Patent Publication Number: US-11640310-B2

Title: Processor virtualization in unmanned vehicles

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
     This application is a divisional application of U.S. patent application Ser. No. 15/875,350 filed Jan. 19, 2018, the contents of which are hereby incorporated by reference in their entirety. 
    
    
     FIELD 
     The present disclosure relates generally to unmanned vehicles, and more particularly to control systems for unmanned vehicles. 
     BACKGROUND 
     An unmanned vehicle (UV) is a vehicle having no onboard pilot. Typically, UVs such as unmanned aerial vehicles (UAVs) are controlled remotely by a pilot, by onboard control systems, or by a combination of a remote pilot and onboard control system. Most unmanned aerial vehicles include a control system to control vehicle operations. Often, a control system for a UAV includes one or more vehicle control systems including onboard navigation systems such as inertial navigation systems and satellite navigation systems. Unmanned aerial vehicles may use inertial navigation sensors such as accelerometers and gyroscopes for flight positioning and maneuvering and satellite-based navigation for general positioning and wayfinding. Most control systems additionally include one or more mission control systems for performing one or more mission control functions, such as capturing images or delivering a payload. Typically, individual hardware components are provided onboard a UAV for each vehicle control system and each mission control system. 
     BRIEF DESCRIPTION 
     Aspects and advantages of the disclosed technology will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the disclosure. 
     According to example aspects of the present disclosure, there is provided a processing system for an unmanned vehicle (UV), comprising a first processing unit of an integrated circuit, a second processing unit of the integrated circuit, and a first operating system provisioned using the first processing unit. The first operating system is configured to execute a first vehicle control process. The processing system comprises a virtualization layer configured using at least the second processing unit, and a second operating system provisioned using the virtualization layer. The second operating system is configured to execute a second vehicle control process. 
     According to example aspects of the present disclosure, there is provided a computer-implemented method for controlling an unmanned vehicle (UV), that comprises provisioning a first operating system using a first processor of an integrated circuit, configuring the first operating system to execute a first vehicle control process using the first processor, provisioning at least one virtual machine using a second processor of the integrated circuit, and configuring the at least one virtual machine to execute a second vehicle control process. The at least one virtual machine is isolated from the first operating system. 
     According to example aspects of the present disclosure, there is provided a processing system for an unmanned vehicle (UV), comprising an integrated circuit comprising a first processor and a second processor, a first operating environment provisioned using the first processor, a virtualization layer configured using at least the second processor, and a first virtual machine provisioned using the virtualization layer. The first virtual machine is configured to execute at least one vehicle control process in a second operating environment. The second operating environment is isolated from the first operating environment. The processing system includes a second virtual machine provisioned using the virtualization layer. The second virtual machine is configured to execute at least one mission control process in a third operating environment. The third operating environment is isolated from the second operating environment and the first operating environment. 
     These and other features, aspects and advantages of the disclosed technology will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosed technology and, together with the description, serve to explain the principles of the disclosed technology. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which: 
         FIG.  1    is a block diagram depicting an example of an unmanned aerial vehicle (UAV) in which embodiments of the present disclosure may be practiced; 
         FIG.  2    is a block diagram depicting an example of a typical control system for a UAV including a backplane and card architecture; 
         FIG.  3    is a block diagram depicting an example of a UAV having an onboard control system according to example embodiments of the present disclosure; 
         FIG.  4    is a block diagram depicting a first circuit board comprising a control module for a control box of the onboard control system according to example embodiments of the present disclosure; 
         FIG.  5    is a block diagram depicting a first processing system of the first circuit board according to example embodiments of the present disclosure; 
         FIG.  6    is a block diagram depicting a second processing system of the first circuit board according to example embodiments of the present disclosure; 
         FIG.  7    is a block diagram depicting a second circuit board comprising a carrier module for the control box according to example embodiments of the present disclosure; 
         FIG.  8    is a block diagram depicting an example of partitioned operating environments for a heterogeneous processing system according to example embodiments of the present disclosure; 
         FIG.  9    is a flowchart describing a process of monitoring, by a second processing system, process execution at a first processing system; 
         FIG.  10    is a flowchart describing a process of initiating control actions based on an output of a processing system; 
         FIG.  11    is a block diagram depicting an example of monitoring execution of processes by a first processing system and transferring control of a vehicle function to a second processing system; 
         FIG.  12    is a block diagram depicting an example of a software architecture of a processing system in accordance with example embodiments of the present disclosure; 
         FIG.  13    is a flowchart describing a process of configuring a software architecture using virtualization of one or more processing elements in accordance with example embodiments of the present disclosure; 
         FIG.  14    is a flowchart describing a process of configuring a computational accelerator using a programmable logic array in accordance with example embodiments of the present disclosure; 
         FIG.  15    is a flowchart describing a process of interfacing with a computational accelerator executing in a programmable logic array in accordance with example embodiments of the present disclosure; 
         FIG.  16    is a perspective view of a control box in accordance with embodiments of the present disclosure; 
         FIG.  17    is a perspective view showing internal components of a control box in accordance with embodiments of the present disclosure; 
         FIG.  18    is an exploded perspective view of a control box in accordance with embodiments of the present disclosure; 
         FIG.  19    is a perspective top view of a system-on-module circuit board in accordance with embodiments of the present disclosure; and 
         FIG.  20    is a perspective bottom view of a system-on-module circuit board in accordance with embodiments of the present disclosure. 
     
    
    
     DETAILED DESCRIPTION 
     Reference now will be made in detail to embodiments of the disclosure, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation, not limitation of the disclosed embodiments. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the claims. For instance, features illustrated or described as part of example embodiments can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents. 
     As used in the specification and the appended claims, the singular forms “a,” “an,” and “the” include plural referents unless the context clearly dictates otherwise. The use of the term “about” in conjunction with a numerical value refers to within 25% of the stated amount. 
     Example aspects of the present disclosure are directed to systems and methods for controlling unmanned vehicles (UV), and more particularly, to systems and methods for controlling unmanned vehicles and vehicle devices of the unmanned vehicles using a control system to provide integrated vehicle and mission management control. In example embodiments, the control system may include one or more processing systems. For example, a control board including a processing system having a first processing unit and a second processing unit may be provided. The processing system may additionally include a programmable logic array such as a field programmable gate array (FPGA). Multiple partitioned operating environments are provided using the various processing elements in order to provide a reliable, configurable, and certifiable software configuration suitable to the operating needs of a UV. 
     In accordance with example embodiments of the disclosed technology, a first operating system can be provisioned from the first processing unit in order to execute a first vehicle control process. A virtualization layer is configured from at least the second processing unit. A second operating system can then be provisioned from the virtualization layer. The second operating system can be configured to execute a second vehicle control process. The second operating system may additionally be configured to execute mission control processes. A third operating system can also be provisioned from the virtualization layer. The third operating system can be configured to execute vehicle and/or mission control processes. 
     In a particular aspect, a first virtual machine can be provisioned from the virtualization layer and a second virtual machine can be provisioned from the virtualization layer. In example embodiments, the first virtual machine can be a real-time virtual machine including the second operating system and the second virtual machine can be a non-real-time virtual machine including the third operating system. More particularly in some examples, the first operating system can be provisioned using a real-time processing unit and the first and third virtual machines configured using an application processing unit. 
     The first operating system includes a high integrity partitioned operating environment in some examples. The first operating system may include a hardware and software partition isolating the first operating system from other virtual machines and operating systems of the control system. For instance, the first operating system may be configured using a real-time processing unit while other operating systems are configured using other processing units. In various aspects, vehicle control processes and/or mission control processes can be configured for execution in the high integrity partitioned operating environment. For example, critical vehicle control processes and/or mission control processes may be configured in the high integrity partition. Additional vehicle control processes and/or mission control processes can be configured for other operating environments such as in one or more virtual machines provisioned using an application processing unit. In this manner, the critical vehicle and/or mission control processes can be isolated from other processes using hardware and software. By way of example, a vehicle control process associated with controlling at least one propulsion and movement device of the UV may be configured in a high integrity partitioned operating environment. More specifically, an autopilot process can be configured in a high integrity partition. 
     According to some aspects, at least one computational accelerator is configured in a field programmable gate array of the processing system. At least one interface for the computational accelerator can be configured in a virtualization layer in order to provide access to the computational accelerator from other processing elements of the system. 
     In example embodiments, the control system includes a housing defining an interior and one or more circuit boards disposed within the interior. More particularly, the control system can include a first circuit board having one or more integrated circuits that provide a first processing system and a second processing system. In example embodiments, the first and second processing systems have heterogeneous field programmable gate array architectures to provide diverse, configurable, and certifiable UV applications. 
     In some examples, the first circuit board forms a control module for a control box and is configured to control vehicle and mission functions for a UV. For example, the second processing system can control a first vehicle device or function of the UV based on execution of a first mission or vehicle control process by the first processing system and execution of a second mission or vehicle control process by the second processing system. 
     In example embodiments, the first processing system can include one or more first processing units and a volatile programmable logic array such as a RAM based field programmable gate array. A second processing system can include one or more second processing units and a nonvolatile programmable logic array such as a flash-based field programmable gate array. In some implementations, the flash-based field programmable gate array manages control of one or more vehicle devices of the UAV based on a first vehicle process executed by the one or more first processing units and a second vehicle process executed by the one or more second processing units. In example embodiments, the second processing system can be configured with multiple operating systems including standalone operating systems and virtual machines as described with respect to the first operating system. Each processing system may include one or more processing units such as central processing units (CPU), application processing units (APU), real-time processing units (RPU), co-processing processing units, and graphics processing units (GPU). Additionally, each processing system may include an embedded programmable logic array such as a field programmable gate array (FPGA) forming an integrated part of the respective processing system. 
