GB2415943A - Aircraft-infrastructure collision intervention system - Google Patents
Aircraft-infrastructure collision intervention system Download PDFInfo
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- GB2415943A GB2415943A GB0415226A GB0415226A GB2415943A GB 2415943 A GB2415943 A GB 2415943A GB 0415226 A GB0415226 A GB 0415226A GB 0415226 A GB0415226 A GB 0415226A GB 2415943 A GB2415943 A GB 2415943A
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- aircraft
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- 230000006266 hibernation Effects 0.000 claims abstract description 16
- 238000004891 communication Methods 0.000 claims description 36
- 239000013598 vector Substances 0.000 claims description 17
- 230000000694 effects Effects 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 239000000446 fuel Substances 0.000 claims description 6
- 238000005259 measurement Methods 0.000 claims description 6
- 238000013475 authorization Methods 0.000 claims description 3
- 238000012986 modification Methods 0.000 claims description 3
- 230000004048 modification Effects 0.000 claims description 3
- 238000011084 recovery Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 description 22
- 238000012544 monitoring process Methods 0.000 description 2
- 230000004913 activation Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/04—Anti-collision systems
- G08G5/045—Navigation or guidance aids, e.g. determination of anti-collision manoeuvers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0015—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems
- B64D45/0031—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems means for overriding or restricting access to flight controls
- B64D45/0034—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems means for overriding or restricting access to flight controls by ground-control override
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0015—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems
- B64D45/0031—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems means for overriding or restricting access to flight controls
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/0015—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems
- B64D45/0059—Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems by communicating emergency situations to ground control or between crew members
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S5/00—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations
- G01S5/0009—Transmission of position information to remote stations
- G01S5/0018—Transmission from mobile station to base station
- G01S5/0027—Transmission from mobile station to base station of actual mobile position, i.e. position determined on mobile
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/0047—Navigation or guidance aids for a single aircraft
- G08G5/0056—Navigation or guidance aids for a single aircraft in an emergency situation, e.g. hijacking
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Traffic Control Systems (AREA)
Abstract
An aircraft collision intervention system comprises a system intervention processor coupled to position detecting means and an onboard infrastructure database, the intervention system being configured to isolate the pilot controls and execute collision avoidance manoeuvres in the event of the aircraft flying within a predetermined range, indicated by an inner radius boundary 2, from the origin of infrastructure (e.g. multi-storey building or power station). The intervention system may, subsequent to the collision avoidance manoeuvres, return control of the aircraft to the pilot at the request of air traffic control, or alternatively the system may transfer control to a system hibernation processor which will execute a controlled landing of the aircraft if it is still in the air, or perform a controlled immobilisation of the aircraft it it is on the ground.
Description
24 1 5943
AIRCRAFT INTELLIGENT INTERVENTION FLY-BY-WIRE SYSTEM
BACK GROUND OF THE INVENTION
FIELD OF THE INVENTION
This invention relates to an aircraft intelligent intervention fly-bywire system Where, when a commercial passenger aircraft or cargo aircraft is flying on a collision vector the invention provides systems for designated infrastructure avoidance, and provides systems for avoidance of specific sensitive infrastructures such as power station / nuclear power stations / multi-storey buildings or other city centre complex structures collision avoidance. More particular, the invention provides systems for detecting an aircraft collision vector and assess the situation and to take evasive manoeuvres.
DESCRIPTION OF THE PROBLEM
When a commercial passenger aircraft or cargo aircraft is in flight most likely in low altitude in the climb phase just after takeoff or in decent phase from the cruising altitude during the approach for landing, The infrastructures such as city centre multi-storey buildings if located near to a airport or vital resources such as power station (nuclear power station) are not protected from a direct collision.
The commercial passenger / cargo aircrafts fly-by-wire-control system has no independent means to assess the situation and to take evasive manoeuvres, or return the aircraft safely to a runway If Air Traffic Control needs to stop / prevent a commercial passenger aircraft or cargo aircraft from taking off from an Airport,.
