United States Patent [19J
`Monroe
`
`I IIIII IIIIIIII Ill lllll lllll lllll lllll lllll lllll lllll lllll 111111111111111111
`US006009356A
`[11] Patent Number:
`[45] Date of Patent:
`
`6,009,356
`*Dec. 28, 1999
`
`[54] WIRELESS TRANSDUCER DATA CAPTURE
`AND RETRIEVAL SYSTEM FOR AIRCRAFT
`
`[75]
`
`Inventor: David A. Monroe, San Antonio, Tex.
`
`[73] Assignee: Raytheon TI Systems, Lewisville, Tex.
`
`[ *] Notice:
`
`This patent issued on a continued pros(cid:173)
`ecution application filed under 37 CFR
`1.53( d), and is subject to the twenty year
`patent term provisions of 35 U.S.C.
`154(a)(2).
`
`This patent is subject to a terminal dis(cid:173)
`claimer.
`
`[21] Appl. No.: 08/745,536
`
`[22] Filed:
`
`Nov. 12, 1996
`
`Related U.S. Application Data
`
`[63] Continuation-in-part of application No. 08/729,139, Oct. 11,
`1996, and a continuation-in-part of application No. 08/738,
`487, Oct. 28, 1996, Pat. No. 5,798,458, which is a continu(cid:173)
`ation-in-part of application No. 08/729,139, Oct. 11, 1996.
`Int. Cl.6
`................................ G06G 7/76; H04N 7/18
`[51]
`[52] U.S. Cl. ................................. 701/14; 701/29; 701/35;
`701/2; 73/587; 340/439; 340/963
`
`[58] Field of Search .................................... 701/3, 14, 15,
`701/16, 35, 29, 1, 2; 364/550, 551.01, 580;
`340/963, 439, 945, 438, 436; 73/587
`
`[56]
`
`References Cited
`
`U.S. PATENT DOCUMENTS
`
`5,581,464 12/1996 Woll et al. ................................ 701/35
`5,761,625
`6/1998 Honcik et al. ............................ 701/14
`5,778,203
`7/1998 Birkedahl et al. ........................ 701/14
`5,798,458
`8/1998 Monroe et al. ........................... 701/14
`
`Primary Examiner-Jacques H. Louis-Jacques
`Attorney, Agent, or Firm-Bracewell & Patterson
`
`[57]
`
`ABSTRACT
`
`A wireless safety and surveillance recorder system for
`aircraft incorporates a plurality of strategically spaced wire(cid:173)
`less sensors for monitoring critical components and opera(cid:173)
`tional characteristics of the aircraft. The captured data and a
`wireless image are transmitted to a monitor in the cockpit
`and recorded on a "black box" flight recorder, and may be
`transmitted to ground control stations for real time or near
`real time surveillance. The system may include a second
`recorder for providing redundancy and may include redun(cid:173)
`dant sensors.
`
`22 Claims, 9 Drawing Sheets
`
`SENSOR I
`
`19a
`
`296
`
`MU.TIPL.EXER
`
`215
`
`61
`
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`
`51
`
`RECEIVER
`
`52
`
`FLIGHT DATA
`RECORDER
`
`LOCAL
`POWER RESERVE
`
`110
`
`117
`
`~114
`
`AIRCRAFT
`POWER SOlRCE
`
`SAMSUNG EXHIBIT 1015
`
`Page 1 of 15
`
`

`
`FIG. 1
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`Page 2 of 15
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`

`
`U.S. Patent
`
`Dec.28,1999
`
`Sheet 2 of 9
`
`6,009,356
`
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`Page 3 of 15
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`TO AIRCRAFT ~ 55
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`61
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`Page 4 of 15
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`TO AIRCRAFT
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`Page 5 of 15
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`Page 6 of 15
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`Page 7 of 15
`
`

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`Page 8 of 15
`
`

`
`FIG. 8
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`Page 9 of 15
`
`

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`Page 10 of 15
`
`

`
`6,009,356
`
`1
`WIRELESS TRANSDUCER DATA CAPTURE
`AND RETRIEVAL SYSTEM FOR AIRCRAFT
`
`CROSS REFERENCE TO RELATED
`APPLICATIONS
`
`This application is a continuation in part of my applica(cid:173)
`tion entitled: VIDEO AND DATA CAPTURE AND
`RETRIEVAL SURVEILLANCE SYSTEM FOR
`AIRCRAFT, Ser. No. 08/729,139, filed on Oct. 11, 1996,
`now pending and is directly related to my appliction entitled:
`ACOUSTIC CATASTROPHIC EVENT DETECTION
`AND DATA CAPTURE AND RETRIEVAL SYSTEM FOR
`AIRCRAFT, Ser. No. 08/738,487, filed on Oct. 28, 1996,
`now U.S. Pat. No. 5,798,458, which is also a continuation in
`part of application Ser. No. 08/729,139 Oct. 11, 1996.
