CN114314424A - Jacking device for nose landing gear of airplane - Google Patents

Abstract

The invention provides a jacking device for a nose landing gear of an airplane, which relates to the technical field of maintenance of air transportation tools and comprises a landing gear supporting beam, a first lifting mechanism and a second lifting mechanism; a bearing groove which is sunken downwards is arranged in the middle of the landing gear support beam, one end of the landing gear support beam is connected to the first lifting mechanism, and the other end of the landing gear support beam is connected to the second lifting mechanism; the first lifting mechanism and the second lifting mechanism are configured to control the synchronous lifting of the two ends of the landing gear support beam. The invention solves the technical problems that in the prior art, when two front wheels of an aircraft undercarriage are steered or other aircraft wheel performance tests are carried out, a jack supports the undercarriage to occupy the bottom space of the two front wheels, so that the performance test of the front wheels cannot be carried out by using the device for detecting the aircraft wheel performance, and the test efficiency and the accuracy of test results are influenced.

Description

Aircraft nose landing gear jacking device

technical field

The invention relates to the technical field of overhaul of air transport vehicles, in particular to a jacking device for the front landing gear of an aircraft.

Background technique

The nose landing gear of an aircraft is an accessory device used by the lower part of the aircraft to support the aircraft and move on the ground (or water) during take-off and landing or taxiing on the ground (or water). The nose landing gear is the only part that supports the entire aircraft, so it is an integral part of the aircraft; without it, the aircraft cannot move on the ground. When the aircraft takes off, the nose landing gear can be retracted depending on the performance of the aircraft.

The two front wheels of the nose landing gear of the aircraft are connected by a beam. At present, the nose landing gear is mainly supported by using a jack to support the beam part of the nose landing gear of the aircraft, so as to lift the two front wheels of the nose landing gear of the aircraft, and then the front wheel Perform performance tests such as repairs or steering. However, since the jack supports the beam part of the nose landing gear of the aircraft, the jack chassis or other parts occupy the space at the bottom of the two wheels of the landing gear, so it is impossible to insert the wheel performance testing device into the bottom of the two wheels of the landing gear. The steering wheel is used for steering or other wheel performance tests, but the steering status of the front wheel can only be checked by manually turning the wheel, including whether the steering is flexible and whether the wheel shakes during the steering process, which greatly reduces the impact on the front wheel of the aircraft landing gear. The efficiency of performing steering or other performance tests can seriously affect the accuracy of the test results.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a device for jacking up the nose landing gear of an aircraft, so as to solve the problem that in the prior art, when performing steering or other wheel performance tests on the two front wheels of the aircraft landing gear, the jack supports the landing gear and occupies the bottom of the two front wheels. Space, resulting in the inability to use the wheel performance testing device for the performance test of the front wheel, which affects the technical problem of the test efficiency and the accuracy of the test results.

To achieve the above purpose, the embodiment of the present invention adopts the following technical solutions:

An embodiment of the present invention provides an aircraft nose landing gear jacking device, comprising a landing gear support beam, a first lift mechanism, and a second lift mechanism; a bearing groove recessed downward is provided in the middle of the undercarriage support beam , one end of the landing gear support beam is connected to the first lifting mechanism, and the other end of the landing gear support beam is connected to the second lifting mechanism; the first lifting mechanism and the second lifting mechanism The lift mechanism is configured to be able to control the simultaneous lifting and lowering of both ends of the landing gear support beam.

When in use, use two of the above-mentioned aircraft nose landing gear jacking devices to lift the aircraft nose landing gear, so that the two wheels respectively fall inside the bearing grooves of the landing gear support beams in the aircraft nose landing gear jacking device. , start the first lifting mechanism and the second lifting mechanism to slowly lift the support beam of the landing gear, thereby slowly lifting the wheel, and then supporting the front landing gear of the aircraft, and further, repairing the front landing gear of the aircraft, the embodiment of the present invention Compared with manually using a jack to lift and support the nose landing gear of the aircraft, the process of jacking up and supporting the nose landing gear of the aircraft is more efficient, which is conducive to the rapid maintenance of the nose landing gear of the aircraft.

In addition, in particular, for the connection between the two front wheels of the aircraft landing gear through the beam, the jack supports the beam part of the nose landing gear of the aircraft, and the jack chassis or other parts occupy the space at the bottom of the two wheels of the landing gear, so that it is impossible to pass the two wheels of the landing gear. The wheel performance testing device is inserted into the bottom to test the steering or other wheel performance of the two front wheels of the aircraft landing gear, and the steering status of the front wheels can only be checked by manually rotating the control handwheel, including whether the steering is flexible, and during the steering process. Whether there is jitter in the wheel, etc., which greatly reduces the efficiency of steering or other performance tests on the nose wheel of the aircraft landing gear and seriously affects the accuracy of the test results. The aircraft nose landing gear jacking device provided in this embodiment is used After the first lift mechanism, the second lift mechanism and the landing gear support beam support the two front wheels of the nose landing gear of the aircraft, the space at the bottom of the two front wheels is not occupied, so that the bottom of the two front wheels can be stuffed into the aircraft. Then slowly drop the nose wheel of the aircraft onto the device for wheel performance testing, remove the nose landing gear jacking device, and then perform the corresponding performance test on the nose wheel of the landing gear. After the test is completed, put the The aircraft nose landing gear jacking device provided in the embodiment is moved back to support the two front wheels again.

The device for jacking up the nose landing gear provided by this embodiment has a simple structure, and does not occupy the bottom space of the two front wheels after supporting the two front wheels of the aircraft nose landing gear during use, thereby overcoming the need for the jack supporting the landing gear to occupy the bottom space of the two front wheels The technical obstacle that makes it impossible to use the wheel performance testing device for the performance test of the front wheel makes it possible to use the wheel performance testing device to replace the pure manual runner for the performance test of the front wheel, thereby improving the test efficiency and the accuracy of the test results. application prospects.

In an optional implementation manner of the embodiment of the present invention, the first lifting mechanism and the second lifting mechanism include respective hydraulic cylinder assemblies, servo valves, and servo valve lifting drive assemblies;

The hydraulic cylinder assembly includes a hydraulic cylinder and a piston rod, the hydraulic cylinder is arranged vertically, the lower end of the piston rod is telescopically connected to the interior of the hydraulic cylinder, and the upper end of the piston rod is fixed to the landing gear support beam end of ;

The servo valve includes a valve seat and a valve core mounted on the valve seat; the valve seat is fixedly connected to the hydraulic cylinder through a valve seat connecting plate, and the valve seat is connected to the hydraulic cylinder through an oil pipe; The upper end of the valve core is fixedly connected to the upper end of the piston rod through a valve core connecting plate; the valve seat and the valve core are both connected to the servo valve lift drive assembly, and the servo valve lift drive assembly is configured to be able to The valve core is driven to rise and fall, so as to drive the piston rod to rise and fall, thereby driving the end of the support beam of the landing gear to rise and fall.

Further optionally, the servo valve lift drive assembly includes a ball screw, a screw nut and a rotary drive combined structure;

The ball screw is arranged in the vertical direction and passes through the valve seat, the screw nut is threadedly sleeved on the outside of the ball screw, and the valve core is fixed on the screw nut; the rotation driving combination The structure is connected to one end of the ball screw, and the rotary drive combination structure is configured to drive the ball screw to rotate, so as to drive the screw nut to rise and fall, and then drive the valve core to rise and fall relative to the valve seat.

Further optionally, the rotary drive combination structure includes a drive assembly support frame, a rotary drive part, a first transmission belt, a second transmission belt, a first transmission wheel, a second transmission wheel, a third transmission wheel, a fourth transmission wheel, a a bevel gear and a second bevel gear;

The side facing each other of the drive assembly support frame in the first lifting mechanism and the drive assembly support frame in the second lift mechanism is the inner side of the drive assembly support frame, and the drive assembly supports One of the inner and outer sides of the frame is the first side of the drive assembly support frame, and the other side is the second side of the drive assembly support frame:

The first transmission wheel is rotatably mounted on the top first side of the drive assembly support frame through the first axle; the second transmission wheel is rotatably installed on the bottom first side of the drive assembly support frame through the second axle, and the second axle passes through the drive assembly support frame, the third transmission wheel is mounted on one end of the second axle at the second side of the drive assembly support frame; the fourth transmission wheel passes through the third transmission wheel The axle is rotatably mounted on the second side of the bottom of the drive assembly support frame, and the fourth transmission wheel and the third transmission wheel are spaced apart from each other; the third axle passes through the drive assembly support frame, and the first A bevel gear is mounted on one end of the third axle on the first side of the drive assembly support frame, the second bevel gear is mounted on the lower end of the ball screw, and the second bevel gear is connected to the first bevel gear. A bevel gear is perpendicular to each other and meshes with each other; the first transmission belt is sleeved and abutted on the outside of the first transmission wheel and the second transmission wheel, and the second transmission belt is sleeved and abutted against the third transmission the outer part of the wheel and said fourth transmission wheel;

