Patent Application
20240344814
The present invention relates to a projectile system (or “bullet system”, or simply “bullet”), hereinafter referred to also as “Starchaser”, “StarChaser” and/or simply “SC” (trademark expression(s) used and/or own by the Applicant(s)). More particularly, the present invention relates to a new and improved projectile system for use with various types of firearms, and also relates to a method for assembling the same, and to corresponding methods of manufacturing, operating and/or use associated thereto.
Firearms and the various types of ammunitions used therewith (ex. projectiles, bullets, etc.), are well known in the art, and have been used for many years.
It is also known that a conventional bullet in flight forms a partial vacuum immediately therebehind. This partial vacuum or low pressure area creates a force which acts on the projectile in a direction opposite to its motion, thereby lessening the flight velocity of the projectile. This force is commonly referred to as “base drag”. Drag may be defined as that force acting on the projectile in a direction opposite to its motion. Base drag is that drag acting on the projectile at its base.
In regards to conventional projectiles (or “bullets”), it is also known that they are affected by a pressure difference that occurs on the rearward face (i.e. “base drag”). This drop in pressure causes drag and can generate flight instability (ex. turbulence, etc.). These factors will reduce the precision and accuracy of a projectile grouping, for example.
It is also well known that ammunitions (ex. projectiles, bullets, etc.), have evolved over the years, and have been the object of various patent applications.
For example, known to the Applicant(s) is U.S. Pat. No. 3,913,487, granted on Oct. 21, 1975, in the name of SCHERR, and relating to a “projectile”. This document describes a projectile of the type adapted to be propelled from a gun barrel by expanding gas. The projectile is formed with a chamber in its base and an outlet passage leading from the chamber through the base. The chamber is of nonuniform cross-sectional area with the cross-sectional area generally diminishing from a wall at the nose end of the chamber to the outlet passage. The wall of the nose end of the chamber may vary in shape from concave through flat to convex. The chamber may vary in shape from generally hemispheric to generally conical. In a modified form of the invention, at least two chambers are formed in the base and connected in series.
U.S. Pat. No. 7,823,510 B1, granted on Nov. 2, 2010, in the name of HOBART et al., relates to an “extended range projectile”. This document describes a projectile and method of extending the range of the projectile. The projectile includes a storage tank operable to release a working fluid through an exhaust manifold to at least partially fill a wake aft of the projectile during projectile flight.
U.S. Pat. No. 3,345,948, granted on Oct. 10, 1967, in the name of SARVIS, relates to a “projectile”. This document describes a projectile that comprises a body having a chamber or cavity therein, closed at the rear and open at the front. A gas generating charge is disposed in the rear end portion of the cavity. The charge may be of any type well known to one skilled in the munitions art which will produce hot combustion gases while doing substantially little or no damage to the body.
U.S. Pat. No. 4,133,265, granted on Jan. 9, 1979, in the name of DIESINGER et al., relates to a “training projectile”. This document describes a training projectile having an auxiliary drive mechanism for counteracting the aerodynamic resistance to which the projectile is exposed during the training flight phase of projectile travel. The auxiliary drive mechanism preferably is in the form of a rocket or jet drive. The training projectile is also provided with a mass so that the ratio of the resultant axial force to the mass of the training projectile is at least approximately equal to the ratio of the resistance force to the mass of a corresponding live projectile during the training flight phase.
U.S. Pat. No. 5,058,503, granted on Oct. 22, 1991, in the name of ADAMS, III, relates to an “aerodynamic projectile”. This document describes a solid projectile having identical tapered leading and trailing sections that are integral with and which extend from opposite ends of a central bearing section having a constant diameter throughout its length.
International patent application No. PCT/CH2016/000028, made public on Aug. 25, 2016, under WO/2016/131158A1, in the name of MUSTER et al., relates to a “tracer ammunition”. This document describes a tracer ammunition for tracking the trajectory and/or the impact of projectiles in the target, said tracer ammunition containing mostly pyrotechnics. Said pyrotechnics have various disadvantages, wherein the main disadvantage is the further combustion of the pyrotechnics even after penetration of the projectile in the target. This causes an increased risk of fire and an acute risk of injury. A mixture according to the invention of light metal and a carbon-containing substrate ignites during the firing of a projectile and burns during its flight by effect of the air oxygen introduced into the combustion chamber via tear-off edges and produces a tracer that extinguishes in the target.
