CN216468436U

CN216468436U - Detachable nose landing gear

Info

Publication number: CN216468436U
Application number: CN202123003438.XU
Authority: CN
Inventors: 姜明泽
Original assignee: Aerospace Shenzhou Aircraft Co ltd
Current assignee: Aerospace Shenzhou Aircraft Co ltd
Priority date: 2021-12-02
Filing date: 2021-12-02
Publication date: 2022-05-10
Anticipated expiration: 2031-12-02

Abstract

The utility model discloses a detachable nose landing gear, which comprises a U-shaped seat, a landing gear unit, a rotating shaft handle, a first quick-release pin and a second quick-release pin, wherein the U-shaped seat is fixed on the floor of a machine body structure through bolts, the landing gear unit is internally provided with the rotating shaft handle which is connected with wheels and controls the rotation, the middle of the U-shaped seat is provided with a positioning pin hole for positioning the rotating shaft handle, the rotating shaft handle penetrates through a bearing positioned in the landing gear unit and is positioned with the U-shaped seat through the positioning pin hole, the front part of the landing gear unit, which is close to the U-shaped seat, is of a fork-shaped structure, one quick-release pin at two sides is respectively inserted into corresponding hole positions of the U-shaped seat and the landing gear unit to install and fix the U-shaped seat and the landing gear unit, the U-shaped seat and the first quick-release pin are quickly installed through the quick-release pin and are positioned through the positioning pin hole before installation, the requirements of quick disassembly and accurate positioning and installation of daily operation of the airplane are met.

Description

Detachable nose landing gear

Technical Field

The utility model relates to a detachable nose landing gear of a small unmanned aerial vehicle, which is mainly used for fixed wing unmanned aerial vehicles below 100 kilograms.

Background

In recent years, the field of unmanned aerial vehicles in China has achieved very high performance from both types and performances, in the application of the unmanned aerial vehicles, there are several modes of wheeled takeoff and rocket-assisted zero-length takeoff, and the unmanned aerial vehicles with multiple takeoff modes are relatively few in one type, mainly the wheeled takeoff needs an undercarriage, and the unmanned aerial vehicle with zero-length launch has very large wind resistance on the undercarriage in the process of flying in the air, so that the performance of the aircraft is influenced to a certain extent, and the undercarriage is removed in a short time, so that time and labor are wasted.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects of the prior art, the utility model aims to provide a method which aims to solve the technical problems that: the landing gear is subjected to large wind resistance, certain influence is caused to the performance of the airplane, and the landing gear is dismounted in a short time, which wastes time and labor.

In order to solve the technical problem, the utility model adopts the following technical scheme:

the utility model provides a detachable nose landing gear, includes U type seat, undercarriage unit, rotation axis handle, quick-release round pin one, quick-release round pin two, the U type seat passes through the bolt fastening on the floor of organism structure, be equipped with in the undercarriage unit and be connected and control pivoted rotation axis handle with the wheel, the centre of U type seat is equipped with the location pinhole that supplies rotation axis handle location usefulness, and the rotation axis handle passes the bearing that is located the undercarriage unit and passes through the location pinhole and realize the location with U type seat, the undercarriage unit is close to the front portion of U type seat and is the fork type structure, and the hole site that U type seat and undercarriage unit correspond is inserted respectively to quick-release round pin one of both sides is fixed with U type seat and undercarriage unit installation.

Furthermore, a steering engine is fixedly mounted on one side of the U-shaped seat, a steering engine rocker arm is connected to an output shaft of the steering engine, the other end of the steering engine rocker arm is connected with a first connecting rod through a quick-release pin II, the first connecting rod is hinged to the rotating shaft handle, and the steering engine controls the rotation of the rotating shaft handle through the steering engine rocker arm and the first connecting rod so as to control the rotation of the wheels.

Furthermore, a rear seat is further arranged on one side of the steering engine, one end of the inclined support rod is fixedly installed on the rear seat through a third quick-release pin, and the other end of the inclined support rod is installed on the side wall of the undercarriage unit.

And furthermore, the device also comprises a second connecting rod, one end of the second connecting rod is hinged with the first connecting rod through a quick-release pin, and the other end of the second connecting rod is fixedly connected with the rotating shaft handle.

Compared with the prior art, the utility model has the beneficial effects that:

according to the utility model, the quick disassembly type structure combination comprises a fork-shaped structure of the undercarriage unit, the U-shaped seat and the quick assembly through the quick disassembly pin I, and the quick positioning through the positioning pin hole is realized before the quick assembly, so that the requirements of quick disassembly and accurate positioning and assembly in daily operation of the airplane are met.

