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Патент USA US2125063

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July 26, ‘193$.
2,125,063
R. H. BURGESS
PROPULSION MECHANISM FOR AIRCRAFT
Filed May 27, 1936
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‘2,125,063
Patented July 26, 1938
UNITED STATES PATENT OFFICE
,
2,125,063
PROPULSION MECHANISM FORv AIRCRAFT
Richard H. Burgess, San Antonio, Tex.
Application May 27, 1936, Serial No. 82,119'
5 Claims.
(Cl. 244—-'72)
This invention relates to an improved pro
pulsion’ mechanism for aircraft, being especially
designed for use in conjunction with aeroplanes
and gliders.
Among other objects, the invention seeks to
5
provide a Wing tip which may be oscillated, ei
ther manually or by power, relative to the body
of the Wing for propelling the aircraft forwardly
with the greatest ei?ciency in proportion to the
10
effort expended.
A further object of the invention is to provide
a wing tip composed of a plurality of parallel
blades and wherein said blades will be so con
structed and mounted that as the wing tip is
15 swung upwardly, the blades will yieldably de?ect
downwardly to act on the air for driving the air
craft forwardly while, as the wing tip is swung
downwardly, the blades will yieldably de?ect
upwardly to act on the air for a like purpose.
And the invention seeks, as a still further ob
20
ject, to provide a wing tip of unique and novel
construction.
Other and incidental objects of the inven
tion not speci?cally mentioned in the foregoing
25 will appear during the course of the following
description and in the drawing which forms a
part of my application,
Figure l is a plan view of my improved mech
anism.
Figure 2 is an enlarged detail sectional View
showing the construction of the blades of the
wing tip.
Figure 3 is a transverse section through one of
the blades and showing the manner in which the
blades are adapted to be de?ected both upwardly
and downwardly.
Figure 4 is a detail section showing the levers
for rocking the wing tip.
Figure 5 is a fragmentary section showing a
slightly modi?ed form of blade.
Figure 6 is an enlarged detail section of the
modi?ed structure.
Referring now more particularly to the draw
ing, I have shown the body of an aeroplane or
glider wing at Ill. The wing body may be of
any approved construction and is straight at its
outer end.
Mounted to swing up and down relative to
the wing body H1 at the outer end thereof is a
50 wing tip. This wing tip comprises a hinge rod or
header II from which projects a plurality of
spaced parallel lateral studs l2 and ?xed to said
studs are blades I3 slightly spaced apart and all
normally lying in the same plane.
Each of the blades I3 includes a flexible re
silient stem l4 looped .at its free end portion to
provide a substantially U-shaped frame [5 and
slipped over said frame from the outer end there
of is a bag of canvas or the like forming a
web H5. The bag is closed at its outer end and
will be held taut by the resiliency of the frame
I5, the overlapping thicknesses of the bag being
cemented together by dope which will also serve
to secure the web on the frame. While any ap
proved material may be employed still, the stems
0
l5 are each preferably formed of a length of
bamboo cored out at its larger end and slipped
over one of the studs l2 to- which the length of
bamboo is suitably ?xed. This construction is
light in weight and the bamboo possesses the 15
necessary strength, toughness and resiliency.
Extending between the stems near their inner
ends is an appropriate brace rod ll.
If preferred, a straight length of bamboo may
be employed to form a stem [8 and ?xed to said
stem at spaced points are loops IQ of resilient
wire. These loops are provided With studs 20
which extend through the stem and securing the
loops to the stem are cotter pins 2|. The sev
eral loops provide a frame which carries a web 25
22 like the webs I 6.
Projecting from the outer end of the wing body
l0 are spars 23 to which the rod H is hingedly
connected in any appropriate manner and ex
tending laterally in opposite directions from said 30
rod are levers 24.
Attached to said levers are
cables 25 which extend into the fusilage of the
aircraft and may be operated manually or by
power for swinging the wing tip up and down.
As the wing tip swings upwardly, downward
canting of the webs l6 of the blades l3 will be‘
resisted by the stems M of said blades but the
Webs will, however, be de?ected by the air and
move into a downward angular position to act on
the air for propelling the aircraft forwardly.
Similarly, as the wing tip swings downwardly, the
webs l6 of the blades will be de?ected into an up
ward angular position for propelling the aircraft
forwardly so that both the upward and down
ward movement of the wing tip will be utilized
for driving the aircraft ahead.
Having thus described the invention what I
claim is:
1. Propulsion mechanism for aircraft including
in combination with a wing body, a wing tip '“
hinged to the wing body and composed of a plu
rality of blades including ?exible stems provided
with lateral webs, the stems being resiliently
twistable to torsionally resist but yield to both
upward and downward de?ection of the Webs by
2
2,125,063
the air as the wing tip is swung, and means for
swinging said tip.
2. Propulsion mechanism for aircraft including
a header, ?exible resilient stems carried by the
header and looped to form U-shaped frames
each having a single leg thereof ?xed to the
header, envelops ?tting over said frames and pro
viding blades having webs extending laterally
from the stems, the several blades forming a wing
10 tip, means for hingedly connecting said tip with
a wing, and means for swinging said tip.
3. Propulsion mechanism for aircraft including
a rod having spaced studs extending therefrom
to form a header, ?exible resilient stems ?xed to
15 said studs and looped to form frames each hav
ing a single leg thereof engaged with one of said
studs respectively, fabric bags engaged over said
20
frames and forming blades having webs extend
ing laterally from said stems, the several blades
forming a wing tip, means for hingedly con
necting said tip with a wing, and means for
swinging said tip.
4. Propulsion mechanism for aircraft includ
ing a wing body, a plurality of double-acting
blades hinged at the outer end of the wing body
to form a swingingly supported wing tip, the
blades being spaced to freely and individually
twist downwardly as the wing tip is swung up
wgardly and upwardly as the wing tip is swung
downwardly and being torsionally resilient for
exerting a forward propelling force on both the
upward and downward movement of the wing 10
tip, and means for swinging said tip.
5. Propulsion mechanism for aircraft including
a plurality of blades, means supporting the blades
to swing as a unit, said blades being spaced to
freely and individually twist downwardly as the 15
blades are swung upwardly and upwardly as the
blades are swung downwardly and being torsion
ally resilient for exerting a forward propelling
force on both the upward and downward swing
ing movement of the blades, and means for 20
swinging the blades.
RICHARD H. BURGESS.
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