If Air Traffic Control needs to land a commercial airliner automatically by overriding the control inputs from the pilot or co-pilot or Autopilot or Auto throttle If the commercial aircraft is intercepted by military aircraft and the military aircraft needs to land the commercial passenger aircraft or cargo aircraft automatically by overriding the control inputs from the pilot or co-pilot or Autopilot instead of waiting for the authority to shoot the commercial aircraft or cargo aircraft down causing the loss of the entire aircraft passengers and crew and people on the ground.
STATMENT OF INVENTION essential technical features According to the present invention there is provided an airborne an aircraft intelligent intervention fly-by-wire system comprising an aircraft position detecting means for detecting the position of the aircraft; an onboard infrastructure database arranged to be coupled to the position detecting, wherein information has been stored regarding the plurality of infrastructures with each individual infrastructure comprising the following Information such as.
(a) the Infrastructures infrastructure ID, (b) the infrastructures global position co-ordinates, (c) the infrastructures height, (d) the infrastructures predefined measurement for the outer radius boundary distance from the Infrastructures origin outwardly (e) the infrastructures predefined measurement for the inner radius boundary distance from the infrastructures origin outwardly the outer radius boundary distance is greater than the inner radius boundary distance; a Communications means such that Air Traffic Control can receive flight path vector information; a AircraK Unique Identification key means such that said Communications unique to a particular aircraft; The said AircraK Unique Identification key means is comprising information as (id1) Flight number/A'rcraft type, (ids) Number of passenger and crew onboard, (id2) Time / date, (ids) GPS location from take off/ GPS present; The said AircraK Unique Identification key Is sent as a header to a packet of information sent across the said Communications means; a system intervention processor coupled to said position detecting means and said onboard infrastructure database and said Communications means wherein the processor is configured and programmed to perform the following computing activities comprising (ip1) monitor position of the aircraft by means of the said positioning detecting means when the aircraft is below a predefined altitude; (ip2) compare the aircrafts relative position and present flight path vector in relation to a nearby infrastructure wherein details thereof acquired from the said onboard infrastructure database; (ip3) calculate collision avoidance flight path vectors for the aircraft when the aircraft Is within a predefined range Indicated by said outer radius boundary distance from the said infrastructures origin; (ip4) Generate an audio warning when the aircraft is within a predefined range indicated by said outer radius boundary distance from the said infrastructures origin, (ip5) periodically determining a distance between arcrafts relative position and said at least one infrastructure and re-calculate said collision avoidance flight path vectors to any input changes from the pilot or auto pilot or auto throttle; (ip6) Transmit the most recent collision avoidance flight path vectors to Air Traffic Control and other Aircraft in the vicinity when the aircraft is within a predefined range indicated by said outer radius boundary distance from the said infrastructures origin;
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(ip7) Set the aircrafts transponder to an emergency code when the aircraft is within a predefined range indicated by said inner radius boundary distance from the said infrastructures ongin, (ip8) isolate the controNnputs from the pilot or auto pilot or auto throttle and control the aircraft to execute the collision avoidance manoeuvres by means of Internal fly-by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle inputs, when the aircraft Is within a predefined range indicated by said inner radius boundary distance from the said infrastructures ongin; (ip9) Isolate the control inputs from the pilot or auto pilot or auto throttle and maintain the engine power during the execution of the collision avoidance manoeuvres by means of an internal fly-by- wire control computers coupled to Actuator Control System (ACS) Isolated from pilot input or autopilot or auto throttle inputs, when the aircraft within a predefined range indicated by said inner radius boundary distance from the said infrastructures origin, (ip10) Notify Air Traffic Control by Communication means of the next recovery procedure executed by the a system hibernation processor or return controNnput back to the pilot or auto pilot or auto throttle after the execution of the collision avoidance manoeuvre is completed, only if Air Traffic Control requests the system intervention processor to return control to the pilot or auto pilot or auto throttle, A system hibernation processor coupled to said intervention processor said position detecting means and said onboard Navigation database and Communications means wherein the processor computer is configured and programmed to execute a controlled forced landing procedure or a controlled immobilisabon of the aircraft on the ground the said processor performing activities are as follows.
