Landing gear locking device

Abstract

A locking device comprising a hydraulic actuator (21) connected to a rotary distributor (30), the rotary distributor (20) comprising: - means for operatively connecting the rotary distributor (30) to a landing gear; - a first supply port (35) fluidically connected to a first hydraulic supply (A1); - a second supply port (36) fluidically connected to a second hydraulic supply (A2); - a first outlet port (37) fluidically connected to the hydraulic actuator (21). A landing gear provided with such a device. An aircraft comprising such a landing gear.

Description

Technical Field

[0001] The present invention relates to the field of deployable aircraft landing gear and, more particularly, to an apparatus for locking the landing gear in position. Background Art

[0002] Conventionally, an aircraft landing gear comprises a landing gear strut, a first end of which is hinged to the aircraft and a second end of which carries a wheel set. A deployment jack extends between the structure of the aircraft and the landing gear strut and makes it possible to selectively move the landing gear between a deployed position and a retracted position. Typically, such a landing gear comprises a device for locking the strut in its deployed and / or retracted position. The locking device comprises a stabilizing member which maintains the locking device in its state before the deployment jack is controlled.

[0003] Such a device does not make it possible to act on the locking device and ensure its state. For a solid landing gear, the stabilizing member is dimensioned to deliver sufficient force, which is bulky and heavy. Summary of the invention

[0004] The object of the present invention is to improve the compactness and reliability of a landing gear locking device.

[0005] To this end, a locking device is provided, which is intended to lock a landing gear rotatably mounted on an aircraft, the landing gear being equipped with a hydraulic deployment jack, the hydraulic deployment jack comprising a first chamber connected to a first hydraulic supply and a second chamber connected to a second hydraulic supply. The locking device comprises a hydraulic actuator connected to a rotary distributor. The rotary distributor comprises means for operatively connecting the rotary distributor to the landing gear, a first supply port fluidly connected to the first hydraulic supply, and a first outlet port fluidly connected to the hydraulic actuator.

[0006] The state of the dispenser supplying the locking device is thus mechanically indexed as a function of the position of the undercarriage and does not require a separate control or a dedicated controlled fluid connection. The reliability of such a simplified locking device is increased.

[0007] Advantageously, the actuator is a jack comprising a third chamber connected to the first outlet port. Furthermore, the actuator may comprise a fourth chamber, the rotary distributor comprising a second supply port fluidly connected to the second hydraulic supply, and a second outlet port fluidly connected to the fourth chamber.

[0008] According to a preferred embodiment, the rotary distributor is arranged such that:

[0009] - In the first state, the first supply port is connected to the second outlet port, and the second supply port

[0010] The response port is connected to the first outlet port;

[0011] In the second state, the first supply port is connected to the first outlet port and the second outlet port via the first throttle, and the second supply port is connected to the first outlet port via the second throttle.

[0012] an inlet port and a second outlet port;

[0013] - In a third state, the first supply port is connected to the first outlet port and the second supply port is connected to the second outlet port.

[0014] Preferably, the means for operatively connecting the rotary distributor to the landing gear comprises a coupling to the landing gear strut.

[0015] Likewise advantageously, the distributor comprises a third outlet port which is in constant fluid connection with the first supply port and / or a fourth outlet port which is in constant fluid connection with the second supply port.

[0016] When the first connecting pipe between the third port and the hydraulic actuator and the second connecting pipe between the fourth port and the hydraulic actuator are rigid, the reliability of the device is further improved.

[0017] The invention also relates to a landing gear intended to be rotatably mounted on an aircraft and equipped with a hydraulic deployment jack comprising a first chamber connected to a first hydraulic supply and a second chamber connected to a second hydraulic supply, the landing gear comprising a locking device of the above-mentioned type.

[0018] Preferably, the frame of the actuator is fixed to a strut of the landing gear carrying the wheels.

[0019] Advantageously, the locking device comprises a first locking link hinged on a second locking link, the actuator being connected to the first link or to the second link.

[0020] The invention also relates to an aircraft comprising such an undercarriage.

