CN206856971U - A kind of plate composite pressure bulkhead - Google Patents
A kind of plate composite pressure bulkhead Download PDFInfo
- Publication number
- CN206856971U CN206856971U CN201720512460.1U CN201720512460U CN206856971U CN 206856971 U CN206856971 U CN 206856971U CN 201720512460 U CN201720512460 U CN 201720512460U CN 206856971 U CN206856971 U CN 206856971U
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- Prior art keywords
- pressure
- plate
- frame
- fuselage frame
- fuselage
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- 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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Abstract
A kind of plate composite pressure bulkhead, belongs to airplane design technical field.The plate web connected including fuselage frame with fuselage frame, the web both sides are respectively pressure-bearing side and non-pressure side, uniform intervals are provided with longitudinal sinew adding strip on pressure-bearing coxostermum, uniform intervals are provided with transversal reinforcement bar on non-pressure coxostermum, and the transversal reinforcement bar and longitudinal sinew adding strip are mutually perpendicular to；During installation, longitudinal sinew adding strip of pressure-bearing coxostermum arranges that the transversal reinforcement bar on non-pressure coxostermum is arranged in horizontal direction in vertical direction.The utility model can reduce pressure bulkhead and be taken up space, and mitigate weight, reduce design and manufacture cost.Fuselage frame of the present utility model is connected and composed by multiple c-type fuselage frame sections, convenient installation and maintenance；The fuselage circle outer edge strip of non-pressure side is higher than inframe edge strip, and stiffener plate is uniformly arranged between inframe edge strip and outer frame edge strip, increases intensity.
Description
Technical field
The invention belongs to airplane design technical field, more particularly to a kind of plate composite pressure bulkhead.
Background technology
The body of seating plane is divided into anallobar and unpressurized area.In afterbody, will be typically pressurized by pressure bulkhead
Area separates with unpressurized area, and this pressure bulkhead can bear supercharging and produce supercharging load, ensure the air-tightness of anallobar.Existing
Having in design, pressure bulkhead is usually the metal structure of dome-type, and the pressure bulkhead of this structure takes up space, and big, weight is big,
It is more with fuselage junction design difficulty.
The content of the invention
For above-mentioned technical problem, the present invention provides a kind of plate composite pressure bulkhead, and utilization is compound
The advantages of strength of materials is high, rigidity is high, density is low, good corrosion resistance, traditional metal structure dome-type pressure bulkhead is designed
Into composite material flat plate type, it is possible to reduce pressure bulkhead is taken up space, and mitigates weight, reduces design and manufacture cost.
The purpose of the present invention is achieved through the following technical solutions：
A kind of plate composite pressure bulkhead, including the plate web that fuselage frame connects with fuselage frame, it is described
Web both sides are respectively pressure-bearing side and non-pressure side, and uniform intervals are provided with longitudinal sinew adding strip, non-pressure side on pressure-bearing coxostermum
Uniform intervals are provided with transversal reinforcement bar on web, and the transversal reinforcement bar and longitudinal sinew adding strip are mutually perpendicular to；During installation, pressure-bearing
Longitudinal sinew adding strip of coxostermum arranges that the transversal reinforcement bar on non-pressure coxostermum is arranged in horizontal direction in vertical direction.
Further, the fuselage frame is connected and composed by multiple c-type fuselage frame sections, and the fuselage frame section includes inframe edge strip
With outer frame edge strip, the outer frame edge strip of non-pressure side is highly higher than inframe edge strip height.
Further, the fuselage frame section being installed in the fuselage frame at stringer erect-position, in its inframe edge strip and outer frame edge
Stiffener plate is uniformly arranged between bar.
Further, the adjacent two fuselages frame of the fuselage frame is intersegmental is connected and composed by cornual plate, non-pressure side fuselage frame
Interface frame, mating frame in edge strip connected by cornual plate II, interface frame, mating frame outer edge strip is connected by cornual plate III, and cornual plate II and cornual plate III are angle
Type structure, coordinate respectively with the inframe edge strip or outer frame edge strip being connected；The fuselage frame of pressure-bearing side is connected by cornual plate IV, cornual plate IV
For the structure in mating connection with pressure-bearing side fuselage frame and web, for connecting fuselage frame and web.
