Abstract:
The present invention is a method and apparatus for providing a control system that controls at least one of a plurality of display units. In one embodiment, the control system includes a remote control circuit capable of activating a remote signal for moving the display unit between one of a first, a second and a third positions and another one of the first, the second and the third positions. The control system further includes a local display unit movement control circuit coupled to the display unit, and a transmitter coupled to the local display unit movement control circuit. The transmitter is configured to transmit a light beam capable of being reflected from a reflective surface near the transmitter to make a reflected light beam, and a receiver coupled to the local display unit movement control circuit. The receiver provides a signal to the local display unit control circuit upon detection of the reflected light beam to move the display unit between one of the first, the second and the third positions and another one of the first, the second and the third positions. Various embodiments are described.

Description:
BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention relates to the field of entertainment control systems. More particularly, the present invention relates to an entertainment control system for deploying one or more display units at one of a plurality of angles. 
     2. Description of Related Art 
     Over the last few decades, commercial aircraft have become a necessary mode of transportation for personal and business reasons. In order to improve passenger comfort, many commercial airlines have in-flight entertainment systems that include in-flight television display units for displaying movies and other programming. The display units are typically stowed in a cavity in the ceiling of the passenger cabin located above the passenger seats. Prior to viewing, the display units are typically deployed to an exposed position at a single, fixed angle with respect to the passenger cabin. Such single fixed deployment angles are often less than ideal. 
     As a result, viewing of the display screen by passengers is restricted. Moreover, when a liquid crystal display (LCD) screen is implemented within a display unit that is deployed at a non-optimal viewing angle, colors often appear dull. At times, the entire picture appears to be washed out, thus obscuring optimal viewing of the image. 
     It would therefore be desirable to have a vehicle entertainment control system that facilitates deployment of one or more display units at various angles between a maximum exposed position and a stowed position. Such a control system will facilitate flexible and optimal viewing of displayed images. 
     SUMMARY OF THE INVENTION 
     The present invention is a method and apparatus for providing a control system that controls at least one of a plurality of display units. In one embodiment, the control system includes a remote control circuit capable of activating a remote signal for moving the display unit between one of a first, a second and a third positions and another one of the first, the second and the third positions. The control system further includes a local display unit movement control circuit coupled to the display unit, and a transmitter coupled to the local display unit movement control circuit. The transmitter is configured to transmit a light beam capable of being reflected from a reflective surface near the transmitter to make a reflected light beam, and a receiver coupled to the local display unit movement control circuit. The receiver provides a signal to the local display unit control circuit upon detection of the reflected light beam to move the display unit between one of the first, the second and the third positions and another one of the first, the second and the third positions. Various embodiments are described. 
    
    
     BRIEF DESCRIPTION OF THE DRAWINGS 
     The objects, features and advantages of the present invention will become apparent from the following detailed description of the present invention in which: 
     FIG. 1 illustrates a display unit assembled into a passenger cabin of an aircraft. 
     FIG. 2 illustrates a side view of a display unit typically installed in a passenger cabin overhead of an aircraft. 
     FIG. 3 is a system block diagram of one embodiment of the deployment assembly of FIG.  2 . 
     FIG. 4A illustrates a rear perspective view of one embodiment of the deployment assembly provided in accordance with the principles of the present invention. 
     FIG. 4B illustrates an enlarged view of the sensor wheel  30  of FIG.  6 A. 
     FIG. 4C is a cross section of one embodiment of the sensor wheel  30  of FIG.  4 B. 
     FIG. 5 is a system block diagram of a second embodiment of the deployment assembly of FIG.  2 . 
     FIG. 6A illustrates a rear perspective view of the deployment assembly of FIG. 5 provided in accordance with the present invention. 
     FIG. 6B is a detailed perspective view of the sensor wheels  60 ,  62  and  64  of FIG.  6 A. 
     FIG. 6C is a cross section of one embodiment of the sensor wheel  60  of FIG.  6 B. 
     FIG. 7A is a system block diagram of a third embodiment of the deployment assembly of FIG.  2 . 
     FIG. 7B illustrates a rear perspective view of the deployment assembly of FIG. 7A provided in accordance with the present invention. 