[0021] Other characteristics and advantages of the invention will emerge on reading the following description of a specific non-limiting embodiment of the invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] - Figure 1 is a schematic diagram of a landing gear according to the present invention in a deployed position;

[0023] - Figure 2 yes Figure 1 Detailed view of the deployment jack of the actuator;

[0024] - Figure 3 yes Figure 1 Schematic detail view of the landing gear locking device;

[0025] - Figure 4 yes Figure 1 Schematic diagram of the landing gear;

[0026] - Figure 5 is a schematic detail view of a dispenser according to a first embodiment of the present invention in a first state along a first cutting plane;

[0027] - Figure 6 is established along the second cutting plane Figure 5 Same view;

[0028] - Figure 7 It is in the second state Figure 5 A schematic detail view of a dispenser along a first cutting plane;

[0029] - Figure 8 is established along the second cutting plane Figure 7 Same view;

[0030] - Fig. 9 It is in the third state Figure 5 A schematic detail view of a distributor of;

[0031] - Fig.10 It is in the third state Figure 5 A schematic detail view of a dispenser along a first cutting plane;

[0032] - Fig.11 is established along the second cutting plane Fig.10 Same view;

[0033] - Fig.12 is in the first position Figure 1 Schematic diagram of the landing gear;

[0034] - Fig.13 is in the second position Figure 1 Schematic diagram of the landing gear;

[0035] - Fig.14 is in the third position Figure 1 Schematic diagram of the landing gear;

[0036] - Fig.15 It is in the fourth position Figure 1 Schematic diagram of the landing gear;

[0037] - Fig.16 It is in the fifth position Figure 1 Schematic diagram of the landing gear;

[0038] - Fig.17 is a schematic detail view of a dispenser according to a second embodiment of the invention. DETAILED DESCRIPTION

[0039] refer to Figures 1 to 16 , the landing gear (generally referenced 100) comprises, in a manner known per se, a strut 1, articulated to the structure of the aircraft 1000 (indicated in dashed lines) about an articulation axis X1 (in this case visible at the end), the distal end of which carries a wheel 90. The strut 1 is movable between a deployed position and a retracted position, as shown in FIG. Figure 8 As shown, in the deployed position, the landing gear 100 is pre-brought to the landing position, Fig.12 The retracted position can be seen in , which is the landing gear in flight. The frangible strut 2 is hinged on the one hand to the strut 1 and on the other hand to the structure of the aircraft 1000. The frangible strut 2 comprises two links 2a, 2b hinged to each other at a knee 3. Furthermore, the link 2a is hinged to the aircraft 1000 at a first point 1001 about an articulation axis X2, while the link 2b is hinged to the strut 1. The frangible strut 2 is brought into a substantially aligned position with the aid of a stabilizing member 4, which comprises a first link 4a and a second link 4b, which are also hinged to each other. The first link 4a is hinged to the strut 1 about the axis X3, while the second link 4b is hinged to the frangible strut 2, in this case at the knee 3. The first link 4a and the second link 4b are kept in a substantially aligned position by a spring 5, which returns the first link 4a, the second link 4b to the position in which they are aligned. Figure 1 The locking position shown, in which the first link 4a is aligned with the second link 4b. The alignment of the first link 4a and the second link 4b is defined by the contact of the first abutment 6a and the second abutment 6b mounted respectively on the first link 4a and the second link 4b.

[0040] The thus stable frangible strut 2 prevents any rotation of the strut 1 about its articulation axis X1, so that the deployed position ( Figure 1 ) is a stable position. As is well known, the connecting rods 2a, 2b and the connecting members 4a, 4b are designed so that in order to reach Figure 1 In the locking position shown, the knees for articulating the connecting rods 2a, 2b and for articulating the first and second links 4a, 4b slightly exceed the geometric alignment of the connecting rods 2a, 2a and the geometric alignment of the links 4a, 4b.

[0041] The control actuator, in this case a first hydraulic deployment jack 10, is articulated on the aircraft 1000 about an articulation axis X4 on the one hand and on the landing gear strut 1 about an articulation axis X5 on the other hand. The first jack 10 comprises a first chamber 11 provided with a deployment supply port 12, and a second chamber 13 provided with a retraction supply port 14. The deployment supply port 12 is connected by a first tap at a first hydraulic supply line A1, while the retraction supply port 14 is connected by a second tap at a second hydraulic supply line A2.

[0042] The landing gear 100 also comprises a locking device 20 comprising a second jack 21 connected to the rotary distributor 30. The second jack 21 is articulated on the one hand to the strut 1 and on the other hand to a handle 22 fixed to the first link 4a. The second jack 21 comprises a third chamber 23 provided with a deployment supply port 24, and a fourth chamber 25 provided with a retraction supply port 26.

[0043] The rotary distributor 30 comprises a cylindrical plug 31.1 fixed and attached to the base 31 and rotatably received about the axis of rotation X6 in a tubular sleeve 32. The sleeve 32 is rigidly connected to the strut 1 by means of a crank 33. The base 31 is connected to the structure of the aircraft 1000 by means of fixing lugs 34.

[0044] The base 31 comprises a first supply port 35 and a second supply port 36. The sleeve 32 comprises a first outlet port 37 and a second outlet port 38. Thus, the position of the plug 31.1 in the sleeve 32 is itself indexed according to the position of the strut 1 of the landing gear 100 relative to the structure of the aircraft 1000.

[0045] like Figure 5 and Figure 6 As shown, the first hydraulic supply line A1 is fluidly connected to the deployment supply port 12 and the first supply port 35. The second hydraulic supply line A2 is fluidly connected to the retraction supply port 14 and the second supply port 36. The first outlet port 37 is fluidly connected to the port 24 of the second jack 21 through a first rigid hydraulic connection tube 80 (in this example, made of stainless steel), and the second outlet port 38 is fluidly connected to the port 26 of the second jack 21 through a second rigid hydraulic connection tube 81 (in this example, made of stainless steel).

[0046] The plug 31.1 comprises a first supply conduit 40 connected to a first supply port 35, which supplies a first chamber 41 and a second chamber 42. The plug 31.1 also comprises a second supply conduit 43 connected to a second supply port 36, which supplies a third chamber 44 and a fourth chamber 45. The first chamber 41, the second chamber 42, the third chamber 44 and the fourth chamber 45 are implemented in the form of grooves, extending parallel to the axis of rotation of the plug 31.1 at the periphery of the plug 31.1. The first chamber 41, the second chamber 42, the third chamber 44 and the fourth chamber 45 are 90 degrees to each other about the axis of rotation X6 of the plug 31.1. The second chamber 42 is separated from the third chamber 44 by a first cylindrical portion 46. The second chamber 42 is separated from the fourth chamber 45 by a second cylindrical portion 47.

[0047] The third outlet duct 37 . 1 is connected to the first outlet port 37 and opens into the sleeve 32 along a first section 37 . 2 .

[0048] The fourth outlet duct 38 . 1 is connected to the second outlet port 38 and opens into the sleeve 32 along a second section 38 . 2 .

[0049] The first, second, third and fourth chambers 41 , 42 , 44 and 45 fluidly connect the first, second and third supply ports 35 , 36 , 37 and 38 according to several configurations depending on the relative angular positions of the plug 31 . 1 and the sleeve 32 .

[0050] Thus, in the first state, which corresponds to the retention of the sleeve 32 and the plug 31.1 in a first relative angular position with a deviation between zero and eighty-nine degrees (in the direction of rotation of the strut 1 corresponding to the landing gear from its retracted position to its deployed position), the first supply port 35 supplies the second outlet port 38 ( Figure 6 ). Equivalently, the second supply port 36 supplies the first outlet port 37 via the fourth chamber 45 ( Figure 5 ).

[0051] exist Figures 7 to 9 In the second state shown, which corresponds to a second relative angular position of the sleeve 32 and the plug 31.1 with a deviation substantially equal to 90 degrees, the first cylindrical portion 46 faces the third outlet duct 37.1 and the second cylindrical portion 47 faces the fourth outlet duct 38.1. Fig. 9As can be seen more specifically in FIG. 4 , the area of ​​the outer surface of the first cylindrical portion 46 facing the third duct 37.1 is smaller than the area of ​​the first section 37.2. This area difference creates a calibrated first leak 48.1 between the second chamber 42 and the first outlet port 37. This area difference also creates a calibrated second leak 48.2 between the third chamber 44 and the first outlet port 37. Similarly, a third calibrated leak 49.1 is established between the fourth outlet duct 38.1 and the second chamber 42. A fourth calibrated leak 49.2 is established between the fourth outlet duct 38.1 and the fourth chamber 45.

