Projectile Construction and Payloads Therefor

Description

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application is a non-provisional application of and claims priority under 35 U.S.C. § 119 on pending U.S. Provisional Patent Application Ser. No. 63/549,928, filed on Feb. 5, 2024, on pending U.S. Provisional Patent Application Ser. No. 63/677,383 filed on Jul. 30, 2024, and on pending U.S. Provisional Patent Application Ser. No. 63/742,481 filed on Jan. 7, 2025, the disclosures of which are incorporated by reference.

FIELD OF THE DISCLOSURE

The present disclosure relates to projectiles and related launching mechanisms and accessories and more specifically, to those projectiles with a payload that may interfere with or disable a moving object by disrupting or deactivating the moving object's navigational system or capabilities.

BACKGROUND OF THE DISCLOSURE

As the use of drones, unmanned aerial vehicles (UAV) and other uncrewed aerial systems (UAS) in combat, reconnaissance, and related environments expands, solutions for countering such uses also necessarily develop. There are a number of types of such solutions that fall into certain broad categories such as physically destroying a drone and neutralizing a drone. While promising as countermeasures to current drone and UAS technology have potential, each of these categories suffers from drawbacks.

Traditional projectiles and launching systems are commonly used in an effort to destroy a drone or other moving object. Typically, such weapons systems require a projectile to burst on or in the vicinity of the target and thus require very precise targeting to accomplish their intended effect. This increases the expense associated with such projectile systems and is often uneconomical. Furthermore, there is the risk of collateral damage should such an explosive projectile miss its intended target and instead impact a different object, or in the case of a kinetic projectile, land far away from the drone or UAS. Furthermore, drones are often inexpensive and traditional interceptor means are expensive and/or require specialized infrastructure or additional equipment which must be carried.

An approach for neutralizing a drone utilizes a net that is designed to be dropped upon a drone to interfere with a propeller or propellers of the drone. While this approach reduces the possibility of collateral damage, precise targeting is nonetheless still required, as the net, once deployed, becomes subject to atmospheric currents and therefore can be brought off target quite quickly.

Another approach for neutralizing a drone is to cause interference with its operating system, such as by interrupting or interfering with a drone's radio frequency processing (which can be done, for example, by subjecting the drone to an unusual and/or large amount of RF energy that breaks the communication link between the drone and its pilot). However, a negative effect of using EMP's or jammers, as they are known, includes accidental disablement of friendly equipment. Furthermore, jammers are ineffective if the drone is piloted by Artificial Intelligence linked to an optic or sensor array.

All of the currently available methods and systems for interfering with and/or disabling a moving target such as a drone suffer from one or more of the following disadvantages: difficult to target, not suitable for close range, not suitable for long range, inaccurate, sometimes lethal and often otherwise not effective, costly to manufacture, complex in configuration, and not reliably powered and not easily fielded within the existing infrastructure of law enforcement and/or infantry.

SUMMARY OF THE DISCLOSURE

In view of the foregoing disadvantages inherent in the prior art, the general purpose of the present disclosure is to provide a projectile construction (also referred to herein as “projectile” in context), projectile launcher, and launcher accessory that include all the advantages of the prior art, and overcomes the drawbacks inherent therein. As used herein, “payload” may refer to a substance, object, compound, or material that is capable of delivering an incapacitating force to and/or resulting in an incapacitating effect upon a target. Such a payload can be in powder, liquid or aerosol, or foam form and/or in the form of confetti (or a combination thereof) without departing from the spirit of the disclosure. The payload may comprise a material which interferes with optics, infrared and/or control surfaces of the drone or UAS. The projectile may also comprise an energy storage means. As used herein, “energy storage means” is a storage means that lacks sufficient energy (such as a charge, for example) to activate or arm the projectile or another component of the projectile until the energy storage means has been energized or re-energized by an outside source (such as a launcher or an accessory thereof). The minimum energy to activate or arm the projectile (or to initiate a reaction as described elsewhere herein) is referred to as the “threshold energy”, meaning that at energy levels below the threshold energy, the projectile will not be armed or activated and/or cannot initiate a mechanical or chemical reaction. In an embodiment, the energy storage means comprises a capacitor, which capacitor may be charged or energized by the launcher or launcher accessory prior to or coincident with launching of the projectile. As used herein, “launch” and “launching” of the projectile refers to a period of time between when the projectile first begins moving in the barrel to when the projectile exits the barrel or accessory of the launcher.

