Abstract
A cartridge incorporating a projectile assembly, the projectile assembly having a base, mid body component housing a marking powder and metallic nose cap. The projectile's mid-body component houses liquids in a cylindrical compartment, where set-back and rotation induce chemical mixing, and in flight allowing for a chemical reaction, and at impact the projectile undergoes wall failure in the mid body, resulting from shear and residual rotational momentum, the actions in combination releasing and expelling marking materials, the ejection suspended signature producing materials, including liquid, powdered metals or fine particles released into the atmosphere emit and reflect light, the signature materials producing an observable signature at the projectile's impact location.
Claims
1. A gun fired ammunition cartridge incorporating a spin stabilized projectile, said projectile comprising: (1) a metal ogive comprising a forward metal bore riding feature, (2) a mid-body frangible cylindrical assembly coupled to the forward metal bore riding feature at a forward end, the mid-body cylindrical assembly incorporating a cylindrical capsule configured to house a liquid marking payload comprising one or more chemical liquid materials, and to be aligned to the projectile's axis of rotation, and proximate to the projectile's center of gravity; and (3) an aft metal base comprising a driving band, wherein the cartridge retains strength when compressed upon being loaded into a weapon, and upon firing, the projectile's break-up ejects the liquid marking payload perpendicular to the projectile's direction of flight.
2. The ammunition cartridge in claim 1, wherein the forward metal bore riding feature in combination with the driving band allows the projectile to be spun-up when transiting a barrel, the projectile's exterior features imparting rotational forces about the projectile's center of gravity.
3. The ammunition cartridge in claim 2, wherein rotation imparted on the projectile transiting the barrel induces rotational laminar flow in the cylindrical capsule about the projectile's axis of rotation, said projectile exhibiting minimal yaw and pitch at a muzzle exit such that perturbations resident in the liquid marking payload are minimized and the projectile has a stable ballistic flight in a flight path in direct fire.
4. The ammunition cartridge in claim 1, wherein said cylindrical capsule includes one or more segregated compartments allowing for segregation of respective one or more chemical liquid marking materials in storage.
5. The ammunition cartridge in claim 4, wherein the cylindrical capsule includes a mass suspended in a chemical liquid marking material housed in a forward compartment of the one or more segregated compartments, the mass, at set-back, moving aft and puncturing a barrier material segregating the one or more segregated compartments.
6. The ammunition cartridge in claim 4, wherein the projectile traversing the barrel induces rotation on the exterior of the projectile, mixing all of the chemical liquid marking material in the cylindrical capsule.
7. The ammunition cartridge of claim 6, wherein the viscosity of the mixed chemical liquid marking materials affords laminar flow in the cylindrical capsule, the flow induced by the capsule's rotation around the projectile's axis of rotation.
8. The ammunition cartridge of claim 7, where the mixed liquid marking materials comprise at least 70% of the volume of the cylindrical capsule, the mixing of the one or more chemical liquid marking materials creating a chemical reaction.
9. The ammunition cartridge of claim 8, wherein the chemical reaction occurs in flight before projectile impact.
10. The ammunition cartridge of claim 9, wherein the chemical reaction creates a chemiluminescent reaction.
11. The ammunition cartridge of claim 9, wherein the chemical reaction creates an exothermic reaction.
12. The ammunition cartridge of claim 11, wherein the mixed liquid marking materials is heated based at least in part on the exothermic reaction, becoming atomized into droplets, when ejected from the projectile after impacting a surface.
13. The ammunition cartridge of claim 1, wherein the projectile houses an additional dry marking material surrounding the capsule, the dry marking material including high contrast pigment or dye.
14. The ammunition cartridge of claim 1, wherein the forward metal bore riding feature and the driving band are equidistant from the center of gravity of the projectile.
