U.S. patent number 3,776,490 [Application Number 05/275,970] was granted by the patent office on 1973-12-04 for missile with thrust vector and aerodynamic control.
This patent grant is currently assigned to Messerschmitt-Bolkow-Blohm GmbH. Invention is credited to Dieter Weis.
United States Patent |
3,776,490 |
Weis |
December 4, 1973 |
MISSILE WITH THRUST VECTOR AND AERODYNAMIC CONTROL
Abstract
A jet propelled missile is provided with jet spoilers at its
trailing end for thrust vector control and with other spoilers
forwardly of its center of gravity for aerodynamic control. Both
the jet spoilers and the other spoilers are operated from the same
control device. The other spoilers are located adjacent the
trailing ends of fins located on the forward end of the missile and
can be displaced between an inoperative position recessed in the
surface of the missile and an operative position projecting
outwardly from the outer surface of the missile. The side edges of
the other spoilers which extend outwardly from the missile can be
recessed for a portion of their length for increasing the
efficiency of aerodynamic control.
Inventors: |
Weis; Dieter (Neubiberg,
DT) |
Assignee: |
Messerschmitt-Bolkow-Blohm GmbH
(Munchen, DT)
|
Family
ID: |
5817280 |
Appl.
No.: |
05/275,970 |
Filed: |
July 28, 1972 |
Foreign Application Priority Data
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|
|
|
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Aug 20, 1971 [DT] |
|
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P 21 41 744.7 |
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Current U.S.
Class: |
244/3.21;
244/3.27 |
Current CPC
Class: |
F42B
10/64 (20130101); F42B 10/665 (20130101) |
Current International
Class: |
F42B
10/00 (20060101); F42B 10/64 (20060101); F42b
013/32 (); F42b 015/02 () |
Field of
Search: |
;102/49.4,49.5
;244/3.21,3.22,3.24,3.25,3.26,3.27,3.28,3.29,3.3 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Borchelt; Benjamn A.
Assistant Examiner: Hanley; James M.
Claims
What is claimed is:
1. A jet propelled missile including first means for thrust vector
control and second means for aerodynamic control for the
application of transverse forces, control means for regulating both
of said first and second means, and fins extending in the axial
direction of said missile and positioned on and extending outwardly
from said missile forwardly of its center of gravity; wherein the
improvement comprises that said first means includes first spoilers
located at the trailing end of said missile, and said second means
includes second spoilers positioned adjacent the trailing edges of
said fins and forwardly of the center of gravity of said missile,
said spoilers arranged to be displaced between an inoperative
position and an operative position and in the operative position
said second spoilers project outwardly from the outer surface of
said missile at the trailing edges of said fins.
2. A jet propelled missile, as set forth in claim 1, wherein said
second spoilers comprise a first end located adjacent the outer
surface of said missile in the operative position, a second end
located spaced outwardly from the outer surface of said missile in
the operative position, and a pair of spaced side edges extending
between said first end and said second end and said side edges
being recessed inwardly toward one another for a portion of the
length thereof between said first and second ends.
3. A jet propelled missile, as set forth in claim 2, wherein said
missile having recesses formed in its outer surface for receiving
said second spoilers in the inoperative position, and the first
ends of said second spoilers being pivotally secured to said
missile within said recesses.
4. A jet propelled missile, as set forth in claim 3, wherein a
displaceable latch member is located within each of said recesses
for holding said second spoilers in the inoperative position within
said recesses.
5. A jet propelled missile, as set forth in claim 4, wherein a
spring means is arranged within said missile in engagement with
said second spoiler for biasing said second spoiler into the
operative position when said latch member is released.
Description
SUMMARY OF THE INVENTION
The present invention concerns a jet propelled missile provided
with thrust vector controls and aerodynamic controls with both of
the controls regulated by the same device and, more particularly,
it is directed to the arrangement of the aerodynamic controls.
Missiles with both thrust vector and aerodynamic controls have the
advantage, unlike missiles provided only with thrust vector
control, that they can be controlled after the completion of the
powered phase of jet propulsion and at the start of the trajectory,
unlike missiles controlled only aerodynamically; see "A4" in F.
Mueller "Leitfaden der Fernlenkung," Deutsche
Radar-verlagsgesellschaft m.b.H., 1955, page 148. In this
publication, the missile was controlled over mechanically coupled
jet and rear surface controls. Such a solution requires, in
addition to a higher mechanical expenditure, considerable space
which is only available in larger missiles. Further, long storage
periods are frequently necessary, particularly for missiles used
for military purposes, where a mechanically complicated
construction suffers, for example, due to corrosion or oxidation of
the lubricants used, so that the proper functioning of the missile
after prolonged storage is jeopardized.
Therefore, it is the primary object of the present invention, to
provide a missile with a simple construction for effecting both
thrust vector and aerodynamic control and particularly for avoiding
mechanical coupling between the two types of control apparatus.
