IMPROVED JOINT FOR AIRCRAFT OPENING

Abstract

The invention relates to a hinged joint for an aircraft opening (P), said joint comprising a first series of hinges (C1) supported by the fuselage (F) and a second series of hinges (C2) supported by the opening, the hinges of one series being coaxially interlocked with the hinges of the other series, thus enclosing a longitudinal shaft (A) that pivots the opening. The invention is characterized in that the first series of hinges (C1) extends, at each end of the longitudinal shaft (A), into a lateral bracket (B) carrying an intermediate connecting rod (1) that provides rotary connections, respectively, with said bracket (B) and with a deflector (2) pivotally mounted on the opening (P) and intended to cover, at least in the closed position, the two series of hinges (C1, C2) while remaining flush with the fuselage. Abstract figure: Figure 1

Description

Title of the invention: IMPROVED ARTICULATION FOR AIRCRAFT OPENING technical field

[0001] The invention relates to the field of aeronautics and, more particularly, to the so-called "piano" hinge joints integrated into the architecture of aircraft openings and is concerned with an improvement of joints of this type.

[0002] In general, aircraft openings, and in particular outward and upward rotating doors (known as "outward" doors), offer the possibility of controlled movement and structural strength. This type of design makes it possible to limit structural reinforcements because the opening contributes to the overall rigidity of the aircraft fuselage.

[0003] Such openings are traditionally equipped with a hinged joint mounted in the upper part of the opening and comprising a pivot shaft engaged between hinges.

[0004] This hinge protrudes, at least partially, from the outside of the fuselage skin and also has gaps necessary to allow the mounting of the hinge pins and their relative free movement. Without additional means to complement this type of hinge, it is observed that the more the hinge protrudes outwards, the smaller the gaps become, and vice versa.

[0005] It therefore appears that this design creates aerodynamic disturbances at the interface between the opening and the aircraft fuselage, whether caused primarily by the hinge protrusion or by the gaps. These disturbances produce drag that can lead to both increased fuel consumption and noise pollution detrimental to passenger comfort.

[0006] In this problematic context, a technical solution was sought to eliminate the protrusions and gaps between the hinges, or at least reduce their impact, while maintaining the lowest possible constant clearance.

[0007] In order to achieve this objective, the invention proposes automatic and autonomous means for positioning the hinge inside the aerodynamic surface of the fuselage while sealing the gaps.

[0008] This objective is achieved, according to the invention, by means of a hinged joint for an aircraft opening, said joint comprising a first series of hinges carried by the fuselage and a second series of hinges carried by the opening, the links of one of the series being coaxially interlocked between the hinges of the other series by trapping a longitudinal shaft ensuring the pivoting of the opening, characterized in that the first series of hinges is extended, at each end of the longitudinal shaft, by a lateral bracket carrying an intermediate connecting rod ensuring rotary links, respectively, with said bracket and with a deflector pivotally mounted on the opening and intended to cover, at least in the closed position, the two series of hinges by being flush with the fuselage.

[0009] According to an advantageous feature of the articulation of the invention, the first series of hinges is mounted on a protruding plate inside the fuselage.

[0010] According to a specific embodiment of the articulation of the invention, the support extends in line with the projecting plate and is provided, at its free end, with an axis ensuring the rotational connection with the connecting rod.

[0011] According to another advantageous feature of the articulation of the invention, the second series of hinges is carried by a plate projecting on the inner face of the opening.

[0012] Preferably, the deflector has lateral legs and the width of the plates is less than the width of the opening so as to delimit a passage for the legs of the deflector when pivoting outwards from the fuselage.

[0013] According to yet another feature of the articulation of the invention, the plate of the opening is provided with lateral openings receiving the axes ensuring, respectively, the pivoting of the deflector relative to the opening and the rotation of the opening relative to the fuselage.

[0014] According to yet another embodiment of the invention, the deflector comprises two lateral arms framing the opening and each carrying an axis ensuring the rotational connection with the connecting rod.

[0015] Preferably, the rotating link axis of the deflector with the connecting rod is offset transversely from its pivot axis on the opening.

[0016] According to a preferred embodiment of the articulation of the invention, the connecting rod has a right-angled profile with two arms, each of which has an orifice forming a bearing for a rotating link axis.

