• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a monitoring of the state of a servomotor in an aircraft. It comprises a processor unit for data processing and for operating a system model of the servomotor (30), at least one sensor (151, 152, 153, 154, 155, 156) for obtaining an adjustment value of the servomotor (30) and a memory unit (54) in which characteristic data of the servomotor (30) is stored. The processor unit is adapted to perform status monitoring based on the system model, with reference to the servomotor setting value (30) and the characteristic data from the memory unit (54). Preferably, the processor unit is identical to the processor unit of a control electronics (50) of the servomotor (30).
    公开号:FR3038740A1
    申请号:FR1656400
    申请日:2016-07-05
    公开日:2017-01-13
    发明作者:Andre Dorkel；Nikolaus Dreyer
    申请人:Liebherr Aerospace Lindenberg GmbH；
    IPC主号:
    专利说明:

    MONITORING THE STATE OF A SERVOMOTOR IN AN AIRCRAFT
    The present invention relates to a device for monitoring the state of a servomotor in an aircraft and a corresponding method.
    The purpose of monitoring the state of components in an aircraft, often called in English "Health Monitoring", is to obtain at any time information concerning the structural integrity. , remaining life or other safety information. It is then of fundamental interest to be able to predict the failure of a component in an aircraft in order to be able to take countermeasures before the damage arrives. The purpose of health monitoring is then to obtain the current status of the monitored systems, for example of a servomotor, in order to be able to coordinate the maintenance tasks for the aircraft and in order not to let failures that are critical for safety.
    [0003] Traditional state surveillance methods in the field of aviation relate to the airframe of the aircraft or the structural integrity of a landing gear. The methods applied here for the monitoring of structural components, which are based on fracture mechanics, have been examined in detail in the state of the art and are common practice in monitoring the state of a cell. airplane and landing gear. It should be noted that the design of the elements monitored here, such as for example the airframe, includes an error tolerance. When a crack in an airplane cell appears, the progression of this crack is first monitored and, subsequently, measures limiting the damage are taken.
    State monitoring for a landing gear of an aircraft is known from EP 1815224 A1. In a manner similar to the state of the art discussed above, state monitoring is largely concerned with the structural integrity of large components.
    To determine the structural integrity of large components, the oscillatory behavior of the components is generally measured and the data obtained is transformed in the frequency domain. Then, using a filter, it is best to search using a matched filter, that is to say a matched filter, or a Kalman filter. oscillatory behavior that is typical for a damaged or weakened component in its structure. For this targeted filtering, however, it is important to know what is the appearance, in the frequency domain, of the basic form of the desired signal, so that the filter adapted to this can detect the desired signal form. This knowledge can be obtained only by a large number of series of tests without destruction and with destruction of the components to examine the aircraft. In addition to these many data, experience with the operation of similar components and experience with the component itself contribute significantly. From this it is necessary for the component to be examined to be available long enough in advance so that there is enough time to perform the series of tests.
    As stated, the database for such a method is very large, so the need for memory capacity for this is immense. In addition, the necessary memory capacity is increased even more by real-time recording of a multitude of sensors not defined here in detail (for example a vibration sensor). Similarly, the hardware investment for the communication between the means for obtaining data at the sensor and a memory unit is significant, so that an increased sensitivity to turbulence and failure, in addition to analysis costs, of acquisition, operation and maintenance, contribute to a reduction in total safety and / or a reduction in the availability of the system.
    As already indicated above, what is disadvantageous in the state of the art, is that it is necessary to establish, prior to the state monitoring, a database particularly large and complex to produce, since it is only in this way that the form of the signal of an error or error about to occur can be recognized. On the basis of this, it is unacceptable to transpose the application of the systems traditionally used to less essential components of an aircraft. This would significantly increase the cost of developing an aircraft or developing a component of an aircraft and at the same time increase the weight of the aircraft, since the components required for traditional state surveillance should be integrated more.
    The object of the present invention is to provide a status monitoring for a physical unit of operation, such as a servomotor for an aircraft, which overcomes the disadvantages described above. Also subject of the present invention is a method for carrying out state monitoring.
