Abstract:
An aircraft cabin lighting kit includes: at least one lighting unit configured for installation in an aircraft cabin; a driving/dimming module generating output signals for controlling illumination of the at least one lighting unit according to command signals from a cabin management system; and at least one wire assembly interfacing the driving/dimming module with a power bus for receiving operational power, and a communication bus for receiving the command signals and for communicating the output signals to the at least one lighting unit. The present aircraft cabin lighting kit is certified by a governmental aviation-regulating body for installation in multiple aircraft. An aircraft cabin lighting system, which includes the kit, is also provided

Description:
FIELD OF THE INVENTION 
     This invention pertains generally to aircraft interiors. More particularly, the present invention relates to an aircraft cabin lighting system and a kit for facilitating installation of the same. 
     BACKGROUND OF THE INVENTION 
     As known in the art, items (e.g., systems, sub-systems and components) that are installed on aircraft need to be reviewed and approved by a governmental aviation-regulating body to ensure that such items comply with applicable standards (e.g., airworthiness and other safety concerns). For example, in the United States the Federal Aviation Administration (FAA) requires any person or company producing replacement or modification parts for installation on a type-certificated product (i.e., aircraft) to obtain a parts manufacturer approval (PMA), which is a combined design and production approval for replacement parts. Also in some instances, a supplemental type certificate (STC) may additionally be needed to approve the design and installation of PMA parts on an aircraft when the PMA parts modify the type certificate (TC). 
     Since aircraft owners and operators are becoming more and more interested in refurbishing, upgrading or otherwise customizing the aircraft cabin interior with replacement and/or new items such as, for example, seating systems, in-flight entertainment (IFE) systems, and lighting systems, it can be appreciated that these replacement and/or new items need to be certified by PMA and/or STC before installation. Certification is made difficult because refurbishing, upgrading or otherwise customizing the aircraft cabin interior has, until now, entailed the use of custom-designed products. One custom-designed product is an aircraft-specific, light-controlling module with a unitary wiring harness that has a customized length or customized connectors terminating the wiring harness. Since the light-controlling module is custom-configured and certified for installation in the environment of one specific aircraft, when the module is adapted for another aircraft (e.g., by changing the wiring harness length or the terminating connector thereof) it can be appreciated that the adapted version of the certified module must be re-certified despite a minor structural change. Because the certification processes involved in obtaining a PMA and/or STC are time-consuming and complicated ordeals for parts manufacturers and/or installers, a pre-certified kit that facilitates installation of a customized aircraft cabin lighting system would be an important improvement in the art. 
     BRIEF SUMMARY OF THE INVENTION 
     In one aspect, an aircraft cabin lighting kit is provided. The present aircraft cabin lighting kits are certified by a governmental aviation-regulating body for installation in multiple aircraft. 
     The aircraft cabin lighting kit may comprise: at least one lighting unit configured for installation in an aircraft cabin; a driving/dimming module generating output signals for controlling illumination of the at least one lighting unit according to command signals from a cabin management system; and at least one wire assembly interfacing the driving/dimming module with a power bus for receiving operational power, and a communication bus for receiving the command signals and for communicating the output signals to the at least one lighting unit. 
     In another aspect, an aircraft cabin lighting system is provided. The aircraft cabin lighting system may comprise: a DC power bus; a communication bus; a cabin management system in communication with the communication bus, the cabin management system outputting command signals to the communication bus for controlling illumination of the aircraft cabin; and an aircraft cabin lighting kit. The aircraft cabin lighting kit may include a plurality of lighting units electrically connected to the DC power bus and the communication bus, a driving/dimming module electrically connected to the communication bus for generating light-controlling signals which dim and drive the plurality of lighting units according to the command signals from the cabin management system, and at least one wire assembly for interfacing the driving/dimming module with the power bus and the communication bus. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  illustrates a block diagram of an example aircraft cabin lighting system; 
         FIG. 2  illustrates one embodiment of an aircraft cabin lighting kit for the system of claim  1 ; 
         FIG. 3  illustrates a dimmer/driver module of the kit of  FIG. 2 ; 
         FIG. 4  illustrates another embodiment of an aircraft cabin lighting kit for the system of claim  1 ; 
         FIG. 5  illustrates an example schematic for the dimming/driving module of the kit shown in  FIG. 4 ; and 
         FIG. 6  illustrates an example addressing module for an aircraft cabin lighting kit and system. 
