Patent Publication Number: US-7216576-B2

Title: Trampoline responsive armor panel

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
   This application claims priority to prior-filed, now abandoned, U.S. Provisional Patent Application Ser. No. 60/548,716, filed Feb. 27, 2004, for “Armor Manufacturing Process”. All of the disclosure content of that provisional case is hereby incorporated herein by reference. 

   BACKGROUND AND SUMMARY OF THE INVENTION 
   This invention pertains to an anti-projectile, anti-spall, anti-ricochet, trampoline-action armor panel. In particular, it pertains to such a panel which is formed preferably with a plural-layered armor core, or core structure, including a hardened-material tile strike layer, and a plurality of armoring back-up flexure, or flex, layers (or at least one such layer) arranged in a stack, with lateral edges in the stack bound against motion relative to one another. The panel of the invention further includes a load-managing, stranded, around-the-core enveloping core-wrap of a special nature, with a coating provided on the outside at least of the lateral edges and of the strike face of the panel, which coating is formed of a high-elastomer, self-puncture-healing and energy-dissipating material, which, as will be discussed, and among other things, enhances trampoline action in response to a projectile strike. 
   In further general terms, the panel is constructed preferably with a modular, tile-like configuration so that it can easily be organized with other modularly-related similar panels to form a protective shield on, adjacent, etc., a selected site or object. Appropriate attaching structure/mechanism may be suitably integrated into the panel during its construction, if desired, for enabling ready mounting and attaching of the panel in its intended operative location. 
   The mentioned back-up layers may be employed in different numbers depending upon the projectile threat level to which the panel&#39;s use is directed, and these back-up layers are preferably each formed with plural sub-layers of appropriately disposed aramid fibers, preferably in a fabric weave, which are suitably facially bonded internally to unify the layer. The hardened-material, preferably ceramic-tile, strike layer which defines the projectile strike side of the panel of this invention is preferably formed as a row-and-column array of smaller ceramic tile units. These tile units are disposed substantially in edge-adjacent-edge, slightly edge-spaced, lateral adjacency, with an appropriate, shock-absorbing, elastomeric binder resin disposed between these edges to maintain a desired slight amount of spacing between adjacent edges in order to minimize lateral telegraphing of impact shattering and fragmentation of one tile to its neighbors. This same resin is employed to bind the strike layer to one facial side of the stack of adjacent back-up layers, and the core-wrap structure to the opposite facial side of the back-up layer stack. 
   The edge binding, or anchoring, of the lateral edges of all of the back-up layers in the core of the panel of this invention via a suitable hot-melt adhesive effectively converts substantially the entire lateral edge perimeter (the perimetral boundary) of the back-up layer portion of the core into a non-relative-motion singularity. This singularity prevents these edges effectively from moving relative to one another during response to an impact, while at the same time permitting a kind of trampoline-like, broad-beam flexing across the broad expanses of all of the back-up layers collectively. The bound edge structure further accommodates interfacial sliding motion between the confronting faces (facial expanses) of these layers as a consequence of a projectile impact event. This edge-bound structure thus renders, or characterizes, a unique core arrangement which responds with what is referred to herein as trampoline-broad-beam, slide-face behavior. One way of thinking about, or visualizing, how this beam-like characterization/analogy attaches to the structure of the invention is to imagine viewing any number of transverse cross-sectional sections taken through the core stack of layers in any plane which effectively intersects the planes of these layers at right angles. Doing this, one will notice that what one sees in each of these view planes is an elongate, laminar, beam-like “section” with opposite ends effectively locked into unified and interconnected structures (the entire bound perimeter), and with central, laminar stretches between these ends bendable in response very much like what one would observe in the behavior of an elongate, double-end-supported beam structure in, for example, the frame of a building. 