Drawings

FIG. 1: the utility model is a schematic view of the whole structure of the utility model installed on the machine body structure;

FIG. 2: the utility model is a patent integral structure diagram I;

FIG. 3: the utility model is a second integral structure diagram;

in the figure: the aircraft comprises an engine body structure-1, a U-shaped seat-2, an undercarriage unit-3, a rotating shaft handle-4, a quick-release pin I-8, a quick-release pin II-11, a steering engine-5, a steering engine rocker-7, a first connecting rod-6, a rear seat-10, an inclined supporting rod-9, a quick-release pin III-12 and a second connecting rod-13.

Detailed Description

The present invention will be further described with reference to the accompanying drawings and the detailed description, and it should be noted that any combination of the embodiments or technical features described below can be used to form a new embodiment without conflict.

Referring to fig. 1 to 3:

example 1: the embodiment discloses a detachable nose landing gear, which is used for solving the problem that the nose landing gear of an airplane is inconvenient to detach, and comprises a U-shaped seat 2, a landing gear unit 3, a rotating shaft handle 4, a first quick-release pin 8 and a second quick-release pin 11, wherein the U-shaped seat 2 is fixed on the floor of a machine body structure 1 through bolts, the rotating shaft handle 4 which is connected with wheels of the airplane and controls the rotation of the landing gear unit 3 is arranged in the landing gear unit 3, a positioning pin hole for positioning the rotating shaft handle 4 is arranged in the middle of the U-shaped seat, the rotating shaft handle 4 penetrates through a bearing in the landing gear unit and is positioned with the U-shaped seat 2 through the positioning pin hole, two U-shaped end parts of the U-shaped seat are provided with mounting holes, the front part of the landing gear unit 3, which is close to the U-shaped seat 2, is of a fork-shaped structure, the fork-shaped structure is also provided with mounting holes, the first quick-release pins 8 on two outer sides of the U-shaped seat 2 are respectively inserted into the two mounting holes from two sides to connect the U-shaped seat 2, Undercarriage unit 3 installation is fixed, and what this embodiment announced is a removable nose landing gear, and the structural grouping who plays quick dismantlement formula wherein is undercarriage unit 3's fork type structure, and the fork type structure should be installed fast through quick-release pin 8 with U type seat 2 to through the quick location of locating pin hole before the installation, satisfy the demand that the daily operation of aircraft was dismantled fast and accurate location installation.

Example 2: on the basis of embodiment 1, a rotation control mechanism of an aircraft wheel is added, specifically, a steering engine 5 is fixedly installed on one side of a U-shaped seat 2, it should be noted that the steering engine 5 is also fixed on a floor of a machine body structure through a bolt, an output shaft of the steering engine 5 is connected with a steering engine rocker arm 7, the other end of the steering engine rocker arm 7 is connected with a first connecting rod 6 through a second quick-release pin 11, the first connecting rod 6 is hinged to a rotating shaft handle 4, the steering engine 5 controls the rotation of the rotating shaft handle 4 through the steering engine rocker arm 7 and the first connecting rod 6, so as to control the rotation of the wheel.

Example 3: on the basis of embodiment 1, a rear seat 10 and an inclined support rod 9 are added, a rear seat 10 is further arranged on one side of the steering engine 5, one end of the inclined support rod 9 is fixedly installed with the rear seat 10 through a quick-release pin III 12, the other end of the inclined support rod 9 is installed on the side wall of the landing gear unit 3, specifically, a fork-shaped structure is also arranged at the end part of the rear seat 10, an installation hole is arranged on the fork-shaped structure, an installation hole is also arranged at the position where the inclined support rod 9 is connected with the rear seat 10, the quick-release pin III 12 penetrates through the two installation holes to connect the inclined support rod 9 with the rear seat 10, the other end of the inclined support rod 9 is fixedly connected with the side wall of the landing gear unit 3 through a bolt, in this embodiment, the inclined support rod 9 is added on the basis of embodiment 1, so that a more stable supporting effect can be achieved on the landing gear, the stability of the landing gear can be increased when the aircraft is lifted and the landing gear is also in a quick connection mode through the quick-release pin, when the maintenance or the disassembly is needed, the inclined supporting rod 9 connected with the rear seat 10 can be quickly disassembled.

