U.S. patent application number 10/173633 was filed with the patent office on 2002-12-26 for missile spiralling mechanism -2.
Invention is credited to Kusic, Tom.
Application Number | 20020195520 10/173633 |
Document ID | / |
Family ID | 3829801 |
Filed Date | 2002-12-26 |
United States Patent
Application |
20020195520 |
Kind Code |
A1 |
Kusic, Tom |
December 26, 2002 |
Missile spiralling mechanism -2
Abstract
A missile 1 with a spiral inducing assembly 2 which is capable
of inducing the missile to travel in a continuous spiralling motion
without the missile rolling. Two fins 3 and 4 are attached to a
tube 5 that is able to rotate around the encircled part of the
missile fuselage. The fins 3, 4 are able to rotate in a pivoting
manner on the rotatable tube 5 with respect to the rotatable tube
5, thereby changing their pitch relative to the longitudinal axis
of the rotatable tube 5. Fin 3 is larger than fin 4. The difference
in sizes between the fins makes the larger fin 3 exert a greater
force on the rotatable tube 4 than the smaller fin 4 when the fins
are pitched in unison. The aerodynamic imbalance between the fins
thus causes the rotatable tube 5 to rotate. When pitched at an
angle to the longitudinal axis in unison, both fins 3, 4 would
exert a lateral force on the rotatable tube 5. Thus, as well as
forcing the rotatable tube 5 to rotate, the fins 3, 4 would also
push the rotatable tube sideways. But as the rotatable tube is
pushed sideways, it rotates, and hence the lateral direction of
push constantly revolves, causing a spiralling motion of the
missile when in flight.
Inventors: |
Kusic, Tom; (Melbourne,
AU) |
Correspondence
Address: |
TOM KUSIKC
PO BOX 932
GPO MELBOURNE
3001
AU
|
Family ID: |
3829801 |
Appl. No.: |
10/173633 |
Filed: |
June 19, 2002 |
Current U.S.
Class: |
244/99.11 |
Current CPC
Class: |
B64C 5/04 20130101; B64C
9/02 20130101; B64C 9/00 20130101; B64C 13/18 20130101; B64C 13/16
20130101; B64C 5/10 20130101 |
Class at
Publication: |
244/75.00R |
International
Class: |
B64C 005/00; B64C
013/00; B64C 017/00; B64D 031/00 |
Foreign Application Data
Date |
Code |
Application Number |
Jun 20, 2001 |
AU |
PR 5830 |
Claims
The claims defining this invention are as follows:
1. A missile comprising a missile fuselage and a spiral inducing
assembly, which said spiral inducing assembly is capable of forcing
the missile to travel in a spiralling motion during flight of the
missile, and which said spiral inducing assembly consists of a
tube, and which said tube encircles part of the missile fuselage of
the missile and is able to rotate relative to the encircled part of
the missile fuselage, with a plurality of fins connected to the
said tube, which said fins are connected to the tube such that the
fins protrude laterally outward from the tube and such that the
said fins can be rotated in a pivoting manner relative to the tube,
and such that the said fins can be rotated in the said pivoting
manner in the same direction, and which said spiral inducing
assembly comprises a fin rotating mechanism by which fin rotating
mechanism the said fins can be rotated in the said pivoting manner,
and by which said fin rotating mechanism the said fins can be
rotated in the said pivoting manner and simultaneously in the same
direction as each other such that during flight of the missile one
of the said fins connected to the tube can continuously exert a
greater magnitude of force on the said tube than can another of the
said fins that is connected to the said tube.
2. A missile comprising a missile fuselage and a spiral inducing
assembly, which said spiral inducing assembly is capable of forcing
the missile to travel in a spiralling motion during flight of the
said missile, and which said spiral inducing assembly consists of a
tube, and which said tube encircles part of the missile fuselage of
the missile and is able to rotate relative to the encircled part of
the missile fuselage, with a plurality of fins connected to the
said tube, which said fins are connected to the tube such that the
fins protrude laterally outward from the tube and such that the
said fins can be rotated in a pivoting manner relative to the tube,
and which said spiral inducing assembly comprises a fin rotating
mechanism by which fin rotating mechanism the said fins can be
rotated in the said pivoting manner such that during flight of the
said missile one of the said fins connected to the tube can
continuously exert a greater magnitude of force on the said tube
than can another of the said fins that is connected to the said
tube.
3. A missile comprising a missile fuselage and a spiral inducing
assembly, which said spiral inducing assembly is capable of forcing
the missile to travel in a spiralling motion during flight of the
missile, and which said spiral inducing assembly consists of a
tube, and which said tube encircles part of the missile fuselage of
the missile and is able to rotate relative to the encircled part of
the missile fuselage, with a plurality of fins connected to the
said tube, which said fins are connected to the tube such that the
fins protrude laterally outward from the tube and such that the
said fins can be rotated in a pivoting manner relative to the tube,
and such that the said fins can be rotated in the said pivoting
manner in the same direction, and which said spiral inducing
assembly comprises a fin rotating mechanism by which said fin
rotating mechanism the said fins can be rotated in the said
pivoting manner and in the same direction as each other and by
which said fin rotating mechanism the said fins thus can be rotated
in the said same direction relative to the tube such that one of
the said fins connected to the tube can be rotated to a greater
degree relative to the tube than can another of the said fins that
is connected to the said tube.
4. A missile comprising a missile fuselage and a spiral inducing
assembly, which said spiral inducing assembly is capable of forcing
the missile to travel in a spiralling motion during flight of the
said missile and which said spiral inducing assembly consists of a
tube, and which said tube encircles part of the missile fuselage of
the missile and is able to rotate relative to the encircled part of
the missile fuselage, with a plurality of fins connected to the
said tube, which said fins are connected to the tube such that the
fins protrude laterally outward from the tube and such that the
said fins can be rotated in a pivoting manner relative to the tube,
and such that the said fins can be rotated in the said pivoting
manner in the same direction, and which said spiral inducing
assembly comprises a fin rotating mechanism by which said fin
rotating mechanism the said fins can be rotated in the said
pivoting manner and in the same direction as each other, and with
the said fins being such that one of said fins connected to the
tube is of larger size than is another of the said fins.
5. The missile of claim 1 wherein the said fin that is able to
exert a greater magnitude of force on the tube can be pivotly
rotated to a greater degree than the said other fin by means of the
fin rotating mechanism, such that when the said fin that can be
rotated to greater degree is rotated to a greater degree than the
said other fin the fin that is rotated to a greater degree exerts a
greater magnitude of force on the tube during flight of the missile
than the said other fin.
6. The missile of claim 1 wherein the said fin that is able to
exert a greater magnitude of force on the tube is of larger size
than the said other fin such that by being of larger size the fin
that is of larger size can exert a greater magnitude of force on
the tube than the said other fin during flight of the missile.
7. The missile of claim 2 wherein the said fin that is able to
exert a greater magnitude of force on the tube can be pivotly
rotated to a greater degree than the other said fin by means of the
fin rotating mechanism, such that when the said fin that can be
rotated to greater degree is rotated to a greater degree than the
said other fin the fin that is rotated to a greater degree exerts a
greater magnitude of force on the tube during flight of the missile
than the said other fin.
8. The missile of claim 2 wherein the said fin that is able to
exert a greater magnitude of force on the tube is of larger size
than the said other fin such that by being of larger size the fin
that is of larger size can exert a greater magnitude of force on
the tube than the said other fin during flight of the missile.
9. A missile comprising a missile fuselage and a spiral inducing
assembly, which said spiral inducing assembly is capable of forcing
the missile to travel in a spiralling motion during flight of the
said missile, and which said spiral inducing assembly consists of a
tube, and which said tube encircles part of the missile fuselage of
the missile and is able to rotate relative to the encircled part of
the missile fuselage, with a plurality of fins connected to the
said tube, which said fins are connected to the tube such that the
fins protrude laterally outward from the tube and such that the
said fins can be rotated in a pivoting manner relative to the tube,
and such that the said fins can be rotated in the said pivoting
manner in the same direction and in unison relative to the tube and
which said spiral inducing assembly comprises a fin rotating
mechanism by which said fin rotating mechanism the said fins can be
rotated in the said pivoting manner in the same direction as each
other and in unison relative to the tube and with the said fins
being such that during flight of the said missile one of the said
fins connected to the tube can continuously exert a greater
magnitude of force on the said tube than can another of the said
fins that is connected to the said tube.
10. The missile of claim 9 wherein the said fin that is able to
exert a greater magnitude of force on the tube is of larger size
than the said other fin such that by being of larger size the fin
that is of larger size can exert a greater magnitude of force on
the tube than the said other fin during flight of the missile.
11. The missile of claim 1 wherein the spiral inducing assembly can
force the said missile to travel in a continuous spiralling motion
while the said fins are continuously maintained in a rigid position
with respect to the said tube.
12. A missile comprising a missile fuselage and a spiral inducing
assembly, which said spiral inducing assembly is capable of forcing
the missile to travel in a spiralling motion during flight of the
said missile, and which said spiral inducing assembly consists of a
tube, which said tube encircles part of the missile fuselage of the
missle and which said tube is able to rotate relative to the
encircled part of the missile fuselage, with a plurality of fins
connected to the said tube, which said fins are connected to the
tube such that the fins protrude laterally outward from the tube
and such that the said fins can be rotated in a pivoting manner
relative to the tube, and such that the said fins can be rotated in
the said pivoting manner in the same direction, with a stem
connected to one fin and another stem connected to another fin, and
with an additional tube encircling part of the missile fuselage of
the missile, which missile fuselage comprises a fore end and an aft
end, and which said additional tube is able to move between the
fore end and the aft end of the missile fuselage, with at least one
hydraulic actuator connected to the missile fuselage, which
hydraulic actuator is connected to the missile fuselage such that
the hydraulic actuator is able to push the additional tube and
force the additional tube to move between the fore end and the aft
end of the missile fuselage, such that as the additional tube is
moved the additional tube can be pressed against the said stems,
such that as the additional tube presses against the stems, the
respective fins are rotated in a pivoting manner with respect to
the tube that is able to rotate relative to the missile fuselage,
with the stems of such relative lengths with respect to one another
and with the stems connected to the respective fins such that the
said fins can be rotated in the said pivoting manner and in the
same direction as each other such that one of the said fins can be
pivotly rotated to a greater degree relative to the tube that is
able to rotate relative to the missile fuselage than can another of
the said fins be rotated relative to tube that is able to rotate
relative to the missile fuselage.
13. The missile of claim 12 wherein the said stems are positioned
such that they extend longitudinally with respect to the missile
fuselage of the missile.
14. The missile of claim 12 wherein the additional tube is in the
form of a ring.
15. The missile of claim 12 wherein an additional hydraulic
actuator is connected to the missile fuselage, which additional
hydraulic actuator is connected to the missile fuselage such that
as hydraulic pressure is applied to the additional hydraulic
actuator, the additional hydraulic actuator is able to be pressed
against the tube that is able to rotate around the missile fuselage
such that friction can be induced between the additional hydraulic
actuator and the tube that is able to rotate around the missile
fuselage.
16. The missile of claim 12 wherein a lever is connected to the
missile fuselage, which lever is connected to the missile fuselage
such that the lever is able to be pressed against the tube that is
able to rotate around the missile fuselage such that friction can
be induced between the lever and the tube that is able to rotate
around the missile fuselage.
17. The missile of claim 1 wherein an additional hydraulic actuator
is connected to the missile fuselage, which additional hydraulic
actuator is connected to the missile fuselage such that as
hydraulic pressure is applied to the additional hydraulic actuator,
the additional hydraulic actuator is able to be pressed against the
tube that is able to rotate around the missile fuselage such that
friction can be induced between the additional hydraulic actuator
and the tube that is able to rotate around the missile
fuselage.
18. The missile of claim 1 wherein a lever is connected to the
missile fuselage, which lever is connected to the missile fuselage
such that the lever is able to be pressed against the tube that is
able to rotate around the missile fuselage such that friction can
be induced between the lever and the tube that is able to rotate
around the missile fuselage.
19. The missile of claim 2 wherein an additional hydraulic actuator
is connected to the missile fuselage, which additional hydraulic
actuator is connected to the missile fuselage such that as
hydraulic pressure is applied to the additional hydraulic actuator,
the additional hydraulic actuator is able to be pressed against the
tube that is able to rotate around the missile fuselage such that
friction can be induced between the additional hydraulic actuator
and the tube that is able to rotate around the missile
fuselage.
20. The missile of claim 2 wherein a lever is connected to the
missile fuselage, which lever is connected to the missile fuselage
such that the lever is able to be pressed against the tube that is
able to rotate around the missile fuselage such that friction can
be induced between the lever and the tube that is able to rotate
around the missile fuselage.
21. The missile of claim 3 wherein an additional hydraulic actuator
is connected to the missile fuselage, which additional hydraulic
actuator is connected to the missile fuselage such that as
hydraulic pressure is applied to the additional hydraulic actuator,
the additional hydraulic actuator is able to be pressed against the
tube that is able to rotate around the missile fuselage such that
friction can be induced between the additional hydraulic actuator
and the tube that is able to rotate around the missile
fuselage.
22. The missile of claim 3 wherein a lever is connected to the
missile fuselage, which lever is connected to the missile fuselage
such that the lever is able to be pressed against the tube that is
able to rotate around the missile fuselage such that friction can
be induced between the lever and the tube that is able to rotate
around the missile fuselage.
23. The missile of claim 4 wherein an additional hydraulic actuator
is connected to the missile fuselage, which additional hydraulic
actuator is connected to the missile fuselage such that as
hydraulic pressure is applied to the additional hydraulic actuator,
the additional hydraulic actuator is able to be pressed against the
tube that is able to rotate around the missile fuselage such that
friction can be induced between the additional hydraulic actuator
and the tube that is able to rotate around the missile
fuselage.
24. The missile of claim 4 wherein a lever is connected to the
missile fuselage, which lever is connected to the missile fuselage
such that the lever is able to be pressed against the tube that is
able to rotate around the missile fuselage such that friction can
be induced between the lever and the tube that is able to rotate
around the missile fuselage.
25. The missile of claim 9 wherein an additional hydraulic actuator
is connected to the missile fuselage, which additional hydraulic
actuator is connected to the missile fuselage such that as
hydraulic pressure is applied to the additional hydraulic actuator,
the additional hydraulic actuator is able to be pressed against the
tube that is able to rotate around the missile fuselage such that
friction can be induced between the additional hydraulic actuator
and the tube that is able to rotate around the missile
fuselage.
26. The missile of claim 9 wherein a lever is connected to the
missile fuselage, which lever is connected to the missile fuselage
such that the lever is able to be pressed against the tube that is
able to rotate around the missile fuselage such that friction can
be induced between the lever and the tube that is able to rotate
around the missile fuselage.
Description
[0001] The aim of this invention is to provide a missile that has
higher chance of surviving attacks from anti-missile weapons when
flying towards an enemy than missiles currently in use. The missile
according to this invention is fitted with a mechanism that enables
the missile to travel in a continuous spiralling motion while
flying towards an enemy, without the need to make continues control
adjustments. The mechanism is such that once activated, the
spiralling motion is automatic. The spiralling motion is achieved
during flight without rolling the missile.
