Hinge for hinging two panels of an aircraft propulsion assembly

Abstract

The invention relates to an aircraft propulsion assembly (10) comprising a hinge (20) for articulating a first panel and a second panel, the hinge (20) comprising a yoke (22) rigidly connected to the first panel (16) and a counter-yoke (24) rigidly connected to the second panel (18), the counter-yoke being received between two lugs (28) of the yoke (22), the yoke (22) and the counter-yoke (24) being crossed by a hinge pin (26) which is mobile between an extended position between the lugs (28) of the yoke (26) and a retracted position outside the yoke (26), characterized in that the hinge comprises a bayonet mounting device (30) interposed between the pin (26) and the yoke (22).

Description

TECHNICAL FIELD

[0001] The present invention relates to an aircraft propulsion assembly comprising a hinged hinge between two panels of the aircraft propulsion assembly, in particular between panels of a nacelle which make it possible to access a turbine housed in the nacelle. BACKGROUND

[0002] The nacelles of aircraft propulsion assemblies comprise nacelles which house a turbojet engine, the nacelles generally comprising at least two wing sheath-like hinged panels which make it possible to access the turbojet engine. For obvious protection and aerodynamic reasons, the hinged hinges of these panels are generally carried by the inner faces of the panels and by the walls of the nacelle, so as to avoid any aerodynamic drag. The hinges are thus not easily accessible, making it difficult to assemble the hinges.

[0003] Such a hinged hinge comprises a U-shaped clip which is fixed to one of the panels, a counter U-shaped clip being housed between the ears of the U-shaped clip, the counter U-shaped clip being hinged in the U-shaped clip by a shaft passing through the ears of the U-shaped clip and the counter U-shaped clip.

[0004] Conventionally, the shaft comprises a screw, one head of which is supported on one of the ears of the U-shaped clip and the screw is fixed on the opposite ear of the U-shaped clip by a nut. Such a design is described in document EP-3.184.434-A1.

[0005] The drawback of such a design is that a spanner is necessary to tighten the screw on each side of the U-shaped clip, such an operation not being easily done due to the limited space available. It is not possible to transpose the teaching of document FR-817.184 which describes a furniture hinge with two opposite extractable shafts to such a hinge, since this solution does not solve the accessibility problem.

[0006] In order to overcome this drawback, a device such as described in document US-2008 / 0056814-A1 comprises a shaft equipped with a small diameter ball swell device. The introduction of the shaft is done from one side of the U-shaped clip, then by means of a control device located on the side of the U-shaped clip into which the shaft is introduced, the ball swell device is extended so that the ball swell device makes it possible to lock the ball swell device on the opposite side of the U-shaped clip.

[0007] The drawback of such a design is that, due to the small size of the ball, the resistance of the device to vibrations is limited, so that the shaft can be unlocked and extracted from the hinge by vibrations alone, with the risk of losing the panel which follows.

[0008] Other devices have also been considered, for example the device in document EP-3.553.331-A1 which comprises a shaft which is axially fixed by a swellable device.

[0009] There is therefore a real need for an aircraft propulsion assembly comprising a first panel and a second panel between which a hinge is arranged, the hinge being equipped with a shaft which can be introduced on one side of the clamp, thereby guaranteeing the reliable locking of the shaft in the hinge. Hinges of this type are known from the document WO-01 / 16450-A1 but have never been applied to the hinging of panels of this type. SUMMARY

[0010] The invention meets this need by providing a new hinge design comprising a shaft which can be introduced on one side of a U-shaped clamp and which can be securely locked in the U-shaped clamp.

[0011] To this end, the invention proposes a propulsion assembly comprising a nacelle housing a turbojet engine, said nacelle comprising at least a first panel and a second panel between which a hinging hinge is arranged, the hinging hinge comprising a U-shaped clamp fixed to the first panel and a reverse U-shaped clamp fixed to the second panel, the reverse U-shaped clamp being received between the two ears of the U-shaped clamp, the U-shaped clamp and the reverse U-shaped clamp being crossed by a hinging shaft which can move between an extended position between the ears of the U-shaped clamp and a retracted position outside the U-shaped clamp, characterized in that the hinge comprises a bayonet mounting device inserted between the shaft and the U-shaped clamp.

