Projectile Construction, Launcher, and Launcher Accessory

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, the disclosure of which is incorporated by reference.

FIELD OF THE DISCLOSURE

The present disclosure relates to projectiles and related launching mechanisms and accessories and more specifically, to projectiles which are not active until launched and which can be programmed by the launcher in a stationary position prior to activation which occurs during the launch and which self-separate via an initiator at pre-defined distances, times or altitudes from the launcher or proximities to a target.

BACKGROUND OF THE DISCLOSURE

Projectiles and launching systems are commonly used by law enforcement for purposes of crowd control or to individually subdue a suspect. Increasingly, they may find usage for self-defense. The projectiles and systems are designed to incapacitate a target such as a drone or subdue an individual or individuals without causing permanent harm. Typically, such weapons systems require impact with the target, accurate targeting, significant capital investment and/or significant expense for each individual projectile. Furthermore for targeting an individual or individuals, the most common devices require direct impact to the person, thus risking injury (eye for example) or in the case of a high voltage system, the risk of inducing cardiac events. In the case that the target is a unmanned aerial vehicle (UAV) or drone, high velocity rounds or specialized equipment such as shotguns and or missiles are often used. All of these existing means suffer from a number of disadvantages outlined in more detail below.

For the use in immobilizing a suspect, high voltage electric shock, kinetic rounds (beanbags for example), or capsaicin filled paintballs and the like have been used for a number of years. Drawbacks for kinetic rounds and paintballs are obvious in that poor targeting can result in impacting a suspect's neck, face or eyes resulting in permanent injury. The use of high voltage requires close proximity to the suspect and can result in cardiac arrest or be ineffectual if the suspect is wearing thick clothing. Additionally, all of these require accurate targeting as they rely on direct impact to the suspect. In the case of electric shock, the payload is tethered back to the launcher thus limiting range to typically less than 20 feet. In the case of a paintball filled with a capsicum or PAVA powder, range is not a limitation, but accurate targeting and ricochet (impact without bursting) become issues as does the direction in which the suspect is running. Running away from the projectile means that any dispersion is behind the suspect, rendering the projectile less effective. Another approach is to provide for a projectile, the rupture or separation of which is caused by components that are powered by a battery or batteries that is/are internal to the projectile. There are numerous drawbacks to this approach including “duds” in the event that the battery self-discharges, expense due to battery cost, and size and weight of the projectile which both increase to accommodate an active battery.

For use in disabling a drone or uncrewed aerial systems (UAS), there are a number of types of solutions that fall into broad categories such as physically destroying a drone and neutralizing a drone. While promising as countermeasures to current drone and UAS technology, each of these categories suffers from drawbacks including economics such as using a guided missile to destroy an inexpensive drone, requiring soldiers and or law enforcement to carry additional gear such as shotguns, jammers etc., accurate targeting for rounds which disable a drone by kinetic impact, collateral damage as can be the case for rifles used to down a drone. Rounds that miss often return with lethal force at significant distances from the target with the potential to inflict unintended damage, injury and death. Traditional projectiles and launching systems are commonly used to in an effort to destroy a drone or other moving object. Typically, such weapons systems require a projectile to burst on impact with the suspect and thus require very precise targeting to accomplish their intended effect. Furthermore, there is the risk of collateral damage should such an explosive projectile miss its intended target and instead impact a different object or land as live ordinance.

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, the jamming of radio signals is not specific to the drone and can result in jamming friendly communications unless it is directed. Directed jamming requires precise positioning and tracking the drone. Furthermore, such measures require specialized equipment and extra infrastructure.

All of the currently available methods for temporarily incapacitating a suspect or drone management suffer from one or more of the following disadvantages: difficult to target, not suitable for close range, not suitable for long range, inaccurate, causing unintended injury or fatalities, and often not effective for intended effect, costly to manufacture, complex in configuration, single use functionality and requirement of additional infrastructure. For example, law enforcement and/or soldiers may have to carry additional gear.

