Description
`
`AN AIRCRAFT SURVEILLANCE SYSTEM
`
`0232031
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`2
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`This invention relates to an aircraft surveillance
`system.
`It is an aim of the present invention to provide an
`aircraft surveillance system which can be used to
`survey the inside of an aircraft during an emergency
`such for example as a hijack or which can be used to
`survey land or objects outside the aircraft such for
`example as a border sheltering terrorists.
`Accordingly. this invention provides an aircraft
`surveillance system comprising an aircraft. at least
`one closed circuit slow scan television camera which
`is positioned in the aircraft and which is for surveying
`a predetermined area. first transducer means which
`is positioned in the aircraft and which
`is
`for
`converting video signals from the camera into audio
`signals. first transceiver means which is positioned
`in the aircraft and which is for transmitting the audio
`signals from the first transducer means and for
`receiving command signals. second transceiver
`means which is positioned in a command base
`remote from the aircraft and which is for receiving
`the audio signals from the first transceiver means
`and for sending the command signals, second
`transducer means which is positioned in the com-
`mand base and which is for converting the audio
`signals received by the second transceiver means
`into video signals, and at least one television monitor
`for providing a visual display consequent upon
`receiving the video signals from the second trans(cid:173)
`ducer means.
`The aircraft surveillance system of the invention is
`especially useful for surveying the inside of an
`aircraft during a hijack. When a hijack occurs, the
`hijackers invariably inform ground control that they
`have hijacked the aircraft and, with the surveillance
`system of the present invention, it is only necessary
`for the ground control to issue an appropriate
`command signal to cause the camera to operate and
`to cause pictures of the hijack to be transmitted
`back to a television monitor in ground control. The
`transmitted pictures can be enlarged as may be
`desired. for example to ascertain the identity of a
`hijacker andl or whether or not the hijacker has a real
`gun. grenade or the like or whether the gun, grenade
`or the like is an imitation device. It will thus be
`apparent. that by the time the aircraft is forced to
`land at its destination determined by the hijacker,
`ground control will be in a good position to know
`exactly what action to take.
`The aircraft surveillance system of the invention is
`also of a special use for surveying land. In this case,
`the aircraft will usually be a slow flying aircraft such
`for example as a helicopter. as opposed to a
`passenger flying aircraft. Pictures of the land can be
`relayed to a command base and the pictures may
`help to establish the position of terrorists. escaped
`prisoners or the like on the land.
`The pictures can be displayed as black and white
`or colour pictures.
`The command base will usually be a ground
`command base but. if deSired, the command base
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`could be in another aircraft, a ship or a vehicle.
`The command signals will usually be start-up
`signals for initiating operation of the aircraft surveill(cid:173)
`ance system. However. if desired. the start-up
`signals may be other Signals for actuating the
`commencement of other desired functions.
`The first and the second transceiver means may
`be substantially identical pieces of equipment.
`The first transducer means will usually convert the
`video signals from the camera to audio Signals on
`cassette tape. The audio signals will usually be
`transmitted from the aircraft to the command base
`as radio signals. For example. the audio Signals may
`be transmitted on normal aircraft radio frequencies
`such for example as the aircraft Mayday frequency.
`Advantageously, the first transducer means and
`the first transceiver means are housed together in a
`single piece of equipment. Similarly. the second
`transducer means and the second transceiver
`means are also advantageously housed together in a
`single piece of eqUipment. Such single pieces of
`equipment can be arranged to be mobile or static.
`The transducer means and the transceiver means
`are advantageously in the form of a single piece of
`equipment known as IBSONSCAN II. The IBSON(cid:173)
`SCAN II is manufactured and sold by Ibsonmain
`Limited, of Uxbridge. Middlesex, England. Other
`equipment can of course by used if desired.
`Preferably, the first and the second transceiver
`means record on to tape so that they have a
`playback facility for helping repeated surveillance of
`an area or an object in that area.
`Usually, the first and the second transceiver
`means will have a rewind facility.
