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Патент USA US2404829

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My 30, ‘1946.
c. E. DARROW
2,404,829
HELICOPTER
Filed Sept. 3, 1943
4 Sheets-Sheet l
Inventor
July 30, 1946-
c. E. DAR§OW-
)
2,404,329
HELICOPTER
Filed Sept. 3, 1943
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Inventor
di’iawelii'e? Farrow M
July 39, 1946.
c. E. DARROW
2,404,829
HELICOPTER‘
Filed sepi. . 3,‘ 1945
I
4 Sheets-Sheet 4
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2,404,829
Patented July 30, 1946
UNITED STATE s PATENT‘ ferries.
2,404,829
HELICOPTER
Clarence E. Darrow, Miami, Fla.
7
Application September 3, 1943, Serial No. 501,121 ‘
2 Claims.
(01. 244-17) ‘
1
I comprises a cabin 3. The forward portion of
the‘ fuselage I further includes an anti'clinal'top
portion 4. Rising from the‘ apex or peak of the
top portion 4 of the fuselage I is a panel 5..
Mounted on the forward portion of the fuse
lage I is a frame structure 6; ‘The frame struc
ture 6 is transversely elongated and mounted for
rotation in opposite directions-on the ends there
The present invention relates to new and use- ‘
,ful improvements in helicopters, and has‘ for
one of its important objects to provide a flying
machine of this character comprising’ a unique
arrangement of rotors driven in opposite direc
tions through the medium of twin engines.
‘
Another very important object of the invention
is to provide a helicopter of the aforementioned
character which embodies novel propulsion and
control means.
Other objects of the invention are to provide a
10.
I0, gears I I, et cetera.
helicopter of the character’ described which will
be comparatively simple in‘ construction,-strong,
durable, reliable in operation, and‘ which may be
manufactured at low cost.
the upper portion of theframe structure 6 on
and advantages of the invention, will become
several views, and wherein:
:20
‘
Figure 1 is a top plan view of a helicopter con
structed in accordance with the present inven
tion.
‘
Figure 2 is a-view in‘front elevation thereof. ‘
Figure 3 is a View in side elevation of the ma
chine.
.
'
Figure 4 is a fragmentary view in vertical 1on
gitudinal section, taken substantially on the line
4—4 of Figure 2.
.
Figure 5 is a view inside elevation‘ of the
elevator assembly.
.
‘
opposite sides of the fuselage I.' In the embodi
ment shown, the safety'?aps I2 are releasably
secured in vertical or inoperative‘ position by
means including shafts I3 which‘ are journaled
in bearings I4 on the frame structure 6 and
‘
designate corresponding parts throughout the
‘
Safety flaps I2 are hingedly suspended from
All of the foregoing, and still further objects
apparent from a study of the following specifi;
cation, taken in connection with the accompany
ing drawing wherein like characters of reference
of is a pair of rotors ‘I. Engines 8 in thefuse
lage I drive the rotors ‘I in opposite“ directions by
suitable means, such as shafts 9,'universal joints
‘
Figure 6 is a top plan view of the rudder as
sembly with portions of the surfaces broken 1:
away in section, the elevator assembly shown in
which are operable from within the cabin 3. As
best seen in Figure 7 of [the drawings, the shafts
I3 have ?xed thereon pairs of spaced ?ngers I5
which receive the flaps lz'therebetween for re
leasably securing said‘ flaps against swinging
movement and in vertical position.’
'
j Mounted on top of theframe structure 6," be
neath the inner portions of the rotors ‘I, are pairs
of inverted U frames I6. ‘ Series of slats I1 are
journaled for vertical swinging ‘adjustment be
tween'the pairs of frames I6 for receiving the
air blast or wash from the rotors "1. Bars I8
“are pivotally connected to the upper ends of the
series of slats I‘! for actuating said slats: in uni
son. ‘,Cables I9 fromhandlevers‘lbin‘the cabin
3 are connected to the‘en‘ds of the bars IB'for
adjusting the slats Il as desired. Two such
Figure 5 being omitted from the rear end of the
levers 20 are provided, onefor each- set or series
fuselage.
of the slats I1.‘
Figure 7 is a fragmentary view in horizontal
section showing, in top plan,vthe means for re
leasably securing the safety ?aps in vertical or
inoperative position.
Figure 8 is a view principally in horizontal sec
tion through the fuselage.
Figure 9 is a cross-sectional view through the ~
forward portion of the fuselage.
Figure 10 is a view in horizontal section on an
enlarged scale through the elevator assembly.
Referring now to the drawings in detail, it will
be seen that the embodiment of the invention 1.
which has been illustrated comprises a fuselage
of suitable dimensions and material which is
designated generally by reference numeral I.
Landing wheels 2 are provided beneath the
’
‘
Built into the fuselage I is a pair of wind
tunnels 2!. The tunnels ‘2| comprise, at their
forward end portions, upwardly opening intakes
22 (see Fig. 9) on opposite sides of the anticlinal
top portion 4 of the fuselage I. Thus, the tun
nels 2| are adapted to receive the air blast or
wash from the inner portions of the rotors ‘I.
The upstanding panel 5 prevents air turmoil
between the rotors ‘I and the oppositely inclined
sides of the top portion 4 of the fuselage I direct
the air into the intakes 22. At an intermediate
point, the tunnels 2| merge into a single tunnel
23 (see Fig. 8) which extends to the rear end of
the fuselage I.
