Patent Publication Number: US-11650036-B2

Title: Payload platform for unmanned vehicles

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     The present application is a nonprovisional application of, and claims the benefit of, U.S. Provisional Application 63/220,700 entitled “Payload Platform For Unmanned Vehicles” filed on Jul. 12, 2021, the contents of which is incorporated by reference. 
    
    
     BACKGROUND 
     The present invention relates generally to a system and method for delivering a weapons system with an unmanned vehicle, more specifically, to a system and method for mounting and deploying a weapons system autonomous or semi-autonomous vehicles. 
     Autonomous or semi-autonomous vehicles, also referred to as unmanned aerial vehicles (UAVs), remotely piloted aircraft (RPA) and autonomous ground vehicle (UGVs), are a small, typically portable, vehicle that have found a variety of uses in commercial and military application, such as but not limited to surveying, surveillance, aerial photography, and package delivery. A UAV typically consists of a body, a device such as a camera, a navigation system, and a propulsion system. The propulsion system usually consists of a plurality of rotors (e.g. four) that generate lift in the same manner as a helicopter. The vehicle is launched and is either guided by an operator or follows a path using navigation techniques to an end location. The vehicle then performs a task (e.g. photographs an area) and then returns to a landing site. In the case of UAV&#39;s and RPA&#39;s that include ordnance, the vehicle was expendable and did not return from the mission. 
     Accordingly, while existing autonomous or semi-autonomous vehicles are suitable for their intended purposes the need to improvement remains, particularly in providing a weapons platform having the features described herein. 
     SUMMARY 
     Embodiments include a system that is mountable to an unmanned vehicle. The system includes an attachment plate configured to couple to the unmanned vehicle, the attachment plate having a first feature. A control module is configured to removably couple to the attachment plate, the control module having one or more processors and a power source, the control module having a pin arranged to move from a first position to a second position when the control module is coupled to the attachment plate, the one or more processors being energized when the pin is moved from the first position to the second position. A payload having an energetic element is provided, the payload being coupled to the control module. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the pin being removable from the control module in the second position. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the pin further having a key FOB, the key FOB being configured to operably couple to a control device, the control device being remote from the control module. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the control module further having a communications circuit that is operably coupled to the one or more processors and is coupled to communicate with the control device. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the control device being coupled to communicate with the communications circuit in response to the key FOB being operably coupled to the control device. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the control module further having a first static arming inhibit element operably coupled to the one or more processors, the one or more processors being configures to close the first static arming inhibit element in response to a first signal from the control device. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the control module further having a solenoid operably coupled to the one or more processors and the energy source, the solenoid having a plunger that is movable from an extended position to a retracted position, the plunger being coupled to a second feature on the attachment plate, the control module being decoupled from the attachment plate when the plunger is in the retracted position. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the one or more processors being further configured to initiate a timer in response to the decoupling of the control module from the attachment plate. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the one or more processors being further configured to close a dynamic arming inhibit element in response to an expiration of the timer, the dynamic arming inhibit element being electrically coupled to the energy source. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the control module having a high voltage capacitor operably coupled to the dynamic arming inhibit element and to a low energy exploding foil initiator, the low energy exploding foil initiator being electrically coupled between the dynamic arming inhibit and the energetic element. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the one or more processors being further configured to close a firing switch in response to a third signal from the control device, the firing switch being electrically coupled between the high voltage capacitor and the low energy exploding foil initiator. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the system may include the energetic element being one of fragmentary rounds, high explosives, thermite, or shaped charges. 
     Further embodiments include a method of deploying a payload from an unmanned vehicle. The method includes coupling an attachment plate to the drone, the attachment plate having a first feature. A control module is coupled to the attachment plate, the control module having a pin. The pin is moved from a first position to a second position with the first feature in response to attaching the control module to the attachment plate. One or more processors are energized with an energy source when the pin is in the second position. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the method may include removing the pin from the control module when the pin is in the second position; and coupling a key FOB on the pin to a control device. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the method may include the control device being coupled to communicate with a communications circuit in the control module when the key FOB is coupled to the control device, the communications circuit being operably coupled to the one or more processors. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the method may include transmitting a first signal from the control device to the communications circuit and closing a first static arming inhibit element in response to receiving the first signal. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the method may include transmitting a second signal from the control device to the communications circuit; retracting a solenoid plunger disposed in the control module in response to receiving the second signal; decoupling the control module from the attachment plate in response to retracting the solenoid plunger; and initiating a timer in response to decoupling the control module. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the method may include closing a dynamic arming inhibit element and flowing electrical power from the energy source to a high voltage capacitor in response to expiration of the timer; transmitting a third signal from the control device to the communications circuit; and closing a firing switch in response to receiving the third signal. 
     In addition to one or more of the features described herein, or as an alternative, further embodiments of the method may include activating an energetic element with a low energy exploding foil initiator in response to closing the firing switch. 
