WO2015079124A1

WO2015079124A1 - Support to be attached to an aircraft structure under maintenance, infrared emission assembly for heating a polymer material during maintenance and maintenance method for replacing an aircraft windshield

Info

Publication number: WO2015079124A1
Application number: PCT/FR2013/052895
Authority: WO
Inventors: Bruno Comoglio; Thierry REGOND
Original assignee: Sunaero-Helitest
Priority date: 2013-11-28
Filing date: 2013-11-28
Publication date: 2015-06-04

Abstract

This support (2) comprises: a frame (2.1); at least three suction cups (2.2); and connecting elements (2.4) for connecting an infrared emitter (4) to the frame (2.1). The frame (2.1) defines a closed outline. The support (2) further comprises at least three articulated arms (2.11, 2.12, 2.13) for connecting the suction cups (2.2) to the frame (2.1).

Description

SUPPORT FOR ATTACHING TO AN AIRCRAFT MAINTENANCE STRUCTURE, INFRARED EMISSION ASSEMBLY FOR HEATING A POLYMERIC MATERIAL IN MAINTENANCE, AND MAINTENANCE METHOD FOR REPLACING AN AIRCRAFT WINDSCREEN

The present invention relates to a support adapted to be removably attached to an aircraft structure so as to operate the maintenance of a structural component by means of infrared radiation. In addition, the present invention relates to an em ission assembly for emitting infrared radiation so as to heat a polymeric material for such a maintenance operation. In addition, the present invention relates to a maintenance method for replacing an aircraft windshield.

The present invention finds particular application in the field of aeronautical maintenance. In particular, the present invention finds application in the field of repair or replacement of aircraft windshields.

FR2705914A1 discloses an infrared em ission assembly comprising a support carrying an infrared emitter. The support of FR2705914A1 includes a support plate and two suction cups. Each suction cup is mounted on the backing plate with a clearance to adjust the position of the suction cups on the surface of the structural component to be repaired.

However, the use of suction cups at the support plate allows only a relatively small deflection, which limits the range allowed for adjusting the position of the suction cups. In other words, the support of FR2705914A1 can only be installed on planar structural components or with large radius of curvature.

In addition, the two suckers realize a hypostatic connection, and therefore an unstable installation, of the support on the structural component to be repaired. The FR2705914A1 can only be installed on structural components that are slightly inclined to the horizontal. The support of FR2705914A1 thus allows only repairs in the workshop, after dismantling the structural component of the aircraft structure, which requires a prolonged immobilization of the aircraft under maintenance.

The present invention aims to solve, in whole or in part, the problems mentioned above. To this end, the object of the invention is a support, intended to be removably attached to an aeron structure and so as to operate the maintenance of a structural component by means of infrared radiation. support comprising:

- a chassis ;

suckers, each sucker having a connector arranged for connection to a suction circuit for generating a depression under the suction pad;

at least one connecting element arranged to link at least one infrared emitter to the chassis;

the support being characterized in that the frame defines a closed contour, in that the number of suction cups is greater than or equal to three, and in that it further comprises at least three articulated arms arranged to connect the suction cups to the frame respectively. .

A ns i, u n such su pport makes it possible to operate the m n n n n an a structural component regardless of the local geometry of the aircraft structure. In particular, the number of at least three suction cups makes it possible to choose optimal locations for fixing the suction cups reliably. The closed contou of the chassis makes it possible to use the su pport for the maintenance of particular components, such as an aircraft windshield.

According to one embodiment of the invention, each connector comprises a non-return valve arranged to block a gaseous flow flowing in the direction of the suction cup.

Thus, such a non-return valve makes it possible to maintain the vacuum under a respective suction cup when the suction circuit is at a standstill.

According to one embodiment of the invention, each of the articulated arms comprises a three-segment kinematic chain, the intermediate segment comprising two pivot links.

Thus, such articulated arms allow a great latitude for adjusting the position of the suction cups, because each articulated arm makes it possible to reach any point of a sphere centered on the connection of the articulated arm to the frame.

According to one embodiment of the invention, each of the articulated arms is connected to the chassis by a spherical connection.

Thus, such a spherical connection allows great freedom of maneuvering the articulated arm. According to one embodiment of the invention, the closed contour is formed by at least two, preferably at least three, and more preferably at least four, intersecting bars at respective vertices, the support further comprising articulations, each articulation being arranged at a respective vertex so as to bond two respective bars.

In other words, when the closed contour is formed by four bars, it forms a three-dimensional quadrilateral or a tetrahedron with one edge missing.

Thus, such a closed contour allows to use the support for the maintenance of aircraft windshields.

According to a variant of the previous embodiment, each bar has a length greater than 200 mm.

Thus, such a length is suitable for most aircraft windshields.

