CN203623970U - Composite material integral air intake duct - Google Patents
Composite material integral air intake duct Download PDFInfo
- Publication number
- CN203623970U CN203623970U CN201320800591.1U CN201320800591U CN203623970U CN 203623970 U CN203623970 U CN 203623970U CN 201320800591 U CN201320800591 U CN 201320800591U CN 203623970 U CN203623970 U CN 203623970U
- Authority
- CN
- China
- Prior art keywords
- inlet channel
- air intake
- intake duct
- ring stiffener
- lip
- Prior art date
- 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.)
- Expired - Lifetime
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 20
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 17
- 239000006260 foam Substances 0.000 claims abstract description 13
- 239000003351 stiffener Substances 0.000 claims description 26
- 238000003032 molecular docking Methods 0.000 claims description 23
- 125000004122 cyclic group Chemical group 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 9
- 239000012528 membrane Substances 0.000 claims description 4
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 abstract description 4
- 238000000465 moulding Methods 0.000 abstract description 4
- 239000000835 fiber Substances 0.000 abstract 1
- 210000001503 joint Anatomy 0.000 abstract 1
- 238000000034 method Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
Images
Abstract
The utility model relates to an airplane back embedded type composite material integral moulding double-S-shaped air intake duct, belonging to the field of airplane structure design and relating to an improvement of an air intake duct structure. The air intake duct is a tubular S-shaped structure member formed by an air intake duct sheath 2, circular reinforcing ribs 3, a lip sleeving and butt-joint reinforcing ring 1, a reinforcing ring 4 in butt joint with the rear section of the air intake duct, and sandwiched foam 5. The air intake duct structure is integrally formed by composite materials by means of fiber bundle pavement technology, the circular reinforcing ribs are additionally arranged to enhance the strength and rigidity of the air intake duct structure, the interval between every two adjacent reinforcing ribs L is in the range of 170mm-200mm. The air intake duct structure is applicable to a conventional air intake duct which is small in caliber and is difficult to combine and assemble, and the air intake duct provided is simple in structure, light in weight, easy to assembly, high in size accuracy, and good in aerodynamic configuration, the strength and the rigidity of the air intake duct structure, which can bear large load and is long in service life, can be greatly improved, and the air intake duct provided can be widely applied to the technical field of small and medium-sized military unmanned plane structural design.
Description
technical field:
the invention belongs to aeroplane structure design field, relate to the improvement to airplane intake.
background technology:
It is for aero gas turbine engine provides required charge air that the basic training of airplane intake is used, and makes the high velocity air deceleration supercharging head-on flowing into, to adapt to the flow velocity requirement of engine intake.Therefore Design of Inlet is had higher requirement, the complex contour of airplane intake, dimensional accuracy and inner surface quality require all very high, also higher to the requirement of rigidity, generally adopt the form that metal piecemeal sheet-metal formed recombinant connects or composite material piecemeal moulding recombinant connects now.The form of this piecemeal needs a large amount of attaching partss, also higher to the space requirement connecting, and due to piecemeal, inlet channel inwall has a large amount of opposite joints, the precision of the interior type of inlet channel is difficult to guarantee, for unmanned plane because inlet channel caliber is little, accessibility is poor, if cannot entering inlet channel, inlet channel piecemeal instrument carries out mechanical connection, need to carry out mechanical connection from inlet channel outside, this uses the attaching parts that one side connects in a large number, this increases the weight of inlet channel greatly, and the difficulty of assembling and location is all very large, the interior type that is difficult to meet inlet channel requires to be difficult to meet, the form of this piecemeal also needs a large amount of forming moulds and frock simultaneously, manufacturing cost is larger, and weight is heavier.
summary of the invention:
The object of the invention is: the weak point existing for above-mentioned prior art, provides a kind of and can guarantee aircraft overall performance, strength and stiffness are high, lightweight, inner surface quality is good, dimensional accuracy is high, easy to assembly, the life-span long, can bear the airplane intake of the larger aerodynamic loading of aircraft.
The technical solution adopted for the present invention to solve the technical problems is: a kind of composites inlet channel, its one end and aircraft lip fit, the other end is connected on the fuselage metal flange at inlet channel rear portion, it is characterized in that, it is two serpentine inlet channels, cross section is to be transitioned into gradually circular thin-walled annular structure by square, and by composite material tow lay global formation, it has the ring stiffener of lip fit docking ring stiffener, inlet channel covering, the docking of inlet channel back segment.
Between the ring stiffener that lip fit docking ring stiffener and inlet channel back segment dock, be distributed with 3 cyclic reinforcing ribs 3.The spacing of reinforced rib is L=170mm ~ 200mm.
Lip fit docking ring stiffener matches with the inside face of lip, and its fitting surface is ruled surface.
Not uniform thickness of lip fit docking ring stiffener fitting surface reinforced region, convenient for assembly.
The type of attachment that lip fit docking ring stiffener adopts splicing and high locked bolts to coordinate with lip.
The ring stiffener of inlet channel back segment docking is connected by high locked bolts with inlet channel rear portion metal flange.
The cyclic reinforcing rib of inlet channel is directly laid on sandwich foam, and sandwich foam is bonded on inlet channel covering by glued membrane.Cyclic reinforcing rib, sandwich foam and inlet channel covering co-curing.