[0017] According to the invention, the deflector is provided to extend in the plane of the opening in the closed position and in a substantially perpendicular plane in the open position.

[0018] Another object of the invention is an aircraft opening equipped with a hinge as defined above allowing it to be flush with the fuselage in the closed position and to be oriented upwards and outwards from the fuselage in the fully open position.

[0019] According to an advantageous feature of the invention, this opening is provided with a deflector designed to cover the series of swages, being flush with the fuselage in the closed position of the opening. PRESENTATION OF THE FIGURES

[0020] Other features and advantages of the invention will become apparent from the following non-limiting description, with reference to the accompanying drawings in which:

[0021] [Fig. 1] is a perspective view of the inner face of an aircraft opening equipped with a preferred embodiment of the articulation of the invention, in the closed position.

[0022] [Fig.2] is an exploded perspective view of the outer face of the opening of [Fig.1].

[0023] [Fig.3] is a side view of the opening of [Fig.1] in the intermediate position of opening outwards from the fuselage and upwards.

[0024] [Fig.4] is a detail and side view of the opening of [Fig.1] in the fully open position.

[0025] [Fig.5] is a detailed perspective view from outside the opening of [Fig.1] in the fully open position.

[0026] [Fig.6] is a detail view from below from outside the opening of [Fig.1] in the fully open position.

[0027] For clarity, identical or similar elements are indicated by identical reference numerals in the following description and in the figures. Naturally, the embodiments of the invention schematically illustrated in the figures above and described below are given only by way of non-limiting examples. It is explicitly provided for in the scope of the invention that different embodiments may be proposed and combined to provide others. DETAILED DESCRIPTION

[0028] The invention relates to aircraft openings and is particularly concerned with the articulation of openings that open upwards and outwards from the fuselage. Such openings are traditionally equipped with a hinged joint mounted on the upper part of the opening.

[0029] As illustrated by figures 1 and 2, this known hinge comprises a first series of hinges Cl carried by the fuselage F and a second series of hinges C2 carried by the opening P. The respective hinges of each series are nested coaxially within each other by trapping a longitudinal shaft A ensuring the pivoting of the opening P.

[0030] However, this hinge generally protrudes outside the fuselage skin and, moreover, has gaps between the chamons Cl, C2. Therefore, this hinge architecture generates aerodynamic disturbances that are detrimental to the connection between the opening P and the fuselage F of the aircraft.

[0031] The invention aims to modify the architecture of these hinges to eliminate, or at least mitigate, aerodynamic disturbance phenomena.

[0032] To this end, and as illustrated, in particular, by figures 2 and 5, the invention consists in the first series of hinges Cl extending, at each end of the longitudinal shaft A, by a lateral bracket B. The bracket B carries an intermediate connecting rod 1 ensuring rotational links, respectively, with the bracket B and with a deflector 2 pivotally mounted on the opening P. This deflector 2 is intended to cover, at least in the closed position of the opening P ([Fig.1]), the two series of hinges Cl, C2 while remaining flush with the fuselage F.

[0033] In order to move the hinge towards the inside of the fuselage to avoid disturbances, the two sets of hinges Cl, C2 are mounted, respectively, on a first protruding Fl plate carried by the internal wall of the fuselage and on a second protruding PI plate on the inner face of the opening P.

[0034] The support B thus extends in line with the plate Fl and is provided, at its free end, with an axis 10 ensuring the rotational connection with the connecting rod 1. The plate PI of the opening P is provided, for its part, with lateral orifices receiving the pivot axes 20 of the deflector 2.

[0035] Preferably, the deflector 2 has lateral legs 2a ([Fig.5]) and, consequently, the width of the plates Fl, PI is less than the width of the opening P so as to delimit a passage for these legs when pivoting the deflector 2 outwards from the fuselage, as illustrated by figures 3, 4 and 5.

[0036] The deflector 2 further comprises two lateral arms 22 framing the opening P and each carrying an axis 21 ensuring the rotational connection with the connecting rod 1. The axis 21 of rotational connection of the deflector 2 with the connecting rod 1 is transversely offset from its pivot axis 20 on the opening P.

