LOCKING SYSTEM FOR TURBOMACHINE NACAPE AND NACAPE WITH IT

Abstract

The invention relates to a locking system (100) for a turbomachine nacelle comprising a first and a second cowling (44A, 44B), the system comprising: - a bracket (112) for attachment to the first cowling; - a three-point lock (122) for attachment to the second cowling, comprising a support, a hook (124) integral with the support, and a three-point mechanism (125) articulated at a point on the support and movable between a locked and an unlocked position; - an actuation system (130) for the three-point mechanism (125) arranged at a distance from the three-point lock. Furthermore, the locking system (100) includes a linkage mechanism (150) connecting the actuation system to the three-point lock (122) and configured to maneuver the three-point lock between the locked and unlocked positions according to the actuation system. Figure for the abstract: Figure 9

Description

Title of the invention: LOCKING SYSTEM FOR TURBOMACHINE NACELLE AND NACELLE CONTAINING IT technical field

[0001] The present invention relates to a locking system for a turbomachine nacelle, particularly an aircraft turbomachine nacelle, and a nacelle equipped with such a locking system comprising a first cowling and a second cowling. The locking system is configured to lock the cowlings in the closed position when in a locked configuration and to allow the cowlings to be opened when in an unlocked configuration. Previous technique

[0002] Aircraft engine assemblies generally comprise a nacelle forming a generally annular outer casing housing a turbomachine arranged along the longitudinal axis of this nacelle. The turbomachine receives fresh air from the upstream side and expels hot gases from fuel combustion, which provide thrust, on the downstream side.

[0003] An aircraft turbomachine generally comprises, from upstream to downstream, a fan and several modules such as a low-pressure compressor followed by a high-pressure compressor, a combustion chamber, a high-pressure turbine followed by a low-pressure turbine, which drive the corresponding low- or high-pressure compressor, and a gas ejection system. Upstream and downstream are defined with respect to the normal direction of gas flow in a flow channel (from upstream to downstream).

[0004] In the case of dual-flow turbomachinery, the high- and low-pressure sections are traversed by a primary airflow, and the fan produces a secondary airflow that circulates within the turbomachine, between a casing and a nacelle forming an external shell of the turbomachine, in a cold-flow channel. At the nozzle outlet, the gases from the primary flow are mixed with the secondary flow to produce a propulsion force, the secondary flow providing the majority of the thrust in normal operation, resulting in a direct jet.

[0005] Some nacelles include a thrust reversal system that at least partially closes the annular stream of cold air and rejects the secondary flow forward, forming a reverse jet that generates a braking thrust for the aircraft. One known type of nacelle comprises two half-hoods or cowls covering the midsection surrounding the secondary flow fan, connected to each other by a hinge. having a longitudinal axis located in the upper part, so as to allow the lower parts of these hoods to be opened for maintenance operations.

[0006] The covers are held in the closed position, generally at the lower part, by latches that provide a tangential clamping between the two covers. Figures 1 and 2 show schematic and cross-sectional views of the covers 1000A and 1000B equipped with such a latch 1100, respectively in the locked position for closing the covers and in the unlocked position for opening the covers.

[0007] As is known, these locks 1100 comprise a hook 1110 and a loop 1120, each fixed to one of the covers 1000A, 1000B. In a locked configuration ([Fig. 1]) of the locks 1100, the hook 1110 cooperates in a retaining position with the loop 1120 in a closed position of the covers. In an unlocked position ([Fig. 2]) of the locks 1100, the hook 1110 is disengaged from the loop 1120 and allows the covers to be opened.

[0008] The locks are generally operated manually by a control handle 1130. The locks and the control handle are either integrated into a dedicated cavity in the nacelle and accessible through a hatch, or they are positioned externally to the nacelle.

[0009] The lock and control handle are arranged on the platform at the 6 o'clock position, analogous to the face of a clock. As a result, maintenance operators have limited access to the handle and lock, requiring them to lie down under the platform in a space vertically restricted to 45 cm. This limited accessibility leads to difficulties in closing the platform or detecting improper locking.

[0010] In addition, the locks and / or the control handle create aerodynamic defects Dl, D2 which reduce the performance of the turbomachine.

[0011] The objective of the present invention is thus to propose a locking system for a nacelle that overcomes at least some of the disadvantages of the prior art, in particular by improving the aerodynamics of the nacelle and the accessibility of the lock, especially in the event of maintenance. Summary of the invention

[0012] For this purpose, the invention relates to a locking system for a turbomachine nacelle comprising a first and a second hood, the locking system comprising: - a bracket intended to be fixed to the first hood; - a three-point lock intended to be fixed to the second cover, comprising a support, a hook integral with the support and a three-point mechanism articulated at a point on the support, the three-point mechanism being movable between a locked position in which the hook cooperates with the retaining bracket in a closed position hoods and an unlocking position in which the hook is disengaged from the bracket and allows the hoods to be opened; - a three-point mechanism actuation system between the locking and unlocking positions. According to the invention, the actuation system is arranged at a distance from the three-point lock and in that the locking system includes a linkage mechanism connecting the actuation system to the three-point lock and configured to maneuver the three-point lock between the locking and unlocking positions according to the actuation system.

[0013] Thus, the invention proposes a nacelle locking system in which the actuation and locking mechanism is offset from conventional locking systems. According to the invention, the actuation and locking mechanism no longer has external access to the nacelle, and in particular, no access to an aerodynamic zone. Indeed, the locking system according to the invention no longer requires an access hatch or a locking handle located external to the nacelle. As a result, the invention reduces the impact on the external aerodynamic surface of the hoods, greatly improving performance compared to current locks that require clearances leading to gaps and / or spaces around the handles.

[0014] The locking system according to the invention may include one or more of the following features, taken individually or in combination with each other in all technically possible combinations: - the three-point mechanism includes a first connecting rod and a second connecting rod, each having a first end and a second end, the first and second connecting rods being articulated to each other by their respective second ends around an axis of rotation; the three-point mechanism includes a rocker arm movable between two respective extreme positions, the movement of the rocker arm from one extreme position to the other resulting in the implementation of the three-point mechanism between the locking and unlocking positions, the rocker arm being integral with the first connecting rod or the second connecting rod;and the linkage mechanism includes a linkage having a first end connected to the actuation system and a second end connected to the rocker arm; - the linkage means is configured so that a translation of its first end causes the three-point mechanism to switch between the locking and unlocking positions via the rocker arm; - in which the linkage means is configured so that a rotation of its first end causes the three-point mechanism to tilt between the locking and unlocking positions via the rocker arm; - the rocker arm and the second connecting rod form a single piece; - the rocker arm and the first connecting rod form a single piece; - the referral mechanism includes: * a threaded rod movable relative to the support of the three-point lock and having one end connected to the three-point mechanism and configured so that a movement of the threaded rod operates the three-point lock between the locking and unlocking positions; * a set of drive gears for the threaded rod comprising at least one toothed wheel; * a worm screw having a first end connected to the actuation system and a second end connected to the support of the three-point lock and configured to cooperate with the threaded rod via the toothed wheel of the gear set so that a rotation of the worm screw by the actuation system causes a displacement of the threaded rod; - the return mechanism includes a housing and the gear set includes several toothed wheels arranged between the worm gear and the threaded rod, the housing containing the gear set of the threaded rod, the housing being movable relative to the support of the three-point lock; - the rocker arm is connected to the end of the threaded rod in such a way that a movement of the threaded rod operates the three-point lock between the locking and unlocking positions via a tilting of the rocker arm; - the means of connection is a rotating cable linking the actuation system to the first end of the worm gear.

