CN202624628U - Aircraft spoiler control plane made of composite material - Google Patents
Aircraft spoiler control plane made of composite material Download PDFInfo
- Publication number
- CN202624628U CN202624628U CN 201220246708 CN201220246708U CN202624628U CN 202624628 U CN202624628 U CN 202624628U CN 201220246708 CN201220246708 CN 201220246708 CN 201220246708 U CN201220246708 U CN 201220246708U CN 202624628 U CN202624628 U CN 202624628U
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- CN
- China
- Prior art keywords
- composite material
- honeycomb core
- spoiler
- control plane
- rudder face
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Abstract
An aircraft spoiler control plane made of a composite material relates to the technical field of the structures of aircraft spoiler control planes made of composite materials. According to the utility model, the number of parts which are required to be assembled during the forming process of the whole spoiler control plane is reduced from 9 to 6, so as to reduce surfaces matched with the connection of parts, improve the assembling manufacturability, and improve the formation stability and the assembling efficiency of the spoiler control plane.
Description
Technical field
The present invention relates to the technical field of structures of the plane spoiler rudder face of composite material.
Background technology
Plane spoiler is arranged at upper surface of the airfoil usually, opens and the closed airflow pattern of adjusting upper surface of the airfoil through it; Spoiler is to be made up of manipulation, suspension joint that rudder face and rudder face are connected with wing.The structure of common composite material spoiler rudder face is as shown in Figure 1; By the cross section be trapezoidal honeycomb core 7 and with trailing edge bar 5, the honeycomb core 7 high-end grooves of honeycomb core 7 low side bonded assembly wedge shapes play the effect of obturaging the block 6 of obturaging, constitute the wedge shape clamping plate with honeycomb core 7 high end side surface bonded assembly beams 3 and honeycomb core 7 both sides bonded assembly Z fonts or grooved end rib 4, the upper and lower surface of wedge shape clamping plate is obturaged by covering 2 under covering on the tabular 1 and the tabular.Because the Z font of end rib 4 or the height that trench structure causes lower end can not be processed very low; So must carry out shutoff through 5 pairs of honeycomb cores of trailing edge bar 7 of wedge shape; It is more to cause needing to connect the face that cooperates in the whole spoiler rudder face forming process, and assembly process process is complicated, and product stability is poor.
Summary of the invention
The objective of the invention is: in order to reduce the face that needs to connect cooperation in the whole spoiler rudder face forming process, improve the manufacturability of assembling, improve the stability of spoiler rudder face moulding, a kind of improved composite material spoiler rudder face of special disclosure.
Technical scheme of the present invention is: the structure of improvement composite material spoiler rudder face of the present invention is as shown in Figure 2; Cancel Z font or grooved end rib 4 and trailing edge bar 5 in the common spoiler rudder face structure; Correspondingly changing covering under the tabular 2 into lower wall panels 8 that both sides have upward receipts side plate, is trapezoidal honeycomb core 7 honeycomb core 9 that to change the cross section into be triangle, both sides is complementary for the side plate with the lower wall panels 8 of upward receipts side plate with the cross section; The trapezoid cross section of honeycomb core 7 changes the space that leg-of-mutton cross section can remedy cancellation trailing edge bar 5 just into; The side plate that following covering 2 increases and the improvement of its corresponding honeycomb core 7 both sides will remedy the space of cancellation Z font or grooved end rib 4; Honeycomb core 9 high-end bonded assembly beams 3 and the block 6 obturaged keep with common spoiler rudder face structure in consistent; The block 6 of obturaging is obturaged honeycomb core 9 high-end grooves; The lower surface of block 6 obturaged combines with wallboard 8, and a side end face of two beams 3 combines with the side plate of lower wall panels 8, beam 3 web faces combine with the high end side surface of honeycomb core 9 and the block 6 of obturaging, and two beam 3 lower surfaces combine with lower wall panels 8; Directly combine with the trailing edge and the side plate of wallboard 8 respectively by the low side and the both sides of last covering 1 at last, directly combine with the upper surface of beam 3 respectively with the block 6 of obturaging at the high-end place of rudder face at rudder face.So, need the part count of assembling to be reduced to six in the whole spoiler rudder face forming process by nine, reached and reduced the face that part connects cooperation, improve the manufacturability of assembling, improve the purpose of spoiler rudder face forming stability.