[0002] In this invention the spiralling motion of the missile is
achieved using moveable fins on a rotatable tube, with the tube
encircling a part of missile (preferrably the forward part of the
missile fuselage) and able to rotate around the encircled part of
the missile. The fins are attached to the rotatable tube so that
they can be rotated in a pivoting manner relative to the rotatable
tube.
[0003] For the missile to enter a spiralling motion, the fins would
need to revolve around part of the missile so that the missile is
pushed in changing directions. In the invention this achieved by
using the rotatable tube, that allows the fins to revolve around
part of the missile--using the rotatable tube as means of
travelling around a part of the missile. The invention provides a
number of means by which rotation of the rotatable tube can be
achieved. One way is to use fins that are of unequal size with
respect to one another. Having fins that are of unequal size would
cause an aerodynamic imbalance when the fins are moved from the
horizontal position. With one fin pushing harder than the other,
rotation of rotatable tube would result. The rotation of the
rotatable tube would be automatic and continuous while the
imbalance between the fins was maintained. Placing the fins back in
a horizontal position would remove the imbalance, allowing the
rotatable tube to come to rest. Friction between the missile and
the rotatable tube or a braking mechanism such as a hydraulicly
activated brake pad being push against the rotatable tube could
help to stop the rotatable tube from rotating.
[0004] Another way of causing the rotatable tube to rotate
according to the invention is to increase the pitch of one fin more
than that of the other. Increasing the pitch of one fin relative to
the other would cause an aerodynamic imbalance on the rotatable
tube, thereby forcing it to rotate. Allowing the fins to return to
a horizontal position would remove the aerodynamic imbalance,
allowing the rotatable tube to come to rest.
[0005] FIG. 1 shows a missile 1 according to this invention, fitted
with one form of a spiral inducing assembly 2.
[0006] Referring to FIG. 1, a rotatable tube 3 forming part of the
spiral inducing assembly 2 can be seen encircling part of the
missile fuselage 4 of the missile 1. The missile fuselage has a
fore end and an aft end. Referring to this tube 3 as the primary
tube 3, the primary tube 3 is able to rotate around the part of the
missile fuselage encircled by the primary tube. The primary tube is
shown as being narrower in the front than at the rear. Also shown
is another tube 5 that is fitted to the missile 1 such that it
encircles part of the missile fuselage 4 of the missile. Referring
to this tube 5 as the activation tube 5, the activation tube 5 is
fitted so that it can be moved in a forward direction relative to
the part of the missile fuselage 4 encircled by the activation tube
and then back to its original position on the missile fuselage.
FIG. 1 also shows the edge of one horizontal fin 6 that is
connected to the outside of the primary tube 3. The fin 6 is
connected to the outside of primary tube 3 such that it can rotate
in a pivoting manner as shown in FIG. 2.
