CN109406090A - Flutter model connecting device - Google Patents
Flutter model connecting device Download PDFInfo
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- CN109406090A CN109406090A CN201811318591.1A CN201811318591A CN109406090A CN 109406090 A CN109406090 A CN 109406090A CN 201811318591 A CN201811318591 A CN 201811318591A CN 109406090 A CN109406090 A CN 109406090A
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- 230000008878 coupling Effects 0.000 claims description 37
- 238000010168 coupling process Methods 0.000 claims description 37
- 238000005859 coupling reaction Methods 0.000 claims description 37
- 238000013461 design Methods 0.000 abstract description 8
- 238000004088 simulation Methods 0.000 abstract description 2
- 238000012360 testing method Methods 0.000 description 14
- 238000004519 manufacturing process Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 4
- 239000000725 suspension Substances 0.000 description 4
- 206010052904 Musculoskeletal stiffness Diseases 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 235000021170 buffet Nutrition 0.000 description 2
- 230000015556 catabolic process Effects 0.000 description 2
- 210000000078 claw Anatomy 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 230000005284 excitation Effects 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000007634 remodeling Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- -1 element Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011002 quantification Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Springs (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention relates to a flutter model connecting device, which is used for connecting a main wing surface and a control surface in a flutter model, the flutter model connecting device is in a hinge-free type and comprises a plurality of plate springs, the plate springs are arranged along the spanwise direction of the main wing surface of the model, two ends of a main body part of each plate spring are respectively connected with the main wing surface and the control surface, and the flutter model of the connecting device can realize the simulation of control surface control rigidity and control surface rotation mode, can obtain linear control rigidity, obtain higher control surface connecting strength and obtain simpler spring section form and connection design form.
Description
Technical field
The present invention relates to field of airplane design more particularly to a kind of aircraft wings (the especially main plane and rudder face of aircraft)
Flutter wind tunnel tests process.More specifically, the present invention relates to a kind of flutter model attachment device, the flutter model attachment devices
It is mainly used for for the model main plane in plane flutter model connecting with model rudder face.
Background technique
To main plane and rudder face and its between connection relationship model in technical field to carry out wind tunnel test, rudder
Face manipulates the key content that influence of the rigidity to buffet characteristic is research, also to consider control surface deflection to buffet characteristic sometimes
Influence.Therefore, it is necessary to according to a kind of test model suitable for flutter wind tunnel test of achievable form design of structure, the mould
Type should preferably play the role of connecting rudder face and manipulation rigidity is simulated.
In this regard, it is known that technical staff generallys use following two classes realization means.
First way is to add the company of the structure type implementation model rudder face and main plane of manipulation rigidity using hinge suspension
It connects.For example, teaching a kind of flutter model rudder face steerable system in patent document CN104897361A comprising: first
Seat；First holder top is hingedly arranged in first adjusting screw rod, one end；Second support is located on first support
The bottom of the side of the main plane, second support is fixed on rudder face；Second adjusting screw rod, one end are hingedly arranged
In second holder top, and second adjusting screw rod is equal at a distance from the hinge to the rudder face of second support
First adjusting screw rod is at a distance from the hinge to the main plane of first support.
However, adding the connection of the structure type implementation model rudder face and main plane of manipulation rigidity, structure using hinge suspension
Form is complex, and since the structure feature of itself of suspension is along with gap and friction, can introduce a certain amount of damping
And linear Stiffness, lead to a degree of unnecessary quantification difficult.
The second way is the connection using the structure type implementation model rudder face and main plane of cross spring.For example,
The cross spring scheme provided in some teaching materials, although can effectively reduce damping, gap and the friction of steerable system, not
Connection suitable for high aspect ratio flexibility rudder face (the conventional configuration rudder face of such as civil aircraft) model.
Especially, the shortcomings that structure type of cross spring piece is that structure is relatively complicated, occupy main plane and rudder face it
Between space it is more, created great difficulties particularly with the aerodynamic force d type of entire aerofoil, this transonic wind tunnel test in, nothing
It doubts and destroys the distribution of surface aerodynamic force, will seriously affect the accuracy of test result.
In addition, known also proposed in patent document CN202485892U manipulates in flutter wind tunnel test model rudder face again
The elastic device that section is in U-typed is provided in rigidity analogue, the elastic device structure includes U section, fixed part；Institute
It states U section thickness R and represents different rigidity levels, R numerical value is bigger, and rigidity is bigger；The fixed part is equipped with fixation hole.But this
Kind scheme is not suitable for high aspect ratio flexibility rudder face although the space occupied is smaller, materials are convenient, structure size is relatively small
Higher bonding strength need.