     
    
    
     DETAILED DESCRIPTION 
     Turning now to the Figures, an aircraft cabin lighting system and kit are provided.  FIG. 1  illustrates an example aircraft cabin lighting system. As shown in  FIG. 1 , the aircraft cabin lighting system  100  includes a power bus  110 , a communication bus  120 , a cabin management system  130 , a dimmer/driver module  140 , and a plurality of lighting units  160 ,  180 . The cabin management system (CMS)  130  may be user interface such as a computer with a display and an input device (e.g., a keyboard and/or a mouse), a touch-screen, a flight attendant or crew panel with actuators (e.g., buttons, switches, etc.) and the like for operating/controlling lights, the crew intercom, and overhead announcement speakers as well as other cabin environmental and entertainment features. The CMS  130  is in communication with the aircraft communication bus  120  for outputting command signals to the communication bus  120  and for receiving signals (e.g., status signals and the like) via the communication bus  120  from downstream components such as, for example, the dimming/driving module  140  and the plurality of lighting units  160 ,  180  as shown. The communication bus  120  as shown is a two-wire bus, and the wires may be configured as a twisted pair (e.g., according to the RS485 or ARINC 429 specifications). Signals on the communication bus  120  may be of one or more protocols known in the art (e.g., CAN, ARINC 429, pulse width modulated (PWM) type signals, or the like). As further shown, the dimming/driving module  140  and the plurality of lighting units  160 ,  180  are in communication with the aircraft communication bus  120  as well as a power bus  110  for receiving operational power (e.g., 28 Volts DC as shown). 
     The dimming/driving module  140  includes a power and a communication interface for electrically connecting the module  140  with the busses  110 ,  120 . As shown in  FIG. 1 , a wiring assembly or harness  150  is configured to engage with the power and communication busses  110 ,  120  as well as the power and the communication interfaces of the module  140  such that the module  140  is configured as a controlling node of the system  100 . As can be appreciated, the lighting units  160 ,  180  of the plurality include a power interface and a communication interface. Another wiring assembly or harness indicated by reference number  170  is configured to engage with the power and communication busses  110 ,  120  as well as the power and the communication interfaces of the lighting units  160 ,  180  such that the lighting units  160 ,  180  are configured as controlled nodes of the system  100 . As shown, the system  100  includes one or more lighting units  160  that are configured for direct connection with the busses  110 ,  120  via wiring harness  170 . However, the system  100  may also include one or more lighting units  180  that are configured for direct and/or indirect connection with the busses  110 ,  120 . That is, as shown the one or more lighting units  180  may be configured in a series connected, daisy chain configuration or the like such that one lighting unit  180  receives power and signals via another (preceding or upstream) lighting unit  180 . Although not shown, it can be appreciated that the lighting units  160 ,  180  may include one or more white or colored light emitting diodes (LEDs). Furthermore, the lighting units  160 ,  180  may be configured as wash-type lights that provide ambient illumination within the passenger cabin, or as personal ambient lights (e.g., reading lights) that illuminate one passenger&#39;s seating area. 
