Abstract:
One embodiment of the present invention is a unique platform. Another embodiment is a unique engine system. Another embodiment is a unique wiring harness system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for one or more of various types of platforms, such as aircraft, ground vehicles, water-borne vessels and stationary platforms; engine systems; and wiring harness systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
       [0001]    The present application claims benefit of U.S. Provisional Patent Application No. 61/581,517 filed Dec. 29, 2011, entitled AIRCRAFT, AIRCRAFT ENGINE SYSTEM AND WIRING HARNESS SYSTEM, which is incorporated herein by reference. 
     
    
     GOVERNMENT RIGHTS 
       [0002]    The present application was made with the United States government support under Contract No. N00019-03-C-0057, awarded by the United States Navy. The United States government may have certain rights in the present application. 
     
    
     FIELD OF THE INVENTION 
       [0003]    The present invention relates to engine powered machines, and more particularly, to platforms of various types having wiring harnesses. 
       BACKGROUND 
       [0004]    Platforms, such as aircraft, ships, vehicles and stationary platforms; engines for platforms; and wiring harness systems that effectively protect against electromagnetic interferences remain an area of interest. Some existing systems have various shortcomings, drawbacks, and disadvantages relative to certain applications. Accordingly, there remains a need for further contributions in this area of technology. 
       SUMMARY 
       [0005]    One embodiment of the present invention is a unique platform. Another embodiment is a unique engine system. Another embodiment is a unique wiring harness system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for one or more of various types of platforms, such as aircraft, ground vehicles, water-borne vessels and stationary platforms; engine systems; and wiring harness systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0006]    The description herein makes reference to the accompanying drawings wherein like reference numerals refer to like parts throughout the several views, and wherein: 
           [0007]      FIG. 1  illustrates some aspects of a non-limiting example of a platform in the form of an aircraft in accordance with an embodiment of the present invention. 
           [0008]      FIG. 2  schematically illustrates some aspects of non-limiting examples of a platform in the form of an aircraft and an engine in accordance with an embodiment of the present invention. 
           [0009]      FIG. 3  schematically illustrates some aspects of a non-limiting example of a wiring harness in accordance with an embodiment of the present invention. 
           [0010]      FIG. 4  schematically illustrates some aspects of a non-limiting example of a junction box in accordance with an embodiment of the present invention. 
       
    
    
     DETAILED DESCRIPTION 
       [0011]    For purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments illustrated in the drawings, and specific language will be used to describe the same. It will nonetheless be understood that no limitation of the scope of the invention is intended by the illustration and description of certain embodiments of the invention. In addition, any alterations and/or modifications of the illustrated and/or described embodiment(s) are contemplated as being within the scope of the present invention. Further, any other applications of the principles of the invention, as illustrated and/or described herein, as would normally occur to one skilled in the art to which the invention pertains, are contemplated as being within the scope of the present invention. 
         [0012]    Referring to  FIG. 1 , there are illustrated some aspects of a non-limiting example of a platform  10  in accordance with an embodiment of the present invention. In one form, platform  10  is an aircraft. In other embodiments, platform  10  may be, for example, a ground vehicle, such as a battle tank, a mobile weapon system, an armored personnel carrier, a personal, troop or supply transport vehicle or the like; a water-borne vessel, such as a skiff, a boat, a ship, a landing craft or the like; or a stationary platform, such as a generating or pumping station or system, or any platform having a system controlled by control system and/or a system that interfaces with one or more control systems, sensors, and/or other systems or devices. Platform  10  includes one or more structures  11 . In one form, structure  11  is an airframe having a fuselage  12 , wings  14  and an empennage  16 . In other embodiments, other structures  11  may be employed in place of airframe structures. For example, structures  11  may be or include a ground vehicle frame, body and/or chassis; one or more structures of a water-borne vessel, e.g., a bridge, propulsion system structures and/or related control structures, generator system structures, flight deck structures, navigation and/or communication system structures; stationary system structures and the like. Platform  10  also includes one or more controlled systems  18  that are electrically and/or electronically operated and/or controlled, and includes external pods  20 . In one form, a controlled system  18  is an engine, referred to herein as engine  18  (e.g., wherein four engines  18  in the form of propulsion engines are illustrated in the non-limiting example of  FIG. 1 ). In other embodiments, controlled system  18  may take other forms, e.g., a transmission, a weapon system, or any other system that is electrically and/or electronically operated and/or controlled. 