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), a 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 incapacitating a target. Such a payload can be in powder, liquid or aerosol, dye, ink, powder, foam. The payload further may include shrapnel, streamers, entanglement elements and adhesives without departing from the spirit of the disclosure. The payload may still further comprise a debilitating material such as Pava or Capsacin when used as incapacitating agent for biological (man, animal) targets. Payload may also comprise fire suppressants, flammable materials and the like for specialized cases.

In an embodiment, a launcher 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 may be disposed within or in proximity to the barrel 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. (See FIG. 1, for example). The at least one magnet is preferably magnetically-aligned with the launch axis. 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 causes a rapid change in magnetic flux of coil of the moving projectile as it moves along the launch axis. 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.

• • 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

( ε = - N ⁢ d ⁢ Φ B dt ) .

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, an accessory for a launcher comprises at least one magnet. 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. 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 an embodiment, the projectile separates into two or more components on exit from 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 another embodiment, an initiator 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. For example, the projectile may comprise an activating compound such as nitrocellulose in the center of the projectile and a payload surrounding the nitrocellulose, such that upon initiation of the activating compound, the projectile separates and the payload expands radially creating a payload cloud. The activating compound may also comprise at least one of a one of smokeless powder, hydrogen peroxide and catalyst, and the like.

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 another embodiment, the launcher comprises a range-finding means or configuration, a means or configuration of communicating and/or transmitting information to the projectile, and a means or configuration of communicating and/or transmitting power to the projectile. In an embodiment, the means or configuration of communicating information to the projectile is accomplished at a lower voltage than the voltage of the means or configuration of transmitting power to the projectile. In an embodiment, the means or configuration of communicating information is below the threshold energy level required to initiate separation of the projectile. 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 to separate the projectile. This is a safety feature that prevents accidental deployment of the payload.

In another embodiment, the projectile comprises a coil of wire and a control board, an energy storage means (such as a capacitor) for powering the control board, and a timing circuit, which timing circuit is in communication with the control board and which timing circuit is capable of delaying separation, rupture, etc. of the projectile. In an embodiment, the launcher, and in a preferred embodiment, the barrel of the launcher provides a constant magnetic field through which the projectile moves. The field may be provided by a magnet or magnetic element (such as an electromagnet) in or proximate to the barrel. The launcher may also comprise means or configuration for adjusting the launch velocity of the barrel for achieving a particular level of charge of the projectile as it passes through and is inductively charged by the magnetic field. Exemplary means of controlling projectile launch velocity include varying the air pressure the launcher uses to launch the projectile, changing the compression of a spring that may be used to launch the projectile, and varying the amount of an accelerant that may be used to launch the projectile.

In a still a further embodiment, the control board may include sensors such as barometric, proximity, acoustic, infrared and the like. The initiation of the payload release can be as a result of inputs from such sensors in addition to low voltage or particular energy programming which may occur prior to launch.

In another embodiment, a launcher comprises a control circuit and a tether (for example a rope, string, line etc.) which tether is operably coupled to a projectile. The coupling of tether to projectile can include at least coupling of tether to a switching circuit of the projectile and coupling of the tether to a mechanical ignition element (for example, a matchstick) of the projectile. The launcher is capable of unspooling the tether and capable of clamping the tether (this method of unspooling and clamping is common in fishing reels). In said embodiment, the launcher comprises a range finding means (for example, LiDar) and can detect a distance to target. The distance-to-target information can be communicated to the control circuit of the launcher. In said embodiment, the launcher can launch the projectile, which unspools the tether. Said launcher may further comprise a means for detecting how much tether is unspooled and therefore can determine real time distance of the projectile. Said launcher can clamp the tether at a distance corresponding to the distance-to-target information, wherein, clamping of the tether activates a control circuit of the projectile (for example, by pulling a toggle switch). It is understood that activation of the control circuit can have many forms and should not be construed as limiting the scope of the disclosure. Said control circuit can activate release of the projectile payload. In another embodiment, the clamping of the tether can activate a mechanical ignition (for example, striking of a match), which mechanical ignition initiates release of the projectile payload. It is understood that there are several forms of mechanical ignition may accomplish the same result and the that example provided above should not be construed as limiting the scope of the disclosure.

