• 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 present invention relates to a landing gear provided with a landing gear leg (11) carrying at least one rocket (15), said rocket (15) being provided with a hollow member (20). An onboard device (25) comprises a bar (30) and at least one measuring assembly (35). This measuring assembly (35) comprises two devices, one of said equipment comprising a measuring member (45) and one of said equipment comprising a wall (50). One of said two devices is secured to the bar (30) and one of said two devices is secured to the hollow member (20), said onboard device (25) having a test system (60). This test system (60) has a moving means (61) generating on request a relative movement (MOV) between said equipment to detect a possible malfunction and to generate an alert if a malfunction is detected.
    公开号:FR3068004A1
    申请号:FR1770674
    申请日:2017-06-26
    公开日:2018-12-28
    发明作者:Stephane Bailly；Vincent SCHMIDT
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    Landing gear provided with an on-board load measurement device for an aircraft, and aircraft
    The present invention relates to a landing gear provided with an on-board load measurement device for an aircraft, and an aircraft such as for example a rotorcraft.
    Devices on board an aircraft are sometimes implemented to obtain an accurate measurement of the aircraft load, for example to determine its mass or even the position of its center of gravity before a flight.
    Some of these on-board devices assess the deformation of part of a landing gear. For example, sensors measure the deformation of a deformable member of an aircraft wheel landing gear to deduce the load applied to this wheel.
    As an illustration, document FR 2 875 598 presents an on-board device of this type. A rod having at one end an eddy current sensor is arranged in a wheel spindle to evaluate the deformation of this wheel spindle.
    When the aircraft rests on the ground, the wheel spindle tends to deform. The magnitude of the deformation is a function of the weight of the aircraft. Therefore, a sensor is used to assess this deformation, and to deduce the mass of the aircraft.
    Document EP 3121576 presents an on-board device provided with optical sensors.
    The document FR 1355098 is also known.
    Regardless of its construction, a sensor in an on-board load measurement device is liable to fail. Maintenance operations can be implemented to detect faults. For example, an operator tests the on-board device using lifting means to verify that the on-board device provides correct measurements.
    The document FR 2986322 describes an on-board device which is used in particular for measuring the mass of an aircraft. This on-board device comprises a bar arranged in a wheel spindle. One end of the bar comprises a first sensor performing a first measurement and a second sensor performing a second measurement. One of said sensors is used to determine information relating to a mass through the deformation of the rocket. In addition, a processing means is connected to the first sensor and to the second sensor to generate an alert when a sum of the first measurement and the second measurement is not constant.
    The processing means thus tends to allow monitoring of the on-board device without setting up heavy maintenance operations.
    The present invention relates to an on-board device for measuring a load at the level of an aircraft landing gear, said on-board device having a test system for checking the operation of this on-board device.
    The invention thus relates to a landing gear intended for an aircraft, for example a rotorcraft. This landing gear is provided with a landing gear carrying at least one rocket. This rocket carries at least one contact member. In addition, the rocket has a hollow element. The landing gear comprises an on-board device, this on-board device comprising a bar extending inside said hollow element from a fixing end towards a free end. The fixing end can be fixed to the rocket or to the landing gear.
    The on-board device comprises at least one measurement assembly, said measurement assembly comprising two pieces of equipment cooperating with each other to perform a measurement relating to a distance separating said bar and an internal face of said hollow element, one of said pieces of equipment comprising a measurement member belonging to a sensor arranged inside said hollow element, one of said equipment comprising a wall facing said sensor, said sensor emitting a signal as a function of said distance.
    One of said two pieces of equipment is attached to the bar and one of said two pieces of equipment is attached to the hollow element, said on-board device comprising a test system, said test system having a displacement means generating on request a relative movement between said two pieces of equipment. a measurement assembly, said test system having a computer connected to the sensor, said computer being configured to process said signal when said relative movement is operated in order to detect a possible malfunction of said sensor and to generate an alert if a malfunction is detected.
    The term "end" subsequently designates the end as such of the element concerned, and / or a section of the element concerned including said end. An organ can for example be divided into two end sections.
    Thus, the landing gear is provided with one or more measurement assembly (s) comprising a sensor housed inside the rocket, each sensor being able to assess a distance and a deformation of the rocket. Using the measurements made by the sensors, a computer in the on-board device can usually deduct the load applied to the landing gear along one or more axes.
    The expression "two pieces of equipment cooperating with each other" means that the two pieces of equipment in a measurement set participate in the measurement concerned. For example, the measuring member is an optical member targeting the wall. According to another example, the measuring member comprises a probe of an LVDT sensor, the probe being in contact with the wall. The acronym LVDT corresponds to the English expression "Linear Variable Differential Transformer".
    In addition, the on-board device is provided with a test system comprising a means of movement. The expression "means of movement generating on request a relative movement between said two pieces of equipment" means that if the means of movement is requested then the two pieces of equipment of a measurement unit perform a relative movement.
