Patent Publication Number: US-10775139-B2

Title: Debris-free combustible aerial shell with improved pyrotechnic dispersion

Description:
FIELD OF THE INVENTION 
     This invention relates to a pyrotechnic/firework effect containing combustible aerial shell that achieves an improved time delay compared to conventional fuse to ignite a main burst of the aerial shell to thereby disperse secondary contained pyrotechnic/firework effects with controlled pyrotechnic effect dispersion whereby debris remaining from the aerial shell following ignition of the main burst is substantially reduced or eliminated. 
     BACKGROUND OF THE INVENTION 
     Most fireworks or pyrotechnics launch projectiles or pyrotechnic effects from launch tubes that may include one-use disposable cardboard tubes. An aerial shell is an example of a pyrotechnic (fireworks) projectile, where the volume inside the shell is loaded with fireworks effects adjacent to or packed within a dispersive explosive, together referred to as a main burst. The pyrotechnic effects may include many different types of effects such as colored stars, hummers, whistles, etc. In conventional operation, upon detonation of the dispersive explosive, the pyrotechnic effects are dispersed and are subsequently ignited to give a typical visual pyrotechnic effect, such as one or more of colorful, sparkling, and/or streaming effects. 
     The projectiles come in many different shapes and sizes and shapes, but all are typically launched from a launcher (such a tube) with a lift charge which may be contained in an outer shell of the projectile and/or within the launch tube. For example, one suitable low-smoke producing launching system that may be used is found in U.S. Pat. No. 9,062,943, the disclosure of which is hereby incorporated by reference herein in its entirety. 
     Several factors contribute to the pyrotechnic projectile being successfully raised to a desired selected altitude within a selected time and with a subsequent successful main burst and dispersion of a pyrotechnic effect display. For example, the type and amount of lift charge used to propel the projectile, the size and weight of the projectile, the shape of the projectile, and the time delay of a fuse to ignite the main burst, are some of the many factors that may be desirably controlled. 
     For example, exemplary nitrocellulose and nitroguanidine based smokeless powders may be used within the lift charge (or within the dispersive charge enclosed within the aerial shell) are described in U.S. Pat. No. 9,217,624 “Spooling pyrotechnic device” which is hereby fully incorporated herein by reference. 
     Projectiles that include aerial shells containing fireworks effects have typically been constructed with a shell made from non-combustible materials or materials that cannot easily sustain combustion, such as paper, cardboard, molded plastic, glue, pressed wood particles, and tape. 
     In cases where the projectiles have included a fuse delay, the fuse delay has typically included chemical fuses such as columns of slow burning combustible material (self sustaining combustion) located below the main burst within a projectile or shell. In addition, a typical delay fuse may take the form of a chemical or electronic fuse that may penetrate the main burst from outside the aerial shell. 
     One problem with prior art chemical fuse systems has included the reliable lighting of the fuses upon launch and a sustainable burn rate of the fuses during flight. 
     One significant problem with prior art projectiles is projectile debris fallout upon explosion of the main burst. The projectile debris fallout may be undesirable in terms of obvious environmental and safety concerns. Some approaches in the prior art taken to address debris fallout have been to make the material of the projectile/shell destructible into a finer debris upon main burst explosion. 
     Another associated problem has been the requirement that the shell/projectile be formed of materials sufficiently strong to withstand resulting forces during and after launch and as well as the use of materials that may be produced without associated manufacturing non-uniformities that may degrade aerodynamic properties. 
     Therefore there is a continuing need in the art to provide a predictable and sustainably burning delay fuse associated with a pyrotechnics effects aerial shell that has improved aerodynamic properties and which upon main burst explosion produces little or substantially no debris. 
     It is therefore among the objects of the invention to provide a predictable and sustainably burning delay fuse associated with a pyrotechnics effects aerial shell that has improved aerodynamic properties and which upon main burst explosion produces little or substantially no debris. 
     These and other objects, aspects and features of the invention will be better understood from a detailed description of the preferred embodiments of the invention which are further described below in conjunction with the accompanying Figures. 
