CN211494436U - Nose landing gear of small aircraft - Google Patents
Nose landing gear of small aircraft Download PDFInfo
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- CN211494436U CN211494436U CN201921919051.9U CN201921919051U CN211494436U CN 211494436 U CN211494436 U CN 211494436U CN 201921919051 U CN201921919051 U CN 201921919051U CN 211494436 U CN211494436 U CN 211494436U
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- small aircraft
- landing gear
- piston rod
- plunger
- pillar urceolus
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Abstract
The utility model belongs to the technical field of the small aircraft spare part, concretely relates to small aircraft's nose landing gear. Including tire, wheel fork, oil gas formula buffer includes pillar urceolus, plunger and piston rod, and the plunger sets up in the pillar urceolus, and the piston rod can slide between plunger and pillar urceolus, and the piston rod lower extreme is connected with the wheel fork, and the pillar urceolus passes through fixed joint and lower fixed joint and the fuselage fixed connection of small aircraft, the outer wall of pillar urceolus sets up rotatory clamp, is connected with between rotatory clamp and the pillar urceolus and subtracts the pendulum ware. In the technical scheme, the swing of the tire of the light airplane is realized by adding the shimmy damper, the whole structure is simple, the number of parts is small, and the whole weight is light.
Description
Technical Field
The utility model belongs to the technical field of the small aircraft spare part, concretely relates to small aircraft's nose landing gear.
Background
With the gradual opening of the field of general aviation in China, light airplanes are developed to meet the opportunity, and the nose landing gear of modern airplanes is various in types, is often complex in structure, has more parts and heavier in weight, and is not suitable for light airplanes.
Disclosure of Invention
The utility model aims at: a nose landing gear for a small aircraft is provided to overcome the above-mentioned deficiencies of the prior art.
The utility model discloses the technical solution who adopts is:
the nose landing gear of a small airplane is characterized in that: including tire, wheel fork, oil gas formula buffer includes pillar urceolus, plunger and piston rod, and the plunger sets up in the pillar urceolus, and the piston rod can slide between plunger and pillar urceolus, and the piston rod lower extreme is connected with the wheel fork, and the pillar urceolus passes through fixed joint and lower fixed joint and the fuselage fixed connection of small aircraft, the outer wall of pillar urceolus sets up rotatory clamp, is connected with between rotatory clamp and the pillar urceolus and subtracts the pendulum ware.
Furthermore, a torsion-proof arm is connected between the rotary hoop and the wheel fork.
Furthermore, a fairing is arranged on the wheel fork and wraps the periphery of the tire.
Furthermore, an oil needle is arranged in the piston rod.
Furthermore, an inflation valve is arranged at the upper end of the plunger.
The utility model has the advantages that: in the technical scheme, the swing of the tire of the light airplane is realized by adding the shimmy damper, the whole structure is simple, the number of parts is small, and the whole weight is light.
Drawings
Fig. 1 is a schematic structural diagram provided by the present invention.
In the figure, 1-torsion-proof arm, 2-rotary hoop, 3-wheel fork, 4-tyre, 5-shimmy damper, 6-fairing, 7-pillar outer cylinder, 8-piston rod, 11-frame of machine body 1, 12-lower wall plate, 13-upper fixed joint and 14-lower fixed joint.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings of the present 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.
As shown in fig. 1, the present embodiment provides a nose landing gear of a small aircraft, which is composed of an oil-gas damper, a torsion-proof arm 1, a rotary yoke 2, a wheel fork 3, a tire 4, a shimmy damper 5, a fairing 6, and the like.
The front landing gear is a fixed landing gear; the forward rake angle of the nose landing gear is 14.1 degrees, namely the line angle between the oil-gas type buffer and the plane vertical to the plane of the airplane structure. The oil-gas type buffer mainly comprises a strut outer cylinder 7, a piston rod 8, a plunger, an oil needle and the like, is mainly used for bearing the load of an airplane acting on a nose landing gear, reducing the impact force borne by the airplane during landing and ground movement, and weakening the bumping and jumping of the airplane caused by impact. The lower part of the piston rod is provided with a connecting hole connected with the ground traction pull rod.