The rotation driving part is connected to the first axle, and the rotation driving part is configured to be able to drive the first transmission wheel to rotate, so as to drive the second transmission wheel, the third transmission wheel, the first transmission wheel in sequence. The four transmission wheels, the first bevel gear and the second bevel gear rotate, thereby driving the ball screw to rotate.

Further optionally, the first axle connected to the support frame of the drive assembly in the first lifting mechanism is connected to the first axle connected to the support frame of the drive assembly in the second lift mechanism through a connecting rod.

Optionally, the rotation driving part adopts a hand wheel.

In an optional implementation manner of the embodiment of the present invention, an anti-rotation structure is provided between the valve core and the valve core connecting plate.

Further optionally, the anti-rotation structure includes an anti-rotation plate and an anti-rotation sliding sleeve;

The upper plate surface of the valve core connecting plate is fixed or integrally connected with a vertical guide column, one end of the anti-rotation plate is mounted on the valve core, and the bottom of the anti-rotation sliding sleeve is fixed on the anti-rotation plate, And the central axis of the anti-rotation sliding sleeve extends along the vertical direction, and the vertical guide column passes through the anti-rotation sliding sleeve.

In an optional implementation manner of the embodiment of the present invention, the first lifting mechanism and the second lifting mechanism further include respective hydraulic cylinder support frames, and the hydraulic cylinders are fixed to the hydraulic cylinder support frames.

Further optionally, a sleeve-type structure with an open top is provided on the hydraulic cylinder support frame, and the hydraulic cylinder extends into and is fixed inside the sleeve-type structure.

Description of drawings

In order to illustrate the specific embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the specific embodiments or the prior art. Obviously, the accompanying drawings in the following description The drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings without creative efforts.

1 is a front view of the overall structure of an aircraft nose landing gear jacking device provided in an embodiment of the present invention;

2 is an axonometric view of the overall structure of an aircraft nose landing gear jacking device provided in an embodiment of the present invention;

Fig. 3 is the partial structure enlarged view of A part among Fig. 2;

Fig. 4 is the partial structure enlarged view of B part in Fig. 2;

5 is a C-C sectional view of the aircraft nose landing gear jacking device shown in FIG. 1;

Fig. 6 is the partial structure enlarged view of D part in Fig. 5;

FIG. 7 is an enlarged view of a part of the structure of part E in FIG. 5 .

Icons: 1-landing gear support beam; 11-bearing groove; 2-first lifting mechanism; 3-second lifting mechanism; 41-hydraulic cylinder; 42-piston rod; 43-servo valve; 431-valve seat ;432- valve core; 44- valve seat connecting plate; 45- oil pipe; 46- valve core connecting plate; 461- vertical guide column; 51- ball screw; 52- screw nut; 60- drive assembly support frame; 61-rotation drive part; 62-first transmission belt; 63-second transmission belt; 64-first transmission wheel; 65-second transmission wheel; 66-third transmission wheel; 67-fourth transmission wheel; 68-first transmission Bevel gear; 69-Second bevel gear; 7-Connecting rod; 81-Anti-rotation plate; 82-Anti-rotation sliding sleeve; 9-Hydraulic cylinder support frame.

Detailed ways

In order to make the purposes, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments These are some embodiments of the present invention, but not all embodiments. The components of the embodiments of the invention generally described and illustrated in the drawings herein may be arranged and designed in a variety of different configurations.

Thus, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

It should be noted that like numerals and letters refer to like items in the following figures, so once an item is defined in one figure, it does not require further definition and explanation in subsequent figures.

In the description of the present invention, it should be noted that the orientations or positional relationships indicated by the terms "upper", "lower", "vertical", "horizontal", "inner", "outer", etc. are based on those shown in the accompanying drawings. The orientation or positional relationship of the invention, or the orientation or positional relationship that is usually placed when the product of the invention is used, is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, It is constructed and operated in a particular orientation and is therefore not to be construed as a limitation of the present invention. Furthermore, the terms "first", "second", "third", etc. are only used to differentiate the description and should not be construed as indicating or implying relative importance.

