Classifications

• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
  • G01P13/00—Indicating or recording presence, absence, or direction, of movement
  • G01P13/02—Indicating direction only, e.g. by weather vane
  • G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D43/00—Arrangements or adaptations of instruments
• • G—PHYSICS
  • G01—MEASURING; TESTING
  • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
  • G01P21/00—Testing or calibrating of apparatus or devices covered by the preceding groups
  • G01P21/02—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers
  • G01P21/025—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers for measuring speed of fluids; for measuring speed of bodies relative to fluids

Definitions

• the invention relates to a device for precise and in situ angular positioning of an incidence probe on a wall, of the type comprising a wind vane movable around an axis.
• aircraft In the context of the invention, and more particularly of the preferred application above, the term "aircraft must be understood in its most general sense. It naturally relates to aircraft of all types, but also to other flying machines and in particular helicopters. In what follows, below, for the purpose of simplification and without limiting in any way the scope of the invention, we will place our within the framework of the preferred application and we will simply use the word "airplane”.
• the incidence sensors are generally two in number and are fixed on the cabin, at approximately 3 H and 9 H, respectively, compared to the longitudinal axis of the airplane. They must be placed on as close as possible to the nose of the aircraft, so that the wind vane is driven by a stream of air which is not yet disturbed, or as little as possible disturbed.
• the probe 1 comprises a main body constituted by a housing 10, generally cylindrical, closed on its upper part by a plate 11, advantageously circular.
• the wind vane 12 comprises a lower support 120, thin and mobile around an axis ⁇ s , which will be called the probe axis, surmounted by a flag 121.
• the shape and profile of the section of this flag 121 are determined by the final application of the probe, i.e. essentially the type of aircraft for which it is intended, the degree of precision of the angle measurements. to obtain and a certain number of physical parameters describing the environmental conditions to which the incidence probe is subjected: maximum speed reached by the aircraft, therefore also air flowing along the walls of the cabin, variations maximum temperatures, etc. these considerations go beyond the precise scope of the invention. Indeed, the positioning device object of the invention, and this is one of the advantages of it, remains compatible with all types of flag probes of the known art and does not require any modification, either structural or functional. .
• the housing in particular contains a rotation angle sensor of the vane 12, and more precisely of the flag, around the axis ⁇ s .
• the latter can use a measurement based on the use of a potentiometer whose axis is driven by the rotation of the flag 121, a sensor of the so-called “resolver” type or any other sensor of known art. suitable for this area of application.
• the amplitude of the rotation of the vane 12 around the axis ⁇ S is converted into electrical signals, transmitted by links 13 to a signal processing device (not shown) located inside the aircraft, generally in the cockpit, to be finally displayed on an on-board instrument in an appropriate form, according to the parameters measured.
• the housing 10 of the incidence sensor is placed in an orifice (not shown) provided for this purpose in the cabin of the aircraft and covered with a cover (not shown) so that what is called the " skin "of the aircraft, referenced PA, is flush with the upper surface of the support 120 of the flag 121. It is indeed necessary that, with the exception of the protrusion formed by the flag 121, no roughness remains which would disturb the flow of the air streams on the surface of this skin PA.
• a test tool is used to calibrate in situ the wind vane 12 (FIG. 1), and more particularly its flag 121, in variable spatial positions relative to a reference axis of this tool.
• This tool 2 is shown in Figure 2 appended to this description.
• Tool 2 comprises a plate 20 provided with a graduated scale 210, in an area which will be called arbitrarily higher, and with an orifice 200, in an area which will be called lower, orifice which can be thread on the flag 121 of the wind vane 12.
• the plate 20 comprises fastening members on the aircraft, 201 and 202, for example with screws.
• the surface of the cabin includes threaded orifices (not shown) in appropriate spatial relationship with the fixing members, 200 and 201, on the one hand, and with the axis of rotation ⁇ s of the flag 121 the wind vane 12, on the other hand. Outside the test periods, these orifices are closed so as not to disturb the local flow of the air streams.
