Actuation method, components, and systems for initiation or fuzing a device

Abstract

An actuation method, components, and systems for initiation or fuzing a device includes a PCB with a plurality of switches and a microcontroller. At least one of the plurality of switches is an electronic switch controlled by the microcontroller. At least one power supply is connected to and powering the PCB. External sensor inputs are connected to the microcontroller of the PCB. An output terminal of the PCB is configured to connect the device to the printed circuit board. Wherein, the PCB is configured to control the connection of the power supply to the device connected to the output terminal for initiating or fuzing the device based on signals from the external sensor inputs. Wherein, when the plurality of switches are closed, including the electronic switch being closed by the microcontroller based on the signals from the external sensor inputs, the PCB connects the power supply with the device.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application claims benefit to U.S. Provisional Patent Application No. 63 / 745,054 filed on January 14, 2025, entitled ACTUATION METHOD, COMPONENTS, AND SYSTEMS FOR INITIATION OR FUZING A DEVICE, which is incorporated by reference in its entirety.FIELD OF THE DISCLOSURE

[0002] The present disclosure relates to unmanned aerial systems or drones and to an actuation method, components, and systems for initiating or fuzing a device on such unmanned aerial systems or drones.BACKGROUND

[0003] In general, an unmanned aerial vehicle (UAV), also known as a drone, is defined as a powered, aerial vehicle that does not carry a human operator, uses aerodynamic forces to provide vehicle lift, can fly autonomously or be piloted remotely, can be expendable or recoverable, and can carry a lethal or nonlethal payload. UAV is a term that is commonly applied to military use cases. UAVs can also be seen as a component of an unmanned aircraft system (UAS), which also includes a ground-based controller, and a system of communications with the aircraft. It includes elements such as ground control stations, data links and other support equipment and software. In common usage, "drone" is often applied to both military and civilian UAVs, while technical and regulatory documents may prefer terms such as UAV, UAS, RPAS (Remotely Piloted Aircraft System), or uncrewed aircraft. In addition to the software, autonomous drones also employ a host of advanced technologies that allow them to carry out their missions without human intervention, such as cloud computing, computer vision, artificial intelligence, machine learning, deep learning, and thermal sensors.

[0004] The instant disclosure recognizes the safety issues and expense associated with circuits and electrical circuits used on such UAVs or drones for initiating or fuzing devices or munitions. This may include the safety and expense of supplying power to auxiliary electronic mechanisms, including but not limited to, a munition, a signal flare, GPS beacons, laser beacons, LED lights, or other signals between manned or unmanned objects for purposes of indicating a status, indicating a directional navigation mark or marker, or for triggering or initiating a fuze or other electronic circuit on a munition or other device. The main disadvantage of available expensive solutions include high price, complex building that requires skilled people to work so you need training, expensive materials that may need special orders, no unification with many different expensive solutions for same purpose, and / or complex, hard and long manufacturing.

[0005] The instant disclosure may be designed to address at least certain aspects of the problems or needs discussed above by providing the disclosed actuation method, components, and systems for initiating or fuzing a device.SUMMARY

[0006] The present disclosure may solve the aforementioned limitations of the currently available means and mechanisms for initiating or fuzing a device, like in a unmanned aerial system (UAS) or other unmanned systems, by providing the disclosed actuation method, components and systems for initiating or fuzing a device. The disclosed actuation method, components and systems for initiating or fuzing a device may generally include a printed circuit board or PCB with a plurality of switches and a microcontroller. At least one of the plurality of switches may be an electronic switch controlled by the microcontroller. At least one power supply may be connected to and powering the printed circuit board. External sensor inputs may be connected to the microcontroller of the printed circuit board. An output terminal of the printed circuit board may be configured to connect the device to the printed circuit board. Wherein, the printed circuit board may be configured to control the connection of the power supply to the device connected to the output terminal for initiating or fuzing the device based on signals from the external sensor inputs. Wherein, when the plurality of switches are closed, including the electronic switch being closed by the microcontroller based on the signals from the external sensor inputs, the printed circuit board may connect the at least one power supply with the device for initiating or fuzing the device.

[0007] The disclosed actuation method, components and systems for initiating or fuzing a device may be configured for initiation or fuzing a device carried by or attached to a vehicle. The vehicle may be any vehicle. In select embodiments, the vehicle may be an unmanned aerial vehicle (UAV) or a drone. Wherein, in use with a UAV, the actuation system may be included with an unmanned aerial system (UAS) of the UAV.

[0008] In select embodiments of the disclosed actuation method, components and systems for initiating or fuzing a device, the device may be a munition carried by the UAV. Wherein, the actuation system may be configured to initiate or fuze the munition. In these embodiments, the actuation system may be configured as a proximity fuze for the munition. Wherein, the external sensor inputs may include proximity sensors. In select embodiments, the proximity sensors of the external sensor inputs may include ultrasonic proximity sensors.

[0009] In select embodiments of the disclosed actuation method, components and systems for initiating or fuzing a device, the plurality of switches may include at least one mechanical switch. In select embodiments, the plurality of switches may include two mechanical switches. In select possibly preferred embodiments, the two mechanical switches may include a first mechanical pin switch and a second mechanical pin switch. The first mechanical pin switch may include a first removable pin that can be configured to be pulled out prior to the UAV taking off. The second mechanical pin switch may include a second removable pin that can be configured to be pulled out when the munition is dropped from the UAV.

[0010] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be the inclusion of a housing device. The housing device may be configured to house components of the actuation system. The components housed in the housing device may include the printed circuit board, the at least one power supply, the external sensor inputs, and / or the output terminal. In select embodiments, the housing device may be a rapid-prototyped housing.

[0011] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to provide safe control of electrical currents on-board an un-manned aerial vehicle. Wherein the disclosed actuation system, components and method may be designed to regulate the power supplied to auxiliary electronic mechanisms comprised of the printed circuit board with proprietary control software of sensing and initiation, a battery or batteries for the power supply, an array of redundant electric switches included with the plurality of switches including, but not limited to, a combination of two mechanical switches or one mechanical and one electronic or remotely controlled switch, developed for purposes of ensuring safe actuation, paired with a proximity sensor to begin electric current flow to the auxiliary mechanism when certain criteria is met.

[0012] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to allow an economical and safe use of sensors for adaptation to attritable sensors and devices. Wherein the devices include unmanned aerial systems (UAS) or other unmanned systems including ground vehicles, maritime surface and underwater vessels, and fixed-wing and rotary wing aircraft.

[0013] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to enable the development of methods of communication and munitions deployment, tactics, techniques, and procedures (TTPs) for employment in training and combat scenarios.

[0014] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to be used for a munition, a signal flare, GPS beacons, laser beacons, LED lights, or other signals between manned or unmanned objects for purposes of indicating a status, indicating a directional navigation mark or marker, or for triggering or initiating a fuze or other electronic circuit on a munition or other device.