Specifically, as a further improvement of embodiment 2, this detachable nose landing gear still includes second connecting rod 13, the one end of second connecting rod 13 is articulated through quick-release pin four with first connecting rod 6, and the other end and rotation axis handle 4 fixed connection, so set up the flexibility of controlling when multiplicable steering wheel 5 passes through first connecting rod 6 control rotation axis handle 4 and thereby control aircraft wheel, realize the angular rotation of greater amplitude.

Specifically, the fork-shaped structural member, the U-shaped seat 2, the inclined supporting rod 9, the rear seat 10 and the matching end of the rotating shaft handle 4 and the U-shaped seat 2 are in small clearance fit, so that smooth combination during installation is guaranteed, and no shopping amount is produced.

Specifically, the turning of the undercarriage is controlled by a steering engine 5, the steering engine unit comprises a steering engine 5 and a connecting rod, the steering engine 5 is installed on a structural floor of the undercarriage, preferably, a fork-shaped structure of the undercarriage unit 3 is rapidly connected with a U-shaped seat 2, an inclined support rod 9 and a rear seat 10, which are installed on the undercarriage, and holes of a rotating shaft handle 4 and the U-shaped seat 2 are rapidly connected in a pairwise matching mode through quick-release pins, the rotating shaft handle 4 is arranged on the undercarriage unit 3, an output shaft of the steering engine 5 is matched with the rotating shaft handle 4 of the undercarriage through the connecting rod and is also connected through the quick-release pins, and when the undercarriage is controlled to rotate, the rotation of the undercarriage is realized by controlling the rotation of the steering engine 5, so that the turning of the airplane is realized; the whole system is convenient to operate and can be installed and adjusted within 1.5 minutes.

This detachable nose landing gear installation order does:

1. matching a fork-shaped structure of the undercarriage unit 3 with a U-shaped seat 2 arranged on the mechanism, and simultaneously inserting a rotating shaft handle 4 of the undercarriage unit into a positioning pin hole on the U-shaped seat 2 to align the undercarriage unit into a quick-release pin I8 inserted at the rear two sides;

2. matching the inclined support rod 9 with the rear seat 10, aligning the hole position and inserting a quick release pin III 12;

3. and the first connecting rod 6 and the steering engine rocker arm 7 are aligned with the hole position and inserted into the second quick-release pin 11.

The disassembly sequence is reverse, the whole operation does not need any tool, the installation and the adjustment can be completed within 1.5 minutes, and the operation is simple and rapid.

The above embodiments are only preferred embodiments of the present invention, and the protection scope of the present invention is not limited thereby, and any insubstantial changes and substitutions made by those skilled in the art based on the present invention are within the protection scope of the present invention.

Claims

1. A detachable nose landing gear, its characterized in that: including U type seat, undercarriage unit, rotation axis handle, quick-release round pin one, quick-release round pin two, the U type seat passes through the bolt fastening on the floor of organism structure, be equipped with in the undercarriage unit and be connected and control pivoted rotation axis handle with the wheel, the centre of U type seat is equipped with the location pinhole that supplies rotation axis handle location usefulness, and the rotation axis handle passes the bearing that is located the undercarriage unit and realizes the location through location pinhole and U type seat, the undercarriage unit is close to the front portion of U type seat and is the forked type structure, and one of the quick-release round pin of both sides inserts the hole site that U type seat and undercarriage unit correspond respectively and fixes U type seat and undercarriage unit installation.

2. A removable nose landing gear according to claim 1, wherein: a steering engine is fixedly mounted on one side of the U-shaped seat, a steering engine rocker arm is connected to an output shaft of the steering engine, the other end of the steering engine rocker arm is connected with a first connecting rod through a quick-release pin II, the first connecting rod is hinged to a rotating shaft handle, and the steering engine controls the rotation of the rotating shaft handle through the steering engine rocker arm and the first connecting rod, so that the wheels are controlled to rotate.

3. A removable nose landing gear according to claim 2, wherein: and a rear seat is further arranged on one side of the steering engine, one end of the inclined support rod is fixedly installed with the rear seat through a third quick-release pin, and the other end of the inclined support rod is installed on the side wall of the undercarriage unit.

4. A removable nose landing gear according to claim 2, wherein: the quick-release type electric spindle further comprises a second connecting rod, one end of the second connecting rod is hinged with the first connecting rod through a quick-release pin, and the other end of the second connecting rod is fixedly connected with the rotating shaft handle.