Aircraft landing gear equipped with a leaf spring locking device

Abstract

Landing gear (1) comprising: a leg (2) arranged to be movably mounted on a structure (3) between a deployed and a retracted position; at least one bracing member (4) for maintaining the leg in the deployed position, comprising a first connecting rod (4a) articulated on the structure and a second connecting rod (4b) articulated on the first connecting rod and on the leg; a stabilizing member (6) for maintaining the first and second connecting rods (4a, 4b) in an aligned position, comprising a first connecting rod (6a) and a second connecting rod (6b) articulated with each other, and the second connecting rod being articulated on the first connecting rod; and at least one leaf spring (11) and a rocker (12) for elastically returning the joints of the first and second connecting rods to a substantially aligned position. FIGURE IN ABRIDGED DIAGRAM: Fig. 1

Description

Title of the invention: Aircraft landing gear equipped with a leaf spring locking device

[0001] The present invention relates to the field of landing gear and more particularly to means of locking the landing gear in the deployed position.

[0002] BACKGROUND OF THE INVENTION

[0003] Aircraft landing gear is known comprising a leg mounted movable on the structure of an aircraft between a deployed position (for takeoff and landing) and a retracted position (for flight) under the action of a maneuvering actuator.

[0004] The leg is held in the deployed position by a breakaway strut which is attached to the leg and to the aircraft structure, and which comprises two connecting rods articulated together and held in an aligned position by a stabilizing member.

[0005] The stabilizing member comprises two connecting rods articulated between each other and held in a substantially aligned position by a passive locking member in order to prevent misalignment of the counter brace.

[0006] Passive locking devices are known to comprise a leaf spring having one end fixed to one of the connecting rods, and an opposite end permanently bearing on an arm of a rocker arm mounted to rotate freely about the articulation axis of said connecting rods. The rocker arm is arranged so that the leaf spring is brought to an elastically deformed state under a bending force generated by the rotation of the rocker arm when the joints of the first and second connecting rods leave their substantially aligned position.

[0007] The rotation of the rocker arm generates friction between the rocker arm and the end of the leaf spring, which leads to premature wear of said rocker arm and of said end of the leaf spring.

[0008] SUBJECT OF THE INVENTION

[0009] The invention therefore aims to provide a lander that at least partially overcomes the aforementioned drawback. Summary of the invention

[0010] To this end, a lander is proposed comprising: • a leg arranged to be mounted movably on a structure between a deployed position and a retracted position; • at least one bracing element to maintain the leg in the deployed position, comprising a first connecting rod articulated on the structure and a second connecting rod articulated on the first connecting rod and on the leg; • a stabilizing device to maintain the first and second connecting rods in an aligned position, comprising a first connecting rod and a second connecting rod articulated with each other, and of which the second connecting rod is articulated on the first connecting rod; and • at least one leaf spring and a rocker arm to elastically return the joints of the first connecting rod and the second connecting rod to a substantially aligned position.

[0011] According to the invention, the leaf spring has one end rigidly fixed to the first connecting rod or the second connecting rod, and an opposite end permanently supported on a first rocker arm via a roller, the rocker being mounted to rotate freely around the articulation axis of the first connecting rod and the second connecting rod, and the roller being arranged to roll on the leaf spring or the rocker arm during a pivoting of said rocker around the articulation axis.

[0012] The roller helps to limit friction between the leaf spring and the rocker and therefore to reduce their wear and increase their lifespan.

[0013] According to a particular feature, the roller bearing is spherical.

[0014] According to another particular feature, the pebble comprises a cylindrical external surface.

[0015] According to another particular feature, the roller is carried by the first arm of the rocker.

[0016] In particular, the leaf spring includes a pad on which the roller is in permanent contact.

[0017] According to another particular feature, the leaf spring is arranged to be brought to an elastically deformed state under a bending force exerted by the roller when the joints of the first and second connecting rods leave their substantially aligned position, and to escape the bending force and be in a state of least deformation when the leg is between the retracted position and an intermediate position between the retracted position and the deployed position.

[0018] According to another particular feature, the rocker is rotationally linked to the first connecting rod when the leg is between the retracted position and the intermediate position, and rotationally linked to the second connecting rod when the leg is between the intermediate position and the deployed position.

[0019] In particular, the rocker has a second arm bearing against a surface of the first connecting rod when the leg is between the retracted position and the intermediate position, and bearing against a surface of the second connecting rod when the leg is between the intermediate position and the deployed position.

