US3011602A - Panel construction - Google Patents

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US3011602A
US3011602A US82672159A US3011602A US 3011602 A US3011602 A US 3011602A US 82672159 A US82672159 A US 82672159A US 3011602 A US3011602 A US 3011602A
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Prior art keywords
sheet
panel
bridges
embossed
skin
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Alf F Ensrud
Mario L Ochieano
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Lockheed Corp
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Lockheed Corp
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    • EFIXED CONSTRUCTIONS
    • E04BUILDING
    • E04CSTRUCTURAL ELEMENTS; BUILDING MATERIALS
    • E04C2/00Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
    • E04C2/30Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure
    • E04C2/32Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by the shape or structure formed of corrugated or otherwise indented sheet-like material; composed of such layers with or without layers of flat sheet-like material
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00Metal working
    • Y10T29/49Method of mechanical manufacture
    • Y10T29/49826Assembling or joining
    • Y10T29/49879Spaced wall tube or receptacle
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24273Structurally defined web or sheet [e.g., overall dimension, etc.] including aperture
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24628Nonplanar uniform thickness material
    • Y10T428/24661Forming, or cooperating to form cells
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24628Nonplanar uniform thickness material
    • Y10T428/24669Aligned or parallel nonplanarities
    • Y10T428/24678Waffle-form
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00Stock material or miscellaneous articles
    • Y10T428/24Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree
    • Y10T428/2495Thickness [relative or absolute]

Description

Dec. 5, 1961 A. F. ENSRUD EI'AL PANEL CONSTRUCTION 5 Sheets-Sheet 1 Filed July 13, 1959 uwuvrons ALF F. ENSRUD MARIO L. OCHIEANO Dec. 5, .1961 A. F. ENSRUD ETAL PANEL CONSTRUCTION 5 Sheets-Sheet 2 Filed July 13, 1959 mmvroxs ALF E ENSRUD MARIO L.OCHIEANO Dec. 5, 1961 A. F. ENSRUD ETAL 3,011,602

PANEL CONSTRUCTION Filed July 13, 1959 5 Sheets-Sheet s Dec. 5., 1961 A. F. ENSRUD ElAL PANEL CONSTRUCTION 5 Sheets-Sheet 4 Filed July 13, 1959 Ail;

Dec. 5, 1961 A. F. ENSRUD ETAL PANEL CONSTRUCTION 5 Sheets-Sheet 5 Filed July 13, 1959 INVENTORj 41/ 2. 145 900 W400! QW/MA/d United States Patent 3,011,602 PANEL CONSTRUCTION Alf F. Ensrud, North Hollywood, and Mario L. Ochieano,

Burbank, Calif, assiguors to Lockheed Aircraft Corporation, Burbank, Calif.

Filed July 13, 1959, Ser. No. 826,721 6 Claims. (1. 189-34) This invention relates to panel structures and relates more particularly to panels incorporating askin sheet and an embossed or formed sheet secured to the skin sheet to impart materially increased structural strength and rigidity thereto.

This application is a continuation-in-part of Serial Number 607,642, filed September 4, 1956, now abandoned.

It is the general object of the invention to provide a single skin sheet panel of extraordinary rigidity and physical strength characteristics. Panels have been proposed and introduced having two-spaced external sheets or skins of metal, or the like, and an embossed or formed sheet therebetween having special wafile patterns intended to lend rigidity and strength to the assembly and yet permit the assembly to remain relatively light in weight. Scurlock 2,481,046 is representative of such panels. In these prior panel arrangements the inner rigidity imparting sheet has usually been formed or embossed to have a multiplicity of indentations on each side providing the sheet with a plurality of elevations at each side, terminating in flat or relatively fiat plateaus or lands to which the spaced skins are secured by welding, riveting, brazing, cementing, or the like.

In such prior double-faced panels the pyramids or other elevated regions are joined one with another by what we will term bridges and because the lands or apices of the elevated regions occupy the outermost planes of the embossed sheet these bridges occupy planes between said outermost planes and usually about midway therebetween. We have found that the bridges add greatly to the rigidity of the sheet but that the location of the bridges in areas or planes spaced between the planes to be occupied by the skin sheets is not conducive to the development of maximum strength and rigidity in the panel, particularly, in the case of single skin sheet panels. Therefore, it is an object of this invention to provide panels of the class referred to having an inner or reinforcing sheet of special configuration, particularly designed to impart greatly increased strength and rigidity to the panel.

Another object of the invehtion is to provide a panel construction of the class referred to wherein the angular portion or bridges join the elevated areas or projections at or occupy the plane most remote from the plane occupied by the lands to which the skin sheet is attached. The angular bends or bridges joining the embossed elevations are in the plane which defines the side of the panel opposite the side to which the skin sheet is attached and are, therefore, in the most advantageous locations from the standpoint of imparting strength and rigidity to the panel structure.