(h1) determine If activated by the said intervention processor which Indicates the aircraft is in the air by means of Air data and said position detecting means; (h2) determine if activated by the authorization codes received from the said Communication means transmitted from the Air Traffic Control or from or an intercepting military aircraft; (h3) Once activation is accepted the hibernation processor performing computer activates comprising.
(i) determine If the aircraft is in the air the hibernation processor will acquire the fuel state from the arcrafts flight management computer and locate the nearest runway supporting automatic landing capabilities for the aircraft type based on the fuel remaining; (II) determine if the aircraft Is on the ground at an airport the hibernation processor will close the throttle and mmobilise the aircraft by means of internal fly-by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot Input or autopilot input or auto throttle Input; (h4) monitor the weather by means of information from the weather satellites and then generate an emergency flight plan; (h5) The said emergency flight plan is constructed by means of nformabon from the onboard Navigation database comprising the following Information: (n1) Airways, (n2) Airports, (n3) Runways, (n4) Routes, (n5) SID, (n6) STARS; (he) Transmit the emergency flight plan by said Communication means to Air Traffic Control (h7) Execute the emergency flight plan by means of Internal fly-by-wire control computers coupled to Actuator Control System (ACS) Isolated from pilot input or autopilot or auto throttle input and monitor any flight plan updates or modification from Air Traffic Control or Intercepting military aircraft; (he) Execute a fully automatic landing by means of internal fly-by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle input;
ADVANTAGES
The aircraft intelligent intervention fly-by-wire system will improve aircraft flight safety and return the aircraft and protect infrastructures.
The onboard position detecting means is preferably provided by a Global Positioning System (GPS) although the position detecting means may also be provided by other means, such as Inertia Navigation System (INS) or Omni directional Radio Range (VOR) or Distance Measuring Equipment (DOE).
The onboard Communication means is preferably provided by Aircraft Communications And Reporting System(ACARS) although the Communication means may also be provided by other means such as Satellite Communications (SATCOM) or Aircraft Transponder(AT)or Air Traffic Control (ATC) The onboard fully automatic landing means Is preferably provided by Instruments landing System(lLS) or Microwave Landing System(MLS) The infrastructure identification means is provided by onboard infrastructure database And information therein or Infrastructure DME mounted on a specific building,
BRIEF DESCRIPTION OF THE DRAWINGS
For a better understanding of the Invention, an embodiment of the Invention will now be described by way of a non-limting example with reference to the accompanying drawing which: Fig 1. Shows a diagram of some of the aircraft intelligent intervention fly-by-wire system
DETAILED DESCRIPTION OF THE INVENTION
The following descnpbon is a preferred embodiment of the aircraft intelligent intervention fly-by wire system an aircraft position detecting means for detecting the position of the aircraft; an onboard infrastructure database arranged to be coupled to the position detecting, wherein information has been stored regarding the plurality of infrastructures with each individual infrastructure comprising the following Information such as: (a) the infrastructures infrastructure ID, (b) the infrastructures global position co-ordinates, (c) the infrastructures height, (d) the infrastructures predefined measurement for the outer radius boundary distance 1 from the infrastructures origin outwardly, (e) the infrastructures predefined measurement for the inner radius boundary distance 2 from the infrastructures origin outwardly, the outer radius boundary distance Is greater than the inner radius boundary distance; a Communications means such that Air Traffic Control can receive flight path vector Information; a Aircraft Unique Identification key means such that said Communications unique to a particular aircraft, The said Aircraft Unique Identification key means is comprising information as (id1) Flight number / Aircraft type, (ids) Number of passenger and crew onboard, (id2) Time / date, (ids) GPS location from take off / GPS present; The said Aircraft Unique Identification key Is sent as a header to a packet of information sent across the said Communications means; < a system intervention processor coupled to said position detecting means and said onboard infrastructure database and said Communications means wherein the processor is configured and programmed to perform the following computing activities or operation FIG 2. is a flowchart showing an operation of the embodiment. The operation of the embodiment will be explained with reference to the flowchart in FIG 2.
