Fire suppression and protection apparatus

Abstract

A fire suppression method and system, including: a projectile including a payload of fire suppressing materials disposed therein; and a launching mechanism for launching the projectile; and a detection and ballistic calculation system for identifying a target and calculating a ballistic trajectory of the projectile, the projectile configured to disperse the fire suppressing materials at a predefined location or relative position related to the target.

Description

[0001] Fire Suppression and Protection Apparatus

[0002] FIELD OF THE INVENTION

[0003] The present invention relates to a systems and methods for fire suppression, and more specifically to a system for launching fire suppressant projectiles that are configured to release a fire suppressant material from the projectile at predetermined coordinates or at a relative position to the target area.

[0004] BACKGROUND OF THE INVENTION

[0005] Dropping a significant payload at a predetermined point in space can serve for many purposes, such as a means for extinguishing a fire in its early stages, when the fire arena is relatively small. For example, the arena may be within a few kilometers of an operational site and may be known to the operational site, but not easily accessible.

[0006] Giving fire extinguishing as an example, there are several means for bringing a mass of water and / or fire-retardant material to a point above a fire and discharging it there. Unfortunately, current methods suffer from significant limitations and disadvantages, for example:

[0007] Firefighters and fire trucks are limited in their response time, range and accessibility, as well as risking the lives of the firefighters.

[0008] An airplane or helicopter can carry a large load of water and / or fire-retardant material, but it takes time to prepare the payload, get airborne, and reach the fire; all of which require skilled pilots. Furthermore, the effectiveness of the deployed material is low due to the height of release above ground. When the material reaches the ground most of the water has evaporated resulting in less effective fire suppression.

[0009] Drones can be launched faster but are limited in their range, weight of payload that they can carry, battery lifetime, and need for operator skills. Furthermore, drones cannot operate effectively in windy conditions commonly occurring with or causing wildfires. External sprinklers spray fire suppressant material onto the structure and the surrounding area to prevent embers from starting a fire. However, their effectiveness is not guaranteed, especially in windy conditions. Furthermore, sprinklers depend on critical infrastructure (i.e., water, electricity) to function.

[0010] These methods imply a long delay (several minutes to tens of minutes) between the detection of the location of the fire and the response. The carrier medium must be dispatched at a remote location and arrive at the scene, highly depending on human skills (firefighter / pilot) - while the fire spreads rapidly, destroying acres of land, potentially killing civilians and livestock, causing air pollution and massive CO2 emissions to the atmosphere. Residential fires also suffer from slow response, as current fire suppressant means react to the fire usually after it spreads inside the house and outside of it, and not upon ignition.

[0011] SUMMARY OF THE INVENTION

[0012] The system presented herein overcomes the challenges detailed above by addressing at least the following issues:

[0013] Accuracy - the payload should be distributed over a predetermined area, with a superior accuracy of the state-of-the-art airdrop equipment such as an airplane.

[0014] Timeliness - the payload should reach a specific target within a very short period of time from the fire’s detection and subsequent deployment of the pay load, allowing multiple payloads to be deployed in rapid succession.

[0015] Automation - the launching process can be automated and autonomous.

[0016] Accessibility - the payload should be able to reach any point within the range of coverage.

[0017] Self-Sufficient & Durable - the system has its own water and power supply and sufficient materials to actively suppress spot fires for weeks.

[0018] According to the present invention there is provided a fire suppression system, including: a projectile including a payload of fire suppressing materials disposed therein; and a launching mechanism for launching the projectile; and a detection and ballistic calculation system for identifying a target and calculating a ballistic trajectory of the projectile, the projectile configured to disperse the fire suppressing materials at a predefined location or relative position related to the target.

[0019] According to further features in preferred embodiments of the invention described below the launching mechanism includes a linear actuator for propelling the projectile along the ballistic trajectory.

[0020] According to still further features in the described preferred embodiments the linear actuator is a belt-driven linear actuator powered by a rotational motor, a slingshot mechanism, a flywheel mechanism, a trebuchet-like mechanism, a pneumatic motor, and / or a linear hydraulic motor.

[0021] According to further features the linear actuator is an electromagnetic launcher, the electromagnetic launcher includes an electromagnetically powered rail-carriage assembly.

[0022] According to further features the electromagnetic launcher includes a static copper coil induction guide with a yoke connecting two magnetic plates that are propelled along the induction guide and a plurality of copper coils are disposed along a length of the induction guide. According to further features the electromagnetic launcher includes two facing sets of static magnets which propel a fin that is disposed between the sets of magnets, the fin housing therein a copper coil inductor.

[0023] According to further features the electromagnetic launcher includes a pump and heat exchanger disposed on a carriage couple to the fin, the heat exchanger being connected to the copper coil inductor and the pump being configured to pump cooling liquid through the heat exchanger and back into the copper coil inductor.

[0024] According to further features the electromagnetic launcher includes two facing sets of static magnets which propel a dynamic member that is disposed between the sets of magnets, the dynamic member housing three copper coil inductors. Further, the electromagnetic launcher includes a quick connector assembly that is configured to connect to open ends of the hollow tubes of the three copper coil inductors when the dynamic member is in a stationary position and inject cooling fluid into the hollow tubes.

[0025] According to further features the electromagnetic launcher includes N inductors that are connected by N connections to N busbars via brushes, using electrical commutation.

[0026] According to further features the electromagnetic launcher includes: a plurality of ferromagnetic cores the copper windings, the plurality of ferromagnetic cores disposed along two sides of a channel running a length of the electromagnetic launcher, a dynamic magnetic member connected to a carriage and a basket, the dynamic magnetic member having disposed therein N magnets where N > 1 ; wherein the dynamic magnetic member is disposed in an air gap between the ferromagnetic cores on each side of the channel. In embodiments, the channel is defined by a U-shaped piece that provides electrical communication between the plurality of ferromagnetic cores disposed along each of the sides of the channel. More accurately the U-shaped piece is used as a magnetic core material (yoke) for conducting the magnetic flux between the plurality of ferromagnetic cores and air gaps disposed along each of the sides of the channel and permanent magnets.

[0027] According to further features the projectile includes a trigger mechanism that causes the pay load to be released. According to further features the projectile includes a sensor kit in communication with the trigger mechanism, wherein the trigger mechanism is actuated based on sensor data from the sensor kit.

[0028] According to further features the sensor kit includes one or more sensors selected from the group including: a timer, an accelerometer, a barometer, a GPS sensor, a micro-electromechanical system (MEMS), and a radio receiver.

[0029] According to further features the projectile further includes a release mechanism in communication with the trigger mechanism. According to further features the release mechanism includes a pellet holding one or more chemicals, wherein activation of the one or more chemicals releases an expansive gas causing overinflation of a polymeric skin of the projectile resulting in a rupture of the skin and dispersal of the payload.

[0030] According to further features the release mechanism includes a hotwire that runs over an outside or along an inner perimeter of the projectile (possibly even between layers of the polymeric skin of the projectile), which, upon receipt of a signal from the triggering mechanism, heats up and causes a polymeric skin of the projectile to rupture.

