EP2143095A2 - Système de navigation aérienne pour l'aviation comportant une station au sol, destiné à remédier de manière automatique aux perturbations de service qui se produisent pour des avions, ainsi que procédé correspondant - Google Patents

Système de navigation aérienne pour l'aviation comportant une station au sol, destiné à remédier de manière automatique aux perturbations de service qui se produisent pour des avions, ainsi que procédé correspondant

Info

Publication number
EP2143095A2
EP2143095A2 EP08707264A EP08707264A EP2143095A2 EP 2143095 A2 EP2143095 A2 EP 2143095A2 EP 08707264 A EP08707264 A EP 08707264A EP 08707264 A EP08707264 A EP 08707264A EP 2143095 A2 EP2143095 A2 EP 2143095A2
Authority
EP
European Patent Office
Prior art keywords
ground station
aircraft
avionics
parameters
activation
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08707264A
Other languages
German (de)
English (en)
Other versions
EP2143095B1 (fr
Inventor
Marcel Fok
Shinji Shirai
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Swiss Re AG
Original Assignee
Swiss Reinsurance Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from PCT/EP2007/050708 external-priority patent/WO2007088133A2/fr
Application filed by Swiss Reinsurance Co Ltd filed Critical Swiss Reinsurance Co Ltd
Priority to EP20080707264 priority Critical patent/EP2143095B1/fr
Priority to US12/524,389 priority patent/US8244414B2/en
Priority to AT08707264T priority patent/ATE533142T1/de
Priority claimed from PCT/EP2008/000553 external-priority patent/WO2008089988A2/fr
Publication of EP2143095A2 publication Critical patent/EP2143095A2/fr
Application granted granted Critical
Publication of EP2143095B1 publication Critical patent/EP2143095B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • G—PHYSICS
    • G08—SIGNALLING
    • G08G—TRAFFIC CONTROL SYSTEMS
    • G08G5/00—Traffic control systems for aircraft
    • G08G5/50—Navigation or guidance aids
    • G08G5/56—Navigation or guidance aids for two or more aircraft

Definitions

  • the invention relates to an avionic aviation system with ground station for the automatic correction of occurring malfunctions in aircraft.
  • the avionic aviation system is connected to a variety of aircraft via a wireless avionics interface.
  • a switching device of the ground station of the aviation system dedicated malfunction use device for automatic malfunction rectification is activated if a malfunction detected by a sensor occurs in an aircraft.
  • the behavior of the operator can be taken into account.
  • One of the drawbacks of these systems is that the turnover only reflects the current and immediately following future and technically allows only very indirect breakdown of causes of breakdowns. In addition, technically there is rarely a direct dependency between the turnover and the malfunctions that occur.
  • Some prior art systems are also based on the number of aircraft in service, which is taken as a marginal parameter of the type and technical possibilities for realizing an automated flight system for the purpose of repairing malfunctions. These systems may better reflect the occurrence of malfunction.
  • not all operators of aircraft need to use the same technical equipment, technical know-how, maintenance of the machines, bases, etc., let alone use the same for all aircraft operated.
  • rens is based on the difficulty of extrapolating breakdowns and their expected values for future malfunctions. This is u.a. in the complexity and non-linearity of the external influences on the operation of the aircraft.
  • Efficient and reliable early warning signal generation and automated troubleshooting can therefore be vital to aircraft survival.
  • Efficient malfunction correction includes complex technical subdevices of the aircraft as well as the many thousand sensors and measuring signals, or monitoring and control systems based on difficult-to-control environmental influences such as meteorological (storms, hurricanes, floods, termions) influences. Automation of troubleshooting should be able to take into account all these influences without affecting the reaction speed of troubleshooting. Such systems are not known in the prior art.
  • EP-A-563616 shows a system of the prior art, with which operating data of an aircraft can be collected and transmitted to a ground station via means of communication of the on-board system.