[0012] Bayonet mounting devices are well known in the state of the art in general engineering. Such mounting devices comprise means for attaching an object to a cylindrical base, such as a shaft equipped with one or more lugs, the lugs being engaged by rotation in the seats provided for this purpose in another cylindrical element. Such mounting devices are reversible by a translational movement of the shaft, followed by a limited rotational movement of the shaft, to bring the lug(s) into the seats, the security of the lock being obtained by the pressure on the shaft, or directly on the lugs, of an elastic return device, to retain the lugs in the seats. The unlocking operation is carried out by the action of a translational force opposite to that exerted by the elastic return device, followed by a rotation in the opposite direction to extract the lugs from the seats and a reverse translational movement of the shaft.

[0013] According to other characteristics of the propulsion assembly:

[0014] - the bayonet mounting device comprises:

[0015] o two opposite lugs extending radially from the shaft,

[0016] o a housing, a bottom plate of which is attached to the ear of the clevis outside the clevis, a shaft passes through the housing, and the housing comprises a cylinder which extends from the bottom plate and outside the clevis, the cylinder receiving a mechanism for locking / unlocking the lugs according to the axial and angular position of the shaft, and a tubular sleeve which extends from the cylinder, the tubular sleeve being intended to receive the shaft and guide it in translation and in rotation so as to enable the shaft to pass from an extended position of the shaft in the clevis to a retracted position of the shaft outside the clevis and into the housing,

[0017] o a handle which projects from the sleeve at the free end of the shaft, enabling the shaft to be manipulated axially and angularly,

[0018] - the locking / unlocking mechanism comprises:

[0019] o two opposite flat walls parallel to the shaft, a first slot being formed in each of the two flat walls, the first slot comprising a slit for fixing the lug and a window portion for disengaging and introducing the lug, the slit being oriented perpendicularly to the shaft and being configured to receive and axially fix an end extension of the corresponding lug between the laterally oriented edges of the slit, the window portion being adjacent to the fixing slit and having a substantially trapezoidal shape, the lug being able to pass through the window portion to disengage from said wall and from said fixing slit when the shaft is rotated to unlock the shaft, the edge of the window portion being able to guide the lug towards the fixing slit when the shaft is rotated in the opposite direction to lock the shaft,

[0020] o at least one device for locking the lug in the slit to fix the first slot,

[0021] - the device for locking the lug comprises a cam which is diametrically opposite with respect to the shaft and which carries a notch complementary to the intermediate extension of said lug and a ramp adjacent to said notch, the cam being received in an internal housing of the cylinder around the shaft, the cam being elastically returned by at least one return spring when it slides against the lug, and the cam being able to move between a position in which it fixes the lug in the notch of the cam and a position of pivoting of the shaft which enables the lug to exert a pressure on the ramp of the cam and then to exit the slit for fixing the first slot, against the force exerted by the at least one return spring,

[0022] - the cam is carried diametrically opposite to each other by the outer periphery of a ring which slides on the shaft and which is fixed in rotation with respect to the housing, the ring being elastically returned against the lug by a spring which slides on the shaft and which is supported between the ring and the surface of the bottom plate through which the shaft passes,

[0023] - the housing comprises two walls arranged at 90° to the flat walls, in which two longitudinal guide slots are arranged diametrically opposite with respect to the shaft and extending at least between the intermediate portion of the cylinder and the sleeve, for receiving the lug between the edges of the longitudinal guide slots after the shaft has been rotated through 90° and the lug has been disengaged from the fixing slot, so as to enable the lug to exit from the housing and thus the lug and the shaft to slide in the sleeve, which enables the shaft to be transferred from the extended position of the shaft in the clevis to the retracted position of the shaft in the housing,

[0024] - the longitudinal guide slots extend into the intermediate portion of the cylinder, the ring being fixed in rotation with respect to the housing by means of two diametrically opposite arms extending from the ring and received in the longitudinal guide slots,

[0025] - the spring has a diameter smaller than that of the through hole in the bottom plate through which the shaft is introduced into the housing, and the flat walls of the housing each comprise, in the vicinity of the bottom plate, a second oblong slot oriented perpendicularly to the shaft, the second oblong slot being configured to enable at least a lateral introduction of a washer for supporting the spring, the washer having a diameter greater than that of the through hole,

[0026] - the lug is formed by a cylindrical pin which is housed in a transverse through hole of the shaft,

[0027] The invention also relates to a method for locking and unlocking the shaft of a hinge of the aforementioned type, characterized in that it comprises:

[0028] - a locking step comprising:

[0029] o a first locking sub-step, in which the lug of the shaft is received in the longitudinal slot, the shaft is subjected to an axial pressure until the lug exerts a pressure on the ring and compresses the spring,

[0030] o a second locking sub-step, in which the shaft is rotated through 90° in a first direction until the lug, guided by the disengagement of the first slot and the ramp of the extension and of the ring, enters the fixing slot of the first slot and the notch of the ring, then the shaft occupies the extended position of the shaft,

[0031] o a third locking sub-step, in which the shaft is released.