15. An ammunition cartridge incorporating a spin stabilized projectile, the projectile comprising: an ogive configured to house a fuze, aft of the fuze being a mid-body housing inert materials; a mid-body cylindrical assembly comprising a frangible metal cylindrical capsule configured with a first inert low-density powder payload, the frangible metal cylindrical capsule coupled to an energetic; and a base, wherein the fuze initiating ignition of the energetic causes pressurization of the frangible metal cylindrical capsule and a transfer of heat into the frangible metal cylindrical capsule, the heat causing expansion of gases momentarily pressurizing the frangible metal cylindrical capsule, and the pressurization causes a failure of a frangible exterior wall of the mid-body cylindrical assembly, gaseous by-products of combustion ejecting a marking payload, under pressure, perpendicular to the projectile's direction of travel.
16. The ammunition cartridge of claim 14, wherein the fuze initiates an energetic component in flight prior to impact.
17. The ammunition cartridge of claim 14, wherein the frangible metal cylindrical capsule is produced from a powdered metal fabrication process.
18. The ammunition cartridge of claim 16, wherein the frangible metal cylindrical capsule is configured with a second inert low-density powder payload, with a high contrast pigment or dye.
Description
DESCRIPTION OF PREFERRED EMBODIMENTS
[0025] The preferred embodiments of the present invention will now be described with reference to FIGS. 1A to FIG. 19 of the reference drawings. Identical elements of the various figures are designated with the same reference numbers, incorporated into three different types of gun fired cartridges depicted herein in three configurations—30 mm×113 cartridge, 40 mm×53 cartridge and a 105 mm Tank cartridge.
[0026] FIGS. 1A-8C depicts embodiments of the cartridge configuration in 30 mm, 40 mm and 105 mm projectiles.
[0027] FIG. 1A depicts 30 mm gun fired cartridges (2) with driving bands (42). A cartridge case (4) encloses propellant powder (8).
[0028] FIG. 1B depicts 40 mm gun fired cartridges (2) with driving bands (42). A cartridge case (4) encloses propellant powder (8).
[0029] FIG. 1C depicts 105 mm (tank) gun cartridges (2) with driving bands (42). A cartridge case (4) encloses propellant powder (8).
[0030] FIG. 2A depict a 30 mm cartridge (2) configured in a belt of ammunition (6).
[0031] FIG. 2B depict a 40 mm cartridge (2) configured, connected by a link (5), forming a belt of ammunition (6).
[0032] FIG. 3A depicts a 30 mm projectile (10) incorporated into a cartridge case (4). FIG. 3B depicts a 40 mm projectile (10) and cartridge case (4). FIG. 3C depicts a 105 mm tank projectile (10) and a cartridge case (4).
[0033] FIG. 4A depicts external and section views of a 30 mm marking projectile (10) composed of three principle components—a nose cap (20), marking body (30) and a metallic, non-frangible projectile base (40).
[0034] FIG. 4B depicts external and section views of a 40 mm marking projectile (10) composed of three principle components—a nose cap (20), marking body (30) and a metallic, non-frangible projectile base (40).
[0035] FIG. 4C depicts external and section views of a 105 mm marking projectile (10) composed of three principle components—a nose cap (20), marking body (30) and a metallic, non-frangible projectile base (40).
[0036] FIG. 5A depict an exploded view of a 30 mm marking projectile (10) and the principle elements—a nose cap (20), marking body (30) and a metallic, non-frangible projectile base (40).
[0037] FIG. 5B depict an exploded view of a 40 mm marking projectile (10) and the principle elements—a nose cap (20), marking body (30) and a metallic, non-frangible projectile base (40).
[0038] FIG. 5C depict an exploded view of a 105 mm marking projectile (10) and the principle elements—a nose cap (20), marking body (30) and a metallic, non-frangible projectile base. The base may also include a tracer assembly (46) or tracer element (48), the tracer providing a visual cue of the projectile's flight path.
[0039] FIG. 5D depicts and exploded view of a 105 mm marking projectile (10), the principle elements (20,30 and 40) and an exploded view of the marking body (30) including a pusher plate (36), and a base including a driving band (42) affixed to a non-frangible body (44), tracer assembly (46) and tracer element (48).
[0040] FIG. 6A-6C depict metallic nose caps (20) for 30 mm, 40 mm and 105 mm projectiles.
[0041] FIG. 7A-7B depict mid body marking bodies fabricated from a frangible body (32) and encapsulating a marking powder (34). FIG. 7C Depicts components in a 105 mm marking body including a frangible body (32), Contained marking powder (34) and a pusher plate (36).
[0042] FIG. 8A-8B depict the non-frangible base preferably produced from a dense metal and incorporates a driving band (42). FIG. 8C depicts the non-frangible body (44) with driving band (42).
[0043] FIG. 9A depicts the trajectory and impact angle of 30 mm×113 projectiles fired from a helicopter firing at targets from 500-2500 meters. The table below the diagram (altitude versus range) identifies the impact angle of 30 mm projectiles at various ranges.
[0044] FIG. 9B depicts the trajectory and impact angle of 40 mm×53 projectiles fired from a ground position at ranges for 500-1500 meters. The table below the diagram (altitude versus range) identified the impact angle of the 40 mm projectile.
PROJECTILE IMPACT, BREAK-UP AND MARKING SIGNATURE
[0045] Impact Geometry and Signature: FIG. 10A-10F illustrate the impact function of the projectile, where translational momentum and inertia (124), coupled with rotational moment and inertia (128) and impact shear forces (130), incident to impact, produce wall compression (66), wall tension (68) and shear forces (130) the cause the frangible body to fracture (76) ejecting the marking material perpendicular to translational (linear momentum and inertia) vector (124) in various impact angles (56), surface angles (58) with various trajectories (52, 54) usable in most training environments.
[0046] FIG. 10A depicts the impact angle (56) of a 30 mm projectile impacting on a surface (58) with a residual travel vector (62) and the projectile's center of gravity (64), and forward momentum (124) at the moment of impact.
[0047] FIGS. 10B1 and 10B2 depicts a 30 mm projectile's travel vector (62) when impact on the surface (58) milliseconds after the moment of impact, where the forward momentum (124) creates areas of compression (66) and tension (68) in the projectile's mid body.
[0048] FIG. 10C depict a 105 mm projectile's translational (Linear) Momentum and Inertia Vector (124), milliseconds after impact on an upright angular surface, with an impact angle (56) marking material ejected perpendicular to the translational (Linear) moment and inertia vector (72), decelerating in the atmosphere becoming momentarily suspended in the atmosphere (74).
[0049] FIG. 10D depicts the body fracture (70) caused when the forward momentum (124) and impact shear force (130) produced by the impact on a surface (58).
[0050] FIG. 10E depicts a 30 mm projectile, at the moment of impact, where rotational inertia (128A) of the base (40), is different than the marking body (30) rotational inertia (128B) and the nose cap's rotational inertia (128C). In combination, the differing inertias at impact, impart torsional loads that tear the mid body marker apart with a twisting action, the broken body wall, with residual rotation, releasing and ejecting marking material (72) into the atmosphere. At the moment of impact, the friction between the surface (58) and the projectile's nose (132) coupled with the residual inertia in each of the projectile's three components (10,20,30) produce torsional loads about the residual axis of rotation (134A,B,C), which, in combination with impact related compression and tension, act to fracture (70) the wall of the marking body (30).
