KINETIC UNMANNED AERIAL VEHICLE FLIGHT DISRUPTION AND DISABLING DEVICE, SYSTEM AND ASSOCIATED METHODS

Abstract

The present invention is a device, system(s) and/or method(s) for disrupting, capturing, and/or disabling and unmanned aerial vehicle(s) in flight, on the ground, or preparing for flight that may or may not be under the control of the invention operator. In certain embodiments, the invention is supported and carried by an unmanned aerial vehicle that is controlled by a ground operator, a computer process and associate hardware, or any combination thereof. In other embodiments, the invention contains physical destruction devices such as projectiles, explosives, spikes, electric shock generators, etc. The invention is manipulated to track, intercept, capture, disrupt, disable and/or move a target unmanned aerial vehicle. In certain embodiments, the invention includes materials able to contain, at least in part, hazardous materials and/or conditions caused by the target unmanned aerial vehicle. In certain embodiments, the invention interfaces with external unmanned aerial vehicle detection/tracking systems. A unique design element in certain embodiments is the ability to limit the potential of the captured aerial vehicle escaping the device and/or falling to the ground. Another unique design element in certain embodiments is the ability of the invention to limit collateral damage caused by the captured unmanned aerial vehicle or apparatuses contained thereon. Another unique design element is the ability of the invention to interface with external unmanned aerial vehicle detection/tracking systems.

Claims

1. An unmanned aerial vehicle capture apparatus comprising: an unmanned aerial vehicle disruption area where the disruption area engages at least one unmanned aerial vehicle directly or at a distance; a support aircraft for positioning said disruption area in order to inhibit a target unmanned aerial vehicle's ability to maintain flight; an at least one onboard sensor in order to detect unmanned aerial vehicles in the vicinity of the support aircraft selected from at least one of the group radar, Lidar, sonar, an auditory sensor, a visual sensor, a light sensor, an infrared sensor, a heat sensor, a laser sensor, a radio frequency sensor, a pressure sensor, and a direct contact switch; an onboard computer to receive and process data collected by an onboard sensor suite; a flight control system onboard the support aircraft in order to stabilize the aircraft, gather telemetry data, respond to flight commands received from a command source selected from the group of an onboard computer, remote computer connected through a transmission device, a preprogrammed flight path, and an operator control station; and an onboard camera to monitor the area surrounding the support aircraft.

2. The unmanned aerial vehicle capture apparatus of claim 1 further comprising: an at least one capture sensor selected from at least one of the group of radar, Lidar, sonar, an auditory sensor, a visual sensor, a light sensor, an infrared sensor, a heat sensor, a laser sensor, a radio frequency sensor, a pressure sensor, and a direct contact switch; a capture computer selected from at least one of the group of the onboard computer, the base station computer, a remote computer and an auxiliary computer to receive signals from the capture sensor in order to determine if a successful capture has been detected.

3. The apparatus of claim 1, where the disruption area is selected from at least one of the group of a net, a launched net, a mesh, chain, wire, fabric, plastic, metal, and wood, in order to engage and capture at least one unmanned aerial vehicle and disable its ability to maintain flight however preventing it from falling to the ground.

4. The apparatus of claim 1, where the disruption area is comprised of a device selected from the group of an explosive, a compressed air cannon, a battering ram, a projectile, an electric arc generator, a reinforced area, a chemical sprayer, a mechanical grinder, and a spike in order to impact the target unmanned aircraft and disable its ability to maintain flight with no regard to whether it falls to the ground.

5. The apparatus of claim 1, further comprising a base station computer tracking the support aircraft's status, calculating and sending commands to the support aircraft, updating connected computers if any, receiving commands from an operator if present, and providing status information to an operator if present; a data communication device providing communication between the base station computer device and the onboard computer through wireless engagement; and an operator console providing system status and processing operator input.

6. The apparatus of claim 3, further comprising a lower shelf made from material as used for the disruption area, the shelf providing support to an at least one target unmanned aerial vehicle, and the shelf being located at the bottom of the disruption area to provide fall protection should the captured target improperly or incompletely engage in the disruption area.

7. The apparatus of claim 3, further comprising a side containment area made from material as used for the disruption area and attached to the disruption area on any side, the top, or any combination thereof, in order to contain the target unmanned aerial vehicle and to provide protection to the support aircraft should the target improperly or incompletely engage in the disruption area.

