CN204775996U - Combined material elevator trailing edge strip - Google Patents
Combined material elevator trailing edge strip Download PDFInfo
- Publication number
- CN204775996U CN204775996U CN201520434279.4U CN201520434279U CN204775996U CN 204775996 U CN204775996 U CN 204775996U CN 201520434279 U CN201520434279 U CN 201520434279U CN 204775996 U CN204775996 U CN 204775996U
- Authority
- CN
- China
- Prior art keywords
- trailing edge
- edge strip
- edge bar
- foam core
- material elevator
- 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.)
- Active
Links
- 239000000463 material Substances 0.000 title abstract description 4
- 239000006260 foam Substances 0.000 claims abstract description 23
- 239000011347 resin Substances 0.000 claims abstract description 12
- 229920005989 resin Polymers 0.000 claims abstract description 12
- 238000000465 moulding Methods 0.000 claims abstract description 5
- 239000002131 composite material Substances 0.000 claims description 28
- 239000011120 plywood Substances 0.000 claims description 18
- 238000003475 lamination Methods 0.000 abstract 3
- 230000003028 elevating Effects 0.000 description 22
- 238000004519 manufacturing process Methods 0.000 description 6
- 229910000838 Al alloy Inorganic materials 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000003628 erosive Effects 0.000 description 2
- 238000007731 hot pressing Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 239000012528 membrane Substances 0.000 description 2
- 238000007493 shaping process Methods 0.000 description 2
- 239000000956 alloy Substances 0.000 description 1
- 239000011162 core material Substances 0.000 description 1
- 230000000875 corresponding Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006011 modification reaction Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
Abstract
The utility model provides a combined material elevator trailing edge strip, relates to aircraft control surface structural design field for covering and lower covering on the hookup elevator, including trailing edge strip body, trailing edge strip body includes foam core, lamination board, the lamination board is spread around the foam core and is pasted curing molding. The foam core pass through the resin with the lamination board couples into trailing edge strip body. Trailing edge strip body formula structure as an organic whole. The utility model provides a combined material elevator trailing edge strip simple structure, having alleviateed the weight of trailing edge strip, having reduced elevator overall structure weight, the mass balance of the elevator of being convenient for improves the structure efficiency and the driving efficiency of aircraft, and device stability improves, safe and reliable.
Description
Technical field
The utility model relates to aircraft control surface structure-design technique field, in particular to a kind of Composite material elevator trailing edge bar.
Background technology
Trailing edge bar is arranged at elevating rudder afterbody, and Main Function connects covering, lower covering on elevating rudder, to improve elevating rudder integral structure rigidity and to maintain elevating rudder trailing edge aerodynamic configuration.Because civil aircraft elevating rudder afterbody aerodynamic configuration height is general lower, therefore elevating rudder tail side-strip structure mostly is elongate configuration, highly less, and cross sectional shape is complicated, opens up to accessory size variation in thickness large.
In prior art, elevating rudder trailing edge bar mainly adopts aluminum alloy manufactured by fine limit work or customize section bar manufacture, on the one hand the heavier-weight of part own, and has certain influence to controlsurface balancing of mass, and then affects aircraft handling efficiency; On the other hand in order to ensure trailing edge bar curved profile, dimensional accuracy and surface quality, having to carry out fine limit work to the surface of trailing edge bar, thus affecting the productive costs of part.Therefore, the problem needing now solution badly is a kind of elevating rudder trailing edge bar of design, can imitate and alleviate structural weight, raising structure efficiency and driving efficiency.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency of the prior art, provides a kind of simple and reasonable, Composite material elevator trailing edge bar of reducing part quality and manufacturing cost, raising aircaft configuration efficiency.
The purpose of this utility model is achieved through the following technical solutions: a kind of Composite material elevator trailing edge bar, comprises trailing edge bar body, and trailing edge bar body comprises foam core, ply wood, and ply wood is around foam core paving curing molding.
Preferably, foam core is connected into trailing edge bar body by resin and ply wood.
In above-mentioned either a program preferably, trailing edge bar body is integral type structure.
The beneficial effect of Composite material elevator trailing edge bar provided by the utility model is, alleviates the weight of trailing edge bar, thus reduces elevating rudder integral structure weight, be convenient to the balancing of mass of elevating rudder, improve structure efficiency and the driving efficiency of aircraft, device stability improves, safe and reliable.