     In some examples, the first processing system and/or the second processing system may each be provided as a multi-processing core system-on-a-chip. Together, two or more systems on chip configured with processing systems as described may provide a heterogeneous processing system for a UV. 
     In example embodiments of the disclosed technology, the first processing system and the second processing system cooperate to provide more reliable, robust, and/or certifiable UV applications. For example, the first processing system of the first circuit board can be configured to execute a first process for the UV. The first process may be associated with a first vehicle device of the UV. The second processing system can be configured to monitor execution of the first process by the first processing system. Similarly, the first processing system can be configured to monitor execution of a process by the second processing system. 
     Embodiments of the disclosed technology provide a number of technical benefits and advantages, particularly in the area of unmanned vehicles such as unmanned aerial vehicles. As one example, the technology described herein enables control of an unmanned vehicle (UV) using compact and lightweight electronic solutions. Circuit boards having integrated heterogeneous processing systems enable reduced hardware implementations that provide multiple vehicle control processes and mission management processes for a UV. Additionally, such solutions provide backup functions and multiple fail point implementations that can meet the high certification requirements of airborne applications. Moreover, the integration of such heterogeneous processing systems into a housing with one or more circuit boards that provide input/output (I/O) interfaces further enables reduced space and weight requirements. Furthermore, the disclosed software system enables partitioned operating environments to be used to meet the requirements of code certifications for computer readable instructions in UV applications. 
     Embodiments of the disclosed technology also provide a number of technical benefits and advantages in the area of computing technology. For example, the disclosed system can provide diverse computing environments to meet the various demands of UV applications. Multiple processing units spread across multiple integrated circuits provide a range of high speed processing options for application integration. Vehicle and mission control processes can be allocated to various hardware and/or software partitions according to criticality and performance needs. Moreover, embedded field programmable gate arrays tightly coupled to these processing units via integration on a single integrated circuit with corresponding processing units provides additional diversity and reliability. 
       FIG.  1    is a schematic view of an example unmanned aerial vehicle (UAV) UAV  10 . UAV  10  is a vehicle capable of flight without an onboard pilot. For example, and without limitation, UAV  10  may be a fixed wing aircraft, a tilt-rotor aircraft, a helicopter, a multirotor drone aircraft such as a quadcopter, a blimp, a dirigible, or other aircraft. 
     UAV  10  includes a plurality of vehicle devices including at least one propulsion and movement (PM) device  10 . A PM device  14  produces a controlled force and/or maintains or changes a position, orientation, or location of UAV  10 . A PM device  14  may be a thrust device or a control surface. A thrust device is a device that provides propulsion or thrust to UAV  10 . For example, and without limitation, a thrust device may be a motor driven propeller, jet engine, or other source of propulsion. A control surface is a controllable surface or other device that provides a force due to deflection of an air stream passing over the control surface. For example, and without limitation, a control surface may be an elevator, rudder, aileron, spoiler, flap, slat, air brake, or trim device. Various actuators, servo motors, and other devices may be used to manipulate a control surface. PM device  14  may also be a mechanism configured to change a pitch angle of a propeller or rotor blade or a mechanism configured to change a tilt angle of a rotor blade. 
     UAV  10  may be controlled by systems described herein including, without limitation, an onboard control system including a control box  100 , a ground control station (not shown in  FIG.  1   ), and at least one PM device  14 . UAV  10  may be controlled by, for example, and without limitation, real-time commands received by UAV  10  from the ground control station, a set of pre-programmed instructions received by UAV  10  from the ground control station, a set of instructions and/or programming stored in the onboard control system, or a combination of these controls. 
     Real-time commands can control at least one PM device  14 . For example, and without limitation, real-time commands include instructions that, when executed by the onboard control system, cause a throttle adjustment, flap adjustment, aileron adjustment, rudder adjustment, or other control surface or thrust device adjustment. 
     In some embodiments, real-time commands can further control additional vehicle devices of UAV  10 , such as one or more secondary devices  12 . A secondary device  12  is an electric or electronic device configured to perform one or more secondary functions to direct propulsion or movement of the UAV. Secondary devices may be related to propulsion or movement of the UAV, but typically provide one or more vehicle or mission functions independent of direct control of vehicle propulsion or motion control. For example, secondary devices may include mission-related devices such as cameras or other sensors used for object detection and tracking. Other examples of secondary devices  12  may include sensors such as LIDAR/SONAR/RADAR sensors, GPS sensors, communication devices, navigation devices, and various payload delivery systems. For example, and without limitation, real-time commands include instructions that when executed by the onboard control system cause a camera to capture an image, a communications system to transmit data, or a processing component to program or configure one or more processing elements. 
     UAV  10  is depicted by way of example, not limitation. Although much of the present disclosure is described with respect to unmanned aerial vehicles, it will be appreciated that embodiments of the disclosed technology may be used with any unmanned vehicle (UV), such as unmanned marine vehicles and unmanned ground vehicles. For example, the disclosed control systems may be used with unmanned boats, unmanned submarines, unmanned cars, unmanned trucks, or any other unmanned vehicle capable of locomotion. 
       FIG.  2    is a block diagram depicting an example of a typical control system  50  for a UAV. In this example, a control system is formed using a backplane  60  having a plurality of card slots  71 ,  72 ,  73 ,  74 ,  75 . Each card slot is configured to receive a card meeting a predefined set of mechanical and electrical standards. Each card includes one or more circuit boards, typically including one or more integrated circuits configured to perform specific vehicle or mission control functions. The card slot provides structural support for the card, as well as an electrical connection between the card and an underlying bus. A particular example is depicted having a CPU card  61  installed in a first card slot  71 , a co-processor card  62  installed in a second card slot  72 , and add-on cards  63 ,  64 ,  65  installed in card slots  73 ,  74 ,  75 , respectively. By way of example, CPU card  61  may include a circuit board having a processor, PCI circuitry, switching circuitry, and an electrical connector configured to both structurally and electrically connect card  61  to card slot  71 . Similarly, co-processor card  62  may include a processor, PCI circuitry, switching circuitry, and a connector. 
     Add-on cards  63 ,  64 ,  65  may include any number and type of cards configured to perform one or more vehicle and/or mission functions. Examples of add-on cards include input/output (I/O) cards, network cards, piloting and navigation function cards, sensor interface cards (e.g., cameras, radar, etc.), payload delivery systems control cards, graphics processing unit (GPU) cards, and any other card for a particular type of vehicle and/or mission function. 
     Typical backplane architectures like that in  FIG.  2    include a switch  66  that allows each card to communicate with cards in any other slot. Numerous examples including various standards exist to define different types of backplane architectures. For example, although switch  66  is shown separate from the card slots  71 ,  72 ,  73 ,  74 ,  75 , some architectures may place a central switch in a particular slot of the backplane. In each case, the node devices can communicate with one another via the switch. While five card slots are depicted in  FIG.  2   , a backplane may include any number of card slots. 
     An onboard control system for a UAV utilizing a backplane architecture like that of  FIG.  2    may be effective in providing some function control. Additionally, such an architecture may provide some configurability through hardware changes. However, traditional backplane architectures may have a number of drawbacks in implementations for UAVs. For example, the structural performance of a backplane coupling to a plurality of cards through a combined electrical and mechanical connection may not be well-suited to the high-stress environments of some UAVs. Mechanical and/or electrical failures may occur for one or more cards in the backplane due to vibrations, temperatures, and other factors. Additionally, such architectures provide a limited processing capability, while requiring considerable space and weight. Each card typically includes its own circuit board including connectors, switching circuitry, communication circuitry, etc. Because each circuit board requires its own circuitry for these common functions, a backplane architecture may provide relatively high weight and space requirements. Moreover, the computing ability and capacity of these types of systems is typically limited by a multiple card approach. Communication between the cards, and between the various processing elements may lead to reduced computational abilities. 
       FIG.  3    is a block diagram depicting an unmanned aerial vehicle (UAV)  10  including a control system  80  in accordance with embodiments of the disclosed technology. Control system  80  includes a control box  100  that provides centralized control of vehicle and mission functions. The control box includes a housing  110  defining an interior. A first circuit board  120  and second circuit board  122  are disposed within the interior of housing  110 , and an I/O connector  126  extends from the second circuit board  122  through the housing  110  as described hereinafter. Control box  100  includes a heat sink  118  provided to dissipate heat from the electric components of the control box  100 . In example embodiments, heat sink  118  may form at least a portion of housing  110  as described hereinafter. Control system  80  may include additional components such as additional control units or other elements that perform vehicle or mission control processes. 
     In some implementations, first circuit board  120  comprises a control module for controlling vehicle and mission control processes of UAV  103 , and second circuit board  122  comprises a carrier module for providing a communication interface between the control unit and various PM devices and secondary devices of the UAV. 
     In some examples, the first circuit board includes multiple heterogeneous processing systems, each having a reconfigurable processing architecture to provide management of the various vehicle and mission functions. The multiple heterogeneous processing systems with reconfigurable functionality are suited to the diverse functions performed by unmanned airborne vehicles, as well as the high level of certifications typically needed for these vehicles. 
     In example embodiments, the second circuit board  122  is a carrier module providing an interface between the first circuit board  120  and the various PM devices and secondary devices of UAV  10 . For example,  FIG.  3    depicts a set of PM devices including a thrust device  30 , control surface  32 , and positioning system  34 . Additionally,  FIG.  3    depicts a set of secondary devices including an image sensor  20 , a radar sensor  22 , a LIDAR sensor  24 , a sonar sensor  26 , a GPS sensor  28 , a payload delivery system  36 , and a communication system  38 . The second circuit board  122  may include an I/O connector that connects to a corresponding I/O connector of the first circuit board, as well as an I/O connector that extends from the housing. Additionally, the second circuit board may include a plurality of sensor connectors that extend from the housing. The second circuit board may provide a communications or input/output (I/O) interface including associated electronic circuitry that is used to send and receive data. More specifically, the communications interface can be used to send and receive data between any of the various integrated circuits of the second circuit board, and between the second circuit board and other circuit boards. For example, the item interface may include I/O connector  126 , I/O connector  238 , and/or I/O connector  124 . Similarly, a communications interface at any one of the interface circuits may be used to communicate with outside components such as another aerial vehicle, a sensor, other vehicle devices, and/or ground control. A communications interface may be any combination of suitable wired or wireless communications interfaces. 
     In some examples, control box  100  may include additional components. For example, a third circuit board such as a mezzanine card can be provided within control box  100  in another embodiment. The third circuit board may include one or more nonvolatile memory arrays in some examples. For example, a solid-state drive (SSD) may be provided as one or more integrated circuits on a mezzanine card. Moreover, control box  100  may include additional circuit boards to form a control module as well as additional circuit boards to form additional carrier modules. 
       FIG.  4    is a block diagram describing a first circuit board  120  in accordance with example embodiments of the disclosed technology. In  FIG.  4   , first circuit board  120  is configured as a control module (e.g., control board) for an unmanned aerial vehicle (UAV). In example embodiments, first circuit board  120  is a system-on-module (SOM) card. First circuit board  120  includes a first processing system  230 , second processing system  232 , memory blocks  234 , and an I/O connector  238 . 
     The first and second processing systems can include or be associated with, any suitable number of individual microprocessors, power supplies, storage devices, interfaces, and other standard components. The processing systems can include or cooperate with any number of software programs (e.g., vehicle and mission control processes) or instructions designed to carry out the various methods, process tasks, calculations, and control/display functions necessary for operation of the aerial vehicle  10 . Memory blocks  234  may include any suitable form of memory such as, without limitation, SDRAM, configured to support a corresponding processing system. For example, a first memory block  234  may be configured to support first processing system  230  and a second memory block  234  may be configured to support second processing system  232 . Any number and type of memory block  234  may be used. By way of example, four memory blocks each comprising an individual integrated circuit may be provided to support the first processing system  230  and two memory blocks may be provided to support the second processing system  232 . 
     I/O connector  238  extends from a first surface of first circuit board  122  to provide an operative communication link to second circuit board  122 . 
     First processing system  230  and second processing system  232  form a heterogeneous and reconfigurable computing architecture in example embodiments of the disclosed technology, suitable to the diverse and stable needs of UAV  10 . First processing system  230  includes one or more processing units  302  forming a first processing platform and one or more programmable logic circuits  304  forming a second processing platform. By way of example, one or more processing units  302  may include a central processing unit and programmable logic circuit  304  may include a volatile programmable logic array such as a RAM-based field programmable gate array (FPGA). Any number and type of processing unit may be used for processing units  302 . Multiple processing units  302  and programmable logic circuit  304  may be provided within a first integrated circuit, referred to generally as a processing circuit in some embodiments. 
     Second processing system  232  includes one or more processing units  322  forming a third processing platform and one or more programmable logic circuits  324  forming a fourth processing platform. By way of example, one or more processing units  302  may include a co-processing unit and programmable logic circuit  324  may include a flash-based FPGA. Any number and type of processing unit may be used for processing units  324 . One or more processing units  324  and programmable logic circuit  324  may be provided within the second integrated circuit, also referred to as a processing circuit in some embodiments. 
     By providing different processing unit types as well as different programmable logic circuit types in each processing system, first circuit board  120  provides a heterogeneous computing system uniquely suited to the processing, reliability, and operational requirements of high-stress application UAVs. For example, the RAM-based and flash-based FPGA technologies are combined to leverage the strengths of both for UAV applications. The unique abilities of heterogeneous processing units  302  and  322  and heterogeneous programmable logic circuits  304  and  324  support both hardware and software-partitioned operating environments. Vehicle and mission management functions can be allocated to different partitions according to criticality and performance needs. This provides a control and monitor architecture suitable for critical operations. For example, an on/off or red/green architecture for control of irreversible critical functions is provided. By way of further example, one or more of the field programmable gate arrays may be configured to provide a fabric accelerator for onboard sensor processing 
       FIG.  5    is a block diagram describing additional details of first processing system  230  in accordance with example embodiments of the disclosed technology. In  FIG.  5   , first processing system  230  includes three processing units  302  as described in  FIG.  4   . More particularly, first processing system  230  includes an application processing unit (APU)  306 , a graphics processing unit (GPU)  308 , and a real-time processing unit (RPU)  310 . Each of processing units  306 ,  308 ,  310  may be supported by memory  312  which may include any number and type of memory such as an SDRAM. Each processing unit is implemented on an individual integrated circuit referred to as a processing circuit. In one example, APU  306  is formed on a first processing circuit and includes a quad core processing unit comprising four processors. RPU  310  is formed on a third processing circuit and includes a dual core processing unit comprising two processors. GPU  308  is formed on a fourth processing circuit and includes a single core processing unit. A second processing unit is provided for the second processing system as described below. A switch fabric  316  connects the various components of processing system  230 . Switch fabric  316 , for example, may include a low-power switch and a central switch in some examples. Communication interface  314  couples first processing system  232  to first circuit board  120 . 
     Programmable logic circuit  304  includes a volatile programmable logic array  305 . In example embodiments, logic array may include a RAM-based programmable logic array such as a RAM-based floating point gate array including RAM logic blocks or memory cells. Volatile programmable logic array  305  can be programmed with configuration data provided to the first processing system through communication interface  314 . For example, a RAM-based FPGA can store configuration data in the static memory of the array, such as in an organization comprising an array of latches. The logic blocks are programmed (configured) when programmable logic circuit  304  is started or powered up. The configuration data can be provided to logic array  305  from an external memory (e.g., nonvolatile memory of first circuit board  120  or a mezzanine board as described hereinafter) or from an external source of UAV  10  (e.g., using second circuit board  122 ). A RAM-based FPGA provides high levels of configurability and re-configurability. Although not shown, logic array  305  may include various programmed circuits such as ethernet interfaces and PCI interfaces, and the various vehicle and mission management processes described herein. 
       FIG.  6    is a block diagram describing additional details of second processing system  232  accordance with example embodiments of the disclosed technology. In  FIG.  6   , second processing system  232  includes an application processing unit (APU)  326  and memory  332 . In one example, APU  326  is formed on a second processing circuit and includes a quad core processing unit comprising four processors. Memory  332  may include any number and type of memory such as SDRAM. A switch fabric  336  connects the various components of processing system  232 . Communications interface  334  couples first processing system  232  to first circuit board  120 . 
     Programmable logic circuit  324  includes a nonvolatile programmable logic array  325 . In example embodiments, logic array  325  may include a flash-based programmable logic array such as a flash-based floating point gate array including flash logic blocks or memory cells. Nonvolatile programmable logic array  325  can be programmed with configuration data provided to the second processing system through communication interface  334 . For example, a flash-based FPGA can store configuration data in the nonvolatile memory of the array. Flash memory is used as the primary resource for storage of the configuration data such that RAM-based memory is not required. Because the configuration data is stored within the nonvolatile memory, there is no requirement for reading the configuration data to the logic array upon startup or power up. As such, the flash-based logic array may execute applications immediately upon power up. Moreover, external storage of configuration data is not required. The flash-based logic array can be reprogrammed or reconfigured by providing updated configuration data to override the configuration data presently stored in the logic array. The flash-based logic array may consume less power than the RAM-based logic array, as well as provide more protection against interference. Although not shown, logic array  325  may include various programmed circuits, such as for the various vehicle and mission management processes described herein. In one example, logic array  325  may include at least one FPGA fabric accelerator for onboard sensor processing. 
       FIG.  7    is a block diagram depicting additional details of second circuit board  122  in accordance with example embodiments of the disclosed technology. In  FIG.  7   , second circuit board  122  is configured as a carrier module (e.g., carrier card) for an unmanned aerial vehicle (UAV). Second circuit board  122  includes a plurality of integrated circuits such as interface circuits providing I/O capabilities for control box  100 . The interface circuits are configured to receive outputs of the plurality of vehicle devices of the UAV via the sensor connectors. The interface circuits provide vehicle device data based on outputs of the vehicle devices to the first circuit board via I/O connector  124 . Second circuit board  122  includes an I/O connector  126  that extends from a housing of control unit  100  to provide an operative communication link to PM devices and secondary devices of UAV  10 . Additionally, second circuit board  122  includes an I/O connector  124  extending from a first surface of second circuit board  122  to provide an operative communication link to first circuit board  120 . Although not shown, second circuit board  122  may include an additional I/O connector for coupling to a mezzanine card including a solid-state drive, for example. Any one or a combination of I/O connectors  126 ,  124 , and  228  may form an I/O interface between the interface circuits of the second circuit board and the first and second processing systems of the first circuit board. 
       FIG.  7    describes a particular set of interface circuits as may be used in the particular implementation of control box  100 . It will be appreciated, however, that any number and type of interface circuit may be used as suited for a particular implementation. Second circuit board  122  includes a plurality of interface circuits such as a LIDAR/SONAR interface  420 , a Pitot/static interface  422 , an electro-optical grid reference system (EOGRS) receiver interface  424 , and a first circuit board interface  432  for communicating with first circuit board  122 . Second circuit board  122  also includes interface circuits such as a software defined radio  426 , a navigation system  125 , a controller area network bus (CANBUS)  430 , and a power supply  434 . In some embodiments, navigation system  428  is an integrated circuit providing an integrated navigation sensor suite, including various sensors such as inertial measurement sensors. Additionally, second circuit board  122  includes a number of interface circuits in operative communication with a plurality of vehicle devices (e.g., PM devices or secondary devices) of the UAV  10 . A plurality of sensor connectors  458  extend from the housing of control unit  100  for coupling to the vehicle devices of UAV  10 . 
