CN111017188A - Aircraft floor longeron course passes carries structure - Google Patents
Aircraft floor longeron course passes carries structure Download PDFInfo
- Publication number
- CN111017188A CN111017188A CN201911346469.XA CN201911346469A CN111017188A CN 111017188 A CN111017188 A CN 111017188A CN 201911346469 A CN201911346469 A CN 201911346469A CN 111017188 A CN111017188 A CN 111017188A
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- China
- Prior art keywords
- floor
- stringer
- diagonal draw
- course
- aircraft
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 230000005540 biological transmission Effects 0.000 description 6
- 238000005452 bending Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 230000000087 stabilizing effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/18—Floors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Rod-Shaped Construction Members (AREA)
Abstract
The invention discloses a course load transfer structure of an airplane floor longitudinal beam, which comprises floor cross beams, floor longitudinal beams, upright posts, diagonal draw bars, a common frame and a stringer, wherein the two floor cross beams, the floor longitudinal beams, the two upright posts, the two common frames and the stringer form a quadrilateral structure, the two diagonal draw bars are respectively hinged with two opposite angles of the quadrilateral structure, and the middle part of one of the two diagonal draw bars is provided with a lower limit, so that the other diagonal draw bar [4] is fixedly connected on the lower limit.
Description
Technical Field
The invention belongs to the field of airplane structure design, and particularly relates to an airplane floor longitudinal beam course load transferring structure.
Background
The front and the back of a floor longitudinal beam on an airplane are generally not provided with effective load transmission structures, the self course bearing capacity is poor, and course load needs to be diffused to an airplane body structure so as to ensure that the floor longitudinal beam is not damaged when being loaded. The course load of the existing airplane floor longitudinal beam is mostly transmitted through the side part of the airplane body, the load transmission path is far, the efficiency is low, and the course load is transmitted to the lower part of the airplane body generally in a fixed connection mode, so that the structure is complex and the weight is heavy. The invention aims to spread the course load of the floor longitudinal beam to the lower structure of the fuselage. The large height difference exists between the floor longitudinal beams and the lower part of the fuselage, additional bending moment is easy to generate when load is transmitted to the lower part structure of the fuselage in parallel, the complexity of the lower part bearing structure of the fuselage is increased, and the structure weight is increased. Therefore, when load transmission is required, force transmission is directly carried out, the path is short, the efficiency is high, the structure is simple and reliable, additional bending moment is not generated, and the arrangement of the original structure is further influenced.
Disclosure of Invention
The purpose of the invention is as follows: the aircraft floor longitudinal beam course load transferring structure can ensure that the floor longitudinal beam course load can be transferred to a lower part structure of an aircraft body, avoids the generation of additional bending moment on the lower part of the aircraft body, simplifies the load transferring form and the structural complexity, shortens a force transferring path, lightens the structural weight of the aircraft, improves the reliability and the safety, and reduces the structural design cost.
The technical scheme of the invention is as follows:
the utility model provides an aircraft floor longeron course passes carries structure, includes floor crossbeam, floor longeron, stand, diagonal draw bar, ordinary frame, stringer, two floor crossbeams, floor longeron, two stands, two ordinary frames and stringer constitution quadrangle, two diagonal draw bars articulate respectively two diagonal angles of quadrangle, a middle part design in two diagonal draw bars has the lower limit, makes another diagonal draw bar [4] fixed connection in the lower limit on.
The bottom surfaces of the common frame and the stringer are fixed on the skin.
The two diagonal draw bars are respectively hinged with two opposite angles of the quadrilateral structure through bolts.
The cross section of the floor beam is J-shaped.
The cross section of the floor longitudinal beam is J-shaped.
The two ends of the diagonal draw bar are provided with holes for single ear belts.
The sections of the common frame and the stringer are Z-shaped, connecting holes are formed in the common frame, and two ends of the stringer are respectively fixed to the connecting holes of the two common frames.
The vertical surface of the floor longitudinal beam and the vertical surface of the long girder are positioned on the same plane.