[0051] Impact, Frangible Body Break Up and Release of a marking Signature: With continued reference to FIGS. 10A-10E, when a projectile impacts on the ground or on a target, the impact angle (56) and surface angle (58) geometry coupled with the translational (linear) momentum (124) of the projectile base's mass (40) induce a rotational momentum and inertias (128) and at impact shear forces (130) may also act to induce wall compression (66) and wall tension (68). The forgoing four forces (124, 128 and, 130) act in combination to fracture (70) the mid body′ wall. Further compression and residual rotation forces acting further to eject the marking material (72) such that the low-density marking powder, preferably incorporating a high contrasting pigment or dye is released into the atmosphere, air-resistance rapidly de-accelerating becoming momentarily suspended (74) in the vicinity of the impact point.
[0052] Weapon Feeding and Cartridge Modes of Use: FIG. 11A-F illustrate modes of function fire for a 40 mm cartridge function fired from a MK19 weapon system. FIG. 11A depict the feeding cycle of an open bolt MK19 40 mm AGL. When a liked cartridge (6) loaded into a weapon, a weapon's feeding system, that normally includes a bolt (92) and a barrel (94). As depicted in FIG. 11B, the bolt is released, and a compressed spring releases the bolt (110) forward to the closed bolt position depicted in FIG. 11C. In this position, the linked cartridge (6) is in a compressed position (120, 122). The bolt's extractors de-link the cartridge chambering and functioning the cartridge, firing the projectile (1) thru the barrel (94). The process of “feeding” a weapon may include extraction of the cartridge (2) from the linked ammunition belt (6). The process of feeding induces compression (120) and tension (112) requiring the entire cartridge remains intact prior to function fire. At function fire the projectile (10), at cartridge ignition, moves through the barrel (94), and the lands and grooves in the barrel (not depicted) engrave the projectile's driving band (42) inducing rotation of the projectile (10), said projectile (10) remaining assembled acting as a unitary body, with the base (40) inducing rotation on the frangible marking body (30), which in turn, induces spin on the nose (20).
[0053] FIG. 12 depicts annotated drawings from U.S. Pat. No. 8,065,962 to Haeselich, showing a projectile with a frangible nose cap (15), and a monolithic projectile body with a forward bore riding feature (16) and a driving band (42) incorporated into the same projectile body. The frangible liquid payload (18) is located forward of the projectile's center of gravity (46).
[0054] With reference to FIG. 14A, FIG. 13A sets forth the measurable effects where misaligned liquid rotation (152) about the projectile's center of gravity causes a measurable instability in flight (150), the relationship identifying conditions for stable (156) and unstable projectile flight (158). Similarly, FIG. 13B sets forth the measurable effects related to the distance (154) between the liquid cavity (80) and the projectile's center of gravity (46). The measurable relationship strongly correlates to the time a projectile exhibits observable instability (150).
[0055] FIG. 14A depicts the projectile's center of gravity (46) aligned with the projectile's axis of rotation (48). It also depicts the alignment of the liquid payload capsule (80) and liquid payload (82) proximate to the center of gravity (46). FIG. 14B depicts a projectile (10′) that has a forward bore riding feature (26) to provide good rotational alignment of the projectile's rotational axis (48), to align with the centerline of the barrel (95). The projectile (10′) consists of a forward nose cap (e.g., ogive) (20′), a mid-body (30′), and a projectile base (40′). The forward nose cap (20′) is configured to incorporate the forward bore riding feature (26) and may be formed of a ductile material such as metal (e.g., aluminum, brass, copper, etc.). With reference to FIGS. 14B, 14C and 15, the liquid capsule (80) may be affixed to a base (36) or alternatively may be affixed to the ogive (20′) by either being either crimped or otherwise connect with a retaining feature (37) to either or both components (36,20′). The metal plate (36) or ogive (20′), at impact, imparts a shearing and twisting action on the capsule (80) housing containing the liquid, the forces in combination acting to break the capsule, releasing the liquid payload (not depicted).
[0056] FIG. 14C depicts the liquid payload capsule (80) that is fabricated from a frangible polymer and physically connected to a metal base (36), or alternative connected to the ogive (20′) the metal base, the connections imparting a torque and shear action (not depicted) on the frangible cylindrical container (38) at impact. The projectile's center of gravity (46) aft-to-nose is positioned approximately equidistant (47) between the forward bore riding feature (26) and the aft driving band (42,42′).