    Thus, the sensor measurement member and / or the associated wall moves (s) under the stress of the displacement means. At least one of the two devices moves at least between a nominal position to be used outside of the test phases and a test position. The displacement means can comprise a lever or equivalent maneuverable by an individual, an automatic actuator of the motor type for example, or any other means making it possible to make the transition between the nominal position and the test position.
    Due to this relative displacement between the two pieces of equipment in a measurement set, the signal emitted by the sensor varies. The computer scans this signal to process it, possibly taking into account other parameters such as the outside temperature, the attitude of the aircraft equipped with the landing gear, etc. In addition, the computer compares the result of the processing with a reference to determine whether the on-board device is in working condition.
    For example, the signal variation is translated into a position deviation compared to a range of theoretical values. Indeed, an individual can determine using tests the theoretical value of the deviation to be measured, and can express it in the form of a range of values. During a test, the computer determines the current deviation measured by the sensor and compares it with said range of values.
    Thus, the test system can make it possible to regularly test the on-board device autonomously in order to determine whether the on-board device is capable of fulfilling its function with the expected performance. If not, the computer can communicate with an alert device to generate a visual, and / or audible and / or tactile alert ...
    The test can also be carried out if required. According to variants, the test can be carried out independently, for example by requesting a motorized actuator when the aircraft starts.
    Optionally, the test can identify the state of degradation of the on-board device, by comparing the measurements made with said reference.
    According to one aspect, if it is impossible to move one of said pieces of equipment, the test system makes it possible to deduce the presence of a malfunction. This impossibility of obtaining the desired relative movement can indeed be caused by the presence of foreign bodies, ice, or an abnormal mechanical deformation of the mechanical parts binding the contact member to the structure.
    According to one aspect, the monitoring of the signals emitted by the sensors over a long period can make it possible to take into account the phenomena of wear of the sensors and / or interface parts, in order to solicit these sensors in a range which is not not likely to be impacted during wear of this sensor.
    The landing gear may further include one or more of the following features.
    According to a first embodiment, the wall is a portion of said hollow element, said wall being provided with said face, said sensor being fixed to the bar.
    Optionally, the hollow element extends from a first end integral with the landing gear towards a second end which carries at least one contact member.
    Alternatively, the rocket comprises a hollow bar which extends from a first end zone integral with the landing gear towards a second end zone which carries at least one contact member, said hollow element being fixed to said hollow bar and being arranged inside said hollow bar.
    According to this alternative, the hollow element is an intermediate piece arranged between the bar and the bar carrying at least one contact member. Such a bar is a relatively expensive important piece. Therefore, the use of an intermediate member forming the hollow element may make sense to avoid making modifications to an expensive member. The hollow element can also be replaced in the event of wear.
    According to a second embodiment, said wall is a part of the bar, said sensor being fixed to the hollow element.
    According to another aspect and independently of the embodiment, the sensor may comprise a body and said measuring member, said measuring member comprising a rod emerging from said body and carrying a feeler, said feeler being in contact against said wall, said stem being free in translation relative to the body in a first direction from the sensor to said wall. According to a first version of the displacement means, said displacement means is configured so that the relative movement is a translation of the measuring member relative to said wall.
    Therefore, the displacement means is configured to move the probe in translation relative to the body of the sensor. In the nominal position, the probe is in a predefined position relative to the body. On the other hand and in the test position, the probe is moved relative to the body by the means of displacement by a predetermined distance, for example by being brought closer to the body.
    According to a first variant of a first version, this displacement means comprises a finger movable in translation in a plane orthogonal to said first direction, said finger sliding in a slot in said body, said sensor comprising in said body a shoulder which is integral with said rod, a spring member pressing against said shoulder and tending to move said probe away from said body, said finger being configured to exert a force on said shoulder in order to bring said probe closer to said body during said translation of said finger in a first direction of translation.
    According to actuator actuator translation an aspect, the means of said "finger actuator being connected to said finger.
    movement may include a finger >> for convenience, said finger to move in
    Such a finger actuator may comprise a lever secured to the finger. This lever can be located outside the rocket so that it can be grasped and moved in translation by an operator.
    Alternatively or additionally, the finger actuator may include a motor, for example but not exclusively electric, capable of moving the finger in translation on request. Such an engine can be controlled by a computer or by a button operated by a pilot for example.
    According to a second variant of the first version, said sensor comprising a body and said measuring member, said measuring member comprising a rod leaving said body and carrying a probe, said probe being in contact against said wall, said rod being free in translation relative to the body in a first direction from the sensor to said wall, said displacement means may comprise an actuator called "rod actuator" for convenience to move said rod relative to the body.
    For example, the displacement means comprises an excitation device in each sensor, for example a solenoid, an ultrasonic motor, etc. This excitation device can be controlled by the computer to which the sensors are connected.
