• 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:
    BREAK DETECTION DEVICE OF A PRIMARY ROUTE IN A FLIGHT CONTROL UNIT. The present invention relates to a device (13) for detecting the rupture of a primary path in a flight control actuator, that actuator having a primary path (1), comprising a rotating hollow screw (2), a path secondary (10) that includes a safety charge (3) for resumption of effort through the screw (2), this device (13) being characterized by the fact that it comprises a position pickup (15), connected to the screw (2) to measure information representative of its angular position and a connection system (17), able to disconnect the pickup (15) from the screw position (2), in case of relative displacement of the rod (3) in relation to the screw (2 ), when a primary path rupture occurs.
    公开号:BR112012027852B1
    申请号:R112012027852-5
    申请日:2011-04-14
    公开日:2020-11-17
    发明作者:Thomas Moulon；Raphael Medina
    申请人:Goodrich Actuation Systems Sas；
    IPC主号:
    专利说明:

    General technical domain.
    [0001] The present invention relates to the detection of failure in a flight command actuator.
    [0002] Notably, but not limited to, it refers to the detection of the rupture of a primary path of an aircraft flight command actuator and the resumption of effort by a secondary avia of that actuator. State of the art
    [0003] Classically, these actuators comprise two mechanical pathways, one primary, the other secondary, this being intended to resume the effort, when the primary pathway is failed, generally as a result of a rupture of that primary pathway.
    [0004] The general structure of this actuator is outlined in figure 1.
    [0005] In operation on the primary track 1, the efforts pass through a hollow screw 2, for example with balls or cylinders.
    [0006] This feature allows a security rod 3 to resume effort (bar called “fail safe”), grooved at its ends and loosely connected to screw 2.
    [0007] This structure ensures the continuity of the transmission of efforts and the rotation of the set, avoiding axial separation of the screw elements, in case of rupture of the screw itself.
    [0008] The screw 2 ends at one of its ends by a connection piece, called primary high connection 4, by which it is connected to a structure 5 of the aircraft.
    [0009] In case of failure of primary path 1, that is, in the event of a rupture of an element of primary path 1, efforts are resumed by secondary path 10, and notably by the safety rod 3, the end of which is a male form 7 (for example a sphere) arranged in a female form of a connecting piece 8 of the secondary track, said secondary high connection 8.
    [00010] This secondary high link 8 is itself linked to the aircraft, by means of an airplane connecting piece 9 different from that used to support primary track 1.
    [00011] From the state of the art, there are numerous systems for detecting rupture of the primary path and resumption of secondary path effort in a flight control actuator.
    [00012] FR 2858035 describes a detection system configured to detect the relative displacement in translation of the free end of the safety bar in relation to the secondary high connection.
    [00013] EP 1557588 discloses a device for detecting load transfer from the primary to the secondary path based on the detection of shear between parts of the secondary high connection.
    [00014] EP 1972549 discloses a solution, comprising a sensor capable of detecting a washed effort on parts, ensuring the high connection of the secondary path, such as secondary path fixing screws or secondary path fixing plates, and able to detect the placement under such effort.
    [00015] However, the proposed solutions currently have drawbacks, as they require a specific and complex implementation in terms of the secondary high connection of the flight control actuators.
    [00016] In addition, they require the installation of bulky and heavy detection cables at the level of the secondary high connection. These solutions cause an increase in the mass of the aircraft.
    [00017] Certain solutions also require, by positioning the sensors at the interface of the actuator parts, to increase the clearance between the actuator parts, which is detrimental to the vibratory stability of the assembly. The gap between the actuator parts is known to the technician with the Anglo-Saxon terminology “Flutter” and meets demanding specifications on an aircraft.
    [00018] Finally, the solutions proposed today require a heavy electronic treatment of the measured signals, and have perfective reliability !. Presentation of the invention
    [00019] The invention aims to prevent the drawbacks of prior art solutions.