     In the specific example of  FIG.  7   , one or more pulse width modulators (PWM)  402  are in operative communication with one or more servos  442  via a first sensor connector  458 . Although a PWM servo command interface is depicted, other types of servo command interfaces may be used. For example, analog voltage, current loop, RS-422, RS-485, MIL-STD-1553 are all examples of possible servo control signals. A GPS receiver  404  is in operative communication with one or more GPS antennas  444  via a second sensor connector  458 . GPS antennas  444  are one example of a GPS sensor  28 . A datalink receiver  406  is in operative communication with one or more datalink antennas  446  via a third sensor connector  458 . A serial receiver link (SRXL) input  408  is in operative communication with a Pilot in Command (PIC) receiver  448  via a fourth sensor connector  458 . A programmable power supply unit (PSU)  410  is in operative communication with a servo power  450  via a fifth sensor connector  458 . One or more comparators  412  are in operative communication with one or more discrete inputs  452  via a sixth sensor connector  458 . One or more drivers  414  are in operative communication with one or more discrete outputs  454  via a seventh sensor connector  458 . One or more analog-to-digital converters (ADC)  416  are in operative communication with one or more analog inputs  456  via an eighth sensor connector  458 . 
       FIG.  8    is a block diagram depicting an example of first circuit board  120  in accordance with embodiments of the disclosed technology.  FIG.  8    depicts a specific implementation of first circuit board  120 , as may be configured for a particular flight or mission.  FIG.  8    depicts first processing system  230  second processing system  232  as previously described. For clarity of description, only a subset of the components of processing systems  230  and  232  are depicted. A simplified version of first processing system  230  is depicted including processing unit  302  and volatile programmable logic array  305 . Second processing system  232  is depicted with processing units  322  and programmable logic array  305 . 
       FIG.  8    depicts a plurality of partitioned operating environments POE 0 -POE  7  created across the heterogeneous processing system.  FIG.  8    also depicts a specific allocation of vehicle and mission control processes to further illustrate the disclosed subject matter. Specifically, a first partitioned operating environment POE 0 , a second partitioned operating environment POE 1 , and a third partitioned operating environment POE 2  are allocated at the one or more processing units  302 . In some examples, the partitioned operating environments are hardware partitions. For example, POE 0  may be allocated at APU  306 , POE 1  may be allocated at RPU  310 , and POE 2  may be allocated at GPU  308 . In other examples, the partitioned operating environments are software partitions, such as different virtual machines virtualized from one or more processing units. For example, one or more of APU  306 , GPU  308 , and RPU  310  may be virtualized to create the three partitioned operating environments. A fourth partitioned operating environment POE 3  is allocated to programmable logic array  305 . Although a single operating environment is depicted in  FIG.  8   , multiple operating environments may also be created within a programmable logic array. In one example individual partitioned operating environments with her programmable logic array represent different hardware elements such as different logic blocks. In other examples, virtualization or other software techniques may be used to create individual partitioned operating environments. Moreover, some embodiments include a combined virtualization of both processing unit  302  and programmable logic array  305 . Any number and combination of hardware processors and virtual machines may be used to create individual partitioned operating environments as depicted in  FIG.  8   . 
     In  FIG.  8   , one or more first vehicle control processes (VCP)  502  and one or more first mission control processes (MCP)  504  are allocated to the first partitioned operating environment POE 0 . One or more VCPs  506  and one or more MCPs  508  are allocated to the second partitioned operating environment POE 1 . One or more MCPs  510  are allocated to the third partitioned operating environment POE 2 . One or more MCPs  512  are allocated to the fourth partitioned operating environment POE 3 . 
       FIG.  8    illustrates that a plurality of vehicle control processes and mission control processes may be allocated across multiple partitioned operating environments to meet the needs of a particular implementation. For example, control processes may be categorized and the categories used to assign control processes to particular partitioned operating environments. In some implementations, the first processing system can provide at least two partitioned operating environments. Similarly, the second processing system can provide at least two partitioned operating environments. For example, the first processing system may include a high integrity partition and a cluster partition. The high integrity partition may include real-time operating environment. Such an operating environment may be configured for execution of one or more critical vehicle navigation processes for example. Other processes may be placed into the high integrity partition as well. The cluster partition may include non-real-time operating environment. Such an operating environment may be configured for execution of one or more mission control processes. Other processes may be placed into the cluster partition as well. 
     By way of specific example, POE 0  may be used to execute critical control processes. For instance, POE 0  can be a high integrity partitioned including autopilot, guidance, and navigation processes with auto-generated code from a model based design flow. In one example, a standalone operating system can be used for a first partitioned operating environment allocated for critical processes. POE 1  may be used to execute less critical, but time sensitive vehicle and mission control processes. For example, mission navigation processes, datalink management processes, sensor data management processes, and/or ground station/other C2 processes may be allocated to the second partitioned operating environment. By way of further example, sensor processing and backend parameter analysis of health and/or other parameters, etc. may be allocated to the third partitioned operating environment POE 2 . Finally, a fourth partitioned operating environment POE 3  may be allocated to high processing requirement applications such as image analysis and object detection and tracking. For example, sensor-relative navigation and robotic perception/cognition may be performed in the fourth partitioned operating environment. In other examples geo-registration of sensor collection including targeting and alternate navigation sources may be allocated to POE  3 . Additionally, software defined radio including signal intelligence collection and flexible data links for payload data dissemination may be allocated. In some examples, one or more of POE 1 , POE 2 , and POE 3  may be a virtualized computing cluster form for mission control processes that are isolated from the high integrity partition. It will be appreciated that the examples are provided by way of explanation only and numerous other options allocations may be made according to the requirements of a particular implementation. 
     Referring to the second processing system  232 , a fifth partitioned operating environment POE 4  may be allocated for additional vehicle control processes. In some examples, POE 4  may be used to execute critical and/or time sensitive vehicle control processes such as backup navigation and piloting processes. The sixth partitioned operating environment POE 5  may be allocated for additional mission control processes. In some examples, POE 5  may be used to execute less critical or time sensitive mission control processes. The seventh partitioned operating environment POE 6  is allocated to programmable logic array  325 . In this example, POE 6  is allocated for execution of one or more vehicle control processes. By way of particular example, navigation monitoring and/or control processes may be configured in the seventh partitioned operating environment POE 6  in one embodiment. As described in more detail hereinafter, one or more monitoring and/or control processes may be implemented in POE 6  in one implementation. 
     The heterogeneous processing system provided by first circuit board  120  is uniquely situated to handle the diverse and high reliability requirements of UAV&#39;s. More particularly, the heterogeneous processing system enables joint processing by two disparate processing systems to provide monitoring, correction, and backup functions. For example, one or more components of first processing system  230  may monitor execution of one or more processes at the second processing system  232  and generate control actions based on the monitor execution. Similarly, one or more components of the second processing system  232  may monitor execution of one or more processes at the first processing system  234  and generate control actions based on the monitored execution. By way of example, the second processing system may detect one or more anomalies associated with execution of a process by the first processing system and restart the process and/or the first processing system. By way of additional example, the second processing system may execute a backup process in response to a detected anomaly associated with the first processing system. In yet another example, the second processing system may monitor an output of the first processing system and check for a concurrence with an output of the second processing system. In response to a concurrence, a control action such as enabling a vehicle device may be initiated. 
       FIG.  9    is a flowchart describing a process  600  of joint processing of a management processes by a heterogeneous processing system in accordance with embodiments of the disclosed technology. Although process  600  describes monitoring by the second processing system execution of a process by the first processing system, it will be appreciated that the process may be similarly used by the first processing system to monitor execution of the process by the second processing system. In one example, process  600  can be performed by a dedicated process within a programmable logic array of the processing system. In another example, process  600  may be performed by one or more processing units. 
     At ( 602 ), a first process is executed by the first processing system. For example, an application or other set of instructions can be executed by one or more processing units and/or the volatile programmable logic array of the first processing system. 
     At ( 604 ), the second processing system monitors execution of the first process at the first processing system. In some implementations, monitoring execution of a process includes monitoring an output of the first processing system. In other examples, monitoring execution of a process includes monitoring for one or more anomalies associated with execution of the process by the first processing system. 
     At ( 606 ), the second processing system determines whether the output of the first processes is valid. In some examples, determining whether the output is valid includes determining whether the first processing systems is generating the output. If the first processing system is generating an output, the second processing system determines that the output is valid. In another example, monitoring the output includes determining whether the output includes a valid signal. For example, the second processing system can determine whether the output includes a signal consistent with the first process being executed at the first processing system. In another example, the second processing system can determine whether the output matches or shares a concurrence with another output. For instance, the second processing system can determine whether the output of the first processing system matches or is the same as an output of the second processing system in one example. 
     At ( 608 ), process  600  branches based on whether the output of the first process was determined to be valid and/or shared a concurrence with another output. If the output of the first process is determined to be valid, a first control action is generated for the unmanned aerial vehicle at ( 610 ). If the output of the first process is determined to be invalid, a second control action is generated for the unmanned aerial vehicle at ( 612 ). As described in more detail hereinafter, the first control action may include providing the output of the first process. The second control action may include restarting the first process or the first processing system, executing a backup process, configuring a new process, or other suitable actions. 
       FIG.  10    is a flowchart describing a process  650  of initiating control actions based on monitoring execution of a first processing system by a second processing system or vice versa. More particularly, process  650  describes second control actions that may be generated based on invalid output of the first processing system. For example, process  650  may be performed by second processing system  232  at ( 612 ) of process  600  shown in  FIG.  9   . 
     At ( 652 ), process  650  determines whether the first process associated with the invalid output signal is associated with a high criticality function of the UAV. For example, the second processing unit may take different actions based on type of process for which an invalid output was detected. In this manner, the second processing system may be adapted to the particular requirements of various implementations. In a particular example, all vehicle control processes may be considered to be associated with high criticality vehicle functions. Similarly, a subset of mission management processes such as navigation or certain sensor data management may be considered to be associated with high criticality functions. 
