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Патент USA US2404544

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July 23, ‘1946.
_ 2,404,544
Filed Feb. 9‘, 1945
[1 z’ 141' {Zr/40¢
Patented July 23,1946
William Stelzer, Detroit, Mich.
Application February 9, 1943, SerialNo. 475,23":
2 Claims.
(o1. 244--34) ’
The invention relates to aircraft and more par
ticularly to a flying machine having a plurality
not limited in its application to the details of '
construction and arrangement of parts, illus
trated in the accompanying drawing, since the
neath a kite-balloon.
invention is capable of other embodiments and
The object of the invention is to provide a safe
of being practised or carried out in various ways.
and novel airplane with a greatly reduced wing
Also it is to be understood that the phraseology
loading and an increased wing area, to be capa
orrterminology employed herein is for the pur
ble of ?ying at a, very low speed.
pose of description and not limitation.
It it known that the size and carrying capac
The novel ?ying machine comprises a fuse
ity of conventional airplanes is limited because lo lage» I propelled by an air screw 2 driven by a
power plant 3. A ?n 4 extending upwardly has
of the di?iculty to maintain rigidity of the struc
ture without a prohibitive increase in weight and
attached to it a tensile member such as a cable
of superposed carrying surfaces suspended be
the necessity of maintaining a high speed to sus
tain itself in ?ight. There is a de?nite need
for an aircraft capable of ?ying at very low speed
or of carrying large loads'that cannot be car
ried by conventional means.
or wire 5 to which are clamped tubular members
To accomplish this, I provide a plurality of
superposed carrying surfaces with a tensile mem
6 having lateral arms 1 whose extremities have
trunnions 8 (shown in Fig. 2)v pivotally engag
ing carrying surfaces 9 at a point forward of their
center of pressure. Each carrying surface 9 is
equipped with a. ?n [0 at the end of a longeron
ber to transmit the lift, whereby the carrying 20
The upper end of cable 5 is secured to a kite
balloon 12 whose purpose is to hold up the wings
when the lift is insufficient, as for instance be
?ight, a kite-balloon is provided at the top to
fore the plane is in ?ight. This kite-balloon gives
hold all Wings or carrying surfaces in suspen
the plane an inherent stability as it holds the
25 upper wings in a position where they produce
An important aim of the invention is to co
ordinate all carrying surfaces to operate in unison
The control means of the novel airplane com
prise a. control cable l3 connecting all longerons
while their structural ?exibility with relation to
each other is maintained.
l I and balloon l2 whereby the angle of attack
Other objects and advantages of this inven
of the wings may be controlled by raising or
tion will be apparent from the following de
lowering said control cable, which operation in
tailed description considered in connection with
this embodiment may be accomplished by means
the accompanying drawing submitted for the pur
of a joy stickv I4 pivoted to the fuselage at I5,
l6 designating a sheave. Directional control is
pose of-illustration and not intended to de?ne
the scope of the invention, reference being had :.v. VI provided with a rudder I‘! hinged to ?n l8 and
for that purpose to the subjoined claims. In
operated by means of a rudder bar [9 and wires
the drawing, wherein similar reference charac
3! in a conventional manner. 32 is an elevator
ters refer to similar parts throughout the sev
?n, which may be provided with operable eleva
eral views:
tors. However, the latter are not‘ essential to
Fig. 1 is a. perspective view of the novel air
the functioning of the airplane and therefore
are not shown speci?cally.
Fig. 2, a perspective detail view showing the
It is apparent that instead of the airfoils 9
method of securing a carrying surface to the ten
other types of carrying surfaces may be used.
In the modi?ed embodiment in Fig. 3 I use pairs
sile member;
Fig. 3, a fragmentary cross-sectional elevation 45 of rotatable wings 20 secured to a hub "2|. revolv
showing a modi?ed carrying surface rotatable on
able about tubular shafts 22 clamped to cable 5
surfaces are in no rigid relation with each other.
In order to make'such a construction stable in
a swivel;
and having thrust collars 23.‘ The airfoils 20
Fig. 4, a diagrammatic illustration of the wing
setting of the modi?ed construction shown in Fig.
of a gyroplane, having a negative setting as shown
3; and
Fig. 5, a diagram showing how the wings in Fig.
in Fig. 4, where 24 indicates the axis about which
the wings rotate, 25 the “propeller; plane,” 26
are arranged in a similar manner as the blades
3 may be set resiliently to assume the proper angle
Before explaining the present invention in de
tail it is to be understood that the invention is 55
the direction of rotation, and arrow 21 the direc
tion of traction. In this embodiment control
cable I3 is eliminated.