`Any appropriate camera may be employed. Exam(cid:173)
`ples of cameras that may be employed are those
`manufactured by Ademco,Philips and Norbane. The
`cameras may be pOSitioned where desired and
`appropriate in the aircraft. For example, for a
`passenger aircraft there will usually be one camera
`positioned in the cockpit together with a number of
`other cameras positioned in the passenger. accom(cid:173)
`modation of the aircraft, the actual number of
`cameras employed being dependent upon the size
`of the passenger accommodation. For a jumbo jet. it
`is envisaged that at least four cameras will be
`required for the passenger accommodation, whilst it
`is envisaged that a minimum of two cameras will be
`required for the passenger accommodation of a
`Boeing 737 or a Boeing 757.
`The cameras will usually be connected to the
`aircraft TPU power circuit to ensure that the power
`to the cameras cannot easily be switched off.
`Indeed. it is desirable that the entire aircraft
`surveillance system is such that it cannot by
`switched on or off or otherwise generally interferred
`with by aircraft personnel so that. in the event that
`the hijackers should know that they are being filmed,
`they cannot instruct the aircraft personnel to switch
`off the aircraft surveillance system.
`The cameras can be positioned at random
`
`Sony, Ex. 1002, p.501
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`

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`3
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`0232031
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`4
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`positions in the same type of aircraft if desired in
`order that hijackers cannot easilly know the location
`of the cameras. The cameras can also be concealed
`where possible, for example in overhead compart-
`ments, again so that their presence cannot easily be
`established.
`Preferably, the aircraft surveillance system is such
`that the TV monitor has a picture hold facility.
`The aircraft surveillance system may be one which
`has a visual display facility only. the signals passing
`from the aircraft to the command base then being
`signals which are only for permitting the visual
`display. Alternatively. the aircraft surveillance system
`may be one which has a visual display facility and
`also a speech facility, the signals passing from the
`aircraft to the command base then being first signals
`which permit the visual display and second signals
`which permit the speech.
`An embodiment of the invention will now be
`described solely by way of example and with
`reference
`to the accompanying drawing which
`shows in diagrammatic form an aircraft surveillance
`system.
`Referring to the drawing, there is shown an
`aircraft surveillance system 2 comprising an air-
`craft 4 and four closed circuit slow scan television
`cameras 6 which are positioned in the aircraft 4 and
`which are for surveying predetermined areas in the
`aircraft 4 such for example as the cockpit area and
`the passenger areas. One camera 6 will be employed
`for surveying each predetermined area.
`The aircraft surveillance system 2 also comprises
`first transducer means 8 which is positioned in the
`aircraft 4 and which is for converting video Signals
`from
`the cameras 6
`into audio Signals. First
`transceiver means 10 is positioned in the aircraft 4
`and is for transmitting the audio signals from the first
`transducer means 8 and for receiving command
`signals.
`The aircraft surveillance system 2 also comprises
`second transceiver means 12 which is positioned in
`a command base 14 remote from the aircraft 4 and
`which is for receiving aUdio signals from the first
`transceiver means 10 and for sending the command
`signals. The command base 14 is also provided with
`second transducer means 16 which is for converting
`the audio signals received by the second transceiver
`means 12 into video signals. A television monitor 18
`is linked to the second transducer means 16 for
`providing a visual display consequent upon receiving
`the Video signals from the second transducer means
`16.
`The cameras 6 are controlled by a control device
`20 which is activated by receiving appropriate
`control signals from the first transducer means 8.
`The control device 20 can be used to make the
`cameras 6 pan, tilt. zoom or perform other functions.
`Ti'e control device 20 can also be used to activate
`lights or perform other control functions.