Further, the pressure-bearing side of the fuselage frame is additionally provided with dividing plate I, connection end and the pressure-bearing side of the dividing plate I
Web and fuselage frame coordinate installation, and the other end is connected with stringer, and the exterior rim of dividing plate I is connected with fuselage skin；Non-pressure side is also set
It is equipped with dividing plate II, the one end fits of dividing plate II connect fuselage frame, and the other end is used for the stringer for connecting non-pressure area, outside dividing plate II
Rim is connected with fuselage skin.
Further, the dividing plate I is groove profile frame structure, overall trapezoidal, and one end is rectangular channel, the long side of rectangular channel
For the dovetail groove base of one end open, short side top is angular aperture type groove, and the openend of the dovetail groove is connected with stringer.
Further, the dividing plate II and stringer connection end are open trapezoid groove, and openend connects stringer.
Further, the transversal reinforcement bar on the web is identical with longitudinal sinew adding strip structure, and section is with extension
Filling laminboard layer is formed in the trapezoid groove structure on side, and the extension side connects web, and the laminboard layer is that honeycomb or foam are filled out
Fill structure.
Further, the web is Carbon fiber laminated board structure.
Beneficial effects of the present invention are：
1. the present invention uses plate web structure, and the pressure-bearing side uniform intervals in web both sides set longitudinal reinforcement
Bar, non-pressure side uniform intervals set transversal reinforcement bar, and transversal reinforcement bar and longitudinal sinew adding strip are mutually perpendicular to；During installation, longitudinal direction
Sinew adding strip is arranged in vertical direction.Sinew adding strip section is to fill laminboard layer in the trapezoid groove structure with extension side to form, folder
Sandwich layer is honeycomb or foam-filled structure, it is possible to reduce pressure bulkhead is taken up space, and mitigates weight, and reduction is designed and manufactured into
This.
2. the fuselage frame of the present invention is connected and composed by multiple c-type fuselage frame sections, convenient installation and maintenance；The machine of non-pressure side
Body circle outer edge strip is higher than inframe edge strip, and stiffener plate is uniformly arranged between inframe edge strip and outer frame edge strip, increases intensity.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram of the present invention.
Fig. 2 is Fig. 1 pressure-bearing side front view.
Fig. 3 is Fig. 2 rearview.
Fig. 4 is Fig. 2 A-A sectional views.
Fig. 5 is the enlarged diagram that dividing plate I is strengthened in non-pressure side in Fig. 1.
Fig. 6 is the enlarged diagram that dividing plate II is strengthened in pressure-bearing side in Fig. 1.
Fig. 7 is the structural representation of Fig. 1 middle fuselage frame sections.
Fig. 8 is the schematic cross-section of strengthening rib strip in Fig. 7.
Fig. 9 is the connection enlarged diagram of the adjacent two fuselages frame in non-pressure side in Fig. 1.
Figure 10 is that the schematic diagram of cornual plate I is connected in Fig. 9.
Figure 11 is that the schematic diagram of cornual plate II is connected in Fig. 9.
Figure 12 is the connection enlarged diagram of the adjacent two fuselages frame in pressure-bearing side in Fig. 1.
Figure 13 is Figure 12 schematic diagram of connection cornual plate III.
Figure 14 is fuselage frame schematic cross-section.
In figure：1. web, 2. fuselage frames, 21. inframe edge strips, 22. outer frame edge strips, 3. reinforcement dividing plates I, 31. rectangular channels,
32. long side, 33. short sides, 4. reinforcement dividing plates II, 41. open trapezoid grooves, 42. plates, 5. cornual plates I, 6. cornual plates II, 7. cornual plates III, 8.
Cornual plate IV, 9. laminboard layers, 10. longitudinal sinew adding strips, 11. transversal reinforcement bars, 12. stiffener plates, 13. prolong side.
Embodiment
The present invention will be described in detail with reference to the accompanying drawings and examples.
Embodiment 1：As Figure 1-3, a kind of plate composite pressure bulkhead of the present invention, including fuselage frame 2 and with
The plate web 1 that fuselage frame 2 connects, the both sides of web 1 are respectively pressure-bearing side and non-pressure side, on pressure-bearing coxostermum 1
Even to be arranged at intervals with longitudinal sinew adding strip 10, uniform intervals are provided with transversal reinforcement bar 11 on non-pressure coxostermum 1, and the transverse direction adds
Rib 11 and longitudinal sinew adding strip 10 are mutually perpendicular to；During installation, longitudinal sinew adding strip 10 of pressure-bearing coxostermum 1 is arranged in vertical direction,
Transversal reinforcement bar 11 on non-pressure coxostermum 1 is arranged in horizontal direction.