     As can be appreciated, the dimming/driving module  140  is configured to receive command signals output from the CMS  130  (via the communication bus  120  and wiring harness  150 ), and output signals to the communication bus  120  for controlling illumination of the lighting units  160 ,  180  relative to the command signals. Signals output by the dimming/driving module  140  are communicated along the communication bus  120  to the lighting units  160 ,  180  for controlling illumination of the lighting units  160 ,  180 . For example, the dimming/driving module  150  may be operable for turning the lighting units  160 ,  180  on and off, dimming, changing color and/or color temperature of the illumination, etc. The lighting units  160 ,  180  may be configured in a zone to provide illumination to a designated portion of the passenger cabin such as a first class, business class or economy class area of the cabin. Although not shown, additional dimming/driving modules may be provided such that each module  140  is configured to control illumination of a cabin class or portion of a cabin class. To this end, each module  140  may be configured with a communication address (e.g., a unique code) such that the CMS  130  can independently control illumination of various distinct areas in the cabin. The dimming/driving module  140  may be pre-set or programmed with a communication address, however as will be described hereinafter in further detail, the address may be changed, programmed or otherwise customized by the aircraft operator or installer of the system  100  before or after the module  140  is installed. 
     Turning now to  FIG. 2 , an example aircraft cabin lighting kit is described. As shown in  FIG. 2 , an embodiment of the example aircraft cabin lighting kit is indicated by reference number  200 . The illustrated aircraft cabin lighting kit  200  includes a dimming/driving module  220  and a wiring apparatus or harness  240 . The dimming/driving module  220  is generally octagonal in shape and includes power and communication interfaces on two adjacent sides (e.g., the left-most side and the side intermediate the lower side and the left-most side as shown in  FIG. 2 ) of the module  220 . The module  220  may be coupled, connected, mounted, attached or otherwise secured to a generally vertical or generally horizontal surface within the cabin interior (e.g., behind a wall or ceiling panel). Although the dimming/driving module  220  is generally octagonal, other embodiments of the module may be shaped otherwise, for example with various geometrically-shaped (e.g., polylinear or curvilinear) configurations. Furthermore, as can be appreciated, depending on the desired configuration of the system  100  and other factors (e.g., the layout of the cabin, distance between the module  220  and the busses  110 ,  120  and/or the lighting units  160 ,  180 , etc.), the aircraft cabin lighting kit may be configured otherwise. For example, the aircraft cabin lighting kit may include one or more wiring harnesses of various lengths, one or more lighting units (e.g., if the aircraft cabin does not include pre-installed lighting units), etc. 
     As shown in  FIG. 2 , the wiring harness  240  includes a main wiring body (e.g., a bundle of wires or conductors) with a first end terminated by a first connector  260 , which interfaces with the power and communication busses  110 ,  120  ( FIG. 1 ). The illustrated wiring harness  240  further includes a second end defined by two connectors  250 ,  252  that terminate two wire assemblies that bifurcate from the main wiring body of the harness  240 . One connector  252  of the second end of the wiring harness is configured to couple, connect or otherwise interface with the module  220  to provide operational power to the module  220 , whereas the other connector  250  of the second end is configured to couple, connect or otherwise interface with the module  220  to communicate signals to and from the module  220 . To this end, it can be appreciated that the power and communication interfaces and busses  110 ,  120  are isolated such that command signals or light-controlling output signals are not subject to crosstalk or other interference (e.g., due to momentary voltage spikes on the power bus  110 ). 