`
`BACKGROUND OF INVENTION
`
`2
`Typically, the hardwired systems of the prior art will stop
`collecting data once there has been a structural failure of the
`airframe or a disruption in aircraft power. This is because the
`transmission lines of the hardwired system are interrupted,
`5 or the power system is either interrupted or the aircraft
`power source ceases to operate. This precludes the collection
`and transmission of critical data at the very moment when it
`is most critical, i.e., at the moment when a catastrophic event
`occurs.
`Therefore, it would be desirable to have a data collection
`and retrieval system that would continue to monitor and
`collect data after a power interruption or other catastrophic
`failure. Further it would be desirable to have redundant
`recordings of the critical data and redundant monitors and
`capture as well. While such a system would be of great
`benefit to the airline industry in general and to the commer(cid:173)
`cial airlines in particular, there are no systems currently
`available which meet these needs.
`
`10
`
`15
`
`1. Field of Invention
`The subject invention is generally related to safety and 20
`surveillance equipment for aircraft and is specifically
`directed to a wireless data collection and transmission
`system for commercial aircraft.
`2. Discussion of the Prior Art
`Aircraft safety is of ever increasing importance. This is
`particularly true with respect to commercial airlines as more
`and more people and freight are moved in this manner. The
`airways are becoming increasingly crowded with traffic.
`While air travel is still the safest form of transportation, if
`the present growth rate continues there will be a fatal
`accident involving aircraft on a daily basis within the next
`decade. Therefore, not only is it of critical importance that
`additional safety precautions be devised and adapted but
`also that better and more efficient accident reconstruction
`methods be developed, as well. The effort to reconstruct the
`cause of the fatal crash of TWA Flight 800 in July, 1996 has
`exceeded $25,000,000.00.
`Electronic systems have already greatly enhanced the
`safety record of commercial aircraft. Global tracking sys(cid:173)
`tems are now in place to monitor the flight of the aircraft
`from its destination. Radar and global positioning systems
`are commonplace. All of these electronic systems have
`increased the ability to track the performance of an aircraft
`frame the moment it lifts off until it safely lands.
`In addition, the on board avionics including electronic
`monitoring and diagnostic equipment, particularly on large
`commercial jets, continues to evolve, giving both the on
`board crew and the tracking station more complete, accurate
`and up-to-date information regarding the condition of the 50
`aircraft while in flight.
`Flight recorders long have been incorporated in order to
`provide a record of each flight and in order to provide critical
`information to aid in the determination of the causes of an
`accident or malfunction should one occur. In the prior art 55
`systems transducers, sensors and other monitoring
`equipment, such as by way of example, pressure gauges,
`temperature sensors and the like are positioned at strategic
`locations throughout the aircraft for monitoring the opera(cid:173)
`tion of these components. The transducers, sensors and other 60
`monitoring equipment are hardwired to the on board "black
`box" data recorders and to various monitoring equipment in
`the cockpit. While the data collected and transmitted by this
`equipment provides useful real-time information to the flight
`crew and is useful in reconstructing the cause and effect of 65
`catastrophic incidents, the systems of the prior art have
`shortcomings reducing the effectiveness of the data.
`
`SUMMARY OF IBE INVENTION
`
`25
`
`30
`
`35
`
`The subject invention is specifically directed to a wireless
`data generation, transmission and collection system wherein
`the critical data generated by the monitoring equipment on
`board an aircraft may be displayed on cockpit monitors and
`recorded through wireless transmission. The preferred
`embodiment of the invention includes a plurality of redun(cid:173)
`dant "black box" data recorders. The transducers, sensors
`and other monitoring equipment of the system, as well as the
`recorders and, where desired, the monitors, are all self(cid:173)
`contained with independent power supply systems whereby
`the overall system continues to generate, collect, transmit,
`display and record data even after an airframe structural
`failure or other catastrophic event.
