CN114314424A - Jacking device for nose landing gear of airplane - Google Patents
Jacking device for nose landing gear of airplane Download PDFInfo
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- CN114314424A CN114314424A CN202210131588.9A CN202210131588A CN114314424A CN 114314424 A CN114314424 A CN 114314424A CN 202210131588 A CN202210131588 A CN 202210131588A CN 114314424 A CN114314424 A CN 114314424A
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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
Technical Field
The invention relates to the technical field of maintenance of air transportation tools, in particular to a jacking device for a nose landing gear of an airplane.
Background
An aircraft nose landing gear is an attachment device for supporting an aircraft and for ground (or surface) movement when the lower portion of the aircraft is being used for takeoff and landing or ground (or surface) taxiing. The nose landing gear is the only part supporting the whole aircraft, and therefore it is an indispensable part of the aircraft; without it, the aircraft cannot move on the ground. After the aircraft takes off, the nose landing gear may be retracted depending on the aircraft performance.
The two front wheels of the nose landing gear of the airplane are connected through a cross beam, at present, the nose landing gear is supported mainly in a mode of supporting the cross beam part of the nose landing gear of the airplane through a jack, so that the two front wheels of the nose landing gear of the airplane are lifted, and then the front wheels are maintained or steered to perform performance tests. However, because the jack supports the cross beam part of the nose landing gear of the airplane, the chassis of the jack or other parts occupy the space at the bottom of the two wheels of the landing gear, and therefore, the device for detecting the performance of the wheels is plugged into the bottom of the two wheels of the landing gear to steer or test the performance of other wheels, but the steering state of the front wheels can only be checked through manual rotating wheels of people, including whether the steering is flexible or not, whether the wheels shake or not in the steering process, and the accuracy of the test result is seriously influenced by the efficiency of steering or testing the performance of the front wheels of the landing gear of the airplane.
Disclosure of Invention
The invention aims to provide a jacking device for a nose landing gear of an airplane, and the jacking device is used for solving the technical problems that in the prior art, when two nose wheels of the nose landing gear of the airplane are steered or other airplane wheel performance tests are carried out, a jack supports the landing gear to occupy the bottom space of the two nose wheels, so that the performance test of the nose wheels cannot be carried out by using a device for detecting the airplane wheel performance, and the test efficiency and the accuracy of test results are influenced.
In order to achieve the above purpose, the embodiment of the invention adopts the following technical scheme:
the embodiment of the invention provides a jacking device for a nose landing gear of an airplane, which comprises a landing gear support beam, a first lifting mechanism and a second lifting mechanism; a bearing groove which is sunken downwards is formed 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 and second lifting mechanisms are configured to control the simultaneous lifting of the two ends of the landing gear support beam.
When the airplane nose landing gear jacking device is used, the airplane nose landing gear is lifted by using the two airplane nose landing gear jacking devices, the two airplane wheels respectively fall into the bearing grooves of the landing gear supporting beams in the airplane nose landing gear jacking device correspondingly, the first lifting mechanism and the second lifting mechanism are started to slowly lift the landing gear supporting beams, so that the airplane wheels are slowly lifted, the airplane nose landing gear is further supported, and further, the airplane nose landing gear is maintained.
In addition, particularly, for the connection between two front wheels of an aircraft landing gear through a cross beam, a jack supports the cross beam part of the aircraft landing gear, and a chassis or other parts of the jack occupy the space at the bottom of two wheels of the landing gear, so that the steering or other wheel performance tests of the two front wheels of the aircraft landing gear cannot be performed by stuffing the device for detecting the wheel performance at the bottom of the two wheels of the landing gear, but the steering state of the front wheels can only be checked through manually rotating a control hand wheel, including whether the steering is flexible, whether the wheels shake in the steering process, and the like, which greatly reduces the efficiency of the steering or other performance tests of the front wheels of the aircraft landing gear and seriously affects the accuracy of test results, the jacking device of the aircraft landing gear provided by the embodiment utilizes a first lifting mechanism, a second lifting mechanism and a supporting beam to jack up the two front wheels of the aircraft landing gear, the space of two front wheel bottoms is not occupied to can fill in the device for wheel performance detection to two front wheel bottoms, then slowly fall the aircraft nose wheel to the device for wheel performance detection on, remove aircraft nose landing gear jacking device, and then carry out corresponding capability test to the undercarriage nose wheel, after the test is accomplished, move back the aircraft nose landing gear jacking device that this embodiment provided again, support two front wheels again.