[0057] FIG. 15 depicts the capsule (80) housing one or more liquid marking payloads may include solid and/or liquid payloads (82) in compartments (39). Where more than one liquid is utilized, the capsule (80) may have barriers segregating the different liquids (82). The forward capsule may house a solid mass (33). At set-back the solid mass perforates the capsule's inner compartment walls (35), allowing the different chemicals in the department to mix during spin up and in initial flight. The chemical mixing in the capsule (80) is initiated as the projectile undergoes spin-up in the barrel and continues as the projectile is in external ballistic flight, the reacting chemicals producing a chemiluminescent, optically emissive liquid payload or a thermally heated liquid payload, the reaction emitting light or heat in certain spectrum (visual, IR, thermal).
[0058] FIG. 16A-16C depicts a projectile (10′) that features two bore riding features, the forward bore riding feature (26) incorporated in the ogive (20′) and a driving band (42′) incorporated in the projectile base (40′). The projectile (10′) is further comprised of a frangible capsule (80) configured within in the projectile's mid body (30′) the capsule (80) in the stored configuration houses one or more liquid payloads (82). The liquid payloads (82) in the cylindrical container (38) are aligned proximate to the center with the projectile's (10′) center of gravity/mass (46). When the cartridge (2) fires (not depicted), the projectile (10′), the projectile undergoes “set-back” traversing the length of the barrel (94), and the bore riding features (26, 42′) on the projectile (10′) engage the barrel lands (96) and grooves (98) on the inner diameter of the barrel, the barrel transit, engaging and engraving the driving band (42′) and forward bore riding feature (26). The projectile's engagement of barrels twisted lands (96) and groves (98) on the barrel's (94) inner diameter impart rotational force on the projectile (10′), the spinning projectile (10′) exiting the barrel (not depicted) on a ballistic flight trajectory (50′), the liquid payload (82) in the cylindrical capsules (80) having laminar flow of mixing chemicals inside the rotating capsule (not depicted). The capsule configuration is fabricated to allow for mixing of one or chemicals, the mixing occurring at set-back or at impact. The projectile's (10′) forward bore ridding feature (26) and driving band (42,42′) equidistant from the projectile's (10′) center of gravity (46), such geometry minimizing induced yaw and pitch at barrel exit (not depicted). The capsule (80) housing a liquid chemical marking payload (82) is located in the projectile's mid body (30, 30′), precisely alignment with the projectile's center of rotation (48) and in close proximity to the projectile's center of gravity (46), such that liquid (82) in the rotating projectile (10′) encounters minimal destabilizing perturbations, with the liquid marking payload material (82) housed in the frangible mid-body (30′) of the projectile (10′) exhibits laminar flow (not depicted) about the projectile's axis of rotation (48) as the projectile (10′) is in ballistic flight (50′).
[0059] FIG. 17A-17C disclose an alternative embodiment where the metallic ogive (20′) includes a safe and arm device (24) which is a principle component of a fuze (21). This projectile's mid body marking component (30′) is configured to break when impacting on a surface (58), or preferably when the fuze (21) initiates the energetic squib (86). Either impact or fuze function may cause the mid-body (30′) to eject and release one or more marking payloads (e.g., marking powder 34, ejected atomized chemiluminescent droplets 76, and heat low-density metal powder 78). When the fuze (21) ignites an energetic squib, igniter or a detonator (86) in proximity to the mid-body (30, 30′) the ignition (88) pulverizes and heats the frangible cylinder material in the internal cavity (31) of the mid-body (30′). The frangible cylinder material then atomizes and flows under pressure, pushing on the lower density marking powder (34). The overpressure within the mid-body (30′) breaches the outer wall (32) of the frangible mid-body (30′). As a consequence of the pressurization, gas ejects the low-density marker (72, 72′) and heated, denser pulverized material (78), ejecting the materials (72, 72′ and 78) perpendicular to the axis of rotation (48). The ejected materials quickly deaccelerate and become momentarily suspended in the atmosphere (136) for a few seconds, depending on conditions. As such, the atomized low density materials or droplets (72, 72′, 78, 104) are momentarily suspended in the atmosphere (102), emitting or reflecting light in a spectrum that provides for an optical contrasts with the foreground earth (134) and vegetation (104) and ambient atmosphere (136).