`The wireless system of the subject invention has the
`advantage of reducing the weight of the surveillance and
`safety system by eliminating wiring harnesses and the like.
`Due to the wireless configuration of the system, it can be
`readily retrofitted in existing equipment with a minimum of
`40 difficulty. Further, the addition of the wireless system of the
`invention to existing equipment will provide additional
`redundancy to many of the hardwired monitoring compo(cid:173)
`nents currently in place.
`The wireless system of the subject invention is configured
`45 to be a stand alone system for monitoring, collecting,
`displaying and recording critical data. As stated, it can also
`be used in combination with the prior art hardwired systems
`to provide a redundant system. Further, the wireless system
`of the subject invention can be used in combination with my
`aforementioned copending applications entitled: VIDEO
`AND DATA CAPTURE AND RETRIEVAL SURVEIL-
`LANCE SYSTEM FOR AIRCRAFT, Ser. No. 08/729,139,
`filed on Oct. 11, 1996 and ACOUSTIC CATASTROPHIC
`EVENT DETECTION AND DATA CAPTURE AND
`RETRIEVAL SYSTEM FOR AIRCRAFT, Ser. No. 08/738,
`487,filed on October, 1996, now U.S. Pat. No. 5,798,458
`incorporated by reference herein, to provide a comprehen(cid:173)
`sive multi-media safety and surveillance system, as therein
`described. The multi-media sytem provides both visual and
`audio information as well as critical data to the flight crew,
`and to a ground tracking station, and also permits recording
`the information and data generated during flight.
`In its preferred form, a plurality of sensor units are placed
`strategically throughout the aircraft. The data sensors/
`transducers, such as by way of example, the engine tem(cid:173)
`perature sensor, oil pressure and hydraulic pressure sensors
`and strain gauges and the like generate critical performance
`
`Page 11 of 15
`
`

`
`6,009,356
`
`4
`It is another object and feature of the subject invention to
`provide a fully integrated, self-contained power supply
`system for powering the data system of the subject invention
`in the event of a airframe structural failure and/or a disrup-
`tion in aircraft power, whereby the data can continue to be
`collected and recorded after the occurrence of such an event.
`It is an additional object and feature of the subject
`invention to provide a record of critical components and
`areas of an aircraft during flight for archival and retrieval
`10 purposes.
`It is yet another object and feature of the subject invention
`to provide apparatus for permitting ground personnel to
`receive data relating to critical components and areas of and
`aircraft during flight.
`It is an additional object and feature of the invention to
`provide real time data monitoring the various systems and
`components of an aircraft using a wireless transmission
`system.
`It is also an object and feature of the invention to
`providing historical data both before and after an event in
`order to enhance reconstruction.
`It is a further object and feature of the subject invention
`to provide accurate information of where the aircraft is
`during a flight path when specific data is generated and
`transmitted.
`It is also an object and feature of the subject invention to
`provide a system for linking recorded data with an inertial
`navigation system or other navigational data source such as,
`30 by way of example, a global positioning system for archival
`purposes.
`It is still another object and feature of the invention to
`permit the monitoring, storing and retrieval of any of a
`variety of data by the tracking, surveillance and imaging
`equipment on board the aircraft.
`Other objects and features of the subject invention will be
`readily apparent from the accompanying drawings and
`detailed description of the preferred embodiments.
`
`5
`
`3
`data which is transmitted to a cockpit monitor for use by the
`flight crew and to one or more "black box" recorders for
`recording the data to aid in reconstruction of a catastrophic
`event, performance history or the like.
`The wireless system provides assurances against disrup(cid:173)
`tion of data transmission and collection during a catastrophic
`airframe failure. In the preferred embodiment, the wireless
`system is fully self-contained with each sensor unit having
`an independent power supply.
`In the preferred embodiment, the monitoring and record(cid:173)
`ing systems for collecting and transmitting the data are also
`self-contained. This assures that the entire collection,
`transmission, display and recording system will continue to
`operate in the event of either a malfunction or a structural
`failure of the aircraft causing a disruption in aircraft power. 15
`Typically the data is transmitted to a monitor provided on
`the flight deck and to a "black box" recorder which may be
`placed in the tail section, as is common for flight data and
`voice recorders currently in use. In the preferred
`embodiment, dual recorders are provided to provide redun- 20
`dancy. For example, one recorder may be installed in the
`nose section and a second in the tail section to better assure
`that the recorded data may be retrieved in the event of a
`catastrophic event. The flight deck has instant real time
`access to all of the data being collected and the recorders 25
`provide an historic record for archive purposes.