First, In Step ip1 a processing for monitoring the position of the aircraft periodically is performed by means of the said positioning detecting means and part of the positioning information acquired will include the aircraft altitude reading Is read by the Intervention processor and then the control proceeds to Step ip2.
In Step ip2 a processing for when the aircraft Is below a predefined set altitude value Ref ALT Is determined according to a processing for determining if aircraft altitude ≤ Ref ALT. The set values Ref ALT is a predetermined reference altitude.
This reference altitude has such a value that when an aircraft position is below reference altitude, an aircraft is near to the height of surface Infrastructure. Therefore In the case of aircraft altitude ≤ Ret ALT the control proceeds to Step ip3, but processing for reading aircraft altimeter in Step ip1 is performed in case aircraft altitude > Ref ALT In Step ip3 a processing for compare the aircrafts relative position and present flight path vector in relation to a nearby infrastructure wherein details thereof acquired from the said onboard infrastructure database; and the control proceeds to Step ip4.
In Step ip4 a processing for calculating collision avoidance flight path vectors for the aircraft when the aircraft is within a predefined range indicated by said outer radius boundary distance 1 from the said infrastructures origin and the control proceeds to Step ip5.
In Step ip5 a processing for Generating an audio warning when the aircraft Is within a predefined range indicated by said outer radius boundary distance 1 from the said infrastructures origin; and the control proceeds to Step ip6.
In Step ip6 a processing for periodically determining a distance between arcrafts relative position and said at least one infrastructure and recalculate said collision avoidance flight path vectors to any Input changes from the pilot or auto pilot or auto throttle, and the control proceeds to Step ip7.
In Step ip7 a processing for Transmitting the most recent collision avoidance flight path vectors to Air Traffic Control and other Aircraft In the vicinity when the aircraft is within a predefined range Indicated by said outer radius boundary distance 1 from the said infrastructures origin and the control proceeds to Step ip8.
In Step ip8 a processing for Setting the aircrafts transponder to an emergency code when the aircraft Is within a predefined range indicated by said inner radius boundary distance 2 from the said infrastructures origin and the control proceeds to Step ip9.
In Step ip9 a processing for isolating the control inputs from the pilot or auto pilot or auto throttle and control the aircraft to execute the collision avoidance manoeuvres by means of internal fly- by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle inputs, when the aircraft Is within a predefined range indicated by said inner radius boundary distance 2 from the said infrastructures origin and the control proceeds to Step ip10.
In Step ip10 a processing for Isolating the controNnputs from the pilot or auto pilot or auto throttle and maintain the engine power during the execution of the collision avoidance manoeuvres by means of an internal fly-by-wire control computers coupled to Actuator Control System (ACS) Isolated from pilot input or autopilot or auto throttle inputs, when the aircraft within a predefined range Indicated by said inner radius boundary distance from the said infrastructures origin; and the control proceeds to Step ip11.
In Step ip11 a processing for Notifying Air Traffic Control by Communication means of the next recovery procedure executed by the a system hibernation processor or return control input back to the pilot or auto pilot or auto throttle after the execution of the collision avoidance manoeuvre is completed, only If Air Traffic Control requests the system intervention processor to return control to the pilot or auto pilot or auto throttle; FIG 3. is a flowchart showing an operation of the embodiment. The operation of the embodiment will be explained with reference to the flowchart in FIG 3.
A system hibernation processor coupled to said intervention processor said position detecting means and said onboard Navigation database and Communications means wherein the processor computer Is configured and programmed to execute a controlled forced landing procedure or a controlled immobilization of the aircraft on the ground the said processor performing activities are as follows In Step h1 a processing for determining If activated by the said intervention processor which indicates the aircraft is in the air by means of Air data and said position detecting means and the control proceeds to Step he.
