US1554843A - Airplane - Google Patents

Description

Spt. 22, w25.. L5'5443 J. c. DAYNux AIRPLANE Filed, Dec. 25, 1924 INVENTOR ATTORNEY Patented Sept. 22, 1925.

UNITED STATES PATENT OFFICE.

AIRPLANE.

Application led December 26, 1924., Serial No. 758,101'.

To all 'whom t may concern:

Be it known that I, JOHN C. DAYNIX, a citizen of the United States, residing at Philadelphia, in the county of Philadelphia and State of Pennsylvania, have invented certain new and useful Improvements in Airplanes, of which the following is a specifcation.

This invention has reference to airplanes and more particularly to aerofoils having the major dimension disposed lengthwise of the flight direction, the primary object being to provide an airplane with means designed to produce vacuum waves tending to ensure the maximum factors of longitudinal and lateral stability, with consequent positive balance and safety in flight.

Another object of this invention is to provide an airplane characterized by means productive of suction currents longitudinally directed during flight whereby greatly in? creased carrying capacity results with 1ncidental increased buoyancy.

A further object of this invention is to provide an airplane with means whereby correctional currents are induced during flight, said currents being so directed t0 enhance upward suction and longitudinal buoyancy and thereby automatically counter- 30 act overbalancing tendencies.

With the foregoing and other objects in view, which will be apparent from the following detail explanation, my invention consists of the matter hereinafter described, typically illustrated in the accompanying sheet of drawings, and tersely stated as to subject-matter and scope by the appended claims. y

In the drawings, Fig. 1, is a diagrammatic plan view of a flying machine ernbodying a supporting plane in accordance with this invention.

Fig. 2, is a longitudinal section through the supporting plane, taken approximately as (indicated by the arrows 2 2 on Fig. 1; an

Fig. 3, is an end view of the machine.

Referring more in detail to the drawings my novel airplane or supporting unit 5, is substantially rectangular in contour with the major dimension lengthwise to the direction of flight, while the fuselage or car is designated 6, and the vertical tail rudder 7, said latter parts ybeing merely referred to as they form no part of the present invention.

The airplane or supporting unit 5, it will be observed has the longitudinal edges 8, downwardly cambered to aid banking of the air, and said unit may be constructed in so far as its texture or body is concerned in ac-cordance with general practice. Transversely of the airplane 5, however, I form laterally directed openings or current inducing apertures 9, the same having associated rear ribs or ri'liles 10 preferably of bull-nose cross-section, as clearly shown in Fig. 2. These ribs or rilfles 10 extend from the walls of the fuselage or car 6 and merge at their outer ends with the downwardly cambered longitudinal edges 8, and they are preferably grooved at their backs 11 to create-with the adjacent upper face of the airplane --lateral suction pockets which function to ensure positive balance in fli ht. Similarly the unit 5 is provided wit a rib or nose riifle 10 at its forward end functional in like manner.

It is also noteworthy that the openings or I apertures 9 flare downwardly in cross-sec* tion-as shown-so `that the air flowing therethrough is, in a measure, compressed' and caused to flow in the direction, indiezted by the arrows, over the ribs or rifiles Longitudinally below the airplane or sustaining unit 5, I provide air tubes 12, having open ends that constitute flow passages for buoyancy currents of air longitudinally below the plane.- It will be-therefore-obvious that by the peculiar cross-section of the tubes 12, the air in itsflow therethrough will, in a measure, be subject to slight expansion thereby materially aiding the general stability of the plane.

In addition to the foregoing stabilizing means the flying machine is provided with pontoons 13, in which the landing wheels 14, are journaled, saidy pontoons being bridged as shown in Fig. 3, to afford a. rigid backbone for the entire structure.

From the foregoing it Ywill be apparent that I have devised a novel and serviceable airplane, whichembodies the features and advantages enumerated as most desirable, and while I have, in the present instance, shown and described one practical embodiment that will ensure satisfactory results, it is to be understood that the same is susceptible of modification without departing from the spirit or scope of my inventlon much less sacrificing any of its merits.

Having described my invention I claim 1. An airplane with the major dimension coinciding with the direction of Hight and its longitudinal edges downwardly cambered, lateral ribs with grooved backs on said airplane with the ends thereofmerging into the cambered edges, and apertures adjoining the forward part of the aforesaid ribs functional to set up suction currents.

2. An airplane with the major dimension coinciding with the direction of Hight and its longitudinal. edges downwardly cambered, lateral ribs with grooved backs on said airplane with the ends thereof merging into the cambered edges, and downwardly Hared apertures adjoining the forward part of the ribs functional to set up suction currents.

3. An airplane' with the major dimension coinciding with the direction of Hight and its longitudinal edges downwardly cambered, lateral ribs with grooved backs on said airplane with ends thereof merging into the cambered edges, downwardly Hared apertures adjoining the forward part of the ribs, and a complementary configured rib transversely at the front end of the air plane.

4. An airplane with the major dimension coinciding with the direction of Hight having lateral ribs on the uppers-surface with ladjoining apertures forwardV of said ribs,

and longitudinal air tubes on the undersideI thereof.

5. A11 airplane with the major' dimension coinciding with the direction of Hight having lateral ribs on the upper surface with v tures in advance of the lateral ribs, and

spaced longitudinal tubes under the air plane functional as How passages for buoyancy current.

In testimony whereof, I aHiX my signature the 22nd day of December, 1924.

l JOHN o. DAYNIX.

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