CN117550109A - Aircraft and rear fuselage structure thereof - Google Patents
Aircraft and rear fuselage structure thereof Download PDFInfo
- Publication number
- CN117550109A CN117550109A CN202311831138.1A CN202311831138A CN117550109A CN 117550109 A CN117550109 A CN 117550109A CN 202311831138 A CN202311831138 A CN 202311831138A CN 117550109 A CN117550109 A CN 117550109A
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- Prior art keywords
- reinforcing frame
- girder
- cross beam
- fuselage structure
- 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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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 69
- 238000005452 bending Methods 0.000 claims abstract description 20
- 230000002787 reinforcement Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 5
- 229910000838 Al alloy Inorganic materials 0.000 abstract description 4
- 238000005260 corrosion Methods 0.000 abstract description 3
- 230000007797 corrosion Effects 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 description 14
- 230000005540 biological transmission Effects 0.000 description 10
- 238000012546 transfer Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- ZCDOYSPFYFSLEW-UHFFFAOYSA-N chromate(2-) Chemical compound [O-][Cr]([O-])(=O)=O ZCDOYSPFYFSLEW-UHFFFAOYSA-N 0.000 description 1
- KRVSOGSZCMJSLX-UHFFFAOYSA-L chromic acid Substances O[Cr](O)(=O)=O KRVSOGSZCMJSLX-UHFFFAOYSA-L 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- AWJWCTOOIBYHON-UHFFFAOYSA-N furo[3,4-b]pyrazine-5,7-dione Chemical compound C1=CN=C2C(=O)OC(=O)C2=N1 AWJWCTOOIBYHON-UHFFFAOYSA-N 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/70—Constructional aspects of the UAV body
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention discloses an aircraft and a rear aircraft body structure thereof, which are structures capable of transmitting external bending moment of a reinforcing frame surface at a large opening of the aircraft, all parts adopt 7050-T7451 aluminum alloy integral machine addition type, the process is mature, a cross beam in the structure can bear the external bending moment of the reinforcing frame surface, the other parts can transmit longitudinal load of the aircraft body, and the structure can meet the requirement of opening a large opening cover on the aircraft body. Meanwhile, the structure has strong load carrying capacity, light structure weight, simple assembly, corrosion resistance and good manufacturability and feasibility by using common standard components.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft and a rear fuselage structure thereof.
Background
The aft fuselage structure of an aircraft is positioned at the aft-most end of the fuselage structure and is typically a semi-monocoque structure formed by the combination of transverse formers, longitudinal stringers or beams, and their skins. The general need to arrange retractable landing gear and engines in the rear fuselage requires the design of large opening structures in the rear fuselage structure for retraction of the landing gear and maintenance of the engines.
The placement of large openings in the aircraft structure can affect the stiffness and strength of the structure and the transfer of loads. The aircraft fuselage structure mainly transmits load through a transverse framework and a longitudinal framework, wherein the transverse framework is a reinforcing frame, and the longitudinal framework is a girder. The reinforcing frame can only bear in-plane load and cannot bear out-of-plane load, so that the girder for transmitting longitudinal load needs to be continuous at the reinforcing frame.
However, in the area where the large opening cover is required, continuity of the girder cannot be ensured, and it is necessary to design a structure capable of transmitting the load outside the reinforcing frame surface at the large opening of the structure.
Disclosure of Invention
In view of the above, the invention provides an aircraft and a rear fuselage structure thereof, which solve the problem that the reinforcing frame at the large opening of the aircraft structure cannot transmit out-of-plane bending moment.
In order to achieve the above purpose, the present invention provides the following technical solutions:
a rear fuselage structure comprising: the cross beam, the reinforcing frame, the left rear girder, the right rear girder and the front girder;
the reinforcing frame is respectively connected with the left rear girder and the right rear girder, the cross beam is connected with the reinforcing frame, and the cross beam is connected with the front girder.
Preferably, the cross beam is a hollow structure that can withstand bending moments.
Preferably, two ends of the cross beam are connected with the web plate of the reinforcing frame.
Preferably, the inner webs at the two ends of the cross beam are connected to the webs of the reinforcing frame through bolts.
Preferably, the middle section of the cross beam is connected to the rear section of the front girder.
Preferably, the middle web of the cross beam is connected to the rear web of the front girder through bolts.
Preferably, the outer webs at the two ends of the cross beam are respectively connected to the front ends of the left rear girder and the right rear girder through bolts.
Preferably, ribs are arranged between the front web plate and the rear web plate of the cross beam.
Preferably, the method further comprises: a front skin;
the front skin is connected with the beam outer edge strip of the beam, and the front skin is connected with the front edge strip of the reinforcing frame.
An aircraft comprising a rear fuselage structure as described above.
According to the technical scheme, the invention provides an airplane and a rear airplane body structure thereof, which are in a structure form capable of transmitting bending moment outside a reinforcing frame surface at a large opening of the airplane, and the structure comprises a cross beam, a reinforcing frame, a left rear girder, a right rear girder, a left rear skin, a right rear skin, a front girder, a front skin, a maintenance flap, a plurality of connecting bolts, drawing nails and rivets.
The front girder and the front skin are positioned at the lowest end of the main landing gear cabin in front of the reinforcing frame, and enough space is reserved on two sides of the main landing gear cabin for retraction of the main landing gear, so that a large opening structure is formed.
The left rear girder, the right rear girder, the left rear skin, the right rear skin and the maintenance cover are positioned at the rear of the reinforcing frame, the left rear girder, the right rear girder, the left rear skin and the right rear skin are positioned at the two sides of the cabin section, the maintenance cover is positioned below the cabin section, and the maintenance cover provides a channel for daily maintenance of the engine and accessories thereof, so that a large-opening structure is also formed.
The longitudinal load of the engine transmitted to the left rear girder and the right rear girder cannot be directly transmitted to the front girder after being transmitted to the reinforcing frame, a cross beam is required to be added between the reinforcing frame and the front girder, and the cross beam can transmit the longitudinal load of the left rear girder and the right rear girder to the front girder, so that the transmission of the longitudinal load at the reinforcing frame is realized.
The invention relates to a structure capable of transmitting the external bending moment of a reinforcing frame surface at a large opening of an airplane, all parts adopt 7050-T7451 aluminum alloy integral machine-added type, the process is mature, a cross beam in the structure can bear the external bending moment of the reinforcing frame, other parts can transmit the longitudinal load of the airplane body, and the structure can meet the requirement of opening a large opening cover on the airplane body. Meanwhile, the structure has strong load carrying capacity, light structure weight, simple assembly, corrosion resistance and good manufacturability and feasibility by using common standard components.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a structural component of the present invention for transmitting bending moment out of the reinforcing frame face at a large opening of an aircraft;
FIG. 2 is a structural skeleton structure of the present invention for transmitting bending moment outside the reinforcing frame surface at the large opening of an aircraft;
FIG. 3 is a specific structural form of the cross beam in the present invention;
FIG. 4 is a schematic view of the bolt hole structure of the beam as a whole in accordance with the present invention;
FIG. 5 is a schematic view of the bolting configuration of the left side of the beam of the present invention;
FIG. 6 is a schematic view of the bolting configuration of the midsection of the beam of the present invention;
fig. 7 is a schematic diagram of a bolting structure of the left rear girder and the reinforcing frame rib of the present invention.
The device comprises a 1-cross beam, a 2-reinforcing frame, a 3-left rear girder, a 4-right rear girder, a 5-left rear skin, a 6-right rear skin, a 7-front girder, an 8-front skin and a 9-maintenance cover.
Detailed Description
The large opening problem of reinforcing frame department in the aircraft structure is solved, and the structure capable of transmitting the external bending moment of the reinforcing frame face at the large opening of the aircraft is adopted for not only realizing the transmission of the external load of the reinforcing frame department, but also realizing the arrangement of the large opening cover at the reinforcing frame department so as to meet the overall requirements.
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The rear fuselage structure provided by the embodiment of the invention comprises: the cross beam 1, the reinforcing frame 2, the left rear girder 3, the right rear girder 4 and the front girder 7 can be shown by referring to fig. 1 and 2;
wherein, the reinforcing frame 2 is connected with the left rear girder 3 and the right rear girder 4 respectively, the cross beam 1 is connected with the reinforcing frame 2, and the cross beam 1 is connected with the front girder 7.
The load transmission path of the scheme is as follows: after the longitudinal load is transferred to the reinforcing frame 2 through the left rear girder 3 and the right rear girder 4, the reinforcing frame 2 transfers the longitudinal load to the cross beam 1, and the cross beam 1 transfers the longitudinal load to the front girder 7, so that the transfer of the longitudinal load at the reinforcing frame 2 is completed.
Furthermore, the cross beam 1 is a key load transmission part in the structure and is a hollow structure capable of bearing bending moment, so that the problem that the reinforcing frame at the large opening of the aircraft structure cannot transmit out-of-plane bending moment is solved better.
Preferably, the two ends of the cross beam 1 are connected with the web plates of the reinforcing frame 2 so as to optimize the load transmission path and facilitate the transmission of longitudinal loads from the left and right sides.
