CN202177502U - Large aspect ratio wing transonic flutter model - Google Patents
Large aspect ratio wing transonic flutter model Download PDFInfo
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- CN202177502U CN202177502U CN 201120294839 CN201120294839U CN202177502U CN 202177502 U CN202177502 U CN 202177502U CN 201120294839 CN201120294839 CN 201120294839 CN 201120294839 U CN201120294839 U CN 201120294839U CN 202177502 U CN202177502 U CN 202177502U
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- hollow beam
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- ratio wing
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Abstract
The utility model relates to a large aspect ratio wing transonic flutter model which includes a hollow beam and an outermost glass fiber reinforced plastic skin. Lightweight foam is filled between the hollow beam and the glass fiber reinforced plastic skin. The hollow beam is a rectangular hollow structure. The two sides of the rectangle are provided with lugs. The hollow beam is provided with ribbed slabs which are perpendicular to the hollow beam. The material of the hollow beam is a low density high-modulus metal material. The hollow beam possessing the lugs can reduce the total weight of the model while satisfying the three-dimensional rigidity requirement, and can make the simulation more accurate. The lightweight foam which is produced by the numerical control machining is filled between the hollow beam and the skin, so the inertia distribution is precisely guaranteed, and the arrangement facilitates the production and assembling of the model.
Description
Technical field
The present invention relates to a kind of model, especially high aspect ratio wing flutter model transonic speed belongs to the flutter model field.
Background technology
At high aspect ratio wing low speed model or transonic speed in the making of flutter model, generally adopt following dual mode at present:
(1) roof beam structure adopts solid construction, outer convered glass cloth, and the middle foaming mode that adopts is filled.Adopt in such a way model and be easy to design, processing is simple, but additional stiffness and quality can't accurately control, the too high situation of additional stiffness and additional mass often appears;
(2) main structure adopts compound substance fully, and the root web member adopts metal material.This version is model configuration rigidity and mass distribution preferably.Practice shows, in the place of metalwork and compound substance transition, often appears at the situation of cracking under the big ram compression, because mould processing, receives the restriction of quality control and the restriction of model geometric size unlike the manufacturing of aircraft components, intensity does not often reach requirement.
Summary of the invention
For solving in the wind tunnel test; High aspect ratio aerofoil low speed and problem such as too high or undercapacity of the overweight and additional stiffness of flutter test model transonic speed; The present invention provides a kind of design weight requirement of both having satisfied, and can guarantee the transonic speed flutter model of its buffet characteristic again.
A kind of high aspect ratio wing is flutter model transonic speed, comprises hollow beam, fiberglass covering, is filled with light foam between hollow beam and the fiberglass covering.
The floor of vertical hollow beam is installed on the above-mentioned hollow beam further.
Further, above-mentioned hollow beam is a rectangular configuration, and the rectangle both sides have auricle.
Further, the material of above-mentioned hollow beam is a low-density high-modulus metal material.
The good effect that the present invention produces: adopt the hollow beam of band auricle to make that simulation is more accurate satisfying the overall weight that alleviates model under the situation that three-way rigidity requires; Fill the light foam of digital control processing between hollow beam and the covering, accurately guaranteed the inertia distribution, this version makes the production of model and assembling be easy to carry out.
Description of drawings
Fig. 1 is the utility model one-piece construction synoptic diagram, wherein, and 1: hollow beam, 2: floor, 3: light foam, 4: the fiberglass covering;
Fig. 2 is the hollow beam structural representation, 5: auricle.
Embodiment
Describe in further detail below in conjunction with 1,2 pairs of the utility model of Figure of description.
A kind of high aspect ratio wing is flutter model transonic speed, comprises hollow beam 1, fiberglass covering 4, is filled with light foam 3 between hollow beam 1 and the fiberglass covering 4, recommends to adopt the Degussa foam.Adopt under the situation that the hollow beam structure makes that rigidity remains unchanged basically quality the lightest.
As the another optimal way of the utility model, the floor 2 of vertical hollow beam 1 is installed on the above-mentioned hollow beam 1.The quantity of floor 2 confirms according to actual conditions, owing to filled by light foam 3 fully in the middle of the model, so the suitable attenuate of the thickness of floor 2, but can bear the overload more than the 5g will guarantee that lumped mass applies on it through calculating the time, and is as shown in Figure 1.
As one of optimal way of the utility model, above-mentioned hollow beam 1 is a rectangular configuration, and the rectangle both sides have auricle 5, and are as shown in Figure 2.
Further, the material of above-mentioned hollow beam is a low-density high-modulus metal material.Recommend to adopt prestretched aluminum alloy plate materials 7075-T7451, it is light that it has density, and strength character is good, the advantage that material property is stable.
Technique effect: the utility model adopts the hollow beam of band auricle fundamentally to have solved the transonic speed overweight problem of flutter model satisfying the overall weight that alleviates model under the situation that three-way rigidity requires; Fill the light foam of digital control processing between hollow beam and the covering, accurately guaranteed the inertia distribution, make that simulation is more accurate; This version makes that the modelling process and assemble is easy to carry out, and the whole project cycle is significantly shortened.
