Lethal Projectile Construction and Launcher

Abstract

A lethal projectile for immobilizing a target is capable of self-separating or otherwise opening after launch by a launcher and may release a payload prior to impact with a target. Opening may caused after an energy storage means of the projectile is charged beyond a threshold energy level. Charging of the energy storage means may be accomplished through dynamic induction when the projectile moves through a stationary magnetic field generated by a magnet of the launcher prior to launch, A control circuit can increase or decrease the magnetic field strength of the magnetic field in order to control the distance at which the projectile releases its payload, A rangefinder may provide distance information to the control circuit for charging the energy storage means to a specific energy level associated with the distance to a target.

Description

FIELD OF THE DISCLOSURE

The present disclosure relates to projectiles for use in weapons or other launching mechanisms and more specifically, to those projectiles and launchers that incorporate an electrical energy source.

BACKGROUND OF THE DISCLOSURE

Projectiles and launching systems are commonly used by law enforcement and military for purposes of self-protection, for example. The projectiles and launching systems may also be designed to subdue a target (such as a person or a location). Typically, such weapons systems require accurate and precise targeting of a projectile to be effective, i,e., the projectile must make physical contact with the target’s body or physical mass to work. If the projectile doesn’t strike the target, it likely does not affect the target.

To overcome this defect in traditional projectiles, projectiles have been developed that fragment into multiple pieces, thus increasing the effective radius of the projectile (and lowering the requisite targeting precision). Such fragmentation may be caused by components that are powered by a battery or batteries that is/are internal to the projectile or by the actual impact on the target. However, in that batteries are inherently respectively large and heavy when compared to a projectile, and therefore limit the potential configurations of the projectile (due at least to the fact that the batteries occupy a substantial amount of space within the projectile). Furthermore, batteries are relatively expensive, thereby driving up the cost of manufacture of such a projectile. Moreover, and quite concerningly, batteries drain and lose charge over time, which means that a projectile so configured may not be in a usable state for firing if it has been on the shelf for a length of time. This drawback is not acceptable, as the conditions under which such projectiles are to be used requires that they be ready to fire at all times.

Another attempted solution is an airburst-style projectile that is programed for particular detonation after launch of the projectile and/or has a distance to burst adjusted based on the distance of a previously-launched projectile. The programming of adjustments is done by the user. This system is also based on a battery, and therefore has all the drawbacks of the aforementioned battery-based system. Such a solution is complex and subject to misfires due to potential interference with radio frequencies while programming is attempted to be communicated to a projectile while in flight. Also, this system is extremely costly to manufacture.

Therefore, all of the currently available solutions suffer from one or more of the following disadvantages: a requirement of impact with the target, costly to manufacture, complex in configuration, and not reliably powered.

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) and projectile launcher that include all the advantages of the prior art, and overcomes the drawbacks inherent therein. As used herein, it is understood that “payload” refers to a substance, object, compound, or material that is capable of delivering a lethal or incapacitating force to and/or resulting in a lethal or incapacitating effect upon a target. In an embodiment, payload may be released from the lethal projectile disclosed herein when the projectile or projectile housing ruptures, disintegrates, separates or otherwise has an opening created therein. The payload may also comprise fragments of the projectile that are generated when the projectile disintegrates or fragments into multiple pieces.