In Step h2 a processing for determining if activated by the authorization codes received from the said Communication means transmitted from the Air Traffic Control or from or an intercepting military aircraft and the control proceeds to Step ha.
In Step ha a processing for determining if the aircraft on the ground then the control proceeds to Step h4 else the control proceeds to Step he.
In Step h4 a processing for determining If the aircraft is on the ground at an airport the hibernation processor will close the throttle and immobilise the aircraft by means of Internal fly- by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot input or auto throttle input; In Step he a processing for monitoring the weather by means of information from the weather satellites the hibernation processor will acquire the fuel state from the aircrafts flight management computer and locate the nearest runway supporting automatic landing capabilities for the aircraft type based on the fuel remaining; then generate an emergency flight plan and the control proceeds to Step he.
In Step he a processing for Constructing the said emergency flight plan by means of Information from the said onboard Navigation database comprising the following information.
(n1) Airways, (n2) Airports, (n3) Runways, (n4) Routes, (n5) SID, (n6) STARS; and the control proceeds to Step h7.
In Step h7 a processing for transmitting the emergency flight plan by said Communication means to Air Traffic Control and the control proceeds to Step he.
In Step he a processing for executing the emergency flight plan by means of internal fly-by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle input and monitor any flight plan updates or modification from Air Traffic Control or intercepting military aircraft and the control proceeds to Step he.
In Step he a processing for executing a fully automatic landing by means of internal fly-by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle input then Immobilize the aircraft when safe to do so;
ADVANTAGES
The aircraft intelligent intervention fly-by-wire system will improve aircraft flight safety and return the aircraft and protect Infrastructures.
The onboard position detecting means Is preferably provided by a Global Positioning System (GPS) although the position detecting means may also be provided by other means, such as Inertia Navigation System (INS) or Omni directional Radio Range (VOR) or Distance Measuring Equipment (DME).
The onboard Communication means is preferably provided by Aircraft Communications And Reporting System(ACARS) although the Communication means may also be provided by other means such as Satellite Communications (SATCOM) or Aircraft Transponder(AT)or Air Traffic Control (ATC) The onboard fully automatic landing means is preferably provided by Instruments landing System(lLS) or Microwave Landing System(MLS) Alternative infrastructure sensing means The infrastructure Identification means Is provided by onboard infrastructure database And information therein or Infrastructure DME mounted on a specific building, Distance Measuring Equipment is a method of pulse ranging the frequency is usually in the range or 960-1215Mhz band used to acquire the distance of the aircraft from a predetermined infrastructure The aircraft equipment transmits an interrogation pulse toward the infrastructure when this signal is received a reply pulse is sent back to the aircraft the IDME on board is able to determine the distance from the infrastructure
Claims (8)
1. An airborne aircraft intelligent intervention fly-by-wire system (AIIFBW) for deployment on a given aircraft composing: an aircraft position detecting means for detecting the position of the aircraft; an onboard infrastructure database arranged to be coupled to the position detecting, wherein information has been stored regarding the plurality of Infrastructures with each individual infrastructure comprising the following Information such as: (a) the infrastructures infrastructure ID, (b) the infrastructures global position co-ordinates, (c) the Infrastructures height, (d) the infrastructures predefined measurement for the outer radius boundary distance from the infrastructures origin outwardly, (e) the Infrastructures predefined measurement for the inner radius boundary distance from the Infrastructures origin outwardly, the outer radius boundary distance is greater than the inner radius boundary distance; a Communications means such that Air Traffic Control can receive flight path vector information; a Aircraft Unique Identification key means such that said Communications unique to a particular aircraft; The said Aircraft Unique Identification key means is comprising information as (id1) Flight number/aircraft type, (ids) Number of passenger and crew onboard, (id2) Time / date, (ids) GPS location from take off / GPS present, The said Aircraft