FR3098195A1 - Aircraft comprising at least one cowl associated with a spacing system - Google Patents

Abstract

Aircraft comprising at least one cowl associated with a spacing system The subject of the invention is an aircraft comprising: at least one cowl (22) connected to a fixed structure by a pivot axis, movable relative to the fixed structure between a open position and a closed position, at least one locking mechanism configured to occupy a locked state in which it maintains the cover (22) in the closed position and an unlocked state in which it allows the cover (22) to pivot at least one system spacer (30) configured to push the cover (22) into a ajar position when the locking mechanism is not properly locked. Figure 5

Description

Aircraft comprising at least one cowl associated with a spacer system

The present application relates to an aircraft comprising at least one cowl associated with a spacer system allowing the cowl to be pushed back into the open position if it is not correctly locked.

According to one embodiment, an aircraft nacelle comprises two cowls, positioned symmetrically with respect to a vertical median plane of the nacelle, each of them being articulated in the upper part of the nacelle so as to be able to pivot between a position open in which it allows access to the engine in particular and a closed position in which the outer surface of the cover is arranged in the extension of the rest of the outer surface of the nacelle. The lower edges of the covers are substantially contiguous in the closed position and held in this position by locking mechanisms distributed along the lower edges of the covers.

Each locking mechanism is configured to occupy a locked state in which it holds the covers in the closed position and an unlocked state in which the covers are free to pivot. Each locking mechanism includes a handle accessible from the outside of the nacelle, allowing the state of the locking system to be changed.

Before takeoff, it is essential to check that the cowls are in the closed position and in the locked state so that they do not open in flight.

However, due to their weight and the position of their pivot axis, the cowls tend to position themselves automatically in the closed position so that it is difficult for an operator to determine whether the cowls are properly locked.

To ensure detection of the unlocked state of the covers, the nacelle includes visual type detection devices. Thus, the handles of the locking mechanisms protrude from the outer surface of the nacelle as long as the locking mechanisms are not in the locked state.

Furthermore, the nacelle may comprise elements other than the handles, such as for example a flap or flags which project as long as the locking mechanisms are not in the locked state.

According to another embodiment described in the document FR-3,007,390, at least one locking mechanism comprises a sensor making it possible to detect whether the locking mechanism is in the locked state.

These various detection devices are not fully satisfactory because it is possible that a bonnet in the closed position but not correctly locked is not detected.

The present invention aims to remedy all or part of the drawbacks of the prior art.

To this end, the subject of the invention is an aircraft comprising at least one cowl connected to a fixed structure by a pivot axis, said cowl being movable relative to the fixed structure between an open position and a closed position, the aircraft comprising at least one locking mechanism configured to occupy a locked state in which it holds the cover in the closed position and an unlocked state in which it allows the cover to pivot. According to the invention, the aircraft comprises at least one spacer system comprising a lever which has a first end connected to a first element among the cowl and the fixed structure as well as a second end configured to bear against a second element between the cover and the fixed structure, different from the first element, the lever being movable between a first position in which the second end bears against the second element in the closed position of the cover and a second position in which the lever holds the cover in a half-open position, the spacer system comprising an elastic element configured to hold the lever in the second position.

If the locking mechanism is not correctly locked, the spacer system pushes the bonnet to a half-open position, making it easier to detect incorrect locking.

According to another characteristic, the spacer system comprises a pivot pin, connected to the first element, to which the first end of the lever is connected, the pivot pin being approximately parallel to the pivot pin of the cover.

According to another characteristic, the elastic element is a spiral spring, wound around the pivot axis of the spacer system, having a first end connected to the pivot axis and a second end connected to the first element.

According to another characteristic, the spacer system comprises a casing secured to the first element in which the spiral spring is positioned and to which the second end of the spiral spring is connected, the pivot axis being connected to the casing by a pivoting connection .

According to another characteristic, the housing comprises two flanges between which the spiral spring is positioned, the two flanges being connected at their peripheral edges and having openings forming bearings for the pivot axis.

According to another feature, the spacer system comprises a stop to limit movement of the lever when the bonnet is in the open position.

According to another characteristic, the spacer system comprises a pivoting roller, integral with the second element, against which the lever rolls.

According to another characteristic, the pivoting roller is connected by a pivot axis to a support fixed to the second element.

Other characteristics and advantages will emerge from the description of the invention which follows, description given by way of example only, with regard to the appended drawings, among which:

is a perspective view of an aircraft,

is a perspective view of an aircraft propulsion system,

is a perspective view of two cowls of an aircraft nacelle equipped with a spacer system which illustrates an embodiment of the invention,

is a perspective view of the lower parts of the two covers visible in Figure 3,

is a front view of a spacer system which illustrates one embodiment of the invention, and

is a perspective view of part of the spacer system visible in Figure 5.