The projectile also preferably comprises an energy storage means and an inductive energy element that is operatively coupled to the energy storage means. As used herein, “energy storage means” is a storage means that lacks a sufficient charge to activate or arm the projectile or another component of the projectile until the projectile has been launched and is moving down the barrel of the launcher. The minimum charge 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 response or chemical or electrical reaction. In an embodiment, the threshold energy is achieved through dynamic induction with a minimum projectile speed. It is understood to those familiar in the art that electromagnetic induction can occur in two ways: static induction and dynamic induction. Static induction refers to EMF generated in a stationary conductor (hence the term “static”) by modulating the magnetic field with respect to time. Dynamic induction refers to EMF generated in the conductor by moving the conductor (hence the term “dynamic”) through a stationary magnetic field. In an embodiment, a magnet or magnetic element is present along the launch axis of the projectile which produces a stationary magnetic field. Therefore, when the projectile that comprises an inductive energy element (such as a coil of wire for example), is moving down the launch axis of the projectile (i.e. through a barrel), said inductive energy element can be energized via dynamic induction. The amount of energization of the inductive energy element is dependent upon two important factors: (1) the projectile velocity as mentioned above (2) the magnetic field strength of the stationary magnetic field. If the projectile velocity is too low (such as in the event of a faulty launch, for example) the energization of the inductive energy element will not reach the threshold energy required to arm/activate the projectile. This provides for safer operation than prior art that utilizes static induction to energize/activate a lethal projectile.

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 initiation can be varied depending on the distance to the suspect or target.

In another embodiment the projectiles and launchers include various means of adjustment of the aforementioned embodiments in which the release or dispersion of the payload occurs at fixed or predetermined distances from the barrel of the launcher. For example, selective release can be accomplished by a timed reaction or time delay to initiate a reaction when using a controlled muzzle velocity, and such velocity can be controlled by an expansion gas or by propellant control. In an embodiment where the projectile comprises an inductive energy element coupled to an energy storage means, the energy storage means is energized above the threshold energy only when the velocity of the projectile is above the threshold velocity. In said embodiment, the amount of energization of the energy storage means can be used to vary the distance at which the aforementioned selective release occurs. As mentioned previously, in the case of dynamic induction, the amount of energization of an inductive energy element and by association, an energy storage means, is dependent on at least the speed of the projectile and the magnetic field strength of the stationary magnetic field. In an embodiment, an electromagnet is used to create a stationary magnetic field along the launch axis of the projectile. It is known that the magnetic field strength of an electromagnet is at least dependent on the amount of current supplied to the coil element of the electromagnet. In an exemplary embodiment of the present disclosure, the launcher comprises a control circuit that can be used to increase or decrease the magnetic field strength of the stationary magnetic field of the electromagnet. In an embodiment, the user can selectively adjust the magnetic field strength of the electromagnet in order to control the distance at which the projectile releases its payload. In an embodiment, the projectile has a control circuit that reads the amount of energization of the energy storage means. In said embodiment, the control circuit can associate (through a microcontroller, for example) certain energization levels with specific time delays. Said time delays can be used to control the distance at which the projectile releases its payload. In an embodiment, the projectile control circuit can be preprogrammed (i.e. outside of launcher), to separate at a specific distance after the projectile is energized past the threshold energy level. Projectiles that are preprogrammed to separate at a certain distance can be color coded or marked for distinguishability.

In an embodiment, a chargeable electrical circuit may be contained within the projectile. The electrical circuit the energy storage means may either initiate a chemical reaction or otherwise cause a separation of the projectile through an electromechanical method. Such methods can include an electromagnet, shape memory alloy or the like.

In an embodiment to a projectile that comprises an inductive energy element, the inductive energy element may be activated only when the projectile is moving along the launch axis of the launcher with a velocity above the threshold velocity. By limiting activation to the launcher, it is possible to encode the projectile and improve the safety characteristics by eliminating the likelihood of an accidental fragmentation or separation of the projectile outside of said launcher, for example during handling or transportation of projectile.

In a still further embodiment in which the separation is a result of a chemical reaction, such reaction may be initiated with an “electric match” or other initiator. The electric match may consist of a nichrome or similar high resistance element that is preferably coated with a pyrogen. The initiation may be in response to electrical energy such as from a battery, capacitor, or the like that has been charged by dynamic induction.

