• 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 device for measuring the angular positions of a blade element (2) of a rotorcraft, said blade element (2) being arranged mobile in rotation with respect to a hub (4) of rotor (5) around at least one axis of rotation (6, 7, 8). The invention also relates to a rotorcraft equipped with such a measuring device and a corresponding measuring method.
    公开号:FR3029284A1
    申请号:FR1402694
    申请日:2014-11-27
    公开日:2016-06-03
    发明作者:Julien Hocquette
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a measuring device for determining the angular positions of at least one axis of a rotorcraft blade element relative to a rotor hub, associated rotorcraft and corresponding measurement method. rotation of a rotorcraft blade member relative to a hub of a main lift and propulsion rotor or an anti-torque rotor. Indeed, during the rotation of the hub of a rotorcraft rotor 10 such as for example a helicopter, a blade member is generally able to pivot, in a rotating orthogonal reference linked to the hub, about three axes of rotation. A first axis of rotation is called the pitch axis and makes it possible to modify the aerodynamic incidence of the blades, as a result of the aerodynamic forces on the blades, and is responsible for the lift and traction exerted by the rotor on the rotorcraft. . Such a pitch axis therefore extends substantially parallel to a longitudinal direction corresponding to the span of the blade member. A second axis of rotation is called a flapping axis and allows, at a free end of the blade member, to move substantially perpendicular to the plane of rotation of the rotor. Such a beat axis is therefore substantially inscribed in the plane of rotation of the rotor blades. A third axis of rotation is referred to as the screen axis and is arranged substantially perpendicular to the first and second axes of rotation of the blade member.
    [0002] The invention therefore relates more particularly to a measuring device for automatically recording and recording data relating to these angular positions which are variable during rotation of the rotor, including during each revolution.
    [0003] Indeed, the evaluation of the rotational movements of a rotor blade member for a limited period in the predetermined time or during the entire life of the rotorcraft is particularly interesting. Such a measurement of these rotational movements, under normal flight conditions, makes it possible to understand and evaluate very precisely the dynamic stresses to which the rotorcraft rotor is subjected. In general, for measuring the angular positions of a blade element, it is known to use optical sensors as described in document JP 2010149602. This document proposes a measuring device in which a light source is placed on the blade and a detector is placed on the hub. Such a solution therefore only makes it possible to measure the flapping angle of the blade element. Such a device then makes it necessary to equip the blade element with a light source that must be housed and secured to the blade element. Such an integration of the light source then makes it necessary to modify the structural design of the blade element. In addition, it is also necessary to route electrical energy to this source so that it can emit light. However, such a routing of electricity is particularly complex to achieve at a rotorcraft rotor, that is to say in rotating axes. In addition, the relative movements between the different parts of the rotor can produce wear of the electrical contacts and make such a solution unreliable over time. In addition, such a light source, as small as it is, generates an additional rotating mass and then requires a rebalancing of the rotor. The present invention therefore aims to provide a measuring device, a rotorcraft and a method to overcome the limitations mentioned above. The measuring device can thus make it possible to maintain an existing structural design of the rotor blade elements and to provide a simple, safe, effective and reliable solution over time, so as to measure the angular positions of a blade element by relative to an orthogonal reference linked to the hub of said rotor. The invention therefore relates to a device for measuring the angular positions of a rotorcraft blade element, the blade element being arranged mobile in rotation with respect to a rotor hub around at least one axis of rotation. In other words, the blade member has at least one degree of freedom in rotation with respect to the hub of the rotor. According to the invention, the device is characterized in that it comprises: at least one checkerboard pattern adapted to be secured to the blade member, the checkerboard pattern comprising two groups of surfaces respectively having luminance factors; different, each surface of a first group having a first luminance factor and being juxtaposed with at least one surface of a second group having a second luminance factor, the first luminance factor being greater than the second luminance factor; least one camera capable of taking a plurality of images of the checkered pattern as a function of time, the camera being able to be secured to the hub, a synchronization member which makes it possible to assign to each image taken by the camera a parameter temporal function of the azimuth angle of the rotor, - a memory for recording each image with the corresponding temporal parameter, - a calculator for automatically terminating the angular positions of the blade member in at least one