extended position.
6. A flying body construction, according to claim 5, wherein said
web includes a base portion which is guided on said conical portion
and which includes a surface which conforms to the conical portion
and which is engageable with notch means when it moves along said
conical portion to an extended position.
7. A flying body construction, according to claim 5, including a
plurality of webs extending radially outwardly from said flying
body casing, said flying body casing having a longitudinal slot for
each of said webs, a guide fin associated with each of said web
members, each of said guide fins being of a considerable arcuate
extend and occupying a major portion of the periphery of said
casing when said guide fins are held in juxtaposition
therewith.
8. A flying body construction, according to claim 7, extends a
thrust ring extending around said conical portion of said guiding
surface and being axially displaceable within said casing, a
compression spring biasing said thrust ring to a rearward
direction, said thrust ring having a guide face engageable with the
interior wall of said casing and including a projection engageable
with the slot of said flying body casing for guiding said thrust
ring during its extension movement.
9. A flying body construction, according to claims 2 including a
reaction motor carried within said casing of the flying body having
a nozzle portion of conical configuration forming said guiding
means for said guide fin assembly.
Description
SUMMARY OF THE INVENTION
This invention relates in general to the construction of flying
bodies and in particular to a new and useful projectile or missile
adapted to be ejected from a tube or receptacle and which includes
fins, particularly tail fins which are moved by extension means
outwardly from the body of the projectile automatically when the
projectile is expelled from the tube.
Extensible fins for flying bodies such as projectiles or missiles
are known, for example, tail fins are known which may be pivoted
about supporting axes to extend substantially radially to the fin
carrier in the operative state and to extend in the folded state
coaxially to the longitudinal axis of the associated projectile. In
such operations, the pivot shafts are arranged at the rear in
respect to the direction of flight of the projectile. Such an
arrangement and design of the tail fins requires a relatively large
overall length so that it is disadvantageous for small caliber
projectiles. The turning of the tail fins about a fixed shaft also
has the disadvantage that due to the small lever arm available
between the fulcrum and the point of action of the force, rather
great forces may be expended for the swing out. This leads to a
relatively large and correspondingly heavy compression spring for
effecting this movement. Such heavy compression springs can not be
used in very small caliber projectiles. In addition the aerodynamic
action of the oriented tail fins is unfavorable since a torque is
produced.
In accordance with the invention there is provided a projectile or
missile construction which includes one or more tail fins or
similar fin elements which are formed to the configuration of the
outer casing of the projectile so that they may overlie this casing
in the retracted position in order to permit them to be positioned
within a firing or storage tube. The construction includes a simple
means for causing the automatic extension of the fins to move the
fin elements in a direction away from the associated casing into an
operative position at which they are extended outwardly from the
casing. This automatic extension takes place after the projectile
is directed out of the associated firing tube. The extension
equipment avoids the disadvantages of the known tail fins or tail
units and it is accommodated within a very small area, permitting
favorable space utilization within the projectile which is
particularly useful in the construction of small caliber
projectiles. The construction is attained without reducing the
aerodynamic effective surface and the fins may be transferred to
their operative position with a simple operating mechanism.
For this purpose the tail fins are connected by radially extending
webs which are carried on a ring member which may be moved axially
in respect to the associated projectile or missile. The fins are
arranged so that they can be extended in a translatory movement
perpendicular to the air flow direction. The webs connecting the
fins are mounted so that they are moved in a direction counter to
the flight direction and outwardly to project the fins from the
surface of the associated projectile. The connecting webs which are
contained on a retaining member are guided on an inwardly inclined
surface defined within the projectile casing. In the extended
position, the associated web and the fins held thereby are held in
a form-locking manner. Form-locking may be effected in the
operative extended position, for example, by a wedging effect
between the inclined surface guiding the webs and the associated
web for each fin.
The arrangement of the tail fins so that they extend parallel to
the axis of the projectile and so that they are held in this manner
by associated projecting web elements permits the fins to be
oriented for the first time to extend perpendicularly to the air
flow direction. This has the advantage that only the mass of the
individual tail fins has to be moved during the extension movement
without having to overcome any flow resistances. In addition, the
extension movement is enhanced by the air flow which presses
against the facing fin cross section in the direction of the
extension movement. The inertia also acts in the direction of the
extension movement due to the displacement of the fins against the
direction of flight. The aerodynamically effective lever length
between the center of gravity of the projectile and the tail fins
increases during the displacement. The tail fins bear, during their
entire displacement movement for extension, on the inclined surface
so that fluttering of the fins and the disturbance of the
projectory of the projectile is prevented.
The inclined guiding surface for the web portions of the fins is
advantageously defined as a shell of a truncated cone which is
formed as an axially symmetrical hollow body which is secured to
the bottom of the projectile through a cylindrical extension. The
arrangement has the advantage that the interior of the truncated
cone can be used for accommodating a jet propulsion unit if the
tail fins are to be used in projectiles with their own propulsion
system, i.e. in missiles. However, the hollow truncated cone
interior can also receive a corresponding tip of another
projectile, as is necessary, for example, when a number of
projectiles or other flying bodies filling successively the cross
section of a firing tube, have to be expelled from a single firing
tube. For drop type missile bodies which are ejected from a
receptacle which bursts automatically shortly after the drop, the
arrangement of the tail fins of the invention is also suitable.
The extension mechanism for extending the tail fins advantageously
comprises a compression coil spring, which holds the extended tail
fins in an extended position, together with a force-locking
notch-like engagement formed on a ring which contacts the web
portion of the fins in the extended position. The tail fins are
guided in a known manner by the movement of a web member in a slot
formed in the projectile casing. The webs are guided by the
inclined surface of the cone shell and in this manner a
satisfactory flutter-free movement into the effective operating
position is ensured.
The stability of each individual tail fin and its exact guidance is
favorably increased by the fact that each tail fin has a thin base
which is adapted to the configuration of the cone shell. Each tail
fin includes an outer wing tip plate which conforms to the
configuration of the outer casing of the projectile so that the
tail unit is aerodynamically stable. The wing tip plates are
advantageously made large enough to extend over a large circular
arc surrounding the projectile to form an ample aerodynamically
effective surface. In addition this provides ample surfaces of
mutual contact between adjacent projectiles, in cases in which, as
already mentioned, a number of projectiles have to be provided in
one and the same cross sectional plane of a firing tube. The
individual projectiles can be introduced into the associated tube
without requiring the formation of the outer tip plates within
narrow tolerances since the tail fins are held in their rest
position by the associated part of the casing wall and as the case
may be by adjacent projectiles.
A thrust ring which bears against all of the web portions of the
tail fins is provided with guide ways which are adapted to the
inner wall of the projectile casing and it is secured against
rotation by projections which engage in slots in the casing.
Accordingly, it is an object of the invention to provide a flying
body, in particular a projectile or missile, of a type which is
adapted to be launched from a tube which includes a tubular casing
having at least one tail fin with a plate portion of the
configuration of the outer casing of the projectile and which
overlies this casing when the fin is in a retracted position and
the projectile is located within the firing tube, and wherein
extension means are associated with the fin for automatically
moving it outwardly to extend the tail plate away from the casing
of the projectile after the projectile is expelled from the firing
tube.
A further object of the invention is to provide a flying body, and
in particular a projectile construction which includes a plurality
of tail fin elements which are carried on webs which move in
respective slots of a projectile casing and which are retained in
their inoperative position by an approximately perpendicularly
acting force, and including a member for guiding the tail fin
elements outwardly from the casing upon release of the tail fin
elements, and including a spring means for driving a thrust ring
with the associated web means along the guiding member so as to
move the tail fin elements radially outwardly from the surface of
the associated projectile casing.
A further object of the invention is to provide a flying body
having extensible tail fins which are simple in design, rugged in
construction, and economical to manufacture.
The various features of novelty which characterize the invention
are pointed out with particularity in the claims annexed to and
forming a part of this specification. For a better understanding of
the invention, its operating advantages and specific objects
attained by its use, reference should be had to the accompanying
drawings and descriptive matter in which there is illustrated and
described a preferred embodiment of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
In the drawings:
FIG. 1 is a perspective view partly in section of the trailing
portion of a projectile constructed in accordance with the
invention; and
FIG. 2 shows a detail of FIG. 1 on a larger scale.
GENERAL DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring to the drawing in particular, the invention embodied
therein includes a projectile generally designated 50 having an
extensible tail fin assembly generally designated 52 and which is
of a type which is adapted to be accommodated in and launched from
a firing tube 1.
In accordance with the invention, the tail fin assembly 52 includes
a plurality of tip plates or end members 19 which are adapted to be
extended after the projectile is launched out of the tube. In the
embodiment shown in the drawing, the projectile 50 includes a total
of four separate tip plates 19 of the configuration of the body or
casing 2 of the projectile and which rest against this outer casing
and are spaced around the periphery thereof when the projectile is
located within the firing tube 1. A feature of the construction is
that the projectile casing 2 accommodates supporting webs or guide
plates 17 for each of these four separate fins 19 and the
associated extension mechanism generally designed 54 for displacing
the guide plates 17 rearwardly and outwardly to space the fins 19
outwardly from the casing after the projectile is ejected from the
tube 1.
