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.

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.