Accompanying drawing explanation
Fig. 1 is the structural representation of the preferred embodiment according to Composite material elevator trailing edge bar of the present utility model;
Fig. 2 is the cross-sectional view embodiment illustrated in fig. 1 according to Composite material elevator trailing edge bar of the present utility model;
Fig. 3 is the assembling schematic diagram embodiment illustrated in fig. 1 according to Composite material elevator trailing edge bar of the present utility model.
Reference numeral:
Covering under 1-trailing edge bar body, 2-foam core, 3-ply wood, the upper covering of 4-, 5-.
Detailed description of the invention
In order to understand the Composite material elevator trailing edge bar according to the utility model scheme better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to Composite material elevator trailing edge bar of the present utility model.
As Figure 1-3, the Composite material elevator trailing edge bar that the utility model provides, comprises trailing edge bar body 1, and trailing edge bar body 1 comprises foam core 2, ply wood 3, and ply wood 3 is around foam core 2 paving curing molding.Foam core 2 is connected into trailing edge bar body 1 by resin and described ply wood 3.Trailing edge bar body 1 is integral type structure.
In prior art, elevating rudder trailing edge bar mainly adopts aluminum alloy manufactured by fine limit work or customize section bar manufacture, adopts the elevating rudder trailing edge bar sole mass of this material manufacture heavier and the driving efficiency of the aircraft that affects on the balance of controlsurface quality, affect.In addition, in order to ensure trailing edge bar curved profile, dimensional accuracy and surface quality, having to carry out fine limit work to the surface of trailing edge bar, thus affecting the productive costs of part.The Composite material elevator trailing edge strip adoption composite material that the utility model provides makes, and adopts the molded method of vacuum assisted resin transfer membrane shaping, greatly reduces hot pressing and fills with shaping manufacturing cost.
In concrete use procedure, corresponding trailing edge bar moulds of industrial equipment are produced according to the theoretical space between covering on elevating rudder 4, lower covering 5, the Composite material elevator trailing edge strip adoption composite material foam core sandwich structure that the utility model provides, moulds of industrial equipment are adopted to carry out paving to ply wood 3 around foam core 2, obtained trailing edge bar preformed parts, are coated with resin between ply wood 3 and foam core 2.Preformed parts, by frock preheating, during this period, are vacuum seal, vacuum between ply wood 3 and foam core 2.Resin melting in frock warm, ply wood 3 and foam core are linked together by resin, then solidification, the demoulding, carry out machine up, repairing to Composite material elevator trailing edge bar profiled member, makes the Composite material elevator trailing edge bar body 1 being formed and meet usage condition.
The Composite material elevator trailing edge bar that the utility model provides is less with the central aluminum alloy trailing edge bar phase specific mass adopted of prior art, reduce the weight of trailing edge bar, thus reduce the weight of elevator structure, be convenient to the balance realizing elevating rudder quality, improve aircraft handling efficiency.
Shown in Fig. 1 is the structure of the Composite material elevator trailing edge bar preferred embodiment that the utility model provides.Be the elevating rudder trailing edge bar shown in Fig. 1 according to the trailing edge bar that the Configuration Design of covering on elevating rudder 4, lower covering 5 junction goes out, upper covering 4, the lower covering 5 of elevating rudder are placed in the groove of elevating rudder trailing edge bar respectively, make covering 4, lower covering 5 respectively with the transition face of elevating rudder trailing edge bar on the same face.Shown in Fig. 2 is the cross-sectional view of the Composite material elevator trailing edge bar that the utility model provides, by the elevating rudder trailing edge bar cross section after moulds of industrial equipment mold pressing, curing molding as shown in Figure 2, wherein the shape of foam core 2 is theoretical profile according to elevating rudder and designs, and ply wood 3 is in the surperficial paving of foam core 2.Be provided with resin between ply wood 3 and foam core 2 and make resin melting by frock preheating, ply wood 3 and foam core 2 being linked together by resin, ply wood 3 is integrated with foam core 2 one-tenth.
The trailing edge bar body 1 of a kind of Composite material elevator trailing edge bar that the utility model provides adopts composite material to make, there is compressive resistance compared with aluminum alloy materials high, hardness is large, high temperature resistant, erosion resisting feature, higher temperature is subject to not yielding outside the performance needed for maintenance trailing edge bar, there is the erosion resisting feature not available for metallic material, greatly reduce the maintenance cost of trailing edge bar, improve the safety of aircraft.