    [00020] For this purpose, the invention proposes a device for detecting the rupture of a primary path in a flight control actuator, that actuator having a primary path, comprising a rotating hollow screw, a secondary path comprising a safety rod of resumption of effort through the screw, this device being characterized by the fact that it comprises a position sensor, connected to the screw to measure information representative of its angular position, and a disconnection system, able to disconnect the position sensor from the screw, in case of relative displacement of the stem in relation to the screw, when there is a rupture of the primary path.
    [00021] The invention is advantageously complemented by the following characteristics, considered alone or in combination: - the device comprises a computer configured to compare the information measured by the position sensor, and information representative of the angular position of the screw measured by a second sensor. independent position of the disconnection system; - the computer is configured to detect a rupture of the primary path, when the comparison is above or below a predetermined limit; - the disconnection system is disconnecting the screw position sensor, when the stem exerts a predetermined load on the screw, corresponding to a mechanical effort exerted by the stem on the screw, when the screw breaks or another element of the screw primary pathway; - the disconnection system comprises a breakable pin; - the breaking pin has a cross section calibrated to break at a predetermined load, corresponding to a mechanical effort exerted by the rod on the screw, when a primary path rupture; - the ruptured pin is subjected to a predetermined extraction load, allowing an extraction of the bolt pin in case of rupture of that pin; - the position sensor is an angular position sensor.
    [00022] The invention also proposes a flight control actuator, comprising a primary pathway, which comprises a rotating hollow screw, a secondary pathway that includes a safety resumption rod through the screw, the secondary pathway being able to resume efforts exerted on the primary path, in case of rupture of the primary path, this actuator being characterized by the fact that it comprises a device for detecting the primary path rupture, as described above.
    [00023] The invention has numerous advantages.
    [00024] An advantage of the invention is that it offers a simple and inexpensive solution.
    [00025] Another advantage of the invention is to offer a light solution, increasing the mass of the aircraft in a negligible way.
    [00026] Another advantage of the invention is to offer a solution, whose reliability is improved.
    [00027] Yet another advantage of the invention is that it allows for a reduction in clearance between the actuator parts.
    [00028] Finally, another advantage of the invention is that it allows detection in difficult environmental conditions. Presentation of figures
    [00029] Other features and advantages of the invention will also stand out from the description that follows, which is purely illustrative and not limiting and should be read in relation to the attached drawings in which: - figure 1 is a schematic representation, illustrating the principle of a flight command actuator; figure 2 is a schematic representation of a detection device and a flight control actuator, according to the invention; figure 3 is a schematic representation of a detection device and a flight control actuator, according to the invention, in the event of a primary path rupture; figure 4 is a schematic representation of an embodiment of a detection device and a flight control actuator, according to the invention; figure 5 is a schematic representation of an embodiment of a detection device and a flight control actuator, according to the invention, in the event of a primary path rupture. Detailed Description
    [00030] A device 13 for detecting the rupture of a primary path, according to the invention, as well as a flight control actuator 12, according to the invention, equipped with this device, has been shown in figure 2. The invention concerns both the detection device, the flight command actuator equipped with this device, and the aircraft that comprises this flight command actuator. As explained above, the flight control actuator 12 comprises a primary path 1 and a secondary path 10.
    [00031] This actuator 12 is, for example, a THSA type jack, for the control of a variable horizontal plane of the aircraft (not shown).
    [00032] The primary and secondary routes comprise numerous elements, and only certain of those elements will be described. The structure of the flight control actuators, comprising a primary and a secondary path, is widely known to the technician.
    [00033] The primary track 1 comprises a hollow rotating screw 2, terminating at one of its ends by a connecting piece, said primary high connection 4, by which it is connected to an aircraft structure 5.
    [00034] In general, the primary track 1 also comprises a nut (not shown), which cooperates with the screw 2, being mounted on it and which is connected to the plane to be controlled.