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT 
     The present invention relates to a vehicle entertainment control system having deployment assembly for moving one or more display units between a plurality of exposed positions and a stowed position, the vehicle entertainment system preferably being implemented during in-flight. In the preferred embodiment, the display unit is a liquid crystal display (“LCD”) monitor. As discussed herein, a “vehicle” may include, but is not limited to, an aircraft, train, ferry, bus, or any other mode of mass transit. For clarity, the present invention will be described during implementation within a commercial aircraft. Throughout the detailed description, a number of illustrative embodiments are described in order to convey the spirit and scope of the present invention. While numerous specific details are set forth to describe the preferred embodiment of the invention, such details may not be required to practice the present invention. 
     FIG. 1 illustrates a display unit or monitor  10  assembled into a passenger cabin  12  of an aircraft. Referring to FIG. 1, a frame  14  is mounted into a ceiling cavity  16  of a cabin overhead  18  above the passenger seating area for stowing a display unit. Although FIG. 1 shows only one display unit, the passenger cabin  12  includes a plurality of such display units. Normally, the display units  10  are placed in a stowed position, parallel with the frame  14 . During viewing of programming such as a movie, the display units  10  are moved into an exposed position. In the embodiment of FIG. 1, the display units  10  are pivotally coupled to the frame  14 . However, in a first alternative embodiment, the display units  10  are placed in the cabin overhead  18  perpendicular to the frame  14  when in the stowed position and moved down vertically (either automatically or manually) until they are viewable by passengers. In a second alternative embodiment, the display units  10  are placed outside the ceiling cavity  16  positioned at an angle with respect to the frame  14  when in the stowed position. With respect to the embodiment of FIG. 1, the display units  10  are spaced apart every three rows of seats, so that they are viewable by the passengers. 
     FIG. 2 illustrates a side view of a display unit  10  typically installed in a passenger cabin overhead  18  of an aircraft. Referring to FIG. 2, the display unit  10  is moved between a stowed position and one of a plurality of exposed positions under the control of a deployment assembly  20 . Alternatively, the display unit  10  may be moved between a plurality of exposed positions under the control of the deployment assembly  20 . 
     As discussed earlier, the display unit  10  is typically installed in the passenger cabin overhead  18  of an aircraft. In one embodiment, a retract surface  22  is located below the bottom side of the cabin overhead  18 . The retract surface  22  has an aperture  22   a  for operating the deployment assembly  20  via a receiver  24 . In one embodiment, the receiver  24  is an infrared IR receiver. In one embodiment, the receiver  24  is mounted on the inside of  25  the cabin overhead  18 , and may be controlled from the passenger seating area. In one embodiment, the deployment assembly  20  may be activated via the receiver  24  using a remote control unit  25 . The ceiling cavity  16  below the passenger cabin overhead  18  has two side walls  16   a  and  16   b.  The side wall  16   a  located on the back side of the display unit  10  includes an aperture  26  for monitoring the deployment angle of the display unit  10  via a transceiver  28 . In one embodiment, the transceiver is an infrared (IR) transceiver. In a further embodiment, the transceiver  28  includes a photodiode that transmits an IR beam, and a photodetector that detects the reflected IR beam. In particular, a sensor wheel  30  having a plurality of calibration marks (see FIG. 4) may be implemented to facilitate deployment of the display unit  10  at a corresponding plurality of deployment angles. In one embodiment, the calibration marks are reflective. 
     FIG. 3 is a system block diagram of one embodiment of the deployment assembly  20  of FIG.  2 . The deployment assembly  20  comprises receiver  24  that receives control information from the remote controller  25 , a micro-controller  26 , the transceiver  28  that receives control information from the sensor wheel  30  located on the pivoting monitor shaft  32  of the display unit  10 . In alternative embodiments, the micro-controller  26  may be any control unit, including, but not limited to, processors. The pivoting monitor shaft  32  is coupled to a motor  34  and a brake  36  that is also coupled to the pivoting monitor shaft  32 . During deployment, as the display unit  10  rotates about a longitudinal axis of the pivoting monitor shaft  32 . The sensor wheel  30  located on the pivoting monitor shaft  32  also rotates along the same axis and in the same direction as the pivoting monitor shaft  32 . Based on information provided from the receiver  24  and/or the transceiver  28 , the micro-controller  26  generates deployment control signals to the motor  34  and brake  36 , which subsequently control the movement of the display unit  10 . The deployment positions of the monitor  10  may be pre-calibrated and stored in memory  40 , as discussed in detail in the following sections. 
