CN208291490U - One kind being used for aircraft integral tank mount structure - Google Patents
One kind being used for aircraft integral tank mount structure Download PDFInfo
- Publication number
- CN208291490U CN208291490U CN201820847477.7U CN201820847477U CN208291490U CN 208291490 U CN208291490 U CN 208291490U CN 201820847477 U CN201820847477 U CN 201820847477U CN 208291490 U CN208291490 U CN 208291490U
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- CN
- China
- Prior art keywords
- web
- camber member
- mount structure
- tank mount
- integral tank
- 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.)
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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
Abstract
The utility model relates to one kind to be used for aircraft integral tank mount structure, belong to field of aerospace technology.Reinforce band plate by composite material web, upper camber member, lower camber member, frame to constitute, web is installed at fuselage transversal cross-section center, and the web is composite honeycomb sandwich structures.The frame of left and right two reinforces band plate and is respectively placed in web upper limb and upper camber member upper limb, arranges double rivet interlacement assembly.There are two upper camber member settings, is respectively symmetrically installed at left and right sides of web.Lower camber member is divided into two and is partially disposed at left and right sides of web, is fixed with stringer, web by rivet interlacement.Upper and lower camber member is longitudinally connected to collectively form fuselage horizontal skeleton with web.The utility model is applied to the design and manufacture of unmanned plane, have many advantages, such as that weight-loss ratio is high, designability is strong, connection is simple, corrosion-resistant, antifatigue and increases fuel oil carrying amount.
Description
Technical field
The utility model relates to one kind to be used for aircraft integral tank mount structure, belong to field of aerospace technology.
Background technique
In recent years, unmanned plane is widely used in military and civilian field, and high altitude long time represents the water of Development of UAV
Gentle trend, it is desirable that under the premise of meeting bearing strength and fatigue life, carry out Optimal Structure Designing to reduce as far as possible
Housing construction weight increases volume of fuel tank, to increase fuel oil carrying amount, increase voyage, raising climbing ability, improvement flight
Energy.Advanced composite material has the advantages that specific strength height, specific stiffness height, endurance, corrosion-resistant, designability is strong, is used for
It can be compared with common metal structural weight reduction 25%~30% on aircaft configuration.Currently, composite material is applied to time load-carrying member such as machine more
The components such as the wing, empennage, antenna house and covering, and fuselage mount structure, as primary load bearing component, structure type is mostly that metal machine adds
Frame and metal plate frame.Wherein, machine adds frame processing cost high, and metal plate frame bearing capacity is weaker, and connection is complicated, the two housing construction weight
It is bigger than normal, more fuel oils can not be carried, endurance and voyage are restricted.
Based on this, present application is made.
Utility model content
In order to overcome drawbacks described above present in existing mount structure, the utility model provides a kind of for aircraft integral tank
Mount structure, compared with traditional metal machine adds frame, satisfy the use demand, intensity, rigidity requirement in the case where, not only structure weight
Measure substantially reduced, cost is relatively low, also has the advantages that corrosion-resistant, antifatigue.Compared with metal plate frame, bearing capacity is higher, assembly
Connection is simple, can optimize edge strip according to bearing requirements and web, designability are strong.
To achieve the above object, the technical solution that the utility model is taken is as follows:
One kind being used for aircraft integral tank mount structure, and it includes composite material web, upper camber member, lower camber member and frame add
Strong band plate；The upper lower edge of composite material web is connected by way of riveting with fuselage skin, and frame reinforces band plate for upper arch
Part is attached fixation by double rivet with web；Upper camber member is connected by way of longitudinally riveting with lower camber member
It connects.
Web is located at fuselage transversal cross-section center, and upper camber member, lower camber member are located at web two sides, and frame reinforces band plate peace
Loaded on web and upper camber member edge strip.
Further, as preferred:
The web uses composite honeycomb sandwich structures, by carbon fiber/epoxy resin twill prepreg and 15mm
Aramid fiber paper honeycomb is laid with, and honeycomb upper and lower surface is respectively laid with one layer of glue film, using autoclave process solidified forming.It is more highly preferred to
, the web outermost layer, which is laid with layer of glass plain cloth, prevents electrochemical corrosion.
The web border is the web edge strip of drum section, is conducive to the stability for improving combination mount structure.
The laying angle has 0/90 °, ± 45 ° two kinds.The symmetrical simultaneously balanced-ply in laying face along web, avoids laminated
The buckling deformation and layering of plate.Outermost layer laying is ± 45 ° of layings, improves web surface anti-shear ability.
The web honeycomb divides into two parts up and down, is equipped with insert, the installation for airborne equipment.Honeycomb
Structural perimeter and fabrication hole are sealed with sealant.