`The first transducer means 8 and
`first
`the
`transceiver means 10 are advantageously formed
`together in a single housing as a single piece of
`equipment 22. Similarly. the second transceiver
`means 12 and the second transducer means 16 are
`advantageously formed together in a single housing
`
`as a single piece of equipment 24. The equipment
`22.24 is advantageously the equipment referred to
`above and known as IBSONSCAN II. The equipment
`22,24 is such that it enables the pictures to be set as
`a continuous series of still pictures, updated every
`twenty two seconds. through standard voice fre(cid:173)
`quency radio channels. The equipment 22 is able to
`take a televiSion frame from the television cameras 6,
`convert the video signals to audio signals, record
`then, dial the command base 14, make a security
`check, and send the pictures, if desired accompa(cid:173)
`nied by the time. date. source and any other required
`information. The equipment 24 is able to receive the
`signals from the eqUipment 22, make a security
`check, accept the signals, and record the signals,
`The equipment 24 contemporaneously restores the
`signal to a video mode and allows the picture to be
`displayed on the television monitor 18, together with
`any other transmitted information such for example
`as the above mentioned time, date and source.
`The equipment 22,24 can control the entire aircraft
`surveillance system 2 and the transmitting equip(cid:173)
`ment by sending up to sixty four separate instruc(cid:173)
`tions. If a poor connection is made, the equipment
`22 can be instructed to rewind and replay its
`recording of an entire sequence. The eqUipment 24
`can receive an entire transmission and it also has the
`facility to enable a single frame to be held on the
`television monitor 18. An entire transmission can be
`played back later for analYSis and hard copying if
`desired.
`It is envisaged that the aircraft surveillance
`system 2 will be especially useful for dealing with
`hijack situations and also for enabling aircraft border
`patrols to spot terroriste.
`It is to be appreCiated that the embodiment of the
`invention described above with reference to the
`accompanying drawing has been given by way of
`example only and that modifications may be ef(cid:173)
`fected. Thus, for example, more or less than the
`illustrated four cameras 6 may be employed, and
`more than one television monitor 18 may also be
`employed. Also, the cameras 6 could be directed
`outside an aircraft to survey a predetermined area
`such as a border or a coastline.
`
`Claims
`
`1. An aircraft surveillance system comprising
`an aircraft, at least one closed circuit slow scan
`television camera which is positioned in the
`aircraft and which is for surveying a predeter(cid:173)
`mined area, first transducer means which is
`positioned in the aircraft and which is for
`converting video signals from the camera into
`audio signals, first transceiver means which is
`positioned in the aircraft and which is for
`transmitting the audio signals from the first
`transducer means and for receiving command
`signals. second transceiver means which is
`positioned in a command base remote from the
`aircraft and which is for receiving the audio
`signals from the first transceiver means and for
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`Sony, Ex. 1002, p.502
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`

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`5
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`0232031
`
`6
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`sending the command signals, second trans(cid:173)
`ducer means which is positioned in the com(cid:173)
`mand base and which is for converting the
`audio signals received by the second trans(cid:173)
`ceiver means into video signals. and at least
`one television monitor for providing a visual
`display consequent upon receiving the video
`signals from the second transducer means.
`2. An aircraft surveillance system according
`to claim 1 in which the first transducer means is
`for converting the video signals from
`the
`camera to audio signals on cassette tape.
`3. An aircraft surveillance system according
`to claim 1 or claim 2 in which the first transducer
`means and the first transceiver means are
`housed together in a single piece of equipment.
`and in which the second transducer means and
`the second transceiver means are also housed
`together in a single piece of equipment.
`4. An aircraft surveillance system according
`to anyone of the preceding claims in which the
`first and the second transceiver means record
`on to tape so that they have a play back facility
`for helping repeated surveillance of an area of
`an object in that area.
`5. An aircraft surveillance system according
`to anyone of the preceding claims in which the
`first and the second transceiver means have a
`rewind facility.
`6. An aircraft surveillance system according
`to anyone of the preceding claims in which the
`television monitor has a picture hold facility.
`7. An aircraft surveillance system according
`to anyone of the preceding claims and which
`has a visual display facility only, the signals
`passing from the aircraft to the command base
`then being signals which are only for permitting
`the visual display.
`S. An aircraft surveillance system according
`to anyone of claims 1 - 6 and which has a visual
`display facility and also a speech facility. the
`signals passing from the aircraft to the com(cid:173)
`mand base then being first signals which permit
`the visual display and second signals Which
`permit the speech.