[0015] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to establish and function as a communication node or relay, configured to indicate when one system has reached a location and has come within pre-programmed parameters of a destination, wherein an indicator of a proximity sensor and an LED indicates that the UAS has reached the destination and is in position.

[0016] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to enable inexpensive triggering or initiation of electrical circuits for the purposes of communication, munitions deployment, navigation, or other purposes.

[0017] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to incorporate multiple redundant sensors in order to prevent false-triggering or inadvertent actuation while being handled, during transport in a container or in a bulk shipment, or during other administrative operations when actuation is not expected nor required, thereby being a safety feature as well as a feature to preserve battery life and durability of the actuation system.

[0018] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to offer a low-cost alternative to more traditional fuzing mechanisms which rely on complex mechanical systems including air turbines, accelerometers, gear trains, and counters and chronometers to gauge the number of rotations in order to initiate a circuit or to estimate airspeed and to calculate proximity to the ground. Whereby, by enabling the low-cost alternative and reliable methods to perform these tasks, the actuation system is configured to enable a widespread application of inexpensive systems for reconnaissance and tactical operations in a training and combat environment.

[0019] Another feature of the disclosed actuation method, components and systems for initiating or fuzing a device may be that it can be designed and / or configured to provide an electrical disconnect from critical electrical circuitry unless and until certain other conditions are met, which ensures the safety of the device and prevents the device from operating unintentionally.

[0020] In another aspect, the instant disclosure embraces a proximity fuze for a munition for an unmanned aerial vehicle (UAV). The proximity fuze is a component of the disclosed actuation system and may include any of the various embodiments and / or combinations of embodiments shown and / or described herein. In general, the disclosed proximity fuze may include the printed circuit board or PCB including the plurality of switches and the microcontroller. Wherein at least one of the plurality of switches may be an electronic switch controlled by the microcontroller. At least one power supply may be connected to and powering the printed circuit board. The external sensor inputs may be connected to the microcontroller of the printed circuit board. The external sensor inputs may include proximity sensors. An output terminal of the printed circuit board may be configured to connect the munition to the printed circuit board. Wherein, the printed circuit board may be configured to control the connection of the power supply to the munition connected to the output terminal for initiating or fuzing the munition based on signals from the external sensor inputs. Wherein, when the plurality of switches are closed including the electronic switch being closed by the microcontroller based on the signals from the external sensor inputs, the printed circuit board may connect the at least one power supply with the munition for initiating or fuzing the device.

[0021] In select embodiments of the disclosed proximity fuze, the proximity sensors of the external sensor inputs may include ultrasonic proximity sensors.

[0022] In select embodiments of the disclosed proximity fuze, the plurality of switches may include at least one mechanical switch. In select possibly preferred embodiments of the disclosed proximity fuze, the plurality of switches may include two mechanical switches. The two mechanical switches may include a first mechanical pin switch and a second mechanical pin switch. The first mechanical pin switch may include a first removable pin that can be configured to be pulled out prior to the UAV taking off. The second mechanical pin switch may include a second removable pin that can be configured to be pulled out when the munition is dropped from the UAV.

[0023] In select embodiments, the disclosed proximity fuze may further include a housing device. The housing device may house components of the proximity fuze. Wherein, the components housed in the housing device may include the printed circuit board, the at least one power supply, the external sensor inputs, and / or the output terminal. In select embodiments, the housing device may be a rapid-prototyped housing.

[0024] One feature of the disclosed proximity fuze may be that it can be configured to provide safe control of electrical currents on-board the UAV. Wherein, the proximity fuze may be designed to regulate the power supplied to the munition comprised of the printed circuit board with proprietary control software of sensing and initiation, a battery or batteries for the power supply, an array of redundant electric switches included with the plurality of switches including a combination of two mechanical switches or one mechanical and one electronic or remotely controlled switch, developed for purposes of ensuring safe actuation, paired with a proximity sensor to begin electric current flow to the munition when certain criteria is met.

[0025] Another feature of the disclosed proximity fuze may be that it can be configured to allow an economical and safe use of sensors for adaptation to attritable sensors and devices, wherein the devices include unmanned aerial systems (UAS).

[0026] Another feature of the disclosed proximity fuze may be that it can be configured to enable the development of methods of communication and munitions deployment, tactics, techniques, and procedures (TTPs) for employment in training and combat scenarios.

[0027] Another feature of the disclosed proximity fuze may be that it can be configured to establish and function as a communication node or relay, configured to indicate when one system has reached a location and has come within pre-programmed parameters of a destination, wherein an indicator of a proximity sensor and an LED indicates that the UAS has reached the destination and is in position.

[0028] Another feature of the disclosed proximity fuze may be that it can be configured to enable inexpensive triggering or initiation of electrical circuits for the purposes of communication, munitions deployment, navigation, or for other purposes.

[0029] Another feature of the disclosed proximity fuze may be that it can be configured to incorporate multiple redundant sensors in order to prevent false-triggering or inadvertent actuation while being handled, during transport in a container or in a bulk shipment, or during other administrative operations when actuation is not expected nor required, thereby being a safety feature as well as a feature to preserve battery life and durability of the proximity fuze.

[0030] Another feature of the disclosed proximity fuze may be that it can be configured to offer a low-cost alternative to more traditional fuzing mechanisms which rely on complex mechanical systems including air turbines, accelerometers, gear trains, and counters and chronometers to gauge the number of rotations in order to initiate a circuit or to estimate airspeed and to calculate proximity to the ground.

[0031] Another feature of the disclosed proximity fuze may be that it can be configured to provide an electrical disconnect from critical electrical circuitry unless and until certain other conditions are met, which ensures the safety of the munition and prevents the munition from operating unintentionally.

[0032] In another aspect, the instant disclosure embraces a method of initiating or fuzing a device. The disclosed method of initiating of fuzing a device may include utilizing the disclosed actuation system and / or components in any of the embodiments and / or combination of embodiments shown and / or described herein. As such, the disclosed method of initiating or fuzing a device may generally include providing the disclosed proximity fuze in any of the embodiments and / or combination of embodiments shown and / or described herein. The provided proximity fuze may generally include a circuit including the plurality of switches and the microcontroller. Wherein the plurality of switches may include: a first mechanical switch; a second mechanical switch; and a third electronic switch controlled by the microcontroller. An output terminal of the printed circuit board may be configured to connect the device to the printed circuit board. With the provided proximity fuze, the disclosed method of initiating or fuzing a device may further include: determining if the first mechanical switch is closed. If the first mechanical switch is closed, the method includes determining if the second mechanical switch is closed. If the first mechanical switch and the second mechanical switch are both closed, the method includes determining if the third electronic switch should close by, after a 2 second delay; continuously measuring a distance to a target. Wherein, if the measured distance to the target is less than or equal to a target distance, the method including closing the third electronic switch whereby the device is initiated or fuzed.