[0032] - an unlocking step comprising:

[0033] o a first unlocking sub-step, in which the shaft is rotated in a second direction until the lug exits from the notch of the ring, then exerts a pressure on the ramp of the ring and pushes the ring backwards, the lug leaving the slot for fixing the first slot,

[0034] o a second unlocking sub-step, in which, by continuing the rotation of the shaft by 90 degrees, the lug leaves the first slot and is aligned with the longitudinal guide slit,

[0035] o a third unlocking sub-step, in which the shaft is released so that the lug enters the portion of the longitudinal guide slit that extends into the sleeve under the thrust of the ring, which is subjected to the pressure exerted by the return force of the spring, and then the shaft occupies the retracted position of the shaft. BRIEF DESCRIPTION OF DRAWINGS

[0036] Other characteristics and advantages of the application will become apparent from the following detailed description, made with reference to the attached drawings, which are provided by way of non-limiting example and in which:

[0037] [ Figure 1 ] Figure 1 is a schematic view of the underside of a fuselage of an aircraft comprising a hinge according to the application;

[0038] [ Figure 2 ] Figure 2 is a perspective view of a hinge according to the application;

[0039] [ Figure 3 ] Figure 3 is a side view showing the shaft locked in the extended position and the bayonet mounting device for this shaft;

[0040] [ Figure 4 ] Figure 4 is a cross-sectional view showing the shaft locked in the extended position and the bayonet mounting device for this shaft;

[0041] [ Figure 5 ] Figure 5 is a partial perspective view showing the shaft pulled out, locked in the extended position, and the bayonet mounting device for this shaft;

[0042] [ Figure 6 ] Figure 6 is a perspective view of the elements inside the housing of the bayonet mounting device;

[0043] [ Figure 7 ] Figure 7 is a detailed perspective view of the ring forming part of the internal elements of Figure 6 ;

[0044] [ Figure 8 ] Figure 8 is a perspective view showing the shaft locked in the extended position and the bayonet mounting device for this shaft;

[0045] [ Figure 9 ] Figure 9 is a transparent view of Figure 8 ;

[0046] [ Figure 10 ] Figure 10 is a transparent perspective view of the beginning of the first sub-step of locking the shaft;

[0047] [ Figure 11 ] Figure 11 is a transparent perspective view of the end of the first sub-step of locking the shaft;

[0048] [ Figure 12 ] Figure 12 is a transparent side view during the second sub-step of locking the shaft;

[0049] [ Figure 13 ] Figure 13 is a transparent side view of the end of the second sub-step of locking the shaft;

[0050] [ Figure 14 ] Figure 14 is a transparent side view of the first sub-step of unlocking the shaft;

[0051] [ Figure 15 ] Figure 15 is a transparent side view during the second sub-step of unlocking the shaft;

[0052] [ Figure 16 ] Figure 16 is a perspective transparent view of the end of the second sub-step of unlocking the shaft;

[0053] [ Figure 17 ] Figure 17 is a perspective transparent view during the third sub-step of unlocking the shaft;

[0054] [ Figure 18 ] Figure 18 is a perspective transparent view of the end of the third sub-step of unlocking the shaft;

[0055] [ Figure 19 ] Figure 19 is a block diagram showing the steps of the locking and unlocking methods according to the application. DETAILED DESCRIPTION

[0056] Figure 1 An aircraft propulsion assembly 10 is shown. In a well-known manner, the propulsion assembly 10 comprises a nacelle 12 housing a turbojet engine 14. The nacelle 12 comprises various fixed panels 16 and at least two pteryloid pivoting panels 18 which are pivoted in a well-known manner about respective axes of pivoting 20. Figure 1The pivoting panels 18 are shown in the open position and enable access to the turbojet engine 14. These pivoting panels 18 comprise free edges 19 which can be locked together by locks 21, 23 when in the closed position. These pivoting panels are hinged to the fixed panels by hinges 20 which are the subject of the application.