  • European patent specification EP 1 455 313 shows another system of the prior art in which flight and operating parameters can be monitored with a so-called Aircraft Condition Analysis and Management System (ACAMS) and any occurring or expected malfunctions can be detected.
  • European Patent EP 1 630 763 A1 shows another monitoring and control system. The purpose of this system is to detect any malfunctions based on the transmitted measurement parameters. be avoided.
  • the alarm device shown here is based in particular on predicted by the system, projected trajectories de monitored aircraft. In case of impending malfunctions, a corresponding alarm signal is automatically generated.
  • the solution should make it possible to provide a fully automated, electronic aviation system which reacts dynamically to changed conditions and interruptions in operation and / or adapts itself.
  • it should be a solution that allows to design the avionic aviation system such that changeable causality and dependency of the operational disturbances (eg location of use, type of use, operation of the aircraft, external influences such as weather, landing base, etc.) with the necessary accuracy of the aviation system are considered and integrated in the technical implementation so that human interaction is not necessary.
  • the avionic aviation system is connected to ground station for automatically remedying incidents occurring in aircraft with a plurality of aircraft via a wireless avionics interface of the aircraft, dedicated anti-malfunctioning apparatus for automatically malfunctioning by means of a scan of the aircraft Ground station are activated, if an operating fault detected by means of a sensor occurs, that the aviation system comprises in the avionics of the aircraft integrated detection devices for electronically detecting executed takeoff and / or landing units of the aircraft, wherein logging parameters assigned to an aircraft for takeoff and landing are carried out Starting and / or landing units is transmitted from the detection devices via the wireless interface to the ground station that the ground station for each Flu tool stack includes an incrementable Techlog stack with readable stack height value, wherein the Techlog stack height value is increased by means of a counter module based on filtered start and / or landing units of the transmitted log parameters of the respective aircraft after transmission of the parameters that the counter module comprises means for reading the Techlog stack height value and the ground station comprises a filter module, by means of a
  • the associated log parameters can be transmitted directly to the ground station, for example, via the wireless interface of the avionics of the aircraft via a satellite-based network. However, the associated log parameters can also be transmitted to the ground station via the wireless interface of the avionics (on-board system) of the aircraft via a wireless communication network of a served landing base, for example.
  • the detection devices can be completely integrated into the avionics of the aircraft.
  • the landing bases can also comprise at least parts of the detection device, for example.
  • the detection device can be realized, for example, at least partially as part of a control system of a landing base, eg an airport or airfield.
  • the detection device can also be partially realized, for example, as part of a control system of an air service provider and / or flight operations provider.
  • This has the advantage that with the avionics of the aircraft no further technical adaptations or realizations are necessary, than already existing.
  • the detection device can be implemented at any possible flight / landing base or the cycles can be recorded elsewhere and transmitted to the aviation system.
  • the invention has the advantage, inter alia, that by means of the device according to the invention a uniform, avionics aviation system with ground station which can be technically integrated into the existing electronics of the aircraft (avionics) can be implemented for the automatic repair of occurring malfunctions in aircraft. Until now, this was not possible in the state of the art, since the automations without human interaction often had unpredictable instabilities.
  • the activation parameters are determined variably by means of the filter module based on the detected number of takeoff and / or landing units.
  • the ground station is thus dynamically signaled by the aircraft and the aircraft it is carrying.
  • base-specific data of the assigned landing / take-off base for aircraft such as air freight transport means and / or passenger air transport means, can be dynamically detected.
  • the aircraft assigned to the aviation system have detection devices with an interface to the ground station and / or landing base and / or satellite-based network.
  • the interface to the ground station can be realized, for example, by means of an air interface.
  • This embodiment variant has the advantage, among other things, that the aviation system allows real-time acquisition of the cycles (take-off / landing). This also results in the possibility of a dynamic adaptation of the operation of the aviation system in real-time to the current conditions and / or in particular a corresponding real-time
  • the malfunction use means are selected by means of the filter module when detecting a malfunction by means of the sensor system of the aviation system in accordance with the malfunction and / or the aircraft type concerned and activated by means of the switching device.