[0031] According to further features the system further includes an automatic loading system for loading the projectile and placing the projectile onto a basket of the launching mechanism. According to further features empty projectile bags are disposed on a pipe connected to a reservoir of the fire suppressing materials in such a manner that a bottom-most empty bag thereof is positioned so as to be filled with the fire suppressing materials, sealed, and deposited onto the basket. According to further features a sensor kit, trigger mechanism, or both are disposed in or on the projectile prior to launching the projectile.

[0032] According to further features the detection and ballistic calculation system includes: at least one detection element for detecting or identifying the target location, a ballistic calculator for calculating the ballistic trajectory, the ballistic calculator further adapted to communicate data from the ballistic calculator to a sensor kit disposed in or on the projectile indicating when a triggering signal is to be transmitted to effect release of the payload. According to further features the system further includes a processor adapted to process raw sensor data received from said at least one detection element.

[0033] According to another embodiment there is provided a method of fire suppression or prevention, including: detecting a target; communicating a location of the target to a ballistic calculator; calculating, by the ballistic calculator, a trajectory to predetermined coordinates; launching a projectile with a payload of fire-suppression material along the trajectory; sensing, by at least one sensor in or on the projectile, arrival of the projectile at the predetermined coordinates; triggering, based on that sensing, a release mechanism to offload the payload from the projectile so as to optimally deploy the payload to the target.

[0034] In another embodiment the release mechanism is done by pulling a wire and / or a string that opens the capsule bag (e.g. like a thread from a woolen sweater unravels the entire sweater). BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Various embodiments are herein described, by way of example only, with reference to the accompanying drawings, wherein: FIG. 1 is a pictorial depiction of an example fire suppressant system according to the present invention;

[0036] FIG. 2 is an exploded view of an example embodiment of a rotational motor linear actuator;

[0037] FIG. 3 is an example slingshot launching mechanism;

[0038] FIG. 4 is a launching mechanism with an electromagnetic launcher according to a first configuration.

[0039] FIG. 4A is a magnified back view of a section of the electromagnetic launcher launching mechanism depicted in Fig. 4.

[0040] FIG. 4B is a partial sectional view of the example electromagnetic launcher launching mechanism.

[0041] FIG. 4C is a magnified view of a Fig. 4B;

[0042] FIG. 5 is a launching mechanism with an electromagnetic launcher according to a second configuration;

[0043] FIGS. 6-6D are a third configuration of the electromagnetic launcher propulsion mechanism;

[0044] FIGS. 7, 7A and 7B depict a launching mechanism with an electromagnetic launcher according to a fourth configuration;

[0045] FIG. 8 A is an example embodiment of the projectile;

[0046] FIG. 8B is another example embodiment of the projectile;

[0047] FIGS. 9A-9E are an example embodiment of a capsule, that is part of an automatic filling and loading sub-system;

[0048] FIG. 10 is a logic block flow diagram of the system operation process.

[0049] DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0050] The principles and operation of a fire suppressant system according to the present invention may be better understood with reference to the drawings and the accompanying description.

[0051] Figure 1 illustrates a pictorial depiction of an example fire suppressant system according to the present invention.

[0052] The example system 100 includes a launching mechanism 10, a projectile 20 with fire suppressing materials disposed therein, and a detection / aiming sub-system, hereafter referred, inter alia, as a detection and ballistic calculation system 30 that, among other functions, calculates a ballistic trajectory of the projectile 20. The ballistic calculations are fed into the launching mechanism which then propels the projectile (and, potentially, one or more additional projectiles to a same, similar, or different position) in order to suppress the fire F. In some cases, the projectile is dispatched to a position that is not over the fire, but rather some other area in order to disperse the fire suppressing materials at a location to serve as a preemptive action to prevent the spread of the fire or of a future fire that may break out.

[0053] In some embodiment of the invention, the launching mechanism includes a flywheel. A flywheel is a mechanical device that uses the conservation of angular momentum to store rotational energy, a form of kinetic energy proportional to the product of its moment of inertia and the square of its rotational speed. In particular, assuming the flywheel's moment of inertia is constant (i.e., a flywheel with fixed mass and second moment of area revolving about some fixed axis) then the stored (rotational) energy is directly associated with the square of its rotational speed.

[0054] In some embodiments of the invention, the launching mechanism includes a trebuchet or trebuchet-like mechanism. A trebuchet is a type of catapult that uses a rotating arm with a sling attached to the tip to launch a projectile. The design of a trebuchet allows it to launch projectiles of greater weights and further distances than that of a traditional catapult. There are various types of trebuchets. It is made clear that modifications and variations of the flywheel and trebuchet are included within the scope of the invention.

[0055] A pneumatic motor (air motor), or compressed-air engine, is a type of motor which does mechanical work by expanding compressed air. Pneumatic motors generally convert the compressed-air energy to mechanical work through either linear or rotary motion. A pneumatic launcher, according to an embodiment of the invention, uses a pneumatic motor to propel the carriage to launch the capsule.

[0056] A hydraulic cylinder (also called a linear hydraulic motor) is a mechanical actuator that is used to give a unidirectional force through a unidirectional stroke. A hydraulic cylinder is a hydraulic actuator that provides linear motion when hydraulic energy is converted into mechanical movement. In some embodiments of the invention, a linear hydraulic motor is used to launch a projectile along a precalculated ballistic trajectory.

[0057] In some embodiments the launcher is a pipe, and the propulsive energy is created by explosive materials and / or gas generation and / or pyrotechnic-based mechanisms. In some embodiments the launcher launches a singular or multiple payloads, for example 1 to 1000 payloads launched simultaneously.

[0058] In some embodiments the launcher may be stationary, i.e., installed in a fixed position (e.g., calculated to be the most efficient position to protect a predefined area). Alternatively, in other embodiments the launcher may be mobile, such as a vehicle mounted device or a device that can be transported from place to place by a vehicle

[0059] In some embodiments of the invention, the launching mechanism includes a linear actuator for propelling the projectile along the ballistic trajectory. In example embodiments, the linear actuator is powered by a rotational motor, referred to hereafter as a rotational motor linear actuator. One or more rotational motors may be employed. Figure 2 depicts an exploded view of an example embodiment of a rotational motor linear actuator. This type of mechanism is also referred to herein as a belt-driven actuator.

[0060] In the example linear actuator depicted in Fig. 2, the belt-driven actuator includes two rotational motors 210, a belt 220, which is assembled on two roller wheels 230. In the depicted example embodiment, the linear actuator includes two motors.

[0061] In other example embodiments, only a single motor is used. In such embodiments, one roller wheel is rotated by the motor which causes the belt to rotate around the rollers. In still other example embodiments, there are more than two motors. In other example embodiments, there is more than one belt, and / or more than two wheels, and / or some of the wheels may be used as gears to change the speed between the motor and other wheels in the system. Furthermore, in some configurations a spindle and / or tenon and / or disk and / or other connectors and / or joints might be used for converting the rotational motion from the motor to a linear motion of the belt. Another application for the added joints could be for starting and / or stopping the belt and / or the carriage 240, for example a breaking disk or other breaking mechanism.

