US1951353A - Method of and apparatus for strengthening the framework and the covering of airships - Google Patents

Description

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G. FULTON March 20, 1934.

METHOD OF AND APPARATUS FOR STR FRAMEWORK AND THE COVERING OF AIRSHIPS Filed Nov. 14, 1929 ATTORNEY March 20, 1934. G FULTON 1,951,353

METHOD OF AND APPARATUS FOR STRENGTHENING THE FRAMEWORK AND THE COVERING 0F AIRsHIPs 1929 4 Sheets-Sheet 3 Filed Nov. 14

ANA.

ATTORNEY 1,951,353 ENGTHENING THE 1929 4 Sheets-Sheet 4 March 20, 1934. G, FULTON METHOD oF AND APPARATUS FOR sTR FRAMEWORK AND THE covERING oF AIRsHIPs Filed Nov. 14

/NVENTOR Gar/anal Fulon BY RMDUSQM ATTORNEY Patented Mar. 20, 1934 UNITED STATES PATENT OFFICE Garland Fulton, Cincinnati, Ohio Application November 14, 1929, Serial No. 407,086

33 Claims.

(Granted under the act of March 3, 1883, as

amended April 30, 1928; 370 0.

My invention relates to a method of and apparatus for airships, and more particularly applies to the outer covering of airships.

Heretofore it has been the practice to cover 5 airships with cloth in sections tailored to conform to the various shaped frame interstices which said covering is desired to convert into a suitable streamline contour and to secure the edges of each piece of said fabric to the frame or other portions of the airship by lacing or other suitable means.

This covering has been free to vibrate. This yvibration which is caused mainly by the air currents encountered more intensively in flight, tends substantially to weaken and ultimately destroy the fabric and increase resistance of the airship through the air, and also tends to set up vibrations in the frame members. These frame vibrations so induced tend to weaken the frame structure as Well as to cause its premature crystallization.

Heretofore various attempts have been made to employ a thin metal covering extending over the entire outer surface of airships but dimculties have been encountered which rendered such attempts impraoticable. These difficulties have arisen from diiferent causes. For example, Where rivets were employed to secure the metal sheets to the frame structure, the vibration of the sheets has torn them from the rivets. This vibration of such metal sheets'has occasioned very substantial rattling as well as the Vibrations and their effect heretofore stated in connection with the cloth covering.

In connection Withl the employment of thin metal as such complete outer covering attempts have also been made to prevent the vibration of each of the numerous metal sheets comprising such complete outer covering by going to the extreme of confining air under pressure upon and extending throughout the inner surface of such metal covering so that such pressure would substantially prevent the vibration of such metal covering and its component sheets; but this involves more or less fundamental vchanges in design and construction of the airship and requires additional apparatus, and the weight incident thereto, for maintaining such pressure, besides such an expedient is inapplicable to the outer cover of the so called rigid type of airship to which my invention may be applied.

Heretofore the outer coverings for airships have not in any sense tended to strengthen the airship structurally.

The panels of the outer covering of airships are, for the most part, very large in area with extensive portions substantially unsupported and free to vibrate. Such vibratory areas of such covering have heretofore also been substantially straight and uncurved which increased their tendency to vibrate.

The object of my invention is to provide a method of and apparatus for airships which not only enables strength of the outer covering to augment the strength of the frame structure and 05 to substantially prevent the vibration of the component parts of the outer covering, but which also obviates the heretofore stated effects of such vibration. The further object of my invention is to obtain a more durable and weather-proof outer 10 covering affording minimum resistance to the air and to maintain such covering substantially free from vibration and resilience.

To obtain these and other objects and in accordance with the general features of this unitary invention of related and interdependent components, my improved method contemplates imparting strength of the outer covering of the airship to the frame structure thereof by securing each, or a plurality, of the portions of the outer coverings to the frame structure at a plurality of points' at, as Well as Within, the edges of such panel or panels comprising portions of the outer covering, and further contemplates the substantial lessening of the resistance and of vibrations of the outer covering of the airship by securing the same, or panels or portions thereof, to a relatively more rigid structure, such for instance as the frame structure, at a plurality of points at, as Well as Within, the edges of each, or a plurality, of the panels of the outer covering; and further contemplates that a plurality of said securements shall be rigid, such for instance as rigid brace members, and further contemplates ,that Where metal to metal securements Aoccur of the outer covering to the frame or other convenient relatively more rigid portion, non-metal or fabric may be interposed between all juxtaposed metal portions of such securement to insulate vibrations and obviate the resonance of the metal portions of the outer coverings of the airship.