As shown in Fig. 1, Fig. 7, Fig. 8, the fuselage frame 2 is connected and composed by multiple c-type fuselage frame sections, the fuselage frame section point
For inframe edge strip 21 and outer frame edge strip 22, the height of outer frame edge strip 22 of non-pressure side is higher than the height of inframe edge strip 21.In fuselage frame 2
Stiffener plate 12 is uniformly arranged between the inframe edge strip 21 and outer frame edge strip 22 of the fuselage frame section being installed at stringer erect-position.
As shown in Fig. 9-Figure 13, the adjacent two fuselages frame of the fuselage frame 2 is intersegmental to be connected and composed by cornual plate, non-pressure side
Edge strip 21 is connected by cornual plate II 6 in the interface frame, mating frame of fuselage frame 2, and interface frame, mating frame outer edge strip 22 is connected by cornual plate III 7, cornual plate II 6
It is corner-shape structure with cornual plate III 7, coordinates respectively with the inframe edge strip 21 or outer frame edge strip 22 being connected；The fuselage frame 2 of pressure-bearing side
Connected by cornual plate IV 8, cornual plate IV 8 is the structure in mating connection with pressure-bearing side fuselage frame 2 and web 1, for connecting fuselage
Frame 2 and web 1；Ensure the air-tightness of anallobar.
As shown in Fig. 5, Fig. 6, Figure 14, the pressure-bearing side of the fuselage frame 2 is additionally provided with dividing plate I 3, the connection of the dividing plate I 3
The web 1 and fuselage frame 2 of end and pressure-bearing side, which coordinate, to be installed, and the other end is connected with stringer；The dividing plate I 3 is groove profile frame structure,
Overall trapezoidal, one end is rectangular channel 31, and the long side 32 of rectangular channel 31 is the dovetail groove base of one end open, and the top of short side 33 is
Angular aperture type groove, during installation, the openend of the dovetail groove and the stringer of anallobar connect, the openend both sides of dovetail groove it is outer
Rim is connected with fuselage skin.
As shown in Fig. 6, Figure 14, the non-pressure side of the fuselage frame 2 is additionally provided with dividing plate II 4, the dividing plate II 4 and stringer
Connection end is open trapezoid groove 41, and openend connection stringer, the other end is the structure coordinated with fuselage frame 2：Connected by cornual plate I 5
The inframe edge strip 21 of fuselage frame 2 is connected on, is coordinated by plate 42 and stiffener plate 12；During installation, the other end notch of dividing plate II 4 with it is non-
The stringer connection of confined area, two exterior rims of the notch of dividing plate II 4 are connected with fuselage skin.
As shown in figure 4, the transversal reinforcement bar 11 on the web 1 is identical with longitudinal structure of sinew adding strip 10, section is band
There is filling laminboard layer 9 in the trapezoid groove structure on extension side to form, the extension side connects web 1, the laminboard layer 9 be honeycomb or
The foam-filled structure of person；The web 1 is Carbon fiber laminated board.
The air-tightness of the present invention：Fuselage frame 2 and the air-tightness of the bonding pad of web 1, by the fastening of fuselage frame 2 and web 1
Sealing is realized in part connection.The air-tightness in the adjacent segment of fuselage frame 2 docking region mainly considers the fuselage frame section butt seam of two docking
Partial airtight guarantee, a butt seam part are covered by web surface, and another part docks web cornual plate I 5 by fuselage frame section and covered
Lid, and connected by fastener, so as to realize sealing.
The load transmission of the present invention：When being pressurized in fuselage compartment, overwhelming majority supercharging load is born by web 1, this part
Load is transferred on fuselage frame 2 by the connection of web 1 and fuselage frame 2, fuselage frame 2 by the reinforcement dividing plate I 3 with both sides and
Strengthen dividing plate II 4, load is diffused in neighbouring structure.
Because the reinforcement and reinforcement dividing plate of fuselage frame 2 are arranged at stringer erect-position, so stringer load transmission can
To be transmitted by the 3- fuselage frame 2- dividing plates II 4 of dividing plate I, load transmission continuity is realized.
The load of fuselage frame 2 is by outer edge strip cornual plate II 6, cornual plate III 7, cornual plate IV 8 and fuselage frame section docking abdomen in frame docking
Plate angle piece I 5 realizes the transmission of load.