    Optionally, the rod actuator can coil fixed to the body and a magnetized coil zone being electrically supplied on command of said relative movement.
    include a rod, said request for
    According to a second version, the wall may have circumferentially at least one recess and at least one bump to generate a variation of said signal during said relative movement.
    The term "circumferentially" refers to a closed curve limiting an area of the wall. For example, the wall takes the form of a cylinder with a substantially circular base, that is to say near the recesses and bumps.
    The displacement means then makes it possible to rotate the sensor relative to the wall, or the wall relative to the sensor. For example, the sensor is fixed to the hollow element, and the wall is a part of the bar that can rotate on itself. According to another example, the wall is a part of the hollow element, the sensor being fixed to the bar and being able to rotate on itself.
    Regardless of this aspect, the recesses and the bumps form calibrated geometrical specificities of the wall making it possible to generate calibrated measurement deviations when passing from the nominal position to the test position. In the presence of several sensors, these geometrical specificities can be distributed differently between the different sensors.
    Optionally, said sensor comprises a body and said measuring member, said measuring member comprising a rod leaving said body and carrying a feeler, said feeler being in contact against said wall, said rod being free in translation relative to the body according to a first direction from the sensor to said wall.
    Furthermore, the displacement means can comprise a rotary actuator inducing the circulation of said feeler over said at least one recess and said at least one hump, said relative movement being a rotary movement, said rotary actuator driving said measuring member in rotation and / or said wall of a measuring assembly.
    A rotary actuator may include a lever or equivalent maneuverable by an individual. This lever can be located outside the rocket so that it can be grasped and moved in rotation by an operator or by interaction with a fixed part allowing movement during the train's maneuver.
    The rotary actuator can also be an automatic actuator of the motor type for example, or any other means making it possible to generate the required relative movement.
    The rotation generated by the rotary actuator allows the probe to slide in translation relative to the body when passing from a recess to a bump and vice versa.
    According to one aspect, the landing gear being able to comprise several measurement assemblies, said test system comprises at least one said displacement means generating on request a relative movement between the equipment of each measurement assembly.
    In this case, the test system can provide for soliciting the sensors one after the other.
    For example, the wall may have a bump or a cavity by sensor, the bumps being for example out of phase.
    Two sensors can also be mounted head to tail according to the teaching of document FR 2986322 to allow monitoring of the sum mentioned in this document.
    Furthermore, the invention relates to an aircraft which minus one landing gear according to the invention.
    features at
    The invention also relates to a method for detecting a failure of a measurement unit of a landing gear according to the invention.
    This process includes the following steps:
    - emission of a signal with said sensor during a said relative movement between said two devices, one of said two devices being moved from a nominal position to a test position,
    - processing of said signal for comparison with a reference,
    - issue of an alert when said processed signal does not correspond to said reference.
    Optionally, said operation of transmitting a signal with said sensor during a relative movement between said two pieces of equipment comprises the following operations:
    o transmission of said signal called "first signal" with said sensor when said equipment is in the nominal position, o displacement of one of said equipment in the test position, o transmission of said signal called "second signal" with said sensor following says displacement,
    Said processing may include an operation of determining a difference between the first signal and the second signal,
    Said comparison may include an operation of comparing said deviation to a range of values of said reference,
    Said issue of an alert can be carried out when said deviation does not belong to said range of values.
    Optionally, the first signal and the second signal are transformed before determining a deviation, in order to overcome the influence of external conditions by taking into account additional information such as the outside temperature, the speed of the device, the pressure of the tire carried by the rocket, the condition of the landing gear (retracted, extended, on the ground, in flight, etc.), the pressure of different chambers of a cylinder of the landing gear ...
    The invention and its advantages will appear in more detail in the context of the description which follows with examples given by way of illustration with reference to the appended figures which represent:
    FIG. 1, a front view of a rotorcraft provided with three landing gears according to the invention,
    FIGS. 2 to 12, diagrams illustrating landing gear according to the invention, and
    - Figure 13, a diagram illustrating a load measurement system.
    The elements present in several separate figures are assigned a single reference.
    FIG. 1 presents a view of an aircraft G according to the invention, for example a rotorcraft provided with a fuselage F. On the ground, this rotorcraft G rests on two landing gear 10 provided with a contact member with the ground and on a landing gear 10 provided with two bodies for contact with the ground. Each landing gear 10 is provided with a landing gear 11 carrying at least one rocket 15, said rocket 15 carrying a contact member
    2.
    The undercarriages 10 shown are of the "train wheel" type, each contact member therefore being a wheel. Such a contact member can however take the form of a skate, a ski, etc.
    Under the action of the mass of rotorcraft G, the rockets 15 of the landing gear 10 deform. By measuring these deformations, we can for example deduce by calculation the load exerted on each landing gear, the mass of the rotorcraft G as well as the position of its center of gravity.
