US1686071A - Aeroplane - Google Patents

Description

Oct. 2, 1928.

V. CAVALERI AEROPLANE Filed Aug. 20, 1927 3 Sheets-Sheet 1 V. CAVALERI Oct. 2, 192st AEROPLANE 3 Sheets-Sheet Filed Aug. 20, 1927 Inventor kw/ff 5am/5w' oct. 2, 192s. 1,686,071

V. CAVALERI AEROPLANE Filed A ug. 2o, 1927 3 sheets-shet 3 i Inventor Wfcefff al/a/e/v' Patented oci. 2, 192e.

rATENr ortica.

VINCENT CAVALERI, F BROOKLYN, NW YORK.

i. annorLaNn.

Application mea august 2o, 1927.y temi mamada.

The resent invention relates'to improvements 1n aeroplanes and more particularly to an improved propulsion unit for aeroplanes and the like, A

An important obj'ect of Ithe'invention resides in the provision of a pro ulsion unit .Which-sucks in air from the ront of the aeroplane, compresses it, stores it, and ex"- hausts it rearwardly of the aeroplane as needed for propulsion purposes.

A still further important object of the invention resides in the provision of a propulsion unit of this nature which is simple in `its construction, comparatively inexpensive l5 to`manufacture, thoroughly efficient and reliable in use| and operation, -and'otherwise well adapted for the purpose for which it is desi ed. I .ith` the above and numerous other objects in view aswill appear as the description proceeds, the inventlon resides in 'certain novel features of constructiomwand in the combination and arrangement ofl parts as will be hereinafter more fully described and claimed. ff)

In the drawing Figure 1 is asectional elevation of an aeroplane embodying the features of lI ny invention,

Figure 2 is a fragmentary top plan. view thereof, f t,Figure is a fragmentary front elevation thereof, and, f Figure 4 is a detail' section through one of the compressors. Referring-to the ,drawing in detail it will be seen that the numeral 5 denotes a fuselage `designed as to the usual well known constructionhaving conventional steering mpans at o -therear thereof. The nose-of the fuselage "is `preferably pointed and .has intake suction pipes 6 leading rearwardly, onefto each side of the point and connected to compressorsl f 7 operativelyconected by suitable gearing above.

wardly for a short distance. All of these' p1pes 14, 15 and 16 have valves 18' therein controlled in unison by a lever`1 9 conveniently located in respect to the drivers seat so that the compressed air 11 may be exhausted as needed for propelling the aeroplane.

From the above detailed description, it w1ll be seen that I have devised a very simple and efficient unit for propelling the aeroplane which will cause afrarity of air in/ frontof the aeroplane and a thickness of air in' the rear of the aeroplane so as to push the aeroplane forwardly. In this way a great deal of speed may beaccomplished and d angers caused by unexpected eddies, air pockets, and the like will be greatly minimized. It is preferable to construct the -machine with wings or planes 20. In the present instance I have shown a single plane. This plane 20 is hollow so as to be -filled with a lighter than air gas such as helium, hy-

drogen, or the like, through a valve 21. It is alsol preferable to mount pontoons 23 on the bottom of the fuselage for;` landing in the water and" also to obtain maximum buoyancy in the air by making the pontoons hollow and filling the/in through' a valv'e 24 with lighter than air gas such as mentioned. i

/e 85 It is thought that the construction, oper-y ation, utility, and advantage. of the inven'- tion will now -be clearly understood without a more detailed description thereof. How- V ever, .I have disclosed in Figure 4 a form. 9o of compressor 7 which may be used whereinthe `cylinder has a piston 26 reciprocable therein by means of a pitman 27y operated by .an eccentric 28 o'n a shaft 29 from the gearing 8. Check valves S30-'and 31 are so arranged that the air may pass kin one direcltion only, `thus the downward stroke of ther piston will suck the air 'into the cylinder through-the one pipe andthe upward stroke 4 Lofthe piston Willexhaust this air through 190 l5 8'with a' prime mover 9 such as anfinternal` the other pipe and linally cause a comprescombustion engine. Pipes 10 leadfromr the compressors to a storage tank 11 and these pipes 10 have checkvalves 12 thereim O'utet pipes'14 and 15' and 16 lead from` the 50 front of the tank 11. The pipe 1i-leads latorally and then rearwardly to terminate ady 'acent the tail of the fuselage. The pipes 1 5 ead laterally from the tank and terminate intermediate the ends thereof while the p'ipe 55 16 extends forwardlyto theforward portion` of the fuselage, then laterally dnd tlen rear-s sion in. thetank 11 becausel of the check valves 12. l

The present .embodiment of the invention, however, has'been disclosedin detail merely by"wa v. of example since in actual practice -it attains' the featr'esof advantage enumery,ated as desirable in the 'statementof. the', invention and the above descriptionl It will be apparent that changes in the details of construction, and in the combination and arrangement of parts may be resortedto Without departing from the spirit; or scope of the inventionr as hereinafter claimed or sacrificing any of its/advantages.

Having thus described my invention, what I claim as new is p 1. In combination, an aeroplaney fuselage, a pipe leading from the front of the fuselage, a compressor connected with the pipe,

a. prime mover, means for operatively condiflerent directions, and then rearwardly, valves in said last mentioned pipes, and means 'for simultaneously operating the valves.

` 2. In an aeroplane havin a'fuselage, a tank in the rear of the fuse age, said tank adapted to store air under ressure, a plurality of pipes extending orwardly from the tank, then' laterally, in diierent directions, and then rearwardly, valves in said p`pes, and means for simultaneously operatin the valves.

n testimony whereof .I affix my signature. y

VINCENT CAVALERI.

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