Unique Identification key is sent as a header to a packet of information sent across the said Communications means; a system intervention processor coupled to said position detecting means and said onboard infrastructure database and said Communications means wherein the processor is configured and programmed to perform the following computing activities comprising (ip1) monitor position of the aircraft by means of the said positioning detecting means when the aircraft is below a predefined altitude; ('p2) compare the aircrafts relative position and present flight path vector in relation to a nearby infrastructure wherein details thereof acquired from the said onboard infrastructure database; (ip3) calculate collision avoidance flight path vectors for the aircraft when the aircraft is within a predefined range indicated by said outer radius boundary distance from the said infrastructures origin; (ip4) Generate an audio warning when the aircraft is within a predefined range Indicated by said outer radius boundary distance from the said Infrastructures origin, ('p5) periodically determining a distance between aircrafts relative position and said at least one infrastructure and re-calculate said collision avoidance flight path vectors to any input changes from the pilot or auto pilot or auto throttle; \O (ip6) Transmit the most recent collision avoidance flight path vectors to Air Traffic Control and other Aircraft In the vicinity when the aircraft is within a predefined range Indicated by said outer radius boundary distance from the said infrastructures origin, (ip7) Set the aircrafts transponder to an emergency code when the aircraft is within a predefined range indicated by said inner radius boundary distance from the said infrastructures origin, (ip8) isolate the controNnputs from the pilot or auto pilot or auto throttle and control the aircraft to execute the collision avoidance manoeuvres by means of internal fly-by-wre control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle inputs, when the aircraft is within a predefined range indicated by said inner radius boundary distance from the said infrastructures origin; (ip9) isolate the control inputs from the pilot or auto pilot or auto throttle and maintain the engine power during the execution of the collision avoidance manoeuvres by means of an internal fly-by- wire control computers coupled to Actuator Control System (ACS) isolated from pilot Input or autopilot or auto throttle Inputs, when the aircraft within a predefined range Indicated by said inner radius boundary distance from the said Infrastructures origin; (ip10) Notify Air Traffic Control by Communication means of the next recovery procedure executed by the a system hibernation processor or return controNnput back to the pilot or auto pilot or auto throttle after the execution of the collision avoidance manoeuvre Is completed, only if Air Traffic Control requests the system intervention processor to return control to the pilot or auto pilot or auto throttle; A system hibernation processor coupled to said intervention processor said position detecting means and said onboard Navigation database and Communications means wherein the processor computer is configured and programmed to execute a controlled forced landing procedure or a controlled mmobilisation of the aircraft on the ground the said processor performing activities are as follows: (h1) determine if activated by the said intervention processor which indicates the aircraft is In the air by means of Air data and said position detecting means; (h2) determine If activated by the authorization codes received from the said Communication means transmitted from the Air Traffic Control or from or an intercepting military aircraft; (h3) Once actvaton Is accepted the hibernation processor performing computer activates comprising: (i) determine If the aircraft Is in the air; the hibernation processor will acquire the fuel state from the arcrafts flight management computer and locate the nearest runway supporting automatic landing capabilities for the aircraft type based on the fuel remaining; (II) determine if the aircraft is on the ground at an airport the hibernation processor will close the throttle and immoblse the aircraft by means of internal fly-by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot Input or auto throttle input; d (h4) monitor the weather by means of information from the weather satellites and then generate an emergency flight plan; (h5) The said emergency flight plan is constructed by means of information from the onboard Navigation database comprising the following Information: (n1) Airways, (n2) Airports, (n3) Runways, (n4) Routes, (n5) SID, (n6) STARS; (h6) Transmit the emergency flight plan by said Communication means to Air Traffic Control (h7) Execute the emergency flight plan by means of internal fly-by-wire control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle Input and monitor any flight plan updates or modification from Air Traffic Control or intercepting military aircraft; (he) Execute a fully automatic landing by means of internal fly-by-wre control computers coupled to Actuator Control System (ACS) isolated from pilot input or autopilot or auto throttle input then immobilize the aircraft when safe to do so;
