CN104897355A - Folded wing non-linear flutter test device - Google Patents
Folded wing non-linear flutter test device Download PDFInfo
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- CN104897355A CN104897355A CN201510350838.8A CN201510350838A CN104897355A CN 104897355 A CN104897355 A CN 104897355A CN 201510350838 A CN201510350838 A CN 201510350838A CN 104897355 A CN104897355 A CN 104897355A
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Abstract
The invention relates to the technical field of aeroelastic tests and specifically relates to a folded wing non-linear flutter test device. On a wing flutter model, the folded wing non-linear flutter test device can realize gap nonlinearity respectively and simultaneously in bending and torsion two directions, and the size of each gap can be adjusted by the folded wing non-linear flutter test device. The folded wing non-linear flutter test device comprises a wing inner spar, a wing outer spar, a bending bearing support, a torsion bearing support, a torsion shaft, a bending spring, a torsion spring, a bending gap limiting angle sheet and a torsion gap limiting angle sheet. An outer wing can follow the torsion bearing support to rotate, so that the gap nonlinearity in the central bending direction is realized relative to an inner wing. The outer wing can further follow the torsion shaft to rotate, so that the gap nonlinearity in the central torsion direction is realized relative to the inner wing. In addition, the sizes of a first strip-shaped gap and a second strip-shaped gap can be adjusted, the structure is compact and highly efficient, the simulation of a plurality of test states can be realized on one set of module, and the module machining and testing cost is saved.
Description
Technical field
The present invention relates to aeroelastic effect test technical field, be specifically related to a kind of folding wings Nonlinear Flutter test unit.
Background technology
Wing-folding technology is one of gordian technique of unmanned plane and carrier-borne aircraft design, by being folded by wing, significantly can reduce aircraft and parking shared space.Be generally chain connection between aerofoil inside and outside folding wings, and driven by hydraulic actuation device.Owing to certainly existing gap in hinge arrangement, the backlash nonlinearity caused must affect the structural dynamic characteristics of wing, and then affects the aeroelastic characteristic of wing.Therefore, in the flutter model design of flex-wing vehicle, the impact of backlash nonlinearity must be taken into account.Traditional flutter model method for designing can not realize the folding nonlinear simulation of interplane gap.
Summary of the invention
The object of this invention is to provide a kind of folding wings Nonlinear Flutter test unit, can on flutter of aerofoil model respectively with the backlash nonlinearity simultaneously realizing bending and torsion both direction, and can gap length be regulated.
Technical scheme of the present invention is:
A kind of folding wings Nonlinear Flutter test unit, comprising:
Spar, the outer spar of wing, bending bearing bridge, bending bearing cover, torsion bearing support, torsion shaft, flexural spring, torsionspring, the spacing gusset plate of bent gap and torsion gap limit gusset plate in wing;
The side of described bending bearing bridge is fixedly attached to spar one end end face in described wing, the axial two ends of described bending bearing bridge are symmetrically arranged with bearing seat, the axial two ends of described torsion bearing support are forwarded respectively by bending axis and are dynamicly arranged in the described bearing seat of described bending bearing bridge, and the pivot center of described torsion bearing support is perpendicular to the axis of spar in described wing;
Described torsion bearing support has bearing seat, one end of described torsion shaft is rotated by torsion bearing and is arranged in the described bearing seat of described torsion bearing support, the dead in line of spar in the pivot center of described torsion shaft and described wing, the other end end face of described torsion shaft is fixedly connected with one end end face of the outer spar of described wing;
Described flexural spring is U-shaped, be positioned at described bending bearing cradle top, article one, limit be removably fixed on described bending bearing bridge close described wing in the side of spar, the U-shaped opening direction of described flexural spring is along being parallel to spar upper surface direction in described wing, and with spar axes normal in described wing;
The spacing gusset plate of described bent gap is removably fixed on the top of described torsion bearing support, the spacing gusset plate of described bent gap has a broad-adjustable first bar shaped gap, the length direction in described first bar shaped gap is parallel with spar upper surface in described wing, simultaneously also vertical with spar axis direction in described wing, another limit of described flexural spring is positioned at described first bar shaped gap;
Described torsion gap limit gusset plate is removably fixed on the top of described torsion bearing support, described torsion gap limit gusset plate has a broad-adjustable second bar shaped gap, and the length direction in described second bar shaped gap is perpendicular to the upper surface of the outer spar of described wing;
Described torsionspring is tabular, one end is removably fixed on the outer spar upper surface of described wing, the other end is positioned at the described second bar shaped gap of described torsion gap limit gusset plate, the surface of described torsionspring is vertical with the upper surface of the outer spar of described wing, and the projection of described torsionspring on the outer spar of described wing and the dead in line of the outer spar of described wing.