   The stranded core-wrap structure employed herein is one wherein two, wrapped, fabric-like components are employed, each having what is referred to herein as a load-transmitting grain direction (a fiber-based direction) which is effectively defined by elongate, substantially parallel, elongate, tension-load-bearing (TLB) fibers, preferably aramid fibers. These elongate TLB fibers in each wrap component substantially parallel the grain direction of the component. The two wrap components are organized into overlapping adjacency with respect to one another in such a fashion that (a) their respective grain directions are disposed at angles, and preferably at right angles, relative to one another at the two locations where these two components extend across the broad faces of the panel of this invention, and (b), these same grain directions are aligned in a common direction along the lateral edges of the panel, and specifically in a common direction which extends substantially normally between what can be thought of as the planes of the strike and opposite faces of the finished panel. 
   Significantly, the portions of the core-wrap structure which lie adjacent the bound edges of the back-up layers are adhered thereto, and this arrangement aids, as will be explained, in the trampoline response action of the panel of the invention. Additionally, in the region where these two core-wrap components centrally cross and overlap one another, they are anchored to that side of the stack of back-up layers which faces away from the strike layer of ceramic tiles. 
   The mentioned high-elastomer coating, which may be applied to the entirety of the surface areas of all sides of the panel of this invention, but which in the specific embodiment described herein extends over only the strike side and the lateral edges of the disclosed panel, operates as a significant energy dissipater with respect to an impacting projectile, such as a bullet, a fragmentation shrapnel-like shard, etc. This elastomer coating also integrates mechanically with the core-wrap structure, as will be explained, and co-acts therewith, along with the edge-bound core-structure back-up layers, via the connections which exist between these layers and the core-wrap structure, to enhance the broad-beam trampoline-response behavior of the overall panel. 
   In testing and observing the responses of many panels constructed in accordance with the teachings of this invention, we have observed that this panel not only is very effective in its role of defeating an incoming projectile threat, but also, after an impact has occurred, is strongly effective in preventing post-impact threat developments arising from spall. In other words, it does not allow the regeneration, so-to-speak, of fragmentation projectiles due, for example, to the breaking up of an incoming impacting projectile, or the breaking up of an internal armoring tile. Put another way, the panel appears to swallow/contain both impacting threat projectiles and the resulting internal fragments which may develop (as by bullet break-up and tile shattering) as a consequence of a received impact. The panel also is effective in greatly minimizing ricochets. Further, and as will be mentioned again later, the cooperative relationship which exists between the outer elastomer coating and the core-wrap structure, appears to handle an internal, blast-like, pressure-wave event, which immediately follows a projectile impact, in a unique outward-bulge-and-return manner. 
   All in all, the structure of the panel of this invention operates with a unique, broad-beam, trampoline-like and related actions which deal with a projectile impact through internal tile fragmentation to “burn” energy and break up a projectile, through energy dissipation occurring in the response provided by the elastomer layer, through broad-beam, trampoline-like flexure and yielding deflection which occurs in the behavior of the stacked assembly of the back-up layers included in the panel core, and through the bulge-and-return behavior just mentioned above. As will be seen, and as has been noted earlier, trampoline response is enhanced by the presence in the panel of the elastomer outer coating which is anchored to the panel edge regions in the immediately underlying core-wrap fabric structure. 
   Further, because of the unique edge-to-edge, resin-filled, shock-absorbing spacing which characterizes the strike layer of the employed hardened-material (ceramic) tile array, fragmentation of a directly hit tile effectively does not telegraph to its neighbors. Thus the armor panel of this invention has demonstrated a remarkable ability to receive and disable multiple, closely-spaced projectile impacts. 
   These and various other features and advantages which are offered by the invention will now become more fully apparent as the description which shortly follows is read in conjunction with the accompanying drawings. 
   While those skilled in the art will recognize from the description of this invention which now follows that various specific materials may be employed in different regions of the structure of the present invention, there are certain preferred materials upon which we have settled, and we here identify those materials. 
   IDENTIFICATIONS OF PREFERRED MATERIALS  
   Among the preferred materials employed in the construction of the preferred embodiment of the panel of this invention are the following: 
   1. Fabric (woven material) with the so-called TLB strands that define a grain direction in the two elongate core-wrap components of the core-wrap structure is a woven aramid fiber fabric made by Hexel Schwebel of Anderson, S.C.—a 3000-Denier material which is designated Configuration #745. 