• the plate 20 is fixed to the aircraft by means of the abovementioned members 200 and 201.
• the orifice 200 is a priori circular in shape and its axis of symmetry is theoretically merged with the axis of rotation symmetry ⁇ s of the flag 121 of the wind vane 12.
• the plate 20 also includes a movable index 22, one of the ends of which, which will be called arbitrarily upper, is also provided with a graduated scale 220 and the other end, which will be called lower, is secured to 'a ring 24 coaxial with the orifice 200.
• This ring 24, integral with the plate 20, is movable around an axis of rotation, which will be called a tool ⁇ 0 , centered on the axis of symmetry of the orifice 200 and therefore also, theoretically, on the axis of rotation ⁇ s of the flag 121.
• the ring 24 supports, in proximity relationship with the orifice 200, and on either side of an axis of symmetry of measurement ⁇ M , which will arbitrarily be called vertical, ⁇ v , a pair 23 of door -jaws, 230 and 231.
• the arrangement of these jaw holders, 230 and 231, is such that one can introduce the flag 121 between them, more precisely between jaws, 2300 and 2301.
• the first jaw 2300 is fixed and forms spatial reference, when one of the faces of the flag 121 is pressed against this jaw 2300.
• the other jaw is movable in translation along an axis perpendicular to the axis ⁇ M. it is pushed back by a spring 2311 disposed between its free end and the jaw holder 231.
• a thumb wheel 2312 makes it possible to pull the jaw 2311 and to compress the spring 2311. This operation makes it possible to place the flag 121 between the two jaws, 2310 and 2300, and after releasing the lock in position pressed against the jaw 2300, which forms a reference, and allows it to be aligned on the measurement axis ⁇ M.
• the scale 210 is graduated in degrees or in any other appropriate angle unit. In the example described, the scale is graduated from + 50 to -50 degrees, on either side of the zero graduation. The central part, between +5 and -5 degrees, is graduated more precisely, in degrees. Scale 210 forms the main graduation scale. Likewise, the scale 220, carried by the rotating movable index 22, carries graduations on either side of a value zero (+10 to -10 in the example). This scale, which can be called secondary, plays the role of a vernier caliper and makes it possible to determine fractions of graduation units.
• the flag 121 of the wind vane 12 is aligned on the axis ⁇ M , which is supposed to define the absolute zero of the incidence probe. It then suffices to check on the on-board instruments associated with the angle of attack probe being tested whether this zero is indeed reflected and, if not, to calibrate them accordingly. Then, it suffices to rotate the movable index 22 around its axis ⁇ O, in predetermined increments, on either side of the zero, which also causes the flag 121. The successive angles of rotation are read on the instruments of edge, which allows determining the degree of linearity accuracy of the incidence sensor 1.
• This tool for positioning the flag of the incidence probes although widely used, is not without its drawbacks.
• the main drawback of this device is its low precision. For the most part, the origin of the errors is, moreover, twofold.
• the first source of error is due to the fact that the axis of rotation of the tool ⁇ ⁇ is not identical to the axis of rotation ⁇ s of the flag 121 of the wind vane 12. In fact, as has been remembered, these axes of symmetry are physically distinct. Even if the initial positioning of the housing 10 (during the mounting of the probe 1 on the aircraft) is carried out with care, and the orifices intended for fixing the measuring tool 2 are produced with great precision, following the constraints to which the cabin surface is subjected, the initial precision obtained initially degrades over time. On the other hand, the method of fixing the tool 2 does not allow great precision and / or a high repetition of positioning of the axis ⁇ o relative to the axis ⁇ s .
