Nose landing gear of ultra-light aircraft

Abstract

A nose landing gear of an ultra-light aircraft comprises a steering vertical pipe, a damping sleeve, a piston rod, a pressure spring, a steering sleeve, a front fork, a wheel, a connecting rod and a pair of hinge arms. Wherein the steering vertical pipe is fixed on a fuselage of the airplane; the damping sleeve is installed in the steering vertical pipe and can rotate and slide along the axis of the steering vertical pipe. The piston rod and the pressure spring are mounted in the damping sleeve for damping; the rod portion of the piston rod is fixedly connected with the upper end of the steering vertical pipe, the steering sleeve is hinged to the lower end of the steering vertical pipe, the front fork is fixedly connected to the lower end of the damping sleeve, the wheels are installed on the front fork, the pair of hinge arms is hinged between the steering wheel and the front fork assembly, and the connecting rod is hinged to the steering wheel and used for driving the wheels to steer. The nose landing gear has the characteristics of light weight, simple structure and easiness in maintenance, and meets the design requirements of ultra-light aircrafts. Compared with a single-side braking steering mode, the steering angle of the nose landing gear is easy to control, each wheel only rolls, and tires cannot be seriously abraded due to lateral slippage.

Description

Technical Field

[0001] The utility model relates to the technical field of ultra-light aircraft, in particular to a nose landing gear of an ultra-light aircraft. Background Art

[0002] Ultra-light aircraft have the advantages of small size, light weight, simple structure, easy operation, easy maintenance, short take-off distance, and low requirements for take-off sites.

[0003] In order to meet the design requirements of light weight, simple structure, and easy maintenance, current light aircraft and ultra-light aircraft usually adopt non-retractable landing gears. However, most aircraft's nose landing gears still use complex hydraulic shock absorption or gas-liquid shock absorption structures. From the perspectives of weight, structure, and maintenance, the current nose landing gears do not meet the design requirements of light weight, simple structure, and easy maintenance.

[0004] In addition, most light aircraft and ultra-light aircraft turn on the ground by braking one of the wheels of the main landing gear. Its disadvantages are mainly reflected in two aspects: one is that the steering angle is difficult to control, and over-braking on one side easily causes the aircraft to roll over; the other is that the wheels will have lateral slip, resulting in serious tire wear. Summary of the Utility Model

[0005] In order to overcome the deficiencies in the background art, the utility model discloses a nose landing gear of an ultra-light aircraft, and its purposes are:

[0006] 1. Make the nose landing gear have the characteristics of light weight, simple structure, and easy maintenance, meeting the design requirements of ultra-light aircraft;

[0007] 2. Make the steering angle of the nose landing gear easy to control and solve the problem of serious tire wear caused by lateral slip.

[0008] Specifically, the utility model adopts the following technical solutions:

[0009] A nose landing gear of an ultra-light aircraft, comprising:

[0010] A steering riser, fixed to the fuselage of the aircraft;

[0011] A shock-absorbing sleeve, installed in the steering riser and capable of rotating and sliding along the axis of the steering riser;

[0012] A piston rod and a compression spring, installed in the shock-absorbing sleeve for shock absorption; wherein, the rod part of the piston rod is fixedly connected to the upper end of the steering riser;

[0013] A steering sleeve, hinged to the lower end of the steering riser;

[0014] A front fork, fixedly connected to the lower end of the shock-absorbing sleeve;

[0015] A wheel, mounted on the front fork;

[0016] A pair of articulated arms, articulated between the steering wheel and the front fork assembly;

[0017] A connecting rod, articulated with the steering wheel, for driving the wheel to steer.

[0018] After implementing the above technical solution, the beneficial effects are as follows:

[0019] 1. The shock-absorbing sleeve, piston rod and compression spring constitute a shock-absorbing structure. When the aircraft takes off and lands, the shock-absorbing structure can reduce the impact caused by the ground on the aircraft;

[0020] 2. The connecting rod, steering sleeve, articulated arm and front fork constitute a steering mechanism. Moreover, due to the existence of the articulated arm, the steering mechanism is not restricted by the telescopic movement of the shock-absorbing sleeve;

[0021] 3. The steering of the aircraft on the ground is realized by the steering mechanism. Compared with the steering method of unilateral braking, the steering angle of the steering mechanism is easy to control, and the tires will not be severely worn due to lateral sliding.

[0022] Furthermore, the technical solution is improved. An oil injection nozzle is installed on the steering vertical pipe, and grease can be injected between the shock-absorbing sleeve and the steering vertical pipe through the oil injection nozzle.

[0023] After implementing the above technical solution, the beneficial effects are as follows: Regularly injecting grease between the shock-absorbing sleeve and the steering vertical pipe through the oil injection nozzle can reduce the friction between the shock-absorbing sleeve and the steering vertical pipe, extend the service life, and at the same time improve the sealing performance between the shock-absorbing sleeve and the steering vertical pipe to prevent dust from entering.