    Thus, at least one landing gear or all of the landing gears are of the type of the invention having an on-board device 25 for measuring such deformation of a rocket.
    With reference to FIG. 2, the invention therefore relates in particular to a landing gear 10 provided with a train leg 11 and at least one rocket 15. The train leg may comprise a rod, a shock absorber, a jack ...
    Rocket 15 extends laterally from the strut to a contact member.
    The rocket 15 is provided with a hollow element 20. According to FIG. 2, this hollow element 20 can extend from a first end 21 secured to the landing gear towards a second end 22 carrying at least one contact member 2 .
    According to another possibility illustrated in FIG. 3, the rocket comprises said hollow element 20 but also a hollow bar 19. The hollow bar then extends from a first end zone 191 secured to the landing gear towards a second zone end 192 carrying at least one contact member 2. The hollow element 20 is then fixed inside INT of the hollow bar, and for example in particular at the level of the second end zone 192.
    Regardless of these possibilities and with reference to FIG. 2, under the action of the mass of the aircraft on the ground, the hollow element 20 moves and / or deforms.
    As a result, the on-board device 25 comprises a bar 30.
    This bar 30 extends inside INT of the hollow element 20 from a fixing end 31 to a free end 32.
    The fixing end 31 according to FIG. 2 is fixed to the train leg 11. However, this fixing end 31 can be fixed to an end portion of the rocket, or even of the hollow element 20. On the other hand, the free end 32 of the bar 30 is not secured to the hollow element or to the train leg, but remains within this hollow element.
    In addition, when no force is exerted on the hollow element 20, this hollow element 20 and the bar 30 are for example coaxial, both extending along the same axis of symmetry AX. For example, the bar 30 and the hollow element 20 are of substantially cylindrical shape.
    On the other hand, when the aircraft rests on the ground, the distance separating the free end 32 of the bar 30 and the hollow element 20 varies compared to an instant when the landing gear does not rest on the ground. This variation can be measured using at least one sensor to assess the load on the landing gear on the ground.
    Thus, the on-board device comprises at least one sensor 40 capable of measuring a distance between said bar 30 and an internal face 23 of the hollow element 20. Such a sensor 40 then comprises a measuring member 45 for carrying out said distance measurement. The sensor can take various forms, for example being an optical sensor.
    Alternatively but not exclusively, the sensor 40 can take the form of an LVDT sensor. An LVDT sensor is provided with a body 41 carrying measuring coils. In addition, the LVDT sensor is provided with a measuring member 45 partially leaving the body 41. This measuring member 45 can thus have a rod 46 carrying a probe 47. The rod 46 is provided in the body with a ferromagnetic core cooperating with the measuring coils. The rod 46 and the feeler are free in translation relative to the body in a first direction D1 going from the hollow element 20 and vice versa. The displacement of the rod 46 in translation relative to the body 41 generates a modification of the electrical signal emitted by the coils.
    Regardless of its nature, the sensor 40 can also comprise an electronic card 74, for example arranged in the landing gear or even in the bar. This electronic card 74 is connected to the measurement coils. The electronic card 74 filters the measured data to send information in the form of a signal, for example an electrical signal, to a computer 70 via a wired and / or non-wired link 8, this information being relative to the measured distance. For example, this information can take the form of a numerical value, or it can take the form of an electrical voltage.
    Such a computer 70 can comprise for example at least one unit 71 provided with at least one processor 72 and at least one memory unit 73. However, the computer can comprise for example at least one integrated circuit, at least one programmable system, at least one logic circuit, these examples not limiting the scope given to the expression "computer".
    The computer 70 can deduce from the information received and coming from the sensor data relating to the mass of the aircraft. The aircraft may include a single computer 70, or several computers communicating with each other.
    Furthermore, each measuring member 45 cooperates with a wall 50 of the landing gear to evaluate the distance separating the bar 30 and the internal face 23.
    Thus, the on-board device 25 comprises at least one measurement assembly 35 provided with two pieces of equipment. One of these two pieces of equipment is a measuring member 45 and the other piece of equipment is a wall 50 facing the sensor 40, and if necessary in contact with a probe 47 of the measuring member 45.
    One of said two pieces of equipment is secured to the bar 30 and the other piece of equipment is secured to the hollow element 20. According to a first embodiment, the wall 50 is thus a portion of the hollow element 20, the sensor 40 being fixed to the bar 30 According to a second embodiment, the wall is a part of the bar 30, the sensor 40 being fixed to the hollow element 20.
    The landing gear 10 may include several measurement assemblies.
    In addition, at least one measuring assembly can be confined in a sealed enclosure placed in the rocket 15.
    Whatever the embodiment, the on-board device includes a test system 60 in order to be able to test the operation of the sensors 40.
    This test system 60 can include the computer 70. In addition, the test system comprises a displacement means 61 which causes a relative movement MOV between the said items of equipment of each measurement assembly, successively or jointly for example.