    [00035] Screw 2 is controlled in rotation by a motor, which allows the displacement of the nut mentioned in translation, which is being blocked for rotation. The translational displacement of the nut thus allows the oscillation to be given to the variable horizontal plane to be controlled.
    [00036] A safety rod 3 extends inside the hollow screw 2. The safety rod is one of the elements of the secondary track 10.
    [00037] In general, this rod 3 ends with a spherical head 7 loosely placed inside a female spherical shape of a connecting piece 8 of the secondary track, said secondary high connection. This secondary high connection 8 is itself connected to the aircraft by means of an airplane connecting piece 9 different from that used to support the primary route 1.
    [00038] The fixing of the secondary high connection is known in itself, and it is notably accomplished by systems with plates and fixing screw.
    [00039] In “normal” operation, it is the primary route 1 that supports the efforts. In the event of failure of the primary pathway 1, notably due to the rupture of one of the constituent elements of the primary pathway 1, such as, for example, the primary high connection 4 or the screw 2, it is a secondary avenue 10 that resumes the effort.
    [00040] This failure must be detected in order to inform the pilot and attract any maintenance operations on the ground, even in flight.
    [00041] The device 13 for detecting the rupture of the primary pathway is able to detect these failures.
    [00042] The primary path rupture detection device 13 comprises a position sensor 15, connected to screw 2, to measure information representative of its angular position.
    [00043] In one embodiment, sensor 15 is an angular position sensor 15. In this case, the information representing the angular position of the screw 2 is the angular position itself.
    [00044] The angular position sensor 15 is configured to measure the angular position of screw 2 and / or its angular displacement. It can be a displacement and / or angular positioning, which can be absolute or relative, according to the chosen conventions. When sensor 15 and screw 2 are connected, sensor 15 therefore measures the angular position of screw 2.
    [00045] The angular position sensor 15 can, for example, be an active (inductive) electric sensor for measuring displacements in rotation type RVDT (according to the Anglo-Saxon acronym Rotary Variable Differential Transformee). Other angular position sensors can be used.
    [00046] Alternatively, it can be a linear position sensor, such as, for example, a linear displacement measurement sensor of the LVDT type (according to the Anglo-Saxon acronym Linear Variable Differential transformer).
    [00047] In this case, the linear position sensor 15 is, for example, connected to screw 2, via a ball screw type mechanism, which transforms the rotation movement of screw 2 into a translational movement.
    [00048] The linear position sensor 15 therefore measures a linear position or displacement, but which are representative of the angular position of screw 2.
    [00049] Any position sensor 15 capable of measuring information representative of the angular position of screw 2 can be used, that is, that the measured information (for example, a position) is correlated to the angular position of screw 2, and thus allows deduce that angular position.
    [00050] According to the invention, the device 13 for detecting the rupture of the primary path comprises a disconnection system 17, capable of disconnecting the screw 2 of the position sensor 15, in case of relative displacement of the stem 3 in relation to the screw 2 , when there is a rupture of the primary pathway 1.
    [00051] This disconnection therefore results in the rupture of the connection of sensor 15 and screw 2.
    [00052] The disconnection system 17 is calibrated to disconnect the connection between screw 2 and sensor 15 only in case of rupture of the primary path 1.
    [00053] In fact, in the case of the rupture of an element of the primary route 1, it is a secondary route 10 that resumes the effort.
    [00054] In particular, the stem 3 then undergoes a relative displacement in relation to the screw 2, the essential of that displacement being oriented parallel to the screw 2, according to a translation movement, in one direction or the other. This relative displacement of the stem 3 in relation to the screw 2 is detected by the disconnection system 17, which then causes a cut in the connection between the screw 2 and the position sensor 15. This cut is triggered when the relative displacement of the stem 3 in relation to the screw exceeds a predetermined limit, corresponding to a rupture of the primary path 1, this limit being known by simulation, or by in situ measurement. In fact, it is a matter of avoiding false detections, due to the relative movements of screw 2 and stem 3 that do not result from a rupture of the primary path 1. Only a relative displacement of stem 3 in relation to screw 2 above the limit corresponds a rupture of the primary pathway 1.
