CN216424736U - Light aircraft nose landing gear structure - Google Patents
Light aircraft nose landing gear structure Download PDFInfo
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- CN216424736U CN216424736U CN202123286047.3U CN202123286047U CN216424736U CN 216424736 U CN216424736 U CN 216424736U CN 202123286047 U CN202123286047 U CN 202123286047U CN 216424736 U CN216424736 U CN 216424736U
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- main shaft
- steering engine
- buffer
- landing gear
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Abstract
The utility model discloses a light aircraft nose landing gear structure, which is arranged on a frame of a machine body through a mounting seat and comprises a main shaft, a buffer strut and a tire component; the main shaft is connected to the mounting seat, the upper half part of the main shaft is connected with the steering engine component through a turning flange, and the lower end of the main shaft is sleeved with a buffer strut (3) in a sliding manner; a spring is sleeved outside the buffer strut, and a tire assembly is fixed at the lower end of the buffer strut; and in order to prevent the buffer support and the main shaft from rotating relatively, a torsion-proof arm is arranged between the main shaft and the buffer support. The utility model discloses shock resistance and shock attenuation, aircraft run and the demand of turning when satisfying the aircraft landing, structural design configuration is simple, and the technology degree of difficulty is low, manufacturing cycle is short, low in manufacturing cost, and the assembly degree of difficulty is low, easy maintenance.
Description
Technical Field
The utility model relates to an aircraft field, in particular to light-duty aircraft nose landing gear structure.
Background
The landing gear is a main component of the airplane, and in the process of taking off and landing of the airplane, the collision impact force between the airplane and the ground is reduced to a level below the level which can be borne by a structure through the combined action of the tires and the damping device; the safe take-off and landing of the airplane are guaranteed.
At present, the front landing gear of a large-scale transport plane or a navigation plane generally adopts an oil-gas buffer and a high-internal-pressure tire to realize the functions of impact resistance and shock absorption, the structure can bear heavy load, and the oil-gas buffer has high buffering efficiency, strong energy absorption capacity and high reliability; the front wheel can be driven to turn by the actuating and shimmy damping device, and some front wheels are provided with large-scale actuators and motion mechanisms, so that the undercarriage can be folded and unfolded, and the requirements of airworthiness on the design and operation of the airplane are met.
However, the nose landing gear structure of a large-scale transport plane or a navigation plane meets the requirements of airworthiness on the design and operation of the plane, but has the following defects: (1) the structure is heavy and the cost is high; (2) the component system is many and complex; (3) the manufacturing process is difficult and the period is long; (4) the assembly precision requirement is extremely high; (5) routine maintenance also requires professional personnel.
Based on this, the utility model provides a light-duty aircraft nose landing gear structure.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a main aim at provides a light-duty aircraft nose landing gear structure both can satisfy necessary function and safety demand, has the nose landing gear structure of characteristics such as low cost, simple, the easy manufacturing of configuration, convenient maintenance again to satisfy the demand of light-duty aircraft trial production fast, experiment, batch production, can effectively solve the problem in the background art.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a light aircraft nose landing gear structure is arranged on a frame of a machine body through a mounting seat (1), and comprises a main shaft (2), a buffer strut (3) and a tire assembly (4); the main shaft (2) is connected to the mounting seat (1), the upper half part of the main shaft (2) is connected with the steering engine component (5) through a turning flange (21), and the lower end of the main shaft (2) is sleeved with the buffer strut (3) in a sliding manner; a spring (6) is sleeved outside the buffer strut (3), and a tire assembly (4) is fixed at the lower end of the buffer strut (3); and a torsion-proof arm (7) is arranged between the main shaft (2) and the buffer support post (3) for preventing the buffer support post (3) and the main shaft (2) from rotating relatively.
Preferably, the mounting seat (1) is formed by a base and two limiting rings perpendicular to the base in an integrated mode, and the base is fixedly mounted on the machine body frame through a plurality of screws; the main shaft (2) penetrates through the two limiting rings, a main shaft limiting pin (22) is arranged at the top end of the main shaft (2), and the main shaft (2) is limited by the main shaft limiting pin (22) to be clamped on the two limiting rings.
Preferably, a thrust needle roller combined bearing (23) is arranged at the position of a contact surface between the main shaft (2) and the bottom end of the upper limiting ring, so that the turning flexibility of the airplane on the ground is ensured, and an engineering plastic flange (24) is arranged at the position of a contact surface between the main shaft (2) and the top end of the lower limiting ring, so that the main shaft (2) can smoothly rotate in the limiting ring of the mounting seat (1).