[0015] The invention also relates to a turbomachine nacelle comprising a first hood, a second hood, and a locking system according to the invention and as described above, the bracket being fixed to the first hood and the three-point mechanism type lock being fixed to the second hood, the locking system being configured to lock the hoods in the closed position when it occupies a locking configuration and to allow the hoods to be opened when it occupies an unlocking configuration.

[0016] Advantageously, the nacelle includes a thrust reverser structure comprising the first and second cowlings and a front frame, and the three-point lock is arranged on the nacelle at 6 o'clock by analogy with a clock face.

[0017] According to one embodiment, the actuation system is arranged on the front frame of the thrust reverser structure.

[0018] According to another embodiment, the actuation system is arranged on the gondola at 3 o'clock or 9 o'clock by analogy with a clock face.

[0019] The invention also relates to a propulsion assembly for an aircraft, comprising at least one nacelle according to the invention and as described above.

[0020] The invention also relates to an aircraft, comprising a propulsion assembly according to the invention and as described above. Brief description of the drawings

[0021] The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the description of a non-limiting example that follows, with reference to the accompanying drawings in which: - Fig. 1, already described, represents a schematic and cross-sectional view of hoods equipped with a lock according to the prior art in a locked position; - Fig. 2, already described, represents a schematic and cross-sectional view of hoods equipped with a lock according to the prior art in an unlocked position; - Fig. 3 is a schematic longitudinal cross-sectional view of an aircraft propulsion system comprising a turbofan engine; - Figure 4 is a schematic perspective view of the propulsion system of the [Fig.3]; - Fig. 5 is a schematic perspective view of the propulsion assembly of Fig. 3; - Fig. 6 is a schematic perspective view of half of a D-structure thrust reverser; - Fig. 7 is a schematic perspective view of the propulsion assembly of Fig. 3, in maintenance configuration; - Fig. 8 is a schematic perspective view of the propulsion assembly of Fig. 3, in thrust reversal configuration; - Fig. 9 represents a schematic and cross-sectional view of hoods equipped with a lock according to a first embodiment in a locked position; - Fig. 10 represents a schematic and cross-sectional view of the hoods equipped with a lock according to the first embodiment in an unlocked position; - The [Fig.1 1] is a schematic view in enlarged perspective of part of the locking system of figures 9 and 10; - Fig. 12 is a schematic perspective and partial section view of a first example of a gondola equipped with the locking system according to the first embodiment; - Fig. 13 is a schematic perspective and partial section view of a second example of a gondola equipped with the locking system according to the first embodiment; - Fig. 14 represents a schematic and cross-sectional view of hoods equipped with a lock according to a second embodiment in a locked position; - Fig. 15 represents a schematic and cross-sectional view of the hoods equipped with a lock according to the second embodiment in an unlocked position; - Fig. 16 represents a schematic and cross-sectional view of hoods equipped with a lock according to a third embodiment in a locked position; - Fig. 17 represents a schematic and cross-sectional view of the hoods equipped with a lock according to the third embodiment in an unlocked position; - Fig. 18 represents a schematic and cross-sectional view of hoods equipped with a lock according to a fourth embodiment in a locked position; - Fig. 19 represents a schematic and cross-sectional view of the hoods equipped with a lock according to the fourth embodiment in an unlocked position; - Fig. 20 shows a schematic cross-sectional view of hoods equipped with a lock according to a fifth embodiment in a locked position; and - Fig. 21 shows a schematic cross-sectional view of hoods equipped with a lock according to the fifth embodiment in an unlocked position.

[0022] Elements having the same functions in the different implementations have the same references in the figures.

[0023] The figures include a relative X, Y, and Z reference frame defining longitudinal (or axial), vertical, and lateral directions orthogonal to each other, respectively. Description of embodiments

[0024] Figures 3 and 4 show a propulsion assembly 1 having a longitudinal central axis A.

[0025] Subsequently, the terms "upstream", "downstream", "front" and "rear" are defined relative to a direction S of gas flow through the propulsion assembly 1 along the longitudinal central axis A, from left to right on the [Fig.3].

[0026] The propulsion unit 1 comprises a turbomachine 2 (visible in [Fig.3]), a nacelle 3 and a mast 4 or pylon (visible in [Fig.4]) allowing the propulsion unit 1 to be connected to a wing of an aircraft (not shown).

[0027] In the example of [Fig.3], the turbomachine 2 is a turbofan engine comprising, from upstream to downstream, a fan 21, a low-pressure compressor 22, a high-pressure compressor 23, a combustion chamber 24, a high-pressure turbine 25 and a low-pressure turbine 26. The compressors 22 and 23, the combustion chamber 24 and the turbines 25 and 26 form a gas generator.

[0028] The turbomachine 2 includes a blower housing 27 connected to the gas generator by structural arms 28.

[0029] The nacelle 3 comprises an upstream section 32 forming an air inlet, a middle section 34 which includes fan hoods enveloping the fan casing 27 and a downstream section 36 forming downstream of the propulsion assembly 1 an outlet for the evacuation of gases generated by the turbomachine 2.

[0030] In a manner known per se, during the operation of the turbomachine 2, an airflow F enters the propulsion assembly 1 through the air inlet 32, passes through the fan 21, and then splits into a central primary flow Fl and a secondary flow F2. The primary flow Fl flows in a primary gas circulation duct or channel VI within the gas generator. The secondary flow F2, on the other hand, flows in a secondary duct or channel V2 surrounding the gas generator and radially bounded outwards by the fan casing 27 and by the downstream section 36 of the nacelle 3.

[0031] Figures 5 and 6 show in more detail the downstream section 36 of the nacelle 3.

[0032] With reference to [Fig.5], the downstream section 36 comprises two half-assemblies 40A and 40B of hemicylindrical shape and symmetrical to each other with respect to a median longitudinal plane P passing through the central longitudinal axis A and parallel to the vertical direction Z. Thus, the half-assemblies 40A and 40B extend laterally on either side of the plane P and in particular on either side of the mast 4.

[0033] In the following description and in certain figures, reference numerals are used to distinguish elements located on one side of plane P from symmetrical elements located on the other side of this plane. This distinction is made by adding the suffix "A" to these reference numerals for elements located on one side of plane P and the suffix "B" for those located on the other side. Generally, not all symmetrical elements are shown in all the figures. Furthermore, when a part of the propulsion assembly 1 has two symmetrical halves with respect to plane P, the following description details, in most cases, only one of these halves. Unless otherwise indicated, this description applies by analogy to the other corresponding half.

[0034] In particular, it is described below with reference to [Fig.6], the half-assembly 40A. The following description relating to the half-assembly 40A therefore applies by analogy to the half-assembly 40B.

[0035] The half-assembly 40A comprises two parts which are movable relative to each other. One of these parts forms a structure 42A here referred to as the "fixed structure" which, in flight configuration, remains in the same position relative to the mast 4. The other part of the half-assembly 40A forms a cowling 44A movable relative to the fixed structure 42A (see further below).

[0036] The fixed structure 42A includes on the one hand an internal fairing 45A radially delimiting inwards a circumferential sector of a longitudinal portion of the secondary vein V2.

[0037] The internal fairing 45A, commonly referred to as the "fixed internal structure", comprises, vertically from bottom to top on the [Fig.6], a lower junction wall 46A also called "island" or "bifurcation" "six o'clock" (by analogy with a clock face), a central wall 47A of semi-annular shape and an upper junction wall 48A also called "bifurcation" "twelve o'clock" (by analogy with a clock face).

[0038] The fixed structure 42A further comprises a lower beam 49A attached to a radial end of the lower junction wall 46A and an upper beam 50A attached to a radial end of the upper junction wall 48A.

[0039] The upper beam 50A includes a connecting element allowing the half-assembly 40A to be connected to the propulsion assembly 1, and more specifically to the mast 4, in such a way as to allow the half-assembly 40A to rotate around an axis of rotation B.

[0040] The half-assembly 40A is thus mobile between a flight configuration, illustrated in [Fig.4], and a maintenance configuration illustrated in [Fig.7].

[0041] In this example, the axis of rotation B is substantially parallel to the longitudinal central axis A. In general, the axes A and B can form an angle between 0° and 3°.

[0042] Regarding the movable hood 44A, it extends radially outside the central wall 47A of the fixed structure 42A and also has a semi-annular shape.

[0043] Thus, the central wall 47A of the fixed structure 42A and the movable hood 44A define radially between them said circumferential sector of longitudinal portion of the secondary vein V2, this sector extending circumferentially around the central longitudinal axis A between the lower junction wall 46A and the upper junction wall 48A of the fairing 45A.

[0044] In this example, the fixed structure 42A includes a wall 52A connected to the central wall 47A and extending behind it so as to form half of an exhaust nozzle 53 visible in [Fig.5].

[0045] In a manner known per se, the movable hood 44A is connected to the lower beam 49A and to the upper beam 50A of the fixed structure 42A by means of a sliding connection.

[0046] In this example, this connection is made by means of slides (not shown) attached to the lower beam 49A and upper beam 50A and by means of rails (not shown) attached to the movable hood 44A which cooperate with these slides.

[0047] Such a sliding joint allows the movable hood 44A to be moved, for example by means of jacks (not shown), relative to the fixed structure 42A in translation along the longitudinal central axis A between an advanced position, illustrated in figures 3, 4 and 5, and a rearward position, illustrated in [Fig.8].

[0048] In the forward position, a front end of the movable hood 44A is flush with a rear end of the fan hood located on the same side of the plane P as the movable hood 44A, so as to reduce the discontinuity between these hoods and thus reduce aerodynamic disturbances outside the nacelle 3.

[0049] In the retracted position, the front end of the movable hood 44A and the rear end of the corresponding blower hood of the median section 34 are separated from each other by a distance L defining a space forming a radial opening (see [Fig.8]).

[0050] In this example, the nacelle 3 comprises grids 55 extending respectively on one side and the other of plane P. The grids 55 extend through the aforementioned radial opening when the movable hood 44A is in the retracted position. The deflection grids 55 are further arranged adjacent to one another in an annular area surrounding the secondary channel V2 and comprise series of blades extending from upstream to downstream.

[0051] With reference to [Fig.6], the half-assembly 40A also includes flaps 57A and connecting rods 59A.

[0052] According to an example known per se, each of the flaps 57A is articulated on the movable hood 44A and each of the connecting rods 59A is connected on one side to one of the respective flaps 57A and on the other side to the central wall 47A of the fairing 45A of the fixed structure 42A so that, when the movable hood 44A moves from the forward position to the rearward position, the flaps 57A deploy radially in the secondary vein V2 so as to close this conduit V2.

[0053] The downstream section 36 of the nacelle 3 thus forms a thrust reverser.

[0054] The deflection grids 55 are usually fixed to a front frame 62 and to a frame rear of fixed structure 42A.

[0055] The deflection grids 55 are attached to the turbomachine housing via the front frame 62.

[0056] When the movable cowling 44A and 44B of each of the half-assemblies 40A and 40B is in the forward position, also called the "direct thrust position," the secondary flow F2 is directed to the rear of the propulsion assembly 1 by passing through the longitudinal portion of the secondary flow V2 defined by the downstream section 36. In this direct thrust configuration, the flaps 57A of half-assembly 40A, as well as the flaps (not shown) of half-assembly 40B, are folded against the inner wall of the corresponding movable cowling 44A or 44B. The secondary flow F2 thus contributes to generating thrust.

[0057] When the movable cowling 44A and 44B of each of the half-assemblies 40A and 40B is in the retracted position, also called the "thrust reversal position," the flaps 57A of half-assembly 40A, as well as the flaps of half-assembly 40B, close the secondary flow V2 so as to redirect the secondary flow F2 towards said radial opening. The secondary flow F2 thus passes through the grids 55, being deflected by them towards the front of the propulsion assembly 1. The secondary flow F2 thus generates a counter-thrust.

[0058] In flight configuration, the movable cowlings 44A and 44B of each of the half-assemblies 40A and 40B close by connecting along the plane of symmetry P. The two movable cowlings 44A and 44B are clamped against each other along a tangential direction denoted Y in the illustrated examples. The locking of the half-assemblies 40A and 40B in flight configuration, and more specifically the position of the two movable cowlings 44A and 44B, is ensured by at least one locking system according to the invention and as described in detail with reference to Figures 9 to 21. More specifically, Figures 9 to 21 illustrate five non-limiting embodiments of the invention.

[0059] Figures 9 to 13 illustrate a locking system 100 according to a first embodiment of the invention. Figures 9 and 10 schematically represent a cross-sectional view of hoods equipped with a locking system 100 according to the first embodiment of the invention, respectively in a locked position and an unlocked position.

[0060] The locking system 100 is configured to lock the first hood 44A and the second hood 44B in the closed position when it is in a locked configuration and to allow the hoods to be opened when it is in an unlocked configuration.

[0061] The locking system 100 comprises two parts, each intended to be fixed to one of the hoods: a first part 110 intended to be fixed to the first hood 44A and a second part 120 intended to be fixed to the second hood 44B.

[0062] The first part 110 includes a support (not shown) intended to be fixed to the first hood 44A and a bracket 112 (also called a loop) integral with said support.

[0063] The second part 120 includes a lock called a three-point lock 122 intended to be fixed to the second cover 44B. The three-point lock 122 includes a support 123, a hook 124 supported by the support and a three-point mechanism 125.

[0064] The support 123 preferably comprises two parallel and integral lateral walls, the walls extending in transverse planes, that is to say extending along the Y and Z directions.

