Method and system for aircraft maintenance

0001The invention relates to a diagnostic system and a diagnostic method of Support of aircraft maintenance.

0002currently for the maintenance of aircraft in predetermined, periodically performed extensive maintenance checks. to to achieve the necessary reliability and safety for flight operations, be it the individual components of the aircraft systems regularly reviewed and / or replaced after a certain time of use. Due to the Variety and complexity of the to be tested parts, it is often expensive, the expand each component, error checking and testing of conduct and reinstate assemble functional capacity or for a new one Unit exchange. Also, you may experience errors during a flight on, which are not detected during ground checks. So can For example, the wear in the actuators of the wing flap systems to cause the whole aircraft by hunting in vibration is added. At the bottom of this error is often not reproducible, the defective actuator can not be safely located and it be made Security may also functional actuators replaced, which would be extremely expensive. The maintenance costs are therefore an essential part of ongoing Operating costs of commercial aircraft.

0003The invention is therefore based on the object to support the maintenance an airliner rapid and reliable detection of errors and an appropriate provision of information for the maintenance personnel with to realize a minimum of effort and thus shortening the repair time to achieve.

0004This object is achieved in a generic device with the patent claim Measures referred to 1 dissolved. A generic method is defined in claim 18th

0005It is particularly advantageous that maintenance costs as an essential Part of the ongoing operating costs of commercial aircraft significantly can be reduced. A review of the systems and components and a secure localization of errors is possible in a shorter time become. By providing diagnostic information due to actual measurements of aircraft systems is targeted achieved maintenance support.

0006Further developments and advantageous embodiments are in the dependent claims 2 to 17 and 19 to 21 and also in the following description indicated.

0007In the drawing, embodiments of the invention are shown, the following is described with reference to Figures 1 to 4. FIG. In the figures, the same Components provided with the same reference numerals.

0008The drawing shows in detail:<dl tsize="7" compact="compact"><dt>Fig. 1</dt><dd>a schematic representation of an aircraft in "Walkaround check"</dd><dt>Fig. 1A</dt><dd>Darstelllung the operation of a energy-independent diagnostic sensor,</dd><dt>FIG. 2</dt><dd>the representation of a fault diagnosis at actuators in Wing area of ​​a commercial aircraft,</dd><dt>Fig. 3</dt><dd>the representation of a diagnosis of water content in Hydraulic system of the aircraft,</dd><dt>Fig. 4</dt><dd>the representation of a diagnosis on the water content in Fuel tank of an aircraft system and</dd><dt>Fig. 5</dt><dd>the representation of the sequence of a diagnostic request.</dd></dl>

0009In Fig. 1 is a schematic representation of an onboard ground Airliner 1 visible. Before each flight is a "Walk to complete Around "check, ie a mechanic checks the Functioning of important systems. For this is - as indicated in arrows - a circumnavigation of the entire aircraft necessary and important Aircraft systems and aircraft components checked, for example be Tests on nose wheel landing gear wheel 3A and 3B with interrogation of the air pressure and a control of the brakes. Among other things, a check is made the flap systems 4 and 4 ', such as spoilers and flaps and necessary for the adjustment of hydraulic actuators - exemplified with 5 designates. A problem here is, in particular, that the flap systems 4, 4 'and their control devices 5, 5' on the wing due to the height of the are difficult to access wing and due to existing covers. Flap actuators are for example at large Commercial aircraft at a height of 4 to 5 meters from the Floor surface. The invention is characterized in that a check with the ground commissioned mechanics a handset 6 as part of a diagnostic system 2 as Work equipment is replaced, on the one hand, the special for a maintenance task required maintenance information (checklist to be processed points) show on a display 7 and diagnostic information from can query maintenance-intensive aircraft systems. The Maintenance information depends on the application of the diagnostic system comprising on the handset 6, preferably by a removable Storage medium are provided. In a further embodiment is a compound of the handheld device 6 to a stationary unit, For example, a personal computer or a server, said the connection is via a suitable interface, which according to the select data to be transferred amount. For detection of diagnostic information is sensor means 8 to the to serviceable aircraft systems provided. For example, sensors on the Hydraulic actuators 5 and 5 'are provided to detect Aktuatordefekte to can. The sensor information during ground checks queried, analyzed and a fault diagnosis (locally specific actuator in Order or faulty) is displayed on the display 7 of the handset. 6 An embodiment for the diagnosis of actuators is more detail in FIG. 2 described.

