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Publication numberUS2420292 A
Publication typeGrant
Publication dateMay 13, 1947
Filing dateOct 23, 1942
Priority dateOct 23, 1942
Publication numberUS 2420292 A, US 2420292A, US-A-2420292, US2420292 A, US2420292A
InventorsBaer John M, Heineman Arnold H
Original AssigneeGuardite Corp
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Airplane body
US 2420292 A
Abstract  available in
Images(3)
Previous page
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Claims  available in
Description  (OCR text may contain errors)

May 13, i947. J; M. BAER :TAL 2,420,292

AIRPLANE [BODY:

Filed 9ct. 23, 1942 3 Sheets-Sheet 1 Jig-QJ.

May is; 1947.

J. M. BAER EI'AL AIRPLANE BODY Filed ot. 25, 1942 3 Sheets-Sheet 2 May 13, 1947- J. M. BAER Erm.

AIRPLANE BODY s shets-sheet s- Filed Oct. 23, 1942 jfzk'gf.

Patented May 13, 1947 AIRPLANE BODY John M. Baer and Arnold H. Heineman, Chicago, Ill., assignors to The Guardite Corporation, Chicago, Ill., a corporation of Illinois Application October 23, 1942, Serial No. 463,032

2 Claims.

This invention relates to improvements in airplane body or fuselage.

Among the features of our invention is the provision of a strong rigid body adapted to withstand excessive internal pressure. Consequently, the invention is well adapted for use in airplanes designed for high altitude flying where the pressure inside of the body or cabin is considerably higher than the atmospheric pressure at such altitudes.

Another feature of our invention is the provision of a body that can be easily and cheaply made.

Other features and advantages of our invention will appear more fully as we proceed with our specication.

In those forms of devices embodying the fea tures of our invention, shown in the accompanying drawings, Fig. 1 is a view in side elevation; Fig. 2 is a fragmentary vertical sectional view; Fig. 3 is a view taken as indicated by the line 3 of Fig. 2; Figs. 4 and 5 are enlarged vertical sectional views showing a modied form of construction; Figs. 6 and 7 are similar vieWs showing another modification; Figs. 8 and 9 are similar views showing another modification; and Figs. 10, 11, 12 and 13 are similar views each showing an.. other modification.

For the purpose of illustrating the invention it is assumed that the body is circular in transverse cross section and that it has a short forward tapering portion, a main cylindrical portion, and a longer rear tapering portion. It is obvious, of course, that the transverse sections, instead of being circular, could be oval, ovaloid, elliptical, or any other desired shape. For example, the transverse Vertical sections could even be square or polygonal. It will serve to illustrate the invention, however, to assume here that they are circular.

In general, the body comprises a plurality of ring shaped channel members placed side by side, alternating members having their anges turned inwardly, and the intermediate members having their flanges turned outwardly, the adjacent flanges of adjacent members being fastened together, as by welding. In Figure l, the rings are indicated by i9 and Ilia., alternating with each other. Each ring is formed of a channel. 'Ihe rings I have the ilanges Il, il turned outwardly, whereas the rings la have the flangeslla, lla turned inwardly. In order to form the tapers, each ring is somewhat tapered. This is shown more clearly in the enlarged views, Figures 4 and 5. Figure 4 is a section of the cylindrical por-1 tion, whereas Figure 5 is a section of the tapered tail portion. We have not shown the welding in all the views as this is unnecessary, but we have indicated it in a few places in Figure 4 by the reference numeral l2. Riveting or other fastening means may be used.

i3, i3 indicate cover plates enclosing the spaces formed between the flanges of the channels and these spaces thus enclosed by the cover plates are preferably filled with compressed sealing material I4 which, for example, may be sponge rubber, or some material adapted automatically to seal holes that might be formed in the shell by bullets. For example, rubber partially dissolved in some solvent that will quickly evaporate upon exposure to air could be used. As long as the material is sealed against the air it will remain soft, but, if a hole is formed, as the material oozes through the hole, the solvent will dry, causing the hole to become clogged.