[0020] According to another particular feature, the volume occupied by the leaf spring and the rocker when the leg is in the deployed position is contained within the volume swept away by the first connecting rod when the leg moves from the retracted position to the deployed position.

[0021] The invention also relates to an aircraft comprising at least one such landing gear. Brief description of the drawings

[0022] The invention will be better understood in the light of the following description, which is purely illustrative and not limiting, and should be read in conjunction with the accompanying drawings, among which:

[0023] [Fig-1] [Fig.1] is a side view of an aircraft landing gear according to a first embodiment of the invention, shown in retracted position;

[0024] [Fig.2] [Fig.2] is a view analogous to [Fig.1] showing the lander in a first intermediate position at the beginning of the deployment phase;

[0025] [Fig.3] [Fig.3] is a view analogous to [Fig.1] showing the lander in a second intermediate position at the end of the deployment phase;

[0026] [Fig.4] [Fig.4] is a view analogous to [Fig.1] showing the lander in the deployed position;

[0027] [Fig.5] [Fig.5] is a perspective view of part of the lander illustrated in [Fig.4];

[0028] [Fig.6] [Fig.6] is a partial perspective view, enlarged, of the part of the lander illustrated in [Fig.5];

[0029] [Fig.7A] [Fig.7A] is a schematic view of a first variant of the ball joint between the leaf spring and the rocker of the lander illustrated in [Fig.1];

[0030] [Fig. 7B] [Fig. 7B] is a schematic view of a second variant of the ball joint between the leaf spring and the rocker arm of the lander illustrated in [Fig. 1]. DETAILED DESCRIPTION OF THE INVENTION

[0031] With reference to Figures 1 to 4, an aircraft landing gear 1 comprises, in a manner known per se, a leg 2 having a first end carrying wheels R and, opposite it, a second end articulated to an aircraft structure 3 along a substantially horizontal articulation axis XI in operation. The leg 2 is movable between a retracted position illustrated in [Fig. 1] and a deployed position illustrated in [Fig. 4]. The leg 2 is held in the deployed position by means of a bracing member 4 comprising a first connecting rod 4a articulated to the aircraft structure 3 along a articulation axis X2 and a second connecting rod 4b articulated to the leg 2 and to the first connecting rod 4a along respective articulation axes X3 and X4. In the deployed position, the first connecting rod 4a and the second connecting rod 4b are in a substantially aligned position.

[0032] A rotary actuator 5 is mounted for free rotation on the aircraft structure 3 along a rotation axis X5 parallel to the articulation axes XI-X4. The actuator 5 comprises a housing equipped with an appendage forming a first connecting rod 6a, and includes a shaft mounted to rotate about the axis X5 and carrying a crank 7. The relative angular position between the first connecting rod 6a and the crank 7 can be modified by supplying power to the actuator 5 to rotate the shaft relative to the housing. The first connecting rod 6a is coupled to the first connecting rod 4a of the bracing member 4 by means of a second connecting rod 6b articulated to the first connecting rod 6a about an axis X6 and articulated to the first connecting rod 4a about an axis X7. The crank 7 is coupled to the leg 2 by means of another connecting rod 8 articulated to the crank 7 about an axis X8 and articulated to a horn of the leg 2 about an axis X9. All axes XI to X9 are parallel to each other here.

[0033] In the position illustrated in [Fig. 4], in which the leg 2 is in the deployed position, the relative angular position of the connecting rod 6a and the crank 7 is such that the connecting rods 6a, 6b are in a substantially aligned position, referred to as the first alignment. As is known per se, the first alignment is a position obtained by moving the connecting rods 6a, 6b slightly beyond their geometric alignment (which is defined by the perfect alignment of the axes X5, X6, and X7 in the same plane) to bring them against their respective stops. The connecting rods 6a, 6b thus form a stabilizing element 6 that maintains the connecting rods 4a, 4b of the bracing element 4 in a substantially aligned position, and therefore stabilizes the leg 2 in the deployed position. The shaft is blocked by the crank 7, which is itself blocked from rotation by its connection to the leg 2 via the connecting rod 8 which is not aligned with the crank 7.