    As a field of application for state monitoring according to the invention, there is the primary control of the flight of an aircraft, namely the elevators, fin, steering, roll deflectors , ground spoilers, adjustments of the main rotor and / or the rear rotor. In addition, the invention can be applied in high lift flap systems. Another additional field of application of the present invention is the actuation of a horizontal stabilizer for the ballast, the air inlet adjustment of air conditioning apparatus or aircraft engines, the control of tank pipes. , the actuation of cargo doors and / or other electronic control, communication and power.
    The present invention is implemented by a device for monitoring the state of a servomotor in an aircraft, which device comprises a processor unit for data processing and for operating a system model of the servomotor at least one sensor for obtaining a servomotor adjustment value and a memory unit in which servomotor characteristic data is stored. In addition, the processor unit is adapted to perform status monitoring based on the system model, with reference to the actuator setting value and the characteristic data from the memory unit.
    The combination of a system model with the reference to the actuator adjustment value and the characteristic data from the memory unit makes it possible, in the case of a servomotor, to simply determine the service life. effectively remaining, future investment in maintenance, or immediate action for pilots, flight attendants, maintenance personnel, the aviation company and / or the probate office.
    As already mentioned, a servomotor is a physical actuation system that is designed to support different functions in an aircraft. Thus, for example, a servomotor is used in the primary control of flight, for example for the change of position of the elevators, or for the positioning of a high lift system, for example attacking flaps or flaps. A system model of the servomotor may be an observer (eg Lüneburg), a filter (eg Kalman) or a simulation model (eg Simulink), which describes or calculates the behavior of the servomotor under different conditions. It is clear that this system model can be operated virtually using the processor unit.
    The adjustment value of the servomotor is provided by a sensor. This sensor can be for example an oil temperature sensor, an oil pressure sensor, an oil quality sensor, a vibration sensor, a structural noise sensor, or another unspecified sensor in details. . The characteristic values which are stored in the memory unit, preferably describe structural characteristics and servomotor limits, which have been obtained preferably during the servomotor design phase.
    By combining the results of the system model, the existing signal coming from a sensor (setting value) and the characteristic values, the state monitoring obtains an effective monitoring of the state that does without prior knowledge. specific to the actual aging of the servomotor.
    Advantageously, the design of the state monitoring consists mainly of control values and conventional monitoring, simulation models that are available from the approval process of the device, data publicly. available on the materials, evidence of resistance that is available from the approval process of the device and safety and reliability analyzes also available from the approval of the device.
    Since these components are performed independently of the actual state monitoring and are not specifically performed for them either, the additional effort of state monitoring according to the invention consists only of a correct combination and adaptation of these different elements. The state monitoring according to the invention thus makes it possible to determine in a simple manner the lifetime actually remaining, the future investment in maintenance, or the measures to be taken immediately, in view of the state of the servomotor, without the series of tests specifically required according to the state of the art.
    According to another advantageous characteristic of the invention, the processor unit for the implementation of the state monitoring is the processor unit of a control electronics of the servomotor. It is further designed to control the servomotor. This means that, in addition to the status monitoring, the processor unit performs servo control (control) at the same time.
    This design has the advantage that, in a particular state of state monitoring that requires intervention of a control electronics, the reaction time to perform the requested command is particularly short. This is because the processor unit of the servomotor control electronics is at the same time the processor unit for the implementation of the state monitoring. Another advantage of this feature is that no other component is needed for the implementation of state monitoring. In addition, based on this characteristic, the status monitoring can be fed directly by signals from the drive-specific regulation and it can also use signals from communication with higher computers (computer flight or maintenance computer) or with servomoteers in parallel, without additional components. On the basis of this, it is considered advantageous to implement the state monitoring algorithm with the processor unit which is also the processor unit of the servomotor control electronics.
    Thus, the processor unit is designed to receive signals from a regulation specific to the servomotor drive, communication with a hierarchically superior computer such as a flight computer, and / or with a servomotor paralleled.
    According to another advantageous modification of the invention, the characteristic data stored in the memory unit are data from strength, safety and / or reliability analyzes of the servomotor (30) which are preferably known. the design phase of the servomotor (30).
    Device according to one of the preceding claims, characterized in that the processor unit is designed to perform state monitoring for the purpose of analyzing the existing data in the aspect of a state of operation and operating safety of the servomotor. These data are preferably known from the servomotor design phase. They have not been compiled specifically for state surveillance. Thus, the characteristic values can only consist of data that has not been generated specifically for the purpose of state monitoring. From this point of view, it is not necessary for the generation of the characteristic values to carry out a large number of series of tests with or without destruction, as is traditionally required for state monitoring. components in aircraft.