In an embodiment, the projectile separates into two or more components after it leaves the barrel of a launcher to distribute a payload. In an embodiment, the separation can be initiated by electrical, mechanical or chemical means or by a combination thereof. In a still further embodiment, the time of initiation can be varied depending on the distance to the target. In an embodiment, the means of initiating separation of the projectile and the payload are disposed in separate compartments or regions of the projectile.

In another embodiment, the disclosure comprises a probe that may be electrically charged with a specific polarity (i.e. positive or negative) and may attach to the target. In such an embodiment, the payload may be electrically charged with the opposite polarity of the target, such that if and when the payload is released in the vicinity of the probe, electrostatic attraction occurs between the target and the payload which will cause the payload to move toward and coat the target with the payload.

In an embodiment, the payload of an exemplary projectile may further comprise a sticky and/or tacky substance or a web or other configuration that may interfere with or affect the propulsion system and or the control surfaces of a drone or other moving object.

In an embodiment, a payload may comprise a ferrofluid and/or a magnetic or ferromagnetic powder that may be dispersed from a projectile to adhere to a metal component or components of a drone (such as a motor) and cause the motor to cease operating, thus disabling the drone. In yet another embodiment, the payload of a projectile may comprise an opaque substance (such as a foam, ink, powder or paint), which opaque substance may be dispersed in proximity to the drone's vision system or camera to impede the optics, infrared sensing, and/or remote control of the drone.

DESCRIPTION OF THE DRAWINGS

The advantages and features of the present disclosure will become better understood with reference to the following detailed description and claims taken in conjunction with the accompanying drawings, wherein like elements are identified with like symbols, and in which:

FIG. 1 shows a launcher and projectile according to an exemplary embodiment of the present disclosure,

FIG. 1A shows a projectile separating after launch from a launcher to release a payload, according to an exemplary embodiment of the present disclosure,

FIG. 2 shows a projectile before and after separating to release a payload, according to an exemplary embodiment of the present disclosure;

FIG. 3 shows a projectile comprising a payload and a coil of wire, according to an exemplary embodiment of the present disclosure;

FIG. 4 shows an accessory for a launcher, according to an exemplary embodiment of the present disclosure,

FIG. 5 shows an initiator, control circuit, and sensor of a projectile, according to an exemplary embodiment of the present disclosure;

FIG. 6A shows a projectile releasing a payload upon a drone after separation of said projectile, according to an exemplary embodiment of the present disclosure, and

FIG. 6B shows a projectile releasing a payload upon a drone after separation of said projectile, according to another exemplary embodiment of the present disclosure.

DETAILED DESCRIPTION OF THE DISCLOSURE

The exemplary embodiments described herein detail for illustrative purposes are subject to many variations in structure and design. It should be emphasized, however, that the present disclosure is not limited to a particular projectile or projectile launcher as shown and described. That is, it is understood that various omissions and substitutions of equivalents are contemplated as circumstances may suggest or render expedient, but these are intended to cover the application or implementation without departing from the spirit or scope of the claims of the present disclosure. The terms “first,” “second,” and the like, herein do not denote any order, quantity, or importance, but rather are used to distinguish one element from another, and the terms “a” and “an” herein do not denote a limitation of quantity, but rather denote the presence of at least one of the referenced item.

In view of the foregoing disadvantages inherent in the prior art, the general purpose of the present disclosure is to provide a projectile construction 100 (also referred to herein as “projectile” in context), projectile launcher 1000, each as shown in FIG. 1, (and optionally, a launcher accessory 1100 as elsewhere described herein) that include all the advantages of the prior art and overcomes the drawbacks inherent therein. As used herein, “payload” may refer to a substance, object, compound, or material that is capable of delivering a degrading or incapacitating force to and/or effect on a target. Such a payload 200 can be in powder, liquid or aerosol, or foam form and/or in the form of shrapnel (or a combination thereof) without departing from the spirit of the disclosure. The payload 200 may comprise a destabilizing material, a visible substance (such as a dye or a powder, for example) or an ink or tacky compound or a combination thereof.

