U.S. patent number 3,827,658 [Application Number 05/348,269] was granted by the patent office on 1974-08-06 for actuating means for a vane.
This patent grant is currently assigned to Lockheed Aircraft Corporation. Invention is credited to Robert Hallworth.
United States Patent |
3,827,658 |
Hallworth |
August 6, 1974 |
ACTUATING MEANS FOR A VANE
Abstract
A mechanism, two of which position a vane in proper working and
aerodynamic relationship with a flap throughout the latter's travel
in a Fowler flap assembly for an aircraft. The forward end of a
folding linkage is operatively connected, via a vane support
fitting, to a vane, and is operatively connected at its rear end to
a flap. Each vane support fitting is secured to one or more
carriages having banks of rollers mounted on tracks fixed to wing
structure. A cam is mounted on the forward end of the linkage to
co-act with a follower stationarily disposed upon wing structure.
In flap extension, the latching of cam upon follower prevents the
folded linkage, its vane support fitting and vane from further
opening and extending. Continued rotation of the unfolding linkage
and cam provides disengagement from the follower. The linkage
unfolds to a biased stiff or unyielding position as the flap pulls
the linkage. In flap retraction, engagement of cam with follower
breaks the biased unyielding position of the linkage. The linkage
folds as the flap retracts. The vane does not further retract until
the linkage is folded to a degree where the cam can pass by its
follower. The folding linkage includes a spring-piston-cable
arrangement which assures biasing thereof in its unyielding and
extended position, until the cam engages the follower in the
retracting mode for the flap.
Inventors: |
Hallworth; Robert (Rochdale,
EN) |
Assignee: |
Lockheed Aircraft Corporation
(Burbank, CA)
|
Family
ID: |
23367305 |
Appl.
No.: |
05/348,269 |
Filed: |
April 5, 1973 |
Current U.S.
Class: |
244/216;
74/471R |
Current CPC
Class: |
B64C
9/16 (20130101); B64C 9/20 (20130101); Y10T
74/20012 (20150115) |
Current International
Class: |
B64C
9/00 (20060101); B64C 9/16 (20060101); B64C
9/20 (20060101); B64d 009/10 (); B64d 009/20 () |
Field of
Search: |
;244/42D,42DA,42DB,42DC,82,75R ;74/471R |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Blix; Trygve M.
Assistant Examiner: Kelmachter; Barry L.
Attorney, Agent or Firm: Corber; Billy G. Zugelter; Frank
L.
Claims
Therefore, what I claim as patentably novel is:
1. In an aircraft wing lift increasing device including a vane and
flap positioned and functioning in accordance with a Fowler flap
action or principle and which includes means for mounting the vane
and flap independently of each other but in sliding relation to
their wing structure for the purposes of extending and retracting
them in an efficient aerodynamic relationship,
an improvement for actuating the vane in proper and efficient
relationship to the flap in such extension and retraction modes,
and comprising in combination,
foldable linkage means comprising a pair of rigid members hingedly
attached together at their adjacent ends, the respective free ends
of said members constituting a forward end and a rear end for said
linkage means, respectively,
means for biasing said members towards an unyielding, unfolded
position for said linkage means,
a cam member in fixed and non-rotatable relation to and mounted on
said forward end for rotation with its rigid member as said members
unfold and fold, said forward end and cam member being adapted for
rotation about the mounting means for the vane, and
means mounted on the wing structure and upon which said cam member
engages as said linkage means movingly folds and unfolds during the
extending and retracting modes for the vane and flap,
said cam member being disposed forwardly of said mounted means and
with folded position for its linkage means, said cam member
engaging said mounted means to prevent extension of the vane as the
flap extends until the flap extends to a point at which said
linkage means becomes unfolded to cause said cam member to become
disengaged from said mounted means to provide for extension of the
vane as the flap continues to extend,
said cam member with its unyielding, unfolded linkage means being
disposed rearwardly of said mounted means, the vane remaining
extended until said cam member engages said mounted means as the
flap is retracting, such engagement overcoming said biasing means
to break the unfolded linkage means, said linkage means continuing
to fold to a point where said cam member disengages from said
mounted means to thereby provide for retraction of the vane as the
flap continues to retract.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
The field of art to which the invention is most likely to pertain
is located in a class of devices generally relating to lift
increasing devices for airplane wings.