In a still further embodiment, the projectile launcher and the projectile are part of a system in which the projectile is encoded with timing and or distance information as a result of range to target. In an embodiment, the launcher comprises an electromagnet along its launch axis that is capable of producing a stationary magnetic field, an electric power source, a control circuit, and a range finder or other means for measuring distance to a target. In said embodiment, the electrical power source is coupled from the control circuit to the electromagnet. In said embodiment, the range finder is coupled to the control circuit. In this manner, the range finder can actively supply distance information to the control circuit which control circuit can use that information to adjust the power to the electromagnet. In an embodiment where the projectile comprises an energy storage means and a control circuit, when the projectile is launched through the electromagnet’s stationary magnetic field, it may be energized to the specific amount of energy associated with the distance to the target. In other words, the range finder information is used by the launcher control circuit to adjust the electromagnet’s stationary magnetic field strength such that when a projectile is fired through the electromagnet, the projectile energy storage means will be energized to a specific energy level associated with the distance to the target. That is, the projectile control circuit will read that specific energy level and cause (through a microcontroller, for example) the projectile to separate at that specific distance. The launch of the projectile by the launcher can be accomplished by compressed air or propellant or other means.

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. 2 is a view of a projectile launcher with a magazine in which the projectiles are set to rupture at various times/distances after launch, in accordance with an exemplary embodiment of the present disclosure.

FIG. 3 is a view of a projectile comprising a payload, a control circuit, an initiator, and an energy storage means, in accordance with an exemplary embodiment of the present disclosure.

FIG. 4 is a view of a projectile comprising a payload, an initiator, and a control circuit, in accordance with an exemplary embodiment of the present disclosure.

FIG. 5 shows a projectile containing a payload, a control circuit, an initiator, a switch and a timer in accordance with an exemplary embodiment of the present disclosure,

FIG. 6 shows a projectile and a launcher in which the projectile may wirelessly communicate with and/or be energized by the launcher, in accordance with an exemplary embodiment of the present disclosure.

FIG. 7 shows a comprising an inductive energy element, an initiator, a timer, and a microcontroller in accordance with an exemplary embodiment of the present disclosure,

FIG. 8 shows a projectile and a launcher in which the projectile may wirelessly communicate with and/or be energized by the launcher, in accordance with an exemplary embodiment of the present disclosure,

FIG. 9 shows a projectile and a launcher with a range finder and in which the projectile may be energized by the launcher, in accordance with an exemplary embodiment of the present disclosure, and

FIG. 10 shows a projectile comprising multiple elements which may be dispersed, 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 items.

The present disclosure provides for a lethal projectile 100 and a launcher 1000 for such a projectile 100, the launcher 1000 and projectile 100 comprising a system. The projectile 100 preferably comprises a payload 200 (such as shrapnel, which shrapnel may comprise fragmentation of part or all of the enclosure etc.) for affecting a target or suspect. The projectile 100 preferably comprises an enclosure, which enclosure may, in an embodiment be formed by an at least partially annular-shaped shell section 102 or shell sections (hereinafter also referred to as “shell”). In such an embodiment, the at least one shell section may include a closed, substantially planar end portion 104 (also referred to herein as “end cap” or “end portion”) that corresponds to a radius of the annular portion of the shell to form the enclosure. The at least one shell section 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 section 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. Furthermore, the shell may be of a one-piece configuration. The payload 200 is preferably contained in the enclosure prior to launch of the projectile 100. In an embodiment, the projectile 100 is capable of self-separating, disintegrating, fragmenting or otherwise opening prior to impact with a target. 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 (and/or launcher accessories) is capable of communicating to the projectile 100 and or arming a projectile 100 coincident with projectile launch. In an embodiment, the projectile is not armed/activated until it is launched down the launch axis (such as barrel 1010) of the launcher 1000. The arming can be, for example, the charging of an energy storage means contained within the projectile.

One end portion 104 of the projectile 100 may be removably attachable to the annular portion of the at least one shell section 102. The attachability of the end portion 104 to the annular portion may be mechanical, adhesive, or welded, for example. The attachability allows for ease of access to the enclosure formed by the end portion 104 and annular portion of the shell 102. The end portion 104 of the shell may have a greater dimension than the diameter of the annular portion of the shell 102 against which it attaches to create a flange. In another embodiment, the shell 102 comprises a first annular portion and a second annular portion in which the end portion 104 is fixedly attached to said first annular portion and in which the first annular portion and second annular portion are removably attached to one another such that the enclosure of the shell 102 may be opened elsewhere than the end portion 104 of the shell.