Furthermore, the terms "horizontal", "vertical" and the like do not imply that a component is required to be absolutely horizontal or overhang, but rather may be slightly inclined. For example, "horizontal" only means that its direction is more horizontal than "vertical", it does not mean that the structure must be completely horizontal, but can be slightly inclined.

In the description of the present invention, it should also be noted that, unless otherwise expressly specified and limited, the terms "arrangement", "installation" and "connection" should be understood in a broad sense, for example, it may be a fixed connection or a connectable connection. Detachable connection, or integral connection; may be mechanical connection or electrical connection; may be direct connection, or indirect connection through an intermediate medium, or internal communication between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood in specific situations.

Some embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The embodiments described below and features in the embodiments may be combined with each other without conflict.

This embodiment provides a device for jacking up the nose landing gear of an aircraft. Referring to FIG. 1 to FIG. 7 , the device for jacking up the nose landing gear of an aircraft includes a landing gear support beam 1 , a first lifting mechanism 2 , and a second lifting mechanism 3 ; Specifically, a bearing groove 11 recessed downward is provided in the middle of the landing gear support beam 1 , one end of the landing gear support beam 1 is connected to the first lifting mechanism 2 , and the other end of the landing gear support beam 1 is connected to the second lift mechanism 2 . Lifting mechanism 3 ; the first lifting mechanism 2 and the second lifting mechanism 3 are configured to be able to control the synchronous lifting and lowering of both ends of the landing gear support beam 1 .

When in use, two above-mentioned aircraft nose landing gear jacking devices are used to lift the aircraft nose landing gear, so that the two wheels respectively fall into the bearing grooves of the landing gear support beam 1 in the aircraft nose landing gear jacking device. 11 Inside, start the first lifting mechanism 2 and the second lifting mechanism 3 to slowly lift the landing gear support beam 1, thereby slowly lifting the wheel, and then supporting the nose landing gear of the aircraft, and further, repairing the nose landing gear of the aircraft Compared with manually using a jack to lift and support the nose landing gear of the aircraft, the process of jacking up and supporting the nose landing gear of the aircraft is more efficient, which is conducive to the rapid maintenance of the nose landing gear of the aircraft.

In addition, in particular, for the part where the jack supports the front landing gear beam of the aircraft, the jack chassis or other parts occupy the space at the bottom of the two wheels of the landing gear, so that it is impossible to insert the device for testing the performance of the aircraft into the bottom of the two wheels of the landing gear. The two front wheels of the landing gear are used for steering or other wheel performance tests, but the steering status of the front wheels can only be checked by manually rotating the control handwheel, including whether the steering is flexible and whether the wheels vibrate during the steering process, which greatly reduces the problem. The efficiency of steering or other performance tests of the nose wheel of the aircraft landing gear seriously affects the accuracy of the test results. The aircraft nose landing gear jacking device provided in this embodiment uses the first lifting mechanism 2 and the second lifting mechanism. 3 and the landing gear support beam 1. After the two front wheels of the nose landing gear of the aircraft are supported, the space at the bottom of the two front wheels is not occupied, so that the wheel performance testing device can be inserted into the bottom of the two front wheels, and then slowly The nose wheel of the aircraft falls on the device for testing the performance of the wheel, remove the lifting device of the nose landing gear of the aircraft, and then perform a corresponding performance test on the nose wheel of the landing gear. The lifting device is moved back to support the two front wheels again.

The device for jacking up the nose landing gear provided by this embodiment has a simple structure, and does not occupy the bottom space of the two front wheels after supporting the two front wheels of the aircraft nose landing gear during use, thereby overcoming the need for the jack supporting the landing gear to occupy the bottom space of the two front wheels The technical obstacle that makes it impossible to use the wheel performance testing device for the performance test of the front wheel makes it possible to use the wheel performance testing device to replace the pure manual runner for the performance test of the front wheel, thereby improving the test efficiency and the accuracy of the test results. application prospects.