Another object is to provide a panel of high heat transferability. In high speed aircraft the skin of the panel used on the exterior surface becomes heated due to the friction of the air. It is, therefore, particularly advantageous to develop an exterior skin surface for aircraft which will permit the dissipation of heat.

As a solution to this problem this invention presents a structural panel which has excellent heat transfer properties due to the fact that air may circulate on the back side of the skin sheet and within the space around the embossed projections on the embossed sheet. In present aircraft construction panels there is no chance for this type of air circulation to cool the skin sheet.

3,011,602 Patented Dem 5, 1961 This particular panel arrangement is, also, particularly configured to be a safe guard against explosive decom- 'pression. If a rupture occurs in the panel it will first occur in the skin sheet and the backing sheet will then not rupture as easily, so as to permit decompression of the fuselage of the aircraft, as it will sustain a higher stress load due to its non-planar configuration.

It is further object to provide a panel which is less expensive to construct and easier to shape and to work with than the presently employed honeycomb panels. There are variousdifiiculties arising with the manufacture of honeycomb panels and, in particular, bonding difiiculties exist in bonding the honeycomb portion to the two outside skin sheets.

Yet another object is to provide a panel having a lower weight per square foot than the honeycomb panels in present use. A weight comparison for steel panels constructed by the teachings of the present invention and by i the conventional honeycomb raised sandwich structure is the following: 7 j a The single skin sheet embossed panel of the present invention has a weight of from 2.3 to 2.5 lbs. per square foot and the double skin honeycomb structure from 2.8 to 3.0 lbs. per square foot.

Other objects and features of this invention will become apparent from the following description of typical preferred embodiments throughout which reference will be made to the accompanying drawings in which:

FIGURE 1 is a plan View of a panel constructed in accordance with the invention with a portion of the skin sheet broken away to show the formed reinforcing sheet;

FIGURE 2 is an enlarged fragmentary vertical sectional view taken as indicated by line 2-2 on FIGURE 1;

FIGURE 3 is a fragmentary perspective view of the panel with the skin sheet and the reinforcing sheet appearing in partial cross section;

FIGURE 4 is a perspective View of a portion of the reverse or inner side of the panel illustrating the configuration of the backing sheet and showing portions of those sheets in cross section;

FIGURE 5 is a plan View of a modification of the planar skin sheet in which the skin sheet has been contoured to conform to the embossed projections;

FIGURE 6 is a view taken on the line 6-6 of FIG- URE 5;

FIGURE 7 is a plan view of the preferred modification of the embossed panel, in which the land portions of the panel are placed out of the plane of the paper;

FIGURE 7a is the reverse view of a panel as positioned in FIGURE 7; in this view of the bridges portion are displaced from the plane of the paper;

FIGURE 8 is a view taken on the line 8-8 of FIG- URE 7 FIGURE 9 is a view taken on the line 99 of FIG- URE 7;

hFIGURE 10 shows the margin portion of an embossed s eet;

FIGURE 10a is a view of the reverse side of an embossed panel with a margin portion as shown in FIG- URE l0; 7

FIGURE 11 is a view taken on the line 11-11 of FIGURE 10a;

FIGURE 12 is an enlarged fragmentary view in plan of the intersection of the bridges portion of the embossed sheet of FIGURES 7 through 11;

FIGURE 13 is a modification of the present invention in which a perforated skin sheet has been attached to the bridges portion of the embossed panel;

FIGURE 14 is a modification of the present invention in which a perforated skin sheet has been attached to the lands portion of the embossed sheet and a heat-resistant plastic layer has been laminated to the skin sheet;

- 3 FIGURE shows another modification of the present invention in which a ceramic filler material has been creased bridge thickness and a perforated and sculptured skin sheet; 7

FIGURE 17 is an alternative structure of that shown in FIGURE 16. This modification of the structural panel has a head of metal deposited in the otherwise normally shaped bridge portion;

FIGURE 18 is a modification showing an orthogonal grid' attached to the bridges of the embossed panel and thereby increasing the strength of said bridges area;

FIGURE '19, is a further modification of the orthogonal grid of FIGURE 18; and V FIGURE '20 is yet another modification of the orthogonal grid of FIGURE 18. 7

FIGURE 21 is an enlarged and dimensioned cross section view of the embossed sheet taken on the line 88 of FIGURE 7.

FIGURE 22 is an enlarged and dimensioned cross section view of the embossed sheet taken on the line 9-9 of FIGURE 7. a

Thepanel of the invention comprises generally two sheets, namely a skin sheet and an embossed sheet or backing sheet. It will usually be found most desirable to form the sheets of metal, such as steel, stainless steel, aluminum alloy or the like, and where the panel is to be employed in aircraft constructions both sheets are preferably relatively thin.

SKIN SHEET The skin sheet (FIGURES l-4) is shown as a plane flat member having parallel surfaces, it being understood the sheet 10 may be shaped or contoured as required for given applications of the panel. The shaped or contoured skin sheet shown in FIGURES 5 and 6 may be formed with sheet areas 2.1 of reduced thickness which willcontact the fiat land portions of the truncated pyramidal configurations of the embossed sheet, to be described below. Between these areas 21 are ridges or grids 22. Areas 21 may be formed by such conventional processes as chemical milling, for example. A second modification is shown in FIGURES 13, wherein the skin sheet 52 is perforated with perforations 53. A third modification of a contoured skin sheet is shown in FIGURES l6 and 17 in which skin sheet 67 has perforations 68 in those portions of the skin sheet not contacting the lands as does the portion 65 of the skin sheet. Perforations 68 are shown with upturned edges 69, which edges impart further structural rigidity to the panel as a whole.

BACKING SHEET The core sheet or backing sheet may be formed from a single flat piece of material by embossing or pressing or plating but is preferably configured by stretch-forming, said stretch-forming'operation being performed by rigidly anchoring the margin portions of the flat pieceof material to be embossed and then striking or stretching the pyramidal projections into the sheet by means of coacting dies. This method of forming thus difiers from the dieshaping procedure of drawing wherein the margins of the blank being shaped are fed from the outside toward thecenter of theblank during the forming process. The stretch-forming formation of the embossed panel imparts superior flexure properties to a panel including the present embossed sheet. a

In accordance with the invention as shown in FIGURES 1 through 4, the embossed orbacking sheet 11 has a multiplicity of depressions or indentations 12 pressed or stretch-formed in one side thereof to leave or provide a multiplicity of. projections 13 on the other side of the sheet, said depressions 12 being the underside of pro' jeetions 13. While the invention contemplates that the indentations 12 and, therefore, the projections 13 may be of selected configuration, it ispreferred to make them of generally truncated pyramidal shapes. Preferably, the projections are a configuration which approximates the combination of a truncated cone and a truncated rectangular pyramid.

FIGURES 1 through 4 show the embossed sheet having truncated rectangular pyramidal projections formed therein. indentations 1 2 and projections 13 have tapered sides which converge toward the rectangular flat land 14. These lands 14 are fiat and are disposed adjacent to the skin sheet 10. so as to be conveniently and effectively joined to the skin sheet by riveting, welding, brazing, cementing 'or otherwise. In the drawings the nu vmeral 15 designates welds such as spot welds joining 7 ing of the lands 14 may be varied considerably, depending upon the particular general proportions and appli cations of a panel, it is of course desirable tomake the lands sufliciently extensive to have adequate engagement with the sheet 10 and to be readily and efiectively secured thereto by the rivets, welds, cement, or the like.

The embossed or backing sheet 11 is further characterized by areas or regions which join the adjacent projections 13, which regions will be termed bridges 16. As seen in thedrawings and as best illustrated in FIGURES 2 and 4, these bridges 16 are in the nature of abrupt or sharp angled ridges or bends, The bridges 16 preferably lie in a common plane, parallel with the plane of the lands 14 and the skin sheet 10, assuming the panel to be planar. Thus the bridges 16 join the projections 13 and occupy the plane most remote from the sheet 10. We have found that this location of the flexure resisting bridges is most advantageous in imparting rigidity and structural characteristics to the composite panel. Furthermore, by inspecting FIGURES l and 4 of the drawing, it will be seen that the bridges 16 are joined one with another to constitute a grid-like pattern of a multiplicity of inter-connected squares or diamonds positioned in diagonal or orthogonal patterns. This diamond pattern of the flexure resisting bridges 16 further imparts extraordinary physical strength characteristics and flexure resisting characteristics to the panel.

The preferred projection configuration, shown in FIG- URES 7 through 12, is resonant between a truncated cone and a truncated rectangular pyramid-shape. These projections ar described by having a pyramidal frustoconical configuration. The embossed backing sheet 30 has projections 31 of the resonant structure described having circular'lands 32 disposed at the converging apices of the slightly curved sides 34; The sides 34 of the projections 31 intersect each other along curvilinear bends 36. The projections are joined at the bases thereof by bridges 38, which bridges intersect one another to form the intersection of said bridges 38. The'cross section of this panel shown in FIGURE 8 shows the broadest dimension of this intersection 39.

It has been found, as a practical matter, that for a one inch base dimension of the projections the maximum height to which the pyramidal projections can be stretchedformed is approximately of an inch. A height of /2 inch for a one inch base dimension has been found desirable for the proper flexure characteristics of the panel. The maximum height to which the metal can be stretchedformed without tearing is, of course, a physical property of the metal used in the formation of the embossed sheet.

MODIFICATIONS In a modification adapted for convenient usage, the embossed sheetis formed with a margin portion around the periphery of the sheet. These margins may be prepared to adapt the panel for ready installation for various intended purposes. The margins 40, shown in FIGURES 10 and are preferably coplanar with the lands 32 of the embossed sheet 30. The skin sheet may be readily attached to the lands and to the margin portion of the sheet so as to provide an integral panel unit. This unit presents a fiat surface on both sides since the plane presented by the skin sheet and the margin portion of the embossed core sheet would present one fiat surface and a second surface would be presented by the fiat plane of the bridge grid Work 38 and 39.