axis of rotation from the images of the checkered pattern. In other words, the device according to the invention makes it possible to determine the different positions of a blade element by means of a check pattern on a rigid part of a blade and almost indeformable under normal stresses of the rotor. Thus, such a rigid portion may be advantageously formed by a foot of the blade member and the checkered pattern be formed by a printed film for example of plastic or cellulosic material. Furthermore, in order to secure the checkered pattern to the blade element, various solutions are envisaged, and in particular solidarisations using a gluing intermediate, an electrostatic and / or magnetic force, self-gripping strips provided with loops and hooks, or latching means. Under these conditions, the first luminance factor of the first group of surfaces of the checkered pattern is advantageously chosen close to the number 1 because the surfaces of the first group are preferably chosen to be white in color. On the contrary, the second luminance factor of the second group of surfaces of the checkered pattern is advantageously chosen close to the number 0 because the surfaces of the second group are preferably chosen black. A strong contrast between the surfaces of the first and second groups thus makes it possible to guarantee easy processing of the images coming from the camera and thus a maximum precision in the determination of angular positions of the blade element. The camera is thus arranged on the hub of the rotor and oriented to allow to constantly "observe" the checkered pattern in its field of vision. Such a camera is secured by embedding with the hub by securing means such as bolts, straps, rivets and the like. In addition, the synchronization member makes it possible, depending on the instant at which the image is taken, to determine an azimuth position of the image, and consequently to make the curve of the angular positions of the blade element. depending on the azimuth positions of the rotor. The calculator determines the relative positions of the checkered pattern in the space for all the images from the camera. To do this, an operator may in particular manually define an absolute position of the checkered pattern in an image corresponding to a predetermined position of the considered blade member. In practice, such a predetermined position is obtained by positioning for example the checkered pattern so that a succession of juxtaposed surfaces constituting it is aligned with a line forming the horizon when the rotor is at a standstill. Another technique may be to use a precise protractor to manually measure the position of the checkered pattern relative to a known repository, such as for example a repository in a shed. Advantageously, the calculator can determine the angular positions of the blade element along three axes of rotation forming an orthogonal reference linked to the hub, the orthogonal coordinate system comprising a first axis, called the pitch axis, a second axis, called the beat axis, and a third axis, called the halftone axis. In other words, the measuring device makes it possible to identify the angular positions of the blade element around the three previously described axes of rotation of the blade element relative to the hub of the rotor. The measuring device thus makes it possible to measure both the pitch angle 6, the beat angle 13 and the raster angle δ of a blade element as a function of the rotor azimuth angle tl) .
    [0004] The synchronization member can in turn come in various forms. According to a first embodiment, the synchronization member may comprise a sensor for detecting each revolution of the rotor.
    [0005] In this case, the azimuth reference is given by the "top" of a rotor position sensor provided after each 360 degree rotation thereof. The images from the camera are then stored in the memory simultaneously with the signal from this sensor. Such a sensor may in particular be magnetic or optical type to identify each new rotor tower. Thus, knowing on the one hand, the acquisition frequency Fs of the camera and, on the other hand, the rotational angular velocity co of the rotor, it is possible to calculate the azimuth angle Wi of each image according to the formula : Fs According to a second embodiment, the synchronization member may use a fixed element relative to the fuselage of the rotorcraft and present on the images from the camera such as for example a tail boom of the rotorcraft. Indeed, such a tail beam appears once in the field of view of the camera at each of its revolutions. It then corresponds to an azimuth angle WO = 0 °. Similarly, the computer and the memory can be in various forms and be integral members of the rotorcraft or removable members. Thus, according to a first configuration of the invention, the computer can be arranged on the rotorcraft. In this case, the memory is also advantageously arranged on the rotorcraft and the data it contains are directly used by the computer to determine the angular positions of the blade element as a function of the azimuth angle of the rotor. Furthermore, and according to a first variant of the first configuration, the computer may be adapted to be secured to the hub of the rotor near the camera. In other words, the computer rotates with the rotor relative to the fuselage of the rotorcraft. According to a second variant of the first configuration, the computer may be adapted to be arranged on a fixed part with respect to a fuselage of the rotorcraft.