In an embodiment, and as shown in FIG. 1A, the projectile 100 separates into two or more components upon or after exit from the barrel 1010 of the launcher 100 to distribute the payload 200. In an embodiment and as will be discussed in further detail herein, the separation can be initiated by electrical, mechanical or chemical means or by a combination thereof.

In an embodiment, the separation of the projectile 100 is in sufficient proximity to a target (such as a drone) to disperse the payload physically upon the target or in close proximity to the target.

In an embodiment, payload 200 may comprise a ferrofluid, a statically-charged powder, a magnetic or ferromagnetic powder or an opaque substance (such as a foam, ink cloud, glue mist or a powder). The payload 200 may also comprise a sticky substance or a web or other configuration that may interfere with or affect the control surfaces and or propulsion of a target. Such tacky or adhesive substance can promote effectiveness of the payload by physical attachment to the target. In an embodiment, the web-configured payload, or payload configured as streamers (or other entanglement materials) or an abrasive powder may physically impede operation of a drone's propulsion system, causing the drone to divert from its intended path or crash to the ground.

In an embodiment, where the payload 200 comprises a ferrofluid and/or a magnetic or ferromagnetic powder, such payload may be dispersed in connection with the separation or disintegration, etc. of a projectile 100 to adhere to a metal object or component or components of a target (such as the motor or propeller of a drone) and cause the component to cease operating, thus disabling the target.

In yet another embodiment and as shown in FIG. 2, where the payload 200 of a projectile 100 comprises an opaque substance (such as a foam, ink, paint, powder or aerosol), said opaque substance may be dispersed in proximity to the target and interfere with the drone's navigational sensors or vision system or camera to impede operation of the drone. Such opaque substance material also may be enhanced by including a tackifier or sticky element causing it to adhere to the drone or UAS and affect both vision (including infrared) as well as control surfaces such as propellers, rudders etc. It is preferred that the particle size of the opaque substance is less than 150 microns. Suitable powders include titanium dioxide, carbon, activated carbon, charcoal, activated charcoal, talc, silicon aerogel, carbon aerogel and the like. Additionally, tackifiers may comprise cyanoacrylate, polyurethane, epoxies, xanthum gum, corn starch, glycerin, cornstarch, gelatin and the like. FIG. 2 also shows projectile separating into projectile portions 100a and 100b to allow payload 200 to be dispersed from the projectile.

In another embodiment, the payload of an exemplary projectile comprises an electrostatic charge. In such an embodiment, the disclosure may comprise a probe that is electrically charged (such as electrostatically charged for example) and that may be directed at and attached to a target, thus charging the target to a specific polarity (i.e. a positive or negative charge). In an embodiment, the payload is electrostatically charged to the opposite polarity of that of the target. In an embodiment, the probe attaches to the target prior to separation of the projectile. When payload is released in proximity to the probe, electrostatic attraction between the oppositely charged probe and payload may cause the payload to accumulate around the target and/or probe. In an embodiment, the launcher may launch the probe as well as the projectile.

In a still further embodiment, the projectile may be charged electrostatically at launch to a polarity that is typically opposite what a flying target object would acquire (typically drones and the like acquire a negative polarity flying through the air). Charging an exemplary projectile of the present disclosure with a positive charge would allow it to release a charged cloud which would be preferentially attracted to the drone or UAS.