    For example, the displacement means 61 is a manual means maneuverable directly by an operator or by interaction with a fixed part allowing movement during the train's maneuver, or an automatic means controlled by the computer.
    In addition, the test system 60 may include an activation means 76 which is connected to the computer 70 to initiate a test procedure. For example, the activation means 76 comprises a button, a tactile member, a visual control member, a voice control member, etc. When the activation means is requested by an operator, the computer 70 deduces that a test procedure is underway. The computer 70 can also be called up automatically, for example when the aircraft starts.
    In addition, an alert means 80 can be connected to the computer 70.
    In this context, Figures 2 to 12 illustrate various ways of carrying out the invention.
    According to FIGS. 2 to 7, the displacement means 61 can induce a relative MOV movement between the two pieces of equipment of a measuring assembly which takes the form of a rotary movement.
    With reference to FIG. 2, the displacement means 61 then includes a rotary actuator inducing rotation of the bar 30. Consequently, the displacement means 61 may comprise a rolling member 63 guiding the bar 30. For example, the member of bearing is interposed between the bar and a support integral with the train leg 11.
    The rotary actuator 60 can be a manual actuator 62 or an actuator controlled by the computer 70.
    According to another aspect, each sensor 40 can be fixed to the bar 30 or to the hollow element 20.
    In this context, FIG. 2 illustrates an exemplary embodiment where the rotary actuator takes the form of a lever 62 situated outside the rocket so that it can be grasped by an operator or by interaction with a fixed part allowing movement when maneuvering the train. The sensor 40 of a measuring assembly 35 is fixed to the bar 30, the wall 50 being a portion of the hollow element 20. In addition, the rotary actuator takes the form of a lever located outside the rocket to be entered by an operator.
    With reference to FIG. 4, the wall can then have, along the circumference of a face 36, a succession of recesses 37 and bumps 38.
    According to another aspect, the sensor 40 can be an optical sensor, or even an LVDT sensor. For example, the probe 47 of an LVDT sensor is then in contact against a recess in the nominal position and against a bump in the test position. The distance measured by the sensor 40 therefore varies between these two positions.
    Figures 5 and 6 then illustrate a landing gear 10 of the type of Figure 2 provided with two sensors 40 fixed to the bar 30. The rotary actuator takes the form of a motor 65 located outside the rocket 15 and connected to the actuator.
    With reference to FIG. 6, the two sensors can be LVDT phase-shifted sensors. Thus, one sensor can be in contact with a recess in the nominal position, while the other sensor is in abutment against a bump.
    FIG. 7 illustrates an exemplary embodiment in which the rotary actuator takes the form of a lever 62 situated outside the rocket 15 so that it can be grasped by an operator. The sensor 40 of a measuring assembly is fixed to the hollow element 20, the wall 50 being a portion of the bar 30. In addition, the rotary actuator takes the form of a lever located outside the rocket 15 so that it can be entered by an operator. Alternatively. An engine is possible
    According to another aspect, the sensor 40 can be an LVDT sensor.
    According to FIGS. 8 to 12, the displacement means 61 can induce a relative movement MOV between the two pieces of equipment of a measuring assembly which takes the form of a translational movement of the measuring member of the sensor 40 relative to the wall 50 in a first direction D1.
    The displacement means 61 then includes a translational actuator inducing a translation of the measuring member. The translational actuator can be a manual actuator or an actuator controlled by the computer 70.
    According to another aspect, each sensor can be fixed to the bar 30 or to the hollow element 20.
    In this context, FIG. 7 illustrates an exemplary embodiment where the sensor of a measuring assembly is fixed to the bar 30, the wall 50 being a portion of the hollow element 20. Each sensor is an LVDT sensor.
    The translational actuator comprises a finger 66 which is movable in translation in a plane P1 orthogonal to the first direction D1. For example, this finger can slide in a longitudinal groove of the bar 30. In addition, the finger 66 can slide in a slot 42 of the body 41 of each sensor.
    In addition and with reference to FIG. 9, each sensor 40 has a shoulder 48 which is integral with a rod 46 carrying a feeler 47. A spring member 43 bears against the shoulder 48 to tend to move the feeler 47 away from the body 41, tending to press the shoulder 48 against a stop 49 of the body 41. The finger 66 is thus configured to exert a force on the shoulder 48 in order to bring the feeler 47 closer to the body 41 during translation of the finger 66 in a first direction of translation D2.
    Referring to Figure 8, when the finger 66 is moved in this first direction of translation, all the probes are moved one after the other in their test positions. A movement of the finger 66 in a second direction opposite to the first direction allows the feelers to return to their nominal positions.
    In addition, the translational actuator can take the form of a lever located outside the rocket 15 so that it can be grasped by an operator. However, a motorized finger actuator is possible.
