WO2002014972A2 - Systeme de maintenance pour un ensemble d'equipements - Google Patents
Systeme de maintenance pour un ensemble d'equipements Download PDFInfo
- Publication number
- WO2002014972A2 WO2002014972A2 PCT/FR2001/002569 FR0102569W WO0214972A2 WO 2002014972 A2 WO2002014972 A2 WO 2002014972A2 FR 0102569 W FR0102569 W FR 0102569W WO 0214972 A2 WO0214972 A2 WO 0214972A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- equipment
- monitoring
- electronic circuits
- central maintenance
- maintenance computer
- Prior art date
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Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/0055—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot with safety arrangements
Definitions
- the present invention relates to the maintenance of a set of equipment, such as all of the avionics equipment of an aircraft which fulfill the various functions necessary for the accomplishment of a flight.
- An aircraft comprises a large number of equipment, of various kinds, mechanical, hydraulic, electrical or electronic, the proper functioning of which is essential during a flight.
- the BITE function of an equipment is assumed by electronics which can be specific or shared with other functions of the equipment in question. This electronics performs the software processing required by the BITE function. It includes a more or less important hardware part integral with the equipment, with, at a minimum, in this hardware part, a non-volatile memory in which are saved the crossing of standards by the monitored parameters, the test results, the diagnostic of failure when it exists as well as the failure messages sent.
- the failure messages of the BITE functions of the monitored equipment of an aircraft are sent, by an aircraft data transmission link, to a centralizing equipment placed on board the aircraft in order to collect the various failure messages sent.
- fault messages from the BITE functions of the various equipment can be viewed from the cockpit. They are also pretreated, in order to facilitate the task of crews and maintenance personnel, by a specialized central computer known by different names such as CMC from the English expression “Central Maintenance Computer” or CFDIU of the Anglo-Saxon expression “Centralized Fault Display Interface Unit ".
- This central maintenance computer is accessible to the crew by a keyboard and screen interface which can be that known by the abbreviation MCDU taken from the English expression of" Multipurpose Control Display Unit "but which can be also a PC-type laptop connected by a disconnectable data link, whether or not using the airplane bus. Its main function is to diagnose the general situation of the aircraft in real time or at the end of the flight.
- the BITE function test function exists at each of the two possible levels of standard exchange of parts within an aircraft: LRU equipment level and LRM equipment module level. It is called a BITE resource function when it is interested in a hardware composition (hardware in English) or in the first level software used (such as the operating system) and BITE application function when it s interested in higher level software. It is provided by electronics, a more or less significant part of which follows the fate of the part capable of standard exchange.
- the BITE function can also exist at a third level of assembly grouping together several LRM modules placed in the same cabinet or shelf. It is then called global BITE function and consists of a pre-diagnosis facilitating that of the central maintenance computer.
- the present invention aims to reduce manual intervention in the process of informing a repair station about the reasons and conditions for removing a part of equipment or equipment to be repaired by taking advantage of the presence, at the within the deposited part, a non-volatile memory dedicated to the BITE function of this part, to make this non-volatile memory play a role of storage, not only of the diagnosis of the BITE function of the deposited part, but also of the PFR / LLR "post-flight" report established by the central maintenance computer and, possibly, diagnostics of BITE functions of other assembly levels including that of the part deposited: function
- BITE of the equipment including the part deposited when it is an LRM module and this equipment is also provided at its level with a BITE function, and / or global BITE function when the equipment belonging to the part deposited is grouped with other equipment in a cabinet or shelf provided at its level with a global BITE function.
- NFF abbreviation of the Anglo-Saxon expression "No Fault Found"
- the object of the invention is a maintenance system for a set of equipment comprising:
- - electronic circuits for monitoring the proper functioning of each item of equipment each provided with means for developing proper functioning tests and for issuing fault messages in the event of failure of the tests, as well as a non-volatile memory integral with the equipment monitored, - a central maintenance computer in relation to said electronic circuits for monitoring correct operation, provided with means for diagnosing the operating state of the set of equipment, operating on the basis of the fault messages of said equipment electronic monitoring circuits of good operation and drawing up a report on the overall operating state of the set of equipment, - one or more data transmission links connecting said electronic circuits for monitoring correct operation to the central maintenance computer, said maintenance system for a set of equipment being characterized in that the central computer comprises means for making available its report on the overall operating state of the set of equipment on the data transmission link or links connecting it to the electronic circuits for monitoring correct operation and in that the electronic circuits for monitoring correct operation include means for detecting, capturing and transferring into their non-volatile memories integral with the equipment, the report on the overall operating state of the assembly of equipment developed by the central maintenance computer when
- the electronic circuits for monitoring the proper functioning of this equipment are also provided with means for detecting, capturing and transferring in their non-volatile memories integral with the equipment, fault messages sent by the electronic circuit (s) for monitoring the proper functioning of the or sub-assemblies to which the monitored equipment belongs, when these messages pass over the data transmission link or links connecting the monitoring circuits for correct operation to the central maintenance computer.