[0060] Therefore, the embodiments of the projectile (10′) in accordance with the present disclosure differs from prior art, FIG. 12 depicts the prior art with a modest liquid payload within a frangible ogive, located forward of the projectile's center of gravity and with a bore rider and driving band incorporated into a monolithic projectile body. The embodiments of FIG. 13A depict the relationship between instability, alignment of the projectiles center of gravity and a liquid payload. Further, FIG. 13B further depicts how the location (aft or forward) of the liquid cavity relates to projectile stability. FIGS. 14A-D, 15 and FIGS. 16A-D depict a projectile (10′) with a center of gravity/mass (46) aligned with the axis of rotation (48) with the cylindrical capsule (80) containing liquid marking payload (82) centered approximately equidistant (47) between the forward bore riding feature 26 and the driving band (42,42′). Such equidistant relationship positions the cylindrical liquid payload such that at spin-up, in the barrel (94) the centerline of the barrel (95) aligns precisely with the projectile's axis of rotation (48), the precise alignment minimizing projectile balloting (not depicted) in the barrel, such that the encapsulated liquid (82) at spin-up, realizes laminar flow about the axis of rotation (48), the controlled component relationships and geometry within the projectile (10′) minimizing disruptive perturbations that induce yaw and pitch at barrel exit (not depicted).
[0061] FIG. 15 depicts the cylindrical capsule (80) with an attachment interface (37) to a metal disk or the forward ogive (20′), with the cylindrical capsule (8) having barriers (35) forming containers, or ampoules (39) housing one or more liquids (82). The container (39) forward to the projectile nose, may have a mass (33) suspended in a liquid (82). The mass (33) at set-back is forced aft, breaking barriers (35) segregating the liquids (82).
[0062] FIGS. 16A-D also depict a projectile (10″) with a mid-body (30) having an outer frangible body (32), housing a marking compound (34) and an encapsulated liquid payload (80, 82) positioned perpendicular to the axis of rotation (48) and an adjacent to a plate (36). The marking compound (34) may be marking powder.
[0063] Further, the additional embodiments include details regarding chemical payload and signature emissions, as set forth in FIG. 15 depicting a capsule (80), with segregated compartments (36) housing liquid payloads (82). Liquid payloads may include chemiluminescent compounds that generate chemical reaction. Diphenyl oxalate (Cyalume™) is a solid whose oxidation products when mixed with hydrogen peroxide are responsible for the visible chemiluminescence in a glowstick. Unfortunately, both these chemicals are toxic, and, when used as marker materials in gun-fired ammunition, and the light emission from these mixed chemicals rapidly fall off when exposed to air. While chemiluminescent payloads generate visible light, a wide range of chemical reactions are exothermic. Many exothermic reactions rapidly heat mixed chemicals and when released into the atmosphere, the chemical mix radiates heat emissions in longer wavelength region of the electromagnetic spectrum. Importantly, these emissions are radiated in the wavelengths of 3 to 5 and 8 to 14 micrometer regions. These wavelengths provide for an optimum transmission of heat emissions, in atmospheric windows, allowing for observation by thermal imaging devices. Examples of safe highly exothermic reactions are (1) anhydrous metal salts (e. g. calcium chloride) in combination with water, and (2) sodium sulfite with sodium hypochlorite (bleach). With reference to FIG. 14C, 15, and FIG. 18A the images depicts the projectile (10′) at impact on a surface (134), the shear and torsional stresses, coupled with retained momentum of the base fracture the projectile's frangible mid body (30′), causing the collapse of both the mid body frangible wall (32) and frangible container (80) at impact function, the impact causing ejection of both dry powder (34, 72′) and release of the reactive liquid payload (76,78) creating a marking plume adjacent to the impact point.