8. The apparatus of claim 1, wherein said disruption area is further comprised of a disabling mechanism selected from at least one of the group of an electric shock generator, a detonation device, a chemical sprayer, a laser, and a faraday cage in order to prevent a captured aerial vehicle from attempting to fly or release itself should the captured vehicle not engage fully in the disruption area.

9. The apparatus of claim 1, further comprising an at least one collateral damage mitigation material for materially reducing hazardous conditions potentially inflicted by the target unmanned aerial vehicle, devices contained thereon or items released from the target, where the at least one collateral damage mitigation material is selected from the group of explosive resistant material, projectile resistant material, chemical resistant material, biological resistant material, fire resistant material, heat resistant material, and entanglement material in order to protect the support aircraft as well as items, objects, property, vehicles and people in the vicinity.

10. The apparatus of claim 9, further comprising: an at least one forward collateral damage mitigation material; an at least one release mechanism selected from at least one of the group of an electric release, a pneumatic release, a hydraulic release, a magnetic release, and a mechanical release, to deploy the forward collateral damage mitigation material; and a triggering system to activate the release mechanism.

11. The apparatus of claim 10 wherein the triggering system is commanded by the operator using the operator console and the transmission device between the console and the support aircraft.

12. The apparatus of claim 2 wherein the triggering system is commanded using the capture computer to release the forward mitigation material.

13. The apparatus of claim 10 wherein the triggering system is commanded using the capture computer to release the forward mitigation material.

14. A system for interfacing an unmanned aerial vehicle detection device and at least one unmanned aerial vehicle disruption device, comprising: an external unmanned aerial vehicle detection and tracking system of design and operation separate from the unmanned aerial vehicle disruption device which is able to calculate a location, at least approximate, of potential target unmanned aerial vehicles; an unmanned aerial vehicle disruption base station computer; a computer data transmission media enabling communications between said external unmanned aerial vehicle detection and tracking device and said unmanned aerial vehicle disruption base station computer; a defined data communications protocol transferring potential target unmanned aerial vehicle location and ancillary information between said detection computer and said unmanned aerial vehicle disruption base station computer; an unmanned aerial vehicle disruption device; an unmanned aerial vehicle disruption interface computer; a wireless data transmitter and receiver pair enabling communications between said disruption base station and said unmanned aerial vehicle disruption aircraft device; an unmanned aerial vehicle disruption aircraft flight control system; an unmanned aerial vehicle disruption aircraft power source; an operator computing device accepting operator input and calculating system information; an operator display device displaying system information; and an operator input device accepting operator input and commands through tactile, visual and/or auditory means.

15. The system of claim 14 wherein the data communications protocol is comprised of defined data fields selected from at least one of the group target location information, disruption device commands, ancillary information and status information, and when included, the disruption device command is selected from at least one of the group of launch, follow, capture, destroy, return to home, land, loiter, and ancillary commands, thereby facilitating the transfer of information from a multitude of potential unmanned aerial vehicle detection systems and the unmanned aerial vehicle disruption device.

16. The system of claim 15, where the unmanned aerial vehicle disruption base station computer receives and transmits data according to said data communications protocol, calculates system state, processes operator input, and calculates system response.

17. The system of claim 16 where the disruption device interface computer calculates command and status conditions selected from at least one of the group aircraft state, processes base station computer data transmissions, aircraft response, onboard sensor input, appropriate aircraft movement according to onboard sensors, desired response to sensor input, system health, and responses to emergency conditions.

18. The system of claim 14 further comprising a safety system which monitors an at least one status condition selected from the group of location, power state, operator input, proximity to structures, proximity to aircraft, proximity to terrain, signal strength, and ancillary conditions, and further comprises use of a programmed condition response table to calculate and command aircraft response to the detected condition.

Description

BRIEF DESCRIPTION OF THE FIGURES

[0025] FIG. 1 is an isometric perspective view according to an embodiment of the present invention.

[0026] FIG. 2 is a front perspective view according to an embodiment of the present invention depicting the invention attached to a support vehicle for illustrative purposes only and not intended to be a limitation of any kind.

[0027] FIG. 3 is a front perspective view according to an embodiment of the present invention depicting the placement of a targeting camera for illustrative purposes only and not intended to be a limitation of any kind.

[0028] FIG. 4 is an isometric perspective view according to an embodiment of the present invention depicting a capture net launching solution for illustrative purposes only and not intended to be a limitation of any kind.