The invention has the beneficial effects that: compared with the traditional fixed connecting structure, the invention simplifies the stress condition of the floor longitudinal beam structure and the connecting structure of the airplane, shortens the force transmission path, and ensures that the floor longitudinal beam, the floor cross beam, the common frame, the stringers, the upright post and the diagonal draw bars form a plurality of stable triangular structures, the course load of the floor longitudinal beam is transmitted to the stringers through the diagonal draw bars and finally converted into the shearing force on the skin at the lower part of the airplane body, and the vertical component force of the axial force of the diagonal draw bars is borne through the upright post and the frame structure. The formation of a plurality of triangular stabilizing structures and the application that the diagonal draw bars only bear axial load enable the aircraft floor longitudinal beam course load transfer structure to have high efficiency, good manufacturability, light weight, low cost and easy production and assembly.
Drawings
FIG. 1 is a schematic structural view of the present invention;
the floor comprises 1-floor cross beams, 2-floor longitudinal beams, 3-upright columns, 4-diagonal draw bars, 5-common frames, 6-stringers and 7-skin.
Detailed Description
The invention is further described by combining the accompanying drawings, and the aircraft floor longitudinal beam course load transfer structure comprises a floor cross beam 1, a floor longitudinal beam 2, upright posts 3, diagonal draw bars 4, a common frame 5 and a stringer 6, wherein the two floor cross beams 1, the floor longitudinal beam 2, the two upright posts 3, the two common frames 5 and the stringer 6 form a quadrilateral structure, the two diagonal draw bars 4 are respectively hinged with two opposite corners of the quadrilateral structure, two ends of each diagonal draw bar 4 are provided with a single lug belt hole, a middle part of each diagonal draw bar 4 is provided with a lower limit, the other diagonal draw bar 4 is fixedly connected to the lower limit, the quadrilateral structure is divided into a plurality of triangular structures by the two diagonal draw bars 4, and the diagonal draw bars 4 bear axial loads. .
The bottom surfaces of the common frames 5 and the bottom surfaces of the stringers 6 are fixed on the skin 7, and the vertical surfaces of the floor longitudinal beams 2 and the vertical surfaces of the stringers 6 are located on the same plane.
And the two diagonal draw bars 4 are respectively hinged with two opposite angles of the quadrilateral structure through bolts.
The cross section of the floor beam 1 is J-shaped, and the cross section of the floor longitudinal beam 2 is J-shaped; the sections of the common frame 5 and the long purlin 6 are Z-shaped, connecting holes are formed in the common frame 6, and two ends of the long purlin 6 are respectively fixed to the connecting holes of the two common frames 5.
The upper end of the upright post 3 is fixedly connected with the floor beam 1 and the floor longitudinal beam 2 through bolts, and the lower end is fixedly connected with the common frame 6. The course load of the floor longitudinal beam 2 is converted into the axial force on the diagonal draw bar 4, the vertical component force of the axial force of the diagonal draw bar 4 is diffused to the upright post 3, and the horizontal component force is transmitted to the stringer 6 and finally diffused to the skin 7.
The invention simplifies the stress condition of the floor longitudinal beam structure and the connecting structure of the airplane, shortens the force transmission path, leads the floor longitudinal beam 2, the floor cross beam 1, the common frame 5, the long trusses 6, the upright post 3 and the diagonal draw bars 3 to form a plurality of stable triangular structures, transfers the course load of the floor longitudinal beam 2 to the long trusses 6 through the diagonal draw bars 4, and finally converts the course load into the shearing force on the skin 7 at the lower part of the airplane body, and the vertical component force of the axial force of the diagonal draw bars 4 is born through the upright post 3 and the frame structure. The formation of a plurality of triangular stabilizing structures and the application that the diagonal draw bars 4 only bear axial load enable the course load-transferring structure of the airplane floor longitudinal beam 2 to have high efficiency, good manufacturability, light weight, low cost and easy production and assembly.