[0057] In a known manner, as shown in Figure 2 , each hinge 20 comprises a U-shaped clip 22 fixed to a first panel which receives an inverted U-shaped clip 24 fixed to a second panel. In Figure 1 and Figure 2 , the U-shaped clip 22 is fixed to a first fixed panel 16 and the inverted U-shaped clip 24 is fixed to a second pivoting panel 18, but it will be understood that this arrangement does not limit the application.

[0058] As shown in Figure 2 , each hinge 20 comprises a hinging shaft 26 between the U-shaped clip 22 and the inverted U-shaped clip 24.

[0059] In particular, the inverted U-shaped clip 24 is received between the two ears 28 of the U-shaped clip 22. The ears 28 of the U-shaped clip 22 and the inverted U-shaped clip 24 are crossed by the shaft 26.

[0060] The shaft 26 can be extracted from the U-shaped clip 22 and the inverted U-shaped clip 24 to enable the panels 18 to be dismantled. To this end, the shaft must be able to move between an extended position between the ears 28 of the U-shaped clip 22, as shown in Figure 2 , and a retracted position outside the U-shaped clip 22 which enables the inverted U-shaped clip 24 to be released.

[0061] As shown in Figure 1 , the hinges 20 are arranged inside the nacelle 12 so that the shafts 26 of the hinges are not easily accessible and in particular not easily accessible to a spanner which enables installation and dismantling by conventional means, such as a screw and a nut. It is therefore desirable for the shafts 26 of these hinges 20 to be installed without a tool and only on one side of the hinge 20.

[0062] To meet this need, the application proposes a bayonet mounting device 30 which is inserted between the shaft 26 and the U-shaped clip 22, which enables the shaft to be mounted on the U-shaped clip 22 and extracted from the U-shaped clip 22 only from one side of said U-shaped clip 22.

[0063] As shown in the transparent view in Figure 9 , the bayonet mounting device 30 first comprises two opposite lugs 32 which extend radially from the shaft 26.

[0064] The lugs 32 are formed, for example, by a single cylindrical pin 31 which is housed in a transverse through-hole 33 in the shaft 26, as shown in Figure 6 .

[0065] The bayonet mounting device 30 also comprises a housing 34, the floor 36 of which is attached to the lug 28 of the clevis 22 outside the clevis 22, as shown in Figure 2 . The floor 36 is attached to the lug 28 of the clevis 22, for example, by screws 40 which pass through perforations 41 in the floor 36.

[0066] The housing 34 is crossed by the shaft 26. The shaft 26 passes through a through-hole 85 in the floor 26, as can be seen in particular in Figure 3 and Figure 8 . The housing 34 comprises, in general, a barrel 38 which extends from the floor 36 and outside the clevis 28, the barrel receiving, in an internal housing 44, more particularly visible in Figure 4 , a mechanism 46 for locking / unlocking the lugs 32 as a function of the axial and angular position of the shaft 26.

[0067] A tubular sleeve 48 extends from this barrel 38, for receiving the shaft 26 and guiding it in translation and in rotation, so as to enable the shaft 26 to pass from an extended position of the shaft in the clevis 22, as shown in Figures 3 to 9 , Figure 13 and Figure 14 , to a retracted position of the shaft outside the clevis 22 and into the housing 34, as shown in Figure 18 .

[0068] As mentioned above, the locking and unlocking of the shaft 26 as a function of the axial and angular position of the shaft 26, enabling the lugs 32 to be locked or unlocked, is achieved by the bayonet mounting device 30, the shaft comprising, for this purpose, a handle 50 which projects from the sleeve 48 at the free end of the shaft 26, so as to enable the shaft to be manipulated axially and angularly.

[0069] In order to enable the lugs 32 to be locked or unlocked, the locking / unlocking mechanism 46 comprises, as shown in Figure 3 and Figure 8 , two opposite flat walls 51 of the barrel 38 which are parallel to the shaft 26, each of the two flat walls being formed with a first slot 52 comprising a slit 56 for fixing the lug 32, the slit being oriented perpendicularly to the shaft 26 and for fixing the lug 32 axially and therefore the shaft 26.

[0070] More particularly, as shown in Figure 8 and Figure 9 , each slit 56 comprises a transversely oriented edge 58 for receiving and fixing axially an end extension 60 of the corresponding lug 32.