An exemplary launcher 1000 is shown in FIG. 1 and FIG. 9. The launcher comprises a launch axis (such as barrel 1010) for directing and launching a projectile 100. The launcher 1000 may also comprise a chamber or breech for holding a projectile prior to firing thereof. It will be apparent that the launcher 1000 shown herein (such as in FIG. 1 and/or FIG. 9) may be in other configurations so long as the launcher 1000 is capable of firing a projectile 100 of the projectiles disclosed herein.

In another embodiment, the projectile housing separates or fragments and becomes part of or is the lethal force.

In another embodiment the projectile 100 disclosed herein include various means of adjustment of the aforementioned embodiments in which the release or dispersion of the payload 200 occurs at fixed or predetermined distances from the barrel 1010 of the launcher 1000.

In another embodiment, the release may be accomplished by a control circuit 120. In another embodiment as shown in FIGS. 3 and 5, for example, a reaction may be initiated in response to a timer 130. Such reaction may increase the pressure inside the projectile 100 or otherwise cause a breach in the projectile housing. Furthermore, the breach in the projectile housing may be initiated by a chemical reaction and comprise materials such as nitrocellulose, NaN₃ or the like. In a further embodiment part or all of the control circuit can be encased in a gel, liquid, or potting compound, for example, to minimize damage from the forces resulting from acceleration of the projectile.

The launcher may also comprise at least one accessory thereto such as a magazine, for example, which at least one accessory may be in communication with a projectile using the same or other communications means as the launcher. As shown in FIG. 2, the launcher and projectile system may comprise a magazine 1040 that holds a plurality of projectiles 100 and that feeds said projectiles 100 to the launcher 1000 for firing/launching the projectiles 100. In an embodiment, the various projectiles 100 of the magazine 1040 may be configured to separate or rupture, etc. at the same distance “D” or time after launch, or they may be configured to separate or rupture, etc. at different distances and/or times after launch. In the embodiment where the various projectiles are configured to separate or rupture, etc. at the same distance “D” or time after launch, it will be apparent that a user may concentrate the effect of the payload from the ruptured projectiles within a certain defined area. In an embodiment where the various projectiles are configured to separate or rupture, etc. at different distances and/or time after launch, it will be apparent that the particular distance and/or time after launch at which the separation, etc. of each particular projectile of the various projectiles may be accomplished by selectively setting the separation, etc. of each projectile of the various projectiles as elsewhere set forth herein. Further, the separation, etc. of the various projectiles at different distances may provide for a more distributed dispersion of the payload in the event that dispersion of such material over a greater area is desired. In an embodiment, the magazine comprises an energy source (such as, but not necessarily limited to, a charger) for energizing the energizable storage means of a projectile while such a projectile is disposed within the magazine.

Referring again to FIG. 3, the projectile 100 may further comprise an energy storage means 140 (such as, but not limited to, a capacitor) and an initiator 150 (such as, but not limited to, a heating element). As will be discussed elsewhere herein, the projectile may also comprise an inductive energy element 160 that is operatively coupled to energy storage means 140. The charging of the energy storage means may also be referred to herein as “energizing” the energy storage means, The energy storage means disclosed herein may also be referred to as an energizable energy storage means. The energy storage means 140 and initiator 150 may be operatively coupled to a switch 180, and the timer 130 may cause the switch 180 to trip at a particular time after launch of the projectile 100, after which the energy storage means 140 may deliver stored energy to the initiator 150 to cause the initiator 150 to perform a reaction (such as heating) that results in the projectile 100 opening, separating, disintegrating or fragmenting.