[0037] The two axes 21 located on either side only ensure the rotation between the arms 22 and the connecting rod 1 and are not connected to the opening P. The two axes 20 also located on either side ensure the pivoting of the deflector 2 relative to the opening P. The shaft A allows the rotation of the opening P relative to the plate PI and the support Fl attached to the fuselage F.

[0038] According to a preferred embodiment of the articulation of the invention, the connecting rod 1 has a right-angled profile with two branches la, 1b, each of which has an orifice forming a bearing for the axes 10, 21 ensuring the rotary connections, respectively, with the support B and with the deflector 2.

[0039] The invention provides that the deflector 2 extends in the plane of the opening P in the closed position ([Fig.1]) and in a substantially perpendicular plane in the open position (figures 4 and 6).

[0040] When the opening P is opened outwards, the cams Cl, C2 pivot around the shaft A, and the movement of the plate PI causes the connecting rod 1 to rotate outwards from the fuselage. Simultaneously, this rotation of the connecting rod 1 causes the deflector 2 to pivot around its axis 20 relative to the plate PL.

[0041] Thanks to the combination between the plates Fl, PI and the deflector 2, the invention makes it possible to move the chamons Cl, C2 from the hinge towards the inside of the fuselage and to cover them flush with the fuselage by closing the intercalary spaces and thus avoiding aerodynamic disturbances.

Claims

Demands

1. Hinged joint for aircraft opening (P), said joint comprising a first series of shanks (Cl) carried by the fuselage (F) and a second series of shanks (C2) carried by the opening, the shanks of one of the series being coaxially interlocked between the shanks of the other series by enclosing a longitudinal shaft (A) ensuring the pivoting of the opening, characterized in that the first series of shanks (Cl) extends, at each end of the longitudinal shaft (A), by a lateral bracket (B) carrying an intermediate connecting rod (1) ensuring rotary links, respectively, with said bracket (B) and with a deflector (2) pivotally mounted on the opening (P) and intended to cover, at least in the closed position, the two series of shanks (Cl, C2) by being flush with the fuselage.

2. Articulation according to claim 1, characterized in that the first series of cams (Cl) is mounted on a plate (Fl) projecting inside the fuselage.

3. Articulation according to the preceding claim, characterized in that the arm (B) extends in the continuation of the projecting plate (Fl) and is provided, at its free end, with an axis (10) ensuring the rotational connection with the connecting rod (1).

4. Articulation according to one of the preceding claims, characterized in that the second series of cams (C2) is carried by a plate (PI) projecting on the inner face of the opening (P).

5. Articulation according to claims 3 and 4, characterized in that the deflector has lateral legs (2a) and the width of said plates (Fl, PI) is less than the width of the opening (P) so as to delimit a passage for said legs of the deflector when pivoting outwards from the fuselage.

6. Articulation according to claims 3 and 4, characterized in that the plate (PI) of the opening (P) is provided with lateral openings receiving the axes (20, A) ensuring, respectively, the pivoting of the deflector (2) relative to the opening (P) and the rotation of the opening (P) relative to the fuselage (F).

7. Articulation according to any one of the preceding claims, characterized in that the deflector (2) comprises two lateral arms (22) framing the opening (P) and each carrying an axis (21) ensuring the rotary connection with the connecting rod (1).

8. Articulation according to the preceding claim, characterized in that the axis (21) of rotational connection of the deflector (2) with the connecting rod (1) is transversely offset from its axis (20) of pivoting on the opening (P).

9. Joint according to one of the preceding claims, characterized in that the connecting rod (1) has a right-angled profile with two arms (la, 1b) each of which has a bearing-forming orifice for a rotating link axis (10,21).

10. Articulation according to any one of the preceding claims, characterized in that the deflector (2) extends in the plane of the opening (P) in the closed position and in a substantially perpendicular plane in the open position.

11. Aircraft opening (P) equipped with a hinge according to one of the preceding claims enabling it to be flush with the fuselage (F) in the closed position and to be oriented upwards and outwards from the fuselage in the fully open position.

12. Aircraft opening according to the preceding claim, characterized in that said deflector (2) is intended to cover the series of hinges (Cl, C2) by being flush with the fuselage (F) in the closed position of the opening (P).

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