• Os origin of the axis of rotation of the probe 12, that is to say of the flag 121; Oo: origin of the axis of rotation of the tool 2 (that is to say of the movable index 22);
• X ' axis parallel to the X axis passing through ⁇ s ;
• P projection of M onto X ';
• oo so-called tool angle with respect to X;
• ots so-called probe angle (flag 121) relative to X;
• d distance separating M from the axis axis ⁇ ⁇ of rotation of the tool 2; and e: offset value (distance between axes X and X ').
• the flag 121 of the vane 12 can undergo deformations, either by shocks, or by erosions, or by thermal stresses. These deformations result in twisting and / or veiling of this flag.
• the device 2 according to the prior art does not make it possible to detect these deformations. Only a human operator could see them visually, but these would be very large deformations. The device according to the prior art therefore does not make it possible to verify compliance with the original form.
• the invention aims to overcome the drawbacks of the devices of the known art, some of which have just been mentioned.
• the invention sets itself the goal of a device for precise positioning of the flag of the wind vane which will allow not only linearity measurements under very good conditions of precision, but also a measurement of zero under these same conditions.
• the axis of rotation of the incidence probe is used directly, and no longer any axis linked to the device, to serve as a reference for the angular positioning of the flag.
• This axis serves as a reference both for an initial positioning, that is to say to achieve "zero", as for the measurement of subsequent angular displacements of the probe, for example by fixed increments.
• a so-called "enveloping" structure of the flag of the wind vane is provided, that is to say a structure making it possible to trap it reversibly inside an internal enclosure.
• This second characteristic has the additional advantage of making it possible to verify compliance with the original form. Any twisting or veiling of the flag makes it impossible to fix the structure within the limits of its machining tolerances.
• the so-called "enveloping" structure can be produced in several variants, which makes it possible to accommodate both the so-called prismatic flag profiles and the non-prismatic profiles.
• the main object of the invention is therefore a device for angular positioning in situ of an incidence probe of the so-called wind vane type provided with a flag movable about an axis of rotation, said incidence probe being arranged on a wall, said wall comprising fixing means temporary of said device on said wall around said incidence probe, characterized in that it comprises a first structure, called an enveloping structure, provided with an internal enclosure into which said flag can be inserted and reversibly blocked, a so-called structure fixed can be secured to said wall by means of fixing members and said temporary fixing means comprising a movable member on said fixed structure, said drive, a coupling member between said movable drive member and said enveloping structure, so as to position the latter and said flag in a determined angular position around said axis of rotation, and means for measuring said angular position, integral with said enveloping structure, so as to obtain said angular position.
• FIG. 1 schematically illustrates an embodiment of an aircraft incidence probe of the type comprising a wind vane movable around an axis
• FIG. 2 schematically illustrates an exemplary embodiment of a device for angular positioning of a vane type incidence probe according to known art
• - Figure 3 is a geometric construction for the calculation of homokinetic error encountered in the device of Figure 2
• FIGS. 4A to 4C illustrate a preferred embodiment of a so-called fixed structure according to one of the characteristics of the invention, intended to be subjected to the airplane during the control phases of the incidence probe and comprising a member d 'training thereof;
• FIGS. 1 schematically illustrates an embodiment of an aircraft incidence probe of the type comprising a wind vane movable around an axis
• FIG. 2 schematically illustrates an exemplary embodiment of a device for angular positioning of a vane type incidence probe according to known art
• - Figure 3 is a geometric construction for the calculation of homokinetic error encountered in the device of Figure 2
• FIG. 5A and 5B schematically illustrate a first embodiment of a so-called enveloping structure in which the flag of the incidence probe is inserted and locked in a reversible manner, according to another characteristic of the invention
• - Figures 6A to 6D illustrate a practical embodiment of a so-called enveloping structure according to a second embodiment
• FIG. 7 illustrates in more detail an embodiment of a drive member coupling the fixed and enveloping structures
• FIG. 8 schematically illustrates a complete angular positioning device according to the invention and its operation
• - Figure 9 schematically illustrates an additional arrangement for defining an absolute reference for angular positioning of the incidence probe;
• FIG. 10 schematically illustrates, in section, a third embodiment of a so-called enveloping structure; and - Figure 11 schematically illustrates, in section, a fourth embodiment of a so-called enveloping structure more particularly suitable for a flag of so-called non-prismatic shape.