2. A system according to claim 1, in which onboard fully automatic landing means is provided by Instruments landing System(lLS) or Microwave Landing System(MLS)
3. A system according to claim 1, In which onboard position detecting means is provided by Inertia Navigation System (INS) or Global Positioning System (GPS) or Instrument Landing System (ILS) or Microwave Landing System (NILS) or Omni directional Radio Range (VOR) or Distance Measuring Equipment (DEE)
4. A system according to claim 1, in which Air Data means is provided by Inertial Reference System (IRS) or Air Data Computer (ADC) or Air Data and Inertial Reference System (ADIRS)
5. A system according to claim 1, in which Infrastructure Database (ID) means is provided by Infrastructure Global Position Data (IGPD) or Infrastructure Distance Measuring Equipment (IDME) or Infrastructure Non Directional Beacon (INDB)
6. A system according to claim 1, in which Communication means is provided by at least one Satellite Communications (SATCOM) or Aircraft Transponder and Air Traffic Control (ATC) or Aircraft Communications And Reporting System(ACARS)
7. A system according to claim 6, in which said Satellite Communications (SATCOM) is provided by at least one International Maritime Satellite Organisation (INMARSAT)
8. A system according to claim 1, in which said system intervention processor and system hibernation processor computing activity is provided by at least one processor or microprocessor or microcomputer or microcontroller
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0415226A GB2415943A (en) | 2004-07-07 | 2004-07-07 | Aircraft-infrastructure collision intervention system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB0415226A GB2415943A (en) | 2004-07-07 | 2004-07-07 | Aircraft-infrastructure collision intervention system |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB2415943A8 GB2415943A8 (en) | |
| GB0415226D0 GB0415226D0 (en) | 2004-08-11 |
| GB2415943A true GB2415943A (en) | 2006-01-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB0415226A Withdrawn GB2415943A (en) | 2004-07-07 | 2004-07-07 | Aircraft-infrastructure collision intervention system |
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| Country | Link |
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| GB (1) | GB2415943A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110213513A1 (en) * | 2007-09-20 | 2011-09-01 | Michael Naderhirn | Method for automatic avoidance of collisions between a craft and further objects |
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| GB2379035A (en) * | 2001-09-20 | 2003-02-26 | Matthew Emmerson Allen | Aircraft control system for avoiding predetermined geographical boundaries |
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| WO2004025600A1 (en) * | 2002-09-12 | 2004-03-25 | The Boeing Company | Automatic control system for aircraft |
| GB2405847A (en) * | 2003-08-30 | 2005-03-16 | Eads Deutschland Gmbh | Low altitude flight system |
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2004
- 2004-07-07 GB GB0415226A patent/GB2415943A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5867804A (en) * | 1993-09-07 | 1999-02-02 | Harold R. Pilley | Method and system for the control and management of a three dimensional space envelope |
| US5892462A (en) * | 1995-06-20 | 1999-04-06 | Honeywell Inc. | Adaptive ground collision avoidance system |
| GB2379035A (en) * | 2001-09-20 | 2003-02-26 | Matthew Emmerson Allen | Aircraft control system for avoiding predetermined geographical boundaries |
| US20030055540A1 (en) * | 2001-09-20 | 2003-03-20 | Hansen James K. | Anti-terrorism aircraft flight control system |
| WO2004025600A1 (en) * | 2002-09-12 | 2004-03-25 | The Boeing Company | Automatic control system for aircraft |
| GB2405847A (en) * | 2003-08-30 | 2005-03-16 | Eads Deutschland Gmbh | Low altitude flight system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110213513A1 (en) * | 2007-09-20 | 2011-09-01 | Michael Naderhirn | Method for automatic avoidance of collisions between a craft and further objects |
| US8467953B2 (en) * | 2007-09-20 | 2013-06-18 | Michael Naderhirn | Method for automatic avoidance of collisions between a craft and further objects |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2415943A8 (en) | |
| GB0415226D0 (en) | 2004-08-11 |
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| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |