US1763507A - Aircraft - Google Patents

Description

June 10, 1930. Y c. L. FORTIER AIRCRAFT Filed Aug. 6, 1928 2 Sheets-Sheet 1 Attorneyd June 10, 1930.

C. L. FORTIER AIRCRAFT Filed Aug. 6, 1928 2 Sheets-Sheet 2 mi N 3 \m H 1 b sA 3H 3$ I 1 h g Q i Hm 9% I 6 I Inventor Patented June 10, 1930 CHARLES L. FOBTIER, OF MONTREAL, QUEBEC, CANADA AIRCRAFT Application filed August 6, 1928. Serial No. 297,753..

vision of a flying machine of the multiplane type having. a relatively large carrying capacity.

Still another object of the invention is the provision of a flying machine of the above type having great stability and positive balance.

A still further object of the invention is the provision of a flying machine of the above character embodying airfoil construction designed to compress air currents longitudinally of the machine to provide increased buoyancy. v

Other objects and advantages of the invention will become apparent as the description progresses.

In the accompanying drawings forming a part of this specification and in which like reference characters are employed to designate corresponding parts throughout the same: v Figure 1 is a side elevational view of the assembled machine,

Figure 2 is a front elevational view of the same,

Figure 3 is a longitudinal section takenon the line 3-3 of Figure 2, and

Figure 4 is a transverse section taken on the line 4-4 of Figure 1.

' Referring to the drawings, wherein for the purpose of illustration is shown a preferred embodiment of the invention, the

numeral 10 generally designates a fuselage,

preferably constructed in the form of a boatlike. hull extending longitudinally. The hull is of comparatively great width to provide an extremely stable and buoyant supgreat.

porting structure when the craft is on the water.

The forward end of the hull is formed with 'a. forwardly projecting nose portion 11,

Figures 2 and 4, the bottom portion has an exterior contour constructed to form a central convex portion merging into laterally opposed concave trough grooves. The lower edges of the lateral extremities of the hull terminatesubstantially in a horizontal plane with the central convex bottom portion to secure a suitably balanced fuselage. On the inside, the hull is provided with an interior double bottom 12 arranged horizontally over the elevated side portions to form a double bottom tank or reservoir 13 for carrying fuel or freight. The interior hull construction is designed to accommodate the engines and other elements of the propelling apparatus and suitable accommodations for packages and freight.

Arranged horizontally across the hull is a bottom .or deck plane 14 somewhat wider than the hull structure and designed so that its transverse dimension is comparatively The longitudinal edges of the deck plane are curved downwardly, as indicated at 15 in Figures 2 and 4, and overhang the sides of the hull.

Supported immediately above the deck plane 14, in a position parallel therewith, is I an intermediate sustaining plane or airfoil 16 having the same proportional dimensions 'as the deck plane and likewise curved at the longitudinal edges, as indicated at 17.

A second intermediate sustaining plane 18 is disposed above the lower intermediate sustaining plane 16 and provided with downwardly curved side edges 19. As illustrated in Figure 1, the extreme longitudinal edges of the sustaining plane or airfoil 18 are formed with a convex. curvature, the purpose ofwhich will be later described.

Above the upper intermediate sustaining plane 18 is mounted a top or mainplane 20 formed with longitudinally directed, downwardly curved portions 21 intermediate the longitudinal edges. The outer side portions of this plane project lateral}; outward in a horizontal lane, as indicate at 22, and terminate in ownwardly curved longitudinal edge portions 23. As shown to advantage in fuselage 10 and interconnected by a series of durable struts embodying a plurality of main centrally disposed struts 24 arranged vertically through the fuselage and plane structure, a plurality of an larly disposed struts 25 pro ectin upward at an angular inclination from t e sides 0 the hull to securely connect the curved longitudinal edges of the airfoils and a number of relatively short plane connecting struts 26. This constructlon is designed to provide an exceedingly durable aircraft capable of comparatively great carrying capacity.

The multiplane construction further embodies, a series of airfoil sections designed to increase stabilization and the sustaining power of the machine. This is effected by mounting on the lateral extensions 22 of the to or main airfoil aseries of longitudinally aligned airfoil sections 27 formed to provide arcuate, funnel-like airfoils open at the forward ends and tapering gradually on to the airfoil structure at the rear. The sections 27 are arranged so that their outer longitudinal portions are curved downwardly and merge into theouter depending edges of the supporting plane. The inner edges of the sections 27 extend into the arcuate portions 21 of the" main plane. This plane is conj structed so that openings 28 are provided in the lower sections of the curved portions 21 so as to provide communication between the sections 27 and the under surface of the carrying plane. Similar airfoil sections 29 are mounted on the outer longitudinal portions of the lower intermediate sustaining plane or airfoil 16, these sections bein designed to direct the air currents inwar 1y during flight on to the sustaining plane 18. A series of central airfoil sections 30 are mounted in longitudinal alignment on'the central portion of the u per intermediate sustaining plane or airfo l 18, as illustrated in Figures 2,3 and 4, these sections tapering from an elevated structure at the forward open end to merge into the plane at the rear end. These sections direct the currents downwardly through transversely elongated openings 31 apparent from the drawings, the

so that the buoyancy current is directed to the under side of the plane 18.