    Also advantageously, the processor unit is designed to carry out state monitoring with the aim of analyzing the existing data in the aspect of a state of operation and of operational safety and for determine the need for maintenance measures, maintenance measures, component replacement and / or device replacement. The processor unit is also designed to transmit corresponding information to higher instances whose receiver may vary depending on the urgency of an action to implement. Thus, depending on the lifetime actually remaining, an immediate measure may be reasonable for the aircraft's pilot, an attendant (an air hostess) of the aircraft, for maintenance personnel, for an airline and / or a probate office.
    Also preferably, the processor unit is designed to capture at least one real-time signal for the control of a servomotor or to obtain a setting value of a servomotor and to transform it into a determined number of characteristic values, the number of data of the real-time signal being preferably greater than the number of data of the characteristic values. In addition, the processor unit is adapted to store the characteristic values in the memory unit for further transmission, processing and / or operation.
    The processor unit is therefore designed to capture a signal in real time and to extract from this signal in real time, or to calculate, one or more values -characteristics. The signal data is then reduced in real time to the characteristic value (s). This prior preparation for obtaining the characteristic values from the real time signal is then stored in the memory unit for further transmission, processing and / or operation.
    Preferably, the memory unit is a permanent memory, particularly a very small permanent memory.
    According to another embodiment of the invention, it is proposed that the memory unit is at the same time also a memory unit for a control electronics of the servomotor. By this, a separate memory unit for state monitoring is unnecessary, so that the total number of components for state monitoring is further reduced.
    Advantageously, in the memory unit are also stored reference values for the characteristic values, the processor unit being also designed to compare one of the characteristic values with its associated reference value. Preferably, the reference values are generated during a servomotor homologation process, so that series of tests are not specifically necessary for state monitoring.
    By comparing the reference values stored in the memory unit, with the characteristic values extracted from the real-time signal, the current operating state of the servomotor and the drift of the servomotor of a normal range is easy to recognize. And since, in addition, according to an advantageous embodiment, the reference values are obtained during the approval procedure of the servomotor, it does not result in additional effort for the generation of these data.
    Advantageously, the processor unit is designed to perform the status monitoring in such a way that it results in a conclusion regarding the remaining service life and the state of the servomotor.
    As indicated above in more detail, this possibility of conclusion results from the combination of the system model, an existing signal of a setting value and the characteristic values of the servomotor.
    By predicting the remaining service life and by estimating the state of the servomotor, maintenance intervals and replacement normally chosen in a traditional manner, can be increased or be linked to a particular determined state.
    Advantageously, the device according to the invention is designed not to transmit in real time the conclusions of the state monitoring to a higher instance such as a maintenance computer or the aircraft personnel, so that interfaces existing control electronics of the servomotor can be used for the transmission of information.
    Thus, communication lines only necessary for state monitoring can be omitted.
    In addition, it may be advantageous for the device according to the invention that it further comprises at least one additional sensor which generates data only for state monitoring, said at least one additional sensor being preferably a structural noise sensor, vibration sensor, oil pressure sensor, oil quality sensor and / or oil temperature sensor.
    It is also advantageous that the power supply of said at least one additional sensor is performed by transforming device vibrations and / or heat.
    Thanks to this, it is particularly easy to make the arrangement of such an additional sensor, since in case of a wireless communication with the processor unit, no wired connection is necessary for communication or for the power supply.
    In addition, the present invention relates to a method for monitoring the state of a servomotor in an aircraft using a device according to one of the embodiments described above, the method comprising the steps: to obtain setting values, setpoints and / or status values from the command or control of a servomotor drive control, reduce setting values, setpoints and / or status values at characteristic values for damage, fatigue and / or wear analyzes, use these characteristic values to determine the state of the servomotor and conclude from the determined state of the servomotor on a necessary action of maintenance and / or maintenance.
    Preferably, the analysis of damage, fatigue and / or wear is performed using reference data of the respective analysis. These reference data are chosen according to the state characteristics of the surroundings. Preferably, one or more of the steps are performed outside the device, for example in a flight computer or a maintenance computer of the device. aircraft.