In said attainment and accordance my improved method further contemplates increasing the durability, efficiency and Weather-proof characteristics of the outer covering, as Well as to substantially decrease the normal tendency of all metal panels or portions of the outer covering of airships to transmit to frame members their normal intensive or accelerating ight vibrations by interposing metal and non-metal or fabric in such 1W outer covering; and further contemplates that the metal and the non-metal or fabric occupy different contiguous areas or planes in the formation of the o-uter covering, or each or any panel or portion thereof; and it furthermore and more specifically contemplates that the non-metal or fabric portion or portions of the outer covering, or each or any panel thereof, may be interposed between the metal portion of the outer covering and the frame or other members to which the same are secured.

Further contemplations of my said method and of the various steps thereof will be made more apparent from the hereinafter description and claims.

To demonstrate the practical utility of my said method, a related, improved and novel apparatus is provided embodying my invention and which may be used advantageously and economically in practicing said improved method as an unitary invention. Such provided apparatus also serves as an example, to those skilled in the art, of the facility with which, after becoming familiar with my invention, the many forms and kinds of existing apparatus, with or without substantial modification, may be employed in the efiicient practice of my said method.

Said provided apparatus and the foregoing and other objects of my invention will each be more apparent from the following detailed description and the accompanying drawings illustrating one embodiment of my invention in an improved apparatus of the many forms .and characters of apparatus, each of which may be employed in the 'Ir practice of my improved method.

In the drawings in which like characters of reference denote the same parts, Fig-ure 1 is a plan View of one of the very large portions or panels of an airships outer covering embodying my invention and in which a portion of the outer covering is broken away to illustrate parts beneath.

Figure 2 is a sectional View on line 2-2 of Figure 1, and illustrating frame members in their relative position in one type of airship.

Figure 3 is a sectional view on line 3 3 of Figure 1 and illustrates other frame members in their relative positions in one type of airship.

I Figure 4 is an enlarged plan detailed View of a very small portion of one of the vertical edges of Figure 1 and' shows a corresponding portion of an abutting outer covering panel.

Figure 5 is a sectional view on line 5--5 of Figure 4.

Figure 6 is a sectional view on line 6 6 of Figure 4.

Figure 7 is an enlarged sectional elevation view on line 7 7 of Figure 1.

Figure 8 is an enlarged end View of one of the outer covering brace members, substantially on` line 8 8 of Figure 7.

Figure 8a is a perspective View of an optional modification of the rigid brace member 32 shown i in Figure 8.

Figure 8b is a fragmentary sectional View on line 8b--8b of Figure 7.

Figure 9 is a view similar to Figure 4 but illustrating optional details of construction. Figure 10 is a sectional elevation on lines 10-10 of Figure 9.

Figure 1"1 is a View similar to Figure 9 but illustrating other optional details of construction. Figure 12 is a sectional View on lines 12-12 of Figure 112.

Inasmuch as airshipsare of diierent general designs and constructions in which diierent frames may be employed, I have not shown any of the framework except the longitudinalV and transverse frame members which are directly associated with the outer covering. 21 represents the longitudinal ones of such frame members and 22 the transverse ones of such frame members. In the instance shown, the frame members 22 are arranged so that their outer surfaces are slightly beneath the exterior portions of the frame members 2l and the projecting outer surfaces of the members 21 are provided as shown more clearly in Figure 7 with a plurality of eyelet openings 23 in each of which openings are mountedL eyelets 24.

At points in the length of the frame members 21 at which it may be desired to establish as the length of the different panels or portions of the outer covering, wires 25 are suitably secured to and extended between each or a plurality of the members 21.

Each panel or portion of the outer covering of the airship is tailored to t into the bay or areas defined between selected rows of eyelets 24 and between wires 25.