         [0013]    In one form, wings  14  and empennage  16  are coupled to fuselage  12 ; and engines  18  and external pods  20  are coupled to wings  14 . In other embodiments, other coupling arrangements of fuselage  12 , wings  14 , empennage  16 , one or more engines  18  and/or one or more external pods  20  may be employed. In one form, as an aircraft, platform  10  is a multi-engine military turboprop aircraft. In other embodiments, platform  10  may be any fixed-wing aircraft, including turbofan aircraft, turbojet aircraft and turboprop aircraft, having any number of engines, e.g., as propulsion engines and/or APU (auxiliary power unit) engines. In still other embodiments, platform  10  may be a rotary-wing aircraft or a combination rotary-wing/fixed-wing aircraft. 
         [0014]    In one form, engines  18  are gas turbine engines. In other embodiments engines  18  may be one or more of turboshaft, turbofan, turbojet or turboprop engines and/or may be combined cycle engines or any other type of gas turbine engines and/or other types of engines, such as diesel or spark-ignition internal combustion engines, ramjet engines, scramjet engines and/or any other types of engines. Although described with respect to engines, the present invention is equally applicable to other components and systems. 
         [0015]    In various embodiments, platform  10  may have a single engine  18  or a plurality of engines  18 . In addition to engines  18  in the form of propulsion engines, platform  10  may include one or more engines  18  in the form of APU&#39;s. In addition, in various embodiments, platform  10  may employ any number of wings  14 . Empennage  16  may employ a single flight control surface or multiple flight control surfaces. Although the depiction of  FIG. 1  illustrates two external pods  20 , in other embodiments, any number of external pods  20  may be employed, e.g., one or more external pods  20 , or no external pods may be employed. 
         [0016]    Referring to  FIG. 2 , some aspects of a non-limiting example of platform  10  and an engine  18  are schematically illustrated in accordance with an embodiment of the present invention. Platform  10  includes an electrical system  22 . In one form, electrical system  22  is an aircraft electrical system, which may include, for example and without limitation, flight controls, navigational systems, sensors, and which in various embodiments is generally disposed in or about one or more portions of structure  11 . In other embodiments, electrical system  22  may be any platform  10  electrical system, e.g., associated with one or more structures  11  or associated with platform  10  generally. Although illustrated as a unitary element, it will be understood that a plurality of electrical systems  22  may be distributed across many locations. In addition, it will be understood that  FIG. 2  and the description herein may be representative of an APU or other engine mounted on and/or in platform  10  in addition to or in place of a propulsion engine. 
         [0017]    Engine  18  includes an electronic control system  24 . In one form, electronic control system  24  is an engine control system. In other embodiments, electronic control system  24  may be a control system configured to control one or more other devices and/or systems, e.g., one or more other types of controlled systems  18  in addition to or in place of one or more engines. In one form, electronic control system  24  includes at least one controller  26  for controlling one or more controlled systems  18 . In one form, controller  26  is configured to control the operation of engine  18  or a plurality of engines  18 , and may be, for example, an engine controller, such as a full authority digital engine control (FADEC). Electronic control system  24  may also include one or more other engine control components, for example and without limitation, a plurality of sensors  28 , e.g., of various types typically employed in gas turbine and/or other engines; and one or more actuators  30 , e.g., of various types typically employed in gas turbine and/or other engines; and one or more of other types engine control components. In various embodiments, the engine control components may provide signals to and/or receive signals from controller  26  and/or electrical system  22 . One or more components of electronic control system  24  are in electrical communication with electrical system  22  via a controlled system wiring harness  32  (referred to herein as an engine wiring harness  32 ) coupled to and in electrical communication with a platform wiring harness  34 , e.g., an aircraft wiring harness or another platform  10  related wiring harness, e.g., associated with structure  11 . 