Claims (4)
1. high aspect ratio wing flutter model transonic speed, it is characterized in that: comprise hollow beam, outermost fiberglass covering is filled with light foam between hollow beam and the fiberglass covering.
2. high aspect ratio wing according to claim 1 is flutter model transonic speed, it is characterized in that: the floor that vertical hollow beam is installed on the hollow beam.
3. high aspect ratio wing according to claim 1 is flutter model transonic speed, it is characterized in that: hollow beam is the rectangle hollow structure, and the rectangle both sides have auricle.
4. high aspect ratio wing according to claim 1 and 2 is flutter model transonic speed, it is characterized in that: the material of hollow beam is a low-density high-modulus metal material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120294839 CN202177502U (en) | 2011-08-15 | 2011-08-15 | Large aspect ratio wing transonic flutter model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120294839 CN202177502U (en) | 2011-08-15 | 2011-08-15 | Large aspect ratio wing transonic flutter model |
Publications (1)
| Publication Number | Publication Date |
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| CN202177502U true CN202177502U (en) | 2012-03-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN 201120294839 Expired - Lifetime CN202177502U (en) | 2011-08-15 | 2011-08-15 | Large aspect ratio wing transonic flutter model |
Country Status (1)
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| CN (1) | CN202177502U (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102645317A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Hollow beam with four lugs for high-speed flutter model and fabrication method of hollow beam |
| CN102874417A (en) * | 2012-09-29 | 2013-01-16 | 西安电子科技大学 | Truss structure of large-span large-deflection cantilever test bed |
| CN102968526A (en) * | 2012-11-12 | 2013-03-13 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining counterweight of flutter model of high-aspect-ratio wing |
| CN103077286A (en) * | 2013-01-18 | 2013-05-01 | 大连理工大学 | Method for correcting frequency errors of aircraft flutter model |
| CN104048809A (en) * | 2014-05-06 | 2014-09-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-freedom-degree simulation external store flutter model for wind tunnel test |
| CN104890899A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Rotation flutter simulation device |
| CN105571816A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Combined flutter model with adjustable gap |
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
| CN108001706A (en) * | 2017-11-29 | 2018-05-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of big span aircraft wing elastic deformation computational methods |
| CN108216570A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of high aspect ratio wing main plane structure |
| CN110595728A (en) * | 2019-09-02 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Pre-stress technology-based flutter model and design method thereof |
| CN110887633A (en) * | 2019-12-25 | 2020-03-17 | 中国航空工业集团公司西安飞机设计研究所 | Elastic gust response wind tunnel test device |
-
2011
- 2011-08-15 CN CN 201120294839 patent/CN202177502U/en not_active Expired - Lifetime
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102645317B (en) * | 2012-05-11 | 2014-10-22 | 中国航空工业集团公司西安飞机设计研究所 | Hollow beam with four lugs for high-speed flutter model and fabrication method of hollow beam |
| CN102645317A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Hollow beam with four lugs for high-speed flutter model and fabrication method of hollow beam |
| CN102874417A (en) * | 2012-09-29 | 2013-01-16 | 西安电子科技大学 | Truss structure of large-span large-deflection cantilever test bed |
| CN102968526B (en) * | 2012-11-12 | 2016-06-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of high aspect ratio wing flutter model counterweight defining method |
| CN102968526A (en) * | 2012-11-12 | 2013-03-13 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining counterweight of flutter model of high-aspect-ratio wing |
| CN103077286A (en) * | 2013-01-18 | 2013-05-01 | 大连理工大学 | Method for correcting frequency errors of aircraft flutter model |
| CN103077286B (en) * | 2013-01-18 | 2016-01-13 | 大连理工大学 | A kind of frequency error correction method of plane flutter model |
| CN104048809B (en) * | 2014-05-06 | 2016-05-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Three Degree Of Freedom simulation store Combinations flutter model for wind tunnel test |
| CN104048809A (en) * | 2014-05-06 | 2014-09-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Three-freedom-degree simulation external store flutter model for wind tunnel test |
| CN105571816B (en) * | 2014-10-11 | 2018-01-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of combined type flutter model of adjustable clearance |
| CN105571816A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Combined flutter model with adjustable gap |
| CN104890899A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Rotation flutter simulation device |
| CN106043735A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Rigidity-equivalent wing static gas spring model |
| CN108001706A (en) * | 2017-11-29 | 2018-05-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of big span aircraft wing elastic deformation computational methods |
| CN108001706B (en) * | 2017-11-29 | 2021-03-09 | 中国航空工业集团公司西安飞机设计研究所 | Large-span aircraft wing elastic deformation calculation method |
| CN108216570A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of high aspect ratio wing main plane structure |
| CN108216570B (en) * | 2017-12-14 | 2023-08-18 | 中航(成都)无人机系统股份有限公司 | Main wing surface structure of high aspect ratio wing |
| CN110595728A (en) * | 2019-09-02 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Pre-stress technology-based flutter model and design method thereof |
| CN110595728B (en) * | 2019-09-02 | 2021-07-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Pre-stress technology-based flutter model and design method thereof |
| CN110887633A (en) * | 2019-12-25 | 2020-03-17 | 中国航空工业集团公司西安飞机设计研究所 | Elastic gust response wind tunnel test device |
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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: 20120328 |