CN107128475B - Flat composite pressure bulkhead - Google Patents
Flat composite pressure bulkhead Download PDFInfo
- Publication number
- CN107128475B CN107128475B CN201710324550.2A CN201710324550A CN107128475B CN 107128475 B CN107128475 B CN 107128475B CN 201710324550 A CN201710324550 A CN 201710324550A CN 107128475 B CN107128475 B CN 107128475B
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- frame
- bearing side
- web
- pressure
- machine body
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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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Laminated Bodies (AREA)
- Tents Or Canopies (AREA)
Abstract
A flat composite pressure bulkhead belongs to the technical field of aircraft design. The machine comprises a machine body frame and a flat web connected with the machine body frame, wherein the two sides of the web are a pressure-bearing side and a non-pressure-bearing side respectively, longitudinal ribs are uniformly arranged on the pressure-bearing side web at intervals, transverse ribs are uniformly arranged on the non-pressure-bearing side web at intervals, and the transverse ribs and the longitudinal ribs are mutually perpendicular; when the installation is carried out, the longitudinal reinforcing ribs of the pressure-bearing side web plates are arranged in the vertical direction, and the transverse reinforcing ribs on the non-pressure-bearing side web plates are arranged in the horizontal direction. The invention can reduce the space occupied by the pressure bulkhead, lighten the weight and reduce the design and manufacturing cost. The machine body frame is formed by connecting a plurality of C-shaped machine body frame sections, so that the machine body frame is convenient to install and maintain; the frame outer edge strip of the fuselage on the non-bearing side is higher than the frame inner edge strip, and reinforcing rib plates are uniformly arranged between the frame inner edge strip and the frame outer edge strip, so that the strength is improved.
Description
Technical Field
The invention belongs to the technical field of aircraft design, and particularly relates to a flat composite pressure bulkhead.
Background
The body of the civil airliner is divided into a booster zone and a non-booster zone. The pressure bulkhead is used for separating the pressurizing area from the non-pressurizing area at the tail part of the machine body, and the pressure bulkhead can bear pressurizing load generated by pressurizing and ensure the air tightness of the pressurizing area. In the existing design, the pressure bulkhead is usually of a hemispherical metal structure, and the pressure bulkhead of the structure occupies large space and has large weight, and the design of the joint with the machine body has more difficulties.
Disclosure of Invention
Aiming at the technical problems, the invention provides the flat composite pressure bulkhead, which utilizes the advantages of high strength, high rigidity, low density and good corrosion resistance of the composite material, and designs the traditional hemispherical pressure bulkhead with a metal structure into a composite flat plate type, so that the occupied space of the pressure bulkhead can be reduced, the weight is reduced, and the design and manufacturing cost is reduced.
The aim of the invention is realized by the following technical scheme:
the flat composite material pressure bulkhead comprises a fuselage frame and a flat web connected with the fuselage frame, wherein the two sides of the web are a pressure-bearing side and a non-pressure-bearing side respectively, longitudinal ribs are uniformly arranged on the pressure-bearing side web at intervals, transverse ribs are uniformly arranged on the non-pressure-bearing side web at intervals, and the transverse ribs and the longitudinal ribs are mutually perpendicular; when the installation is carried out, the longitudinal reinforcing ribs of the pressure-bearing side web plates are arranged in the vertical direction, and the transverse reinforcing ribs on the non-pressure-bearing side web plates are arranged in the horizontal direction.
Further, the fuselage frame is formed by connecting a plurality of C-shaped fuselage frame sections, the fuselage frame sections comprise frame inner edge strips and frame outer edge strips, and the height of the frame outer edge strips on the non-bearing side is higher than that of the frame inner edge strips.
Further, the fuselage frame section arranged at the stringer station in the fuselage frame is uniformly provided with reinforcing rib plates between the frame inner edge strips and the frame outer edge strips.
Further, two adjacent frame sections of the frame are connected through corner pieces, the butt joint frame inner edge strips of the frame at the non-bearing side are connected through corner pieces II, the butt joint frame outer edge strips are connected through corner pieces III, and the corner pieces II and the corner pieces III are of corner structures and are respectively matched with the connected frame inner edge strips or frame outer edge strips; the fuselage frame on the bearing side is connected through the corner piece IV, and the corner piece IV is a structure which is matched and connected with the fuselage frame on the bearing side and the web plate and is used for connecting the fuselage frame and the web plate.
