DUAL-SAFE FUZE FOR UAS DRONE APPLICATIONS

Abstract

A dual-safe fuze incorporating electrical and/or mechanical fuzing for unmanned aerial system (UAS) drone applications includes an electrical power source configured to initiate a munition, and circuitry. The electrical and mechanical circuitry is positioned between the electrical power source and the munition for controlling the initiation of the munition via the electrical power source. The circuitry is configured to initiate the munition from an unmanned aerial vehicle (UAV). The circuitry positioned between the electrical power source and the munition includes a nose-proximity fuze circuit, a body-proximity fuze circuit, a shear lanyard safety circuit, and combinations thereof.

Claims

1. A dual-safe fuze for unmanned aerial system (UAS) drone applications comprising: an electrical power source configured to initiate a munition; circuitry positioned between the electrical power source and the munition for controlling initiation of the munition via the electrical power source, the circuitry is configured to initiate the munition from an unmanned aerial vehicle (UAV), the circuitry positioned between the electrical power source and the munition including: a nose-proximity fuze circuit; a body-proximity fuze circuit; a shear lanyard safety circuit; and combinations thereof.

2. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 1, wherein the circuitry is electrical circuitry and mechanical circuitry including: the nose-proximity fuze circuit; the body-proximity fuze circuit; and the shear lanyard safety circuit.

3. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 2, wherein the nose-proximity fuze circuit is configured to detect a proximity to a target.

4. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 3, wherein the nose-proximity fuze circuit is a normally open electrical circuit, when the nose-proximity fuze circuit comes in a proximity of the target, the nose-proximity fuze circuit is configured to close to allow connection of electrical power through the nose-proximity fuze circuit.

5. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 4, wherein the nose-proximity fuze circuit is configured as a first-person view (FPV) circuit configured to allow a user to initiate the munition by flying the unmanned aerial vehicle (UAV) with the dual-safe fuze into the target in a kamikaze style, whereby, when the unmanned aerial vehicle (UAV) with the dual-safe fuze comes in the proximity of the target, the dual-safe fuze is configured to initiate the munition.

6. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 2, wherein the body-proximity fuze circuit has a body-proximity fuze sensor, the body-proximity fuze circuit is an electrical circuit which is a normally open electrical circuit and is configured to not permit passage of electrical current or voltage until it is closed electrically, wherein when the body-proximity fuze sensor detects that the munition has been dropped, then the body-proximity fuze circuit is configured to close to allow connection of electrical power through the body-proximity fuze circuit.

7. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 2, further comprising a timer circuit.

8. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 7, wherein the timer circuit is configured to enable a user to set a time period in which the timer circuit is electrically open, thereby allowing the munition and the unmanned aerial vehicle (UAV) to be handled for the set time period before the timer circuit is electrically energized.

9. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 8, wherein the timer circuit is part of the body-proximity fuze circuit; and wherein, the timer circuit is configured to enable the user to set the time period in which the timer circuit is electrically open, thereby allowing the munition and the unmanned aerial vehicle (UAV) to be handled for the set time period before the timer circuit is electrically energized before the normally open body-proximity fuze circuit is electrically closed enabling potential of electricity to pass through the body-proximity fuze circuit.

10. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 1, wherein the shear lanyard safety circuit including: a normally closed lanyard switch; a safety lanyard, the safety lanyard is connected on one side to the unmanned aerial vehicle (UAV) and the other side of the safety lanyard is inserted into a sliding receptable in the lanyard switch for opening the normally closed lanyard switch and not allowing electrical current to flow therethrough; and whereby, when the munition is dropped from the unmanned aerial vehicle (UAV), the other side of the safety lanyard is configured to pull out of the sliding receptacle for closing the normally closed lanyard switch.

11. The dual-safe fuze for unmanned aerial systems (UAS) drove applications of claim 10, wherein the shear lanyard safety circuit including a mission selector configured to allow a user to select a mission mode, the mission selector including selectable mission options including: an FPV mission option for first-person view for flying the unmanned aerial vehicle with the munition into a target in a kamikaze style; a DROP/LAN mission option for dropping the munition from the unmanned aerial vehicle (UAV) onto the target; and a DUAL mission option for providing the user the option of the FPV mission or the DROP/LAN mission.

12. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 10, wherein, the shear lanyard safety circuit further including a collapsible element in a nose assembly, the collapsible element in the nose assembly including a shear pin or other mechanical element that is configured to break on impact with the target.

13. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 12, wherein when the nose assembly impacts the target and the shear pin or other mechanical element breaks, the collapsible element is configured to come into electrical contact with elements in the nose assembly to close the shear lanyard safety circuit and allow electrical energy to be applied to the shear lanyard safety circuit; and wherein, when the shear pin or other mechanical element breaks and the collapsible element comes into electrical contact with the elements in the nose assembly, the collapsible element is configured to allow electrical connection from the electrical power source which applies electrical power through the nose-proximity sensor and circuit, through the body-proximity fuze circuit and the timer circuit, and then through the shear lanyard safety circuit either when the safety lanyard is pulled from its sliding receptacle or when the nose impact damages or pushes physically past the shear pin or other mechanical element and electrically connects the circuit, where once these conditions are met, the munition is able to be fully energized and can be initiated.

14. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 1 being designed and configured for arming and initiating munitions when carried by unmanned aerial system (UAS) or other vehicle, vessel, aircraft, or system guidance which do not have the natural accelerative loads or forces for initiating arming of the munitions, or which do not have the natural impacting forces and decelerative forces to begin the initiation process of the munition which is typically found on impacting the target at high velocity.

15. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 1 being designed and configured to enable the use of traditional munitions/warheads/ explosives while employing a method to safely manipulate them during assembly to the unmanned aerial vehicle (UAV) or other vehicle that will be using them, and also permitting safe deployment for the mission.

16. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 1, wherein the dual-safe fuze is configured and designed to: enable the use of traditional munitions/warheads/explosives in non-traditional means, such as when mounted to a relatively slow moving UAS when a UAS speed is compared to a rocket, missile, mortar, grenade, rocket-propelled grenade, artillery munition, or other traditionally delivered munition; enable the safe fitment of a munition to a UAS enabling the safe mounting and manipulation of the munition/warhead/explosive charge to a UAS, wherein a rocket system which would typically or traditionally deliver a munition/warhead/explosive in a manner which would put the munition beyond the range of the target, can be fitted to a UAS and delivered to the target at any distance closer than the minimum effective range of the typical munition; provide a blank interface in order to allow it to be configured with multiple thread specifications in order to mate with a near-universal array of munition/warhead/explosive vendors that are found on the battlefield, wherein these munitions/warheads/explosives are commonly known as NATO- or Eastern Bloc- munitions; or combinations thereof.

17. A dual-safe fuze for unmanned aerial system (UAS) drone applications comprising: an electrical power source configured to initiate a munition; circuitry positioned between the electrical power source and the munition for controlling the initiation of the munition via the electrical power source, the circuitry is configured to initiate the munition from an unmanned aerial vehicle (UAV), the circuitry positioned between the electrical power source and the munition is electrical circuitry and mechanical circuitry including: a nose-proximity fuze circuit, the nose-proximity fuze circuit is configured to detect a proximity to a target, wherein the nose-proximity fuze circuit is a normally open electrical circuit, when the nose-proximity fuze circuit comes in proximity of the target, the nose-proximity fuze circuit is configured to close to allow the connection of electrical power through the nose-proximity fuze circuit, wherein the nose-proximity fuze circuit is configured as a first-person view (FPV) circuit configured to allow a user to initiate the munition by flying the unmanned aerial vehicle (UAV) with the dual-safe fuze into the target kamikaze style, whereby, when the unmanned aerial vehicle (UAV) with the dual-safe fuze comes in proximity of the target, the dual-safe fuze is configured to initiate the munition; a body-proximity fuze circuit, the body-proximity fuze circuit has a body-proximity fuze sensor, the body-proximity fuze circuit is an electrical circuit which is normally open and is configured to not permit passage of electrical current or voltage until it is closed electrically, wherein when the body-proximity fuze sensor detects that the munition has been dropped, then the body-proximity fuze circuit is configured to close to allow the connection of electrical power through the body-proximity fuze circuit; a timer circuit, the timer circuit is configured to enable a user to set a time period in which the timer circuit is electrically open, thereby allowing the munition and the unmanned aerial vehicle (UAV) to be handled for the set time period before the timer circuit is electrically energized; the timer circuit is part of the body-proximity fuze circuit, wherein, the timer circuit is configured to enable the user to set the time period in which the timer circuit is electrically open, thereby allowing the munition and the unmanned aerial vehicle (UAV) to be handled for the set time period before the timer circuit is electrically energized before the normally open body-proximity fuze circuit is electrically closed enabling the potential of electricity to pass through the body-proximity fuze circuit; and a shear lanyard safety circuit, the shear lanyard safety circuit including: a normally closed lanyard switch; a safety lanyard, the safety lanyard is connected on one side to the unmanned aerial vehicle (UAV) and the other side of the safety lanyard is inserted into a sliding receptable in the lanyard switch for opening the normally closed lanyard switch and not allowing electrical current to flow therethrough; whereby, when the munition is dropped from the unmanned aerial vehicle (UAV), the other side of the safety lanyard is configured to pull out of the sliding receptacle for closing the normally closed lanyard switch; the shear lanyard safety circuit including a mission selector configured to allow the user to select the mission mode, the mission selector including selectable mission options including: FPV mission option for first-person view for flying the unmanned aerial vehicle with the munition into the target kamikaze style; DROP/LAN mission option for dropping the munition from the unmanned aerial vehicle (UAV) onto the target; DUAL mission option for providing the user the option of the FPV mission or the DROP/LAN mission; and the shear lanyard safety circuit further including a collapsible element in a nose assembly, the collapsible element in the nose assembly including a shear pin or other mechanical element that is configured to break on impact with the target, wherein when the nose assembly impacts the target and the shear pin or other mechanical element breaks, the collapsible element is configured to come into electrical contact with elements in the nose assembly to close the shear lanyard safety circuit and allow electrical energy to be applied to the shear lanyard safety circuit, wherein, when the shear pin or other mechanical element breaks and the collapsible element comes into electrical contact with the elements in the nose assembly, the collapsible element is configured to allow electrical connection from the electrical power source which applies electrical power through the nose-proximity sensor and circuit, through the body-proximity fuze circuit and the timer circuit, and then through the shear lanyard safety circuit either when the safety lanyard is pulled from its sliding receptacle or when the nose impact damages or pushes physically past the shear pin or other mechanical element and electrically connects the circuit, where once these conditions are met, the munition is able to be fully energized and can be initiated.

18. The dual-safe fuze for unmanned aerial system (UAS) drone applications of claim 17 being designed and configured for: arming and initiating munitions when carried by unmanned aerial system (UAS) or other vehicle, vessel, aircraft, or system guidance which do not have the natural accelerative loads or forces for initiating arming of the munitions, or which do not have the natural impacting forces and decelerative forces to begin the initiation process of the munition which is typically found on impacting the target at high velocity; enabling the use of traditional munitions/warheads/ explosives while employing a method to safely manipulate them during assembly to the unmanned aerial vehicle (UAV) or other vehicle that will be using them, and also permitting safe deployment for the mission; enabling the use of traditional munitions/warheads/explosives in non-traditional means, such as when mounted to a relatively slow moving UAS when a UAS speed is compared to a rocket, missile, mortar, grenade, rocket-propelled grenade, artillery munition, or other traditionally delivered munition; enabling the safe fitment of a munition to a UAS enabling the safe mounting and manipulation of the munition/warhead/explosive charge to a UAS, wherein a rocket system which would typically or traditionally deliver a munition/warhead/explosive in a manner which would put the munition beyond the range of the target, can be fitted to a UAS and delivered to the target at any distance closer than the minimum effective range of the typical munition; providing a blank interface in order to allow it to be configured with multiple thread specifications in order to mate with a near-universal array of munition/warhead/explosive vendors that are found on the battlefield, wherein these munitions/warheads/explosives are commonly known as NATO- or Eastern Bloc- munitions; or combinations thereof.

19. A munition for unmanned aerial system (UAS) drone applications comprising: a dual-safe fuze comprising: an electrical power source configured to initiate the munition; circuitry positioned between the electrical power source and the munition for controlling the initiation of the munition via the electrical power source, the circuitry is configured to initiate the munition from an unmanned aerial vehicle (UAV), the circuitry positioned between the electrical power source and the munition is electrical circuitry and mechanical circuitry including: a nose-proximity fuze circuit; a body-proximity fuze circuit; a shear lanyard safety circuit; and combinations thereof.