0010The sensor means 8 can also search for the water concentration, the particle concentration or the level in hydraulic systems or in Fuel will be provided. Embodiments of this kind are shown in Figs. 3 and 4, respectively.

0011For the review of the aircraft systems during ground checks the corresponding sensor signals over transmission facilities to a Processing unit sent 9 and processed there and on a Display unit 10 as information for the mechanics provided. The processing unit 9 receives wirelessly to a receiver 11, Sensor signals. Processing of the information, by means of conventional stationary computers or in a preferred embodiment directly by carried Pocket PC or laptop and asked the mechanic available will. It is preferably provided that the handset 6 as the working medium the mechanic for addition to the display device 10 and the Processing unit 9 includes and he thus directly and locally perform verification of aircraft components and fault diagnosis can. It is further provided that a signal transmission from the Sensor means 8 to the processing unit 9 wirelessly over a larger , Is about the distance of at least 12 m, possible range. Thus is a remote access of information especially for wide-body aircraft, with which for example have a access to certain doors, Adjusting devices and the wings due to the large dimensions without Tool does not work, achieved with great reliability. A Signal transmission is possible, for example by wireless connections or Infrared signals. The necessary for signal generation and signal transmission Energy is provided in the field of sensor devices. 8 The Sensor means 8 are preferably possible without interfering with existing Aircraft systems designed energy independent. This ensures that an integration of the sensor means 8 in the plane the does not affect functionality of the existing aircraft systems and no additional connections to the energy supply of the aircraft necessary is. The energy supply of the sensor means 8 can for example, provided via separate energy sources or energy storage be. Preferably, power generators are to be applied, consisting of the environment Generating energy, such as from the vibration. Shown is this energy-independent diagnostic sensor with the possibility of an active wireless Query 80 in FIG. 1A. The sensor device 8 comprises a transmitter / receiver unit (Receiver / transmitter) 81, a sensor 82 and a Microcontroller (C, signal converter A / DC, Time) 83 for detecting the data and for example the time. If the handset 6 an interrogation signal is triggered, the transmission of data to the transmitter / receiver unit is (Receiver / Transmitter) 11 of the handheld device 6. The processing unit 9 with the display device (Display and Control) and with a mikroprozessorgestützen interface (Controlled Interface) and can perform at least some of the functions listed below: View work progress, wirelessly Check sensor means register and display of data, exchange of data and instructions, and / or See the visualized repair instructions. In addition to the possibility of active wireless interrogation 80 of the sensor means 8, a passive wireless interrogation 84 by the handset 6 occur. Here the need Sensors not have its own energy. While the query is on a shorter Distance, for example, &lt;0.1 m, starting from a transceiver 85 a identified sensor and an RF (rf [radio-frequency]) - transponder 86 is activated, a sensor interrogation carried out and this measured value to the transceiver 85 transmitted. For example, a measurement of the air pressure in the tire is provided with measurable and indirectly this method. The required energy is from here taken from the transmission power. Another embodiment of the invention uses as a diagnostic sensor system sensing means having an active storage of reading provide. The energy required for this can be very low. Retrieving the memory value is the called passive wireless Query 84, wherein the required energy from the transmission power of the Transceiver is provided 85th Also conceivable is the use of optical transponders, optical passive and active queries enable.