[0007] FIG. 1A shows an enlarged illustration of the left side of
the spiral inducing assembly 2. The fin 6 in FIG. 1A is connected
to the outside of the primary tube 3 by a connecting joint 7 which
is in the form of a connecting rod 7. Extended from the connecting
rod 7 in FIG. 1A is a protruding section 8 which is used to rotate
the connecting rod 7. Rotation of the connecting rod 7 causes the
fin 6 to rotate in a pivoting manner around the connecting rod 7
(in the manner shown in FIG. 2). Linked to the protruding section 8
in FIG. 1A is a stem 9. Referring to this stem 9 as an activation
stem 9, the activation stem 9 is used as a means for pushing the
protruding section 8 such that when the protruding section 8 is
pushed, the protruding section 8 forces the connecting rod 7 to
rotate around the longitudinal axis of the connecting rod 7. The
activation stem 9 is linked to the protruding section 8 by a rivet
10. The activation stem 9 is shown as being fitted on the outside
of the primary tube 3 and is supported on the primary tube 3 by a
retaining bracket 11. The retaining bracket 11 is rigidly joined to
the primary tube but is channelled to allow the activation stem 9
to move longitudinally between the retaining bracket 11 and the
primary tube 3. The activation stem 9 is allowed to protrude
rearward from the primary tube so that it can be reached by the
activation tube 5 when the activation tube 5 is moved forward on
the missile fuselage 4. The activation tube 5 is forced to move
forward by an activation mechanism 12 consisting of hydraulic
actuators 13 and 14. FIG. 3 shows the hydraulic actuators 15 and 16
located on the right side of the spiral inducing assembly 2 which
also form part of the activation mechanism 12 by which the
acivation tube 5 is forced to move. When the hydraulic actuators 13
14 15 and 16 are forced to extend as hydraulic pressure is applied
to them, they force the activation tube 5 to move forward as shown
in FIG. 2. FIG. 2 shows that as the activation tube 5 is forced to
move forward on the missile fuselage 4 when the hydraulic actuators
13 and 14 extend, it eventually makes contact with the activation
stem 9. As the activation tube 5 is forced to move further forward,
it pushes the activation stem 9 forward on primary tube. As the
activation stem 9 is pushed forward, the activation stem pushes
against the protruding section 8 and moves the protruding section
8, thereby rotating the fin 6 around the connecting rod 7 in a
pivoting manner.
[0008] In FIG. 2 a rivet 10 is shown connecting the activation stem
9 to the protruding section 9, which allows movement between the
activation stem 9 and the protruding section 8. The retaining
bracket 11 keeps the activation stem from moving laterally around
the primary tube. The retaining bracket 11 however does allow
longitudinal sliding movement of the activation stem 9 so that it
can be pushed and moved by the activation tube 5.
[0009] FIG. 3 shows the the right side of the spiral inducing
assembly 2 of FIG. 1. Shown is another fin 17, another connecting
joint 18 in the form of a connecting rod 18 that connects the fin
17 to the outside of the primary tube 3. Another protruding section
19 is used to rotate the connecting rod 18, and the activation stem
20 is used to push the protruding section 19, with the activation
stem 20 linked to the protruding section 19 by a rivet 21. Also
visible in FIG. 3 is the activation tube 5. The connecting rod 18
allows the fin 17 to rotate in a pivoting manner. Another retaining
bracket 22 is shown supporting the respective activation stem
20.
[0010] Thus, it can be seen from FIGS. 1, 1A, 2 and 3 that the
activation tube 5, the activation stems 9 and 20, retaining
brackets 11 and 22, protruding sections 8 and 19, rivets 10 and 21
used to connect the activation stems 9 and 20 to respective
protruding sections 8 and 19, the connecting joints 7 and 18 in the
form of connecting rods 7 and 18, and the activation mechanism 12
used to move the activation tube 5 consisting of the hydraulic
actuators 13, 14, 15 and 16, collectively form a fin rotating
mechanism.
[0011] FIG. 4 shows the missile 1 of FIG. 1 from underneath. It
shows that one fin 6 is larger than the other fin 17. When these
fins 6 and 17 are rotated in a pivoting manner and in the same
direction to the same extent, an aerodynamic imbalance between the
fins 6 and 17 arises furing flight of the missile because of size
diference between the fins 6 and 17. The larger fin 6 will exert a
greater magnitude of force on the primary tube 3 during flight of
the missile 1 than the smaller fin 17. As a result, the aerodynamic
imbalance between the fins 6 and 17 would cause the primary tube 3
to rotate. But both fins 16 and 17 would also be pushing the
missile laterally, in a similar manner to canards. Thus, because
the primary tube 3 is forced to rotate, the lateral force exerted
on the missile by the fins 6 and 17 keeps changing, thus forcing
the missile to keep changing its direction and hence entering a
spiralling motion.