     Referring now to  FIG. 3 , the dimming/driving module  220  is further described. As shown in  FIG. 3 , the dimming/driving module  220  includes a housing defined by a first housing portion  222  and a second housing portion  224 . The two housing portions  222 ,  224  may be secured together (e.g., by glueing, welding or other mechanical means such as a screw or other fastener known in the art) such that the portions  222 ,  224  enclose a circuit board  226  and partially enclose jacks, connectors or the like  230 - 234  (hereinafter connectors) that are configured to interface the module  220  with, for example, one or more components of the lighting system  100  ( FIG. 1 ). In some embodiments of the dimming/driving module, the circuit board may be removable from the housing such that the circuit board may be replaced. Additionally, some embodiments of the dimming/driving module may include a second housing portion with knock-outs or the like and cover plates so that the module&#39;s housing can be configured to accept a circuit board with fewer or additional connectors. As will be described in further detail hereinafter with reference to  FIG. 5 , the circuit board  226  includes electrical and/or electronic components for communicating with the CMS  130 , and for communicating with and controlling illumination of the lighting units  160 ,  180  via the communication bus  120 . As shown, the module  220  includes first, second and third connectors  230 ,  232 ,  234  respectively. However, the module  220  may include fewer or additional connectors (e.g., see module  320  shown in  FIG. 4  which includes five connectors). Connectors  230 ,  232 ,  234  may be surface-mounted to the circuit board  226  for interfacing the electrical and/or electronic elements on the board with one or more components (e.g., busses  110 ,  120 , the CMS  130 , and lighting units  160 ,  180  shown in  FIG. 1 ) of the lighting system  100 . As can be appreciated from comparing  FIG. 3  with  FIG. 2 , the first connector  230  defines a communication interface of the module  220  whereas the second connector  232 , which is adjacent to the connector  230 , defines a power interface of the module  220 . The third connector  234  may be configured to interface the module  220  with various products or system components. In one embodiment, the third connector  234  may be configured as an in-circuit serial programming (ICSP) interface for testing, programming, troubleshooting, etc. the dimming/driving module  200 . In another embodiment, the third connector  234  may be configured to interface with an address module which will be described hereinafter. In yet another embodiment, the third connector  234  may be configured to interface the module  220  with components of the system such as another wiring harness (e.g., wiring assembly or harness  170  shown in  FIG. 1 ) for connecting the module  220  directly or indirectly with one or more lighting units  160 ,  180 . 
     Referring now to  FIG. 4  another example aircraft cabin lighting kit is described. As shown in  FIG. 4 , an embodiment of the example aircraft cabin lighting kit is indicated by reference number  300 . The illustrated aircraft cabin lighting kit  300  includes a dimming/driving module  320 , a first wiring apparatus or harness  340 , and a second wiring apparatus or harness  380 . The module  320  may be coupled, connected, mounted, attached or otherwise secured to a generally vertical or generally horizontal surface within the cabin interior (e.g., behind a wall or ceiling panel). Although the dimming/driving module  320  is illustrated as being generally octagonal, other embodiments of the module may be shaped otherwise, for example with various geometrically-shaped (e.g., polylinear or curvilinear) configurations. Furthermore, although the wiring harnesses  340 ,  380  may be electrically isolated from each other, in some instances the first and second wiring harnesses  340 ,  380  may be electrically interconnected (e.g., by jumper  378  as shown which includes a wire or wires). 
     The dimming/driving module  320  includes power and communication interfaces on two adjacent sides (e.g., the left-most side and the side intermediate the lower side and the left-most side as shown in  FIG. 4 ) of the module  320 . As shown in  FIG. 4 , the wiring harness  340  includes a main wiring body (e.g., a bundle of wires or conductors) with a first end terminated by a first connector  360 , which interfaces with the power and communication busses  110 ,  120  ( FIG. 1 ). The illustrated wiring harness  340  further includes a second end defined by two connectors  350 ,  352  that terminate two wire assemblies that bifurcate from the main wiring body of the harness  340 . As can be appreciated, the power and communication interfaces of the module  320  are configured to receive the connectors  350 ,  352 . 
     One connector  352  of the second end of the wiring harness is configured to couple, connect or otherwise interface with the module  320  to provide operational power to the module  320 , whereas the other connector  350  of the second end is configured to couple, connect or otherwise interface with the module  320  to communicate signals to and from the module  220 . The module  320  further includes output interfaces. As shown in  FIG. 4 , the output interfaces of module  320  are configured on two adjacent sides (e.g., the right-most side and the side intermediate the upper side and the right-most side). The output interfaces are configured to receive connectors  372 ,  374 ,  376  of the second wiring harness  380 , with the connectors  372 ,  374 ,  376  defining a first end  370  of the second wiring harness  380 . A second end  390  of the second wiring harness  380  is defined by two wire assemblies that bifurcate from the main wiring body of the wiring harness  380  and which terminate in two connectors  392 ,  394 . The connectors  392 ,  394  of the second end  390  of wiring harness  380  may be configured to engage with lighting units  160 ,  180  ( FIG. 1 ) or other components of the system  100  that are downstream of the module  320 . 