    According to the example of FIG. 10, such a motorized finger actuator 68 is used.
    Furthermore, this FIG. 10 illustrates the possibility of fixing each sensor 40 to the hollow element 20.
    According to FIG. 11, a rod actuator 69 is associated with an LVDT sensor to move the rod 46 relative to the body 41.
    For example, such a rod actuator 69 may comprise a coil 75 fixed to the body 41 and a magnetic zone 77 of the rod 46, the coil 75 being electrically supplied by the electronic card 74 at the request of the computer to control said relative MOV movement.
    FIG. 12 illustrates the possibility of fixing the bar 30 to the free end of the hollow element 20.
    FIG. 13 presents a diagram illustrating the aircraft 1 according to the invention provided with three landing gears 10. Each landing gear 10 comprises a hollow element 20 in which a bar 30 is inserted. Each landing gear 10 is furthermore provided with at least one sensor 40 cooperating with a wall 50. In addition, each landing gear comprises at least one test system 60 provided with displacement means 61.
    Each sensor 40 communicates with a computer 70 via a wired and / or non-wired connection. According to a first variant, a cable connects each sensor directly to the computer 70. However, according to a second variant, each sensor is connected to a wireless transceiver E, for example of the microwave type, arranged on the landing gear. A transceiver electrically powers a sensor and transmits information from the sensor 40 to the computer 70.
    In a nominal operating mode, the computer determines the total mass of the aircraft as well as the position of its center of gravity by usual methods using the signals transmitted by the sensors. Optionally, the computer can take into account additional information provided by additional measurement means M1. For example, complementary measurement means M1 transmit to the computer 70 two secondary signals respectively relating to the pitch and roll angles of the aircraft with respect to the ground. These complementary measurement means M1 may in particular comprise two inclinometers, which respectively measure the pitch and roll angles, dedicated specifically to this application or any other means already present on the aircraft and fulfilling this function.
    To test the landing gear, a test mode is engaged. This test mode can be engaged when the aircraft starts, or even at the request of a pilot via an activation means 76.
    The displacement means are then requested either by an operator or by the computer 70 according to the variant.
    Consequently and for each landing gear 10, each displacement means displaces one with respect to the other the two pieces of equipment of a measuring assembly. The computer 70 is then configured to process the signal emitted by the sensor of this measurement assembly in order to detect a possible malfunction and to generate an alert if a malfunction is detected.
    In particular and according to the method of the invention, mobile equipment of a measuring assembly is effectively placed in a nominal position POS1 before the start of the test. The sensor of this measurement assembly then emits a signal called the first signal for convenience. The computer can deduce a first distance from it, possibly by taking into account additional information coming from complementary M2 systems. Such complementary systems may include an outside temperature sensor, a temperature sensor arranged in a rocket, a sensor measuring the speed of the aircraft, a sensor measuring the pressure of the tire carried by the rocket, a sensor indicating the state of the landing gear (retracted, extended, on the ground, in flight, etc.), a sensor measuring the pressure of different chambers of a landing gear cylinder ...
    During the test, this mobile equipment is moved by the means for moving from the nominal position POS1 to the test position POS2.
    The computer processes the signal received for comparison with a reference and to issue an alert when said processed signal does not correspond to said reference. For example, an alert means 80 is connected to the computer to issue said alert.
    More specifically, during the relative movement induced by the displacement means, the signal emitted by the sensor varies. This signal takes the form of a second signal for convenience. The computer deduces a second distance from it, possibly taking into account said additional information.
    During a processing operation, the computer can determine a difference between the first signal and the second signal, namely between the first distance and the second distance.
    The computer then compares this deviation to a range of values of said reference, and issues an alert if the deviation is not included in said range.
    At the end of the test, the equipment is repositioned in the nominal position.
    Naturally, the present invention is subject to numerous variations as to its implementation. Although several embodiments have been described, it is understood that it is not conceivable to identify exhaustively all the possible modes. It is of course conceivable to replace a means described by an equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (16)
    [1" id="c-fr-0001]
    1. Landing gear (10) intended for an aircraft (G), said landing gear (10) being provided with a landing gear leg (11) carrying at least one rocket (15), said rocket (15) being provided with a hollow element (20), said landing gear (10) comprising an on-board device (25), said on-board device (25) comprising a bar (30) extending inside (INT) of said hollow element (20) from a fixing end (31) to a free end (32), said on-board device (25) comprising at least one measurement assembly (35), said measurement assembly (35) comprising two cooperating equipment between them to make a measurement relating to a distance separating said bar (30) and an internal face (23) of said hollow element (20), one of said pieces of equipment comprising a measuring member (45) belonging to a sensor (40) arranged inside said hollow element (20), one of said pieces of equipment comprising a facing wall (50) of said sensor (40), said sensor (40) emitting a signal depending on said distance, characterized in that one of said two pieces of equipment is secured to the bar (30) and one of said two pieces of equipment is secured to the hollow element (20) , said on-board device (25) comprising a test system (60), said test system (60) having a displacement means (61) generating on request a relative movement (MOV) between said two pieces of equipment of a measuring system , said test system having a computer (70) connected to the sensor (40), said computer (70) being configured to process said signal when a said relative movement (MOV) is operated in order to detect a possible malfunction of said sensor and for generate an alert if a malfunction is detected.