  • This embodiment variant has the advantage that, in order to remedy the occurring malfunction by means of the filter module, the activated malfunctioning means of use are specifically selected and adapted to the resulting malfunction and / or location of the malfunction can.
  • the filter module may comprise correspondingly implemented expert systems, neural network modules.
  • the filtering and selection can be realized, for example, by means of adapted lookup tables. This allows an automation of aviation systems based on the inventive system, as it was not nearly possible in the prior art until now.
  • the malfunction application means are additionally selectable by means of the filter module based on the activation stack storage altitude value and selectively activated by means of the switching device.
  • This variant has u.a. the advantage that the aviation system can respond dynamically to the transmitted activation parameters.
  • the memory threshold and the cumulative activation parameters need not necessarily be identical. This allows e.g. by means of the filter module, a dynamic adaptation of the selected Radiostorungs Ranvor- directions based on the transmitted activation parameters.
  • the log parameters additionally include measured value parameters of the flight management system (FMS) and / or the inertial navigation device (INS) and / or the fly-by-wire sensors and / or flight monitoring devices of the aircraft, wherein the memory threshold value is dynamically determined by means of the filter module for the particular time window based on the Techlog stack height value and the additional log parameter.
  • FMS flight management system
  • INS inertial navigation device
  • the memory threshold value is dynamically determined by means of the filter module for the particular time window based on the Techlog stack height value and the additional log parameter.
  • Variant has u.a. the advantage that e.g. the aviation system can be adjusted dynamically and in real-time using the additional log parameters.
  • the activation parameters and / or the memory threshold value can be adapted dynamically by means of the filter module by means of the additional log parameters to the type and probability of a malfunction.
  • the avionics of the aircraft comprises a height sensors and / or a tachometer and / or a variometer and / or a horizon gyro and / or a turning pointer and / or an accelerometer and / or a Questionziehwamsensorik and / or an outdoor temperature sensor and / or a location determining device, wherein the
  • Log parameters additionally comprise measurement parameters of at least one of the sensors and wherein the memory threshold is dynamically generated by the filter module for the respective time window based on the Techlog stack height value and the additional log parameters.
  • the memory threshold is dynamically generated by the filter module for the respective time window based on the Techlog stack height value and the additional log parameters.
  • the location detection module of the detection device eg location coordinate parameters of the current location of the aircraft can be generated and transmitted to the ground station for triggering the intervention to remedy a malfunction by means of the dedicated selected operation disturbance deployment devices.
  • the malfunction of the aircraft can be automated or at least semi-automatically remedied.
  • the operating disturbance use devices such as automated extinguishing devices, Aiarrnvor ⁇ chfungeri aids or intervention units, such as police orhomuniseren, automated closing or Ab- / switching units, etc. automated and / or real-time based optimized and / or activated at the current location of the aircraft.
  • the malfunctioning deployment device may also include additional monetary value-based transmission modules in addition to automated direct intervention devices. Since, for example, location coordinate parameters of the current location of the aircraft can be generated by means of the location detection module of the detection device and transmitted to the ground station, the activation parameters and / or the memory threshold value can be dynamically adapted to the probabilities of the occurrence of a malfunction, for example by means of the filter module. For example, difficult landing bases, such as Honkong, may be assigned higher activation parameters or memory thresholds, while high security landing sites, such as Frankfurt or Zurich, may have smaller values for the activation parameters and / or the memory threshold. The behavior and the environmental influences are thus fully and dynamically taken into account during the operation of the aircraft. This was not possible in the prior art so far. The same applies to detected measuring parameters of the height-measuring sensor, the tachometer, the variometer, the horizon gyro, the turning pointer, the accelerometer, the stall warning sensor system or the outside temperature sensor system of the aircraft.
  • ATIS measurement parameters based on the automatic terminal information service (ATIS) of the approached landing base are generated by means of the avionics of the aircraft or the means of communication of the landing base at each Landing and starting unit is automatically transmitted to the ground station, wherein the memory threshold is determined dynamically for the respective time window based on the Techlog stack height value and dynamically adjusted by means of the ATIS measurement parameters.
  • the aviation system can be adapted dynamically and in real-time based on the ATIS measurement parameters.
  • the activation parameters and / or the memory threshold can be adapted dynamically by means of the ATIS measurement parameters to the type and probabilities of a malfunction.
  • the filter module of the filter module of the filter module
  • Ground station dynamically transmit certain first activation parameters on the avionics of the aircraft and / or on a respective aircraft associated réellesbord- systern, and generated for incrementing the Aktivieru ⁇ gsstapelsers protected second activation parameters of the avionics or the associated supplementary onboard system and transmitted to the ground station.
  • the protected second activation parameters may e.g. an uniquely identifiable identification number or other electronic identification (ID), such as a. include an IMSI.
  • ID electronic identification
  • This variant has u.a. the advantage that the second activation parameters and the first activation parameters need not be identical. This allows e.g. a dynamic see adaptation of the selected operation failure use devices based on the second activation parameters by means of the filter module.
  • the activation parameters can be determined, in particular, e.g. also easily communicate over networks or by decentralized systems edit.
  • the ground station comprises an interface for accessing one or more databases with land-base-specific data records, each start and / or landing unit detected by the detection apparatus being recorded as a log parameter being assigned to at least one land-base-specific data record and the log parameters being determined by means of a weighting module weighted and / or weighted generated according to the associated landing-base-specific data record.
  • the aviation system may additionally include means for dynamically updating the one or more databases of landing-site-specific data records, wherein the updating of the landing-site-specific data records may be implemented periodically and / or on request.
  • the one or more databases may be decentralized to a landing pad for aircraft be assigned, being transmitted by means of an interface data unidirectional and / or bidirectional to the ground station.
  • This variant has, inter alia, the same advantages as the previous Ausf ⁇ hrungssection.
  • a real-time adaptation of the aviation system for example with regard to the technical conditions in the used landing sites, becomes possible. This always allows the aviation system to be kept up-to-date automatically. This may be particularly important when considering new developments and implementations of technical systems for increasing safety, etc. in the cycles.
  • the realization of the databases has the advantage that by means of a filter module or suitable decentralized filter means, data, such as metadata, can be generated from acquired data and can be updated dynamically. This allows quick and easy access. In the case of a local database at the ground station with periodic updating, for example, the air gap mystery can continue to function dynamically even if the connections are interrupted in the interim to individual landing bases.
  • an electrical clock signal with a reference frequency is generated by means of an integrated oscillator of the filter module, based on the clock signal, the filter module periodically determine the variable activation parameters and / or optionally transferred to the corresponding incremental incrementable stack.
  • the present invention relates not only to the aviation system with ground station according to the invention but also to a corresponding method.
  • FIG. 1 shows a block diagram, which schematically represents an exemplary embodiment of an avionic aviation system 80 according to the invention with ground station 81 for the automatic correction of occurring malfunctions in aircraft 40/41/42.
  • the avionics aviation system 80 is connected to a plurality of aircraft 40/41/42 via a wireless interface 403 of the avionics 402.
  • a skipping device 1 of the ground station 81 dedicated malfunction use device 603 for automatic malfunction elimination is activated if a malfunction detected by means of a sensor system 3/401 / 601 occurs.
  • a filter module 2 changes the control of the switching device 1.
  • FIG. 2 likewise shows a block diagram, which schematically represents an exemplary embodiment of an avionic aviation system 80 according to the invention with ground station 81 for the automatic correction of occurring malfunctions in aircraft 40/41/42.