[0034] To raise leg 2 to the retracted position, actuator 5 is powered to rotate the shaft and thus change the relative angular position of connecting rod 6a and crank 7. As illustrated in Figures 2 and 3, this rotation has the initial effect of breaking the alignment of connecting rods 6a, 6b of the stabilizing member 6, and therefore breaking the alignment of connecting rods 4a, 4b of the bracing member 4. Leg 2 is therefore no longer stabilized in the deployed position and can be raised to the retracted position. As actuator 5 continues to be powered, the second connecting rod 6b pulls on connecting rod 4a while connecting rod 8 pushes on leg 2, which has the effect of raising said leg 2 to the retracted position illustrated in [Fig. 1].

[0035] When leg 2 is in the retracted position, the relative angular position of connecting rod 6a and crank 7 is such that crank 7 and connecting rod 8 are in a substantially aligned position, referred to as the second alignment. Similar to the first alignment, the second alignment is a position obtained by moving crank 7 and connecting rod 8 slightly beyond their geometric alignment (which is defined by the perfect alignment of axes X5, X8, and X9 in a (same plane) to bring them onto their respective stops. This alignment locks leg 2 in the retracted position so that this position is stable and does not require the use of a hook box.

[0036] According to the invention, the connecting rods 6a, 6b are held in a substantially aligned position by two locking members 10 which return the connecting rods 6a, 6b to the locked position illustrated in [Fig. 4] and defined by the respective stops of said connecting rods 6a, 6b. The locking members 10 are identical and provide redundancy in case of failure of one of the two locking members 10.

[0037] With reference to Figures 5 and 6, each of the locking members 10 includes a spring for elastically maintaining the connecting rods 6a, 6b in a substantially aligned position. The spring includes an elongated metal blade 11 extending along the connecting rod 4a, substantially along an axis XI1 forming an acute angle with the axes X1-X9. The blade 11 has a generally constant thickness and a variable width, the width extending substantially along the axes XI-X9 and being greater than the thickness. The width of the blade 11 varies generally linearly so as to homogenize the mechanical stresses experienced by the blade 11 when it is subjected to the bending force P described later. The blade 11 thus comprises a first end 11.1 of greater width and a second end 11.2 of lesser width. The first end 11.1 is rigidly fixed (fixed-type connection) to the connecting rod 4a near the articulation axis X2.The second end 11.2 carries a pad 11.3, generally parallelepiped in shape, positioned near the articulation axis X7. The pad 11.3, here made of bronze, extends substantially along the longitudinal axis XI1 of the blade 11 and comprises an upper surface SI1 forming a flat rolling surface.

[0038] The locking member 10 further comprises a rocker 12 mounted to rotate freely about the articulation axis X7 of the bracing member 4. The rocker 12 is substantially L-shaped and comprises a first arm 12.1, one end of which is fitted with a roller 20 bearing permanently against the upper surface SI1 of the pad 11.3, and a second arm 12.2, one end of which bears against a surface S4 of the connecting rod 4a and / or a surface S6 of the connecting rod 6b, depending on the relative angular position of the connecting rod 4a and the connecting rod 6b ([Fig. 1]). It should be noted that the pad 11.3 and the roller 20 have not been shown in Figures 1 to 4 for reasons of clarity.

[0039] With reference to [Fig. 6], the roller 20 comprises a bearing ring 21 inside which a nut 22 is mounted. The ring 21 is in the form of a body of revolution having a cylindrical external surface 21.1 in linear contact with the upper surface SI 1 of the pad 11.3 and arranged to roll freely and without slipping on it, and an internal surface 21.2, spherical, delimiting a housing in which the nut 22 is received. The nut 22 is in the form of a truncated sphere with two axial ends and comprises an external surface 22.1, spherical, complementary to the internal surface 21.2 of the ring 21, and an axial orifice 22.2, cylindrical, through which passes a bolt 30 for fixing the roller 20 to a clevis 12.3 provided at the end of the first arm 12.1 of the rocker 12. The ring 21 is thus free to rotate relative to the nut 22 and forms with said nut 22 a ball joint about a common center to the internal surface 21.2 of the ring 21 and the external surface 22.1 of the nut 22: the roller 20 of the bearing is said to be ball jointed. The ring 21 and the nut 22 are here made of stainless steel (for example 440C, PH 13-8MO, 17-4 PH...), and the roller 20 is self-lubricating.