In the practiceof my method the outer covering may be constructed in various ways by those skilled in the art after becoming familiar with my method. In the instance shown in the drawings, the panel or panels of the outer covering are constructed of a plurality of relatively long sheets 26 of very thin metal whose edges overlap, and these overlapping edges are secured together by a plurality of rows of stitching or rivets 26', or by any other convenient or suitable securing means. Any number of said strips 26 may be secured together to form a desirable area of this metal covering. To each of the outer edges of the joined strips 26 are secured fabric strips 27. Figure 1 shows the panel having two all metal areas and therefore contains three longitudinal strips 27, the central one of which is secured at its opposite edges to the respective edges of the metal panels formed by said united sheets 26. Adjacent the outer edges of the outer strips 27 are formed a plurality of eyelet openings each preferably containing eyelets The eyelets 24 and 28, in the instance shown in Figures 1, 4, 5, and 7 are secured by lacing 29 along the upper and lower edges of Figure 1, while the vertical edges of Figure 1 have their eyelets 28 similarly secured to their respective lacing wires 25. Said lacing 29 may be drawn up to the extent desired to give the requisite tension resiliently distributed throughout the edges and area of the panel or portion of the outer covering comprised within the limits of the eyelets 28.

In the instance shown in Figures 1 and 2, one panel of thev outer covering is secured at its opposite side to every other one of the frame members 21 so that the central portion of said panel is stretched over the interveningl frame member 21 whose outer surface is in contact with the central fabric strip 27.

It will therefore be understood that the intensive or accelerating flight vibrations to which the outer covering of the airship is subjected will not be harmfully communicated from the metallic portions 26 of the outer covering panel to either the frame members 21 or 22 because of the fabric strips 27 interposed between said metal sheets 26 and said frame members 21 and 22, the nonmetallic or fabric strips 27 insulating such vibrations from the frame members.

It will furthermore be understood that the overlapping edges of the sheets 26 upon each other, as well as of the sheets 2By uponthe nonme'tallic or fabric strips 27, afford' reinforced areas which not o-nly tend to lessen the vibrations but afford as well an extremely light and far more durable and weather-proof covering which is-substantially free from resilience.

Before as well as after eachpanel has been secured in place, the same may be treated by dope or other suitable material and after being secured in place and preferably before the nal exterior application of dope or other suitable material a sealing strip 30, Figures 4, 5g 9 and 1l, applied over the joint between the edges of the respective panels of the outer covering and over the securing lacing 29' thereof so as tol render each such joint weather-proof.

Aluminum or other paint or suitable protective material may be applied to the whole or desired portions of the exterior or outer covering of the airship, which not only adds to the external appearance but increases the Weather-proof qualities of the material as well as of the joints and decreases air resistance.

Secured to the outer edges of convenient portions of the framework are preferably taut wires 31, Figures l, 2, 3, 'l and 8. Said wires 31 are preferably arranged in diagonal rows, each row extending at an angle substantially opposite that of the other row. To each of said wires 31 is suitably secured a preferably rigid brace member 32 occupying the space between the covering and the bracing 311 and whose outer ends 33 are increased to substantial area and suitably secured to the under surface of the outer covering 35 which is formed in the instance shown' in Figures l and 2 of the strips26 and 27. The members 32 are preferably of thin, very light metal and where outer edges 33 are secured to the metal strips 26, non-metallic or fabric portions 34 are interposedl between allv juxtaposed metal portions of such securement to still further insulate vibrations and obviate the sonic resonance of the metal outer covering.

Should variations occur in the distance between wires 3l and the outer covering, due to the varying of the fore and aft diameters of the` airship in streamlining and otherwise, or for convenience in assembly, the optional construction of rigid brace number 32 shown inv Figure 8a may be employed in which tubular member 32a, having vertical flanges 32h, is adapted to clamp each wire 31. T-shaped member 32e, which may be formed either of a T bar or a formed sheet of metal, having the web- 32d doubled, is adapted to be secured between the flanges 32h byi rivets, or otherwise, after having any surplus metal trimmed therefrom where necessary to conform to the distance between wires 3l and the outer covering and have the inner edge of web 32d bear against its wire 31. The anges 330i` are adapted to be secured to the outer covering as shown in Figure 8.

At points where the wires 3l cross each other' i the members 32 terminate and at their ends are provided with suitable flanges or separate angle clips 36 which are riveted or otherwise desirably secured to their adjacent members 32.

It will be observed that the rigid members 32', being thus secured to and extending between portions of the framework, such as the wires 31 for instance, and the outer covering at a plurality of points within the area of the panels forming the outer covering, substantially prevent vibration of the outer covering as Well as join at frequent intervals the outer covering andthe framework so that each supplenfients the strength of the other.

Formerly the vibration of the outer covering exerted a leverage action on` the frame members, which* was l'iarrnfull to the frame structure. My invention eliminates suoli leverage action, as well as substantially evenly distributes over the framework the stresses of the varying forces.