0012In FIG. 2 is an embodiment of the diagnostic system in the range of Controls for lift systems 4, 4 'on the wings of Airliner 1 shown. A plurality of actuators 5 are for is adjusting the flaps on and wear of the actuators regularly to check. Wear of the spoiler actuators 5 can for example, cause the entire aircraft in each flight phase offset by hunting in vibration (called Slipping effect). At the bottom of this error is usually no longer reproducible and accurate determination of faulty actuators can with the help of the made corresponding actuator 5 arranged sensor device 8A are included, the measurement data during the flight, optionally has processed and stored. A pre-processing of the sensor signal within one Vorverarbeitungsmoduls the sensor device 8 be advantageous in order to achieve data reduction. Is visible in FIG. 2 in an enlarged view of the aircraft spoiler actuator 5, on which the Sensor device 8 is applied externally. With a sensor as For example, a piezo sensor (allowing signal generation due to mechanical pressure) and / or an acceleration sensor is at least occurring one of the diagnosis in case of vibrations (Slipping effect) significant parameters such. as hydraulic control pressure surges or spool Osszillation measured, stored, possibly pre - ie only certain data or intermediate results for the further procedure needed - and these are stored and if necessary transmitted wirelessly to the Processing unit 9 transmitted. The mechanic can on the display 7 of the Handset 6 the appropriate diagnostic information of each actuator 5 Check and safely decide whether a result of Slipping effects Replacement of the actuator 5 is necessary. Since a plurality of actuators 5 are used for the movement of the doors on the passenger aircraft, it will allows the exact localization of defective actuators, an exchange or even of costly upgrades and test a functional spoiler actuator to avoid.

0013In Fig. 3, an embodiment of the diagnosis system 2 is in the range of Hydraulic system for adjusting devices in airliner 1 shown. At a hydraulic container 12, which in the embodiment shown in the region of the Landing gear wells 13 of the aircraft 1 is arranged, is regularly the determine water content of the hydraulic fluid, because by water entry the life of the hydraulic fluid is significantly reduced. A high Water content leads to damage of the entire hydraulic system. By a determination of the state, such as, inter alia, the water content or the Concentration of particles in the hydraulic fluid can be signaled at an early stage be whether cleaning or replacement of the fluid is necessary. The sensor device 8B is for this application to measure the Concentration of water in the hydraulic reservoir to the underside of Container 12. About transmission means the measured values ​​are to the processing unit 9 received in the handset. 6 The Mechanic to make a diagnosis condition of the hydraulic fluid, may at Display 7, the diagnostic information, for example, read the water content. He must not enter through the access door in the landing gear bay and the hydraulic reservoir to make immediate 12 measurements.

0014In FIG. 4, an embodiment of the diagnosis system 2 is in the range of Fuel tank 14 shown in the airliner. 1 Water deposits in Fuel tank 14 must be removed regularly. This is a Water drainage valve 15 is provided. In proximity to this valve 15, a fuel Water detection sensor is 8C disposed within the tank 14th By Sensor device 8C, the amount of water in the tank and the water level the deposited amount of water can be measured and to the processing unit 9 transmitted, the maintenance personnel can diagnose the water level over the display device will be communicated 10 (screen 7). The timing for necessary water drain is thus relatively accurately determined and the Work required need only be carried out as required. As already explained for the previous embodiments, also takes place here the transmission of the measurement signals from the sensor means to 8C Processing unit 9 wirelessly. On handset 6 on the display 7 when done a request of diagnostic information by maintenance personnel a Remote access of the water level in the tank 14. The signal is from Fuel Water Detection sensor 8C transmitted to the processing unit 9 and by means of a Evaluation software, the measured value processing and as diagnostic information prepared. In a preferred embodiment, depending on the Evaluation of the mechanics of the reading also shows whether a water drain is necessary. Such maintenance information depends on the application of the diagnostic system comprising the handset 6, preferably by a removable storage medium available be provided.

0015In Fig. 5 is an example of a flow chart illustrating a Diagnostic query shown. Sensor signals are applied to a sensor device 8 before and can by an appropriately addressed by the request Handset 6 from retrieved. If a query is unsuccessful and no response within a certain time, for example 10 ms, has been received, the query is repeated. The sensor signals are applied to the Processing unit transmits 9, processed, stored and the result if necessary, displayed. After completing the search, a new query a next diagnostic sensor be performed.

0016The present invention is not limited to the mentioned embodiments limited, but the use of the invention for a sensor-based Maintenance support to many aircraft components or Aircraft systems possible. Maintenance-intensive system components, ie Components that due to frequent failure or security relevance must be checked frequently, with the present invention be fitted or checked what the maintenance costs for this Components considerably lowers.