The present invention's beneficial effect is compared with prior art:
The present invention changes into composites profiled member by combination forming part, and inner surface does not exist opposite joint, and attaching parts is few, only has attaching parts at tandem docking position, lightweight; Dimensional accuracy is high, and inner surface quality is good, and aerodynamic configuration is good; Increase cyclic reinforcing rib 3 in inlet channel outside, increased the strength and stiffness of inlet channel, reduced the distortion under larger load; Efficiently solve and assemble difficult problem, reduced fitting work amount; Extend service life, effectively guaranteed the indicators of overall performance of aircraft.
accompanying drawing explanation:
Concrete structure of the present invention is provided by following embodiment and accompanying drawing thereof.But therefore do not limit the present invention among described scope of embodiments.
Fig. 1 is structural representation of the present invention,
Fig. 2 is the A-A cutaway view of Fig. 1,
Fig. 3 and Fig. 4 are the fragmentary detail view of Fig. 2.
In figure: 1. lip fit docking ring stiffener, 2. inlet channel covering, 3. cyclic reinforcing rib, 4. inlet channel back segment docking ring stiffener, 5. sandwich foam, 6. glue, 7. high locked bolts, 8. lip, 9. inlet channel rear portion metal flange.
the specific embodiment:
in Fig. 1 and Fig. 2, inlet channel is mainly by the ring stiffener 1 docking with lip fit, inlet channel covering 2, increase the cyclic reinforcing rib 3 of inlet channel structural strength and rigidity, the ring stiffener 4 docking with inlet channel rear portion metal flange 9, the tubular structure that sandwich foam 5 forms, its cross sectional shape is transitioned into circular thin-walled annular gradually by square, takes composite material tow lay technology global formation; Lip fit docking ring stiffener 1 matches with the inside face of lip, and its fitting surface is ruled surface, convenient for assembly; The ring stiffener 4 of inlet channel back segment docking matches with inlet channel rear portion metal flange, it is characterized in that:
(1) between the ring stiffener 4 that lip fit docking ring stiffener 1 and inlet channel back segment dock, be distributed with 3 cyclic reinforcing ribs 3, the spacing of reinforced rib is L=170mm ~ 200mm;
(2) inlet channel covering 2 adopts the moulding of composite material tow lay technology;
(3), because inlet channel is S type, the lip fit docking ring stiffener 1 being connected with lip must be ruled surface, convenient for assembly;
(4) cyclic reinforcing rib 3 is directly laid on sandwich foam 5, and sandwich foam is bonded on inlet channel covering 2 by glued membrane, with inlet channel covering co-curing.
In an example of the present invention, cyclic reinforcing rib has 3, the process of its process implementing is: by inlet channel covering 2 by composite material tow layer by tow lay to mould, simultaneously by lip fit docking ring stiffener 1 and in outside with being put into after composite material laying moulding on inlet channel covering 2, add mould at outside face, guarantee bonding pad dimensional accuracy; The directly lay composite material on inlet channel covering 2 of ring stiffener 4 of inlet channel back segment docking; Sandwich foam 5 is added by section machine, by glued membrane, foam is fixed on inlet channel covering 2, use carbon cloth lay cyclic reinforcing rib 3 at sandwich foam 5 with above inlet channel covering 2, after completing, co-curing obtains product.
Claims (6)
1. a composites inlet channel, its one end and aircraft lip fit, the other end is connected on the fuselage metal flange at inlet channel rear portion, it is characterized in that, its structure is two serpentines, cross section is to be transitioned into gradually circular thin-walled annular structure by square, and by composite material tow lay global formation, it has lip fit docking ring stiffener (1), inlet channel covering (2), inlet channel back segment docking ring stiffener (4).
2. a kind of composites inlet channel according to claim 1, is characterized in that, described lip fit docking ring stiffener (1) and inlet channel back segment dock and between ring stiffener (4), be distributed with 3 cyclic reinforcing ribs (3).
3. a kind of composites inlet channel according to claim 1, is characterized in that, described lip fit docking ring stiffener (1) matches with the inside face of lip (8), and its fitting surface is ruled surface.
4. a kind of composites inlet channel according to claim 1, is characterized in that, described lip fit connects the type of attachment that ring stiffener (1) adopts splicing (6) and high locked bolts (7) to coordinate with lip.
5. a kind of composites inlet channel according to claim 1, is characterized in that, described inlet channel back segment docking ring stiffener (4) is connected by high locked bolts (7) with inlet channel rear portion metal flange (9).
6. a kind of composites inlet channel according to claim 2, is characterized in that, it is upper that described cyclic reinforcing rib (3) is directly laid in sandwich foam (5), and sandwich foam (5) is bonded on inlet channel covering (2) by glued membrane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320800591.1U CN203623970U (en) | 2013-12-09 | 2013-12-09 | Composite material integral air intake duct |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320800591.1U CN203623970U (en) | 2013-12-09 | 2013-12-09 | Composite material integral air intake duct |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203623970U true CN203623970U (en) | 2014-06-04 |
Family
ID=50810469
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320800591.1U Expired - Lifetime CN203623970U (en) | 2013-12-09 | 2013-12-09 | Composite material integral air intake duct |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203623970U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691765A (en) * | 2013-12-09 | 2015-06-10 | 成都飞机工业（集团）有限责任公司 | Composite material integrated air inlet way |
-
2013
- 2013-12-09 CN CN201320800591.1U patent/CN203623970U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691765A (en) * | 2013-12-09 | 2015-06-10 | 成都飞机工业（集团）有限责任公司 | Composite material integrated air inlet way |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140604 |
|
| CX01 | Expiry of patent term |