In an optional implementation of this embodiment, the above-mentioned first lifting mechanism 2 and second lifting mechanism 3 have various optional structures. The lifting mechanism 2 and the second lifting mechanism 3 respectively include respective hydraulic cylinder assemblies, a servo valve 43 and a servo valve lifting drive assembly; wherein: the hydraulic cylinder assembly includes a hydraulic cylinder 41 and a piston rod 42, and the hydraulic cylinder 41 is arranged vertically, The lower end of the piston rod 42 is telescopically connected to the interior of the hydraulic cylinder 41, and the upper end of the piston rod 42 is fixed to the end of the landing gear support beam 1; the servo valve 43 includes a valve seat 431 and a valve core 432 installed on the valve seat 431; the valve seat 431 is fixedly connected to the hydraulic cylinder 41 through the valve seat connecting plate 44, and the valve seat 431 is connected to the hydraulic cylinder 41 through the oil pipe 45; the upper end of the valve core 432 is fixedly connected to the upper end of the piston rod 42 through the valve core connecting plate 46; the valve seat 431 The valve core 432 and the valve core 432 are both connected to the servo valve lift drive assembly. The servo valve lift drive assembly is configured to drive the valve core 432 to rise and fall to drive the piston rod 42 to rise and fall, thereby driving the end of the landing gear support beam 1 to rise and fall. In this preferred embodiment, the electro-hydraulic servo-hydraulic system is formed by combining the hydraulic cylinder assembly, the servo valve 43 and the servo valve lift drive assembly, which has the advantages of convenient operation and high action accuracy.

Further preferably, the servo valve lift drive assembly includes a ball screw 51, a screw nut 52 and a combined structure for rotary drive; the ball screw 51 is arranged in a vertical direction and passes through the valve seat 431, and the screw nut 52 is threadedly sleeved on the ball Outside the lead screw 51, the valve core 432 is fixed on the lead screw nut 52; the rotary drive combination structure is connected to one end of the ball screw 51, and the rotary drive combination structure is configured to drive the ball screw 51 to rotate, so as to drive the lead screw nut 52 to rise and fall, In turn, the valve core 432 is driven to rise and fall relative to the valve seat 431, and this structure can ensure the smoothness of the lifting action.

Further preferably, the above-mentioned rotary drive combination structure includes a drive assembly support frame 60, a rotary drive part 61, a first transmission belt 62, a second transmission belt 63, a first transmission wheel 64, a second transmission wheel 65, a third transmission wheel 66, The fourth transmission wheel 67 , the first bevel gear 68 and the second bevel gear 69 . The side of the drive assembly support frame 60 in the first lifting mechanism 2 and the drive assembly support frame 60 in the second lift mechanism 3 that face each other is the inner side of the drive assembly support frame 60, and the drive assembly support frame 60 One of the inner side and the outer side is the first side of the drive assembly support frame 60, and the other side is the second side of the drive assembly support frame 60: the first transmission wheel 64 is rotatably installed on the drive assembly support frame 60 through the first axle. The first side of the top; the second transmission wheel 65 is rotatably installed on the bottom first side of the drive assembly support frame 60 through the second wheel shaft, and the second wheel shaft passes through the drive assembly support frame 60, and the third transmission wheel 66 is installed on the second wheel shaft is located at one end of the second side of the drive assembly support frame 60; the fourth transmission wheel 67 is rotatably mounted on the second side of the bottom of the drive assembly support frame 60 through the third axle, and the fourth transmission wheel 67 and the third transmission wheel 66 are spaced apart from each other; The third wheel shaft passes through the drive assembly support frame 60 , the first bevel gear 68 is installed on the end of the third wheel shaft located on the first side of the drive assembly support frame 60 , the second bevel gear 69 is installed at the lower end of the ball screw 51 , and the second The bevel gear 69 and the first bevel gear 68 are perpendicular to each other and mesh with each other; the first transmission belt 62 is fitted over and abutted on the outside of the first transmission wheel 64 and the second transmission wheel 65 , and the second transmission belt 63 is fitted over and abuts against the third transmission Outside of wheel 66 and fourth transmission wheel 67 . The rotary driving part 61 is connected to the first axle, and the rotary driving part 61 is configured to be able to drive the first transmission wheel 64 to rotate, so as to drive the second transmission wheel 65 , the third transmission wheel 66 , the fourth transmission wheel 67 and the first bevel gear in sequence. 68 and the second bevel gear 69 rotate, thereby driving the ball screw 51 to rotate. The rotary driving part 61 can adopt the structure of a hand wheel, a rotary motor, a rotary hydraulic cylinder 41 or a rotary cylinder, etc. The above axles pass through and are connected to the drive assembly support frame 60 through their respective bearings. In this embodiment, through the above-mentioned drive assembly support frame 60 , the rotary drive part 61 , the first transmission belt 62 , the second transmission belt 63 , the first transmission wheel 64 , the second transmission wheel 65 , the third transmission wheel 66 , and the fourth transmission The combined structure of the wheel 67, the first bevel gear 68 and the second bevel gear 69 is used as the power output structure of the rotary drive, and the overall structure is relatively compact, and it is convenient to adjust the specific setting position of the rotary drive part 61 to make the rotary drive The position of the part 61 is far away from the supporting point of the wheel, so as to obtain a larger operating space and at the same time ensure the smoothness of the transmission.