[0062] A carriage 240 is driven by the movement of the belt 220 to run on two rails 250. The carriage is (or can be) adapted to hold a capsule / projectile of the present invention. The carriage moves rapidly on the rails and the projectile is launched when the carriage slows or stops abruptly.

[0063] In example embodiments, the linear actuator is powered by a biased tension mechanism, hereafter also referred to as a slingshot or catapult mechanism. An example slingshot launching mechanism is depicted in Figure 3.

[0064] The example slingshot 300 of Fig. 3 includes a tensioned contraption set at an inclined angle. The basket or holder 310 for holding the projectile is affixed to a carriage or wagon 320 that is guided up and down in the incline between two rails 322. The wagon includes wings 324 onto which extension or tension springs 332 can be connected. The tension springs are fixed, on one end, to a stationary frame 330. One or more springs can be connected to each of the wings of the wagon. Each spring stores potential energy when extended. The more springs connected to the wings, the more potential energy is stored. The wagon is connected via a steel cable 342 to an electric winch 340. The winch is configured to draw the wagon down the inclined rails towards it, like drawing the string of a bow. As the winch pulls the wagon, the springs (connected to the wings) are extended. A release mechanism 344 releases the cable, freeing the wagon to accelerate upwards at great speed, propelling the projectile out of the basket. Shock absorbers 326 receive the wagon at the top of the rails, bringing the wagon to a stop.

[0065] Fig. 3 demonstrates only one example of a slingshot, and it should be noted that its different sub-systems could be arranged in different manners, for example the springs 332 could be fixed on the ground and connected to the carriage or wagon 320 through a pulley or multiple pulleys that pull the steel cable 342 and may multiply the tension force.

[0066] In other example embodiments, the linear actuator is an electromagnetically powered railcarriage assembly, also referred to hereafter as an electromagnetic-launcher. A linear induction motor (LIM) is an alternating current (AC), asynchronous linear motor that works by the same general principles as other induction motors but is typically designed to directly produce motion in a straight line. The following example embodiments and configurations employ principles of linear induction motors with various unique modifications and variations.

[0067] In legacy design of this type of electric motor, the force is produced by a linearly moving magnetic field acting on conductors in the field. Any conductor, be it a loop, a coil, or simply a piece of plate metal, that is placed in this field will have eddy currents induced in it thus creating an opposing magnetic field in accordance with Lenz's law. The two opposing fields will repel each other, creating motion as the magnetic field sweeps through the metal.

[0068] An example embodiment of a launching mechanism with an electromagnetic launcher is depicted in Figure 4. Figure 4A is a magnified back view of a section of the electromagnetic launcher launching mechanism depicted in Fig. 4. Figure 4B is a partial sectional view of the example electromagnetic launcher launching mechanism. Figure 4C is a magnified view of a Fig. 4B. The depicted example embodiment in Figs. 4, 4A, 4B, and 4C is referred to herein as a coreless, copper static and magnet dynamic launcher. The aforementioned word ‘coreless’ refers to the fact that the propulsion system / motor is devoid of an iron core.

[0069] The electronics are installed on the launcher rail 410 which includes a static copper part (epoxy plate, coil and electronic unit) and the magnetic part (two magnetic plates) 422 is installed on the yoke (moving part) 420 that carries the capsule (inside a basket / carrier member 430). This configuration is different from the existing configuration of a linear motor and / or a railgun and / or a coil-gun.

[0070] The launcher rail 410 includes a fiberglass epoxy plate 414 that contains a cooled copper coil 416 that receives a peak of current from the hardware (electronic unit) 418 underneath it. This is the static copper element referred to by the phrase ‘copper static’ in the aforementioned descriptive name ‘coreless, copper static, magnet dynamic launcher’. The yoke / carriage includes rollers that run on metal guiderails 412.

[0071] The partial cut-away view of Figs. 4B and 4C allows a view of one copper coil 416 that is connected to its electronic unit 418. The depicted coil is a single-turn coil. Two vertical sections and one horizontal section of the coil are visible. The second horizontal section (not visible) of the coil, that completes the circuit, is disposed inside the electronic unit which, inter alia, provides power to the coil. In this example a single turn is pictured, however a multiturn coil could be used as well. Furthermore, a plurality of these copper coils and electronic units are disposed along the length of the launcher rail. Sequentially energizing the coils propels the magnetic plates (and hence yoke / carriage) along the launcher rail. This is the meaning of the term ‘magnet dynamic’ in the aforementioned descriptive name ‘coreless, copper static, magnet dynamic launcher’.

[0072] Along with the magnetic field created by adjacent magnetic plates 422 (from both sides of the fiberglass plate), a force is built with the direction of the rail, which drives the capsule in the basket along the launcher rail at high speed. In Fig. 4C the vectors of the electric field (IL), magnetic field (B) and Lorentz force (F) are depicted where the applied force is linearly proportional to the current and the magnetic field (F = IL x B). Part of the carriage itself is made from a ferromagnetic material, that functions as a yoke 420 to close the magnetic field between the two magnetic plates 422. In other example embodiments, coils with two or more turns may be used. The more turns, the more electromagnetic power. The direction of the flow of energy inside the coil determines the direction of the moving magnets (magnetic plates and yoke). Once the magnets pass the first vertical portion of the coil, the direction of energy is reversed so that the second vertical section now has the same direction as the first vertical section had, ensuring that the magnets continue in the same direction. After passing the first coil, the magnets arrive at the second coil where the same process is repeated, moving the magnets (and hence the carriage) up the launcher rail.

[0073] The aforementioned configuration is merely exemplary. Other configurations are envisioned using the same basic components but different placement and / or structural, electrical, and / or magnetic configurations.

[0074] A second configuration of a launching mechanism with an electromagnetic launcher can be seen in Figure 5. Figure 5 is a cut-away / sectional view of a portion of a launcher rail 510, exposing a portion of the carriage 520. Some components have been rendered transparent for increased clarity. The launcher rail has the same general form as the one depicted in Fig. 4, but with a different configuration of the propulsion system. The second configuration is also devoid of an iron core. What it does include is a static set of magnets each having a south pole 540S and north pole 540N. The magnets are disposed along the length of the launcher rail, on each side of a copper fin 522. A carriage 520 is connected to the copper fin 522 which is propelled by the magnetic field that is generated by the static magnets. A copper coil / inductor 524, disposed inside the fin 522, is exemplarily depicted with five turns. More or less turns are considered to be included within the scope of the invention. The depicted coil with five turns is merely an example embodiment.

[0075] Here too, the direction of movement is dependent on the direction of the current flowing in the coil, relative to the poles of the static magnets lining each side of the channel. The vertical direction of the current (up or down) flowing in the vertical segment of the coil, must correspond to the correct pole to keep the copper coil moving in the same direction. Therefore, each time the vertical sections of the coil move from pole to pole of the magnets, the direction of the current is reversed. The current is actually reversed at the point where the vertical sections are between magnets, which is a dead zone, where the carriage continues to move through inertia.