[0012] FIG. 5 shows the front cut out of the spiral inducing
assembly 2 of FIG. 1. Shown here is the primary tube 3, the fins 6
and 17, (with fin 6 being larger than fin 17), the missile fuselage
4 of the missile, the activation stems 9 and 20, linked by rivets
10 and 21 to the protruding sections 8 and 19 respectively, the
connecting rods 7 and 18 penetrating the primary tube 3, and with
the protruding sections 8 and 19 screwed in the connecting rods 7
and 18 respectively. FIG. 5 shows the primary tube 3 as being
creased in sections 23, 24 and 25. The creased sections 23, 24 and
25 are used as a means to support the primary tube 3 on the on the
encircled part of the missile fuselage 4, while allowing for gaps
26 and 27 to exist between the primary tube 3 and the encircled
part of the missile fuselage 4. The gaps 26 and 27 allow the
connecting rods 7 and 18 to protrude inwardly through the primary
tube 3 without making contact with the encircled part of the
missile fuselage 4. Securing bolt nuts 28 and 29 are shown securing
the connecting rods 7 and 18 to the primary tube 3, with thrust
bearings 30 and 31 allowing for easy rotation of the connecting
rods 7 and 18 around their respective longitudinal axes'.
[0013] FIG. 6 shows the rear of the primary tube 3 of FIG. 1 as a
cut out. Shown in FIG. 6 are the rear ends of the activation stems
9 and 20, and the retaining brackets 11 and 22 that support the
activation stems 9 and 20, and prevent uncontrolled lateral
movement of the activation stems 9 and 20. The primary tube 3 is
shown as having sections creased 32, 33 and 34.
[0014] The primary tube can be formed in various geometric shapes,
including cylindrical or cone shaped.
[0015] FIG. 7 shows a side cutting of the part of the missile
fuselage 35 encircled by the primary tube 3 of FIG. 1. The
encircled part of the missile fuselage 35 can be seen to be
narrower than the rest of the missile fuselage 4. Thrust bearings
36 and 37 are positioned on the narrowed section of the missile
fuselage 35. The thrust bearings are used to support the primary
tube and to prevent the primary tube moving longitudinally relative
to the missile fuselage 4.
[0016] FIG. 8 shows another way that the primary tube 3 of FIG. 6
can be supported, with wheels 38, 39 and 40 attached to the creased
sections 32, 33 and 34 of the primary tube 3. The wheels 38, 39 and
40 help to support the primary tube 3 on the encircled part of the
missile fuselage 35.
[0017] FIG. 9 shows another way of supporting the primary tube 3.
Shown is a tube of smaller diameter 41 than the primary tube 3.
This smaller tube 41 is a supporting tube 41 in that it can be used
to support the primary tube 3. It has a smaller diameter than the
primary tube 3 to provide a gap 42 between the primary tube 3 and
the supporting tube 41. The gap 42 is used to allow freedom of
movement to the protruding sections 8 and 19, and the activation
stems 9 and 20 shown positioned inside the primary tube 3. The
protruding sections 8 and 19 and the connecting rods 7 and 18 have
been formed as moulded units, allowing easier assembly. Bolts 43,
44, 45 and 46 are used to join the primary tube 3 to the supporting
tube 41. The supporting tube 41 is able to rotate around the
encircled part of the missile fuselage 35.
[0018] FIG. 9A shows a side view of an missile 1 using the fin
rotating mechanism of FIG. 9. The activation stem 9 of FIG. 9 can
be seen to be protruding rearward from inside the primary tube
3.
[0019] FIG. 10 shows a cut out of the front of the primary tube 3
of FIG. 1, but with the protruding sections 8 and 19 protruding
from the fins 6 and 17 respectively.
[0020] FIGS. 11 and 12 show another manner in which the aerodynamic
imbalance between the fins can be created during forward
flight.
[0021] In FIG. 11 the protruding section 8, on the left side of the
spiral inducing assembly 2 is shorter than the protuding section 19
in FIG. 12 on the right side of the spiral inducing assembly 2. The
shorter protruding section 8 would generate a greater degree of
movement of fin 6 in FIG. 11 than the movement of fin 17 that the
protruding section 19 would cause in FIG. 12 for an equal movement
in the respective activation stems 9 and 20. An aerodynamic
imbalance between the fins could thus be created.