     If the control action is being initiated in response to a high criticality function, process  652  continues at ( 654 ). At ( 654 ), a backup process for the first process is executed by the second processing system. In some examples, the second processing system executes the backup process in one or more processing units  322 . In other examples, the second processing system executes the backup process in programmable logic circuit  324 . 
     At ( 656 ), function control is transferred to the backup process. For example, the second processing system can transfer control of the high criticality function from the first process to the backup process. It will be appreciated that the backup process may be executed by the second processing system prior to detecting an invalid output. For example the backup process may already be executing in the second processing system. In response to an invalid output from the first processing system, function control can be transferred to the backup process. 
     After transferring function control to the backup process, or in response to determining that the function is not a high criticality function, process  650  continues at  658 . At ( 658 ), process  650  determines whether the first processing system has been compromised. For example, the second processing system can determine whether the invalid output is associated with an unauthorized modification of the first process at the first processing system. In some examples, the second processing system may detect an unauthorized modification in response to unexpected outputs of the first processing system. In other examples, the second processing system may detect an unauthorized modification by the presence of malicious code. 
     If the first processing system has been compromised, process  650  continues at ( 664 ). At ( 664 ), the second processing system obtains updated configuration data and/or an updated instruction set for the primary process. The updated configuration data may be obtained locally from memory  332  for example, or remotely from information transmitted by a ground station for example. 
     At ( 666 ), the first processing system is reconfigured and/or preprogrammed based on the updated configuration data and/or instruction set. For example, the second processing system may transmit an updated configuration data file and/or instruction set to the first processing system. One or more processing units of the first processing system can be reprogrammed and/or the programmable logic array can be reconfigured. In some examples, the primary process can be reconfigured to avoid a subsequent unauthorized modification of the first processing system. For example, the primary process can be modified to avoid a subsequent exploit of a vulnerability that may have been used to have initially compromised the first processing system. 
     At ( 670 ), function control is transferred back to the first processing system. In some examples, ( 670 ) includes transferring function control from the backup process to the reconfigured primary process. 
     If the first processing system is not compromised, process  650  continues at ( 660 ). At ( 660 ), process  650  restarts the first processing system or restarts execution of the first process by the first processing system. For example, the second processing system may restart execution of the first process or restart the first processing system in its entirety in an effort to alleviate the cause of the invalid output. For example, the invalid output may be detected as a loss of the output signal due to a power or other failure of the first processing system. Restarting the first processing system or the first process may again cause the output to be validly generated. At ( 662 ), function control is transferred to the primary process if function control was earlier transferred to the backup process at ( 656 ). 
       FIG.  11    is a block diagram depicting first circuit board  120  and a monitoring process that can be performed by second processing system  232  in accordance with example embodiments of the disclosed technology. In another example, a similar process may be performed by first processing system  230 . 
     First processing system  230  is depicted with real-time processing unit (RPU)  310  executing a primary control process for a first UAV function. By way of example, the primary control process may include a first instruction set stored in memory and executed by RPU  310 . Primary control process  702  generates an output  722  that is provided to one or more support processes  704 . Support processes  704  are associated with the first UAV function. By way of example, the primary control process may be an autopilot process configured to generate output commands for navigating of piloting the UAV based on sensor data. The one or more support processes  704  may include a pulse width modulation (PWM) servo command generation unit. The PWM servo command generation unit may receive the commands from output  722  of the autopilot process and generate as an output  724 , the appropriate PWM servo commands. In another example, the primary control process  702  may be a payload delivery control process. Although PWM servo commands are described, any type of servo command signal and servo command generation unit may be used, such as serial data bus, analog phase/amplitude, etc. 
     Second processing system  232  includes one or more support processes  708  that are also associated with the first UAV function. By way of example, support processes  708  may include a de-serializer process in some examples. The de-serializer process may receive serial PWM servo commands and generate PWM commands that can be stored in the buffer. Support processes  708  provide an output  726  to process monitor/controller  710 . Process monitor/controller  710  is configured to determine whether primary control process  702  is generating a valid output. In one example, process monitor/controller  710  is configured to determine whether an output  726  is received from support processes  708  in order to determine whether the primary control process  702  is generating a first output  722 . In another example, process monitor/controller  710  is configured to determine whether an output  724  is received by support processes  708  in order to determine whether the primary control process  702  is generating a first output  722  that is valid. In another example, process monitor/controller  710  is configured to determine whether the content of output  726  is valid in order to determine whether first output  722  is valid. If process monitor/controller  710  determines that the first output  722  is valid, an output  728  is provided. In one example, output  728  includes PWM servo commands received from support processes  708 . 
     Support processes  708  are further configured to receive a second output  732  from a backup control process  706  executed by APU  326  of the second processing system  232 . For example, backup control process  706  may be a backup autopilot process or a backup payload delivery process. Support processes  708  may receive commands from the backup autopilot process and generate PWM servo commands in one example. Support processes  708  generate an output  734  which is provided to process monitor/controller  710 . If process monitor/controller  710  determines that the output  722  of the primary control process  702  is invalid, it can generate an output  736  including the output  732  of the backup control process. 
     In some implementations, processor monitor/controller  710  may determine whether the first output  722  of the first processing system  230  is valid based on comparing the first output to the second output  732  from the second processing system. For example, process monitor/controller  710  can determine whether the first output  722  and the second output  732  match or are otherwise have a concurrence. If there is a concurrence between the first output  722  and the second output  732 , the processor monitor/controller  710  may determine that the first output  722  is valid. 
       FIG.  11    is a specific example where process monitor/controller  710  enables a backup control process  706  in response to an invalid output associated with the primary control process  702 . In other examples, process monitor/controller  710  can be configured to enable a vehicle device or initiate a particular function based on the output of a process executed by each processing system. For example, a payload delivery system may be enabled or activated based on a concurrence between an output generated by the first processing system and an output generated by the second processing system. 
     Referring now to  FIG.  12   , additional details of processing system  230  of control box  100  are described in accordance with example embodiments of the disclosed technology. More particularly,  FIG.  12    is a block diagram depicting a subset of the hardware components of first processing system  230 , along with an example of a software architecture used to control the hardware components. 
       FIG.  12    depicts the various processing elements of processing system  230  as hardware layer  801 . More specifically, hardware layer  801  includes the volatile programmable logic array  305 , real-time processing unit (RPU)  310 , and application processing unit (APU)  306 . Although not shown, hardware layer  801  may also include graphics processing unit  308  and other computing elements.  FIG.  12    additionally depicts an operating system layer  803  provisioned from the hardware layer  801 . A virtual machine layer  807  is provisioned using a hypervisor  810  or other virtualization layer to virtualize one or more processors. 
     A standalone operating system (OS)  802  is provisioned in operating system layer  803  using at least a first processor of processing system  230 . In the particular example of  FIG.  12   , the standalone OS  802  is provisioned using real-time processing unit (RPU)  310 . The standalone OS  802  may be provisioned to control one or more processors of RPU  310 . In some examples, standalone OS  802  is a lightweight or simple operating system configured to manage critical processes or applications of UAV  10 . For instance,  FIG.  12    depicts one or more critical vehicle control processes  804  and one or more critical mission control processes  806  that been configured for execution by standalone OS  802 . In some examples, OS  802  is configured to only execute critical vehicle control processes  804 . In other examples, OS  802  is configured to only execute critical mission control processes  806 . 
     In various examples, critical vehicle control processes may refer to a category or class of control processes that are critical to safe operation of UAV  10 . Various criteria may be used to classify different processes. For example, certain aviation standards may specify that vehicle and/or mission processes including computer readable instructions be subject to various levels of certification. These levels of certification may be applied in order to guarantee or to increase safe operation of UAV  10 . Thus, critical vehicle control process  804  and critical mission control processes  806  may refer in some examples to control processes that are subject to a highest level certification. However, it will be appreciated that other control processes at lower levels of certification may also be deemed critical for placement in standalone OS  802  in various implementations. In examples, a primary autopilot process is a critical vehicle control process  804 . In examples, a process for controlling at least one propulsion and movement device of the UAV is a critical vehicle control process. 
     A hypervisor  810  is provisioned using the application processing unit (APU)  306 . In another example, hypervisor  810  may be used to virtualize APU  306  and/or volatile programmable logic array  305 . For example, the FPGA may be used as computational resources for the virtualized APU  306 . Hypervisor  810  may be executed by APU  306  in some examples. While a hypervisor  810  is depicted in  FIG.  12   , other techniques for virtualizing hardware processing elements may be used. 
     Multiple domains including domain  820  (DOM 0 ), domain  830  (DOM 1 ), and domain  840  (DOM 2 ) are provisioned in virtual machine layer  807  using hypervisor  810 . It will be appreciated that three domains are depicted by way of example only, as any number of domains may be provisioned in accordance with a particular implementation. In  FIG.  12   , domain  820  is a host domain provisioned to manage the other virtual machines and virtual machine layer  807 . Domain  820  includes a virtual machine (VM) manager  822 , an input output (I/O) mediator  824 , and a host operating system (OS)  836 . VM manager  822  can manage provisioning of virtual machines using hypervisor  810 . I/O mediator  824  can mediate communications such as packets, objects, or other data between virtual machines and between a virtual machine and the underlying layers of computing system  230 . 
     Domain  830  is a first guest domain configured using hypervisor  810 . In  FIG.  12   , domain  830  hosts a first virtual machine (VM)  838 . In the example depicted, the first virtual machine  838  is a real-time virtual machine. For instance, domain  830  can be configured to execute real-time processes. Real-time processes may include processes that need fast execution to deliver results for vehicle and/or mission control functions. In some examples, domain  830  may be provisioned using RPU  310 . In other examples, domain  830  may be provisioned using APU  306 . A first guest operating system (OS 1 )  836  is provisioned for the real-time virtual machine  838 . Domain  830  configures real-time VM  838  to execute vehicle control processes  832  and first mission control processes  834 . In some examples, vehicle control processes  832  are at a lower certification level than critical vehicle control processes  804 . Similarly, first mission control processes  834  may be at a lower certification level than critical mission control processes  806 . In some examples, a primary navigation process may be a vehicle control process  832 . For example, an overall navigation process including an autopilot navigation process may be configured in domain  830 . A primary autopilot process may be configured in the standalone operating system. 
     Domain  840  is a second guest domain configured using hypervisor  810 . In  FIG.  12   , domain  840  hosts a second virtual machine (VM)  846 . In the example depicted, the second virtual machine  846  is a non-real-time virtual machine. For instance, domain  840  can be configured to execute less time critical processes. Less time critical processes may include high intensive computing requirements in some examples. For example, sensor processing of dense sensor data such as may be acquired by various image, radar, lidar, or other sensors may be executed in virtual machine  846 . In some examples, domain  840  may be provisioned using RPU  310 , APU  306 , and/or volatile programmable logic array  305 . A second guest operating system (OS 2 )  844  is provisioned for the non-real-time virtual machine  846 .  FIG.  12    depicts a set of second mission control processes  842  executed by virtual machine  846 . In some examples, second mission control processes  842  are at a lower certification level than mission control processes  834 . Although not shown, vehicle control processes may also be configured for execution by domain  840 . 
     Standalone OS  802  is an example of a first partitioned operating environment. More particularly, standalone OS  802  is part of a first hardware partition  809  corresponding to RPU  310 . Domain  820  is an example of a second partitioned operating environment. More particularly, domain  820  is part of a second hardware partition  811  corresponding to APU  306 . Hardware partition  811  includes software partitions  813 ,  815 , and  817  from a virtualization of APU  306 . Domain  820  is a part of software partition  813 . Domain  830  is an example of a third partitioned operating environment. More particularly, domain  830  is part of the second hardware partition  811  and the second software partition  815 . Domain  840  is an example of a fourth partitioned operating environment. More particularly, domain  840  is part of the second hardware partition  811  and the third software partition  817 . 
     Accordingly, standalone OS  802 , domain  820 , domain  830 , and domain  840  are isolated from one another using hardware partitions and/or software partitions. Specifically, standalone OS  802  is in its own hardware partition and thus, it is isolated from operating systems  826 ,  836 , and  844 , including virtual machines  838  and  846 . Domains  820 ,  830 , and  840  including virtual machines  838  and  846  are in the same hardware partition  811 . However, each domain and corresponding virtual machine are in isolated software partitions. 
     In the specific example of  FIG.  12   , standalone OS  802  can be a high integrity partition configured for critical processes. By isolating (also referred to as partitioning) standalone OS  802  from other domains, high levels of certifications as may be required for critical vehicle control processes  804  and critical mission control processes  806  may not be required for processes executed in the other domains. In one example, standalone OS  802  is provisioned from RPU  310 . On the other hand, the other domains  820 ,  830 ,  840  are provisioned using APU  306 . In this manner, standalone OS  802  is a hardware partitioned operating environment. That is, standalone OS  802  is provisioned using different hardware than the other domains as well as using a separately provisioned operating system. 
       FIG.  12    depicts one example of a software system configured for processing system  230 . It will be appreciated that a similar software system may be configured for processing system  232 , although this is not required. 
       FIG.  13    is a flowchart describing a process  900  of configuring a software system for a control system in accordance with example embodiments of the disclosed technology. Process  900  may be performed by any one of the processing units and/or programmable logic arrays of processing systems  230  or  232 . In other examples, process  900  may be performed by another computing system. 
     At ( 902 ), a first operating system is provisioned using a first processing unit of an integrated circuit. For example, a standalone operating system  802  may be provisioned at RPU  310  as shown in  FIG.  12   . The standalone operating system may be a high integrity partition in some examples. For example, the standalone operating system may be a high integrity partitioned operating environment isolated from other operating environments. 
     At ( 904 ), one or more critical vehicle control processes and/or critical mission control processes are configured in the standalone operating system. For example, the standalone operating system may be configured to execute critical vehicle and/or mission control processes. In some examples, critical vehicle control processes are used to control at least one propulsion and movement device the UAV. 
     At ( 906 ), a virtualization layer is created using a second processing unit. For example, a hypervisor can be configured using an application processing unit such as APU  306  as shown in  FIG.  12   . 
     At ( 908 ), other processing elements can be virtualized. It is noted that ( 908 ) is optional and is not required to be performed. By way of example, ( 908 ) may include virtualizing a portion of programmable logic array  305 . 
     At ( 910 ), a first virtual machine is provisioned from the virtualization layer. For example, a first virtual machine such as real-time VM  838  can be provisioned in a first domain  830  as shown in  FIG.  12   . Provisioning the first virtual machine may include provisioning the first virtual machine using the second processing unit. For example, the first virtual machine may be provisioned using APU  306 . The first virtual machine is a partitioned operating environment isolated from the standalone operating system in example embodiments. More particularly, the first virtual machine is in a different hardware partition relative to the standalone operating system. For example, the first virtual machine may be associated with APU  306  while the standalone operating system is associated with RPU  310 . In this manner, standalone operating system  802  may be considered a high integrity partition due to its hardware and software isolation from other operating environments. 
     At ( 912 ), additional vehicle and/or mission control processes are configured in the first virtual machine. For example the first virtual machine can be configured to execute one or more vehicle control processes and/or mission control processes. It examples, the vehicle and mission control processes configured for execution at ( 912 ) are at a lower certification level than those configured at ( 904 ). The first virtual machine can be isolated from the standalone operating system. In this manner, computer readable instructions associated with the vehicle and/or mission control processes at ( 912 ) may not be subject to the same level of certification as vehicle and/or mission control processes at ( 904 ). 
     At ( 914 ), a second virtual machine is provisioned from the virtualization layer. For example, a second virtual machine such as non-real-time VM  846  can be provisioned at a second domain  840  as shown in  FIG.  12   . The second virtual machine may include a second operating system. For example, a guest operating system such as guest OS 1   836  as shown in  FIG.  12    may be provisioned in the second virtual machine. Provisioning the second virtual machine may include provisioning the second virtual machine using the second processing unit. For example, the second virtual machine may be provisioned using APU  306 . 
     At ( 916 ), additional vehicle and/or mission control processes may be configured at the second virtual machine. For example, the second virtual machine can be configured to execute one or more vehicle control processes and/or mission control processes at a lower certification level than those of ( 912 ). The second virtual machine can be isolated from the standalone operating system and the first virtual machine. In this manner, computer readable instructions associated with the vehicle and/or mission control processes at ( 916 ) may not be subject to the same level of certification as vehicle and/or mission control processes at ( 912 ). The second virtual machine is in a different hardware partition relative to the standalone operating system. The second virtual machine is in a different software partition relative to the first virtual machine. 
     In accordance with example embodiments, programmable logic array  305  and/or  325  may be configured with one or more computational accelerators for onboard sensor processing and other vehicle control and/or mission control processes. One or more memory blocks  234  can be dedicated to the programmable logic arrays in order to facilitate accelerated processing. Such processes may be suitable for image classification, object detection and tracking, sensor relative navigation, robotic perception/cognition, geo-registration of sensor collection for targeting and alternative navigation sources for example, as well as software defined radio including signal interference collection and flexible data links for payload data dissemination. 
       FIG.  14    is a flowchart describing a process  924  for virtualizing at least a portion of the programmable logic array in accordance with example embodiments of the disclosed technology to configure a computational accelerator. For example, process  920  may be used to configure a flash-based FPGA and/or a RAM-based FPGA. 
     At ( 922 ), one or more computational accelerators are configured in a programmable logic array. For example, ( 922 ) may include providing configuration data to an FPGA for configuring the FPGA as a computational accelerator. 
     At ( 924 ), at least a portion of the computational accelerator is virtualized. In various examples, ( 924 ) may include virtualizing an FPGA and configuring the FPGA in accordance with configuration data for a computational accelerator. Block  924  may include virtualizing an instance of the computational accelerator without virtualizing the entire FPGA. 
     At ( 926 ), at least one interface for accessing the virtualized computational accelerator is provided. For example, one or more protocols for exchanging objects and or other data units may be established for interfacing with the computational accelerator. In this manner, the computational accelerator can be configured to receive objects from other processing elements such as a processing unit and generate an output based on accelerated computations performed on the object. Accordingly, a first process executing at a processing unit may interface with a second process executing in the FPGA. The first process may pass objects or other data to the FPGA for faster computational processing. Results may then be received and used within the first process at the processing unit. In this manner, a processing system may provide a uniquely situated architecture for handling the unique processing needs of a UAV. 
       FIG.  15    is a flowchart describing a process  940  of using a virtualized architecture for accessing a computational accelerator for onboard sensor processing associated with the UAV in accordance with example embodiments of the disclosed technology. At ( 942 ), an object including an output from a process executing in a virtual machine of the processing system is received at a programmable logic array. For example, the object may be received from a first vehicle control process executing in a virtual machine provisioned at APU  306 . 
     At ( 944 ), the object is input to a computational accelerator configured in the programmable logic array. The object can be input to the computational accelerator using an interface configured for accessing the accelerator. In one example, the interface is provided by virtualizing the computational accelerator in the FPGA. In another example, the interface is provided without virtualizing the computational accelerator. 
     At ( 946 ), and output is generated using the computational accelerator in the FPGA. In one example the output includes an object including a value calculated using the computational accelerator. In another example, the output includes a value which is then placed into an object by the interface configured for the computational accelerator. 
     At ( 948 ), an object including an output from the computational accelerator is provided to the virtual machine from which the original object was received at ( 942 ). At ( 950 ), the object from the FPGA is accessed and the output from the computational accelerator processed at the virtual machine. In this manner, an object from the virtual machine can be passed to the FPGA and an output return from the computational accelerator. The output from the computational accelerator can then be used again by the process executing the virtual machine. 
     Referring now to  FIGS.  16  through  20   , further embodiments of improved control boxes  100  and components thereof are generally provided. As discussed, control box  100  in accordance with the present disclosure generally houses the various electrical/computing components which control operation of an unmanned aerial vehicle (“UAV”), and the control box  100  is thus generally mounted on the UAV. Control boxes  100  in accordance with the present disclosure are particularly advantageous due to their modular design, wherein various components of the control boxes  100  such as the heat sink, cover, and/or stiffener, as discussed herein, are each interchangeable with various different designs for each such component. Certain features as discussed herein help to facilitate such modularity. Additionally, as discussed herein, various features of such control boxes  100  such as the heat sink, the stiffener, and the system on module (“SOM”) circuit board include advantageous heat transfer features for transferring heat from the SOM circuit board and from the control box  100  generally. Other advantageous features will be discussed herein. 
     A control box  100  in accordance with the present disclosure may define a lateral direction  102 , a longitudinal direction  104 , and a transverse direction  106 , as shown. Such directions  102 ,  104 ,  106  may together define an orthogonal coordinate system for the control box  100 . 
     Control box  100  may include a housing  110  which defines an interior  112 . The housing  110  in exemplary embodiments includes a cover  114  and one or more stiffeners  116 . In some embodiments, only a single stiffener  116  is utilized in a control box  100 , although in alternative embodiments more than one stiffener  116  may be utilized. In embodiments wherein the housing  110  includes a cover  114  and stiffener(s)  116 , at least one such stiffener  116  is removably connected in contact with the cover  114 , and the stiffeners  116  are stacked on each other and the housing  110  along the transverse direction  106 . Control box  100  may further include a heat sink  118 . The heat sink  118  may be removably connected to the housing  110 , such as in contact with one of the plurality of stiffeners  116 . The heat sink  118  may further be stacked on the stiffeners  116  and the housing  110  along the transverse direction  106 . 
     One or more circuit boards may be disposed within the interior  112 . For example, a first circuit board  120  may be disposed in the interior  112 . In exemplary embodiments, the first circuit board  120  is a system on module (“SOM”) circuit board such as the example SOM circuit board  200  as discussed herein. Such first circuit board  120  may in exemplary embodiments be positioned between the housing  110  and the heat sink  118 , such as between a stiffener  114  and the heat sink  118 . Further, the first circuit board  120  may be in contact with the heat sink  118  such that heat from the first circuit board  120  is dissipated from the first circuit board  120  through the heat sink  118 . Additionally, the first circuit board  120  may be in contact with a stiffener  114 . 
     For example, the first circuit board  120  may include one or more computing components. Such computing components may include a first processing system  230 , a second processing system  232 , and/or one or more memory blocks  234 , all of which are discussed in detail herein, such as in the context of SOM circuit board  200 . Further, a thermal interface material  236  (discussed in detail below in the context of SOM circuit board  200 ) may be disposed on one or more of such computing components. In exemplary embodiments, the first circuit board  120 , such as the thermal interface material  236  disposed on one or more of the computing components, may contact the heat sink  118  and/or a stiffener  116 . 
     In some embodiments, the thermal interface material  236  may be in contact with the heat sink  118 . In particular, the thermal interface material  236  that is disposed on one or more computing components (such as first processing system  230 , a second processing system  232 , and/or one or more memory blocks  234  that are mounted on a first face surface  210  of the circuit board  120  as discussed below in the context of the SOM circuit board  200 ) may be in contact with the heat sink  118 , such as a base  130  thereof. 
     Additionally or alternatively, the stiffener  116  may include a plurality of fingers  140 . Fingers  140  are generally planer inner surfaces of the stiffener  116  which contact other components for support and heat transfer purposes. The first circuit board  120  may contact such fingers  140 . In particular, the thermal interface material  236  that is disposed on one or more computing components (such as one or more memory blocks  234  that are mounted on a second face surface  212  of the circuit board  120  as discussed below in the context of the SOM circuit board  200 ) may be in contact with the fingers  140 . 
     In exemplary embodiments, the stiffener  116  includes an outer frame  142  and one or more cross-members  144 . Stiffener  116  may additionally include fingers  140 . When first circuit board  120  contacts stiffener  116 , the first circuit board  120  may contact the outer frame  142  and/or one or more of the cross-members  144 , and may further contact fingers  140  as discussed above. 
     In exemplary embodiments, heat sink  118  is formed from a metal. Heat sink  118  may include a base  130 . Base may in exemplary embodiments be in contact with the first circuit board  120 , such as components thereof as discussed above. Further, in some exemplary embodiments (not shown), heat sink  118  may include a plurality of fins  132  which extend externally from the base  130 . In these embodiments, heat sink  118  may provide convective heat transfer from the control box  100  via fins  132 . In other embodiments, as illustrated in  FIGS.  16 - 20   , no fins  132  may be provided and heat sink  118  may provide conductive heat transfer from the control box  100  via contact of the base  130  with other components in, for example, the subject UAV to which the control box  100  is mounted. In still other embodiments, heat sink  118  may further include single use or reversible phase change materials, liquid cooling materials, and/or other suitable components for facilitating heat transfer. 
     Control box  100  may further include a second circuit board  122 . Second circuit board  122  may, for example, be a carrier card-type circuit board which generally includes communications related components, such as sonar, radar, GPS, radio, etc. related components, including various integrated circuits forming interface circuits. The second circuit board may be disposed within the interior  112 . For example, such second circuit board  122  may in exemplary embodiments be positioned between the cover  114  and the stiffener  116 . Further, the second circuit board  122  may be in contact with the stiffener  116 . 
     In example embodiments, second circuit board  122  is in operative communication with first circuit board  120 . For example, second circuit board  122  may further include one or more input/output connectors  124  which are positioned on the second circuit board  122  to operatively contact mating input/output connectors (such as connectors  238  in SOM circuit board  200  embodiments) of the first circuit board  120 . 
     In some embodiments, second circuit board  122  may further include one or more sensor connectors  125 . Such sensor connectors  125  may extend from the housing  110 , such as along the longitudinal direction  104  as shown in  FIGS.  16    through  18  or in another suitable direction. These sensor connectors  125  may be ports for connection of the second circuit board  122  to suitable external sensors or other secondary devices  12  (such as those discussed herein) which may, for example, be mounted on the UAV on which the control box  100  is mounted. 
     Control box  100  may additionally include one or more input/output connectors  126  which extend from the housing  110 . In exemplary embodiments, one or more of such connector(s)  126  are components of the second circuit board  122 . Such input/output connectors  126  may connect the control box  100  and components thereof to other components of, for example, the UAV on which the control box  100  is mounted. In some embodiments, as illustrated in  FIGS.  16 - 20   , the input/output connector(s)  126  extend from the housing  110  along the longitudinal direction  104 , such as through an end faceplate  115  of the housing  110 . In other embodiments, the input/output connector(s)  126  extend from the housing  110  along the transverse direction  106 , such as through the cover  114 . 
     In some embodiments, control box  100  may further include a mezzanine card  128 . Mezzanine card  128  may be disposed within interior  112 , and may be in operative communication with the second circuit board  122 . Mezzanine card  128  may, for example, be disposed between second circuit board  122  and cover  114 . In some embodiments, one or more of the input/output connectors  126  are components of the mezzanine card  128 . 
     As shown, the heat sink  118  and components of the housing  110  may include through-holes. The various through-holes may advantageously align to facilitate the modularity of the various components of control box  100 . For example, a plurality of through holes  150  may extend through the base  130  of heat sink  118 , such as along the transverse direction  106 . Such through holes  150  may be arranged in a pattern. Further, a plurality of through holes may extend through the housing  110 , such as along the transverse direction  106 . Such through holes may be arranged in a pattern. Such through holes may, for example, include through holes  152  which extend through the cover  114  along the transverse direction  106  and in a pattern, and through holes  154  which extend through the stiffener  116  along the transverse direction  108  and in a pattern. In exemplary embodiments, the patterns of through holes in the base  130  and housing  110 , such as the through holes  150 ,  152 , and  154 , are identical. Accordingly, fasteners may be inserted through the through holes  150 ,  152 ,  154  to fasten such components of the control box  100  together. Notably, such identical pattern may extend to a variety of different types of heat sinks  118  and housings  110  (and covers  114  and stiffeners  116  thereof), such that different versions of such components can be swapped with each other in a module fashion. 
     When the heat sink  118  contacts the housing  110 , such as the stiffener  116  thereof, such components may fit together using a “tongue-and-groove” type feature. Such feature advantageously orients the components relative to one another to ensure a proper fit, and also advantageously acts as an electro-magnetic interference (“EMI”) filter. 
     Referring now to  FIGS.  19  and  20   , a control box  100  in accordance with the present disclosure may include a system on module (“SOM”) circuit board  200 , which may be the first circuit board  120  as discussed above. The SOM circuit board  200  may define a lateral direction  202 , a longitudinal direction  204 , and a transverse direction  206 , as shown. Such directions  202 ,  204 ,  206  may together define an orthogonal coordinate system for the SOM circuit board  200 . When the SOM circuit board  200  is installed in a control box  100 , the directions  202 ,  204 ,  206  may correspond to the respective directions  102 ,  104 ,  106 . 
     SOM circuit board  200  may have a main body  208  which includes a plurality of outer surfaces. For example, main body  208  includes a first face surface  210  and a second opposing face surface  212 , both of which generally extend within planes defined by the lateral direction  202  and longitudinal direction  204 . Main body  208  further includes a first end surface  214  and an opposing second end surface  216 , both of which generally extend within planes defined by the lateral direction  202  and the transverse direction  206 . Main body  208  further includes a first side surface  218  and an opposing second side surface  220 , both of which generally extend within planes defined by the longitudinal direction  204  and the transverse direction  206 . 