[0040] The bolt 30 extends along an axis X30 forming a non-zero angle with the axes XI to X9 and comprises a screw 31 having: a first shoulder 31.1, a second shoulder 31.2 and a third shoulder 31.3 arranged between the first shoulder 31.1 and the second shoulder 31.2. The first shoulder 31.1 delimits a first end section 31.4 of the screw 31 extending out of a first cheek 12.4 of the clevis 12.3. The second shoulder 31.2 delimits a second end section 31.5 of the screw 31, opposite the first end section 31.4, the second end section 31.2 extending out of a second cheek 12.5 of the clevis 12.3. The third shoulder 31.3 delimits with the first shoulder 31.2 a first intermediate section 31.6 of the screw 31, the first intermediate section 31.6 being received in a bore of the first cheek 12.4 of the clevis 12.3. The third shoulder 31.3 delimits with the second shoulder 31.2 a second intermediate section 31.7 of the screw 31, the second intermediate section 31.7 receiving the nut 22 of the roller 20 and being received in a bore of the second cheek 12.5 of the clevis 12.3. The roller 20 thus extends between the first cheek 12.4 and the second cheek 12.5 of the clevis 12.3 equipping the end of the first arm 12.1 of the rocker 12. .

[0041] The first end section 31.4 of the screw 31 defines a screw head and includes externally a notch arranged to form, with a relief provided on an external face of the first cheek 12.4 of the clevis 12.3, means of anti-rotation of the screw 31 around its axis X30. The second end section 31.5 of the screw 31 is provided with a thread onto which a nut 32 is screwed. The screw head 31.4 bears directly against the first cheek 12.4, and the nut 32 bears against the second cheek 12.5 via a washer 33. The nut 22 of the roller 20 bears against the second shoulder 31.2 of the screw 31 and against an inner face of the second cheek 12.5 of the clevis 12.3, so that tightening the nut 32 onto the thread of the second end section 31.5 of the screw 31 immobilizes the nut 22 vis-à-vis of the yoke 12.3 and the retention of the roller 20 between the first cheek 12.4 and the second cheek 12.5 of the yoke 12.3. The ring 21 is free to rotate relative to the nut 22.

[0042] The deployment of leg 2 will now be detailed.

[0043] When the lander 1 is between the retracted position illustrated in [Fig.1] (in which the leg 2 describes an extension angle [3 equal to 0°) and the first intermediate position illustrated in [Fig.2] (in which the extension angle [3 of the leg 2 is here substantially equal to 39.5°), the relative angular position of the connecting rod 4a and the connecting rod 6b is such that the roller 20 of the bearing carried by the first arm 12.1 of the rocker 12 is in contact with the pad 11.3 of the blade 11 while the second arm 12.2 of the rocker 12 is only in contact with the surface S4 of the connecting rod 4a, so that the rocker 12 and the connecting rod 4a have a rotational movement together around the axis X7, the blade 11 being slightly flexed and having a minimum deflection F.

[0044] When the lander 1 is in the first intermediate position ([Fig.2]), the relative angular position of the connecting rod 4a and the connecting rod 6b is such that the roller 20 of the bearing carried by the first arm 12.1 of the rocker 12 is in contact with the pad 11.3 of the blade 11 while the second arm 12.2 of the rocker 12 is in contact with both the surface S4 of the connecting rod 4a and the surface S6 of the connecting rod 6b, so that the deflection F of the blade 11 remains unchanged and is always minimal.

[0045] When the lander 1 is between the first intermediate position ([Fig. 2]) and the second intermediate position illustrated in [Fig. 3] (in which the extension angle [3] of the leg 2 is here approximately equal to 98.5°), the relative angular position of the connecting rod 4a and the connecting rod 6b is such that the roller 20 carried by the first arm 12.1 of the rocker 12 is in contact with the pad 11.3 of the blade 11, while the second arm 12.2 of the rocker 12 is only in contact with the surface S6 of the connecting rod 6b, so that the rocker 12 and the connecting rod 6b have a unified rotational movement about the axis X7, the rocker 12 then exerting on the blade 11 a bending force P which tends to increase as the lander 1 approaches the second intermediate position, and therefore to cause an increase in the deflection F of the blade 11. This deformation of the blade 11 causes the roller 20 to roll on the pad 11.3 via a rotation of the ring 21 vis-à-vis the nut 22 along several axes, which makes it possible to limit the friction between the roller 20 and the pad 11.3 and therefore to limit the wear of the first arm 12.1 of the rocker 12 and of the end of the blade 11. .