The construction shown in Figures 6 and 7 is substantially the same as above described, except that the channels IIB and Illia are more nearly in registry so that when the cover plates H3 are placed against the edges of the anges III or Illa, they will be flush with the webs of the adjacent ring members.

The construction shown in Figures 8 and 9 is similar to that shown in Figures 1 to 5, except that the flanges 2| l on the channels 2 I0, and the flanges Zlia on the channels 2llla, instead of being parallel and lying at right angles to the web, flare outwardly from the web.

In the device of Fig. l0 we have employed E sections; that is, each of the channels 3H) and 3 l [la has a center stiffening rib 3 I 5,

In the device of Fig. 11 the channels 4 Illa, Mila all face the same way and are preferably spaced a short distance from each other as shown. The open sides of all these channels may be covered by a single plate `M3 and the spaces between the channels may be closed by the smaller plates 4iso.

In the device of Fig. l2 we'employed Z sections 5H! and Silla, as shown, which have their adacent ilanges 515 and 5I 5a overlapped and welded, as shown. The spaces between these Z sections are closed by the closure plates 5|3.

The device of Fig. 13 is similar to that shown in Fig. l2 except that the webs 6H of the Z sections are parallel instead of ared.

In all of the forms it will be seen that there is formed virtually a double wall with partitions or bulkheads, leaving spaces between. As mentioned above, these spaces may be lled with com- 3 pressed sealing material I4. This material may be sponge rubber or similar cellular material. If such material is put in these spaces at atmospheric pressure substantially at sea level, it will follow that if the plane ascends to a higher altitude Where the atmospheric pressure is much lower, that the sponge rubber or similar material in the spaces between the walls will be under considerableN pressure. That is, the pressure in the cells will be considerably higher than the atmospheric pressure outside at that altitudet Consequently, if the wall be punctured at` that altitude, as by a bullet, the sponge rubber inside will immediately expand and' iflll the hole; In

the same way, other sealing materia-Is may be employed in the spaces in the Walls; It would also be possible merely to put ini the spaces some;

material such as partially cured rubber or rubber partially dissolved in some solvent that will quickly evaporate upon exposure to air. If some 515` thisfmateriali be: putinto the spaces when the plan'e1s1on the ground, forA example substantially atA sea level', andf the spaces then closed; it will follow that". at a higher altitude the air confined intthe; spaces will' be under considerable pressure. Therefore, if a hole be made-in the: wall at such higher altitude` as by the bullet, the air under pressure at; such' an altitude will tend to escape through the hole intovr the atmosphere and force the' sealing: material into the hol'e. Suchl sealing material being therebyA exposed to additional drying air; will' become hardened and' seal the hole; or the mere air pressure inside will probably'force any more or' less soft, plastic, or granularsealln'g material. into the hole to'seal thesame.

The foregoing detailed description has been givemfor cl'earness of understandingY only, and no unnecessaryv limitations should be understood therefrom.

What we claim as1 new, andA desired to secure b'y Letters Patent;L is:

1, A sealedY airplane fuselageA comprising: a

4 plurality of annular channel members, each of said members being constructed of a single piece of metal and comprising anges and a connecting web, said members being secured together at their flanges in abutting relationship, alternate members having their anges turned inwardly and the intermediate members having their flanges turned outwardly; and a separate cover plate secured to each' of the members atthe base of the flanges, said cover plates covering each of the openings between said iianges to form a smooth inner. and a smooth outer wall whereby said fuselage is capable of withstanding large internal pressures.

2. The fuselage of claim 1 in which the base of said ilanges is-in contact with said cover plate.

JOHN M. BAER. ARNOLD H. HEINEMAN.