[0033] The foregoing illustrative summary, as well as other exemplary objectives and / or advantages of the disclosure, and the manner in which the same are accomplished, are further explained within the following detailed description and its accompanying drawings.BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The present disclosure will be better understood by reading the Detailed Description with reference to the accompanying drawings, which are not necessarily drawn to scale, and in which like reference numerals denote similar structure and refer to like elements throughout, and in which:

[0035] FIG. 1 is a printed circuit board schematic for one embodiment for a proximity fuzed munition the components or system for initiating or detonating a device according to select embodiments of the instant disclosure using ultrasonic sensors for proximity to trigger an electric circuit;

[0036] FIG. 2 is a perspective view of a 3-D printed housing of a munition with the components or system for initiating or detonating a device according to select embodiments of the instant disclosure utilizing the ultrasonic sensor and housing an aerodynamically stable faired

[0037] structure with tailfins to ensure that the object falls nose-down ensuring proper alignment and operation of the sensor(s);

[0038] FIG. 3 is a perspective view of a UAV or drone device carrying a munition with a proximity fuze included as the components or system for initiating or detonating a device according to select embodiments of the instant disclosure that could be used for a proximity or kamikaze style munition;

[0039] FIG. 4 is an end view of the UAV or drone device from FIG. 3;

[0040] FIG. 5 is a perspective view of a non-electric variant of the components or system for initiating or detonating a device according to select embodiments of the instant disclosure; and

[0041] FIG. 6 is a flow chart of a method of initiating or detonating a device according to select embodiments of the instant disclosure.

[0042] It is to be noted that the drawings presented are intended solely for the purpose of illustration and that they are, therefore, neither desired nor intended to limit the disclosure to any or all of the exact details of construction shown, except insofar as they may be deemed essential to the claimed disclosure.DETAILED DESCRIPTION

[0043] Referring now to FIGS. 1-6, in describing the exemplary embodiments of the present disclosure, specific terminology is employed for the sake of clarity. The present disclosure, however, is not intended to be limited to the specific terminology so selected, and it is to be understood that each specific element includes all technical equivalents that operate in a similar manner to accomplish similar functions. Embodiments of the claims may, however, be embodied in many different forms and should not be construed to be limited to the embodiments set forth herein. The examples set forth herein are non-limiting examples and are merely examples among other possible examples.

[0044] Referring to FIGS. 1-6, the present disclosure may solve the aforementioned limitations of the currently available means and mechanisms for initiating or fuzing a device, like in a unmanned aerial system (UAS) or other unmanned systems, by providing the disclosed actuation system 10 (see FIGS. 1-5) and actuation method 100 (see FIG. 6). Actuation system 10 and actuation method 100 may be for initiating or fuzing device 12. Device 12 may be any device or the like requiring initiation or fuzing, including, but not limited to, munition 34, as shown in FIGS. 2-4. Actuation system 10 and actuation method 100 may generally include printed circuit board 14 or PCB 14 including, but not limited to, the embodiment of PCB 14 shown in FIG. 1. PCB 14 may have a plurality of switches 16 and microcontroller 18. At least one of the plurality of switches 16 may be electronic switch 20 controlled by microcontroller 18. At least one power supply 22 may be connected to and powering printed circuit board 14. External sensor inputs 24 may be connected to microcontroller 18 of printed circuit board 14. Output terminal 26 of printed circuit board 14 may be configured to connect device 12 to printed circuit board 14. Wherein, printed circuit board 14 may be configured to control the connection of power supply 22 to device 12 connected to output terminal 26 for initiating or fuzing device 12 based on signals from external sensor inputs 24. External sensor inputs 24 may be any desired electrical inputs with any desired sensors or controls, including, but not limited to, location, proximity, temperature, speed, altitude, acceleration, direction, wind, the like, etc. Wherein, when the plurality of switches 16 are closed, including electronic switch 20 being closed by microcontroller 18 based on the signals from external sensor inputs 24, printed circuit board 14 may connect the at least one power supply 22 with device 12 for initiating or fuzing device 12.

[0045] The disclosed actuation system 10 and / or actuation method 100, and their components, for initiating or fuzing device 12 may be configured for initiation or fuzing device 12 carried by or attached to vehicle 28. Vehicle 28 may be any vehicle configured for carrying or moving device 12, including but not limited to manned and unmanned aircrafts and vehicles, ground vehicles, maritime surface and underwater vessels, and fixed-wing and rotary wing aircraft. In select embodiments, as best shown in FIGS. 3 and 4, vehicle 28 may be, but is clearly not limited thereto, unmanned aerial vehicle (UAV) 30 or drone 30. Wherein, in use with UAV 30, actuation system 10 and / or actuation method 100 may be included with unmanned aerial system (UAS) 32 of UAV 30.

[0046] Referring specifically to FIGS. 2-4, in select embodiments of actuation system 10 and / or actuation method 100, and clearly not limited thereto, device 12 that is configured to be initiated or fuzed may be munition 34 carried by UAV 30. Wherein, actuation system 10 may be configured to initiate or fuze munition 34 while being carried, flown or dropped with UAV 30. In these embodiments, actuation system 10 may be configured as proximity fuze 36 for munition 34. Proximity fuze 36, as used herein, may be referred to as an electronic device in an explosive shell or missile (munition 34) that detonates it automatically when it gets within a set distance of a target. Wherein, when actuation system 10 is configured as proximity fuze 36, external sensor inputs 24 of PCB 14 may include proximity sensors 38. In select possibly preferred embodiments, proximity sensors 38 of external sensor inputs 24 may include ultrasonic proximity sensors 40. Ultrasonic proximity sensor or sensors 40 may detect objects and measure distance by emitting high-frequency sound waves (ultrasonic pulses) and listening for the returning echo, much like echolocation used by bats. Whereby, ultrasonic proximity sensor or sensors 40 may calculate the distance based on the time it takes for the sound to travel to the object and bounce back. In these embodiments of actuation system 10 as proximity sensor 38, an adjustment means, mechanism or dial may be included for adjusting the detonation of munition 34. As examples, and clearly not limited thereto, an adjustment dial may be provided to adjust the detonation between 3 meters from the target, 2 meters from the target, 1 meter from the target, and upon contact with the target.

[0047] Actuation system 10 and actuation method 100 may include a plurality of switches 16 for safety and redundancy. In select embodiments of actuation system 10 and / or actuation method 100, the plurality of switches 16 may include at least one mechanical switch 42. In select embodiments, the plurality of switches 16 may include two mechanical switches 42. In select possibly preferred embodiments, like when used as proximity fuze 36, the two mechanical switches 42 may include first mechanical pin switch 44 and second mechanical pin switch 48. The first mechanical pin switch44 may include first removable pin 46 that can be configured to be pulled out prior to UAV 30 taking off. The second mechanical pin switch 48 may include second removable pin 50 that can be configured to be pulled out when munition 34 is dropped from UAV 30.