- the circuits electronic monitoring of the proper functioning of these parts of equipment are also provided with means of detection, capture and transfer in their non-volatile memories integral with the parts of equipment, fault messages sent by the circuit (s) for monitoring proper functioning of the item of equipment to which the monitored parts of equipment belong, when these messages pass over the data transmission link or links connecting the monitoring circuits for correct operation to the central maintenance computer.
- the electronic circuits for monitoring the proper functioning of the parts of this equipment are also provided with means of detection, capture and transfer in their non-volatile memories integral with the parts of equipment, of fault messages sent by the circuit or circuits monitoring the proper functioning of the equipment and equipment subgroup (s) to which the parts of equipment they monitor belong, when these messages pass over the data transmission link (s) connecting the good performance monitoring circuits to the central maintenance computer .
- the circuits electronic devices for monitoring the proper functioning of this equipment are also provided with means of detection, capture and transfer to their non-volatile memories integral with the equipment, fault messages emitted at lower assembly levels by the circuit (s) for monitoring the proper functioning of the component parts of the equipment, when these messages pass over the data transmission link (s) connecting the circuits for monitoring proper functioning to the central computer of maintenance.
- FIG. 1 schematically represents an example of an architecture of a centralized equipment maintenance system for aircraft
- FIG. 2 details an example of electronic circuit for monitoring proper operation according to the invention, intended to be mounted on a piece of equipment or removable equipment whose proper operation is monitored by means of a centralized maintenance system such as in Figure 1.
- the main equipment of a modern aircraft contributing to the completion of the flight such as propulsion engines, engines actuating the rudders and elevator as well as the various flaps, the landing gear, etc., the interfaces of control of these different engines, devices for measuring aerodynamic parameters, heading, altitude, position, speed, autopilot, flight management computer, fuel management computer, radiocommunication devices , etc. are provided with individual monitoring devices for correct operation performing a BITE function, i.e. monitoring the main operating parameters of these devices as well as conducting automatic or semi-automatic tests when necessary and the emission of fault messages when the measured parameters fall outside the authorized value ranges or when the results of a test are not those expected.
- a BITE function i.e. monitoring the main operating parameters of these devices as well as conducting automatic or semi-automatic tests when necessary and the emission of fault messages when the measured parameters fall outside the authorized value ranges or when the results of a test are not those expected.
- Figure 1 shows, schematically, a centralized maintenance system architecture such as can be found in a modern aircraft.
- a set of equipment 1 to 6 geographically dispersed in the airframe of the aircraft and connected to each other, as well as to a central maintenance computer CMC 7, to a keyboard-screen interface MCDU 8 and to a printer 9 , via an aircraft data link 10.
- All equipment 1 to 6 are provided with individual electronic circuits for proper functioning monitoring, assuming a BITE function at their levels. These individual electronic circuits for monitoring correct operation have a hardware part 1a, 2a, 3a, 4a, 5a, 6a integral with the monitored equipment and communicate their fault messages to the central maintenance computer CMC 7 via the aircraft data link 10. Certain equipment, such as equipment 1, 4, 5, 6 are indivisible and only comprises, individually, an electronic circuit for monitoring proper operation ensuring a BITE function at the global level of the equipment itself. This electronic circuit for monitoring correct operation includes a hardware part 1a, 4a, 5a, 6a secured to the equipment being monitored.
- equipment 2 is designed according to a modular architecture, and contains different modules 20, 21, 22, 23 or 30, 31, 32 easily removable and replaceable by standard exchange. These pieces of equipment 2, 3 are then each provided with an electronic circuit for monitoring correct operation ensuring a BITE function at the global level of the equipment, and a set of electronic circuits for monitoring correct operation ensuring individually a BITE function. at the level of their modules.
- the electronic circuits for monitoring correct operation operating at the global level of an item of equipment have a hardware part 2a, 3a integral with the item of equipment or one of its modules when the item of equipment is organized into modules, while the electronic circuits for monitoring proper operation operating at the level of the modules 20, 21, 22, 23, 30, 31, 32 each comprise a hardware part 20a, 21a, 22a, 23a or 30a, 31a, 32a integral with the monitored module.
