Abstract:
A new infrastructure for mobile devices and electronic loose equipment, preferably an aircraft infrastructure, is designed to be deployed for both new production aircraft and the after-market installed base for all parts of the aircraft that have human interaction, such as the galley, cockpit or cabin. The architecture is designed around two main objectives: creating stylized and functional products with flexibility in design and providing reliability and maintainability for operators while integrating power and charging mediums to those devices. This architecture is composed of several elements that as a whole complete our new architecture for mobile devices and electronic loose equipment design.

Description:
[0001]    This application claims priority to U.S. provisional patent application Ser. No. 61/892,721, filed Oct. 18, 2013. 
     
    
     TECHNICAL FIELD 
       [0002]    This invention relates to the infrastructure for mobile devices and electronic loose equipment. More specifically, it relates to the infrastructure for aircrafts, trains, cars or ships. 
       BACKGROUND 
       [0003]    Mobile devices are driving a major technological revolution that is spreading across all facets of human activity from daily life to the work place. Along with the deployment of Wi-Fi and wireless capability onboard aircraft many users and clients are bringing tablets, smartphones or other gadgets onboard. There is a need to address the portability of these technologies inside the aircraft. Therefore, provide options to the different clients and users to bring the electronic loose equipment onboard and place them on arms, holders, or other mechanisms for storage, use or for charging. 
       SUMMARY 
       [0004]    It is an object of the present invention to provide a new infrastructure for mobile devices and electronic loose equipment, preferably an aircraft infrastructure designed to be deployed for both new production aircraft and the after-market installed base. This invention&#39;s scope reaches all parts of the aircraft that have human interaction, such as the galley, cockpit or cabin. 
         [0005]    This new architecture is designed around two main objectives: creating stylized and functional products with flexibility in design and providing reliability and maintainability for operators while integrating power and charging mediums to those devices. This architecture is composed of several elements that as a whole complete our new architecture for mobile devices and electronic loose equipment design. 
         [0006]    These elements are: a power charger, a receptacle, an arm, a connector and a holding plate. 
         [0007]    The aircraft infrastructure for mobile devices and electronic loose equipment is designed to provide universal pairing with the existing mobile devices and tablets and also leaves the door open to adapt new developments in this sector. It provides maintainability and arm placement in aircrafts of all types, also relevant to various sectors (new production or used/after-market) as well as in different locations of the aircraft. 
         [0008]    One of the main elements of said aircraft infrastructure is its interchangeability. This feature is defined as that quality that allows a part to substitute or be substituted by other component parts, and be installed by the application of the attaching means only (bolts, nuts, screws, washers, pins, etc.). This definition specifically precludes the use of trimming, cutting, filing, drilling, shimming, and forming during installation. A set of building blocks is proposed to accommodate different needs of tablet and device functionality inside an aircraft, by providing elements that in between them are interchangeable. 
         [0009]    Accordingly, in some embodiments, there is provided an aircraft device mounting system having at least one type of quick-release mechanical and electrical coupling with complementary male and female portions, an aircraft body mountable unit having a mounting flange, one of the male and female portions, and a power supply connectable to an aircraft power bus and configured to provide lower voltage power, preferably with resettable electronic fuse protection, to the one of the male and female portions, a support arm having two of the male and female portions, a tablet computer holder having one of the male and female portions, wherein the support arm is connectable between the aircraft body mountable unit and the table computer holder. 
         [0010]    Another problem that can arise with mountings secured permanently to an aircraft interior for receiving a removable bracket, arm or device is that the removable portion can be hit or subjected to forces that could damage the portion of the aircraft body to which the mounting is secured. This problem can be solved by providing a portion of the removable device that will break under such extreme force, also called herein a mechanical fuse, thus sparing the mounting that is permanently secured to the aircraft body. In some cases, this portion can be a breakable biscuit that is received by a complementary socket of the mounting. 
         [0011]    In some embodiments, there is provided an aircraft socket for fixed mounting to an aircraft cabin body component and for receiving and mechanically supporting a removable support arm comprising or for supporting an electrical or electronic device, the socket comprising a flange for mounting to said aircraft cabin body component, a rim for engaging and securely supporting a complementary rim of said support arm, a receptacle for receiving and securing a male insert of the support arm, the receptacle spanning a full width of the socket inside the rim, an electrical connector within the rim and located to a side of the receptacle for connecting with a complementary electrical connector of the support arm, and power control circuitry connectable to an aircraft power supply bus and configured to provide electrical power to the electrical connector. The rim can be circular, oval, square, rectangular or any desired polygon in shape. The male insert can be provided within the rim such that one side of the insert is on a diameter or mid-line of the rim, with the electrical connector, for example a USB connector, provided within the rim opposite the insert receptacle. If desired, the male insert can be beveled or shaped to fit within the rim shape. 