A kind of Composite material elevator trailing edge bar that the utility model provides, alleviates trailing edge bar weight, reduces elevator structure weight, be convenient to realize elevating rudder balancing of mass, and then improves aircraft handling quality and efficiency.In addition, adopt the molded technique of vacuum assisted resin transfer membrane, avoid adopting prepreg and hot pressing to fill with curing process, significantly reduce part manufacturing cost.
More than be described in detail in conjunction with Composite material elevator trailing edge bar specific embodiment of the present utility model, but be not to restriction of the present utility model, everyly according to technical spirit of the present utility model, technical scope of the present utility model is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of Composite material elevator trailing edge bar technical scheme of the present utility model.
Claims (3)
1. a Composite material elevator trailing edge bar, comprise trailing edge bar body (1), it is characterized in that: described trailing edge bar body (1) comprises foam core (2), ply wood (3), and ply wood (3) is around foam core (2) paving curing molding.
2. Composite material elevator trailing edge bar as claimed in claim 1, is characterized in that: described foam core (2) is connected into trailing edge bar body (1) by resin and described ply wood (3).
3. Composite material elevator trailing edge bar as claimed in claim 1 or 2, is characterized in that: described trailing edge bar body (1) is integral type structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520434279.4U CN204775996U (en) | 2015-06-23 | 2015-06-23 | Combined material elevator trailing edge strip |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520434279.4U CN204775996U (en) | 2015-06-23 | 2015-06-23 | Combined material elevator trailing edge strip |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204775996U true CN204775996U (en) | 2015-11-18 |
Family
ID=54516098
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520434279.4U Active CN204775996U (en) | 2015-06-23 | 2015-06-23 | Combined material elevator trailing edge strip |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204775996U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606637A (en) * | 2018-11-02 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Composite Sandwich wall panel structure of general-purpose aircraft rudder |
-
2015
- 2015-06-23 CN CN201520434279.4U patent/CN204775996U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606637A (en) * | 2018-11-02 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Composite Sandwich wall panel structure of general-purpose aircraft rudder |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104626605B (en) | Composite material wing integral molding technological method and composite material wing integral molding tool | |
| CN205150216U (en) | Unmanned aerial vehicle's foam presss from both sides core wing | |
| CN102490899A (en) | Composite rotor blade for unmanned helicopter and manufacturing method thereof | |
| CN105216345B (en) | RTM global formation orthogonal stiffenerses structure member (cover)s and its manufacture method | |
| CN106182801A (en) | A kind of aircraft foam core filled composite material rudder face forming method | |
| US10828870B2 (en) | Process for manufacturing apron board of high-speed rail equipment cabin using composite material | |
| CN105500730B (en) | High-precision forming die and method for thick-layer composite material box | |
| CN105034403B (en) | Method for manufacturing composite shell | |
| CN103342167A (en) | Method for making scaled composite material wing model | |
| CN107160753B (en) | A kind of composite material of solar powered aircraft lightweight | |
| CN110439630A (en) | A kind of Varying-thickness composite material stator blade and its forming method | |
| CN104290338A (en) | Method for realization of co-curing of reinforcing rib web composite produced part by high strength soft tooling | |
| CN101758923B (en) | Composite material box-shaped rib and manufacturing method thereof | |
| CN105269833A (en) | Two-time compression molding technology for thermoplastic composite material | |
| CN108943766A (en) | Co-bonding forming process for T-shaped reinforced wall plate made of composite material | |
| CN106584881A (en) | Hollow cap-shaped *-shaped reinforced all-carbon fibre structure and preparation method thereof | |
| CN204775996U (en) | Combined material elevator trailing edge strip | |
| CN104552677A (en) | Manufacturing process of composite material die for autoclave | |
| CN103909659B (en) | A kind of method of resin film infusion moulding resin based composites | |
| CN208664159U (en) | Skins front edges composite material shaping mould on the outside of a kind of aircraft | |
| CN107160709A (en) | The method and rudder face of a kind of composite liquid shaping ultra light aircraft rudder face | |
| US20180361686A1 (en) | Process for manufacturing base board of high-speed rail equipment cabin using composite material | |
| CN202529145U (en) | Composite material rotor blade of unmanned helicopter | |
| CN105423116A (en) | Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood | |
| CN106741823B (en) | By the unmanned plane body and preparation method thereof of composite material preparation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |