U.S. patent number 3,899,953 [Application Number 05/423,241] was granted by the patent office on 1975-08-19 for self-propelled fin stabilized projectiles and launchers therefor.
This patent grant is currently assigned to Constructions Navales et Industrielles de la Mediterranee (C.N.I.M.). Invention is credited to Jean Edmond Labruyere.
United States Patent |
3,899,953 |
Labruyere |
August 19, 1975 |
Self-propelled fin stabilized projectiles and launchers
therefor
Abstract
An improved, self-propelled fin stabilized projectile is
disclosed which ludes a generally cylindrical body, a finned unit
mounted thereon for relative rotational movement with respect
thereto, the cylindrical body having a plurality of rigid studs
symmetrically spaced about and affixed to the periphery of the body
and a plurality of rigid studs mounted for rotation relative to the
body. The distal end of each of the studs is adjacent to the body.
The fin unit includes a plurality of fins symmetrically spaced
about the periphery of the body and extending outwardly therefrom
so that the distal end of the fins is remote from the body, the fin
unit having a plurality of rigid studs symmetrically spaced about
the periphery of the body, the distal end of which is adjacent to
the body. A projectile launcher also is disclosed which includes a
partially cylindrical first rail having a curvilinear surface
spanning an arc of less than 180.degree. and having a groove
obliquely oriented with respect to the projectile longitudinal axis
to receive the projectile body's fixed studs. The launcher also
includes a pair of second rails each having a rectilinear groove
parallel to the projectile's body axis for receiving the projectile
fin unit's studs and the body's relatively rotatable studs.
Inventors: |
Labruyere; Jean Edmond (Paris,
FR) |
Assignee: |
Constructions Navales et
Industrielles de la Mediterranee (C.N.I.M.) (Paris,
FR)
|
Family
ID: |
26929950 |
Appl.
No.: |
05/423,241 |
Filed: |
December 10, 1973 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
|
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236612 |
Mar 21, 1972 |
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Current U.S.
Class: |
89/1.819;
244/3.23; 244/3.24 |
Current CPC
Class: |
F42B
15/00 (20130101); F41F 3/048 (20130101) |
Current International
Class: |
F42B
15/00 (20060101); F41F 3/00 (20060101); F41F
3/048 (20060101); F41f 007/00 () |
Field of
Search: |
;89/1.806,1.808,1.8,1.816,1.819 ;244/3.23,3.24 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Bentley; Stephen C.
Attorney, Agent or Firm: Finnegan, Henderson, Farabow &
Garrett
Parent Case Text
BACKGROUND
This is a continuation-in-part of patent application Ser. No.
236,612 filed Mar. 21, 1973, now abandoned.
Claims
What is claimed is:
1. A self-propelled, fin stabilized projectile comprising an
elongated, generally cylindrical projectile body, a plurality of
rigid first studs symmetrically spaced about the periphery of said
body, the proximate end of said first studs being directly affixed
to said body to prevent relative movement between said first studs
and said body, said first studs having a first length in the radial
direction of said body such that the distal end of said first studs
is adjacent to said body, a fin unit including a plurality of fins
symmetrically spaced about the periphery of said body and extending
outwardly therefrom such that the distal end of said fins is remote
from said body, said fin unit being mounted on said body for
rotational movement relative to said body about the longitudinal
axis of said body and having a plurality of rigid second studs
symmetrically spaced about the periphery of said body, said second
studs having a second length in the radial direction of said body
such that the distal end of said second studs is adjacent to said
body and a plurality of rigid third studs symmetrically spaced
about the periphery of said body and mounted for rotational
movement relative to said body about said longitudinal axis, said
third studs having a third length in the radial direction of said
body such that the distal end of said third studs is adjacent to
said body, said fins having a fourth length in the radial direction
of said body measured to the distal end of said fins, said fourth
length being significantly greater than said first, second and
third lengths.
2. A self-propelled, fin stabilized projectile as defined in claim
1 wherein said fin unit is mounted adjacent to one end of said
projectile.
3. A self-propelled fin stabilized projectile comprising:
a. an elongated generally cylindrical projectile body,
b. a plurality of rigid first guide studs symmetrically spaced
about the periphery of said body, the proximate end of said first
studs being directly affixed to said body to prevent relative
movement between said first guide studs and said body, said first
guide studs being adapted to be received within grooves obliquely
oriented with respect to the longitudinal axis of said body to
effect rotational movement of said body about its longitudinal axis
as said projectile is propelled relative to said grooves, said
first guide studs having a first length in the radial direction of
said body such that the distal end of said first guide studs is
adjacent to said body,
c. a fin unit including a plurality of fins symmetrically spaced
about the periphery of said body and extending outwardly therefrom
such that the distal end of said fins is remote from said body,
said fin unit being mounted on said body to enable rotational
movement about said longitudinal axis of said body relative to said
fin unit, said fin unit having a plurality of rigid second guide
studs symmetrically spaced about the periphery of said body and
being located on one side of the center of gravity of said
projectile, said second guide studs having a second length in the
radial direction of said body such that the distal end of said
second guide studs is adjacent to said body, each of said second
guide studs being adapted to be received within a recess parallel
to said longitudinal axis to longitudinally guide said projectile
and prevent rotational movement of said fin unit relative to said
recess when said projectile is propelled relative to said recess,
and
d. a plurality of rigid third guide studs symmetrically spaced
about the periphery of said body and mounted for rotational
movement relative to said body about said longitudinal axis, said
second guide studs having a third length in the radial direction of
said body such that the distal end of said third guide studs is
adjacent to said body, said third guide studs being spaced
longitudinally from said fin unit and located on the other side of
said center of gravity, said third guide studs being adapted to be
received within a recess parallel to said longitudinal axis to
longitudinally guide said projectile when said projectile is
propelled relative to said recess the length of said fins in the
radial direction of said body measured to the distal end of said
fins is significantly greater than said first, second and third
lengths and the distance between said body and the distal end of
each of said first second and third guide studs being substantially
equal.
4. A self-propelled, fin stabilized projectile as defined in claim
3 wherein said fin unit is mounted adjacent to one end of said
projectile.
5. A self-propelled, fin stabilized projectile as defined in claim
4 including an annular collar mounted on said body for rotation
relative thereto, said third guide studs being rigidly attached to
said collar.
6. A self-propelled, fin stabilized projectile as defined in claim
4 wherein said first guide studs are aligned within a first plane,
said second guide studs are aligned within a second plane and said
third guide studs are aligned within a third plane, said first,
second and third planes being perpendicular to said longitudinal
axis and spaced apart longitudinally.
7. In combination,
a self-propelled, fin stabilized projectile comprising an elongated
generally cylindrical projectile body, a plurality of rigid first
studs symmetrically spaced about the periphery of said body and
affixed thereto to prevent relative movement between said first
studs and said body, said first studs having a first length in the
radial direction of said body such that the distal end of said
first studs is adjacent to said body, and a fin unit including a
plurality of fins symmetrically spaced about the periphery of said
body and extending outwardly therefrom such that the distal end of
said fins is remote from said body, said fin unit being mounted on
said body for rotational movement relative to said body about the
longitudinal axis of said body and having a plurality of rigid
second studs symmetrically spaced about the periphery of said body,
a plurality of rigid third studs symmetrically spaced about the
periphery of said body and mounted for rotational movement relative
to said body about said longitudinal axis, each of said second
studs having a second length and said third studs having a third
length in the radial direction of said body such that the distal
end of each of said second and third studs are adjacent to said
body, said fins having a fourth length in the radial direction of
said body measured to the distal end of said fins, said fourth
length being significantly greater than said first, second and
third lengths,
said projectile being placed in a projectile launcher comprising a
first rail having a longitudinal axis parallel to the longitudinal
axis of said projectile body, said first rail including a first
groove extending longitudinally along a length of said first rail
and having at least a portion thereof obliquely oriented with
respect to the projectile longitudinal axis, one of said first
studs being received within said first groove and coacting
therewith to effect rotation of said projectile body about its
longitudinal axis when said projectile is propelled relative to
said launcher, said one of said first studs remaining in said first
groove while said projectile moves longitudinally relative to said
launcher and at least two spaced apart second rails each having a
rectilinear groove extending parallel to the projectile body
longitudinal axis, one of each of said second and third studs being
received within each of said rectilinear grooves and coacting
therewith to prevent rotation of said fin unit relative to said
launcher during propulsion of said projectile body relative to said
launcher and to guide said projectile during longitudinal movement
thereof relative to said launcher.
8. The combination projectile and launcher of claim 7 wherein said
first groove is aligned at an angle of approximately 1.degree. to
3.degree. with respect to the longitudinal axis of the projectile
body, according to projectile launching speed.
9. The combination projectile and launcher of claim 7 wherein
launching speed of said projectile and the angle of orientation of
said first groove relative to the projectile body longitudinal axis
are jointly formed to rotate the projectile body during launching
within the range of 90 to 270 r.p.m.
10. In combination,
a self-propelled, fin stabilized projectile comprising an elongated
generally cylindrical projectile body, a plurality of rigid first
studs symmetrically spaced about the periphery of said body and
affixed thereto to prevent relative movement between said first
studs and said body, said first studs having a first length in the
radial direction of said body such that the distal end of said
first studs is adjacent to said body, a plurality of fins
symmetrically spaced about the periphery of said body and extending
outwardly therefrom such that the distal end of said fins is remote
from said body, said fin unit being mounted on said body for
rotational movement relative to said body about the longitudinal
axis of said body and having a plurality of rigid second studs
symmetrically spaced about the periphery of said body, a plurality
of rigid third studs symmetrically spaced about the periphery of
said body and mounted for rotational movement relative to said body
about said longitudinal axis, said second and third studs being
located on opposite sides of the center of gravity of said
projectile, each of said second studs having a second length and
said third studs having a third length in the radial direction of
said body such that the distal end of each of said second and third
studs are adjacent to said body, said fins having a fourth length
in the radial direction of said body measured to the distal end of
said fins, said fourth length being significantly greater than said
first, second and third lengths,
said projectile being mounted in a projectile launcher comprising
at least two spaced apart rails each having a rectilinear groove
extending parallel to the projectile body longitudinal axis, one of
each of said second and third studs being received within each of
said rectilinear grooves and coacting therewith to prevent rotation
of said fin unit relative to said launcher and to provide
rectilinear guiding of said projectile during the propulsion
thereof relative to said launcher, and an elongated rail aligned
parallel to said projectile body and having an elongated groove
extending along a length of said elongated rail and having a
portion thereof obliquely oriented with respect to the projectile
longitudinal axis, one of said first studs being received within
said obliquely oriented groove and coating therewith while said
projectile moves longitudinally relative to said rail to effect
rotation of said projectile body about its longitudinal axis, said
obliquely oriented groove being located so that the projectile and
said first studs may move longitudinally relative to said launcher
prior to engagement of the obliquely oriented portion of said
elongated groove by said first studs.
11. A combination projectile and launcher as defined in claim 10
wherein said obliquely oriented groove has a rectilinear portion
parallel to said longitudinal axis.
12. A combination projectile and launcher as defined in claim 10
wherein said obliquely oriented groove is in the shape of a partial
helix.
13. A combination projectile and launcher as defined in claim 7
wherein said first rail is partially cylindrical and has a
curvilinear surface spanning a finite arc of less than
180.degree..
14. A combination projectile and launcher as defined in claim 10
wherein said first rail is partially cylindrical and has a
curvilinear surface spanning a finite arc of less than 180.degree..
Description
This invention relates to improved, self-propelled fin stabilized
projectiles and, more particularly, to rockets and their launchers
having improved and simplified mechanical means for guiding the
rocket during launching so that it leaves its launcher with a
desired translational trajectory and a desirable slow rotation.
While unguided rocket projectiles have many desirable features, one
particular problem of great concern is their relative flight
inaccuracy resulting in a substantial dispersion of a salva of
rockets. There are two primary systems used for improving the
accuracy of unguided rocket projectiles. One system is spin or
gyroscopic stabilization wherein a rapidly spinning projectile
resists being disturbed and maintains the orientation of its
longitudinal (spin) axis. Rotation of the projectile also tends to
cancel or average out geometrical irregularities and mass
imbalance. These physical irregularities commonly exist for various
reasons, including problems inherent in mass producing weapons
requiring absolute symmetry about a longitudinal axis, nozzle
misalignment, variation or shift in center of gravity due to uneven
burning of the propellant and other similar reasons. However,
gyroscopic stabilization causes most rocket projectiles to tend to
maintain a fixed attitude throughout its flight thereby preventing
it from orienting itself during the flight of the projectile so
that its longitudinal axis remains tangential to its trajectory.
The result of this fixed attitude is an increase of drag resulting
in reduced range and an increase in dispersion in the direction of
flght thereby lessening the projectile's accuracy. Furthermore,
external forces on the projectile, such as lateral wind forces and
gravity produce gyroscopic precession which also adversely affects
flight accuracy. While the problems of gyroscopic stabilization can
be overcome, the resultant rocket projectile will have several
limitations, including a narrow flight speed range and a relatively
large weight requiring a launcher capable of handling the heavy
projectile. Consequently, such stabilization is unsuitable for
small and medium caliber rocket projectiles.
A further problem involved with spin stabilization of rocket
projectiles is the added static friction caused by the projectile
rotating means. Rocket powered projectiles have relatively low
static thrust and any increase in static friction which has to be
overcome during launching of rocket would seriously adversely
affect the ultimate range of the rocket projectile.
A second system for controlling the flight of a rocket projectile
is fin stabilization in which the rocket projectile is stabilized
during flight by aerodynamic forces provided by relative movement
of air over the rocket projectile and its guidance fins. A fin
stabilized rocket maintains its longitudinal axis tangential to its
flight trajectory; however, fin stabilization does not compensate
for geometrical or mass asymmetry resulting in dispersion and
reduced accuracy.
Accordingly, it is an objective of this invention to provide an
unguided rocket projectile having substantially improved flight
accuracy without sacrifice of firing range and which is relatively
inexpensive to manufacture.
It is a further objective of this invention to provide a rocket
projectile and launcher therefor which enables a plurality of
rocket projectiles to be fired from a launcher of minimal size
without loss of accuracy.
Additional objectives and advantages of the invention will be set
forth in part in the description which follows, and in part will be
obvious from the description, or may be learned by practice of the
invention. The objectives and advantages of the invention may be
realized and attained by means of the instrumentalities and
combinations particularly pointed out in the appended claims.
BRIEF DESCRIPTION OF THE INVENTION
To achieve the foregoing objectives and in accordance with the
purpose of the invention, as embodied and broadly described herein,
the self-propelled, fin stabilized projectile of this invention
comprises an elongated, generally cylindrical projectile body, a
plurality of rigid first studs symmetrically spaced about the
periphery of the projectile body and affixed thereto to prevent
relative movement between the first studs and the body, the distal
end of the first studs being adjacent to the body, a fin unit
including a plurality of fins symmetrically spaced about the
periphery of the body and extending outwardly therefrom such that
the distal end of the fins is remote from the body, the fin unit
being mounted on the body for rotational movement relative to the
body about the longitudinal axis of the body, the fin unit being
mounted on the body for rotational movement relative to the body
about the longitudinal axis of the body, the fin unit having a
plurality of rigid second studs symmetrically spaced about the
periphery of the body, the distal end of the second studs being
adjacent to the body and a plurality of rigid third studs
symmetrically spaced about the periphery of the body and mounted
for rotational movement relative to the body about the body's
longitudinal axis, the distal end of the third studs being adjacent
to the body.
This invention further comprises a projectile launcher having the
above described projectile placed therein, the launcher including a
partially cylindrical first rail having a longitudinal axis
parallel to the longitudinal axis of the projectile body and having
a curvilinear surface spanning an arc of less than 180.degree., the
first rail including a first groove obliquely oriented with respect
to the projectile longitudinal axis, the first studs of the
projectile being received within the first groove and coacting
therewith to effect rotation of the projectile body about its
longitudinal axis when the projectile is propelled relative to the
launcher, and at least two equally spaced apart second rails each
having a rectilinear groove extending parallel to the projectile
body's longitudinal axis, the second and third studs of the
projectile's fin unit being received within the rectilinear groove
and coacting therewith to prevent rotation of the fin unit relative
to the launcher during propulsion of the projectile body relative
to the launcher.
The invention consists in the novel parts, constructions,
arrangements, combinations and improvements shown and described.
The accompanying drawings, which are incorporated in and constitute
a part of the specification, illustrate preferred embodiments of
the invention and, together with the description, serve to explain
the principles of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
Of the drawings:
FIG. 1 is a side view, partially cutaway, of a self-propelled fin
stabilized projectile formed in accordance with one embodiment of
this invention.
FIG. 2 is a schematic illustration of an end view of a multiple
projectile launcher for launching a plurality of projectiles
illustrated in FIG. 1.
FIG. 3 is a sectional view of one of the launchers of FIG. 2 having
a projectile in place for launching.
FIG. 4 is an enlarged perspective view of a curvilinear launching
rail which forms a part of the launcher of FIG. 3.
FIG. 5 is a side view of a self-propelled fin stabilized projectile
formed in accordance with a second embodiment of this
invention.
DETAILED DESCRIPTION OF THE INVENTION
SELF-PROPELLED PROJECTILE
Reference will now be made in detail to the present preferred
embodiments of the invention, two examples of which are illustrated
in the accompanying drawings.
Referring to FIGS. 1-4, there is illustrated a self-propelled fin
stabilized projectile and a launcher for the projectile.
In accordance with the invention, a self-propelled fin stabilized
projectile includes a generally cylindrical body and a fin unit
mounted to permit rotational movement between the projectile body
and fin unit. As here embodied, a projectile 10 is formed with a
generally cylindrical body 12 having a conical forward portion or
nose 14 and a finned unit 16. While the finned unit 16 may be
located at any one of several locations along the length of the
projectile body 12, preferably the finned unit 16 forms the tail of
the projectile 10. The nose 14, depending upon the ultimate use of
the projectile 10, may carry a warhead (not shown) of conventional
construction. The cylindrical body 12 houses a conventional rocket
propellant, such as a solid propellant grain (not shown) and a
conventional convergent-divergent nozzle 18 is mounted at the aft
end of the projectile.
In this first embodiment, the finned tail unit 16 is formed of a
cylindrical sleeve 20 having a plurality of aerodynamic fins 22
extending therefrom and equally spaced about the sleeve 20. Large
span fins having a large surface area and wherein the distal end of
the fins is remote from the projectile body 12 are used in order to
ensure a sufficient stabilization as soon as the projectile leaves
its launcher. Preferably, the total fin span is more than twice the
diameter of the projectile body 12. In the embodiment illustrated,
the fin unit 16 includes four fins 22 spaced apart by 90.degree..
The fin unit 16 is mounted to permit rotation of the projectile
body 12 relative to the fin unit. One method of accomplishing this
rotational mounting is to journal the fin sleeve 20 onto a reduced
portion 24 of the projectile body 12. If desirable, bearing means
(not shown) may be employed to facilitate free rotation of the
projectile body 12 relative to the fin unit 16. The finned tail
unit 16, being very light and freely rotating about the projectile
body 12, easily and quickly turns to present the maximum fin
surface when subjected to cross winds.