Also known to the Applicant(s) are the following documents: U.S. Pat. No. 466,056; U.S. Pat. Nos. 2,941,469; 3,754,507; 3,988,990; 3,995,558; 4,003,313; 4,091,732; 4,108,073; 4,213,393; 4,528,911; 4,742,774; 5,353,711; 6,186,072 B1; U.S. Pat. No. 6,581,522 B1; U.S. Pat. No. 7,171,905 B2; U.S. Pat. No. 8,122,833 B2; U.S. Pat. No. 8,291,828 B2; U.S. Pat. No. 8,511,233 B2; US 2008/0035008 A1; US 2016/0131465 A1; EP 2,811,256 A1; and WO 1991/011676 A2.
Also known in the art is the technology having been developed by the very same main inventor of the present patent application, and by the same Assignee, namely, the technology being described in corresponding U.S. Pat. No. 11,162,768 B2, granted on Nov. 2, 2021, in the name of BINEK et al., and relating to an “improved bullet”, the content of which is incorporated herein by reference. This document describes namely a bullet configured to be propelled by a blast of a cartridge, the bullet comprising a main body provided with an internal body cavity and having a frontward section and a rearward section provided with an opening in fluid communication with the internal body cavity, the internal body cavity by means of the opening being capable of recovering a portion of gun gas resulting from the blast of the cartridge.
Despite these known improvements over the years, there is a need to continue innovating and finding better and/or different ways of firing projectiles so as to improve ballistic performances, in terms of accuracy, range and terminal energy.
Thus, it would be particularly useful to be able to provide an improved bullet system which, by virtue of its design and components, would be able to overcome or at least minimize some of the known drawbacks (ex. accuracy, drag, instability, limited range, etc.) associated with conventional bullets.
An object of the present invention is to provide a new projectile (hereinafter referred to also simply as “bullet”) which, by virtue of its design and components, is intended to satisfy the above-mentioned need and which is thus an improvement over other related bullets, corresponding weapons, associated accessories and/or firing devices, systems, assemblies and/or methods known in the prior art.
In accordance with the present invention, the above main object is achieved, as will be easily understood, with a bullet (and/or a corresponding weapon and/or associated accessory provided with at least one such bullet, as well as corresponding kits for assembling the same (ex. bullet, weapon, etc.), and corresponding methods of manufacturing, assembling, operating, use, etc.), such as the one(s) briefly described herein and such as the ones exemplified in the accompanying drawings.
More particularly, and according to one aspect of the present invention, an objective is to provide a bullet system for use with a cartridge for propelling out from a barrel of a weapon upon firing, the bullet system comprising:
It is important to note that one and/or several of the aforementioned drag-reducing assemblies may be integrated into a same and/or single given drag-reducing assembly.
According to another aspect of the present invention, there is also provided a kit with corresponding components for assembling the above-mentioned bullet.
According to another aspect of the present invention, there is also provided a corresponding weapon (ex. rifle, etc.) and/or an associated accessory (ex. loader, etc.) provided with at least one of the above-mentioned bullet(s), and preferably, with a plurality of such bullets.
According to another aspect of the present invention, there is also provided a kit with corresponding components for assembling the above-mentioned weapon.
According to another aspect of the present invention, there is also provided a weapon system comprising the above-mentioned bullet(s) and/or weapon.
According to another aspect of the present invention, there is also provided a kit with corresponding components for assembling the above-mentioned weapon system.
According to another aspect of the present invention, there is also provided a method of reducing drag from a bullet being propelled out of a barrel of a weapon upon firing with the above-mentioned bullet system.
According to another aspect of the present invention, there is also provided a method of reducing drag from a bullet during flight thereof with the above-mentioned bullet system.
According to another aspect of the present invention, there is also provided a method of reducing base drag from a bullet during flight thereof with the above-mentioned bullet system.
According to another aspect of the present invention, there is also provided a method of reducing frontal drag from a bullet during flight thereof with the above-mentioned bullet system.
According to another aspect of the present invention, there is also provided a method of reducing skin drag from a bullet during flight thereof with the above-mentioned bullet system.
According to another aspect of the present invention, there is also provided a method of manufacturing (ex. making, creating, producing, generating, assembling, etc.) the above-mentioned bullet, bullet system, weapon, weapon system, part(s) thereof, component(s) thereof and/or associated accessory (ies).