     SUMMARY OF THE INVENTION 
     In an exemplary embodiment, An aerial shell comprising at least one combustible layer of combustible material, the at least one combustible layer including an outermost combustible layer surrounding the at least one combustible layer, the outermost combustible layer configured to ignite on substantially an entire outer surface, the outermost combustible layer including a relatively higher combustion rate than the at least one combustible layer; the at least one combustible layer including an innermost combustible layer surrounding and containing at least one pyrotechnic effect and a dispersive explosive charge; the at least one pyrotechnic effect is preferentially disposed with respect to the innermost combustible layer at least one of immediately adjacent including integral with an inner surface of the innermost combustible layer and spaced away from the inner surface of the innermost combustible layer; the at least one combustible layer configured to burn substantially throughout the at least one combustible layer. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The disclosure will now be made, by way of example, with reference to the accompanying drawings, in which: 
         FIG. 1A  is a schematic illustration of an exemplary spherical shaped combustible aerial shell according to embodiments. 
         FIG. 1B  is a schematic illustration of an exemplary cylindrical shaped combustible aerial shell according to embodiments. 
         FIG. 1C  is a schematic illustration of an exemplary combustible aerial shell showing an arrangement of pyrotechnic effects according to embodiments. 
         FIG. 1D  is a schematic illustration of an exemplary combustible aerial shell showing an arrangement of pyrotechnic effects according to embodiments. 
         FIG. 1E  is a schematic illustration of an exemplary combustible aerial shell showing an arrangement of pyrotechnic effects according to embodiments. 
         FIG. 1F  is a schematic illustration of an exemplary combustible aerial shell showing an arrangement of pyrotechnic effects according to embodiments. 
         FIG. 2  is a schematic illustration of an exemplary combustible aerial shell in a launcher according to embodiments. 
         FIG. 3  is a schematic illustration of an exemplary combustible aerial shell launched from a launcher according to embodiments. 
         FIG. 4  is a schematic illustration of an exemplary method of forming and using a combustible aerial shell according to embodiments. 
     
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
     Referring to  FIGS. 1A-1F , in embodiments a combustible aerial shell  100  is provided that fully encloses a volume that contains a dispersive explosive charge e.g.,  108  and one or more pyrotechnic (fireworks) effects, e.g.,  110 . 
     It will be appreciated that the aerial shell  100  may be in any shape such as spherical with a circular cross section, and cylindrical with a rectangular cross section. Exemplary embodiments are shown as spherical in  FIGS. 1A, and 1C-1F , and as cylindrical in  FIG. 1B . It will be appreciated that the arrangement of the pyrotechnic effects  110  in  FIGS. 1C-1F  may be adapted to aerial shells having different cross sectional shapes including cross sectional shapes determined by the inner cross-sectional shape of the mortar (launcher). 
     For example, the aerial shell  100  may be in any shape such as spherical, cylindrical or prolate spheroidal (e.g. football shaped), as long as the cross section at the widest part of the shape of the aerial shell (e.g., outer diameter) is about the same or smaller than the cross section (e.g., inner diameter) of the mortar. 
     It will be further appreciated that aerial shells can be launched from square or triangular cross-sectional shaped mortars, where the smallest inside width of the launch opening cross section of the mortars is preferably about the same to larger than the largest outer width of the cross-section of the aerial shell, which may have a similarly shaped cross-section as that of the mortar. 
     By the term pyrotechnic effects is meant combustion driven effects such as explosions, flashes, smoke, flames, fireworks or other audio and/or visual effects. By the term a “combustible” is meant a self sustaining combustion driven by burning of energetic material. By the term energetic material is meant one or more of explosives, pyrotechnic compositions, fireworks, propellants and fuels. 
     In another embodiment, the combustible aerial shell  100  is configured to function as a delay fuse to ignite the dispersive explosive charge  108  at a preselected altitude following launch from a launcher or mortar e.g.,  200 . 
     In another embodiment, the combustible aerial shell  100  may include a relatively high combustion rate (primer) of combustible material  104  as an outermost relatively integrated thin portion or layer of the aerial shell or as a thin layer coating on the outermost surface of the aerial shell (e.g., combustible layer  102 ). 
     In another embodiment, the combustible aerial shell  100  may be configured to ignite within a launch tube  202  (see  FIG. 2 ) such as by ignition of an outer primer portion  104  and/or combustible layer  102  to subsequently burn throughout or on substantially the entire outer surface of the aerial shell (e.g., combustible layer  102 ), the combustion occurring in a direction toward the contained dispersive explosive charge  108 . 
