CN105571816A - Combined flutter model with adjustable gap - Google Patents
Combined flutter model with adjustable gap Download PDFInfo
- Publication number
- CN105571816A CN105571816A CN201410535670.3A CN201410535670A CN105571816A CN 105571816 A CN105571816 A CN 105571816A CN 201410535670 A CN201410535670 A CN 201410535670A CN 105571816 A CN105571816 A CN 105571816A
- Authority
- CN
- China
- Prior art keywords
- frame section
- lower frame
- linking springs
- section
- springs sheet
- 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.)
- Granted
Links
Landscapes
- Joining Of Building Structures In Genera (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
Abstract
The invention provides a combined flutter model with an adjustable gap. The combined flutter model is characterized in that the combined flutter model comprises frame segments (1), a beam rack (2) and connecting spring leafs (3); each frame segment (1) is divided into an upper frame segment (1-1) and a lower frame segment (1-2); the upper frame segment (1-1) is detachably connected with the lower frame segment (1-2); each connecting spring leaf (3) is mounted on the lower frame segment (1-2) and is connected with the adjacent lower frame segment (1-2); the adjacent lower frame segment (1-2) is integrated with the beam rack (2) through the connecting spring leaf (3); and the connecting spring leaf (3) is used for adjusting a clearance between the adjacent frame segments (1-2).
Description
Technical field
The invention belongs to aeroelastic effect test technical field, particularly relate to a kind of combined type flutter model of adjustable clearance.
Background technology
Flutter model wind tunnel test is the important means of checking airplane flutter characteristic, and the design of flutter model is particularly important.Traditional flutter model normally simulates rigidity with beams of metal, and wooden frame section simulates profile, and wooden frame section is connected on beams of metal by middle stiffening rib, when model is installed, be subject to Action of Gravity Field, between frame section, inevitably there will be difference in height, be difficult to repair; And when designing flutter model, usually can design the model of multiple rigidity state, this just needs the metal roof beam structure producing different size.According to processing mode in the past, during processing profile frame section, directly rib is directly glued on beams of metal by respective erect-position, be stained with dimension shape stringer and covering subsequently again, this just cannot be detailed the qualitative data of measurement profile frame section, this just calculates the counterweight of model and brings difficulty, and the mass property of flutter model cannot be consistent with computation model, and each rigidity state just needs a set of roof beam structure and profile frame section, and this just considerably increases experimentation cost and modelling time.
Summary of the invention
The object of the invention is: the combined type flutter model that a kind of adjustable clearance is provided, when installing flutter model, the profile frame section of model can be removed and installed efficiently, the gap between profile frame section can be adjusted.
Technical scheme of the present invention is: a kind of combined type flutter model of adjustable clearance, it is characterized in that, comprise: frame section [1], roof beam structure [2], linking springs sheet [3], frame section [1] is divided into again upper ledge section [1-1] and lower frame section [1-2] two parts, removably connect between upper ledge section [1-1] and lower frame section [1-2], linking springs sheet [3] is arranged on the adjacent lower frame section [1-2] of the upper connection of lower frame section [1-2], adjacent lower frame section [1-2] is connected in one by linking springs sheet [3] and roof beam structure [2] again, linking springs sheet [3] is for regulating the gap between adjacent lower frame section [1-2].
Further, frame section [1] respectively by dimension shape stringer [1-3], dimension property rib [1-4], stiffening rib [1-5], covering [1-6] is cementing forms, in each frame section [1], dimension shape stringer [1-3] two ends are stiffening rib [1-5], middle is dimension shape rib [1-4], the outer surface that dimension shape stringer [1-3] and dimension property rib [1-4], stiffening rib [1-5] are formed is sticky covering [1-6] again, and the stiffening rib [1-3] of described lower frame section [1-2] is provided with linking springs sheet [3].
Further, be connected with plate nut [1-8] by pre-buried attachment lug [1-7] between upper ledge section [1-1] and lower frame section [1-2].
Further, linking springs sheet [3] is for inverted U-shaped, and the auricle [3-1] on linking springs sheet [3] top and roof beam structure [2] is bolted integral.
Advantage of the present invention is: the profile frame section of the flutter model of the present invention's design is divided into upper and lower two parts, between frame section, frame section is connected by spring leaf with between roof beam structure, the intersegmental gap of profile frame can be adjusted by adjustment spring leaf, and achieve the detachable of flutter model profile frame section, the mass property of profile frame section can be measured accurately, different rigidity states can use same set of profile frame section, saves experimentation cost and modelling time.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
Fig. 2 is skeleton view of the present invention;
Fig. 3 is lower frame section connection diagram;
Wherein, 1-frame section, 2-roof beam structure, 3-linking springs sheet, 1-1-upper ledge section, 1-2-lower frame section, 1-3-ties up shape stringer, and 1-4-ties up shape rib, 1-5-stiffening rib, 1-6-covering, 1-7-attachment lug, 1-8-plate nut.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail, refers to Fig. 1 to Fig. 3.