Claims (9)
- A kind of 1. plate composite pressure bulkhead, it is characterised in that：The plate abdomen connected including fuselage frame with fuselage frame Plate, the web both sides are respectively pressure-bearing side and non-pressure side, and uniform intervals are provided with longitudinal sinew adding strip on pressure-bearing coxostermum, non- Uniform intervals are provided with transversal reinforcement bar on pressure-bearing coxostermum, and the transversal reinforcement bar and longitudinal sinew adding strip are mutually perpendicular to.
- 2. plate composite pressure bulkhead according to claim 1, it is characterised in that：The fuselage frame is by multiple c-types Fuselage frame section connects and composes, and the fuselage frame section includes inframe edge strip and outer frame edge strip, and the outer frame edge strip height of non-pressure side is high In inframe edge strip height.
- 3. plate composite pressure bulkhead according to claim 2, it is characterised in that：Length is installed in the fuselage frame Fuselage frame section at the erect-position of purlin, stiffener plate is uniformly arranged between its inframe edge strip and outer frame edge strip.
- 4. plate composite pressure bulkhead according to claim 2, it is characterised in that：Adjacent two machine of the fuselage frame Body frame is intersegmental to be connected and composed by cornual plate, and edge strip is connected by cornual plate II in the interface frame, mating frame of non-pressure side fuselage frame, outside interface frame, mating frame Edge strip is connected by cornual plate III, and cornual plate II and cornual plate III are corner-shape structure, respectively the inframe edge strip or outer frame edge strip with being connected Coordinate；The fuselage frame of pressure-bearing side is connected by cornual plate IV, and cornual plate IV is the knot in mating connection with pressure-bearing side fuselage frame and web Structure, for connecting fuselage frame and web.
- 5. plate composite pressure bulkhead according to claim 2, it is characterised in that：The pressure-bearing side of the fuselage frame is also Dividing plate I is provided with, the connection end of the dividing plate I coordinates with the web of pressure-bearing side and fuselage frame is installed, and the other end is connected with stringer, The exterior rim of dividing plate I is connected with fuselage skin；Non-pressure side is additionally provided with dividing plate II, and the one end fits of dividing plate II connect fuselage Frame, the other end are used for the stringer for connecting non-pressure area, and the exterior rim of dividing plate II is connected with fuselage skin.
- 6. plate composite pressure bulkhead according to claim 5, it is characterised in that：The dividing plate I is groove profile framework Structure, overall trapezoidal, one end is rectangular channel, and the long side of rectangular channel is the dovetail groove base of one end open, is to open above short side Bicker type groove, the openend of the dovetail groove are connected with stringer.
- 7. plate composite pressure bulkhead according to claim 5, it is characterised in that：The dividing plate II is connected with stringer Hold as open trapezoid groove, openend connection stringer.
- 8. plate composite pressure bulkhead according to claim 1, it is characterised in that：Transversal reinforcement on the web Bar is identical with longitudinal sinew adding strip structure, and section is to fill laminboard layer in the trapezoid groove structure with extension side to form, described outer Prolong side connection web, the laminboard layer is honeycomb or foam-filled structure.
- 9. plate composite pressure bulkhead according to claim 1, it is characterised in that：The web is laminated for carbon fiber Harden structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720512460.1U CN206856971U (en) | 2017-05-10 | 2017-05-10 | A kind of plate composite pressure bulkhead |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720512460.1U CN206856971U (en) | 2017-05-10 | 2017-05-10 | A kind of plate composite pressure bulkhead |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206856971U true CN206856971U (en) | 2018-01-09 |
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ID=60822246
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720512460.1U Expired - Fee Related CN206856971U (en) | 2017-05-10 | 2017-05-10 | A kind of plate composite pressure bulkhead |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206856971U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112193399A (en) * | 2020-11-17 | 2021-01-08 | 中航通飞华南飞机工业有限公司 | Spherical airtight end frame with large opening |
-
2017
- 2017-05-10 CN CN201720512460.1U patent/CN206856971U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112193399A (en) * | 2020-11-17 | 2021-01-08 | 中航通飞华南飞机工业有限公司 | Spherical airtight end frame with large opening |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180109 Termination date: 20190510 |
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| CF01 | Termination of patent right due to non-payment of annual fee |