    [0006] In this case, the computer is arranged immovably with respect to the fuselage of the rotorcraft Finally, according to a second configuration of the invention, the computer can be deported from the rotorcraft.
    [0007] Thus, the exploitation of the images making it possible to measure the angular positions of the rotorcraft blade element is carried out on an auxiliary member, such as a computer that is not loaded on the rotorcraft. Advantageously in this case, the memory may be of the removable type and cooperate with an interface secured to the camera. Indeed, once the images are made, they are stored in the memory while being synchronized with the temporal parameter. The memory can then be removable and be in the form of a memory card for example which is extracted from a read / write interface arranged directly at the camera. This map is then introduced into another interface connected to a computer external to the rotorcraft. The data from the images of the camera are therefore in this case exploited by a computer independent of the rotorcraft. Moreover, the checkerboard pattern may comprise in practice: at least three lines formed by an alternation of surfaces having different luminance factors, the lines being parallel to each other and arranged on the blade element in a direction parallel to a pitch axis of the blade element, and, - at least three columns formed by an alternation of surfaces having different luminance factors, the columns being parallel to each other and arranged on the blade element in a direction parallel to a beat axis of the blade member. In other words, the checker pattern is arranged on the blade member so that the lines of the pattern are parallel to a direction corresponding to the span and that the columns are perpendicular to that same direction. According to a particular embodiment, the check pattern may comprise five lines formed by an alternation of surfaces having different luminance factors and nine columns formed by an alternation of surfaces having different luminance factors. Such a checkerboard pattern makes it possible to guarantee optimal exploitation of the images taken by the camera to determine the angular positions of the blade element on a rotor turn. Advantageously, the checkered pattern may comprise an entourage whose luminance factor is substantially equal to the first luminance factor of the first group of surfaces. In other words, the entourage of the lines and columns is substantially white in color and makes it possible to clearly identify each row and column of the pattern. In practice, the surfaces of the first group and the second group may be square. In this way, all the surfaces of the first and second groups have the same dimensions in length and width. Such an arrangement then makes it possible to simplify an algorithm for recognizing the inner corners of the pattern defined by their position (px, py) in pixels in the image. To do this, it is sufficient to indicate the number of surfaces in the X and Y directions of a direct orthogonal reference associated with the checkered pattern. According to a particular embodiment, the check pattern 5 may comprise surfaces of the second group arranged at each of the corners of the shape defined by the two groups of surfaces. Thus, the surfaces of the first group and the surfaces of the second group are positioned to form a rectangle or square having a surface of the second group at each of its corners. Such an arrangement, combined with a surround whose luminance factor is substantially equal to the first luminance factor, thus makes it possible to ensure optimum recognition of the corners of the shape defined by all the surfaces of the first and second groups. The processing of the images from the camera then makes it possible to recognize the positions of the corners of the checkered pattern and the corners of each surface constituting it and thus to determine the mathematical transformation for determining the angular positions of the corresponding blade member. The invention also relates to a remarkable rotorcraft in that it comprises a device for measuring the angular positions of a blade element relative to a rotor hub as described above. In other words, the invention is not limited to a device for measuring the angular positions of a rotorcraft blade element. It also relates to a rotorcraft comprising: at least one checkerboard pattern secured to the blade element, the checkerboard pattern having two groups of surfaces respectively having different luminance factors, each surface of a first group having a first factor luminance and being juxtaposed with at least one surface of a second group having a second luminance factor, the first luminance factor being greater than the second luminance factor; at least one camera capable of taking a plurality of images of the checkered pattern as a function of time, the camera being secured to the hub; a synchronization member which makes it possible to assign to each image taken by the camera a temporal parameter which is a function of the azimuth angle of said rotor; a