The present invention has the following advantages: through the enforcement of technique scheme, reached and reduced the face that part connects cooperation, improved the manufacturability of assembling, improved the stability of spoiler rudder face moulding and the efficient of assembling.
Description of drawings
Fig. 1 is the scheme drawing of common composite material spoiler rudder face structure;
Fig. 2 is the scheme drawing of composite material spoiler rudder face structure of the present invention.
The specific embodiment
Below in conjunction with the accompanying drawing and the specific embodiment the present invention is described in further detail:
The rudder face of certain type plane spoiler has adopted version of the present invention.Last covering 1, lower wall panels 8, beam 3 all adopt the hot setting carbon fiber composite material, and honeycomb core 9 adopts paper honeycomb core materials, and the block 6 of obturaging adopts glass fiber compound materials.
Last covering 1 surface is the aerodynamic configuration face, lower wall panels 8 both sides with the side plate and the bottom surface angulation of upward receipts be 120 °; Last covering 1 adopts the hot setting epoxy glue directly to fit with the junction of lower wall panels 8, and applying width in both sides is 30mm, and joint place thickness is 3.5mm; Applying width in trailing edge place is 33mm, and joint place thickness is 3mm; All adopt the hot setting epoxy glue to fit between the upper and lower surfaces of last covering 1, lower wall panels 8 and honeycomb core 9, block 6, two beams 3; Use the high temperature foamed glue to carry out bonding between the high-end and block 6 of honeycomb core 9, the beam 3 web faces and the honeycomb core lattice on the bonding plane are filled.
Owing to need the part count of assembling to be reduced to six in the whole spoiler rudder face forming process by nine, reduce part and connected fitting surface, improved efficiency of assembling.
Claims (2)
1. the composite material spoiler rudder face of an aircraft; It is that upward covering (1), lower wall panels (8) are obturaged the low side and the both sides of honeycomb core (9); The block (6) of obturaging is obturaged the high-end groove of honeycomb core (9); Bonded assembly beam (3) is characterized in that the high-end formation of obturaging of honeycomb core (9): the structure of lower wall panels (8) upward receipts side plate for both sides have.
2. aircraft composite material spoiler rudder face according to claim 1 is characterized in that: honeycomb core (9) is structure that the side plate with the lower wall panels (8) of upward receipts is complementary for the cross section is triangle, both sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220246708 CN202624628U (en) | 2012-05-29 | 2012-05-29 | Aircraft spoiler control plane made of composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220246708 CN202624628U (en) | 2012-05-29 | 2012-05-29 | Aircraft spoiler control plane made of composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202624628U true CN202624628U (en) | 2012-12-26 |
Family
ID=47377852
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220246708 Expired - Lifetime CN202624628U (en) | 2012-05-29 | 2012-05-29 | Aircraft spoiler control plane made of composite material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202624628U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103754353A (en) * | 2013-12-09 | 2014-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Composite material elevator |
| CN104417749A (en) * | 2013-08-29 | 2015-03-18 | 空中客车营运有限公司 | An aircraft structure and method of manufacture |
| CN105000196A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Airplane spoiler manufacturing method, airplane spoiler and airplane |
| CN105416566A (en) * | 2015-11-26 | 2016-03-23 | 中国运载火箭技术研究院 | Mortise and tenon type wing rudder structure suitable for reentry vehicle |
-
2012
- 2012-05-29 CN CN 201220246708 patent/CN202624628U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104417749A (en) * | 2013-08-29 | 2015-03-18 | 空中客车营运有限公司 | An aircraft structure and method of manufacture |
| CN103754353A (en) * | 2013-12-09 | 2014-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Composite material elevator |
| CN105000196A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Airplane spoiler manufacturing method, airplane spoiler and airplane |
| CN105416566A (en) * | 2015-11-26 | 2016-03-23 | 中国运载火箭技术研究院 | Mortise and tenon type wing rudder structure suitable for reentry vehicle |
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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 | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121226 |