CN112027053A - Framework structure of frame beam of middle fuselage of airplane - Google Patents
Framework structure of frame beam of middle fuselage of airplane Download PDFInfo
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- CN112027053A CN112027053A CN202010946899.1A CN202010946899A CN112027053A CN 112027053 A CN112027053 A CN 112027053A CN 202010946899 A CN202010946899 A CN 202010946899A CN 112027053 A CN112027053 A CN 112027053A
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- fuselage
- frame
- longitudinal beam
- reinforcing frame
- ribs
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 70
- 239000000654 additive Substances 0.000 claims description 3
- 230000000996 additive effect Effects 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 abstract 4
- 238000010276 construction Methods 0.000 abstract 2
- 230000005540 biological transmission Effects 0.000 description 8
- 239000000463 material Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
Images
Classifications
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
Abstract
The application belongs to the technical field of the design of frame beam skeleton construction of fuselage in the aircraft, concretely relates to fuselage frame beam skeleton construction in aircraft, include: the two fuselage reinforcing frames are oppositely arranged; two longitudinal beams of the fuselage, set up oppositely; every fuselage longitudinal beam and two fuselage strengthening frames intersect, integrated into one piece, the cross-section at the crossing position of fuselage longitudinal beam and fuselage strengthening frame is the cross, does not have the disconnection position on fuselage longitudinal beam, the fuselage strengthening frame, passes the load continuous, is difficult to take place fatigue damage, need not set up a large amount of structures, part auxiliary connection, and weight is lighter, and designs fuselage longitudinal beam and fuselage strengthening frame integrated into one piece, passes the load by the plane before and becomes three-dimensional and passes the load, and the structure rigidity improves.
Description
Technical Field
The application belongs to the technical field of design of frame beam framework structures of middle airframes of airplanes, and particularly relates to a frame beam framework structure of a middle airframe of an airplane.
Background
The frame beam framework of the middle fuselage of the airplane is an important bearing structure on the airplane and mainly comprises two oppositely arranged fuselage reinforcing frames and two oppositely arranged longitudinal fuselage beams, at present, all parts of the framework are processed and manufactured respectively and are spliced together, in order to facilitate the splicing among all the parts, two fuselage reinforcing frames or two longitudinal fuselage beams are disconnected, corresponding lower limits are arranged at the disconnected parts, structures such as flanges are connected through corner boxes and fasteners, the frame beam framework of the middle fuselage of the airplane in the form, the fuselage reinforcing frames or two longitudinal fuselage beams have a plurality of disconnected parts, the load transmission at each disconnected part is discontinuous, fatigue damage is easy to occur, a large number of structures and parts are required to be arranged for auxiliary connection, the structure is complicated, the splicing is difficult, and the weight is large.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present patent application.
Disclosure of Invention
It is an object of the present application to provide an aircraft midbody frame beam skeletal structure that overcomes or alleviates at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
an aircraft midbody frame beam skeletal structure, comprising:
the two fuselage reinforcing frames are oppositely arranged;
two longitudinal beams of the fuselage, set up oppositely; each fuselage longitudinal beam is intersected with the two fuselage reinforcing frames and integrally formed.
According to at least one embodiment of the application, in the framework structure of the frame beam of the middle fuselage of the airplane, two reinforcing frames of the fuselage and two longitudinal beams of the fuselage are manufactured by an additive manufacturing technology.
According to at least one embodiment of the application, in the framework structure of the frame beam of the middle fuselage of the airplane, each fuselage reinforcing frame is provided with a plurality of transverse reinforcing frame ribs; each transverse reinforcing frame rib is intersected with the two fuselage reinforcing frames.
According to at least one embodiment of the application, in the framework structure of the frame beam of the middle fuselage of the airplane, each fuselage reinforcing frame is provided with a plurality of vertical reinforcing frame ribs; each vertical reinforcing frame rib is intersected with each transverse reinforcing frame rib.