- All the physical parts of the electronic circuits for monitoring proper operation, integral with equipment modules such as parts 20a, 21a, 22a, 23a or 30a, 31a, 32a, with equipment such as parts - 1a, 2a 3a, 4a, 5a, 6a, or groupings of equipment in a cabinet or shelf, such as part 11a, are connected to the airplane data transmission link 10 which can for example be an ARINC 429, 629 or Ethernet type bus to which are equally connected the central maintenance computer 7, the keyboard-screen interface MCDU 8 and a printer 9.
- the airplane data transmission link 10 which can for example be an ARINC 429, 629 or Ethernet type bus to which are equally connected the central maintenance computer 7, the keyboard-screen interface MCDU 8 and a printer 9.
- the central maintenance computer 7 performs, in real time or at the end of the flight, a diagnosis of the general condition of the aircraft, locates the faulty item or items of equipment causing fault messages reaching it from the various BITE functions assumed by the electronic circuits for monitoring correct operation distributed over equipment modules, items of equipment and groupings of aircraft equipment, signals to the crew or maintenance personnel, the equipment (s) actually failing, backs up in a non-volatile part of its memory, a history of the failure messages received, of the alarms sent to the crew and establishes a "post-flight" PFR / LLR report to the team providing maintenance on the ground of the aircraft, which includes a summary of the pa nne, alarms and general context information (date, time, flight phase, etc.) useful for the interpretation of this information.
- This PFR / LLR "post-flight" report available immediately after landing can be printed by means of the printer 9 installed on board the aircraft, automatically at the end of each flight or on request from an operator making the request, from the keyboard-screen interface MCDU 8 placed in the cockpit of the aircraft. It can also be transmitted to a fleet management center belonging, for example, to the operator operating the aircraft, via an on-board external telecommunications network such as the ACARS network of the Anglo-Saxon "Aircraft Communication Addressing and Reporting System ", using a VHF, UHF or other type of transmission link.
- an on-board external telecommunications network such as the ACARS network of the Anglo-Saxon "Aircraft Communication Addressing and Reporting System ", using a VHF, UHF or other type of transmission link.
- the MCDU screen-keyboard interface 8 which allows an exchange of commands and information between an operator and the central maintenance computer 7, is the interface used elsewhere, and this is its main function, to allow the crew exchange instructions and information with the PA autopilot, the FMS (Flight Management System in English) flight management computer and the fuel management computer. Autopilot, flight management, fuel management and centralized maintenance functions can be assumed by the same computer or by several separate computers often grouped in the same cabinet or shelf.
- This keyboard-screen interface MCDU 8 can, with regard to the dialogue with the central maintenance computer 7, be duplicated or replaced by a portable computer like PC connected to the central maintenance computer 7 by a disconnectable data link using or not the airplane data bus 10.
- the printer 9 is placed in the cockpit in an easily accessible location and connected, by the aircraft data transmission bus 10, to various pieces of equipment, including the central maintenance computer 7.
- the aircraft ground maintenance team When it has carried out a standard exchange of an equipment module or a complete equipment following the indications contained in the PFR / LLR "post-flight" report delivered by the central maintenance computer 7, indications possibly specified by additional functional tests programmed from the screen-keyboard interface MCDU 8, the aircraft ground maintenance team sends the part deposited: module or complete equipment, to a repair station for revision with a note guide explaining the reasons for removal. Arrived at the repair station, the deposited part is subjected to tests to establish a repair diagnosis, repaired and checked before being declared again good for service. In a number of cases, the diagnosis of repair is difficult to establish.
- the operation is facilitated by the fact that the fault messages generated by the electronic circuits for monitoring proper functioning assuming the BITE functions are often available at a time or at another on the aircraft data transmission link 10. If this is not the case, the BITE functions of the upper assembly levels being connected to the central maintenance computer 7 by a specific data transmission link, it suffices to have these BITE functions of higher assembly level perform, by means of an adapted programming, a provision of the history of their fault messages on the aircraft data transmission bus, at each end of flight or on operator intervention.
- FIG. 2 gives a possible example of configuration of the hardware part, which remains integral with the deposited part, of an electronic circuit for monitoring correct operation 40a assuming a BITE function, allowing local storage, at its level, not only of the history of the BITE function of the part but also of the PFR / LLR "post-flight" ratio of the central maintenance computer and possibly, histories of other BITE functions assumed by other electronic circuits of good functioning.