    [2" id="c-fr-0002]
    2. Landing gear according to claim 1, characterized in that said wall (50) is a portion of said hollow element (20), said wall being provided with said face, said sensor (40) being fixed to the bar (30) .
    [3" id="c-fr-0003]
    3. Landing gear according to claim 2, characterized in that said hollow element (20) extends from a first end (21) integral with the landing gear leg (11) towards a second end (22) which carries at least one contact member (2).
    [4" id="c-fr-0004]
    4. Landing gear according to claim 2, characterized in that said rocket (15) comprises a hollow bar (19) which extends from a first end zone integral with the train leg (11) towards a second end zone which carries at least one contact member (2), said hollow member (20) being fixed to said hollow bar (19) and being arranged inside said hollow bar (1 9).
    [5" id="c-fr-0005]
    5. Landing gear according to claim 1, characterized in that said wall (50) is a part of said bar (30), said sensor (40) being fixed to the hollow element (20).
    [6" id="c-fr-0006]
    6. Landing gear according to any one of claims 1 to 5, characterized in that said sensor (40) comprising a body (41) and said measuring member (45), said measuring member (45) comprising a rod (46) coming out of said body (41) and carrying a feeler (47), said feeler (47) being in contact against said wall (50), said rod (46) being free in translation relative to the body (41) according to a first direction (D1) going from the sensor (40) towards said wall (50), said relative movement (MOV) is a translation of the measuring member (45) relative to said wall (50).
    [7" id="c-fr-0007]
    7. Landing gear according to claim 6, characterized in that said displacement means (61) comprises a finger (66) movable in translation in a plane (P1) orthogonal to said first direction (D1), said finger (66 ) sliding in a slot (42) of said body (41), said sensor (40) comprising in said body (41) a shoulder (48) which is integral with said rod (46), a spring member (43) being in abutment against said shoulder (48) and tending to move said probe (47) away from said body (41), said finger (66) being configured to exert a force on said shoulder (48) in order to bring said probe (47) closer to said body (41 ) during a translation of said finger (66) in a first direction of translation (D2).
    [8" id="c-fr-0008]
    8. Landing gear according to claim 7, characterized in that said displacement means (61) comprises a finger actuator (68) connected to the finger (66) to move said finger (66) in translation.
    [9" id="c-fr-0009]
    9. Landing gear according to any one of claims 1 to 6, characterized in that, said sensor (40) comprising a body (41) and said measuring member (45), said measuring member (45) comprising a rod (46) leaving said body (41) and carrying a feeler (47), said feeler (47) being in contact with said wall (50), said rod (46) being free in translation relative to the body (41) in a first direction (D1) going from the sensor (40) towards said wall (50), said displacement means (61) comprises a rod actuator (69) for displacing said rod (46) relative to the body (41).
    [10" id="c-fr-0010]
    10. Landing gear according to claim 9, characterized in that said rod actuator (69) comprises a coil (75) fixed to the body (41) and a magnetized area (77) of the rod (46), said coil (75) being electrically supplied on request to control said relative movement (MOV).
    [11" id="c-fr-0011]
    11. Landing gear according to any one of claims 1 to 6, characterized in that said wall (50) has circumferentially at least one recess (37) and at least one hump (38) to generate a variation of said signal during of said relative movement (MOV).
    [12" id="c-fr-0012]
    12. Landing gear according to claim 11, characterized in that the displacement means (61) comprises a rotary actuator (62,65) inducing the circulation of said feeler (47) on said at least one recess (37) and said at least one bump (38), said relative movement (MOV) being a rotary movement, said rotary actuator rotating said measuring member and / or said wall of a measuring assembly.
    [13" id="c-fr-0013]
    13. Landing gear according to any one of claims 1 to 1 2, characterized in that said landing gear (10) comprising several measuring assemblies, said test system (60) comprises at least one said means of displacement (61) generating, on request, a relative movement (MOV) between the devices of each measuring assembly (35).
    [14" id="c-fr-0014]
    14. Aircraft (G), characterized in that said aircraft (G) comprises at least one landing gear (10) according to any one of claims 1 to
    13.
    [15" id="c-fr-0015]
    15. Method for detecting a failure of a measuring assembly of a landing gear (10) according to any one of claims 1 to 1 3, characterized in that said method comprises the following steps:
    - emission of a signal with said sensor (40) during a said relative movement (MOV) between said two devices, one of said two devices being moved from a nominal position (POS1) to a test position (POS2),
    - processing of said signal for comparison with a reference,
    - issue of an alert when said processed signal does not correspond to said reference.