Specifically, the inner webs 102 at both ends of the cross beam 1 are connected to the webs of the reinforcing frame 2 by bolts, and the structure thereof can be shown with reference to fig. 3 and 4. In this embodiment, the inner webs 102 at the ends of the cross beam are bolted to the web of the reinforcing frame 2 using 12 high lock bolts, such as bolts 1-6 of FIG. 5 (only the left side is shown).
Preferably, the middle section of the cross beam 1 is connected to the rear section of the front girder 7, so that the longitudinal loads on both sides can be collected to the centrally arranged front girder 7.
Specifically, the beam middle web 103 of the beam 1 is connected to the rear end web of the front girder 7 by bolts, and the structure thereof can be shown with reference to fig. 3 and 4. In this embodiment, the rear end web of the front girder 7 is connected to the beam middle web 103 by 15 high lock bolts, see fig. 5 bolts 1-15.
Further, both left and right ends of the cross member 1 are connected to the front ends of the left and right rear girders 3 and 4, respectively. Preferably by bolting, the construction of which can be seen in figures 3 and 4, the front ends of the left and right rear girders 3, 4 are each bolted to the outer webs 101 at both ends of the cross beam using 3 high lock bolts.
Specifically, ribs 105 are arranged between the front web plate and the rear web plate of the cross beam 1, so that stability and load transfer capacity are improved.
The rear fuselage structure provided by the embodiment of the invention further comprises: a front skin 8, the structure of which can be seen with reference to fig. 1;
the front skin 8 is connected to the beam outer edge strips 106 of the beam 1, as shown in fig. 3; the front skin 8 is connected to the front edge strip of the stiffening frame 2.
The embodiment of the invention also provides an aircraft, which comprises the rear fuselage structure.
The manufacturing and assembling processes and the load transmission path of the structure capable of transmitting the external bending moment of the reinforcing frame surface at the large opening of the airplane are described in detail below with reference to the accompanying drawings.
Referring to fig. 1, the invention is a structural form capable of transmitting bending moment outside a reinforcing frame surface at a large opening of an airplane, and comprises a cross beam 1, a reinforcing frame 2, a left rear girder 3, a right rear girder 4, a left rear skin 5, a right rear skin 6, a front girder 7, a front skin 8, a maintenance flap 9, a plurality of connecting bolts, drawing nails, supporting plate nuts and rivets.
The two ends of the cross beam 1 in the structure are connected with the web plates of the reinforcing frame 2, the middle section of the cross beam 1 is connected with the rear section of the front girder 57, and the left rear girder 3, the right rear girder 4 and the reinforcing frame 2 are connected to form a framework component. The front skin 8 is connected with the cross beam 1, the front edge strip of the reinforcing frame 2 and the front girder 7, and the left rear skin 5, the right rear skin 6 are connected with the rear edge strip of the reinforcing frame 2, the left rear girder 3 and the right rear girder 4, so that a non-detachable structure is formed. The maintenance flap 9 is connected with the rear edge strip of the reinforcing frame 2, the left rear girder 3 and the right rear girder 4, so as to form a detachable maintenance flap.
All parts in the structure except for a maintenance cover 9 are all 7050-T7451 aluminum alloy integral machined parts, and the maintenance cover 9 is of a carbon fiber composite sandwich structure. For corrosion control, all aluminum alloy parts were chromic acid anodized and chromate blocked, and finally coated with a TB06-9 strontia yellow primer.
The structure assembly method is as follows:
first, the skeleton structure is assembled. The reinforcing frame 2 is arranged on an assembly type frame, and inner webs 102 at two ends of the cross beam are connected to the webs of the reinforcing frame 2 by 12 high-locking bolts, see bolts 1-6 (only the left side is shown) in fig. 5; the rear end web plate of the front girder 7 is connected to the middle web plate 103 of the cross girder through 15 high locking bolts, see bolts 1-15 in fig. 6; finally, the front ends of the left rear girder 3 and the right rear girder 4 are respectively connected to the web plate of the reinforcing frame 2 and the outer web plates 101 at the two ends of the cross beam by using 3 high locking bolts, and the web plates of the left rear girder 3 and the right rear girder 4 are respectively connected to the ribs of the reinforcing frame 2 by using 3 high locking bolts, see bolts 1-6 (only the left side is shown) of fig. 6, so that the framework assembly is assembled.