       DEFINITION, TERMS, ELEMENTS 
       [0012]    Aircraft: any machine capable of flying by means of buoyancy or aerodynamic forces, such as a glider, helicopter, or airplane. 
         [0013]    Charger: power supply that transforms a certain voltage into another voltage value. 
         [0014]    Receptacle: mechanical structure used to support another part by providing physical support or also a bridge for electrical power. 
         [0015]    USB: is a technology industry standard developed in the mid-1990s that defines the cables, connectors and communications protocols used in a bus for connection, communication, and power supply between computers and electronic devices. 
         [0016]    Cat 5 Ethernet Cable: is a twisted pair cable for carrying signals. This type of cable is used in structured cabling for computer networks such as Ethernet. 
         [0017]    USB Extender: it is an electronic device with the sole functionality of repeating the signal (data) from the sender side and transmitting it to the receiver side without the loss of information or quality of data. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0018]    The invention will be better understood by way of the following detailed description of embodiments of the invention with reference to the appended drawings, in which: 
           [0019]      FIG. 1  shows an oblique view of a receptacle part of a mechanical and electrical coupling according to a first embodiment; 
           [0020]      FIG. 2A  shows a front view of the receptacle of  FIG. 1 ; 
           [0021]      FIG. 2B  shows a variant of  FIG. 2A  in which the receptacle has a square support rim; 
           [0022]      FIG. 2C  shows a variant of  FIG. 2A  in which the receptacle has a rectangular support rim; 
           [0023]      FIG. 3  shows the receptacle of  FIG. 1  with a support arm and device holder according to one embodiment, in which the support arm has at a base end a male portion complementary to the receptacle and at another end a universal coupler female portion, and the device holder is connectable to the universal coupler, the figure including an magnified transparent view detail of the mechanical fuse; 
           [0024]      FIG. 4  shows an oblique rear view of the device holder according to the embodiment of  FIG. 3 ; 
           [0025]      FIG. 5  shows an oblique view of a small arm and a holder for a handheld smartphone device; 
           [0026]      FIG. 6  shows a front view of the small arm and a holder for a handheld smartphone device of  FIG. 5 ; 
           [0027]      FIG. 7  shows an oblique view of a cockpit console mountable male portion of the universal coupling; 
           [0028]      FIG. 8  shows an oblique view of a cockpit support arm connectable between the console mountable universal coupling male portion of  FIG. 7  and the male portion of the universal coupling of the device holder of  FIG. 4 , the cockpit support arm having two adjustable and lockable universal joints for adjusting the device holder within a cockpit; 
           [0029]      FIG. 9  is a schematic block diagram of a power supply circuit; and 
           [0030]      FIG. 10  illustrates normal and protection voltages at three points in the circuit of  FIG. 9 . 
       
    
    
     DETAILED DESCRIPTION 
       [0031]    Referring to  FIG. 1 , there is shown a quick-release mechanical and electrical coupling female portion  10 . As also seen in  FIG. 2A , the female portion  10  is an aircraft body mountable unit that has a mounting flange  12  for fastening to a panel of the aircraft, such as a wall, seat-back, armrest or the like. A rim  14  is circular in  FIG. 2A  and rectangular in  FIG. 2B . The rim may protrude through a hole in a panel to which the unit  10  is mounted from the rear, or the unit can be surface mounted. As illustrated, the unit  10  can have fastening holes on a front face and on a side for accommodating different mounting configurations, and it will be understood that different fastening arrangements can be implemented. 
         [0032]    A slot  16  is provided in the unit  10  that receives a corresponding male biscuit  22  of a male portion  20  (shown in  FIG. 3 ). The slot  16  can be covered by a flap that can be biased t be closed when not in use. An electrical or a combined electrical and data connector  18  is provided in the unit  12 , and is shown in  FIG. 2A  to be a female USB connector. The type and gender of the connector can vary depending on the application. 
         [0033]    The USB female connector  18  in  FIGS. 1 and 2A  are connected to a male USB plug  18  that in turn is connected to a power supply circuit as will be described with reference to  FIGS. 9 and 10 , that is housed in a housing not shown. It will be appreciated that the power supply circuit can be housed within the unit  10 , if desired. 
         [0034]    As shown in  FIG. 3 , an arm  30  has the male portion  20  connected to its lower end, and a universal coupling member  40  connected to its upper end. The male portion  20  has a corresponding rim  24  for contacting rim  14 , a biscuit  22  for inserting into slot  16  and a male USB connector  26  for connecting to the female connector  18 . As shown in the detail, the biscuit  22  can be made of metal, such as aluminum or a die-cast metal, or any other suitable material that is able to support normal use forces applied to the coupling  20 , 10 . The biscuit  22  is connected to the male portion  20  by a shear screw  23  that will break when arm  30  is subjected to a large force, for example a weight of about 200 pounds (900 N) at the end of the arm  30 . In this way, an excessive force breaks the shear screw  23  in the biscuit  22  to protect the aircraft body connected to the unit  10  from damage. This protection is called a mechanical fuse. 
         [0035]    While not shown in  FIG. 3 , the coupling  20  can comprise, for example, a push button in the middle of the joint between arm  30  and coupling  20  for actuating a release for a latch mechanism that operates to lock the male member  22  within the slot  16 . In this way, the arm  30  can be held not only by the friction between the biscuit  22  and the slot  18 , along with gravity, but also using a latch or locking mechanism. 
         [0036]    The arm  30  also supports in the embodiment illustrated in  FIG. 3  a rotation and pivot joint  32  for adjusting an orientation of the segment  34  carrying member  40 . 
         [0037]    The universal coupling female member  40  has a slot  42 , electrical connector  44 , and locking recess  46 . The tablet holder  50  has a tablet power connector (e.g. USB micro, USB mini, Lightning, etc.)  52 , and a complementary male universal connector as better shown in  FIG. 4 . 
         [0038]    While providing electric power is important, it will be understood that the connectors are designed to be able to provide power and data. Data connectivity between connected devices and the aircraft is optional, but can be desirable for a variety of applications. In some embodiments, it is contemplated to have a charging circuit adapt aircraft bus power to suitable low voltage power for devices, while a network interface connects the data of the connector  18  or  44  to an aircraft data network bus for the intended purpose of device connectivity. Such circuits can be housed with a housing of unit  10 . 
         [0039]    The rear of the tablet holder  50 , as shown in  FIG. 4 , has a top and bottom bracket  54  for engaging and holding a tablet computer from opposed sides or ends, and a lever  55  for controlling a separation of the brackets  54  to grip the tablet. The upper portion of the holding plate  50  moves while the lower portion is fixed, and it will be appreciated that a variety of mechanical arrangement can be used to secure the tablet to the holding plate  50 . For example, the upper portion can be simply biased to grip the tablet. 
         [0040]    The male portion  40 ′ of the universal coupling  40 / 40 ′ has a flange  42 ′ for engaging with the slot  42 , an electrical connector  44 ′ for connecting to the connector  44 , and a locking tab  46 ′ for engaging the locking recess  46 . The connector  44  is connected to the coupling  52  by conductors integrated with the holder  50 . Release of the locking tab  46 ′ can be done using release tab  48  that can be used to move the tab  46 ′ against the action of a spring. It will be appreciated that other quick release mechanisms can be used for locking and unlocking the portions  40  and  40 ′ from one another. 
         [0041]    While the arm  30  provides an ability to position and orient a tablet device with a radius of movement of about 40 cm, it will be understood that the arm can take a variety of forms and functions. For example, the arm  30  can be much smaller and provide no or only one degree of freedom for supporting a smartphone-size holder  50 ′ as illustrated in  FIGS. 5 and 6 . Such a smaller device holder  50 ′ may provide only a base with connector  52  and a support for holding the smartphone or small tablet inclined or vertically for viewing by a passenger, crew member or pilot. 
         [0042]    Alternatively, the arm  30  of  FIG. 3  can provide more degrees of freedom to provide height adjustability. While the arm  30  is illustrated as having portion  40  of a universal connector at its end, it will be appreciated that it may directly have its desired holder or device at its end. For example, the arm  30  can comprise a reading light built in. Alternatively, a reading light can use a coupling portion  40 ′ to connect to an arm  30  having coupling portion  40 . While the arm  30  is shown to have different coupling types at each end, it will be appreciated that the arm  30  can have the same type of couplings at both ends, as in the embodiment of  FIG. 8 . 
         [0043]      FIG. 7  shows the male universal coupling portion  40 ′ arranged as a cockpit console or panel mountable unit. This is a surface mounted unit that is fastened to the outer surface of a panel (e.g. using fastener holes as shown). The unit  40 ′ can have the same function as described with reference to  FIG. 4 , namely locking tab  46 ′, release  48 , connector  44 ′ and flange  42 ′. The unit  40 ′ can be connected to a USB charger circuit via connector  19 . The unit  40 ′ can use a proprietary electrical connector  44 ′ to connect to the complementary connector  44  (shown in  FIG. 8 ), or a standard connector, such as mini-USB or Lightning. 