    [00055] Below the predetermined limit, disconnection system 17 does not cut the connection between screw 2 and position sensor 15, which avoids false detections.
    [00056] In certain embodiments, the disconnect system 17 therefore comprises a sensor or set of sensors measuring the relative movement of the stem 3 in relation to the screw 2 (or inversely), which allows disconnecting the screw 2 from the sensor 15 position in case of rupture of the primary road 1.
    [00057] In other embodiments, the disconnect system 17 is configured to disconnect the position sensor 15 from the screw 2, when the stem 3 exerts a predetermined load on the screw 2, corresponding to a mechanical effort exerted by the stem 3 on screw 2, when there is a rupture of the primary path 1.
    [00058] In this case, the relative displacement of screw 2 in relation to stem 3, in case of rupture of primary pathway 1 is detected, indirectly, via the load exerted by stem 3 on screw2.
    [00059] In fact, in case of rupture of the primary path, the stem 3 moves in relation to the screw 2 and then exerts a mechanical effort against the screw 2 above a predetermined limit, this mechanical effort being used by the system 17 disconnect switch to disconnect the screw 2 of the position sensor 15, in case of rupture of the primary path 1.
    [00060] The device 13 further comprises a computer 18 configured to compare the representative information of the angular position of the screw 2 measured by the position sensor 15, and an information representative of the angular position of the screw 2 measured by a second position sensor 19 of the detection device 13. The information representing the angular position of the screw 2 measured by the second position sensor 19 can be the angular position itself.
    [00061] The second position sensor 19 differs from sensor 15 in that it is not connected to screw 2 via disconnection system 17. The second position sensor 19 is, therefore, independent of disconnection system 17. Outside this difference, it is a sensor of the same type, able to measure information representative of the angular position of screw 2. This sensor can be an angular position sensor, linear, or other, as previously described for sensor 15.
    [00062] It can, for example, be an angular position sensor of the aircraft itself, used to control and subject the rotation of screw 2, in “normal” operation.
    [00063] It can advantageously be, in particular, the angular position sensor connected to screw 2, and existing in all flight control actuators, which avoids installing new sensors. This type of sensor '[is used to control and fasten screw 2 of primary path 1.
    [00064] Advantageously, the position sensor 15 and the second position sensor 19 are integrated into one and the same sensor several times.
    [00065] The invention therefore makes it possible to use the sensors installed in the area, simply integrating the detection device 13 and notably the disconnection system 17 into the actuator.
    [00066] Computer 18 can be a dedicated computer, or more advantageously, be part of the aircraft computer, boarding the actuator 12.
    [00067] Figure 3 shows a rupture of the primary pathway 1 and a resumption of effort in the secondary pathway 10.
    [00068] The break is illustrated at the level of the primary high connection 4, but it can be performed on any elements that participate in the primary path 1 of the actuator.
    [00069] Before this break, this is in “normal” operation, the sensor 15 is connected to screw 2, and therefore measures information representative of the angular position of screw 2.
    [00070] On the other hand, screw 2 is controlled in rotation by the pilot via the pilot commands that he communicates to the aircraft. Information representing the angular position of the screw 2 is measured by a second position sensor 19, which continues to measure information representative of the angular position of the screw 2, even in the event of a rupture of the primary path 1, since it is not connected to screw 2 via disconnection system 17.
    [00071] In case of rupture of the primary route 1, it is the secondary route 10 that resumes the effort. In this case, the stem 3 underwent a relative displacement compared to the screw 2, this displacement exceeding a predetermined limit, characteristic of the rupture of the primary pathway 1.
    [00072] When this displacement exceeds the limit, the disconnection system 17 causes the connection between screw 2 and position sensor 15 to be cut.
    [00073] Therefore, sensor 15 no longer measures information representative of the angular position of screw 2.