In accordance with the present invention, a missile is afforded
with thrust vector control in the form of jet spoilers located at
the rearward end of the missile and is provided with aerodynamic
control by spoilers mounted on the missile forwardly of its center
of gravity and at the trailing edge of fins projecting outwardly
from the forward end of the missile. Preferably, the spoilers used
for aerodynamic control can be moved from an inoperative position
recessed in the outer surface of the missile to an operative
position extending outwardly from the outer surface of the
missile.
The arrangement and design of the thrust vector controls and the
aerodynamic controls formed in accordance with the present
invention are characterized in particular by their simple
mechanical construction and the high degree of compatibility of the
two different controls. Since the jet spoilers and the aerodynamic
spoilers are operated by the same device, the magnets for the jet
spoilers can also be used for positioning the aerodynamic spoilers
so that the construction of the missile is simplified by reducing
the number of parts required.
During the flying stage of the missile, its aerodynamic drag and
its aerodynamic properties are not disturbed by the spoilers used
for aerodynamic control, since these spoilers are retained in
recesses in the missile surface and are displaced into the
operative position only after the main burning and thrust of the
jet propulsion has ceased.
Furthermore, because the aerodynamic spoilers are positioned
forwardly of the center of gravity of the missile, the spoiler
forces act on a long lever arm. Accordingly, the aerodynamic
spoilers can be small in size so that the aerodynamic resistance of
the missile is only slightly increased when the spoilers are moved
into the operative position.
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 disclosure. 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 are illustrated and
described preferred embodiments of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
In the drawings:
FIG. 1 is a side view of a missile embodying the present
invention;
FIG. 1a is a rear end view of the missile illustrated in FIG.
1;
FIG. 2 is an enlarged partial view, partly in section, of the
missile shown in FIG. 1 disclosing the arrangement of an
aerodynamic spoiler;
FIG. 3 is a view, taken transversely of the missile, showing one of
the aerodynamic spoilers illustrated in FIG. 2;
FIG. 3a is a view of the aerodynamic spoiler shown in FIG. 3, in a
displaced position;
FIG. 4 is a view, similar to FIG. 3, of another embodiment of the
aerodynamic spoiler; and
FIG. 4a is a view similar to FIG. 4 with the aerodynamic spoiler
located in a displaced position.
DETAILED DESCRIPTION OF THE INVENTION
In FIG. 1, a jet propelled missile 1 is shown having a propulsion
unit nozzle 2 and a pair of jet spoilers 3 at its trailing end for
guiding the missile about two axes. On the outer surface of the
missile just ahead of its trailing end, four aerodynamic fins 4 are
arranged spaced equiangularly apart.
At the forward end of the missile spaced rearwardly from its nose
and ahead of its center of gravity are four destabilizer fins 5
also disposed equiangularly apart. These fins 5 impart favorable
conditions to the missile at the commencement of its flight shortly
after the launching and, as a result, make it easier to guide.
Immediately rearwardly of each fin in the fuselage or surface of
the missile 1 is a trapezoidally shaped recess 6 containing a
spoiler 7 having the same shape as the recess, see FIGS. 2 to 4.
The spoiler is pivotally mounted in the recess about an axis 8 so
that it can be displaced between an inoperative position within the
recess, shown in dashed lines, and an operative position, shown in
full lines, extending outwardly from the outer surface of the
missile and at the rearward end of the fin 5. Within the recess, a
latch 9 is arranged for holding the spoiler 7 in the inoperative
position shown in dashed lines. The latch is operated by means of a
magnet system, not shown.
After the burnout of the jet propulsion system, when the jet
spoilers 3 used for guiding the missile 1 are no longer effective,
the spoilers 7 are released by displacing the latches 9 and springs
10, note FIG. 2, bias the spoilers outwardly into the operative
position at the rearward end of the fins 5. To prevent the spoilers
from being driven back into the recess 6, due to windgusts and the
like, in the operative position they are locked in place in a known
manner. In FIGS. 3 and 4 the spoiler 7 is shown positioned
symmetrically relative to the fin 5, however, it can be displaced
through a plane extending transversely of the axis of the missile
in the direction indicated by the double arrows 12.
The jet spoilers 3 and the spoilers 7 are compatible with a
stabilizing system, not shown, of the missile so that they can be
regulated and positioned by a single guide circuit 13 by means of
the same control signals. Accordingly, the trajectory of the
missile is controlled in the same manner, regardless of whether the
jet spoilers 3 or the spoilers 7 are controlled by the same
signal.
If the missile 1 is used in the supersonic range, slit-shaped
recesses 21 are formed in the side or lateral edges of the spoilers
which extend from the end adjacent to the outer surface of the
missile to the other end spaced outwardly from the outer surface of
the missile. The recesses extend for the greater part of the length
of the sides of the spoilers 7. As a result, when a spoiler 7 is
deflected or displaced into the position shown in FIG. 4a, an
opening or interval is provided by the recess 21 along the trailing
end of the fin 5 and the aerodynamic efficiency of the fins 5 and
of the spoilers 7 is increased.
While specific embodiments of the invention have been shown and
described in detail to illustrate the application of the inventive
principles, it will be understood that the invention may be
embodied otherwise without departing from such principles.
* * * * *