  • the avionic aviation system 80 is connected to a plurality of aircraft 40/41/42 via a wireless interface 403 of the avionics 402.
  • a switching device 1 of the ground station 81 dedicated malfunctioning use device 603 is activated for automatic malfunction correction if a malfunction due to S ⁇ nso ⁇ k 3/401 / 60 I occurs.
  • Figures 1 and 2 illustrate an architecture that may be used to implement the invention.
  • the avionics aviation system 80 is connected to ground station 81 for automatic repair of incidents occurring in aircraft 40/41/42 with a plurality of aircraft 40/41/42 via a wireless interface 403 of the avionics 402 of the aircraft 40,41, 42 is.
  • the aviation system 80 with ground station 81 may be, for example, as part of a technical system of an operator of aircraft 40,..., 42, such as an airline or air cargo / air freight carrier, but also of a manufacturer of aircraft such as Airbus or Boeing or air traffic control services.
  • the aircraft may, for example, include airplanes for goods transport 40/41 and / or passenger transport 42 and / or airships such as zeppelins or even shuttles or other means of space flight.
  • the aircraft 40 42 may also include motorized and non-motorized means of transport, in particular sailors, motor gliders, Delta sailors, among others.
  • dedicated malfunctioning use device 603 for automatic malfunction elimination is activated by means of a switching device 1 of ground station 81 if a malfunction detected by means of a sensor system 3/401 / 601 occurs.
  • the ground station 81 and / or the malfunctioning utilization devices 603 may partially comprise, for example, automated emergency and alarm devices with monetary value-based transmission modules.
  • the sensor system 3/401 / 601 may be at least partially integrated to detect malfunction in the avionics 402 of the aircraft 40, ..., 42, the control device of the malfunction correction devices 603 and / or the ground station 81 and / or landing base 1 1.
  • the malfunctioning device 603 may be, for example, control, alarm or direct technical intervention systems on the affected aircraft 40,..., 42, the operator of the aircraft 40, and / or the ground base 1 1 and / or the ground station 81 is affected when detecting appropriate malfunctions.
  • several aircraft 40 42, ground stations 81 and / or landing bases 1 1 may be affected simultaneously or detected by the aviation system.
  • the malfunction correction can be done, for example, by coupled and / or graduated technical interventions, such as triggering different control services or throttling and dosing filters with appropriate dosing devices or valves, etc.
  • malfunction correction devices 603 are possible, which are activated by the flight system 80, for example in the sense of automated or partially automated emergency interventions (or their triggering) of medically trained personnel or automated triggering of flight-related emergency situations such as ambulance services, etc., which are alerted by selectively transmitted signal data generated by the fuselage system 80.
  • Operational disturbance correction devices 603 can be used, for example, to control the devices 603 by means of the aviation system 80 for automated troubleshooting in the event of malfunctions by means of an interface unidirectionally or bidirectionally with the aircraft 40,..., 42 and / or the ground station 81 and / or the landing base 11 be connected.
  • the reference number 60 describes the intervention device as a whole, comprising the communication interface 601 with possibly sensor failure measurement, the control device 602 for electronically monitoring and controlling the operation failure use device 603, and the operation failure use device 603
  • the malfunctioning means 603 e.g. according to the malfunction and / or type of aircraft affected
  • the aviation system 80 comprises detection devices 41 integrated in the avionics 402 of the aircraft 40/41/42.
  • the take-off and / or landing units of an aircraft 40/41/42 are detected electronically by means of the detection devices 41 1, corresponding aircraft 40 42 associated log parameters of the executed start and / or
  • Landing units are transmitted from the detection devices 41 1 via the wireless interface 403 to the ground station 81.
  • the log parameters may, for example, at least partially be recorded in the form of absolute value parameters.
  • the wireless interface 403 of the avionics 402 of the aircraft 40,..., 42 for example, the associated log parameters can be transmitted via a satellite-based network 70 directly to the ground station 81 be transgressed.