20. The munition for the unmanned aerial system (UAS) drone applications of claim 19, wherein: the nose-proximity fuze circuit, the nose-proximity fuze circuit is configured to detect a proximity to a target, wherein the nose-proximity fuze circuit is a normally open electrical circuit, when the nose-proximity fuze circuit comes in proximity of the target, the nose-proximity fuze circuit is configured to close to allow the connection of electrical power through the nose-proximity fuze circuit, wherein the nose-proximity fuze circuit is configured as a first-person view (FPV) circuit configured to allow a user to initiate the munition by flying the unmanned aerial vehicle (UAV) with the dual-safe fuze into the target kamikaze style, whereby, when the unmanned aerial vehicle (UAV) with the dual-safe fuze comes in proximity of the target, the dual-safe fuze is configured to initiate the munition; the body-proximity fuze circuit, the body-proximity fuze circuit has a body-proximity fuze sensor, the body-proximity fuze circuit is an electrical circuit which is normally open and is configured to not permit passage of electrical current or voltage until it is closed electrically, wherein when the body-proximity fuze sensor detects that the munition has been dropped, then the body-proximity fuze circuit is configured to close to allow the connection of electrical power through the body-proximity fuze circuit; a timer circuit, the timer circuit is configured to enable a user to set a time period in which the timer circuit is electrically open, thereby allowing the munition and the unmanned aerial vehicle (UAV) to be handled for the set time period before the timer circuit is electrically energized; the timer circuit is part of the body-proximity fuze circuit, wherein, the timer circuit is configured to enable the user to set the time period in which the timer circuit is electrically open, thereby allowing the munition and the unmanned aerial vehicle (UAV) to be handled for the set time period before the timer circuit is electrically energized before the normally open body-proximity fuze circuit is electrically closed enabling the potential of electricity to pass through the body-proximity fuze circuit; the shear lanyard safety circuit, the shear lanyard safety circuit including: a normally closed lanyard switch; a safety lanyard, the safety lanyard is connected on one side to the unmanned aerial vehicle (UAV) and the other side of the safety lanyard is inserted into a sliding receptable in the lanyard switch for opening the normally closed lanyard switch and not allowing electrical current to flow therethrough; whereby, when the munition is dropped from the unmanned aerial vehicle (UAV), the other side of the safety lanyard is configured to pull out of the sliding receptacle for closing the normally closed lanyard switch; the shear lanyard safety circuit including a mission selector configured to allow the user to select the mission mode, the mission selector including selectable mission options including: FPV mission option for first-person view for flying the unmanned aerial vehicle with the munition into the target kamikaze style; DROP/LAN mission option for dropping the munition from the unmanned aerial vehicle (UAV) onto the target; DUAL mission option for providing the user the option of the FPV mission or the DROP/LAN mission; the shear lanyard safety circuit further including a collapsible element in a nose assembly, the collapsible element in the nose assembly including a shear pin or other mechanical element that is configured to break on impact with the target, wherein when the nose assembly impacts the target and the shear pin or other mechanical element breaks, the collapsible element is configured to come into electrical contact with elements in the nose assembly to close the shear lanyard safety circuit and allow electrical energy to be applied to the shear lanyard safety circuit, wherein, when the shear pin or other mechanical element breaks and the collapsible element comes into electrical contact with the elements in the nose assembly, the collapsible element is configured to allow electrical connection from the electrical power source which applies electrical power through the nose-proximity sensor and circuit, through the body-proximity fuze circuit and the timer circuit, and then through the shear lanyard safety circuit either when the safety lanyard is pulled from its sliding receptacle or when the nose impact damages or pushes physically past the shear pin or other mechanical element and electrically connects the circuit, where once these conditions are met, the munition is able to be fully energized and can be initiated; wherein, the dual-safe fuze is designed and configured for: arming and initiating munitions when carried by unmanned aerial system (UAS) or other vehicle, vessel, aircraft, or system guidance which do not have the natural accelerative loads or forces for initiating arming of the munitions, or which do not have the natural impacting forces and decelerative forces to begin the initiation process of the munition which is typically found on impacting the target at high velocity; enabling the use of traditional munitions/warheads/ explosives while employing a method to safely manipulate them during assembly to the unmanned aerial vehicle (UAV) or other vehicle that will be using them, and also permitting safe deployment for the mission; enabling the use of traditional munitions/warheads/explosives in non-traditional means, such as when mounted to a relatively slow moving UAS when a UAS speed is compared to a rocket, missile, mortar, grenade, rocket-propelled grenade, artillery munition, or other traditionally delivered munition; enabling the safe fitment of a munition to a UAS enabling the safe mounting and manipulation of the munition/warhead/explosive charge to a UAS, wherein a rocket system which would typically or traditionally deliver a munition/warhead/explosive in a manner which would put the munition beyond the range of the target, can be fitted to a UAS and delivered to the target at any distance closer than the minimum effective range of the typical munition; providing a blank interface in order to allow it to be configured with multiple thread specifications in order to mate with a near-universal array of munition/warhead/explosive vendors that are found on the battlefield, wherein these munitions/warheads/explosives are commonly known as NATO- or Eastern Bloc- munitions; or combinations thereof.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0024] 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:

[0025] FIG. 1. is a side view of a UAS carrying an improvised munition that is taken from a rocket propelled grenade (RPG), or other like-type missile, and mounted in a field expedient manner (using ty-raps, or the like) according to the prior art;

[0026] FIG. 2. is a side view of a standard warhead body and fuze assembly according to the prior art threaded together in the traditional fashion;

[0027] FIG. 3. is a pictorial representation of a flowchart diagram of the circuitry of the disclosed dual-safe fuze for UAS drone applications according to select embodiments of the instant disclosure and a cross-sectional view of a standard warhead body and fuze assembly with the disclosed dual-safe fuze according to select embodiments of the instant disclosure;

[0028] FIG. 4 is a flowchart diagram of the circuitry for the disclosed dual-safe fuze for UAS drone applications according to select embodiments of the instant disclosure;

[0029] FIG. 5 is a flowchart diagram of the circuitry for the disclosed dual safe fuze for UAS drone applications according to select embodiments of the instant disclosure showing a first mission to drop a munition with time delay and shear lanyard;

[0030] FIG. 6 is a flowchart diagram of the circuitry for the disclosed dual-safe fuze for UAS drone applications according to select embodiments of the instant disclosure showing a second mission with FPV impact of the munition with time delay and nose proximity; and

[0031] FIG. 7 is a flowchart diagram of the circuitry for the disclosed dual-safe fuze for UAS drone applications according to select embodiments of the instant disclosure showing a third mission with FPV impact of the munition or optional drop munition with time delay, body proximity and nose proximity;

[0032] 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

[0033] Referring to FIG. 1, a side view of UAS 1 carrying improvised munition 2 that is taken from a rocket propelled grenade (RPG) or like missile and mounted in a field expedient manner via using ty-raps 3 is shown according to the prior art. Currently in these cases these improvised munitions 2 are adapted to the UAS or FPV drone 4 and then carefully re-wired with loose wire 5, electrical tape 6, and other methods to cause an explosion. These methods generally are not safe and do not feature or give consideration to return to base scenarios, safe munitions handling, or disarming the UAS or FPV drone in the event that this is necessary. The present disclosure of a dual-safe fuze 10 for UAS applications may address all of these scenarios and considerations.