In accordance with the invention, the projectile body 12 is
provided with a plurality of small rigid projections or guide studs
28, preferably cylindrical, symmetrically spaced about the
periphery of the body 12 and affixed to the body 12 to prevent
relative movement between the studs 28 and the body 12. One method
of attaching the studs 28 to the body is to press fit the studs 28
into perforations which have a diameter slightly smaller than the
stud diameter for a firm force fit. In order to minimize drag, the
studs 28 are very small in diameter and the distal end 30 of the
studs is adjacent to the projectile body; however, to facilitate
illustrating the invention, the studs 28 shown in the drawings are
magnified. For example, with a projectile body having a 138 mm
caliber and a length of 2m, the distance between the distal end 30
of the studs 28 and the outer surface of the body 12 is 8mm, while
the stud diameter is 6mm. In order to provide symmetry for the
projectile body, at least two studs 28 must be employed and, in
that case, they are spaced apart by 180.degree.. However, it is
obvious that more than two studs may be used provided they are
disposed at equal intervals about the periphery of the projectile
body 12, such as 90.degree. for four studs or 120.degree. for three
studs.
In accordance with the invention, a plurality of rigid projections
or guide studs 32, preferably cylindrical, also are symmetrically
spaced about the fin unit sleeve 20 and fixedly attached thereto to
prevent relative movement between the studs 32 and the sleeve 20.
As was discussed above with respect to the studs 28, at least two
studs 32 must be mounted on the fin unit for aerodynamic symmetry
and the studs also must be small to minimize drag. The size of the
fin unit studs 32 preferably are the same as the projectile body
studs 28.
A third group of guide studs 34 also is provided, with the studs
being equally spaced about the periphery of the projectile body and
positioned on the side of the projectile's center of gravity
opposite that of the fin unit 16. In the embodiment illustrated,
the studs 34 are spaced forwardly from the fin unit 16, at least
slightly ahead of the projectile's center of gravity. The third
group of studs 34 is mounted for relative rotational movement with
respect to the projectile body 12. The studs 34 may be fixedly
mounted, such as by a force fit, on an annular collar 36 which is
journalled onto the projectile body 12 to permit free rotation
therebetween.
The projectile body 12 may be formed of seamless cold drawn steel
which is swaged at its tail end to receive the fin tail unit 16. An
annular depression can also be swaged into the body to receive the
stud collar 36. The fin tail unit preferably is formed of a light
alloy casting in order to minimize its weight while still providing
aerodynamic guidance. All of the studs 28, 32 and 34 preferably are
steel with the studs 32 being attached to the fin sleeve 20 by
molding the sleeve 20 around the base of the studs.
LAUNCHER
Further in accordance with this invention, there is provided a
launcher for accurately firing the projectile 10. The design of the
projectile 10 and the launcher are particularly suited for
launching multiple projectiles while minimizing the size of the
multiple rocket launcher. FIG. 2 illustrates a multiple rocket
launcher 50 formed of a plurality of individual launchers 52, one
of which is illustrated in FIG. 3 and is shown with a projectile 10
in position for launching. The launcher 52 essentially includes a
partially cylindrical launching rail 54 having a curvilinear
surface 56 which conforms to the periphery of the projectile 10.
The maximum arc spanned by the curvilinear surface 56 is determined
by the number of fins 22 borne by the projectile 10, the surface 56
being designed to reside between two adjacent fins 22. For a four
finned projectile 10, wherein the fins are spaced apart 90.degree.,
theoretically the arc span for the surface 56 may approach
90.degree.. However, to accommodate fin thickness and insure
complete clearance between the rail 54 and the fins, the
curvilinear surface 56 preferably spans approximately 50.degree..
If desired, more than one cylindrical rail 54 could be used. For
example, a second such rail (not shown) could be mounted
diametrically opposite to the rail 54 shown in FIG. 3.