[0024] Furthermore, the technical solution is improved. An oil injection nozzle is installed on the steering sleeve, and grease can be injected between the steering sleeve and the steering vertical pipe through the oil injection nozzle.

[0025] After implementing the above technical solution, the beneficial effects are as follows: Regularly injecting grease between the steering sleeve and the steering vertical pipe through the oil injection nozzle can reduce the friction between the steering sleeve and the steering vertical pipe, which is beneficial to improving the working efficiency of the steering mechanism.

[0026] Furthermore, the technical solution is improved. Shock-absorbing sleeves made of nylon material are provided at the upper and lower ends of the shock-absorbing sleeve.

[0027] After implementing the above technical solution, the beneficial effects are as follows: The shock-absorbing sleeves made of nylon material have the advantages of light weight, high strength, corrosion resistance and impact resistance.

[0028] Furthermore, the technical solution is improved. The piston on the piston rod is connected by two upper and lower parts, and its material is nylon or polytetrafluoroethylene.

[0029] After implementing the above technical solution, the beneficial effects are as follows: Nylon and polytetrafluoroethylene not only have the advantages of light weight, high strength, corrosion resistance, and impact resistance, but also have self-lubricity, which can significantly reduce the wear on the shock-absorbing sleeve. The piston is composed of two upper and lower parts connected together, simplifying the manufacturing process of the piston rod and facilitating the replacement of the piston.

[0030] Furthermore, in the improved technical solution, the upper and lower ends of the steering riser are fixed to the fuselage of the aircraft through a space truss structure.

[0031] After implementing the above technical solution, the beneficial effects are as follows: The space truss structure composed of welded rods has the advantages of light weight and high structural strength, and can effectively improve the fixing strength of the steering riser. Description of the Drawings

[0032] Figure 1 Shown is a schematic diagram of the overall structure of the nose landing gear of an ultra-light aircraft.

[0033] Figure 2 Shown is a schematic cross-sectional structure diagram of the connection between the shock-absorbing sleeve and the steering riser.

[0034] Figure 3 Shown is a schematic diagram of the structure of the nose landing gear during steering.

[0035] Figure 4 Shown is a schematic diagram of the structure of the steering mechanism when the shock-absorbing sleeve retracts.

[0036] In the drawings: 1. Steering riser; 2. Shock-absorbing sleeve; 3. Piston rod; 4. Compression spring; 5. Steering sleeve; 6. Connecting rod; 7. Hinge arm; 8. Front fork; 9. Wheel; 10. Grease nipple; 11. Shock-absorbing sleeve. Detailed Embodiments

[0037] The preferred embodiments of the present utility model will be described below with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are only used to explain the technical principles of the present utility model and are not intended to limit the protection scope of the present utility model. It should be noted that in the description of the present utility model, the terms indicating directions or positional relationships such as "front", "rear", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings. This is only for the convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present utility model. It should also be noted that in the description of the present utility model, unless otherwise clearly specified and limited, the terms "installation", "connection", "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, or the communication inside two elements. For those skilled in the art, the specific meanings of the above terms in the present utility model can be understood according to specific situations.

[0038] The attached Figure 1 shows a schematic diagram of the overall structure of the nose landing gear of a super-light aircraft. As can be seen from the attached Figure 1 It can be seen that the present nose landing gear includes a steering riser 1, a shock-absorbing sleeve 2, a steering sleeve 5, a connecting rod 6, a front fork 8, a wheel 9, and a pair of articulated arms 7. Among them, the upper and lower ends of the steering riser 1 are fixed to the fuselage of the aircraft through a space truss structure. The space truss structure formed by welding rods has the advantages of light weight and high structural strength, and can effectively improve the fixing strength of the steering riser 1.

[0039] Referring to the attached Figure 2 , the attached Figure 2 shows a schematic cross-sectional structure of the connection between the shock-absorbing sleeve and the steering riser. As can be seen from the attached Figure 2 It can be seen that the shock-absorbing sleeve 2 is installed inside the steering riser 1, and the shock-absorbing sleeve 2 can rotate and slide along the axis of the steering riser 1.

[0040] Shock-absorbing sleeves 11 are respectively fixed to the upper and lower ends of the shock-absorbing sleeve 2. The material of the shock-absorbing sleeve 11 is nylon, and nylon has the advantages of light weight, high strength, corrosion resistance, and impact resistance. A piston rod 3 and a compression spring 4 are installed between the two shock-absorbing sleeves 11. Among them, the compression spring 4 is located at the bottom of the piston rod 3, and the rod part of the piston rod 3 is fixedly connected to the upper end of the steering riser 1 through a nut.

[0041] In this embodiment, the piston on the piston rod 3 is composed of two upper and lower parts, and its material is polytetrafluoroethylene. In addition to the advantages of light weight, high strength, corrosion resistance, and impact resistance, polytetrafluoroethylene also has self-lubricating properties, which can significantly reduce the wear on the shock-absorbing sleeve 2. This split design simplifies the manufacturing process of the piston rod 3 and facilitates the replacement of the piston.