According to another variant of the preceding embodiment, at least two articulated arms are connected to two respective joints and wherein at least one articulated arm is connected to an intermediate portion of a bar.

Thus, two such articulated arms are positioned in different nodes of the frame, which distributes the weight of the support fairly uniformly on each suction cup.

According to one embodiment of the invention, the support comprises three articulated arms, the links of the arms articulated to the frame occupying the vertices of a triangle, preferably an isosceles triangle.

It is possible to use isocer l permeability and distributes the weight of the support fairly uniformly over each of the three suction cups.

According to one embodiment of the invention, each element of the ison is configured to allow pivoting of a respective infrared emitter with respect to the chassis.

Thus, such pivoting makes it possible to adjust the orientation and the position of each infrared emitter, which makes it possible to adapt the support to different geometries of structural components.

According to one embodiment of the invention, the support comprises at least two connecting elements for linking an infrared emitter to the chassis. Thus, the weight of each infrared transmitter can be divided into several points of the chassis.

In addition, the present invention relates to an emission assembly, for emitting infrared radiation so as to heat a polymer material, such as an epoxy resin, for a maintenance operation of an aircraft structural component, transmission unit comprising a support according to the invention and at least one infrared emitter with power supply, said at least one infrared emitter being connected to the chassis by a respective connecting element.

In this application, the term "maintenance operation" may refer to the repair or replacement of an aircraft structural component.

Thus, such an emission unit makes it possible to operate the maintenance of a structural component irrespective of the local geometry of the aircraft structure.

According to one embodiment of the assembly that is the subject of the invention, the support is, according to the embodiment, having a closed contour formed by at least two, preferably at least three, and more preferably at least four, intersecting bars. transmission unit comprising four electrically powered infrared transmitters, each infrared transmitter being linked to a respective bar.

According to a variant of the invention, the closed contour is formed by at least two, preferably at least four, intersecting bars at respective vertices ("quadrilateral"), the support further comprising articulations, each articulation being arranged in a respective vertex so as to bond two respective bars, the transmission assembly comprising infrared emitters with power supply, each infrared emitter being connected to a respective bar.

Thus, such an emission unit makes it possible to operate the maintenance of particular components, such as an aircraft windshield.

According to one embodiment of the invention, each infrared emitter has a rectilinear shape and a length similar to the length of a respective bar.

Thus, such an infrared emitter is suitable for heating cords joining the edges of an aircraft windshield opening. Furthermore, the subject of the present invention is a maintenance method, for this runpa rebreath aircraft, comprising in particular the steps:

arranging beads of polymeric material, such as silicone, on each edge of a windshield opening to form the windshield seals;

installing an emission assembly according to the invention, with the suction cups removably attached to the aircraft structure around the edge of the windshield;

replace a windshield by tying it on the cords;

adjust the position of the infrared emitters; and activate the infrared emitters to heat the cords.

Thus, such a method allows to perform maintenance in situ, that is to say directly on the aircraft, different aircraft windshields.

The embodiments of the invention and the variants of the invention mentioned above can be taken individually or in any combination technically possible.

The present invention will be well understood and its advantages will also emerge from the following description, given solely by way of nonlimiting example and with reference to the appended drawings, in which:

Figure 1 is a perspective view of an emission assembly according to the invention, comprising a support according to the invention; Figure 1 illustrates connections of the support to a suction circuit;

Figure 2 is a perspective view of a control unit of the transmission assembly of Figure 1, with connections to the suction circuit;

Figure 3 is a view similar to Figure 1 of the transmission assembly of Figure 1; Figure 3 illustrates connections of the transmit assembly to an electrical power circuit; Figure 4 is a view similar to Figure 2 of the control unit of Figure 2, with connections to the power circuit;

Figure 5 is a perspective view of an inner portion of the control unit of Figure 2;

Figure 6 is a perspective view of an inner portion of the control unit of Figure 4;

Figure 7 is a perspective view of the emission assembly of Figure 1, installed in situ around an aircraft windshield;

Figure 8 is a detail view VIII in Figure 7; and Figure 9 is a flowchart illustrating a method according to the invention.

FIGS. 1, 2, 3, 4, 5, 6, 7 and 8 illustrate an emission unit 1 for emitting infrared radiation so as to heat a polymer material for a maintenance, repair or replacement operation of a component aircraft structure. In the example of Figures 7 and 8, the polymer material is a silicone bead (polysiloxane) applied to the edges of a windshield to form a seal.

As shown in FIG. 1, the emission unit 1 comprises a support 2 and four infrared emitters 4 with electrical power supply. The four infrared emitters 4 are linked to the support 2.

As shown in Figures 7 and 8, the support 2 is intended to be removably attached to an aircraft structure, here an aircraft, so as to operate the maintenance of a structural component, here a windshield, to means of infrared radiation

The support 2 comprises a frame 2.1, three suction cups 2.2 and connecting elements 2.4 which are arranged to link a respective infrared transmitter 4 to the frame 2.1. In the example of Figures 1 and 3, each connecting element 2.2 is configured to allow pivoting of a respective infrared transmitter 4 relative to the chassis 2.1. Each infrared transmitter 4 is here linked to the frame 2.1 by two respective connecting elements 2.4.

The chassis 2.1 defines a closed contour. In the example of the figures, this closed contour is formed by four bars 2.6 which are two by two intersecting in four respective vertices. Each infrared transmitter 4 is linked to a respective bar 2.6.

Each bar 2.6 has a length greater than 500 mm. In this case two bars 2.6 have a length of about 500 mm and two other bars 2.6 have a length of about 850 mm. In the example of FIGS. 1 and 3, each infrared emitter 4 has a rectilinear shape and a length similar to the length of the respective bar 2.6 to which it is linked.

In addition, the seat 2 comprises four hinges 2.8 belonging to the frame 2.1. Each hinge 2.8 is arranged at u respective vertex so as to link two respective bars 2.6. In other words, the closed outline forms a quadrilateral in three dimensions (plane or not).

The support 2 further comprises three articulated arms 2.1 1, 2.12 and 2.13 which are arranged to connect respectively the suction cups 2.2 to the frame 2.1. In the example of FIGS. 1 and 3, the links of the articulated arms 2.1 1, 2.1 2 and 2.13 to the chassis 2.1 occupy the vertices of an isosceles triangle. The articulated arms 2.1 2 and 2.13 are connected to two respective joints 2.8, as the articulated arm 2.1 1 is connected to an intermediate portion of a bar 2.6.

Each of the arms 2.1 1, 2.12 and 2.1 3 is connected to the frame 2.1 by a spherical connection, sometimes referred to as a ball joint. Each of the articulated arms 2.1 1, 2.12 and 2.13 comprises a three-segment kinematic chain, such as the segments 2.121, 2.122 and 2.1 23 for the articulated arm 2.12.

The intermediate segment 2.1 22 comprises two pivot links, respectively with the first segment 2.121 and with the third segment 2.123. Each of these pivot links is arranged to allow pivoting of one segment relative (2.1 21, 2.1 22) to another (2.1 22, 2.1 23) of about 90 ° and in a plane substantially transverse to a plane defined by the four bars 2.6.

Each suction cup 2.2 has a fitting 2.21. Su pport 2 therefore comprises three connectors 2.21. Each connector 2.21 is arranged for connecting the respective suction cup 2.2 to a suction circuit 12. The suction circuit 1 2 is symbolized by curved lines in FIGS. 1 and 2. Each of these curved features materializes a flexible hose. consistent for the vacuum level prevailing in the suction cups 2.2, for example 850 mbar absolute pressure.

When the emission unit 1 is in use, the suction circuit is intended to generate a vacuum under the suction pad 2.2. Each connector 2.21 comprises a not shown check valve which is arranged to block a gas flow flowing in the direction of the respective suction pad 2.2.

Figure 2 illustrates a control unit 20 which is configured to control and control the operation of the transmit unit 1. The control unit 20 includes an interface 21 for displaying information to an operator. The control unit 20 is connected to the suction circuit 12 by two flexible pipes 22.

As shown in Figure 5, the control unit 20 further comprises two vacuostats 24 adapted to detect any shutdown of the suction circuit 12. A vacuum switch has the function of detecting a depression. When a vacuum switch 24 detects a shutdown of the suction circuit 12, the control unit issues an alert. The threshold of this alert can be set according to the configuration of use.

The suction circuit 12 is essentially operated by a vacuum pump 26, which here is of the double-body vacuum pump type. The vacuum pump 26 makes it possible to evacuate in the suction circuit 12, thus in the suction cups 2.2, at an absolute pressure of approximately 850 mbar.

The vacuum pump 26 is electrically powered at a voltage of 24 V by a transformer 30 itself connected to a power outlet 31 at a voltage of 500 V.

FIGS. 3 and 4 illustrate a control circuit connecting the control unit 12 to the transmission unit 1. The control unit 12 furthermore comprises an electric disconnector 41, electrical protection elements (fuses or differentials) 42, three-phase relays 44, a setpoint cable 46 connecting the interface 21 to the three-phase relays 44 and a power cable 48 to supply the transmission assembly 1.

Furthermore, the emission unit 1 further comprises temperature sensors 50. Each temperature sensor 50 is arranged to remotely measure the temperature of the target to be heated. Each Temperature sensor 50 may be formed of an infrared sensor to receive infrared rays emitted by the heated target.

