CN202193205U - Adopt foam with filling combined material structure's unmanned aerial vehicle and wing - Google Patents
Adopt foam with filling combined material structure's unmanned aerial vehicle and wing Download PDFInfo
- Publication number
- CN202193205U CN202193205U CN2011201731082U CN201120173108U CN202193205U CN 202193205 U CN202193205 U CN 202193205U CN 2011201731082 U CN2011201731082 U CN 2011201731082U CN 201120173108 U CN201120173108 U CN 201120173108U CN 202193205 U CN202193205 U CN 202193205U
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- foam
- wing
- adopts
- composite material
- aerial vehicle
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- 239000006260 foam Substances 0.000 title claims abstract description 51
- 239000000463 material Substances 0.000 title abstract description 6
- 239000002131 composite material Substances 0.000 claims abstract description 30
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 5
- 229910052799 carbon Inorganic materials 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 abstract description 3
- 238000005253 cladding Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 240000007182 Ochroma pyramidale Species 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
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Abstract
A composite material unmanned aircraft adopting a foam sandwich process comprises a main wing, a horizontal tail wing, a vertical tail wing, an aircraft body and a tail honing, wherein: at least the main wing is cut into wing shapes by foam to serve as an inner core, and the outer surface of the foam inner core is coated with a layer of composite material. And a structural support member can be locally arranged to form an integral structure, thereby achieving the performances of light weight and high strength. The utility model also discloses an adopt the aircraft wing of the combined material structure of foam sandwich technology, the wing adopts the foam to cut into the wing section as the inner core, at foam inner core surface cladding one deck combined material.
Description
Affiliated technical field
The utility model relates to a kind of robot airplane and wing that adopts foam sandwich structure.
Background technology
At present, the structure of known unmanned aerial vehicle is to adopt various material cut such as cork wood, aviation laminate, carbon fiber board to become corresponding rib and other structural supports, covers cork wood, plastic skin or glass-felt plastic etc. outside after being overlapped to form global shape again.But adopt the aircraft weight of this structure very big.Because the fuel of unmanned plane is limited, the weight of aircraft own has greatly just caused that the task load-carrying capacity of unmanned plane is low, flying distance is little, transportation is inconvenient, has reduced the utility function of unmanned plane.Aircraft such as model airplane also have the needs that alleviate structure member weight and increase structural strength.
Summary of the invention
Defectives such as to carry the task load few in order to overcome existing unmanned plane, and working area is little, the utility model provides a kind of structure, makes the weight of unmanned plane be minimized, thereby has increased unmanned plane task load-carrying capacity, increased flying distance.
The utility model solves the technical scheme that its technical matters adopted: adopt foam to cut into aerofoil profile and other shapes as inner core; Can increase carbon beam isostructuralism strut member in the bigger place of local pressure in case of necessity; Coat one deck composite material at the foam core outside face, form a kind of integral structure; The utility model provides a kind of composite material unmanned aerial vehicle that adopts the sandwich technology of foam; Comprise main wing; Tailplane, vertical tail, fuselage, the tail top gem of a girdle-pendant, wherein: main wing adopts foam to cut into aerofoil profile as inner core, at foam core outside face coating one deck composite material at least; The utility model also provides a kind of aircraft wing that adopts the composite structure of the sandwich technology of foam, wherein: adopt foam to cut into aerofoil profile as inner core, at foam core outside face coating one deck composite material.
The beneficial effect of the utility model is, the aircraft weight that adopts this structure to produce is light, and intensity is big, has directly reduced the weight of unmanned plane self, thereby has increased the task load-carrying capacity of aircraft, has increased the flying distance of unmanned plane.This structure also can be used for making aircraft such as model airplane, alleviates structure member weight and increases structural strength.
Description of drawings
Below in conjunction with accompanying drawing and embodiment the utility model is further specified.