[0065] The stirrup 112 has an axis C for gripping the hook 124 which extends along the longitudinal direction X.

[0066] The three-point mechanism 125 is also housed between the two side walls of the support 123. It is articulated relative to the support of the three-point lock. For this purpose, the three-point mechanism 125 comprises two connecting rods articulated relative to each other: - a first connecting rod 126, a first end 126a of which is mounted freely to rotate about an axis of rotation Cl and a second end 126b is also mounted to rotate about an axis of rotation C2, and - a second connecting rod 127, a first end 127a of which is mounted freely to rotate around the axis of rotation C2 and a second end 127b is also mounted to rotate around an axis of rotation C3.

[0067] The rotation axes Cl, C2 and C3 are parallel to each other and parallel to the axis C of the hook 124. The axis Cl is also called the main axis of the lock and is integral with the second cover 44B. The axis C2 is the connecting axis between the two connecting rods 126, 127 of the three-point mechanism 125.

[0068] The three-point mechanism 125 is movable between a locking or locked position ([Fig.9]) in which the hook 124 cooperates in retention with the loop 112 in a closed position of the hoods 44A, 44B and an unlocking or unlocked position ([Fig. 10]) in which the hook 124 is released from the loop 112 and allows an opening of the hoods 44A, 44B.

[0069] In the unlocked position illustrated in particular in [Fig. 10], the three-point mechanism 125 is such that the three axes Cl, C2 and C3 are misaligned with respect to a line denoted X0, called the line of alignment of forces, along which the three axes Cl, C2 and C3 are aligned. Regardless of the position of the lock, this line denoted X0 passes through the axes Cl and C3.

[0070] More specifically, in the example illustrated in Figures 9 and 10, in the unlocked position ([Fig. 10]), the axis C2 of the three-point mechanism 125 is below the line of alignment of the forces X0 in the vertical direction Z. In other words, the axis C2 of the three-point mechanism 125 is closer to the outside of the nacelle 3 (and the hoods 44A, 44B) than the axes Cl and C3.

[0071] On the contrary, in the locking position shown in particular in [Fig. 9], the three-point mechanism 125 is such that the three axes Cl, C2 and C3 are also misaligned with respect to the force alignment line X0 so that the axis C2 of the three-point mechanism 125 is above the force alignment line X0 in the vertical direction Z. In other words, the axis C2 of the three-point mechanism 125 is further from the outside of the nacelle 3 (and the hoods 44A, 44B) than the axes Cl and C3.

[0072] In the example illustrated in the figures, it is therefore necessary to apply a force, in particular a vertical force from bottom to top on the figures on the C2 linkage axis of the connecting rods to move the three-point mechanism 125 from its unlocked position to its locked position and vice versa.

[0073] Of course, according to another example, the vertical effort to be provided can be from top to bottom to move the three-point mechanism 125 from its unlocked position to its locked position and vice versa, the "orientation" of the lock depending on the available space.

[0074] In other words and more generally, according to the invention, it is necessary to provide an effort to tilt the axis C2 from one side to the other of the line X0 of alignment of forces to move the three-point mechanism 125 from its unlocked position to its locked position and vice versa.

[0075] According to the invention, the three-point mechanism 125 further comprises a rocker arm 128 configured to move the three-point mechanism 125 from its unlocked position to its locked position and vice versa.

[0076] The rocker arm 128 is movable between two positions: a first position corresponding to the locking position of the three-point mechanism 125 ([Fig. 9]) and a second position corresponding to the unlocking position of the three-point mechanism 125 ([Fig. 10]). Hereafter, the first position of the rocker arm 128 will also be referred to as the locking position or locked, and the second position of the rocker arm 128 as the unlocking position or unlocked.

[0077] The rocker arm 128 is movable in rotation about the axis C3 at a first end 128a. In other words, the rocker arm 128 can be manipulated to tilt reversibly between the locked and unlocked positions.

[0078] In addition, the axis C2 of the three-point mechanism 125 is integral with the rocker arm 128. For this purpose, the rocker arm 128 has an opening for the passage of the central axis C2 of the three-point mechanism 125.

[0079] As a result, the first end 128 a is fixed and connected to the second connecting rod 127 of the three-point mechanism 125. The rocker arm has a V shape, one of whose arms carrying the first end 128a is similar in shape to the second connecting rod 127 and fixed to it.

[0080] Alternatively and preferably, the second connecting rod 127 and the rocker arm 128 are advantageously formed from a single block, i.e., with continuous material, as in the illustrated example. In other words, the second connecting rod 127 and the rocker arm 128 form a monolithic piece with an overall V-shape.

[0081] Thus, the tilting of the rocker arm 128 from the locked position ([Fig.9]) to the unlocked position ([Fig. 10]) allows the three-point mechanism 125 to be maneuvered by driving the axis C2 of the three-point mechanism 125 from a position in which it is above / on one side of the line X0 of alignment of forces to a position in which it is below / on the other side of the line X0 of alignment of forces.

[0082] More specifically, the rocker arm 128 rotates around the axis C3, driving the axis C2 into a rotational and translational movement.

[0083] The rocker arm 128 has a second end 128b opposite the first end 128a. The opening for the central axis C2 of the rocker arm 128 is arranged between the first end 128a and the second end 128b.

[0084] The locking system 100 further includes an actuation system 130 of the three-point mechanism 125 allowing the three-point mechanism 125 to be moved reversibly between the locking position ([Fig.9]) and the unlocking position ([Fig. 10]) by tilting the axis C2 to one side or the other of the line X0 via the rocker arm 128.

[0085] The actuation system 130 is arranged at a distance from the three-point lock 122. In other words, the actuation system 130 is offset from the three-point lock 122, in particular in a non-aerodynamic area of ​​the nacelle 3.

[0086] The three-point lock 122 is preferably arranged on the gondola at 6 o'clock by analogy with the face of a clock. According to the invention, the actuation system 130 can be arranged on the front frame 62 as in the first embodiment (Figures 9 to 13) or on the gondola at 3 o'clock or 9 o'clock by analogy with the face of a clock as detailed below, particularly for the other embodiments.

[0087] Therefore, the locking system 100 includes a linking mechanism 150 connecting the actuation system 130 to the three-point lock 122. The linking mechanism 150 is configured to maneuver the three-point lock 122 between the locking ([Fig.9]) and unlocking (Figures 10 and 12) positions depending on the state of the actuation system 130.

[0088] According to the first embodiment, the linking mechanism 150 comprises a return mechanism 140 and a linking means or cable 155.

[0089] The return mechanism 140 is configured to maneuver the three-point lock 122 between the locking ([Fig.9]) and unlocking ([Fig. 10]) positions depending on the state of the actuation system 130.

[0090] In the example illustrated in figures 9 to 11, the return mechanism 140 comprises a threaded rod 142, at least one set of drive gears 144 and a screw without a screw 146.