   2. The same fabric is employed in single sub-layers (five are illustrated) to create the five, individual, integrated, stacked back-up layers employed in the illustrated and described core structure of the invention. 
   3. Centrally bonding the two core-wrap components (a) to one another, and (b) to one face of the non-strike side of the stack of back-up layers is a 2-part resilient urethane resin material made by Development Associates, Inc. of North Kingstown, R.I. This is referred to by its manufacturer as A-Z-7050-15A and B-Z-7050-15B. 
   4. Bonding facially adjacent sub-layers in each back-up layer structure is a 0.003-inch thick, heat-sensitive adhesive layer also made by Hexel Schwebel, called Hexform. Conveniently, this adhesive may be prepared as an initial coating on the aramid-fiber fabric material. 
   5. The ceramic tiles used in the so-called strike layer in the panel of this invention are each made of aluminum oxide (98.5%). 
   6. Edge bonding of the back-up layers herein is handled by a suitable and conventional hot-melt adhesive, which adhesive is also employed to bridge and bond adjacent edges in the wrapped, two core-wrap components which collectively make up the core-wrap structure. 
   7. Bonding the ceramic tile (strike) layer to one face in one of the back-up layers is the same resilient urethane material mentioned above for bonding the two employed core-wrap components. This same material occupies the spaces provided between next-adjacent, confronting edges of tiles in the tile layer. 
   8. The over-coating elastomer product, which is formed with a thickness herein of about 0.1-inches to about 0.125-inches, is made of a self-puncture-healing material sold under the trademark TUFF STUFF®, manufactured by Rhino Linings USA, Inc. in San Diego, Calif. 

   
     DESCRIPTION OF THE DRAWINGS 
       FIG. 1  is a top isometric view of a trampoline response armor panel constructed, and designed to perform in accordance with, the features of the of the present invention. 
       FIG. 2  is a reduced-scale, differently proportioned and partially fragmentary drawing illustrating certain general overall features of the panel of  FIG. 1 . 
       FIG. 3A  is a cross-sectional view, presented on a larger scale than that employed in  FIG. 2 , and drawn without specific regard to exact relative proportions of components, taken generally along the line  3 A— 3 A in  FIG. 2 . 
       FIG. 3B  is a further enlarged fragmentary portion of  FIG. 3A  illustrating details of construction of a back-up layer in the panel of  FIGS. 1–3A , inclusive. 
       FIGS. 4–6 , inclusive, illustrate, in a stylized fashion, several stages involved in the construction of the panel shown in  FIGS. 1–3B , inclusive. 
       FIGS. 7–9 , inclusive, are simplified and stylized drawings illustrating the proposed organization, in a core-wrap structure included the panel of this invention, of the so-called grain directions in a pair of stranded core-wrap components which form the mentioned core-wrap structure. 
       FIGS. 10A and 10B  provide a pair of stylized schematic illustrations useful in understanding the “trampoline broad-beam” characterization of the armor panel of this invention. 
       FIG. 11  provides two simplified isometric views of pre-impact and post impact conditions of a stack of back-up flex layers employed in the panel of the invention. 
       FIG. 12  is a simplified, schematic side elevation isolating, and illustrating the projectile-impact cooperative behavior&#39;s of, a stack of edge-bound back-up layers, of a core wrap structure which effectively envelopes these layers, and of a panel outer coating made of a high-elastomeric material. 
       FIGS. 13A and 13B  collectively illustrate certain aspects of a response to a projectile impact provided by the mentioned edge-bound back-up layers. 
       FIG. 14  is an enlarged fragmentary and stylized drawing illustrating how strike-fragmentation of a single tile in the strike layer contained in the panel of this invention is prevented from telegraphing its fragmentation to adjacent strike-layer tile neighbors. 
       FIG. 15  is a fragmentary and simplified view illustrating an armoring installation employing a plurality of panels constructed in accordance with the present invention adhered to the surface of a structure which is to be protected through a pressure-sensitive adhesive layer. 