According to one embodiment visible in Figures 1 and 2, an aircraft 10 comprises several thruster assemblies 12 positioned under each of the wings 14 of the aircraft. Each propulsion unit 12 comprises an engine 16, a nacelle 18 positioned around the engine 16 as well as a mast 20 connecting the engine 16 and the wing 14.

Motor 16 includes an axis of rotation A16.

To ensure daily maintenance as well as the upkeep of the engine 16 and its components, the nacelle 18 comprises, at its outer surface, an opening allowing access to the interior of the nacelle 18 and a movable part called the cover. 22 which has an outer face 24, movable relative to a fixed structure (the engine 16, the rest of the nacelle and/or the mast 20) between a closed position in which the outer face 24 of the cover 22 is arranged in the extension of the outer surface of the nacelle 18 so as to close said opening and an open position in which the cover 22 frees, at least partially, the opening.

According to one configuration, the nacelle 18 comprises symmetrical right and left cowls 22, 22', hinged around pivot axes A22, A22' arranged on either side of the mast 20 and approximately parallel to the motor axis A16.

For the remainder of the description, a longitudinal direction is parallel to the pivot axes A22, A22'. A transverse plane is a plane perpendicular to the pivot axes A22, A22'.

Each cover 22, 22' has a lower edge 26, 26', the lower edges 26, 26' of the covers 22, 22' being substantially contiguous in the closed position and held in this position by at least one locking mechanism 28 (visible on figures 3 and 4). According to one configuration, the covers 22, 22' comprise several locking mechanisms 28 distributed along the lower edges 26, 26' of the covers 22', 22'.

According to one embodiment, each locking mechanism 28 comprises an anchoring point, provided at the level of the lower edge 26 of a first cover 22, as well as an articulated hook provided at the level of the lower edge 26' of a second cover 22' and configured to grasp the anchor point in order to hold the two covers 22, 22' in the closed position. To maneuver the hook, the locking mechanism 28 includes a handle.

The locking mechanism 28 is configured to occupy a locked state in which the covers 22, 22' are held in the closed position, the hook being hooked to the anchor point, and an unlocked state in which the covers 22, 22' are free to pivot, the hook not being or being incorrectly attached to the anchoring point.

Of course, the invention is not limited to this configuration. Thus, the invention can be implemented on any movable cowl 22 of an aircraft, relative to a fixed frame, between an open position and a closed position, said cowl being equipped with at least one locking mechanism 28 configured to occupy a locked state in which the cover 22 is held in the closed position and an unlocked state in which the cover 22 is free and can pivot into the open position.

At least one of the two covers 22 is associated with a spacer system 30 configured to push the cover 22 into a half-open position when the locking mechanism 28 is in the unlocked state. Consequently, if the locking mechanism 28 is not in the locked state, the cover 22 is automatically pushed into the half-open position, thus facilitating the detection of a bad locking.

According to one embodiment, the spacing system 30 comprises a lever 32 having a first end 32.1 connected to a fixed element 34 and a second end 32.2 configured to bear against the cover 22 or against any element connected to the cover 22. The lever 32 is movable between a first position in which the second end 32.2 bears against the cover 22 in the closed position, the locking mechanism 28 being in the locked state, and a second position (visible in FIG. 6 in dotted lines ) in which the lever 32 maintains the cover 22 in the half-open position.

According to one configuration, the first end 32.1 is secured to a pivot pin 36 connected to the fixed element 34 by a pivoting connection 38 so as to allow the pivot pin 36 to pivot on itself. The pivot axis 36 is oriented approximately parallel to the longitudinal direction so that the lever 32 moves in a transverse plane.

The spacing system 30 comprises an elastic element 40 configured to maintain the lever 32 in the second position. When the cover 22 is in the closed position and the locking mechanism 28 in the locked state, the elastic element 40 is in the compressed state. According to the invention, as long as the locking mechanism 28 is not locked well enough to resist a predetermined opening force, the elastic element 40 pushes the cover 22 back into the half-open position. The elastic element 40 has a stiffness adjusted to hold the cover 22 in the half-open position.

According to one embodiment, the elastic element 40 is a spiral spring 42 wound around the pivot axis 36 and having a first end connected to the pivot axis 36 as well as a second end connected to the element fixed 34. Of course, the invention is not limited to this type of spring. Thus, the spacer system 30 could include a compression spring. However, a spiral spring 42 makes it possible to obtain a spacer system 30 that is compact and has a higher energy absorption capacity than other springs.

Moreover, the elastic element 40 could not be a spring. Thus, the lever 32 and the elastic element 40 could be a single element such as for example an elastic strip whose first end is integral with a fixed element 34 and whose second end is configured to bear against the cover 22.

According to one embodiment, the fixed element 34 is a housing 44, connected to the fixed structure (the motor 16 and/or the nacelle 18), in which is positioned the spiral spring 42, the pivot axis 36 being connected to the housing 44 by the pivoting connection 38. This housing 44 comprises two flanges between which the spiral spring 42 is positioned, the two flanges being connected at their peripheral edges and having openings forming bearings for the axis of swivel 36.