[0034] Referring specifically to FIG. 2, a pictorial image of a standard warhead body 7 and fuze assembly 8 threaded together in the traditional fashion is shown according to the prior art. This image shows where a typical warhead body 7 would start and end, and then fuze assembly 8 would thread into the end of the warhead body 7. The fuze body 8 shown is a point detonation fuze with a safety that is armed by the high-G launch out of a rocket launcher. Absent this high-G event, the fuze 8 will not arm and will not detonate. This is fine for rocket and missile applications which have high-G launch events, but not suitable for UAS and FPV drone applications.

[0035] Referring now to FIGS. 3-7, 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.

[0036] Referring to FIGS. 3-7, the present disclosure may solve the aforementioned limitations of the currently available munitions for unmanned aerial systems (UAS) drone applications, by providing the disclosed dual-safe fuze 10 for unmanned aerial system (UAS) drone applications. Dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may generally include electrical power source 14 configured to initiate munition 16, and circuitry 18. Circuitry 18 may be positioned between electrical power source 14 and munition 16 for controlling the initiation of munition 16 via electrical power source 14. The circuitry may be configured to initiate munition 16 from an unmanned aerial vehicle (UAV). Electrical power source 14 (i.e., the electrical power source that initiates the primer/explosive/munition) may be any power source for providing electrical power 34 for initiating munition 16, including, but not limited to a capacitor, a battery, or the like. Circuitry 18 positioned between electrical power source 14 and munition 16 may be the novel feature of the disclosed dual-safe fuze 10 and may include various circuits, printed circuit boards (PCBs), switches, sensors, the like, etc. configured to initiate munition 16 from unmanned aerial vehicle (UAV) 20, or the like. Circuitry 18 of dua-safe fuze 10 positioned between electrical power source 14 and munition 16 may include electrical circuitry, mechanical circuitry, the like, and/or both. In select embodiments, the electrical and/or mechanical circuitry of circuitry 18 for dual-safe fuze 10 may include nose-proximity fuze circuit 22, body-proximity fuze circuit 24, shear lanyard safety circuit 26, the like, and/or combinations thereof. In select possibly preferred embodiments of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications, the electrical and/or mechanical circuitry of circuitry 18 for dual-safe fuze 10 may include nose-proximity fuze circuit 22, body-proximity fuze circuit 24, and shear lanyard safety circuit 26.

[0037] One feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that nose-proximity fuze circuit 22 can be configured to detect a proximity to a target. Nose-proximity fuze circuit 22 may be normally open electrical circuit 32. As a result, when nose-proximity fuze circuit 22 comes in proximity of the target (any desired or set proximity distance to the target), nose-proximity fuze circuit 22 may be configured to close to allow the connection of electrical power 34 through nose-proximity fuze circuit 22. In select embodiments, nose-proximity fuze circuit 22 may be configured as first-person view (FPV) circuit 36. First-person view (FPV) circuit 36 may be configured to allow a user to initiate munition 16 by flying the unmanned aerial vehicle (UAV) 20 with dual-safe fuze 10 into the target, also known as kamikaze style. Whereby, when unmanned aerial vehicle (UAV) 20 with dual-safe fuze 10 comes in proximity to the desired target, circuitry 18 with first-person view (FPV) circuit 36 of dual-safe fuze 10 is configured to initiate munition 16 thereby blowing up munition 16, unmanned aerial vehicle (UAV) 20 carrying munition 16, and the desired target.

[0038] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that body-proximity fuze circuit 24 may have body-proximity fuze sensor 40. Body-proximity fuze circuit may be configured to detect when munition 16 with dual-safe fuze 10 is in proximity to unmanned aerial vehicle (UAV) 20, or when munition 16 with dual-safe fuze 10 is not in proximity (any set or desired distance) to unmanned aerial vehicle (UAV) 20. Body-proximity fuze circuit 24 may be normally open electrical circuit 32 and may be configured to not permit passage of electrical current or voltage (i.e. electrical power 34) until it is closed electrically. Wherein, when body-proximity fuze sensor 40 detects that munition 16 has been dropped (is no longer in proximity to UAV 20), then body-proximity fuze circuit 24 may be configured to close to allow the connection of electrical power 34 through body-proximity fuze circuit 24.

[0039] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be the inclusion of timer circuit 42. Timer circuit 42 may be configured to enable a user to set time period 44 in which timer circuit 42 is electrically open, thereby allowing munition 16 and unmanned aerial vehicle (UAV) 20 to be safely handled for set time period 44 before timer circuit 42 is electrically energized. Time period 44 may be any desired time period, including, but not limited to 1 minute, 3 minutes, 25 minutes, or any other programmable time period 44. In select possibly preferred embodiments, as shown in the Figures, timer circuit 42 may be part of body-proximity fuze circuit 24. Wherein, timer circuit 42 may be configured to enable the user to set time period 44 in which timer circuit 42 is electrically open, thereby allowing munition 16 and unmanned aerial vehicle (UAV) 20 to be handled for the set time period 44 before timer circuit 42 is electrically energized before the normally open body-proximity fuze circuit 24 is electrically closed enabling the potential of electricity 34 to pass through body-proximity fuze circuit 24.

