CN204310031U - A kind of modularization Flying-wing - Google Patents
A kind of modularization Flying-wing Download PDFInfo
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- CN204310031U CN204310031U CN201420760818.9U CN201420760818U CN204310031U CN 204310031 U CN204310031 U CN 204310031U CN 201420760818 U CN201420760818 U CN 201420760818U CN 204310031 U CN204310031 U CN 204310031U
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Abstract
The utility model belongs to airplane design technical field, relates to a kind of modularization Flying-wing technology.What the utility model proposes passes through shared inner wing, and configuration difformity outer wing, can form aerodynamic arrangement's configuration that the gentle motivation level of multiple stealthy level is different, adapt to different aerial missions, improve fighting efficiency and aircraft utilization rate, and then improve efficiency-cost ratio.
Description
Technical field
The utility model belongs to airplane design technical field, relates to a kind of Flying-wing that can adapt to multiple-task needs.
Background technology
Flying-wing is compared with normal arrangement, and do not have vertical fin and independently fuselage, stealth is good; Fuselage and inner wing height merge, streamlined design, and 1ift-drag ratio is high.The typical aerodynamic arrangement that these advantages of all-wing aircraft make it become present military aircraft often to adopt, as B2 bomber, X-47B unmanned plane, ghost line unmanned plane X-45C, neuron unmanned plane, RQ-170 unmanned plane, etc.
The aspect ratio of Flying-wing and leading edge sweep affect comparatively large on Stealth and aerodynamic characteristic, highly stealthyly requires that leading edge sweep is greater than 45 ° greatly usually, and high lift-drag ratio requires that large aspect ratio, leading edge sweep are little and is usually less than 35 °.Therefore, requirement of flying when the Flying-wing's 1ift-drag ratio usually designed for high stealth capabilities is discontented with foot length boat, the Flying-wing for flight performance design during long boat does not meet high stealth capabilities requirement.This causes Flying-wing to there is limitation when executing the task, not as good as RQ-170 unmanned plane during as navigated for the X-47B unmanned plane of high stealthing design, and for the RQ-170 unmanned plane stealth capabilities designed during long boat not as good as X-47B unmanned plane.If all go to design a kind of Flying-wing for often kind of aerial mission, aircraft quantity will be made greatly to increase, supporting support facility equipment is also very huge, and cost is high; Meanwhile, if a certain aerial mission is also few, just aircraft will be caused to be left unused for a long time, reduce Occupation coefficient, increase unit use cost.
Summary of the invention
The purpose of this utility model proposes a kind of Flying-wing's technology that can adapt to multiple aerial mission, can adapt to high stealthy aerial mission, can adapt to again aerial mission when length is navigated.
Technical solution of the present utility model is, a kind of modularization Flying-wing, is made up of inner wing and outer wing.Wherein, there are 2 secondary above difformity outer wings, corresponding outer wing can be selected to be contained on inner wing according to different aerial mission.
The advantage that the utility model has and beneficial effect, the modularization Flying-wing that the utility model proposes, can select corresponding outer wing according to different aerial mission, improve fighting efficiency and aircraft utilization rate, and then improve efficiency-cost ratio.
Accompanying drawing explanation
Fig. 1 is modularization Flying-wing composition schematic diagram.
Fig. 2 is the high stealthy configuration schematic diagram of typical high speed.
Stealthy configuration schematic diagram when Fig. 3 is typical long boat.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is further illustrated.
Modularization Flying-wing forms primarily of inner wing 1, outer wing 2, and inner wing 1 is furnished with other aerodynamic arrangement's key elements such as inlet channel 3 and jet pipe 4.
There are 2 secondary above difformity outer wings 2, corresponding outer wing 2 can be selected to be contained on inner wing 1 according to different aerial mission.
When performing the aerial mission of high stealthy requirement, select large sweepback low aspect ratio outer wing 2, as shown in Figure 2.The leading edge sweep of outer wing 2 is identical with the leading edge sweep of inner wing 1, and the trailing sweep of outer wing 2 is identical with the trailing edge sweepforward angle of inner wing 1, at utmost to reduce the reflection direction of radar wave, improves stealth capabilities.
During the aerial mission required when executive chairman navigates, select little sweepback high aspect ratio outer wing 2, as shown in Figure 3, to make aircraft 1ift-drag ratio the highest.
Claims (3)
1. a modularization Flying-wing, form primarily of inner wing (1), outer wing (2), it is characterized in that, there are 2 secondary above difformity outer wings (2), corresponding outer wing (2) can be selected to be contained on inner wing (1) according to different aerial mission.
2. a kind of modularization Flying-wing as claimed in claim 1, it is characterized in that, when performing the aerial mission of high stealthy requirement, select large sweepback low aspect ratio outer wing (2), the leading edge sweep of outer wing (2) is identical with the leading edge sweep of inner wing (1), and the trailing sweep of outer wing (2) is identical with the trailing edge sweepforward angle of inner wing (1).
3. a kind of modularization Flying-wing as claimed in claim 1, is characterized in that, during the aerial mission required when executive chairman navigates, selects little sweepback high aspect ratio outer wing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420760818.9U CN204310031U (en) | 2014-12-05 | 2014-12-05 | A kind of modularization Flying-wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420760818.9U CN204310031U (en) | 2014-12-05 | 2014-12-05 | A kind of modularization Flying-wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204310031U true CN204310031U (en) | 2015-05-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201420760818.9U Active CN204310031U (en) | 2014-12-05 | 2014-12-05 | A kind of modularization Flying-wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN204310031U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110254745A (en) * | 2019-06-03 | 2019-09-20 | 西安飞机工业（集团）有限责任公司 | A kind of modularization flying wing type multimachine body aircraft joining method |
| CN115649417A (en) * | 2022-12-14 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | High subsonic speed self-balancing high stealth airfoil profile |
-
2014
- 2014-12-05 CN CN201420760818.9U patent/CN204310031U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110254745A (en) * | 2019-06-03 | 2019-09-20 | 西安飞机工业（集团）有限责任公司 | A kind of modularization flying wing type multimachine body aircraft joining method |
| CN115649417A (en) * | 2022-12-14 | 2023-01-31 | 中国空气动力研究与发展中心空天技术研究所 | High subsonic speed self-balancing high stealth airfoil profile |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |