US1353212A - Aeroplane - Google Patents

Description

E. V. BOILER.

AEROPLANE:

APPLICATION FILED JAN.29, {920.

1,353,212. I PatontedSept. 21,1920.

3 SHEET$-SHEET 1.

. E..V.BOILER.

AEROPLANE. APPLICATION MEDIAN-291L920. I 1,353,212., 1 PatentedSept. 21,1920.-

3 SHEETS-SHEET 2.

E. v. BOILER.

AEROPLANE.

APPLICATION men mmzs, I920.

Patented Sept. 21, 1920. 3 SHiETS-SHEET 3.

m 0 m 0 I I M q EnwARnv. BOILER, or wnsr, SIDE, rows.

Application filed January 29 To all whom it may concern:- 7 i r v 13s it known that'I, EDWARD V. BOILER,

i a citizen of. the United States, residing at West Side, in the county of Crawford and State of ,Iowa, have invented certain new {and useful Improvements in Aeroplanes, of'

which thefollow'ing is a specification.

@MyIinvention relates to improvements in aeroplanes An important object of the invention is to provide an aeroplane which operates upon the principle of an inclined'plane to pelledforwardly, at high or low speeds.

I (A further object of the invention is to so construct the aeroplane-that it may beeasily controlled in-flight, little'afi'ected by 'alI'yCUI'I'GIItS, and at all times maintaining a state of balance in flight, thereby prevent- A further object of thelinvention is to i .provide longitudinal stabilizing wings, of

large area, which not only effectually pre- .vent'slide slipping, but compensatefor the provide means to adjust the dihedralangle loss in wing-spread, due to the-reduction in. size of the sustaining-wings or planes.

A: further object of the invention is to of the longitudinal-stabilizing wings. I 1 .A further-object of the invention is to;

provide a flying machine of theabove-men-- f tioned character, having its 'sustamlng and Y gravity, and-the planes are disposed in they:

stabilizing jwings so connected withand arranged with; relation to the fuselage, that the machine as a whole has a flow center of whip .stream' .ofthe propeller, whereby they conditions, at all times, during flight.

a provide-longitudinal 1 stabilizing wings are subjected.tosubstantially' the same air- A furth'er object of the iinvention is towhich are cambered, and adapted to func- ;.tion as true sustaining planes, in addition-- to theinstabilizmg action. 7 i- Other objectsandadvantages of the'invention will be apparent during the course of thezfollowing description. j

. In the; accompanylng drawings forming a part'of this specification, and: in which like numerals are employed to designate likeparts throughout-thesame-- V Figure 1 is a plan view; of an aeroplane embodying my invention, .7 r

Fig. 2 is a side elevation of the same, i Fig. 3 is a front end elevation of the same,

' AEROPLANE.

,192d SeriaiNo. 354,919. r

I Fig. is a transversesection through the fuselage, taken on line 4-4 of Fig. 2 arts being omitted, p

Fig. 5 is a;similar .view taken on line 1 5 5 of Fig. 2, 2

. Fig.6 isasimilar view taken onfline Fig. 7 is a perspective view of an operating'lever and associated; element's- 'In the drawlngs, wherein for the purpose of illustration is showna preferred embodiment ofmy invention, the numeral 5 desig- .raise the machine into the 'air,-when pronates the-fuselage of the aeroplane, having the cockpit 6, arrangedv as shown, The motor 7 is carried in the forward end of the fuselage, and drives the tractor propeller 8, as shown. The fuselage has its forward portion supported upon avchassis l9, and a skidlO is secured to its rear portion.

--The numeral 11v designates the transverse supporting planes, .arrangedupon opposite sides of the fuselage; and rigidly secured thereto, I preferably employ diagonal struts 12, connected with the supporting planes 11, near their-outer ends, and with the fuselage 5, near its bottom, as shown.

The rear edges'of the supporting planes 11, which are cambered, are cutiaway,vpro- Viding spaces 13, receiving ailerons 14, hinged thereto, at 15, by any suitable means; The usual masts 16 are rigidly secured to the supporting planes 11, and carryelements 17, engaging cables 18, which extend to the cockpit 6, and are operated by the usual joystick. I .7 i a a The numeral 19 designates the longitudinal stabilizing planes, which are cambered and tapered longitudinally, increasing in width rearwardly. "Thesestabilizing planes are suitably hinged, as at20, to the fuselage 5, and are. normally arranged at a slight, dihedral angle. Both the supporting planes and the stabilizingplanes 19 are disposed at the upper longitudinal edges; of

the fuselage. The stabilizing planes are therefore normally inclined'with the fuselage, as shown in Fig. 2. i Q.

Means are provided to swing the stabilizing planes 19 upon their pivots 20, to vary the dihedral. angle thereof, comprising di agonal struts 21, secured to. the outer edges of the-stabilizing planes, preferably having pivotal connection therewith, The struts 21 are provided at their lower ends with sockets '22, recei ing ba s-23, ar ied y vertically adjustable shafts 24. V The shafts 24 operate within sleeves 25, angularly disposed, and rigidly secured to' the fuselage 5. The shafts 24 extend to the exterior of the fuselage, as clearly shown in Fig. 4.

