US1759164A - Aeroplane - Google Patents

Description

May 20, 193@E l. G. Mms mssm;

AEROPLANE Filed March s, '1928 :s sheets-sheet l l f/ f f Q ATTO RN EY May 20, 1930- J. G. L YoNs 1,759,164

AEROPLANE Filed March 6, 1928 5 Sheets-Shea?l 2 ATTORN EY J. G. LYONS May 20, 1930. I

AEROPLANE Filed Maron e, 192e 5 Sheets-Sheet 5 INVENTOR QT. G. Ltg/012.5 Q

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Patented May 20, 1930 UNITED STATES .TAMS G. LYONS, F STOCXTON, CALIFORNIA AEBOPLANE Application led March 8, 1928. Serial No. 259,438.

This invention relates to improvements in aircraft, my princi al objects being to provide a machine of tliis character constructed so that it will have great carrying power with a relatively narrow wing spread; one which can safely alight on water and which can then be properly propelled and navigated while on the water; and one which is provided with power generating devices operated by the air currents set up with the operation of the propellers and the forward movement of the machine.

These objects I accomplish by means of such structure and relative arrangement of parts as will fully appear by a perusal of the following specification and claims.

In Vthe drawings similar characters of reference indicate corresponding .parts in the several views:

ing my improved aeroplane in li ht.

' Fig. 2 is a top plan view of t e machine partly broken out.

Fig. 3 is a frontend view, the forward body compartment being shown in section.

Fig. 4 is a longitudinal section of the machine.

Fig. 5 is a lon itudinal section of a wing showing a modi ed air discharge arrangement for the power generating turbines or wind mills.

Fig. 6 is a fragmentary rear end View show'- ng modified form of ground engaging mem- Referring now more particularly to the characters of reference on the drawings, and particularly at present to Figs. 1-4, the aeroplane comprises a fuselage or body 1 which is shaped like the hull of a boat and is adapt- 40 ed to float on Water on an even keeland to a certain depth just like the hull of a vessel.

The wing structure projects laterally from the upper edgeof the hull and comprises a main front end portion 2, which merges unbroken into an intermediate and somewhat narrower portion 3, which portion in turn merges unbroken into the 'rear portion 4, whose side edges converge to the rear and terminate some distance rearwardly of the 5 rear end of the hull as shown in Fig. Q.

Fig. 1 is a fanciful perspective view showi surface being had.- The main -forward pro- 4 peller 6 is mounted on the nose of the hull and is directly connected to a stationary 'gas engine 7 or the like which is mounted in the hull at the rear end'of the forward compartment 8; the ceiling of which compartment extends to and joins inwith the to surface of the wing. The side propel ers 9 which are somewhat higher than the central propeller are mounted just under and ahead of the. front edge of the wing structure, and are driven from a ,stationary engine 10 which is mounted in the body below the engine 7, said engine being connected to the Propellers bysuitable drive connections such as are indicated at 11. Using stationary engines located inside the body makes them very easy to attend and keep in proper working order and they are not exposed to the weather.

`They may also be posltioned where they aid in balancing the machine. The side propellers being higher than the central one they may be operated when the hull is floating on the water to propel the craft without churn-` ing up any water.

The horizontal direction rudderv 12 is located at the rear of the hull and below the rear end win portion, and extends downwardly to the ttom of the hull. This rudder can therefore be used for steering when the hull is floating on the water as well as when the machine is in flight.

The vertical direction rudder 13 projects rearwardly from and is longitudinally alined with the rear end wing surface and extends alongside the edges of such surface for a certain distance to a junction therewith as shown in Fig. 2. The rudder is pivoted at its forwardside tips as indicated at 14. Both rudders are connected to the usual form of control means indicated at 15 which are mounted in the forward compartment 8 of the body; this being the one occupied by the pilot.