[0048] Another feature of the disclosed actuation system 10 for initiating or fuzing device 12 may be the inclusion of housing device 52. Housing device 52 may be designed and configure based on the type of device 12 being initiation or fuzed. Housing device 52 may be configured to house components of actuation system 10. The components housed in housing device 52 may include printed circuit board 14, the at least one power supply 22, the external sensor inputs 24, and / or the output terminal 26. In select possibly preferred embodiments, housing device 52 may be configured to house all of the components of actuation system 10 including printed circuit board 14, the at least one power supply 22, the external sensor inputs 24, and the output terminal 26. In select embodiments, housing device 52 may be rapid-prototyped housing 54. Rapid-prototyped housing 54 may be a quick, often 3D-printed, physical model of an electronic device's casing or a temporary, quickly deployable shelter, allowing for fast design changes. As best shown in FIG. 2, in select embodiments, housing device 52 for munition 34 may include an aerodynamic structure and may include tail stabilizer 56 or fins 56 configured to ensure munition 34 falls nose-down ensuring proper alignment and operation of proximity sensors 38.

[0049] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to provide safe control of electrical currents on-board an un-manned aerial vehicle 30. Wherein the disclosed actuation system 10, components and method 100 may be designed to regulate the power supplied to auxiliary electronic mechanisms (i.e. device 12) comprised of printed circuit board 14 with proprietary control software of sensing and initiation, a battery or batteries for the power supply 22, an array of redundant electric switches included with the plurality of switches 16 including, but not limited to, a combination of two mechanical switches 42 or one mechanical switch 42 and one electronic switch 20 or remotely controlled switch 20, developed for purposes of ensuring safe actuation, paired with proximity sensor or sensors 38 to begin electric current flow to the auxiliary mechanism or device 12 when certain criteria is met.

[0050] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to allow an economical and safe use of sensors for adaptation to attritable sensors 24 and devices 12. Wherein the devices 12 include unmanned aircraft systems (UAS) or other unmanned systems including ground vehicles, maritime surface and underwater vessels, and fixed-wing and rotary wing aircraft, and components thereof.

[0051] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to enable the development of methods of communication and munitions deployment, tactics, techniques, and procedures (TTPs) for employment in training and combat scenarios.

[0052] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to be used for munition 34, a signal flare, GPS beacons, laser beacons, LED lights, or other signals between manned or unmanned objects for purposes of indicating a status, indicating a directional navigation mark or marker, or for triggering or initiating a fuze or other electronic circuit on munition 34 or other device 12.

[0053] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to establish and function as a communication node or relay, configured to indicate when one system has reached a location and has come within pre-programmed parameters of a destination, wherein an indicator of proximity sensor or sensors 38 and an LED indicates that the UAS 32 has reached the destination and is in position.

[0054] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to enable inexpensive triggering or initiation of electrical circuits for the purposes of communication, munitions deployment, navigation, or other purposes.

[0055] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to incorporate multiple redundant sensors 24 and switches 16 in order to prevent false-triggering or inadvertent actuation while being handled, during transport in a container or in a bulk shipment, or during other administrative operations when actuation is not expected nor required, thereby being a safety feature as well as a feature to preserve battery life and durability of the actuation system 10.

[0056] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to offer a low-cost alternative to more traditional fuzing mechanisms which rely on complex mechanical systems including air turbines, accelerometers, gear trains, and counters and chronometers to gauge the number of rotations in order to initiate a circuit or to estimate airspeed and to calculate proximity to the ground. Whereby, by enabling the low-cost alternative and reliable methods to perform these tasks, actuation system 10 and / or actuation method 100 may be configured to enable a widespread application of inexpensive systems for reconnaissance and tactical operations in a training and combat environment.

[0057] Another feature of actuation system 10 and / or actuation method 100 for initiating or fuzing device 12 may be that it can be designed and / or configured to provide an electrical disconnect from critical electrical circuitry unless and until certain other conditions are met, which ensures the safety of device 12 and prevents device 12 from operating unintentionally.

[0058] Referring now specifically to FIG. 1, an embodiment of a circuit diagram for printed circuit board 14 or PCB 14 is shown. The circuit diagram shown in FIG. 1 may be, but is not limited to, a detonator ignition schematic with double protection, both line positive and negative don’t connect to the detonator or device 12 through output terminal 26, where MOSFETSs Q1 and Q2 may control this. To prevent detonation from moisture the circuit makes protection by generating enable signals to open MOSFETS Q1 and Q2 via multiplying by C3 / D3 / C4 and signal for multiply generated via microcontroller 18 (U1). So, when moisture may short the circuit it may not be possible to generate signal via microcontroller 18 (U1) or multiply it (as it requires U1 / C3 / D3 / C4 to work normal) and just short circuit doesn’t have enough power to ignite the detonator, i.e. close the electronic switch and connect power supply 22 with output terminal 26. Only proper working schematic may make it possible to open Q1 and Q2 correctly.

[0059] As such, this circuit diagram of PCB 14 illustrates a battery-powered system controlled by microcontroller 18 (U1) and multiple switches 16. The primary power source or power supply 22 (B1) is shown as a 3.7 V 45 mAh battery that is configured to serve as the primary power source. Microcontroller 18 is shown as U1 and may be the central brain of the circuit, featuring several pins labeled for specific functions like FIRE EN (Enable), FIRE PWM, and communication lines like 12C2 SCL / SDA for external sensor inputs 24. Switches 16 shown as SW1& SW2 are input components (labeled MSK-03G2.0 and DM1-03P) that are designed and configured to allow for manual user interaction or state changes within the system, like via first mechanical pin switch 44 and second mechanical pin switch 48. Indicator LED (D2) is shown as a green LED connected through a 470Ω resistor (R1), which may serve as a status indicator when the circuit is active. The circuit uses a BAT54S Schottky diode (D3) and various capacitors (like C3 at 0.1uF and C4 at 10uF) to stabilize voltage and protect microcontroller 18 from electrical noise or reverse current, or from voltage spikes. Resistors R7 (200Ω), R8 (10kΩ), and R9 (200kΩ) are used to pull signals to specific levels (high or low) to ensure microcontroller 18 reads inputs correctly, like external sensor inputs 24. Multiple ground symbols (the sets of three horizontal lines) indicate a common return path to the negative terminal of the battery or power supply 22, completing the electrical loop. Resistors R7 (200Ω), R8 (10kΩ), and R9 (200kΩ) may act as pull-up or pull-down resistors, where they ensure the pins of microcontroller 18 don't float and cause accidental activations when the switches 16 aren't closed. Pins PA11 and PA12 are labeled 12C2 SCL and 12C2 SDA, indicating the device can talk to other digital components (like a screen or a sensor) using the I2C communication protocol, like for use with external sensor inputs 24 including proximity sensors 38, like ultrasonic proximity sensors 40.