    [00074] The position sensor 15 then measures a null or constant signal, which makes it possible to detect the rupture of the primary path T and, therefore, the failure.
    [00075] Advantageously, the failure is detected, comparing the information representing the angular position measured by the position sensor 15, and the information representing the angular position of the screw 2, measured by the second position sensor 19. In fact, in case of rupture of the primary path 1, the second sensor 19 continues to measure the information representative of the angular position of the screw 2 and the variations of that positioning.
    [00076] If the computer 18 compares this signal with the signal measured by the sensor 15 of the disconnected position of the screw 2, through the disconnection system 17, it is clear that the signals will be different, whereas before the failure, these were the same or at least correlates.
    [00077] Advantageously, the computer 18 is configured to detect a failure, when the comparison between the information measured by the position sensor 15 and the information measured by the second position sensor 19 is higher or lower than a predetermined limit.
    [00078] The invention is triggered by the state of the art, since it detects a failure directly at the level of the screw 2 and the safety rod 3 and not at the level of the high connection 8 of the secondary path or of the high connection 4 of the primary path.
    [00079] Considering that the invention does not need to position sensors between the actuator parts, the gap between the parts ("flutter") can be reduced, which is very advantageous.
    [00080] Indeed, it is known to the technician that the specifications on the “flutter” are very demanding.
    [00081] On the other hand, the proposed solution is simple and inexpensive. That is, notably due to the fact that the invention requires little additional sensors.
    [00082] There is also a significant reduction in aircraft mass, of the order of 7 kg in relation to certain solutions of the prior art, requiring shielded connection, which connects the sensors located on the level of the secondary high connection to the airplane computer.
    [00083] In addition, considering the simplicity of the required material, the invention is capable of detecting breakdowns even in difficult external conditions (low temperatures ...).
    [00084] A particular embodiment of the device 13 and the flight control actuator 12 according to the invention has been shown in figure 4.
    [00085] In this embodiment, the disconnect system 17 comprises a breakable pin 23. This breakable pin 23 has a cross-section calibrated to break at a predetermined load, corresponding to a mechanical effort exerted by the stem 3 on the screw 2, when a rupture of the primary path 1 (rupture of the screw 2 or another element of the primary pathway 1).
    [00086] In effect, according to the invention, the disconnection system 17 disconnects screw 2 from sensor 15, in case of relative movement of the stem 3 in relation to screw 2, when the primary path 1 is broken. previously, this displacement causes a mechanical effort exerted by the stem 3 on the screw 2, which allows, therefore, to have information about the relative movement of the stem 3 in relation to the screw 2.
    [00087] Below the load exerted by the rod 3 on the screw 2, when a rupture of the primary track 1, this pin 23 is calibrated so as not to break, in order to avoid false detections. This load limit is known as simulation and / or measurements in situ.
    [00088] Pin 23 can be placed in a notch that crosses screw 2 and stem 3, or be screwed into a grooved housing for this.
    [00089] In addition, the shaft of this ruptible pin 23 is subjected to a predetermined extraction load, allowing an extraction of pin 23 from screw 2, in the event of rupture of that pin 23. This extraction load is exerted by springs 20, orthogonally to screw 2.
    [00090] Pin 23 connects the screw to a pinion 22, which, via a gear train, activates the position sensor 15, for example an angular position sensor driven in rotation.
    [00091] In case of rupture of the primary track 1, and as shown in figure 5, the stem 3 exerts a mechanical effort above the rupture limit of pin 23, which causes the rupture of that pin 23. Due to the spring load exerted on pin 23, it is released from screw 3. Releasing pinion 22 becomes free in rotation, notably thanks to a bearing 21.
    [00092] Pinion 22 does not, therefore, recopy the rotation of screw 2 anymore, which means that sensor 15 no longer measures information representative of the angular position of screw 2., and is disconnected from that screw 2, which allows to detect a rupture of the primary pathway
    [00093] When computer 8 compares the signal measured by the position sensor 15 with the signal measured by the second position sensor 19, it detects a failure when the comparison is higher (or lower, if applicable) to a predetermined limit . Other disconnection systems 17 are feasible.