The aircraft nose landing gear jacking device that this embodiment provided simple structure, do not occupy two nose wheel bottom spaces behind two nose wheels of propping up aircraft nose landing gear in the use, thereby overcome jack support undercarriage and taken up two nose wheel bottom spaces and caused the technical obstacle that can't use device for wheel performance testing to carry out nose wheel performance testing, feasible device for wheel performance testing replaces pure manual runner to carry out nose wheel performance testing through device for wheel performance testing, and then improve efficiency of software testing and test result degree of accuracy, good application prospect has.
In an alternative implementation of the embodiment of the present invention, the first lifting mechanism and the second lifting mechanism each comprise a respective hydraulic cylinder assembly, a servo valve, and a servo valve lift drive assembly;
the hydraulic cylinder assembly comprises a hydraulic cylinder and a piston rod, the hydraulic cylinder is vertically arranged, the lower end of the piston rod is connected to the inside of the hydraulic cylinder in a telescopic mode, and the upper end of the piston rod is fixed to the end portion of the landing gear supporting beam;
the servo valve comprises a valve seat and a valve core arranged 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 with 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 connected to the servo valve lifting driving assembly, and the servo valve lifting driving assembly is configured to drive the valve core to lift so as to drive the piston rod to lift and further drive the end part of the undercarriage supporting beam to lift.
Further optionally, the servo valve lift drive assembly comprises a ball screw, a screw nut, and a rotary drive assembly;
the ball screw is arranged in the vertical direction and penetrates through the valve seat, the screw nut is sleeved outside the ball screw in a threaded manner, and the valve core is fixed on the screw nut; the rotary driving combined structure is connected to one end of the ball screw, and the rotary driving combined structure is configured to drive the ball screw to rotate so as to drive the screw nut to lift, and further drive the valve core to lift relative to the valve seat.
Further optionally, the rotation driving combination structure includes a driving assembly support frame, a rotation driving portion, a first driving belt, a second driving belt, a first driving wheel, a second driving wheel, a third driving wheel, a fourth driving wheel, a first bevel gear and a second bevel gear;
with drive assembly support frame among the first lifting mechanism with the drive assembly support frame among the second lifting mechanism one side that faces each other is the inboard of drive assembly support frame, with one side in the inboard and the outside of drive assembly support frame is the first side of drive assembly support frame, the opposite side is the second side of drive assembly support frame:
the first driving wheel is rotatably arranged on the first side of the top of the driving component supporting frame through a first wheel shaft; the second driving wheel is rotatably arranged on the first side of the bottom of the driving component support frame through a second wheel shaft, the second wheel shaft penetrates through the driving component support frame, and the third driving wheel is arranged at one end, located on the second side of the driving component support frame, of the second wheel shaft; the fourth driving wheel is rotatably arranged on the second side of the bottom of the driving component supporting frame through a third wheel shaft, and the fourth driving wheel and the third driving wheel are spaced from each other; the third axle penetrates through the driving component support frame, the first bevel gear is mounted at one end, located at the first side of the driving component support frame, of the third axle, the second bevel gear is mounted at the lower end of the ball screw, and the second bevel gear and the first bevel gear are perpendicular to each other and meshed with each other; the first transmission belt is sleeved and abutted to the outer parts of the first transmission wheel and the second transmission wheel, and the second transmission belt is sleeved and abutted to the outer parts of the third transmission wheel and the fourth transmission wheel;
the rotation driving part is connected to the first wheel shaft, and the rotation driving part is configured to drive the first transmission wheel to rotate so as to sequentially drive the second transmission wheel, the third transmission wheel, the fourth transmission wheel, the first bevel gear and the second bevel gear to rotate, and further drive the ball screw to rotate.