According to another aspect of the present invention, there is also provided a method of operating and/or using the above-mentioned bullet, bullet system, weapon, weapon system, part(s) thereof, component(s) thereof and/or associated accessory (ies).
According to another aspect of the present invention, there is also provided a set of components for interchanging with components of the above-mentioned kit(s).
According to another aspect of the present invention, there is also provided a method of assembling components of the above-mentioned kit(s) and/or set(s).
According to another aspect of the present invention, there is also provided a method of doing business with the above-mentioned bullet, bullet system, weapon, weapon system, part(s) thereof, component(s) thereof, associated accessory (ies), method(s), kit(s), set(s) and/or any other possible aspects(s) thereof.
According to another aspect of the present invention, there is also provided a bullet (ex. a blank and/or body with hollowed portion(s)) having been obtained and/or processed (modified, altered, etc.) with the above-mentioned method(s), kit, set, system, etc.
The objects, advantages and other features of the present invention will become more apparent upon reading of the following non-restrictive description of preferred embodiments thereof, given for the purpose of exemplification only, with reference to the accompanying drawings.
In the following description, the same numerical references refer to similar elements. Furthermore, for sake of simplicity and clarity, namely so as to not unduly burden the figures with several reference numbers, only some figures have been provided with reference numbers, and components and features of the present invention illustrated in other figures can be easily inferred therefrom. The embodiments, geometrical configurations, materials mentioned and/or dimensions shown in the figures are preferred, for exemplification purposes only.
Moreover, although the present invention was primarily designed as a “projectile” (ex. “bullet”, etc.) for use with various types of weapons, such as rifles and the like, it may be used with other types of objects, and in other fields, as apparent to a person skilled in the art. For this reason, expressions such as “projectile”, “bullet”, “weapon”, “rifle”, etc., used herein should not be taken as to limit the scope of the present invention and include all other kinds of objects and/or fields with which the present invention could be used and may be useful, as apparent to a person skilled in the art.
Moreover, in the context of the present invention, the expressions “projectile”, “bullet”, “device”, “product”, “system”, “method”, “kit” and “assembly”, as well as any other equivalent expressions and/or compounds word thereof known in the art will be used interchangeably, as apparent to a person skilled in the art. This applies also for any other mutually equivalent expressions, such as, for example: a) “projectile”, “bullet”, “Starchaser™”, “system”, “product”, “assembly”, “device”, “apparatus”, “unit”, “component”, “equipment”, “add-on”, “retrofit”, etc.; b) “producing”, “manufacturing”, “assembling”, “making”, “processing”, “altering”, “modifying”, “changing”, etc.; c) “body”, “shell”, “chassis”, “support”, “frame”, etc.; d) “removing”, “reducing”, “diminishing”, etc. e) “drag”, “resistance”, “friction”, etc.; f) “hollow”, “cavity”, “hole”, “orifice”, “recess”, “grove”, “slot”, etc.; g) “channel”, “conduit”, “passage”, “link”, etc.; h) “tip”, “extremity”, “end”, “distal”, etc.; i) “cartridge”, “propellant”, “fuel”, “explosive”, “energetic material”, etc.; j) “material”, “substance”, “solid”, “liquid”, “fluid”, etc.; k) “blast”, “explosion”, “ignition”, “propulsion”, “expansion”, “expulsion”, “discharge”, etc.; l) “gun gas”, “combustion gas”, “energy”, “heat”, etc.; m) “flight”, “trajectory”, “travel”, “displacement”, “movement”, etc.; as well as for any other mutually equivalent expressions, pertaining to the aforementioned expressions and/or to any other structural and/or functional aspects of the present invention, as also apparent to a person skilled in the art. Also, in the context of the present description, expressions such as “can”, “may”, “might”, “will”, “could”, “should”, “would”, etc., may also be used interchangeably, whenever appropriate, as also apparent to a person skilled in the art.