Circular hole is set on the web, as line channel, two layers of local laying is inserted into for adding in circular hole neighboring area
By force, one layer of complete laying of outermost layer paving.
The upper camber member is divided into two components in left and right, symmetrical about aircraft median plane, is closed using 7050-T7451 aluminium
Golden machine add-on type is surface-treated as sulfur acid anodizing+zinc yellow epoxy primer.
The lower camber member is divided into two components in left and right, symmetrical about aircraft median plane, is closed using 7050-T7451 aluminium
Golden machine add-on type is surface-treated as sulfur acid anodizing+zinc yellow epoxy primer.
The frame reinforces band plate and is divided into two components in left and right, symmetrical about aircraft median plane, using 7050-T7451 aluminium
Alloy machine add-on type is surface-treated as sulfur acid anodizing+zinc yellow epoxy primer.
The working principle of the utility model is: lower edge is connected using the form of riveting with fuselage skin on composite material web
It connects, in aircraft flight, web edge strip bears direct stress caused by frame bending moment of section, and web supports covering and bears its biography
The shearing passed, web rear surface bear tank pressure.Frame reinforces band plate and consolidates upper camber member by double rivet interlacement with web
It is fixed.Upper and lower camber member longitudinally rivets, and is fixed with stringer, web or so edge strip by rivet interlacement, is combined into fuselage transverse direction bone
Frame.
The beneficial effects of the utility model are as follows:
(1) when guaranteeing same strength and stiffness, compared with traditional monoblock type metal frame, construction weight can subtract
It is light by 35% or more, a kind of effective technological approaches is provided for fuselage loss of weight.
(2) edge strip, web, upper and lower camber member can be optimized according to bearing requirements, designability is strong.
(3) insert is installed on honeycomb sandwich construction, is easily installed airborne equipment.
(4) web, be provided with reinforcement circular hole on camber member, as line channel, line arrangement is beautiful, succinct.
(5) web constitutes sealing bay section with covering, fuel tank wainscot under whole stringer, fuselage, is conducive to improve whole oil
The leakproofness of case.
Detailed description of the invention
Fig. 1 is the main view of the utility model；
Fig. 2 is the isometric view of the utility model.
Fig. 3 is the honeycomb sandwich construction schematic diagram of the web of the utility model.
Fig. 4 is the connecting-piece structure schematic diagram (upper covering does not show) of the utility model.
Figure label: 1. composite material webs；Camber member on 2.；3. lower camber member；4. frame reinforces band plate；5. on the right side of fuselage
Covering；6. right vertical beam；7. covering under fuselage；8. left stringer；9. covering on the left of fuselage；10. fuel tank wainscot.
Specific embodiment
Embodiment 1
It is described in further details below by design and prepare technology of the embodiment to the utility model
The present embodiment one kind is used for aircraft integral tank mount structure, in conjunction with Fig. 1, by composite material web 1, upper camber member 2,
Lower camber member 3, frame are reinforced band plate 4 and are constituted.The frame of left and right two reinforces band plate and is respectively placed in web upper limb and upper camber member upper limb, cloth
Double rivet interlacement assembly is set, bonding strength is increased.There are two upper camber member settings, is respectively symmetrically installed on web or so two
Side, upper camber member are fixed with stringer, web by rivet interlacement.Lower camber member is divided into two and is partially disposed at left and right sides of web,
It is fixed with stringer, web by rivet interlacement.Upper and lower camber member is longitudinally connected to collectively form fuselage horizontal skeleton with web.Abdomen
Plate upper limb and lower edge are connected with fuselage skin.Web and fuel tank wainscot, lower covering, two side girders constitute the whole oil of sealing
Case.
In addition, web lower edge is connect using sealing riveting with lower covering, stringer lower edge for the leakproofness for guaranteeing integral tank
It connects, between all binding faces and edge is filled up with sealant and had the gap.Stringer, web, camber member binding face edge and tight
Sealant is covered at the surrounding and component space of firmware.
Its process designed and prepared and method are as follows:
(1) according to the receiving load condition of body mount structure, thickness, laying number and the angle of web composite material are determined
Degree, prepares composite material web 1 using manual paving+vacuum bag-autoclave forming process.
(2) machine adds camber member 2 on aluminium alloy, lower camber member 3, frame reinforcement band plate 4.
(3) web, upper and lower camber member, frame are reinforced being connected and fixed between band plate using riveting form, all binding faces,
Sealant sealing is covered at gap, fastener.
The above content is combination preferred embodiments of the present invention to further detailed made by provided technical solution
Describe in detail bright, and it cannot be said that the utility model specific implementation is confined to these above-mentioned explanations, technology affiliated for the utility model
For the those of ordinary skill in field, without departing from the concept of the premise utility, several simple deductions can also be made
Or replacement, it all shall be regarded as belonging to the protection scope of the utility model.