Extending longitudinally within the fuselage 5 are rock shafts 26 and 27, journaled in bearings 28, rigidly secured to the fuselage. These rock shafts carry sprocket wheels 29, rigidly secured thereto, and connected by a sprocket chain 30, so that the two rock shafts turn in unison in the same direction.

Each rock shaft 26 and 27 is provided with a plurality of cranks 31, 32 and 33, rigidly secured thereto, and having pivotal connection with links 34:, pivoted to the shafts 24. These cranks are of different lengths, increasing in length rearwardly, so that they will move all portions of the stabilizing plane 19 a corresponding distance.

One rock shaft 27 is shown as equipped with a worm 35, engaged by a worm 36, rigidly secured upon a transverse shaft 37, arranged within the fuselage. This shaft is turned by a lever 38, positioned to be operated by the party in the cockpit 6.

Fromthe foregoing description, it will be seen that the stabilizing planes 19 are normally locked in a suitable dihedral angular position, which may be varied by the operation'of, the lever 30. The ailerons 14, the elevators 32, and vertical rudder, are operated in the usual manner, as is well known in the art, whereby it is thought to be unnecessary to further describe the same, it being understood that any suitable means may be employed for that purpose. By arranging the stabilizing planes and supporting planes at or near the upperedge of the fuselage, and imparting to them a dihedral angle, the machine has a very low center of gravity,

' and further practically all parts of the ma chine are arranged in the whip stream of the propeller, so that the machine-is'not subjected to the change in air conditions, to any considerable extent, during'flight.

It is to'be understood thatthe form of my invention herewith shown and described is to be taken as a preferred example of the same, and that various changes in the shape, size, and arrangement of parts may be resorted to without departing from the spirit of my invention, or the scope of the subjoined claims.

=Having thus described my invention, I claim 1. An aeroplane comprising a fuselage,

supporting planes connected therewith and arranged upon opposite sidesthere'o'f, longitllCllhil'StRblllZlllQ planes arranged upon opposite sides of the fi'iselage in the rear of the supporting planes, and pivotally connected with the fuselage near its top, said stabilizing planes tapering longitudinally and increasing in width rearwardly, a plurality of spaced elements secured to the stabilizing planes near their outer edges and extending inwardly toward the fuselage, means to simultaneously move the elements upon each side of the fuselage and to move each succeeding rear element a greater distance than the next preceding forward element and propelling means carried by the fuselage.

2. An aeroplane of the character described, comprising a fuselage, supporting planes connected with thefuselage and arranged upon opposite sides thereof, longitudinal stabilizing planes arranged upon opposite sides of the fuselage and pivotally connected therewith, said stabilizing planes extending from a point adjacent the supporting planes to a point adjacent'the rear end of the fuselage, said stabilizing planes tapering and increasing in width rear wardly, a plurality of spaced elements arranged upon each side of the fuselage and connected with the stabilizing plane near its outer edge, said elements being inclined inwardly toward'the fuselage, means carried by the fuselage to simultaneously move all of said elements and to move the elements in each set for different distances, and

propelling means carried by the forward end of the fuselage.

3. An aeroplane of the character described, comprising a'fuselage, supporting planes connected therewith and arranged upon opposite sides thereof, longitudinal stabilizing planes arranged upon opposite sides of the fuselage in the rear of the supporting planes and pivotally connected with the fuselage, said stabilizing planes taper ing longitudinally and increasingin width rearwardly, a plurality of diagonal struts connected with each stabilizing plane and inclined downwardly toward the fuselage, a corresponding number of pivoted elements carried by the fuselage and connected with the struts, said pivoted elements increasing in diameter rearwardly, and propelling means carried by the fuselage.

4. An aeroplane comprising a fuselage,

supporting planes connected therewith and ilizing planes and converging downwardly toward the botton1 of the fuselage, means to longitudinally move the struts with re lation to the'fusel-a'ge, and propellin'gmeans connected with the'forward end of the fusela e.

5. An aeroplane comprising a fuselage which is longitudinally tapered and decreases in width rearwardly, supporting planes arranged upon the opposite sides of the forward portion of the fuselage and connected therewith, the fuselage extending forwardly beyond said planes, longitudi nally tapered stabilizing planes increasing in width rearwardly and pivotally connected with the tapered side of the fuselage in the rear of the supportin planes, diagonal struts pivotally connecte stabilizing planes near their longitudinal with the tapered edges and converging downwardly toward the fuselage, means arranged upon the fuselage to longitudinally adjust said struts, a propeller connected to the forward end of the fuselage, and means to drive the pro peller.

ANDREW BELL,'J1., G. F. MALLOY.

In testimony whereof I aifix my signature

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