    In this context, a unit can perform a process step of several servomotors.
    According to another modification of the invention, the method also obtains a status monitoring of the entire flight control around a flight axis or a direction of movement along the longitudinal axis, the transverse axis and / or the vertical axis.
    In the following, the present invention is described in more detail with reference to exemplary embodiments shown in the figures. He is represented there:
    Figure 1: a general diagram of the servomotors to be monitored in an airplane and their interconnection,
    Figure 2: a system design of servo state monitoring in the aircraft,
    Figure 3: Interfaces of state monitoring of a servo-controlled servo motor (EHSA),
    Figure 4: Interfaces of the state monitoring of a linear electromechanical servomotor,
    Figure 5: Interfaces for state monitoring of an electro hydrostatic servomotor (EHA),
    Figure 6: Interfaces for state monitoring of an electric drive for a high lift system (E-PCU) and
    Figure 7: a flowchart for the implementation of state monitoring according to the invention.
    FIG. 1 represents an aircraft in a side view and in a view from above in which the various servomotors (1 to 12) and their interconnection with a flight computer 13 and / or a maintenance computer 14 are shown. . In the side view of the aircraft, several different servomotors are provided with reference numbers. The air inlet and the air outlet 10 are recognized to the aircraft reactor, the dynamic air shutters 9 of the air conditioning system, a cargo door 11 with locking, a refueling device 12, a ballast 8 of the horizontal stabilizers and rudder 3.
    On the view of the aircraft disposed below, on which we look on the plane from above, other servomotors are provided with reference numbers. In addition, it is recognized, for example, a few links of the various servomotors to the flight computer 13. For the sake of clarity of representation, the links of the servomotors to the maintenance computer 14, which can be provided optional, are not mounted entirely. Thus, for example, the power supply module 15 is recognized, a servomotor at the leading edge 6, a base spoiler 5, a multifunctional spoiler 4, the fin 2, the flaps 7, a folding mechanism wing 16 with locking and elevator 1. For a better orientation, a definition of the axes is given in the lower right zone of Figure 1. The arrow bearing the reference number 27 describes the extent of the longitudinal axis, the arrow bearing reference numeral 29 describes the extent of the transverse axis and the arrow extending perpendicularly to the longitudinal axis and to the transverse axis, which bears the reference numeral 28, describes the vertical axis for the lower part of the representation.
    Thus, using the representation in FIG. 1, it is recognized that there are a plurality of different servomotors in an airplane. These can produce different effects on the stability and flight characteristics of an aircraft and can have applications in a wide range, from essential security functions to less important security functions.
    FIG. 2 represents a system architecture in state monitoring of servomotors 30 in the aircraft. The figure is roughly divided into three parts, so that it comprises a left part, a central part and a right part. In the left part are disclosed various servomotors 30 which can communicate either directly or via a power supply module 15 which is arranged in the central part of the figure, with a flight computer 13 and / or with a maintenance computer 14 The flight computer 13, or respectively the maintenance computer 14, is arranged in the right part of the figure. The basic design of the said plurality of servomotors 30 shown in the left-hand part of the figure does not vary or hardly change from each other with respect to the main components thereof.
    It is recognized that each servomotor 30 comprises a set of sensors 100 which communicate with a control electronics 50 or respectively with a status monitor 53 installed thereon.
    The communication of the servomotor 30 can be performed directly with the maintenance computer 14, the flight computer 13 or a power supply module 15 inserted between the flight computer 13 and / or the computer. 14. In addition, direct communication of a few servomotors with one another is possible, as shown in the upper left-hand part of the figure. In addition, the flight computer 13, the maintenance computer 14 and the power supply module 15 and the servomotor 30 comprise an interface 24 for accessing the data and using data from the unit. respectively. As servomotors, all the physical actuation units shown with reference to FIG. 1 may be used. In addition, it is clear to those skilled in the art that there are a plurality of other servomotors in an aircraft which are suitable for use in the implementation of the invention and are included therein .
    FIG. 3 represents a device according to the invention for the state monitoring of a servomotor, with the aid of an example of an electrohydraulic servovalve with a corresponding control electronics and sensors.