Further, a partition board I is arranged on the bearing side of the fuselage frame, the connecting end of the partition board I is matched with the web plate of the bearing side and the fuselage frame, the other end of the partition board I is connected with the stringer, and the outer edge of the partition board I is connected with the fuselage skin; the non-bearing side is also provided with a partition plate II, one end of the partition plate II is connected with the frame of the machine body in a matched mode, the other end of the partition plate II is used for connecting the stringers of the non-bearing area, and the outer edge of the partition plate II is connected with the skin of the machine body.
Further, the baffle I is groove type frame structure, wholly is trapezoidal, and one end is the rectangle groove, and the long limit of rectangle groove is one end open-ended dovetail groove base, and the minor face top is open angle type groove, the open end and the stringer of dovetail groove are connected.
Further, the connecting end of the partition plate II and the stringer is an open trapezoid groove, and the open end is connected with the stringer.
Further, the transverse rib and the longitudinal rib on the web are identical in structure, the cross section is formed by filling a sandwich layer in a trapezoid groove structure with an outer extension edge, the outer extension edge is connected with the web, and the sandwich layer is in a honeycomb or foam filling structure.
Further, the web is a carbon fiber laminate structure.
The beneficial effects of the invention are as follows:
1. the invention adopts a flat plate type web plate structure, longitudinal ribs are uniformly arranged at intervals on the pressure-bearing sides of the two sides of the web plate, transverse ribs are uniformly arranged at intervals on the non-pressure-bearing sides, and the transverse ribs and the longitudinal ribs are mutually perpendicular; when in installation, the longitudinal ribs are arranged in the vertical direction. The section of each rib is formed by filling a sandwich layer in a trapezoid groove structure with an outer extension edge, and the sandwich layer is in a honeycomb or foam filling structure, so that the occupied space of the pressure bulkhead can be reduced, the weight is reduced, and the design and manufacturing cost is reduced.
2. The machine body frame is formed by connecting a plurality of C-shaped machine body frame sections, so that the machine body frame is convenient to install and maintain; the frame outer edge strip of the fuselage on the non-bearing side is higher than the frame inner edge strip, and reinforcing rib plates are uniformly arranged between the frame inner edge strip and the frame outer edge strip, so that the strength is improved.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is a front view of the pressure-bearing side of fig. 1.
Fig. 3 is a rear view of fig. 2.
Fig. 4 is a cross-sectional view of the longitudinal ribbing of fig. 2.
FIG. 5 is a schematic view showing a partial structure of the non-pressure-bearing-side reinforcing partition I of the present invention.
Fig. 6 is a schematic view of a partial structure of a pressure-bearing side reinforcing partition plate ii according to the present invention.
Fig. 7 is a schematic view of the frame section of the fuselage of fig. 1.
Fig. 8 is a schematic cross-sectional view of the reinforcing rib of fig. 7.
Fig. 9 is an enlarged view of the connection between two adjacent frames on the non-pressure-bearing side in fig. 1.
Fig. 10 is a schematic view of the connecting gusset II of fig. 9.
Fig. 11 is a schematic view of the connecting corner piece iii of fig. 9.
Fig. 12 is an enlarged view of the connection between two adjacent frames on the bearing side in fig. 1.
Fig. 13 is a schematic view of the connecting gusset iv of fig. 12.
Fig. 14 is a schematic cross-sectional view of a fuselage frame.
In the figure: 1. the frame comprises a web plate, a frame body, a frame inner edge strip, a frame outer edge strip, a reinforcing partition plate I, a rectangular groove 32, a long edge, a short edge, a reinforcing partition plate II, a rectangular opening groove 41, a plate 42, corner pieces I, 6, corner pieces II, 7, corner pieces III, 8, corner pieces IV, 9, a sandwich layer, 10, longitudinal ribs, 11, transverse ribs, 12, reinforcing ribs and 13.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
Example 1: as shown in fig. 1-3, the flat composite pressure bulkhead comprises a fuselage frame 2 and a flat web 1 connected with the fuselage frame 2, wherein the two sides of the web 1 are respectively a pressure-bearing side and a non-pressure-bearing side, longitudinal ribs 10 are uniformly arranged on the pressure-bearing side web 1 at intervals, transverse ribs 11 are uniformly arranged on the non-pressure-bearing side web 1 at intervals, and the transverse ribs 11 and the longitudinal ribs 10 are mutually perpendicular; when the non-pressure-bearing side web plate is installed, the longitudinal ribs 10 of the pressure-bearing side web plate 1 are arranged in the vertical direction, and the transverse ribs 11 on the non-pressure-bearing side web plate 1 are arranged in the horizontal direction.