`Where random access recording techniques are used, such
`as, by way of example, digital memory storage devices, the
`flight deck and the ground station personnel may also be able
`to search and retrieve stored information. For example,
`current hydraulic pressure of a component may be compared
`with the pressure of a past point in time to monitor rate of
`change.
`That is, the ground tracking station will have the capa- 35
`bility of interrogating the in flight data while the aircraft is
`in flight. Near real time data can be received and historical
`data can be retrieved, as well, when the random access
`storage device is utilized.
`The plurality of sensors may be synchronized through an 40
`on board multiplexing system. In the preferred embodiment,
`the system is adapted for incorporating the data signal
`generated by the aircraft navigational data such as that
`provided by an inerntial navigation system or global posi(cid:173)
`tioning system ( GPS) for tracking the altitude, latitude and 45
`longitude coordinates synchronized with the collected data
`in order to provide accurate information of where the aircraft
`is in its flight plan when an incident occurs. A time or
`chronology signal may also be incorporated in the data
`scheme. Any signal which is capable of being captured and 50
`stored may be monitored in this manner. By tying each of the
`signals to a reference such as the GPS signal or a clock, the
`retrieval of data and reconstruction of an on board incident
`is facilitated.
`Preferably, the entire capture, retrieval, monitor and
`archive system is installed utilizing a wireless transmitting/
`receiving system in order to assure that transmission will not
`be lost in the event of a power shutdown or a structural
`failure causing possible open circuit conditions which could
`occur in a hard wired system. In the preferred embodiment, 60
`such a system would be completely self-contained with an
`integrated power supply and an integrated illumination
`system.
`It is, therefore, an object and feature of the subject
`invention to provide a wireless data monitoring, collecting, 65
`displaying, transmitting, receiving and storage safety and
`surveillance scheme for aircraft.
`
`BRIEF DESCRIPTION OF THE DRAWINGS
`FIG. 1 is a cutaway illustration of the fuselage of an
`aircraft showing exemplary placement various sensors,
`transducers and monitors throughout the aircraft in accor(cid:173)
`dance with the invention.
`FIG. 2 is a block diagram of a wireless system in
`accordance with the subject invention
`FIG. 3 is a block diagram similar to FIG. 2, showing a
`hardwired monitor in combination with the system.
`FIG. 4 is a block diagram of a system incorporating the
`features of the wireless system of FIG. 2 in combination
`with a hardwired system to provide redundancy,
`FIG. 5 is a block diagram of a wireless redundant system.
`FIG. 6 is a block diagram incorporating the teaching of
`55 the invention in a multiple sensor device.
`FIG. 7 is a an expansion of the block diagram of FIG. 7,
`illustrating redundant recording systems.
`FIG. 8 is a block diagram showing the system of the
`subject invention in combination with a multi-media system.
`FIG. 9 is a block diagram illustrating the use of a
`multiplexer in combination with close proximity sensors
`prior to transmission via a wireless system.
`
`DETAILED DESCRIPTION OF THE
`PREFERRED EMBODIMENTS
`FIG. 1 shows a cutaway diagram of a typical commercial
`airline fuselage 10, with the cargo hold 12, the passenger
`
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`cabins 14, 16 and the flight deck or cockpit 18 partially
`visible. A plurality of sensors, transducers, and other moni(cid:173)
`toring equipment are strategically placed throughout the
`aircraft as diagrammatically illustrated by the sensors
`19a-m. These include strain gauges, engine temperature
`sensors, hydraulic pressure gauges and the like, as generally
`well known by those who are of ordinary skill in the art. The
`placement and number of devices is a matter of choice
`depending upon the configuration of the system.
`In the embodiment shown and described, a "black box"
`data recorder 52 is installed in the tail section of the aircraft,
`in the same manner as the current flight data and cockpit
`voice recorder "black boxes" (not shown). In the preferred
`embodiment, a redundant "black box" data recorder 53 is
`also installed in the nose section of the aircraft. A flight deck
`monitor 55 and control panel 54 is located on the control
`panel in the cockpit 18. Other monitors may be provided
`where desired. While the system of the subject invention is
`specifically designed to operate as a stand alone system, it is
`also adapted to be used in combination with the multi-media
`systems described in my aforementioned applications. When
`used is such a combination, the system may include video
`cameras 20, 22, 24, 26, 28, 30, 32, 34, 36, 38, 40, 42, 44, 48
`and 50. This combination system is more fully described in
`those applications and is shown and described later herein
`with specific reference to FIG. 9.