2. The Prior Art
Examples of prior art devices in the arts to which this invention
most likely pertains are U.S. Letters Pat. Nos. 2,169,416;
2,404,956; 2,624,532; 3,528,632; and German Pat. No. 1,296,527 (May
29, 1969).
3. Problems in the Prior Art
It is believed that this invention is a completely novel one, as I
am not aware of any major problems existing with similar mechanisms
that have been utilized in aircraft in the past. Long sliding
mechanisms are known to be commonly used for extending and
retracting flaps and vanes; however, a need for this invention has
developed in view of the heavier wide-bodied and jumbo jet aircraft
of today. This need demands a simple, lightweight and nevertheless
efficient mechanism for extending and retracting flaps and vanes of
such aircraft. This invention solves such need.
SUMMARY OF THE INVENTION
This invention relates to lift increasing devices mounted on
aircraft wings, and in which a trailing portion is separated from
the wing's main portion, and is particularly related to a mechanism
which actuates such a trailing portion.
Briefly summarized, the present invention is utilized in connection
with a Fowler flap action desired to be taken for extending and
retracting a vane and flap of a wing of an aircraft. A pair of vane
actuator mechanisms are employed in an expanding double-slotted
flap configuration for the wing. Each vane actuator mechanism
includes a folding linkage at each (rib) side of the vane. The
forward end of the linkage connects to a vane support fitting and
its rear end connects to a flap actuating yoke or fitting, however,
being driven by a flap actuating trunnion. Each linkage is held in
an unyielding, unfolded position when the vane is fully separated
from the flap, by means of a biasing means coupled with an
over-center pivotal hinge connecting the members of the linkage. As
the flap retracts, a cam at the forward end of each linkage engages
and is held by or latches upon a roller mounted on relatively fixed
structure thereby exerting a force on the linkage to cause it to
break from its biased unyielding position. As the flap continues to
retract to its nested position, the linkage continues to fold to
its closed position. Continued folding of the linkage frees the cam
from its follower and the vane approaches its nested position with
the flap. Upon extending the flap, the cam engages its follower,
such contact serving as a forward latch preventing the vane from
further extending until the folded linkage is unfolded to a degree
at which the cam passes by the follower. The extending flap in its
movement can then continue to draw the linkage and the vane until
the flap is in its fully extended position. Means are provided the
linkage to bias it in its unyielding position.
An object of this invention, therefor, is to extend and retract
such trailing portion by novel means.
Another object of this invention is to properly separate and space
a wing, vane and flap relative to each other during such extension
and retraction, for realization of advantages gained by the
aerodynamic slotting achieved.
A further object of this invention is to maintain such proper
separation and spacing of the wing, vane and flap during the
retracting and extending modes of operation for the flap
system.
A further object of this invention is to provide an actuator
mechanism which is unaffected by any wing deflection or
flexing.
A still further object of this invention is to provide an
aerodynamically clean, lightweight, simple and efficient
apparatus.
These and other objects of the invention will become more fully
apparent upon a complete reading of the following description,
appended claims thereto, and the drawing comprising five
sheets.
BRIEF DESCRIPTION OF THE DRAWING
FIGS. 1-4 schematically represent in four views various positions
of an airfoil on which the Fowler flap principle is employed and in
which such airfoil this invention is employed.
FIG. 5 is an elevational view of a mechanism, in a closed or folded
position, embodying the invention.
FIG. 6 is a view taken on line 6--6 of FIG. 5.