Therefore, a kind of completely new optinal plan is needed in flutter model field, it can come effective in simple structure
Ground solves the problems, such as the linear problem of manipulation rigidity and the higher bonding strength of high aspect ratio flexibility rudder face.
Summary of the invention
For this purpose, the flutter model attachment device is used for the present invention provides a kind of attachment device for flutter model
Main plane in flutter model is connect with rudder face, the flutter model attachment device constitutes hingeless chain type, by multiple flat springs
Composition, along model main plane spanwise arrangement, flat spring main part both ends are connected respectively at main plane with rudder face, and attachment device is quivered
While vibration model can realize that rudder face manipulation rigidity and rudder face revolving mode are simulated, linear manipulation rigidity can be obtained, is obtained more
High rudder face bonding strength obtains relatively simple spring section form and connection design form.
In some embodiments, a kind of flutter model attachment device is provided, is used for the model master in flutter model
Aerofoil is connect with model rudder face, which is configured to hingeless chain type, and including multiple flat springs, flat spring
Along the spanwise arrangement of the model main plane, flat spring includes plate-like body part, which includes close to model main wing
The opposite second end of the first end in face and close model rudder face, wherein the middle line and model rudder face of the end section of first end
The rudder face pivot axis pivoted around it relative to model main plane is consistent.The flutter model attachment device (i.e. flat spring as a result,
Plate-like body part) at a distance from rudder face pivot axis minimum (being substantially zero) so that its same rigidity (i.e.
Obtain same revolving mode) under the conditions of, intensity is more preferable.
Preferably, flutter model attachment device further includes main plane connecting elements, and flat spring is in the side of the first end
The model main plane is connected to via the main plane connecting elements.By the main plane connecting elements, can be conducive to tie
The manufacture of structure.
It is highly preferred that flutter model attachment device further includes rudder face connecting elements, flat spring the side of second end via
Rudder face connecting elements is connected to model rudder face.It, can be in order to the manufacture of attachment device by the connection structure of this non-Unitary
Technique improves replaceability.
Especially, flat spring can be connected to main plane connecting elements and rudder face connecting elements by clamp device.Therefore,
Between the two be fixedly connected is realized in a manner of it simply can be removed.
Advantageously, flat spring can also include the main plane extended from the first end of main part to main plane connecting elements
Coupling part and at least one of the rudder face coupling part extended from second end to rudder face connecting elements.In particular, main wing
The connection between connection and/or rudder face coupling part and rudder face connecting elements between face coupling part and main plane connecting elements
It can be connected for plane, and main plane coupling part and rudder face coupling part can respectively include the hole for receiving screw.It can
With it is understood that when between main plane coupling part and main plane connecting elements and rudder face coupling part and rudder face connecting elements it
Between there are when plane overlapping part, the connection between them is especially reliable and securely.
In some embodiments, main plane coupling part and rudder face coupling part can be integrally manufactured with main part, from
And realize the manufacture of substitution, and be conducive to generate higher structural strength.
When flat spring number be more than or equal to 3, be also particularly advantageous.
According to the present invention, the length and width of main part an order of magnitude higher than thickness, and main part is in plate
Shape.It is very simple by the structure and type of attachment of this flat spring, the use in space can be effectively reduced, flutter model is avoided
Physical breakdown the problem of.
In certain embodiments, extending to the shape of the section taken for main part is elongate rectangular.Due to the master
The section form of body portion is simple, so that the rigidity Design of attachment device becomes simply, the processing is simple, and frequency analog deviation is easy to
Control.
Detailed description of the invention
Fig. 1 shows the arrangement schematic diagram of flutter model attachment device according to an embodiment of the invention, there is shown with
Model main plane and model rudder face；
Fig. 2 shows the diagrammatic cross-sections of the flutter model attachment device taken according to the line A-A in Fig. 1；
The solid of the flat spring of flutter model attachment device according to an embodiment of the invention is shown respectively in Fig. 3 A-3C
The sectional view that figure, plan view and the line B-B in Fig. 3 B take；And
Fig. 4 shows flutter model attachment device according to the present invention and the connection in the prior art comprising hinge spring fills
The sinusoidal excitation frequency test comparative result figure set.
Specific embodiment
It should be noted that the attached drawing of reference is not all drawn to scale, but can expand to illustrate each aspect of the present invention, and
This respect, attached drawing are not necessarily to be construed as restrictive.