The shimmy damper is connected between the pillar outer cylinder and the rotary hoop, and when the airplane slides on the ground, the shimmy damper performs shimmy damping on the tire through internal friction.
The nose landing gear is arranged on a frame 11 and a lower wall plate 12 of a machine body 1, the load of the nose landing gear mainly comprises vertical load, course load and lateral load, the load absorbed on a tire is transmitted to a piston rod through a wheel fork by the nose landing gear, the piston rod compresses in an outer cylinder to absorb a part of vertical load, the rest load is transmitted to a strut outer cylinder, and the load is transmitted to the plane of the frame 1 and a lower wall plate of the machine body through an upper fixed joint 13 and a lower fixed joint 14 which are fixed on the strut outer cylinder.
The front landing gear is mainly made of 4130 structural steel, 4340 structural steel and 7050 aluminum alloy, wherein the outer cylinder of the strut, the piston rod and the plunger are made of 4130 structural steel, and the rotary hoop, the torsion-proof arm and the wheel fork are made of 7050-T7451 aluminum alloy.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (5)
1. A nose landing gear for a small aircraft, comprising: including tire, wheel fork, oil gas formula buffer includes pillar urceolus, plunger and piston rod, and the plunger sets up in the pillar urceolus, and the piston rod can slide between plunger and pillar urceolus, and the piston rod lower extreme is connected with the wheel fork, and the pillar urceolus passes through fixed joint and lower fixed joint and the fuselage fixed connection of small aircraft, the outer wall of pillar urceolus sets up rotatory clamp, is connected with between rotatory clamp and the pillar urceolus and subtracts the pendulum ware.
2. A nose landing gear for a small aircraft according to claim 1, wherein: and a torsion-proof arm is connected between the rotary hoop and the wheel fork.
3. A nose landing gear for a small aircraft according to claim 1, wherein: and the wheel fork is provided with a fairing which is wrapped on the periphery of the tire.
4. A nose landing gear for a small aircraft according to claim 1, wherein: an oil needle is arranged in the piston rod.
5. A nose landing gear for a small aircraft according to claim 1, wherein: and an inflation valve is arranged at the upper end of the plunger.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921919051.9U CN211494436U (en) | 2019-11-08 | 2019-11-08 | Nose landing gear of small aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921919051.9U CN211494436U (en) | 2019-11-08 | 2019-11-08 | Nose landing gear of small aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211494436U true CN211494436U (en) | 2020-09-15 |
Family
ID=72408919
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921919051.9U Active CN211494436U (en) | 2019-11-08 | 2019-11-08 | Nose landing gear of small aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211494436U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407260A (en) * | 2020-11-05 | 2021-02-26 | 北京空间机电研究所 | Composite nose landing gear buffer with pre-lifting and pre-rotating light structure |
| EP4382414A1 (en) * | 2022-12-06 | 2024-06-12 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A rotorcraft with a non-retractable wheel-type landing gear |
| EP4382416A1 (en) * | 2022-12-08 | 2024-06-12 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A non-retractable wheel-type landing gear for a rotorcraft |
| EP4382415A1 (en) * | 2022-12-06 | 2024-06-12 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A rotorcraft with a non-retractable wheel-type landing gear |
-
2019
- 2019-11-08 CN CN201921919051.9U patent/CN211494436U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407260A (en) * | 2020-11-05 | 2021-02-26 | 北京空间机电研究所 | Composite nose landing gear buffer with pre-lifting and pre-rotating light structure |
| EP4382414A1 (en) * | 2022-12-06 | 2024-06-12 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A rotorcraft with a non-retractable wheel-type landing gear |
| EP4382415A1 (en) * | 2022-12-06 | 2024-06-12 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A rotorcraft with a non-retractable wheel-type landing gear |
| EP4382416A1 (en) * | 2022-12-08 | 2024-06-12 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A non-retractable wheel-type landing gear for a rotorcraft |
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