[0029] FIG. 4 is an isometric perspective view according to an embodiment of the present invention depicting a collateral damage limiting liner or capture area for illustrative purposes only and not intended to be a limitation of any kind.

[0030] FIG. 5 is a flow chart depicting an implementation of the external UAV detection and tracking system interface methodology, system and associated equipment according to an embodiment of the present invention for illustrative purposes only and not intended to be a limitation of any kind.

REFERENCE NUMERALS IN THE DRAWINGS

[0031] 1Harness

[0032] 2Upper support

[0033] 3Rear capture area

[0034] 4Side containment area

[0035] 5Lower support

[0036] 6Lower containment area

[0037] 7Lower attach point

[0038] 8Flight path

[0039] 9Upper attach point

[0040] 10Support vehicle

[0041] 11Harness attach point

[0042] 12Extension

[0043] 13Targeting camera

[0044] 14Front containment area

[0045] 15External detection/tracking system.

[0046] 16Tracking packet.

[0047] 17Ready for command?

[0048] 18Error packet.

[0049] 19Automatic mode?

[0050] 20Operator approves command?

[0051] 21Transmit command.

[0052] 22Disruption device execution?

[0053] 23Perform command.

[0054] 24Monitor command result.

[0055] 25Update status.

[0056] 26Status packet.

[0057] 27System status.

[0058] 28Status display.

DETAILED DESCRIPTION OF THE INVENTION

[0059] The invention is directed to a device, system and associated methods to disrupt, capture and/or disable aerial vehicles, more specifically unmanned aerial vehicles, while those vehicles are in flight, on the ground or preparing for flight. The device, system and associated methods according to the present invention are specifically and uniquely designed to intercept a target unmanned aerial vehicle, or target unmanned vehicles in the case of a swarm, while that target vehicle(s) is in flight, on the ground or preparing for flight. In certain embodiments, the invention is intended to ensnare, capture, disrupt and/or disable the target vehicle in such a manner as to limit potential collateral damage caused by the disrupted UAV. In certain embodiments the invention is to be aided by interfacing with external UAV detection and tracking systems. And, in certain embodiments and some instances, to move a captured target vehicle(s) to a predetermined location, calculated location, or a location of the operator's choosing. When referring to the figures, numerals indicate like or corresponding parts throughout the views.

[0060] Referring to FIG. 1, the invention, in some embodiments but not all, is designed to be hung from a support vehicle or structure. The support vehicle may be, but is not limited to, a manned or unmanned vehicle. For purposes of illustration, and not in any way intended to be limiting, the following description will make reference to an unmanned aerial vehicle support vehicle, referring to FIG. 2, support vehicle 10.

[0061] Referring to FIG. 1 and FIG. 2, the harness 1 can attach to support vehicles or structures of varying configurations. The upper portion of the harness 1 can, in some embodiments but not all, be fitted with extensions 12 at the harness attach point 11, such as, but not limited to, chains, wires, bolts, etc., that attach to the support vehicle 10. The harness 1 transfers the weight of the disruption device and any load contained therein from the upper support 2 to the extensions 11 and/or the support vehicle 10 directly. The harness 1 is also designed in such a manner to distribute the load across the upper support 2. By spreading the attach points of harness 1 across the upper support 2, the support vehicle 10 is able to exert more positive control over the yaw axis of the disruption device and better stabilize the disruption device in flight. This is as opposed to an attachment harness or method that utilizes an alternate configuration with the harness attaching at a single central point on the upper support 2 or at centrally located points.

[0062] The harness 1 is made from, but not limited to, rope, chain, wire, pipe, etc. Other embodiments may use other materials as desired. The harness 1 is attached to the upper support using, but not limited to, knots, washers, bolts, pull ties, twist ties, wire, restraints, etc. The attachment is performed such that the load from the upper support 2 is able to be transferred into the harness 1 and ultimately into the support vehicle 10.