In an embodiment, and as shown in FIG. 1, the launcher comprises an electromagnet or other magnetic element (such as a permanent magnet for example) capable of producing a stationary magnetic field along the launch axis (e.g. barrel 1010) of the projectile. In this manner, the projectile energy storage means will not be energized (via dynamic induction) until it passes through the stationary magnetic field, Due to the energy requirement of at least the initiator of the projectile, there exists a necessary threshold energy value which must be exceeded before the projectile is armed/activated. Due to the fact that the amount of inductive energy from dynamic induction is at least partially dependent on the velocity of the inductive energy element (i.e. the projectile), the activation/arming of the projectile is dependent on the velocity of the projectile through the stationary magnetic field. Therefore, if the launching of the projectile was faulty or the projectile were to fall out of the front of the barrel due to a chambering issue, the projectile would not be armed/activated. It should be apparent that if the primary energization mechanism of the launcher were static induction (described in detail earlier in this application) and the projectile were to fall out of the barrel, it would be armed/activated and could cause serious harm to the user.

In another embodiment, and referring to FIG. 4, the control circuit 120 is directly coupled to the initiator 150 such that the control circuit 120 activates the initiator 150. Initiator 150 may be an electric match, which electric match may heat upon activation to cause a future reaction, causing the shell of the projectile 100 to release the payload 200 and/or to fragment.

In still another embodiment as shown in FIGS. 6, 8 and 9, the projectile 100 and the launcher 1000 communicate through a wireless means. This allows the launcher to set parameters within the projectile allowing for more precise control of the point at which the housing is breached or ruptured, i.e. to set a particular distance or time at which the projectile may rupture. In a still further embodiment, the projectile has an energy source (such as an energy storage means 140) which is activated or powered or energized by the launcher 1000. In an embodiment, as shown in FIG. 6, launcher comprises an electromagnet concentric with and/or proximate to the launch axis of the projectile. In said embodiment, the projectile (and, in an embodiment, the energy storage means 140 thereof) can be charged or energized via dynamic induction. In a still further embodiment and as shown in FIG. 9, the launcher 1000 includes a means for measuring distance, such as a rangefinder, which means may communicate with the control circuit 120 and which means may permit in-situ customization of at least one parameter related to the burst or breach of the projectile 100, thus further increasing its ability to disperse the payload 200 at a more preferred or precise location. As shown in FIG. 6, the launcher 1000 may comprise a trigger 1080 to initiate the launch process. It will be apparent that the charging of the energy storage means by the launcher eliminates the requirement that the energy storage means comprise a self-contained power source (i.e., a battery for the energy storage means is not required), thereby eliminating the possibility that the energy storage means will suffer a power drain prior to launch. It will be apparent that the energy storage means can also be charged by an outside source other than the launcher prior to loading a projectile in the launcher. Further, a capacitor as an exemplary storage means is significantly lighter and cheaper than a battery, thereby improving performance and reducing the cost of manufacture of the present projectile.

In yet another embodiment and referring to FIG. 10, the projectile 100 comprises a payload of at least one mass 110 (such as a pellet, for example) and preferably, a plurality of masses 110, disposed in and/or on the housing of the projectile 100.

In an embodiment, the launcher comprises an electromagnet 1060 and an electrical power source (such as a battery for example). In said embodiment, the electrical power source is coupled to the electromagnet to create a stationary magnetic field (via DC voltage) through the launch axis of the launcher. It should be apparent that when a projectile with an inductive energy element (such as inductive energy element 160 as shown in FIGS. 3, 4, 5, 6 and 7 for example) is fired through the stationary magnetic field, the projectile will be energized and therefore armed/activated to rupture after exiting the launcher. The amount of energization of the inductive energy element 160 (comprised within the projectile 100) is importantly dependent on (1) the velocity of the projectile as it passes through the stationary magnetic field and (2) the magnetic field strength. The former factor is related to Faraday’s Law of Induction, which says a higher projectile velocity equals a higher energization. This fact inherently makes dynamic induction (the primary energization and projectile activation method in the present disclosure) safer than static induction (which can activate/arm the projectile regardless of whether it has been launched with a threshold velocity). In an embodiment where the projectile comprises an energy storage means 120, an inductive energy element 160 such as a coil of wire, a control circuit 120, and a timer 130 (such as the projectile pictured in FIG. 5), the projectile can be programmed to separate, rupture etc. after a certain amount of time has elapsed upon energization of the energy storage means to the threshold energy value, In another related embodiment, the projectile control circuit can read (through a microcontroller 170, for example) the amount of energy in the energy storage means and change the timer based on the amount of energization. It should therefore be apparent that by controlling the magnetic field strength, the distance at which the projectile will separate. rupture etc. can be controlled.