[0060] Still referring specifically to the circuit diagram of the embodiment of PCB 14 shown in FIG. 1, fire labels on microcontroller 18 are shown. FIRE EN (Enable), as shown in pin 9, may act as a safety gate. When the microcontroller 18 (U1) wants to activate electronic switch 20, it sends a signal here to "unlock" the power path. FIRE PWM (Pulse Width Modulation), as shown in pin 10, may control the intensity or temperature of the "fire". By rapidly pulsing the power on and off (PWM), the circuit can precisely manage how much heat is generated. FIRE DEACT (Deactivate), as shown in pin 8, may be hardware-level safety or feedback line. It may be used to instantly shut down the "fire" function if a fault is detected or if a specific timer limit is reached. The presence of R7 (200Ω) and R8 (10kΩ) resistors near these pins are used to ensure the "fire" signals don't trigger accidentally due to electrical noise. For example, R8 may keep the activation line "pulled down" to ground so the device stays off unless microcontroller 18 actively turns it on.

[0061] Still referring specifically to the circuit diagram of the embodiment of PCB 14 shown in FIG. 1, output terminal 26 is generally shown as J1 for a jack or connector. Specifically the XY118-5.0-2P may be a two-pin screw terminal block for use as output terminal 26 for connection to device 12. Its primary purpose may be to provide a physical interface where external wires can be securely attached to printed circuit board 14. Output terminal 26 may be connected to the drains of two IRLML0040 MOSFETs (Q1 and Q2) of electronic switch 20. This indicates that output terminal 26 may be used to power the "Fire" mechanism from microcontroller 18. When microcontroller 18 activates the MOSFETs of electronic switch 20, the circuit closes, allowing current to flow from the battery (power supply 22) through whatever device 12 is connected to output terminal 26 (J1). XY118 may refer to the specific series of the terminal block. 5.0 may indicate a 5.0mm pitch, which is the distance between the centers of the two pins. 2P may stand for 2-Pole (or 2-pin), matching the two connection points (labeled 1 and 2) seen in the diagram.

[0062] Still referring specifically to the circuit diagram of the embodiment of PCB 14 shown in FIG. 1, electronic switch 20 is shown with two MOSFETS Q1 and Q2 which may act as high-power electronic switches that control the delivery of power to output terminal 26 (J1). The two MOSFETs Q1 and Q2 are wired in parallel, which means their drains (the output side) are both connected to Pin 2 of the J1 terminal block of output terminal 26. This configuration serves a specific purpose to increase current capacity and reduce resistance. By using two MOSFETs in parallel, the circuit can safely handle more current than a single MOSFET could alone. The IRLML0040 is rated for a continuous drain current of up to 3.6A, so doubling them allows the device to drive a much heavier load, without overheating the individual components. Placing them in parallel also halves the total "on-resistance" of the switch. This makes the circuit more efficient by reducing the amount of power wasted as heat during operation. In use, microcontroller 18 (U1) may send a control signal from its "FIRE" pins (specifically FIRE PWM) to the gates of Q1 and Q2. When the signal is "High," the MOSFETs "turn on," creating a low-resistance path between the source and the drain. This may allow current from the battery (VBAT) to flow through whatever device 12 is connected to output terminal 26 (J1 or screw terminal), effectively "firing" or activating it. The R8 (10kΩ) resistor may acts as a pulldown resistor for the gates, whereby it may ensure that if microcontroller 18 is off or restarting, the MOSFETs stay firmly "OFF," preventing the device from firing accidentally. VBAT (Variable Battery) represents the battery voltage supply for the circuit. It is connected to a battery source (labeled B1) with a capacity of 3.7 V 45 mAh. The power from VBAT is controlled by a slide switch (labeled SW2), which is a DM1-03P model. This voltage supply provides power to various parts of the circuit, including the D2 Green LED through resistor R1 (470 ohms) and the MOSFETs Q1 and Q2 (model IRLML0040).

[0063] The disclosed printed circuit board 14 may be provided in many different embodiments for actuation system 10 for providing a safe and economical circuit for fuzing or activating device 12, like munition 34. In select embodiments, main PCB 14 of actuation system 10 may be provided in both a dropper configuration and a kamikaze configuration for proximity fuze 36. In the dropper configuration, a first fuse or switch 16 may be provided as a mechanical circuit breaker (on / off switch) for first mechanical switch 42. A second fuse or switch 16 may be provided as a mechanical circuit breaker (pull pin). A third fuse or switch 16 may be provided as double MOSFETS before the blast cap, to prevent if one is broken or shorted by rain / snow / other weather. As such, both polarities must be broken to initiate. A fourth fuse or switch 16 may be provided to control signals to control MOSFESTS generated from microcontroller 18. This may create a situation that if there is a short of the MOSFET control pins, then the MOSFETS will not open. A fifth fuse or switch 16 may be provided, where because of the double MOSFETS, the system will only ignite charge caps due to internal resistance. This may prevent from a situation when someone is testing, so if an LED bulb is connected for testing, it will somehow be somewhat damaged as an indicator. A sixth fuse or switch 16 may be provided that is configured to make it nearly impossible for enemy to shine an IR beam at fuse and initiate. In addition, the system and circuit may be designed and configured to ignore sun reflections as well, because of the use of internal sensor with additional filters. These features may help to prevent any manufacturing defects from becoming an issue

[0064] In another embodiment, main PCB 14 of actuation system 10 may be provided with additional fuses for a Kamikaze version Power Pack. In this embodiment, a first fuse or switch 16 may be provided as a mechanical chain breaker (i.e., an on / off switch). In addition, a second fuse or switch 16 may be an electronic switch enabled from microcontroller 18 that may be configured to analyze levels of PWM signal from a flight controller.

[0065] Referring now specifically to FIGS. 2-4, in another aspect, the instant disclosure embraces proximity fuze 36 for munition 34 for an unmanned aerial vehicle (UAV) 30. Proximity fuze 36 may be a component of the disclosed actuation system 10 and may include any of the various embodiments and / or combinations of embodiments shown and / or described herein. In general, the disclosed proximity fuze 36 may include printed circuit board 14 or PCB 14 including the plurality of switches 16 and microcontroller 18. Wherein at least one of the plurality of switches 16 may be an electronic switch 20 controlled by microcontroller 18. At least one power supply 22 may be connected to and powering printed circuit board 14. The external sensor inputs 24 may be connected to microcontroller 18 of printed circuit board 14. The external sensor inputs 24 of proximity fuze 36 may include proximity sensors 38. Output terminal 26 of printed circuit board 14 may be configured to connect munition 34 to printed circuit board 14. Wherein, printed circuit board 14 may be configured to control the connection of power supply 22 to munition 34 connected to output terminal 26 for initiating or fuzing munition 34 based on signals from external sensor inputs 24 with proximity sensors 38. Wherein, when the plurality of switches 16 are closed including the electronic switch 20 being closed by microcontroller 18 based on the signals from the external sensor inputs 24 from proximity sensors 38, printed circuit board 14 may connect the at least one power supply 22 with munition 34 for initiating or fuzing munition 34. In select possibly preferred embodiments of fuze 36, proximity sensors 38 of external sensor inputs 24 may include ultrasonic proximity sensors 40. Ultrasonic proximity sensor or sensors 40 may detect objects and measure distance by emitting high-frequency sound waves (ultrasonic pulses) and listening for the returning echo, much like echolocation used by bats. Whereby, ultrasonic proximity sensor or sensors 40 may calculate the distance based on the time it takes for the sound to travel to the object and bounce back. In select embodiments of proximity sensor 38, an adjustment means, mechanism or dial may be included for adjusting the detonation of munition 34. As examples, and clearly not limited thereto, an adjustment dial may be provided to adjust the detonation between 3 meters from the target, 2 meters from the target, 1 meter from the target, and upon contact with the target.