Preferably, a turning flange (21) is fixed on the main shaft (2) between the upper limiting ring and the lower limiting ring, and the turning flange (21) is rotatably connected with a steering engine component (5) through a bolt; the steering engine component (5) comprises a steering engine connecting rod (51) and a steering engine (52), the turning flange (21) is connected with one end of the steering engine connecting rod (51), the other end of the steering engine connecting rod (51) is connected with the steering engine (52), and the steering engine (52) is fixed through a steering engine support (8) installed on the frame of the machine body.
Preferably, a buffer support column (3) is installed at the lower end of the main shaft (2), the upper end of the buffer support column (3) is sleeved in the main shaft (2), and an elliptical flange linear bearing (27) is fixed at the lower part of the main shaft (2) through a main shaft flange (26), so that the buffer support column (3) can smoothly slide up and down along the inner wall of the elliptical flange linear bearing (27).
Preferably, the torsion-proof arm (7) comprises an upper torsion-proof arm (71) and a lower torsion-proof arm (72) which are rotatably connected at one end, the other end of the upper torsion-proof arm (71) is connected to the spindle flange (26) through a bolt, and the other end of the lower torsion-proof arm (72) is connected to the wheel fork (41) through a bolt.
Preferably, the lower end of the buffer strut (3) is fixed with a tire assembly (4), the tire assembly (4) comprises a wheel fork (41) and a tire (42), the wheel fork (41) is fixed at the bottom of the buffer strut (3), and the wheel fork (41) is connected with the tire (42) through a wheel axle (43); and the axis of the cushion stay (3) is located in front of the axis of the tire (42).
Compared with the prior art, the utility model discloses following beneficial effect has: the requirements of impact resistance and shock absorption, aircraft sliding and turning during aircraft landing are met, the structural design and configuration are simple, the process difficulty is low, the manufacturing period is short, the manufacturing cost is low, the assembly difficulty is low, and the aircraft landing device is easy to maintain.
Drawings
FIG. 1 is a schematic view of a nose landing gear structure of a light aircraft;
FIG. 2 is a schematic view of landing gear strut axis and tire axis positions;
FIG. 3 is a structural diagram of an initial state of a nose landing gear before an aircraft lands;
FIG. 4 is a view of the landing gear spring in a fully compressed state;
FIG. 5 is a schematic view of a landing gear turning condition.
In the figure: 1. a mounting seat; 2. a main shaft; 3. a cushion strut; 4. a tire component; 5. a steering engine component; 6. A spring; 7. a torsion arm; 8. a steering engine bracket; 21. a turning flange; 22. a main shaft limit pin; 23. a thrust needle roller combined bearing; 24. an engineering plastic flange; 26. a main shaft flange; 27. an elliptical flange linear bearing; 41. a wheel fork; 42. a tire; 43. a wheel axle; 411. a fork base; 412. a fin; 413. a fixing assembly; 51. a steering engine connecting rod; 52. a steering engine; 71. an upper torsion arm; 72. and a lower torsion arm.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "provided," "connected," and the like are to be construed broadly, such as "connected," which may be 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 meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1, a light aircraft nose landing gear structure is mounted on a fuselage frame through a mounting seat 1; the aircraft nose landing gear structure comprises a main shaft 2, a buffer strut 3 and a tire assembly 4; the main shaft 2 is connected to the mounting seat 1, the upper half part of the main shaft 2 is connected with the steering engine component 5 through a turning flange 21, and the lower end of the main shaft 2 is sleeved with the buffer strut 3 in a sliding mode; a spring 6 is sleeved outside the buffer strut 3, and a tire assembly 4 is fixed at the lower end of the buffer strut 3; and a torsion preventing arm 7 is installed between the main shaft 2 and the buffer stay 3 in order to prevent the buffer stay 3 and the main shaft 2 from rotating relatively.
Specifically, the mounting seat 1 is formed by a base and two limiting rings perpendicular to the base in an integrated mode, and the base is fixedly mounted on the machine body frame through a plurality of screws. The main shaft 2 penetrates through the two limiting rings, a main shaft limiting pin 22 is arranged at the top end of the main shaft 2, and the main shaft 2 is limited by the main shaft limiting pin 22 to be clamped on the two limiting rings.
A thrust needle roller combination bearing 23 is arranged on the contact surface between the main shaft 2 and the bottom end of the upper limiting ring to ensure the turning flexibility of the airplane on the ground, and an engineering plastic flange 24 is arranged on the contact surface between the main shaft 2 and the top end of the lower limiting ring to ensure that the main shaft 2 can smoothly rotate in the limiting ring of the mounting seat 1.