[0071] The first slot 52 also comprises window portions 62 for the disengagement and introduction of the lugs 32. Each window portion 62 is adjacent to and communicates with the fixed slit 56, and each window portion is shaped as a trapezoid. This window portion 62 enables the release of the lug 32 so that, when the shaft 26 is rotated to unlock the shaft, the lug 32 can disengage from the fixed slit 56, and thus from the wall 51, as Figure 15 illustrated.

[0072] In Figures 14 to 18 , it is shown that the unlocking of the lug 32 is obtained by a clockwise rotation of the shaft 26. Obviously, it should be understood that, if the first slot 52 were reversed with respect to the configuration shown, the unlocking of the lug 32 would be achieved by a rotation of the shaft 26 in the opposite direction, i.e. anticlockwise.

[0073] As Figure 2 and Figure 3 illustrated, the window portion 62 comprises a sloped edge 64 forming a ramp through which the lug 32 can be guided towards the fixed slit when the shaft 26 is counter-rotated, i.e. here in the anticlockwise direction, to lock the shaft. Figure 12 This configuration shown illustrates the lug 32 sliding on the edge 64 before entering the fixed slit 56.

[0074] It should be noted that the retention of the lug 32 in the fixed slit 56 is achieved by a locking device 66 which will now be described.

[0075] In principle, Figure 6 and Figure 7 , the locking device 66 for the lug 32 comprises cams 68 which are diametrically opposite with respect to the shaft 26 and which are elastically returned against the lug 32. In Figure 7 , the position of the theoretical axis A of the shaft 26 is shown.

[0076] These cams 68 are received in the internal housing 44 of the barrel 38 around the shaft 26.

[0077] The cams 68 can be carried by the inner surface of the opposite flat walls 51 and are independent of each other.

[0078] However, as will be seen in the remainder of the present description, the cams 68 are carried by a common element for reasons of manufacturing simplification.

[0079] The cams 68 carry notches 70 which are complementary to the intermediate extension 72 of the lug 32. Thus, the cams do not interfere with the end extension 60 of the lug 32 shown previously. The cams 68 also comprise ramps 74 adjacent to the notches 70. Finally, the cams 68 are elastically returned by at least one return spring 76 when sliding against the lug 32.

[0080] The resetting of the cams 68 by at least one spring 76 has the advantage of guaranteeing the locking of the lugs 32 whatever the vibrations to which the bayonet mounting device 30 is subjected. In particular, the resetting of the cams by at least one spring makes it possible to ensure the continuous contact of the cams 68 on the lugs 32, which guarantees the integrity of the hinge 20 and therefore of the pivoting panel 18.

[0081] It will thus be understood that if the locking / unlocking mechanism were to comprise independent cams 68, these would be reset by two independent resetting springs 76, but since in the configuration illustrated here the cams are carried by a common element, the cams are reset by a single resetting spring 76.

[0082] The cams 68 are able to move between a position in which the cams fix the lugs 32 in the notches 70, as illustrated in Figure 6 , Figure 9 , Figure 13 and the pivoting of the shaft 26 makes it possible for the lugs 32 to exert a pressure on the slopes 74 and then to exit the fixing slits 56 of the first slots 52, as illustrated in Figure 15 .

[0083] As illustrated in Figure 6 , the cams 68 are carried radially opposite one another by the outer periphery of a ring 78, which slides around the shaft 26 and which is fixed in rotation relative to the housing 34. The ring 78 is elastically reset against the lugs 32 by a single spring 76, which slides around the shaft 26 and which is supported between the ring 78 and a surface 80 of the bottom plate 36, the perforation 85 of which is passed through by the shaft 26. In this way, the ring 78 exerts a pressure on the lugs 32, in particular when the lugs are received in the notches 70, so as to lock the lugs 32 and thus fix the shaft 26 in rotation. Details of how the ring 78 is fixed in rotation will be described later in the present description.