[0040] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that shear lanyard safety circuit 26 can include normally closed lanyard switch 46 with safety lanyard 48. Safety lanyard 48 may be connected on one side to unmanned aerial vehicle (UAV) 20. The other side of safety lanyard 48 may be inserted into sliding receptable (or the like) in lanyard switch 46 for opening normally closed lanyard switch 46 and not allowing electrical current 34 to flow therethrough. Whereby, when munition 16 is dropped from unmanned aerial vehicle (UAV) 20, the other side of safety lanyard 48 may be configured to pull out of sliding receptacle for closing normally closed lanyard switch 46. Lanyard switch 46 may also be removed by the operator of UAV 20 in the case where they want to use UAV 20 as an explosive charge to place it in a structure, or the operator may also pull safety lanyard 48 from sliding receptacle of lanyard switch 46 prior to takeoff and flight to minimize the safety timer for immediate effect on targets in close proximity of the operator.

[0041] Another feature of dual-safe fuze 10 for unmanned aerial systems (UAS) drove applications may be that shear lanyard safety circuit 26 may include mission selector 56. Mission selector 56 may be configured to allow the user to select mission mode 58. Mission selector 56 may include selectable mission options 59 including, but not limited to: FPV mission option 60 for first-person view for flying unmanned aerial vehicle (UAV) 20 with munition 16 into the target, like kamikaze style; DROP/LAN mission option 62 for dropping munition 16 from unmanned aerial vehicle (UAV) 20 onto the target; and DUAL mission option 64 for providing the user the option of the FPV mission and/or the DROP/LAN mission.

[0042] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that shear lanyard safety circuit 26 may further include collapsible element 66. Collapsible element 66 of shear lanyard safety circuit 26 may be in nose assembly 68. Collapsible element 66 in nose assembly 68 may include shear pin or other mechanical element 70 that can be configured to break on impact with the target. Shear pin or other mechanical element 70 may be any element configured to shear or break to effectuate electrical contact with the elements to initiate munition 16. As examples, and clearly not limited thereto, on a bomblet, shear pin or other mechanical element 16 may be one housing sliding over another (like two cup shaped housings nested but spaced) so that when one of the cup shaped housings hits the ground with their small end, the nesting distance decreases and then the electrical connection is made. Wherein, when nose assembly 68 impacts the target and shear pin or other mechanical element 70 breaks, collapsible element 66 may be configured to come into electrical contact with elements in nose assembly 68 to close shear lanyard safety circuit 26 and allow electrical energy 34 to be applied through shear lanyard safety circuit 26. As such, when shear pin or other mechanical element 70 may break and collapsible element 66 comes into electrical contact with the elements in nose assembly 68, collapsible element 66 may be configured to allow electrical connection from electrical power source 14 which applies electrical power 34 through nose-proximity fuze sensor and circuit 22, through body-proximity fuze circuit 24 and timer circuit 42, and then through shear lanyard safety circuit 26 either when safety lanyard 48 is pulled from its sliding receptacle or when nose impact damages or pushes physically past shear pin or other mechanical element 70 and electrically connects shear lanyard safety circuit 26. Wherein, once these conditions are met, munition 16 is able to be fully energized and can be initiated.

[0043] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that it can be designed and configured for arming and initiating munitions 16 when carried by unmanned aerial system (UAS) 20 or other vehicle, vessel, aircraft, or system guidance which do not have the natural accelerative loads or forces for initiating arming of standard munitions, or which do not have the natural impacting forces and decelerative forces to begin the initiation process of the standard munition which is typically found on impacting the target at high velocity.

[0044] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that it can be designed and configured to enable the use of traditional munitions/warheads/explosives while employing a method to safely manipulate them during assembly to the unmanned aerial vehicle (UAV) 20 or other vehicle that will be using them, and also permitting safe deployment for the mission.

[0045] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that it can be designed and configured to enable the use of traditional munitions/warheads/explosives in non-traditional means, such as when mounted to a relatively slow moving UAS 12 when a UAS speed is compared to a rocket, missile, mortar, grenade, rocket-propelled grenade, artillery munition, or other traditionally delivered munition.

[0046] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that it can be designed and configured to enable the safe fitment of munition 16 to UAS 12 enabling the safe mounting and manipulation of the munition/warhead/explosive charge to UAS 12. Wherein, a rocket system which would typically or traditionally deliver a munition/warhead/explosive in a manner which would put the munition beyond the range of the target, can be fitted to UAS 12 and delivered to the target at any distance closer than the minimum effective range of the typical munition. Traditional munitions have a minimum effective distance which can be thousands of meters from the launch point. But with dual safe-fuze 10 for unmanned aerial systems (UAS) drone applications, the effective distance can be essentially from the launch point outward to the maximum flight range of UAS 12.

[0047] Another feature of dual-safe fuze 10 for unmanned aerial system (UAS) drone applications may be that it can be designed and configured to provide a blank interface in order to allow it to be configured with multiple thread specifications in order to mate with a near-universal array of munition/warhead/explosive vendors that are found on the battlefield, wherein these munitions/warheads/explosives are commonly known as NATO- or Eastern Bloc- munitions.