FIG. 7 is a perspective view of the mechanism in a fully extended
position.
FIGS. 8, 9 and 10 schematically represent the vane actuating
mechanism in fully closed, partially open, and fully open or
unfolded positions, respectively.
FIG. 11 is a view partly in section and partly in full, of a
biasing device employed in the invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Background. The schematic views of FIGS. 1-4 represent the desired
positions for a flap f and a vane v employed in an aircraft wing W
utilizing the well-known Fowler flap principle. In a retracted
position shown in the first view, the flap and vane are nested
together in the trailing edge or portion of the wing, and thereby
occupy minimum space. In FIG. 2, the Fowler principle becomes
apparent, as the flap is extended for take-off of the aircraft. The
flap panel has been extended for a maximum increase in wing area of
a given aircraft, and is deflected to a desired angle .alpha.. In
this position, the vane remains nested and is separated from the
flap, exposing a single slot s.
FIG. 3 represents further deployment of the flap towards its fully
extended position (for landing) which is shown in FIG. 4. The third
view shows that the vane plugs the cavity formed in the trailing
edge as the flap further extends, and also serves as an air control
panel for a smooth flow of air through the original slot s. As the
flap is continued to be fully deployed, or extended for landing,
the vane extends from its position near the trailing edge. A second
slot S is established and is shown in FIG. 4. The angle of the flap
in the meantime is further increased to another desired angle
.beta..
This invention is directed to achieving the maintenance of an
efficient aerodynamic relationship for the vane with the flap
throughout the latter's travel in the retracting and extending
modes of their operation.
Description. Referring now to the drawing in which reference
characters correspond to like numerals hereinafter, reference
character 20 (FIG. 7) refers to and identifies a preferred
embodiment of the invention. It should be understood that a pair of
mechanisms 20 is used at each side or rib end of each flap and its
associated vane on an aircraft; however, for clarity of description
of the invention, the following description and the accompanying
drawings are directed to just one mechanism 20. A like mechanism 20
complements same in actual outboard or inboard installation and
operation of a flap and vane mounted in a wing of the aircraft, and
its elements are merely situated in a reverse position to their
corresponding elements shown in the accompanying drawing.
The actuator 20 comprises a linkage 21 having its forward end
connected to a support member or fitting 22 on the rear end of
which a vane lug 23 is adapted for pivotal connection thereto. The
rearward end of the linkage 21 is operatively connected to an
actuating yoke or flap hinge fitting 24 to which a flap (not shown)
is secured. At the forward end of the linkage 21, a cam member 25
is mounted for cooperative action with a follower 26 mounted upon a
bracket or extension member 27 secured to wing structure, or in
this instance to a torque box 28. The vane support fitting or
member 22 is connected to one or more carriage assemblies 29 having
banks of rollers 30 which cooperate with fixed opposing tracks 31
(FIG. 6) included in the torque-box 28 fixed to wing structure. The
actuating yoke or flap hinge fitting 24 for the mechanism 20 is
adapted to be secured to the flap by suitable means such as bolts
or the like extending through apertures 32 provided in the yoke 24
and as shown in FIG. 7. Although not illustrated, each flap is
operatively mounted upon carriages or the like also having banks of
rollers which ride in corresponding tracks in the same manner as
the carriage assemblies 29 and rollers 30 which provide the guiding
movement for the vane fitting or support member 22. The actuation
of the flap itself may be accomplished by operation of a
conventional ball-screw mechanism 33 to which a flap actuator
fitting or trunnion 34 is operatively mounted. The actuating yoke
or flap hinge fitting 24 is rotatably mounted about the trunnion
34. It is sufficient to note that actuation of the flap ball-screw
mechanism 33 causes the trunnion 34 to extend or retract and
thereby extend or retract the flap and operate the mechanism
20.
The linkage 21 includes a pair of rigid members or casings 35, 36
(FIGS. 7, 11) having their complementary ends pivotally connected
together as at 37. A bifurcated element 38 is included in the
forward end of the rigid member 35 for securing it to a lug 39
projecting from a rotatable spindle 40 (FIG. 6) laterally supported
by and mounted in the vane support fitting 22. A bifurcated element
42 is mounted at the rear end of the rigid member 36, to be
pivotally attached, such as by a bolt 43 to an arm 44. The arm 44
is spline bolted by a bolt 45 to the flap actuator trunnion 34. It
should be understood that the arm 44 is required in the operation
of the linkage as illustrated in this embodiment. However, it is
not a necessary limitation on the spirit or to the merits of the
invention.
As shown in FIGS. 7 and 11, the pivotal connection 37 for the rigid
members 35, 36 is offset from their longitudinal axes. This offset
coupled with a biasing arrangement 50 of elements (FIG. 11) for the
casings forming the rigid members 35, 36 biases the linkage 21 in a
direction tending to maintain it in an open or unfolded, and
unyielding position.
Such arrangement 50 comprises an elongated coil spring 51 mounted
in the length of a hollow casing for the rigid member 36, a piston
52 seated on one end of the spring 51, and a cable 53 one end of
which being attached to the piston 52 and its other end to a point
54 on the rigid member 35. An opening 55 is provided in the casing
base 56 in order that the cable 53 extends for attachment to the
rigid member 35. The compressive force of the spring 51 tends to
maintain the piston 52 at the top or right end (FIG. 11) of the
rigid member 36, thereby exerting a force through the cable 53 to
maintain the rigid member 35 in a hard position relative to the
base 56 of the other member 36.
As shown in FIGS. 5 and 7, the cam 25 is mounted at the one end of
the rigid member 35, and by virtue of its securement to the lug 39
to which the bifurcation 38 is fixed, it rotates or turns in unison
with such rigid member 35 in the folding and unfolding of the
linkage 21. The cam 25 comprises a circular riding face 60 and a
tang 61 formed thereto. The tang 61 includes a cut-away face 63
contiguous to the circular face 60. In the folded position for the
linkage means 21, it will be observed (FIG. 5) that as the circular
face 60 cooperates with the stationarily disposed follower 26, by
direct contact, the cam 25 is prevented from further moving to its
right. However, as the linkage unfolds, the cam rotates with the
rotation of the rigid member 35. The follower 26 continues to latch
upon the face 60 until the rigid member 35 has rotated through an
arc at the end of which the face 60 no longer contacts the
follower. The cam's cut-away face 63 in turn does not fall along a
path through the follower 26 and is in a position to pass by the
follower 26, thereby freeing the unfolding linkage 21 to translate
rearwardly.
Each vane support fitting or support member 22 is connected to one
or more carriages 29. Preferably, a carriage assembly 29 includes a
mounting element 65 (FIG. 7) mounted to a universal ball joint (not
shown) situated on an extension shaft 66 integrally projecting from
a bolt 67 which is secured to and through the lateral thickness of
the vane support fitting 22. In the preferred embodiment, the
carriage assembly 29 for each vane support fitting 22 comprises two
in number and are spacedly mounted along an exterior side of and
along the forward half of each support fitting. It will thus be
seen from FIGS. 6 and 7 that each vane support fitting 22 is guided
in its movement by the translation of its associated carriage
assembly 29 within the torque box 28 and upon the vertically
oriented tracks 31 by means of rollers 30.
A stop block 70 (FIGS. 8, 9, 10) is securely provided in the
forward extremity of each torque box 28 to prevent the banks of
rollers 30 on the carriage assemblies 29 from running off their
tracks while also maintaining each actuator mechanism 20 in
operable relationship relative to its associated vane and flap.
OPERATION
Extension. Referring now to FIGS. 8, 9, 10 and FIGS. 1-4, the
extension of each flap f and vane v from their nested position
(FIG. 1) is initiated by the flap's own ball-screw mechanism 33 in
a manner well known in the art. Each actuating yoke 24 thus pulls a
folded linkage 21 along with the extending flap. As the flap
continues to extend, the circular face 60 of each cam 25 continues
to engage or latch upon its stationarily disposed follower 26 to
prevent translation of its associated vane support fitting 22,
etc., and the vane v. Each linkage 21 continues to unfold with the
extending flap, as shown in FIG. 9 and FIG. 2. Each cam 25 is
continuing to rotate until the cut-away face 63 on its tang 61 is
able to pass by or unlatch from its follower 26. The flap assumes
the position shown in FIG. 3 and FIG. 10 wherein the members 35, 36
of each linkage are hard against each other. As the flap f
continues to be extended, each vane support fitting 22, etc.,
translates rearwardly, by the pulling of the flap. Both the flap f
and the vane v now assume a fully extended position shown in FIG.
4.
Retraction. The retraction of the flap f is initiated by its
ball-screw mechanism. Both the flap and the vane translate
forwardly, as each biased linkage 21 continues to remain in its
unfolded or unyielding position. As soon as each cam's tang 61
engages its follower 26, a force is exerted upon its corresponding
linkage 21 to break it about its over-centered pivotal hinge 37.
Each linkage 21 pivots about the pin 37, thus initiating its
folding. The vane v no longer continues to retract with the flap;
however, the flap f continues to retract while further folding each
linkage 21. Each cam 25 continues to rotate around its follower 26
and as soon as each cam in its rotation is free of its follower 26,
the carriage assemblies 29, each vane support fitting 22, etc., and
thus the corresponding vane v, again translates further inwardly
until each fitting 22 engages its stop block 70 provided at the
front end of its torque box 28. The flap f continues to retract,
and each linkage further folds until it reaches its fully closed
position. Both the flap and vane return to their nested position as
shown in FIG. 1.
It should be understood that various changes and modifications in
design and position of essential elements from the illustrated
embodiment may be made, without departing from the spirit and scope
of the invention. For example, in regard to an inboard
flap-and-vane embodiment, the cam may be mounted on the center line
of the rotatable spindle but between the vane fitting and the
torque box. In such instance then, the roller is mounted on a flat
bracket secured to and spaced from the side of the torque box.
In summary, the invention relates to a foldable linkage mechanism
for delaying the action of a flap actuator to provide a desired
movement of a vane segment of a Fowler flap assembly. The actuator
comprises an elbowed linkage having two arms which constantly tend
to assume an unbent configuration against a spring-piston-cable
arrangement but which, upon application of a force to the forward
end of one of the arms, may assume a folded position at its
intermediate pivot point. Thus, the cable element of the
arrangement bends around the pivot joint and stresses the spring
element within the actuator. The actuator is utilized in
combination with a cam and follower arrangement, the cam being
mounted at such forward end of the linkage and the follower being
attached to fixed wing structure. Upon extension of the flap
system, the vane is initially restrained against motion, or at
least against an undesired motion, by the engagement of the cam
with its follower, until the principal flap segment is extended to
a desired point. The cam element is then at a location with respect
to its follower such that the linkage is enabled to unfold or
function to position the vane in predetermined location with
respect to the wing and its flap. Upon retraction of the flap
assembly, the cam engages the follower to cause retraction of the
vane actuator mechanism to its folded condition during the final
retraction phase.
Pursuant to the requirements of the patent statutes, the principle
of this invention has been explained and exemplified in a manner so
that it can be readily practiced by those skilled in the art to
which it pertains, or with which it is most nearly connected, such
exemplification including what is presently considered to represent
the best embodiment of the invention. However, it should be clearly
understood that the above description and illustrations are not
intended to unduly limit the scope of the appended claims, but that
therefrom the invention may be practiced otherwise than as
specifically described and exemplified herein, by those skilled in
the art, and having the benefit of this disclosure.
* * * * *