[0084] More particularly, the spring 68 is not directly supported on the surface 80 of the bottom plate 36, but is supported on an assembly support washer 82 for installation reasons, which itself is supported on this surface 80. This washer 82 makes it possible to prevent the spring 68 from coming out of the housing. The diameter of the spring 68 is less than the diameter of the perforation 85 formed in the bottom surface 80 of the housing 34, and the spring is introduced into the housing 34 on the shaft 26 through this perforation 85. In order to prevent the spring 68 from coming out through this perforation 85, the flat walls 51 of the housing each comprise, near the bottom plate 36, a second oblong slot 81 oriented perpendicularly to the shaft, the second oblong slot being configured so as to make it possible to at least introduce the support washer 82 into the housing 34, which receives the spring 68 in a supporting manner, and the diameter of which is greater than the diameter of the perforation 85, so as to prevent the spring from coming out.

[0085] For example, as shown in Figure 3 , Figure 4 and Figure 8 , the housing 34 comprises, in addition to the two opposite flat walls 51, two walls 86 arranged at 90° from the flat walls 51, in which two longitudinal guide slits 88 are arranged, which are diametrically opposite with respect to the shaft 26 and extend longitudinally at least between the intermediate portion of the barrel 38 and the sleeve 49. These longitudinal slits 88 serve to receive the lugs 32 between the edges of the longitudinal slits, after the shaft 26 has been rotated by 90° and the lugs 32 have been disengaged from the fixing slits 56, to enable the lugs to come out of the housing 34 and thus enable the lugs 32 and the shaft 26 to slide in the sleeve 48. This enables the shaft 26 to be moved back from the extended position of the shaft in the clevis to the retracted position of the shaft in the housing 34, as shown in Figure 17 and Figure 18 .

[0086] Advantageously, the guide slits 88 not only serve to guide the lugs 32 but also enable the fixing of the ring 78. To this end, the longitudinal guide slits 88 extend into the intermediate portion of the barrel 38, the ring 78 being fixed in rotation with respect to the housing by means of two diametrically opposite arms 90 extending from the ring 78 and received in said longitudinal guide slits 88. These arms 90 not only enable the rotation of the ring 78 to be prevented but also guide the sliding of the ring 78 when the ring is subjected to an axial pressure by the lugs 32, as will be seen in the remainder of the description.

[0087] In this configuration, as shown in Figure 19 , the shaft 26 can be very simply locked and unlocked from the hinge 20 and in particular from the clevis 22 by means of a method comprising a locking step ETV and an unlocking step ETD.

[0088] The locking step ETV comprises a first locking sub-step SETV1 during which the lugs 32 of the shaft are received in the longitudinal slits 88 (as shown in Figure 10 ), the shaft 26 being subjected to an axial pressure until the lugs 32 exert a pressure on the ring 78 and compress the spring 76 (as shown in Figure 11 ). Then, in a second locking sub-step SETV2, the shaft 26 is rotated by 90° in a first anticlockwise direction (as shown in Figure 12 ), until the lugs, guided by the inclined edges 64 of the window portion 62 and by the ramp 74 of the ring 78 (as shown in Figure 12 ), enter the fixing slits 56 of the first slot 52 and into the notches 70 of the ring 78 (as shown in Figure 13The locking step ETV comprises a first locking sub-step SETV1 during which the shaft 26 is rotated in the first clockwise direction until the lug 32 is received in the fixed slot 56 of the first groove 52, as shown in figure 6.

[0089] Conversely, the unlocking step ETD comprises a first unlocking sub-step SETD1 during which the shaft 26 is rotated in the second clockwise direction until the lug 32 is received in the fixed slot 56 of the first groove 52, as shown in figure 8. Figure 14 From the position of figure 8 in which the lug 32 is received in the fixed slot 56, the shaft 26 is rotated in the second clockwise direction until the lug 32 comes out of the notch 70 of the ring 78, then by exerting pressure on the ramp 74 of the ring 78 and pushing the ring 78 backwards, the lug exits the fixed slot 56 of the first groove 52, as shown in figure 9. Figure 15

[0090] The unlocking step ETD then comprises a second unlocking sub-step SETD2 in which, by continuing to rotate the shaft by 90°, the lug exits the first groove 52 and is aligned with the longitudinal guide slot 88, as shown in figure 10. Figure 16

[0091] Finally, the unlocking step ETD comprises a third unlocking sub-step SETD3 during which the shaft 26 is released, as shown in figure 11, so that the lug 32 penetrates the portion of the longitudinal guide slot 88 that extends into the sleeve 48 under the thrust of the ring 78 (the ring is pressed by the return force of the spring 68), the shaft 26 moves backwards into the sleeve 48 and then occupies the retracted position of the shaft, as shown in figure 12. Figure 17 Figure 18