memory enabling each image to be recorded with the corresponding temporal parameter; a calculator for automatically determining the angular positions of the blade element according to at least one axis of rotation from the images of the checkered pattern. Such a rotorcraft thus makes it possible to produce a plurality of images 20 of a checkered pattern secured to the blade member. It then makes it possible to process these images so as to recognize the positions of the corners of the pattern and the corners of each surface constituting it. The present invention also relates to the method of measuring the angular positions according to at least one axis of rotation 25 of a rotorcraft blade element relative to a rotor hub. According to the invention, such a method is characterized in that it comprises the steps of: - attaching at least one checkered pattern to the blade member, the checkered pattern having two groups of surfaces respectively presenting factors different luminances, each surface of a first group having a first luminance factor and being juxtaposed with at least one surface of a second group having a second luminance factor, the first luminance factor being greater than the second luminance factor; - Secure with the hub at least one camera capable of taking a plurality of images of the checkered pattern as a function of time; performing a plurality of images of the checkered pattern during a rotation of said rotor; synchronizing each image made by the camera with a temporal parameter that is a function of the azimuth angle of said rotor; - save each image with the corresponding time parameter; automatically determining the angular positions of the blade element according to at least one axis of rotation from the images of the checkered pattern. In other words, the invention also relates to a method for measuring the angular positions of a blade member relative to a rotor hub. According to this method, a plurality of images of a checkered pattern secured to the blade member are made and then these images are processed so as to recognize the positions of the corners of the pattern and the corners of each surface constituting it. According to a particular embodiment, the measurement method may include a step for determining the angular positions of the blade member along three axes of rotation forming an orthogonal reference linked to the hub, the orthogonal reference comprising a first axis, said axis. of step, a second axis, said beat axis and a third axis, said axis of halftone.
    [0008] In this way, the method makes it possible to measure as a function of time the positions in the space of a blade element with respect to a rotor hub. The measurement method thus makes it possible to identify the angular positions according to three degrees of freedom in rotation of the blade element with respect to the hub. Advantageously, the measuring method can make between 5 and 45 images of the checkered pattern on a rotor turn. Thus, such a method can use a camera whose acquisition frequency is between 25 frames / second and 200 frames / second. Depending on the rotational speed of the rotor, such a camera makes it possible, for example, to produce images of the checkered pattern every 50 degrees per revolution at a minimum and every 5 degrees per revolution at most. The invention and its advantages will appear in more detail in the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, a top view of a rotorcraft equipped with 2, a block diagram of a measuring device according to the invention; FIG. 3, a partial perspective view of a rotorcraft rotor according to a first variant of the first configuration, according to the invention, - Figure 4, a top view of a rotorcraft rotor blade element equipped with a checkerboard pattern, according to the invention, - the figure 5, a side view of a rotorcraft equipped with a measuring device according to a second variant of the first configuration, according to the invention, - Figures 6 to 9, different images of a checkered pattern obtained with the camera of the measuring device, according to the invention. The elements present in several separate figures are assigned a single reference. As already mentioned above, the invention relates to the field of rotorcraft and, more particularly, to the field of devices for measuring the angular positions of the blade elements of a rotorcraft rotor. Thus, and as shown in FIG. 1, the measuring device 1 makes it possible to determine the angular positions of the blade element 2 of a rotor 5 around at least one axis of rotation with respect to the hub 4 of the rotor. In addition, as shown in FIGS. 2 and 3, the device 1 fitted to the rotorcraft 3 comprises a checkered pattern 10, a camera 20, a synchronization member 30, memory 40 and a computer 50. The measuring device 1 thus makes it possible to measure the angular positions of the blade member 2 according to at least one of the three axes of rotation 6, 7 and 8 forming an orthogonal reference. Such an orthogonal reference comprises a first axis 6, 25 said axis of pitch, a second axis 7, said beat axis and a third axis 8, said dither axis. Such a checkered pattern 10 is thus able to be secured to a rigid part of a blade member 2. The camera 20 is secured to the hub 4 of the rotor 5 and makes it possible to take a plurality of images of the pattern Each synchronizing member 30, which may for example comprise a sensor 31, makes it possible to assign to each image coming from the camera 20 a temporal parameter which is a function of the angle. of the rotor 5. The images from the camera 20 are then stored in a memory 40 via an interface 21 which may in particular be in the form of a card reader or a communication port when the memory 40 is removable type 10, such as a memory card or a USB key for example. Finally, a calculator 50 makes it possible to determine the measurement of the angular positions of the blade element 2 from the images of the checkered pattern 10 secured to it. As shown in FIG. 3, according to a first variant 15 of a first configuration of the invention, the computer 50 may be integral with the camera 20, and consequently be arranged at the hub 4 of the rotor 5. As shown in FIG. As shown in FIGS. 3 and 4, the check pattern 10 has two groups of surfaces 11 and 12 having different luminance factors, respectively. The surfaces 11 thus form a first group having a first luminance factor and are juxtaposed with surfaces 12 of a second group having a second luminance factor. On the other hand, in order to differentiate them, the first luminance factor is chosen greater than the second luminance factor. In addition, the check pattern 10 comprises five lines 13 formed by an alternation of surfaces 11 and 12 and nine columns 14 also formed by an alternation of surfaces 11 and 12. The lines 13 are arranged parallel to each other and positioned on the element blade 2 in a direction parallel to the pitch axis 6 of the blade member 2. Similarly, the columns 14 are arranged parallel to each other and positioned on the foot of the blade member 2 in a parallel direction to a beat axis 7 of this blade member 2. Furthermore, the checkered pattern 10 also comprises an entourage 15 arranged at the periphery of the grid zone formed by the lines 13 and the columns 14 of the surfaces 11 and 12 juxtaposed and different luminance factor. Such an entourage 15 is then advantageously chosen with a luminance factor substantially equal to the luminance factor of the surfaces 11 of the first group when surfaces 12 of the second group are arranged at the four corners of the grid zone formed by the lines 13 and 13. columns 14.
    [0009] As shown in FIG. 5, and according to a second variant of a first configuration of the invention, the measuring device 101 may comprise a calculator 150 secured to a fixed part of the fuselage 152 of the rotorcraft 103. In this case, only the camera 20 is secured to the hub 4 of the rotor 5.
    [0010] Of course, the computer can also be formed by an independent subsidiary body of the rotorcraft such as a computer. Furthermore, as shown in FIGS. 6 to 9, the images coming from the camera 20 are two-dimensional representations of the checkered pattern 10 whose shape may vary as a function of the angular position of the blade member. Thus, as represented in FIG. 6, the image coming from the camera corresponds to a neutral position of the blade element when the pitch, beat and screen angles are substantially zero according to a pre-established convention.
    [0011] On the other hand, as represented in FIG. 7, the image coming from the camera corresponds in this case to a first position of the blade element when the pitch and halftone angles are substantially zero and the beat angle is not void, according to the said convention. Similarly, as represented in FIG. 8, the image coming from the camera corresponds in this case to a second position of the blade element when the pitch angle is zero and the beat and halftone angles are non null, according to always said convention. Finally, as represented in FIG. 9, the image coming from the camera corresponds here to a position of the blade element when the pitch, beat and screen angles are non-zero. An algorithm for recognizing the shapes and positioning the pixels forming the check pattern then makes it possible to determine the three-dimensional mathematical transformation corresponding to each image and thus the angular positions of the blade element relative to the hub of the rotor. Such an algorithm is particularly known and consists of performing an identification and extraction of singular points of an image such angles or corners. Such a method is generally referred to in the literature as the wedge extraction method or the HarrisStephens method. Indeed, this method has been described in a joint article by Chris Harris and Mike Stephens: "A combined corner and edge detector" which is taken from a conference report held at the University of Manchester of August 31 to September 2, 1988 "Proceedings of the Fourth Alvey Vision Conference", which can be consulted in particular at the following Internet address: http://www.bmva.org/bmvc/1988/avc-88-023. pdf.
    [0012] Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all the possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (16)
    [0001]
    REVENDICATIONS1. Device for measuring (1, 101) the angular positions of a rotorcraft blade element (3, 103), said blade element (2) being arranged to rotate with respect to a rotor hub (4) (5) around at least one axis of rotation (6, 7, 8), characterized in that said measuring device (1, 101) comprises: - at least one checkered pattern (10) adapted to be secured to said blade member (2), said checkerboard pattern (10) having two groups of surfaces (11, 12) respectively having different luminance factors, each surface (11) of a first group having a first luminance factor and being juxtaposed with at least one surface (12) of a second group having a second luminance factor, said first luminance factor being greater than said second luminance factor; at least one camera capable of taking a plurality of images of said checkered pattern as a function of time, said camera being able to be secured to said hub; - a synchronization member (30) for assigning to each image taken by said camera (20) a time parameter according to the azimuth angle of said rotor (5); a memory (40) for recording each image with said corresponding temporal parameter; - a computer (50, 150) for automatically determining said angular positions of the blade member (2) according to at least one axis of rotation (6, 7, 8) from said images of the checkered pattern (10).
    [0002]
    2. Device according to claim 1, characterized in that said computer (50, 150) determines the angular positions of the blade member (2) along three axes of rotation (6, 7, 8) forming an orthogonal reference linked to the hub (4), said orthogonal coordinate system comprising a first axis (6), said pitch axis, a second axis (7), said beat axis and a third axis (8), said dither axis.
    [0003]
    3. Device according to any one of claims 1 to 2, characterized in that said synchronizing member (30) 10 comprises a sensor (31) for detecting each turn of said rotor (5).
    [0004]
    4. Device according to any one of claims 1 to 3, characterized in that said computer (50, 150) is arranged on said rotorcraft (3, 103). 15
    [0005]
    5. Device according to claim 4, characterized in that said computer (50) is adapted to be secured to the hub (4) of the rotor (5) near said camera (20).
    [0006]
    6. Device according to claim 4, characterized in that said computer (150) is adapted to be arranged on a fixed part relative to a fuselage (152) of said rotorcraft (103).
    [0007]
    7. Device according to any one of claims 1 to 6, characterized in that said memory (40) is of removable type and cooperates with an interface (21) integral with the camera (20).
    [0008]
    8. Device according to any one of claims 1 to 7 characterized in that said check pattern (10) comprises: - at least three lines (13) formed by an alternation of surfaces (11, 12) having luminance factors different, said lines (13) being parallel to each other and arranged on said blade member (2) in a direction parallel to a pitch axis (6) of said blade member (2), and, - at least three columns (14). ) formed by an alternation of surfaces (11, 12) having different luminance factors, said columns (14) being parallel to each other and arranged on said blade member (2) in a direction parallel to a beat axis (7) said blade member (2).
    [0009]
    9. Device according to claim 8, characterized in that said check pattern (10) comprises five lines (13) formed by an alternation of surfaces (11, 12) having different luminance factors and nine columns (14) formed by alternating surfaces (11, 12) having different luminance factors.
    [0010]
    10. Device according to any one of claims 1 to 9, characterized in that said checkerboard pattern (10) comprises a surround (15) whose luminance factor is substantially equal to the first luminance factor of said first group of surfaces. (11).
    [0011]
    11. Device according to any one of claims 1 to 10, characterized in that said surfaces (11) of the first group and said surfaces (12) of the second group are of square shape.
    [0012]
    12. Device according to any one of claims 1 to characterized in that said checkerboard pattern (10) comprises surfaces (12) of the second group at each of the corners of the shape defined by the two groups of surfaces (11). , 12).