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`Sony, Ex. 1002, p.503
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`

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`0232031
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`/24
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`Sony, Ex. 1002, p.504
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`

`
`Europaisches Patentamt
`
`European Patent Office
`
`Office europe en des brevets
`
`o Publication number:
`
`o 232 031
`A3
`
`@
`
`EUROPEAN PATENT APPLICATION
`
`€V Application number: 87300392.5
`
`@ Int. CI. 4: G08S 13/18
`
`@ Date of filing: 16.01.87
`
`® Priority: 03.02.88 GB 8802575
`
`@ Date of publication of application:
`12.08.87 Bulletin 87/33
`® Designated Contracting States:
`AT BE CH DE ES FR GR IT LI LU NL SE
`
`® Date of deferred publication of the search report:
`08.02.89 Bulletin 89/06
`
`e Applicant: SAYZEN LIMITED
`
`53 Brookwood Road
`Southfields London SW18 5BQ(GB)
`
`@ Inventor: Hale, Christopher John
`53 Brookwood Road
`Southfields London, SW18 SBQ(GB)
`® Representative: Jones, Graham H.
`Graham Jones & Company 77 Beaconsfield
`Road Blackheath
`London SE3 7LG(GB)
`
`/2,
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`@ An aircraft surveillance system.
`
`@ An aircraft surveillance system (2) comprising an
`aircraft (4). at least one closed circuit slow scan
`television camera (6) which is positioned in the air(cid:173)
`craft (4) and which is for surveying a predetermined
`area. first transducer means (8) which is positioned
`in the aircraft (4) and which is for converting video
`signals from the camera (6) into audio signals, first
`transceiver means (10) which is pOSitioned in the
`aircraft (4) and which is for transmitting the audio
`signals from the first transducer means (8) and for
`receiving command signals. second
`transceiver
`means (12) which is positioned in a command base
`(14) remote from the aircraft (4) and which is for
`receiving the audio signals from the first transceiver
`means (10) and for sending the command signals.
`C'l)second transducer means (16) which is positioned in
`c(the command base (14) and which is for converting
`the audio signals received from the second tran(cid:173)
`~ sceiver means (12) into video signals. and at least
`oone television monitor (18) for providing a visual
`NdiSPlay consequent upon receiving the video signals
`C'I) from the second transducer means (16).
`N
`o
`D.
`W
`
`Xerox Copy Centre
`
`Sony, Ex. 1002, p.505
`
`

`
`European Patent
`Office
`
`EUROPEAN SEARCH REPORT
`
`Application Number
`
`DOCUMENTS CONSIDERED TO BE RELEVANT
`Citation of document with indication, where appropriate,
`Category
`of relevant passages
`EP-A-O 137 320
`(ATIS)
`". Page 3, line 33 - page 4, line 33;
`figure 1 ".
`
`y
`
`Relevant
`to claim
`1-7
`
`y
`
`A
`
`A
`
`(ASCOTTS LTD)
`EP-A-O 028 933
`". Page 4, line 23 - page 5, line 29;
`figure 1 ".
`
`(DUCROT)
`CH-A-
`651 984
`". Whole document ".
`
`FR-A-2 551 240
`". Abstract ".
`
`(ARPHI)
`
`1-7
`
`1,8
`
`1
`
`EP 87 30 0392
`
`CLASSIFICATION OF TIlE
`APPUCATION (lDI. CL4)
`
`G 08 B 13/18
`
`TEOINICAL FIElDS
`SEARCHED (Int. CI.4)
`
`G 08 B
`
`The present search report has heen drawn up for all claims
`
`Dlie of CIImpletiDll of tile seardI
`
`ExmaiDer
`
`I
`PI .... of seardI
`I
`1~_T_HE __ HA_G_UE ________ ~ ____ 2_2-_1_1-_1_98_8 ______ ~S_G_U_~_S_. ________ ~
`CATEGORY OF CITED DOCUMENTS
`~
`T : tbeory or principle underlying tbe Invention
`E : earlier patent document, but publisbed 011, or
`X: particularly relevant if taken alone
`after the fding date
`~
`Y : particularly relevant if combined With another
`D : document cited in the applicatiun
`document or the same category
`~ ..