Alternatively, described bending bearing bridge comprises bending bearing cover, is arranged on the axial two ends of described bending bearing support, forms described bearing seat at the axial two ends of described bending bearing bridge.
Alternatively, described torsion bearing support comprises torsion bearing cover plate, props up be configured to described bearing seat at described torsion bearing cradle top and described torsion bearing.
Alternatively, described torsionspring is removably fixed on the torsionspring bearing of the outer spar upper surface of described wing.
Alternatively, the pivot center of described torsion bearing support and the pivot center of described torsion shaft are positioned at same level.
Alternatively, described folding wings Nonlinear Flutter test unit also comprises bending motion locking plate, and one end is removably fixed on described torsion bearing bracket end, and the other end is removably fixed on described bending bearing bracket end.
Alternatively, caging bolt is provided with between described torsion shaft and described torsion bearing support.
Beneficial effect of the present invention:
Folding wings Nonlinear Flutter test unit of the present invention, outer wing can follow the rotation together of torsion bearing support, thus relatively inner wing realize in the backlash nonlinearity of bending direction; Outer wing can also follow the rotation together of torsion shaft, thus relatively inner wing realize in the backlash nonlinearity of torsional direction; In addition, the size in the first bar shaped gap and the second bar shaped gap can regulate, and compact conformation is efficient, a set of model can realize the simulation of multiple trystate, save mould processing and experimentation cost.
Accompanying drawing explanation
Fig. 1 is the structural representation of folding wings Nonlinear Flutter test unit of the present invention;
Fig. 2 is the axle side structure schematic diagram of key structure of the present invention;
Fig. 3 is the side view of key structure of the present invention;
Fig. 4 is the vertical view of key structure of the present invention;
Fig. 5 is the axle side structure schematic diagram of bending bearing bridge;
Fig. 6 is the axle side structure schematic diagram of torsion bearing support;
Fig. 7 is the axle side structure schematic diagram of torsion bearing cover plate;
Fig. 8 is the axle side structure schematic diagram of torsion shaft.
Embodiment
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.
As depicted in figs. 1 and 2, a kind of folding wings Nonlinear Flutter test unit provided by the invention, at least comprises spar 1 in wing, the outer spar 2 of wing, bending bearing bridge 3, bending bearing cover 4, torsion bearing support 5, torsion shaft 7, flexural spring 9, torsionspring 10, the spacing gusset plate 11 of bent gap and reverses gap limit gusset plate 12.
The side of bending bearing bridge 3 is bolted to connection spar 1 one end end face to wing, and the axial two ends of bending bearing bridge 3 are symmetrically arranged with bearing seat; The axial two ends of torsion bearing support 5 are forwarded respectively by bending axis and are dynamicly arranged in the bearing seat of bending bearing bridge 3, and the pivot center of torsion bearing support 5 is perpendicular to the axis of spar in wing 1.Further, in the present embodiment, bending bearing bridge 3 also comprises bending bearing cover 4, is arranged on the bending axial two ends of bearing bridge 3, and bending bearing bridge 3 forms above-mentioned bearing seat at the axial two ends of bending bearing bridge 3.
Torsion bearing support 5 has bearing seat, and one end of torsion shaft 7 is rotated by torsion bearing and is arranged in the bearing seat of torsion bearing support 5, the dead in line of spar 1 in the pivot center of torsion shaft 7 and wing; One end end face of the other end end face of torsion shaft 7 and the outer spar 2 of wing is bolted to connection.Further, in the present embodiment, torsion bearing support 5 also comprises torsion bearing cover plate 6, forms bearing seat at torsion bearing support 5 top and torsion bearing support 5.Further, in the present embodiment, the pivot center of torsion bearing support 5 and the pivot center of torsion shaft 7 are positioned at same level, can make more compact structure.