Furthermore, in the context of the present description, it will be considered that all elongated objects will have an implicit “longitudinal axis” or “centerline”, such as the longitudinal axis of an elongated bullet, or the centerline of a hole, for example (and as a result, there is a “transversal axis” being substantially “perpendicular” for each longitudinal axis, etc.), and that expressions such as “connected” and “connectable”, or “mounted” and “mountable”, may be interchangeable, in that the present invention also relates to a kit with corresponding components for assembling a resulting fully-assembled and/or fully-operational bullet, for use with various types of weapons, such as rifles and the like (and/or the present invention also relates to a weapon provided with at least one of such bullet(s), to a kit for assembling the same (ex. bullet, weapon, associated accessory, etc.), and to corresponding methods of manufacturing, operating and/or use associated thereto, etc.).
Moreover, components of the bullet(s), weapon(s), associated accessory (ies) and/or steps of the method(s) described herein could be modified, simplified, altered, omitted and/or interchanged, without departing from the scope of the present invention, depending on the particular applications which the present invention is intended for, and the desired end results, as briefly exemplified herein and as also apparent to a person skilled in the art.
In addition, although the preferred embodiment of the present invention as illustrated in the accompanying drawings may comprise various components, and although the preferred embodiments of the bullet, weapon, accessory and/or associated method(s) (ex. of manufacturing, assembling, operating, use, etc.) may consist of certain preferred steps and components as explained herein, not all of these steps and components are essential to the invention and thus should not be taken in their restrictive sense, i.e. should not be taken as to limit the scope of the present invention. It is to be understood, as also apparent to a person skilled in the art, that other suitable steps, components and cooperation thereinbetween, may be used for the present drag-reducing assembly (ies)/method(s) of a bullet and corresponding bullet (as well as corresponding components thereof) according to the present invention, as will be briefly explained hereinafter and as can be easily inferred herefrom by a person skilled in the art, without departing from the scope of the invention.
Other possible aspect(s), objective(s), embodiment(s), variant(s) and/or resulting advantage(s) of the present invention, all being preferred and/or optional, are briefly summarized hereinbelow.
For example, and as will be explained in greater detail hereinbelow, the present system is particularly advantageous in that, due to its components and features, the bullet is capable of considerably increasing ballistic performances (ex. more precise trajectory, much longer range, greater travelling speed, more powerful impact, etc.).
Broadly described, and as better exemplified in the accompanying drawings, the present invention relates to a bullet that incorporates in its design three different drag-reducing capabilities (ex. devices, components, features, etc.) in order to reduce Base Drag, Frontal drag and/or Skin-Friction drag.
By reducing all possible sources of aerodynamic drag, the present Starchaser™ bullet can maintain nearly all kinetic energy at the point of impact located at about 1500 m to about 2000 m (approximately), as at the muzzle, with the help of impulse-assisted device that is part of the bullet.
Brief Overview of Preferred and/or Optional Features of the Present Starchaser™ Bullet:
Starchaser™ is a bullet of mono-block construction that is build using advanced techniques of additive manufacturing. Preferably and/or optionally, three are three sections in the Starchaser™ bullet. The rear section has a shape of empty propulsion/impulse nozzle with large diameter facing the back of the bullet. The inside of the nozzle has a sprayed-on energetic material. The small diameter is facing front of the bullet and the small diameter is actually an orifice to frontal cavity. The frontal cavity is in shape of an oval with two orifices at each end. The nose of the bullet is housing a cylindrical cavity, the centerline of which is the same as the longitudinal axis of the bullet.
At the ignition, the flame propagates inside the cartridge case and spreads into the propellant that is in the “Nozzle” of the Starchaser™ bullet. The effect is that as the bullet moves forward some of the propellent moves forward with the bullet resulting in “pressure vs time” curve that has no peak but looks more like gentle rise resulting in more area under the “pressure vs time” curve. This effect is called “travelling charge”. The burning charge propellant ignites much slower burning energetic material grain that is on the inside of the “Nozzle”. Under high acceleration, the liquid that is stored in cylindrical cavity in front of the bullet drops into frontal cavity right into oncoming gas from the rear. The result is that the liquid evaporates, and the vapors are pushed through cylindrical cavity in the nose to outside of the bullet. As vapors are lighter than ambient air, the rushing air outside of the barrel pushes the vapor on the bullet forming a boundary layer of vapor and prevent direct contact between air and surface of the bullet. The vapors that are around the bullet have lower density and viscosity than air and therefore form a “bubble” around the bullet and reduce frontal and skin drag. In the back of the bullet, the energetic material is burning reducing the base drag to near zero and propelling the bullet forward.