    [00094] The invention applies to any flight control actuator that has a primary path and a secondary path capable of resuming an effort, in the event of a primary path rupture and as previously described.
    [00095] The invention offers numerous advantages in terms of cost, simplicity, reliability and integration.
    权利要求:
    Claims (9)
    [0001]
    1. Device (13) for detecting the rupture of a primary path in a flight control actuator, said actuator featuring: - a primary path (1), comprising a rotating hollow screw (2); - a secondary track (10) that includes a safety rod (3) for resumption of effort that passes through the screw (2), said device (13) being characterized by the fact that it comprises - a position sensor (15), connected to the screw (2) to measure information representative of its angular position, and - a disconnection system (17), able to disconnect the screw position sensor (15), in case of relative displacement of the rod (3) in relation to the screw (2), when there is a rupture of the primary path (1).
    [0002]
    2. Device according to claim 1, characterized in that it additionally comprises a computer (18) configured to compare the information measured by the position sensor (15); and information representative of the angular position of the screw (2) measured by a second position sensor (19) independent of the disconnecting system (17).
    [0003]
    3. Device, according to claim 2, characterized by the fact that the computer (18) is configured to detect a rupture of the primary path (1), when the comparison is higher or lower than a predetermined limit.
    [0004]
    4. Device according to any one of claims 1 to 3, characterized by the fact that the disconnect system (17) is able to disconnect the sensor (15) from the screw position (2), when the rod (3) exerts a predetermined load on the screw (2), corresponding to a mechanical stress exerted by the rod (3) on the screw (2), when a screw rupture (2) or another element of the primary path (1 ).
    [0005]
    Device according to any one of claims 1 to 4, characterized in that the disconnecting system (17) comprises a breakable pin (23).
    [0006]
    6. Device according to claim 5, characterized by the fact that the breakable pin (23) has a section calibrated to break at a predetermined load, corresponding to a mechanical stress exerted by the rod (3) on the screw (2 ), when there is a rupture of the primary pathway (1).
    [0007]
    Device according to either of claims 5 or 6, characterized by the fact that the breakable pin (23) is subjected to a predetermined extraction load, allowing an extraction of the pin (23) from the screw (2), in case of rupture of this pin (23).
    [0008]
    Device according to any one of claims 1 to 7, characterized in that the position sensor (15) is an angular position sensor (15).
    [0009]
    9. Flight control actuator (12), comprising - a primary path (1), comprising a rotating hollow screw (2); - a secondary path (10) that includes a safety rod (3) for resumption of effort that passes through the screw (2), - the secondary path (10) being able to resume efforts exerted on the primary path (1), in case of rupture of the primary pathway (1); - said actuator (12) being characterized by the fact that it comprises a device (13) for detecting the rupture of the primary pathway, as defined in any one of claims 1 to 8.
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    EP3404395B1|2017-05-19|2020-01-29|Goodrich Actuation Systems SAS|Test method and apparatus for flight actuator check device|
    US10955033B2|2018-10-02|2021-03-23|Eaton Intelligent Power Limited|Linear actuator|
    EP3789294A1|2019-09-04|2021-03-10|Goodrich Actuation Systems SAS|Actuator|
    法律状态:
    2018-12-26| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-11-12| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-07-14| B09A| Decision: intention to grant|
    2020-11-17| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 14/04/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1053366A|FR2959482B1|2010-04-30|2010-04-30|DEVICE FOR DETECTING THE BREAKAGE OF A PRIMARY LANE IN A FLIGHT CONTROL ACTUATOR|
    FR1053366|2010-04-30|
    PCT/EP2011/055890|WO2011134799A1|2010-04-30|2011-04-14|Device for detecting the breakage of a primary path in a flight control actuator|
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