As here embodied, a groove 58 is provided in the curvilinear
surface 56 having a width sized to receive the studs 28 affixed to
the projectile body 12. The groove 58 is obliquely oriented with
respect to the longitudinal axis of the projectile 10 in order to
rotate the projectile body 12 as the projectile is launched as is
described in detail below. Preferably, the groove 58 takes the form
of a portion of a helix as can be best seen in FIG. 4. Because
rocket projectiles have a constant acceleration and because the
groove 58 has a relatively constant slope, rotation is imparted to
the projectile 10 at a constant acceleration. Since the studs will
not experience shocks their size can be minimized thereby
minimizing drag and friction.
As here embodied, the launcher 52 also includes two additional
launching rails 60, 62 located on diametrically opposed sides of
the projectile 10 and very close to the projectile body 12 to
suppress projectile vibrations. The launching rails 60, 62 are
formed with rectilinear grooves 64, 66, respectively, sized to
receive the studs 32 of the finned tail unit 16 and the third group
of studs 34. The rectilinear grooves 64, 66 are aligned parallel to
the longitudinal axis of the projectile 10.
In a preferred form of launcher 52 the rectilinear launching rails
60, 62 are angularly offset from the cylindrical launching rail 54
to insure no interference between the fin tail unit studs 32 and
the cylindrical rail 54. As can be seen in FIGS. 2 and 3 the
launcher 52 is relatively open (as compared with launch tubes) to
eliminate the effect of the inversion of flow of burned gases at
the exit end of the launcher as the projectile leaves the launcher,
which is a substantial problem with launch tubes.
Upon ignition of the projectile propellant, the projectile 10 is
propelled along the length of the launcher 52. The rectilinear
grooves 64, 66 provide axial stability and guide the projectile
during launching and prevent rotation of the finned tail unit 16
relative to the launcher 52. The longitudinally spaced apart group
of studs 32, 34 in the launching rails 60, 62 support the
projectile 10 so that the projectile body 12 does not rest on and
slide along the surface 56 of launching rail 54 which would involve
substantial friction. The shape and small size of the studs, in
addition to producing minimum aerodynamic drag also minimize the
launcher sliding friction. However, as a safety feature, if one of
the studs 32, 34 break the projectile body 12 will rest on the
launcher rail 54 and can still be launched with reasonable
accuracy, albeit not as accurately as if all of the studs 32, 34
are in the grooves 64, 66. The partially cylindrical rail 54, in
which the rigid studs 28 firmly affixed to the projectile body 12
reside and with which they coact causes the projectile body 12 to
rotate about its longitudinal axis relative to the launcher 52 and,
hence, relative to the fin tail unit 16. The particular shape and
angular orientation of the groove 54 controls, at least partially,
the ultimate speed of rotation of the projectile body 12. For
example, for a given launch velocity, the angular orientation of
the groove 58 relative to the longitudinal axis of the projectile
10 determines the speed of rotation of the body 12. Alternatively,
for a particular groove orientation, the rotational speed of the
body 12 can be modified by varying the projectile launch
velocity.
In order to avoid the deleterious effects of gyroscopic
stabilization while obtaining the benefits afforded by rotating the
projectile body, namely to equalize mass or geometrical
irregularities and asymmetries, the projectile body desirably is
rotated at a relatively slow speed, preferably on the order of 90
to 270 r.p.m., as compared to gyroscopic stabilization rates of
10,000 r.p.m. and higher. Satisfactory results have been obtained
with a body rotation of 150 r.p.m. when a projectile weighing 52 kg
and having a length of 2m and caliber of 138mm is launched at 33
meters per second. To accomplish this slow rotational speed, the
angle at which the helical groove 58 crosses a longitudinal element
of the partial cylindrical curvature of the internal surface 56 of
the launch rail 54 is small, preferably within the range of
1.degree. to 3.degree.. For a 30 meter per second launch velocity
the rotational speed for a 1.degree. groove angle is 90 r.p.m. and
for a 3.degree. groove angle the rotational speed is 270 r.p.m.