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 is a longitudinal cross-sectional view of a projectile launcher 1000 with a projectile, according to an exemplary embodiment of the present disclosure.

FIG. 1A is a view of the barrel of a projectile launcher and at least one magnet of the launcher.

FIG. 2 are views of a projectile both before launch and then during flight in which the housing of the projectile has separated and released a payload, in accordance with an exemplary embodiment of the present disclosure.

(NTS: Pending review of revisions to figures, existing FIG. 4 may be renumbered) FIG. 4 is a view of a projectile comprising a payload and an initiator, in accordance with an exemplary embodiment of the present disclosure.

(NTS: Pending review of revisions to figures, existing FIG. 6 may be renumbered) FIG. 6 shows a cross-sectional view of a projectile comprising a coil of conductive wire in accordance with an exemplary embodiment of the present disclosure.

(NTS: existing FIG. 7 and other remaining figures may be renumbered) FIG. 7 shows a projectile, launcher, launcher trigger and a launcher accessory, the accessory comprising at least one magnet which magnetic field lines are shown in accordance with an exemplary embodiment of the present disclosure.

FIG. 8 shows a projectile launcher comprising a plurality of charging chambers and a programmable projectile in accordance with an exemplary embodiment of the present disclosure,

FIG. 9 shows an embodiment in accordance with an exemplary embodiment of the present disclosure,

FIG. 10 shows an embodiment in accordance with an exemplary embodiment of the present disclosure, and

FIG. 11 shows an embodiment in accordance with an 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.

The present disclosure provides for a projectile 100 and a launcher 1000, and, in an embodiment, a launcher accessory 1100. The projectile 100 preferably comprises a payload 200 for incapacitating a target or suspect. It will be understood that payload as used herein may also comprise a substance, object, compound, or material that is capable of incapacitating the target. Targets are not necessarily suspects or otherwise living organisms and can also include drones and UAS.

The projectile 100 preferably comprises an enclosure, which enclosure may be formed by an at least partially annular-shaped shell 102. The shell may include a closed, substantially planar end portion 104 (also referred to herein as “end cap”) that corresponds to a radius of the annular portion of the shell to form the enclosure. The shell and end portion may individually and collectively refer to herein as a housing of projectile 100. It will be apparent that the projectile housing is not limited to the shell and end portion configuration mentioned in the preceding exemplary embodiment, and that the projectile housing may comprise any shape that forms an enclosure without deviating from the spirit of the disclosure, such as, but not necessarily limited to a sphere or a cone. Additionally, it is preferable that the projectile housing be in the diameter range of 12 to 45 millimeters to take advantage of existing law enforcement and or military armament such as an M203 launcher and the like.

In an embodiment, the projectile 100 is capable of self-separating, disintegrating or otherwise opening prior to impact with a target or other impact surface. In an embodiment, the launcher 1000 is capable of initiating separation or disintegration or rupturing or opening, etc. of the projectile 100. In an embodiment, the launcher 1000 is capable of communicating to the projectile 100 and/or arming a projectile 100 prior to or coincident with projectile launch. In another embodiment, the launcher comprises a safety and/or trigger, which safety and/or trigger, until activated, prevent the projectile from becoming armed. The arming can be, for example, capable of activating an initiator contained within the projectile.

FIG. 1 represents a projectile launcher 1000. It is understood that the projectile is not limited to a particular launching method which can include compressed air, a separate cartridge (such as firearm blank), combustion and primer or a propellant for example. In an embodiment, the projectile herein is of lightweight construction (for at least the reason that it does not require an internal battery), However, the disclosure may, in other embodiments include, a primer and/or propellant on the projectile and a hammer of the launcher to strike such primer, as well as other means of launching the projectile.