As shown in Figure 1, for structural representation of the present invention, a kind of combined type flutter model of adjustable clearance, comprise frame section 1, roof beam structure 2, linking springs sheet 3, frame section 1 is divided into again upper ledge section 1-1 and lower frame section 1-2 two parts, removably connect between upper ledge section 1-1 and lower frame section 1-2, linking springs sheet 3 is arranged on the lower frame section 1-2 that on lower frame section 1-2, connection is adjacent, adjacent lower frame section 1-2 is connected in one by linking springs sheet 3 and roof beam structure 2 again, and linking springs sheet 3 is for regulating the gap between adjacent lower frame section 1-2.
Frame section 1 respectively by dimension shape stringer 1-3, dimension property rib 1-4, stiffening rib 1-5, covering 1-6 is cementing forms, in each frame section 1, dimension shape stringer 1-3 two ends are stiffening rib 1-5, middle is dimension shape rib 1-4, the outer surface sticky covering 1-6 again that dimension shape stringer 1-3 and dimension property rib 1-4, stiffening rib 1-5 are formed, the stiffening rib 1-3 of described lower frame section 1-2 is provided with linking springs sheet 3.
Be connected with plate nut 1-8 by pre-buried attachment lug 1-7 between upper ledge section 1-1 and lower frame section 1-2.
Linking springs sheet 3 is inverted U-shaped, and the auricle 3-1 on linking springs sheet 3 top and roof beam structure 2 is bolted integral.
The present invention, when installing flutter model, can remove and install the profile frame section of model efficiently, can adjust the gap between profile frame section.When model is installed, first adjacent lower frame section 1-2 linking springs sheet 1-3 is connected, by bolt, linking springs sheet 1-3 is fixed on the stiffening rib 1-5 of lower frame section 1-2, by bolt, linking springs sheet 3 top is connected with the auricle 3-1 on roof beam structure 2 again, again the attachment lug 1-7 on upper ledge section 1-1 is aimed at the plate nut 1-8 on lower frame section 1-2, by bolt, upper ledge section 1-1 is connected with lower frame section 1-2, composition frame section 1.After assembling flutter model, according to the gap length of frame section 1, the angle of adjustment linking springs sheet 1-3, until gap length is suitable.When needing the replacing of the rigidity state of carrying out model, first the bolt of the plate nut 1-8 of the attachment lug 1-7 on connection box section 1-1 on lower frame section 1-2 is unloaded, take off upper ledge section 1-1, the bolt of the auricle 3-1 connected on linking springs sheet 3 top and roof beam structure 2 is unloaded, take off lower frame section 1-2, change roof beam structure 2, then by appeal step installing frame section 1.
Claims (4)
1. the combined type flutter model of an adjustable clearance, it is characterized in that, comprise: frame section [1], roof beam structure [2], linking springs sheet [3], frame section [1] is divided into again upper ledge section [1-1] and lower frame section [1-2] two parts, removably connect between upper ledge section [1-1] and lower frame section [1-2], linking springs sheet [3] is arranged on the adjacent lower frame section [1-2] of the upper connection of lower frame section [1-2], adjacent lower frame section [1-2] is connected in one by linking springs sheet [3] and roof beam structure [2] again, linking springs sheet [3] is for regulating the gap between adjacent lower frame section [1-2].
2. the combined type flutter model of adjustable clearance according to claim 1, it is characterized in that, frame section [1] is respectively by dimension shape stringer [1-3], dimension property rib [1-4], stiffening rib [1-5], covering [1-6] is cementing to be formed, in each frame section [1], dimension shape stringer [1-3] two ends are stiffening rib [1-5], middle is dimension shape rib [1-4], dimension shape stringer [1-3] and dimension property rib [1-4], the outer surface that stiffening rib [1-5] is formed is sticky covering [1-6] again, the stiffening rib [1-3] of described lower frame section [1-2] is provided with linking springs sheet [3].
3. the combined type flutter model of adjustable clearance according to claim 1, is characterized in that, is connected between upper ledge section [1-1] and lower frame section [1-2] by pre-buried attachment lug [1-7] with plate nut [1-8].