[0066] Actuation system 10 and actuation method 100 may include a plurality of switches 16 for safety and redundancy. In select embodiments of actuation system 10 and / or actuation method 100, the plurality of switches 16 may include at least one mechanical switch 42. In select embodiments, the plurality of switches 16 may include two mechanical switches 42. In select possibly preferred embodiments, like when used as proximity fuze 36, the two mechanical switches 42 may include first mechanical pin switch 44 and second mechanical pin switch 48. The first mechanical pin switch 44 may include first removable pin 46 that can be configured to be pulled out prior to UAV 30 taking off. The second mechanical pin switch 48 may include second removable pin 50 that can be configured to be pulled out when munition 34 is dropped from UAV 30.

[0067] Another feature of proximity fuze 36 for initiating or fuzing munition 34 may be the inclusion of housing device 52. Housing device 52 may be designed and configured based on the type of munition 34 being initiation or fuzed. Housing device 52 may be configured to house components of proximity fuze 36. The components housed in housing device 52 may include printed circuit board 14, the at least one power supply 22, the external sensor inputs 24 with proximity sensors 38, and / or the output terminal 26. In select possibly preferred embodiments, housing device 52 may be configured to house all of the components of proximity fuze 36 including printed circuit board 14, the at least one power supply 22, the external sensor inputs 24 with proximity sensors 38, and the output terminal 26. In select embodiments, housing device 52 may be rapid-prototyped housing 54. Rapid-prototyped housing 54 may be a quick, often 3D-printed, physical model of an electronic device's casing or a temporary, quickly deployable shelter, allowing for fast design changes. As best shown in FIG. 2, in select embodiments, housing device 52 for munition 34 may include an aerodynamic structure and may include tail stabilizer 56 or fins 56 configured to ensure munition 34 falls nose-down ensuring proper alignment and operation of proximity sensor or sensors 38 for proximity fuze 36.

[0068] One feature of the disclosed proximity fuze 36 may be that it can be configured to provide safe control of electrical currents on-board UAV 30. Wherein, proximity fuze 36 may be designed to regulate the power supplied to munition 34 comprised of printed circuit board 14 with proprietary control software of sensing and initiation, a battery or batteries for power supply 22, an array of redundant electric switches included with the plurality of switches 16 including a combination of two mechanical switches 42 or one mechanical switch 42 and one electronic or remotely controlled switch 20, developed for purposes of ensuring safe actuation, paired with proximity sensor 38 to begin electric current flow to munition 34 when certain criteria is met.

[0069] Another feature of the disclosed proximity fuze 36 may be that it can be configured to allow an economical and safe use of sensors for adaptation to attritable sensors and devices, wherein the devices include unmanned aerial systems (UAS) 32.

[0070] Another feature of the disclosed proximity fuze 36 may be that it can be configured to enable the development of methods of communication and munitions deployment, tactics, techniques, and procedures (TTPs) for employment in training and combat scenarios.

[0071] Another feature of the disclosed proximity fuze 36 may be that it can be configured to establish and function as a communication node or relay, configured to indicate when one system has reached a location and has come within pre-programmed parameters of a destination, wherein an indicator of proximity sensor 38 and an LED indicates that UAS 32 has reached the destination and is in position.

[0072] Another feature of the disclosed proximity fuze 36 may be that it can be configured to enable inexpensive triggering or initiation of electrical circuits for the purposes of communication, munitions deployment, navigation, or for other purposes.

[0073] Another feature of the disclosed proximity fuze 36 may be that it can be configured to incorporate multiple redundant sensors 24 or switches 16 in order to prevent false-triggering or inadvertent actuation while being handled, during transport in a container or in a bulk shipment, or during other administrative operations when actuation is not expected nor required, thereby being a safety feature as well as a feature to preserve battery life and durability of proximity fuze 36.

[0074] Another feature of the disclosed proximity fuze 36 may be that it can be configured to offer a low-cost alternative to more traditional fuzing mechanisms which rely on complex mechanical systems including air turbines, accelerometers, gear trains, and counters and chronometers to gauge the number of rotations in order to initiate a circuit or to estimate airspeed and to calculate proximity to the ground.

[0075] Another feature of the disclosed proximity fuze 36 may be that it can be configured to provide an electrical disconnect from critical electrical circuitry unless and until certain other conditions are met, which ensures the safety of munition 34 and may prevent munition 34 from operating unintentionally.

[0076] Referring now specifically to FIG. 5, a perspective view of a non-electric variant 58 of the components or system for initiating or detonating device 12 is shown for use with actuation system 10, like when used as proximity fuze 36.

[0077] Referring now specifically to FIG. 6, in another aspect, the instant disclosure embraces method 100 of initiating or fuzing device 12. The disclosed method 100 of initiating of fuzing device 12 may include utilizing the disclosed actuation system 10 and / or components in any of the embodiments and / or combination of embodiments shown and / or described herein. As such, the disclosed method 100 of initiating or fuzing device 12 may generally include step 102 of providing the disclosed proximity fuze 36 in any of the embodiments and / or combination of embodiments shown and / or described herein. The provided proximity fuze 36 may generally include a circuit (like PCB 14 shown in FIG. 1) including the plurality of switches 16 and microcontroller 18. Wherein, the plurality of switches 16 may include: first mechanical switch 42; second mechanical switch 42, and third electronic switch 20 controlled by microcontroller 18. Output terminal 26 of printed circuit board 14 may be configured to connect device 12, like munition 34, to printed circuit board 14. With the provided proximity fuze 36, the disclosed method 100 of initiating or fuzing device 12 may further include: step 104 of determining if first mechanical switch 42 is closed. If first mechanical switch 42 is closed, method 100 may include step 106 of determining if second mechanical switch 42 is closed. If first mechanical switch 42 and second mechanical switch 42 are both closed, method 100 may include step 108 of determining if the third electronic switch 20 should close by, after a 2 second delay; step 110 of continuously measuring a distance to a target. Wherein, if the measured distance to the target is less than or equal to a target distance, method 100 including step 112 of closing the third electronic switch 20 whereby device 12, like munition 34 is initiated or fuzed.

[0078] A feature of the present disclosure may be its ability to enable inexpensive triggering or initiation of electrical circuits for the purposes of communication, munitions deployment, navigation, or for other purposes.