Flexural spring 9 is U-shaped, be positioned at bending bearing bridge 3 top, article one, limit be removably fixed on bending bearing bridge 3 close wing in the side of spar 1, the U-shaped opening direction of flexural spring 9 is along being parallel to spar 1 upper surface direction in wing, and with spar in wing 1 axes normal.It should be noted that, above-mentioned removably fixing can adopt multiple applicable mode, adopts bolt to fix in the present embodiment, and follow-up is removably fixing similar with it, will repeat no more.
The spacing gusset plate 11 of bent gap is removably fixed on the top of torsion bearing support 5, the spacing gusset plate of bent gap 11 has a broad-adjustable first bar shaped gap, the length direction in the first bar shaped gap is parallel with spar in wing 1 upper surface, simultaneously also vertical with spar in wing 1 axis direction, another limit of flexural spring 9 is positioned at the first bar shaped gap.Wherein, the spacing gusset plate of bent gap 11 can be multiple applicable structure and size, thus the size in its first bar shaped gap also can have multiple applicable size, can adjust the size of bent gap by changing the spacing gusset plate 11 of bent gap.
Reverse gap limit gusset plate 12, removably be fixed on the top of torsion bearing support 5, described torsion gap limit gusset plate 12 has a broad-adjustable second bar shaped gap, and the length direction in described second bar shaped gap is perpendicular to the upper surface of the outer spar 2 of described wing.Equally, reversing gap limit gusset plate 12 can be multiple applicable structure and size, thus the size in its second bar shaped gap also can have multiple applicable size, can reverse the size that the adjustment of gap limit gusset plate 12 reverses gap by changing.
Torsionspring 10 is in tabular, one end is removably fixed on outer spar 2 upper surface of wing, the other end is positioned at the second bar shaped gap reversing gap limit gusset plate 12, the surface of torsionspring 10 is vertical with the upper surface of the outer spar 2 of wing, and the projection of torsionspring 10 on the outer spar 2 of wing and the dead in line of the outer spar 2 of wing.Further, torsionspring 10 is removably fixed on the torsionspring bearing 8 of outer spar 2 upper surface of wing.
All right bending motion locking plate 13 in folding wings Nonlinear Flutter test unit of the present invention, one end is removably fixed on torsion bearing support 5 end, the other end is removably fixed on bending bearing bridge 3 end, can be limited the rotary motion of the outer bending axis axis of spar 2 on torsion bearing support 5 of wing by bending motion locking plate 13.
In folding wings Nonlinear Flutter test unit of the present invention, between torsion shaft 7 and torsion bearing support 5, can also caging bolt be set, the rotary motion of the outer torsion shaft axis of spar 2 on torsion shaft 7 of wing can be limited.
When spar frame model of the present invention is installed, first bending bearing bridge 3 to be installed in wing on spar 1 by bolt; Load onto bearing at torsion bearing support 5 two ends, torsion bearing support 5 is installed on bending bearing bridge 3, cover bending bearing cover 4, be bolted; Then by bolt, torsion shaft 7 is installed on the outer spar 2 of wing, torsion shaft 7 loads onto bearing, and torsion shaft 7 is installed on torsion bearing support 5, cover torsion bearing cover plate 6, be bolted; By bolt, flexural spring 9 side is installed on bending bearing bridge 3 subsequently, by torsionspring bearing 8, torsionspring 10 is installed on the outer spar 2 of wing, then by bolt, spacing for bent gap gusset plate 11 and torsion gap limit gusset plate 12 is installed on torsion bearing cover plate 6; Finally by bolt, bending motion locking plate 13 is connected with bending bearing bridge 3, torsion bearing support 5, the rotary motion of the outer bending axis axis of spar 2 on torsion bearing support 5 of restriction wing, by caging bolt, torsion bearing support 5 is connected with torsion shaft 7, the outer spar 2 of restriction wing is around the rotary motion of torsion shaft 7 axis, and now wing model is linear system state.
When needs wing model exists backlash nonlinearity at bending direction, bending motion locking plate 13 being unloaded, by changing the spacing gusset plate 11 of bent gap of different size, the size in bent gap (the first gap) can be adjusted.
When there is backlash nonlinearity at torsional direction in needs wing model, caging bolt between torsion bearing support 5 and torsion shaft 7 is unloaded, by changing the torsion gap limit gusset plate 12 of different size, the size reversing gap (the second gap) can be adjusted.
When there is backlash nonlinearity in bending and torsion direction in needs wing model simultaneously, bending motion locking plate 13 and the caging bolt between torsion bearing support 5 and torsion shaft 7 are unloaded simultaneously, by the spacing gusset plate 11 of the bent gap of replacing different size and torsion gap limit gusset plate 12, the size in bent gap and torsion gap can be adjusted simultaneously.