Fig. 1 is the overall diagram (oblique drawing) of the utility model
Fig. 2 is the overall diagram (birds-eye view) of the utility model
Fig. 3 is the overall diagram (front elevation) of the utility model
Fig. 4 is the overall diagram (lateral plan) of the utility model
Fig. 5 is the structure principle chart of the utility model
The wing of 1. foam sandwich structures among Fig. 1～Fig. 4,2. foam sandwich structure tailplane, 3. foam sandwich structure vertical tail, 4. the tail top gem of a girdle-pendant, 5. fuselage, the 6. engine installation of optional dress, 7. the task device gondola of optional dress.
8. prefabricated foam core, the 9. structural support of optional dress, 10. composite surface material among Fig. 5
The specific embodiment:
An example of the utility model provides a kind of composite material unmanned aerial vehicle that adopts the sandwich technology of foam; Comprise main wing; Tailplane; Vertical tail, fuselage, the tail top gem of a girdle-pendant, wherein, main wing adopts foam to cut into aerofoil profile and other shapes as inner core, coat one deck composite material at the foam core outside face at least.Further example is that tailplane, vertical tail etc. also adopt foam to cut into aerofoil profile and other shapes as inner core, coat one deck composite material at the foam core outside face.
According to an example of the utility model, can increase carbon beam isostructuralism strut member in the bigger place of wing local pressure in case of necessity.Wing can refer to main wing, main wing, one of any or their general name in tailplane, the vertical tail etc.The composite material unmanned aerial vehicle that this adopts the sandwich technology of foam can also comprise engine installation and task device gondola etc., with the expanding application scope.
An example according to the utility model provides a kind of aircraft wing that adopts the composite structure of the sandwich technology of foam, adopts foam to cut into aerofoil profile and other shapes as inner core, coat one deck composite material at the foam core outside face.Said wing one of comprises in main wing, tailplane, the vertical tail at least.And, can increase carbon beam isostructuralism strut member in the bigger place of wing local pressure in case of necessity.
Make the unmanned plane main wing: in Fig. 5, utilize the foam core of making in advance (8), increase structural support (9) in the place that the wing local pressure is concentrated in case of necessity, coat layer of surface composite material (10) outside, treat that composite surface material solidifies aftershaping.Make the unmanned plane tailplane: main wing method for making capable of using; Make the unmanned plane vertical tail: main wing method for making capable of using; As required, can increase engine installation; As required, can increase the task device gondola;
Assembling: utilize each detail assembly of making to become complete unmanned aerial vehicle.In Fig. 1, with each parts of making: the wing of foam sandwich structure (1), foam sandwich structure tailplane (2); Foam sandwich structure vertical tail (3), the tail top gem of a girdle-pendant (4), fuselage (5); The engine installation of optional dress (6), the task device gondola (7) of optional dress is grouped together and gets final product.
Claims (9)
1. composite material unmanned aerial vehicle that adopts the sandwich technology of foam; Comprise main wing; Tailplane, vertical tail, fuselage, the tail top gem of a girdle-pendant is characterized in that: main wing adopts foam to cut into aerofoil profile as inner core, at foam core outside face coating one deck composite material at least.
2. a kind of composite material unmanned aerial vehicle that adopts the sandwich technology of foam according to claim 1 is characterized in that: tailplane adopts foam to cut into aerofoil profile as inner core, at foam core outside face coating one deck composite material.
3. a kind of composite material unmanned aerial vehicle that adopts the sandwich technology of foam according to claim 1 is characterized in that: vertical tail adopts foam to cut into aerofoil profile as inner core, at foam core outside face coating one deck composite material.
4. a kind of composite material unmanned aerial vehicle that adopts the sandwich technology of foam according to claim 1 is characterized in that: increase the carbon beam as structural support in the bigger place of wing local pressure.
5. a kind of composite material unmanned aerial vehicle that adopts the sandwich technology of foam according to claim 1 is characterized in that: also comprise engine installation.
6. a kind of composite material unmanned aerial vehicle that adopts the sandwich technology of foam according to claim 1 is characterized in that: also comprise the task device gondola.
7. an aircraft wing that adopts the composite structure of the sandwich technology of foam is characterized in that: adopt foam to cut into aerofoil profile as inner core, at foam core outside face coating one deck composite material.
