WO2017187107A1

WO2017187107A1 - Propulsion assembly for an aircraft comprising a radio-identification device fixed in a tamperproof manner to a component

Info

Publication number: WO2017187107A1
Application number: PCT/FR2017/051020
Authority: WO
Inventors: Jean-Michel Bazet; Fabien Lamazere; François THERMY; Xavier FRANCEZ; François GEEREBAERT
Original assignee: Safran Helicopter Engines
Priority date: 2016-04-28
Filing date: 2017-04-28
Publication date: 2017-11-02
Also published as: FR3050877A1; FR3050877B1

Abstract

Proposed is a propulsion assembly for an aircraft, comprising at least one component (80) held on an element (84) of the propulsion assembly by means of at least two removable fasteners (86A, 86B), and a radio-identification device (82) comprising a radio-identification tag (24) borne by a support (74) and a non-removable fixing mechanism (90, 92A, 92B) connecting the support (74) to each of the removable fasteners (86A, 86B) so that the removable fasteners are mutually locked by the non-removable fixing mechanism (90, 92A, 92B). The device allows the radio-tag to be connected to the component without resorting to bonding, and in such a way that the non-removable fixing mechanism or some other part of the device has to be broken in order to separate the radio-tag from the component. The radio-identification device is thus rendered inseparable from the component.

Description

AIRCRAFT PROPULSIVE ASSEMBLY COMPRISING A RADIALLY IDENTIFICATION DEVICE FIXED INVIOLABLY ON A COMPONENT

DESCRIPTION TECHNICAL FIELD

The present invention relates to the field of propulsion assemblies intended for the propulsion of aircraft, in particular turbomachines, and concerns the configuration management of these propulsion units, that is to say the monitoring of the state of the elements composing the propulsion assembly and maintenance operations of these elements.

The invention more particularly relates to a radio-identification device for an aircraft propulsion system component, an aircraft propulsion unit comprising such a device, and a method for attaching such a device to a component of a propulsion unit. aircraft. STATE OF THE PRIOR ART

Patent Application US 2014/0207726 provides aircraft operators with maintenance assistance services aimed notably at improving the fault location, managing the configuration of the propulsion unit, and improving the performance of the aircraft. traceability of maintenance operations. These services are based on the knowledge of the real-time configuration, also called "configuration as fly" according to the English terminology, that is to say the identification of equipment mounted in the propulsion system.

The means for configuring the configuration of the propulsion units first consisted in manually reading (by visual reading) the identity of the elements making up the propulsion unit in a booklet provided for this purpose, called a "motor book", which is a paper document maintained by the users, and which is not normally communicated at regular intervals to the manufacturer of the propulsion system (engine). Real-time configuration management imposes the need for an automatic wireless system, in connection with the engine information system, and preferably integrable with existing propulsion systems with a minimum of mechanical evolution.

Beyond the strict configuration management "asfly" which identifies each replacement of one equipment by another, the knowledge of the removal / installation of the same equipment on a propulsion unit is also important information to the extent that it can reinforce the authenticity of a declaration of maintenance action (inspection, cleaning, adjustment ...). This is called "extended" configuration automatic reading.

To meet the need for wireless identification, it has been proposed to use RFI D systems (of the "Radio Frequency Identification Device"), composed of a radio-identification reader (also called "RFID reader"). "), And radio tags (also called" transponders "or" TAG ") respectively carried by the components of the propulsion system.

Radio tags are readable and readable memories by radio waves, usually in the ultra-high frequency (UHF) band.

There is therefore a need for a device and method for attaching a radio tag to an aircraft propulsion unit component.

STATEMENT OF THE INVENTION

The invention aims in particular to provide a device and a method for attaching a radio-tag to an aircraft propulsion unit component, which are simple, compatible with the environmental conditions encountered within a propulsion unit. aircraft, and which guarantee the inviolability of the configuration management, especially in the context of an automatic reading configuration "extended".

According to a general aspect of the present description, a radio-identification device for an aircraft propulsion unit component comprising a radio-identification tag and a releasable fastening mechanism for attaching the radio-identification tag to an aircraft propulsion assembly component.

In general, such a device allows the radio tag to be fixed to the corresponding propellant assembly component in such a way that it is necessary to break the releasable fixing mechanism or another part of the device to dissociate it. the radio-tag and the component.

The radio-identification device is thus rendered inseparable from the component, except to break at least part of the device and thus render the device unusable.