Mounted on the rear end of the fuselage I
is an elevator assembly 24. The assembly 24 in
fuselage I. The forward portion of the fuselage 55 cludes a pair of rearwardly projecting. Substam
2,404,829
3
tially U-shaped brackets 25 which are ?xed on
V the upper portion of the fuselage l.
Journaled
at an intermediate point for vertical swinging
movement between the brackets 25 is a gang of
elevators 26. A vertical bar 21 is pivotally
mounted on the forward end portions of the ele
vators 26 for actuating same in unison. Cables
28 connect the bar 21 to a swinging column 29
4
It is believed that the many advantages of
a helicopter constructed in accordance with the
present invention will be readily understood, and
although a preferrred embodiment of the ma
chine is as illustrated and described, it is to be
understood that changes in the details of con
struction and in the combination and arrange- '
ment of parts may be resorted to which will fall
_ in the cabin 3 for actuating the elevators 26.
within the .scopeof the invention as claimed.
Also mounted on the rear end of the fuselage 10
What is claimed is:
'
I, beneath the elevator assembly 24, is a rudder
1. A helicopter comprising a fuselage including
assembly 30. The assembly 30 includes a pair' o a forward part provided with an anticlinal roof
of substantially U-shaped brackets 3| which are
portion having a ridge extending longitudinally,
mounted transversely on the rear end of the '
of‘ said fuselage, a frame structurev mounted on
fuselage I. Pivotally mounted for horizonal v15 and extending laterally from opposite sides of
swinging movement on the brackets 3| and ex
the fuselage, rotors mounted on and disposed
tending rearwardly therefrom is a gang of
above said frame structure at opposite sides of
spaced, parallel rudders 32. A- bar 33 is pivotally
the fuselage, means for actuating the rotors, a
connected to the rudders '32 at intermediate
panel rising from and parallel with the ridge of
points in said rudders for actuating same in uni 20 the anticlinal roof portion of the fuselage, be
son. Cables '34 connect the ‘bar 33 to the’rotat
tween'the rotors, longitudinal air tunnels in the
able wheel 35 on the swinging column 29 in the
fuselage, said air tunnels including upturned in
cabin 3 for actuating the rudders 32.
a
takes opening at their upper ends at ‘opposite
It is thought that the operation of ‘the ‘ma
sides of the anticlinal roof portion of the fuselage
chine will be readily apparent ‘from a consider 25 and below the inner portions of the rotors for
ation of the foregoing. Brie?y, the desired lift
receiving the air blasts therefrom, said tunnels
is had from the oppositely rotating rotors 1, said
opening through ‘the rear end of the fuselage,
rotors being actuated by their respective en
and control surfaces mounted on said rear end
gines 8. Forward or backwardmovement‘is had
of the fuselage for receiving the air ‘from- the
through the medium of the slats l1. With the 30 tunnels.
‘
slats l1 adjusted ‘to the inclination shown ‘in
2. A helicopter comprising a'fuselage includ-v
Figure 4 of the drawings, thewash or downward
ing a forward part provided with an anticlinal
blast of air from the rotors '1 strikes said slats
roof portion having a‘ ridge extending longitudil
and drives the machine forwardly. The speed
nally' of said fuselage, a frame structure‘ mounted
is governed by the inclination of the slats I1. 35 on and extending laterally from opposite sides
With the slats IT in a vertical position, ‘the ‘ma
chine will ascend or descend vertically or hover.
Rearward tilting of the slats I‘! will'cause the
of the fuselage, rotors mounted on and disposed
above said frame structure at opposite sides of
the fuselage, means for actuating the rotors, a
panel rising from and ‘parallel with thejridge of
the anticlinal ‘roof portion of the fuselage be
machine to travel ‘backward. As vthe series of
slats are adjustable independently, said ‘slats
may, if desired, be utilized to turn ‘or'as'sist in
turning the machine. Air from vthe'rotors 1'! is
directed into the intakes ‘22 of the‘ tunnels ‘2|
by the top portion 4 of the fuselage 'l. The air
thus is caused to enter the tunnels under pres
45
sure. This blast of air emerges at the rear'end
of the fuselage ‘l and assists in propelling ‘the
machine forwardly. This air also strikes ‘the
surfaces 26 -and"32 in amanner to‘ materially
tween the rotors, longitudinal air ‘tunnels ‘in‘the
fuselage, said air tunnels including upturned
intakes opening at their upper ends at opposite
sides of the anticlinal roof portion of the fuselage
and below the inner portions of the rotors for
receiving the air blasts therefrom, said tunnels
opening through the rear end of the fuselage,
a series of transverse slats mounted for vertical
swinging adjustment on the frame sections 'be
increase'the effectiveness thereof. ‘Should one 50 neath the inner portion of each rotor and ‘di
of the engines fail, that-side of the machine will,
rectly above said intakes for receiving the air
of course, drop. When this oocurs,';the safety
blasts from said rotors, and means for "actuat
?aps l2 are released and said ?aps swing up
ing each series of said slats in unison.
wardly to a horizontal positionbeneath the upper
portion of the frame structure 6 where they are 55
arrested and function asplanes to assist thepilot
in bringing the craft to a safe landing.’ '
‘ CLARENCE E. DARR'OW._
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