A turning flange 21 is fixed on the main shaft 2 between the upper limiting ring and the lower limiting ring, and the turning flange 21 is rotatably connected with a steering engine component 5 through a bolt; the steering engine component 5 comprises a steering engine connecting rod 51 and a steering engine 52, the turning flange 21 is connected with one end of the steering engine connecting rod 51, the other end of the steering engine connecting rod 51 is connected with the steering engine 52, and the steering engine 52 is fixed through a steering engine support 8 arranged on the frame of the machine body. The steering engine 52 drives the steering engine connecting rod 51 to move, and the steering engine connecting rod 51 drives the turning flange 21 to move, so that the main shaft 2 fixed on the turning flange 21 is driven to rotate, and the airplane turns.
The lower end of the main shaft 2 is provided with the buffer support column 3, the upper end of the buffer support column 3 is sleeved in the main shaft 2, and in order to ensure that the buffer support column 3 can smoothly slide up and down in the main shaft 2, the lower part of the main shaft 2 is provided with the elliptical flange linear bearing 27 through the main shaft flange 26, so that the buffer support column 3 can smoothly slide up and down along the inner wall of the elliptical flange linear bearing 27.
The outer side of the buffer support 3 is sleeved with a spring 6, the upper end of the spring 6 is contacted with an elliptical flange linear bearing 27 arranged at the bottom of the main shaft 2, and the lower end of the spring 6 is contacted with the bottom of the buffer support 3. Wherein, the diameter of spring 6 will be greater than oval flange linear bearing 27's internal diameter to the base width of buffering pillar 3 will be greater than spring 6 diameter, and spring 6 can play the cushioning effect when guaranteeing that buffering pillar 3 slides from top to bottom in main shaft 2 is inside.
The lower end of the buffer strut 3 is fixed with a tire assembly 4, the tire assembly 4 comprises a wheel fork 41 and a tire 42, the wheel fork 41 is fixed at the bottom of the buffer strut 3, and the wheel fork 41 is connected with the tire 42 through a wheel shaft 43. The positions of the axis of the cushion post 3 and the axis of the tire 42 are shown in fig. 2, in order to ensure that the heading of the airplane during ground running is correct, the axis of the cushion post 3 is arranged in front of the axis of the tire 42, and the cushion post 3 drives the tire 42 to move forward, so that the tire 42 can stably and automatically return to the center when deflection occurs.
In order to prevent the relative rotation of the main shaft 2 and the buffer strut 3, a torsion-proof arm 7 is arranged between the main shaft 2 and the buffer strut 3; specifically, the torsion-preventing arm 7 includes an upper torsion-preventing arm 71 and a lower torsion-preventing arm 72, one end of which is rotatably connected, the other end of the upper torsion-preventing arm 71 is bolted to the spindle flange 26, and the other end of the lower torsion-preventing arm 72 is bolted to the wheel fork 41. Wherein, the fork 41 includes fork base 411 and sets up two fins 412 in fork base 411 bilateral symmetry, and fork base 411 upper end fixed connection cushions the bottom of pillar 3, still extends to be provided with fixed subassembly 413 in the upper end of fork base 411, and fork base 411, fin 412 and fixed subassembly 413 are preferably integrated into one piece, and the other end of preventing torsion arm 71 down passes through bolted connection on this fixed subassembly 413.
Before the aircraft lands, the nose gear initial state structure is shown in fig. 3. When the aircraft lands, the landing gear bears impact load, the buffer strut 3 slides upwards in the main shaft 2 through the elliptical flange linear bearing 27, and compresses the spring 6, so that the lower torsion-proof arm 72 and the upper torsion-proof arm 71 are driven to move together until the spring 6 is completely compressed, as shown in fig. 4. Then, under the reaction force of the spring 6, the buffer support 3 slides downward in the main shaft 2 through the elliptical flange linear bearing 27 until the initial state is restored, and at the same time, the spring 6 also restores the initial state.
When the airplane needs to turn when sliding on the ground as shown in fig. 5, the steering engine 52 deflects, the steering engine connecting rod 51 drives the turning flange 21, the main driving shaft 2, the buffer supporting column 3, the wheel fork 41 and the tire 42 deflect together, and the landing gear turns.