     Additional features are realized through the techniques of the present invention. Other embodiments and aspects of the invention are described in detail herein and are considered a part of the claimed invention. For a better understanding of the invention with the features, refer to the description and to the drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The forgoing and other features of embodiments of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which: 
         FIG.  1    depicts a block diagram of an autonomous or semi-autonomous vehicle having a weapons platform in accordance with an embodiment of this disclosure; 
         FIG.  2    depicts a block diagram of a controller for autonomous or semi-autonomous vehicle in accordance with an embodiment of this disclosure; 
         FIG.  3    is a front view of an autonomous or semi-autonomous vehicle having a weapons platform in accordance with an embodiment of this disclosure; 
         FIG.  4 A  is a perspective view of an autonomous or semi-autonomous vehicle with a payload being released from the platform in accordance with an embodiment of this disclosure; 
         FIG.  4 B  is a partial perspective view of the vehicle of  FIG.  4 A  with a FOB key inserted in the control module; 
         FIG.  4 C  is a partial perspective view of the vehicle of  FIG.  4 B  with the FOB key being removed from the control module; 
         FIG.  5 A  is a partially unassembled perspective view of the weapons platform of  FIG.  3    in accordance with an embodiment of this disclosure; 
         FIG.  5 B  is a perspective view of the weapons platform of  FIG.  5 A  with the control module in the process of being assembled to the energetic module; 
         FIG.  6    is a perspective view, partially in section, of the weapons platform of  FIG.  5    in accordance with an embodiment of this disclosure; 
         FIG.  7    is a block diagram of the arming system for the weapons platform of  FIG.  5    in accordance with an embodiment of this disclosure; 
         FIG.  8    is a perspective view of hand held controller for use with the weapons platform in accordance with an embodiment; 
         FIG.  9 A  is a front perspective view of a weapons platform in accordance with another embodiment; 
         FIG.  9 B  is a side view of the weapons platform of  FIG.  9 A ; 
         FIG.  9 C  is rear perspective view of the weapons platform of  FIG.  9 A ; 
         FIG.  10    is a side view of a weapons platform in accordance with yet another embodiment; and 
         FIG.  11 A  and  FIG.  11 B  are perspective and front views of a hand held controller for use with a weapons platform of  FIG.  1   ,  FIG.  3   ,  FIG.  9 A  and  FIG.  10    in accordance with an embodiment. 
     
    
    
     DETAILED DESCRIPTION 
     Embodiments of the present disclosure are directed to a system for mounting a weapons system to an unmanned vehicle. Embodiments further include a system that is mountable to different models of unmanned vehicles. Still further embodiments provide a system that operates independently from the unmanned vehicle and does not draw power, telemetry, or data from the unmanned vehicle. 
     It should be appreciated that while embodiments herein refer to an unmanned aerial vehicle (UAV), this is for example purposes and the claims should not be so limited. In other embodiments, the unmanned vehicle may be an RPA, an UGV, or a surface or sub-surface watercraft for example. Further, the unmanned vehicle may be autonomous, semi-autonomous, or operator controlled. 
     Referring now to  FIG.  1   , an embodiment is shown of an autonomous drone  20  or unmanned aerial vehicle. As used herein, the term “drone” refers to an aerial, ground, or water vehicle capable to operating autonomously or semi-autonomously from a human operator to perform a predetermined function, such as deliver a payload or package for example. In some embodiments, the drone  20  may also be operated by the human operator. The drone  20  includes a fuselage  22  that supports at least one thrust device  24 . In an embodiment, the drone  20  includes a plurality of thrust devices  24 A,  24 B, such as four thrust devices arranged about the periphery of the fuselage  22 . In an embodiment, the thrust devices  24  include propeller member that rotates to produce thrust. The thrust devices  24  may be configurable to provide both lift (vertical thrust) and lateral thrust (horizontal thrust). The vertical and horizontal components of the thrust allow the changing of the altitude, lateral movement and orientation (attitude) of the drone  20 . 
     In the exemplary embodiment, the fuselage  22  and thrust devices  24  are sized and configured to carry a system  30  having a payload  26 . The payload  26  being releasably coupled from the fuselage  22  during operation. As will be discussed in more detail herein, the system  30  further includes a payload control module  32  and an attachment plate  34 . The attachment plate  34  includes a mechanical connection  28  that fixedly and removable couples the plate to the drone  20 . The mechanical connection  28  may include a means, such as multiple bolt hole patterns for example, that allows the plate  34  to be coupled to a variety of different unmanned vehicles. The mechanical connection  28  further allows for the removal of the system  30 , such as in the event that either the drone  20  or the system  30  is damaged. As discussed in more detail herein, the attachment plate further includes one or more features that allow the payload to be at least partially armed and allow the payload to be releasably coupled to the attachment plate  34 . 