FIGURE 12 is an enlarged fragmentary view showing the intersection of four of the bridges 38 to form the rounded cornered intersection 39 of the embossed sheet 30. This intersection 39 is formed by the integrated intersection of the four bridges 38 as well as the lower portions of the four curvilinear bends 36 of the four adjacent projections 31. As shown, the intersection is disposed coplanar to the flat portions of the bridges and has rounded corners due to the round cornered rectangular base of the projections 31. The curvilinear bends of the four adjacent projections are curved so as to de fine the sides of two normally intersecting parabolas, which parabolas would have flattened apices as would be formed by the planar intersection 39 of the bridges 38.

FIGURE 13 shows a modification of the present invention in which the panel 56 is composed of skin sheet 52, formed with preforations 53, attached to the bridges portions 54 of the embossed sheet 55. This panel modification is particularly suitable for acoustical boards or panels for use in aircraft, buildings, and other structures requiring panels with sound-proofing characteristics. It is also useful as a button board or lath board in that it is adapted to receive plaster and other surfacing materials. In this modification the backing sheet 55 may be the same as above described.

When intended for acoustical or sound-absorbing and damping purposes, the skin sheet 52 may be secured to the bridges 54- of the backing sheet, as illustrated in FIGURE 13, or may be secure to the lands 57 of the backing sheet 55, as in FIGURES l4 and 15. As shown in FIGURE 13 the perforations 53 are opposed or aligned with the lands 57. The panel shown in FIGURE 13 is especially well adapted as a plaster backing board or lath since the plaster, or like material, when applied thereto enters the openings 53 to form buttons behind the skin sheet 52 which effectively locks the plaster to the panel.

This type of panel is also well adapted for a heat insulating panel as a layer of heat-resistant plastic material may be attached to the perforated skin sheet. A modification of this type is shown in FIGURE 14, wherein the panel 50a consists of embossed backing sheet 55 having attached thereto, at the lands 57, a perforated skin sheet 52 with perforations 53 therein, and a heat-resistant plastic layer 53 attached to the outer surface of the perforated skin sheet.

Also, as shown in FIGURE 15, the perforated panel of this modification is easily adapted to have a ceramic material such as an insulating ceramic compound 59 poured into the perforations of the skin sheet 52 and then smoothed over in a cover layer so as to provide an insulating building panel.

FIGURE 16 shows a modification of the instant invention in which the panel 60 is composed of a special embossed panel 62 which has lands 64 and a thickened bridge portion 66. Alternatively to a fiat skin sheet as has been heretofore described in connection with various panels, a contoured skin sheet 67 may be provided for any of the embossed backing sheets. As shown in FIGURE 16 such a contoured sheet 67 has perforations 63 in those portions of the skin sheet not contacting the land portions 64 of the embossed sheet. These perforations 68 are shown with up turned edges 69, which edges impart further structural ridgity to the panel.

FIGURE 17 shows another modification of the present invention including a deposite of a head of metal 70 on the inner portion of the bridges 72 of the embossed 6 sheet 74 of panel 76 so that a thickened area may be presented for resisting excess stresses placed upon the panel. Both this modification and the modification shown in FIGURE 16 would serve this same function in resisting excess strsses. FIGURE 17 is also shown with a contoured skin sheet which has been described in the foregoing paragraph.

A third modification is shown in FIGURES 18 through 20. In this modification a thickening of the bridges portion of the embossed sheet is accomplished by attaching an orthogonal grid 80 to the embossed sheet which is attached through its lands 82 to a skin sheet 84. A slightly different configuration of the orthogonal grid 80 is shown in FIGURE 19 as 80a, in which the outer edges of the orthogonal grid, at each opening in the grid, are slightly downturned. FIGURE 20 shows the orthogonal grid 80b conforming to the contour of the bridges.

The embossed sheet of FIGURE 16 may be formed by any method from a blank sheet which has an integral grid work of portions which are thicker than the remaining portion of the blank. This blank sheet may be formed by such processes as selective chemical-milling, which is a chemical etching process to thin the metal not in the grid work, selective machining, or roll forging, etc.

PANEL CHARACTERISTICS The panel herein described is extremely light in Weight and yet possesses great strength in shear and in compression, both transverse and edgewise, and is highly resistant to recurring bending forces. This well adapts the panel for use in large sections where it may be required to span considerable distances between supports or framed members of the building, aircraft, or other structure in which it is to be used.