The skin is then assembled on the basis of the carcass assembly to form the non-detachable structure. The front skin 8 is connected with the front edge strip of the reinforcing frame 2 through rivets, the front skin 8 is connected with the beam outer edge strip 106 through the rivets, the front skin 8 is connected with the front edge strip of the reinforcing frame 2 and the beam outer edge strip 106 through 8 high-locking bolts, and finally the front skin 8 is connected with the front edge strip of the reinforcing frame 2 through drawing nails. And then the left rear skin 5 and the right rear skin 6 are connected with the rear edge strips of the reinforcing frame 2, the left rear girder 3 and the right rear girder 4 through rivets, so that a non-detachable structure is formed.
Finally, the maintenance flap 9 is assembled on the non-removable structure to form a unitary structure. And the maintenance cover 9 is connected with the rear edge strip of the reinforcing frame 2, the left rear girder 3 and the right rear girder 4 through support plate nuts and countersunk bolts, so that the assembly of the structure is completed.
The load transmission path of the structure capable of transmitting the external bending moment of the reinforcing frame surface at the large opening of the airplane is as follows: after the longitudinal load is transferred to the reinforcing frame 2 through the left rear girder 3 and the right rear girder 4, the reinforcing frame 2 transfers the longitudinal load to the cross beam 1, and the cross beam 1 transfers the longitudinal load to the front girder 7, so that the transfer of the longitudinal load at the reinforcing frame 2 is completed. The beam 1 is a key load-carrying part in the structure and is a hollow structure capable of bearing bending moment. The two ends and the middle of the cross beam 1 are provided with bolt holes, the two ends are connected with the web plate and the edge strip of the reinforcing frame 2, the middle is connected with the front girder 7, and 45 high locking bolts are arranged in total, as shown in fig. 4. The beam 1 can convert longitudinal loads on two sides into bending moments to be transmitted to the middle part, and the ribs 105 between the front web plate and the rear web plate of the beam increase stability and load transmission capacity. The beam web 104 does not need to be connected with the web of the reinforcing frame 2, so that the connection form is simplified.
In summary, the invention aims to provide a structure capable of transmitting the external bending moment of the reinforcing frame surface at the large opening of an airplane, which uses a mature manufacturing process, has the characteristics of light weight, simple connection, simple assembly, reasonable force transmission path and the like, and solves the problem that the reinforcing frame at the large opening of the airplane structure cannot transmit the external bending moment.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A rear fuselage structure comprising: the cross beam (1), the reinforcing frame (2), the left rear girder (3), the right rear girder (4) and the front girder (7);
the reinforcing frame (2) is respectively connected with the left rear girder (3) and the right rear girder (4), the cross beam (1) is connected with the reinforcing frame (2), and the cross beam (1) is connected with the front girder (7).
2. The aft fuselage structure according to claim 1, characterized in that the cross beam (1) is a hollow structure that can withstand bending moments.
3. The aft fuselage structure according to claim 1, characterized in that the two ends of the cross beam (1) are connected to the web of the reinforcing frame (2).
4. The rear fuselage structure according to claim 1, characterized in that the inner webs (102) at both ends of the cross beam (1) are connected to the webs of the reinforcement frame (2) by means of bolts.
5. The rear fuselage structure according to claim 1, characterized in that the middle section of the cross beam (1) is connected to the rear section of the front girder (7).
6. The aft fuselage structure according to claim 1, characterized in that the cross beam midsection web (103) of the cross beam (1) is bolted to the aft end web of the front girder (7).
7. The rear fuselage structure according to claim 1, characterized in that the outer webs (101) at both ends of the cross member (1) are connected to the front ends of the left and right rear girders (3, 4), respectively, by means of bolts.
8. The aft fuselage structure according to claim 1, characterized in that ribs (105) are provided between the front and rear webs of the cross beam (1).
9. The aft fuselage structure of claim 1, further comprising: a front skin (8);
the front skin (8) is connected with a beam outer edge strip (106) of the beam (1), and the front skin (8) is connected with a front edge strip of the reinforcing frame (2).
10. An aircraft comprising a rear fuselage structure as defined in any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311831138.1A CN117550109A (en) | 2023-12-26 | 2023-12-26 | Aircraft and rear fuselage structure thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311831138.1A CN117550109A (en) | 2023-12-26 | 2023-12-26 | Aircraft and rear fuselage structure thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117550109A true CN117550109A (en) | 2024-02-13 |
Family
ID=89823324
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311831138.1A Pending CN117550109A (en) | 2023-12-26 | 2023-12-26 | Aircraft and rear fuselage structure thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117550109A (en) |
-
2023
- 2023-12-26 CN CN202311831138.1A patent/CN117550109A/en active Pending
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