As shown in fig. 1, 7 and 8, the frame 2 is formed by connecting a plurality of C-shaped frame sections, and the frame sections are divided into an inner frame edge strip 21 and an outer frame edge strip 22, and the height of the outer frame edge strip 22 on the non-bearing side is higher than that of the inner frame edge strip 21. Reinforcing rib plates 12 are uniformly arranged between frame inner edge strips 21 and frame outer edge strips 22 of a frame section of the fuselage, which are arranged at the stringer station, of the fuselage frame 2.
As shown in fig. 9-13, two adjacent frame sections of the frame 2 are connected by a corner piece, the butt joint frame inner edge strip 21 of the non-bearing side frame 2 is connected by a corner piece ii 6, the butt joint frame outer edge strip 22 is connected by a corner piece iii 7, the corner piece ii 6 and the corner piece iii 7 are both in a corner structure, and are respectively matched with the connected frame inner edge strip 21 or frame outer edge strip 22; the fuselage frame 2 on the bearing side is connected through the corner pieces IV 8, and the corner pieces IV 8 are structures which are matched and connected with the fuselage frame 2 on the bearing side and the web plate 1 and are used for connecting the fuselage frame 2 and the web plate 1; the air tightness of the pressurizing area is ensured.
As shown in fig. 5, 6 and 14, the bearing side of the frame 2 is further provided with a partition board i 3, the connecting end of the partition board i 3 is installed in cooperation with the web 1 on the bearing side and the frame 2, and the other end is connected with the stringer; the baffle I3 is groove type frame structure, wholly is trapezium, and one end is rectangular groove 31, and the long limit 32 of rectangular groove 31 is one end open-ended dovetail groove base, and the minor face 33 top is open angle type groove, during the installation, the open end and the stringer of booster zone of dovetail groove are connected, and the outer fringe limit and the fuselage skin of dovetail groove's open end both sides are connected.
As shown in fig. 6 and 14, the non-bearing side of the frame 2 is further provided with a partition plate ii 4, the connection end of the partition plate ii 4 and the stringer is an open trapezoid slot 41, the open end is connected with the stringer, and the other end is a structure matched with the frame 2: the frame inner edge strip 21 is connected to the frame 2 of the machine body through the corner piece I5 and is matched with the reinforcing rib plate 12 through the plate 42; during installation, the notch at the other end of the partition plate II 4 is connected with the stringers in the non-bearing area, and two outer edges of the notch of the partition plate II 4 are connected with the fuselage skin.
As shown in fig. 4, the transverse ribs 11 and the longitudinal ribs 10 on the web plate 1 have the same structure, the cross section is formed by filling a sandwich layer 9 in a trapezoid groove structure with an outer extension edge, the outer extension edge is connected with the web plate 1, and the sandwich layer 9 is in a honeycomb or foam filling structure; the web 1 is a carbon fiber laminate.
The air tightness of the invention: the air tightness of the connection area of the frame body 2 and the web plate 1 is realized by the connection of the frame body 2 and the web plate 1 by the fastening piece. The air tightness of the abutting area of the adjacent sections of the frame 2 mainly considers the air tightness guarantee of the abutting gap parts of the two abutting frame sections, one part of the abutting gap is covered by the web surface, the other part of the abutting gap is covered by the abutting web corner piece I5 of the frame sections, and the abutting gap is connected by a fastener, so that the sealing is realized.
Load transfer of the present invention: when the cabin is pressurized, most of the pressurized load is borne by the web plate 1, and the load is transmitted to the frame 2 through the connection between the web plate 1 and the frame 2, and the frame 2 diffuses the load into the adjacent structure through the reinforced partition plates I3 and II 4 at two sides.
Because the reinforcing ribs and the reinforcing partition plates of the fuselage frame 2 are arranged at the stringer station, the stringer load transmission can be realized through the partition plates I3-the fuselage frame 2-the partition plates II 4, and the load transmission continuity is realized.
The load of the frame 2 of the machine body is transferred by the frame butt joint inner and outer edge strip corner pieces II 6, III 7, IV 8 and the frame section butt joint web corner piece I5 of the machine body.