Flutter model attachment device according to the present invention is mainly used for for the main plane 1 of aircraft being attached with rudder face 2, and
And it is mainly used in the wind tunnel test of flutter model.In general, in test, rudder face 2 can be carried out relative to main plane around an axis
It pivots, therefore, no matter whether flutter model attachment device includes hinge arrangement, there is theoretic pivot always in flutter model
Shaft axis.The theoretical position of this rudder face pivot axis 4 is clearly shown in Fig. 2.
In the present invention, flutter model attachment device is advantageously configured to hinge-less form, and the knot including flat spring 3
Structure.In other words, the present invention has abandoned the dependence that the connection structure between main plane 1 and rudder face 2 hangs conventional hinge, but
Using " hinge pivots deformation " for replacing routine with " cantilever beam deformed ".
Specifically, flutter model attachment device 100 according to the present invention includes multiple, i.e. at least two flat springs 3, with
Realize aforementioned beam type bending deformation.In addition, for high aspect ratio (that is, wing span and mean geometric chord is bigger)
For rudder face 2, it is particularly preferred that being disposed at least three flat springs 3 (for example, being exemplarily illustrated four plate bullets in Fig. 1
Spring 3).
The main part 301 of flat spring 3 is configured to plate, especially tabular.But it is further envisaged that arriving the plate of non-flat forms
Shape main part 301, such as main part 301 require to be in the curved moulding in part according to rigidity Design.By this flat spring 3
Structure and type of attachment it is very simple, the problem of the use in space can be effectively reduced, avoid the physical breakdown of flutter model.
These multiple flat springs 3 are generally along the spanwise arrangement of the rudder face 2 in other words of model main plane 1.In the present invention, term
" open up to " refers to that the longitudinal direction of rudder face 2 or the longest direction of dimension, the arm i.e. in model aircraft open up direction to main plane 1 in other words.
When the flat spring 3 in attachment device is along the spanwise arrangement of model main plane 1 or rudder face 2, the main body of flat spring 3
Part 301 along the exhibition to or be roughly parallel to the exhibition to the plane of extension be flat spring 3 principal plane.In the principal plane
In, the main part 301 of flat spring 3 includes a length and a width, and on the dimension direction vertical with the plane, the plate bullet
The main part 301 of spring 3 includes a thickness.
The length and width of the main part 301 of flat spring 3 can for example be designed to extend in the plane to extension
Having a size of width (length of flat spring 3 is for example clearly shown in Fig. 1), and transverse to the size opened up to extension in the plane
For length (length of flat spring 3 is for example clearly shown in the cross section depicted in fig. 2), wherein length is greater than width.But it can also incite somebody to action
The main part 301 of flat spring 3 is designed to that width is greater than length.
So far, in the present invention, term " plate " refers to that the thickness of the main part 301 of flat spring is significantly less than flat spring
Main part 301 length and width, and thickness be preferably less than length and width an order of magnitude in other words and be length and
At most 1/10th of width.One of skill in the art will understand that, the main part 301 of flat spring is mainly in as a result,
(thin) plate, rather than it is block-like.
Particularly advantageously, extending to the section of interception for the plate-like body part 301 of flat spring 3 is in rectangular elongated shape,
As shown in FIG. 3 C.But the section of other simple geometric shapes (rectangle that such as rounded corner is crossed, class ellipse, other polygons)
Also within the protection scope of the present invention.Since the section form of the main part 301 of flat spring 3 is simple, so that attachment device
Rigidity Design become simply, the processing is simple, and frequency analog deviation is easily controllable.
Furthermore, it is to be understood that arriving, length L, the width W and thickness T of the main part 301 of flat spring 3 are (for example, can join
See one embodiment shown in Fig. 3 A-3C) be flat spring primary stiffness control size, i.e., the rigidity of flat spring 3 is by main body
These sizes of part 301 and ratio between them control.
In addition, the main part 301 of flat spring 3 includes close to the first end of model main plane 1 and close to model rudder face 2
Opposite second end.Flat spring 3 according to the present invention may also include other parts other than plate-like body part 301, below
It will be described in detail.Therefore, the first end and second end under meaning of the present invention may not be opposite the two of flat spring 3
Terminal.
Flutter model attachment device 100 according to the present invention can also include that main plane connecting elements 5 and/or rudder face connect
Component 6.Flat spring 3 can be connected to model master via the main plane connecting elements 5 in the side of the first end of main part 301
Aerofoil 1, and flat spring 3 can be connected to model rudder via the rudder face connecting elements 6 in the side of the second end of main part 301
Face 2.In other words, by main plane connecting elements 5 and rudder face connecting elements 6, flutter model attachment device 100 can be separately connected
To the main plane 1 and rudder face 2 for being located at its two sides.Here, " two sides " refer to flutter model attachment device 100 across exhibition to (that is,
Be substantially perpendicular to the spanwise, especially in principal plane) opposite sides.
