CN207191484U - The gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test - Google Patents
The gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test Download PDFInfo
- Publication number
- CN207191484U CN207191484U CN201721131657.7U CN201721131657U CN207191484U CN 207191484 U CN207191484 U CN 207191484U CN 201721131657 U CN201721131657 U CN 201721131657U CN 207191484 U CN207191484 U CN 207191484U
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- wall
- rib
- fixed
- clamping apparatus
- trailing edge
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Abstract
It the utility model is related to wing experimental technique field, specifically provide the gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test, box section and supporting construction are supported including aerofoil profile, aerofoil profile supports box section to include wainscot, lower wall panels, end rib, exterior wall, interior wall structure and leading edge middle rib, end rib is located at two wallboard both sides, exterior wall is located at two wallboard afterbodys and is connected with variable trailing edge structure, interior wall structure and leading edge middle rib are respectively positioned between two wallboards, supporting construction includes horizontal mounting arm and vertical legs, it is located at two wallboard both sides and is connected with end rib, the gripping clamping apparatus maintain the continuity of aerofoil profile, rigidity is provided for variable trailing edge structure wind tunnel test and intensity is supported, variable trailing edge structure wind tunnel test is smoothed out.
Description
Technical field
It the utility model is related to the support of wing experimental technique field, the more particularly to wind tunnel test of aircraft variable trailing edge structure
Fixture.
Background technology
With the development of aeronautical technology, the research for the variant aircraft using self-adapting intelligent structure is more and more, especially
It is the research for variable trailing edge intelligence variant structure.Variable trailing edge typical structure is and traditional when carrying out wind tunnel test
The belly or posterior bracket supporting way of aircraft wind tunnel model are different, it is necessary to design special experiment gripping clamping apparatus, i.e., to ensure
The integrality of aerofoil profile section, and keep certain strength and stiffness to cause the smooth company of malformation in trailing edge deformation process
It is continuous, ensure installation and the driving space of intelligent driving system again, while also to ensure the fairing of air-flow to reduce supporting construction
Influence to result of the test.
Utility model content
To enable variable trailing edge structure to carry out wind tunnel test, the utility model provides aircraft variable trailing edge structure wind-tunnel
The gripping clamping apparatus of experiment, including：
Aerofoil profile supports box section, and it includes wall panel structure, end rib, exterior wall, interior wall structure and leading edge middle rib, the wall panel structure
Including wainscot and lower wall panels, the end rib is fixed on the wall panel structure both sides, and the exterior wall is fixed on the wall panel structure
Afterbody, variable trailing edge structural test part are connected with the upper and lower edge strip of the exterior wall, and support that box section is smooth continuous with the aerofoil profile
Transition, the interior wall structure are located in the wall panel structure, and its upper/lower terminal connects with the wainscot and the lower wall panels respectively
Connect, the leading edge middle rib has on middle rib an edge strip under edge strip and middle rib, and edge strip is connected with the wainscot on the middle rib, described
Edge strip is connected with the lower wall panels under middle rib；
Supporting construction, it is located at the both sides that the aerofoil profile supports box section, and the supporting construction is including horizontal mounting arm and vertically
Support arm, one end of the horizontal mounting arm are fixed with method wheel disc, and the horizontal mounting arm passes through the method wheel disc and corresponding institute
End rib connection is stated, the horizontal mounting arm is fixed in one end of the vertical legs, and the other end is fixed on ground fixed structure.
Preferably, in addition to skins front edges, the skins front edges and the end rib, the leading edge middle rib and the interior wall knot
Structure connects.
Preferably, the interior wall structure includes middle wall and interior wall, the middle wall between the interior wall and the exterior wall,
The upper/lower terminal of the middle wall is connected with the wainscot and the lower wall panels respectively, the upper/lower terminal of the interior wall respectively with
The wainscot connects with the lower wall panels.
Preferably, the web of the web of the middle wall and the leading edge middle rib is demountable structure.
Preferably, it is fixed with radome fairing on the horizontal mounting arm.
Preferably, one end of the vertical legs is mutually fixed with the horizontal mounting arm by way of welding, the wheel of the law
Disk is fixed on one end of the horizontal mounting arm by way of welding.
The gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test provided by the utility model, maintain the continuous of aerofoil profile
Property, provide rigidity for variable trailing edge structure wind tunnel test and intensity is supported, inside provides installing space for driving structure, aerofoil profile
With being connected at the aerofoil profile pressure heart for supporting construction so that caused moment of torsion is minimum, and the radome fairing on the outside of horizontal mounting arm can reduce pair
The interference of air-flow, ensure the correctness of wind tunnel test data.
Brief description of the drawings
Embodiment below with reference to accompanying drawing description is exemplary, it is intended to for explanation and illustration the utility model, without
It is understood that as the limitation to the scope of protection of the utility model.
Fig. 1 is a kind of stereogram of illustrative examples of the present utility model；
Fig. 2 is a kind of rearview of illustrative examples of the present utility model；
Fig. 3 is a kind of top view of illustrative examples of the present utility model；
Fig. 4 is a kind of left view of illustrative examples of the present utility model.
Reference：
11 wainscots
12 lower wall panels
20 end ribs
31 exterior walls
Wall in 32
33 interior walls
40 leading edge middle ribs
Edge strip on 41 middle ribs
Edge strip under 42 middle ribs
50 skins front edges
60 horizontal mounting arms
61 method wheel discs
62 radome fairings
70 vertical legs
Embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.
It should be noted that：In the accompanying drawings, from beginning to end same or similar label represent same or similar element or
Element with same or like function.Described embodiment is the utility model part of the embodiment, rather than whole
Embodiment, in the case where not conflicting, the feature in embodiment and embodiment in the application can be mutually combined.Based on this reality
With the embodiment in new, those of ordinary skill in the art are obtained every other under the premise of creative work is not made
Embodiment, belong to the scope of the utility model protection.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of description the utility model and simplifies description, rather than indicates or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
Herein, " schematic " expression " serving as example, example or explanation ", will should not be described herein as " showing
Any diagram, the embodiment of meaning property " are construed to a kind of preferred or more advantageous technical scheme.
As shown in Figures 1 to 4, the utility model provides the gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test, is
The wind tunnel test of variable trailing edge structure is supported and constraint so that the wind tunnel test of variable trailing edge structure can be smoothed out, and be obtained
Correct test data.The gripping clamping apparatus include aerofoil profile and support box section and supporting construction.
Aerofoil profile supports box section to include wall panel structure, end rib 20, exterior wall 31, interior wall structure and leading edge middle rib 40, wherein wall with
The quantity of rib is arranged that wall panel structure includes wainscot 11 and lower wall panels 12, and end rib 20 is fixed on wall panel structure both sides by stability
And be connected with wainscot 11 and lower wall panels 12, exterior wall 31 is fixed on wall panel structure afterbody and connected with wainscot 11 and lower wall panels 12
Connect.Aerofoil profile supports the interface design technology docking parting surface of box section, the upper and lower edge of variable trailing edge structural test part and exterior wall 31
Bar connects, and supports the smooth continuous transition of box section, composition analysis aerofoil profile with aerofoil profile.Interior wall structure is located in wall panel structure,
Its upper/lower terminal is connected with wainscot 11 and lower wall panels 12 respectively, and leading edge middle rib 40 has edge strip 41 and middle rib lower edge on middle rib
Bar 42, edge strip 41 is connected with wainscot 11 on middle rib, and edge strip 42 is connected with lower wall panels 12 under middle rib；It is understood that upper wall
Plate 11 is demountable structure, for safeguarding drive mechanism or equipment.
Supporting construction is located at the both sides that aerofoil profile supports box section, and supporting construction includes horizontal mounting arm 60 and vertical legs 70, water
One end of flat support arm 60 is fixed with wheel of the law disk 61, and in the present embodiment, wheel of the law disk 61 is fixed on horizontal mounting arm by way of welding
60 one end.Horizontal mounting arm 60 is connected by wheel of the law disk 61 and corresponding end rib 20, and junction is located at the wing of end rib 20
At the type Pneumatic pressure heart.In the present embodiment, radome fairing 62 is fixed with horizontal mounting arm 60, and preferably mutually fixed by spot welding mode.
Horizontal mounting arm 60 is fixed in one end of vertical legs 70, and the other end is fixed on ground fixed structure.In the present embodiment, vertical legs
70 one end is mutually fixed with horizontal mounting arm 60 by way of welding.
In another embodiment, the gripping clamping apparatus also include skins front edges 50, skins front edges 50 with end rib 20, leading edge
Rib 40 connects with interior wall structure.Skins front edges 50 dock at leading edge and trailing edge, are bolted with wall, rib, middle part is upper and lower
Covering is detachably to safeguard drive mechanism or equipment.
In yet another embodiment, interior wall structure includes middle wall 32 and interior wall 33, and middle wall 32 is located at interior wall 33 and exterior wall 31
Between, the upper/lower terminal of middle wall 32 is connected with wainscot 11 and lower wall panels 12 respectively, the upper/lower terminal of interior wall 33 respectively with it is upper
Wallboard 11 and lower wall panels 12 connect.In the present embodiment, the web of middle wall 32 and the web of leading edge middle rib 40 are demountable structure,
For according to drive mechanism installing space dismounting or perforate, and adapt to intelligent drives mechanism installation and driving.
It is described above, only specific embodiment of the present utility model, but the scope of protection of the utility model is not limited to
In this, any one skilled in the art is in the technical scope that the utility model discloses, the change that can readily occur in
Change or replace, should all cover within the scope of protection of the utility model.Therefore, the scope of protection of the utility model should be with described
Scope of the claims is defined.
Claims (6)
1. the gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test, it is characterised in that including：
Aerofoil profile supports box section, and it includes wall panel structure, end rib (20), exterior wall (31), interior wall structure and leading edge middle rib (40), described
Wall panel structure includes wainscot (11) and lower wall panels (12), and the end rib (20) is fixed on the wall panel structure both sides, described outer
Wall (31) is fixed on the wall panel structure afterbody, and variable trailing edge structural test part is connected with the upper and lower edge strip of the exterior wall (31),
And the smooth continuous transition of box section is supported with the aerofoil profile, the interior wall structure is located in the wall panel structure, its upper/lower terminal point
Be not connected with the wainscot (11) and the lower wall panels (12), the leading edge middle rib (40) have middle rib on edge strip (41) and in
Edge strip (42) under rib, edge strip (41) is connected with the wainscot (11) on the middle rib, under the middle rib edge strip (42) with it is described
Lower wall panels (12) connect；
Supporting construction, it is located at the both sides that the aerofoil profile supports box section, and the supporting construction is including horizontal mounting arm (60) and vertically
Support arm (70), one end of the horizontal mounting arm (60) are fixed with method wheel disc (61), and the horizontal mounting arm (60) passes through the wheel of the law
Disk (61) and the connection of the corresponding end rib (20), the horizontal mounting arm is fixed in one end of the vertical legs (70)
(60), the other end is fixed on ground fixed structure.
2. gripping clamping apparatus according to claim 1, it is characterised in that also including skins front edges (50), the skins front edges
(50) it is connected with the end rib (20), the leading edge middle rib (40) and the interior wall structure.
3. gripping clamping apparatus according to claim 1, it is characterised in that the interior wall structure includes middle wall (32) and interior wall
(33), the middle wall (32) is between the interior wall (33) and the exterior wall (31), the upper/lower terminal point of the middle wall (32)
Be not connected with the wainscot (11) and the lower wall panels (12), the upper/lower terminal of the interior wall (33) respectively with the upper wall
Plate (11) and the lower wall panels (12) connection.
4. gripping clamping apparatus according to claim 3, it is characterised in that the web and the leading edge middle rib of the middle wall (32)
(40) web is demountable structure.
5. gripping clamping apparatus according to claim 1, it is characterised in that be fixed with radome fairing on the horizontal mounting arm (60)
(62)。
6. gripping clamping apparatus according to claim 1, it is characterised in that one end of the vertical legs (70) and the level
Support arm (60) is mutually fixed by way of welding, and the method wheel disc (61) is fixed on the horizontal mounting arm by way of welding
(60) one end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721131657.7U CN207191484U (en) | 2017-09-05 | 2017-09-05 | The gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721131657.7U CN207191484U (en) | 2017-09-05 | 2017-09-05 | The gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207191484U true CN207191484U (en) | 2018-04-06 |
Family
ID=61791083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721131657.7U Active CN207191484U (en) | 2017-09-05 | 2017-09-05 | The gripping clamping apparatus of aircraft variable trailing edge structure wind tunnel test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207191484U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
-
2017
- 2017-09-05 CN CN201721131657.7U patent/CN207191484U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108414182A (en) * | 2018-04-23 | 2018-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile sideway oscillation flow tunnel testing device |
| CN108414182B (en) * | 2018-04-23 | 2023-11-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Wing type yaw oscillation wind tunnel test device |
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