    The servomotor 30 is connected to a hydraulic supply 20, a power supply 19, the flight computer 13, the maintenance computer 14 and an interface 24 for access to data and the use of data. In addition, the servomotor 30 comprises a control electronics 50 and an electrohydraulic 70.
    The control electronics 50 further comprises a power electronics, a drive control 52 of the servomotor and a status monitor 53. The electronics. power supply 51 comprises a temperature sensor 112 of the electronics, an output current sensor 111 and a return signal unit 103 of the servovalves. In addition, the power electronics 51 receives signals from the drive control 52.
    The drive control 52 receives signals from the output current sensors 111 of the power electronics 51 and data from the return signal unit 103 of the servovalves and feedbacks of the push-rods 104. the drive control receives regulation commands from a hydraulic cylinder 71 from a position sensor 101 of the servomotor and from a load sensor 102.
    In addition, the drive control 52 is connected to the status monitoring 53 via a bidirectional communication line.
    The state monitoring 53 comprises a memory unit 54 which is preferably made as a permanent memory, and receives a plurality of signals from the power electronics 51, the drive control 52 and the electrohydraulic 70. Thus, the status monitoring 53 receives a signal from the temperature sensors 112 of the electronics, a signal from the output current sensors 111, the state values 55 of the regulation as well as a multitude of signal signals. electrohydraulic sensors 70.
    It is recognized that the status monitoring 53 is incorporated in the control electronics 50. The electrohydraulic 70 receives signals from the power electronics 51 for the transformation of the corresponding reference values. The hydraulics 70 includes an oil quality sensor 153, an oil pressure sensor 152, an oil temperature sensor 151, other sensors 156, a structural noise sensor 155 and a vibration sensor. 154. In addition, the hydraulics 70 further comprises a memory unit 54 which comprises a bidirectional communication link with the state monitoring 53. In addition, the hydraulics 70 comprises a servovalve 74, a switching valve 73, a pusher group 72 with a feedback device 104 of the pusher group, a brake 78 and a cylinder 71 which includes a position sensor 101 and a load sensor 102.
    It is recognized that the state monitoring is adapted to be implemented on the basis of the system model of the servomotor to be monitored, with reference to a setting value of the servomotor 30 and data stored in the control unit. memory 54.
    FIG. 4 represents a diagram of a state monitoring of a linear electromechanical servomotor whose design is very close to that of the servomotor described with reference to FIG. 3. Consequently, only elements which differ from that of the actuator. will be described in the following. The servomotor 30 now comprises a control electronics 50 and an electromechanical 70. The electromechanical 70 comprises a motor 77, a brake 78, a reducer 79, a clutch 80 and a worm 81. In addition, the electromechanical 70 comprises a vibration sensor 154 and a structural noise sensor 155 as well as other sensors 156. In addition, the motor 77 comprises a temperature sensor 110, the brake, a feedback signal device 107, the gearbox, a sensor of oil temperature 151 and an oil quality sensor 153, clutch 80, a return signal device 106, the worm gear, an oil pressure sensor 152, the output values of the sensors enumerated above all being provided for status monitoring 53 in the control electronics 50.
    FIG. 5 represents a diagram of the state monitoring of an electro-hydrostatic servomotor (EHA). That is no longer distinguishable with regard to the basic design of the control electronics 50 and the components of the power electronics 51, the drive control 55 and the state monitor 53. Only, the type of sensor data used for status monitoring changes due to servomotor type variation. The electrohydraulic 70 comprises a motor 77, a pump 76, a switching valve 73, a pressure accumulator 75, a pusher group 72 and a hydraulic cylinder 71. In addition, the electrohydraulic 70 comprises an oil temperature sensor. 151, an oil pressure sensor 152, an oil quality sensor 153, a vibration sensor 154, a structure noise sensor 155 and other sensors 156.
    As has been demonstrated with reference to Figures 2 to 5, for monitoring according to the invention, it is irrelevant what type of servomotor should be monitored regarding its state. In this regard, the specific embodiment of the servomotor 30 is unimportant. Therefore, the device according to the invention is also conceivable together with an electromechanical rotary actuator or a servomotor electrohydrostatically assisted.