Further optionally, a first wheel axle connected to the driving assembly support frame in the first lifting mechanism is connected to a first wheel axle connected to the driving assembly support frame in the second lifting mechanism through a connecting rod.
Optionally, the rotary drive portion employs a handwheel.
In an optional implementation manner of the embodiment of the invention, an anti-rotation structure is arranged between the valve core and the valve core connecting plate.
Further optionally, the anti-rotation structure comprises an anti-rotation plate and an anti-rotation sliding sleeve;
the upper plate surface of the valve core connecting plate is fixedly or integrally connected with a vertical guide post, one end of an anti-rotation plate is installed on the valve core, the bottom of the anti-rotation sliding sleeve is fixed on the anti-rotation plate, the central axis of the anti-rotation sliding sleeve extends along the vertical direction, and the vertical guide post penetrates through the anti-rotation sliding sleeve.
In an optional implementation manner of the embodiment of the present invention, each of the first lifting mechanism and the second lifting mechanism further includes a respective hydraulic cylinder support frame, and the hydraulic cylinder is fixed to the hydraulic cylinder support frame.
Further optionally, a sleeve-type structure with an open top is arranged on the hydraulic cylinder support frame, and the hydraulic cylinder extends into and is fixed inside the sleeve-type structure.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is an overall structural elevation view of an aircraft nose landing gear jacking device provided in accordance with an embodiment of the present invention;
FIG. 2 is an isometric view of the overall structure of an aircraft nose landing gear jacking device provided in accordance with an embodiment of the present invention;
FIG. 3 is an enlarged view of a portion A of FIG. 2;
FIG. 4 is an enlarged view of a portion B of FIG. 2;
FIG. 5 is a C-C section view of the aircraft nose landing gear jack shown in FIG. 1;
FIG. 6 is an enlarged view of a portion D of FIG. 5;
fig. 7 is a partial structure enlarged view of a portion E in fig. 5.
Icon: 1-landing gear support beam; 11-a bearing groove; 2-a first lifting mechanism; 3-a second lifting mechanism; 41-hydraulic cylinder; 42-a piston rod; 43-a servo valve; 431-valve seat; 432-a valve core; 44-valve seat connecting plate; 45-oil pipe; 46-a spool connection plate; 461-vertical guide post; 51-ball screw; 52-lead screw nut; 60-drive assembly support bracket; 61-a rotation drive; 62-a first drive belt; 63-a second drive belt; 64-a first drive wheel; 65-a second transmission wheel; 66-a third transmission wheel; 67-a fourth drive wheel; 68-a first bevel gear; 69-second bevel gear; 7-a connecting rod; 81-rotation prevention plates; 82-anti-rotation sliding sleeves; 9-hydraulic cylinder support frame.
Detailed Description
In order to make the objects, 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 drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "upper", "lower", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings or orientations or positional relationships conventionally laid out when products of the present invention are used, and are only for convenience of description and simplicity of description, and do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical" and the like do not imply that the components are required to be absolutely horizontal or pendant, but rather may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Some embodiments of the invention are described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
The embodiment provides an aircraft nose landing gear jacking device, and referring to fig. 1 to 7, the aircraft nose landing gear jacking device comprises a landing gear support beam 1, a first lifting mechanism 2 and a second lifting mechanism 3; specifically, a downward-recessed bearing groove 11 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 both ends of the landing gear support beam 1.