According to at least one embodiment of the application, in the framework structure of the frame beams of the middle fuselage of the airplane, each longitudinal beam of the fuselage is provided with a plurality of transverse longitudinal beam ribs; each transverse longitudinal beam rib extends to a fuselage reinforcing frame and intersects the fuselage reinforcing frame.
According to at least one embodiment of the application, in the framework structure of the frame beams of the middle fuselage of the airplane, each longitudinal beam of the fuselage is provided with a plurality of vertical longitudinal beam ribs; part of the vertical longitudinal beam ribs intersect with the plurality of transverse longitudinal beam ribs.
The application has at least the following beneficial technical effects:
the cross section of the crossed part of the longitudinal beam of the airplane body and the reinforcing frame of the airplane body is cross-shaped, no disconnected part exists on the longitudinal beam of the airplane body and the reinforcing frame of the airplane body, the load transmission is continuous, the fatigue damage is not easy to occur, a large number of structures are not needed to be arranged, the parts are connected in an auxiliary mode, the weight is light, the longitudinal beam of the airplane body and the reinforcing frame of the airplane body are designed to be integrally formed, the plane load transmission is changed into three-dimensional load transmission, and the integral rigidity of the structure is improved.
Drawings
FIG. 1 is a schematic illustration of a frame-beam skeletal structure of an aircraft fuselage provided in an embodiment of the present application;
wherein:
1-a fuselage reinforcing frame; 2-fuselage longitudinal beams; 3-transverse reinforcing frame ribs; 4-vertical reinforced frame
Ribs; 5-transverse longitudinal beam ribs; 6-vertical longitudinal beam ribs.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1.
An aircraft midbody frame beam skeletal structure, comprising:
the two fuselage reinforcing frames 1 are oppositely arranged;
two longitudinal fuselage beams 2 arranged oppositely; each fuselage longitudinal beam 2 is intersected with the two fuselage reinforcing frames 1 and integrally formed.
For the framework structure of the frame beam of the middle fuselage of the airplane disclosed in the above embodiments, it can be understood by those skilled in the art that the longitudinal beam 2 of the fuselage and the reinforcing frame 1 of the fuselage are designed to be integrally formed, and it can be understood that the cross section of the intersection of the longitudinal beam 2 of the fuselage and the reinforcing frame 1 of the fuselage is cross-shaped.
For the frame beam skeleton structure of the middle fuselage of the airplane disclosed by the embodiment, a person skilled in the art can also understand that the longitudinal beam 2 of the fuselage and the reinforcing frame 1 of the fuselage are designed to be integrally formed, no disconnected part exists on the longitudinal beam 2 of the fuselage and the reinforcing frame 1 of the fuselage, the load transmission is continuous, the fatigue damage is not easy to occur, a large number of structures and parts do not need to be arranged for auxiliary connection, and the weight is light.
For the framework structure of the frame beam of the middle fuselage of the airplane disclosed in the above embodiments, it can be understood by those skilled in the art that the longitudinal beam 2 of the fuselage and the reinforcing frame 1 of the fuselage are designed to be integrally formed, and the whole rigidity of the structure is improved by changing the previous plane load transmission into three-dimensional load transmission.
In some alternative embodiments, in the above-described framework structure of the frame beams of the middle fuselage of the aircraft, the two fuselage reinforcing frames 1 and the two longitudinal fuselage beams 2 are manufactured by additive manufacturing techniques.
For the framework structure of the frame beam of the middle fuselage of the airplane disclosed in the above embodiment, those skilled in the art can understand that the two fuselage reinforcing frames 1 and the two fuselage longitudinal beams 2 can be manufactured by a 3D printing technology, and the laser, the electron beam and the electric arc are used as heat sources, and the metal powder material and the metal wire material are used as raw materials, and are directly melted and deposited layer by layer according to a design model, and finally are grown to form an integral structure.