[0048] In another aspect, the instant disclosure may embrace dual-safe fuze 10 for unmanned aerial system (UAS) drone applications in any of the embodiments and/or combinations of embodiments shown and/or described herein.

[0049] In another aspect, the instant disclosure may embrace munition 16 for unmanned aerial system (UAS) drone applications that include the disclosed dual-safe fuze 10 for unmanned aerial system (UAS) drone applications in any of the embodiments and/or combinations of embodiments shown and/or described herein.

[0050] Referring specifically to FIG. 3, a pictorial representation of dual-safe fuze 10 with circuitry 18 of is shown and how it gets packaged into the various replacement fuze assemblies and then is threaded onto the warhead body of munition 16. The switches (like for timer circuit 42 and/or mission selector 56) may be located on the outside of the body of dual-safe fuze 10. As shown in FIG. 3, munition 16 itself may be typically attached to UAS 12 or FPV drone 20.

[0051] Referring specifically to FIG. 4, a pictorial description flowchart showing the nature of circuitry 18 of dual-safe fuze 10 and the arming and disarming features which enable the munition 16 to function using the conventional munitions/warheads/explosives to the initiation point but controlling them using the new energetic circuit logic. In FPV or kamikaze mode, the nose-proximity fuze circuit 22 may be on nose assembly 68. As a result, as nose assembly 68 gests close to a target, the normally open electrical circuit 32 or relay of nose-proximity fuze circuit 22 may close (this may be similar in function to a car parking sensor).

[0052] Still referring specifically to FIG. 4, if munition 16 is not going to be dropped, or it is unclear what type of mission, then body-proximity fuze circuit 24 with timer circuit 42 (may be similar to other munitions, like Grayhill 0KST45-01B05N provided by Grayhill, Inc. of Illinois), the proximity fuze circuit 24 may be set for a time delay from launch of UAS 12. The time delay may keep the normally open electrical circuit 32 of body-proximity fuze circuit 24 open for the delay period selected and then apply power after the time selected. A proximity sensor (like a car parking sensor), placed against a feature on the UAV 20 would indicate that it has not been dropped.

[0053] Still referring specifically to FIG. 4, when munition 16 is dropped, the tether of safety lanyard 48 will remain attached to UAV 20. The removal of the tether of safety lanyard 48 from sliding receptacle completes the normally closed lanyard switch 46 on munition 16, allowing nose-proximity fuze circuit 22 clear access, electrically, to apply the charge from electrical power source 14 (like a capacitor, battery, or the like) to the explosive/primer/ignitor of munition 16 once the nose-proximity sensor gets in proximity of the target.

[0054] Still referring specifically to FIG. 4, body-proximity fuze circuit 24 may replace the traditional setback on a fuze on a rocket launch, since the UAV 20 of UAS 12 would not experience the Gs to initiate the fuze. If the mission ends with the UAV 20 of UAS 12 returning to base without dropping munition 16, the switch of body-proximity fuze circuit 24 can be set to OFF position. If not dropped, and returned to base, then shear lanyard safety circuit 26 would still be open, and thus, munition 16 would not be able to detonate. Returning the body-proximity fuze switch to OFF would double circuit protect munition 16 from receiving an electric charge even if the user stepped in front of the nose-proximity sensor (i.e. parking sensor) on nose assembly 68.

[0055] Referring specifically to FIG. 5, a pictorial description flowchart of circuitry 18 of dual-safe fuze 10 is shown as it would be fuzed for a first mission mode 58 to drop munition 16. In this first mission mode 58 to drop munition 16, normally open (N.O.) circuits 32 which enable munition 16 to be considered dual-safe in order to allow the user to arm and disarm munition 16 safely. As shown in FIG. 5, dual-safe fuze 10 has its switches set to a first mission mode 58 for dropping munition 16, with time delay of 25 minutes for time period 44 set on timer circuit 42, safety lanyard 48 of shear lanyard safety circuit 26 positioned in sliding receptacle, and mission selector 56 set in position on DROP/LAN mission option 62.

[0056] Referring specifically to FIG. 6, a pictorial description flowchart of circuitry 18 of dual-safe fuze 10 with circuitry 18 is shown as it would be fuzed for a second mission mode 58 to impact a target in FPV mode, and identifying the components, specifically the normally open (N.O.) electrical circuits 32 for the time delay circuit 42 as well as the shear lanyard safety circuit 26 which enable the munition to be considered dual-safe in order to allow the users to arm and disarm the munition safely in the event that the UAV 20 of UAS 12 or FPV drone returns to base without deploying its munition 16. As shown in FIG. 6, dual-safe fuze 10 has its switches set to a second mission mode 58 for FPV impact, with time delay of 25 minutes for time period 44 set on timer circuit 42, nose-proximity fuze circuit 22 normally open and ready to close upon proximity to target, and mission selector 56 set in position on FPV mission option 60.