• the angular positioning device comprises a first member which will be called hereinafter the angular drive member.
• the configuration of this member can be common to all the variant embodiments of the device according to the invention.
• FIG. 4A It firstly comprises a fixed structure 3, an exemplary embodiment of which is illustrated in FIG. 4A, in top view.
• the term “fixed” means that it can be made temporarily integral with the airplane, by screwing for example, in a similar manner to the device of the known art in FIG. 1.
• the fixed structure 3, in the example illustrated in FIG. 4A, has the general shape of a ring 30 comprising two fixing members to the aircraft, 33 and 34. These fixing members are arranged parallel to an axis V that we assume vertical, of a pair of orthonormal axes V and H, the latter being assumed to be horizontal.
• the aircraft has holes for fastener (not shown), normally closable, in correspondence relationship with the fasteners, 33 and 34.
• the fastening holes on the aircraft are spatially positioned so that the inner hole 300 of the ring 30 or centered substantially on the axis ⁇ s of the probe ( Figure 1: 1), that is to say on the axis of rotation of the flag 121.
• the ring 30 finally comprises, on either side of the vertical axis connecting the two fixing members, 33 and 34, two through grooves, 31 and 32, aligned on a circle whose center is substantially coincident with the axis of symmetry of the ring and therefore also with the axis ⁇ s , when the structure 3 is subject to the airplane.
• the grooves 30 and 31 constitute guide rails for a slider 4, shown in dotted lines, which can move around the circumference of the ring 30.
• the amplitude of the movement is limited by the length of the grooves.
• FIG. 4B shows the right part (in FIG. 4A) of the ring 30 in side view and in partial section.
• This FIG. 4B illustrates in greater detail the cursor 4, mounted on the ring 30.
• the cursor 4 comprises a body in the shape of an inverted "U" 40 which can be threaded on the edge of the ring 30.
• the lower branch of the "U” comprises a housing for the head 420 of a screw 42 and the upper branch an orifice allowing the rod of the screw 42 to emerge. The latter passes through the groove 31.
• the body supports a part 41, itself provided with 'an orifice 410 into which the rod 421 of the screw 42 is inserted.
• a thumbwheel screwed onto the threaded rod 421 of the screw 42, keeps the carriage 4 secured to the ring 30.
• the thumbwheel 43 is loosened , the carriage 4 can be moved by hand along the groove 31. It would be the same if it had been hooked to the groove 30.
• an operator screws the thumb wheel fully , the part 41 is pressed firmly against the upper surface of the ring and / or the branches of the "U" pinc ent the ring 30. It follows that the cursor 4 is blocked at the position reached along the groove 31 (or 30).
• Under the ring there are legs, for example 340, drilled, for example 3400. These legs are made at the level of the fixing members
• FIG. 4C illustrates the part 41 in more detail. It has, on the side intended to be turned towards the inside of the ring 30, a face 411, bevelled on the upper part. The latter has a longitudinal slot 412, also facing the interior of the ring 30. The usefulness of this slot will be explained below.
• the structure 3 (ring 30 and slider 4) can be made of light metal, for example aluminum, with the exception of the legs 340 which can be made of plastic material (in PVC for example), so as not to not scratch the support surface of the structure.
• the external diameter of the ring 30 is approximately 330 mm, the internal diameter of approximately 240 mm and the circle along which the grooves run approximately 300 mm.
• the opening angle of these grooves, 31 and 32 is approximately 60 degrees ( ⁇ ⁇ M ).
• the angular positioning device comprises a second main part, constituted by a structure which will be called "enveloping" of the flag of the weather vane.
• This second structure is capable of several embodiments and several variants in each of these embodiments, in particular to take account of the conformation of the flag. Indeed, there are two main types of flag shapes. The first is called “prismatic” and the second is called “non-prismatic”.
• the prismatic structure relates to a flag profile capable of being threaded, by simple translation, into a dual-shaped orifice.
• the shape of the flag 121 shown in FIG. 1 is a prismatic shape.
• FIG. 5A very schematically illustrates the enveloping structure 5 in perspective and FIG. 5B, this same enveloping structure in section AA of FIG. 5A.
• the enveloping structure 5 comprises a main body 50, of rectangular parallelepiped shape in the example described. This is provided with an open longitudinal internal enclosure 500.
• the shape of this enclosure is such that it allows the insertion of the flag 121 of the wind vane 12 by translation along a longitudinal ⁇ axis, with very little play. can therefore claim that the shape of the enclosure 500 is almost dual to that of the flag 121.
• a screw-wheel system 51 passing through the wall of the body 50 and whose lower part 510, opposite the wheel 511 (the latter being accessible from the outside) can rest on one of the edges of the flag 121, a priori the rear part 1210 of the flag 121, that is to say say the most tapered part.
• the screw-wheel system 51 is tightened (see more particularly FIG. 5B, the section AA being produced at the level of this system 51), the front part 1211 of the flag 121 is pressed against the corresponding internal wall of the cavity 500 and the flag 121 is blocked in this cavity 500.
• the angular positioning device comprises a third main part, in this case an apparatus for measuring the rotation of the flag 121 around the axis ⁇ s .
• the fixed structure 3 (FIGS. 4A to 4C) does not include any means of measuring the rotation of the wind vane 12.
• this structure will only be used for training and immobilizing the flag 121, by means of the aforementioned cursor 4.
• the enveloping structure 5 which follows the rotational movements of the flag 121, supports an apparatus for measuring the amplitude of these rotational movements.
• an inclinometer 6 integral with the body 50 of the structure 5.
• This device measures, at any time, the inclination of the flag 121 relative to a local horizontal plane.
• a digital type inclinometer is used displaying the measurement results on a screen 60, which avoids any error of interpretation on the part of an operator (parallax errors in particular in the case of a device of the type analog).
• the inclinometer 6 is not fixedly mounted on the structure 5. In this way, there is less risk of damaging the incidence probe 12 when the enveloping structure 5 is put on, the weight total and the size thereof being reduced to a minimum.
• the inclinometer 6 is coupled to the structure 5, for example by inserting into slides provided for this purpose (not shown in Figure 5A).
• FIG. 6A illustrates the enveloping structure 5a in side view and FIG. 6B in section BB of FIG. 6A.
• the main body of the enveloping structure 5a comprises a first part in the shape of an inverted "U" 50a, trapping two superimposed parts 52a and 53a.
• Each of these parts is provided with a recessed imprint, 520a and 530a, respectively.
• the two imprints, 520a and 530a are arranged opposite and facing one another, so as to define an enclosure of dual form to that of the flag 121, as previously.
• These parts will preferably be made from a non-abrasive material, so as not to risk damaging the flag 121, for example a polyamide.
• the "U" piece 50a is integral with a lower support 54a.
• the relative thicknesses of the parts, 520a and 530a are such that they leave a small possible clearance ⁇ between the bottom of the "U" and the upper face of the part 52a.
• the "U" -shaped part 50a has on its upper part a threaded orifice 500a so as to be able to screw a screw-wheel system 51a, the lower part 511a of which presses on the upper part 52a.
• FIG. 6A represents, in dotted lines, the flag 121 fully inserted in the enveloping structure 5a.
• the pieces, 52a and 53a protrude on either side of the "U" piece 50a, so as to precisely wrap the flag 121 over most of its length. They advantageously have lower faces (for example 522a for the part 52a) and upper faces (for example 521a for the part 52a) planar and substantially orthogonal to the axis of rotation ⁇ s of the flag 121.
• a stop 55a can be provided on the underside, for example 522a. the latter presses on the rotating support 120 of the flag 121 and defines a maximum depression of the enveloping structure 5a.
• the support 54a of the components constituting the enveloping structure 5a is an elongated part arranged along an axis ⁇ 5 substantially orthogonal to the axis ⁇ s .
• this part is also assigned the inclinometer support function 6, illustrated by FIG. 6C. More precisely, the part 54a plays the role of a reversible fixing slide for this inclinometer 6.
• FIG. 6D illustrates the support 54a, in side view, but opposite to that of FIG. 6A.
• the body 540a is provided with two lateral slides, 5400a and
• the slides, 5400a and 5401a are provided with a front bevel, 5402a and 5403a, respectively, to facilitate the insertion of the shoe 66.
• One of the ends is provided with a nipple 63 intended to be inserted into an orifice 5406a (FIG. 6D) provided for this purpose on the corresponding end of the support 54a.
• the other end has a protrusion 64 (downwards in the example) intended to be inserted into a fork 5404a (FIG. 6D) provided at the corresponding end of the support 54a.
• These complementary parts are each provided with a through orifice orthogonal to the axis ⁇ 5l 640 and 5405a, respectively.
• a stud 65 is provided which can be threaded into these holes and attached, for example using a chain 67, to the body of the inclinometer 6. Once threaded on its support 54a, the latter thus remains blocked in this position.
• the inclinometer 6 is preferably of the digital type. It includes inside electronic circuits and an autonomous electrical energy supply (for example based on cells or batteries). On a side face, a display 60 is provided, as well as in particular an on / off switch 62.
• the angular positioning device finally comprises a fourth main part, allowing the drive of the enveloping structure, for example in its version 5a, using the cursor 4 (FIGS. 4A to 4C).
• FIG. 7 illustrates in perspective an exemplary embodiment of a coupler member 7 allowing cooperation between the enveloping structure 5a (FIGS. 6A and 6B) and the cursor 4.
• the coupling member 7 comprises a first solid part 70. If we refer again to FIG. 6A, this part is profiled so that it has a flat wall which can be fixed by any suitable means (screws, etc. ) on one of the lateral faces of the "U" -shaped part 50a, for example the straight face 500a, in the example described.
• the face which will be called lower 701 of the part 70 is planar and forms an angle with the face 700 such that it is parallel to the axis ⁇ 5 .
• an elongate piece 71 with elastic properties is fixed, advantageously constituted by a flat spring.
• FIG. 8 schematically illustrates, in perspective, the cooperation of the main components of the angular positioning device according to the invention and will make it possible to explain the operating mode thereof.
• the fixed ring-shaped structure 3 is fixed on the aircraft, using screws or similar members, 330 and 340, cooperating with threaded orifices 331 and 341 produced on the cabin of the aircraft A v ⁇ as it was indicated.
• the ring 30 surrounds the wind vane 12 and its flag 121 which alone protrudes from the wall of the aircraft A v .
• the enveloping structure 5a is threaded, shown diagrammatically in FIG. 8 by a rectangular parallelepiped. Once this operation is complete, the flag is blocked inside the structure 5a (using the wheel 511a: FIG. 6B).
• the inclinometer 6 is then fixed, also shown diagrammatically by a rectangular parallelepiped on the body of the enveloping structure 5a.
• an absolute initialization value can be obtained, for example by using one or the other of the two methods below.
• the wind vane 12 is positioned at the reference angle of the airplane and performs a relative zero of the inclinometer 6.
• a zero adjustment or calibration device In the context of the invention, the zero will not necessarily correspond to the local horizontal (axis H).
• angles read on the inclinometer 6 are the actual local incidence angles, naturally to the accuracy near the reference angle and to that of the angle measured by the inclinometer 6.
• a reference is created on the wall of the aircraft during the first mounting of the incidence probe 1 (FIG. 1).