[0052] The first leakage 48 . 1 and the third leakage 49 . 1 act as two first flow restrictors, which connect the first supply port 35 to the first outlet port 37 and the second outlet port 38 .

[0053] The second leakage 48 . 2 and the fourth leakage 49 . 2 serve as two second flow restrictors, which connect the second supply port 36 to the first outlet port 37 and the second outlet port 38 .

[0054] exist Fig.10 and Fig.11 In the third state shown, which corresponds to a third relative angular position of the plug 31.1 in the sleeve 32 with a deviation between 90 and 180 degrees, the first supply port 35 supplies the first outlet port 37 ( Fig.10 ). Equivalently, the second supply port 36 supplies the second outlet port 38 via the fourth chamber 45 ( Fig.11 ).

[0055] In operation, from Fig.12 Starting from the retracted position of the landing gear 100 shown in FIG, the deployment of the first jack 10 is caused by controlling the application of supply pressure in the first supply line A1 and the connection of the line A2 with the fluid reservoir. The distributor 30 is in Figure 5 and Figure 6 2, and the pressurization of the supply line A1 causes the rod of the second jack 21 to retract. This exerts a force on the link 4a, which acts to pivot the link 4a about its axis of rotation X3, thereby overcoming the action of the spring 5 and destroying the alignment of the links 4a, 4b ( Fig.13 The locking device is thus in the unlocked position and the landing gear 100 begins its deployment under the action of the first jack 10. The rotation of the strut 1 about the axis X1 causes the plug 31.1 and the sleeve 32 to rotate relative to each other, thereby bringing the dispenser 30 into its second state ( Figures 7 to 9 and Fig.14 In this second state, the second jack 21 does not offer resistance to the movement of the strut 1. During the deployment movement of the landing gear 100, the retraction of the rod of the second jack 21 can be observed ( Fig.14 ), which is not hindered by the fluid connection of the second state of the distributor 30.

[0056] Once the landing gear 100 approaches its fully extended position ( Fig.15 ), the dispenser 30 moves into its third state ( Fig.10 , Fig.11 and Fig.16 ). The fluid connection thus established makes it possible to keep the locking device 20 in the locked position.

[0057] During the retraction movement of the landing gear 100 , the relative movement of the plug 31 . 1 in the sleeve 32 takes place in the opposite direction and the sequence “retraction of the second jack 21 / second free-movement jack 21 ” is indexed according to the movement of the landing gear 10 .

[0058] according to Fig.17 In the second embodiment shown, the distributor 30 includes a third outlet port 60 and a fourth outlet port 61. The third port 60 is in fluid connection contact with the first supply port 35, while the fourth outlet port 61 is in constant fluid connection with the second supply port 36. In this embodiment, the third port 60 is connected to the deployment supply port 12 of the first jack 10, while the fourth port 61 is connected to the retraction supply port 14 of the first jack 10.

[0059] The invention is not limited to what has just been described, but on the contrary comprises any variant coming within the ambit defined by the claims.

[0060] Specifically,

[0061] - although in this example the locking device comprises a hydraulic jack, the invention is also applicable to other types of hydraulic actuators, such as rotary actuators;

[0062] - Although in the present case the distributor comprises a sleeve rigidly connected to a strut of the landing gear and a plug fixed to the axis of rotation of the strut on the aircraft, the invention is also applicable to other types of operative connection of the distributor to the landing gear, for example a reducer, a connecting rod / crank system, a toothed belt and toothed wheel connection or any other device making it possible to index the movement of the distributor according to the movement of the landing gear during its deployment and during its retraction. The distributor can also be connected to another axis of the landing gear, for example the axis connecting the first deployment jack to the strut, the axis connecting the frangible strut to the strut, the axis connecting one of the links to the strut, the axis connecting the first deployment jack to the aircraft;

[0063] - Although in this example the plug comprises a groove and a drilled channel, the invention is also applicable to other means of selectively connecting the inlet and outlet ports in a rotary distributor, such as a central supply channel and a peripheral channel;

[0064] - although in this example the rotary distributor comprises a third outlet port and a fourth outlet port which are respectively in constant fluid connection with the first supply port and the second supply port, the invention is also applicable to distributors provided with a single outlet port which is in constant fluid connection with the inlet port;