[0076] However, with this configuration there are at least two drawbacks. One drawback is that there are these dead zones between the magnets. Another drawback is that one coil handles the entire job of propelling the carriage. These drawbacks are addressed in the third configuration discussed hereafter.

[0077] A third configuration of the electromagnetic launcher propulsion mechanism is depicted in Figures 6-6D. Figure 6 depicts a representation of a portion of the propulsion system of the third configuration. Figure 6A is a magnified view of a section of Fig. 6. Figure 6B is a sectional view of Fig. 6A. Figure 6C is another sectional view of Fig. 6A. Figure 6D is a sectional view of Fig. 6C.

[0078] Fig. 6 depicts a portion of the launcher rail which serves as a channel 610 through which a dynamic member 622 moves. Unlike the second configuration discussed above, in the present configuration the dynamic member includes three coils / inductors 624, 626, and 628, which overlap each other. As discussed above, the channel is populated with magnets arranged with alternating poles 640S, 640N placed side by side along each side of the channel. In the example embodiment, each of the three coils has five turns. In Fig. 6D, each coil is sectioned at a different height, making it easy to identify each of the different coils.

[0079] Similar to a three-phase motor, here, two of the coils work while one is inactive. Looking at Fig. 6D, the left-hand side of coil 624 is on one magnet pole and the right-hand side of the coil is on an adjacent pole. Likewise, the left-hand side of coil 628 is definitively on one pole while the right-hand side of coil 628 is definitively on an adjacent (and opposite) pole. As such, coils 624 and 628 are active in moving the dynamic member along the channel. However, both the left and right sides of coil 626 are (at least partially) in-between magnets (or poles thereof) and therefore are inactive. As the dynamic member 622 moves, the direction of the current running through coil 626 is reversed so that the member keeps moving in the same direction in the manner described above. As the dynamic member moves, one of the other coils will come out of alignment with the magnetic poles and become inactive and then reactivate with reversed current direction. In this configuration, two coils are active and one coil inactive at all times during the journey through the channel. This configuration addresses both of the aforementioned drawbacks by spreading the work between three coils and eliminating the dead zones. As the coils run the shuttle / dynamic member up and down the launcher rail, the coils heat up (or the single coil in the second configuration). Unlike most linear motors where the magnets move and the coils are stationary, in the second and third configurations, it is the coil or coils that move while the magnets are stationary. This causes the coil or coils to heat up much more than their legacy counterparts. To cool such coils down, cooling fluid is run through the hollow copper pipes of the coils. However, in configurations two and three the coils are mobile, making it undesirable to have a fluid line connected all the time, as could be the same, for example, in configuration one, where the coils are stationary.

[0080] However, unlike legacy linear motors, the instant motors spend a relatively large portion of their time parked at the bottom of the launcher (e.g., waiting for the next operation and / or while the automatic loading system prepares and loads a capsule into the basket). As such, the present invention, according to example embodiments, includes a quick connector assembly 650 (see Fig. 6C) that connects to the open ends of the hollow tubes of the coil when the carriage returns to the parked position at the bottom of the launcher rail and injects cooling fluid into the hollow tubes.

[0081] According to another example embodiment, a pump can be placed on the carriage which circulates a cooling fluid using electrical power from the brushes. In another example a flexible container such a balloon could be connected and filed with cooling fluid while parking and circulates the fluid in the coils during the carriage movement. Furthermore, the basket (which carries the capsule) is used as a radiator / heat exchanger to cool the cooling liquid. An example embodiment of the aforementioned configuration is depicted in Fig. 5. A pump 550 and heat exchanging arrangement 552 is depicted on the carriage. The pump circulates the cooling fluid up to the basket to be cooled as the basket moves rapidly through the air.

[0082] In some example embodiments, the coils (or coil, in the case of configuration two) receive electricity in a unique manner. The N inductors are connected by N connections to N busbars via brushes. In the second configuration N=l, in the third configuration N=3. The number of coils / inductors in the example configurations are example embodiments. More or less coils / inductors are considered to be within the scope of the invention. The busbars are stationary throughout the length of the motor. Three busbars 670 are depicted in Figs. 6, 6A, and 6B.

[0083] Each busbar is connected to power electronics commutation device (inverter, half bridge, full bridge or other topology / circuit - not shown) so as to provide the required voltage and current to the coil. Uniquely, the present embodiment has a brushed induction rotor that utilizes power electronics commutation instead of mechanical commutation. As such, the third configuration provides a three-phase linear motor with three brushes but without commutation in the brushes but rather using electrical commutation. A fourth configuration of the electromagnetic launcher propulsion mechanism is depicted in Figure 7. The launcher is disposed on an example rotatable platform 714 and elevation of the launcher is effected by an actuator 712 which may be pneumatic, telescopic, or otherwise actuated. Figure 7 is a side view of the launcher with a side of the launcher rail rendered transparent. A plurality of cores 740, which are disposed along one side of the rail, are visible in Fig. 7. Each core is laminated steel or some other ferromagnetic material. Copper wire 742 is wound around the iron core. Multiple cores are disposed along the length of the rail and configured to propel a permanent magnet, or multiple permanent magnets, which are attached to the yoke, along the rail.

[0084] Figure 7A depicts a magnified portion of the launcher system of Fig. 7 with a cutaway section. Figure 7B is a back isometric view of the launcher rail 710. A U-shaped iron / metal channel 752 runs along the length of the launcher rail. Iron cores 740 are disposed along each vertical wall of the U-shaped piece. Between the iron cores is a gap referred to as an air gap 754. A dynamic magnetic member 720 is disposed in the air gap. The dynamic magnetic member is connected to the carriage and basket. The dynamic magnetic member includes at least one magnet with a North and a South pole. In embodiments, N number of magnets are disposed on the dynamic magnetic member. N may be 1 or more than 1.

[0085] In some embodiments, there is no U-shaped channel, just cores disposed on either side without a connecting (horizontal) piece / yoke.

[0086] When the copper windings are electrified, the magnetic field pulls the magnetic member until the magnet is opposite the core. When a magnet is positioned opposite an iron core, the magnet does not move. This is a dead zone. The next core must then be electrified, in order to pull the magnetic member forward until reaching the dead zone, and then the next core is electrified and so on. In some embodiments, once the magnet is out of the dead zone, the direction of the current can be reversed to now push the magnetic member away, towards the next core.

[0087] It is made clear that wherever a feature or component is described, drawn, and / or otherwise detailed with relation to a specific configuration and / or embodiment, it is to be seen as if that feature, whether optional or essential to the functioning of the system / device, is described in full for each and every configuration and / or embodiment as being optional or essential for that configuration / embodiment, based on the context and the understanding of one of ordinary skill in the field when presented with these descriptions. So, for example, the irrigation system 650 for coils 624, 626, and 628, is to be seen as if fully described and drawn, mutatis mutandis, for coil 524. And, in another example, the heat exchanger 552 and pump 550 of Fig. 5 is to be seen as if drawn as an optional embodiment for the configuration of Fig. 6 with corresponding text describing this feature, mutatis mutandis. Furthermore, each coil in any of the configurations can be as a single turn or multiple turns and / or each magnetic pole could be with different layers and different orientations, for example using a Halbach array, and / or each current pulse could be either DC or AD or any pulse waive configuration. Another use of the electromagnetic force in addition to acceleration is deceleration of the moving parts. Also, the electromagnetic force could be used for returning the moving part back to its starting point.

[0088] PROJECTILE

[0089] By way of introduction, each embodiment of the projectile 20 (generically depicted in Fig. 1) has a number of features one, some, or all the features may be included in the various embodiments. One feature is the contents or payload 22. In general, the payload will be one or more materials used for suppressing a fire and / or forming a fire-line barrier and / or covering assets with fire retardant for protecting communities. Another feature is a sensor mechanism / kit that determines when the payload should be released. This is also referred to herein as a trigger or trigger mechanism 24. In some embodiments, this mechanism further includes a safety or failsafe feature that triggers the release of the payload if the projectile falls below a predefined height threshold above the surface. This mechanism may be attached to the projectile or disposed inside the projectile. One optional feature is the actuation or release mechanism that causes the payload to discharge from the projectile. In some embodiments, the projectile may not release the payload at all, but rather the projectile will explode on contact with the fire / ground.

[0090] In one example embodiment, the projectile may be a 45 kg, 50 cm diameter capsule containing 12 US gallons of off-the shelf, environmentally approved, fire-retardant material mixed with water.

[0091] In one embodiment of the invention, the payload is a liquid material, for example a composition of water with a weight percentage of 0% to 100% of fire retardant such as ammonium phosphate, in volume ranging from 0.5L to l,000L.

[0092] In another embodiment of the invention, the payload is a gaseous material, for example CO2 in volume ranging from 0.5L to l,000L.

[0093] In another embodiment of the invention, the payload is a solid material, for example a powder, or other dry chemicals in mass ranging from O.OlKg to l,000Kg.

[0094] In one embodiment of the invention, the payload is carried by a plastic bag, or other polymeric based bags or multi-layer sheets, such as thermolamination PE / PA(Nylon) / PE, of thermoforming film, or natural materials, or composite materials, such as plastic-metal laminates. In one embodiment, the capsules are made of polymeric (possibly biodegradable and / or corrosion resistant) materials which are harmless to the environment. In other embodiments the payload is carried by a glass container or other ceramic and / or metallic and / or paper containers.

[0095] In one embodiment of the invention the release mechanism is triggered by relative barometric pressure. In another embodiment of the invention the release mechanism is triggered by multidimensional acceleration. In another embodiment of the invention the trigger mechanism is triggered by duration of a time of flight. In another embodiment of the invention the trigger mechanism is triggered by temperature. In another embodiment of the invention the trigger mechanism is triggered by barometric pressure representing elevation above sea-level. In another embodiment of the invention the trigger mechanism is triggered by a remote command. In one embodiment of the invention the release mechanism is triggered by a GPS or other guidance / navigation system. In another embodiment the trigger mechanism is based on a MEMS [navigation] system.

[0096] In one embodiment of the invention the actuation is done by inflation of the payload container / capsule / bag so it is torn open. In another embodiment of the invention the actuation is done by cutting or opening or breaking the container. In another embodiment of the invention the actuation is done by disintegration of the payload container through a chemical reaction. In another embodiment of the invention, the release mechanism is a hot-wire that burns through the polymeric container or melts the polymeric bag, causing the capsule to rupture and the payload to be dispersed.

[0097] In one embodiment of the invention, the system verifies if its mission is completed or not, thus repeating the launching operation towards the target with an intelligent payload, such as a sensor, for example a camera or a thermal sensor or a navigation system with maneuvering ability.

[0098] In example embodiments, each capsule contains a sensor kit (e.g., including one or more of an accelerometer, barometer, timer, receiver, GPS, and the like) that ensures the capsule will initiate (i.e., release the contents of the capsule) at the desired coordinate and disperse the fire retardant on the ground below. In case this initiation mechanism fails, the barometer (or other mechanisms such as a built-in timer, remote detonator, etc.) will act as a second, independent mechanism to initiate the capsule at a predetermined height (safety mechanism) or after some time-of-flight. In any case, the capsule itself will not fall on the ground / building / human. Conversely, in some embodiments, as mentioned above, the capsules are launched with the purpose of impacting the ground so as to disperse the payload on the ground upon impact.

[0099] Each capsule that is adapted to open in flight also contains an initiation / detonation mechanism (e.g., housed in the sensor kit or otherwise initiated by an initiating mechanism in or near the sensor kit, or distanced therefrom) that accurately rips open the capsule at the preprogrammed coordinates.

[0100] One example embodiment of the projectile 800 is depicted in Figure 8A. The initiator consists of a trigger mechanism 810 and an actuator / release mechanism 820. The payload 832 in this example is contained in a polymeric capsule 830. The polymer should be strong enough to be able to be launched from a selected launcher, but also elastic to be inflated later after the activation of the actuator, and finally to be torn down at the predetermined coordinates, to release the payload. The trigger for example can be an accelerometer which identifies at which acceleration the initiator with its content reaches the predetermined coordinates. Alternatively, any other sensor or triggerbased mechanism may be used.

[0101] When the projectile reaches the predetermined acceleration (or GPS coordinates, or flight time, etc.), the trigger mechanism 810 activates the actuator 820, for example by sending it an electrical pulse 812. This pulse activates the actuator, e.g., a solenoid which opens a partition between chemicals 842, 844 in a pellet 840 disposed inside the projectile. When the two chemicals mix, they react to each other forming a gas 850 that expands and over inflates the projectile and causes the polymeric skin of the capsule to rupture, tearing open the container containing the payload 832 and allowing the fire suppressing material to be offloaded from the projectile 800, at the exact coordinates. It is made clear that the chemical reaction of two chemicals is merely an example. Another example may be a single chemical being warmed up by the actuator and transforming from a powder or liquid to a gas.

[0102] An additional advantage of this activation could be while using foaming materials. As the payload consists of water with some percentage of foaming materials, when the chemicals in the actuator form the gas, this gas can be used as a foaming agent. A specific example of this reaction could be the mixing of sodium azide (NaN3) with potassium nitrate (KN03) by the actuator to form nitrogen gas (N2) with some other byproducts (such as Na2O and K2O). The nitrogen gas formation results in foaming of the liquid payload of water with protein foam. The result is an effective foam being spread next to the fire ignition point effectively and promptly upon detection, even if the ignition point is in the middle of a forest and not accessible. This logic allows fast and efficient reaction to fire ignition in wildland in this specific example. Furthermore, even without foaming agent, the gas generator may support efficient dispersion of fire-retardant droplets on the ground, increasing the evaporation of water from the mixture for tacit heat cooling in addition to efficient coverage of the fire-retardant dissolved salts on the vegetation below. In embodiments, the payload is a foaming material with or without water, for example a 3% protein foam.