     The drone  20  includes a controller  38  having a processing circuit. The controller  38  may include processors that are responsive to operation control methods embodied in application code, such as for navigating the drone  20 . These methods are embodied in computer instructions written to be executed by the processor, such as in the form of software. The controller  38  is coupled transmit and receive signals from the thrust devices  24 , the transfer member  34  and the coupling device  36  to determine and change their operational states (e.g. extend transfer member  34 , change polarity of coupling device  36 , adjust lift from thrust devices  24 ). The controller  38  may further be coupled to one or more sensor devices that enable to the controller to determine the position, orientation and altitude of the drone  20 . In an embodiment, these sensors may include an altimeter  40 , a gyroscope or accelerometers  42  or a global positioning satellite (GPS) system  44 . 
       FIG.  2    illustrates a block diagram of a controller  38  for use in implementing a system or method according to some embodiments, such as the control module  32  for example. The systems and methods described herein may be implemented in hardware, software (e.g., firmware), or a combination thereof. In some embodiments, the methods described may be implemented, at least in part, in hardware and may be part of the microprocessor of a special or general-purpose controller  38 , such as a personal computer, workstation, minicomputer, or mainframe computer. 
     In some embodiments, as shown in  FIG.  2   , the controller  38  includes a processor  105 , memory  110  coupled to a memory controller  115 , and one or more input devices  145  and/or output devices  140 , such as peripheral or control devices, that are communicatively coupled via a local I/O controller  135 . These devices  140  and  145  may include, for example, battery sensors, position sensors (altimeter  40 , accelerometer  42 , GPS  44 ), indicator/identification lights and the like. Input devices such as a conventional keyboard  150  and mouse  155  may be coupled to the I/O controller  135  when the drone is docked to allow personnel to service or input information. The I/O controller  135  may be, for example, one or more buses or other wired or wireless connections, as are known in the art. The I/O controller  135  may have additional elements, which are omitted for simplicity, such as controllers, buffers (caches), drivers, repeaters, and receivers, to enable communications. 
     The I/O devices  140 ,  145  may further include devices that communicate both inputs and outputs, for instance disk and tape storage, a network interface card (NIC) or modulator/demodulator (for accessing other files, devices, systems, or a network), a radio frequency (RF) or other transceiver/communications-circuit, a telephonic interface, a bridge, a router, and the like. 
     The processor  105  is a hardware device for executing hardware instructions or software, particularly those stored in memory  110 . The processor  105  may be a custom made or commercially available processor, a central processing unit (CPU), an auxiliary processor among several processors associated with the controller  38 , a semiconductor based microprocessor (in the form of a microchip or chip set), a macroprocessor, or other device for executing instructions. The processor  105  includes a cache  170 , which may include, but is not limited to, an instruction cache to speed up executable instruction fetch, a data cache to speed up data fetch and store, and a translation lookaside buffer (TLB) used to speed up virtual-to-physical address translation for both executable instructions and data. The cache  170  may be organized as a hierarchy of more cache levels (L1, L2, etc.). 
     The memory  110  may include one or combinations of volatile memory elements (e.g., random access memory, RAM, such as DRAM, SRAM, SDRAM, etc.) and nonvolatile memory elements (e.g., ROM, erasable programmable read only memory (EPROM), electronically erasable programmable read only memory (EEPROM), programmable read only memory (PROM), tape, compact disc read only memory (CD-ROM), disk, diskette, cartridge, cassette or the like, etc.). Moreover, the memory  110  may incorporate electronic, magnetic, optical, or other types of storage media. Note that the memory  110  may have a distributed architecture, where various components are situated remote from one another but may be accessed by the processor  105 . 
     The instructions in memory  110  may include one or more separate programs, each of which comprises an ordered listing of executable instructions for implementing logical functions. In the example of  FIG.  2   , the instructions in the memory  110  include a suitable operating system (OS)  111 . The operating system  111  essentially may control the execution of other computer programs and provides scheduling, input-output control, file and data management, memory management, and communication control and related services. 
     Additional data, including, for example, instructions for the processor  105  or other retrievable information, may be stored in storage  120 , which may be a storage device such as a hard disk drive or solid state drive. The stored instructions in memory  110  or in storage  120  may include those enabling the processor to execute one or more aspects of the systems and methods of this disclosure. 
     The controller  38  may further include a display controller  125  coupled to a user interface or display  130 . In some embodiments, the display  130  may be an LCD screen. In other embodiments, the display  130  may include a plurality of LED status lights (e.g. visual indicator  558 ,  FIG.  5   ). In some embodiments, the controller  38  may further include a network interface  160  for coupling to a network  165 . The network  165  may be an IP-based network for communication between the controller  38  and an external server, client and the like via a broadband connection. In an embodiment, the network  165  may be a satellite network. The network  165  transmits and receives data between the controller  38  and external systems. In an embodiment, the external system may be another aerial drone or a drone docking system. In some embodiments, the network  165  may be a managed IP network administered by a service provider. The network  165  may be implemented in a wireless fashion, e.g., using wireless protocols and technologies, such as WiFi, WiMax, cellular, satellite, etc. The network  165  may also be a packet-switched network such as a local area network, wide area network, metropolitan area network, the Internet, or other similar type of network environment. The network  165  may be a fixed wireless network, a wireless local area network (LAN), a wireless wide area network (WAN) a personal area network (PAN), a virtual private network (VPN), intranet or other suitable network system and may include equipment for receiving and transmitting signals. 
     Referring now to  FIG.  3    and  FIGS.  4 A- 4 C , an embodiment is shown of a drone  320  that includes a weapons system  330 . In an embodiment, the drone  320  may be a Pegasus unmanned aerial vehicle manufactured by Robotic Research LLC of Clarksburg, Md., USA. The drone  320  is substantially similar to the drone  20  of  FIG.  1   . In an embodiment, the drone  320  is configured to switch between aerial vehicle and ground vehicle operations. The drone  320  includes a fuselage  322  and a plurality of thrust devices  324 . 
     In an embodiment, the weapons system  330  includes an attachment plate  334 . In an embodiment that system  330  includes a single attachment plate  334  that multiple control modules  332  and multiple energetic modules  326  are attached. As used herein, the term “payload module” refers to an assembly consisting of a control module and an energetic module. In another embodiment multiple attachment plates  334  are provided and each attachment plate  334  has an associated control module  332  and payload  326 . In the example embodiment, while the weapons system  330  is coupled to the drone  320 , the weapons system  330  is functionally independent from the drone  320 . In other words, there is no power, communications, or data transfer between the drone  320  and the control module  332  or energetic module  326 . It should be appreciated that this independence allows the weapons system  330  to be coupled or redeployed to different drones without needing to reconfigure or alter the weapons system  330 . As will be discussed in more detail herein, when the payload module is coupled to the attachment plate  334 , a key FOB  377  is disengaged from the control module and may be removed by the operator ( FIG.  4 C ). In an embodiment, when the key FOB  377  is coupled to the control module, the energetic module  326  cannot be activated. 
     Referring now to  FIG.  5 A ,  FIG.  5 B , and  FIG.  6    an embodiment is shown of the payload module  530 . In this embodiment, the payload module  530  includes a energetic module  526  and a control module  532 . The energetic module  526  includes a housing  540 . In an embodiment, the housing  540  has a generally cuboid shape and contains an energetic  541 , such as but not limited to polymer-bonded explosive (PBX) or thermite for example. Arranged on at least one end  542  is a latch  544  that interconnects and fixes the housing  540  to the control module  532 . The latch  544  includes a slidable lever that engages a locking element  550  in the control module  532 . It should be appreciated that in other embodiments, other types of locking elements  550  may be used. In an embodiment, the housing  540  includes a cover  546  having a coupling element  548 . In an embodiment, the coupling element  548  slidably couple the housing  526  to the control module  532  ( FIG.  5 B ). In an embodiment, the coupling element  548  has a dovetail shape. In an embodiment, the energetic module  526  is removably coupled to the control module  532 , which allows for different energetics to be coupled to the payload module  530 . To replace the energetic module  526 , the operator disengages the interlock  544  from the locking element  550  and then slides the housing  540  relative to the control module  532  to remove the energetic module  526 . 
     The control module  532  includes a housing  552  that includes a coupling element  554  that cooperates with the coupling element  548 . Disposed on the end  556 , adjacent to the locking element  550  is a visual indicator  558 . The visual indicator  558  is configured to display a different color or symbol based on the operational setting (e.g. safe or armed). 
     Disposed within the housing  552  is an electronic safe and arm circuit  560 , a communications circuit  562 , and a mechanical release assembly  564 . In an embodiment, the mechanical release assembly  564  includes a solenoid or servo  566  that engages a pin on the attachment plate  334  ( FIG.  4   ). When energy is applied to the solenoid  566 , the solenoid retracts and releases its connection on the control module  532  and energetic module  526 . 
     It should be appreciated that since the payload module  530  includes energetics  541 , a safety architecture is incorporated into the assembly to reduce the risk of inadvertent activation of the energetic  541 . In an embodiment, the operation of the payload module  530  is guided by Mil Spec MI-STD-1911, which provides for two independent inhibiting mechanisms to prevent unintentional arming of the energetic. As such the arming inhibits are removed by independent and sequential actions. 
     To accomplish this standard, two elements are used to interlock the arming of the energetic. First a feature on the attachment plate  334  removes a pin  760  from the an energetic safety interlock  762  ( FIG.  7   ) when the payload module  530  is attached to the attachment plate. In an embodiment, the arrangement is configured such that a safety pin  760  can only be removed and replaced when the payload module  530  is attached to the attachment plate  334 . Removal of the safety pin  760  closes switches  764  to electrically couple the internal circuitry  700  to battery  766 . In other embodiments, the feature on the attachment plate  334  engages a switch that disengages an interlock that holds/prevents-removal of the pin  760 . 