       FIG. 16  is a simplified side elevation illustrating an observed momentary outward bulge which occurs after a projectile impact relative to the panel of this invention—a bulge which is believed to be involved in dealing with an internal pressure-wave, explosion-like event which occurs inside the panel of the invention. 
   

   RELEVANT BACKGROUND LITERATURE 
   Useful in providing relevant background information regarding the present invention is published PCT Patent Application No. WO 03/089869 A2, published Oct. 30, 2003. Accordingly, the entirety of that document is hereby incorporated herein by reference for background purposes. 
   DETAILED DESCRIPTION OF THE INVENTION 
   Turning now to the drawings, and referring first of all to  FIGS. 1–3B , inclusive,  14  and  15 , indicated generally at  20  is an armor panel, referred to herein as a trampoline response armor panel, and as a trampoline broad-beam anti-projectile-strike armor panel, constructed in accordance with the present invention. As can be seen, panel  20  is substantially square in relation to its “broad-area” footprint, and planer in nature (see plane  20 A in  FIG. 3A ), with illustrative dimensions herein of about 10×10×0.75-inches. These dimensions are matters of design choice, with thickness being determined chiefly by the intended “defeating” capability of the panel relative to a projectile, such as a bullet, a shard of shrapnel, etc., and the lateral dimensions being determined principally by the “site” to which it is to be attached to provide protection. It should be understood that the panel&#39;s footprint need neither be square, nor for that matter rectilinear. The panel&#39;s thickness herein is designed to protect against a projectile threat which is somewhat in excess of that produced by a typically fired AK47 round of ammunition. Accordingly, the panel specifically illustrated and described herein is to be considered to be merely illustrative. 
   Conveniently, it may be desirable to think of an armor panel made in accordance with this invention to be a versatile module to be incorporated in an armoring installation wherein it is arrayed with size-and-configuration-compatible other panels to form an overall armoring barrier.  FIG. 15  shows fragmentarily a tiled, row-and-column array  22  of plural panels  20 , attached to a structure  24 , which is to be barriered, by a suitable film  26  of a pressure-sensitive adhesive. It should be understood, of course, that panels  20  may be prepared in a wide variety of ways for in-place attachment, and may also, if desired, be manufactured with “integral” attaching devices, mechanisms, etc. which themselves form no part of the present invention. 
   In general, high-level terms, panel  20  includes what are referred of herein as generally parallel-planar strike-and non-strike faces, or sides,  20   a ,  20   b , respectively, which are bridged, so-to-speak, by four, orthogonally related (both to each other and to sides  20   a ,  20   b ) edges  20   c ,  20   d ,  20   e ,  20   f.    
   In terms, generally, of the componentry which makes up panel  20 , included are a planar armor core, or core structure,  28 , a stranded core-wrap structure  30  which preferably completely envelops core  28 , and an outer, high-elastomeric, surface coating  32  which, herein, only covers strike face  20   a  and edges  20   c ,  20   d ,  20   e ,  20   f  in panel  20 . This surface coating could, naturally, be applied to cover the entire panel if desired. Preferably, it at least covers the specific panel portions just mentioned. Core  28  is also referred to herein as an impact reaction core. 
   Core  28  in panel  20 , as illustrated, is formed as an edge-aligned stack of six, substantially planar layers, including a strike layer  34 , and five back-up layers, or layer elements,  36 ,  38 ,  40 ,  42 ,  44 . The five back-up layers are also referred to herein as slide-face layers, and as flex-response layers. Strike layer  34  possesses what are termed herein substantially parallel-planar strike and non-strike sides, or faces,  34   a ,  34   b , respectively, with strike face  34   a  disposed toward previously mentioned panel strike side  20   a , and with the mentioned back-up layers being located as a collection adjacent the non-strike face of layer  34 . Layer  34  is also referred to as a flex-response layer. The lateral edges of the various layers included in the stack of layers which make up core structure  28  are essentially aligned with one another in edge planes which are disposed substantially normally relative to the planes of these layers. 