Folding wings Nonlinear Flutter test unit of the present invention, outer wing can follow the rotation together of torsion bearing support, thus relatively inner wing realize in the backlash nonlinearity of bending direction; Outer wing can also follow the rotation together of torsion shaft, thus relatively inner wing realize in the backlash nonlinearity of torsional direction; In addition, the size in the first bar shaped gap and the second bar shaped gap can regulate, and compact conformation is efficient, a set of model can realize the simulation of multiple trystate, save mould processing and experimentation cost.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (7)
1. a folding wings Nonlinear Flutter test unit, is characterized in that, comprising:
Spar (1), the outer spar (2) of wing, bending bearing bridge (3), bending bearing cover (4), torsion bearing support (5), torsion shaft (7), flexural spring (9), torsionspring (10), the spacing gusset plate of bent gap (11) and torsion gap limit gusset plate (12) in wing;
The side of described bending bearing bridge (3) is fixedly attached to spar (1) one end end face in (passing through bolt) described wing, the axial two ends of described bending bearing bridge (3) are symmetrically arranged with bearing seat, the axial two ends of described torsion bearing support (5) are forwarded respectively by bending axis and are dynamicly arranged in the described bearing seat of described bending bearing bridge (3), and the pivot center of described torsion bearing support (5) is perpendicular to the axis of spar (1) in described wing;
Described torsion bearing support (5) has bearing seat, one end of described torsion shaft (7) is rotated by torsion bearing and is arranged in the described bearing seat of described torsion bearing support (5), the dead in line of spar (1) in the pivot center of described torsion shaft (7) and described wing, the other end end face of described torsion shaft (7) is fixedly connected with one end end face of the outer spar (2) of described wing;
Described flexural spring (9) is U-shaped, be positioned at described bending bearing bridge (3) top, article one, limit be removably fixed on described bending bearing bridge (3) close described wing in the side of spar (1), the U-shaped opening direction of described flexural spring (9) is along being parallel to spar (1) upper surface direction in described wing, and with spar (1) axes normal in described wing;
The spacing gusset plate of described bent gap (11) is removably fixed on the top of described torsion bearing support (5), the spacing gusset plate of described bent gap (11) has a broad-adjustable first bar shaped gap, the length direction in described first bar shaped gap is parallel with spar (1) upper surface in described wing, simultaneously also vertical with spar (1) axis direction in described wing, another limit of described flexural spring (9) is positioned at described first bar shaped gap;
Described torsion gap limit gusset plate (12) is removably fixed on the top of described torsion bearing support (5), described torsion gap limit gusset plate (12) has a broad-adjustable second bar shaped gap, and the length direction in described second bar shaped gap is perpendicular to the upper surface of the outer spar (2) of described wing;
Described torsionspring (10) is in tabular, one end is removably fixed on outer spar (2) upper surface of described wing, the other end is positioned at the described second bar shaped gap of described torsion gap limit gusset plate (12), the surface of described torsionspring (10) is vertical with the upper surface of the outer spar (2) of described wing, and the projection of described torsionspring (10) on the outer spar (2) of described wing and the dead in line of the outer spar (2) of described wing.
2. folding wings Nonlinear Flutter test unit according to claim 1, it is characterized in that, described bending bearing bridge (3) comprises bending bearing cover (4), be arranged on the axial two ends of described bending bearing bridge (3), form described bearing seat at the axial two ends of described bending bearing bridge (3).
3. folding wings Nonlinear Flutter test unit according to claim 1 and 2, it is characterized in that, described torsion bearing support (5) comprises torsion bearing cover plate (6), forms described bearing seat at described torsion bearing support (5) top and described torsion bearing support (5).
4. folding wings Nonlinear Flutter test unit according to claim 3, is characterized in that, described torsionspring (10) is removably fixed on the torsionspring bearing (8) of outer spar (2) upper surface of described wing.
5. folding wings Nonlinear Flutter test unit according to claim 3, is characterized in that, the pivot center of described torsion bearing support (5) and the pivot center of described torsion shaft (7) are positioned at same level.
6. folding wings Nonlinear Flutter test unit according to claim 3, it is characterized in that, also comprise bending motion locking plate (13), one end is removably fixed on described torsion bearing support (5) end, and the other end is removably fixed on described bending bearing bridge (3) end.