In an embodiment and referring again to FIG. 1, a launcher 1000 comprises at least one permanent magnet (hereinafter “magnet” as used throughout shall mean a permanent magnet unless particularly specified otherwise). The at least one magnet 500 may be disposed within or in proximity to the barrel 1010 of the launcher, and in a further embodiment, proximate to the point of projectile exit, and in any event along the launch axis of the projectile. The at least one magnet is preferably magnetically-aligned with the launch axis in an embodiment similar to the alignment of the at least one magnet of the launcher accessory shown in FIG. 4 herein. In an embodiment and as shown in FIG. 3, the projectile—100 comprises at least one coil of wire 550. In an embodiment, when the projectile is launched, the at least one magnet of the launcher causes a rapid change in magnetic flux of coil of the moving projectile as it moves along the launch axis. This rapid change causes a current to be induced through the coil of the projectile, causing an inductive energy to be produced. In this way, it is understood that the at least one magnet of the launcher is capable of providing energy to the projectile. Those familiar in the art will recognize this as Faraday's Law of Induction

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That is, electrical energy can be generated thereby from the change in magnetic flux as the projectile moves through the magnetic field caused by the at least one magnet of the launcher. As used herein, this inductive method may be referred to as “inductive activation” when it refers to activating a circuit and/or initiator of the projectile.

In another embodiment and as shown in FIG. 4, an accessory 1100 for a launcher 1000 comprises at least one magnet 1500. The accessory is configured to be removably attached to a launcher, and in an embodiment, to the barrel of a launcher. The at least one magnet of the accessory may be disposed within or in proximity to the barrel of the launcher, and along the launch axis of the projectile. The at least one magnet is preferably magnetically-aligned with the launch axis. In an embodiment, accessory 1100 comprises multiple magnets (as shown as elements 1500 and 1501 in FIG. 4). As used herein, magnetic alignment comprises the creation of magnetic flux lines in the barrel or accessory such that a coil moving through the barrel or accessory receives an induced electrical charge. In an embodiment, the projectile comprises at least one coil of wire. When the projectile is launched, the at least one magnet of the launcher accessory causes a rapid change in magnetic flux of coil of the moving projectile as it moves along the launch axis. This rapid change causes a current to be induced through the coil of the projectile, causing an inductive energy to be produced. In this way, it is understood that the at least one magnet of the launcher accessory is capable of activating a circuit or an initiator of a projectile.

In another embodiment and referring to FIG. 5, an initiator 150 may be disposed within the projectile. The initiator may either initiate a chemical reaction or otherwise cause a separation of the projectile through a mechanical or electromechanical method such as upon receiving a signal from a control circuit 120 of the projectile. The initiator and reaction can be initiated when current has been induced in the coil of wire of the projectile by the at least one magnet. In an embodiment, the initiator comprises an electric match, a nichrome wire coupled with a mechanical energy storage device (such as a spring), or a resistive heating filament. In an embodiment, the nichrome wire, when activated may cause the spring to expand to rupture the projectile.

In a still further embodiment in which the separation, opening, etc. of the projectiles is a result of a chemical reaction, an activating compound such as nitrocellulose may be initiated with the electric match, for example. The electric match may consist of a nichrome or similar high resistance wire that is coated with a pyrogen. In an embodiment, wherein the launcher and/or launcher accessory comprises at least one magnet, when the projectile is launched, the at least one magnet of the launcher and/or accessory can activate the electric match by inductive activation.

In embodiment, a projectile comprises piezoelectric material to generate a spark to start a reaction in the projectile and/or cause the projectile to rupture, separate, etc.

In another embodiment, the projectile comprises a propeller or other agitator for facilitating distribution of the payload.

In an embodiment, a projectile capable of rupturing/disintegrating and/or delivering a payload to a target comprises at least one sensor 110, as shown in an exemplary embodiment in FIG. 5. Said sensor may be capable of sensing a target and proximity to a target, and in an embodiment, a frequency or frequencies and/or amplitude or amplitudes emitted by a target. In an embodiment, the sensor may comprise an electromagnetic interference detector sensor and/or a radio frequency detection scanner. In operation, the sensor may provide inputs to a control circuit 120 so that the control circuit may initiate the disintegration operation (via the initiator 150, for example) or delivery of the payload of the projectile such as on determining the presence and/or strength of a particular frequency, electromagnetic interference, or radio frequency that may be associated with the target and that indicates a particular proximity to the target.