    Figure 6 shows the state monitoring interfaces for an electrical drive that is typical for a high lift system (E-PCU). The servomotor 30 here comprises two electronic control units 50 and two electromechanical devices 70. In addition, a main gear reducer stage 79 is recognized which receives signals from the two blocks of the electromechanical unit 70. In addition, each of the electromechanical blocks 70 comprises a link to each of the control electronics 50. Similarly, the control electronics 50 comprise a bidirectional communication line between them. In all, a redundant realization of the control electronics 50 and the electromechanical 70 necessary for the adjustment of the main stage of the reducer 79 is recognized. Since the state monitoring is included in the control electronics 50 or is performed on the processor thereof, it is also performed in two copies.
    FIG. 7 represents a flowchart for the implementation of state monitoring according to the invention. The program begins with the element marked with reference number 201 and then divides into two action sequences to be implemented in parallel. However, according to one alternative, these action sequences can also be implemented in a serial manner. This helps for example when a processor unit for the implementation of state monitoring is less efficient. After the start of the status monitoring, the state values are measured 202 in the system. For this, we use 203 sensors internal to the system. After the measurement of the state values in the system, the unknown state values of the system are estimated 204. Here, the estimate is made using reference data for the functional behavior 205 and signals from the system. 228 Then, it is tried to recognize a specific behavior in time 206. For periodic unknown state values of the system, a frequency analysis 207 is performed, i.e. say a behavioral analysis over time. For this, reference data are used in the frequency domain 208 which represents a known error in the frequency domain. Then, an amplitude analysis is carried out 209, to which however it can happen directly when, during the recognition of a specific behavior in time 206, periodic structures are recognized. In amplitude analysis 209, too, reference data are used in the time domain 210. After the exploitation of these two analyzes, the damage analysis 211, which also uses to reference data concerning the damage behavior 212. The result thus obtained from the damage analysis then contributes to the determination of the remaining life time 213.
    In parallel with this series of actions since the beginning of the state monitoring, there is another sequence of actions which is presented below. After the start of the status monitoring, the surrounding state values are measured using sensors 218 at interfaces 219. Using this measurement, the reference data used above, such as the reference data for the functional behavior 205, the reference data in the frequency domain 208, the time domain reference data 209 and the reference data for the damage behavior 212 are determined (see A). In addition, the fatigue load is estimated 222 by measuring the surrounding state values 218. After estimating the fatigue load, a fatigue analysis 223 is performed based on reference data concerning the behavior of the fatigue. fatigue 224, these reference data having also been chosen as a function of the measurement of the state values of the surroundings. The fatigue analysis 223 thus contributes, as the damage analysis 211, to the determination of the remaining life time 213. After the measurement of the surrounding state values 218, is performed in addition, parallel to the estimating the fatigue load 222 and selecting the reference data 220, in which an index of the reference data set is determined 221, an estimation of the wear 225. After the estimation of the wear a wear analysis is performed 226 using reference wear behavior data 227 which has been set based on the index of the reference data set 221. The results of Wear analysis 226 is also used for the determination of the remaining life time 213. Using the damage analysis 211, the fatigue analysis 223 and the wear analysis 226, the duration of the remaining life can be determined 21 3. Subsequently, it is possible to determine whether or not this remaining remaining service life is still sufficient or not.
    When the service life is sufficiently large, that is to say it exceeds a predetermined threshold value, the process starts again 215. If it is found that the service life falls below a threshold value, the resulting maintenance action is determined 216. In a final step, the maintenance action thus determined is triggered 217.
    权利要求:
    Claims (15)
    [1" id="c-fr-0001]
    A device for monitoring the condition of a servomotor (30) in an aircraft, comprising: a processor unit for data processing and for operating a system model of the servomotor (30), at least one sensor (151, 152, 153, 154, 155, 156) for obtaining an adjustment value of the servomotor (30) and a memory unit (54) in which characteristic data of the servomotor (30) are stored, the processor unit extinguished configured to perform status monitoring based on the system model, with reference to the servomotor setting value (30) and the characteristic data from the memory unit (54). ).
    [2" id="c-fr-0002]
    2. Device according to claim 1, characterized in that the processor unit is the processor unit of a control electronics (50) of the servomotor (30) and is adapted to carry out the control of the servomotor (30).
    [3" id="c-fr-0003]
    3. Device according to claim 1 or 2, characterized in that the processor unit is adapted to receive signals from a drive-specific control of the servomotor (30), a communication with a computer (13). , 14) hierarchically superior such as a flight computer (13), and / or with a servomotor (30) in parallel.