8. a kind of aircraft wing that adopts the composite structure of the sandwich technology of foam according to claim 7 is characterized in that: said wing one of comprises in main wing, tailplane, the vertical tail at least.
9. a kind of aircraft wing that adopts the composite structure of the sandwich technology of foam according to claim 7 is characterized in that: increase the carbon beam as structural support in the bigger place of wing local pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201731082U CN202193205U (en) | 2011-05-27 | 2011-05-27 | Adopt foam with filling combined material structure's unmanned aerial vehicle and wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201731082U CN202193205U (en) | 2011-05-27 | 2011-05-27 | Adopt foam with filling combined material structure's unmanned aerial vehicle and wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202193205U true CN202193205U (en) | 2012-04-18 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201731082U Expired - Lifetime CN202193205U (en) | 2011-05-27 | 2011-05-27 | Adopt foam with filling combined material structure's unmanned aerial vehicle and wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN202193205U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105008222A (en) * | 2012-12-27 | 2015-10-28 | 欧洲航空防务及航天公司Eads法国 | Energy absorption device for aircraft structural element |
| CN105416567A (en) * | 2015-11-13 | 2016-03-23 | 中国人民解放军国防科学技术大学 | Skin, unmanned aerial vehicle wing, manufacturing method of unmanned aerial vehicle wing, empennage and manufacturing method of empennage |
| CN105480403A (en) * | 2015-11-12 | 2016-04-13 | 中国人民解放军国防科学技术大学 | Three-section type dihedral wing |
-
2011
- 2011-05-27 CN CN2011201731082U patent/CN202193205U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105008222A (en) * | 2012-12-27 | 2015-10-28 | 欧洲航空防务及航天公司Eads法国 | Energy absorption device for aircraft structural element |
| CN105480403A (en) * | 2015-11-12 | 2016-04-13 | 中国人民解放军国防科学技术大学 | Three-section type dihedral wing |
| CN105416567A (en) * | 2015-11-13 | 2016-03-23 | 中国人民解放军国防科学技术大学 | Skin, unmanned aerial vehicle wing, manufacturing method of unmanned aerial vehicle wing, empennage and manufacturing method of empennage |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: BEIJING TIANYI HECHUANG TECHNOLOGY DEVELOPMENT CO. Free format text: FORMER OWNER: WANG ZHIGANG Effective date: 20140304 Free format text: FORMER OWNER: MA YONG Effective date: 20140304 |
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| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 100012 CHAOYANG, BEIJING TO: 102210 CHANGPING, BEIJING |
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| TR01 | Transfer of patent right |
Effective date of registration: 20140304 Address after: 102210 4B220 room, No. 11 Huatong Road, Changping District science and Technology Park, Beijing Patentee after: Beijing Tianyi Hechuang Technology Development Co., Ltd. Address before: 100012 Beijing city Chaoyang District Lishuiqiao Beiyuan Mo pigweed Park No. 17 Building 2 unit 1303 Patentee before: Wang Zhigang Patentee before: Ma Yong |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181217 Address after: 455000 9th Floor of China Road Unmanned Aerial Vehicle Building, Beiguan District, Anyang City, Henan Province Patentee after: Anyang Tianyi Co-Creation Technology Development Co., Ltd. Address before: Room 4B220, No. 11 Huadao Road, Changping District Science Park, Beijing 102210 Patentee before: Beijing Tianyi Hechuang Technology Development Co., Ltd. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200317 Address after: 102213 4B220 room, No. 11 Huatong Road, Changping District science and Technology Park, Beijing Patentee after: BEIJING TIANYI HECHUANG TECHNOLOGY DEVELOPMENT Co.,Ltd. Address before: 455000 9th Floor of China Road Unmanned Aerial Vehicle Building, Beiguan District, Anyang City, Henan Province Patentee before: ANYANG TIANYI HECHUANG TECHNOLOGY DEVELOPMENT Co.,Ltd. |
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| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120418 |
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| CX01 | Expiry of patent term |