It is thus possible to guarantee the traceability of any intervention on the component concerned, whether it is a replacement of the component but also a simple removal / installation operation. More generally, it is thus possible to prevent any falsification of the configuration management process.

By "fixing mechanism" is meant any type of mechanical means, that is to say means implementing a mechanical cooperation between several parts or between parts of the same room.

Such a mechanism makes it possible to avoid the use of adhesives, which generally do not withstand the environment within an operating aircraft engine, particularly the thermal conditions and the possible projections of fluids (oil, fuel, solvent, etc.). ).

Preferably, the device further comprises a support carrying the radio identification tag, and a cable or clamp, having a first end fixedly connected to the block and a second end connected to the support by means of the locking mechanism. unmountable fixing.

Preferably, the clamping cable, respectively the clamping collar, comprises a tip configured to fit into a corresponding orifice of the support by irreversible snapping or crimping, the endpiece and the orifice together forming said fixing mechanism unbreakable.

The present description also relates to an aircraft propulsion unit, comprising at least one component provided with a radio-frequency device. identification of the type described above whose clamping cable, respectively the clamp, is tightened around a part of the component.

The invention relates more particularly to a propulsion unit for an aircraft, comprising at least one component held on an element of the propulsion unit by means of at least two removable fixing members, and a radio-identification device comprising a radio tag. -identification and a releasable fixing mechanism connecting the radio-identification tag to each of the removable fasteners so that the removable fasteners are mutually blocked by the releasable fastening mechanism.

The invention thus provides a simple means of connecting a radio identification tag to an aircraft propulsion unit component in a tamper-proof manner.

In a preferred embodiment of the invention, the releasable fastening mechanism comprises a wire secured to the radio identification tag and locking means, the wire and each of the removable fastening members being mutually engaged and being prevented from any mutual disengagement by means of blocking.

The present disclosure also relates to a method of attaching a radio identification device of the type described above to a component of an aircraft propulsion unit, comprising connecting the radio identification tag to the component by means of the unmountable fixing mechanism of the device.

In particular examples, the radio-identification device comprises a support bearing the radio-identification tag, and a cable or clamp, having a first end fixedly connected to the support and a second end initially free, to which case the method comprises a first step of arranging the clamping cable, respectively the clamp, around the component, and a second step of connecting the second end to the support by means of the releasable fixing mechanism.

The invention relates more particularly to a method for attaching a radio-identification device to a component of an aircraft propulsion unit held on an element of the propulsion unit by means of at least two transmission members. the radio-identification device comprising a radio-identification tag and a releasable fastening mechanism, the method of connecting the radio-identification tag to each of the removable fasteners by means of the releasable fastening mechanism of so that the removable fasteners are mutually locked by the releasable fastening mechanism.

In a preferred embodiment of the invention, the releasable fastening mechanism preferably comprises wire secured to the radio identification tag and locking means, in which case the method comprises a first step of mutually engaging the wire. and each of the detachable fasteners, and a second step of activating the locking means so as to prevent any mutual disengagement of the wire and each of the removable fasteners.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the following description given by way of nonlimiting example and with reference to the accompanying drawings in which:

- Figure 1 is a schematic perspective view of an aircraft engine;

FIG. 2 is a partial schematic perspective view of a first component of the engine of FIG. 1, equipped with radio-identification devices;

- Figure 3 is a schematic cross-sectional view of a second component of the engine of Figure 1, equipped with a radio-identification device, seen from the front;

- Figure 4 is a schematic front view of a third component of the engine of Figure 1 equipped with a radio-identification device, according to one embodiment of the invention.

In all of these figures, identical references may designate identical or similar elements. DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

FIG. 1 generally illustrates a propulsion unit 10 of an aircraft, comprising a nacelle 12 and a turbojet engine housed in the nacelle (not visible in the figure). The invention is however applicable to any type of aircraft propulsion system, for example a helicopter engine.

The propulsion unit 10 comprises a configuration management system comprising a radio-identification reader (which is not visible and is not the subject of the present invention), as well as radio-identification devices respectively associated with various components of the propulsion system.

In general, each of the radio-identification devices comprises a radio-identification tag, and an unmountable fixing mechanism for irreversibly connecting the radio-identification tag to the corresponding component of the propulsion unit. .

Several of these components are described in the following with their associated radio-identification device.

FIG. 2 illustrates a first of these components 20, which is for example cylindrical in shape of revolution, and which is for example equipped with two radio-identification devices 22.

Each of the radio identification devices 22 includes the radio identification tag 24, a support 26, for example in the form of a block, bearing the radio identification tag 24, and a cable 28 having a fixed first end 30. to the support 26 permanently, for example by gluing, welding or the like or by irreversible snapping or crimping, and a second end 32 having a tip 34 configured to be inserted with irreversible snap in a hole 36 of the support. The tip 34 and the orifice 36 thus form the releasable fixing mechanism for the radio-identification device 22.

For this purpose, the tip 34 is for example provided with a collar which engages with a pawl arranged inside the orifice 36 and shaped to produce irreversible snap-fastening. The opposite configuration is of course also possible. For such a radio-identification device 22, the method of fixing the device to the component 20 comprises a first step of passing the clamping cable 28 around the component 20 so as to bring the tip 34, which is initially free, into view of the orifice 36, then a second step of inserting the tip 34 in the orifice 36 until the irreversible snap effect. The tip 34 is therefore retained in the support 26 without the possibility of withdrawal.

Alternatively, the tip 34 may be shaped to be crimped into the hole 36 of the support. In this case, the second step of the method of fixing the device to the component 20 consists in inserting the endpiece 34 into the orifice 36 and then crimping the endpiece 34 in the orifice 36, which again makes it possible to prohibit any subsequent extraction of the tip 34 out of the orifice 36.

FIG. 3 illustrates a second component 40 of the propulsion unit, which is for example also of cylindrical shape of revolution, and which is equipped with a radio-identification device 42 comprising a clamping collar 44 made in one piece with the support 46. The clamping collar 44 further comprises a tip 48 provided with a set of ribs 50 parallel to each other cooperating with at least one pawl arranged in a hole 52 of the support 46 so as to produce an effect. irreversible snap.

More specifically, as illustrated in FIG. 3, the clamping collar 44 has a slotted ring-shaped portion 54 having a first end 56 integrated with the support 46, and a second end 58 designed to come into contact with the first end 56. when the slotted ring-shaped portion 54 is clamped around the component 40. The slotted ring-shaped portion 54 further includes a tab 59 projecting radially outwardly and carrying the tip 48. This the last extends coaxially with the slotted ring-shaped portion 54, from the tab 59, towards the support 46. The orifice 52 of the support 46 has a shape complementary to the general shape of the nozzle 48.

The method of attaching the radio identification device 42 to the component 40 is similar to the method described above with respect to the radio identification device 22 and the component 20 of FIG. FIG. 4 illustrates a third component 80 of the propulsion unit, which is equipped with a radio-identification device 82 according to a preferred embodiment of the invention.

The component 80 is attached to another element 84 of the propulsion unit by means of two removable fasteners 86A, 86B, such as fixing screws, each having a respective head 68A, 68B provided with a hole through the head transversely (masked in Figure 4).

The releasable fixing mechanism of the device 82 comprises a wire 90 integral with the radio identification tag 24 and locking means. More specifically, the device 82 comprises for example a support 74 bearing the radio identification tag 24 and to which the wire 90 is fixedly connected. The wire is for example a "wire to be braked" wire (commonly used for braking bolts), or any other type of wire having sufficient strength to support the radio identification tag 24 and the support 74.

The support 74 is for example fixed to a middle portion of the wire 90, while two crimping ferrules are respectively arranged at two ends of the wire 90, forming free ends.

The support 74 may be a block made of a low melting point material, such as lead, in which the wire is embedded, and on which the radio tag 24 is fixed. Alternatively, the support 74 may be made of a material of another type and may incorporate the wire in any other suitable manner prohibiting the separation of the wire and the support.

In the example shown, the locking means consist of two seals 92A, 92B, for example lead, respectively able to seal the crimping ferrules, as will become clearer in the following (the crimping ferrules being masked by seals 92A, 92B in Figure 4).

The releasable fixing mechanism ensures the attachment of the radio identification tag 24 to each of the two removable fasteners 86A, 86B.

Thus, a first end portion of the wire passes through the opening of the removable fixing member 86A and is provided with a first crimping ferrule crimped into said orifice and sealed by means of the seal 92A, while a second end portion of the wire passes through the opening of the removable fastener 86B and is provided with a second crimp ferrule crimped into the latter orifice and sealed by means of the seal 92B.

Each crimping ferrule is thus embedded in the corresponding seal 92A, 92B, so as to prevent any mutual disengagement of the wire 90 and each of the removable fasteners 86A, 86B.