According to one arrangement, the housing 44 is connected to a support 46 integral with the motor 16.

The spacing system 30 includes a stop 48 to limit the movement of the lever 32 when the cover 22 is in the open position. According to one configuration, the spiral spring 42 is always compressed, even when the cover 22 is in the partially open position. According to one configuration, the stop 48 is integral with the housing 44. According to one embodiment, the position of the stop 48 is adjustable.

In operation, when an operator closes the cover 22, the latter pivots with respect to its pivot axis A22, comes into contact with the second end 32.2 of the lever 32 and pushes it until it comes into the closed position by compressing the spring at spiral 42. If the locking mechanism 28 is correctly locked and resists the predetermined opening force, the cover 22 is held in the closed position, the spiral spring 42 being compressed. If the locking mechanism 28 is not correctly locked and cannot resist the predetermined opening force, the compressed spiral spring 42 pushes the cover 22 back into a half-open position (facilitating the detection of poor closing of the cover 22) and comes to rest against the stop 48.

According to one embodiment visible in Figure 5, to limit friction between the lever 32 and the cover 22, the spacer system 30 comprises a pivoting roller 50 connected to the cover 22 by a pivot axis A50 approximately parallel to the direction longitudinal, the lever 32 and the pivoting roller 50 being respectively positioned on the motor 16 and the cover 22 so as to cooperate with each other when the cover 22 is in the closed position. Thus, when the cover 22 is closed, the lever 32 rolls against the pivoting roller 50.

According to one configuration, the pivoting roller 50 is connected by the pivot axis A50 to a support 52 fixed to a reinforcement 54 of the cover 22.

According to the embodiment visible in Figure 5, the spacing system 30 comprises a first part comprising the lever 32, the pivot pin 36, the spiral spring 42 and the casing 44 as well as a second part comprising the roller swivel 50. According to a first configuration, the first part is supported by a fixed element such as the motor 16 and/or the nacelle 18 and the second part is supported by the cover 22. According to a second configuration, the first part is supported by the cowl 22 and the second part is supported by a fixed element such as the engine 16 and/or the nacelle 18.

Whatever the embodiment, the spacer system 30 comprises at least one lever 32 as well as an elastic element 40 and can be connected to the cover 22 or to the fixed structure with respect to which the cover 22 pivots.

According to another advantage, the spacer system 30 is versatile and can be mounted either on the right and/or left cover 22, 22' of the nacelle 18.

Claims (8)

Aircraft comprising at least one cowl (22, 22') connected to a fixed structure by a pivot pin (A22, A22'), said cowl (22, 22') being movable relative to the fixed structure between an open position and a closed position, the aircraft comprising at least one locking mechanism (28) configured to occupy a locked state in which it maintains the cowl (22, 22') in the closed position and an unlocked state in which it authorizes the cowl (22 , 22') to pivot, characterized in that the aircraft comprises at least one spacer system (30) comprising a lever (32) which has a first end (32.1) connected to a first element among the cowl (22, 22') and the fixed structure as well as a second end (32.2) configured to bear against a second element among the cover (22, 22') and the fixed structure, different from the first element, the lever (32) being mobile between a first position in which the second end (32.2) bears against the second element in the closed position of the cover (22, 22') and a second position in which the lever (32) holds the cover (22, 22' ) in a half-open position, the spacer system (30) comprising an elastic element (40) configured to maintain the lever (32) in the second position. Aircraft according to Claim 1, characterized in that the spacer system (30) comprises a pivot pin (36), connected to the first element, to which the first end (32.1) of the lever (32) is connected, the pin pivot (36) being approximately parallel to the pivot axis of the cover (22, 22'). Aircraft according to the preceding claim, characterized in that the elastic element (40) is a spiral spring (42), wound around the pivot axis (36) of the spacer system (30), having a first end connected to the pivot axis (36) and a second end connected to the first element. Aircraft according to the preceding claim, characterized in that the spacer system comprises a casing (44) integral with the first element in which the spiral spring (42) is positioned and to which the second end of the spiral spring (42) is connected. , the pivot axis (36) being connected to the housing (44) by a pivoting connection (38). Aircraft according to the preceding claim, characterized in that the casing (44) comprises two flanges between which the spiral spring (42) is positioned, the two flanges being connected at their peripheral edges and having openings forming bearings for the pivot axis (36). Aircraft according to one of the preceding claims, characterized in that the spacer system (30) comprises a stop (48) to limit movement of the lever (32) when the cowl (22, 22') is in the open position. Aircraft according to one of the preceding claims, characterized in that the spacer system (30) comprises a pivoting roller (50), integral with the second element, against which the lever (32) rolls. Aircraft according to the preceding claim, characterized in that the pivoting roller (50) is connected by a pivot pin (A50) to a support (52) fixed to the second element.