Where the eyelets 28 are located, as well as where the edges of the strips 26 are secured to the strips 27, the strips 27 when of fabric or other very light material preferably have their edges folded back to'reinforce the fabric at such secured points.

In the instance shown in Figures 9 and l() the panels, or some of them, comprising' the outer covering of the airshipare formed of metal preferably extending throughout the entire area of the outer surface of each such panel. Each such panel may be formed of the strips 26 overlapping at their adjacent edges and secured' together as heretofore explained, or thev same may otherwise be formed. The eyelets 28a formed about the edges of each such panel are preferably of non-metallic insulating material. Looped spring wires 40 are secured on opposite sides of the respective lacing wires 25a by bands 40a while the opposite loops of wire 40 are secured to eyelets 23a by bands 40h,

In the instance shown in Figures 1l andV l2 the panels may be constructed as shown and described in connection with either Figures 1 and 2 or 9 and l0, but instead of their respective lacing 29 and 40 a lacing comprising a plurality of flat coiled springs 4l is employed' with the opposite hooked ends 42 of each of said' springs 41 passing through their respective eyelets 23a and the lacing wire 28h.

The lacing of Figures l', 4, 5, and 7 distributes the securing strain among the eyelets through which the lacing extends, while the spring securements of Figures 9, l0, 11, and 1:2 distribute the securing strain among the eyelets by the resiliency of the springs.

Respecting the lacing shownl and described: in

connection with Figures l, 2, and 7, when the lacing is first applied the panels are of the requisite degree of tautness but when there exists any stretching in either the lacing or the panels or both there is a tendency for the panels to be'- come loose at their edges but by reason of thesecure'ment of the panels at a plurality of points intermediate their edges toa corresponding plurality of points upon the framework *or asso'- ciated with the framework, the panels are held substantially in place. The instances shown in Figures 9 toA 12 inclusive overcome the lstretching tendency of the lacing 29 bythe employment of the respective springs 40 and 4:1 to maintain the requisite degree of talutness throughout the areas of the panels comprising the outer covering,

kThe strips 2'5l preferably extend longitudinally of the airship so that the overlapping edges of such strips may not tend to increase the resistance of the air to the covering.

The panels, composed for instance of the strips 25 and 27', are secured at their edges to the framework by securements which render eachI panel taut. These panels are of such substantial areas and are liable to encounter such varying air pres-- sures and velocities as would tend to bow each panel1 inward and thus increase the air resist-Y ance of the' outer covering. Variations in such pressures and velocities would cause inward vibrations of substantial magnitude of such panels.

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In flight, as well as in substantial air velocities, such vibrations would be likely to be of high and accelerating frequencies which would produce substantial noises, be communicated to the frame Work, and substantially tend to lessen the efiiciency and durability of the panels as well as of the framework. Such vibrations would require that the panels as well as the framework be constructed of greater strength which requires greater weight. Weight is a critical factor in airships which must be lighter than the air which their lifting gases displace.

From the foregoing it will be understood by those skilled in the art that my invention overcomes this tendency of the panels to inward vibration by the step of my method and the part of my apparatus which, secures the taut panels substantially rigidly to the airship at a plurality of points Within the areas of the normal securements of said panels.

It will also be understood by those skilled in the art that the panels are each secured to the airship at the required degree of tautness by the normal panel securing means and that the taut panels are then rigidly secured to the airship at a plurality of points within the areas of each of their normal securements and that said rigid securements increase as well as maintain the tautness of the panels and obviate any increased resistance of the panels to the air by maintaining each of the same in their respective predetermined planes or positions, as well as prevent the inward as well as the outward vibrations of the panels intermediate their usual edge securements.

It should also be appreciated that in airships the large area of each of the covering panels and the essential requisites, including that the structure be lighter than the air which its lifting gases displace, preclude the strengthening of the outer covering merely by cambering or otherwise shaping it. This increased the difliculties overcome by my invention.

It will further be understood by those skilled in the art, that the non-metallic or fabric jportions 27, interposed between each of the various metal portions 26 of the outer covering panels and the framework, tend to insulate from the framework the static. electricity which may be formed upon the outer covering; and that the metallic meansv which fasten each of the flanges 33 of each rigid brace member 32 to the strips 26 and '27 of the outer covering will -act as conductors of the static electricty liable to accumulate upon the outercovering and conduct such static electricity through the metallic members 32 and wires 3l to the metal frame, thereby grounding such static electricity upon the framework at frequent intervals throughout the area of the outer covering of the airship.