     In generally, the SOM circuit board  200  and main body  208  thereof has a hyperrectangular shape, as shown. Accordingly, first and second end surface  214 ,  216  also each have a length  222 , which is a maximum length along the lateral direction  202 . First and second side surfaces  218 ,  220  each also have a length  224 , which is a maximum length along the longitudinal direction  204 . As shown, in exemplary embodiments, the maximum lengths  224  are greater than the maximum lengths  222 . 
     The SOM circuit board  200  may further include a plurality of computing components. Each computing component may be mounted on the main body  208 , such as on the first face surface  210  or second face surface  212 . For example, the computing components may include a first processing system  230 , a second processing system  232 , and a plurality of memory blocks  234 . Notably, the first and second processing systems  230 ,  232  and the memory blocks  234  may in exemplary embodiments be integrated together in a cohesive computing system with the two processing systems  230 ,  232  operating together. Accordingly, for example, the first processing system  230  can monitor and back up the second processing system  232  and the second processing system  232  can monitor and back up the first processing system  230 . 
     In some embodiments, for example, the first processing system  230  may be a random access memory (“RAM”) based processing system. Additionally or alternatively, the second processing system  232  may in some embodiments be a flash memory-based processing system. Additionally or alternatively, the memory blocks  234  may be RAM memory blocks. 
     As shown, in exemplary embodiments, the first and second processing systems  230 ,  232  may be mounted on the first face surface  210  of the main body  208 . Alternatively, however, one or both of the first and second processing systems  230 ,  232  may be mounted on the second face surface  212  of the main body  208 . Further, in some embodiments, at least one or more of the memory blocks  234  may be mounted on the first face surface  210 . Additionally or alternatively, at least one or more of the memory blocks  234  may be mounted on the second face surface  212 . 
     In some embodiments, a thermal interface material  236  may be disposed on one or more of the computing components. The thermal interface material  236  may facilitate heat transfer from such computing components to other components of the control box  100 , as discussed herein. Suitable thermal interface materials  236  may, for example, be relatively compliant materials which may for example be curable. In exemplary embodiments, such materials  236  may be thixotropic materials. In exemplary embodiments, such materials  236  may have a thermal conductivity of between 3.2 and 4 W/m-K, such as between 3.4 and 3.8 W/m-K, such as 3.6 W/m-K. One suitable materials is Gap Filler 3500S35, which is commercially available from The Bergquist Company. 
     In exemplary embodiments, the thermal interface material  236  may be disposed on the memory blocks  234 , such as one or more of the memory blocks  234  mounted on the first face surface  210  and/or one or more of the memory blocks  236  mounted on the second face surface  212 . Additionally or alternatively, the thermal interface material  236  may be disposed on the first processing system  230  and/or the second processing system  232 . 
     One or more input/output connectors  238  may additionally be mounted on the main body  208 . These connectors  238  may connect the SOM circuit board  200  to other circuit boards, as discussed herein, in the control box  100 , thus allowing communication between the SOM circuit board  200  and such other circuit boards. The connectors  238  may, for example, be mounted on the second face surface  212  as shown, or alternatively may be mounted on the first face surface  210 . In some embodiments, the connectors  238  may be disposed proximate the first side surface  218 , and thus closer to the first side surface  218  than the second side surface  220  along the lateral direction  202 . In some of these embodiments, no connectors  238  may be provided proximate the second side surface  220 . Further, longitudinal axes of the connectors  238  may be aligned along the longitudinal direction  204 , as shown. 
     As further illustrated, a plurality of mounting holes  240  may extend through the main body  208 . One or more of these mounting holes  240  may, for example, be utilized to connect the SOM circuit board  200  to other components in the control box  100 . Each mounting hole  240  may extend along the transverse direction  206  through and between the first face surface  210  and the second face surface  212 . 
     The locations of the mounting holes  240  in the main body may be particularly advantageous. For example, a first array  242  of the mounting holes  240  may be disposed proximate the first side surface  218 , and in exemplary embodiments between the connectors  238  and the first side surface  218  along the lateral direction  202 . The mounting holes  240  of the first array  242  may be spaced apart from each other along the longitudinal direction  204 . In exemplary embodiments, the first array  242  may include three or more mounting holes, although in alternative embodiments two mounting holes may be utilized. A second array  244  of the mounting holes  240  may be disposed proximate the second side surface  220 , and in exemplary embodiments may be spaced along the lateral direction  202  an equal distance from the second side surface  220  as the first array  244  is from the first side surface  218 . The mounting holes  240  of the second array  244  may be spaced apart from each other along the longitudinal direction  204 . In exemplary embodiments, the second array  244  may include three or more mounting holes, although in alternative embodiments two mounting holes may be utilized. The first and second arrays may advantageously both connect the SOM circuit board  200  to other components in the control box  100  and minimize any relative motion of the SOM circuit board  200  with respect to such components. 
     Additionally, one or more third mounting holes  246  may be disposed between the first array  242  and the second array  244  along the lateral direction  202 . In exemplary embodiments, the one or more third mounting holes  246  may be positioned generally centrally between the first side surface  218  and the second side surface  220 , such as along the lateral direction  202 . The third mounting holes  246  may this be equally spaced from the first array  242  and the second array  244  along the lateral direction  202 . Further, in embodiments wherein only a single third mounting hole  246  is utilized, the third mounting hole  246  may be positioned generally centrally between the first end surface  214  and the second end surface  216 , such as along the longitudinal direction  204 . The third mounting hole(s)  246  may be particularly advantageous, as such hole(s)  246  reduce resonant frequency issues during use of the SOM circuit board  200  and provide improved stiffness to the SOM circuit board  200 . 
     In some embodiments, a plurality of vias  250  may be provided in SOM circuit board  200 . Each via may extend through the body  208  along the transverse direction  206 , and may protrude from the first face surface  210  and/or second face surface  212 . Vias  250  may be located proximate the first side surface  218  and/or the second side surface  220 . Vias  250  may in exemplary embodiments be formed from a metallic material, such as gold or copper, and may serve as heat transfer conduits to transfer heat from within the main body  208  and transfer this heat from the main body  208  and SOM circuit board  200  generally. 
     In some embodiments, one or more metallic coatings may be plated on the main body  208 , such as on the first face surface  210  and/or second face surface  212  thereof. The metallic coatings may serve as heat transfer conduits to transfer heat from the main body  208  and SOM circuit board  200  generally. 
     For example, a first metallic coating  252  may be plated on portions of the body  208  (such as on the first face surface  210  and/or second face surface  212  thereof) defining the plurality of mounting holes  240  (including those mounting holes in the first and second arrays  242 ,  244  as well as the third mounting hole(s)  246 . Such coating  252  may be discretely plated on such portions of the body  208 , such that the various platings are not connected. In exemplary embodiments, such first metallic coating  252  is a copper coating, although in alternative embodiments gold or other suitable metals may be utilized. 
     Additionally or alternatively, a second metallic coating  254  may be plated the body  208  (such as on the first face surface  210  and/or second face surface  212  thereof). Such coating  252  may be located proximate the first and second side surfaces  218 ,  220 , and may extend to such surfaces  218 ,  220 , such as entirely along the length  224 . In embodiments wherein both first and second metallic coatings  252 ,  254  are utilized, the second metallic coating  254  may be plated over the first metallic coating  252 . In exemplary embodiments, such second metallic coating  254  is a gold coating, although in alternative embodiments copper or other suitable metals may be utilized. 
     Some embodiments of the disclosed technology may be implemented as hardware, software, or as a combination of hardware and software. The software may be stored as processor readable code and implemented in a processor, as processor readable code for programming a processor for example. In some implementations, one or more of the components can be implemented individually or in combination with one or more other components as a packaged functional hardware unit (e.g., one or more electrical circuits) designed for use with other units, a portion of program code (e.g., software or firmware) executable by a processor that usually performs a particular function of related functions, or a self-contained hardware or software component that interfaces with a larger system, for example. Each hardware unit, for example, may include an application specific integrated circuit (ASIC), a Field Programmable Gate Array (FPGA), a circuit, a digital logic circuit, an analog circuit, a combination of discrete circuits, gates, or any other type of hardware or combination thereof. Alternatively or in addition, these components may include software stored in a processor readable device (e.g., memory) to program a processor to perform the functions described herein, including various mission and vehicle control processes. 
     Processing units can include any number and type of processor, such as a microprocessor, microcontroller, or other suitable processing device. Memory device(s) can include one or more computer-readable media, including, but not limited to, non-transitory computer-readable media, RAM, ROM, hard drives, flash drives, or other memory devices. 
     Memory blocks  234  and other memory described herein may can store information accessible by one or more processing units or logic array, including computer-readable instructions that can be executed by the one or more processor(s). The instructions can be any set of instructions that when executed by a processor, cause the processor to perform operations. The instructions can be software written in any suitable programming language or can be implemented in hardware. In some embodiments, the instructions can be executed by a processor to cause the processor to perform operations, such as the operations for controlling vehicle and/or mission functions, and/or any other operations or functions of a computing device. 
     The technology discussed herein makes reference to computer-based systems and actions taken by and information sent to and from computer-based systems. One of ordinary skill in the art will recognize that the inherent flexibility of computer-based systems allows for a great variety of possible configurations, combinations, and divisions of tasks and functionality between and among components. For instance, processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memory, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can operate sequentially or in parallel. 
     Although specific features of various embodiments may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of the present disclosure, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing. 
     This written description uses examples to disclose the claimed subject matter, including the best mode, and also to enable any person skilled in the art to practice the claimed subject matter, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the disclosed technology is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.