     It will be appreciated that the outer primer portion  104  (outermost combustible layer) may be ignited within the launch tube (launcher)  200  (see  FIG. 2 ) by at least one of a lift charge e.g.,  204  and/or one or more columnar shaped (tubular/string like) conventional fuses e.g.,  106  (see  FIG. 1A ) attached to a selected portion of the outermost combustible layer  104 . 
     For example one or more conventional fuses  106  (primary fuse) such as one or more of an electric match, squib, and black powder fuse device e.g. may be attached to a selected portion of the primer layer  104  and/or the outermost combustible layer  102 , where the fuse  106  may be ignited by the lift charge or other means within the launch tube such as by an igniter fuse including one or more of electric matches, squibs, or black powder fuse devices. 
     As is known in the art, electric matches include a resistive wire (bridgewire) embedded in an ignitable material (pyrogen) which ignites upon applying an electric current to the resistive wire which in turn may ignite a fuse. 
     For example, as is known in the art, squibs may include a small tube (e.g., 2-15 mm diameter) filled with an explosive substance, with a detonator running longitudinally through the core. The detonator may be a wire connected to a remote electronic trigger for remote detonation. 
     Black powder fuse devices may include a combustible string, such as cotton covered with black powder which may further be embedded in a combustible tube and may include fuses known by popular names such as quickmatch, blackmatch, and crossmatch. 
     In some embodiments, the fuse  106  may be ignited by any method known in the art. The primary fuse  106  may in turn subsequently ignite the outermost combustible layer  104  and/or the combustible layer  102  within or outside the launch tube. 
     It will be appreciated that in some embodiments, the aerial shell may be launched from non-explosive mortars such as compressed air driven mortars and where a primary fuse e.g.  106  may be attached to a selected surface portion of the primer layer  104  and/or combustible layer  102  and the primary fuse e.g.,  106  may be ignited by explosive or non-explosive means such as electric matches, squibs, black powder devices or any other method known in the art to thereby subsequently ignite the primer layer  104  and/or combustible layer  102 . 
     In one embodiment the combustible aerial shell comprises at least one combustible layer e.g.,  102  which comprises an energetic material which may have substantially the same composition substantially throughout the at least one combustible layer. 
     By substantially the entire outer surface of the aerial shell, it is meant from about 70% to about 100 percent of the outer surface, more preferably from about 90% to about 100 percent of the outer surface. 
     By substantially the same composition substantially throughout the at least one combustible layer is meant that the at least one combustible layer has a composition that is about the same throughout with respect to a weight percent of each ingredient determined with respect to the total weight of the combustible layer where each ingredient weight percent may vary within a range of about 0% to about 10% of the respective ingredient weight percent, more preferably within a range of about 0% to 5% of the respective ingredient weight percent. 
     In another embodiment, the combustible aerial shell (e.g., combustible layer  102 ) may be configured to substantially combust (burn) the ignited surface of the combustible aerial shell at a substantially uniform rate. 
     Preferably, the combustible aerial shell (e.g., combustible layer  102 ) is combusted and burns on substantially the entire surface at substantially the same rate so that the aerial shell burns through substantially the full thickness of the combustible aerial shell (e.g., combustible layer  102 ) toward the contained dispersive explosive charge  108  at substantially the same rate (e.g., within plus or minus 0% to about 10%) to thereby ignite the dispersive explosive  108  (main burst). 
     By substantially the entire thickness is meant, from about 80% to about 100 percent of the thickness, more preferably from about 90% to about 100 percent of the thickness. 
     It will be appreciated that there may be some variability in the thickness of the combustible aerial shell (such as corner portions of cylindrical shaped shells) as well as variations in the burn rate along portions of the shell (e.g., combustible layer  102 ) as noted above. 
     However, preferably the thickness of the combustible aerial shell (e.g., combustible layer  102 ) may be substantially about the same e.g., within a variation of about 0% to about 10% over from about 80% to about 100% of the surface, more preferably having a thickness variation of about 0% to about 5% over from about 90% to about 100% of the surface. 
     In addition, the preferred limits on thickness variations may be sufficiently small to allow for acceptable aerodynamic properties (e.g., minimal variations in drag) together with minimal shell debris upon explosion of the main burst  108 . 
     For example in some embodiments outer corner portions on non-spheroid aerial shells (e.g., combustible layer  102  of corner portions of cylindrical shells in  FIG. 1B ) may be thicker than on wall portions, however this thickness variation at corner portions may be reduced by rounding of the thicker corner portions. 