It will also be understood from the foregoing by those skilled in the art that in highl relative wind velocities, and hail and like conditions, large accumulations of static electricity will be present on the outer covering and the frame; that such static is liable to leap from the outercoverings,

. and repeated such leaps from the same spot are likelyv to pit and ultimately pierce the very thin metal of the outer covering; that the wire stitch-l ing or rivets securing the strips or sheets 26 or 27 together, as well as the rivets securing the rigid brace members 32 to such sheets 26, each constitute slight projections from the surface of such sheets, and when static electricity leaps it will normally tend to leap'from' said frequent projections disposed over the outer surface and substantially tend to obviate the pitting and piercing of the outer covering.

From the foregoing it will be apparent that by my method and its exemplifying apparatus a stronger, more efiicient and durable airship and covering therefor will be obtained. y

The invention herein described may be manufactured and used by or for the Government of the United States for Governmental purposes Without the payment to me of any royalty thereon or therefor.

Having now so fully described my invention that others skilled in the art may make and use the same therefrom, what I claim and desire to secure by Letters Patent is:

1. The method of strengthening the framework and covering of an airship wherein the framework and covering are in panels, comprising securing a covering panel at the edges to a frame panel, holding rigid against inward and outward movement at a plurality of separated points intermediate portions ofthe secured covering panel, and connecting substantially rigidly to the frame said held portions of the covering panels.

2. The method of strengthening the framework and covering of an airship wherein the framework and covering are in panels, comprising securing a covering panel at the edges to a frame panel, holding rigid interior portions of covering panels in diagonal lines; and connecting said held portions of the covering panels substantially rigidly to the frame at points which may be substantially intersected by extensions of said diagonal lines.

3. The method of covering an airship having a frame and covering in panels, comprising the steps of forming, alternating in a covering panel areas of metal and non-metal, securing the covering panels at their edges to frame panels, holding rigid portions of the metal areas of a covering panel, and connecting substantially rigidly to the frame said held portions of the covering panel.

4. The method of covering an airship having a metallic frame in panels, comprising the steps of alternating metal and non-metal component areas of the covering with the non-metal areas juxtaposed to metallic portions of the frame, securing definite portions of the covering taut over a frame panel, applying and maintaining an outward stress against interior portions of the secured area of the covering for increasing the initial tautness of the secured area of the covering, and connecting rigidly to the covered frame panel, the stressed portions of the covering for strengthening and lessening destructive vibration of the frame and covering.

5. The Amethod of controlling static electricity accumulating upon the outer surfaces of aircraft having a frame comprising the steps of interposing connected portions of a thin covering between the outer elements and all outer portions posing connected portions of a thin covering between the outer elements and all outer portions of the frame, extending electrical terminals through and projecting the same from the outer surface of the covering at intervals throughout the extent of the covering, electrically connecting said terminals together, collecting upon the covering electrical energy from the action of the outer elements upon the outer surface o the covering, collecting upon the terminals the Venergy collecting upon adjacent portions of the covering, equalizing substantially the energy collecting upon the connected terminals, and discharging said energy only outwardly from the outer surface of the terminals to the outer elements.

7. In an airship the combination with a frame having openings, taut wires extending diagonally across said openings and secured to the frame, a covering formed of separate panels-each adopted to-extend over only a relatively small portion of the length and breadth of the -ship to be covered thereby, means for securing each of said panels taut to the frame and over one or more of said openings, of means in said openings for substantially rigidly, laterally and relatively immovably connecting at a plurality of points the Wires and one or more o1" said panels.

8. In an airship the combination with a frame formed in panels, wires extending across and connected to said frame panels, a covering therefor, means for securing the covering taut upon said frame, and means extending between the covering and a plurality of said wires for substantially rigidly laterally and relatively immovably connecting the wires and the taut covering at a plurality of points intermediate said securing means.V

9. In an airship the combination of a frame having openings, taut wires extending across said openings and secured to the frame, a covering formed of separable panels, means `for securing each of said panels taut to the frame and over one or more of said openings, and rigid means in said openings and extending from the wires to the panels for-exerting an outward stress upon and increasing the tautness of said panels.

