Locking system, nacelle of an engine of an aircraft, and aircraft

Abstract

The invention relates to a locking system, a nacelle of an engine of an aircraft and an aircraft, the locking system for two fairings of the nacelle comprising: for each fairing, a hook movable in rotation between a locked position in which the hook cooperates with a roller of the fairing and an unlocked position, a handle link movable in rotation between a closed position and an open position, a handle fixed to the handle link, and for each hook, a spring-loaded link operating in traction and mounted between the handle link and the hook, and arranged to move the hook from the locked position to the unlocked position when the handle link is switched from the closed position to the open position, and to move the hook from the unlocked position to the locked position when the handle link is switched from the open position to the closed position. With such an arrangement, there are two hooks under tension and each interacting with one of the fairings.

Description

Technical Field

[0001] The present invention relates to a system for locking a fairing of an aircraft engine nacelle, an aircraft engine nacelle including such a locking system, and an aircraft including such a nacelle. Background Technology

[0002] The cabin surrounds the aircraft's engines and includes fairings that form aerodynamic surfaces. During maintenance operations, it is necessary to open or remove the fairings to allow technicians to work on the components located beneath them.

[0003] Each fairing is mounted hinged to multiple hinges located in the upper portion (typically at the 12 o'clock position) and locked by a locking system in the lower portion (typically at the 6 o'clock position). Current locking systems rely on hooks mounted hinged to one fairing and locked to rollers fixed to another fairing. This invention proposes an alternative that ensures redundancy and enhanced safety. Summary of the Invention

[0004] One object of the present invention is to provide a system for locking the fairing of an aircraft engine nacelle, which provides improved resistance performance.

[0005] To this end, a locking system for the two fairings of an aircraft cabin is proposed, the locking system comprising:

[0006] - Structure;

[0007] - A hook for each fairing, which is mounted to be structurally rotatably movable between a locked position and an unlocked position. In the locked position, the hook is intended to engage with the rollers of the fairing to secure the fairing. In the unlocked position, the hook does not engage with the rollers to release the fairing.

[0008] - A handle linkage that is mounted to be structurally movable in a rotatable manner between a closed position and an open position;

[0009] - A handle, which is fixed to a handle linkage; and

[0010] - A spring-loaded link for each hook, which operates in a traction state and has a first end and a second end, the first end being mounted hinged to a handle link and the second end being mounted hinged to a hook, and the spring-loaded link being arranged to move the associated hook from a locked position to an unlocked position when the handle link is switched from a closed position to an open position, and the spring-loaded link being arranged to move the associated hook from an unlocked position to a locked position when the handle link is switched from an open position to a closed position.

[0011] With this arrangement, there are two tensioned hooks, and each of the two tensioned hooks interacts specifically with one of the fairings via a single handle.

[0012] Advantageously, the connection between each hook and the second end of the associated spring-loaded link is achieved by means of a first link and a second link, the first link being mounted to be structurally rotatable, and the second link being mounted to be hinged to the hook on one side and to the first link on the other side, wherein the first link is mounted to be hinged to the second end of the spring-loaded link.

[0013] Advantageously, the locking system includes a first stop for each first link, the first stop being fixed to the structure, and the first link abutting against the first stop when the associated hook is in the locked position.

[0014] Advantageously, the locking system includes a second stop fixed to the structure, and the handle linkage abuts against the second stop when it is in the closed position.

[0015] Advantageously, the locking system includes a detection lever and a rod for each hook, the detection lever being mounted to be rotatably movable, the rod having a first end and a second end, the first end being mounted to be hinged to the hook and the second end being mounted to be hinged to the detection lever, and the detection lever being movable between a retracted position and an extended position, in which the detection lever does not prevent the handle link from turning toward its closed position, and in the extended position, the detection lever prevents the handle link from turning toward its closed position.

[0016] The present invention also proposes an engine nacelle for an aircraft, the nacelle comprising two fairings and at least one locking system according to one of the aforementioned variations, wherein each fairing is mounted as hinged at the upper portion and has rollers for each locking system, the rollers being arranged at the lower portion and designed to engage with an associated hook in the locked position.

[0017] Advantageously, the cabin includes:

[0018] - Multiple locking systems, wherein the locking systems are distributed along the fairing, and wherein only one of the handle links is equipped with a handle; and

[0019] - A shaft that is coaxial with the rotation axis shared by all the handle links in the handle linkage and is fixed to all the handle links in the handle linkage.

[0020] The present invention also proposes an aircraft having at least one cabin according to one of the aforementioned variations. Attached Figure Description

[0021] The features mentioned above, as well as other features of the invention, will become clearer when reading the following description of an exemplary embodiment, which is given with reference to the accompanying drawings, in which:

[0022] Figure 1 This is a side view of an aircraft equipped with a cabin featuring a locking system according to the present invention.

[0023] Figure 2 This is a schematic diagram of the front view of a locking system in the locked position according to the present invention.

[0024] Figure 3 It is in the unlocked position. Figure 2 A schematic diagram of the front view of the locking system in the diagram, and

[0025] Figure 4 It is in the unlocked position. Figure 2 A 3D diagram of the locking system. Detailed Implementation

[0026] Figure 1 An aircraft 10 is shown, comprising a fuselage 12, with wings 14 fastened to both sides of the fuselage. Each wing 14 carries at least one cabin 50, in which an engine is arranged. The cabin 50 is fastened to the wing 14 by pylons 16.

[0027] In the following description, and by convention, X represents the longitudinal axis of the cabin 50, which is parallel to the longitudinal axis of the aircraft 10 and has a positive orientation in the direction of the forward movement of the aircraft 10; Y represents the lateral axis, which is horizontal when the aircraft 10 is on the ground; and Z represents the vertical axis, which is vertical when the aircraft 10 is on the ground. These three axes X, Y and Z are orthogonal to each other.

[0028] The nacelle 50 includes two fairings 50a and 50b, which are arranged on either side of the vertical midplane XZ. Each fairing 50a and 50b is mounted to the structure of the pylon 16 or the engine via a hinge 20 at the upper portion of the fairing 50a and 50b (typically at the 12 o'clock position).

[0029] The cabin 50 also includes at least one locking system 100 according to the invention. Figure 1 In the embodiment of the invention shown, there are multiple locking systems 100 distributed along fairings 50a to 50b, and more specifically along the lower edges of fairings 50a to 50b.

[0030] Figure 2The previous view shows the locking system 100 according to the invention in the locked position, and... Figure 3 and Figure 4 The same locking system 100 is shown in the unlocked position.

[0031] Each fairing 50a to 50b has a roller 52 disposed at the lower portion of the fairing 50a to 50b (typically at the 6 o'clock position). If multiple locking systems 100 are present, each fairing 50a to 50b has one roller 52 for each of the locking systems 100.

[0032] The locking system 100 includes a structure 102, which may be part of the engine or part of the cabin 50.

[0033] The locking system 100 also includes hooks 104 for each fairing 50a to 50b, the hooks 104 being mounted to be in a locked position on the structure 102. Figure 2 ) and unlock location ( Figure 3 The rectifiers move in a rotational manner between the two parts. In the locked position, the hook 104 engages with the roller 52 of the corresponding rectifier 50a to 50b to fix the rectifier 50a to 50b. In the unlocked position, the hook 104 does not engage with the roller 52 to release the rectifier 50a to 50b, and then the rectifier 50a to 50b can move around the hinge 20.

[0034] In this case, the rotation axis 104a of each hook 104 is parallel to the longitudinal axis X.

[0035] The locking system 100 also includes a handle link 106, which is mounted to be in a closed position on the structure 102. Figure 2 ) and opening position ( Figure 3 The lever 106 moves in a rotating manner between the two. In this case, the axis of rotation 106a of the handle link 106 is parallel to the longitudinal axis X.

[0036] This invention provides a system for transmitting motion between each hook 104 and the same handle link 106. Each transmission system includes two tandem support devices such that if one support device fails, the other can take over to ensure the movement of the hook 104. The two transmission systems are connected to the same axis at the handle link 106: in the illustrated embodiment, the two transmission systems are connected to the axis on both sides of the handle link 106. Additionally, a system for detecting faults in each motion transmission system is provided in parallel with the motion transmission systems. This detection system provides a direct mechanical connection between the hook 104 and the structure 102. The purpose of this mechanical system is not to ensure the transmission of motion (which is ensured by the first path), but to warn the operator in the event of a transmission system failure. The purpose of this mechanical system is to provide a mechanical indication that the motion transmission system has failed and to mechanically prevent the closure of the associated fairings 50a to 50b in such cases.

[0037] The locking system 100 also includes a handle 107, which is attached to a handle link 106 and can be gripped by a technician from the outside of the cabin 50. Movement of the handle 107 by the technician will cause the handle link 106 to move in a rotational manner. In the closed position, the handle 107 retracts into one of the fairings 50a for aerodynamic reasons.