In an embodiment, said projectile may comprise or be operatively coupled to a library or index of frequencies, amplitudes, and electromagnetic signatures for purposes of comparing a sensed frequency, amplitude and/or electromagnetic signature with indexed frequencies, amplitudes, and electromagnetic signatures for associating the sensed frequency, amplitude, and or electromagnetic signature with a particular target.

In an embodiment, the at least one sensor may be combined with one or more supplemental sensors, including, but not limited to light and electromagnetic sensors, to improve target identification and optimal deployment proximity.

In an embodiment, delivery of the payload of the projectile may be used for debris field creation for mechanical disablement of the target.

In operation, this exemplary projectile may be configured to disintegrate and/or disperse a payload upon determination (such as by a sensor) that the projectile is in sufficient proximity to the target, the sensor can inform the control circuit of the projectile, and the control circuit can initiate disintegration of the projectile for delivery of the payload to the target.

In an embodiment, the projectile may disrupt a drone or other moving object by dispensing a payload that obscures or interferes with a drone's (or other object's) navigation system or flight mechanism. For example, a payload that comprises a ferrofluid and/or a magnetic or ferromagnetic powder may be dispersed from a projectile to adhere to a magnetic element of the drone such as the propeller motor for example, and cause the motor to cease operating, thus disabling the drone. In another embodiment, where the payload comprises an abrasive powder or streamers (or other entanglement materials), for example, delivery of the payload may be the result of the payload's attraction to the static charge created by the rotation of the propeller or propellers of the drone. In such an embodiment as shown in FIG. 6A, the payload 200 may contact and interfere with the propeller or propellers of the drone, thus impeding operation of the propeller(s) of the drone.

In yet another embodiment (as shown in FIG. 6B), the payload 200 of a projectile may comprise an opaque substance (such as a foam, ink or paint), which opaque substance may be dispersed in proximity to the drone's vision system or camera to impede operation of the drone. In an embodiment, the opacity of such payload is from 0.2 to 1. In the alternative, the payload may be dispersed in an anticipated flight path of the drone such that the payload is delivered to the drone when the drone flies through a cloud or mass of the payload. In an embodiment, the payload may further comprise a sticky substance, which sticky substance may adhere to a portion of the drone to disrupt the flight capability of the drone by affecting control surfaces such as propellers, rudders and the like and/or drone sensors such as optics (including thermal and infrared sensing capabilities of a drone) or infrared targeting.

In an embodiment, the payload comprises a flammable powder or liquid aerosol which after dispersion in air creates a cloud which is then ignited to form a shock wave. The ensuing shockwave from said ignition destabilizes the target UAV or drone. Suitable materials can be any of a number of metals such as finely divided magnesium or aluminum or other materials such as aerosol fuels. This type of approach is often referred to as thermobaric.

The projectile, launcher, and launcher accessory disclosed herein offer the advantages of more controlled release of payload than existing solutions can offer. The projectile further does not require impact upon a target. Configuration of the shell of the projectile disclosed herein may also increase accuracy of flight of the projectile to further improve the safety of use of the projectile disclosed herein (and furthermore, collateral damage by the payload is minimized compared to the prior art). For example, projectile can have a semi-hemispherical shape to cut through the air. Projectile can have rifling engaging features to impart spin on the projectile. Furthermore, the projectile can be kept in an unarmed state until the projectile is launched from the launcher. The payload of the projectile disclosed herein may greatly reduce the targeting and operational capability of a drone or other moving object. The projectile of the present disclosure can be integrated into existing military and/or police force infrastructure. For example, the projectile may be between 12-45 mm and may be fired by an M203 launcher, which launchers are commonplace in military and police force settings.

The foregoing descriptions of specific embodiments of the present disclosure have been presented for purposes of illustration and description. They are not intended to be exhaustive or to limit the present disclosure to the precise forms disclosed, and obviously many modifications and variations are possible in light of the above teaching. The exemplary embodiment was chosen and described in order to best explain the principles of the present disclosure and its practical application, to thereby enable others skilled in the art to best utilize the disclosure and various embodiments with various modifications as are suited to the particular use contemplated.