7. folding wings Nonlinear Flutter test unit according to claim 3, is characterized in that, is provided with caging bolt between described torsion shaft (7) and described torsion bearing support (5).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510350838.8A CN104897355B (en) | 2015-06-23 | 2015-06-23 | Folded wing non-linear flutter test device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510350838.8A CN104897355B (en) | 2015-06-23 | 2015-06-23 | Folded wing non-linear flutter test device |
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| CN104897355A true CN104897355A (en) | 2015-09-09 |
| CN104897355B CN104897355B (en) | 2017-05-17 |
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Cited By (4)
| 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 |
| CN108267285A (en) * | 2018-04-22 | 2018-07-10 | 北京工业大学 | A kind of folded in three wing kinetic characteristics experimental provision using steering engine |
| CN111982460A (en) * | 2020-08-07 | 2020-11-24 | 北京航空航天大学 | Clearance simulation device of wind tunnel model |
| CN114400926A (en) * | 2021-12-28 | 2022-04-26 | 中国航天空气动力技术研究院 | Flutter energy collecting device of two-degree-of-freedom wing segment and wind power generation equipment |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4046001A (en) * | 1974-07-02 | 1977-09-06 | Lion Fat & Oil Co. Limited | Apparatus for measuring restoring force necessary for raising folded portions of hard paper boxes |
| DE4209976A1 (en) * | 1991-04-05 | 1992-10-08 | Cartotecnica Poligrafica A & G | Folded paper tray to carry e.g. food - is cut from single blank, to be folded manually without using adhesive |
| CN1968878A (en) * | 2004-06-22 | 2007-05-23 | 东丽工程株式会社 | Folding device and printing system |
| CN102095577A (en) * | 2011-01-05 | 2011-06-15 | 哈尔滨飞机工业集团有限责任公司 | Load control method for aircraft flap experiment |
| CN202836959U (en) * | 2012-10-25 | 2013-03-27 | 江西洪都航空工业集团有限责任公司 | Test system for aircraft empennage folding and rotating mechanism |
| CN104122067A (en) * | 2013-04-24 | 2014-10-29 | 成都飞机设计研究所 | Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model |
| CN104217106A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Nonlinear dynamics modeling method for rotor lag damper |
-
2015
- 2015-06-23 CN CN201510350838.8A patent/CN104897355B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4046001A (en) * | 1974-07-02 | 1977-09-06 | Lion Fat & Oil Co. Limited | Apparatus for measuring restoring force necessary for raising folded portions of hard paper boxes |
| DE4209976A1 (en) * | 1991-04-05 | 1992-10-08 | Cartotecnica Poligrafica A & G | Folded paper tray to carry e.g. food - is cut from single blank, to be folded manually without using adhesive |
| CN1968878A (en) * | 2004-06-22 | 2007-05-23 | 东丽工程株式会社 | Folding device and printing system |
| CN102095577A (en) * | 2011-01-05 | 2011-06-15 | 哈尔滨飞机工业集团有限责任公司 | Load control method for aircraft flap experiment |
| CN202836959U (en) * | 2012-10-25 | 2013-03-27 | 江西洪都航空工业集团有限责任公司 | Test system for aircraft empennage folding and rotating mechanism |
| CN104122067A (en) * | 2013-04-24 | 2014-10-29 | 成都飞机设计研究所 | Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model |
| CN104217106A (en) * | 2014-08-26 | 2014-12-17 | 中国直升机设计研究所 | Nonlinear dynamics modeling method for rotor lag damper |
Non-Patent Citations (1)
| Title |
|---|
| 徐孝武等: "折叠机翼变体飞机的动力学建模与分析", 《西北工业大学学报》 * |
Cited By (5)
| 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 |
| CN108267285A (en) * | 2018-04-22 | 2018-07-10 | 北京工业大学 | A kind of folded in three wing kinetic characteristics experimental provision using steering engine |
| CN111982460A (en) * | 2020-08-07 | 2020-11-24 | 北京航空航天大学 | Clearance simulation device of wind tunnel model |
| CN114400926A (en) * | 2021-12-28 | 2022-04-26 | 中国航天空气动力技术研究院 | Flutter energy collecting device of two-degree-of-freedom wing segment and wind power generation equipment |
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| CN104897355B (en) | 2017-05-17 |
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