In an embodiment, the launcher includes a means of controlling the power to the electromagnet (such as a dial switch for example). In said embodiment, the control means can have visual indicators that correspond to different distances from the launcher. In this manner, the user can control the distance at which the projectile will separate etc. In another embodiment, the launcher contains a range finder (as shown in FIG. 9) or other distance measuring means which is directly coupled to the launcher control circuit and therefore to the electromagnet power source. In said embodiment, the range finder can feed the launcher control circuit with distance information which launcher control circuit can process said information and provide the necessary power to the electromagnet such that the projectile is energized with a specific amount of energy. Said specific amount of energy can be read by the projectile control circuit (through a microcontroller 170, for example) which sets a time delay corresponding to the distance information from the range finder. Said time delay is based on the projectile velocity and initiates separation of the projectile at the ideal specified distance. That is, micro controller can compare a specific value against preprogrammed values that are associated with distances. When the microcontroller finds a match between the read value and the preprogrammed value, it will set a time delay after which the projectile will fragment. As an example, if the target were 100 feet away, the launcher control circuit could feed 1 A to the electromagnet; when the projectile was fired through the electromagnet, the energy storage means (such as a capacitor for example) would be charged to 5V via dynamic induction. The projectile control circuit could be preprogrammed to know that between 4.9 and 5.1 V corresponds to a distance of a 100 feet. If the muzzle velocity of the launcher were controlled at 300 feet/see, 100 feet would correspond to a time delay of ~333 milliseconds. The projectile control circuit would set (through a microcontroller 170, for example) a timer for 333 milliseconds and then initiate separation etc. of the projectile.

Additionally, it is possible that, as part of the launcher electronics, the projectile launch velocity may be either measured or otherwise determined such that accurate burst distance of the projectile via a simple timing means may be enabled. For example, if the projectile average velocity is 100 meters per second and the target is at a distance of 100 meters, the timer may be set to enable disruption of the shell and or release of its contents at a time of 1.000 seconds. Such timing may be easily accomplished with either timing chips such as 555 or a microcontroller 170 (as shown in FIG. 7) such as AtTiny. In still a further embodiment of the launcher circuit, the circuit may include fingerprint or other biometric or access means (such as a personal identification number code) which may preclude launcher use except for by authorized individuals.

FIG. 1 represents a projectile launcher 1000 that is preferably based on electrical-driven or a combination of electrical and combustion or compressed gas means. It is understood that the projectile is not limited to a particular launching method but a preferable designed launcher in which the advantages of having an electronic control and communication element with the projectile can be used. The projectile herein being of lightweight construction (for at least the reason that it does not require an internal battery), compressed gas can sufficiently and effectively launch the projectile. Because the projectile is energizable by the launcher or other outside source, the possibility that the projectile would fail to operate due to draining of an internal battery is rendered moot.

The projectile and launcher disclosed herein offer the advantages of more controlled release of payload than existing solutions can offer. For instance, a user can set the range and/or rate at which the payload is delivered by configuring parameters that control the opening in the projectile. This range and/or rate can also be set automatically by a rangefinder that calculates the optimal distance at which fragmentation or separation is to occur. 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, Furthermore, the projectile can be kept in an unarmed state until the energy storage means is sufficiently charged, i,e., beyond a threshold energy. The energizing of the energy storage means by the launcher or other outside source eliminates the possibility that the projectile will suffer from power loss or failure prior to firing and further improves safe handling of a projectile.