  • the assigned logging meters can also be transmitted to the ground station 81, for example, via a wireless communications network 11 of a land base 11 which has arrived.
  • the ground station 81 comprises for each aircraft 40 42 an incrementable Techlog stack 202 with readable stack memory height value.
  • the techlog stack height value is incremented by means of a counter module 203 of the ground station 81 based on filtered start and / or landing units of the transmitted log parameters of the respective aircraft 40, 42.
  • the counter module 203 also includes means for reading out the techlog stack height value.
  • a filter module 2 of the ground station 81 a memory threshold for enabling the activation of the malfunction inserter 603 is determined dynamically for a particular time window based on the Techlog stack height value.
  • the ground station 81 comprises an activation stack 102 of a protected memory module 103, by means of which activation parameters of the aircraft 40 42 are detected.
  • the activation parameters are transmitted to the ground station 81 based on the current memory threshold, and the activation stack 102 is incremented in accordance with the transmitted activation parameters.
  • the activation parameters may include, as a special case, at least partially monetary and / or monetary value-based amounts, in particular electronically protected parameters.
  • first activation parameters can be dynamically determined, for example, by means of the filter module 2 of the base station 81 and can be assigned to the avionics (402) of the aircraft 40,..., 42 and / or to a respective aircraft 40, Supplementary board system 404.
  • protected second activation parameters are generated by the avionics 402 or the associated supplementary off-board system 404 and transmitted to the ground station 81.
  • the protected second activation parameters may include, for example, a unique identification number.
  • the activation stack memory height value of the activation stack 102 is cumulatively detected. The detection can take place, for example, periodically and / or on request and / or upon transmission. If the dynamically determined memory threshold value is reached with the activation stack memory altitude value, the switching module 1 is activated by means of the filter module 2 for dedicated activation of the malfunctioning means 603 in the event of malfunctions occurring.
  • variable activation parameter or memory threshold value is determined periodically by means of the filter module 2 based on the detected number of start and / or landing units or the log parameters, for example, and returned to the Bodenst ⁇ tion 81 is transferable to the activation stack storage 102.
  • the filter module 2 and / or the counter modules 103/203 may comprise an integrated oscillator, by means of which oscillator, an electrical clock signal with a reference frequency can be generated, based on the clock signal, the filter module 2 and / or the counter modules 103/203 are periodically activated .
  • the variable activation parameter and / or activation stack memory can be determined dynamically or partially dynamically, for example, by means of the filter module 2 based on the detected number of start and / or landing units.
  • the malfunction use devices 603 can additionally be selected by means of the filter module 2 based on the activation stack storage height value and activated by means of the switching device 1.
  • the log parameters may include additional measured value parameters of the flight management system (FMS) and / or the inertial navigation device (INS) and / or the fly-by-wire sensors and / or flight suppression devices of the aircraft 4u,..., 42, wherein the memory threshold value by means of the filter module 2 dynamically for the respective time window based on the Techlog stack height value and the additional
  • the avionics 402 of the aircraft 40 42 can also include, for example, a height-measuring sensor system and / or a tachometer and / or a variometer and / or a horizon gyro and / or a turning pointer and / or an accelerometer and / or a stall warning sensor system and / or an outside temperature sensor.
  • sensor and / or a location determining device include, for example, at least one GPS module for generating location-dependent transmissible parameters.
  • the log parameters additionally comprise measurement parameters of at least one of the sensors, the memory threshold being generated by the filter module 2 dynamically for the respective time window based on the techlog stack height value and the additional log parameters.
  • the avionics 402 of the aircraft 40 42 or the communication means 1 1 1 of the landing base 1 for example, ATIS measurement parameters based on the Automatic Terminal Information Service (ATIS) of the approached landing base 1 1 at each landing and starting unit (Cycle ) are automatically transferred to ground station 81, wherein the memory threshold is dynamically generated for the respective time window based on the Techlog stack height value and the transmitted ATIS measurement parameters.
  • the detection device 41 1 comprises measuring sensors for dynamically or partially dynamically detecting start and / or landing units.
  • the detection device 41 1 can describe, as for the avionics 403, for example a height-measuring sensor system and / or a tachometer and / or a variometer and / or a a horizon gyro and / or a turning pointer and / or an accelerometer and / or a Questionziehw ⁇ msensorik and / or an outdoor temperature sensors and / or a location determining device.
  • the detection device 41 1 can also include, for example, sensors and / or detection means for the dynamic detection of land-based data of the assigned LandVStartbasis for air transport means 40/41 and / or Wegbe circumstancessstoff 42.
  • the associated air transport means 40/41 and / or passenger air transport means 42 may comprise, for example, the detection device 41 1 with an interface to the filter module 2 and / or to the user device 11.
  • the mentioned interface from the detection device 41 1 to the filter module 2 and / or to the user device 1 1 may comprise, for example, an air interface.
  • the detection device 41 1 may include, for example, a location determination module for generating location-dependent transmissible parameters.
  • the location determination module of the detection device 41 1 can, for example, comprise at least one GPo module for generating location-dependent overriding parameters.
  • ground station 81 may include an interface for accessing one or more databases of landing-site-specific data records.
  • Each start and / or landing unit (cycle) detected by the detection device 41 1 and recorded as a log parameter is assigned at least one land base-specific data record, the log parameters being weighted by means of a weighting module based on the associated land-base-specific data record.
  • the aviation system 80 may further include means for dynamically updating the one or more databases of landing-site-specific data records. The updating of the landing-site-specific data records can be realized, for example, periodically and / or on request.
  • the one or more databases may, for example, be decentralized to a landing base 1 1 for aircraft 40,..., 42.
  • an interface 1 1 for example, data from the landing base 1 1 unidirectional and / or bidirectional to the ground station 81 can be transmitted.
  • the landing and / or start unit specific data records and / or data can be recorded by accessing databases of state and / or partially state and / or private control bodies and / or other databases of start and landing bases.
  • the acquired data can be stored, for example, allocated in a data memory and, for example, can be updated periodically and / or on request.
  • This embodiment variant can take account of different, for example, country-specific conditions, such as technical and maintenance differences, for example between an airport such as Frankfurt, Hong Kong (difficult landing conditions).
  • the aviation system 80 may also include the aforementioned one or more databases.
  • suitable filter means data such as metadata
  • generated data can be generated and updated dynamically. This allows quick and easy access.
  • the automated alarm and intervention system can continue to function even if the connections to user devices and / or capture units are disrupted.
  • the data can, as mentioned, in particular also include metadata, which are extracted, for example, using a content-based indexing technique.
  • the metadata can be generated at least partially dynamically (in real time) based on the log parameters transmitted by the detection devices 41 1. This has the advantage, for example, that the metadata always have the relevance and accuracy that is meaningful for the system according to the invention.
  • the perturbation utility devices 603 may additionally include petty-based interventional funds to monetarily cover the malfunction remediation of the aircraft 40. For the special case of these service malfunction devices
  • the avionic aviation system 80 may, as mentioned, comprise a plurality of loading bases 1 1 or / or ground stations 81 with aircraft 40 42.
  • the aircraft 40 42 and / or the landing base 1 1 may be connected to the ground station 81, for example via the communication network 50/51 and / or the satellite-based network 70 unidirectional and / or bidirectional.
  • the communication network 50/51 and / or the satellite-based network 70 may, for example, be a GSM or a UMTS network, or a satellite-based mobile network, and / or one or more fixed networks, for example the public switched telephone network, the worldwide Internet or a suitable LAN ( Local Area Network) or WAN (Wide Area Network). In particular, it also includes ISDN and XDSL connections.
