CN104897355B - Folded wing non-linear flutter test device - Google Patents
Folded wing non-linear flutter test device Download PDFInfo
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- CN104897355B CN104897355B CN201510350838.8A CN201510350838A CN104897355B CN 104897355 B CN104897355 B CN 104897355B CN 201510350838 A CN201510350838 A CN 201510350838A CN 104897355 B CN104897355 B CN 104897355B
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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, and in particular to a kind of folding wings Nonlinear Flutter assay device.
Background technology
Wing-folding technology is one of key technology of unmanned plane and carrier-borne aircraft design, by the way that wing is folded, can
Shared space is parked to be substantially reduced aircraft.Chain connection is usually inside and outside folding wings between aerofoil, and by hydraulic pressure
Acting device is driving.Due to certainly existing gap in hinge arrangement, caused by backlash nonlinearity necessarily affect the knot of wing
Structure dynamicss, and then affect the aeroelastic characteristic of wing.Therefore in the flutter model design of flex-wing vehicle, must
The impact of palpus meter and backlash nonlinearity.Traditional flutter model method for designing can not be realized to folding the nonlinear mould of interplane gap
Intend.
The content of the invention
It is an object of the invention to provide a kind of folding wings Nonlinear Flutter assay device, can divide on flutter of aerofoil model
And simultaneously do not realize bending and reverse the backlash nonlinearity of both direction, and gap length can be adjusted.
The technical scheme is that：
A kind of folding wings Nonlinear Flutter assay device, including：
Spar in wing, wing outer spar, the bending support of bearing, bending bearing cover, torsion bearing support, torsional axiss,
The spacing gusset plate of flexural spring, torsionspring, bent gap and torsion gap limit gusset plate；
The side of the bending support of bearing is fixedly attached to spar one end end face in the wing, the bending bearing
The axial two ends of frame are symmetrically arranged with bearing block, and dynamic setting is forwarded in the axial two ends of the torsion bearing support by bending axis respectively
Put in the bearing block of the bending support of bearing, the pivot center of the torsion bearing support is in the wing
The axis of spar；
There is bearing block, one end of the torsional axiss is rotatably arranged on institute by torsion bearing on the torsion bearing support
State in the bearing block of torsion bearing support, the dead in line of the pivot center of the torsional axiss and spar in the wing,
The other end end face of the torsional axiss is fixedly connected with one end end face of the wing outer spar；
The flexural spring is U-shaped, and positioned at the bending bearing cradle top, a line is removably attached to described curved
The side of spar in the close described wing of the bent support of bearing, the U-shaped opening direction of the flexural spring is along parallel to described
Spar upper surface direction in wing, and it is vertical with spar axis in the wing；
The spacing gusset plate of the bent gap is removably attached to the top of the torsion bearing support, the bent gap
Spacing gusset plate has a broad-adjustable first bar shaped gap, the length direction in the first bar shaped gap and the wing inner wing
Beam upper surface is parallel, while also vertical with spar axis direction in the wing, the another a line of the flexural spring is located at institute
State in the first bar shaped gap；
It is described to reverse the top that gap limit gusset plate is removably attached to the torsion bearing support, the torsion gap
Spacing gusset plate has a broad-adjustable second bar shaped gap, and the length direction in the second bar shaped gap is perpendicular to the wing
The upper surface of outer spar；
The torsionspring is plate-like, and one end is removably attached to the wing outer spar upper surface, and the other end is located at
In the second bar shaped gap for reversing gap limit gusset plate, the surface of the torsionspring and the wing outer spar
Upper surface is vertical, and the dead in line of projection of the torsionspring on the wing outer spar and the wing outer spar.
Alternatively, the bending support of bearing includes bending bearing cover, is arranged on the bending bearing support axial direction two
End, at the axial two ends of the bending support of bearing bearing block is constituted.
Alternatively, the torsion bearing support include torsion bearing cover plate, the torsion bearing cradle top with it is described
Torsion bearing support constitutes the bearing block.
Alternatively, the torsionspring is removably attached to the torsionspring bearing of the wing outer spar upper surface
On.
Alternatively, the pivot center of the torsion bearing support is located at same level with the pivot center of the torsional axiss
Face.
Alternatively, described folding wings Nonlinear Flutter assay device also includes curvature movement locking plate, and one end is detachable
Be fixed on the torsion bearing bracket end, the other end is removably attached to the bending bearing bracket end.
Alternatively, it is provided with caging bolt between the torsional axiss and the torsion bearing support.
Beneficial effects of the present invention：
The folding wings Nonlinear Flutter assay device of the present invention, outer wing can follow the rotation together of torsion bearing support,
The backlash nonlinearity of bending direction in realizing so as to relative inner wing；Outer wing can also follow the rotation together of torsional axiss, so as to phase
The backlash nonlinearity of torsional direction in realizing to inner wing；In addition, the size in the first bar shaped gap and the second bar shaped gap can be adjusted
Section, compact conformation efficiently, can realize the simulation of multiple trystates in a set of model, save mould processing and test into
This.
Description of the drawings
Fig. 1 is the structural representation of folding wings Nonlinear Flutter assay device 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 top view of key structure of the present invention；
Fig. 5 is the axle side structure schematic diagram for bending the support of bearing；
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 torsional axiss.
Specific embodiment
Here exemplary embodiment will be illustrated in detail, its example is illustrated in the accompanying drawings.Explained below is related to
During accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawings represent same or analogous key element.
As depicted in figs. 1 and 2, a kind of folding wings Nonlinear Flutter assay device that the present invention is provided, at least including wing
Interior spar 1, wing outer spar 2, the bending support of bearing 3, bending bearing cover 4, torsion bearing support 5, torsional axiss 7, bending bullet
The spacing gusset plate 11 of spring 9, torsionspring 10, bent gap and torsion gap limit gusset plate 12.
The side of the bending support of bearing 3 is bolted to connection to wing one end end face of spar 1, bends the support of bearing
3 axial two ends are symmetrically arranged with bearing block；Held by bending axis respectively and be rotatably arranged in the axial two ends of torsion bearing support 5
In the bearing block of the bending support of bearing 3, the axis of pivot center spar 1 in wing of torsion bearing support 5.Enter one
Step, in the present embodiment, the bending support of bearing 3 also includes bending bearing cover 4, is arranged on the axial two ends of the bending support of bearing 3,
The bending support of bearing 3 constitutes above-mentioned bearing block at the axial two ends of the bending support of bearing 3.
There is bearing block, one end of torsional axiss 7 is rotatably arranged on torsion bearing by torsion bearing on torsion bearing support 5
In the bearing block of support 5, the dead in line of spar 1 in the pivot center and wing of torsional axiss 7；The other end end face of torsional axiss 7
It is bolted to connection with one end end face of wing outer spar 2.Further, in the present embodiment, torsion bearing support 5 also includes
Torsion bearing cover plate 6, bearing block is constituted at the top of torsion bearing support 5 with torsion bearing support 5.Also, in the present embodiment, turn round
The pivot center of the pivot center and torsional axiss 7 that turn the support of bearing 5 is located at same level, enables to more compact structure.
Flexural spring 9 is U-shaped, and positioned at the top of the bending support of bearing 3, a line is removably attached to bend the support of bearing
The side of spar 1 in 3 close wing, the U-shaped opening direction of flexural spring 9 is along parallel to the upper surface side of spar in wing 1
To, and it is vertical with the axis of spar in wing 1.It should be noted that it is above-mentioned be removably secured can with using various suitable modes,
Fixed using bolt in the present embodiment, follow-up being removably secured is similar therewith, will not be described in great detail.
The spacing gusset plate 11 of bent gap is removably attached to the top of torsion bearing support 5, the spacing gusset plate of bent gap
11 have a broad-adjustable first bar shaped gap, and the length direction in the first bar shaped gap is parallel with the upper surface of spar in wing 1,
Simultaneously also vertical with the axis direction of spar in wing 1, the another a line of flexural spring 9 is located in the first bar shaped gap.Wherein, it is curved
Bent gap limit gusset plate 11 can be various suitable structures and size, so as to the size in its first bar shaped gap can also have many
Suitable size is planted, can pass through to change the size that the spacing gusset plate 11 of bent gap adjusts bent gap.
Gap limit gusset plate 12 is reversed, the top of torsion bearing support 5, the torsion gap limit is removably attached to
Gusset plate 12 has a broad-adjustable second bar shaped gap, and the length direction in the second bar shaped gap is outside the wing
The upper surface of spar 2.Equally, it can be various suitable structures and size to reverse gap limit gusset plate 12, so as to its Article 2
The size in shape gap can also have various suitable sizes, can reverse the adjustment torsion of gap limit gusset plate 12 gap by changing
Size.
Torsionspring 10 is plate-like, and one end is removably attached to the upper surface of wing outer spar 2, and the other end is located between reversing
In second bar shaped gap of the spacing gusset plate 12 of gap, the surface of torsionspring 10 is vertical with the upper surface of wing outer spar 2, and reverses
Projection of the spring 10 on wing outer spar 2 and the dead in line of wing outer spar 2.Further, torsionspring 10 is removably
It is fixed on the torsionspring bearing 8 of the upper surface of wing outer spar 2.
Can be with curvature movement locking plate 13 in the folding wings Nonlinear Flutter assay device of the present invention, one end is removably
The end of torsion bearing support 5 is fixed on, the other end is removably attached to bend the end of the support of bearing 3, can be by bending fortune
Dynamic locking plate 13 limits the rotary motion of bending axis axis of the wing outer spar 2 on torsion bearing support 5.
In the folding wings Nonlinear Flutter assay device of the present invention, can also set between torsional axiss 7 and torsion bearing support 5
Caging bolt is put, the rotary motion of torsional axiss axis of the wing outer spar 2 on torsional axiss 7 can be limited.
When the spar frame model of the present invention is installed, bolt is first passed through by the support of bearing 3 is bent and be installed to spar 1 in wing
On；Bearing is loaded onto at the two ends of torsion bearing support 5, torsion bearing support 5 is installed on the bending support of bearing 3, cover bending
Bearing cover 4, is bolted；Then torsional axiss 7 are installed on wing outer spar 2 by bolt, are loaded onto on torsional axiss 7
Bearing, and torsional axiss 7 are installed on torsion bearing support 5, torsion bearing cover plate 6 is covered, it is bolted；Subsequently pass through spiral shell
Bolt is installed to the side of flexural spring 9 on the bending support of bearing 3, and torsionspring 10 is installed to into machine by torsionspring bearing 8
On wing outer spar 2, then the spacing gusset plate 11 of bent gap and torsion gap limit gusset plate 12 are installed to by torsion bearing by bolt
On cover plate 6；Curvature movement locking plate 13 is connected with the bending support of bearing 3, torsion bearing support 5 finally by bolt, is limited
The rotary motion of bending axis axis of the wing outer spar 2 on torsion bearing support 5, by caging bolt by torsion bearing support
5 are connected with torsional axiss 7, limit rotary motion of the wing outer spar 2 around the axis of torsional axiss 7, and now wing model is linear system
State.
When needing wing model to there is backlash nonlinearity in bending direction, curvature movement locking plate 13 is unloaded,
By changing the spacing gusset plate 11 of various sizes of bent gap, the size in bent gap (the first gap) can be adjusted.
When needing wing model to there is backlash nonlinearity in torsional direction, by between torsion bearing support 5 and torsional axiss 7
Caging bolt unload, by changing various sizes of torsion gap limit gusset plate 12, torsion gap (second can be adjusted
Gap) size.
When needing wing model in bending and torsional direction while when there is backlash nonlinearity, by curvature movement locking plate 13
And the caging bolt between torsion bearing support 5 and torsional axiss 7 is unloaded simultaneously, by changing various sizes of bent gap
Spacing gusset plate 11 and torsion gap limit gusset plate 12, can simultaneously adjust bent gap and reverse the size in gap.
The folding wings Nonlinear Flutter assay device of the present invention, outer wing can follow the rotation together of torsion bearing support,
The backlash nonlinearity of bending direction in realizing so as to relative inner wing；Outer wing can also follow the rotation together of torsional axiss, so as to phase
The backlash nonlinearity of torsional direction in realizing to inner wing；In addition, the size in the first bar shaped gap and the second bar shaped gap can be adjusted
Section, compact conformation efficiently, can realize the simulation of multiple trystates in a set of model, save mould processing and test into
This.
The above, the only specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of the claims
It is accurate.