     It will further be appreciated that any minimal amount of shell debris remaining following explosion of the main burst  108  may continue to burn relatively rapidly to thereby substantially eliminate the debris prior to reaching the ground. 
     In addition, the combustion rate of the aerial shell (e.g., combustible layer  102 ) may be substantially the same through the thickness over substantially the entire surface, such as having variations in the combustion rate to be from about preferably within about 0% to about 10%, more preferably from about 0% to about 5% over from about 90% to about 100% of the surface. 
     Referring again to  FIG. 1A  is shown a circular cross section of a spheroidal shaped aerial shell  100  with a combustible layer  102 . It will be appreciated that the aerial shell  100  may be formed in any shape, including a cylindrical shape having a rectangular cross sectional shape as shown in  FIG. 1B . 
     For example, the aerial shell  100  may be formed in non-spherical shapes such as ellipsoidal or spheroidal shapes, so long as the widest cross section dimension of the shape is about the same or smaller than the smallest width cross section dimension (inner diameter) of the mortar. 
     Preferably the aerial shell is formed in a shape such that widest outer cross sectional dimensions of the shape may substantially mate with the inner diameter dimensions (walls) of a launcher (e.g., having about the same to smaller outer cross sectional dimension with respect to the inner cross sectional dimension of the launcher walls), preferably to have a desirably efficient launch from the lift force source such as ignition of the launch charge  204 . In one embodiment, the outer edges (dimensions) of the aerial shell (e.g., including outer primer layer  104 ) are disposed within about 0 to about 10% of the diameter of the outer edges of the aerial shell with respect to the inner walls of the launcher when place in a launcher (mortar), e.g.,  200 , as shown in  FIG. 2 . 
     In another embodiment, the combustible layer  102  may be formed upon a relatively thin support layer  102 A (innermost combustible layer), that also may be combustible, which may have a thickness about 1% to about 10% of the combustible layer  102 , and which may have a combustion rate greater or less than that of combustible layer  102 A. It will be appreciated that multiple layers of combustible material may be used to form the aerial shell. 
     In some embodiments, at least one relatively high combustion rate layer may be configured to overly, or be interleaved with, relatively lower combustion rate layers. 
     For example, in one embodiment, a separate or integrated high combustion rate portion e.g.,  104 A (acting as a primer/igniter) may be disposed between the combustible layer  102  and the support layer  102 A such as being disposed on the outer portion of support layer  102 A (or inner portion of combustible layer  102 ) e.g. coated on the outer portion of  102 A (or inner portion of  102 ) and/or integrated into  102 A and/or  102 . The high combustion rate portion (inner primer layer)  104 A may have a combustion rate that is greater than that of support layer  102 A and/or combustible layer  102 ). For example, the combustion rate of the high combustion rate portion  104 A may have a combustion rate from about 5 to about 50 times greater that the combustion rate of the support layer  102 A and/or combustible layer  102 . It will be appreciated that the support layer  102 A may be combustible and include a material such as nitrocellulose. 
     In a related embodiment, a separate or integrated high combustion rate portion e.g.,  104  (acting as a primer/igniter) may be preferably disposed on the outermost portion of the combustible layer  102 , where the high combustion rate portion  104  has a combustion rate that is greater than that of combustible layer  102 . For example, the combustion rate of the high combustion rate portion (layer)  104  may have a combustion rate from about 5 to about 50 times greater that the combustion rate of the combustible layer  102 . 
     In one embodiment, the high combustion rate portion (primer) e.g.,  104  on combustible layer  102  and/or  104 A on support layer  102 A may have a thickness about 1% to about 20% of the thickness of the adjacent combustible layer  102 . It will be appreciated that the primer material may be coated by conventional methods onto underlying layers such as the combustible layer  102  and/or a support layer  102 A following formation of the respective layer. Such coating methods may include spraying, painting, dipping, vapor deposition or any other coating technique. 
     In a preferred operation, the relatively higher combustion rate layer  104  may be configured to ignite from the launch charge gases following ignition of a lift charge e.g.,  204  within the launcher  200  (see  FIG. 2 ), and where substantially the entire surface combustible layer  102  is ignited as it is propelled upward and/or out of the launcher  200 . 