Claims (8)
1. one kind is used for aircraft integral tank mount structure, which is characterized in that it includes composite material web, upper camber member, lower bow
Shape part and frame reinforce band plate；The upper lower edge of composite material web is connected by way of riveting with fuselage skin, frame reinforcing strip
Upper camber member and web are attached fixation by double rivet by plate；Upper camber member and lower camber member pass through the side longitudinally riveted
Formula is attached.
2. as described in claim 1 a kind of for aircraft integral tank mount structure, which is characterized in that web is located at fuselage transverse direction
At kernel of section, upper camber member, lower camber member are located at web two sides, and frame reinforces band plate and is installed on web and upper camber member edge strip
On.
3. as described in claim 1 a kind of for aircraft integral tank mount structure, which is characterized in that the web is using multiple
Condensation material honeycomb sandwich construction is laid with, on honeycomb by carbon fiber/epoxy resin twill prepreg and 15mm aramid fiber paper honeycomb
Lower surface is respectively laid with one layer of glue film.
4. as described in claim 1 a kind of for aircraft integral tank mount structure, which is characterized in that the web outermost layer
Being laid with layer of glass plain cloth prevents electrochemical corrosion.
5. as described in claim 1 a kind of for aircraft integral tank mount structure, which is characterized in that the web border is
The web edge strip of drum section.
6. as described in claim 1 a kind of for aircraft integral tank mount structure, which is characterized in that the web wing flapping
Degree has 0/90 °, ± 45 ° two kinds；The symmetrical simultaneously balanced-ply in laying face along web.
7. as described in claim 1 a kind of for aircraft integral tank mount structure, which is characterized in that the web cell
It is divided into two parts up and down, is equipped with insert.
8. as described in claim 1 a kind of for aircraft integral tank mount structure, which is characterized in that be arranged on the web
Circular hole, as line channel, two layers of local laying is inserted into for reinforcing in circular hole neighboring area, and one layer of outermost layer paving is completely spread
Layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820847477.7U CN208291490U (en) | 2018-06-03 | 2018-06-03 | One kind being used for aircraft integral tank mount structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820847477.7U CN208291490U (en) | 2018-06-03 | 2018-06-03 | One kind being used for aircraft integral tank mount structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208291490U true CN208291490U (en) | 2018-12-28 |
Family
ID=64722429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820847477.7U Active CN208291490U (en) | 2018-06-03 | 2018-06-03 | One kind being used for aircraft integral tank mount structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208291490U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731494A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Composite fuel tank of aircraft |
| CN114056537A (en) * | 2021-11-19 | 2022-02-18 | 中国直升机设计研究所 | Main bearing structure of middle fuselage of unmanned high-speed helicopter |
| CN114180083A (en) * | 2021-11-19 | 2022-03-15 | 中国直升机设计研究所 | Method for conducting between composite material structural members by using copper cup |
-
2018
- 2018-06-03 CN CN201820847477.7U patent/CN208291490U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731494A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Composite fuel tank of aircraft |
| CN114056537A (en) * | 2021-11-19 | 2022-02-18 | 中国直升机设计研究所 | Main bearing structure of middle fuselage of unmanned high-speed helicopter |
| CN114180083A (en) * | 2021-11-19 | 2022-03-15 | 中国直升机设计研究所 | Method for conducting between composite material structural members by using copper cup |
| CN114056537B (en) * | 2021-11-19 | 2023-04-25 | 中国直升机设计研究所 | Main bearing structure of fuselage in unmanned high-speed helicopter |
| CN114180083B (en) * | 2021-11-19 | 2023-09-01 | 中国直升机设计研究所 | Method for conducting electricity between composite structural members by using copper cups |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 312000 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Patentee after: Shaoxing Baojing composite material Co.,Ltd. Patentee after: JINGGONG (SHAOXING) COMPOSITE TECHNOLOGY R & D CO.,LTD. Address before: 312030 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Patentee before: JINGGONG (SHAOXING) COMPOSITE MATERIAL CO.,LTD. Patentee before: JINGGONG (SHAOXING) COMPOSITE TECHNOLOGY R & D CO.,LTD. |
|
| CP03 | Change of name, title or address | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 312000 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Patentee after: Shaoxing Baojing composite material Co.,Ltd. Patentee after: Shaoxing Baojing Composite Technology Research and Development Co.,Ltd. Address before: 312000 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Patentee before: Shaoxing Baojing composite material Co.,Ltd. Patentee before: JINGGONG (SHAOXING) COMPOSITE TECHNOLOGY R & D CO.,LTD. |
|
| CP01 | Change in the name or title of a patent holder |