REFERENCES CITED Thefcllowing references are of record in the le of this patent:

UNITED ST'IES P'I'ENTS Number' Name' Date 1,460,372A Dornier July 3, 1923 1,533,285? Verville Apr.. 14, 1925 1,965,258 Ragsdaler .July 3', 1934 1,949,787 Dugan Mar. 6, 1934 1,933,861 Kjekstad Nov. 7, 1933 2,104,144 Zandl Jan. 4', 1938 994,116 Boyer'. V June 6, 1911 2,116,020 Gauvin May 3, 1938 1,866,534Y Janin July 12, 1932 1,622,242 Taylor et' al. Mar. 22, 1927 FOREIGN PATENTS Number Country Date 278,372 Great Britain Jan. 26. 1928

Patent Citations
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Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2668606 *Jun 9, 1948Feb 9, 1954Jacksonville Steel CompanyFabricated steel beam
US2784411 *Jan 17, 1955Mar 12, 1957Egleston Aun KAnklet
US2817484 *Jan 8, 1954Dec 24, 1957Mach Tool Works Oerlikon AdminSelf-supporting shell for flying body
US2956652 *Aug 15, 1958Oct 18, 1960Liskey AluminumElevated false floor
US3025935 *Apr 2, 1958Mar 20, 1962Lockheed Aircraft CorpUnicore panel constructin
US3064317 *May 12, 1959Nov 20, 1962North American Aviation IncDouble wall construction
US3093346 *Oct 16, 1959Jun 11, 1963Blanchard Jr Willard SSpace capsule
US5560102 *Oct 13, 1992Oct 1, 1996The Boeing CompanyPanel and fuselage assembly
US5586391 *Jun 6, 1995Dec 24, 1996The Boeing CompanyMethod of making airplane fuselage
US5615483 *Jun 6, 1995Apr 1, 1997The Boeing CompanyMethod of assembling parts on an aircraft skin to form a panel
US5649888 *Jun 6, 1995Jul 22, 1997The Boeing CompanySystem for making a panel
US5694690 *Jun 6, 1995Dec 9, 1997The Boeing CompanyMethod of making large airplane structures
US5806797 *Nov 1, 1995Sep 15, 1998The Boeing CompanyAirplane fuselage
US6003812 *Jun 6, 1995Dec 21, 1999The Boeing CompanyAirplane fuselage panel
US7059034 *Nov 14, 2003Jun 13, 2006Toyota Motor Sales, U.S.A., Inc.One-piece closed-shape structure and method of forming same
US7431239Nov 14, 2003Oct 7, 2008Toyoto Motor Sales, U.S.A., Inc.One-piece closed-shape structure and method of forming same
US8573538 *Jan 30, 2008Nov 5, 2013Airbus Operations S.L.Impact resistant aircraft fuselage
US8939405 *Jun 19, 2009Jan 27, 2015Airbus Operations S.A.S.Aircraft fuselage element
US9359061 *Oct 31, 2005Jun 7, 2016The Boeing CompanyCompliant stiffener for aircraft fuselage
US20040118977 *Nov 14, 2003Jun 24, 2004Toyota Motor Sales, U.S.A., Inc.One-piece closed-shape structure and method of forming same
US20040188025 *Nov 14, 2003Sep 30, 2004Toyota Motor Sales, U.S.A., Inc.One-piece closed-shape structure and method of forming same
US20070095982 *Oct 31, 2005May 3, 2007The Boeing CompanySingle piece fuselage barrel
US20090140096 *Jan 30, 2008Jun 4, 2009Airbus Espana, S.L.Impact resistant aircraft fuselage
US20110180665 *Jun 19, 2009Jul 28, 2011Airbus Operations (S.A.S.)Aircraft fuselage element
Classifications
U.S. Classification52/561, 52/404.1, 52/574, 244/119
International ClassificationB64C1/00, B64C1/06
Cooperative ClassificationB64C1/061
European ClassificationB64C1/06F