     The payload module  530  is secured to the drone  20  by the solenoid  566 . When energy is applied to the solenoid  566 , a solenoid plunger moves from an extended position to a retracted position to release the control module and payload assembly from the attachment plate. When the solenoid is not energized, the plunger retains the payload  526  to the drone  20 . In an embodiment, the solenoid  566  is momentarily energized when the energetic payload is attached. Power is removed when the safety pin  760  is removed or disengaged. When an operator sends the command to release the energetic, such as via communications circuit  562  for example, the solenoid  566  is once again temporarily energized causing the solenoid  566  to retract and allow the control module and payload  526  to decouple from the attachment plate and move away from the drone  20  under the influence of gravity. In an embodiment, once the payload module  530  separates from the attachment plate, the solenoid  566  is deenergized to avoid draining the energy-source/conserve-energy. 
     In an embodiment, the arming circuitry  700  includes a first portion that provides safety logic  768  and a second portion  770  that generates and transfers a high-voltage fire pulse to initiate a low energy exploding foil initiator (LEEFI)  774  to activate the energetic  741 . It should be appreciated that while embodiments herein may refer to the use of a LEEFI to activate the energetic, this is for example purposes and the claims should not be so limited. In other embodiments, other components may be used, such as but not limited to an exploding bridge wire (EBW) detonator or a hot bridge wire (HBW) detonator for example. Two-way radio frequency circuits  772  are provided to allow the operator to initiate operation. In an embodiment, the power is provided by a replaceable and rechargeable battery  766 . 
     The circuit  700  is energized when the pin  760  is removed and communication is established when the key FOB  777  is inserted into an operator controller  800  ( FIG.  8   ). In an embodiment, the key FOB  777  includes a connector, such as a USB connector that couples with the operator controller  800 . The key FOB  777  when coupled with the operator controller  800  allows the operator controller  800  to transmit coded signals to the control module which the key FOB  777  is associated. In an embodiment, when communications are established, the circuit  700  performs a power-on test to verify system readiness to perform a mission. 
     It should be appreciated that in the embodiment of  FIG.  8   , the controller  800  includes two sets of controls that allow the controller to remove inhibits (e.g. arm), release the system  330 , and fire/activate the payload  326 . Two sets of controls are provided to allow the control of the two systems  330  to be operated independently. 
     In an embodiment, two signals from the operator are used to control and arm the energetic module  526 . A first coded (e.g. encrypted) signal is sent by the operator when the drone  20  has reached a safe separation distance. This action closes one of the static arming inhibit switches  778 A. The second coded signal is the command to release the payload module  530  and closes the other static arming inhibit switch  778 B. A timer within control logic gives the drone  20  the opportunity to move from the area before automatically closing the dynamic arming inhibit  780  (in response to the expiration of the timer), which then charges the high voltage firing capacitor  782  which receives electrical power from a high voltage converter  784 . At this time the energetic  741  is fully armed. In an embodiment, once the second coded signal is received, the solenoid is deenergized to conserve energy. A third (final) signal from the operator is used to operate the firing switch  786 , which leads to detonation of the energetic  741  by the LEEFI  774 . The circuit  700  will sterilize the payload  526  if the energetic  741  is not commanded to detonate within a predetermined amount of time, or when power level in the battery  766  drops below a predetermined level. 
     In an embodiment, until the point where the second signal is transmitted and received, the energetic may be returned to a safe condition and the drone  20  moved back to the operator. In an embodiment, the operator returns the energetic to a safe condition by cancelling the first signal (safe separation distance), which opens one of the static arming inhibit switches  778 . When the drone  20  lands adjacent the operator, the operator removes the key FOB  777  from the controller and replaces the safety pin  760  to disconnect the battery  766  from the circuit  700 . 
     It should be appreciated that material used in the energetic  741  may include fragmentary rounds, high explosives, thermite, shaped charges, or non-lethal effects such as sound, pyrotechnics, smoke, or other disorientation or distraction effects. 
     In an embodiment, the operation of the payload  526  is controlled by a handheld remote device. The handheld device is configured to encode the payload  526  over an encrypted channel. In an embodiment, the handheld device is separate from the drone  20  controller. It should be appreciated that this provides advantages in allowing the operator the flexibility to move the system  30  between drones  20 . 
     Referring now to  FIGS.  9 A- 9 C , another embodiment of the system  930 . The system  930  includes a control module  932 , a payload  926 , and a mounting plate  934 . The control module  932  includes a pad  933  that is disposed on a top surface  935 . The pad  933  may be made from an open or closed cell foam material for example. The pad  933  is disposed between the top surface  935  and the bottom surface of the plate  934  to reduce the transfer of vibrations from the drone and the control module  932 . The pad  933  includes an opening  935  that is sized to receive the pin  928  on plate  934 . 