     FIG. 4A illustrates a rear perspective view of one embodiment of the deployment assembly  20  provided in accordance with the principles of the present invention. FIG. 4B illustrates an enlarged view of the sensor wheel  30  of FIG. 4A, and FIG. 4C is a cross section of one embodiment of the sensor wheel  30  of FIG.  4 B. As shown, the sensor wheel  30  has a plurality of calibration marks  30   a,    30   b,  and  30   c,  each of which is capable of reflecting light emitted from the transceiver  28 . In one embodiment, the first two calibration marks  30   a  and  30   b,  are narrow calibration marks, and each provides a predetermined detection angle A 1  for the transceiver  28 . In one embodiment, the predetermined detection angle A 1  is 5 to 10 degrees. The angular distance θ 1  between the first and second calibration marks  30   a  and  30   b,  is predetermined to provide known reference points to the micro-controller  26  for calibration of the motor speed. In one embodiment, θ 1  is 35°-45°. The angular distance θ 2  between the second and third calibration marks  30   b  and  30   c  is also predetermined. In one embodiment, θ 2  is in the range 20°-30°. 
     The third calibration mark  30   c  has a detection angle that provides a deployment angle of (A 2 −X) degrees to (A 2 +X) degrees, where X is a predetermined tolerance. In one embodiment, A 2  is 20° and X is 10 degrees. The deployment range (i.e., A 2 +2X) of the third calibration mark  30   c  enables the micro-controller  26  to determine if the position of the display Unit  10  is within acceptable limits. 
     In an alternate embodiment, the transceiver  28  may be mounted on the pivoting monitor shaft  32  in place of the sensor wheel  30 . In this embodiment, the transceiver  28  may be configured to reflect light off an object or target that has a fixed position with respect to the transceiver  30 . To facilitate deployment of the display unit  10  at multiple angles, the object or target may comprise reflective calibration marks similar to the calibration marks  30   a,    30   b  and  30   c.    
     To calibrate the deployment assembly  20 , the micro-controller  26  first measures the time taken between detection of the first and the second calibration marks  30   a  and  30   b.  Since the positions of the calibration marks  30   a,    30   b  and  30   c  are known, the measured time may then used to determine the deployment speed of the display unit  10 . Once the deployment speed has been determined, the micro-controller  26  waits until it detects the start of the third calibration mark  30   c.  Once it detects the third calibration mark  30   c,  the micro-controller  26  will wait for the required amount of time for the display unit  10  to travel from the starting angle of the third calibration mark  30   c  to the desired deployment angle. At that juncture, the micro-controller  26  will engage the brake  36  and shut off the motor  34 , so as to stop the display unit  10  at the desired viewing angle. 
     By measuring the amount of time between detection of the first and second calibration marks  30   a  and  30   b,  the display unit deployment speed is calibrated, ensuring consistent deployment results among all display units. By measuring the amount of time after the detection of the third mark  30   c,  any number of different angles within the angular definition provided by the detection angle (A 2 +2X) of the third calibration mark  30   a  may be selected. In one embodiment, the micro-controller  26  may be programmed to provide viewing of the display Unit  10  at increments of 5°. 
     Once configured, the deployment assembly  20  may be used. To actuate the deployment assembly  20 , the user selects from one of a plurality of positions for desired viewing of the display unit  10 . In one embodiment, the remote controller  25  may be configured to issue signals corresponding to deployment of the display unit  10  at predetermined deployment angles, starting from an initial position. For example, by pressing a deployment button once, the display unit  10  may be deployed at a 100 degree angle. By pressing the deployment button again, the display unit  10  may be deployed at increments of 5 degrees, up to a final deployment position. In the present example, where (A 2 +2X)=40°, eight deployment positions may be available, e.g., if the initial deployment angle is 100°, the other deployment positions are at 105°, 110°, 115°, 120 °, 125°, 130° and 135°. It is apparent to one of ordinary skill in the art that a greater number of deployment positions, each having different deployment angles, may be configured for operation of the display unit  10 . 