Claims (8)
1. The utility model provides an aircraft floor longeron course passes carries structure which characterized in that: the floor comprises floor cross beams (1), floor longitudinal beams (2), upright posts (3), diagonal draw bars (4), common frames (5) and stringers (6); the method is characterized in that: the floor structure is characterized in that a quadrilateral structure is formed by two floor crossbeams (1), floor longitudinal beams (2), two upright columns (3), two common frames (5) and a stringer (6), the two diagonal draw bars (4) are respectively hinged to two opposite angles of the quadrilateral structure, a lower limit is designed in the middle of each of the two diagonal draw bars (4), and the other diagonal draw bar (4) is fixedly connected to the lower limit.
2. The aircraft floor stringer course carrying structure of claim 1, wherein: the bottom surfaces of the common frame (5) and the stringer (6) are fixed on the skin (7).
3. The aircraft floor stringer course carrying structure of claim 1, wherein: the two diagonal draw bars (4) are respectively hinged with two opposite angles of the quadrilateral structure through bolts.
4. The aircraft floor stringer course carrying structure of claim 1, wherein: the cross section of the floor beam (1) is J-shaped.
5. The aircraft floor stringer course carrying structure of claim 1, wherein: the cross section of the floor longitudinal beam (2) is J-shaped.
6. The aircraft floor stringer course carrying structure of claim 1, wherein: the two ends of the diagonal draw bar (4) are provided with holes for single ear belts.
7. The aircraft floor stringer course carrying structure of claim 1, wherein: the sections of the common frame (5) and the stringer (6) are Z-shaped, connecting holes are formed in the common frame (5), and two ends of the stringer (6) are respectively fixed to the connecting holes of the two common frames (5).
8. The aircraft floor stringer course carrying structure of claim 1, wherein: the vertical surface of the floor longitudinal beam (2) and the vertical surface of the stringer (6) are positioned on the same plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346469.XA CN111017188A (en) | 2019-12-24 | 2019-12-24 | Aircraft floor longeron course passes carries structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911346469.XA CN111017188A (en) | 2019-12-24 | 2019-12-24 | Aircraft floor longeron course passes carries structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111017188A true CN111017188A (en) | 2020-04-17 |
Family
ID=70212986
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911346469.XA Pending CN111017188A (en) | 2019-12-24 | 2019-12-24 | Aircraft floor longeron course passes carries structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111017188A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101074029A (en) * | 2007-06-14 | 2007-11-21 | 侯久荣 | Total-bearing cased coach body |
| CN101432190A (en) * | 2006-04-25 | 2009-05-13 | 空中客车德国有限公司 | Floor structure for a fuselage |
| CN101952167A (en) * | 2008-02-07 | 2011-01-19 | 空中客车运营有限公司 | Floor system for a fuselage section of an aircraft |
| US20130092793A1 (en) * | 2010-04-09 | 2013-04-18 | Premium Aerotec Gmbh | Aircraft, and fastening arrangement for a floor structure in an aircraft |
| CN103318265A (en) * | 2013-06-27 | 2013-09-25 | 长城汽车股份有限公司 | Rear force transmission structure of automobile |
| CN109606619A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of cargo deck stringer posting structure |
-
2019
- 2019-12-24 CN CN201911346469.XA patent/CN111017188A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101432190A (en) * | 2006-04-25 | 2009-05-13 | 空中客车德国有限公司 | Floor structure for a fuselage |
| CN101074029A (en) * | 2007-06-14 | 2007-11-21 | 侯久荣 | Total-bearing cased coach body |
| CN101952167A (en) * | 2008-02-07 | 2011-01-19 | 空中客车运营有限公司 | Floor system for a fuselage section of an aircraft |
| US20130092793A1 (en) * | 2010-04-09 | 2013-04-18 | Premium Aerotec Gmbh | Aircraft, and fastening arrangement for a floor structure in an aircraft |
| CN103318265A (en) * | 2013-06-27 | 2013-09-25 | 长城汽车股份有限公司 | Rear force transmission structure of automobile |
| CN109606619A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of cargo deck stringer posting structure |
Non-Patent Citations (1)
| Title |
|---|
| 张卫文等: "飞机地板常用结构设计与传力分析", 《中国科技信息》 * |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200417 |