   Layer  34  herein is specifically formed as a row and column “tiled array” of square-footprint, hardened-material (preferably ceramic) tiles  46 , each having dimensions in panel  20  of 2×2×0.275-inches. A preferred ceramic material employable in these tiles was mentioned earlier herein. 
   Looking for a moment particularly at  FIGS. 3A and 14 , next-adjacent, confronting edges in tiles  46  do not contact one another. Rather, they are spaced apart in layer  34  by about 0.002- to about 0.005-inches, with the linear spaces between tiles being filled with a resilient, shock-absorbing, urethane interface material  48  whose preferable choice for use was also mentioned earlier. The edge arrangement of tiles  46  in panel  20  is referred to herein as being one possessing an edge-adjacent-edge configuration. Material  48 , in a layer thickness herein of about 0.02-inches, also (a) binds strike layer  34  to the top face of back-up layer  36  (see particularly  FIG. 3A ), and (b) the lower face of back-up layer  44  to core-wrap structure  30  (see particularly  FIG. 4 ). 
   Among the more important contributions made to the performance of the panel of this invention by this just-discussed tile spacing and inter-tile-edge disposition of urethane resin, is that a projectile impact which shatters a particular tile, such as the shattered tile shown in  FIG. 14  at  50 , does not telegraph this shatter event to its neighbors. More will be said about this feature of the invention later. 
   Each of the five back up layers employed in panel  20  is formed by the integration of five, individual sub-layers of the woven, aramid-fiber fabric material described earlier herein. In  FIG. 3B , back-up layer  36  is shown with five such sub-layers  36   a ,  36   b ,  36   c ,  36   d ,  36   e . Preferably, one or both of the facial expanses of these layers which confront and face one another in layer  36  is (are) pre-coated with the heat-sensitive adhesive material also referred to herein earlier as being made by the Hexel Schwebel company. Through appropriate heat application during the preparation of the back-up layers, the individual sheets making up each one these layers become bonded through the heat reaction generated in the mentioned heat-sensitive adhesive. In  FIG. 3B , dashed lines  52  represent this adhesive material. In the regions where this adhesive material is employed, its thickness between components is about 0.003-inches. 
   Implementing edge-to-edge binding of the stack-aligned lateral edges in layers  36 ,  38 ,  40 ,  42 ,  44 , according to an important feature of the invention, is what is referred to herein as edge-to-edge binding structure  54 . In the embodiment of the invention now being described, structure  54  takes the form of the earlier mentioned conventional hot-melt adhesive material. This binding structure unifies the edges in the back-up layers to create an elongate edge singularity which acts as a non-relative-motion unit with respect to preventing any relevant motion from occurring between adjacent edges in the stack of back-up layers. As will be mentioned again herein a little bit further on in this description, this same hot-melt adhesive material binds adjacent edge regions in portions (components) of core-wrap structure  30 . 
   Previously mentioned core-wrap structure  30  herein takes the form of two elongate and generally orthogonally oriented core-wrap components  56 ,  58  which, where they centrally cross one another, as is illustrated generally at  60  in  FIG. 4 , are bonded to one another by the same two-part urethane material which was earlier given reference number  48 . These two core-wrap components are formed from the same aramid fiber fabric material described earlier herein, and they are oriented relative to one another whereby the aramid fibers which extend generally in their (the components&#39;) long directions are referred to herein as tension-load-bearing, or TLB, fibers which effectively define what are also referred to herein as the grain directions for these two components. In  FIGS. 2 ,  4  and  7 , double-ended arrows  56   a ,  58   a  represent the extension directions, and thus the grain directions, of the TLB fibers in core-wrap components  56 ,  58 , respectively. Several specific TLB fibers in components  56 ,  58  are shown in  FIGS. 7–9 , inclusive, at  56 A,  56 B, respectively. 
