US1564469A - Aeroplane - Google Patents

Description

Dec. 8, 1925- 11,564,46g

, H. M. COSEY- AEROPLANE Filed April 13, 1925 Patented Dec. 8, 1925.

UNITED STATES HENRY M. COSEY, OF FLINT, MICHIGAN.

AEROPLANE.

Application filed April 13, 1925. Serial No. 22,649.

I '0 all whom it may concern:

Be it known that I, HENRY M. Cosnr, a citizen of the United States, residing at Flint, in'the county of Genesee and State of Michigan, have invented .a new and useful Improvement in an Aeroplane, of which the following is a specification.

My invention relates to a new and useful improvement in an aeroplane, and has for Another object of the invention is the pro-' vision of a supporting member adapted for preventing the fall of the aeroplane to the earth, should anything go wrong with the driving motor.

' Another object of the invention is the provision of a landing gearing which is spring operated and adapted for absorbing the shock upon the aeroplane alighting, and also adapted for assisting the aeroplane in raising initially from the ground.

Other objects will appear hereinafter.

The invention consists in the combinations and arrangements of parts hereinafter described and claimed.

The invention will be best understood from a reference to the accompanyin drawings which form a part of this speci cation and in which,

Fig. 1 is a side elevational view oi the invention,

Fig. 2 is a front elevational vlew ofthe invention, I

Fi 3 is a sectional view taken on substantlally line 3-3 of Fig. 1,

Fig. 4 is a side elevational view of the invention showing the supporting means in operative form,

Fi 5 is an enlarged fragmentary sec tionfi view, illustrating the mountings of the propeller trunnions in theraceway.

As shown .in the drawings, the invention comprises an aeroplane having a body.- 9,- tormed from suitab e material, and provided with. the necessary reinforcing frame. Pro-' jectin from the rear of the body 9, is a suitab e control rudder 10, a similar rudder 11 projecting from the forward end thereof.

The motive mechanism of the aeroplane is not shown in detail, inasmuch as it forms no part of this specification, the driving motor of the invention being of a conventional type. Supporting members 12 serve to so port the central portion 13 of a wing to t e body, spaced above, as shown in the drawings. The extremities 14 and 15 of this wing are hingedly connected to the rigidly mounted portion 13 and adapted for swingable movement relatively to the main body 13. This swingable movement of the extremities 14 and 15 of the wing will serve to assist in raising the aeroplane from the ground so as to permit an ascent to the desired altitude. Connected at one end to the swingable portions 14 and 15 are rods 16 and 17, a ball and socket joint 18 being provided effecting the necessary connection with the swingable portion of the win Projecting transversely of the body 9 1s a shaft 19 which is adapted to be rotated by the motor of the aeroplane,-a suitable friction clutch being provided for controlling the rotation of theshaft 19, the operating lover of the clutch being positioned within easy access of the driver of the aeroplane. Mounted on the extremities of the shaft 19 are discs 16 and 17 which are adapted to rotate in unison with the shaft 19. The structure is such that, upon a rotation of the shaft 19, a flapping of the swingably mounted portions 14 and 15 is brought about, the rods 16 and 17 beingpivotally connected to the discs 16' and 17 respectively adjacent the periphery -of the discs 16' and 17 so as to provide an eccentric mounting;

The mechanism used for driving the aeroplane in a forward direction, embodies a reciprocating member, which is adapted to travel in an orbit substantially oval-shaped. Mounted upon the body 9 and projecting from opposite sides thereof are U-shaped members 20 having an oval-shaped raceway 21, which is channel shaped, as shown in Fig. 5, in which engages a-roller 37 mounted u on a trunnion 38 which projects outwar 1y from one side of a. spoomshaped propeller 22. A similar trunnlon projects rom the opposite side of the spoon-shaped propeller 22 and engages in a track formed on the projection 21, which is secured to the body 9. The propellers 22 are connected pivotally to driving rods 23, which are eccentrically connected to the disc 24-. This disc 24 is fixedly mounted upon a shaft 25, upon which is fixedly mounted one portion 26 (if a friction clutch, which is adapted to engage the co-operating portion 27, driven by the shaft 28 of the motor. The arrangement is such that when the friction clutch 26 is in engagement with the co-operating portion 27 of the clutch a reciprocation of the driving rod 23 is brought about, which causes the movement of the spoon-shaped propellers 22 in the orbits described by the tracts 21 and 21'. A spoon-shaped propeller 22is positioned at each side of the body 9, so that the mechanism is balanced and an even driving of the body 9 brought about.

lVith. a mechanism of this class, a .substantially noiseless forward driving or the body 9 is had, the concavity of the spoons 22 assuring a forward driving of the vehicle.

I have provided a landing gearing which comprises a projection 29 mounted on the base of the body 9 and having springs 30 projecting outwardly therefrom and adapted for being compressed upon the swingi g of the swingingly mounted cover 31 in o closed position shown in Fig. 1. When this cover 31 is swung into this position, the catch 32 serves toretain the cover in fixed position so as to retain the springs 30 under tension.

When it is desired to start the elevation of the aeroplane, the operator may release the catch 32, so as to permit the springs 30 to force the cover 31 outwardly, thereby giving an upward thrust to the body 9, When flying, the cover 31 is in open position,

so that, when it is moved to closed position,

the springs are compressed and the shock absorbed, when the aeroplane lands. Mounted upon the portion 13 of the win is a housing or receptacle 33, through whic proaccuse 'ects a handle at of an umbrella 35, the

andle 34 being within easy reach of the operator of the aeroplane. Positioned within the receptacle 33 is a parachute cover 36, attached by the ropes 37 to the receptacle 33. The arrangement is such that the operator may, at will, move the handle 34 upwardly, so as to open the umbrella 35. The umbrella, when in open position, will,

' on account of being driven through the air,

cause the parachute 36 to be raised clear of the receptacle 33, to permit its opening into the position shown in Fig. 4, so as to prevent a rapid descent of the aeroplane. The operator, of course, would make use of the parachute 36 for preventing a descent, only in cases of emergency.

While I have illustrated and described the preferred form of structure, I do not wish to limit myself to the precise form of structure shown, but desire to avail myself of such variations and modifications as come within the scope of the appended claim.

Having thus described my invention, what I claim as new and desire to secure by Letters Patent is An aeroplane of the class described, comprising a main body portion; a. wing mounted on said body portion having its central portion fixed relatively to said main body portion audits extremities swingable relatively thereto; a shaft projecting transversely of said main body portion; an arm connecting each of said swinging extremities eccentrically of said shaft, said wings being adapted for swingable movement upwardly and downwardly upon .the rotation of said "shaft.

In testimony whereof, I have signed the foregoing specification.

HENRY M. COSEY.

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