The wire 90 thus ensures mutual blocking of the removable fasteners 86A, 86B, making it necessary to break the wire 90 before any dismantling of the removable fasteners 86A, 86B and therefore of the component 80.

The method of fixing the radio identification device 82 to the component 80 thus comprises a first step of mutually engaging the wire 90 and each of the removable fasteners 86A, 86B. In the example described above, it is thus necessary to pass each free end of the wire provided with the corresponding crimping ferrule through the orifice of the head 68A, 68B of the removable fixing member 86A, 86B corresponding, and then crimp the ferrule crimping in the hole.

The method then comprises a second step of activating the locking means so as to prevent any mutual disengagement of the wire 90 and each removable fastener 86A, 86B. In the example described above, it is thus necessary to drown each crimping ferrule in the seal 92A, 92B corresponding after having previously heated the latter so as to make it malleable, then to let the corresponding seal 92A, 92B cool so that it definitely imprisons the crimping ferrule.

Other methods of engagement of the wire 90 with the releasable fasteners 86A, 86B are of course possible without departing from the scope of the present invention. In some embodiments, the removable fasteners 86A, 86B may thus have no through hole.

Alternatively, the wire 90 may for example comprise two strands twisted with each other, in which case, for each removable fastener 86A, 86B, one of the two strands passes through the orifice of the head 68A, 68B of the fastener dismountable, while the other of the two strands bypasses the removable fastener, according to the well-known principle of the thread to be braked. In this case, the locking means may take the form of seals joining the two strands beyond each of the removable fasteners 86A, 86B, that is to say on the opposite side to the side of the radio label -identification 24.

The corresponding method comprises a first step of twisting the two strands with each other, then engaging each of the removable fasteners 86A, 86B with one of the strands, then joining the two strands by twisting them to beyond each of the removable fasteners 86A, 86B, and a second step of sealing together the respective ends of the two strands beyond each of the removable fasteners 86A, 86B by means of the seals.

In another variant, the free ends of the wire are fixed to the support 74 after having each through the orifice of the head 68A, 68B of the removable fastening member 86A, 86B corresponding. The wire thus forms a loop passing through the aforementioned orifice of each removable fixing member 86A, 86B, and whose two ends are fixed to the support 74. In this case, the support 74 thus constitutes the aforementioned locking means. More specifically, the support 74 may be a block made of a low melting point material, such as lead, in which the two opposite ends of the wire as well as the middle part of the wire are embedded, and on which the radio-tag 24 is fixed. The two strands of the wire extending respectively on either side of the aforementioned orifice are advantageously twisted between each of the removable fasteners 86A, 86B and the support 74.

In general, it should be noted that the label 24 or, where appropriate, the support 26, 46, 74, may be provided with a visual marker 100 (FIGS. 2, 4) making it possible to facilitate the positioning of the radio-identification device relative to the corresponding radio-identification reader of the propulsion unit. Such a marker may also include decodable information by an appropriate optical device.

Claims

A propulsion unit for an aircraft, comprising at least one component (80) held on a component (84) of the propulsion unit by means of at least two removable fixing members (86A, 86B), and a radiator device. identification (82) comprising a radio-identification tag (24) carried by a support (74) and a releasable fastening mechanism (90, 92A, 92B) connecting the support (74) to each of the removable fasteners (86A, 86B) so that the removable fasteners are mutually locked by the releasable fastening mechanism (90, 92A, 92B).

2. Propulsion unit according to claim 1, wherein the releasable fixing mechanism comprises wire (90) integral with the support (74) and locking means (92A, 92B), the wire and each of the removable fasteners (86A). , 86B) being mutually engaged and being prevented from any mutual disengagement by the blocking means.

3. A method of attaching a radio identification device (82) to a component (80) of an aircraft propulsion unit held on a propulsion unit element (84) by at least two members detachable fasteners (86A, 86B), the radio-identification device (82) comprising a radio-identification tag (24) carried by a carrier (74) and a releasable fastening mechanism (90, 92A, 92B), the a method of connecting the support (74) to each of the removable fasteners (86A, 86B) by means of the releasable fastening mechanism so that the removable fasteners are mutually locked by the releasable fastening mechanism (90, 92A, 92B).

4. Method according to claim 3, wherein the releasable fixing mechanism comprises wire (90) integral with the support (74), and locking means (92A, 92B), the method comprising: a first step of mutually engaging the wire and each of the removable fasteners (86A, 86B), and

a second step of activating the locking means so as to prevent any mutual disengagement of the wire and each of the removable fixing members.