[0103] Another example embodiment of a projectile according to the present invention is depicted in Figure 8B. In the example embodiment of Fig. 8B, the release mechanism is a hotwire 860 that runs over the outside or inner perimeter of the capsule / projectile. A sensor pack / kit 870 inside or outside the capsule is in electrical and / or mechanical and / or wireless communication with the hotwire. Upon receiving the triggering signal (e.g., from a receiver or sensor, such as GPS, timer, accelerometer, etc.) the trigger mechanism sends a pulse (or something similar) which electrifies or other causes the hotwire to heat up, causing the capsule to rupture and the contents to disperse. It is made clear that the embodiments discussed herein are merely examples of methods and mechanisms that can be employed and not intended to be limiting in any way.

[0104] In an example embodiment of the invention, the system includes an automatic loading system which loads water and / or fire-retardant material, and a sensor kit (protected from the water by a waterproof envelope) into an empty capsule, in-situ, using a unique mechanism. This loading system enables the capsules to be launched every few seconds, e.g., 3-10 seconds. Figures 9A-9E depict an example embodiment of a capsule, that is part of an automatic filling and loading subsystem. In this example, the capsule is filled as follows:

[0105] Two sheets of polymeric material (see Fig. 9A) are ultrasonically or thermally welded (or sealed using other methods) around the edges forming a bag containing an inner ring that acts like a sleeve that will enable the closing of the capsule on both its ends. In one example embodiment, 10,000 flat empty bags can be stacked on a tall water pipe (see Fig. 9B) and / or fire-retardant mix, and positioned in proximity (e.g., above) to the launching basket or the tip of the pipe can be disposed inside the launching basket.

[0106] Each empty capsule (looks like a disk - see Fig. 9C) moves down to the lower edge of the pipe and the specially designed sleeve enables water and / or a fire-retardant mixture to fill the capsule through the holes in the sleeve (see Fig. 9D). Upon filling the entire capsule, the sleeve then collapses and the two edges of the sleeve form an inherent duckbill valve which closes upon the filling of the capsule (see Fig. 9E). The lower part closes first and then the upper part after the capsule slips down from the pipe. The capsule is then moved from the filling station to the basket of the launcher if the filling is formed above the basket. Alternatively, the capsule is already inside the basket if the filling is done inside the basket, and then the pipe rises above the basket. In this example the capsule shape starts as a disk and forms into a sphere. In other examples the capsule could be a rectangle that forms into an elliptical ball, or any other initially flat shape which forms into another 3D shape. Furthermore, the filling and loading system can start with a 3D bag of the capsule and fill it and load it automatically as well.

[0107] Detection And Ballistic Calculation System

[0108] The third component of the system is the detection and ballistic calculation system 30 (see Fig. 1). For the ballistic calculation system to be accurate, it is necessary to know where the fire is relative to the launcher or where a peripheral protection barrier needs to be created. To this end, any detection element 32 can be used. A stationary launching platform in a pre-known location can receive sensor data from stationary sensors 32 such as cameras, IR sensors, etc. that are mounted in stationary positions (e.g., on telescopic poles, buildings, street light poles, electricity poles etc.). The sensor data can be processed (e.g., with computer image processor 34) to determine the direction and distance D to the fire. With the known positions of both the launcher platform and the sensor(s), it is relatively easy to calculate where the fire is and provide a ballistic solution for the projectile.

[0109] The launcher 10 itself may be disposed on any type of movable platform 12 that provides freedom of movement in either or both azimuth and elevation. For example, a launching mechanism 14 may be seated on a rotatable platform (e.g., rotatable platform 714 in Fig. 7) with a pneumatic or telescopic actuator (e.g., actuator 712 in Fig. 7) for changing the elevation of the launcher. The launcher can be adjusted by an adjustment system, for example pedestal and / or xyz table to allow a yaw and / or tilt adjustment of 0-360 degrees.

[0110] A ballistic calculator / system 36 calculates a ballistic trajectory T based on the sensor data and / or directional information. In embodiments, the calculator receives raw data that his processed by the calculator. In other embodiments, the calculator receives data that was processed elsewhere (e.g., in a subsystem of the sensor itself or in a third location). In some embodiments, the calculator receives both raw and processed sensor information. The ballistic calculations also take into consideration the wind speed and direction in different altitudes and correct the acceleration and time of flight of the capsule to hit the exact required target after wind interruption adjustments.

[0111] On the other hand, if the sensor or sensors is / are mobile, such as a camera from a helicopter, drone, satellite, balloon, etc., then it will be necessary to ascertain precise location data for the moving sensors. Alternatively, or additionally, the launch platform may be mobile, e.g., mounted on a flatbed truck, necessitating precise positional knowledge of the platform itself vis-a-vis the one or more sensors. The detection and ballistic calculation system can also gather sensor data (or information of the same) that relates to meteorological phenomena to predict speed and direct of the fire spread. Based on all the information at hand, the ballistic calculation system directs the launcher where to fire the projectiles for direct fire suppression, preventative measures, or both.

[0112] Another example for the ballistic calculation is the formation of a peripheral protection barrier, The location of the barrier could be precalculated during the installation of the system or determined after the external alert reception, based on fire simulations taking into consideration the fire location and situation and wind real time measurement.

[0113] In embodiments, a software (SW) system that enables the end-to-end accurate and fast response of the system to implement the protection methodology presented herein. In some embodiments, the SW contains Al that is trained to differentiate between ultra small fires caused by embers to fires resulting from BBQ for example. At a later stage, Al will be used for optimization of the fire-retardant deployment during the protection and suppression stages. The Al will differentiate between types of fires and between different types of fuel (vegetation) levels and will adjust the height of capsule initiation that results in different coverage levels and or concentrations on the ground.

[0114] A See-Shoot system - is a communication and control system between the various subsystems in the launcher system. When the ability to detect embers in the protected space (a virtually designated area that is covered by a launcher or launchers) will be monitored and controlled using commercial cameras. In preferred embodiments, the system will be periodically updated with the most advanced image processing algorithms to identify embers in order to enable an automatic response by launching the capsules.

[0115] The module will calculate the coordinates at which the capsule will disperse its contents, the launcher control system (part of the ballistic calculation system) receives the coordinates as input and adjusts to launch the capsule based on those coordinates. Before that, an algorithm will calculate the acceleration and / or yaw and / or the time-of-flight or height or other parameter in which the capsule will be at that point of intended dispersion. This data (calculated direction and acceleration at desired time / location of dispersion, etc.) will be transmitted to the accelerometer or other relevant sensor, thus giving the capsule mechanism a signal for the exact dispersion at the desired coordinates.

[0116] In one embodiment of the invention the ballistic calculation system receives its input data from a built-in detector, for example a thermal / IR camera. In another embodiment of the invention the ballistic calculation system receives its input data from a human operator. In another embodiment of the invention the ballistic calculation system receives data from a communication system such as a satellite transmission, GPS, local coordinates triangulation antennas. In another embodiment of the invention the ballistic calculation system receives data from another fire detection company application such as “Watch Duty”.