         [0018]    Engine wiring harness  32  includes a wiring harness connector  36 . Platform wiring harness  34  includes a wiring harness connector  38 . Engine wiring harness  32  is electrically coupled to platform wiring harness  34  via wiring harness connectors  36  and  38 . In one form, wiring harness connectors  36  and  38  are electrically coupled via a junction box  40 , e.g., wherein each of wiring harness connectors  36  and  38  are mechanically and electrically coupled to junction box  40 . In one form, junction box  40  is electrically shielded. In other embodiments, junction box  40  may not be electrically shielded. In still other embodiments, wiring harness connectors  36  and  38  are directly mechanically and electrically coupled to each other, i.e., without the use of an intervening junction box. 
         [0019]    Each of engine wiring harness  32  and platform wiring harness  34  include at least one, but generally, a plurality of wires for transmitting electrical signals between engine wiring harness  32  and platform wiring harness  34 . In particular, engine wiring harness  32  is configured to transmit electrical signals between electronic control system  24  components and platform wiring harness  34 , which is configured to transmit the electrical signals between engine wiring harness  32  and electrical system  22 . The electrical signals may be power signals and/or control level signals, and may be digital and/or analog. Power signals include, for example and without limitation, the provision of electrical power to/from one or more electrical/electronic components, e.g., including without limitation, controller  26 , any electrically powered actuators, other motor driven or electrically actuated devices, and any other electrically powered device. Control level signals include, for example and without limitation, sensor  28  input and/or output signals, and command and control signals to one or more controllers, such as controller  26  and/or other controllers and/or actuators such as actuator  30 . In some embodiments, engine wiring harness  32  and platform wiring harness  34  may include optical links for transmitting optical signals. 
         [0020]    Referring to  FIG. 3 , some aspects of non-limiting examples of engine wiring harness  32  and wiring harness connector  36  are schematically illustrated in accordance with an embodiment of the present invention. Although a particular geometric configuration is illustrated in  FIG. 3 , it will be understood that  FIG. 3  is schematic in nature, and that the actual configuration of engine wiring harness  32  and wiring harness connector  36  may vary with the needs of the application. Engine wiring harness  32  is depicted as including three (3) wires  42 ,  44  and  46  for electrical connection to three (3) corresponding wires in platform wiring harness  34 . In various embodiments, any number of wires may be included in engine wiring harness  32  and platform wiring harness  34 . In one form, wiring harness connector  36  includes a threaded female connector head  48 . In other embodiments, other connector head types may be employed, male or female. In one form, connector head  48  is configured to engage a corresponding connector head on junction box  40  to couple engine wiring harness  32  with junction box  40 . In other embodiments, connector head  48  may be configured to couple engine wiring harness  32  directly to platform wiring harness  34 . Wiring harness connector  36 , wiring harness connector  38  and junction box  40  are interfaces configured for electrically coupling or connecting engine wiring harness  32  to platform wiring harness  34 . 
         [0021]    Wires  42 ,  44  and  46  terminate at pins  50 ,  52  and  54  configured for electrical communication with corresponding receptacles in junction box  40 , or alternatively, in platform wiring harness  34 . In other embodiments, wires  42 ,  44  and  46  may terminate at receptacles configured for electrical communication with corresponding pins in junction box  40 , or alternatively, in platform wiring harness  34 . In one form, engine wiring harness  32  and platform wiring harness  34  are shielded. In one form, the shielding is provided in the form of a metallic screen surrounding the wires in the wiring harnesses and grounded at each end of the wiring harness, e.g., at the connectors, for example, metallic screen  56  depicted in engine wiring harness  32 . In other embodiments, other forms of shielding may be employed. In other embodiments, one or both of engine wiring harness  32  and platform wiring harness  34  may not be shielded. 
         [0022]    Many engines, such as engine  18 , typically employ shielded harnesses, such as engine wiring harness  32 , to protect against electromagnetic interference (EMI), e.g., including lightning strike and electromagnetic pulse (EMP). However, in some cases, the platform wiring harness does not have the same level of protection against EMI as the engine wiring harness, which may render engine electrical/electronic components susceptible to EMI damage. Also, engines of the same or similar model are often used in more than one platform or aircraft installation; the level of protection against EMI in the different platform models and configurations, e.g., aircraft models and configurations may vary. In order to prevent deleterious effects on the engine electrical/electronic components resulting from EMI, embodiments of the present invention employ an EMI protection component configured to protect one or more engine electrical/electronic components. Although such protection may be employed in the component itself, the variation in the required level of protection against EMI (e.g., inclusive of lightning strike) as between the different platform types or models, e.g., aircraft models, would necessitate the use of electrical/electronic components having protection tailored to each platform installation, e.g., aircraft installation, which may increase costs associated with the components, as well as costs associated with qualification testing of the component and/or the engine. 
         [0023]    In one form, engine wiring harness  32  includes EMI protection components  58  and  60 . In other embodiments, engine wiring harness  32  may include a greater or lesser number of EMI protection components. EMI protection components  58  and  60  are configured for transient suppression of electromagnetic spikes, e.g., voltage spikes. In one form, EMI protection components  58  and  60  are disposed in wiring harness connector  36 . In other embodiments, one or both of EMI protection components  58  and  60  may be disposed in elsewhere in engine wiring harness  32 . In still other embodiments, one or both of EMI protection components  58  and  60  may be disposed in other locations, e.g., in platform wiring harness  34 , including in wiring harness connector  38 , and/or junction box  40  in addition to or in place of engine wiring harness  32 . 
         [0024]    In one form, EMI protection components  58  and  60  are configured to provide EMI protection for controller  26 . In other embodiments, EMI protection components may be employed to provide EMI protection for other components, e.g., including sensors  28  and actuator  30 , in addition to or in place of controller  26 . In one form, EMI protection components  58  and  60  are passive protection devices. In other embodiments, one or both of EMI protection components  58  and  60  may be active protection devices. In one form, EMI protection components  58  and  60  are EMI filters. In other embodiments, EMI protection components  58  and  60  may take other forms. Examples of suitable filter types include, without limitation, one or more of xenon filters, zener diodes, inductor capacitor networks (LC filters) and/or transorbs. In other embodiments, other filter types and/or other types of EMI protection devices may be employed. In one form, EMI protection components  58  and  60  are tailored for the particular electrical/electronic component/circuit sought to be protected, and hence, may not provide the same level of EMI protection. For example, power supply and return lines may require different levels of protection than sensor lines. In other embodiments, EMI protection components  58  and  60  may provide the same degree of EMI protection. 
         [0025]    In one form, EMI protection components  58  and  60  are removable and replaceable, e.g., so that EMI protection may be reconfigured with different EMI protection characteristics in accordance with the needs of the particular application without damaging or destroying either of EMI protection components  58  and  60  (i.e., nondestructive removal and replacement). For example, in some situations, it may be desirable to use the same engine on another platform, e.g., aircraft, which may require reconfiguring the EMI protection. In other embodiments, one or both of EMI protection components  58  and  60  may not be configured for nondestructive removal and replacement. 
         [0026]    Referring to  FIG. 4 , some aspects of a non-limiting example of junction box  40  in accordance with an alternate embodiment of the present invention is schematically depicted. Although a particular geometric configuration is illustrated in  FIG. 4 , it will be understood that  FIG. 4  is schematic in nature, and that the actual configuration of junction box  40  may vary with the needs of the application. In the embodiment of  FIG. 4 , junction box  40  includes male connector heads  62  and  64  for mechanically and electrically coupling wiring harness connectors  36  and  38 , respectively, to junction box  40 . In other embodiments, one or both of connector heads  62  and  64  may be female connector heads. Junction box  40  also includes receptacles  66 ,  68  and  70  in electrical communication with respective receptacles  72 ,  74  and  76  for electrical connection to mating pins in wiring harness connectors  36  and  38 . In other embodiments, pins may be employed in place of receptacles on mating components and vice versa. In the embodiment of  FIG. 4 , EMI protection components  58  and  60  are disposed within junction box  40 . As with the embodiment of  FIG. 3 , in one form, EMI protection components  58  and  60  are removable and replaceable, e.g., so that EMI protection may be reconfigured with different EMI protection characteristics in accordance with the needs of the particular application without damaging or destroying either of EMI protection components  58  and  60  (nondestructive removal and replacement). In other embodiments, one or both of EMI protection components  58  and  60  may not be configured for nondestructive removal and replacement. As set forth above, in other embodiments, the EMI protection components may be disposed in platform wiring harness  34 , e.g., in wiring harness connector  38 , in addition to or in place of engine wiring harness  32  and/or junction box  40 . 