[0057] Referring specifically to FIG. 7, a pictorial description flowchart of the fuzing of dual-safe fuze 10 with circuitry 18 is shown as it would be fuzed for a third mission mode 58 which would entail the possibility of both/either a dropping munition effort or a FPV impact to target mission, showing the placement and settings of the timers associated with the settings on dual-safe fuze 10 in order to effect a safe mission, and to allow the user to have a return to base scenario in the event that there is no need to discharge munition 16. As shown in FIG. 7, dual-safe fuze 10 has its switches set to third mission mode 58 for DUAL mission option 64, with time delay of 3 minutes for time period 44 set on timer circuit 42 and safety lanyard 48 of shear lanyard safety circuit 26 positioned in sliding receptacle.

[0058] In sum, the present disclosure relates to a novel method and a system for arming and initiating munitions when carried by unmanned aerial systems (UAS) 12, unmanned aerial vehicles (UAVs) 20, drones, or other vehicles, vessels, aircraft, or guidance systems which do not have the natural accelerative loads or forces to initiating arming of the munitions, or which do not have the natural impacting forces and decelerative forces to begin the initiation process of the munition which is typically found on impacting the target at high velocity. The FPV circuit 36 of the nose-proximity circuit 22, which is an electrical circuit 32 which is Normally Open (N.O.) in electrical circuit terms, therefore not permitting the passage of electrical current/voltage 34, and which when the FPV circuit 36 comes in the proximity of the target closes the N.O. electrical circuit to allow the connection of electrical power through circuitry 18. The body-proximity fuze (BPF) circuit 24 which is an electrical circuit which is Normally Open (N.O.) in electrical circuit terms , therefore not permitting the passage of electrical current/voltage 34 until it is closed electrically, and which when the body-proximity fuze sensor 40 detects that munition 16 has been dropped then the Normally Open (N.O.) circuit 32 is then electrically closed, to allow the connection of electrical power 34 through circuitry 18. Timer circuit 42 which may be part of body-proximity fuze circuit 24, may enable the user to set a timer in which the circuit is electrically Open and Safe thereby allowing the munition and the UAS 12 to be handled for a certain time period before the circuit is electrically energized, before the normally open electrical circuit 32 is electrically closed enabling the potential of electricity 34 to pass through body-proximity fuze circuit 24. Shear lanyard safety circuit 26 with mission selector 56 (FPV/Drop/Bot) may allow the user to select the mission mode 58, if known, that UAS 12 may be operating in during its mission. If in DROP/LAN mission option 62, mode where it is intending to drop munition 16 onto the target, safety lanyard 48, which is tied on one side to UAV drone 20 and on the other is pinned into sliding receptacle, in which case when it is in sliding receptacle, the circuit is electrically open, thereby not allowing electrical power to energize the circuit. Shear lanyard safety circuit 26 may also have as part of its construction and material specification collapsible element 66 in nose assembly 68 which, when it impacts the target, is able to break shear pin or other mechanical element 70 and move collapsible element 66 into electrical contact with elements in nose assembly 68, and this electrically closes the circuit and allows electrical energy 34 to be applied to the circuit, allowing electrical connection from electrical power source 14 (i.e., battery or capacitor or other energy source), which applies electrical power 34 through FPV sensor and circuit 36, through body-proximity fuze circuit 24 and timer circuit 42, and then through shear lanyard safety circuit 26 either when safety lanyard 48 is pulled from its sliding receptacle or when the nose impact damages or pushes physically past shear pin or other mechanical element 70 and electrically connects the circuit. Once these conditions are met, munition 16 may be able to be fully energized and can be detonated.

[0059] An adapter housing may be provided for dual-safe fuze 10 of the present invention, by which the traditional fuzing mechanism may be removed or modified and the present dual-safe fuze 10 may be connected to munition 16 to make it perform a new purpose on UAS 12 or the FPV UAS of the user. This adapter housing can be 3-D printed in metal or plastic and connected to munition 16 in the traditional manner, and is conceived to be agnostic to munition manufacturer, munition location/country/region of manufacture, and is adaptable to many types of munition. As such, a feature of the present disclosure may be that it can enable the use of traditional munitions/warheads/explosives in non-traditional means, such as when mounted to a relatively slow moving UAS when a UAS speed is compared to a rocket, missile, mortar, grenade, rocket- propelled grenade, artillery munition, or other traditionally delivered munition. Another feature of the present disclosure may be that it enables the safe fitment of a munition to a UAS enabling the safe mounting and manipulation of the munition/warhead/explosive charge to a UAS. In this way, a rocket system which would typically or traditionally deliver a munition/warhead/explosive in a manner which would put the munition beyond the range of the target, can be fitted to a UAS and delivered to the target at any distance closer than the minimum effective range of the typical munition. Another feature of the present disclosure may be that it has been designed with a blank interface in order to allow it to be configured with multiple thread specifications in order to mate with a near- universal array of munition/warhead/explosive vendors that are found on the battlefield. These munitions/warheads/explosives are commonly known as NATO- or Eastern Bloc- munitions.

[0060] 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.

[0061] 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 limitation. Accordingly, the present disclosure is not limited to the specific embodiments illustrated herein but is limited only by the following claims.