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.

Claims

1. A launcher and projectile system, the system comprising a launcher,said launcher comprising an electromagnetic element, a launch axis, and an electrical power source,a lethal projectile,said projectile comprising a housing, a control circuit, an energizable storage means and an inductive energy element, wherein said inductive energy element is operatively coupled to said energizable energy storage means,which coupling enables said energizable energy storage means to be energized via dynamic induction by the said electromagnetic element,wherein movement of the projectile down the launch axis of the launcher during launch causes said energy storage means to be energized past a threshold energy andwherein after launch of said projectile said projectile housing ruptures disintegrates, separates, fragments, or otherwise has an opening created therein.

2. The system of claim 1 wherein the projectile control circuit is preprogrammed before launch to initiate separation of the projectile at least one of a prespecified distance and time.

3. The system of claim 1, wherein the launcher further comprises a control means to control the amount of power sourced to the electromagnetic element.

4. The system of claim 3, wherein the amount of power sourced to the electromagnetic element of the launcher can be controlled by the user and may set the distance and/or time at which the projectile will separate once it is launched.

5. The system of claim 4, wherein the launcher further comprises a means of measuring the distance to a target.

6. The system of claim 5, wherein the amount of power sourced to the electromagnetic element is set by the distance to the target.

7. The system of claim 4, wherein the amount of power sourced to the electromagnetic element of the launcher is used to set the distance/time at which the projectile will separate once it is launched.

8. The system of claim 1, wherein said projectile further comprises at least one initiator, which at least one initiator may initiate a chemical reaction or a mechanical response to cause an opening in the housing of the projectile.

9. The system of claim 1, wherein the threshold energy is defined as the minimum amount of energy required to initiate the initiator.

10. The system of claim 1, further comprising at least one of a trigger and a safety switch, wherein the energy storage means is not energized beyond the threshold energy until after the at least one trigger and/or safety switch is actuated.

11. The system of claim 1, wherein the launcher comprises a magazine, which magazine comprises a plurality of projectiles, each of which projectile of the plurality of projectiles ruptures, disintegrates, separates, fragments or otherwise has an opening created therein after launch at its own specified distance from the launcher.

12. The system of claim 1, wherein the energy storage means is one of a capacitor and a rechargeable battery.

13. The system of claim 1, said projectile further comprising a payload that is released from the projectile after rupture, disintegration, separation, fragmentation, or an opening created therein.

14. A launcher and projectile system, the system comprising a launcher,said launcher comprising a permanent magnet, a launch axis,a lethal projectile,said projectile comprising a housing, a control circuit, an energizable storage means and an inductive energy element, wherein said inductive energy element is operatively coupled to said energizable energy storage means,which coupling enables said energizable energy storage means to be energized via dynamic induction by the said electromagnetic element,wherein movement of the projectile down the launch axis of the launcher during launch causes said energy storage means to be energized past a threshold energy andwherein after launch of said projectile said projectile housing ruptures disintegrates, separates, fragments, or otherwise has an opening created therein.

15. The system of claim 14, wherein the projectile control circuit is preprogrammed before launch to initiate separation of the projectile at least one of a prespecified distance and time.

16. The system of claim 14, wherein said projectile further comprises at least one initiator, which at least one initiator may initiate a chemical reaction or a mechanical response to cause an opening in the housing of the projectile.

17. The system of claim 14, wherein the threshold energy is defined as the minimum amount of energy required to initiate the initiator.

18. The system of claim 14, wherein the launcher comprises a magazine, which magazine comprises a plurality of projectiles, each of which projectile of the plurality of projectiles ruptures, disintegrates, separates, fragments or otherwise has an opening created therein after launch at its own specified distance from the launcher.