[0046] When the lander 1 is in the second intermediate position ([Fig.3]), the bending force P exerted by the first arm 12.1 of the rocker 12 on the blade 11 is maximum, so that the deflection F of the blade 11 is maximum.

[0047] When the lander 1 is between the second intermediate position ([Fig. 3]) and the deployed position illustrated in [Fig. 4] (in which the extension angle [3] of the leg 2 is here substantially equal to 103.5°), the relative angular position of the connecting rod 4a and the connecting rod 6b is such that the roller 20 carried by the first arm 12.1 of the rocker 12 is bearing against the pad 11.3 of the blade 11, while the second arm 12.2 of the rocker 12 is still only bearing against the surface S6 of the connecting rod 6b, so that the rocker 12 and the connecting rod 6b continue to have a unified rotational movement about the axis X7, which tends to decrease the bending force P exerted by the first arm 12.1 of the rocker 12 on the blade 11 as Lander 1 moves closer to the deployed position, and therefore causes a decrease in the deflection F of the blade 11 which tends to bring the connecting rods 6a, 6b back towards the locked position.This deformation of the blade 11 causes the roller 20 to roll on the pad 11.3 via a rotation of the ring 21 relative to the nut 22 along several axes, which limits the friction between the roller 20 and the pad 11.3 and therefore limits the wear of the first arm 12.1 of the rocker 12 and the end of the blade 11.

[0048] Thus, the blade 11 works elastically in bending and tends to return to its rest state. To this end, the blade 11 is slightly flexed when the connecting rods 6a, 6b are in a substantially aligned position ([Fig.4]), and takes on a more arched shape when the connecting rod 6b pivots around the axis X7 ([Fig.3]).

[0049] The blade 11 thus forms a leaf spring elastically subjected to a bending force P via the rocker 12 when the connecting rods 6a, 6b leave their substantially aligned position. The arrangement of the rocker 12 makes it possible to temporarily link the bending force P exerted on the blade 11 to the rotation of the connecting rod 6b, and therefore to limit the force required from the actuator 5 during the retraction of the leg 2.

[0050] The actuator 5 is dimensioned to break the alignment of the connecting rods 6a, 6b by counteracting the bending force P exerted by the rocker 12 on the blade 11. The misalignment of the connecting rods 6a, 6b causes the misalignment of the connecting rods 4a, 4b and therefore the pivoting of the leg 2 towards the retracted position.

[0051] It will be noted that, whatever the position of the lander 1, the blade 11 is held by the rocker 12 in a state of at least minimal deformation so as to ensure a permanent linear contact between the pad 11.3 of the blade 11 and the roller 20 equipping said rocker 12 and thus avoid any separation due to vibrations during flight.

[0052] It should also be noted that the volume occupied by the blade 11 and the rocker 12 when the lander 1 is in the deployed position is contained within the volume swept by the connecting rod 4a when the lander 1 moves from the retracted position to the deployed position. Such a locking member 10 therefore does not impact, unlike springs helical, the integration of other equipment and proves to be generally protected from external aggressions, the blade 11 and the rocker 12 being arranged in the storage compartment of the lander 1 and the connecting rod 4a acting as a shield against bird trajectories and projections of tire debris ([Fig.5]).

[0053] Of course, the invention is not limited to the embodiment described but encompasses any variant falling within the scope of the invention as defined by the claims.

[0054] The pad 11.3 can be removably fixed on the second end 11.2 of the blade 11 in order to facilitate its replacement, in particular in the event of wear of said pad 11.3.

[0055] Although the pad 11.3 and the ring 21 of the roller 20 are here respectively made of bronze and stainless steel, they can be made of any material (metal, composite...) suitable for the contact pressure (linear contact, Hertz pressure...) and the friction conditions.

[0056] In the case where the axis XI1 of the blade 11 is orthogonal to the axes XI to X9, the roller 20 may not be ball-jointed but only pivoting, which may allow the shape of the rocker 12 to be simplified and the mass of said rocker 12 to be reduced.

[0057] The roller 20 can be provided at the end of the blade 11 instead of that of the rocker 12, the pad 11.3 then being fixed at the end of the first arm 12.1 of the rocker 12.