The temperature sensors 50 are connected to a control unit 12 by means of a bundle of four measurement cables 52. Thus, the temperature sensors 50 allow the control unit 12 to regulate the electrical power supplying the control unit. the infrared emitters 4 according to a target temperature to be reached on the target. This produces a control loop.

Figures 7, 8 and 9 illustrate an in situ maintenance process according to the invention. For the clarity of FIGS. 7 and 8, only one infrared emitter 4 is shown.

When the emission assembly 1 is service to replace a windshield P of aircraft A, the steps are carried out:

101) arranging cords not shown in a silicon (polysiloxane) on each edge of a windshield opening. Method for forming the windshield seals P;

102) install the emission assembly 1, with the suction cups 2.2 removably attached to the structure of the aircraft A around the edge of the windshield P;

103) replace a windshield P by plating it on the cords;

104) adjust the position of the infrared emitters 4; and 105) activate the infrared emitters 4 so as to heat the cords.

Claims

1. Support (2) for detachably fastening to an aircraft structure (A) so as to maintain a structural component (P) by means of an infrared ray, the carrier (2) comprising :

a frame (2.1);

suction cups (2.2), each suction cup (2.2) having a connector (2.21) arranged for connection to a suction circuit (12) for generating vacuum under the suction cup (2.2);

at least one connecting element (2.4) arranged to connect at least one infrared emitter to the frame (2.1);

the support (2) being characterized in that the frame (2.1) defines a closed contour, in that the number of suction cups (2.2) is greater than or equal to three, and in that it further comprises at least three arms articulated (2.1 1, 2.12, 2.13) arranged to connect respectively the suction cups (2.2) to the frame (2.1).

2. Support (2) according to claim 1, wherein each connector (2.21) comprises a non-return valve arranged to block a gaseous flow flowing in the direction of the suction cup (2.2).

3. Support (2) according to one of the preceding claims, wherein each of the articulated arms (2.1 1, 2.1 2, 2.1 3) comprises a three-segment kinematic chain (2.1 21, 2.1 22, 2.1 23), the segment intermediate (2.122) having two pivot links.

4. Support (2) according to one of the preceding claims, wherein eq uel each of the articulated arms (2.1 1, 2.12, 2.13) is connected to the frame (2.1) by a spherical connection.

5. Support (2) according to one of the preceding claims, wherein the closed contour is formed by at least two, preferably at least three and more preferably at least four secant bars (2.6) in respective vertices, the support (2) further comprising hinges (2.8), each hinge (2.8) being arranged at a respective vertex so as to connect two respective bars (2.6).

6. Support (2) according to claim 5, wherein each bar (2.6) has a length greater than 200 mm.

7. Support (2) according to one of claims 5 to 6, wherein at least two articulated arms (2.11, 2.12, 2.13) are connected to two respective joints (2.8) and wherein at least one articulated arm (2.11, 2.12, 2.13) is linked to an intermediate portion of a bar (2.6).

8. Support (2) according to one of the preceding claims, comprising three articulated arms (2.11, 2.12, 2.13), the links of the articulated arms (2.11, 2.12, 2.13) to the frame (2.1) occupying the vertices of a triangle. preferably an isosceles triangle.

9. Support (2) according to one of the preceding claims, wherein each connecting element (2.4) is configured to allow pivoting of a respective infrared transmitter (4) relative to the frame (2.1).

10. Support (2) according to claim 9, comprising at least two connecting elements (2.4) for linking an infrared transmitter (4) to the frame (2.1).

Emission assembly (1), for emitting infrared radiation so as to heat a polymeric material, such as an epoxy resin, for a maintenance operation of an aircraft structural component (P) (A), the transmission assembly (1) comprising a support (2) according to one of the preceding claims and at least one infrared emitter (4) with an electrical power supply, said at least one infrared emitter (4) being linked to the chassis (2.1) by a respective connecting element (2.4).

12. emission assembly (1) according to claim 1 1, wherein the carrier (2) is according to one of claims 5 to 7, the transmission assembly comprising four infrared emitters (4) power supply , red emitter sensor (4) being connected to a respective bar (2.6).

The transmission assembly of claim 12, wherein each infrared emitter has a straight shape and a length similar to the length of a respective bar.

14. Maintenance process, for replacing an aircraft windshield (P) (A), comprising in particular the steps:

arranging beads of polymeric material, such as silicone, on each edge of a windshield opening (P) to form the windshield seals (P);

installing a transmission assembly (1) according to one of claims 1 1 to 13, with the suction cups (2.2) removably attached to the aircraft structure (A) around the edge of the windshield (P);

replace a windshield (P) by pressing it on the cords;

adjust the position of the infrared emitters (4); and activate the infrared emitters (4) to heat the cords.