     In this embodiment, the control module  932  includes an antenna  970 . In an embodiment, the antenna  970  is rotationally coupled to the side  953  of the housing  952 . Being able to rotate the antenna  970  provides advantages in allowing the antenna to be repositioned depending on the fuselage geometry of the drone and the payload. On a first end  955 , a key FOB  977  is coupled via a universal serial bus (USB) port. Similar to the FOB  377 , the FOB  977  allows the control module  932  to pair for communications with a handheld controller used by the operator. 
     On an opposite end  956 , a separate mechanical interlock pin  960  extends outward from the housing  952 . In an embodiment, the interlock pin  960  is retained to the housing  952  by a detent mechanism  961 . As discussed in more detail herein, in an embodiment the removal of the interlock pin activates a timer the initiates selected operating components of the control circuitry (e.g. internal circuitry  700 ). Also disposed on the end  956  is an actuator  963 . The actuator  963  is electrically coupled to operate an internal servo or solenoid (e.g. servo  566 ). In an embodiment, the activation of the actuator  963  causes a movement of a cam that allows the pin  928  to be received by the control module  932 . When the pin  928  is inserted, and the actuator  963  is released, the cam engages the pin  928  to mechanically couple the control module  932  to the plate  934 . Arranged adjacent the actuator  963  and the interlock pin  960  is a visual indicator  958 , such as an light emitting diode (LED) for example. In an embodiment, the indicator  958  will emit light of a predetermined color to indicate to the operator the state of the control module  932 . For example, the emitting of a green light may indicate that the pin  960  is removed and the operator should move to a predetermined distance away before a timer expires. The emitting of a yellow light may indicate that the mechanical interlock has been removed and portions of the control circuit are active. 
     In an embodiment, the end  956  further includes a feature that cooperates with a latch member  944  of the payload  926 . When the latch  944  engages the feature, the payload  926  is mechanically coupled to the control module  932  (e.g. the payload will not slide relative to the control module). 
     In this embodiment, the plate  934  includes a planar portion  935  having a plurality of holes  937  that are arranged and sized to allow the plate  934  to mount to a variety of different drone/vehicles. Extending from the planar portion  934  are a pair of ribs  939 . The ribs  939  are arranged on either side of the pin  928 . The ribs  939  prevent side to side movement of the control module  932 . 
     Referring now to  FIG.  10   , an embodiment is shown of a system  1030  having a mounting plate  1034  that is coupled to a vehicle, such as a drone  120 . The system  1030  further includes a control module  1032  and a plurality of payloads  1026 A,  1026 B,  1026 C. In an embodiment, the control module  1032  is the same as that described herein with respect to control modules  332 ,  532 ,  932 . It should be appreciated that in some situations, more than one type of payload may be desired to accomplish the desired goal. For example, where an energetic payload is being delivered, more than one type of energetic may be used to neutralize a target. Where the payload is delivering an article such as medicine or medical supplies, more than one type of medical supply may be desired. In this embodiment, the top most payload  1026 A is removably coupled to the control module  1032  in a similar manner as described herein and is fixed in place by a clip or fastener  1044 . The subsequent payloads  1026 B,  1026 C are then coupled in series to the first payload  1026 A in a similar manner (e.g. slidably engages the previous payload and is secured with a clip). 
     In another embodiment, the control module  1032  may be configured to selectively uncouple the payloads  1026 A,  1026 B,  1026 C to place the payloads at multiple target locations. In this embodiment, each of the payloads  1026 A,  1026 B,  1026 C may include control passthrough that allows signals from the control module  1032  to be transmitted to the desired payload. 
     Referring now to  FIG.  11 A,  11 B , another operator controller  1100  is shown for use with any of the systems  830 ,  530 ,  930 ,  1030  described herein. In this embodiment, the controller  1100 . The controller  1100  includes a housing  1102  that includes a port (not shown) configured to receive a FOB, such as FOB  777 ,  977  for example, that allows one or more processors or circuits within the controller  1100  to communicate with the system  830 ,  530 ,  930 ,  1030 . The controller  1100  further includes an antenna  1104  that is configured transmit signals to, and receive signals from the system  830 ,  530 ,  930 ,  1030 . The controller  1100  includes an actuator  1106 , such as a slide switch for example, that turns-on or activates the controller  1100 . In an embodiment, an indicator, such as LED  1108 , emits light when the controller  1100  is activated. 
     Typically the first step in setting up the controller  1100  is to pair the controller with the system  830 ,  530 ,  930 ,  1030 . This is done by installing the USB FOB  777 ,  977  in the port and then depressing an actuator, such as button  1110  for example, for a predetermined amount of time (e.g. 5 seconds) until an indicator, such as LED  1112  starts flashing. In an embodiment, the operator then releases and immediately depresses the button  1110  again. At this point, if successful, the controller  1100  is paired with the USB. In an embodiment, the power LED  1108  emits green light when the pairing is completed. In an embodiment, any other LED&#39;s on the controller  1100  will flash until the controller is paired with the control module  332 ,  532 ,  932 ,  1032 . 