It should also be noted that the panel described herein will have superior bending characteristics over the panel presently employed in the aircraft industry, i.e. the panel may be formed into acylinder. Once this panel has been bent into the desired shape by the conventional techniques such as employing drop hammers, hydraulic presses, power brakes, stretch-forming machines, etc.; it will retain its structural characteristics in these various shapes. In connection with the superior bending characteristics above mentioned, the fiexure characteristics are also outstanding as this panel will resist biaxial stretching in the event of overloading. But upon overloading the panel will stretch with the forces imposed upon it rather than crumbling or completely collapsing. It has been concluded from test runs on the panel and on other various structural panels that the core configuration of this panel gives the panel these superior properties.

The above superior properties of the panel of the instant invention formed with the particularly configured embossed sheet are partly due to two physical characteristics of the embossed sheet.

One of these physical characteristics of a stretch-formed embossed panel is that the thickness of the panel varies according to various positions on the embossed panel. This varying thickness is shown in FIGURE 21, which figure is an enlarged view of the cross section shown in FIGURE 8. The dimensions shown in FIGURE '21 are the dimensions resulting from the stretch-forming of a sheet blank which was originally 0.04 inch thick. As will be noted from FIGURE 21 the intersections of the bridges portions 39 have an average thickness of .035 inch while the average thickness of the lands portions 32 is 0.021

' inch. The curvilinear bends 36 have an ever decreasing dimension from the intersection of the bridges portions 39 to the edge of the lands portions 32. As the curvilinear bends begin to taper away from the intersection of the F. J is a representation of actual micrometer readings, and thus, the variation between the various readings due to micrometer measurement error. A second view of the embossed panel stretch-formed by the present invention is shown in FIGURE 22, which view is a cross section similar to the cross section shown in FIGURE 9. As this figure shows, the average dimension of the bridges 38 is 0.029 inch while the lands 32 have an average dimension of 0.02 inch. Intermediate the bridges and the lands are the arcuate sides 34 which have, from the bridges, an ever dec'reasing dimension tapering from 0.032 inch to 0.011 inch at the end of the side nearest the lands 32, the

junctions of the side 34 with lands 32 have a dimension of 0.015 inch.

The percentage thinning factors at the various positions throughout the embossed panel stretch-formed as taught by this invention and as shown in FIGURES 21 and 22 may be computed by the following formula:

area thickness, inches 0.04

Table I Thinning factor Average Thickness Average Thinning Factors Portion of Sheet Portion Intersection of bridges Bridge end of bands Center 01' bends. Lands end of bends Lands e- U! COCO! An important advantage of the stretch-forming of a sheet in accordance with the present invention lies in the fact that the thinning occurs in areas which are'of small consequence structurally, as they do not carry 'the primary loads. It is the bridges portion which carry the primary stresses, as far as the backing sheet is concerned, and it will be noted from the Table I the highest average thinning factors are present in the area of the bridges. Thus, it is concluded that by stretch-forming the embossed sheet a considerable weight saving over other forming methods is realized, due to this thinning of the metal.

A second physical characteristic which is present in the stretch-formed embossed sheet constructed by the teachings of the present invention is that, stretch-forming causes the embossed panel to become strain hardened in certain portions. This strain hardening further increases the strength of the panel. In a draw forming operation metal is fed in from the outer periphery of the blank being so formed, which drawing reduces the amount of the stretching required to form a given sheet and thus does not allow this same strain hardening of the metal totake place. In connection with this strain hardening effect as a stretch-forming operation the embossed panel is also left with residual stresses in certain portions of the embossed sheet and in particular, residual stressesare set up in the bridges portion of the embossed sheet.

It should be noted that this same hardening feature is of significance only under conditions where heat treatment following stretch-forming is not employed, for when a panel is manufactured for high-strength efficiency requirements the panel is subjected to heat treatment in order that it will obtain high-strength levels.

The strain hardening and residual stresses effect of the stretch-forming operation result particularly in causing those curved portions of the embossed panel, such as the bridges, the intersection of the bridges, the arcuate sides,

' and the curvilinear bends of the projections,-to'act as individual spring systems which are integrated through the continuity of the metal into one continuous resilient sheet.

As has been above explained it is occasionally desirable to increase the thickness of the metal at the bridges portion of the embossed sheet. This disclosure is shown in FIGURES 16 and 17 which is shown with a preforated and contoured skin sheet 67. It should be noted that where an increased thickness of metal is used in the bridges the skin sheet is preferably perforated as shown in those figures so as to permit proper resiliency characteristics.

While the invention has been described in connection with different embodiments thereof, it will be'understood that it is capable of further modification, and this application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the invention and including such departures from the present disclosure as come within known or customary practice in the art to which the invention pertains, and as may be applied to the essential features hereinbefore set forth and as fall within the scope of the invention or the limits of the appended claims.