The wing structure is of double hollow construction, with a gradual narrowing toward also inclosed in the wings in which casings air turbine wheels 18 are mounted. These wheels are connected with electric generators 19 or the like which are preferably mounted inside the hull where they may be serviced or inspected whenever necessary. By means4 of t is arrangement a rearward flow of air through the passages 16 set up by the rotation of the propellers and the flight of the machine causes the turbine wheels to be rotated and the generators to be driven, thus generating power' for lighting and other purposes. In the type shown in Figs'. 1 and 2 the air passages are substantially straight from end to end. In the arrangementtshown in Fig-a5 the passage 16 beyond the turbine casing 17 a has an auxiliary downwardly projecting discharge outlet 20. This enables the air to be discharged downwardly and thereby aids in exerting a lifting power to the adjacent portion of the machine. The flow of air through the outlet 20 or the horizontal termination of the passage 16aL is selectively controlled by a suitable damper 20. v

The air passages and turbine casings being inclosed in the wings, of themselves, they offer no wind resistance to exert a drag on the forward movement of the plane.

Dependin from the lower wing surface to the sides of t e propellers 9 are longitudinally extending ridges or deflectors 21.` These are positioned relative to the diagonal air currents thrown rearwardly from the central propeller so as to catch such currents and deflect them in a straight rearward direction. This causes the air to be retained and somewhat compressed under the wing structure from front to rear thereof, thereby giving the advantage of the lifting power o such air which would otherwise pass beyond the Vsides of the wings to no effect. These ridges increase in depth toward the rear so as to substantially equalize the lifting power of these air currents over' the length of the wing surfaces with which such air currents are engaged.

The usual landing wheels 22 may be emlployed if the machine' is to be used for land flights and landings on the ground, with the accompanying rear tail skid 23. If desired this skid may be replaced by another wheel 24 as shown in Fig. 6,-in which the wheel is shown as being mounted on the lower end of a pivoted arm 25 which is associated -with a yieldable spring member 26. This arran ement enables the wheel to yield rearwardly and upwardly so as to absorb some of the shock of engagement with the ground.

The main cargo or passenger carrying compartment 27 ofthe body, which is preferably divided oft' from and is rearwardly of the compartment 8 and the engines, has a floor 28 a sufficient distance from the keel of the hull to provide a space under the floor for fuel tanks 29. f

Other fuel tanks 30 are mounted in the forward portions of the wings between the air passages 16 and the outer ends of said win s. The latter tanks may feed to the engines by gravity, since they are above the engines; while the lower tanks must of course have a vacuum or pressure feed means as will be evident.

The ceiling of the main hull compartment may be the top surface of the wings as shown instead of the bottom surface thereof, whichA bottom surface may be left off where the wings intersect the body. This construction as will be evident gives the advantage of a considerable amount of additional head room "over what would otherwise be obtained.

If desired or necessary the upward pressure exerted on the plane by the downward v discharge of the air through the passage outlets 20 may be utilized in banking the machine, by merely manipulating the dampers 2Oa to open or shut off one or the other of such outlets alternately.

From the foregoing description it will be readily seen that I have produced such a device as substantially fulfills the objects of the invention as set forth herein.

While this specification sets forth in detail the present and preferred construction of the device, still in practice such deviations from such detail may be resorted to as do not form a departure from the spiritof the invention, as defined by the appended claims.

Having thus described my invention what I claim as new and useful and desire to secure by Letters Patent is:

1. An aeroplane including a body and a single wing disposed directly over the body and extending lengthwise .thereof tov a point beyond the rear end of the same, a vertical rudder mounted entirely under the rear overhanging portion ofthe wing, and a horizontal rudder hinged in connection with the rear portion of the wing, and projecting rearwardly of the same.

2. An aeroplane including a body, a single tively controlling the opening of the rear-end openings of the passages.

3. An aeroplane including a body and a single Wing disposed directly over the body and extending for substantially the full length thereof; the side edges of the Wing being `formed as a plurality of steps to gradu- :illy decrease the Width of the Wing from front to rear in simulation of the outstretched Wing aree of@ bird, in which the foremost and Widest Step `portion of the Wing is formed with a downward dip toward its outer ends and in e rearward direction ln testimony whereof I aiiix my signature.,

JAMES G.. LYONS..

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