In the utility model, the main shaft 2 is preferably a common stainless steel pipe; the upper torsion-proof arm 71 and the lower torsion-proof arm 72 are all aluminum alloy machining parts, and the spring 6, the elliptical flange linear bearing 27, the steering engine 52, the steering engine bracket 8, the steering engine connecting rod 51, the thrust needle roller combined bearing 23, the engineering plastic flange 24, the tire 42 and the wheel shaft 43 are all common standard parts, so that the structural material of the whole airplane nose landing gear is easy to purchase, the manufacturing cost is low, all parts can be independently installed or disassembled, and the installation and maintenance are simple and easy.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. A light aircraft nose landing gear structure is arranged on a fuselage frame through a mounting seat (1), and is characterized by comprising a main shaft (2), a buffer strut (3) and a tire assembly (4); the main shaft (2) is connected to the mounting seat (1), the upper half part of the main shaft (2) is connected with the steering engine component (5) through a turning flange (21), and the lower end of the main shaft (2) is sleeved with the buffer strut (3) in a sliding manner; a spring (6) is sleeved outside the buffer strut (3), and a tire assembly (4) is fixed at the lower end of the buffer strut (3); and in order to prevent the main shaft (2) and the buffer support (3) from rotating relatively, a torsion-proof arm (7) is arranged between the main shaft (2) and the buffer support (3).
2. A light aircraft nose landing gear structure as claimed in claim 1, wherein the mounting seat (1) is formed integrally by a base and two stop collars perpendicular to the base, the base being fixedly mounted to the fuselage frame by a plurality of screws; the main shaft (2) penetrates through the two limiting rings, a main shaft limiting pin (22) is arranged at the top end of the main shaft (2), and the main shaft (2) is limited by the main shaft limiting pin (22) to be clamped on the two limiting rings.
3. A light aircraft nose landing gear structure as claimed in claim 2, wherein a thrust needle roller combination bearing (23) is installed at the position of the contact surface of the main shaft (2) and the bottom end of the upper limiting ring to ensure the turning flexibility of the aircraft on the ground, and an engineering plastic flange (24) is installed at the position of the contact surface of the main shaft (2) and the top end of the lower limiting ring to ensure that the main shaft (2) can smoothly rotate in the limiting ring of the mounting seat (1).
4. A light aircraft nose landing gear structure as claimed in claim 2, wherein a turning flange (21) is fixed on the main shaft (2) between the upper and lower spacing collars, and the turning flange (21) is rotatably connected with the steering engine assembly (5) through a bolt; the steering engine component (5) comprises a steering engine connecting rod (51) and a steering engine (52), the turning flange (21) is connected with one end of the steering engine connecting rod (51), the other end of the steering engine connecting rod (51) is connected with the steering engine (52), and the steering engine (52) is fixed through a steering engine support (8) installed on the frame of the machine body.
5. A light aircraft nose landing gear structure as claimed in claim 1, wherein a buffer strut (3) is installed at the lower end of the main shaft (2), the upper end of the buffer strut (3) is sleeved in the main shaft (2), and an elliptical flange linear bearing (27) is fixed at the lower part of the main shaft (2) through a main shaft flange (26), so that the buffer strut (3) can smoothly slide up and down along the inner wall of the elliptical flange linear bearing (27).
6. A light aircraft nose landing gear structure as claimed in claim 5, wherein the torsion arm (7) comprises an upper torsion arm (71) and a lower torsion arm (72) rotatably connected at one end, the other end of the upper torsion arm (71) being bolted to the main shaft flange (26), and the other end of the lower torsion arm (72) being bolted to the wheel fork (41).
7. A light aircraft nose landing gear structure as claimed in claim 1, wherein the lower end of the strut (3) is fixed with a tyre assembly (4), the tyre assembly (4) comprises a wheel fork (41) and a tyre (42), the wheel fork (41) is fixed at the bottom of the strut (3), and the wheel fork (41) and the tyre (42) are connected through an axle (43); and the axis of the cushion stay (3) is located in front of the axis of the tire (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123286047.3U CN216424736U (en) | 2021-12-24 | 2021-12-24 | Light aircraft nose landing gear structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123286047.3U CN216424736U (en) | 2021-12-24 | 2021-12-24 | Light aircraft nose landing gear structure |
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| Publication Number | Publication Date |
|---|---|
| CN216424736U true CN216424736U (en) | 2022-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123286047.3U Active CN216424736U (en) | 2021-12-24 | 2021-12-24 | Light aircraft nose landing gear structure |
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| CN (1) | CN216424736U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115258148A (en) * | 2022-08-11 | 2022-11-01 | 上海喆航航空科技有限公司 | Automatic inclinator structure of helicopter |
-
2021
- 2021-12-24 CN CN202123286047.3U patent/CN216424736U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115258148A (en) * | 2022-08-11 | 2022-11-01 | 上海喆航航空科技有限公司 | Automatic inclinator structure of helicopter |
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