   What will be observed is that these TLB fibers in the two core-wrap components ( 56 ,  58 ) are disposed at angles relative to one another, and specifically preferably at right angles relative to one another, in those portions of the wrap components which extend effectively in the planes of the strike and non-strike sides of panel  20 . This angularity is shown clearly in  FIG. 8 . Where, however, these core wrap components are folded to extend as respective continuums along the edges of panel  20 , the grain directions, and the TLB strands, in both core-warp components parallel one another, and specifically extend generally normally between the planes of the opposite faces, or sides, of panel  20 . This is clearly illustrated in  FIGS. 7 and 8 . 
   Those portions, or stretches, of TLB aramid fiber strands in the core-wrap components which extend essentially across the faces of panel  20  are referred to as being first stretch, or strand, portions of these fibers, and those portions which extend on and along the edges of panel  20 , between the strike and non-strike sides of the panel, are referred to herein as being second stretch, or strand, portions of these same TLB strands. Within each TLB fiber, or strand, the so-called first and second stretches are continuums with respect to one another. 
   As was mentioned earlier herein, the portions of core-warp components  56 ,  58  which are disposed along the edges of panel  20   a  are bonded to material  54 . 
   Completing a description of panel  20  per se, outer elastomeric coating  32  is formed herein by spraying onto the core-wrap structure the TUFF COAT® product mentioned above in the portion of this description which outlines preferred materials for use in the making of panel  20 . This coating material, because of its extreme high elasticity, substantially closes back upon itself to self-heal a puncture wound. This behavior helps to capture and contain internally generated projectile and tile fragmentation to defeat spall. 
   Significantly, in the interfacial region between this coating and the engaged portions of the core-wrap components, there is established a robust, load-transmitting bond between these elements of panel  20 . This bond is formed by mechanisms including (a) direct adhesion between the surfaces of the aramid fibers in the core-wrap components and the elastomeric coating, (b) flowing of the elastomeric material into the interstices between crossing strands in the weaves of the core-wrap components per se, and (c) capillary-action entrainment of a certain amount of elastomeric material within the bodies of the woven aramid fibers per se. This load-transmitting, intimate bonding relationship just described plays an important role in enhancing what is referred to herein as the trampoline-response behavior of panel  20  on the occurrence of a projectile strike on the strike side, or face, of the panel. 
   Turning attention now briefly collectively to  FIGS. 4–6 , inclusive, here there is very generally outlined an assembly process for panel  20 . One should understand that components of the panel illustrated in these three figures are not necessarily drawn to scale. 
     FIG. 4  illustrates a preliminary assembly of almost all of the materials which make up panel  20 , and specifically, with these materials in a condition ready for cross wrapping and folding of the two core-wrap components ( 56 ,  58 ) to envelop the stacked, layered core structure of the panel.  FIG. 5  illustrates the assembly condition which exists after such core-structure enveloping, and hot-melt adhesive bonding, at appropriate locations, for the edges of the core-wrap components.  FIG. 6  illustrates a condition after at least the strike face and the lateral edges of the structure of  FIG. 5  have been sprayed with the desired, outer, high-elastomeric coating ( 32 ). 
     FIGS. 7 ,  8  and  9  effectively isolate from other structural components the fabric stranded structures of the two core-wrap components to illustrate the respective dispositions of their grain directions and TLB strands. The large darkened dots in these three figures represent TLB strands which extend essentially normally to the planes of these three figures. 
     FIGS. 10A ,  10 B illustrate aspects of the broad-beam trampoline nature of, particularly, the edge bound back-up layers. The whole edge bound back-up layer assembly is shown in plan view in  FIG. 10A , and in  FIG. 10B , transverse cross sections are illustrated as taken along the three angularly offset view lines (a), (b) and (c) in  FIG. 10A . What one can see in these three sectional views is that, with respect to every transverse section view (just three being shown) taken in a plane which is substantially normal to the nominal plane of the assembly of the back-up layers, the back-up layer assembly effectively looks like a laminated, elongate beam structure. Dashed, curved lines  62  in  FIG. 10B  illustrate “beam-bending” as a reaction response to an impact strike on panel  20 . The fact that the entire perimeter edge structure of the assembly of back-up layers is unified by the earlier mentioned edge-binding structure results in the entirety of the assembly of back-up layers functioning somewhat like a broad-beam trampoline. The word “broad” is herein used to reflect the fact that each back-up layer provides a broad-area structure for responsive action. 