`L: document cited for other reasons
`A: tecbnological background
`o : non-written disclosure
`&·;-;;;;';;j;.-O"ih;~;;;·p7at;i·&;;;iiY:·;~;P;;;;d1;;g·-·--·-"-·"-"
`P : intermediate document
`~
`document
`~~------------------------------------------------------------------------~
`
`Sony, Ex. 1002, p.506
`
`

`
`Europaisches Patentamt
`
`European Patent Office
`
`Office europeen des brevets
`
`111111111111111111111111111111111111111111111111111111111111111111111111111
`@ Publication number: 0 613 109 A 1
`
`@
`
`EUROPEAN PATENT APPLICATION
`
`@ Application number: 94301261.7
`@ Date of filing: 23.02.94
`
`@ Priority: 26.02.93 US 23978
`@ Date of publication of application :
`31.08.94 Bulletin 94135
`@ Designated Contracting States :
`DE ES FR GB IT NL SE
`® Applicant: RAYTHEON COMPANY
`141 Spring Street
`Lexington Massachusetts 02173 (US)
`
`@ Int. C1.5 : G08G 5/06
`
`@ Inventor: Hoover, Peter L.
`20 Kelleher Street
`Marlboro, MA 01752 (US)
`@ Representative: Jackson, David Spence et al
`REDDIE & GROSE
`16, Theobalds Road
`London, WC1X 8PL (GB)
`
`@ Infrared vehicle identification system.
`@) An infrared vehicle identification system [109]
`comprising a microprocessor controlled
`in(cid:173)
`frared (IR)
`transmnitter [112]
`located on an
`aircraft nose wheel landing strut [111] and an
`infrared receiver [128] including a microproces(cid:173)
`sor [44] enclosed in a plurality of edge light
`assemblies [20] located along surface pathways
`of an airport including runways and taxiways.
`The infrared transmitter [112] comprises an ar(cid:173)
`ray of light emitting diodes [120] (LEOs) ar(cid:173)
`ranged
`in a semicircle within
`the horizontal
`plane. The transmitter [112] emits a plurality of
`fields [121, Fig.13] of encoded data to provide
`information.
`vehide identification and pOSition
`One field [122] comprises a steady stream of
`pulses that allows the IR receiver [128] to calcu(cid:173)
`late the baud rate of the transmitter [112] and
`automatically adjust
`its
`intemal
`timing. The
`other fields indude a unique word
`[123] for
`marking the beginning of a message, the num(cid:173)
`ber [124] of characters in the message, the'
`vehide identification number [125], the vehicle
`position [126] and a checksum [127]. The latter
`[127] ensures that a complete and correct mes(cid:173)
`sage has been received. If the transmitted mes(cid:173)
`sage
`is
`interrupted
`for any
`reason,
`the
`checksum [127] will detect it and the messages
`will be voided. The IR receiver [128] relays a
`valid message of vehicle identification [125] and
`position [126] to a central computer system [12,
`Fig.1] at the airport control tower via the edge
`light assembly power wiring [21, Fig.1].
`
`-<C
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`Jouve, 18, rue Saint-Denis, 75001 PARIS
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`
`Sony, Ex. 1002, p.507
`
`

`
`Background of the Invention
`
`EP 0 613109 A1
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`This invention relates to identification of airport surface traffic and in particular to an apparatus and meth(cid:173)
`od for detecting and identifying aircraft or other vehicle movement on airport taxiways, runways and other sur-
`face areas.
`Currently, ground control of aircraft at an airport is done visually by the air traffic controller in the tower.
`Low visibility conditions sometimes make it impossible for the controller to see all parts of the field. Ground
`surface radar can help in providing coverage during low visibility conditions; it plays an important part in the
`solution of the runway incursion problem but cannot solve the entire problem. A runway incursion is defined
`as "any occurrence at an airport involving an aircraft, vehicle, person, or object on the ground that creates a
`collision hazard or results in loss of separation with an aircraft taking off, intending to take off, landing, or in(cid:173)
`tending to land." The U.S. Federal Administration Agency (FAA) has estimated that it can only justify the cost
`of ground surface radar at 29 of the top 100 airports in the United States. However, such radar only provides
`location information; it cannot alert the controller to possible conflicts between aircraft.