     In other embodiments, the relatively higher combustion rate layer  104  and/or combustion layer  102  may be ignited by one or more fuses e.g. fuse  106  (see  FIG. 1A ) attached to the respective higher combustion rate layer  104  and/or combustion layer  102 . As previously noted, the fuse may be ignited by the launch charge gases following ignition of a lift charge, or by other conventional means such as one or more of a electric match, squib, and black powder fuse device, which in turn may ignite the respective higher combustion rate layer  104  and/or combustion layer  102  within or outside the launch tube. 
     The aerial shell  100  and associated combustible layers, e.g., combustible layer  102 , may be formed with a selected substantially uniform thickness, for example varying by about 0% to about 10% of the thickness. It will be appreciated that the combustion rate of the aerial shell will depend on several factors including properties and materials of the combustible layers. 
     Preferably, the burn (combustion) rate of the aerial shell is substantially uniform along the entire surface of the aerial shell, for example having a variation of from about 0 to about 10%, more preferably from about 0% to about 5%. 
     In some embodiments, one or more pyrotechnic effects  110  may be disposed within or adjacent to the explosive dispersant  108  which may include one or more fuels and/or oxidizers including those ingredients listed below as additives for the combustible layer  102  including one or more of ammonium and/or metal nitrates, perchlorates, phosphates, carbonates, aminotetrazoles, arsenites, oxalates, oxychlorides, peroxides, oxides, sulphates, fluorides, and metal powders. Preferably the explosive dispersant  108  has a combustion rate that is explosive, e.g., combusts at rates typical to produce an energetic explosion. 
     In some embodiments, as shown in  FIG. 1C , one or more pyrotechnic effects  110  may be preferentially disposed adjacent such as immediately adjacent the innermost portion (inner surface) of combustible layer  102  or innermost portion of support layer  102 A. 
     For example, preferentially disposing the pyrotechnic effects  110  such as immediately adjacent the innermost portion (inner surface) of combustible layer  102  and/or innermost portion of support layer  102 A may allow control over the dispersion of the pyrotechnic effects  110 , for example to be dispersed in a more evenly and widely dispersed pattern following ignition of the dispersant charge  108 . 
     In a related embodiment, as shown in  FIG. 1D , the pyrotechnic effects  110  can be molded onto or shaped for attachment to the inner surface of  102 A (or  102 ) by glue and/or conventional mechanical means. 
     In another related embodiment, as shown in  FIG. 1E , the pyrotechnic effects  110  may be molded onto or shaped to be made integral with the inner surface of combustible layer  102  or support layer  102 A. For example, a single or multi-piece structure having pyrotechnic effects  110  integral with or attached to the inner surface of combustible layer  102  or support layer  102 A may be made by conventional molding, pressing and/or 3D printing and/or gluing and/or mechanical means. 
     In preferred operation, during combustion of the entire outer surface of the combustible layer  102  (forming a combustion front), the combustible layer  102  may decrease in diameter at substantially the same rate until the combustion front reaches an inner diameter such as  102 B (which may coincide with inner surface of  102 A or an inner surface  102 C of  102 , which may be immediately adjacent explosive dispersant  108 ), whereupon the combustion front may ignite the explosive dispersant  108  and propel the pyrotechnic effects  110 . 
     It will be appreciated that the chemical makeup of pyrotechnic effects  110  may be different from or the same as that of combustible layer  102  and/or support layer  102 A. 
     In another embodiment, as shown in  FIG. 1F , the one or more pyrotechnic effects  110  may be preferentially disposed spaced away from the innermost portion of the combustible layer  102  and/or support layer  102 A, such as preferentially disposed toward a central portion of the aerial shell containing the explosive dispersant  108 . 
     For example, preferentially disposing the pyrotechnic effects  110  such as spaced away from the innermost combustible layer and/or support layer  102 A toward a central portion of the aerial shell may allow control over the dispersion of the pyrotechnic effects  110  upon ignition of the explosive dispersant, for example in a more tightly dispersed pattern. 
     It will be appreciated that the explosive dispersant  108  may be disposed between and/or adjacent to, for example to surround the pyrotechnic effects  110  to achieve a predetermined density of pyrotechnic effects  110  with respect to the explosive dispersant  108 . 
     In some embodiments other ingredients such as colorants or other pyrotechnic effect producing additives may be present in the combustible layer  102  and may be configured to burn with a pyrotechnic effect during flight following launch. 
     For example, the combustible layer  102  may include fuels and/or oxidizers (which may also function as colorants). 