[0038] The locking system 100 includes a spring-loaded link 108 for each hook 104, operating in a traction state. The spring-loaded link 108 has a first end and a second end, the first end being mounted hinged to a handle link 106, and the second end being mounted indirectly hinged to a hook 104. The second end is fixed to a sleeve of the spring-loaded link 108 in this case, and the first end is fixed to a rod of the spring-loaded link 108 in this case. The rod is capable of translational movement relative to the sleeve, i.e., the rod can extend from the sleeve to a greater or lesser extent depending on the force applied between the two ends. The spring-loaded link 108 also has a traction spring mounted in the sleeve and between the sleeve and the rod to pull the rod and retract it back into the sleeve.

[0039] Each spring-loaded link 108 is arranged such that when the handle link 106 is switched from the closed position to the open position by the handle 107, the associated hook 104 moves from the locked position to the unlocked position, and when the handle link 106 is switched from the open position to the closed position by the handle 107, the associated hook 104 moves from the unlocked position to the locked position.

[0040] The hinge associated with each end of the spring-loaded link 108 is at least one rotating part, the axis of which is parallel to the longitudinal axis X in this case.

[0041] With this arrangement, each fairing 50a to 50b is held in a locked position by at least one hook 104, each of the at least one hook 104 being associated with a roller 52 and each hook 104 being subjected to the traction of a spring-loaded link 108, so as to structurally reinforce the fairing 50a to 50b.

[0042] In the embodiment of the invention shown here, the connection between each hook 104 and the second end of the associated spring-loaded link 108 is achieved by means of a combination of a first link 110 and a second link 112.

[0043] The first link 110 is mounted so that it can rotate on the structure 102, in this case rotating about a rotation axis 110a parallel to the longitudinal axis X.

[0044] The second link 112 is mounted such that it is hinged to the hook 104 at the first end on one side and to the first link 110 at the second end on the other side, while the first link 110 is mounted to the second end of the spring-loaded link 108.

[0045] Each end of the second link 112 and the hinge associated with the first link 110 is at least one rotating part, the axis of which is parallel to the longitudinal axis X in this case.

[0046] To stop the hook 104 when it is in the locked position, the locking system 100 includes a first stop 114 for each first link 110, the first stop 114 being fixed to the structure 102, and the first link 110 abutting against the first stop 114 when the associated hook 104 is in the locked position. The first link 110, the second link 112, and the stop 114 form a first support device.

[0047] Similarly, in order to stop the handle link 106 when it is in the closed position, the locking system 100 includes a second stop 116, which is fixed to the structure 102 and abuts against the second stop 116 when the handle link 106 is in the closed position. The handle link 106 and the spring-loaded link 108 together with the stop 116 form a second support device.

[0048] To prevent the handle link 106 or the handle 107 from moving toward the closed position when at least one of the hooks in the hook 104 is not in the locked position, the locking system 100 has a suitable fault detection system, as seen above.

[0049] Therefore, the detection system includes a detection lever 120 and a rod 122 for each hook 104.

[0050] The detection lever 120 is mounted to be rotatably movable between a retracted position and an extended position about a rotation axis 120a. In the retracted position, the detection lever 120 does not prevent the handle linkage 106 from turning toward its closed position. This rotation axis 120a is connected to the structure 102 and, in this case, parallel to the longitudinal axis X. In the embodiment of the invention shown here, the detection lever 120 has a protrusion 120b projecting outward toward the nacelle 50 in the extended position. Therefore, if everything is normal when the handle linkage 106 is in the closed position, the handle linkage 106 is flush with the fairings 50a to 50b, and the operator thus knows that the fairings 50a to 50b are correctly closed. When the handle linkage 106 is in the open position, the protrusion is visible, and the operator knows that the hook 104 has been released. On the other hand, if the transmission system malfunctions, since the hook 104 is directly connected to the structure via the rod 122 and the detection lever 120, if the hook 104 does not move due to the malfunction, the detection lever 120 also does not move, thereby allowing the malfunction to be detected.

[0051] Each lever 122 has a first end and a second end, the first end being hinged to an associated hook 104 and the second end being hinged to a detection lever 120. The hinge associated with each end of the lever 122 is at least one rotating portion, the axis of which is in this case parallel to the longitudinal axis X.

[0052] When the two hooks 104 move from the locked position to the unlocked position, they push the detection lever 120 backward, and the detection lever 120 enters the extended position. When the two hooks 104 move from the unlocked position to the locked position, they pull the detection lever 120, and the detection lever 120 retracts toward the retracted position.

[0053] If at least one of the hooks 104 does not enter the locked position, the detection lever 120 remains in the extended position, and the handle link 106 cannot move toward the closed position.