`In the prior art, an airport control and monitoring system has been used to sense when an airplane reaches
`a certain point on a taxiway and controls switching lights on and off to indicate to the pilotwhen he may proceed
`on to a runway. Such a system sends microwave sensor information to a computer in the control tower. The
`computer comprises software for contrOlling the airport lighting and for providing fault information on the airport
`lighting via displays or a control panel to an operator. Such a system is described in sales information provided
`on a Bi-directional Series 7 Transceiver (BRITEE) produced by ADB-ALNACO, Inc., A Siemens Company, of
`Columbus, Ohio. However, such a system does not show the location of all vehicles on an airfield and is not
`able to detect and avoid a possible vehicle incursion.
`A well known approach to airport surface traffic control has been the use of scanning radars operating at
`high frequencies such as K-band in order to obtain adequate definition and resolution. An existing airport
`ground traffic control equipment of that type is known in the art as Airport Surface Detection Equipment
`(ASDE). However, such equipment provides surveillance only, no discrete identification of aircraft on the sur(cid:173)
`face being available. Also there is a need for a relatively high antenna tower and a relatively large rotation an(cid:173)
`tenna system thereon.
`Another approach to airport ground surveillance is a system described in U. S. Patent No. 3,872,474, is-
`sued March 18, 1974, to Arnold M. Levine and assigned to International Telephone and Telegraph Corporation,
`New York, NY, referred to as LOCAR (Localized Cable Radar) which comprises a series of small, lower pow(cid:173)
`ered, narrow pulses, transmitting radars having limited range and time sequenced along opposite sides of a
`runway ramp or taxiway. In another U. S. Patent No.4, 197,536, issued on April 8, 1980, to Arnold M. Levine,
`an airport surface identification and control system is described for aircraft equipped with ATCRBS (Air Traffic
`Control Radio Beacon System) and ILS (Instrument Landing System). However, these approaches are expen(cid:173)
`sive, require special cabling and for identification purposes require expensive equipment to be included on the
`aircraft and other vehicles.
`Another approach to vehicle identification such as types of aircraft by identifying the unique characteristic
`of the "footprint" presented by the configuration of wheels unique to a particular type of vehicle is described
`in U.S. Patent No. 3,872,283, issued March 18, 1975, to Gerald R. Smith et al. and assigned to The Cadre
`Corporation of Atlanta Georgia.
`An automatic system for surveillance, guidance and fire-fighting at airports using infrared sensors is de(cid:173)
`scribed in U. S. Patent No. 4,845,629, issued July 4, 1989 to Maria V. Z. Murga. The infrared sensors are ar(cid:173)
`ranged along the flight lanes and their output signals are processed by a computer to provide information con-
`cerning the aircraft movements along the flight lanes. Position detectors are provided for detecting the position
`of aircraft in the taxiways and parking areas. However, such system does not teach the use of edge lights along
`the runways and taxiways along with their associated wiring and it is not able to detect and avoid a possible
`vehicle incursion.
`The manner in which the invention deals with the disadvantages of the prior art to provide a low cost in-
`frared vehicle identification system will be evident as the description proceeds.
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`Summary of the Invention
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`Accordingly, it is therefore an object of this invention to provide a low cost infrared system that identifies
`aircraft or other vehicles on airport taxiways and runways.
`It is also an object of this invention to provide at an airport a low cost aircraft or vehicle identification system
`using existing edge light assemblies and associated wiring along runways and taxiways.
`It is another object of this invention to provide an infrared vehicle identification system that generates a
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`Sony, Ex. 1002, p.508
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`graphic display of the airport showing the location of all ground traffic including direction and velocity data and
`identifies such ground traffic.