Further preferably, but not limited to, the first axle connected to the support frame 60 of the drive assembly in the first lifting mechanism 2 is connected to the first axle connected to the support frame 60 of the drive assembly in the second lifting mechanism 3 through the connecting rod 7. , so that the first lifting mechanism 2 and the second lifting mechanism 3 can perform the lifting action at the same time, so as to ensure the stability of the lifting action.

In addition, in order to further ensure the lifting stability, in some optional implementations of this embodiment, preferably, an anti-rotation structure is further provided between the valve core 432 and the valve core connecting plate 46, and the anti-rotation structure can be Not limited to as shown in the figure, it includes an anti-rotation plate 81 and an anti-rotation sliding sleeve 82; The bottom of the valve core 432 and the anti-rotation sliding sleeve 82 are fixed on the anti-rotation plate 81 , and the central axis of the anti-rotation sliding sleeve 82 extends in the vertical direction, and the vertical guide column 461 passes through the anti-rotation sliding sleeve 82 .

In addition, in some optional implementations of this embodiment, preferably but not limited to, the first lifting mechanism 2 and the second lifting mechanism 3 further include respective hydraulic cylinder support frames 9, and the hydraulic cylinder 41 is fixed on the Hydraulic cylinder support frame 9, in order to further increase the support stability of the entire aircraft nose landing gear jacking device, as well as facilitate assembly and maintenance, further preferably, but not limited to, the hydraulic cylinder support frame 9 is provided with a sleeve type with a top opening. structure, the hydraulic cylinder 41 extends into and is fixed inside the sleeve structure.

Finally, it should be noted that: the various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments refer to each other. That is, the above embodiments in this specification are only used to illustrate the technical solutions of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand: It is still possible to modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements to some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the technical solutions of the embodiments of the present invention. range.

Claims (10)

1. The jacking device for the nose landing gear of the airplane is characterized by comprising a landing gear supporting beam (1), a first lifting mechanism (2) and a second lifting mechanism (3);

a bearing groove (11) which is sunken downwards is formed in the middle of the landing gear support beam (1), one end of the landing gear support beam (1) is connected to the first lifting mechanism (2), and the other end of the landing gear support beam (1) is connected to the second lifting mechanism (3);

the first lifting mechanism (2) and the second lifting mechanism (3) are configured to control the synchronous lifting of the two ends of the landing gear support beam (1).

2. An aircraft nose landing gear jacking device according to claim 1, wherein the first lifting mechanism (2) and the second lifting mechanism (3) each comprise a respective hydraulic cylinder assembly, a servo valve (43) and a servo valve lift drive assembly;

the hydraulic cylinder assembly comprises a hydraulic cylinder (41) and a piston rod (42), the hydraulic cylinder (41) is vertically arranged, the lower end of the piston rod (42) is connected to the inside of the hydraulic cylinder (41) in a telescopic mode, and the upper end of the piston rod (42) is fixed to the end portion of the landing gear support beam (1);

the servo valve (43) comprises a valve seat (431) and a valve core (432) mounted on the valve seat (431); the valve seat (431) is fixedly connected to the hydraulic cylinder (41) through a valve seat connecting plate (44), and the valve seat (431) is connected with the hydraulic cylinder (41) through an oil pipe (45); the upper end of the valve core (432) is fixedly connected to the upper end of the piston rod (42) through a valve core connecting plate (46); the valve seat (431) and the valve core (432) are connected to the servo valve lifting driving assembly, and the servo valve lifting driving assembly is configured to drive the valve core (432) to lift so as to drive the piston rod (42) to lift and further drive the end part of the landing gear supporting beam (1) to lift.