In another embodiment and as shown in FIG. 1A, the launcher comprises at least one permanent magnet 500. The at least one magnet 500 may be disposed within or in proximity to the barrel 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. (See FIG. 1, for example). The at least one magnet 500 is preferably magnetically-aligned with the launch axis. In a further embodiment, a launcher accessory 1100 comprises at least one permanent magnet 1500 (see FIG. 7, for example). The launcher accessory may be removably attachable to a launcher 1000, and the at least one magnet 1500 of the accessory may be disposed along the launch axis of the projectile that is to be launched by the launcher to perform a similar function

In an embodiment, and as shown in an exemplary embodiment in FIG. 6, the projectile comprises at least one coil of wire 550. When the projectile is launched, the at least one magnet 500 of the launcher and/or the at least one magnet 1500 of the launcher accessory 1100 causes a rapid change in magnetic flux of coil 550 of the moving projectile. This rapid change causes a current to be induced through the coil 550 of the projectile, causing an inductive energy to be produced. The resultant energy is sufficient to enable activation of an initiator in the projectile and is referred to as the threshold energy. Alternatively, the resultant energy can be used to cause an initiator (described elsewhere herein) to be activated immediately upon exiting the barrel, which is useful for close quarters or short range for example.

Referring again to FIG. 1A, an exemplary launcher 1000 launcher comprises a barrel 1010 for directing and launching a projectile 100. The launcher 1000 may also comprise a chamber 1015 for holding a projectile prior to firing thereof. It will be apparent that the launcher 1000 shown in FIG. 1A may be in other configurations so long as the launcher 1000 is capable of firing a projectile 100 of the projectiles disclosed herein.

In an embodiment, the projectile 100 housing opens or otherwise separates (as shown in FIG. 2 as 100a and 100b) after it leaves the barrel 1010 of a launcher 1000 to distribute a payload. That is, the rupturing or breaching of the projectile housing or the separation of housing components creates an opening in the projectile 100 out of which the payload 200 is dispersed.

In an embodiment, and as shown in FIG. 4, the initiator 150 may be an electric match or any compound capable of creating a spark, such as a flint or a matchstick, which electric match upon activation facilitates an opening in the shell of the projectile 100 by either heat or internal pressure increase for example to release the payload 200. It will be apparent that the initiator may be activated by the energy storage means, at least one magnet 500 of the launcher and/or the at least one magnet 1500 of the launcher accessory. In certain embodiments, the initiator will facilitate an opening of the projectile immediately or shortly after exiting the launcher which is desirable for close quarter operation.

In an embodiment, activation of the initiator 150 does not occur until the projectile 100 reaches a threshold velocity. Such velocity is referred to as the activation velocity or threshold velocity and must exceed 25 feet per second. In such an embodiment the energy required to activate the initiator (minimum threshold energy) cannot be achieved at velocities below the threshold velocity as explained below. As the induced voltage in a coil of wire 550 is directly proportional to change in magnetic flux divided by the change in time, if the change in time is lower (i.e. the projectile 100 passes through the magnetic field lines of the permanent magnet at a higher velocity), a higher voltage in the projectile coil 550 will be induced and hence a higher current will be moved through the coil 550 to the initiator 150 or energy storage device. Therefore, the projectile 100 must be traveling with sufficient threshold velocity to exceed the threshold energy required for activation of the initiator 150.

Referring now to FIG. 7, a launcher accessory 1100 for a launcher is shown. The launcher accessory 1100 comprises at least one magnet 1500. The launcher accessory 1100 may be removably attached to a launcher (including, but not necessarily limited to launcher 1000). The accessory 1100 is preferably attached to a launcher such that the at least one magnet 1500 of the accessory 1100 is disposed in sufficient proximity to the launch axis of the launcher to facilitate launch of the projectile 100 and to engage the coil of wire 550 of the projectile 100 prior to or coincident with launch of the projectile. FIG. 7 also shows exemplary magnetic flux lines 1501 through which a projectile may pass and which may engage the coil of wire 550 of the projectile. In this exemplary embodiment, the magnetic flux 1501 is disposed along the launch axis of the accessory 1100 and is accordingly magnetically aligned with path of the projectile's launch. In an embodiment, the accessory 1100 is an elongated cylinder in shape, with a circumference that corresponds to the circumference of the barrel of the launcher to which the accessory 1100 is attached. Attachment of the accessory 1100 to the launcher 1000 may be by way of complementary engagement features, by a friction- or press-fit engagement, or by threaded connection, for example. Magnets used on the accessory are not limited to a particular shape, configuration or number and can be segmented, cylindrical, prismatic for example