- This material part of the electronic circuit for monitoring proper operation 40a is integral with a part 40, the tribulations of which it follows during installation and removal and which can be, as previously considered, an equipment module (20, 21 , 22, 23, 30, 31, 32 figure 1) or an equipment (1, 2, 3, 4 figure 1).
- It comprises a circuit 400 for bidirectional access to the bus of the aircraft data transmission link 10, a test automaton 401, a clock 402, a circuit 403 for detecting, capturing and transferring messages in transit on the bus.
- the aircraft data transmission link 10 with a first message detection stage 413 and a second message selection stage 423, a non-volatile memory 405 and a circuit. 406 for managing non-volatile memory.
- the circuit 400 for bidirectional access to the bus of the aircraft data link 10 is a specialized circuit found in any equipment connected to a bus of the aircraft data link 10. It interfaces an equipment and the bus of the airplane data transmission link, that is to say on the one hand, the transition, in both directions, between a data organization adapted to an equipment and a data organization adapted to the transmission link of aircraft data and, on the other hand, the passage, in both directions, from a signal conveying data with physical characteristics adapted to an item of equipment, to a signal conveying data with physical characteristics adapted to the bus of the transmission link. It will not be detailed since it is not part of the invention. It suffices to know that it serves as an interface to the bus of the data transmission link for which it provides locally, at the level of an item of equipment, access 400e to the transmission and access 400r to the reception.
- the 401 test controller is connected to elements, sensors, actuators, etc. dispersed within room 40, at the 400e send and receive 400r accesses of the circuit 400 for access to the aircraft data transmission bus 10, to the clock circuit 402 and to the memory management circuit 406. It assumes the BITE function of the part 40. Its connections to sensors and actuators dispersed within the part 40 allow it to monitor operating parameters of the part 40 as well as to carry out tests of good functioning on this part. Its connection to the clock circuit 402 allows it to date its messages and also to carry out tests or measurements with periodicities or at fixed dates.
- the clock circuit 402 can be reset to the time from the central maintenance computer 7 thanks to a connection to the reception access 400r of the circuit 400 for bidirectional access to the bus of the aircraft data transmission link 10. It delivers a time reference to the various elements of the correct operation monitoring circuit 40a.
- the non-volatile memory 405 is, for example, an electrically erasable read only memory called EEPROM (Electrical Erasable / Programable Read-Only Memory in English language).
- EEPROM Electrically erasable read only memory
- the memory management circuit 406 which is associated with the non-volatile memory 405 allows, for example, taking into account the limited capacity of the latter, to use it as a first in - first out type register known by the acronym FIFO (First In First Out in English) so as to always have in memory the most recent part of the history.
- FIFO First In First Out in English
- test automaton 401 receives the fault messages sent by the test automaton 401 passing on the transmission access 400e of the bidirectional access circuit 400 to the bus of the aircraft data transmission link 10 as well as the PFR / LLR reports of "post- theft "of the central maintenance computer 7 and the fault messages of other monitoring circuits of good performance assuming BITE functions, available at the output of the circuit 423 for selecting messages and the dates before entering them into the non-volatile memory 405
- the test machine 401 and the clock circuit 402 has a control input connected to the reception access 400r of the circuit 400 for bidirectional access to the bus of the aircraft data transmission link 10 which allows remote control via this bidirectional access circuit 400.
- the first detection stage 413 of the message detection, capture and transfer circuit 403 connected to the reception access 400r of the bidirectional access circuit 400 to the bus of the aircraft data transmission link 10 isolates each message in transit on the bus of the aircraft transmission link while the second stage 423 of the detection, capture and transfer circuit 403 analyzes the labels or "labels" of the messages in transit on the aircraft transmission link 10 which are made available to it by the first stage of detection of messages 413 so as to keep only those sent by the central maintenance computer 7 and belonging to a PFR / LLR "post-flight" report, and fault messages coming from certain electronic circuits for monitoring proper operation assuming BITE functions, duly referenced at the level of the hardware part 40a of electronic circuit for monitoring proper operation.
- the clock circuit 402 and the memory management circuit 406 has a control input connected to the reception access 400r of the circuit 400 for bidirectional access to the bus of the transmission link.
- data plane 10 which allows remote control via this bidirectional access circuit 400, in particular to provide it with the identities of the electronic circuits of monitoring of proper functioning assuming BITE functions, from which it must receive messages.
