CN211308946U

CN211308946U - Undercarriage stay bar longitudinal beam structure

Info

Publication number: CN211308946U
Application number: CN201922194860.4U
Authority: CN
Inventors: 王红梅; 宫瑞君; 刘端娜; 高杨; 李玉娟
Original assignee: Jinggong Shaoxing Composite Technology R & D Co ltd; Jinggong Shaoxing Composite Material Co ltd
Current assignee: Shaoxing Baojing Composite Material Co ltd; Shaoxing Baojing Composite Technology Research And Development Co ltd
Priority date: 2019-12-10
Filing date: 2019-12-10
Publication date: 2020-08-21
Anticipated expiration: 2029-12-10

Abstract

The utility model relates to an undercarriage vaulting pole longeron structure comprises web, 1# upper flange strip, 2# upper flange strip, 1# lower flange strip, 2# lower flange strip, right front corner box, left front corner box, 1# rib, 2# rib, 3# connection angle bar, 4# connection angle bar, 3# rib, 4# rib, 5# rib, 6# rib, right back corner box, left back corner box. The upper edge strip and the lower edge strip are respectively positioned at two sides of the upper end and the lower end of the web plate and are connected with the web plate to form a metal plate bending part assembly with an I-shaped section structure, and the metal plate bending part assembly is used for improving the torsional stability of the longitudinal beam. The ribs are located on two sides of the web plate and are symmetrically distributed about the neutral plane of the web plate, and the ribs are used for improving the rigidity of the web plate. The front corner box and the rear corner box are respectively arranged at the front end and the rear end of the web plate and connected with the bearing frame of the machine body to form a longitudinal bearing framework, so that the effective transmission of load is ensured. Will the utility model discloses be applied to unmanned aerial vehicle's design and manufacturing, have characteristics such as light in weight, intensity height, rigidity are good, with low costs, security and stability are good.

Description

Undercarriage stay bar longitudinal beam structure

Technical Field

The utility model relates to an unmanned air vehicle technique field, specific undercarriage vaulting pole longeron structure that says so.

Background

In order to ensure the flight performance of the airplane, retractable landing gears are adopted for the airplanes with the speed of more than 250Km/h, and the landing gears are inwards collected in the body skin during flight. Typically, the nose landing gear is mounted on a force-bearing frame riveted to the fuselage skin, with the landing gear load being transferred aft in the form of fuselage skin shear. However, in order to stow the nose landing gear, the lower skin of the fuselage must be formed with a large opening, which results in discontinuity of the structure of the fuselage skin, affects the load transfer of the landing gear, and has a great influence on the landing performance of the aircraft.

The present application was made based on this.

SUMMERY OF THE UTILITY MODEL

The utility model provides an undercarriage vaulting pole longeron structure arranges behind the undercarriage carriage, forms vertical atress skeleton for the undercarriage provides when putting to support when receiving, bears and transmits undercarriage ground load, guarantees the safety and the stability of aircraft organism structure.

In order to achieve the purpose, the utility model adopts the technical proposal that:

a landing gear strut longitudinal beam structure comprises a web plate, a No. 1 upper edge strip, a No. 2 upper edge strip, a No. 1 lower edge strip, a No. 2 lower edge strip, a right front corner box, a left front corner box, a No. 1 rib, a No. 2 rib, a No. 3 connecting angle material, a No. 4 connecting angle material, a No. 3 rib, a No. 4 rib, a No. 5 rib, a No. 6 rib, a right rear corner box and a left rear corner box,

the No. 1 upper edge strip and the No. 1 lower edge strip are respectively positioned at the upper end and the lower end of the web plate,

the No. 2 upper edge strip and the No. 2 lower edge strip are respectively positioned at the upper end and the lower end of the web plate and are connected with the web plate to form a metal plate bending part assembly with an I-shaped section structure;

the No. 1 rib, the No. 2 rib, the No. 3 rib, the No. 4 rib, the No. 5 rib and the No. 6 rib are positioned on two sides of the web plate and are symmetrically distributed about the neutral surface of the web plate;

further, as preferable:

the web is formed by stamping a metal plate with the thickness of 1.2mm, the material is 7050-T7451, 3 circular lightening holes are formed in the web, the structural weight is reduced, the edges of the holes are flanged outwards, the rigidity of the web is improved, and the web is prevented from deforming when loaded.

The welding head is characterized in that the No. 1 upper edge strip, the No. 2 upper edge strip, the No. 1 lower edge strip, the No. 2 lower edge strip, the No. 1 rib, the No. 2 rib, the No. 3 connecting angle material, the No. 4 connecting angle material, the No. 3 rib, the No. 4 rib, the No. 5 rib and the No. 6 rib are all L-shaped sheet metal parts, and the materials are 7050-T7451.

The right front corner box and the left front corner box are both formed by machining 7050-T7451 aluminum alloy, and reinforcing ribs are arranged in the corner boxes, so that the rigidity and the strength of the corner boxes are improved.