As shown in FIG. 7, the launcher 1000 may comprise a trigger 1080 to initiate the launch process. It will be apparent that the activation of the initiator by the launcher and/or launcher accessory eliminates the requirement that the projectile comprise a self-contained power source (i.e., a battery for the projectile is not required), thereby eliminating the possibility that the projectile will suffer a power drain prior to launch.

In another embodiment, as shown in FIG. 8, the launcher 1000 comprises a range-finding means or configuration 210, a means or configuration 220 of communicating information to the projectile 200, and a means or configuration 230 of communicating the minimum threshold energy requirement at launch. The means or configuration 220 of communicating information to the projectile may comprise conductive or inductive relaying of distance information to the projectile wherein analog data in voltage form is transmitted to the projectile, which data which can be converted to a time-delay for example by the control board of the projectile, and time-delay can facilitate setting the distance at which the projectile will separate.

In an embodiment, the means or configuration of communicating information to the projectile is accomplished at a lower voltage or energy than the threshold energy required to activate the projectile. In an embodiment, the means or configuration for communicating information to the projectile communicates distance-to-target information to the projectile, such as a time delay before initiation of separation of the projectile. In an embodiment, the time delay is drawn from distance-to-target information through a known velocity of the projectile. The communication of information is preferably at a voltage lower than the minimum threshold energy such that the projectile is not armed by the communication of information. In an embodiment, the launcher comprises a stationary position (such as a breech) or low velocity position such velocity being less than the aforementioned activation velocity and the voltage for communication of information is applied to the projectile in said position of the launcher. The communication of power to the projectile preferably occurs after the communication of information to the projectile. In an embodiment, the means or configuration for communication of power is accomplished by dynamic induction, such as by a magnet or magnetic component of the launcher energizing an energy storage means and exceeding a threshold energy level required for activation of the initiator of the projectile. In an embodiment, the information of distance to target determines when the projectile disperses its payload, such as through activation of an initiator as described elsewhere herein.

In another embodiment and as shown in FIG. 9, the projectile 100 comprises a coil of wire 550 and a control board or control circuit 120 (which control board or control circuit further comprises a timing circuit), an energy storage means for powering the control board or control circuit, at least one sensor 110, which control board or control circuit in conjunction with the sensor is capable of controlling the time at which the projectile payload is deployed. In an embodiment, the time delay is dependent upon the charge that the projectile receives in connection with its launch as described herein. The charge may be adjusted to provide for a particular time delay (such as a delay corresponds to distance to target). In another embodiment, the time delay is constant regardless of the launch velocity of the projectile and the at least one sensor is used to assist timing of payload deployment. In non-limiting embodiments, the at least one sensor can be barometric (to cause deployment at certain altitudes), proximity (to cause deployment at nearest point of approach to the target), or audible, optical or infrared in order to assist deployment at nearest point of approach to target. In another embodiment, the at least one sensor comprises an altitude sensor, and in a further embodiment, the altitude sensor comprises at least one of an absolute barometric sensor, a relative barometric sensor, and an inclinometer. Additionally, said sensor(s) could be used to prevent live rounds from hitting unintended targets such as the case as in civilians on the ground when targeting a drone or UAS. In an embodiment, deployment of the payload occurs at at least five feet higher than the height or altitude of the launch of the projectile. In an embodiment, deployment of the payload initiates at an elevation below the height or altitude of launch of the projectile. In an embodiment, the payload is deployed upon descent of the projectile of more than five feet from the apex of the trajectory of the projectile. In an embodiment, initiation of deployment of the payload results in a payload or gas volume increase of at least five times the internal volume of the projectile.