`Turning now to FIG. 2, it will be noted that each of the
`transducers or sensors 19 is specifically adapted to monitor
`a critical function and is intended to be a discrete, stand
`alone unit. In the preferred embodiment, transducer will
`produce an output signal on the associated output line 115
`which is introduced to a transmitter 116 for output to antenna
`118 for generating a radio signal. A local reserve power
`supply 110 is provided. This is typically a rechargeable
`supply such as a capacitor system, a rechargeable battery, or 35
`the like. Typically, the rechargeable power supply 110 will
`be coupled directly to the aircraft power source 114, as
`indicated at 117. In most applications it is only necessary
`that the reserve power be sufficient to power the transmitter
`and the transducer for at most a few minutes after aircraft 40
`power shutdown. Therefore, the reserve power system may
`be minimized in both size and weight requirements. Also, it
`should be understood that certain mechanical transducers
`may not require power, in which case the reserve power
`source would only be utilized to power the transmitter 116. 45
`The receiver/recording system for the subject invention
`includes at least crash hardened one "black box" data
`recorder 52 adapted for receiving incoming data on line 51
`received from the receiver 153 via the antenna 61. The 50
`recording system including the receiver and the recorder are
`also supplied with a reserve power supply 111 which is
`coupled to the aircraft power source as previously explained.
`A modification of the system of FIG. 2 is shown in FIG.
`3. As there shown, the signal on line 115 from the transducer
`19 may be introduced directly to a cockpit display or
`monitor 55 via line 60. That is, the transducer may be
`hardwired directly to the monitor as in prior art systems.
`A further modification is illustrated in FIG. 4, wherein the
`wireless system of the subject invention is shown used in
`tandem with a hardwired transducer to provide a redundant
`system. In the embodiment shown, the hardwired transducer
`219 provides the input to the monitor 55. This type of
`configuration is particularly well suited for retrofit applica(cid:173)
`tions where the hardwired system is already in place. The
`self contained, reserve power sensors/transducers of the
`subject invention may be incorporated directly into an
`
`6
`existing system without modifying any of the original hard(cid:173)
`wired components. The transmitter is then used to transmit
`the information directly to the wireless stand alone recorder
`52, as previously described. In this embodiment, the hard-
`s wired recorder (not shown) generally associated with the
`hardwired transducer need not be removed, although typi(cid:173)
`cally it becomes unnecessary.
`A redundant wireless system is shown in FIG. 5. In this
`configuration dual transducers 19a and 19b monitor the
`10 same component or function, with duplicate systems pro(cid:173)
`viding input to the transmitting antenna 118. The recording
`system portion of this embodiment operates as previously
`described, utilizing antenna 61 as the receiving antenna.
`This provides transducer and transmitter redundancy for fail
`15 safe operation.
`Each of the embodiments of FIGS. 2-5 are designed to be
`utilized in a multiple sensor system, as shown in FIG. 6,
`wherein the various transducers or sensors 19a-m, as exem(cid:173)
`plified in FIG. 1 are incorporated into a comprehensive
`20 monitoring and recording system. Each transducer 19a-min(cid:173)
`cludes a dedicated transmitter 116a-m for producing an
`output signal at the dedicated antenna 118a-m. Each trans(cid:173)
`ducer system also includes a dedicated, stand alone reserve
`power system llOa-m for powering the respective transmit-
`25 ter and the respective transducer where required.
`A dedicated receiver 153a-m is associated with each
`transducer 19a-m for receiving the signal and introducing it
`into the flight data recorder 52. Typically each transducer
`30 and each mated receiver will send and receive on a dedicated
`radio frequency for maintaining the distinctive signals from
`each transducer.
`Where redundant recorders 52 and 53 are utilized. The
`recorder system is duplicated as shown in FIG. 7.
`Specifically, once a signal is generated by the various
`transmitters 116a-m, the signal can be received by any
`antenna 61a/61b positioned anywhere in the aircraft. This
`permits the placement of redundant recorders at various
`points in the aircraft for better assuring retrieval in the event
`of a catastrophic event. By using the wireless system, the
`placement and number of recorders is not limited by the
`difficulty in stringing wires or by the added weight from the
`wiring systems. This greatly enhances both the versatility
`and the dependability of the system.
`As previously stated the system of the subject invention
`may be used in combination with a comprehensive multi(cid:173)
`media system as described in more detail in my aforemen(cid:173)
`tioned applications. An exemplary embodiment is shown in
`FIG. 8. As there shown, each of the various cameras C will
`be mounted at the desired site and will include also a
`self-contained power supply 110. This provides a fully
`integrated system which is operational even in the event of
`airframe failure or shut down of the aircraft power supply
`and backup systems. In the preferred embodiment, each
`ss camera unit will include an illuminating source such as, by
`way of example, the light source 211, which will be opera(cid:173)
`tional during a power failure mode, or selectively opera(cid:173)
`tional during certain operating modes. For example, the
`cargo bay camera illumination system would be operational
`60 even if all other aircraft power had failed. Other systems
`such as infrared sensor systems can also be incorporated to
`provide adequate image capturing techniques. The camera
`system also includes the self-contained transmitter 116 and
`an antenna 118 for transmitting the captured video signal via
`65 a dedicated low interference radio frequency. Each signal is
`received by an antenna 60 and deciphered by matching
`receivers 120, 122, 124, 126 ... 150, in one-to-one corre-
`
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`spondence with the cameras 20, 22, 26 ... 50, to provide a
`unique video signal on each of the lines 94 as previously
`described, for providing input into the switching matrix 96
`of the receiver/processing network. The receiver/processor
`network also include a dedicated, self contained power
`supply as indicated by the rechargeable power supply we
`previously described.
`Where a synchronized system is used in a wireless
`multiple camera installation, numerous synchronizing tech(cid:173)
`niques may be utilized. For example, the wires may be
`synched, or the unsynchronized video signal may be trans(cid:173)
`mitted and then resynchronized utilizing digital techniques,
`or as illustrated here, where the synch signal is transmitted.
`Specifically, each camera C will include a self-contained
`synchronizing signal receiver 156 in addition to the trans(cid:173)
`mitter 116 and the power supply. This receiver can also be
`used as an on-off/switching device for the cameras and could
`be set up as a wireless multiplexer by switching cameras.
`The antenna 118 will be used for both transmitting the video
`signal and receiving the sync signal. As diagrammatically
`shown in FIG. 8, the receiver/processing system is modified
`to include a master synchronizing signal source 90, see FIG.
`3 and a transmitter 158 coupled to the antenna 60. The
`various function sensors 19a-m of the subject invention are
`incorporated in the multi-media system and operate in the
`manner described. Additional multi-media sensors may be
`incorporated in the system, as well, and may be wireless or
`hard wired as appropriate.
`All of the data, including all video, audio and digital data
`will be recorded on the "black box" data recorder system 70.
`The combined, comprehensive output signal may also be
`downlinked to the ground tracking station, as described in
`my aforementioned copending applications.
`FIG. 9 is an illustration of a system incorporating a
`multiplexer 296 positioned between an array of close prox(cid:173)
`imity sensors 19a . .. 19m. This permits all of the output
`signals 115a . . . 115m to be combined into a single
`combined output signal 215 before the signal is transmitted
`to the receiver system. This would be particularly useful for
`sensors in close proximity such as, by way of example, the
`complete array of sensors associated with a single engine.
`This would reduce the overall amount of hardware required
`by incorporating the individual signal on lines 115a . ..
`115minto a single combined engine data signal on line 45,
`permitting transmission via a single transmitter 116.
`It will be understood that the wireless configuration can
`be readily adapted to any component of the system once the
`various data signal are available as radio frequency trans(cid:173)
`missions. Therefore, it may be desirable to use wireless 50
`monitors, downlinking systems and other components as
`well to both reduce dependency on wired systems which
`may fail and to further reduce the complexity of the instal(cid:173)
`lation process.
`Any of a variety of recording devices and systems may be 55
`utilized. In addition to the well-known and highly utilized
`analog recording systems, it is desirable to utilize a digital
`data recorder system in many instances to permit global
`searching and downloading capability.
`The video recorders, synchronizing networks and multi- 60
`plexing hardware