- the hardware part of the electronic circuit for monitoring proper operation shown in FIG. 2 is sufficient in itself to perform a complete BITE function. There are however cases where it is more advantageous to simplify this hardware part to the point where it can no longer assume, on its own, only a part of the BITE function, the charge of the remaining part of the BITE function being transferred to the central maintenance computer or on a pre-diagnostic computer.
- FIG. 2 the hardware part of the electronic circuit for monitoring correct operation has been shown in FIG. 2, in the form of an assembly of separate boxes dedicated to distinct functions. It should not be concluded, however, that this assembly implies that such boxes necessarily exist in one embodiment, the functions performed by different boxes being able to be by means of one or more microprocessors controlled by software and operating in multitasking.
- the electronic circuits for monitoring proper functioning which have just been proposed to assume the BITE function of a part of removable equipment or piece of equipment, capable of standard exchange, within a centralized computer maintenance system. , allow a repair station to have, from the part deposited itself, a sufficiently complete vision of the progress of the last campaign to use the part for:
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- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
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- Automation & Control Theory (AREA)
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Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP01963071A EP1307804A2 (fr) | 2000-08-11 | 2001-08-07 | Systeme de maintenance pour un ensemble d'equipements |
CA002387327A CA2387327A1 (fr) | 2000-08-11 | 2001-08-07 | Systeme de maintenance pour un ensemble d'equipements |
US10/089,089 US7908052B2 (en) | 2000-08-11 | 2001-08-07 | Maintenance system for an equipment set |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR00/10584 | 2000-08-11 | ||
FR0010584A FR2812958B1 (fr) | 2000-08-11 | 2000-08-11 | Systeme de maintenance pour un ensemble d'equipements |
Publications (2)
Publication Number | Publication Date |
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WO2002014972A2 true WO2002014972A2 (fr) | 2002-02-21 |
WO2002014972A3 WO2002014972A3 (fr) | 2002-04-25 |
Family
ID=8853503
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2001/002569 WO2002014972A2 (fr) | 2000-08-11 | 2001-08-07 | Systeme de maintenance pour un ensemble d'equipements |
Country Status (5)
Country | Link |
---|---|
US (1) | US7908052B2 (fr) |
EP (1) | EP1307804A2 (fr) |
CA (1) | CA2387327A1 (fr) |
FR (1) | FR2812958B1 (fr) |
WO (1) | WO2002014972A2 (fr) |
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US5628349A (en) * | 1995-01-25 | 1997-05-13 | Pinnacle Cng Systems, Llc | System and method for dispensing pressurized gas |
DE69940161D1 (de) * | 1998-06-18 | 2009-02-05 | Kline & Walker L L C | Automatische vorrichtung zur überwachung von auf abstand zu bedienende ausrüstungen und maschinen weltweit anwendbar |
SE512916C2 (sv) * | 1998-07-16 | 2000-06-05 | Ericsson Telefon Ab L M | Metod och anordning för feldetektering i digitalt system |
US6269319B1 (en) * | 1999-01-29 | 2001-07-31 | The Mcdonnell Douglas Corporation | Reconfigurable integration test station |
US7337210B2 (en) * | 2000-01-13 | 2008-02-26 | International Business Machines Corporation | Method and apparatus for determining availability of a user of an instant messaging application |
US6331770B1 (en) * | 2000-04-12 | 2001-12-18 | Advantest Corp. | Application specific event based semiconductor test system |
WO2003029922A2 (fr) * | 2001-10-01 | 2003-04-10 | Kline & Walker, Llc | Perfectionnements faa au systeme pfn/tracmd pour le controle responsable a distance et robotique pour l'elimination de l'utilisation non autorisee d'aeronefs et pour l'amelioration de la gestion d'equipement et de la securite publique dans le domaine du transport |
-
2000
- 2000-08-11 FR FR0010584A patent/FR2812958B1/fr not_active Expired - Fee Related
-
2001
- 2001-08-07 CA CA002387327A patent/CA2387327A1/fr not_active Abandoned
- 2001-08-07 EP EP01963071A patent/EP1307804A2/fr not_active Withdrawn
- 2001-08-07 WO PCT/FR2001/002569 patent/WO2002014972A2/fr not_active Application Discontinuation
- 2001-08-07 US US10/089,089 patent/US7908052B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
FR2812958B1 (fr) | 2002-11-08 |
US20060155425A1 (en) | 2006-07-13 |
US7908052B2 (en) | 2011-03-15 |
WO2002014972A3 (fr) | 2002-04-25 |
EP1307804A2 (fr) | 2003-05-07 |
FR2812958A1 (fr) | 2002-02-15 |
CA2387327A1 (fr) | 2002-02-21 |
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