[0079] Another feature of the present disclosure may be the ability to incorporate multiple redundant sensors in order to prevent false-triggering or inadvertent actuation while being handled, during transport in a container or in a bulk shipment, or during other administrative operations when actuation is not expected nor required, this being a beneficial safety feature as well as a beneficial feature to preserve battery life and durability of the unit.

[0080] Another feature of the present disclosure may be its ability to offer a low-cost alternative to more traditional fuzing mechanisms which rely on complex mechanical systems such as air turbines, accelerometers, gear trains, and counters and chronometers to gauge the number of rotations in order to initiate a circuit or to estimate airspeed and to calculate proximity to the ground. By enabling lower cost and more reliable methods to perform these tasks the present invention enables more widespread application of inexpensive systems for reconnaissance and tactical operations in a training and combat environment.

[0081] Another feature of the present disclosure may be its electrical disconnect from critical electrical circuitry unless and until certain other conditions are met, which further ensures the safety of device and prevents it from operating unintentionally.

[0082] In sum, the present disclosure provide a novel initiation method 100 and actuation system 10 for the safe control of electrical currents on-board an un-manned aerial vehicle 30, designed to regulate the power supplied to auxiliary electronic mechanisms (to include but not limited to GPS beacons, LED lights, etc.) comprised of printed circuit board 14 with proprietary control software of sensing and initiation, a battery or batteries, an array of redundant electric switches 16, which can be a combination of two mechanical switches 42 or one mechanical and one electronic switch 20 or remotely controlled switch 20, or other combinations developed for purposes of ensuring safe actuation, paired with a sensor such as a proximity sensor 38 (ultrasonic 40 or other type) to begin electric current flow to the auxiliary mechanism or device 12 when certain criteria is met.

[0083] The present disclosure may use not one but a range of optical sensors, which are typically used in cheap electronic devices to receive IR command. Usually these sensors are slow to calculate speed of light and distance. But the instant disclosure may use not standard connection logic for this sensors and compare time between send pulse via emitter and receive it via sensor. Following this, the disclosure may provide the possibility to measure distance over 3000 times per second, which makes it possible to build different air fuses / kamikaze fuses. Also, the disclosure may use building sensor filters to avoid wrong processing and filter possible interference. Using this sensor may make it possible to lower the price for the disclosed system 10 in comparison with expensive Time-Of-Flight (TOF) sensors. The disclosure may also provide a protected ignition circuit which has 2 MOSFETS to avoid wrong detonation because of moisture or damage to PCB 14. The disclosed system 10 may include 2 mechanical fuses or switches 42 in drop version: one will be pulled out before you take off of your aircraft and second one when you drop charge or munition 34 near the target. The disclosed actuation system 10 may have 2 mechanical and 1 electronic fuses in a kamikaze version: one will be disabled before you take off your aircraft, second after you take off, and 3rd you disable remotely near the target in air. The disclosed actuation system 10 may use 3D printed case or housing device 52 adapted for different grenades or mortar projectiles. This may keep the cost low and provide easy usage of the disclosed actuation system 10. This may be a key difference of the disclosed actuation system 10 in compare with other expensive air fuses, or the like.

[0084] Using method 100 and / or system 10 described herein can allow an economical and safe use of sensors for adaptation to attritable sensors and devices. Such devices include but are not limited to unmanned aerial systems 32 (UAS) or other unmanned systems including ground vehicles, maritime surface and underwater vessels, and fixed-wing and rotary wing aircraft.

[0085] Combining the described method 100 and / or system 10 with these other manned and unmanned aircraft, ground vehicles, and vessels enables the user to develop new methods of communication and munitions deployment, tactics, techniques, and procedures (TTPs) for their employment in training and combat scenarios.

[0086] Method 100 and / or system 10 described herein can be used for munition 34, a signal flare, GPS beacons, laser beacons, LED lights, or other signals between manned or unmanned objects for purposes of indicating a status, indicating a directional navigation mark or marker, or for triggering or initiating a fuze or other electronic circuit on a munition or other device.

[0087] Method 100 and / or system 10 with its components described herein can also establish and function as a communication node or relay, which could be used by those skilled in the art to indicate when one system (unmanned aircraft system 32 or UAS, as an example) has reached a location and has come within the pre-programmed parameters of the destination. Using the indicator of the proximity sensor 38 and the LED the User could be made aware that the UAS 32 has reached the destination and is in position.

[0088] In the specification and / or figures, typical embodiments of the disclosure have been disclosed. The present disclosure is not limited to such exemplary embodiments. The use of the term “and / or” includes any and all combinations of one or more of the associated listed items. The figures are schematic representations and so are not necessarily drawn to scale. Unless otherwise noted, specific terms have been used in a generic and descriptive sense and not for purposes of limitation.

[0089] The foregoing description and drawings comprise illustrative embodiments. Having thus described exemplary embodiments, it should be noted by those skilled in the art that the within disclosures are exemplary only, and that various other alternatives, adaptations, and modifications may be made within the scope of the present disclosure. Merely listing or numbering the steps of a method in a certain order does not constitute any limitation on the order of the steps of that method. Many modifications and other embodiments will come to mind to one skilled in the art to which this disclosure pertains having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. Although specific terms may be employed herein, they are used in a generic and descriptive sense only and not for purposes of

[0090] limitation. Accordingly, the present disclosure is not limited to the specific embodiments illustrated herein but is limited only by the following claims.

Claims

1. An actuation system for initiation or fuzing a device comprising:a printed circuit board including a plurality of switches and a microcontroller, wherein at least one of the plurality of switches is an electronic switch controlled by the microcontroller;at least one power supply connected to and powering the printed circuit board; external sensor inputs connected to the microcontroller of the printed circuit board; an output terminal of the printed circuit board configured to connect the device to the printed circuit board;wherein, the printed circuit board is configured to control a connection of the power supply to the device connected to the output terminal for initiating or fuzing the device based on signals from the external sensor inputs; andwherein, when the plurality of switches are closed including the electronic switch being closed by the microcontroller based on the signals from the external sensor inputs, the printed circuit board connecting the at least one power supply with the device for initiating or fuzing the device.

2. The actuation system of claim 1 being configured for initiation or fuzing the device carried by or attached to a vehicle.

3. The actuation system of claim 2, wherein the vehicle is an unmanned aerial vehicle (UAV), wherein the actuation system is included with an unmanned aerial system (UAS) of the UAV.

4. The actuation system of claim 3, wherein the device is a munition carried by the UAV and the actuation system is configured to initiate or fuze the munition.

5. The actuation system of claim 4, wherein the actuation system is configured as a proximity fuze for the munition, wherein the external sensor inputs including proximity sensors.

6. The actuation system for initiating or fuzing a device of claim 5, wherein the proximity sensors of the external sensor inputs including ultrasonic proximity sensors.

7. The actuation system of claim 6, wherein the plurality of switches including at least one mechanical switch.

8. The actuation system of claim 7, wherein the plurality of switches including two mechanical switches.

9. The actuation system of claim 8, wherein the two mechanical switches including:a first mechanical pin switch including a first removable pin configured to be pulled out prior to the UAV taking off; anda second mechanical pin switch including a second removable pin being configured to be pulled out when the munition is dropped from the UAV.

10. The actuation system of claim 1 further comprising a housing device housing components of the actuation system.

11. The actuation system of claim 10, wherein the components housed in the housing device including the printed circuit board, the at least one power supply, the external sensor inputs, and the output terminal.

12. The actuation system of claim 11, wherein the housing device is a rapid-prototyped housing.

13. The actuation system of claim 1 being configured to:provide safe control of electrical currents on-board an un-manned aerial vehicle, designed to regulate power supplied to auxiliary electronic mechanisms comprised of the printed circuit board with proprietary control software of sensing and initiation, a battery or batteries for the power supply, an array of redundant electric switches included with the plurality of switches including a combination of two mechanical switches or one mechanical and one electronic or remotely controlled switch, developed for purposes of ensuring safe actuation, paired with a proximity sensor to begin electric current flow to an auxiliary mechanism when certain criteria is met;allow an economical and safe use of sensors for adaptation to attritable sensors and devices, wherein the devices include unmanned aerial systems (UAS) or other unmanned systems including ground vehicles, maritime surface and underwater vessels, and fixed-wing and rotary wing aircraft;enable development of methods of communication and munitions deployment, tactics, techniques, and procedures (TTPs) for employment in training and combat scenarios;be used for a munition, a signal flare, GPS beacons, laser beacons, LED lights, or other signals between manned or unmanned objects for purposes of indicating a status, indicating a directional navigation mark or marker, or for triggering or initiating a fuze or other electronic circuit on the munition or other device;establish and function as a communication node or relay, configured to indicate when one system has reached a location and has come within pre-programmed parameters of a destination, wherein an indicator of a proximity sensor and an LED indicates that the UAS has reached the destination and is in position;enable inexpensive triggering or initiation of electrical circuits for the purposes of communication, munitions deployment, navigation, or for other purposes;incorporate multiple redundant sensors in order to prevent false-triggering or inadvertent actuation while being handled, during transport in a container or in a bulk shipment, or during other administrative operations when actuation is not expected nor required, thereby being a safety feature as well as a feature to preserve battery life and durability of the actuation system;offer a low-cost alternative to more traditional fuzing mechanisms which rely on complex mechanical systems including air turbines, accelerometers, gear trains, and counters and chronometers to gauge a number of rotations in order to initiate a circuit or to estimate airspeed and to calculate proximity to ground, whereby by enabling the low-cost alternative and reliable methods to perform these tasks, the actuation system is configured to enable a widespread application of inexpensive systems for reconnaissance and tactical operations in a training and combat environment;provide an electrical disconnect from critical electrical circuitry unless and until certain other conditions are met, which ensures safety of the device and prevents the device from operating unintentionally; orcombinations thereof.

14. A proximity fuze for a munition for an unmanned aerial vehicle (UAV) comprising:a printed circuit board including a plurality of switches and a microcontroller, wherein at least one of the plurality of switches is an electronic switch controlled by the microcontroller;at least one power supply connected to and powering the printed circuit board; external sensor inputs connected to the microcontroller of the printed circuit board, the external sensor inputs including proximity sensors; an output terminal of the printed circuit board configured to connect the munition to the printed circuit board;wherein, the printed circuit board is configured to control a connection of the power supply to the munition connected to the output terminal for initiating or fuzing the munition based on signals from the external sensor inputs; andwherein, when the plurality of switches are closed including the electronic switch being closed by the microcontroller based on the signals from the external sensor inputs, the printed circuit board connecting the at least one power supply with the munition for initiating or fuzing the munition.

15. The proximity fuze of claim 14, wherein the proximity sensors of the external sensor inputs including ultrasonic proximity sensors.

16. The proximity fuze of claim 14, wherein the plurality of switches including at least one mechanical switch.17.The proximity fuze of claim 16, wherein the plurality of switches including two mechanical switches, wherein the two mechanical switches including:a first mechanical pin switch including a first removable pin configured to be pulled out prior to the UAV taking off; anda second mechanical pin switch including a second removable pin being configured to be pulled out when the munition is dropped from the UAV.

18. The proximity fuze of claim 14 further comprising a housing device housing components of the proximity fuze;wherein the components housed in the housing device including the printed circuit board, the at least one power supply, the external sensor inputs, and the output terminal; andwherein the housing device is a rapid-prototyped housing.

19. The proximity fuze of claim 14 being configured to:provide safe control of electrical currents on-board the UAV, designed to regulate power supplied to the munition comprised of the printed circuit board with proprietary control software of sensing and initiation, a battery or batteries for the power supply, an array of redundant electric switches included with the plurality of switches including a combination of two mechanical switches or one mechanical and one electronic or remotely controlled switch, developed for purposes of ensuring safe actuation, paired with a proximity sensor to begin electric current flow to the munition when certain criteria is met;allow an economical and safe use of sensors for adaptation to attritable sensors and devices, wherein the devices include unmanned aerial systems (UAS);enable development of methods of communication and munitions deployment, tactics, techniques, and procedures (TTPs) for employment in training and combat scenarios;establish and function as a communication node or relay, configured to indicate when one system has reached a location and has come within pre-programmed parameters of a destination, wherein an indicator of a proximity sensor and an LED indicates that the UAS has reached the destination and is in position;enable inexpensive triggering or initiation of electrical circuits for purposes of communication, munitions deployment, navigation, or for other purposes;incorporate multiple redundant sensors in order to prevent false-triggering or inadvertent actuation while being handled, during transport in a container or in a bulk shipment, or during other administrative operations when actuation is not expected nor required, thereby being a safety feature as well as a feature to preserve battery life and durability of the proximity fuze;offer a low-cost alternative to more traditional fuzing mechanisms which rely on complex mechanical systems including air turbines, accelerometers, gear trains, and counters and chronometers to gauge a number of rotations in order to initiate a circuit or to estimate airspeed and to calculate proximity to ground;provide an electrical disconnect from critical electrical circuitry unless and until certain other conditions are met, which ensures safety of the munition and prevents the munition from operating unintentionally; orcombinations thereof.

20. A method of initiating or fuzing a device comprising:providing a proximity fuze comprising:a circuit including a plurality of switches and a microcontroller, wherein the plurality of switches including:a first mechanical switch;a second mechanical switch; anda third electronic switch controlled by the microcontroller;an output terminal of the circuit configured to connect the device to the circuit;determining if the first mechanical switch is closed;if the first mechanical switch is closed, determining if the second mechanical switch is closed;if the first mechanical switch and the second mechanical switch are both closed, determining if the third electronic switch should close by, after a 2 second delay;continuously measuring a distance to a target; andif the measured distance to the target is less than or equal to a target distance, closing the third electronic switch whereby the device is initiated or fuzed.

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