[0091] The threaded rod 142 extends in a plane perpendicular to the longitudinal direction X, that is, in a transverse plane extending along the Y and Z directions. It is movable relative to the support of the three-point lock 122 in this transverse plane. The threaded rod 142 has a free end 142a and a second end 142b connected to the three-point mechanism 125, in particular via the rocker arm 128.

[0092] The threaded rod 142 is configured so that a displacement of the threaded rod 142 operates the three-point lock 125 between the locking and locking positions. unlocking. More specifically, the threaded rod 142 is configured so that a movement of the threaded rod 142 operates the rocker arm 128 driving the three-point lock 125 between the locking and unlocking positions.

[0093] The second end 142b of the threaded rod 142 is connected to the second end 128b of the rocker arm 128 by a pivot joint with axis D parallel to the axis C of the stirrup 112 (and the rotation axes Cl, C2 and C3 of the three-point mechanism 125).

[0094] The first end 142a of the threaded rod cooperates by threading with the drive gear set 144.

[0095] The drive gear set 144 comprises a wheel 145 having teeth on its outer periphery and a through hole arranged in the center of the wheel. The through hole is configured to receive the first end 142a of the threaded rod and has a thread configured to cooperate with the thread of the threaded rod 142.

[0096] The worm screw 146 extends longitudinally in a direction denoted E. In the illustrated example, the direction E is parallel to the axis C of the stirrup 112 (and of the rotation axes Cl, C2 and C3 of the three-point mechanism 125).

[0097] The worm screw 146 extends between a first end 146a connected to the actuation system 130 and a second end 146b connected to the support of the three-point lock 122 more precisely to an arm of the latter extending vertically in the direction Z.

[0098] The worm screw 146 is configured to cooperate with the threaded rod 142 via the gear set 144 so that a rotation of the worm screw 146 by the actuation system 130 causes a displacement of the threaded rod 142.

[0099] More specifically, the worm screw 146 has at least one portion equipped with teeth adapted to cooperate with the gear set 144.

[0100] The gear set 144 comprises at least two gears or toothed wheels, one of the wheels 145 being traversed by the threaded rod 142.

[0101] Of course, the gear set 144 can include several gears adapted to cooperate with each other so as to form a successive gear train between the worm gear 146 and the threaded rod 142. The ratio of the gears or pinions makes it possible to adjust the rotational force required on the threaded rod 142 and therefore on the three-point mechanism 125. Thus in the example illustrated in Figures 9 to 11, the gear set 144 includes three gears or pinions.

[0102] Advantageously, and as represented in the example illustrated in figures 9 to 11, the return mechanism 140 includes a housing 148 to accommodate the set of gears 144, the toothed wheel 145 of which is traversed by the threaded rod 142.

[0103] The housing 148 has a substantially parallelepiped shape. It comprises two first parallel walls 148a extending in transverse planes, that is to say in planes perpendicular to the longitudinal direction X. It also includes two second parallel walls 148b extending in planes perpendicular to the threaded rod 142.

[0104] The housing 148 also accommodates the portion of the worm gear 146 equipped with teeth adapted to cooperate with the gear set 144. More specifically, the worm gear passes through the housing 148 in the longitudinal direction X. For this purpose, the first two walls 148a of the housing each have a through hole to allow the passage of the worm gear 146.

[0105] Similarly, the threaded rod 142 passes through the housing 148 in a direction perpendicular to the longitudinal direction X. For this purpose, the two second walls 148b of the housing each have a through hole to allow the passage of the threaded rod 142.

[0106] The housing 148 is fixed to the threaded rod 142. Consequently, the housing 148 is movable relative to the support of the three-point lock 125. The housing 148 thus allows the reorientation of the entire worm gear and the wheel(s) of the drive gear of the threaded rod 142 as the locking / unlocking kinematics of the locking system 100 progresses.

[0107] As previously stated, the linkage mechanism 150 connects the actuation system 130 to the three-point lock 122, via the return mechanism 140, since the actuation system 130 is arranged at a distance from the three-point lock 122. In other words, the actuation system 130 is offset from the three-point lock 122, specifically in a non-aerodynamic area of ​​the nacelle 3.

[0108] The actuation system 130 is carried by the downstream section 36 of the nacelle 3, and preferably by the front frame 62 of the downstream section 36, in particular at 6 o'clock by analogy with the dial of a clock.

[0109] The actuation system 130 consists of a movable element 132 that is directly accessible from outside the nacelle. This element is, for example, a lever that can be manually operated by an operator or a footprint that can be actuated by a tool with a shape complementary to the footprint.

[0110] According to the first embodiment, the element 132 is rotationally mobile between a first extreme position corresponding to the unlocked position of the three-point lock 122 and a second extreme position corresponding to the locked position of the three-point lock 122.

[0111] In order to transmit the actuation of the actuation system 130 and in particular the displacement of the moving element 132, the linkage mechanism 150 includes a rotating cable 155 connecting the actuation system 130 to the first end of the worm gear 146 visible in [Fig. 12]. More specifically, the rotating cable 155 extends between a first end 155a connected to the actuation system 130, in particular to the moving element 132, and a second end 155b connected to the return system 140, in particular to the first end of the worm screw 146.

[0112] The rotating cable 155, also known by the Anglo-Saxon term "flexshaft", can advantageously be supported by one or more supports 152 between the actuation system 130 and the worm gear 146 as illustrated in [Fig. 12]. Each support 152 is fixed inside the nacelle 3, and more precisely inside the downstream section 36 of the nacelle 3.

[0113] Thus, in operation, an operator controls the locking system 100 from the actuation system 130 arranged remotely from the three-point lock 122 and in a non-aerodynamic area.

[0114] In the case where the locking system 100 is unlocked ([Fig. 10]) and the hoods are brought together and ready to be locked together, the three-point lock is in its unlocked position, therefore the axis C2 of the three-point mechanism 125 is in a position in which it is on one side of the line X0 of alignment of forces (in particular below in the illustrated example).

[0115] To lock the locking system, the operator maneuvers the movable element 132 from its first extreme position, corresponding to the unlocked position of the three-point lock 122, to its second extreme position, corresponding to the locked position of the three-point lock 122. The actuation of the actuating system 130 is achieved by rotating the movable element 132, either directly by the operator or via a tool. This actuation is then transmitted to the three-point lock 122 by the rotating cable 155 through the return mechanism 140.

[0116] More specifically, this rotation of the moving element 132 of the actuation system 130 is transmitted to the worm screw 146 via the rotating cable 155 and thus causes a rotation of the worm screw 146 around its axis E.

[0117] The rotation of the worm screw 146 by the actuation system 130 causes a displacement of the threaded rod 142 via the gear set 144. Indeed, the rotation of the worm screw 146 causes a rotation of the gear set 144 by the meshing of their respective teeth.

[0118] The rotation of the gear set 144 causes the threaded rod 142 to move between a first position illustrated in [Fig. 10], corresponding to the unlocked position of the three-point lock 122, and a second position illustrated in [Fig. 9], corresponding to the locked position of the three-point lock 122. More precisely, the threaded rod 142 moves at least by translation within the wheel 145 of the gear set 144, causing the threaded rod to tilt around the axis E relative to the lock support. The tilting of the second end 142b of the threaded rod causes the rocker arm 128 to tilt. The three-point locking mechanism 125 is moved between the unlocked position ([Fig. 10]) and the locked position ([Fig. 9]). The axis C2 of the three-point mechanism 125 passes to the other side of the X0 line of alignment of forces (specifically, above it in the illustrated example). The three-point mechanism 125 is in its locked position ([Fig. 9]). This movement allows the hook 124 to engage with the stirrup 112.