     In one embodiment, the combustible layer  102  may include fuels such as nitrocellulose, including low-smoke formulations including nitro-guanidine and nitrocellulose as outlined in U.S. Pat. No. 6,599,379, “Low-smoke nitroguanidine and nitrocellulose based pyrotechnic compositions” which is incorporated herein by reference. For example, the nitrocellulose may be in powder or fiber form. 
     In some embodiments the combustible aerial shell (e.g., combustible layer  102 ) may further include one more fuels as are known in the art including metal fuels such as magnesium, aluminum, silicon, calcium, iron, titanium, zinc, and their alloys, and including non-metal fuels such as charcoal, sulfur, boron, hexamine, nitroguanidine, dextrin, camphor, red gum benzoic acid, and cellulose. The amount of fuels in the combustible aerial shell composition (e.g., combustible layer  102 ) may be from 0-80 wt. % based on the total weight of the respective layer e.g., combustible layer  102 . 
     In another embodiment, pyrotechnic producing additives such as transition and rare earth element containing materials, e.g., containing elements such as Mg, Sr, Ti, and the like may be present in relatively low amounts for visual effects e.g., less than about 10 wt. % In addition, visual effect producing materials (e.g., including one or more of color, spark, and flash effects) (colorants) may be included such as chlorine containing materials and metal colorants as are known in the pyrotechnic art including one or more of Sr(NO)3, SrCO3, PARLON™, Ammonium Perchlorate (AP), hexachloroethane, paroils (chlorinated short-chain hydrocarbons) and polyvinylchloride (PVC), and the like. 
     For example, colorants and/or oxidizers as are known in the art may be provided in the aerial shell (e.g., combustible layer  102 ) including one or more of ammonium and/or metal nitrates, perchlorates, phosphates, carbonates, aminotetrazoles, arsenites, oxalates, oxychlorides, peroxides, oxides, sulphates, fluorides, and metal powders. 
     In some embodiments the colorants and/or oxidizers may be present in an amount of from about 10 to about 90 wt. %, more preferably, in an amount less than about 80 wt % respect to the total weight of the combustible aerial shell (e.g., combustible layer  102 ). 
     In other embodiments, e.g., for low smoke formulations, the colorants and/or oxidizers may be present in an amount of amount from 5 to 50%, preferably less than 35% respect to the total weight of the respective combustible aerial shell layer (e.g., combustible layer  102 ). Low-smoke formulations may have relative large amounts of nitrocellulose, or a combination of nitrocellulose and nitroguanidine, for example from about 30 to about 90 wt %. 
     In one embodiment the combustible aerial shell including combustible layer  102  may be produced by one or more shape formation methods known in the art such as high or low pressure pressing methods, with or without a solvent, such as conventional hot press or cold press methods. 
     In another embodiment, molding methods, such as conventional wet or dry molding methods may be used to shape form the combustible aerial shell layer  102 . 
     In other embodiments, 3-D printing methods may be used to form one or more of the layers in a combustible aerial shell, such as support layer  102 A, and layer  102 , including and including associated igniting or primer layers e.g.,  104 . It will be appreciated that the one or more layers may be provided in one or more of a molten state, a solution, a viscous solid, and/or an uncatalyzed/uncured binder-containing material. It will further be appreciated that 3-D printing methods may be used to “print” (form) the combustible aerial shell  100  (e.g., including combustible layers  102 A,  102 , and  104 ,  104 A) into a final combustible shape, which may be treated to catalyze/cure the layers between printing of layers and/or following printing of a completed layered shape. 
     In one embodiment, the combustible aerial shell may be shape formed in one or more pressed or molded pieces and then attached along seams (e.g.,  105 ), for example, with a combustible glue, to surround a main burst disposed within, e.g., including the dispersive charge e.g.,  108 , and one or more pyrotechnic effect pieces e.g.,  110 , such as stars, streamers, hummers, whistles, or any other pyrotechnic effect. 
     In one embodiment, the combustible aerial shell layer  102  may include cross-linkable organic polymers, such as in a binder or additive, the cross linking taking place during or following shape forming, for example, using a cross linking treatment including one or more of heating, radiation, and/or addition of cross linking catalysts and/or accelerants. It will be appreciated that cross-linking includes polymer linkages formed in a directions transverse to other polymer linkage directions to thereby form a polymer linkage web-like pattern. 