Having thus described our invention what we claim is:

1. A high-strength light-weight sheet adapted for use as a panel component consisting of an embossed sheet having formed therein a plurality of projections spaced in mutually adjacent relationship to one another in a rectangular gridwork, said projections being of a generally pyramidal frusto-conical configuration, said projection having curved sides, said projections having a round cornered rectangular base and a circular top, said top having a planar portion and having rounded edges conneting said planar top with said curved sides, bridges interconnecting the projections at their bases, the center portion of said bridges being generally flat and the portion of said bridges contacting said sides of said projections being curved, four intersecting bridges forming a flattened intersection, said intersection being disposed coplanar, with the flattened portion of said bridges, and said bridges occupying the plane farthest removed from the top of the said projections.

2. A panel as described in claim 1 wherein, said curved sides at the end of said sides nearest said bridges of said embossed sheet have a range of thinning factors of 0.70 to 0.80, a range of 0.20 to 0.40 in the center of said sides, and a range of thinning factors of 0.30 to 0.50 at the top end of said sides, said tops having a thinning factor range of 0.40 to 0.60, said bridges having a thinning factor range of 0.60 to 0.85, and said intersection of said bridges having a thinning factor range of 0.80 to 0.95.

3. A sheet as described in claim 1 wherein, said bridges have a thickness of at least twice the thickness of the remainder of said embossed sheet.

4. A sheet as described in claim 1 wherein, said projections have a maximum ratio of height dimension to base dimension of %1.

5. A sheet as described in claim 1 wherein, said curved sides of said projections are bowed inwardly toward the height axis of said projections.

6. A panel as described in claim 1 wherein, said bridges have portions thereof which are strain hardened.

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Cited By (70)

* Cited by examiner, † Cited by third party
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US3162487A (en) * 1962-08-31 1964-12-22 Phillips Petroleum Co Air-carrying flexible layer for under-body ventilating
US3196763A (en) * 1960-10-05 1965-07-27 Washington Aluminum Company In Panel structure
US3233885A (en) * 1959-11-04 1966-02-08 Miller Herman Inc Panel having multi-directional flexibility
US3258892A (en) * 1962-11-16 1966-07-05 Washington Aluminum Company In Panel structure
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US3365787A (en) * 1963-06-19 1968-01-30 Hexcel Corp Method of making metal honeycomb sandwich structure
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US3461632A (en) * 1965-10-18 1969-08-19 Robert G Kuhne Lightweight cellular structural material
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US3948614A (en) * 1971-12-06 1976-04-06 Bennes Marrel Composite metal sheetings
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US4146666A (en) * 1977-08-08 1979-03-27 Borg-Warner Corporation Thermally expansible sheet
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US20110041455A1 (en) * 2009-08-20 2011-02-24 PHILLIPS Thomas Gusset plate construction
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US9586536B1 (en) * 2015-09-02 2017-03-07 Hyundai Motor Company Strength-reinforcing metal sheet
US20170101788A1 (en) * 2015-10-12 2017-04-13 Playsafer Surfacing, Llc, A Division Of Rubberecycle Multi-level unitary safety surface tiles
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Cited By (93)