[0042] The shock-absorbing sleeve 2, the piston rod 3, and the compression spring 4 constitute a shock-absorbing structure. When the aircraft lands, the shock-absorbing sleeve 2 can expand and contract, reducing the impact on the aircraft caused by the ground.

[0043] Refer to the attached Figure 3 , the attached Figure 3 shows a schematic structural diagram of the nose landing gear during steering. As can be seen from the attached Figure 3 , the connecting rod 6, the steering sleeve 5, the front fork 8, and a pair of articulated arms 7 constitute a steering mechanism. Among them, the steering sleeve 5 is hinged at the lower end of the steering riser 1, the front fork 8 is fixedly connected to the lower end of the shock-absorbing sleeve 2 by bolts, the wheel 9 is installed on the front fork 8 through a wheel axle, and a pair of articulated arms 7 are hinged between the steering wheel and the front fork 8 assembly. The connecting rod 6 is hinged to the steering wheel. In this way, the connecting rod 6 can drive the wheel 9 to turn through the steering sleeve 5, a pair of articulated arms 7, and the front fork 8.

[0044] Compared with the steering method of single-sided braking, the steering angle of this steering mechanism is easy to control. Each wheel 9 will only roll and will not produce lateral slip, and the tire will not be severely worn due to lateral slip.

[0045] Refer to the attached Figure 4 , the attached Figure 4 shows a schematic structural diagram of the steering mechanism when the shock-absorbing sleeve retracts. Comparing the attached Figure 3 and the attached Figure 4 it can be seen that due to the existence of the articulated arm 7, the steering mechanism is not restricted by the expansion and contraction of the shock-absorbing sleeve 2. While the shock-absorbing sleeve 2 expands and contracts, the nose landing gear can still achieve steering.

[0046] Furthermore, improving the technical solution, an oil injection nozzle 10 is installed on the steering riser 1. Through the oil injection nozzle 10, grease can be injected between the shock-absorbing sleeve 2 and the steering riser 1. Regularly injecting grease between the shock-absorbing sleeve 2 and the steering riser 1 through the oil injection nozzle 10 can reduce the friction between the shock-absorbing sleeve 2 and the steering riser 1, extend the service life, and at the same time improve the sealing performance between the shock-absorbing sleeve 2 and the steering riser 1 to prevent dust from entering.

[0047] Furthermore, improving the technical solution, an oil injection nozzle 10 is installed on the steering sleeve 5. Through the oil injection nozzle 10, grease can be injected between the steering sleeve 5 and the steering riser 1. Regularly injecting grease between the steering sleeve 5 and the steering riser 1 through the oil injection nozzle 10 can reduce the friction between the steering sleeve 5 and the steering riser 1, which is beneficial to improving the working efficiency of the steering mechanism.

[0048] As can be seen from the above, the present nose landing gear has the characteristics of light weight, simple structure and easy maintenance, meeting the design requirements of ultra-light aircraft. Compared with the steering method of single-side braking, the steering angle of the present nose landing gear is easy to control, and each wheel only rolls without lateral slip, so the tires will not be severely worn due to lateral slip.

[0049] The parts not described in detail are the prior art. Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The protection scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. The nose landing gear of an ultra-light aircraft, characterized in that, Comprising: A steering riser, fixed to the fuselage of the aircraft; A shock-absorbing sleeve, installed inside the steering riser and capable of rotating and sliding along the axis of the steering riser; A piston rod and a compression spring, installed inside the shock-absorbing sleeve for shock absorption; wherein, the rod part of the piston rod is fixedly connected to the upper end of the steering riser; A steering sleeve, hinged to the lower end of the steering riser; A front fork, fixedly connected to the lower end of the shock-absorbing sleeve; A wheel, installed on the front fork; A pair of articulated arms, articulated between the steering wheel and the front fork assembly; A connecting rod, articulated with the steering wheel for driving the wheel to steer.

2. The nose landing gear of a super-light aircraft according to claim 1, characterized in that, An oil filling nozzle is installed on the steering riser, and grease can be injected between the shock-absorbing sleeve and the steering riser through the oil filling nozzle.

3. The nose landing gear of an ultra-light aircraft according to claim 1, characterized in that, An oil filling nozzle is installed on the steering sleeve, and grease can be injected between the steering sleeve and the steering riser through the oil filling nozzle.

4. The nose landing gear of an ultra-light aircraft as claimed in claim 1, characterized in that, Shock-absorbing sleeves made of nylon are provided at the upper and lower ends of the shock-absorbing sleeve.

5. The nose landing gear of an ultra-light aircraft as claimed in claim 1, characterized in that, The piston on the piston rod is connected by upper and lower parts, and its material is nylon or polytetrafluoroethylene.

6. The nose landing gear of an ultra-light aircraft according to claim 1, characterized in that, The upper and lower ends of the steering riser are fixed to the fuselage of the aircraft through a space truss structure.

Images