     In some embodiments, a liquid-phase binder may be used to form the combustible aerial shell layer  102 . The binder may be mixed with granular material comprising combustible (energetic) material such as fuels used for the combustible aerial shell layer  102  and other pyrotechnic effect producing additives. 
     In other embodiments the binder may be a solid binder dissolved in a solvent, or partially dissolved in solvent, or softened by solvent or a mixture of solvents. 
     In some embodiments, the solid or liquid binder may include one or more of polymers or copolymers of polyvinyl nitrate, nitrocellulose, polyvinyl chloride, polyvinyl acetate, and chlorofluoroethylene. 
     In other embodiments, the binder may include one or more polymerizable or cross-linkable materials such as thermosetting polymers, rubber, including one or more of polybutadiene, polyurethane, furans, and organic resins such as acrylic resins, polyester resins, epoxy resins, vinyl and vinyl ester resins. 
     In some embodiments, during the aerial shell layer  102  formation process, e.g., following the addition of the combustion producing ingredients and the pyrotechnic effect producing ingredients and following a shape forming process, the binder may be polymerized (including cross-linked), e.g., by the addition of a cross-linking catalyst and/or accelerator and/or heating and/or irradiating the shaped composition. 
     Referring to  FIG. 2 , in operation, the projectile including the aerial combustion shell  100  is placed within a launcher  200  e.g., supported on a support  208  overlying a lift charge  204  and an ignition source such as a fuse or electric match  206 . 
     For example, the lift charge  204  may be a conventional loose, pressed, and/or contained explosive lift charge including one or more of black powder, nitrocellulose and other explosively combustible ingredients. 
     In operation, the ignition source  206  ignites the lift charge  204  which produces an explosive force including heated gases which propel the projectile  100  upward within the launcher  200 . While still within the launcher  200 , the outermost high combustion (primer) layer  104  is ignited by the hot gases and in turn acts to ignite the aerial combustion shell layer  102  within and/or outside of the launcher. 
     Referring to  FIG. 3 , in one preferred operation, the aerial combustion shell (e.g. combustible shell layer  102 ) burns during flight  302  as it is propelled upward to an apex. The aerial combustion shell may include a pyrotechnic effects (e.g.,  110 ) packed in a dispersive explosive charge (e.g.,  108 ). aerial combustion shell (e.g. combustible shell layer  102 ) preferably substantially uniformly burns at about substantially the same selected rate (e.g. as a result of combustible composition formulation) along substantially the entire surface and ultimately through substantially the entire thickness of the combustion shell  102 , preferably completing the burn through the shell thickness at a preselected altitude, such as an apex of the launch. The main burst or dispersive explosive  108  is then exploded  304  to disperse one or more pyrotechnic effects  110 , e.g., in a predetermine pattern e.g.,  306 , which thereby in turn ignite and/or produce pyrotechnic effects during their dispersive flight  308 . 
     Thus, the aerial combustible shell operates as a timed fuse delay with improved aerodynamic properties, improved predictable timing, with controlled pyrotechnic effect dispersion and with little or no debris remaining following the main burst. 
     Referring to  FIG. 4  is shown a method according to an embodiment. 
     In step  402 , a combustible aerial shell is provided comprising a one or more combustible layers of material which may optionally include a pyrotechnic effect producing material and which may be formed into a shell shape with a predetermined thickness and predetermined combustion rate, the shell containing at its core an explosive dispersant and one or more pyrotechnic effects arranged in a predetermine pattern within the core to control a dispersion of the pyrotechnic effects upon ignition of the explosive dispersant. 
     In Step  404 , the combustible aerial shell may be coated over substantially the entire outer surface with a high combustion rate material layer. 
     In Step  406 , the combustible aerial shell may be placed in a launcher and launched into the air with a preselected force. 
     In Step  408 , the combustible aerial shell may be ignited within and/or outside of the launcher over substantially the entire outer surface to burn through the predetermined thickness at the predetermined combustion rate. 
     In Step  410 , the combustible aerial shell may burn through the predetermined thickness and ignite and disperse the pyrotechnic effects at a desired altitude to form a pyrotechnic display. 
     Although the embodiments of this disclosure have been described with respect to certain exemplary embodiments, it is to be understood that the specific embodiments are for purposes of illustration and not limitation, as other variations will occur, to those of skill in the art.