[0022] FIGS. 13 and 14 show the left and right sides of the spiral
inducing assembly 2 of another arrangement for creating an
aerodynamic imbalance between the fins 6 and 17. FIG. 14 shows the
activation stem 20 on the right side as being shorter than the
activation stem 9 on the left side in FIG. 13. Hence when the
activation tube 5 is moved forward, it first starts pushing the
activation stem 9 in FIG. 13, forcing fin 6 to rotate, and then
when the activation tube 5 later starts pushing the activation stem
20 of FIG. 14, the activation tube 5 will continue pushing the
longer activation stem 9 of FIG. 13, forcing the fin 6 in FIG. 13
into a higher degree of rotation, or pitch, than fin 17 of FIG. 14,
at all times until both fins are allowed to become horizontal again
by the activation tube 5 being allowed to retreat.
[0023] FIG. 15 shows a spiral inducing assembly 2 with a wheel 47
fitted to the connecting stem 9. The wheel 47 would reduce
frictional forces between the activation stem 9 and the activation
tube 5 as the activation stem travels around the activation tube 5
when the primary tube is rotating.
[0024] FIG. 16 shows the spiral inducing assembly of FIG. 4 with
the fins 6 and 17 of FIG. 4, and with the primary tube 3 in a state
of rotation. It can be seen comparing FIG. 4 with FIG. 16 how the
lateral forces on the missile would be constantly changing,
enabling the spiral inducing assembly 2, to force the missile 1 to
travel in a continuous spiralling motion.
[0025] Looking at the fins 6 and 17 shown in FIG. 16 it can be seen
that the rear section of each fin behind the respective connecting
rods 7 and 18 is greater than the section of each fin in front the
respective connecting rods 7 and 18. This is deliberate. This is
used to allow the fins to adopt a horizontal position when
hydraulic pressure is not applied to the hydraulic actuators 13, 14
(and 15 and 16 of FIG. 3). Aerodynamic forces are in effect used to
allow the fins to remain a resting horizontal position thereby
allowing non-spiralling flight. Friction between activation the
activation tube 5 and activation stems 9 and 20 caused by the
rotation of the activation stems 9 and 20 around the activation
tube (since the activation stems rotate with the primary tube) can
be used as a means of slowing the rotation of the primary tube when
smooth flight is desired. The braking mechanisms shown in FIGS. 17
and 18 could also be used as a means of slowing the primary tube
when smooth flight needs to be resumed.
[0026] FIG. 17 shows a side cutting of the primary tube 3 and the
part of the missile fuselage 35 encircled by the primary tube 3.
Shown here is a hydraulic actuator 48 attached to the encircled
part of the missile fuselage 35, in an extended form. Extended it
creates friction on the primary tube 3 and acts as a brake to help
slow the primary tube 3 when the spiral inducing assembly is
de-activated. Using a braking system lightly would allow the
primary tube 3 to rotate, but would intensify the lateral forces on
the missile 1. To allow use of a braking mechanism, the primary
tube 3 would be kept smooth and round in the area that fricion is
induced. Any creased sections 23, 24, 32, 34 would be restricted to
areas where the hydraulic actuator 48 would not make contact.
[0027] FIG. 17A shows the hydraulic actuator rod 48 in a compressed
state, as when the primary tube 3 is allowed to freely rotate.
[0028] FIG. 18 shows another braking mechanism where a lever is
used to slow the primary tube. The lever 49 is shown protruding
from a hole 50 in the missile fuselage, and is operated by an
actuator in the form of an electric motor 51.
[0029] FIG. 19 shows a spiral inducing assembly 2 where the primary
tube 3 extends over the activation tube 5, but the fin is located
on the outside of the primary tube.
* * * * *