Claims (1)
1. The utility model provides a dull and stereotyped combined material pressure bulkhead which characterized in that: the machine comprises a machine body frame and a flat web connected with the machine body frame, wherein the two sides of the web are a pressure-bearing side and a non-pressure-bearing side respectively, longitudinal ribs are uniformly arranged on the pressure-bearing side web at intervals, transverse ribs are uniformly arranged on the non-pressure-bearing side web at intervals, and the transverse ribs and the longitudinal ribs are mutually perpendicular; when the device is installed, the longitudinal ribs of the pressure-bearing side web plates are arranged in the vertical direction, and the transverse ribs on the non-pressure-bearing side web plates are arranged in the horizontal direction;
the machine body frame is formed by connecting a plurality of C-shaped machine body frame sections, the machine body frame sections comprise frame inner edge strips and frame outer edge strips, and the height of the frame outer edge strips on the non-bearing side is higher than that of the frame inner edge strips;
the frame section of the fuselage, which is arranged at the stringer station, in the fuselage frame is uniformly provided with reinforcing rib plates between the frame inner edge strips and the frame outer edge strips;
the two adjacent frame sections of the frame are connected through corner pieces, the butt joint frame inner edge strips of the frame at the non-bearing side are connected through corner pieces II, the butt joint frame outer edge strips are connected through corner pieces III, and the corner pieces II and the corner pieces III are of corner structures and are respectively matched with the connected frame inner edge strips or frame outer edge strips; the fuselage frame on the bearing side is connected through a corner piece IV, and the corner piece IV is a structure which is matched and connected with the fuselage frame on the bearing side and the web plate and is used for connecting the fuselage frame and the web plate;
the connecting end of the partition board I is matched with the web plate of the bearing side and the fuselage frame, the other end of the partition board I is connected with the stringer, and the outer edge of the partition board I is connected with the fuselage skin; the non-bearing side is also provided with a partition plate II, one end of the partition plate II is connected with the frame of the machine body in a matched mode, the other end of the partition plate II is used for connecting the stringers of the non-bearing area, and the outer edge of the partition plate II is connected with the skin of the machine body;
the partition board I is of a groove type frame structure, the whole partition board I is trapezoid, one end of the partition board I is a rectangular groove, the long side of the rectangular groove is the bottom edge of the trapezoid groove with one end open, the upper part of the short side of the rectangular groove is an open angle type groove, and the open end of the trapezoid groove is connected with the stringer;
the connecting end of the partition plate II and the stringer is an open trapezoid groove, and the open end is connected with the stringer;
the transverse rib and the longitudinal rib on the web are identical in structure, the cross section of the web is formed by filling a sandwich layer in a trapezoid groove structure with an outer extension edge, the outer extension edge is connected with the web, and the sandwich layer is in a honeycomb or foam filling structure;
the web is a carbon fiber laminate structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710324550.2A CN107128475B (en) | 2017-05-10 | 2017-05-10 | Flat composite pressure bulkhead |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710324550.2A CN107128475B (en) | 2017-05-10 | 2017-05-10 | Flat composite pressure bulkhead |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107128475A CN107128475A (en) | 2017-09-05 |
| CN107128475B true CN107128475B (en) | 2023-08-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710324550.2A Active CN107128475B (en) | 2017-05-10 | 2017-05-10 | Flat composite pressure bulkhead |
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| CN (1) | CN107128475B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131824B (en) * | 2018-09-21 | 2022-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane reinforcing frame and vertical tail beam structure |
| CN109131825B (en) * | 2018-09-21 | 2022-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Integral frame structure of front fuselage of airplane |
| CN110920858B (en) * | 2019-12-09 | 2024-01-23 | 中航沈飞民用飞机有限责任公司 | Detachable firewall of compact passenger plane and application method thereof |
| CN112895520A (en) * | 2021-01-15 | 2021-06-04 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Airplane control surface composite material bidirectional reinforcing structure and forming method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6213426B1 (en) * | 1999-07-09 | 2001-04-10 | The Boeing Company | Monolithic structure with redundant load paths |
| CN205675218U (en) * | 2016-06-13 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fuselage and sphere frame docking structure |
| CN205906193U (en) * | 2016-07-22 | 2017-01-25 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft area muscle combined material sphere frame structure |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2959479B1 (en) * | 2010-04-30 | 2012-06-15 | Eads Europ Aeronautic Defence | AIRCRAFT FUSELAGE STRUCTURE COMPRISING AN ENERGY ABSORBER DEVICE |
| EP2532581B1 (en) * | 2011-06-10 | 2013-05-08 | EUROCOPTER DEUTSCHLAND GmbH | T-profile junction of composite materials |
-
2017
- 2017-05-10 CN CN201710324550.2A patent/CN107128475B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6213426B1 (en) * | 1999-07-09 | 2001-04-10 | The Boeing Company | Monolithic structure with redundant load paths |
| CN205675218U (en) * | 2016-06-13 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of fuselage and sphere frame docking structure |
| CN205906193U (en) * | 2016-07-22 | 2017-01-25 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft area muscle combined material sphere frame structure |
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| Publication number | Publication date |
|---|---|
| CN107128475A (en) | 2017-09-05 |
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