Brief Overview of the Technologies that are Involved with the Present System:
Development program is designed in such a way that each technology is an “add-on” to the previous technology ensuring easy verification of the progress.
The outside and inside geometry are designed to maximize the ratio of “Axial moment of inertia” over “Transverse moment of inertia”. Geometries of the cavities.
Combination of reduction of the frontal drag and rear impulse propulsion does not form destabilizing couple as the effects neutralize each other.
As may now be better appreciated, and as described and/or illustrated in the present patent specification, and/or as can be easily inferred therefrom, the present invention is advantageous in that is provides a way of “managing fluid flow inside of a projectile to reduce aerodynamic drag on the outside of the projectile”, and the present bullet system (1) may come in the form of a bullet (1) including one and/or several of the following possible components and features (and/or different possible combination(s) and/or permutation(s) thereof):
As can easily understood by a person skilled in the art, several modifications, alterations and/or additions could be made to the various components and/or features of the present bullet system (1), without departing from the scope of the invention.
For example, and as mentioned above, according to a possible embodiment, a ratio (ex. of surfaces, etc.) between the cross-sectional profile (15) of the rearward portion of the cavity (11a) of the first drag-reducing assembly (5a) and the cross-sectional profile (17) of the frontward portion of said cavity (11a) is about 5, but it is worth mentioning also that this ratio could ultimately be any other appropriate one (and/or fraction(s) of ratio(s), etc.), so long as it ensures gun gas to appropriately “flow through” the corresponding orifice/interface (17,47) separating the associated cavities (11a, 11c), for the intended purpose(s) of the present bullet system (1), as can be easily understood by a person skilled in the art.
Indeed, it is worth mentioning also that the rate of flow of the gun gas through the bullet is an important factor to consider for the present bullet system (1), and that the rate of flow will depend mostly on the inside geometry of the bullet, etc. As way of a possible example, considering that the inside geometry can be a cone, for instance, the base of the cone is the “intake” of the gun gases. The cone is truncated at the top and it represents the orifice between the rear and frontal cavities (11a, 11c). The distance between the base of the cone and the orifice can be a unit “one”. As can easily understood, the rate of the gas flowing inside the bullet will depend mostly on the ratio of the diameters of the base of the cone to the diameter of the orifice. Thus, according to a possible and/or preferred embodiment of the present bullet system (1), a ratio (ex. of surfaces, etc.) between the cross-sectional profile (15) of the rearward portion of the cavity (11a) of the first drag-reducing assembly (5a) and the cross-sectional profile (17) of the frontward portion of said cavity (11a) is about 5, so to ensure that gun gas appropriately flows through the corresponding orifice/interface (17,47) separating the associated cavities (11a, 11c), for the intended purpose(s) of the present bullet system (1), as can be easily understood by a person skilled in the art. In contrast, for a conventional bullet (ex. a 0.5 cal bullet), the base of the cone has a diameter of 0.35 inch, and the orifice diameter is 0.035 inch, and the distance between the base and the orifice is one inch, and thus, the ratio of the diameters is 10, which would most likely “choke” the flow, etc.
Regarding other possible modifications, alterations and/or additions that could be made to the various components and/or features of the present bullet system (1), one could ultimately use the present bullet system (1) with the Nose Tip (ex. plastic tip) being “removed” altogether, so as to let air into the cylindrical cavity of the main body of the bullet. In such an alternate embodiment, the bullet would be rapidly accelerating in the barrel, and ingests air that is in front of the bullet. That process would continue to some degree when bullet is outside the barrel. The ingested air would thus mix with hot gas in the frontal cavity and would/could be expelled forward by hot air in the frontal cavity (about 3000° C.). The mixture of air injected from the outside and super hot air will be less dense than the air outside the bullet, and therefore, such an embodiment would enable a reduction of the frontal drag and skin friction drag, as well.
According to another possible embodiment, the driving band can be made out of the same material as the bullet. The geometry of the driving band can be similar to the existing driving bands, but geometry is preferably/optionally a mesh of criss-cross ridges and grooves of about 0,001 inches (approximately).
According to another possible embodiment, the present bullet system (1), associated bullet and/or corresponding components thereof (ex. main body, driving band, etc.) is/are manufactured by a suitable additive manufacturing method, such as “powder bed fusion” and/or “binder jet”, for example, as can also be easily understood by a person skilled in the art.