In some alternative embodiments, in the above-mentioned framework structure of the frame beam of the middle fuselage of the airplane, each reinforcing frame 1 of the fuselage has a plurality of transverse reinforcing frame ribs 3; each transverse reinforcing frame rib 3 intersects two fuselage reinforcing frames 1.
With regard to the framework structure of the frame beam of the middle fuselage of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the transverse reinforcing frame ribs 3 extend substantially in the vertical direction of the fuselage reinforcing frame 1, and the rigidity of the fuselage reinforcing frame 1 can be greatly enhanced by arranging the fuselage reinforcing frame 1 with a plurality of transverse reinforcing frame ribs 3.
For the frame beam skeleton structure of the middle fuselage of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the cross section of the intersection of the transverse reinforcing frame ribs 3 and the fuselage reinforcing frame 1 is cross-shaped, and is an integrally formed structure, and no disconnection occurs, so that the continuity of load transfer can be ensured.
In some alternative embodiments, in the above-mentioned framework structure of the frame beam of the middle fuselage of the airplane, each fuselage reinforcing frame 1 is provided with a plurality of vertical reinforcing frame ribs 4; each vertical reinforcing frame rib 4 intersects each transverse reinforcing frame rib 3.
For the framework structure of the frame beam of the middle fuselage of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the vertical reinforcing frame ribs 4 extend substantially in the vertical direction of the transverse reinforcing frame ribs 3, and the rigidity of the fuselage reinforcing frame 1 can be greatly enhanced by arranging the fuselage reinforcing frame 1 with the plurality of vertical reinforcing frame ribs 4.
For the frame beam skeleton structure of the middle fuselage of an airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the cross section of the intersection of the transverse reinforcing frame ribs 3 and the vertical reinforcing frame ribs 4 is cross-shaped, and is an integrally formed structure, and no disconnection occurs, so that the continuity of load transmission can be ensured.
In some alternative embodiments, in the above-mentioned framework structure of frame beams of the middle fuselage of an aircraft, each longitudinal fuselage beam 2 has a plurality of transverse longitudinal beam ribs 5; each transverse longitudinal beam rib 5 extends to one fuselage reinforcing frame 1, intersecting the fuselage reinforcing frame 1.
With regard to the framework structure of the frame beam of the middle fuselage of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the transverse longitudinal beam ribs 5 extend substantially in the vertical direction of the fuselage reinforcing frame 1, and the rigidity of the longitudinal fuselage beam 2 can be greatly enhanced by arranging the plurality of transverse longitudinal beam ribs 5 on the longitudinal fuselage beam 2.
For the frame-beam framework structure of the middle fuselage of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the cross section of the intersection of the transverse longitudinal beam rib 5 and the fuselage reinforcing frame 1 is cross-shaped, and is an integrally formed structure, and no disconnection occurs, so that the continuity of load transfer can be ensured.
In some alternative embodiments, in the above-mentioned framework structure of frame beams of the middle fuselage of an aircraft, each longitudinal fuselage beam 2 has a plurality of vertical longitudinal beam ribs 6; part of the vertical longitudinal beam ribs 6 intersects the plurality of transverse longitudinal beam ribs 5.
With regard to the framework structure of the frame beam of the middle fuselage of the airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the vertical longitudinal beam ribs 6 extend substantially in the vertical direction of the transverse longitudinal beam ribs 5, and the provision of the plurality of vertical longitudinal beam ribs 6 on the longitudinal fuselage beam 2 can greatly enhance the rigidity of the longitudinal fuselage beam 2.
For the frame-beam framework structure of the middle fuselage of an airplane disclosed in the above embodiment, it can be understood by those skilled in the art that the cross section of the intersection of the transverse longitudinal beam rib 5 and the vertical longitudinal beam rib 6 is cross-shaped, and is an integrally formed structure, and no disconnection occurs, so that the continuity of load transfer can be ensured.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (6)
1. An aircraft midbody frame beam skeletal structure, comprising:
two fuselage reinforcing frames (1) which are oppositely arranged;
two longitudinal fuselage beams (2) arranged oppositely; each longitudinal beam (2) of the machine body is intersected with the two reinforcing frames (1) of the machine body and is integrally formed.