     In an embodiment, the FOB  777 ,  977  is removed from the controller  1100  and then installed on the control module  332 ,  532 ,  932 ,  1032 . It should be appreciated that at the point when the FOB  777 ,  977  is installed, there is only power to the servo motor or solenoid (e.g. no electrical power to the firing circuit). The servo motor or solenoid only draws power when the actuator on the control module, such as actuator  963  for example, is actuated. The actuating of the actuator  963  allows the control module  332 ,  532 ,  932 ,  1032  to be installed-on/coupled-to the vehicle/drone. In an embodiment, the FOB  777 ,  977  remains coupled to the control module  332 ,  532 ,  932 ,  1032  for the duration of the mission. Where the payload includes an energetic, the FOB  777 ,  977  is either destroyed or damaged to render it inoperable upon activation of the energetic. 
     With the system  830 ,  530 ,  930 ,  1030  installed on the drone, the operator removes the pin  760 ,  960 . In an embodiment, this activates a first predetermined timer (e.g. 30 seconds), that allows the operator to move away from the drone by a predetermined distance. When the time expires, the indicator  958  emits light, such as yellow light for example, to provide a visual indication that power is available to the next level of safety inhibit (e.g. static arming inhibit  778 A,  778 B). In an embodiment, the removal of the pin  760 ,  960  further initiates a second predetermined timer (e.g. 60 minutes). If the second timer expires, all voltage to the high voltage converter  784  is removed/turned-off. In an embodiment, when the second timer expired, power to the servo motor or solenoid remains so that the system  830 ,  530 ,  930 ,  1030  may be removed from the drone. 
     In an embodiment, if the pin  760 ,  960  is reinserted into the control module  332 ,  532 ,  932 ,  1032 , electrical power is removed from the static arming inhibit.  778 A,  778 B and the first and second timers are reset. 
     With the pin  760 ,  960  removed, the control module  332 ,  532 ,  932 ,  1032  established communication with the controller  1100  based at least in part on data stored on the FOB key  777 ,  977 . In an embodiment, when communication is established between the controller  1100  and the control module  332 ,  532 ,  932 ,  1032 , the indicators/LED&#39;s on the controller will stop blinking/flashing. 
     During operation, the operator will typically move the drone a predetermined distance away and then move the arming actuator  1114  from a first or “safe” position to a second or “armed” position. In an embodiment, the indicator/LED  1116  emits a light, such as a red light for example. In an embodiment, this closes the static arming inhibit  778 A,  778 B. 
     The drone is then moved to the desired location (e.g. the target location). At the desired time, the operator opens the drop cover  1118  to expose an actuator, such as a first toggle switch for example. Upon actuation of the first toggle switch, a first signal is transmitted from the controller  1110  to the control module  332 ,  532 ,  932 ,  1032 . When the first signal is received. the servo motor or solenoid is activated allowing the control module  332 ,  532 ,  932 ,  1032  and any payloads  326 ,  526 ,  926 ,  1026 A to move away from the plate  334 ,  534 ,  934 ,  1034  under the influence of gravity. In an embodiment, the receiving of the first signal initiates a third predetermined timer (e.g. 5 second timer), which prevents the arming of the high voltage converter  784  to provide sufficient time for the system to fall out of the way and for the drone to move away from the payloads. 
     Finally, the operator lifts a fire cover  1120  to expose an actuator, such as a second toggle switch for example. Upon actuation of the second toggle switch, a second signal is transmitted from the controller  1110  to the control module  332 ,  532 ,  932 ,  1032 . The receiving of the second signal causes the control module  332 ,  532 ,  932 ,  1032  to close the dynamic arming inhibit  780  causing electrical power to flow from the system battery  766  to the high voltage converter  784  and charge the firing energy storage  782 . The energy from storage  782  is rapidly flowed to the detonator  774 . 
     It should be appreciated that in an embodiment where the payload is an article, such as medical supplies for example, the operator will not need to activate the second toggle switch. 
     In the event that there is a mis-fire, or if the mission of the drone is abandoned, the drone can be moved to a desired location, such as away from personnel and allowed to rest for a minimum of the length of time of the second timer (e.g. 60 minutes) so that energy is removed from the control module  332 ,  532 ,  932 ,  1032  except for the power to the servo motor or solenoid. The operator may turn of power to the controller  1100  (e.g. actuator  1106 ) and optionally remove the battery from the controller  1100 . The operator then approaches the drone and reinserts the pin  760 ,  960  and removes the FOB  777 ,  977 . By pressing the actuator  963 , the system  330 ,  530 ,  930 ,  1030  may be removed from the drone and the payload  326 ,  526 ,  926 ,  1026 A separated from the control module  332 ,  532 ,  932 ,  1032 . In an embodiment, the energy source (e.g. battery) is removed from the control module  332 ,  532 ,  932 ,  1032 . 
     It should be appreciated that while embodiments herein describe the system  20  as having a pair of energetic payloads arranged in parallel, this is for example purposes and the claims should not be so limited. In other embodiments, the system  30  may have a single energetic payload, or a plurality of energetic payloads to meet the goal of the mission the drone is undertaking. 