    [16" id="c-fr-0016]
    16. Method according to claim 15, characterized in that:
    - said operation of transmitting a signal with said sensor (40) during a relative movement between said two pieces of equipment comprises the following operations:
    o transmission of said signal called "first signal" with said sensor (40) when said equipment is in the nominal position (POS1), o movement of one of said equipment in the test position (POS2), o transmission of said signal called " second signal >> with said sensor following said displacement,
    - said processing includes the determination of a difference between the first signal and the second signal,
    said comparison includes a step of comparing said deviation with a range of values of said reference,
    - said emission being carried out when said deviation does not belong to said range of values.
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    同族专利:
    公开号 | 公开日
    EP3421357B1|2019-08-28|
    US10816390B2|2020-10-27|
    CN109110107A|2019-01-01|
    EP3421357A1|2019-01-02|
    US20180372535A1|2018-12-27|
    FR3068004B1|2019-07-19|
    CA3005505C|2019-11-05|
    CN109110107B|2021-10-15|
    KR101993312B1|2019-06-26|
    CA3005505A1|2018-12-26|
    KR20190001510A|2019-01-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB2144225A|1983-07-27|1985-02-27|Sundstrand Data Control|Transducer memory circuit|
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    EP0482289A2|1990-10-20|1992-04-29|VDO Luftfahrtgeräte Werk GmbH|Mounting of at least one sensor on a landing gear of an aeroplane for measuring the weight and the centre of gravity of the aeroplane|
    FR2875598A1|2004-09-23|2006-03-24|Eurocopter France|Aircraft`s e.g. helicopter, centre of gravity position and mass measuring device, has deformable unit with bar having eddy current sensor supplied with power by transceiver, and inclinometers finding aircraft`s pitch and roll angles|
    FR2986322A1|2012-01-30|2013-08-02|Eurocopter France|ON-BOARD DEVICE FOR MEASURING THE MASS AND THE POSITION OF THE CENTER OF GRAVITY OF AN AIRCRAFT|
    US20170158311A1|2012-06-05|2017-06-08|Textron Innovations Inc.|Takeoff/landing touchdown protection management system|CN109878759A|2019-03-29|2019-06-14|中国飞机强度研究所|Aircraft testing device, constraint and loading method, button weight and loading method|
    CN110104207A|2019-05-09|2019-08-09|中国飞机强度研究所|A kind of differential type loading method and system|FR1355098A|1962-06-08|1964-03-13|Cleveland Pneumatic Ind|Installation for determining the weight and center of gravity of an airplane|
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    GB2540430A|2015-07-17|2017-01-18|Airbus Operations Ltd|Calibration of transducers|
    CN106202802B|2016-07-22|2019-02-12|中国航空工业集团公司西安飞机设计研究所|A kind of undercarriage course stiffness simulation method|FR3062722B1|2017-02-03|2019-04-19|Safran Landing Systems|TARGET OF MAGNETIC MEASUREMENT|
    FR3062636B1|2017-02-03|2021-04-16|Safran Landing Systems|AIRCRAFT LANDING|
    US10466093B2|2017-07-12|2019-11-05|Sikorsky Aircraft Corporation|Failsafe electromechanical weight on wheels detection|
    CN109866941A|2019-03-28|2019-06-11|中国飞机强度研究所|The accurate applying method of load during undercarriage large deformation following loading|
    法律状态:
    2018-12-28| PLSC| Search report ready|Effective date: 20181228 |
    2020-06-19| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1770674A|FR3068004B1|2017-06-26|2017-06-26|LANDING TRAIN WITH AN ON-LINE LOAD MEASURING DEVICE FOR AN AIRCRAFT AND AIRCRAFT|
    FR1770674|2017-06-26|FR1770674A| FR3068004B1|2017-06-26|2017-06-26|LANDING TRAIN WITH AN ON-LINE LOAD MEASURING DEVICE FOR AN AIRCRAFT AND AIRCRAFT|
    EP18173189.4A| EP3421357B1|2017-06-26|2018-05-18|Landing gear provided with an on-board device for measuring the load of an aircraft, and aircraft|
    CA3005505A| CA3005505C|2017-06-26|2018-05-18|Landing gear equipped with an onboard load-measurement device for an aircraft, aircraft|
    KR1020180065009A| KR101993312B1|2017-06-26|2018-06-05|An aircraft undercarriage having an onboard load-measuring device, and an aircraft|
    CN201810671759.0A| CN109110107B|2017-06-26|2018-06-26|Aircraft landing gear with on-board load measuring device and aircraft|
    US16/018,264| US10816390B2|2017-06-26|2018-06-26|Aircraft undercarriage having an onboard load-measuring device, and an aircraft|
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