         [0044]    In the tight confines of a cockpit, the support arm  60 , as shown in  FIG. 8 , is shorter than for the cabin, and has two universal ball joints  62  locked in position with a certain resistance to force by a mechanism  64 , as for example a screw clamp, each joint  62  being connected to a respective a female coupling portion  40 . One female coupling portion  40  is for connecting to the cockpit mounted unit, and another is for connecting to the tablet holder  50  as illustrated in  FIG. 4 . Once a tablet is mounted onto the holder  50 , its position and orientation can be adjusted with the clamp handle  64  turned to free the joints  62 , and once in the desired position and orientation, the clamp is tightened. 
         [0045]      FIG. 9  illustrates a schematic block diagram of the power supply circuit  70  that comprises an over current protection circuit  71  connected to an aircraft DC input, an EMI filter  72  connected to the protection circuit  71 , a detection circuit  74  connected to the filter  72  that detects voltage and current coming from the aircraft bus and controls the circuit  71  and an overvoltage protection circuit  75 . The output of the circuit  75  feeds a DC to DC converter  76  that provides the desired low DC voltage to an output protection circuit  77  that is then connected to the device connector, such as the USB power bus. 
         [0046]    As shown in  FIG. 10 , the power supply circuit  70  operates to protect against voltage surges on the aircraft bus, for example as may be caused by an excess of voltage generated by the generator. When the voltage is detected to be over a threshold, for example 50 V, then circuit  74  causes device  75  to open and interrupt the supply of current to converter  76 . Likewise, when the aircraft voltage is too low, the circuit  74  disconnects power from the converter  76  until a stable power level of at least about 8 V is present on the bus. Circuit  74  also measures the current flow into the converter  76 , and if it is above a given threshold, circuit  71  can be controlled to interrupt the supply of current to the filter  72 . Filter  72  absorbs small current and voltage spikes, but cannot handle large spikes or fluctuations in power that last, for example, a few seconds. 
         [0047]    The circuit  70  can include a functionality LED indicator connected to an output of the converter circuit  76 . This indicator is shown in  FIG. 9  as a dot in the block for converter  76 . It can inform the user that power is not available due to a short in the arm or holder, or in the device. It will be appreciated that the source of the indicator signal can be from a different circuit component than converter  76 . 
         [0048]    If a device connected to the low voltage output of the converter  76  should draw too much current, for example due to a short, the output protection circuit  77  measures this current level and interrupts power to the device. The circuit  77  can repeatedly try to deliver current to the device, as long as the continuous power supplied is very low, in order to limit the power delivered to a device in case of a malfunction, and in order to prevent damage to the device and to draw less power. This behavior can be considered to be an intelligent fuse in that it allows for power to restore itself as soon as the problem is not longer present. If a device, such as a laptop, is connected into the power supply through, for example, the USB port, and the device supplies power to the power supply  70 , the presence of such power can be detected and cause the power supply to disconnect from the device. This disconnection need not impair connect of data to a network of the aircraft. Power supply  70  also provides protection both on the high voltage aircraft bus side and on the low voltage device side. 
         [0049]    It will be appreciated that the power supply circuit can be used to power a single connector, such as a USB port, with or without data connectivity, without being associated with a mechanical coupling as described above with reference to  FIGS. 1 to 8 . 
         [0050]    The power charger  70  operates under a fast charge capability. It can utilize a maximum output current of 2.5 A under 5V. It can be housed as a single unit providing all the functionality needed to deliver current to a tablet or a mobile device. It is compact, lightweight and uniquely versatile for an easy installation. It can incorporate an LED, a connector, and perform at high power efficiency. 
         [0051]    The charger circuit  70  can be compatible with most tablets (Apple, Android) and all other PED devices that are present in the current market or will be developed in the future. 
         [0052]    The charger can also meet the DO-160 certification. This is the official Aviation industry standard required for power units to be placed in cockpits and cabins of various aircraft types. 
         [0053]    One very important differentiation between the power charger  70  of the present embodiment and other power charges in the market is the fact that charger  70  provides over current/over voltage protection, bi-directional and reversible voltage protection, automatically resets in the event of a fault, and it can work at a nominal and surge input voltage: 28 VDC/36 VDC. 
         [0054]    Depending on what is the use of the charger  70 , the applicant has created  2  types of them. In one version, the charger is a device that operates in short distances from the power or data source. Though in airplanes, sometimes the luxury of having the main cabin power or green power is not easy to obtain, the applicant also created an extended version of the charger that can support long distances. 
