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Publication numberUS1351395 A
Publication typeGrant
Publication dateAug 31, 1920
Filing dateDec 18, 1918
Priority dateDec 18, 1918
Publication numberUS 1351395 A, US 1351395A, US-A-1351395, US1351395 A, US1351395A
InventorsLaureat L Martineau
Original AssigneeLaureat L Martineau
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Liquid-container for aeroplanes
US 1351395 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

L L. MARTINEAU. LIQUID CONTAINER FOR AEROPLANES.

APPLICATION FILED DEC. I8, I9I8.

1 ,35 1 3 95, Ptented Aug. 31, 1920.

f4. LY M0177 ad Wz'lness es UNITED sTA'rEs LAUREAT L. MARTINEAU, OF ST. JOHN, NORTH DAKOTA.

LIQUID-CONTAINERiFOR AEROPLANES.

Specification of Letters Patent.

Patented Aug. 31, 1920.

Application led December 18, 1918. Serial No. 267,324.

To all whom t may concern.'

Be it known that I, LAUnEA'r L. Man- TiNEAU, a citizen of the United States, residing at St. John, in the State of North Dakota, have invented new and useful Imp piovements in Liquid-Containers for Aeroplanes, of which the following is a specification.

The object of my present invention is the provision of a container for liquids such as gasolene, kerosene and alcohol, designed to form part of the equipment of an aeroplane or other airship and constructed with a view to stopping leaks and preventing the loss of liquid when the container is subjected to gun-fire and even when the container is pierced by a bullet or similar projectile.

IVith the foregoing in mind, the invention in all of its details will be fully understood from the following description and claims` when the same are read in connection with the drawings, accompanying and forming part of this specification, in which:

Figure l is a side elevation of the container constituting the best practical embodiment of my invention that I have as yet devised.

Fig. 2 is a longitudinal central section of the same.

Fig. 3 is a transverse section taken in the plane indicated by the line 3-3 of Fig. 2.

Fig. 4 is a transverse section `taken in ythe plane indicated by the line 4 4 of Fig. 2.

Similar numerals of reference designate corresponding parts in all of the views of the drawings.

My novel container is designed more especially for the carrying of gasolene or analogous hydrocarbon, inasmuch as it is essential in aeroplane practice to avert leakage of the gasolene because of the danger from iire that is ordinarily attendant upon such leakage. It is also essential in the aeroplane art to avoid making the container un:

duly heavy, and this latter consideration has been observed in the conception of my novel container as will hereinafter appear.

In furtherance of my invention, I employ' a liquid tank 1 that is cylindrical in shape and is preferably made of thin steel or of a metal or allo that is not easily ripped, or,

if preferred, or the sake of lightness the provided with. oval. heads 2, and interiorly the tank is provided with light braces 3, which for the sake of stiength are interposed between and fastened to opposite oints of the interior of the tank. I

Fitted in the center of one end of the tank 1 is a solid shaftA 4, and fastened in the opposite end of the tank is a conduit 5, of steel orA other suitable' material, which is connected to a pipe 6 that teminates in the tank close to the bottom thereof and preferably at a point adjacent to the transverse center of the tank. The conduit 5 is preferably equipped with a gage 7 and with a filling appartenance 8, equipped with a non-return valve 9. Manifestly, the said conduit 5 is adapted to conduct the gasolene or other liquid from the interior of the tank 1 to the internal combustion engine or other point of use.

Inclosing and spaced from the tank 1 is the revoluble protection member 10 of my novel container. The said container `10 is chambered as indicated by 11, is provided with inner and outer spaced walls 12 and 13, isy equipped in its outer Wall 13 with a valved induction conduit 14, and ispro-` revoluble member may be quickly and easily turned about its axis as occasion demands. It will also be manifest here that the revoluble protection member 10 is adapted t0 be turned by the impact of a bullet or the like, and that this capacity of function is important in enabling the protection member to prevent leakage of gasolene or other liquid from the container. The walls 12 and, 13 of the protection member `10 are formed of light fireproof fiber, or soft metal or steel in the discretion of the manufacturer of the container. The said Walls 12 and 13 o f the revoluble protection member are each lined ,with a seamless coating 20 of pure rubber combined with four (more or less) layers of fabric consisting of thin rubber sheets andf closely woven textile, generally similar in character to the casings of Wheel tires. In the chamber 11, lined as specified, is disposed a. seamless rubber tube 21, generally similar to the inner tube of an 1nflatable tire. The said tube 21 is connectedl 4 With the inner end of the induction tube 14 hereinbefore alluded to. At this point I Would have it understood that I contemplate forcing through the induction tube 14 and into the rubber tube 211a small quantity of fire and cold-proof rubberA liquid cement, indicated by 22. Sufficient of the liquid cement is employed to fill the bottom space of the tube in the chamber 11'.

I't Will be manifest from the foregoing that in the event of the protection member that my novel protection member 10 is calculated to efficiently guard the container 1 against the puncture or other injury, but, if, for any reason, leakage takes place from the container 1, the liquid that escapes-Will be caughtl and retained in the protection member 10, and consequently there Will be no liability of such liquid causing a fire or explosion.

.claim and desire to secure by Letters Patent, 1s: l

l. The combination of a liquid container, and a revoluble protection member inclosing and spaced from said container; said revoluble protection member comprising inner and .outer spaced Walls, a valved induction tube in the outer Wall, linings at the inner sides of said Walls, an inflatable tube disposed between the Walls and connected to the induction tube, and liquid cement in said inflatable tube.

2. The combination of a liquid container,

ya shaft extending from one end thereof, a

conduit member extending through the op- I-Iaving described my invention, What I l posite end of the container and communieating With the interiorvthereof, a revoluble protection member inclosing the liquid container and mounted to turn about the shaft and conduit member, and mobile means in `the revolublemember to automatically healv punctures therein. d y

3. A fuel tank comprising a fuel container, a revoluble protection member surrounding and spaced from the container, and mobile means in the revoluble protection member to automatically heal punctures therein.

In testimony whereof I afix my signature. LAUREAT L. MARTINEAU.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2482366 *Apr 20, 1945Sep 20, 1949Republic Aviat CorpSelf-sealing oil tank
US2884978 *May 15, 1957May 5, 1959Bruce F GrimmCollapsible fuel tank
US3132762 *Jun 9, 1960May 12, 1964Union Carbide CorpApparatus for dispensing liquefied gases
US6889940 *Jan 29, 2004May 10, 2005The Boeing CompanyAuxiliary fuel tank systems for aircraft and methods for their manufacture and use
US7040579Jan 24, 2005May 9, 2006The Boeing CompanyAuxiliary fuel tank systems for aircraft and methods for their manufacture and use
US7051979Jan 29, 2004May 30, 2006The Boeing CompanyAuxiliary fuel tank systems for aircraft and methods for their manufacture and use
US7357149Jan 29, 2004Apr 15, 2008The Boeing CompanyAuxiliary fuel tank systems for aircraft and methods for their manufacture and use
US7357355May 8, 2006Apr 15, 2008The Boeing CompanyAuxiliary fuel tank systems for aircraft and methods for their manufacture and use
US7568660May 26, 2006Aug 4, 2009The Boeing CompanyAuxiliary fuel tank systems for aircraft and methods for their manufacture and use
US8846382 *Jul 31, 2007Sep 30, 2014Oliver MueckeAirlift bioreactor
Classifications
U.S. Classification244/135.00R, 137/375, 428/912, 220/900, 137/581
International ClassificationB64D37/06
Cooperative ClassificationB64D37/06, Y10S428/912, B64D2700/6235, Y10S220/90
European ClassificationB64D37/06