  • the communications network 50/51/70 can also include broadcast systems (eg Digital Audio Broadcasting DAB or Digital Video Broadcasting) in which broadcasting stations digital audio or video Programs (television programs) and digital data, for example data for the execution of data services, program-associated data (program-associated data, PAD) to broadcast receivers unidirectional spread.
  • broadcast systems eg Digital Audio Broadcasting DAB or Digital Video Broadcasting
  • the unidirectional dissemination property of these broadcast systems may have the disadvantage, inter alia, that, in particular in the case of transmission by means of radio waves, a back channel is missing from the broadcast receivers to the broadcast transmitters, or to their operators. Due to this missing return channel, the possibilities for encryption, data security, billing, etc. of access-controlled programs and / or data are more limited.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Traffic Control Systems (AREA)
  • Transmitters (AREA)
  • Radio Relay Systems (AREA)

Abstract

L'invention concerne un système de navigation aérienne (80) pour l'aviation et un procédé correspondant comprenant une station au sol (81) destiné à remédier de manière automatique aux perturbations de service qui se produisent pour des avions (40/41/42). Le système de navigation aérienne (80) pour l'aviation est relié avec une pluralité d'avions (40/41/42) par intermédiaire d'une interface sans fil (402) de l'avionique (403). Au cas où une perturbation de service pour un avion (40,..., 42) est détecté grâce à un système de capteurs (3/401/601), un dispositif d'insertion de perturbation de service (603) dédié destiné à remédier de manière automatique à une perturbation de service est sélectionné grâce à un module de filtrage (2) et un dispositif de commutation (1) de la station au sol (81) est déclenché de manière spécifique en vue de l'activation du dispositif d'insertion de perturbation de service (603).
EP20080707264 2007-01-24 2008-01-24 Système de navigation aérienne pour l'aviation comportant une station au sol, destiné à remédier de manière automatique aux perturbations de service qui se produisent pour des avions, ainsi que procédé correspondant Active EP2143095B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP20080707264 EP2143095B1 (fr) 2007-01-24 2008-01-24 Système de navigation aérienne pour l'aviation comportant une station au sol, destiné à remédier de manière automatique aux perturbations de service qui se produisent pour des avions, ainsi que procédé correspondant
US12/524,389 US8244414B2 (en) 2007-01-24 2008-01-24 Avionic aviation system with an earth station for automatically eliminating operating malfunctions occurring in airplanes, and corresponding method
AT08707264T ATE533142T1 (de) 2007-01-24 2008-01-24 Avionisches luftfahrtsystem mit bodenstation zur automatischen behebung von auftretenden betriebsstörungen bei flugzeugen, sowie entsprechendes verfahren

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
PCT/EP2007/050708 WO2007088133A2 (fr) 2006-02-02 2007-01-24 Dispositif dynamique de contrôle et de déclenchement destiné à activer des systèmes d'intervention automatisés dans des moyens de transport aérien et/ou des moyens de transport aérien de passagers et procédé correspondant
EP20080707264 EP2143095B1 (fr) 2007-01-24 2008-01-24 Système de navigation aérienne pour l'aviation comportant une station au sol, destiné à remédier de manière automatique aux perturbations de service qui se produisent pour des avions, ainsi que procédé correspondant
PCT/EP2008/000553 WO2008089988A2 (fr) 2007-01-24 2008-01-24 Système de navigation aérienne pour l'aviation comportant une station au sol, destiné à remédier de manière automatique aux perturbations de service qui se produisent pour des avions, ainsi que procédé correspondant

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EP2143095A2 true EP2143095A2 (fr) 2010-01-13
EP2143095B1 EP2143095B1 (fr) 2011-11-09

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ATE533142T1 (de) 2011-11-15
US20100036545A1 (en) 2010-02-11
EP2143095B1 (fr) 2011-11-09
US8244414B2 (en) 2012-08-14

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