         [0055]    Referring to  FIGS. 1, 2A and 2B   FIG. 7 , the USB Receptacle shown incorporates an all-encompassing type design that seamlessly connects to the arms, holders or other functional devices. The unit  10  is designed to fit in multiple places to create flexibility in placement (ex; cabin, cockpit, side ledges, seats, divans, etc.). It also provides for easy installation with the different elements of the new cabin architecture for mobile devices and loose electronic equipment. 
         [0056]    The receptacle  10  can also include a sliding cover (not shown) over the USB connector  18  to protect it when not in use. It is the base mechanical unit to attach all the arms, holders, or other approved products, specifically, those that conform to the support structure for the tablets or electronic devices attached to the cabin architecture. 
         [0057]      FIG. 8A  wide variety of designs for the arms can be contemplated. These arms can be designed to support aerospace requirements in terms of weight, maintainability and life cycle durability. They can be highly stylized tablet-arms that are designed to be sleek, stylized, visually appealing while they try to blend with the interior of the aircraft minimizing any visual interference. They can be ergonomically designed for optimal viewing when passengers are seated in either an erect or reclined viewing position in the cabin or the aircraft. These can be placed in various locations and configurations as long as the receptacle is present as the base or foundation. 
         [0058]    The arms have been developed using a robust design that can accommodate different tablet formats and shapes. They are designed and engineered with a focus on strength, maintainability and reliability. They can provide multiple degrees of freedom to achieve optimal viewing positions (Field Of View) for the seated occupant and by means of a connector they can support any holding plate uniquely fitted to each tablet type. 
         [0059]    The arms can also mitigate against vibration-induced white noise. 
         [0060]    It is important to specify that the arms can come in different shapes, and these shapes can depend on the desired use and placement of the unit. The arms can be long, short, curved or flat depending on the device that they will be supporting and the nature of its functionality. 
         [0061]    The tablet-arm  30  is ergonomically designed to provide the user with a comfortable viewing position both in erect or reclined positions. The design incorporates movement and rotation that balances robustness with efficient maneuverability to effectively optimize the arm usage. The arm can be very robust and designed to meet or exceed typical usage in the cabin while being lightweight. 
         [0062]    Referring to  FIGS. 7 and 8 , the universal coupling  40 , 40 ′ provides a section of the aircraft infrastructure for mobile devices and electronic loose equipment. This equipment is unique and it provides a locking mechanism  46 ,  46 ′ to fit a holding plate  40  with an arm or holder. It has several key features and technologies that provide a robust latch while engaged and an easy removal while disengaged. 
         [0063]    To latch or secure part  40  to part  40 ′, part  40  needs to be slid inside part  40 ′. This is simple and almost effortless. After insertion, the mechanism will “latch” or engage, and part  40  will be locked inside part  40 ′. This will couple the holding plate  40 ′ with the arm  60 . 
         [0064]    To release part  40 ′, a mechanical lever  48  is pressed or pushed. Pressing this lever will disengage the mechanical system and will “unlatch” the coupling, afterwards, a simple push will release and disengage the unit. 
         [0065]    Referring to  FIG. 4 , the aircraft infrastructure for mobile devices and electronic loose equipment is designed to accommodate different tablet formats. Our design is unique in the industry as it can employ tablet specific interchangeable holding-plates that optimize the fit for each electronic device, create a stable housing to minimize vibration (hence cabin noise) and provide safe stable platform. The tablet can be inserted into the holding-plate  50  and mechanically secured with an advanced locking device (lever  55 ). Each holding-plate  50  can contain the charging port  52  for the specific device. This component of the tablet-arm assembly can be made of high-grade aluminum to ensure robustness, thereby optimally accommodating wear and tear from constant usage. 
         [0066]    The holding-plates  50  can be designed for the most popular tablet devices in the consumer market. For example, this currently includes several generations of the Apple iPad (i.e. 2,3,4), the Apple iPad Mini and the Samsung Galaxy Tab. 
         [0067]    The holding plate  50  can be coupled with any arm or holder thanks to the connector  40 , 40 ′. As new tablet brands and formats are introduced to the marketplace, the holding plate  50  will be able to easily accommodate them with minimal changes (i.e. no need to replace arm or receptacle). This will be accomplished by designing a new holding-plate fitted specifically for the new tablet model, which will fit into the tablet-arm without any change to the arm assembly due to the connector. Therefore, the customer will not be restricted when they upgrade tablet devices nor will the arm assembly need replacement. 
         [0068]    For operators who still want holding plates that can accommodate multiple devices, the applicant has also developed a universal variant, called the Universal Holding Plate, based on the same principles highlighted before.