     Technical effects and benefits of some embodiments include the ability to allow a drone to deliver a payload where the payload is independently operable from the drone. Still further embodiments provide technical effects and benefits of allowing a single payload system to be interoperable with a variety of drone manufacturers without changing the operation of the payload system. Still further embodiments provide technical effects and benefits of providing a flexible payload system that can carry one or multiple energetics depending on the goal of the mission. Still further embodiments provide technical effects and benefits of allowing a drone to be used on a mission and returned for reuse or redeployment. 
     The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof. 
     The corresponding structures, materials, acts, and equivalents of all means or step plus function elements in the claims below are intended to include any structure, material, or act for performing the function in combination with other claimed elements as specifically claimed. The description of the present invention has been presented for purposes of illustration and description, but is not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the invention. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated. 
     The present invention may be a system, a method, and/or a computer program product. The computer program product may include a computer readable storage medium (or media) having computer readable program instructions thereon for causing a processor to carry out aspects of the present invention. 
     The computer readable storage medium can be a tangible device that can retain and store instructions for use by an instruction execution device. The computer readable storage medium may be, for example, but is not limited to, an electronic storage device, a magnetic storage device, an optical storage device, an electromagnetic storage device, a semiconductor storage device, or any suitable combination of the foregoing. A non-exhaustive list of more specific examples of the computer readable storage medium includes the following: a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or Flash memory), a static random access memory (SRAM), a portable compact disc read-only memory (CD-ROM), a digital versatile disk (DVD), a memory stick, a floppy disk, a mechanically encoded device such as punch-cards or raised structures in a groove having instructions recorded thereon, and any suitable combination of the foregoing. A computer readable storage medium, as used herein, is not to be construed as being transitory signals per se, such as radio waves or other freely propagating electromagnetic waves, electromagnetic waves propagating through a waveguide or other transmission media (e.g., light pulses passing through a fiber-optic cable), or electrical signals transmitted through a wire. 
     Computer readable program instructions described herein can be downloaded to respective computing/processing devices from a computer readable storage medium or to an external computer or external storage device via a network, for example, the Internet, a local area network, a wide area network and/or a wireless network. The network may comprise copper transmission cables, optical transmission fibers, wireless transmission, routers, firewalls, switches, gateway computers and/or edge servers. A network adapter card or network interface in each computing/processing device receives computer readable program instructions from the network and forwards the computer readable program instructions for storage in a computer readable storage medium within the respective computing/processing device. 
     Computer readable program instructions for carrying out operations of the present invention may be assembler instructions, instruction-set-architecture (ISA) instructions, machine instructions, machine dependent instructions, microcode, firmware instructions, state-setting data, or either source code or object code written in any combination of one or more programming languages, including an object oriented programming language such as Java, Smalltalk, C++ or the like, and conventional procedural programming languages, such as the “C” programming language or similar programming languages. The computer readable program instructions may execute entirely on the user&#39;s computer, partly on the user&#39;s computer, as a stand-alone software package, partly on the user&#39;s computer and partly on a remote computer or entirely on the remote computer or server. In the latter scenario, the remote computer may be connected to the user&#39;s computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or the connection may be made to an external computer (for example, through the Internet using an Internet Service Provider). In some embodiments, electronic circuitry including, for example, programmable logic circuitry, field-programmable gate arrays (FPGA), or programmable logic arrays (PLA) may execute the computer readable program instructions by utilizing state information of the computer readable program instructions to personalize the electronic circuitry, in order to perform aspects of the present invention. 
     Aspects of the present invention are described herein with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and/or block diagrams, and combinations of blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer readable program instructions. 
     These computer readable program instructions may be provided to a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions/acts specified in the flowchart and/or block diagram block or blocks. These computer readable program instructions may also be stored in a computer readable storage medium that can direct a computer, a programmable data processing apparatus, and/or other devices to function in a particular manner, such that the computer readable storage medium having instructions stored therein comprises an article of manufacture including instructions which implement aspects of the function/act specified in the flowchart and/or block diagram block or blocks. 
     The computer readable program instructions may also be loaded onto a computer, other programmable data processing apparatus, or other device to cause a series of operational steps to be performed on the computer, other programmable apparatus or other device to produce a computer implemented process, such that the instructions which execute on the computer, other programmable apparatus, or other device implement the functions/acts specified in the flowchart and/or block diagram block or blocks. 
     The flowchart and block diagrams in the Figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of the present invention. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of instructions, which comprises one or more executable instructions for implementing the specified logical function(s). In some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems that perform the specified functions or acts or carry out combinations of special purpose hardware and computer instructions. 
     The descriptions of the various embodiments of the present invention have been presented for purposes of illustration, but are not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein was chosen to best explain the principles of the embodiments, the practical application or technical improvement over technologies found in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.