[0092] The invention thus advantageously makes it very easy to introduce the shaft 26 into the clevis 22 of the hinge 20 and to extract it from the clevis of the hinge, on one side of the clevis only and simply by manipulating the handle 50 without tools. The invention also proposes an efficient and durable locking system that avoids dismantling of the hinge, since the hinge is a housing in the known devices of the prior art.​​​​

Claims

1. An aircraft propulsion assembly (10) comprising a nacelle (12) housing a turbojet engine (14), the nacelle (12) comprising at least a first panel (16) and a second panel (18) between which is provided a hinged hinge (20) comprising a U-shaped clip (22) fixed to the first panel (16) and a reversed U-shaped clip (24) fixed to the second panel (18), the reversed U-shaped clip being received between two ears (28) of the U-shaped clip (22), the U-shaped clip (22) and the reversed U-shaped clip (24) being crossed by a hinged shaft (26) movable between an extended position between the ears (28) of the U-shaped clip (22) and a retracted position outside the U-shaped clip (22), characterized in that the hinged hinge comprising a bayonet mounting device (30) inserted between the hinged shaft (26) and the U-shaped clip (22), the bayonet mounting device comprising: - two opposite lugs (32) extending radially from the hinged shaft, - a housing (34) whose floor (36) is attached to the ears (28) of the U-shaped clip (22) outside the U-shaped clip (22), the hinged shaft (26) passing through the housing, and the housing comprising a cylinder (38) extending from the floor (36) and outside the U-shaped clip (22), the cylinder receiving a locking / unlocking mechanism (46) for the lugs (32) as a function of the axial and angular position of the hinged shaft (26), and a tubular sleeve (48) extending from the cylinder (38), the tubular sleeve being intended to receive the hinged shaft (26) and to guide it in translation and in rotation so as to enable the hinged shaft (26) to pass from its extended position in the U-shaped clip (22) to its retracted position outside the U-shaped clip (22) and into the housing (34), - a handle (50) protruding from the tubular sleeve (48) at a free end of the hinged shaft (26) so as to enable the hinged shaft (26) to be axially and angularly manipulated.

2. The aircraft propulsion assembly (10) of Claim 1, wherein, the locking / unlocking mechanism (46) comprising: - two opposite flat walls (51) parallel to the articulation axis (26), in each of which a first slot (52) is formed, comprising a fixing slit (56) for fixing the lug (32) and a window portion (62) for disengaging and introducing the lug (32), the fixing slit being oriented perpendicularly to the articulation axis (26) and being configured to receive and axially fix an end extension (60) of the corresponding lug (32) between its transversely oriented edges (58), the window portion being adjacent to the fixing slit (56) and having a substantially trapezoidal shape, the lug (32) being able to disengage from the flat wall (51) through the window portion and from the fixing slit (56) when the articulation axis (26) is rotated to unlock it, the lug (32) being able to be guided towards the fixing slit (56) through the inclined edge (64) of the window portion when the articulation axis (26) is rotated in the opposite direction to lock it, - a locking device (66) for locking the lug in the fixing slit to fix the first slot.

3. The aircraft propulsion assembly (10) of Claim 2, wherein, The locking device (66) for the lug comprises a cam (68) diametrically opposite with respect to the articulation axis (26) and carrying a notch (70) complementary to an intermediate extension (72) of the lug (32) and a ramp (74) adjacent to the notch (70), the cam being received in an internal housing (44) of the cylindrical portion (38) around the articulation axis (26), the cam being elastically returned by at least one return spring (76) when sliding against the lug (32) and being able to move between a position in which it fixes the lug (32) in the notch (70) and a position of the articulation axis (26) in which the lug (32) can exert a pressure on the ramp (74) of the cam (68) against the force exerted by the at least one return spring (76) and then exit the fixing slit (56) for fixing the first slot (52).

4. The aircraft propulsion assembly (10) according to claim 3, characterized in that The cam (68) is carried diametrically opposite to each other by the periphery of a ring (78) which slides around the articulation axis (26) on the articulation axis and is fixed in rotation with respect to the housing (34), the ring being elastically returned against the lug (32) by a single return spring (76) which slides around the articulation axis (26) on the articulation axis and is supported between the ring (78) and a surface (80) of the bottom plate (36) crossed by the articulation axis (26).