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US3233885A (en) * 1959-11-04 1966-02-08 Miller Herman Inc Panel having multi-directional flexibility
US3196763A (en) * 1960-10-05 1965-07-27 Washington Aluminum Company In Panel structure
US3295840A (en) * 1962-06-27 1967-01-03 Dow Chemical Co Tower packing
US3162487A (en) * 1962-08-31 1964-12-22 Phillips Petroleum Co Air-carrying flexible layer for under-body ventilating
US3258892A (en) * 1962-11-16 1966-07-05 Washington Aluminum Company In Panel structure
US3338774A (en) * 1962-12-14 1967-08-29 Dijksterhuis Fokko Device for manufacturing a laminated panel having a cellular internal structure
US3365787A (en) * 1963-06-19 1968-01-30 Hexcel Corp Method of making metal honeycomb sandwich structure
US3369288A (en) * 1963-06-24 1968-02-20 Hexcel Corp Method of diffusion bonding a honeycomb structure
US3364563A (en) * 1963-10-08 1968-01-23 Ohio Metalsmiths Corp Method of making an insulated panel
US3461632A (en) * 1965-10-18 1969-08-19 Robert G Kuhne Lightweight cellular structural material
US3507634A (en) * 1965-10-22 1970-04-21 United Aircraft Corp Composite metal structure
US3619340A (en) * 1969-01-21 1971-11-09 Peter Jones Multilayered thermal insulation material
FR2087984A2 (en) * 1970-05-05 1972-01-07 Raffinage Cie Francaise Composite construction sheet for roofs and - walls
US3955019A (en) * 1971-11-29 1976-05-04 Donald George Keith Cuspated sheet forming
US3948614A (en) * 1971-12-06 1976-04-06 Bennes Marrel Composite metal sheetings
US3884646A (en) * 1972-12-05 1975-05-20 James T Kenney Structural panel and method of fabrication thereof
US4148954A (en) * 1973-12-26 1979-04-10 Union Carbide Corporation Expanded product having a plurality of cells open at one end
US3902348A (en) * 1974-04-15 1975-09-02 Jesse R Hale Method for forming superplastic and super ductile metal alloys
US4035536A (en) * 1975-03-03 1977-07-12 Mcdonnell Douglas Corporation Sandwich panel core
US4146666A (en) * 1977-08-08 1979-03-27 Borg-Warner Corporation Thermally expansible sheet
US4397902A (en) * 1977-12-27 1983-08-09 Ronald D. Resch Construction-element
US4292375A (en) * 1979-05-30 1981-09-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Superplastically formed diffusion bonded metallic structure
US4411121A (en) * 1981-02-02 1983-10-25 Tate Architectural Products, Inc. Structural member with truncated conical portion and composite panel including same
EP0063498A1 (en) * 1981-04-22 1982-10-27 Irving E. Figge Structural panel
US4406628A (en) * 1981-06-03 1983-09-27 Mcneil Corporation Training device for swimmers
US4631221A (en) * 1984-04-05 1986-12-23 Hoechst Aktiengesellschaft Sheet-like sandwich molding
DE3729854A1 (en) * 1986-09-11 1988-03-17 Donn Inc Increased floor panel and process for its manufacture
FR2603930A1 (en) * 1986-09-11 1988-03-18 Donn Inc Floor panel elevated and process for its manufacturing
US4753058A (en) * 1986-09-11 1988-06-28 Donn Incorporated Elevated floor panel and method of manufacturing same
US4856175A (en) * 1986-09-11 1989-08-15 Usg Interiors, Inc. Method of manufacturing elevated floor panels
US4889758A (en) * 1988-03-29 1989-12-26 Isaac Rinkewich High-strength panel structure
US5201154A (en) * 1991-08-23 1993-04-13 Easy Gardener, Inc. Landscape edging and methods of manufacturing and using same
WO1993012304A1 (en) * 1991-12-11 1993-06-24 Riedinger Mmm Gmbh & Co Kommanditgesellschaft Facade element
US5244745A (en) * 1992-04-16 1993-09-14 Aluminum Company Of America Structural sheet and panel
US5399406A (en) * 1993-02-05 1995-03-21 Sky Aluminium Co., Ltd. Paneling material and composite panel using the same
US6012764A (en) * 1997-06-11 2000-01-11 Aluminum Company Of America Vehicle greenhouse support assembly and associated method
ES2156720A1 (en) * 1999-03-31 2001-07-01 Mecanizaciones Aeronauticas S Metal structure applicable to external aeromotor casings
US6200664B1 (en) * 1999-11-01 2001-03-13 Ward Figge Explosion barrier
EP1268184A1 (en) * 1999-11-01 2003-01-02 Atlantic Research Corporation Explosion barrier
EP1268184A4 (en) * 1999-11-01 2003-04-16 Atlantic Res Corp Explosion barrier
US20050212328A1 (en) * 1999-11-11 2005-09-29 Michael Ashmead Energy-absorbing structure
US6797219B1 (en) 2000-11-28 2004-09-28 Steelcase Development Corporation Method for manufacture of floor panels
US6543755B2 (en) * 2001-02-08 2003-04-08 Lockheed Martin Corporation Stacked tetrahedral elastomer mount
US6779835B2 (en) 2001-12-06 2004-08-24 Lear Corporation Energy absorbing structure for automobile interior
US20050084703A1 (en) * 2001-12-21 2005-04-21 Michael Ashmead Structural component
WO2003056111A1 (en) * 2001-12-21 2003-07-10 Cellbond Limited Structural component
US7131674B2 (en) 2003-07-03 2006-11-07 Netshape International, Llc Bumper system incorporating thermoformed energy absorber
US7222897B2 (en) 2003-07-03 2007-05-29 Netshape Energy Management Llc Method of constructing bumper incorporating thermoformed energy absorber
US7073831B2 (en) 2004-06-23 2006-07-11 Netshape International Llc Bumper with crush cones and energy absorber