The projectile 50 includes at its rear or trailing portion a
truncated cone 6 and an intermediate cylindrical piece 4. The
intermediate piece 4 and the truncated cone 6 advantageously form a
single part which is fixed by any suitable means to a base or
bottom 3 of the projectile. The truncated cone 6 is designed as an
axially symmetrical hollow body having a shell 7 which thickens
toward the rear in the range of its base, (FIG. 2). In the shell 7
there is a circumferential recess 9 which serves as a retaining
notch for a foot or guide member 18 of the web 17 in its extended
operative position. The end of the cone shell 7 facing the
projectile casing 2 is flattened to form a collar 10 so that the
truncated cone 6 can be connected with the projectile casing 2, for
example, by means of screws (not shown).
A compression spring 12 of conical form bears with one end on the
projectile bottom 3 and with its opposite end on a recess 13 of a
thrust ring 14. The thrust ring 14 bears against all of the tail
fins, both in their position of rest or retracted position and in
their operative or extended position.
The foot 18 of each of the webs 17 is in operative connection with
the cone 6 and will move upwardly along the surface of the cone to
the extended position shown at the lower portion of FIG. 1 and in
FIG. 2 in which the tip plate 19 provides extended curved fin
surfaces generally designated 16 in the retracted position and 16a
in the extended position.
In the retracted position in which the projectile 50 is located
within the firing tube 1, the tip plates 19 rest on the
circumference of the casing 2 and in bearing contact therewith and
are held in this position by the interior wall of the firing tube
1. The tip plates 19 are constructed so that they extend over a
relatively large circular arc and so that there are only small
intervals between the individual tip plates. The webs 17 of the tip
plates 19 in the assembly shown are spaced approximately 90.degree.
apart. This construction provides a maximum aerodynamic surface for
a give cross section.
The web 17 has a trapezoidal form and is guided in a slot 20
defined in the projectile casing 2 and which extends longitudinally
to the rear thereof. After the assembly of the tail fins the slots
20 are closed at the rear end by the collar 10 of the cone 6 which
is secured to the casing 2.
The foot 18 of each fin extends laterally from both sides of the
web 17 and it includes a projection 24 which engages on its side
facing the cone with the corresponding recess 9 of the cone shell 7
in the extended position. The foot 18 is provided with a recess 22
along its edge which faces the thrust ring 14, which, in turn, is
located to engage with a complementary edge 23 of the thrust ring
14 as indicated in FIG. 2. The thrust ring 14 is provided with four
lugs 25 which are circularly curved to form guiding surfaces which
bear against the inner wall of the projectile casing 2 and which
extend perpendicularly with respect of the ring surface. These lugs
are arranged at equally spaced locations. The parts of the ring
between the lugs form the actual pressure surfaces for extending
the tail fins. The thrust ring 14 engages the top of the end face
27 of the web 17 when the tail fins are in the retracted position
(FIG. 1, top) while it slides downwards along the end face 17 of
each tail fin during the extension movement until the recess 22 of
the foot 18 engages the edge 23 of the ring 14.
The thrust ring 14 preferably includes two diametrically opposed
projections 26 which are located between the lugs 25 as indicated
in FIG. 2 and engage above the slots 20 and serve as an additional
guide for the ring during its extension movement. In addition the
projections 26 permit the proper alignment of the parts to be
assembled. In some instances it may be desirable to use the thrust
ring 14 as a release for a timing mechanism (not shown) adjacent
the projectile bottom 3 In this case the thrust ring 14 is extended
beyond the projectile bottom 3 in order to release the mechanism,
for example a primer or a similar fuse, when being moved into its
operating position.
The method of operating the device of the invention is as
follows:
When the projectile is ejected from the firing tube 1 in the
direction of the arrow F, the tail fins in the retracted state (fin
16 in FIG. 1) will bear on the outside jacket or casing 2 of the
projectile body. When the projectile 50 moves beyond the end of the
tube, so that the retracted fin assembly 16 clears the edge of the
tube, the compression spring 12 will move the thrust ring 14
rearwardly so that the web 17 will be moved outwardly by the
configuration of the cone 6 to position the tip plates 19 at a
spaced location from the casing in the extended position 16a
indicated at the lower portion of FIG. 1. During this time the fin
base 18 or foot runs with its projection 24 into the recess 9 of
the cone shell 7 and it is held in a form locking engagement by the
edge 23 of the thrust ring 14 which falls into the recess 22. In
addition, the compression spring 12 constantly stresses the tail
fins even in the extended position through the thrust ring 14 to
ensure force locking of these fins in the operative extended
position.
* * * * *