As may now be better appreciated, the present bullet system (1) is particularly advantageous in that it includes a series of drag-reducing assemblies (5a,5b,5c) that enable to provide the bullet (1) with reductions of base drag, frontal drag and/or skin drag, during flight and/or associated trajectory. Furthermore, the present bullet system (1) is also a considerable improvement over conventional bullets in that, contrary to conventional bullets that rely on internal “active” components (ex. propellants, etc.) which “burn/combust” during flight of the bullet, in order to produce the propulsion gas/fluid, the present bullet system (1) provides an innovative way of “managing fluid flow inside of a projectile to reduce aerodynamic drag on the outside of the projectile”, by recuperating energy from the gun gas from the blast of the propellant of the cartridge, mixing it with air and/or a non-explosive material (stored inside the bullet) capable of being converted into an operative “vapor” discharge, to then release said operative “vapor” discharge from a corresponding orifice (ex. frontal orifice, etc.) of the main body (3) of the bullet system (1), so as to engulf the bullet (1) with a protective and associated drag-reducing “bubble” during flight, with said “bubble” consisting of the operative “vapor” discharge which is “lighter” (i.e. less dense) and “less viscous” than the ambient air through the bullet (1) is intended to travel, for a reduced overall aerodynamic drag of the bullet (1) during flight, and thus, improved ballistic performances. Indeed, the provision and discharge of such an operative “vapor” discharge which is “lighter” (i.e. less dense) than air, namely helps to reduce frontal drag, and the provision and discharge of such an operative “vapor” discharge which is “less viscous” than air, namely helps to reduce skin drag, etc.
As may now be better appreciated also, the present bullet system (1) is also a considerable improvement over conventional bullets in that, thanks to a suitable additive manufacturing method, such as “powder bed fusion” and/or “binder jet”, for example, the bullet system (1) and associated drag-reducing assemblies (5a,5b,5c) can manufactured as a “single” and/or “unified/uniform” piece, which is advantageous for various reasons (in terms of costs, in terms of structural integrity, in terms of ballistic performance, etc.), contrary to conventional bullets that rely on various components being mechanical and/or thermally connected together, etc.
As may now be better appreciated also, the present bullet system (1) is also a considerable improvement over conventional bullets in that, the provision and discharge of the aforementioned operative “vapor” discharge during flight of the bullet (1) enables to have a bullet (1) having an effective flight geometry that is not “fixed” nor “rigid”, due to said discharge of operative “vapor” during flight (ex. from a frontal orifice of the bullet), and thus, such fontal expulsion of operative “vapor” discharge during flight enables the bullet (1) to have an associated “variable” (i.e. non-fixed, non-rigid, etc.) effective geometry of the bullet (1) during flight, which is also advantageous in that it helps to reduce any possible resulting occurrence of shock wave(s), something that is not possible with conventional bullets that have “fixed” tips, and thus, due to speed(s) being travelled when fired, inherently result into shock wave(s), which is very undesirable from a “drag” point-of-view. Thus, the structural and functional design of the present bullet system (1), and associated drag-reducing assemblies (5a,5b,5c), as well a corresponding discharge/expulsion operative “vapor” from a frontal orifice of the bullet (1) during flight, helps to avoid possible resulting shock wave(s), and thus, advantageously helps to reduce an overall aerodynamic drag of the bullet (1) during flight, for improved ballistic performances, etc.
The present bullet system and corresponding parts are preferably made of substantially rigid materials, such as metallic materials, hardened polymers, composite materials, polymeric materials, and/or the like, so as to ensure a proper operation thereof depending on the particular applications for which the bullet system is intended and the different parameters (weights, loads, moments, etc.) in cause, as apparent to a person skilled in the art.
Of course, and as can be easily understood by a person skilled in the art, the scope of the claims should not be limited by the possible embodiments set forth in the examples, but should be given the broadest interpretation consistent with the description as a whole.
Furthermore, although preferred embodiments of the present invention have been briefly described herein and illustrated in the accompanying drawings, it is to be understood that the invention is not limited to these embodiments and that various changes and modifications could be made without departing form the scope and spirit of the present invention, as defined in the appended claims and as apparent to a person skilled in the art.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/CA2022/051037 | 6/29/2022 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 63202898 | Jun 2021 | US |