[0119] Figure 13 illustrates another example of an implementation of the invention on a turbomachine nacelle. In this example, the nacelle is equipped with two locking systems according to the first embodiment, denoted 100a and 100b. The actuation systems, respectively referenced 130a and 130b, and more specifically the corresponding moving elements 132a and 132b, are advantageously arranged close to one another, i.e., in the same space easily accessible directly from outside the nacelle. Each moving element 132a and 132b is connected to an associated rotating cable 155a and 155b to transmit the state of the actuation system to the corresponding three-point lock 122a and 122b via an associated return system 140a and 140b.

[0120] The rotating cables 155a, 155b can advantageously be supported by one or more common supports 152 between the actuation system and three-point locking.

[0121] The following embodiments of the invention differ from the first in that they do not include a return system 140. The linkage mechanism 150 directly connects the actuation system 130 to the three-point lock 122.

[0122] A second embodiment of the invention will be described with reference to Figures 14 and 15. Figure 14 shows a schematic cross-sectional view of hoods equipped with a locking system 200 according to the second embodiment in a locked position. Figure 15 shows the same view in an unlocked position of the locking system.

[0123] According to this embodiment, the linking mechanism 150 also includes a rotating cable 155 which extends between a first end 155a connected to the actuation system 130, in particular to the moving element 132, and a second end 155b.

[0124] However, according to this second embodiment, the second end 155b of the rotating cable 155 is directly connected to the three-point lock 122 and in particular to the spreader bar 128, and more specifically to the second end 128b of the spreader bar 128.

[0125] In this second embodiment, the second connecting rod 127 and the rocker arm 128 are formed from a single block, that is to say, with continuous material. In other words, the second connecting rod 127 and the rocker arm 128 form a single monolithic piece.

[0126] Thus, consequently, the second end 155b of the rotary cable 155 is directly connected to the three-point lock 122 and in particular to the second connecting rod 127.

[0127] This configuration allows the actuation system 130, and in particular the moving element 132, to be relocated by positioning it on the nacelle, for example at 3 o'clock or 9 o'clock, by analogy with the face of a clock, while the three-point lock 122 is positioned on the nacelle at 6 o'clock, by analogy with the face of a clock. Alternatively, the actuation system 130, and in particular the moving element 132, is positioned on the front frame 62, in particular at 6 o'clock, by analogy with the face of a clock.

[0128] To unlock the locking system 200 ([Fig. 14]), the operator easily maneuvers the movable element 132, which is easily accessible at 3 o'clock or 9 o'clock by analogy with a clock face, to move it from one extreme position corresponding to the locked position of the three-point lock 122 to another extreme position corresponding to the unlocked position of the three-point lock 122 ([Fig. 15]).

[0129] The actuation of the actuation system 130 is achieved by the rotation of the movable element 132 by the operator, either directly or via a tool. This actuation is then transmitted to the three-point lock 122 by the rotating cable 155 directly onto the second connecting rod 127 and, more precisely, onto the second end 128b of the rocker arm 128. The rotation of the movable element 132 in a direction RI causes a pull T1 on the second end 128b of the rocker arm 128, causing the axis C2 of the three-point mechanism 125 to pivot to the other side of the force alignment line X0. The three-point mechanism 125 is in its unlocked position ([Fig. 15]). This movement allows the hook 124 to release the stirrup 112.

[0130] Conversely, to lock the locking system 200, the actuation system 130 is actuated by the operator, either directly or via a tool, to rotate the moving element 132 in the opposite direction R2. This actuation is then transmitted to the three-point lock 122 by the rotating cable 155 directly onto the second connecting rod 127 and, more precisely, onto the second end 128b of the rocker arm 128. The rotation of the moving element 132 in the opposite direction R2 causes a thrust P2 on the second end 128b of the rocker arm 128, causing the axis C2 of the three-point mechanism 125 to pivot to the other side of the force alignment line X0. The three-point mechanism 125 is in its locked position ([Fig. 14]). This movement allows the hook 124 to cooperate in a retaining manner with the stirrup 112.

[0131] Such an arrangement makes it possible on the one hand to do away with a slot or access hatch to the three-point lock, because there is no longer a need for the traditional handle to operate it and the hoods can cover the three-point lock 122, making it possible to considerably improve the aerodynamics of the nacelle.

[0132] On the other hand, the actuation system is located in a more easily accessible area, which facilitates handling by an operator.

[0133] A third embodiment of the invention will be described with reference to Figures 16 and 17. Figure 16 shows a schematic cross-sectional view of hoods equipped of a locking system 300 according to the third embodiment in a locked position. Figure 17 shows this same view in an unlocked position of the locking system.

[0134] This third embodiment differs from the second embodiment by the rocker arm 328 of the three-point mechanism 125.

[0135] The rocker arm 328 is movable between two positions: a first position corresponding to the locking position of the three-point mechanism 125 ([Fig. 16]) and a second position corresponding to the unlocking position of the three-point mechanism 125 ([Fig. 17]).

[0136] The rudder 328 has a V-shape and is formed of two arms connected at one of their ends, called the connecting end. The first arm has a free end 328a opposite the connecting end. The second arm has a free end 328b opposite the connecting end. Thus, the rudder 328 extends between the free end 328a of the first arm and the free end 328b of the second arm.

[0137] The rocker arm 328 is rotationally movable about the axis Cl at the joint between its two arms. In other words, the rocker arm 328 can be manipulated to tilt reversibly between the locked and unlocked positions.

[0138] In addition, the axis C2 of the three-point mechanism 125 is linked to the rocker arm 328 and more specifically connected to the first end 328a of the rocker arm 328.

[0139] As a result, the first end 328a is fixed and connected to the first connecting rod 126 of the three-point mechanism 125.

[0140] Alternatively and preferably, the first connecting rod 126 and the rocker arm 328 are advantageously formed from a single block, i.e., with a continuous material, as in the illustrated example. In other words, the first connecting rod 126 and the rocker arm 328 form a monolithic piece with an overall V-shape as illustrated in Figures 16 and 17.

[0141] Thus, the tilting of the rocker arm 328 from the locked position ([Fig. 16]) to the unlocked position ([Fig. 17]) allows the three-point mechanism 125 to be maneuvered by driving the axis C2 of the three-point mechanism 125 from a position in which it is on one side of the X0 line of alignment of forces to a position in which it is on the other side of the X0 line of alignment of forces.

[0142] More specifically, the rocker arm 328 rotates around the axis Cl, driving the axis C2 into a rotational and translational movement.

[0143] According to this embodiment, the linking mechanism 150 also includes a rotating cable 155 which extends between a first end 155a connected to the actuation system 130, in particular to the moving element 132, and a second end 155b.