     Once the deployment position has been selected, the remote controller  25  (see FIG. 3) generates a signal that is received by the receiver  24  to deploy the display unit  10 . The receiver  24  subsequently forwards a signal to the micro-controller  26 , which releases the brake  36  and actuates the motor  34  to rotate the monitor shaft  32 . At the same time, the transceiver  28  monitors the sensor wheel  30  to determine the deployment position of the display unit  10 . This is accomplished by generating a light beam that is reflected off the sensor wheel  30 . Upon detection of the corresponding calibration mark, the transceiver  28  issues a signal to the micro-controller  26 , which applies the brakes  36  and suspends operation of the motor  34 . The display unit  10  is then held in the desired viewing position. 
     FIG. 5 is a system block diagram of an alternate embodiment of the deployment assembly  20  of FIG.  2 . As shown in FIG. 5, the deployment assembly  20   a  is substantially similar to the deployment assembly  20  with the exception that the deployment assembly  20   a  comprises a plurality of transceivers  50 ,  52 ,  54 , instead of a single transceiver  28  (as shown in FIGS.  3  and  4 A-C), and a plurality of sensor wheels  60 ,  62 ,  64 , instead of a single sensor wheel  30  (as shown in FIGS.  3  and  4 A-C). In one embodiment, the transceivers  50 ,  52  and  54  are IR transceivers. 
     FIG. 6A illustrates a rear perspective view of another embodiment of the deployment assembly provided in accordance with the present invention. FIG. 6B is a detailed perspective view of the sensor wheels  60 ,  62 , and  64  of FIG.  6 A. As shown in FIG. 6A and 6B, each sensor wheel  60 ,  62  and  64  has one or more calibration marks  60   a,    62   a-b  and  64 a. Each calibration mark  60   a,    62   a-b  and  64   a  is offset from every other calibration mark. In one embodiment, the calibration mark  60   a  is offset from the first calibration mark  62   a  of the second sensor wheel  62  by a predetermined angle Φ 1 ; the calibration mark  60   a  is also offset from the first calibration mark  64   a  of the third sensor wheel  64  by a predetermined angle  2 Φ 2 . In one embodiment, Φ 1 =7°. The first and second calibration marks  62   a  and  62   b  of the second sensor wheel are offset by a predetermined angle Φ 2 . In one embodiment, Φ 2 =15°. In one embodiment, Φ 3 =30°. The sensor wheels  60 ,  62 , and  64  are all mounted on the pivoting monitor shaft  32 , and the calibration marks  60   a,    62   a-b  and  64   a  on each of the wheels  60 ,  62  and  64  are monitored by respective transceivers  50 ,  52 , and  54 . FIG. 6C is a section of the sensor wheel  60  of FIG.  6 B. In one embodiment, the calibration marks  60   a,    62   a-b  and  64   a  are of the same width or detection angle. In particular, the first calibration mark  60   a  provides a predetermined detection angle B 1  for the transceiver  50 . Similarly, the first and second calibration marks  62   a  and  62   b  each provides a predetermined detection angle B 1  for the transceiver  52 . In one embodiment, the predetermined detection angle B 1  for the transceiver  50  or  52  is 5 to 10 degrees. The second mark  60   b  is a reflective position that is a landing zone for the deployed position of sensor wheel  60 . In one embodiment, the angle is 40°. 
     The positions of the calibration marks  60   a,    62   a-b  and  64   a,  along with the time taken to travel from a first to a second calibration mark, e.g. from  60   a  to  62   a,  may be used to calculate the deployment speed of the display unit  10 , as discussed above. 
     To calibrate the deployment assembly  20   a,  the micro-controller  26  first measures the time taken between detection of the calibration mark  60   a  of the first sensor wheel and the calibration mark  62   a  of the second sensor wheel  62 . Since the positions of all the calibration marks  60   a,    62   a-b  and  64   a  are known, the measured time may be used to determine the deployment speed of the display unit  10 . Once the deployment speed has been determined, the micro-controller  26  can determine the time at which the final deployed position will be reached. Depending upon the signal or signals issued by the remote controller  25 , the micro-controller  26  may then engage the display unit  10  at positions corresponding to the calibration marks  64   a,    62   b.  In addition, the micro-controller  26  may be further programmed to deploy the display unit  10  at predetermined increments, such as at every 5° upon detection of the start of the calibration mark  60   b  of the first sensor wheel  60 . For example, the initial deployment position corresponding to the start of the detection of the calibration mark  60   b  is 95°, the other deployment positions of the display unit  10  based on the detected deployment speed of the display unit  10 , may be programmed at a 5° interval to provide deployment positions of 100°, 105°, 110°, 115°, 120°. Once configured, the display unit  10  may be deployed in a manner similar to that of the deployment assembly  20 . 