[0058] Although the external surface 21.1 of the ring 21 of the roller 20 is here cylindrical in shape, it may be concave or convex in shape to cooperate respectively with a convex or concave shape of the pad 11.3 so as to form a groove allowing to ensure guidance and orientation of the ring 21 of the roller 20 vis-à-vis said pad 11.3 ([Fig.7A]).

[0059] Although here the roller 20 is ball-jointed, it can also simply pivot, the upper surface SI 1 of the pad 11.3 then having an evolving inclination to ensure a substantially constant linear contact between the ring 21 of the roller 20 and the pad 11.3 during the rolling of said roller 20 on said pad 11.3 ([Fig.7B]).

[0060] The shape and dimensions of the blades 11 may differ from those illustrated. For example, the blade 11 may have a constant width and / or a varying thickness, presenting, for example, a parabolic profile.

[0061] Although here the blade 11 extends along the connecting rod 4a, it can also extend along the connecting rod 6b.

[0062] The blades 11 can be made of any suitable material (metal, composite...).

[0063] The blades 11 can be fixed to the connecting rod 4a by any suitable means.

[0064] Although the lander 1 here includes two locking members 10, it may include only one or at least three.

[0065] Although the leg 2 is here held in the deployed position by a single bracing member 4, the invention can also be applied to landers comprising a leg held in the deployed position by several bracing members. At least one of the bracing members is then equipped with at least one locking member 10 comprising at least one leaf spring.

[0066] Although the lander 1 here is that of an aircraft, it can also be that of any other vehicle equipped with at least one lander (hyperloop train...).

Claims

Demands

1. Landing (1) comprising: - a leg (2) arranged to be movably mounted on a structure (3) between a deployed position and a retracted position; - at least one bracing member (4) for maintaining the leg in the deployed position, comprising a first connecting rod (4a) articulated on the structure and a second connecting rod (4b) articulated on the first connecting rod and on the leg; - a stabilizing member (6) for maintaining the first and second connecting rods (4a, 4b) in an aligned position, comprising a first connecting rod (6a) and a second connecting rod (6b) articulated with each other, and whose second connecting rod is articulated on the first connecting rod; and - at least one leaf spring (11) and a rocker (12) for elastically returning the articulations of the first connecting rod and the second connecting rod to a substantially aligned position; characterized in that the leaf spring has an end (11.1) rigidly fixed to the first connecting rod (4a) or the second connecting rod (6b), and an opposite end (11.2) permanently supported on a first arm (12.1) of the rocker (12) via a roller (20), the rocker being mounted to rotate freely around the articulation axis (X7) of the first connecting rod (4a) and the second connecting rod (6b), and the roller being arranged to roll on the leaf spring or the arm of the rocker during a pivoting of said rocker around the articulation axis (X7).

2. Lander (1) according to claim 1, wherein the rolling roller (20) is spherical.

3. Lander (1) according to any one of the preceding claims, wherein the roller (20) comprises a cylindrical external surface (21.1).

4. Lander (1) according to any one of the preceding claims, wherein the roller (20) is carried by the first arm (12.1) of the rocker (12).

5. Land (1) according to claim 4, wherein the leaf spring (11) comprises a pad (11.3) on which the roller (20) is in permanent bearing.

6. Land (1) according to any one of the preceding claims, wherein the leaf spring (11) is arranged to be brought to an elastically deformed state under a bending force (P) exerted by the roller (20) when the joints of the first and second connecting rods (6a, 6b) leave their substantially aligned position, and to escape the bending force and be in a state of least deformation when the leg (2) is between the retracted position and an intermediate position between the retracted and deployed positions.

7. Lander (1) according to claim 6, wherein the rocker (12) is rotationally linked to the first connecting rod (4a) when the leg (2) is between the retracted position and the intermediate position, and rotationally linked to the second connecting rod (6b) when the leg (2) is between the intermediate position and the deployed position.

8. Lander (1) according to claim 7, wherein the rocker (12) has a second arm (12.2) bearing against a surface (S4) of the first connecting rod when the leg (2) is between the retracted position and the intermediate position, and bearing against a surface (S6) of the second connecting rod when the leg (2) is between the intermediate position and the deployed position.

9. Lander (1) according to any one of the preceding claims, wherein the volume occupied by the leaf spring (11) and the rocker (12) when the leg (2) is in the deployed position is contained within the volume swept by the first connecting rod (4a) when the leg (2) moves from the retracted position to the deployed position.

10. Aircraft comprising at least one landing gear (1) according to any one of the preceding claims.

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