    [4" id="c-fr-0004]
    4. Device according to one of the preceding claims, characterized in that the characteristic data stored in the memory unit (54) are data from strength, safety and / or reliability analysis of the servomotor (30) which are preferably known from the design phase of the booster (30).
    [5" id="c-fr-0005]
    5. Device according to one of the preceding claims, characterized in that the processor unit is designed to perform state monitoring for the purpose of analyzing the existing data in the aspect of a state of operation and of an operational safety of the servomotor (30) and, moreover, preferably to determine the need for maintenance measures, maintenance measures, component replacement and / or device replacement.
    [6" id="c-fr-0006]
    6. Device according to one of claims 2 to 5, characterized in that the processor unit is designed to capture at least one real-time signal for the control of a servomotor (30) or to obtain a setting value of a servomotor (30) and to transform it into a given number of characteristic values, the number of data of the real-time signal being preferably greater than the number of data of the characteristic values, and in that the processor unit is configured to store the characteristic values in the memory unit (54) for subsequent transmission, processing and / or operation.
    [7" id="c-fr-0007]
    7. Device according to one of the preceding claims, characterized in that the memory unit (54) is at the same time also a memory unit (54) for a control electronics (50) of the booster (30).
    [8" id="c-fr-0008]
    8. Device according to one of claims 6 or 7, characterized in that in the memory unit (54) are also stored reference values for the characteristic values, and in that the processor unit is also designed for comparing one of the characteristic values with its associated reference value, the reference values preferably being generated during an approval process of the servomotor (30).
    [9" id="c-fr-0009]
    9. Device according to one of the preceding claims, characterized in that the processor unit is designed to perform state monitoring in such a way that results in a conclusion concerning the remaining life and the state of the booster (30).
    [10" id="c-fr-0010]
    10. Device according to claim 9, characterized in that it is designed not to transmit real-time status monitoring conclusions to a higher instance such as a maintenance computer (14) or the aircraft personnel so that existing interfaces (24) of a control electronics (50) of the servomotor (30) can be used for the transmission of information.
    [11" id="c-fr-0011]
    11. Device according to one of the preceding claims, characterized in that it further comprises at least one additional sensor which generates data only for state monitoring, said at least one additional sensor being preferably a noise sensor. structure (155), a vibration sensor (154), an oil pressure sensor (152), an oil quality sensor (153) and / or an oil temperature sensor.
    [12" id="c-fr-0012]
    12. Device according to claim 11, characterized in that the power supply of said at least one additional sensor is performed by transforming device vibration and / or heat.
    [13" id="c-fr-0013]
    13. Method for monitoring the state of a servomotor (30) in an aircraft using a device according to one of the preceding claims, comprising the steps of: obtaining adjustment values, setpoint values and / or status values from the control or regulation of a drive control of the servomotor (202, 218), reducing setting values, set values and / or status values at characteristic values for damage, fatigue and / or wear analysis (211, 223, 226), use these characteristic values to determine the state of the servomotor (213) and conclude from the determined state of the servomotor (216) on a necessary action of maintenance and / or maintenance.
    [14" id="c-fr-0014]
    14. The method of claim 13, characterized in that one or more of the steps are performed outside the device, preferably in a flight computer (13) or a maintenance computer (14) of the aircraft.
    [15" id="c-fr-0015]
    15. Method according to one of the preceding claims 13 or 14, characterized in that the method also obtains a status monitoring of the entire flight control around a flight axis or a direction of movement following the longitudinal axis, the transverse axis and / or the vertical axis.
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    同族专利:
    公开号 | 公开日
    CN106335645B|2020-02-28|
    US20170069145A1|2017-03-09|
    RU2710513C1|2019-12-26|
    US10431019B2|2019-10-01|
    FR3038740B1|2020-01-24|
    DE102015008754A1|2017-01-12|
    CN106335645A|2017-01-18|
    DE102015008754B4|2018-07-05|
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    法律状态:
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    优先权:
    申请号 | 申请日 | 专利标题
    DE102015008754.1|2015-07-06|
    DE102015008754.1A|DE102015008754B4|2015-07-06|2015-07-06|Condition monitoring of an actuator in an aircraft|
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