[0144] However, according to this second embodiment, the second end 155b of the rotating cable 155 is directly connected to the three-point lock 122 and in particular to the spreader bar 328, and more specifically to the second end 328a of the spreader bar 328.

[0145] The first connecting rod 126 and the rocker arm 328 being a single monolithic piece, the second end 155b of the rotary cable 155 is directly connected to the three-point lock 122 and in particular to the first connecting rod 126.

[0146] This third configuration allows the actuation system 130, and in particular the movable element 132, to be relocated by positioning it on the nacelle, for example at 3 o'clock or 9 o'clock, by analogy with the face of a clock, while the three-point lock 122 is positioned on the nacelle at 6 o'clock, by analogy with the face of a clock. Alternatively, the actuation system 130, and in particular the movable element 132, is positioned on the front frame 62, in particular at 6 o'clock, by analogy with the face of a clock.

[0147] To unlock the locking system 300 ([Fig. 16]), the operator easily maneuvers the movable element 132, which is easily accessible at 3 o'clock or 9 o'clock by analogy with a clock face, to move it from one extreme position corresponding to the locked position of the three-point lock 122 to another extreme position corresponding to the unlocked position of the three-point lock 122 ([Fig. 17]).

[0148] The actuation of the actuation system 130 is achieved by the operator rotating the movable element 132 directly or via a suitable tool. This actuation is then transmitted to the three-point lock 122 by the rotating cable 155 directly onto the first connecting rod 126 and more precisely onto the second end 328b of the rocker arm 328. The rotation of the movable element 132 in a direction RI causes a pull Tl on the second end 328b of the rocker arm 328, causing the axis C2 of the three-point mechanism 125 to pivot to the other side of the force alignment line X0. The three-point mechanism 125 is in its unlocked position ([Fig. 17]). This movement allows the hook 124 to release the stirrup 112.

[0149] Conversely, to lock the locking system 300, the actuation system 130 is actuated by the operator, either directly or via a tool, to rotate the moving element 132 in the opposite direction R2. This actuation is then transmitted to the three-point lock 122 by the rotating cable 155 directly onto the first connecting rod 126 and, more specifically, onto the second end 328b of the rocker arm 328. The rotation of the moving element 132 in the opposite direction R2 causes a thrust P2 on the second end 328b of the rocker arm 328, causing the axis C2 of the three-point mechanism 125 to pivot to the other side of the force alignment line X0. The three-point mechanism 125 is in its locked position ([Fig. 16]). This movement allows the hook 124 to cooperate in a retaining manner with the stirrup 112.

[0150] Such an arrangement makes it possible, on the one hand, to do without a slot or access hatch for the three-point lock, because there is no longer a need for the traditional handle for the maneuvering and the hoods can cover the 122 three-point lock, allowing for a significant improvement in the nacelle's aerodynamics.

[0151] A fourth embodiment of the invention will be described with reference to Figures 18 and 19. Figure 18 shows a schematic cross-sectional view of hoods equipped with a locking system 400 according to the fourth embodiment in a locked position. Figure 19 shows the same view in an unlocked position of the locking system.

[0152] The fourth embodiment differs from the second embodiment in that the linking mechanism 150 comprises a cable 455 extending between a first end 455a connected to the actuation system 130, in particular to the moving element 132, and a second end 455b. The cable 455 is a non-rotating "push-pull cable" type.

[0153] According to this fourth embodiment, the second end 455b of the rotating cable 455 is directly connected to the three-point lock 122 and in particular to the spreader bar 128, and more specifically to the second end 128b of the spreader bar 128.

[0154] In this fourth embodiment, the second connecting rod 127 and the rocker arm 128 are formed from a single block, that is to say, with continuous material. In other words, the second connecting rod 127 and the rocker arm 128 form a single monolithic piece.

[0155] Thus, consequently, the second end 455b of the cable 455 is directly connected to the three-point lock 122 and in particular to the second connecting rod 127.

[0156] This fourth configuration allows the actuation system 130, and in particular the movable element 132, to be relocated by positioning it on the nacelle, for example at 3 o'clock or 9 o'clock, by analogy with the face of a clock, while the three-point lock 122 is positioned on the nacelle at 6 o'clock, by analogy with the face of a clock. Alternatively, the actuation system 130, and in particular the movable element 132, is positioned on the front frame 62, in particular at 6 o'clock, by analogy with the face of a clock.

[0157] To unlock the locking system 400 ([Fig. 18]), the operator easily maneuvers the movable element 132, which is easily accessible at 3 o'clock or 9 o'clock by analogy with a clock face, to move it from one extreme position corresponding to the locked position of the three-point lock 122 to another extreme position corresponding to the unlocked position of the three-point lock 122 ([Fig. 19]).

[0158] The mobile element 132 is directly connected to the second end 455b of the cable.

[0159] The actuation of the actuation system 130 is achieved by the operator pulling the movable element 132 directly or via a suitable tool. This actuation is then transmitted to the three-point lock 122 by the cable 455 directly onto the second connecting rod 127 and more precisely onto the second end 128b of the rocker arm 128. Pulling the movable element 132 causes a pull T1 on the second end 128b of the rocker arm 128, causing the axis to tilt. C2 of the three-point mechanism 125 is on the other side of the XO line of force alignment. The three-point mechanism 125 is in its unlocked position ([Fig. 19]). This movement allows the hook 124 to release the stirrup 112.

[0160] Conversely, to lock the locking system 400, the actuation system 130 is actuated so as to push the moving element 132 by the operator directly or via a suitable tool. This actuation is then transmitted to the three-point lock 122 by the cable 455 directly onto the second connecting rod 127 and more precisely onto the second end 128b of the rocker arm 128. The movement of the moving element 132 in the opposite direction causes a thrust P2 on the second end 128b of the rocker arm 128, causing the axis C2 of the three-point mechanism 125 to pivot to the other side of the force alignment line X0. The three-point mechanism 125 is in its locked position ([Fig. 18]). This movement allows the hook 124 to cooperate in a retaining manner with the stirrup 112.

[0161] Such an arrangement makes it possible on the one hand to do away with a slot or access hatch to the three-point lock, because there is no longer a need for the traditional handle to operate it and the hoods can cover the three-point lock 122, making it possible to considerably improve the aerodynamics of the nacelle.

[0162] A fifth embodiment of the invention will be described with reference to Figures 20 and 21. Figure 20 shows a schematic cross-sectional view of hoods equipped with a locking system 500 according to the fifth embodiment in a locked position. Figure 21 shows the same view in an unlocked position of the locking system.

[0163] The fifth embodiment differs from the third embodiment in that the linking mechanism 150 comprises a cable 455 extending between a first end 455a connected to the actuation system 130, in particular to the moving element 132, and a second end 455b. The cable 455 is a non-rotating "push-pull cable" type.

[0164] According to this fifth embodiment, the second end 455b of the cable 455 is connected directly to the three-point lock 122 and in particular to the spreader bar 328, and more specifically to the second end 328b of the spreader bar 328.