3. An aircraft nose landing gear jacking device according to claim 2, wherein the servovalve lift drive assembly includes a ball screw (51), a screw nut (52) and a rotary drive assembly;

the ball screw (51) is arranged in the vertical direction and penetrates through the valve seat (431), the screw nut (52) is sleeved outside the ball screw (51) in a threaded mode, and the valve core (432) is fixed to the screw nut (52); the rotary driving combined structure is connected to one end of the ball screw (51), and the rotary driving combined structure is configured to drive the ball screw (51) to rotate so as to drive the screw nut (52) to lift and further drive the valve core (432) to lift and lower relative to the valve seat (431).

4. The aircraft nose landing gear jack-up device according to claim 3, wherein the rotary drive combination structure comprises a drive assembly support frame (60), a rotary drive portion (61), a first drive belt (62), a second drive belt (63), a first drive wheel (64), a second drive wheel (65), a third drive wheel (66), a fourth drive wheel (67), a first bevel gear (68) and a second bevel gear (69);

taking a side of the first lifting mechanism (2) where the driving component support frame (60) faces each other and a side of the second lifting mechanism (3) where the driving component support frame (60) faces each other as an inner side of the driving component support frame (60), taking one of the inner side and the outer side of the driving component support frame (60) as a first side of the driving component support frame (60), and taking the other side as a second side of the driving component support frame (60):

the first transmission wheel (64) is rotatably arranged on the first side of the top of the driving component support frame (60) through a first wheel shaft; the second transmission wheel (65) is rotatably arranged on the first side of the bottom of the driving component support frame (60) through a second wheel shaft, the second wheel shaft penetrates through the driving component support frame (60), and the third transmission wheel (66) is arranged at one end, located on the second side of the driving component support frame (60), of the second wheel shaft; the fourth driving wheel (67) is rotatably arranged on the second side of the bottom of the driving component support frame (60) through a third wheel shaft, and the fourth driving wheel (67) and the third driving wheel (66) are spaced from each other; the third axle passes through the driving assembly support frame (60), the first bevel gear (68) is mounted at one end of the third axle on the first side of the driving assembly support frame (60), the second bevel gear (69) is mounted at the lower end of the ball screw (51), and the second bevel gear (69) and the first bevel gear (68) are perpendicular to each other and are meshed with each other; the first transmission belt (62) is sleeved and abutted to the outer parts of the first transmission wheel (64) and the second transmission wheel (65), and the second transmission belt (63) is sleeved and abutted to the outer parts of the third transmission wheel (66) and the fourth transmission wheel (67);

the rotary driving part (61) is connected to the first wheel shaft, and the rotary driving part (61) is configured to drive the first transmission wheel (64) to rotate so as to sequentially drive the second transmission wheel (65), the third transmission wheel (66), the fourth transmission wheel (67), the first bevel gear (68) and the second bevel gear (69) to rotate, so as to drive the ball screw (51) to rotate.

5. Aircraft nose landing gear jacking device according to claim 4, wherein the first axle connected to the drive assembly support bracket (60) in the first lifting mechanism (2) is connected to the first axle connected to the drive assembly support bracket (60) in the second lifting mechanism (3) by a connecting rod (7).

6. Aircraft nose landing gear jack according to claim 4, wherein the rotary drive (61) employs a hand wheel.

7. The aircraft nose landing gear jacking device according to claim 2 wherein an anti-rotation structure is provided between the spool (432) and the spool connecting plate (46).

8. The aircraft nose landing gear jacking device according to claim 7, wherein said anti-rotation structure includes an anti-rotation plate (81) and an anti-rotation sliding sleeve (82);

the upper plate surface of the valve core connecting plate (46) is fixedly or integrally connected with a vertical guide column (461), one end of an anti-rotation plate (81) is installed on the valve core (432), the bottom of the anti-rotation sliding sleeve (82) is fixed on the anti-rotation plate (81), the central axis of the anti-rotation sliding sleeve (82) extends along the vertical direction, and the vertical guide column (461) penetrates through the anti-rotation sliding sleeve (82).

9. Aircraft nose landing gear jacking device according to claim 2, wherein said first lifting mechanism (2) and said second lifting mechanism (3) further comprise respective hydraulic cylinder support brackets (9), said hydraulic cylinders (41) being fixed to said hydraulic cylinder support brackets (9).

10. Aircraft nose landing gear jack according to claim 9, wherein the hydraulic cylinder support frame (9) is provided with an open-topped telescopic structure, and the hydraulic cylinder (41) extends into and is fixed inside the telescopic structure.

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