The working principle of the utility model is as follows:

the upper part of the longitudinal beam structure of the strut of the undercarriage is riveted with the floor of the machine body through an upper edge strip, the front end of the longitudinal beam structure is connected with a front bearing frame of the machine body and a front undercarriage joint support, and the rear end of the longitudinal beam structure is connected with a rear bearing frame of the machine body to form a longitudinal bearing framework. When the airplane lands, runs and brakes, the front undercarriage directly transmits force backwards along the longitudinal beam structure of the strut of the undercarriage, so that the continuity of load transmission is ensured, and the safety and the stability of the airplane body structure are improved.

The utility model has the advantages that:

(1) the utility model provides an undercarriage vaulting pole longeron structure, arranges behind the undercarriage carriage, forms vertical atress skeleton, bears and transmits undercarriage ground load, and the line of biography power is direct, has improved security, the stability of aircraft organism structure.

(2) A landing gear strut longitudinal beam structure adopts a large number of sheet metal parts to form an assembly, and effectively reduces cost under the condition of meeting the requirements of strength and rigidity.

The utility model provides an undercarriage vaulting pole longeron structure, light in weight, intensity are high, rigidity is good, with low costs, and under the condition that satisfies intensity requirement, operation requirement, the line of biography power is direct, has guaranteed the effective transmission of load, has improved security, the stability of aircraft organism structure.

Drawings

Fig. 1 is a front view of the present invention;

FIG. 2 is a schematic structural view of the present invention;

fig. 3 is a schematic view of the structure of the connecting member of the present invention.

Reference numbers in the figures:

1. a web;

2.1 # upper edge strip,

3.2 # upper edge strip;

4.1 # lower edge strip;

5.2 # lower edge strip;

6. a right front corner box;

7. a left front corner box;

8.1 # ribs;

9.2 # ribs;

10.3 # connecting angle bar;

11.4 # connecting angle bar;

12.3 # ribs;

13.4 # ribs;

14.5 # ribs;

15.6 # ribs;

16. a right rear corner box;

17. a left rear corner box;

18. a front start joint support;

19. 4, a machine body frame;

20.4-5 frame middle floor panel;

21. the machine body 5 is a frame.

Detailed Description

Example 1

The landing gear strut longitudinal beam structure of the embodiment is composed of a web, a # 1 upper edge strip, a # 2 upper edge strip, a # 1 lower edge strip, a # 2 lower edge strip, a right front corner box, a left front corner box, a # 1 rib, a # 2 rib, a # 3 connecting angle material, a # 4 connecting angle material, a # 3 rib, a # 4 rib, a # 5 rib, a # 6 rib, a right rear corner box and a left rear corner box, and is combined with a graph 1 and a graph 2. The 1# upper edge strip, the 2# upper edge strip, the 1# lower edge strip and the 2# lower edge strip are respectively positioned at two sides of the upper end and the lower end of the web plate and are connected with the web plate through rivets to form a metal plate bending part assembly with an I-shaped section structure, and the torsional stability of the longitudinal beam is improved. In addition, 3 vertical ribs are respectively arranged on two sides of the web plate, are symmetrically distributed relative to the web plate and are fixed through rivets, so that the rigidity of the web plate is improved.

With reference to fig. 3, the upper part of the undercarriage strut longitudinal beam structure is riveted on a 4-5 frame middle floor panel through a 1# upper edge strip and a 2# upper edge strip, the front end of the undercarriage strut longitudinal beam structure is provided with a 3# connecting angle bar, a 4# connecting angle bar, a right front corner box and a left front corner box which are riveted on a 4 frame of a machine body, the undercarriage strut longitudinal beam structure is fixedly connected with a front starting joint support through bolts, the rear end of the undercarriage strut longitudinal beam structure is provided with a right rear corner box and a left rear corner box, the undercarriage strut longitudinal beam structure is connected with the 5 frames of the machine body through 5 self-plugging rivets to form a longitudinal stress framework.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the concept of the present invention, and these improvements and decorations should also be considered as within the protection scope of the present invention.

Claims

1. A landing gear strut longitudinal beam structure comprises a web plate, a No. 1 upper edge strip, a No. 2 upper edge strip, a No. 1 lower edge strip, a No. 2 lower edge strip, a right front corner box, a left front corner box, a No. 1 rib, a No. 2 rib, a No. 3 connecting angle material, a No. 4 connecting angle material, a No. 3 rib, a No. 4 rib, a No. 5 rib, a No. 6 rib, a right rear corner box and a left rear corner box, and is characterized in that,

the right front corner box, the left front corner box, the right rear corner box and the left rear corner box are respectively arranged at the front end and the rear end of the web.

2. The landing gear strut longitudinal beam structure as claimed in claim 1, wherein the web is formed by stamping a sheet metal with a thickness of 1.2mm, and 3 circular lightening holes are formed in the web.

3. The landing gear strut longitudinal beam structure of claim 1, wherein the # 1 upper bead, the # 2 upper bead, the # 1 lower bead, the # 2 lower bead, the # 1 rib, the # 2 rib, the # 3 connecting angle bar, the # 4 connecting angle bar, the # 3 rib, the # 4 rib, the # 5 rib and the # 6 rib are all L-shaped sheet metal parts.

4. The landing gear strut longitudinal beam structure as claimed in claim 1, wherein the right and left front corner boxes are machined from 7050-T7451 aluminium alloy, and reinforcing ribs are provided in the corner boxes.