[0063] The upper support 2 transfers the load from the capture material, surfaces, support structure and any items contained therein into the harness. The upper support 2 also helps maintain the unique shape and configuration of the invention. It is the central attachment point for the rear capture area 3 and side containment areas 4. In some embodiments, but not intended to be a limitation, the upper support 2 may contain holes to allow the harness 1, the material of the rear capture area 3 and the material of the side containment areas 4 to pass through and be secured to the upper support 2. The material of the rear capture area 3 and the side containment areas 4 may be, but are not limited to, rope, chain, wire, pipe, etc., and are secured to the upper support 2 at upper attach points 9 using, but not limited to, knots, washers, bolts, pull ties, twist ties, wire, restraints, etc. In some embodiments, but not intended to be a limitation, the upper support 2 may be made of plastic pipe, wood, metal rod, fiberglass, carbon fiber, etc. It is made using a strong yet light material in order to properly transfer the load, resist breaking and fatigue and help keep the overall weight of the device to a minimum. In some embodiments, but not intended to be a limitation, the rear capture area 3 and side containment areas 4 may be directly attached to the support vehicle 10 so as to eliminate the upper support 2. In some embodiments, these attach points are distributed across the support vehicle 10, such as across the vehicle's arms or structure, to provide enhanced yaw control over the disruption device similar to that achieved with upper support 2 and harness 1.

[0064] The upper support 2 attaches to, among others, the rear capture area 3 and the side containment areas 4. The rear capture area 3, side containment areas 4 and lower containment area 6 are made in some embodiments, but not intended to be a limitation, out of rope, wire, chain, straps, etc. The areas are comprised of vertical and horizontal components that are arranged in a fashion that, for illustration but not intended as a limitation, resembles a net. The horizontal and vertical components of the rear capture area 3, the side containment areas 4 and the lower containment area 6 are secured to each other in some embodiments, but not intended as a limitation, using knots, wire ties, wound wire, pull ties, fasteners, twist ties, sewn areas, glue, string, etc.

[0065] As described, the rear capture area 3 has horizontal and vertical components fashioned, for illustrative purposes but not intended as a limitation, like a net. The distance between the horizontal components and the distance between the vertical components varies among embodiments and is designed using differing measurements in order to promote the entanglement of target UAVs of varying sizes and configurations. As an example, but not intended as a limitation, a horizontal and vertical distance of 9-inches may be used in some embodiments because this size may promote the entanglement of light to medium sized target UAVs without allowing the target UAV to pass though the capture area. Other embodiments may use larger or smaller distances between horizontal components and vertical components in order to promote the entanglement of larger or smaller target UAVs.

[0066] In some embodiments, rear capture area 3, side containment areas 4 and lower containment area 6 are lined with or made from materials intended to contain hazardous conditions, for example but not intending to be a limitation, blast resistant, projectile resistant, fire resistant and/or chemical resistant fabric or materials as illustrated in FIG. 4. In some embodiments, a front containment area 14 made from such material is fitted to enclose the front of the device depicted by flight path 8 when deployed. The front containment area 14 is in a retracted condition prior to capture to allow the target UAV to enter the device through flight path 8 and then the front containment area 14 is remotely or automatically deployed to fully enclose the captured UAV in the disruption device. This will assist in containing hazardous conditions caused by the UAV, for illustrative purposes but not intending to be a limitation, an explosive, projectile, and/or chemical or biological agent, thereby further reducing the possibility of collateral damage. In some embodiments, but not intending to be a limitation, the front containment area 14 is rolled above the area depicted by flight path 8. An electronic or mechanical latch releases the front containment area 14 which unrolls down a set of guides affixed to the disruption device. In other embodiments, but not intending to be a limitation, the front containment area 14 is deployed using a cable or other mechanism that extends and retracts the material in an accordion fashion across the area depicted by flight path 8.

[0067] Another unique aspect of the invention includes the side containment areas 4 and lower containment area 6. As previously described, it is advantageous to capture a target UAV without allowing it to escape the disruption device or drop to the ground. Having only the rear containment area 3 may allow a disabled or disrupted target UAV to escape the invention. It may also allow a disabled or disrupted target UAV to fall to the ground if the UAV is not fully entangled in the rear capture area 3. The side containment areas 4 provide additional capture or containment material thereby increasing the likelihood of positively capturing and containing a target UAV. The lower containment area 6 provides additional capture or containment material thereby reducing the likelihood that a captured UAV would fall to the ground once disabled or disrupted. This helps protect persons and property in the vicinity of and below the invention and improves the ability of the invention to move the captured target UAV to a location of the operator's choice. It also limits the potential damage that a target UAV containing or carrying illicit or dangerous devices or substances could inflict.