[0064] An alternate embodiment of a mid-body marker FIGS. 17A-C depict a projectile (10″) with a forward ogive bore rider (26) located forward of the projectile's center of gravity (46), and a driving band (42) aft of the center of gravity (46) within a barrel (94) where the forward ogive bore rider (26) is fabricated from a ductile metal and is configured to be engraved by barrel lands (96) and the barrel grooves (98) at spin-up. The projectile (10′) usefully incorporates a safe and arm component (24) housed in a metal ogive (20′) that is located forward of a mid-body (30′), the safe and arm precludes initiation of the energetic component after two environments, typically set-back (launch g-force) and spin (centrifugal force) are measured or induced in the safe and arm component. The safe and arm component (24) is adjacent to a forward end of the cylindrical container (38) and is incorporated in the metal ogive (20′) and the mid-body (30′). The mid-body (30′) includes a cylindrical container (38) containing a liquid marking payload (not shown) and an internal cavity (31). The figures depict an energetic squib, igniter or detonator (86′) aligned to the axis of rotation (48) adjacent to a safe and arm device (24). The safe and arm device (24) is positioned proximate to a special frangible cylinder container (84) surrounded by a marking powder (34) housed in the projectile's mid body frangible wall (32). The frangible cylinder (84) is fabricated from a powdered low-density metal, ceramic or silicate, the material adjacent to and when functioning receiving heat from ignition of the igniter (88). The mid body marker (30′) configuration allows for break-up on function or impact; however, differing from the impact markers, this embodiment provides for air-burst function (FIG. 18), where pressurization of the mid-body component as depicted in FIG. 17C depicts the frangible side walls (32) bursting at the moment of energetic ignition, the metal cylinder (84) decomposes under pressure and heat, and the decomposed metal powder and dry marking materials (34) housed in the projectile (10′) are thus ejected perpendicular to the projectile's flight path (50) as depicted in FIG. 18, the projectile (10′) functioning in free flight, before impacting on a hard surface. FIG. 17C depict an action at ignition (88) of an energetic component produces gases that pulverize the frangible component (84) at ignition. At ignition, combustion gases pressurize the frangible cylinder (84) and the gases and material push on the dry marker (34) within the interior of a frangible mid-body (30′), the expanding gases acting on the interior side of the mid body marker wall (32). FIG. 18B depicts the ejection of marking material (72, 72′) from a design as set forth in FIG. 17 A-C, where a denser, slower moving heated residual powder (78) created by the energetic (88) decomposing the metal cylinder (84), and a low density powder (72′) both materials propelled and engulfed by gases ejecting the material from the projectile's mid body (30′) perpendicular to the projectile's flight path (50). FIG. 19 depicts a mid-body projectile (10′) in reticule image (130) with released marker material suspended momentarily in the atmosphere (132) contrasting with foreground images (134) and ambient background (136).
[0065] Like other embodiments of a mid-body marker, the marking material is ejected into the atmosphere and the low density of powder materials allows for momentary suspension in the atmosphere.
[0066] There has thus been shown and described a novel, marking cartridge which fulfills all of the object and advantage sought, therefore. Many changes, modifications, variations and other use and applications of the subject invention, will become apparent to those skilled in the art after considering this specification and the accompany drawings which disclose the preferred embodiments thereof. All such changes, modifications, variation and other uses and applications which do not depart from the spirit and scope of the invention are deeded to been covered by the invention which is to be limited only by the claims which follow.