     In some instances, the jumper  378  may communicate output signals to the lighting units  160 ,  180  via the wiring harness  380  for controlling illumination of one or more of the lighting units  160 ,  180 , thereby bypassing the communication bus  120 . In an example, when the module  320  is operable to control illumination of lighting units using two or more communication protocols, a first subset, zone or grouping of lighting units may be controlled by the module  320  using a first communication protocol communicated via the bus  120  whereas a second subset, zone or grouping of lighting units may be controller by the module  320  using a second communication protocol communicated via the jumper  378  and second wiring harness  380 . As can be appreciated, depending on the desired configuration of the system  100  and other factors (e.g., the layout of the cabin, distance between the module  320  and the busses  110 ,  120  and/or the lighting units  160 ,  180 , etc.), the aircraft cabin lighting kit  300  may be configured otherwise. For example, the aircraft cabin lighting kit  300  may include fewer or additional wiring harnesses, wiring harnesses of various lengths, one or more lighting units (e.g., if the aircraft cabin does not include pre-installed lighting units), etc. 
     Turning now to  FIG. 5  an example schematic of an embodiment of the dimming/driving module for an aircraft cabin lighting kit is described. As shown in  FIG. 5 , a dimming/driving module (e.g., modules  220 ,  320  of  FIGS. 2 and 4  respectively) includes an electronic circuit  500  for communicating with the CMS  130  ( FIG. 1 ) and for controlling illumination of one or more lighting units. The circuit  500  includes a power interface  510  for receiving operational power (e.g., 28 Volts DC as shown) from the power bus  110 . Power interface  510  is electrically connected with a voltage regulator  550  to process the input voltage and provide a suitable voltage (e.g., 5 Volts DC as shown) to various components of the circuit  500 . The circuit  500  further includes a communication interface  520  for receiving command signals or data from the CMS  130  ( FIG. 1 ) via the communication bus  120 , and for outputting control signals to the lighting units  160 ,  180  ( FIG. 1 ) via the communication bus  120 . Additionally, the dimming/driving module may receive status and other signals from downstream components (e.g., the lighting units  160 ,  180 ) via the communication interface  520  and communication bus  120 . As shown, the signals received or output by the communication interface  520  may be of the RS485 standard or other protocol known in the art. 
     As further shown in  FIG. 5 , the dimming/driving module may include an output interface  530 , which comprises three interfaces  532 ,  534 ,  536 . These three interfaces  532 - 536  may correspond with the connectors  372 - 376  shown in  FIG. 4  for outputting pulse width modulated (PWM) signals to one or more lighting units for controlling illumination intensity, color, color temperature or the like in a step-wise or continuous manner. Furthermore, the circuit  500  includes an in-circuit serial programming (ICSP) interface  525 . As previously mentioned, the ICSP interface  525  may be used for testing, programming, troubleshooting, etc. the dimming/driving module. Additionally, the ICSP interface  525  may be used to change, program or otherwise customize a communication address of the dimming/driving module. 
     The circuit  500 , as shown in  FIG. 5 , further includes a controller  540  (e.g., a microcontroller, microprocessor, DSP, etc.). The controller  540  stores and executes a set of instructions (e.g., software, firmware or the like) for processing inputs received via the communication interface  520  (e.g., command and status signals) and outputting data or signals (e.g., control signals) relative to the inputs. The circuit further includes a switching regulator  560 , a MOSFET driver  570 , communication transceivers  580  (universal asynchronous receiver/transmitter-UART), and a temperature sensor  590  for facilitating control of illumination of the lighting units  160 ,  180  of the system  100  ( FIG. 1 ). 