[0068] Like the rear capture area 3, in some embodiments, the side containment areas 4 and lower containment area 6 are made from horizontal and vertical components fashioned, for illustrative purposes but not intended as a limitation, like a net. The distance between the horizontal components and the distance between the vertical components varies among embodiments and is designed using differing measurements in order to promote the containment of target UAVs of varying sizes and configurations. These measurements may vary from the measurements of other components of the invention, including the rear capture area 3, and from each other. In other embodiments, the side containment areas 4 and lover containment area 6 are lined with or made from materials intended to contain hazardous conditions, for example but not intending to be a limitation, blast resistant, projectile resistant, fire resistant and/or chemical resistant fabric or materials as illustrated in FIG. 4.

[0069] For illustrative purposes, but not intended to be a limitation, the lower containment area 6 may use smaller distances between the horizontal and vertical components as that used for the rear capture area 3. This is because the rear capture area 3 would be the most likely area to encounter a flying target UAV and is intended to entangle it. The lower containment area 6 would be most likely area to encounter a disabled, or partially disabled, target UAV that is no longer flying normally and is falling toward the ground. Smaller distances between the horizontal and vertical components of the lower containment area 6 would be more likely to support the falling device and not allow it to pass through the open areas. In this embodiment, the lower containment area 6 is more likely to support it and prevent it from falling to the ground. Likewise, the side containment areas 4 may also use differing measurements for the horizontal and vertical components commiserate with its intended purpose, in this embodiment, of acting as additional containment areas for the target UAV but not as the primary and most likely initial capture area.

[0070] The rear capture area 3, side containment areas 4 and lower containment area 6 components in some embodiments but not intended as a limitation, pass though or are fastened to the lower support 5. The lower support 5 helps maintain the unique shape and size of the invention. In some embodiments, holes are drilled in the lower support 5 to allow the components of the rear capture area 3, side containment areas 4 and lower containment area 6 to pass through the lower support 5 and to attach to each other. In other embodiments, attachment hardware is attached to lower support 5 to join rear capture area 3, side containment areas 4 and lower containment area 6. In some embodiments, but not intended to be a limitation, the lower support 5 may be made of plastic pipe, wood, metal, fiberglass, carbon fiber, etc. It is made using a strong yet light material in order to properly transfer the load, resist breaking and fatigue and help keep the overall weight of the device to a minimum.

[0071] The front of the invention is open to allow a target UAV to enter the device as illustrated by flight path 8. For illustrative purposes, but not intended as a limitation, the invention may be positioned in front of a moving target UAV, may be moved to a stationary (i.e. hovering) target UAV or may intercept a target UAV in which case both the invention and the target UAV are in motion. The lower containment area 6 is attached to the lower support 5 at lower attach points 7 in order to allow the front of the invention to be open. The lower containment area 6 components are attached at the lower attach points 7 in some embodiments, but not intended as a limitation, using knots, washers, bolts, pull ties, twist ties, wire, restraints, etc. In some embodiments, a front containment area 14 may be deployed to enclose the front of the device as illustrated by flight path 8 once the target UAV(s) is captured.

[0072] Loads from a captured or disabled target UAV(s), and from the various parts of the invention are transferred between the components through the lower support 5. The weight and configuration of the lower support 5 also helps promote the proper orientation of the invention while it is use. It helps stabilize the invention while in motion and in flight, keeps the device below the support vehicle 10 and maintains the size and shape of the invention, especially when it is supporting a captured or disabled target UAV.

[0073] In some embodiments, but not intended as a limitation, disruption and or disabling devices are directly attached to support vehicle 10. This may be in conjunction with or in lieu of the capture areas. Such devices may include, but are not limited to, projectiles, explosives, battering rams, reinforced areas, chemical sprayers, spikes, electric shock generators, etc. In other instances, support vehicle 10 is used to directly impact with the target UAV in order to disabled it. The disruption devices may be controlled by an onboard computer, targeting computer, remote computers and/or the operator. These methods of disruption can be used with collateral damage is unimportant, such as but not limited to, when used in a remote location, when used to protect a high value target, when capture fails or when used as a last line of defense.

[0074] Referring to FIG. 3, another unique aspect of the invention, in some embodiments but not intended to be a limitation, is that it is equipped with a targeting camera(s) and/or sensor(s) 13. A targeting camera(s) and/or sensor(s) provides a significant and unique advantage of providing the operator of the device, targeting program and associated equipment and/or automatic flight control system with a more natural and useful view of the area surrounding the invention, including but not limited to, a target aircraft. The targeting camera and/or sensor is located in the rear capture area 3. This eliminates parallax from the image when capturing a target UAV as opposed to utilizing a camera and/or sensor mounted elsewhere on the invention or on the support vehicle 10. This simplifies target and capture calculations and adjustments required when the targeting camera and/or sensor is remotely located thereby increasing accuracy.