In general, flat spring 3 and main plane connecting elements 5 and rudder face connecting elements 6 in flutter model attachment device 100 are simultaneously
Non-integral construction, this can be conducive to the manufacture of structure.But flat spring 3 can be connected to main plane connection via various modes
Component 5 and rudder face connecting elements 6, such as by means of clamp device.For example, main plane connects structure shown in the cross section depicted in fig. 2
Part 5 (left side in figure) and rudder face connecting elements 6 (right side in figure) are fastened to the opposite sides of flat spring 3 by screw.
As previously mentioned, flat spring 3 can also include prolonging from the first end of its main part 301 to main plane connecting elements 5
In the main plane coupling part 302 stretched and the rudder face coupling part 303 extended from second end to rudder face connecting elements 6 at least
Both one, preferably.
Particularly advantageously, between the main plane coupling part 302 and main plane connecting elements 5 of flat spring 3 and plate bullet
It is overlapping that plane is respectively present between the rudder face coupling part 303 and rudder face connecting elements 6 of spring 3, as it is schematically shown in FIG 2.It can be with
It is understood that when between main plane coupling part 302 and main plane connecting elements 5 and rudder face coupling part 303 is connect with rudder face
It is especially reliable and secured that there are the connections that when plane overlapping part, can make between them between component 6, i.e., between them
Plane connection can be formed respectively.
When there are the connection of this plane, it is preferable that main plane coupling part 302 and rudder face coupling part 303 are respective
Including for receiving the hole of screw.As shown in Figure 2, screw passes through in main plane coupling part 302 and rudder face coupling part 303
Hole and hole be respectively aligned to this some holes, on main plane connecting elements 5 and rudder face connecting elements 6 so that two
Person generates and is reliably fastenedly connected.But it is also contemplated that other connection types, such as welding, riveting, bonding etc..
Particularly advantageously, in flat spring 3, main plane coupling part 302 and rudder face coupling part 303 and main part
301 are integrated manufacture, so that the rigidity of entire flat spring 3 is easier to control and designs.But 302 He of main plane coupling part
Rudder face coupling part 303 and main part 301 be it is split type, to be then attached be also within the scope of the invention.
In a preferred embodiment, as shown in figs. 3 a-3 c, main plane coupling part 302 is the master from flat spring 3
The flat claw form extended at the first end of body portion 301.It will be clear that setting is in these flat cards in Fig. 3 A-3B
The hole for connection on pawl.This flat claw can be snapped fit onto directly on such as main plane connecting elements 5, then pass through fastening
Device connects the two, as shown in Figure 2.
In addition, in this embodiment, rudder face coupling part 303 be from the second end of the main part 301 of flat spring 3 to
The semicircular plate extended outside, and the thickness of the semicircular plate is preferably slightly larger than plate-like body part 301.It can be seen that
There is also the holes for connecting rudder face connecting elements 6 on the semicircular plate.It will be understood that the shape of rudder face coupling part 303
Shape is not limited to this semicircular plate, but can be the plate of any suitable shape, or the moulding of even non-plate, as long as
Suitable for being connect with rudder face connecting elements 6.
By now it should be appreciated that arrive, the first end and second end of the main part 301 of flat spring 3 be not flat spring 3 most
Terminal part, but the main plane coupling part 302 of flat spring 3 and rudder face coupling part 303 are respectively to continue from the two ends
Outwardly extending end.
According to the present invention, the middle line of the end section of the first end of main part 301 should with model rudder face around its relative to
The hinge axes of rudder face pivotal axis, i.e. theory that model main plane pivots are consistent (that is, 4 institute of appended drawing reference is in place in Fig. 2
It sets).
For different types of rudder face manipulates rigid spring, due to attachment device (the i.e. master of flat spring 3 of the invention
Body portion 301) at a distance from rudder face shaft minimum (being substantially zero), cause it (to obtain same rotation in same rigidity
Revolving die state) under the conditions of, intensity is preferable, can be considered strength advantage caused by structure type.
More specifically, compared with the structure type of hinge suspension plus manipulation rigidity, flutter model of the invention connects dress
A 100 big feature is set to be, in the range of small deformation, rigidity it is linear preferably.With similar in the principle, prior art
The cross spring scheme of middle introduction is compared, and flutter model attachment device 100 of the invention is applicable to high aspect ratio flexibility rudder face
The connection of model.Therefore, in civil aircraft flutter model wind tunnel test field, when linearly having special demands to rigidity of model, this hair
Bright flutter model attachment device 100 has irreplaceability.