     Turning now to  FIG. 6 , an address module is described for embodiments of the lighting kit and system. As shown in  FIG. 6 , an example address module  600  includes a first portion  620 ,  640  for interfacing the address module  600  with a dimming/driving module, and a second portion  660  including a user interface defined by actuators  680 ,  690  (e.g., one or more switches such as DIP switches, rotatable knobs, or the like). The address module  600  may be communicatively coupled with the dimming/driving module, for example by inserting the connector  640  into an interface of the dimming/driving module (e.g., the ICSP interface  525  shown in  FIG. 5 ). Additionally, the address module  600  may be communicatively coupled with one or more lighting units. The address module  600  may be used by an installer of the aircraft cabin lighting kit or system or by aircraft maintenance personnel so that the dimming/driving module and/or lighting units may be programmed with a communication address or so that a preset or pre-programmed address may be changed to a different address. The address module  600  may be employed as follows: 
     The maintenance person may set the address into the address module  600  by dialing in the address into two actuators  680 ,  690 . Although not shown in  FIG. 6 , the second portion  660  may bear indicia around or otherwise proximate to the actuators  680 ,  690 . The indicia on the second portion  660  may define a plurality of predetermined addresses relative to rotation of one or both of the actuators  680 ,  690 . The dimming/driving module may be disconnected from the communication bus, and the address module is connected (e.g., to the ICSP interface or to the communication interface of the dimming/driving module). Next the dimming/driving module may be disconnected from and reconnected to the power bus to reset/power cycle the dimming/driving module. After being reset, the dimming/driving module recognizes the address module and the address module communicates an address to the dimming/driving module, the address being stored in a memory of the dimming/driving module such as a nonvolatile memory. Next, the address module may be disconnected from the dimming/driving module, and the dimming/driving module is reconnected to the communication bus. 
     In another embodiment, the address module may be a computing device (e.g., a laptop personal computer, a tablet computer, a personal digital assistant (PDA), a smartphone, etc.) By connecting the computing device to the dimming/driving module a user may program the dimming/driving module with a customized address by, for example typing the address into an address-setting application executing on the computing device. 
     Although the address module  600  may be provided with some aircraft lighting kits and systems, the address module  600  need not be provided or employed for changing, programming or otherwise assigning addresses. In yet another embodiment, the dimming/driving module may be programmed with an address by, for example, electrically connecting input pins of the communication interface (e.g., interface  520  of  FIG. 5 ) to ground. In an example where the dimming/driving module includes four input pins, jumpering these four pins to ground will provide sixteen addresses. As shown in  FIG. 5 , the communication interface may include six input pins (INPUT SIG 1 - 6 ) to provide additional addresses. 
     Still further, a token signal may be used to designate to the dimming/driving units and/or the lighting units that the following address information is intended for the device with the token signal high. After the device is programmed the next unit in the series, is addresses by activating its token line. This process may continue until some or all of the modules and/or lights are addressed. 
     The use of the terms “a” and “an” and “the” and similar referents in the context of describing the invention (especially in the context of the following claims) are to be construed to cover both the singular and the plural, unless otherwise indicated herein or clearly contradicted by context. Recitation of ranges of values herein are merely intended to serve as a shorthand method of referring individually to each separate value falling within the range, unless otherwise indicated herein, and each separate value is incorporated into the specification as if it were individually recited herein. All methods described herein can be performed in any suitable order unless otherwise indicated herein or otherwise clearly contradicted by context. The use of any and all examples, or exemplary language (e.g., “such as”) provided herein, is intended merely to better illuminate the invention and does not pose a limitation on the scope of the invention unless otherwise claimed. No language in the specification should be construed as indicating any non-claimed element as essential to the practice of the invention. 
     Various embodiments of this invention are described herein. It should be understood that the illustrated and described embodiments are exemplary only, and should not be taken as limiting the scope of the invention.