10. In an airship the combination of a vframe having openings, taut wires extending across said openings and secured to the Vframe, a covering formed of separable panels, means for securing each of said panels taut to the frame and over one or more of said openings, and means in said openings for rigidly connecting each of said wires to the covering panels. 1

11. In an airship the combination of a frame having openings, taut wires extending across said openings and secured to the frame, a covering formed of separable panels, means for securing each of said panels taut to the frame and over one or more of said openings, and means including rigid metallic connections secured to said wires and panels for substantially decreasing the sonic resonance of said panels.

l2. In an airship the combination of a frame having openings, taut wires extending across said openings and secured to the frame, a covering formed of separable panels, means for securing each of said panels taut to the frame andover one or more of said openings, and means consisting of separate metallic portions secured together and to said lwires and panels for increasing the tautness and preventing the relative movement of said panels and frame po-rtion intermediate said securing means.

13. In an airship the combination of a frame having openings, taut wires extending across said openings and secured to the frame, a .covering formed of separable panels, means for securing each of said panels taut to the frame and over one or more said openings, of means consisting of a relatively long rigid member secured to each of said wires and the adjacent panel for increasing the tautness and substantially reducing relative movement .of the frame and the portions or" said panels intermediate said securing means, and means for substantially .decreasing the sonic resonance of said panels.

14. In an airship the combination of a frame having openings, taut wires extending across said openings and secured to the frame, a covering formed of separable panels, means for securing each of said panels taut to Vthe frame and over one or more of said openings, means `consisting of a 'relatively long rigid member secured to each of `said wires and having a broad head secured to the adjacent panel for increasing the tautness and preventing the vibration of said panels intermediate said securing means, and means intermediate said panels and said last named means for substantially decreasing the sonic resonance of said panels.

l5. Ina dirigible, the combination of a frame, an outer covering completely enveloping and protecting said frame from the outer elements and adapted to collect electrical energyirom the action ofthe elementsupon its outer surface, a plurality of metal portions mounted upon andvexposed `at intervals throughout the vextent ofthe outer surface of the covering for collecting thereon the electric energy collecting on the covering adjacent thereto, and means for electrically connecting together a plurality of said metallic portions, whereby said energy collecting on the covering in the regionof said Vportions may be equalized between said connected portions and discharged only from the outer surface of said metallic portions directly to the outer elements without liability of injuring or puncturing the covering.

16. In an airship the combination of a metallic frame having openings in its outer sur-face, an outer covering forvsaid frame comprising a plurality of relatively small metallic areas sep'- arated by non-metallic areas, means for securing aplurality of areas of said covering to said frame, and means for electrically connectingtogether a plurality of said areasof covering and discharging static therefrom harmlessly tothe atmosphere at one or more points within the area of the covering intermediate said securing means.

17. A means for connecting an airships covering tothe frame, including a substantially rigid metallic member, having a relatively long surface adapted to be brought into rigid engagement with a portion of the frame, Va relatively long `head adapted to bear `against the Virrner surfaceof thecovering and provided withmeans for facilitating the rigid engagement of vsaid .head with said covering and a connectionrigidly uniting said member and head together.

18. A means for connecting an airships covering to the -framaincluding yasubstantially rigid metallic member having a relatively long surface adapted to be brought into rigid vengagement with a portion of theframe and a relatively long vlaterally flanged head adaptedto bear against the inner surface ofthe covering and means for .Grof

facilitating the rigid engagement of said head with said covering.

19. A means for connecting an airships covering to the frame, including a plurality of substantially rigid metallic members each having a relatively long surface adapted to be brought into rigid engagement with a portion of the frame, a corresponding plurality of rigid metallic relatively long broad heads adapted to bear against the inner surface of the covering, means on said heads for facilitating the rigid engagement of said head with said covering, and means for rigidly securing each of said members and their respective heads together.

20. A means for connecting an airships covering to the frame, including a plurality of substantially rigid metallic members each having a relatively long surface adapted to be brought into rigid engagement with a portion of the frame, a corresponding plurality of rigid relatively long flanged heads, means on said heads for facilitating their rigid engagement with the inner surface of said covering, and means including over- Y. lapping integral portions of each of said members and there respective heads for securing them together.

21. A covering for airships including a plurality of thin flat and relatively narrow strips Y Y of metal overlapping at their adjacent edges, a

non-metallic flat and relatively narrow strip disposed along a plurality of the outer edges of said metallic strips and overlapping the adjacent edges of said metallic strips, and means for ,A Y securing together each of said overlapping edges of said strips to form a covering panel.

22. A covering for airships including a plurality of thin flat and relatively narrow strips 'of metal overlapping at their adjacent edges,

v a non-metallic flat and relatively narrow strip 40" disposed along a plurality of the outer edges of said metallic strips and overlapping the adjacent edges of said metallic strips, means for securing together each of said overlapping edges of said strips to form a covering panel, and

means upon the outer edges of said panel for facilitating the securement of said panel to the airship.

23. A covering for airships including a plurality of thin flat and relatively long narrow strips of metal overlapping at their adjacent edges, a non-metallic flat relatively long and narrow strip disposed along and overlapping each of the outer` edges of said associated metal strips, and means for securing together each of 7 said associated strips to form a covering panel.

24. A covering for airships including a plurality of thin flat and relatively long narrow strips of metal overlapping at their adjacent edges, a non-metallic flat relatively long and narrow istrip disposed along and overlapping each of the outer edges of said associated metal strips, `means for securing together each of said associated strips to form a covering panel, and means upon the outer edges of said panel for facilitating the securement of said panel to the airship.

25. A covering for airships formed of a plurality of panels each of an area forming a relal tively small part of the length and breadth of the airshipt to be covered, each of said panels being formed of a plurality of thin at and relatively narrow strips of metal overlapping at their adjacent edges, a non-metallic ilat and relatively narrow strip disposed along a plurality of the outer edges of said metallic strips and overlap- 26. The method of controlling stresses throughy out the framework and covering of a dirigible, said stresses arising from an inward component of force normal to the covering, comprising the steps of providing an equal and opposite reaction to said component, said reaction being the resultant of forces acting in a plane substantially parallel to the plane of the covering but remote therefrom, and causing reactions to said last-mentioned forces to act through the frame at points remote from the covering.

27. The method of controlling stresses throughout the framework and covering of a dirigible, said stresses arising from an inward component of force normal to the covering, comprising the step of providing an equal and opposite reaction to said component, said reaction being-the resultant of forces acting through but exerting substantially no torsional effort upon the frame.

28. The method of construction for preventing excessive strains in an assembly comprising the covering of a dirigible and the frame work thereof, said strains being due to forces having an Ainward component normal tothe plane of said covering, comprising the steps of transversely bracing said frame work in a plane other than and substantially parallel to the plane to be occupied by said covering, interposing between said planes at least one planar spacing rigid member of a width approximately equal to the distance between said planes, the plane of the spacing member being substantially perpendicular to the plane of said transverse bracing, resiliently securing said covering around its periphery Vto said frame work, securing said covering to the edge of the spacing member, and securing the spacing member to the transverse bracing, whereby any force acting upon said covering and having a component normal thereto is prevented from exerting a leverage action vupon said frame work and covering, and all forces are evenly distributed throughout said assembly. f

29. The method of covering thevframe panel of a dirigible to dispense with the leverage action on said panel of the covering whose substantial intermediate portions tend to move outwardly and inwardly due to the varying air pressure, comprising the steps of securing the frame panel covering material to the outer edges of the frame panel, and rigidly connecting substantial intermediate areas of the covering material to the frame panel, in a plane different from that occupied by the covering material, whereby said leverage action is eliminated and said pressure stresses distributed over the frame panel and thereby enabling the same structural weight of frame panel to afford greater than the former strength, safety and resiliency.

30. In a lighter than air craft, the combination of a metallic frame, a covering extending over the frame and containing a metal sheet, and at least one non-metallic' portion intermediate and contacting with the frame and metal sheet.

31. In a lighter than air craft, the combination of a metallic frame having substantial openings,

a covering containing a metal sheet, said covering Y frame component and in contact with the metal sheet.

32. In a lighter than air craft, the combination of the framework, covering for and secured to said framework and subject to stresses arising from an inward component of force normal to the covering; means for applying an equal and opposite reaction to said component, said reaction being the resultant of forces acting in a plane substantially parallel to the plane of the covering but remote therefrom, and means for causing reactions to said last named forces to act through the frame at points remote from the covering.

33. In a lighter than air craft, the combination of the framework, covering for and secured. to said framework and subject to stresses arising from an inward component of force normal to the covering, and means for applying an equal and opposite reaction to said component, said reaction being the resultant of forces acting through but exerting substantially no torsional effort upon the frame.

GARLAND FULTON.

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