The ?xed wing setting described has the dis;
‘advantage that during forward travel the ad
vancing wing produces more lift than the re
treating wing, causing a certain ?apping motion
which is permitted due to the ?exibility of cable
5. Where this ?apping motion (which is a known
the flight of the body deviates from the original
course, causing a change in the direction of pull
in cable 5 and the alignment of the carrying sur
faces by virtue of ?ns H1. The alignment is ac
celerated due to the action of control cable I3
characteristic of present day gyroplanes) is objec
whose tendency is to urge longerons ll into align
tionable I propose to use a modi?ed wing con
ment with body I.
struction as shown in Fig. 5. For simplicity only
Due to the extreme height of the plane and
one wing is shown; The latter has a rigid lead
the low position of the center of gravity, a pendu- V
ing edge 28: whose root is secured to hub 21 inra 10 lum actionmay result. Its 'frequency'depends
manner similar. to blade 20‘.
Securedyto said
on the height of the plane and is accordingly
leading edge are skin covered'resilient ribs 29 ‘Y . very low.
urged in a position as shown where‘the angle
of ,wing setting‘is approximately zero. The lift
produced .by the wing urges the latter to decrease
the angle of attack which position is illustrated '
by numeral 30. Thus during a rotation the wing
changes its setting to produce a more uniform '
The pendulum action in a lateral di
rection is prevented by ?ns 4 and IB whose size
also determines the minimum turning radius of
the aircraft. The pendulum action fore and aft
may be broken by the operator by manipulation
of the throttle, particularly since the oscillation
is extremely slow.
The operation of the ?ying machine employing ,
In operation, assuming that the embodiment 20 the modi?ed carrying surfaces as shown in-Fig. 3
shown in Fig. 1‘ is on the ground and ready to
is similar to that described in connection with
Fig; 1,>ex;cept that the direction of the gyroplanes
' take ‘off, the wings 9 are raised by virtue of the
is' indifferent, control cable I3 being dispensed
static lift of balloon 12, so that as soon as the
with. While in the construction shown in Fig. 1
‘planejs propelled forwardly by means of pro
peller 2, lift is produced by them; 'When the for 25 theascent or descent of the ?ying machine is
controlled ‘by operation'of', the control stick I4,
ward speed is accelerated, the lift may be in
in’ a construction incorporating the modi?cation ,
creased by pulling back joy stick M, to increase
shown in Fig. 3, the ascent or descent can be
the angle of incidence of the wings, causing the
plane to. rise. Since the point of suspension of " controlled by the thrust of propeller 2 whereby
the body I is at the upper end of ?n 4, the center so anincrease of power would cause the ?ying ma
chine to climb.
of gravity of the body is relatively low, and the
While in the illustrated embodiment I have
‘deviation offthe body from a horizontal longi
shown only a small number of carrying surfaces
tudinalline due to increase or decrease in the
the number of planes or lifting screws may be
pulling force exerted on cable I3 is accordingly
small. It is- apparent that the airfoils 9 may be 35
. Having thus described my invention, I claim:
‘very light in weight because the lifting forces are
1. A flying machine comprising streamlined.
transmitted directly to the tensile member 5 and
lighter-than-air lifting means, ?exible tension
‘all the structural members used in a conventional
lines suspended from said 'lighter-than-air lift
plane to produce a rigid unit are omitted. It ap
lpearsthereforethat a kite balloon of compara 40. ing means, said-airfoils being'pivoted-to swing
about a lateral axis forward, of the. center of pres
tively small sizeis required to lift all of the wings.’
' However, the airplane is operative and safe if
‘ sure,‘ a fuselage suspended at the'lower end .of
said tension lines, said fuselage having a power
the capacity of balloon l2 is__merely su?icient to
‘lift the topmostrairfoil. .Lift of the latter is
plant, propelling ,means ‘driven by‘ said power
'lthereb-y,‘ assured during flight so that it lifts the 45 plant, and directional control means operable
by the pilot,'and a plurality of superposed air
other airfoils and the plane is prevented fromi
7 foils‘ pivotally secured to said tension lines inter
11 'While theairplane ‘is in forward ?ight the lift‘
mediate said fuselage ‘and saidv lighter-than-air
‘cay'blei‘5 slopes upwardly and 'backwardly, pointing
lifting means.
in theidirection of the resultantof the lift and
the drag; Supposing now that theroperator de-'
sires to make a turn and-therefore operates rud
der bar 19 to, cause‘ turning, of body‘l,‘ the direc-
Qtion of the propeller thrust is changed sothat
2. The Tconstructidn as claimed in claim Land
means operable by the pilot to control one of said
tension lines to change. the pitch of said airfoils.
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