`The objects are further accomplished by providing a vehicle identification system for identifying aircraft
`and other vehicles on surface pathways including runways and other areas of an airport comprising means
`disposed on the aircraft and other vehicles for transmitting identification message data, means disposed in
`each of a plurality of light assembly means on the airport for receiving and decoding the message data from
`the transmitting means, means for providing power to each of the plurality of light assembly means, means
`for processing the decoded identification message data generated by the receiving and decoding means in
`each of the plurality of light assembly means, means for providing data communication between each of the
`light assembly means and the processing means, and the processing means comprises means for providing
`a graphic display of the airport comprising symbols representing the aircraft and other vehicles, each of the
`symbols having the identification message data displayed. The transmitting means comprises means for cre(cid:173)
`ating unique message data which includes aircraft and flight identification, and infrared means coupled to the
`message creating means for transmitting a coded stream of the message data. The message data further in-
`cludes position information. The receiving and decoding means comprises an infrared sensor. The receiving
`and decoding means comprises microprocessor means coupled to the infrared sensor for decoding the mes(cid:173)
`sage data. The plurality of light assembly means are arranged in two parallel rows along runways and taxiways
`of the airport. The light assembly means comprises light means coupled to the lines of the power providing
`means for lighting the airport, vehicle sensing means for detecting aircraft or other vehicles on the airport, mi-
`croprocessor means coupled to the receiving and decoding means, the light means, the vehicle sensing means
`and the data communication means for decoding the identification message data, and the data communication
`means being coupled to the microprocessor means and the lines of the power providing means. The symbols
`representing aircraft and other vehicles comprise icons having a shape indicating type of aircraft or vehicle.
`The processing means determines a location ofthe symbols on the graphic display of the airport in accordance
`with data received from the light assembly means.
`The objects are further accomplished by a vehicle identification system for surveillance and identification
`of aircraft and other vehicles on an airport comprising a plurality of light circuits on the airport, each of the light
`circuits comprises a plurality of light assembly means, means for providing power to each of the plurality of
`light circuits and to each of the light assembly means, means in each of the light assembly means for sensing
`ground traffic on the airport, means disposed on the aircraft and other vehicles for transmitting identification
`message data, means disposed in each of the light assembly means for receiving and decoding the message
`data from the transmitting means, means for processing ground traffic data from the sensing means and de(cid:173)
`coded message data from each of the light assembly means for presentation on a graphic display ofthe airport,
`means for providing data communication between each of the light assembly means and the processing means,
`the processing means comprises means for providing such graphic display of the airport comprising symbols
`representing the ground traffic, each of the symbols having direction, velocity and the identification message
`data displayed. Each of the light circuits are located along the edges of taxiways or runways on the airport.
`The senSing means comprises infrared detectors. The transmitting means comprises means for creating
`unique message data which includes aircraft and flight identification, and infrared means coupled to the mes-
`sage creating means for transmitting a coded stream of the message data. The message data further com(cid:173)
`prises position information. The receiving and decoding means comprises an infrared sensor. The receiving
`and decoding means comprises microprocessor means coupled to the infrared sensor for decoding the mes(cid:173)
`sage data. The plurality of light assembly means of the light circuits being arranged in two parallel rows along
`runways and taxiways of the airport. The light assembly means comprises light means coupled to the lines of
`the power providing means for lighting the airport, the ground traffic sensing means for detecting aircraft or
`other vehicles on the airport, microprocessor means coupled to the receiving and decoding means, the light
`means, the ground traffic sensing means and the data communication means for decoding the identification
`message data and proceSSing a detection signal from the ground traffic sensing means, and the data com(cid:173)
`munication means being coupled to the microprocessor means and the lines of the power providing means.
`The light assembly means further comprises a photocell means coupled to the microprocessor means for de(cid:173)
`tecting the light intensity of the light means. The light assembly means further comprises a strobe light coupled
`to the microprocessor means. The processing means comprises redundant computers for fault tolerance op(cid:173)
`eration. The symbols representing the ground traffic comprise icons having a shape indicating type of aircraft
`or vehicle. The processing means determines a location of the symbols on the graphic display of the airport
`in accordance with the data receive from the light assembly means. The processing means determines a future
`path of the ground traffic based on a ground clearance command, the future path being shown on the graphic
`display. The processing means further comprises means for predicting an airport incursion. The power pro(cid:173)
`viding means comprises const