[0117] In embodiments of the invention, the projectile contains a self-powered device capable of generating strong visible light, such as a flare or a LED, which is turned on upon offloading the payload, and falls down with the payload to the same location. The light - especially if the operation takes place at dark - can be seen by a drone camera hovering above the target, which is also visible to the camera due to the open fire, and the calculator or an operator can monitor the displacement between the payload and the target. The operator can then adjust the azimuth and distance of the next launching to bring the payload closer to the target. This makes the system work in a closed control loop, with feedback, and significantly improves the accuracy of bringing the payload to the target.

[0118] In embodiments of the invention, a projectile with a monitoring payload, such as a camera, is identical in shape and weight to the projectile with payload, so that it follows the same trajectory and can provide feedback on the affect of the payload of previous launches on the target.

[0119] In one embodiment of the invention, the ballistic calculation system calculates the number of payloads needed for successful response and the target coordinates for each payload based on the statistics of accuracy and the effect of a single payload.

[0120] In embodiments of the invention, a launcher can launch a single payload or multiple payloads simultaneously, for example between 1 and 1000 payloads / projectiles.

[0121] Figure 10 depicts a logic block flow diagram of the system operation process. The process starts (step 1000) as a detector element, which can be part of the system or an external device, detects a target at step 1002. At step 1004 the detector element communicates with a ballistic calculator the specific location of the target, for example by using satellite communication (any other type of wireless communication, or wired communication is considered to be included within the scope of the invention). At step 1006 the calculator then calculates the specific coordinates, as x, y, z location in space, at which a payload should be offloaded, and its optimal trajectory to get there, to obtain optimal response to the target. At step 1008 the calculator adjusts the launcher using an adjustment system. At step 1010 the launcher launches the projectile containing the payload and trigger mechanism in an optimal trajectory. At step 1012 the projectile and payload reach the predetermined coordinates, and the sensor detects (e.g., based on one or more sensors) the offloading coordinate. At step 1014 the trigger promptly triggers the release mechanism or actuator. At step 1016 the release mechanism offloads the payload, and at step 1018 the fire suppressing material reaches the target. In some embodiments, the means to offload the payload is by impact of the payload with an object, or a target, or a laser. The system is configured to communicate with at least one similar system.

[0122] In embodiments, the launcher is able to propel a capsule to a range of up to 1 mile (1.5 km) radius, resulting in a protected property of up to 2,000 acres. The launcher’s length is within the range of a few meters.

[0123] In embodiments, heating guanidinium nitrate and / or mixing metallic sodium with the content of the capsule by melting its polymeric bag using a hotwire.

[0124] In embodiments, provision of prolonged protection and resistance to extreme heat during the event made possible thanks to the unique loading of the capsules and the preservation of water reservoirs and large concentration of flame -retardant around the client's site. Self-sufficiency of the instant system is due, at least, to water reservoir and fire retardant concentrate tank(s) and / or an off-grid power supply are optional additions to the system

[0125] In embodiments, an optical sensor in the basket will detect the capsule and give a 'green light' to fill the capsule and release it into the launch basket. An algorithm was developed whose purpose is to schedule the basket's location and orientation and the timing of filling the capsule.

[0126] In embodiments, the fire suppression system is configured to communicate with at least one similar fire suppression system or a different type of fire suppression system.

[0127] An example image processing module is based on ANN neural networks for real-time identification of sparks that may pose a fire hazard - in the first step, we will verify proximity to objects that may catch fire such as roofs, trees and dry leaves, etc.

[0128] Implementation of the method and / or system of embodiments of the invention can involve performing or completing selected tasks manually, automatically, or a combination thereof. Moreover, according to actual instrumentation and equipment of embodiments of the method and / or system of the invention, several selected tasks could be implemented by hardware, by software or by firmware or by a combination thereof using an operating system.

[0129] For example, hardware for performing selected tasks according to embodiments of the invention could be implemented as a chip or a circuit. As software, selected tasks according to embodiments of the invention could be implemented as a plurality of software instructions being executed by a computer using any suitable operating system. In an exemplary embodiment of the invention, one or more tasks according to exemplary embodiments of method and / or system as described herein are performed by a data processor, such as a computing platform for executing a plurality of instructions. Optionally, the data processor includes a volatile memory for storing instructions and / or data and / or a non — volatile storage, for example, non-transitory storage media such as a magnetic hard-disk and / or removable media, for storing instructions and / or data. Optionally, a network connection is provided as well. A display and / or a user input device such as a keyboard or mouse are optionally provided as well.

[0130] For example, any combination of one or more non-transitory computer readable (storage) medium(s) may be utilized in accordance with the above-listed embodiments of the present invention. A non-transitory computer readable storage medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. More specific examples (a non — exhaustive list) of the computer readable storage medium would include the following: a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read — only memory (EPROM or Flash memory), a portable compact disc read — only memory (CD — ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the context of this document, a computer readable non — transitory storage medium may be any tangible medium that can contain or store a program for use by or in connection with an instruction execution system, apparatus, or device.

[0131] A computer readable signal medium may include a propagated data signal with computer readable program code embodied therein, for example, in baseband or as part of a carrier wave. Such a propagated signal may take any of a variety of forms, including, but not limited to, electromagnetic, optical, or any suitable combination thereof. A computer readable signal medium may be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device.

[0132] As will be understood with reference to the paragraphs and the referenced drawings, provided above, various embodiments of computer-implemented methods are provided herein, some of which can be performed by various embodiments of apparatuses and systems described herein and some of which can be performed according to instructions stored in non-transitory computer-readable storage media described herein. Still, some embodiments of computer- implemented methods provided herein can be performed by other apparatuses or systems and can be performed according to instructions stored in computer — readable storage media other than that described herein, as will become apparent to those having skill in the art with reference to the embodiments described herein. Any reference to systems and computer — readable storage media with respect to the following computer-implemented methods is provided for explanatory purposes and is not intended to limit any of such systems and any of such non-transitory computer-readable storage media with regard to embodiments of computer-implemented methods described above. Likewise, any reference to the following computer-implemented methods with respect to systems and computer-readable storage media is provided for explanatory purposes and is not intended to limit any of such computer-implemented methods disclosed herein.

[0133] The flowcharts and block diagrams in the Figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present invention. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and / or flowchart illustration, and combinations of blocks in the block diagrams and / or flowchart illustration, can be implemented by special purpose hardware — based systems that perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.

[0134] The descriptions of the various embodiments of the present invention have been presented for purposes of illustration but are not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein was chosen to best explain the principles of the embodiments, the practical application or technical improvement over technologies found in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.

[0135] As used herein, the singular form "a", "an" and "the" include plural references unless the context clearly dictates otherwise.

[0136] The word “exemplary” is used herein to mean “serving as an example, instance or illustration”. Any embodiment described as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments and / or to exclude the incorporation of features from other embodiments.

[0137] It is appreciated that certain features of the invention, which are, for clarity, described in the context of separate embodiments, may also be provided in combination in a single embodiment. Conversely, various features of the invention, which are, for brevity, described in the context of a single embodiment, may also be provided separately or in any suitable sub — combination or as suitable in any other described embodiment of the invention. Certain features described in the context of various embodiments are not to be considered essential features of those embodiments, unless the embodiment is inoperative without those elements.

[0138] The above-described processes including portions thereof can be performed by software, hardware and combinations thereof. These processes and portions thereof can be performed by computers, computer-type devices, workstations, processors, micro-processors, other electronic searching tools and memory and other non-transitory storage-type devices associated therewith. The processes and portions thereof can also be embodied in programmable non — transitory storage media, for example, compact discs (CDs) or other discs including magnetic, optical, etc., readable by a machine or the like, or other computer usable storage media, including magnetic, optical, or semiconductor storage, or other source of electronic signals.

[0139] The processes (methods) and systems, including components thereof, herein have been described with exemplary reference to specific hardware and software. The processes (methods) have been described as exemplary, whereby specific steps and their order can be omitted and / or changed by persons of ordinary skill in the art to reduce these embodiments to practice without undue experimentation. The processes (methods) and systems have been described in a manner sufficient to enable persons of ordinary skill in the art to readily adapt other hardware and software as may be needed to reduce any of the embodiments to practice without undue experimentation and using conventional techniques. While the invention has been described with respect to a limited number of embodiments, it will be appreciated that many variations, modifications and other applications of the invention may be made. Therefore, the claimed invention as recited in the claims that follow is not limited to the embodiments described herein.

Claims

WHAT IS CLAIMED IS1. A fire suppression system, comprising: a projectile including a payload of fire suppressing materials disposed therein; and a launching mechanism for launching the projectile; and a ballistic calculation system for identifying a target and calculating a ballistic trajectory of the projectile, the projectile configured to disperse the fire suppressing materials at a predefined location or relative position related to the target.

2. The fire suppression system of claim 1, wherein the launching mechanism includes a linear actuator for propelling the projectile along the ballistic trajectory.

3. The fire suppression system of claim 2, wherein the linear actuator is a belt-driven linear actuator powered by a rotational motor.

4. The fire suppression system of claim 2, wherein the linear actuator is powered by a slingshot mechanism.

5. The fire suppression system of claim 2, wherein the linear actuator is powered by a propulsion mechanism selected from the group including: a flywheel mechanism, a trebuchet-like mechanism, a pneumatic motor, and a linear hydraulic motor.

6. The fire suppression system of claim 2, wherein the linear actuator is an electromagnetic launcher, the electromagnetic launcher includes an electromagnetically powered rail-carriage assembly.

7. The fire suppression system of claim 6, wherein the electromagnetic launcher includes a static copper coil induction guide with a yoke connecting two magnetic plates that are propelled along the induction guide.

8. The fire suppression system of claim 7, wherein a plurality of copper coils are disposed along a length of the induction guide.

9. The fire suppression system of claim 6, wherein the electromagnetic launcher includes two facing sets of static magnets which propel a fin that is disposed between the sets of magnets, the fin housing therein a copper coil inductor.

10. The fire suppression system of claim 9, wherein the electromagnetic launcher includes a pump and heat exchanger disposed on a carriage couple to the fin, the heat exchanger being connected to the copper coil inductor and the pump beingconfigured to pump cooling liquid through the heat exchanger and back into the copper coil inductor.

11. The fire suppression system of claim 6, wherein the electromagnetic launcher includes two facing sets of static magnets which propel a dynamic member that is disposed between the sets of magnets, the dynamic member housing three copper coil inductors.

12. The fire suppression system of claim 11, wherein the electromagnetic launcher includes a quick connector assembly that is configured to connect to open ends of the hollow tubes of the three copper coil inductors when the dynamic member is in a stationary position and inject cooling fluid into the hollow tubes.

13. The fire suppression system of claim 6, wherein the electromagnetic launcher includes N inductors that are connected by N connections to N busbars via brushes, using electrical commutation.

14. The fire suppression system of claim 6, wherein the electromagnetic launcher includes: a plurality of ferromagnetic cores the copper windings, the plurality of ferromagnetic cores disposed along two sides of a channel running a length of the electromagnetic launcher, a dynamic magnetic member connected to a carriage and a basket, the dynamic magnetic member having disposed therein N magnets where N > 1 ; wherein the dynamic magnetic member is disposed in an air gap between the ferromagnetic cores on each side of the channel.

15. The fire suppression system of claim 14, wherein the channel is defined by a U-shaped piece that functions as magnetic core material for conducting magnetic flux between the plurality of ferromagnetic cores and air gaps disposed along each of the sides of the channel and permanent magnets.

16. The fire suppression system of claim 1, wherein the projectile includes a trigger mechanism that causes the payload to be released.

17. The fire suppression system of claim 16, further includes a sensor kit in communication with the trigger mechanism, wherein the trigger mechanism is actuated based on sensor data from the sensor kit.

18. The fire suppression system of claim 17, wherein the sensor kit includes one or more sensors selected from the group including: a timer, an accelerometer, abarometer, a GPS sensor, a micro-electromechanical system (MEMS), and a radio receiver.

19. The fire suppression system of claim 16, further including a release mechanism in communication with the trigger mechanism.

20. The fire suppression system of claim 19, wherein the release mechanism includes a pellet holding one or more chemicals, wherein activation of the one or more chemicals releases an expansive gas causing overinflation of a polymeric skin of the projectile resulting in a rupture of the skin and dispersal of the payload.

21. The fire suppression system of claim 19, wherein the release mechanism includes a hotwire that runs over an outside or inner perimeter of the projectile, which, upon receipt of a signal from the triggering mechanism, heats up and causes a polymeric skin of the projectile to rupture.

22. The fire suppression system of claim 1, further including an automatic loading system for loading the projectile and placing the projectile onto a basket of the launching mechanism.

23. The fire suppression system of claim 22, wherein empty projectile bags are disposed on a pipe connected to a reservoir of the fire suppressing materials in such a manner that a bottom-most empty bag thereof is positioned so as to be filled with the fire suppressing materials, sealed, and deposited onto the basket.

24. The fire suppression system of claim 23, wherein a sensor kit, trigger mechanism, or both are disposed in or on the projectile prior to launching the projectile.

25. The fire suppression system of claim 1 , wherein the ballistic calculation system includes: at least one detection element for detecting or identifying the target location, a ballistic calculator for calculating the ballistic trajectory, the ballistic calculator further adapted to communicate data from the ballistic calculator to a sensor kit disposed in or on the projectile indicating when a triggering signal is to be transmitted to effect release of the payload.

26. The fire suppression system of claim 25, further including a processor adapted to process raw sensor data received from said at least one detection element.

27. A method of fire suppression or prevention, comprising: detecting a target; communicating a location of the target to a ballistic calculator;calculating, by the ballistic calculator, a trajectory to predetermined coordinates; launching a projectile with a payload of fire-suppression material along the trajectory; sensing, by at least one sensor in or on the projectile, arrival of the projectile at the predetermined coordinates; triggering, based on said sensing, a release mechanism to offload the payload from the projectile so as to optimally deploy the payload to the target.

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