[0054] In the embodiment of the invention shown here, to assist in operating the handle 107, the locking system 100 includes a secondary handle 105, which is mounted to be rotatably movable about a rotation axis 105a on the handle link 106. The secondary handle 105 is movable between an extended position and a retracted position. In the retracted position, the secondary handle 105 extends the handle 107 to form an aerodynamic surface by closing the space between the fairings 50a and 50b. In the extended position, the secondary handle 105 extends outward toward the nacelle 50.

[0055] exist Figure 1In the embodiment of the invention shown, there are multiple locking systems 100, and according to a first variant, each of the multiple locking systems 100 may have a handle 107, and in this case, each handle 107 must be manipulated in order to open and close the fairings 50a to 50b.

[0056] According to another variation, there may be a handle 107 shared by all locking systems in the locking system 100, and thus only one handle link in the handle link 106 is equipped with the handle 107.

[0057] The rotation axis 106a of all the handle links in the handle linkage 106 is coaxial, and the cabin 50 then includes a shaft 130, which is coaxial with the rotation axis 106a and fixed to all the handle links in the handle linkage 106.

[0058] Therefore, the movement of handle 107 will cause all handle links in handle linkage 106 to move.

Claims

1. A locking system (100) for two fairings (50a-50b) of the cabin (50) of an aircraft (10), the locking system (100) comprising: Structure (102); Hooks (104) for each fairing (50a-50b) are mounted to be rotatably movable on the structure (102) between a locked position and an unlocked position. In the locked position, the hooks (104) are intended to engage with rollers (52) of the fairings (50a-50b) to secure the fairings (50a-50b). In the unlocked position, the hooks are not engaged with the rollers (52) to release the fairings (50a-50b). A handle link (106) is mounted to be rotatably movable on the structure (102) between a closed position and an open position; Handle (107), said handle (107) being fixed to said handle link (106); and A spring-loaded link (108) for each hook (104), the spring-loaded link (108) operating in a traction state and having a first end and a second end, the first end of the spring-loaded link (108) being mounted to the handle link (106), the second end of the spring-loaded link (108) being mounted to the hook (104), and the spring-loaded link being arranged to move the associated hook (104) from the locked position to the unlocked position when the handle link (106) is switched from the closed position to the open position, and the spring-loaded link being arranged to move the associated hook (104) from the unlocked position to the locked position when the handle link (106) is switched from the open position to the closed position.

2. The locking system (100) according to claim 1, wherein, The connection between each hook (104) and the second end of the associated spring-loaded link (108) is achieved by means of a first link (110) and a second link (112), the first link (110) being mounted to be rotatably movable on the structure (102), and the second link (112) being mounted to be hinged to the hook (104) on one hand and to the first link (110) on the other hand, wherein the first link (110) is mounted to be hinged to the second end of the spring-loaded link (108).

3. The locking system (100) according to claim 2, wherein, The locking system (100) includes a first stop (114) for each first link (110), the first stop (114) being fixed to the structure (102), and the first link (110) abutting against the first stop (114) when the associated hook (104) is in the locked position.

4. The locking system (100) according to claim 1, wherein, The locking system (100) includes a second stop (116) fixed to the structure (102), and the handle link (106) abuts against the second stop (116) when the handle link (106) is in the closed position.

5. The locking system (100) according to claim 1, wherein, The locking system (100) includes a detection lever (120) and a rod (122) for each hook (104), the detection lever (120) being rotatably movable, the rod (122) having a first end and a second end, the first end of the rod (122) being hinged to the hook (104), the second end of the rod (122) being hinged to the detection lever (120), and wherein the detection lever (120) is movable between a retracted position and an extended position, in the retracted position, the detection lever (120) not preventing the handle link (106) from changing toward the closed position of the handle link (106), and in the extended position, the detection lever (120) preventing the handle link (106) from changing toward the closed position of the handle link (106).

6. An engine compartment (50) of an aircraft (10), the compartment (50) comprising two fairings (50a-50b) and at least one locking system (100) according to claim 1, wherein, Each fairing (50a-50b) is mounted as hinged at the upper portion and has a roller (52) for each locking system (100), the roller (52) being arranged at the lower portion and designed to engage with the associated hook (104) in the locked position.

7. The cabin (50) according to claim 6, wherein, The cabin (50) includes: Multiple locking systems (100) are distributed along the fairing (50a-50b), wherein only one of the handle links (106) is equipped with the handle (107); and Shaft (130), which is coaxial with the rotation axis (106a) shared by all the handle links in the handle link (106) and fixed to all the handle links in the handle link (106).

8. An aircraft (10) comprising at least one cabin (50) according to claim 6.

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