During the use, use two above-mentioned aircraft nose landing gear jacking devices, lift aircraft nose landing gear, make two wheels correspond respectively and fall into the landing gear supporting beam 1 among an aircraft nose landing gear jacking device inside bearing recess 11, start first lifting mechanism 2 and the slow lifting landing gear supporting beam 1 of second lifting mechanism 3, thereby slowly lift the wheel, and then support aircraft nose landing gear, furthermore, maintain aircraft nose landing gear, this jack-up and the process of supporting aircraft nose landing gear are compared in artifical jack-up and support aircraft nose landing gear of using, the process efficiency of jack-up and support is higher, be favorable to examining and repairing aircraft nose landing gear fast.
In addition, especially, for the position of the jack supporting the cross beam of the nose landing gear of the airplane, the chassis or other positions of the jack occupy the space at the bottom of the two wheels of the landing gear, so that the steering state of the front wheels, including whether the steering is flexible, whether the wheels shake in the steering process, and the like, cannot be checked by stuffing the device for detecting the wheel performance at the bottom of the two wheels of the landing gear, but only by manually rotating the control hand wheel, greatly reduces the efficiency of the steering or other performance tests of the front wheels of the landing gear of the airplane and seriously affects the accuracy of the test result, and the space at the bottom of the two front wheels is not occupied after the first lifting mechanism 2, the second lifting mechanism 3 and the supporting beam 1 are used for supporting the two front wheels of the nose landing gear of the airplane, therefore, the device for detecting the performance of the airplane wheel can be plugged into the bottoms of the two front wheels, then the airplane front wheel slowly falls onto the device for detecting the performance of the airplane wheel, the jacking device of the nose landing gear of the airplane is removed, further, the corresponding performance test is carried out on the nose landing gear, and after the test is completed, the jacking device of the nose landing gear of the airplane provided by the embodiment is moved back to support the two front wheels again.
The aircraft nose landing gear jacking device that this embodiment provided simple structure, do not occupy two nose wheel bottom spaces behind two nose wheels of propping up aircraft nose landing gear in the use, thereby overcome jack support undercarriage and taken up two nose wheel bottom spaces and caused the technical obstacle that can't use device for wheel performance testing to carry out nose wheel performance testing, feasible device for wheel performance testing replaces pure manual runner to carry out nose wheel performance testing through device for wheel performance testing, and then improve efficiency of software testing and test result degree of accuracy, good application prospect has.
In an alternative embodiment of the present embodiment, the first lifting mechanism 2 and the second lifting mechanism 3 have various alternative structures, wherein, referring to fig. 1 to 7, preferably, but not limited to, the first lifting mechanism 2 and the second lifting mechanism 3 respectively include a respective hydraulic cylinder assembly, a servo valve 43 and a servo valve lifting driving assembly; wherein: 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 includes a valve seat 431 and a spool 432 attached to 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 both connected to a 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 support beam 1 to lift. In the preferred embodiment, the hydraulic cylinder assembly, the servo valve 43 and the servo valve lifting driving assembly are combined to form an electro-hydraulic servo hydraulic system, and the electro-hydraulic servo hydraulic system has the advantages of convenience in operation, high action precision and the like.
Further preferably, the servo valve lift drive assembly comprises a ball screw 51, a screw nut 52 and a rotary drive assembly; the ball screw 51 is arranged along the vertical direction and penetrates through the valve seat 431, the screw nut 52 is sleeved outside the ball screw 51 in a threaded manner, and the valve core 432 is fixed on the screw nut 52; the rotation driving assembly structure is connected to one end of the ball screw 51, and the rotation driving assembly 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 relative to the valve seat 431.