US20050285418A1 (en) * 2004-06-23 2005-12-29 Darin Evans Bumper with crush cones and energy absorber
US7228723B2 (en) 2004-07-01 2007-06-12 Netshape Energy Management Llc Bumper impact-testing device
US20060225627A1 (en) * 2005-04-08 2006-10-12 Steelcase Development Corporation Work surface, edge treatment and method for configuring work surface
US20090123709A1 (en) * 2005-11-22 2009-05-14 Straza George C P Formed core sandwich structure and method and system for making same
US8052198B2 (en) 2007-03-07 2011-11-08 Alcoa Inc. Pedestrian safe automotive hood having reinforcing foam
US20100140979A1 (en) * 2007-03-07 2010-06-10 Alcoa Inc. Pedestrian safe automotive hood having reinforcing foam
US20100119768A1 (en) * 2007-12-13 2010-05-13 Barney Ernest Simon Light-weight thermoplastic olefin truss core for laminated panels for use in the transportation and RV industries
US20110067731A1 (en) * 2008-07-10 2011-03-24 Tatsuya Satoh Cleaning device and cleaning method
US20100009126A1 (en) * 2008-07-12 2010-01-14 The Boeing Company Method and Apparatus for Forming a Corrugated Web Having a Continuously Varying Shape
US8402805B2 (en) 2008-07-12 2013-03-26 The Boeing Company Method and apparatus for forming a corrugated web having a continuously varying shape
US20100006700A1 (en) * 2008-07-12 2010-01-14 The Boeing Company Aircraft wings having continuously tailored structural strength
US8292227B2 (en) * 2008-07-12 2012-10-23 The Boeing Company Aircraft wings having continuously tailored structural strength
WO2010138066A1 (en) * 2009-05-26 2010-12-02 Ecopals Ab Sandwich structured construction element
US9079377B2 (en) 2009-05-26 2015-07-14 Ecopals Ab Sandwich structured construction element
WO2011011634A1 (en) * 2009-07-22 2011-01-27 Straza George C P Formed core sandwich structures
US9126387B2 (en) 2009-07-22 2015-09-08 George C. P. Straza Formed core sandwich structures
US20110041455A1 (en) * 2009-08-20 2011-02-24 PHILLIPS Thomas Gusset plate construction
US9108239B2 (en) 2009-11-13 2015-08-18 Sumitomo Light Metal Industries, Ltd. Sheet material having concave-convex section, and laminated structure and vehicle panel using the same
US9090288B2 (en) 2010-09-08 2015-07-28 Sumitomo Light Metal Industries, Ltd. Sheet material having a concave-convex part, and vehicle panel and laminated structure using the same
US20120175206A1 (en) * 2010-12-10 2012-07-12 Skydex Technologies, Inc. Interdigitated Cellular Cushioning
US8915339B2 (en) * 2010-12-10 2014-12-23 Skydex Technologies, Inc. Interdigitated cellular cushioning
US8927089B2 (en) 2011-01-11 2015-01-06 Uacj Corporation Sheet material having a concave-convex part, and a vehicle panel and laminated structure using the same
US8920908B2 (en) 2011-01-17 2014-12-30 Uacj Corporation Sheet material having a concave-convex part, and vehicle panel and laminated structure using the same
US8990987B2 (en) 2011-06-07 2015-03-31 Skydex Technologies, Inc. Collapsible layered cushion
US9492018B2 (en) 2011-06-07 2016-11-15 Skydex Technologies, Inc. Collapsible layered cushion
EP2604426A1 (en) * 2011-12-13 2013-06-19 Airbus Opérations SAS Manufacturing method for a sound attenuating panel
US8733501B2 (en) * 2011-12-13 2014-05-27 Airbus Operations Sas Method for producing an acoustic treatment panel
US20130146393A1 (en) * 2011-12-13 2013-06-13 Airbus Operations Sas Method for producing an acoustic treatment panel
FR2983835A1 (en) * 2011-12-13 2013-06-14 Airbus Operations Sas A method of making a panel for acoustic treatment
US9462843B2 (en) 2011-12-16 2016-10-11 Viconic Defense Inc. Cushioning helmet liner
US20130152287A1 (en) * 2011-12-16 2013-06-20 Oakwood Energy Management, Inc. Rebounding cushioning helmet liner
US9622534B2 (en) 2011-12-16 2017-04-18 Viconic Sporting Llc Rebounding cushioning helmet liner
US9420843B2 (en) * 2011-12-16 2016-08-23 Oakwood Energy Management, Inc. Rebounding cushioning helmet liner
US9194136B2 (en) * 2013-04-18 2015-11-24 Viconic Defense Inc. Recoiling energy absorbing system
US9279258B2 (en) * 2013-04-18 2016-03-08 Viconic Defense Inc. Recoiling energy absorbing system with lateral stabilizer
US20140311075A1 (en) * 2013-04-18 2014-10-23 Viconic Defense Inc. Recoiling energy absorbing system with lateral stabilizer
US9739053B2 (en) 2013-04-18 2017-08-22 Viconic Defense Inc. Multi-tiered recoiling energy absorbing system with lateral stabilizer
US20140311074A1 (en) * 2013-04-18 2014-10-23 Viconic Defense Inc. Recoiling energy absorbing system
US9415708B2 (en) 2014-02-18 2016-08-16 Oakwood Energy Management, Inc. Conformable energy absorber
US9586536B1 (en) * 2015-09-02 2017-03-07 Hyundai Motor Company Strength-reinforcing metal sheet
US20170101788A1 (en) * 2015-10-12 2017-04-13 Playsafer Surfacing, Llc, A Division Of Rubberecycle Multi-level unitary safety surface tiles
US9962878B2 (en) * 2015-10-12 2018-05-08 Playsafer Surfacing Llc Multi-level unitary safety surface tiles
US9704467B1 (en) * 2016-04-15 2017-07-11 Rohr, Inc. Acoustic panel with corrugated baffles and septums
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