Claims (7)
1. a kind of folding wings Nonlinear Flutter assay device, it is characterised in that include：
Spar (1), wing outer spar (2), the bending support of bearing (3), bending bearing cover (4), torsion bearing support in wing
(5), torsional axiss (7), flexural spring (9), torsionspring (10), the spacing gusset plate of bent gap (11) and torsion gap limit angle
Piece (12)；
The side of the bending support of bearing (3) is bolted to connection to the wing spar (1) one end end face, described
The axial two ends of the bending support of bearing (3) are symmetrically arranged with bearing block, and the axial two ends of the torsion bearing support (5) lead to respectively
Cross bending axis hold be rotatably arranged on it is described bending the support of bearing (3) the bearing block in, the torsion bearing support (5) turn
The axis of shaft line spar (1) in the wing；
There is bearing block, one end of the torsional axiss (7) is rotatably arranged on by torsion bearing on the torsion bearing support (5)
In the bearing block of the torsion bearing support (5), the pivot center of the torsional axiss (7) and spar (1) in the wing
Dead in line, the other end end face of the torsional axiss (7) is fixedly connected with one end end face of the wing outer spar (2)；
The flexural spring (9) is U-shaped, and positioned at the bending support of bearing (3) top, a line is removably attached to described
The side of spar (1) in the close described wing of the bending support of bearing (3), the U-shaped opening direction of the flexural spring (9) is edge
It is parallel to spar (1) upper surface direction in the wing and vertical with spar (1) axis in the wing；
The spacing gusset plate (11) of the bent gap is removably attached to the top of the torsion bearing support (5), the bending
Gap limit gusset plate (11) with a broad-adjustable first bar shaped gap, the length direction in the first bar shaped gap with it is described
Spar (1) upper surface is parallel in wing, while also vertical with spar (1) axis direction in the wing, the flexural spring (9)
Another a line be located at the first bar shaped gap in；
It is described to reverse the top that gap limit gusset plate (12) is removably attached to the torsion bearing support (5), the torsion
Gap limit gusset plate (12) with a broad-adjustable second bar shaped gap, the length direction in the second bar shaped gap perpendicular to
The upper surface of the wing outer spar (2)；
The torsionspring (10) is plate-like, and one end is removably attached to wing outer spar (2) upper surface, other end position
In the second bar shaped gap of torsion gap limit gusset plate (12), the surface of the torsionspring (10) and the machine
The upper surface of wing outer spar (2) is vertical, and projection and the machine of the torsionspring (10) on the wing outer spar (2)
The dead in line of wing outer spar (2).
2. folding wings Nonlinear Flutter assay device according to claim 1, it is characterised in that the bending support of bearing
(3) including bending bearing cover (4), the bending support of bearing (3) axial direction two ends are arranged on, in the bending support of bearing
(3) axial two ends constitute the bearing block.
3. folding wings Nonlinear Flutter assay device according to claim 1 and 2, it is characterised in that the torsion bearing
Support (5) includes torsion bearing cover plate (6), constitutes with the torsion bearing support (5) at the torsion bearing support (5) top
The bearing block.
4. folding wings Nonlinear Flutter assay device according to claim 3, it is characterised in that the torsionspring (10)
It is removably attached on the torsionspring bearing (8) of wing outer spar (2) upper surface.
5. folding wings Nonlinear Flutter assay device according to claim 3, it is characterised in that the torsion bearing support
(5) pivot center is located at same level with the pivot center of the torsional axiss (7).
6. folding wings Nonlinear Flutter assay device according to claim 3, it is characterised in that also lock including curvature movement
Stator (13), one end is removably attached to torsion bearing support (5) end, and the other end is removably attached to described curved
The bent support of bearing (3) end.
7. folding wings Nonlinear Flutter assay device according to claim 3, it is characterised in that the torsional axiss (7) with
Caging bolt is provided between the torsion bearing support (5).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
|---|---|---|---|
| CN201510350838.8A CN104897355B (en) | 2015-06-23 | 2015-06-23 | Folded wing non-linear flutter test device |
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| CN104897355B true CN104897355B (en) | 2017-05-17 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN108267285B (en) * | 2018-04-22 | 2020-09-25 | 北京工业大学 | Three-section folding wing dynamic characteristic experimental device 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 |
| CN114400926B (en) * | 2021-12-28 | 2024-07-23 | 中国航天空气动力技术研究院 | Two-degree-of-freedom wing panel flutter energy collection device and wind power generation equipment |
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