2. An aircraft midbody frame beam skeleton structure according to claim 1,
the two fuselage reinforcing frames (1) and the two fuselage longitudinal beams (2) are manufactured by an additive manufacturing technology.
3. An aircraft midbody frame beam skeleton structure according to claim 1,
each fuselage reinforcing frame (1) is provided with a plurality of transverse reinforcing frame ribs (3); each transverse reinforcing frame rib (3) is intersected with the two fuselage reinforcing frames (1).
4. An aircraft midbody frame beam skeleton structure according to claim 3,
each fuselage reinforcing frame (1) is provided with a plurality of vertical reinforcing frame ribs (4); each vertical reinforcing frame rib (4) is intersected with each transverse reinforcing frame rib (3).
5. An aircraft midbody frame beam skeleton structure according to claim 1,
each longitudinal beam (2) of the fuselage is provided with a plurality of transverse longitudinal beam ribs (5); each transverse longitudinal beam rib (5) extends to one fuselage reinforcing frame (1) and is intersected with the fuselage reinforcing frame (1).
6. An aircraft midbody frame beam skeleton structure according to claim 5,
each longitudinal beam (2) of the fuselage is provided with a plurality of vertical longitudinal beam ribs (6); part of the vertical longitudinal beam ribs (6) are intersected with the plurality of transverse longitudinal beam ribs (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010946899.1A CN112027053A (en) | 2020-09-10 | 2020-09-10 | Framework structure of frame beam of middle fuselage of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010946899.1A CN112027053A (en) | 2020-09-10 | 2020-09-10 | Framework structure of frame beam of middle fuselage of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112027053A true CN112027053A (en) | 2020-12-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010946899.1A Pending CN112027053A (en) | 2020-09-10 | 2020-09-10 | Framework structure of frame beam of middle fuselage of airplane |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB620863A (en) * | 1947-01-27 | 1949-03-31 | Henrique Emil Mendelssohn | Improvements in or relating to aircraft |
| US6536710B1 (en) * | 2002-02-06 | 2003-03-25 | The Boeing Company | Overhead lattice support structure |
| US20120001023A1 (en) * | 2010-06-30 | 2012-01-05 | Airbus Operations, S.L. | Aircraft fuselage made out with composite material and manufacturing processes |
| US20140186572A1 (en) * | 2012-12-28 | 2014-07-03 | Airbus Operations S. L. | Aircraft structure with integrated reinforcing elements |
| CN109131825A (en) * | 2018-09-21 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft forebody integral frame structure |
| CN109131824A (en) * | 2018-09-21 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft reinforcing frame and vertical fin girder construction |
-
2020
- 2020-09-10 CN CN202010946899.1A patent/CN112027053A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB620863A (en) * | 1947-01-27 | 1949-03-31 | Henrique Emil Mendelssohn | Improvements in or relating to aircraft |
| US6536710B1 (en) * | 2002-02-06 | 2003-03-25 | The Boeing Company | Overhead lattice support structure |
| US20120001023A1 (en) * | 2010-06-30 | 2012-01-05 | Airbus Operations, S.L. | Aircraft fuselage made out with composite material and manufacturing processes |
| US20140186572A1 (en) * | 2012-12-28 | 2014-07-03 | Airbus Operations S. L. | Aircraft structure with integrated reinforcing elements |
| CN109131825A (en) * | 2018-09-21 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft forebody integral frame structure |
| CN109131824A (en) * | 2018-09-21 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft reinforcing frame and vertical fin girder construction |
Non-Patent Citations (1)
| Title |
|---|
| 王向明等: "增材技术在飞机结构研制中的应用", 《航空制造技术》 * |
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Application publication date: 20201204 |
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