[0065] - although in this case the dispenser comprises a fixed chamber in front of which the outlet port moves, the invention is also applicable to a fixed port in front of which movable chambers connected to one another move, these chambers being embodied, for example, in the form of peripheral grooves in the movable plug;

[0066] - although in this example the distributor is connected on the one hand to the structure of the aircraft and on the other hand to the strut of the landing gear, the invention is also applicable to a distributor not connected to the aircraft, for example to a strut on the one hand and to its axis of rotation on the other hand, or to any other pair of elements having a relative movement indexable according to the movement of the landing gear;

[0067] - although in the present example the passage between the first state and the second state is carried out for a relative angular position of the sleeve and the plug equal to 90 degrees, the invention is also applicable to other values ​​of relative angular position of the sleeve and the plug for passage from the first state to the second state. Preferably, the relative angular position of the sleeve and the plug for passage between the first state and the second state corresponds to the relative angular position of the sleeve and the plug when the landing gear is halfway through its extension / retraction stroke, preferably within a range of about 10% of this value;

[0068] -Although in this example, the present invention has been described in conjunction with a double-effect unlocking actuator controlled by a rotary distributor, which includes a first supply port fluidly connected to a first hydraulic supply part, a second supply port fluidly connected to a second hydraulic supply part, and a first outlet port and a second outlet port fluidly connected to the hydraulic actuator, the present invention is also applicable to a single-effect unlocking actuator coupled to a rotary distributor, which includes a single first supply port fluidly connected to the first hydraulic supply part, and a single first outlet port fluidly connected to the hydraulic actuator.

Claims

1. A landing gear (100) intended to be rotatably mounted on an aircraft (1000) and equipped with a deployment hydraulic jack (10), the deployment hydraulic jack comprising a first chamber (11) connected to a first hydraulic supply (A1), and a second chamber (13) connected to a second hydraulic supply (A2), the landing gear (100) comprising a locking device (20), the locking device (20) comprising a hydraulic actuator (21) connected to a rotary distributor (30), the rotary distributor (30) comprising: - means for operatively connecting the rotary distributor (30) to the landing gear (100) so as to index the movement of the rotary distributor according to the movement of the landing gear during its deployment and its retraction; - a first supply port (35) fluidly connected to the first hydraulic supply (A1); - a first outlet port (37) fluidly connected to the hydraulic actuator (21).

2. The landing gear (100) according to claim 1, characterized in that: The actuator (21) is a jack comprising a third chamber (23) connected to the first outlet port (37).

3. The landing gear (100) according to claim 2, characterized in that: The actuator (21) includes a fourth chamber (25), and the rotary distributor (30) includes a second supply port (36) fluidly connected to the second hydraulic supply (A2), and a second outlet port (38) fluidly connected to the fourth chamber (25).

4. The landing gear (100) according to claim 3, characterized in that: The rotary distributor (30) is arranged such that: - in a first state, the first supply port (35) is connected to the second outlet port (38) and the second supply port (36) is connected to the first outlet port (37); - in a second state, the first supply port (35) is connected to the first outlet port (37) and the second outlet port (38) via a first throttle (48.1, 49.1), and the second supply port (36) is connected to the first outlet port (37) and the second outlet port (38) via a second throttle (48.2, 49.2); - In a third state, the first supply port (35) is connected to the first outlet port (37) and the second supply port (36) is connected to the second outlet port (38).

5. The landing gear (100) according to claim 3, characterized in that: The means for operatively connecting the rotary distributor (30) to the landing gear comprise a coupling (33) to a strut of the landing gear (100).

6. The landing gear (100) according to claim 3, characterized in that: A first connection tube (80) between the first outlet port and the hydraulic actuator and a second connection tube (81) between the second outlet port (38) and the hydraulic actuator (21) are rigid.

7. The landing gear (100) according to any one of claims 1 to 6, characterized in that: The frame (32) of the hydraulic actuator (21) is fixed to a strut (1) of the landing gear (100), said strut carrying a wheel (90).

8. The landing gear (100) according to any one of claims 1 to 6, characterized in that: The locking device (20) comprises a first link (4a) hinged on a second link (4b), and the actuator (21) is connected to the first link (4a) or the second link (4b).

9. An aircraft (1000) comprising a landing gear (100) according to any one of claims 1 to 8.

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