• the reference in question is constituted by an additional orifice machined in the wall of the aircraft A v .
• the device according to the invention also makes it possible to determine the conformity of the flag 121 by relying on the entire profile, and not only by considering a point reference as in the known art (FIG. 1: 2300-2301). Indeed, if we again refer in particular to FIG. 6B, it has been indicated that only a small clearance, of amplitude ⁇ i, is provided between the complementary parts 52a and 53a. If the deformations of the flag exceed this clearance e 1t it will not be possible to insert it inside the structure 5a.
• FIG. 10 illustrates, in section, an embodiment of an enveloping structure 5b, comprising a body 50b consisting of two half-housings, 52b and 53b, respectively.
• the first part, 52b is fixed, the second 53b is articulated around an axis of rotation 56b. It can therefore deviate substantially from the first part and allow the flag 121 to penetrate inside the enveloping structure 5b.
• the two parts, 52b and 53b are provided with hollow imprints 520b and 530b. however, these only correspond to the ends of the flag 121.
• the movable part 530b is pivoted about its axis 56b, which has the effect of trapping the flag 121.
• a screw-wheel system 51b comprising a screw body passing through the wall of the part 53b (channel 531b) and the end of which is integral with the fixed part 52b, by means of an axis of rotation 512b.
• FIG. 11 illustrates, in section, such an embodiment.
• the enveloping structure 5c will hereinafter be called the "pen tray" form.
• the structure 5c comprises a second part 53c intended to be inserted between the side walls of the part 52c. This part also has a hollow imprint, 530c, facing the imprint 520c.
• the two imprints define an enclosure whose shape is dual to that of the flag 121, when they are in the operational position. As the latter is assumed not to have a prismatic shape, it cannot be inserted into the aforementioned enclosure by translation.
• the part 53c is removed sufficiently, the flag 121 is placed against the underside of the part 52c, in the imprint 520c. Next, the part 53c is positioned against the underside of the flag 121. The latter is therefore enclosed in the aforementioned enclosure. To maintain this state, a plate 57c forming a flat spring is slid, curved upwards, so as to exert a thrust F on the part 53c and therefore to block the flag inside the structure 5c. There is also a possible clearance, here referenced e 2 , between the two parts of complementary profiles, 52c and 53c, more precisely, as shown in FIG. 11, between the upper wall of the longitudinal grooves, 5201 and 5202, and the lower wall. 53c. Due to the thrust exerted by the spring 57c and of its non-prismatic shape the flag cannot leave its case, as long as said spring 57c remains in place.
• a coupling member is provided, similar to the member 7 in FIG. 7, a member adapted to the external shape of the enveloping structures.
• the so-called fixed structure 3 can be used without modifications for all the embodiments.
• the invention achieves the goals it has set for itself. In particular, it avoids any homokinetic error, since the axis of rotation of the probe is used as a reference. It provides good accuracy, both absolute and relative. The more or less precise fixing of the so-called fixed structure no longer plays a preponderant role in the precision of the measurements, since this structure does not intervene directly in them: there is no scale of graduations on this structure as in known art. Its only role is to drive the flag of the weather vane, via the movement of the cursor, the coupling member and the enveloping structure, block within it the flag.

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• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Physics & Mathematics (AREA)
• General Physics & Mathematics (AREA)
• Length Measuring Devices With Unspecified Measuring Means (AREA)
• Toys (AREA)
• Testing Or Calibration Of Command Recording Devices (AREA)
• A Measuring Device Byusing Mechanical Method (AREA)

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• 1999
  • 1999-12-30 FR FR9916773A patent/FR2803387B1/fr not_active Expired - Fee Related
• 2000
  • 2000-12-28 WO PCT/FR2000/003719 patent/WO2001050136A1/fr active Application Filing
  • 2000-12-28 EP EP00990834A patent/EP1244918A1/de not_active Withdrawn
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