         [0027]    Embodiments of the present invention include a platform, comprising: a structure; a platform electrical system; a platform wiring harness; an engine coupled to the structure, wherein the engine includes an engine control system; and a wiring harness system coupling the engine control system to the platform electrical system, wherein the wiring harness system includes an engine wiring harness; coupled to the platform wiring harness; an interface configured to electrically connect the engine wiring harness to the platform wiring harness; and an electromagnetic interference (EMI) protection component configured to provide EMI protection for the engine control system. 
         [0028]    In a refinement, the interface includes a wiring harness connector installed as part of the platform wiring harness or the engine wiring harness, and wherein the EMI protection component is incorporated in the wiring harness connector. 
         [0029]    In another refinement, the wiring harness connector is an engine wiring harness connector. 
         [0030]    In yet another refinement, the EMI protection component is a passive protection device. 
         [0031]    In still another refinement, the EMI protection component is configured to provide lightning protection for the engine control system. 
         [0032]    In yet still another refinement, the interface includes a junction box configured to connect the engine wiring harness to the platform wiring harness, and wherein the EMI protection component is disposed within the junction box. 
         [0033]    In a further refinement, the junction box is shielded. 
         [0034]    In a yet further refinement, the EMI protection component is configured for nondestructive removal replacement. 
         [0035]    Embodiments of the present invention include a wiring harness system, comprising: a first wiring harness coupled to an electrical system component and configured to transmit an electrical signal to and/or from the electrical system component; an interface configured for coupling the first wiring harness to a second wiring harness; and an electromagnetic interference (EMI) protection component disposed in the wiring harness system and configured to provide EMI protection for the electrical system component. 
         [0036]    In a refinement, the interface includes a wiring harness connector, and wherein the EMI protection component is incorporated in the wiring harness connector. 
         [0037]    In another refinement, the EMI protection component is configured to provide lightning protection for the electrical system component. 
         [0038]    In yet another refinement, the interface includes a junction box configured to connect the first wiring harness to the second wiring harness, and wherein the EMI protection component is disposed within the junction box. 
         [0039]    In still another refinement, the junction box is shielded. 
         [0040]    In yet still another refinement, the EMI protection component is configured for nondestructive removal and replacement. 
         [0041]    In a further refinement, the EMI protection component is a passive protection device. 
         [0042]    In a yet further refinement, the EMI protection component is an EMI filter. 
         [0043]    In a still further refinement, the interface is configured for removable replacement of the EMI protection component with another EMI protection component having a different EMI protection characteristic. 
         [0044]    Embodiments of the present invention include a platform system, comprising: a controlled system; an electronic control system configured to control operation of the controlled system; and a wiring harness system configured to couple the electronic control system to a platform wiring harness, wherein the wiring harness system includes a controlled system wiring harness coupled to the electronic control system and configured to transmit an electrical signal to and/or from the electronic control system; an interface configured for coupling the controlled system wiring harness to the platform wiring harness; and means for providing EMI protection for the electronic control system disposed in the wiring harness system. 
         [0045]    In a refinement, the means for providing EMI protection is configured to provide lightning protection for the electronic control system. 
         [0046]    In another refinement, the means for providing EMI protection is disposed in the interface. 
         [0047]    While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment(s), but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims, which scope is to be accorded the broadest interpretation so as to encompass all such modifications and equivalent structures as permitted under the law. Furthermore it should be understood that while the use of the word preferable, preferably, or preferred in the description above indicates that feature so described may be more desirable, it nonetheless may not be necessary and any embodiment lacking the same may be contemplated as within the scope of the invention, that scope being defined by the claims that follow. In reading the claims it is intended that when words such as “a,” “an,” “at least one” and “at least a portion” are used, there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. Further, when the language “at least a portion” and/or “a portion” is used the item may include a portion and/or the entire item unless specifically stated to the contrary.