The sinusoidal excitation frequency test of 9 groups of springs is provided as a result, wherein in comparison such as Fig. 4, Fig. 4 of specific test result
4 groups of rudder face speed simulations realized for different-stiffness flat spring 3,5 groups of comparison are the rudder face of a certain form hinge spring
Speed with exciting force change as a result, test result is shown, flutter model attachment device 100 of the invention is in exciting force
Under the conditions of than the connection of hinge format there is preferably linear manipulation rigidity.
Although describing various realities of the invention for connecting the attachment device of main plane and rudder face referring on aircraft
Example is applied, is flown it should be understood, however, that the embodiment in the scope of the present invention can be applied to similar structure and/or the other of function
Rudder face structure etc. on row device.
The description of front has been presented for many features and advantage, including various alternative embodiments and device and
The details of the structure and function of method.It is intended that it is illustrative, it is not exhaustive or restrictive.For ability
It obviously can whole indicated by the wide in range upper meaning to the term as expressed by appended claims for the technical staff in domain
Various remodeling are made in range, especially in terms of the arrangement of structure, material, element, component, shape, size and component, including
Combination in these aspects concept described herein.In these various remodeling without departing from the spirit of appended claims
In the degree of range, it is meant that they are also incorporated herein.
Claims (10)
1. a kind of flutter model attachment device (100), the flutter model attachment device is used for the model master in flutter model
Aerofoil (1) is connect with model rudder face (2), which is characterized in that the flutter model attachment device is configured to hingeless chain type, described to quiver
Model attachment device of shaking includes multiple flat springs (3), spanwise arrangement of the flat spring along the model main plane, the plate bullet
Spring includes plate-like body part (301), and the main part includes close to the first end of the model main plane and close to described
The opposite second end of model rudder face, wherein the middle line of the end section of the first end and the model rudder face are opposite around its
It is consistent in the rudder face pivot axis (4) that the model main plane pivots.
2. flutter model attachment device as described in claim 1, which is characterized in that the flutter model attachment device further includes
Main plane connecting elements (5), the flat spring (3) connect in the side of the first end via the main plane connecting elements (5)
It is connected to the model main plane (1).
3. flutter model attachment device as claimed in claim 2, which is characterized in that the flutter model attachment device further includes
Rudder face connecting elements (6), the flat spring are connected in the side of the second end via the rudder face connecting elements (6) described
Model rudder face (2).
4. flutter model attachment device as claimed in claim 3, which is characterized in that the flat spring is connected by clamp device
To the main plane connecting elements (5) and the rudder face connecting elements (6).
5. flutter model attachment device as claimed in claim 4, which is characterized in that the flat spring further includes from the main body
Main plane coupling part (302) that partially first end of (301) extends to the main plane connecting elements (5) and from institute
State at least one of the rudder face coupling part (303) that second end extends to the rudder face connecting elements (6).
6. flutter model attachment device as claimed in claim 5, which is characterized in that the main plane coupling part (302) with
Connection and/or the rudder face coupling part (303) and the rudder face connecting elements between the main plane connecting elements (5)
(6) connection between is plane connection, and the main plane coupling part (302) and the rudder face coupling part (303) are respective
Including for receiving the hole of screw.
7. flutter model attachment device as claimed in claim 6, which is characterized in that the main plane coupling part (302) and
The rudder face coupling part (303) and the main part (301) are integrally manufactured.
8. such as flutter model attachment device of any of claims 1-7, which is characterized in that the flat spring (3)
Number is more than or equal to 3.
9. such as flutter model attachment device of any of claims 1-7, which is characterized in that the main part
(301) length and width an order of magnitude higher than thickness, and the main part (301) is in tabular.
10. such as flutter model attachment device of any of claims 1-7, which is characterized in that the main part
(301) along it is described open up to the shape of the section taken be elongate rectangular.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811318591.1A CN109406090B (en) | 2018-11-07 | 2018-11-07 | Flutter model connecting device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811318591.1A CN109406090B (en) | 2018-11-07 | 2018-11-07 | Flutter model connecting device |
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| CN109406090A true CN109406090A (en) | 2019-03-01 |
| CN109406090B CN109406090B (en) | 2020-11-27 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112161774A (en) * | 2020-11-03 | 2021-01-01 | 长安大学 | Wind tunnel experiment device for three-degree-of-freedom coupled vibration under large wind attack angle |
| CN112693626A (en) * | 2021-03-23 | 2021-04-23 | 中国空气动力研究与发展中心低速空气动力研究所 | Control surface angle sheet applied to wind tunnel test model and installation method |
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