   Turning finally to  FIGS. 11–13B , inclusive, and to  FIG. 16 , here, certain very simplified and schematic views are presented further to illustrate trampoline reaction response to the impact of a projectile. To simplify these two figures, strike layer  34  is omitted. 
   In  FIG. 11 , the upper view labeled (a) represents the back-up layer assembly in panel  20  in a planar and undeflected state before a projectile impact. The lower view labeled (b) illustrates a trampoline-like reaction downward bowing of panel  20  after an impact. 
     FIG. 12  represents about the same projectile-reaction condition which is shown in the lower view in  FIG. 11 , picturing the relationship which exists between elastomeric coating  32 , core-wrap structure  30 , and the back-up layer assembly. Flexing and stretching of coating  32  “arms” the coating to spring back, so-to-speak, thus enhancing trampoline-response behavior of panel  20 . 
   In  FIG. 13A , two, oppositely directed arrows  64 ,  66  are placed over the edge image of a fragmentary potion of the assembly of back-up layers to illustrate the fact that, while the edges of the back-up layers are not permitted to move relative to one another, when the broad facial expanses of these layers flex in response to an impact, a facial sliding motion takes place, and is accommodated as the layers react to the impact. This sliding motion, through facial frictional engagement, serves to dissipate impact energy. 
   In  FIG. 13B , here shown is a facial view of a projectile-created point impact which is non-symmetric with respect to the central region of the footprint of the assembly of back-up layers. Radially outwardly pointing arrows, such as those designated  68  in this figure, help to tell the story that the kind of slide-motion interaction which is permitted facially between adjacent layers in the collection of back-up layers develops substantially radially centrally with respect to the illustrated impact, thus relatively uniformly dissipating energy essentially symmetrically with respect to the point of panel/projectile impact. 
     FIG. 16  in the drawings, which presents a highly stylized and simplified edge view of panel  20 , is provided herein to highlight an observed phenomenon involving the outward bulging, see B in  FIG. 16 , in the direction of a incoming and impacting projectile represented by an arrow  70 . What is believed to result, momentarily and immediately after a projectile impact, is the internal generation of a kind of pressure-wave explosive event taking place inside panel  20  as a projectile enters, fragments a tile, and produces trampoline action. This explosion-like event is represented by the darkened patch shown at  72  in  FIG. 16 . This observed reaction of the panel of this invention strongly suggests that, in addition to its remarkable capability for defeating penetration damage by a projectile, the panel is also very well equipped, at least with respect to the cooperative performances of the core-wrap structure and the elastomer coating, to deal with broad area force events, such as a blast or explosion event. 
   Thus, a preferred embodiment of the armor panel of this invention has been described. The panel features unique cooperative relationships between (a) a layered core structure, including a tiled strike-layer, and a stack of edge-bound, slide-face fabric-material back-up layers, (b) a cross-grain, fabric-material core-wrap structure which envelops the core structure with specially “directed” tension-load-bearing, grain-direction fibers, and (c) an outer coating of a self-healing high-elastomeric material which is appropriately bonded to the core-wrap structure. Hardened-material tiles in the strike-layer are set in an elastomeric resin which inhibits shatter-telegraphing between tiles. 
   Following a projectile strike which is first greeted by the self-healing elastomeric coating, and then energy-dissipated by tile fragmentation, there follow a trampoline-like-energy-quelling response principally offered by the cooperative stack of flex back-up fabric layers which are specially edge bound against relative edge movement, but which are permitted to slide relative to one another in facial frictional engagement for further energy-dissipation action. Trampoline action is enhanced by load-transmission bonding which exists between the back-up core layers, the core-wrap structure, and the outer elastomeric coating. 
   While a preferred embodiment of, and manner of practicing, the invention are thus fully set forth herein, we appreciate that variations and modifications, such as material-type and component-count variations and modifications, may be made without departing from the spirit of the invention.