U.S. patent number 3,790,103 [Application Number 05/282,525] was granted by the patent office on 1974-02-05 for rotating fin.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to John R. Peoples.
United States Patent |
3,790,103 |
Peoples |
February 5, 1974 |
ROTATING FIN
Abstract
A rotatable sleeve with attached clipped double delta shaped
fins for mounting on a missile body so that the fins may achieve a
position of symmetry with respect to incident air flow thereon
without spinning-up.
Inventors: |
Peoples; John R. (China Lake,
CA) |
Assignee: |
The United States of America as
represented by the Secretary of the Navy (Washington,
DC)
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Family
ID: |
23081901 |
Appl.
No.: |
05/282,525 |
Filed: |
August 21, 1972 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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118266 |
Feb 24, 1971 |
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Current U.S.
Class: |
244/3.23 |
Current CPC
Class: |
F42B
10/06 (20130101) |
Current International
Class: |
F42B
10/00 (20060101); F42B 10/06 (20060101); F42b
015/14 () |
Field of
Search: |
;102/34.1,37.1,3
;244/3.24-3.3,3.23 |
References Cited
[Referenced By]
U.S. Patent Documents
Other References
Fuller, Dennis E. and G. J. Foster, N.A.S.A. Technical Note D-1929,
"Aeroamic Characteristics of Rocket Vehicle Configurations,"
Langley Research Center, Hampton, Va., May 6, 1963. .
Yuska, Joseph A, N.A.S.A. Technical Note D-3182, "Aerodynamic
Characteristics of Rocket Vehicle with Thick Wedge Fins and
Sweptback Edges," Lewis Research Center, Cleve. Ohio, Oct. 4,
1965.
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Primary Examiner: Pendegrass; Verlin R.
Attorney, Agent or Firm: Sciascia; R. S. Miller; Roy Beers;
R. F.
Parent Case Text
CROSS-REFERENCE TO RELATED APPLICATIONS:
This application is a continuation-in-part of Ser. No. 118,266
filed Feb. 24, 1971, and now abandoned.
Claims
1. A device for obviating induced roll coupling in a guided missile
comprising:
a missile having a generally elongated cylindrical body member for
providing stablized flight;
a plurality of fins mounted to freely revolve transversally in
either direction to the longitudinal axis of said missile for
allowing said fins to move during said missile flight;
said fins being streamline shaped members having a base aligned
parallel with the longitudinal axis of said missile body, leading
and trailing edges inclined with respect to said base, a tip of
shorter axial dimension than said base dimension and spaced a
substantial distance from said base forming a symmetrical member
for aligning itself in the air stream; and
bearing means positioned on the circumference of said missile body
and having a portion fixably secured to said base for holding said
fins in spaced relationship to one another around the circumference
of said missile body;
whereby the fins rotate with respect to said missile body to seek a
null position during flight of the missile and rotate to maintain
this null
2. The device of claim 1 wherein the profile of said fin is tapered
from said base to said tip and having a front portion tapered
towards said leading edge from a plane perpendicular to said base
and extending through the corner formed by the meeting of said
leading edge and said tip edge.
Description
BACKGROUND OF THE INVENTION
A recurrent problem in guided missiles is that of induced roll
coupling. Induced roll coupling is caused by the torque induced by
the change in air flow over the fins of a guided missile
accompanying a turning maneuver.
When a missile is at an angle of attack the forces due to incident
air flow on one side of the missile are greater than on the other
side. Unless the fixed fins of the missile are at a null position,
roll coupling will be induced. The present invention obviates the
problem of roll coupling by providing the missile fins with means
to achieve a position of symmetry, i.e., a null position, with
respect to the incident air flow.
SUMMARY OF THE INVENTION
The present invention obviates problems incident to induced roll
coupling. The invention comprises mounting the aft fins on a
missile such as Sidewinder on a sleeve which is free to rotate
about the missile axis. The sleeve is supported on bearings fore
and aft and is free to rotate under the force induced on the fins
mounted on the sleeve. The fins are of a clipped double delta
configuration so that the fins and sleeve do not spin-up under the
force induced by the change in air flow accompanying a tunring
maneuver. Instead, the fins are allowed to, and do achieve, a
position of symmetry i.e., a null position with respect to the
incident air flow.
DESCRIPTION OF THE DRAWING
FIG. 1 is an elevational view of the invention in cross section as
it appears on a guided missile;
FIG. 2 is an elevational view of a back of the missile in one of
its null positions;
FIG. 3 is an elevational view of a back of the missile in the other
of its null positions;
FIG. 4 is a graph of torque caused by induced roll coupling versus
the angle between a null position of the fins and a non null
position of the fins for a four fin sleeve;
FIG. 5 is a plan view of the invention;
FIG. 6 is a side elevation view of the invention; and
FIG. 7 is an elevation view of the back end of the fin.
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 shows a missile 10 with stabilizing fins 12 connected to the
missile by a rotatable sleeve 14. The sleeve is supported on
bearings 16 fore and aft and is free to rotate under the force
induced on the fins mounted on the sleeve. FIG. 1 shows the missile
turning in the direction of arrow 18 causing the incident air flow
20 to be greater on the lower side of the fins than on the upper
side. It is seen in FIGS. 2 and 3 that when the missile is in a
turn as shown in FIG. 1, there is greater air flow over the bottom
portions of the fins. If the fins are at an angle .phi. to the null
position of FIGS. 2 and 3, one of the bottom fins will display a
greater area with respect to the incident air flow than will the
other fin. This will cause a missile with nonrotatable fins to spin
in the direction of arrows 22.
The guidance system of the missile is unable to react quickly
enough to cause the swivel nozzle to move quickly enough to
compensate for this spin. The missile will thus veer off in a wrong
direction.
The present invention obviates this problem incident to induced
roll coupling. The sleeve is free to rotate under the force induced
on the fin mounted on the sleeve. The fins are so shaped that the
fins and sleeve do not spin under the force induced by the change
in air flow accompanying a turning maneuver. Instead, the fins
achieve a position of symmetry with respect to the incident air
flow, that is, a null position. It is to be noted that a four fin
rotatable sleeve will never rotate more than 221/2.degree. to
achieve a null position; an eight fin sleeve not more than 11
1/4.degree., etc.
Fin 12 of FIG. 1 is shown in greater detail in FIGS. 5, 6 and 7. It
is seen that the fin is of a clipped double delta configuration.
The perimeter of the fin from point 28 to point 30 is rounded off.
The forward portion 24 of the fin becomes increasingly thicker from
front to back as does the main portion of the fin from top to
bottom with the rear edge 26 of the fin being flat.
* * * * *