In another embodiment, and referring to FIG. 10, a launcher comprises a control circuit and a tether 1002 (for example a rope, string, line etc.) which tether is operably coupled to a projectile 100 such as via a spool 1001. The coupling of tether to projectile can include at least coupling of tether to a switching circuit of the projectile and coupling of the tether to a mechanical ignition element or an activating compound 1004 (for example, an nitrocellulose or a matchstick) of the projectile. In embodiment the activating compound may comprise nitrocellulose in the center of the projectile and a payload 1003 surrounding the nitrocellulose, such that upon initiation of the activating compound, the projectile separates and the payload 1003 expands radially creating a payload cloud. The activating compound may also comprise at least one of a one of smokeless powder, hydrogen peroxide and catalyst, and the like.

The launcher is capable of unspooling the tether and capable of clamping the tether (this method of unspooling and clamping is common in fishing reels). In said embodiment, the launcher comprises a range finding means (for example, LiDar) and can detect a distance to target 1005. The distance-to-target information can be communicated to the control circuit of the launcher. In said embodiment, the launcher can launch the projectile, which unspools the tether. Said launcher may further comprise a means for detecting how much tether is unspooled and therefore can determine real time distance of the projectile. Said launcher can clamp the tether at a distance corresponding to the distance-to-target information, wherein, clamping of the tether arms a control circuit of the projectile (for example, by pulling a toggle switch). It is understood that arming of the control circuit can have many forms and should not be construed as limiting the scope of the disclosure. Said control circuit can activate release of the projectile payload. In another embodiment, the clamping of the tether can activate a mechanical ignition (for example, striking of a match), which mechanical ignition initiates release of the projectile payload. It is understood that there are several forms of mechanical ignition may accomplish the same result and that the example provided above should not be construed as limiting the scope of the disclosure.

In another embodiment and as shown in FIG. 11, the disclosure comprises a projectile 100, a range finder 1110 (such as LiDar), a range finding signal 1111, a communications means or connection 1112, a control circuit 1102, a sensor 1103 (such as, but not limited to, a barometric sensor or an altitude sensor), a means 1104 of communicating information to the projectile, an altitude of target 1105, a target 1106 and a payload 1107. Control circuit in conjunction with sensor is capable of controlling the time at which the projectile payload is deployed. In an embodiment, the time delay is dependent upon the information communicated by the communications means that the projectile receives in connection with its launch as described herein. In another embodiment, the time delay is constant regardless of the launch velocity of the projectile and the at least one sensor is used to assist timing of payload deployment. In non-limiting embodiments, the at least one barometric sensor (to cause deployment at certain altitudes). In another embodiment, the at least one sensor comprises an altitude sensor, and in a further embodiment, the altitude sensor comprises at least one of a absolute barometric sensor, a relative barometric sensor, and an inclinometer. Additionally, said sensor(s) could be used to prevent live rounds from hitting unintended targets such as the case as in civilians on the ground when targeting a drone or UAS. In an embodiment, upon sensing an altitude, barometric condition, and/or a range to target, the payload may be deployed.

The launcher may comprise means or configuration 250 for adjusting and/or regulating the launch velocity of the barrel (“launch velocity regulator”) for achieving a particular level of charge of the projectile as it passes through and is inductively charged by the magnetic field. Exemplary means of adjusting projectile launch velocity include varying an air pressure that the launcher may use to launch the projectile, changing the compression of a spring that may be used to launch the projectile, and varying the amount of an accelerant that may be used to launch the projectile. By varying the launch velocity of the projectile, the time delay before separation and in conjunction with sensors if included, the range at which the projectile payload disperses can be adjusted.

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. 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 requirements in order to incapacitate a drone or other moving object.

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.