Elevating rudders 32 are hingedly mounted on the upward extensions of the central struts 24 over the forward and rear ortion of the top airfoil 20, these rudders being adjustable in a vertical plane. A second pair of elevators 33 are hingedly'mounted below the airfoil 20 and adjustable vertically from a position against the under side of the airfoil to a downwardly inclined arrangement, as shown in Figure 3. In'addition to the foregoing a pair of elevators 34 are pivotallyassociated with the bottom deck plane 14 and disposed over the upper sides of the hull 10.

At the rear of the machine is fitted a steering rudder 35 pivotally connected with a rudder post 36 an operated through the medium of cables 37. The elevating and steering rudders are operated in any preferred manner from a pilot cabin in the hull 10.

The craft is driven by a series of propellers 38, one of which is preferably mounted on the forward end of the hull nose structure 11, while any required additional number may be distributed at suitable positions throughout the machine structure. A suitable numberof propellers are preferably arranged at the forward ends of the sustaining airfoils, while an additional number are fitted in longitudinally spaced positions throughout the multiplane structure. I

From the foregoing description and the drawings, it will be noted that the aircraft forming the subject matter of the present application is designed particularly to provide a stable flying machine capable of carrying extremely heav loads. The airfoil construction is forme so that the air currents will be somewhat compressed and banked at the sides thereof and will be deflected inwardly relative to the multiplane structure to produce a concentrated buoyancy current at the central portions of the sustaining planes. This construction is designed to substantially increase the stability of the craft and minimize the effect of adverse air currents. The airfoil construction, embodying a relatively great longitudinal dimension approximating the transverse spread, substantially enhances the durability of the machine so as to reduce to a minimum the possibility of collapsing or folding up of the Wings. andpermitting extremely durable fuselage connection.

The hull construction, designed to embody. a stream-line bow and stern structure together with undulatory exterior contour of the bottom, is adapted particularly for effective aquatic launching and landing. \Furthermore, this hull structure will provide an additional sustaining surface when the machineis in flight so asto reduce to a minimum the resistance of the fuselage.

It is to be understood that the form of my invention herein shown and described is to be taken as a preferred example of the same, and that various changes as to the shape, size,

and arrangement of parts may heresorted to without departing from the spirit ofthe invention or the sod e of the subjoined claims.

Having thus escribed my invention, I

10 1. In a flying machine, a plurality of superposed sustaining airfoils, a plurality of airfoil sections mounted in longitudinal alignment on the longitudinal side portions of one of said airfoils adapted to deflect air currents inwardly on to the under surface thereof, and a plurality of airfoil sections mounted on the centralportion of a second sustaining airfoil adapted to direct air currents downwardly through openings in said an airfoil to the under side thereof.

2. A flying machine comprising a longitudinally elongated hull, a plurality of sustaining airfoils mounted insuperposed position over the hull and having their longitudinal edges curved downwardly, a plurality of airfoil sections mounted on the longitudinal side portions of two of the sustaining airfoils adapted to deflect air currents inwardly to the central portions thereof, a plurality of airfoil sections mounted on the central portion of one of the sustaining airfoils adapted to deflect air currents downwardly to the under side thereof, a plurality of elevating rudders operatively associated with the machine, driving means mounted on the machine, and a stern rudder operatively associated with the rear end'thereof.

3. In a flying machine, a sustaining plane having a plurality of apertures formed there- 40 in,.a plurality of airfoil sections having an arcuate longitudinal and transverse curvature secured to and extending upwardly from the margins of the said openings adapted to direct air currents to the under side-of the plane, a fuselage suspended from the plane, and meansfor propelling the said machine.

4. A flying machine comprising a longitudinally elongated hull, a sustaining airfoil mounted in superposed position over the hull having downwardly ofi'set side sections formed adjacent the longitudinal margins, a plurality of funnel shaped airfoil sections mounted on the downwardly ofi'set side sections disposed to direct the air current to the under side of the said side sections, and means ifor propelling the said machine. h 115 witness whereof I have hereunto set my an a CHARLES L. FORTIER.

Images