[0075] In some embodiments but not intended to be a limitation, the targeting camera 13 sends a live wireless video feed to a receiver(s). For illustrative purposes, but not intended to be a limitation, the following case is considered. A video feed receiver is located with the operator and is connected to a display device(s) which could be, but is not limited to, a computer, a video monitor, a tablet computer, a smart phone, a head mounted display, etc., and may be augmented with virtual cross-hairs, a target, etc. The operator uses the live video image to assist the capture process while controlling the invention. By keeping the target aircraft centered in the image or located on/within the cross-hairs during the approach and capture, the operator can be assured that the target aircraft will be captured centrally and optimally in the rear capture area 3. This is opposed to, and provides a significant advantage over the case where, a live video feed is provided by a camera that is not centrally located within the rear capture area 3. In this case, the operator must mentally adjust for parallax during the approach and capture phase. This suboptimal process may be difficult and can result in misses, partial captures, offset captures, and/or striking the target aircraft with the support vehicle 10. Therefore, the centrally located targeting camera 13 is advantageous.

[0076] In some embodiments, but not intended to be a limitation, the targeting camera and/or sensor 13 can provide data and imagery to an automated, or semi-automated interception, tracking and/or capture process. A computer program and associated hardware can utilize the data from the targeting camera and/or sensor 13 to control the support vehicle's 10 movements in order to automate or semi-automate the interception, tracking and/or capture process or assist the operator with a semi-autonomous or augmented interception, tracking and/or capture process.

[0077] In some embodiments, but not intended to be a limitation, the targeting camera 13 can be co-located or include distance measuring sensors, such as but not limited to, binocular vision, sonar, laser ranging, radar, etc. In some embodiments, this information is provided to the operator on a display to assist with distance to target or augmented data. In other embodiments, this information is provided to a computer process and associated hardware to assist with an autonomous, semi-autonomous or augmented interception, tracking and/or capture process.

[0078] Referring to FIG. 5, another unique aspect of the invention, in some embodiments but not intended to be a limitation, is the ability to interface with external UAV detection and tracking systems. This ability provides the significant and unique advantage of, among other advantages, permitting the disruption device to accurately and effectively operate at a significant distance from the operator and/or base station and/or launch point thereby permitting beyond-visual-line-of-sight operations (BVLOS). This ability also provides the significant and unique advantage of, among other advantages, having the ability to utilize existing, planned or future UAV detection and tracking systems, whether those systems are known, unknown or yet to be invented. This ability also provides the significant and unique advantage of, among other advantages, pairing the disruption device with a detection and tracking system that is appropriate to the terrain and environment native to the disruption device's intended operating area.

[0079] For illustrative purposes, but not intended to be a limitation, the disruption device may be paired with a radar detection and tracking system for an urban environment and an auditory detection and tracking system for a forested environment. Furthermore, the detection and tracking system can be designed and/or built by a third-party and still be interoperable with the disruption device by utilizing the external detection and tracking interface unique to the invention's design. This provides the unique advantage of modularity to the invention's design allowing it to be interoperable with a wide range of systems.

[0080] As illustrated in FIG. 5, but not intending to be a limitation, the external detection/tracking system 15 detects a potential target UAV using methods and systems of its own design. It then communicates a collection of data to the invention using a tracking packet 16. The tracking packet may be communicated to the invention using hardware such as, but not limited to, a wired connection, serial connection, Ethernet network, Wi-Fi, fiber optics, etc., and may contain information such as, but not limited to, the target's location, threat's altitude, accuracy, time of detection, threat probability, errors, detection method, etc. The tracking packet 16 may also contain a command to instruct the invention to perform a specific, defined function such as, but not limited, launch, return to home, hover, pursue, capture, move to safe area, delay capture, loiter, destroy, land, emergency land, etc.

[0081] A program and associated hardware that is part of the invention, such as, but not intending to be a limitation, a computing device with attached storage and communication equipment, receives the tracking packet and determines if the system is ready to accept the command 17. The program and computing device refers to the system status 27 stored in memory or on an external storage device. The system status 27 is updated according to the status of the various components that makeup the inventions, including the disruption device status 26. For illustrative purposes, but not intending to be a limitation, the system status may contain information regarding the aircraft state, GPS and location data, battery status, hardware status, operator condition, signal strength, sensor status, flight time remaining, etc.

[0082] If the invention is not ready or cannot accept the command and/or tracking packet from the external detection/tracking system 15, the invention send an error packet 18 to the external detection and tracking system 15 indicating the type of error and potentially an estimated time to a ready state. The error packet 18 may contain information such as, but not limited to, battery error, GPS error, computing error, aircraft error, transmission error, malformed tracking packet, operator override, no error, unknown error, etc.

[0083] If the invention can accept the command and/or tracking packet from the external detection and tracking system 15 it then determines if the system is in automatic mode 19. This mode is set by the operator and stored by the invention in internal or external memory and tracked by a program and associated computing hardware. If the system is not in automatic mode 19, the operator is advised of the command and asked to approve it 20. For illustrative purposes, but not intended to be a limitation, the operator may perform this operation using a computer terminal, tablet computing device, smart phone computing device, laptop, desktop, etc. If the operator does not approve the command 20, an error packet 18 is sent to the external detection/tracking system 19 and the system resets the command loop.

[0084] If the operator does approve the command 20, or if the system is in automatic mode 19, the command is transmitted to the disruption device and associated hardware 21. For illustrative purposes, but not intended to be a limitation, the command may be transmitted using wireless data transmission hardware, wi-fi, wired transmission hardware, fiber optics, etc., and their associated programs.

[0085] The disruption device, along with associated hardware and programs, receives the command and determines if it is able to execute the command 22 in part by consulting the current device status 26. The device status 26 is stored in memory or on an external storage device. The device status 26 is updated according to the status of the various components that makeup the disruption device. For illustrative purposes, but not intending to be a limitation, the device status 26 may contain information regarding the aircraft state, GPS and location data, battery status, hardware status, operator condition, signal strength, sensor status, flight time remaining, etc. The device status 26 is communicated to the system status program 27 which may be run on another computing device, perhaps as part of a base station. The communication may be transmitted using wireless data transmission hardware, wi-fi, wired transmission hardware, fiber optics, etc.

[0086] Additionally, the current system status, which may include but is not limited to, sensor output, battery status, ready state, current command, mode, etc., is displayed to the operator 28. For illustrative purposes, but not intended to be a limitation, the status may be communicated to the operator 28 using a computer terminal, tablet computing device, smart phone computing device, laptop, desktop, etc.

[0087] If the disruption device is able to execute the command 22 it then executes the appropriate operation 23 for the command. For illustrative purposes, but not intended to be a limitation, this may be begin launch sequence, perform launch, move up, move down, turn right, turn left, increase speed, decrease speed, stop, hover, land, etc. The commands are performed using a combination of programs and onboard computing devices, potentially including but not limited to, a UAV autopilot system.

[0088] The disruption device then monitors the command result 24 to ensure it was properly executed. The command result 24 is used to update the disruption device's status 25. The disruption device status 25 is also updated if the disruption device was unable to execute the command 22. The updated status 25 is stored and distributed as a status packet 26. At this point the command loop and program structure repeats according to the design of the invention's systems, devices and associated methods. The system and associated methods also have provisions for the immediate takeover of the disruption device by an operator or automatic pilot if an error condition is sensed by any of the sensors, computing devices, hardware, software, systems, etc. or if the operator chooses to assume control of the device.

[0089] Referring to FIG. 5, but not intending to be a limitation, the hardware and programs are split into onboard and ground based. Onboard programs and equipment are contained on the disruption device and its associated support vehicle 10. The ground programs and equipment are contained on a base station. For illustrative purposes, but not intending to be a limitation, the base station may utilize a desktop computing device, laptop, tablet computing device, smart phone computing device, etc., and associated communication and transmission hardware and software.

[0090] While the present invention has been described above in terms of specific embodiments, it is hereby stated and understood that the invention is not limited to these disclosed embodiments. Many modifications and other embodiments of the invention may and will come to mind of those skilled in the art to which this invention pertains, and which are intended to be and are covered by both this disclosure and any appended claims. It is intended that the scope of the invention should be determined by proper interpretations and constructions of any appended claims and their legal equivalents, as understood by those of skill in the art relying upon the disclosure in this specification and the attached drawings.