Still more preferably, the above-mentioned rotary driving combination structure comprises a driving assembly support frame 60, a rotary driving portion 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, a fourth transmission wheel 67, a first bevel gear 68 and a second bevel gear 69. The side facing each other of the driving component support frame 60 in the first lifting mechanism 2 and the driving component support frame 60 in the second lifting mechanism 3 is the inner side of the driving component support frame 60, one of the inner side and the outer side of the driving component support frame 60 is the first side of the driving component support frame 60, and the other side is the second side of the driving component support frame 60: a first driving wheel 64 is rotatably mounted on the top first side of the driving assembly support bracket 60 through a first wheel axle; the second transmission wheel 65 is rotatably mounted 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 mounted at one end of the second wheel shaft, which is positioned on the second side of the driving component support frame 60; the fourth transmission 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 transmission wheel 67 and the third transmission wheel 66 are spaced from each other; the third axle passes through the driving assembly support frame 60, a first bevel gear 68 is mounted at one end of the third axle on the first side of the driving assembly support frame 60, a 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 on the outer portions of the first transmission wheel 64 and the second transmission wheel 65, and the second transmission belt 63 is sleeved and abutted on the outer portions of the third transmission wheel 66 and the fourth transmission wheel 67. The rotation driving part 61 is connected to the first wheel axle, and the rotation driving part 61 is configured to drive the first driving wheel 64 to rotate, so as to drive the second driving wheel 65, the third driving wheel 66, the fourth driving wheel 67, the first bevel gear 68 and the second bevel gear 69 to rotate in turn, and further drive the ball screw 51 to rotate. The rotary driving part 61 may adopt a hand wheel, a rotary motor, a rotary hydraulic cylinder 41, a rotary air cylinder, or other structures, and each wheel shaft passes through and is connected to the driving assembly supporting frame 60 through a respective bearing. In this embodiment, the above-mentioned combined structure of the driving assembly supporting frame 60, the rotation driving portion 61, the first driving belt 62, the second driving belt 63, the first driving wheel 64, the second driving wheel 65, the third driving wheel 66, the fourth driving wheel 67, the first bevel gear 68 and the second bevel gear 69 is used as a power output structure of the rotation driving, so that the overall structure is compact, and the specific setting position of the rotation driving portion 61 is adjusted conveniently, so that the position of the rotation driving portion 61 is far away from the wheel supporting point, thereby obtaining a large operable space, and simultaneously ensuring the transmission stability.
Further preferably, but not limited to, the first wheel axle connected to the driving component support frame 60 in the first lifting mechanism 2 is connected to the first wheel axle connected to the driving component support frame 60 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 lifting actions simultaneously, and the stability of the lifting actions is ensured.
In addition, to further ensure the lifting stability, in some optional embodiments of the present embodiment, it is preferable that an anti-rotation structure is further disposed between the valve core 432 and the valve core connecting plate 46, and the anti-rotation structure may include, but is not limited to, an anti-rotation plate 81 and an anti-rotation sliding sleeve 82 as shown in the drawings; specifically, 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 the 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 in the vertical direction, and the vertical guide column 461 penetrates through the anti-rotation sliding sleeve 82.
Furthermore, in some optional embodiments of this embodiment, it is preferable, but not limited to, that the first lifting mechanism 2 and the second lifting mechanism 3 further include respective hydraulic cylinder support frames 9, and the hydraulic cylinders 41 are fixed to the hydraulic cylinder support frames 9, so as to further increase the support stability of the whole aircraft nose landing gear jacking device and facilitate assembly and maintenance, and it is further preferable, but not limited to, that the hydraulic cylinder support frames 9 are provided with top-opening sleeve structures, and the hydraulic cylinders 41 extend into and are fixed inside the sleeve structures.
Finally, it should be noted that: the embodiments in the present description are all described in a progressive manner, each embodiment focuses on the differences from the other embodiments, and the same and similar parts among the embodiments can be referred to each other; the above embodiments in the present specification are only used for illustrating the technical solutions of the present invention, and not for limiting the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210131588.9A CN114314424A (en) | 2022-02-14 | 2022-02-14 | Jacking device for nose landing gear of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210131588.9A CN114314424A (en) | 2022-02-14 | 2022-02-14 | Jacking device for nose landing gear of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114314424A true CN114314424A (en) | 2022-04-12 |
Family
ID=81030980
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210131588.9A Pending CN114314424A (en) | 2022-02-14 | 2022-02-14 | Jacking device for nose landing gear of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114314424A (en) |
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2022
- 2022-02-14 CN CN202210131588.9A patent/CN114314424A/en active Pending
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