[0165] In this fifth embodiment, the first connecting rod 126 and the rocker arm 328 are advantageously formed from a single block, that is, with continuous material, as in the illustrated example. In other words, the first connecting rod 126 and the rocker arm 328 form a monolithic piece with an overall V-shape, as illustrated in Figures 20 and 21.

[0166] The first connecting rod 126 and the rocker arm 328 being a single monolithic piece, the second end 455b of the cable 455 is directly connected to the three-point lock 122 and in particular to the first connecting rod 126.

[0167] This fifth configuration allows the actuation system 130, and in particular the movable element 132, to be relocated by positioning it on the nacelle, for example at 3 o'clock or 9 o'clock, by analogy with the face of a clock, while the three-point lock 122 is positioned on the nacelle at 6 o'clock, by analogy with the face of a clock. Alternatively, the actuation system 130, and in particular the movable element 132, is positioned on the front frame 62, in particular at 6 o'clock, by analogy with the face of a clock.

[0168] To unlock the locking system 500 ([Fig.20]), the operator easily maneuvers the movable element 132, which is easily accessible at 3 o'clock or 9 o'clock by analogy with a clock face, to move it from one extreme position corresponding to the locked position of the three-point lock 122 to another extreme position corresponding to the unlocked position of the three-point lock 122 ([Fig.21]).

[0169] The mobile element 132 is directly connected to the second end 455b of the cable.

[0170] The actuation of the actuating system 130 is achieved by the operator pulling the moving element 132 directly or via a suitable tool. This actuation is then transmitted to the three-point lock 122 by the cable 455 directly onto the first connecting rod 126 and more precisely onto the second end 328b of the rocker arm 328. Pulling the moving element 132 causes a pull T1 on the second end 328B of the rocker arm 328, causing the axis C2 of the three-point mechanism 125 to pivot to the other side of the force alignment line X0. The three-point mechanism 125 is in its unlocked position ([Fig. 19]). This movement allows the hook 124 to release the stirrup 112.

[0171] Conversely, to lock the locking system 500, the actuation system 130 is actuated so as to push the moving element 132 by the operator directly or via a suitable tool. This actuation is then transmitted to the three-point lock 122 by the cable 455 directly onto the first connecting rod 126 and more precisely onto the second end 328b of the rocker arm 328. The movement of the moving element 132 in the opposite direction causes a thrust P2 on the second end 328b of the rocker arm 328, causing the axis C2 of the three-point mechanism 125 to pivot to the other side of the force alignment line X0. The three-point mechanism 125 is in its locked position ([Fig. 20]). This movement allows the hook 124 to cooperate in a retaining manner with the stirrup 112.

[0172] Such an arrangement makes it possible on the one hand to do away with a slot or access hatch to the three-point lock, because there is no longer a need for the traditional handle to operate it and the hoods can cover the three-point lock 122, making it possible to considerably improve the aerodynamics of the nacelle.

[0173] Although the invention has been described for two thrust reverser cowlings, it applies to any turbomachine nacelle comprising two cowlings or two parts rear side panels that can open and close onto each other. For example, these two hoods could be blower hoods.

[0174] Furthermore, the invention has been described in the context of a grid thrust reverser. However, the invention also applies to other types of thrust reversers, for example to a gate thrust reverser.

Claims

Demands

1. Locking system (100; 200; 300; 400; 500) for a turbomachine nacelle comprising a first and a second cowling (44A, 44B), the locking system comprising: - a bracket (112) for being fixed to the first cowling (44A); - a three-point lock (122) for being fixed to the second cowling (44B), comprising a support (123), a hook (124) integral with the support and a three-point mechanism (125) articulated at a point on the support, the three-point mechanism being movable between a locking position in which the hook (124) cooperates in retention with the bracket (112) in a closed position of the cowlings and an unlocking position in which the hook (124) is disengaged from the bracket (112) and allows the cowlings to be opened;- an actuation system (130) of the three-point mechanism (125) between the locking and unlocking positions, the locking system is characterized in that the actuation system (130) is arranged at a distance from the three-point lock and in that the locking system (100) comprises a linking mechanism (150) connecting the actuation system (130) to the three-point lock (122) and configured to maneuver the three-point lock between the locking and unlocking positions according to the actuation system.;

2. Locking system according to claim 1, wherein: - the three-point mechanism (125) comprises a first connecting rod (126) and a second connecting rod (127) each having a first end (126a, 127a) and a second end (126b, 127b), the first and second connecting rods being articulated to each other by their respective second ends (126b, 127b) around an axis of rotation (C2); - the three-point mechanism (125) comprises a rocker arm (128; 328) movable between two respective extreme positions, the movement of the rocker arm from one extreme position to the other resulting in the activation of the three-point mechanism (125) between the locking and unlocking positions, the rocker arm (128; 328) being integral with the first connecting rod (126) or the second connecting rod (127); and - the linkage mechanism (150) includes a linkage means (155; 455) having a first end (155a; 455a) connected to the actuation system (130) and a second end (155b; 455b) connected to the rocker arm (128; 328).

3. Locking system (400; 500) according to claim 2, wherein the linking means (455) is configured such that a translation of its first end (455a) causes the three-point mechanism (125) to pivot between the locking and unlocking positions via the rocker arm (128; 328).

4. Locking system (100; 200; 300) according to claim 2, wherein the linking means (155) is configured such that a rotation of its first end (155a) causes the three-point mechanism (125) to pivot between the locking and unlocking positions via the rocker arm (128; 328).

5. Locking system (100) according to claim 4, wherein the rocker arm (128) and the first connecting rod (126) form a single piece and the return mechanism (140) comprises: - a threaded rod (142) movable relative to the support of the three-point lock and having an end (142b) connected to the three-point mechanism (125) and configured so that a displacement of the threaded rod operates the three-point lock between the locking and unlocking positions; - a set of gears (144) for driving the threaded rod comprising at least one toothed wheel (145);- a worm screw (146) having a first end (146a) connected to the actuation system (130) and a second end (146b) connected to the support (123) of the three-point lock and configured to cooperate with the threaded rod via the toothed wheel (145) of the gear set (144) so ​​that a rotation of the worm screw by the actuation system (130) causes a displacement of the threaded rod (142).

6. Nacelle (3) for an aircraft propulsion unit (1), comprising a first cowl (44A), a second cowl (44B), and a locking system (100; 200; 300; 400; 500) according to any one of the preceding claims, the locking system being configured to lock the cowls in the closed position when in a locked configuration and to allow the cowls to be opened when in an unlocked configuration.

7. Nacelle according to claim 6, wherein the nacelle (3) comprises a thrust reverser structure including the first and second cowlings (44A, 44B) and a front frame (62), and the three-point lock (122) is arranged on the nacelle (3) at 6 o'clock by analogy with a clock face.

8. Nacelle according to claim 7, wherein the actuation system (130) is arranged on the forward frame (62) of the thrust reverser structure.

9. Propulsion assembly (1) for aircraft, comprising a nacelle (3) according to any one of claims 6 to 8.

10. Aircraft, comprising a propulsion assembly (1) according to the preceding claim 9.

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