5. The aircraft propulsion assembly (10) according to any one of claims 2 to 4, characterized in that, The housing (34) comprises two walls (86) arranged at 90° to the flat wall (51), in which two longitudinal guide slots (88) are arranged diametrically opposite with respect to the articulation shaft (26) and extending longitudinally at least between the cylindrical portion (38) and the intermediate portion of the tubular sleeve (48), for receiving the lug (32) between the edges of the longitudinal guide slot after the articulation shaft (26) has been rotated through 90° and the lug (32) has been disengaged from the fixed slot (56), to enable the lug (32) to come out of the housing (34) and thus the lug (32) and the articulation shaft (26) to slide in the tubular sleeve (48), which enables the articulation shaft (26) to pass from an extended position of the articulation shaft in the U-shaped clamp (22) to a retracted position of the articulation shaft in the housing (34).

6. The aircraft propulsion assembly (10) of Claim 4, wherein, The housing (34) comprises two walls (86) arranged at 90° to the flat wall (51), in which two longitudinal guide slots (88) are arranged diametrically opposite with respect to the articulation shaft (26) and extending longitudinally at least between the cylindrical portion (38) and the intermediate portion of the tubular sleeve (48), for receiving the lug (32) between the edges of the longitudinal guide slot after the articulation shaft (26) has been rotated through 90° and the lug (32) has been disengaged from the fixed slot (56), to enable the lug (32) to come out of the housing (34) and thus the lug (32) and the articulation shaft (26) to slide in the tubular sleeve (48), which enables the articulation shaft (26) to pass from an extended position of the articulation shaft in the U-shaped clamp (22) to a retracted position of the articulation shaft in the housing (34), the longitudinal guide slots (88) extending into the intermediate portion of the cylindrical portion (38), the ring (78) being rotationally fixed with respect to the housing (34) by two diametrically opposite arms (90) extending from the ring (78) and received in the longitudinal guide slots (88).

7. The aircraft propulsion assembly (10) of Claim 4, wherein, The diameter of the return spring (76) is less than the diameter of a through hole (85) in the bottom plate (36) through which the articulation shaft (26) passes, the return spring being introduced in the housing (34) over the articulation shaft (26) through the through hole (85), and the flat walls (51) of the housing (34) each comprise, near the bottom plate (36), a second oblong slot (81) oriented perpendicularly to the articulation shaft (26), configured to enable at least lateral introduction of a washer (82) for supporting the return spring (76), the diameter of the washer being greater than the diameter of the through hole (85).

8. The aircraft propulsion assembly (10) according to any one of claims 1 to 4, characterized in that Said lugs (32) are formed by cylindrical pins (31) which are housed in transverse perforations (33) of said articulated shaft (26).

9. A method for locking and unlocking the articulation axis (26) of the articulating hinge (20) according to claim 6, characterized in that, The method comprises: - a locking step (ETV) comprising: • a first locking sub-step (SETV1) in which said lugs (32) of said articulated shaft are received in said longitudinal guide slots (88), said articulated shaft (26) is subjected to an axial pressure until said lugs (32) exert a pressure on said ring (78) and compress said return spring, • a second locking sub-step (SETV2) in which said articulated shaft is rotated by 90 degrees in a first direction until said lugs (32) guided by said disengagement and introduction window (62) of said first slot (52) and by said ramp (74) of said ring (78) enter said fixed slot (56) of said first slot (52) and said notch (70) of said ring (78), then said articulated shaft (26) occupies an extended position of this articulated shaft, • a third locking sub-step (SETV3) in which said articulated shaft (26) is released, - an unlocking step (ETD) comprising: • a first unlocking sub-step (SETD1) in which said articulated shaft (26) is rotated in a second direction until said lugs (32) come out of said notch (70) of said ring (78), then by exerting a pressure of said lugs on said ramp (74) of said ring (78) and pushing said ring (78) backwards, said lugs exit said fixed slot (56) of said first slot (52), • a second unlocking sub-step (SETD2) in which by continuing to rotate said articulated shaft (26) by 90 degrees, said lugs (32) exit said first slot (52) and are aligned with said longitudinal guide slots (88), • a third unlocking sub-step (SETD3) in which said articulated shaft (26) is released so that said lugs (32) enter, under the thrust of said ring (78) pressed by the return force of said return spring, the part of said longitudinal guide slots (88) which extends into said tubular sleeve (48), then said articulated shaft occupies a retracted position of this articulated shaft.

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