    [0013]
    13.Giravion (3, 103) characterized in that it comprises a device (1, 101) for measuring the angular positions of a blade member (2) with respect to a rotor hub (4) (5) according to any one of claims 1 to 12.
    [0014]
    Method for measuring the angular positions according to at least one axis of rotation (6, 7, 8) of a rotorcraft blade element (3, 103) with respect to a rotor hub (4) ), Characterized in that said method comprises steps of: securing at least one checkerboard pattern (10) with said blade member (2), said checkerboard pattern (10) having two groups of surfaces (11, 12 ) respectively having different luminance factors, each surface (11) of a first group having a first luminance factor and being juxtaposed with at least one surface (12) of a second group having a second luminance factor, said the first luminance factor 25 being greater than the said second luminance factor, fastening with the said hub (4) at least one camera (20) capable of taking a plurality of images of the said check pattern (10) as a function of time; plurality of images of said checkered pattern (10) during a annotation of said rotor (5), - synchronizing each image made by the camera (20) with a time parameter according to an azimuth angle of said rotor (5), - recording each image with said corresponding temporal parameter, - automatically determining said angular positions of the blade member (2) in at least one axis of rotation (6, 7, 8) from said images of the checkered pattern (10).
    [0015]
    15. The method of claim 14, characterized in that said measuring method comprises a step for determining the angular positions of said blade member (2) along three axes of rotation (6, 7, 8) forming an orthogonal reference linked to the hub (4), said orthogonal coordinate system comprising a first axis (6), said pitch axis, a second axis (7), said beat axis and a third axis (8), said dither axis.
    [0016]
    16. Method according to any one of claims 14 to 15, characterized in that said measuring method makes it possible to produce between 5 and 45 images of said checker pattern (10) on a rotor turn (5). 25
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    同族专利:
    公开号 | 公开日
    EP3025958A1|2016-06-01|
    FR3029284B1|2016-12-09|
    US20160153775A1|2016-06-02|
    KR20160063994A|2016-06-07|
    CN105701802B|2018-08-10|
    PL3025958T3|2017-06-30|
    KR101705328B1|2017-02-09|
    EP3025958B1|2017-01-04|
    US9784572B2|2017-10-10|
    CN105701802A|2016-06-22|
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    法律状态:
    2015-11-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-03| PLSC| Search report ready|Effective date: 20160603 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1402694A|FR3029284B1|2014-11-27|2014-11-27|DEVICE FOR MEASURING ANGULAR POSITIONS OF A ROTOR BLADE ELEMENT IN RELATION TO A ROTOR MEANS, ASSOCIATED GIRAVION AND CORRESPONDING MEASUREMENT METHOD|FR1402694A| FR3029284B1|2014-11-27|2014-11-27|DEVICE FOR MEASURING ANGULAR POSITIONS OF A ROTOR BLADE ELEMENT IN RELATION TO A ROTOR MEANS, ASSOCIATED GIRAVION AND CORRESPONDING MEASUREMENT METHOD|
    EP15193203.5A| EP3025958B1|2014-11-27|2015-11-05|A device for measuring the angular positions of a rotorcraft blade element relative to a rotor hub, an associated rotorcraft, and a corresponding measurement method|
    PL15193203T| PL3025958T3|2014-11-27|2015-11-05|A device for measuring the angular positions of a rotorcraft blade element relative to a rotor hub, an associated rotorcraft, and a corresponding measurement method|
    CN201511035942.4A| CN105701802B|2014-11-27|2015-11-20|Measure equipment, method and the associated rotor of gyroplane blade element angle position|
    US14/948,634| US9784572B2|2014-11-27|2015-11-23|Device for measuring the angular positions of a rotorcraft blade element relative to a rotor hub, an associated rotor, and a corresponding measurement method|
    KR1020150164276A| KR101705328B1|2014-11-27|2015-11-23|A device for measuring the angular positions of rotorcraft blade element relative to a rotor hub, an associated rotor, and a corresponding measurement method|
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