Because of the initial thrust developed by rocket motors is
relatively low, it is desirable to reduce the static friction which
must be overcome to a minimum. Since the helical groove 58 provides
a retardant force in the longitudinal direction of propulsion of
the projectile 10 in order to provide a force for effecting
rotation of the projectile body, a preferred form of launching rail
54, shown in FIG. 4, provides an initial portion 66 of the groove
58 which is rectilinear and does not have the added resistance
force in the axial direction which is provided by the helical
portion 68. This permits the rocket motor to overcome the static
friction and begin propulsion of the projectile 10 before the
helical portion 68 of the groove 58 becomes effective for imparting
rotation to the projectile. Similarly, instead of forming the
groove 58 in the form of a partial helix, the groove can be formed
to gradually increase in angularity in order to gradually impart
rotation to the projectile as the projectile is propelled and
attains sufficient inertia to help overcome the braking effect
caused by the helical portion of the groove 58. Preferably, the
projectile body 12 is brought to its cruise rotating speed slightly
before leaving the launcher 52.
Further in accordance with the invention, the multiple pad launcher
50 is formed with the individual launchers 52 positioned in
overlapping formation to minimize the total cross-sectional area
required for a plurality of launchers. In other words, for a fixed
cross-sectional area, more launchers 52 and projectiles 10 can be
accommodated by virtue of the overlapping configuration than if the
launchers were horizontally and vertically aligned. Furthermore,
the overlapping configuration permits the individual launcher's 52
structural members to serve also as supports for adjacent
individual launchers rather than requiring additional structural
members. This overlapping configuration of launchers suitable for
launching finned rockets which are provided with rotational motion
is made possible by the construction of the projectile 10 and the
cooperating launching rails 54 and 60.
SELF-PROPELLED PROJECTILE (SECOND EMBODIMENT)
A second form of projectile formed in accordance with this
invention is illustrated in FIG. 5. The projectile 70 is formed
with a generally cylindrical body 72 which houses the propellant
and nozzle (not shown) and has a nose portion 74 at the forward end
thereof. A cylindrical sleeve 76 is mounted for rotation about the
projectile body 72 such as through the use of journal or ball
bearings (not shown) or other suitable friction reducing means. A
plurality of fins 78 are fixedly attached to the sleeve 76 and are
symmetrically spaced about the periphery thereof. Furthermore, in
accordance with this invention, a plurality of guide studs are
fixedly attached to the sleeve and symmetrically spaced about the
sleeve. As shown in FIG. 5, there are two groups of guide studs 80,
82 spaced longitudinally apart, one group 80 being located adjacent
to the fins 78 and the other group 82 being spaced therefrom. A
third group of guide studs 84 are fixedly attached directly to the
projectile body 72 for imparting rotation to the body 72.
The guide studs 80, 82 mounted on the sleeve 76 cooperate with
longitudinal grooves in a launcher, such as the grooves 64, 66 in
the launcher 52 (FIG. 3) to longitudinally guide the projectile 70
during its launch and to prevent rotation of the sleeve 76 and fins
78. The guide studs 84 attached to the projectile body 72 coact
with the partially helical groove 58 to impart rotation to the
projectile body 72 which then rotates slowly relative to the finned
sleeve 76.
SUMMARY
In operation, when the projectile 10 illustrated in FIG. 1 (or
projectile 70 illustrated in FIG. 5) is launched from the launcher
52, the interaction between the curved launching rail 54 having the
groove 58 therein and the projectile body studs 28 (84 on
projectile 70) imparts a slow rotational motion to the projectile
body, just enough to counterbalance or average out any geometrical
or mass imbalances in the projectile but not fast enough to produce
gyroscopic stabilization. The guide studs 32, 34 (80, 82, on
projectile 70) coacting with the longitudinal grooves 64, 66 in the
launcher 52 provide the longitudinal guidance and prevent
rotational motion of the finned section 16. The finned section 16
(76 on projectile 70) provides the fin stabilization which permits
the rocket to maintain a tangential alignment with respect to its
flight path throughout the entire flight of the projectile. This
combined effect of slow rotation and fin stabilization provides
improved flight accuracy and stability without sacrificing
range.
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