     Alternatively, the deployment assembly  20   a  may be pre-calibrated, and transceiver  50 ,  52 , and  54  may be programmed to direct light towards the respective calibration marks  60   a,    62   a-b  and  64   a  to detect the deployment positions of the deployment unit  10 . For example, the transceivers  50 ,  52 , and  54  may each direct a beam of light towards the respective sensor wheel  60 ,  62 ,  64 . In one embodiment, the beam of light is an IR light beam. When light is reflected off the first calibration mark  60   a  on the first sensor wheel, the micro-controller  26  determines that the first deployment position of the display unit  10  has been reached and the brake  36  may be engaged to stop the display unit  10  at that position. If the user indicates that the display unit  10  should be displayed at the second deployment position, the pivoting shaft  32  rotates until a light is reflected off the second calibration mark  62   b  of the second sensor wheel  62  and detected by the transceiver  52 . At this juncture, the micro-controller  26  determines that the second deployment position of the display unit  10  has been reached. Micro-controller  26  may then engage the display  10  in the second deployment position by applying the brake  36 . 
     Similarly, to engage the display unit  10  at the third deployment position, light is directed from the third transceiver  54  toward the third sensor wheel  64 . Then, when light is reflected off the first calibration mark  64   a  of the third sensor wheel, the micro-controller  26  determines that the third deployment position of the display unit  10  has been reached, and may the apply brake  36 . Likewise, to engage the display unit  10  at the fourth deployment position, light is directed from the second transceiver  52  toward the second sensor wheel  62 . The, when light is reflected off the second calibration mark  62   b,  the micro-controller  26  determines that the fourth deployment position of the display unit  10  has been reached, and may then apply brake  36 . The fifth deployment position of the display unit  10  may be reached by detecting the second calibration mark  60   b  of the first sensor wheel  60 . 
     FIG. 7 is a system block diagram of a third embodiment of the deployment assembly of FIG.  2 . As shown in FIG. 7, the deployment assembly  20   b  is substantially similar to the deployment assembly  20  with the exception that the transceiver  100  includes a transmitter  100   a  located at position C and a detector  100   b  located at position D; and the sensor wheel  110  includes a plurality of slots  110   a,    110   b  and  110   c.  In one embodiment, the transmitter is a photodiode that transmits IR beam, while the receiver is a photodetector that detects the IR beam. In one embodiment, the slots  110   a  and  110   b  have the same width, and the slot  110   c  is substantially wider than either of the slots  110   a  and  110   b.  In a further embodiment, the width of the slots  110   a  and  110   b  are 5° while the width of the slot  110   c  is 40°. In operation, light is transmitted from the transmitter  100   a  towards the receiver  100   b.  However, the light is blocked by the sensor wheel  110  when the monitor is not located at a corresponding deployment position. When light is transmitted from transmitter  100   a  across the slot  110   a  and received by the detector  100   b,  the micro-controller  26  detects that the monitor  10  has reached the first timing position. It then measures the time the period it takes to travel from between the first and second timing positions by determining the time it takes to detect light transmitted through the slot  110   b  as received by detector  100   b.  Since the locations of the slots  110   a  and  110   b  are known and since the time taken for the monitor  10  to travel from the first timing position to the second timingposition may then be calculated, the deployment speed of the monitor  10  may also be determined. The micro-controller  26  may then determine the time it takes to reach the deployment position after passing the first edge of the opening  110   c  and, at the time, may apply the brake  36  to hold the display unit in one or more desired viewing positions, in the same manner as described for the deployment assembly  20  of FIG.  3 . 
     The present invention thus facilitates the deployment of one or more display units at various angles between a maximum exposed position and a stowed position. Such a control system will provide flexibility in the passenger&#39;s viewing of the display unit. 
     While certain exemplary embodiments have been described and shown in the accompanying drawings, it is to be understood that such embodiments are merely illustrative of and not restrictive on the broad invention, and that this invention not be limited to the specific constructions and arrangements shown and described, since various other modifications may occur to those ordinarily skilled in the art.