4. the combined type flutter model of adjustable clearance according to claim 1, is characterized in that, linking springs sheet [3] is for inverted U-shaped, and the auricle [3-1] on linking springs sheet [3] top and roof beam structure [2] is bolted integral.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535670.3A CN105571816B (en) | 2014-10-11 | 2014-10-11 | A kind of combined type flutter model of adjustable clearance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535670.3A CN105571816B (en) | 2014-10-11 | 2014-10-11 | A kind of combined type flutter model of adjustable clearance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105571816A true CN105571816A (en) | 2016-05-11 |
| CN105571816B CN105571816B (en) | 2018-01-16 |
Family
ID=55882202
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410535670.3A Active CN105571816B (en) | 2014-10-11 | 2014-10-11 | A kind of combined type flutter model of adjustable clearance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105571816B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017851A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Movable surface operation gap simulating device |
| CN108033036A (en) * | 2017-11-29 | 2018-05-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flying tail flutter model rotary gap simulator |
| CN114993599A (en) * | 2022-05-31 | 2022-09-02 | 上海交通大学 | Wind tunnel test model for verifying influence of wing trailing edge cabin gap on vibration characteristic of wing trailing edge cabin gap |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0854316A (en) * | 1994-08-12 | 1996-02-27 | Mitsubishi Heavy Ind Ltd | Flutter model for rudder |
| CN101509825A (en) * | 2009-03-13 | 2009-08-19 | 西安交通大学 | Aeroplane buffet air tunnel model integration design and manufacturing method |
| CN201724807U (en) * | 2010-02-26 | 2011-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
| CN202177502U (en) * | 2011-08-15 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Large aspect ratio wing transonic flutter model |
| CN202226068U (en) * | 2011-08-15 | 2012-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Quick demounting port cover for frame segment counterweight cabin of aerofoil flutter model |
| CN202485893U (en) * | 2011-12-20 | 2012-10-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Transonic flutter wind tunnel test model surface modeling maintaining device |
| 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 |
-
2014
- 2014-10-11 CN CN201410535670.3A patent/CN105571816B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0854316A (en) * | 1994-08-12 | 1996-02-27 | Mitsubishi Heavy Ind Ltd | Flutter model for rudder |
| CN101509825A (en) * | 2009-03-13 | 2009-08-19 | 西安交通大学 | Aeroplane buffet air tunnel model integration design and manufacturing method |
| CN201724807U (en) * | 2010-02-26 | 2011-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Connector for horizontal stabilizer and vertical stabilizer of flutter model |
| CN202177502U (en) * | 2011-08-15 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Large aspect ratio wing transonic flutter model |
| CN202226068U (en) * | 2011-08-15 | 2012-05-23 | 中国航空工业集团公司西安飞机设计研究所 | Quick demounting port cover for frame segment counterweight cabin of aerofoil flutter model |
| CN202485893U (en) * | 2011-12-20 | 2012-10-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Transonic flutter wind tunnel test model surface modeling maintaining device |
| 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 |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106017851A (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Movable surface operation gap simulating device |
| CN106017851B (en) * | 2016-05-16 | 2018-11-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of active face manipulation gap simulator |
| CN108033036A (en) * | 2017-11-29 | 2018-05-15 | 中国航空工业集团公司西安飞机设计研究所 | A kind of flying tail flutter model rotary gap simulator |
| CN108033036B (en) * | 2017-11-29 | 2021-03-12 | 中国航空工业集团公司西安飞机设计研究所 | Full-motion horizontal tail flutter model rotating gap simulation device |
| CN114993599A (en) * | 2022-05-31 | 2022-09-02 | 上海交通大学 | Wind tunnel test model for verifying influence of wing trailing edge cabin gap on vibration characteristic of wing trailing edge cabin gap |
| CN114993599B (en) * | 2022-05-31 | 2023-02-24 | 上海交通大学 | Wind tunnel test model for verifying influence of wing trailing edge cabin gap on vibration characteristic of wing trailing edge cabin gap |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105571816B (en) | 2018-01-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2893338A1 (en) | Fuselage structure of an unmanned helicopter | |
| CN105571816A (en) | Combined flutter model with adjustable gap | |
| WO2009133217A8 (en) | Support-model assembly with minimum aerodynamic interference for tests in the transonic range in a wind tunnel | |
| CN205010505U (en) | Control rigidity analogue means and have its rudder face transonic flutter model | |
| CN105178609A (en) | High-altitude bulk construction method for steel-structure grid | |
| CN105486484A (en) | Pylon pitching modal simulation device suitable to be used for flutter wind tunnel model | |
| CN204776081U (en) | A simulation core level and assembly operations platform for large -scale boost motor is experimental | |
| CN203097306U (en) | Assembled type building wallboard installation tool | |
| CN204694442U (en) | A kind of combined type rectification fuselage being applicable to transonic speed wing flutter test | |
| EP2530021A3 (en) | Assembling jig for at least one section of an aircraft fuselage | |
| CN102380835A (en) | Novel air guide sleeve assembly device for simulating wheel hub of wind driven generator | |
| CN204819252U (en) | Novel engine supporting structure | |
| CN204098298U (en) | A kind of metal energy-saving curtain wall | |
| CN202177495U (en) | Novel high speed flutter test model control rigidity analogue means | |
| CN103376220A (en) | Curve or distortion detection and prestressing force infliction experiment table for composite material C-type beam | |
| CN207292477U (en) | A kind of micro- truss aerofoil flutter model | |
| CN203679694U (en) | Adjustable elevator counter-weight frame assembly fixture | |
| CN203843743U (en) | Positioning and replacing device for supporting arm connector part on aircraft wing beam | |
| CN106342053B (en) | A kind of helicopter tailplane jockey and tailplane | |
| CN205176676U (en) | Seat support support frame torsional spring torsion adjusting device | |
| CN202725687U (en) | Adjusting device for skid | |
| CN207522420U (en) | Convenient for being rapidly assembled and disassembled the mounting platform of workpiece | |
| CN106314829B (en) | Simulation core grade and assembly manipulation platform for the experiment of large-scale boost motor | |
| CN203791926U (en) | Maintenance device for deformed rods of tower cranes | |
| CN104369136B (en) | Locomotive cab in-built top board skeleton mounting tool and installation method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |