CN205449433U - Experimental strutting arrangement of transonic wind tunnel - Google Patents
Experimental strutting arrangement of transonic wind tunnel Download PDFInfo
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- CN205449433U CN205449433U CN201620000643.0U CN201620000643U CN205449433U CN 205449433 U CN205449433 U CN 205449433U CN 201620000643 U CN201620000643 U CN 201620000643U CN 205449433 U CN205449433 U CN 205449433U
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Abstract
The utility model discloses an experimental strutting arrangement of transonic wind tunnel, aim at solve big aircraft and adopt current concave type to buckle the supporting mechanism when carrying out the wind tunnel test, to have the distortion of test result part, have certain potential safety hazard, the problem of influence test data accuracy. The utility model discloses a to buckle bearing structure's the improvement of current concave type for the test result is more accurate, changes load -carry duty to draw to press into simultaneously and bears, has increased vertical loaded area of support and rigidity, intensity, has reduced the model shake in the process of the test. The utility model discloses a cooperation of line type bracing piece and wind -tunnel tulwar makes the utility model discloses it is experimental to realize becoming the angle of attack in succession, and the increase of angle of attack excursion, and test efficiency is greatly improved. The utility model relates to a rationally, simple structure can effectively promote the accuracy of data and the efficiency of experiment, reduces the shake phenomenon in the process of the test, has better application prospect.
Description
Technical field
This utility model relates to wind tunnel test field, is specially a kind of transonic wind tunnel test support means.
Background technology
Wind tunnel test refers to dispose aircraft or other object models in wind-tunnel, and learning gas flowing and the interaction with model thereof, to understand a kind of aerodynamic experiment method of the air dynamic behaviour of practical flight device or other objects.At present, wind tunnel test is the Main Means obtaining big aircraft aerodynamic characteristic.During wind tunnel test, model aircraft is fixed in test section by support means, and the mode shape of support means junction can be by destruction in various degree.Owing to big aircraft rear body is that buttock upwarps contraction, profile heavy damage can affect the mensuration to its cruise drag.Therefore, it is necessary to select suitable supporting way, just it is avoided that model afterbody distorts, improves test accuracy.
At present, the model support mode that big aircraft is tested in large-scale transonic wind tunnel uses matrix to bend supporting form mostly, and this supporting form schematic diagram is as shown in Figure 1.In Fig. 1,1 is model aircraft, and 2 is sky flat elements, and 3 support leading portion for matrix, and 4 support stage casing for matrix, and 5 support back segment for matrix, and 6 is wind-tunnel tulwar, and 7 is test section wainscot, and 8 is test section lower wall panels.In Fig. 1, test section wainscot, test section lower wall panels collectively form test section, and wind-tunnel tulwar is arranged on the side of test section.Matrix supports leading portion, matrix supports stage casing, matrix supports back segment and is sequentially connected composition matrix support member, and the matrix of matrix support member supports back segment and is connected with wind-tunnel tulwar, and wind-tunnel tulwar can drive matrix support movements；The matrix of matrix support member supports leading portion and is connected with big model aircraft, and matrix supports leading portion and can provide support for big model aircraft.
But, the employing matrix bending support of existing method carries out big aircraft transonic wind tunnel test and there is many weak points.First, matrix supports stage casing, matrix supports the close together of back segment and big model aircraft fuselage, affects the afterbody flow field of big model aircraft, causes result of the test partial distortion.Secondly, big model aircraft is when carrying out high-angle-of-attack trial, and matrix support member entirety is respectively positioned in test chamber, increases the congestion degree of test.It addition, in process of the test, matrix supports leading portion to be needed to bear the biggest longitudinal loading, and the rigidity of the most this matrix supporting way is weak, easily cause model shake, not only can bring potential safety hazard, also can affect the accuracy of test data.Finally, matrix support stage casing is close together with test section lower wall panels, and in process of the test, maximum angle of attack is affected, and change in angle of attack scope is limited.
To this end, in the urgent need to a kind of new device or method, to solve the problems referred to above.
Utility model content
Goal of the invention of the present utility model is: when using existing matrix bending supporting mechanism to carry out wind tunnel test for big aircraft, there is result of the test partial distortion, there is certain potential safety hazard, the problem affecting test data accuracy, it is provided that a kind of transonic wind tunnel test support means.This utility model is by the improvement to existing matrix bending supporting construction so that result of the test is more accurate, bearing mode changes into tension and compression carrying simultaneously, increases support longitudinal load-bearing area and rigidity, intensity, reduces the model shake in process of the test.This utility model is coordinated by line style support bar and wind-tunnel tulwar so that this utility model can realize becoming the angle of attack continuously and test, and the increase of change in angle of attack scope, and test efficiency is greatly improved.This utility model is reasonable in design, simple in construction, it is possible to effectively promotes accuracy and the efficiency of test of data, reduces the jitter phenomenon in process of the test, have preferable application prospect.
To achieve these goals, this utility model adopts the following technical scheme that
A kind of transonic wind tunnel test support means, including test section wainscot, test section lower wall panels, model aircraft, the sky flat elements being arranged in model aircraft, wind-tunnel tulwar, described test section wainscot, test section lower wall panels constitute test section, described wind-tunnel tulwar is arranged on the side of test section, and described model aircraft is arranged in test section；
Also include line style support bar, it is provided with, in described test section lower wall panels, the fluting matched with line style support bar, the upper end of described line style support bar is connected with the sky flat elements in model aircraft, the lower end of described line style support bar is connected through fluting with wind-tunnel tulwar, and described line style support bar is connected with wind-tunnel tulwar V-shaped structure.
The upper end of described line style support bar connects cone by balance and is connected with the sky flat elements in model aircraft.
The lower end of described line style support bar is fixing with wind-tunnel tulwar to be connected.
The lower end of described line style support bar is connected by screw or screw rod are fixing with wind-tunnel tulwar.
Described line style support bar is perpendicular to its axial section symmetrically aerofoil profile.
It is that following current is to symmetrical airfoil that described line style support bar is perpendicular to its axial section.
The installation method of aforementioned transonic wind tunnel test support means, comprises the steps:
(1) arranging fluting in test section lower wall panels, test section wainscot, test section lower wall panels constitute test section, and wind-tunnel tulwar is arranged on the side of test section；
(2) abdominal part at model aircraft arranges fluting, is connected with the sky flat elements in model aircraft the upper end of line style support bar, and described model aircraft, sky flat elements can be fixed on support bar；
(3) line style support bar is connected through the lower end of test section lower wall panels and support bar with wind-tunnel tulwar, constitutes V-type and supports, makes support bar, model aircraft, sky flat elements be fixed in test section.
The application of aforementioned transonic wind tunnel test support means, is used for big model aircraft transonic wind tunnel test by this support means.
For foregoing problems, this utility model provides a kind of transonic wind tunnel test support means.This support means includes test section wainscot, test section lower wall panels, model aircraft, the sky flat elements being arranged in model aircraft, wind-tunnel tulwar, test section wainscot, test section lower wall panels constitute test section, wind-tunnel tulwar is arranged on the side of test section, and model aircraft is arranged in test section.This utility model also includes line style support bar, the fluting matched with line style support bar it is provided with in test section lower wall panels, the upper end of line style support bar is connected with the sky flat elements in model aircraft, the lower end of line style support bar is connected through fluting with wind-tunnel tulwar, and line style support bar is connected with wind-tunnel tulwar V-shaped structure.In this utility model, first arranging fluting in test section lower wall panels, to substitute former test section lower wall panels, school, flow field is surveyed result and is shown: the test section lower wall panels of this utility model band fluting and original test section lower wall panels flow field quality indifference.Then, make a support bar, be supported by support bar.Abdominal part at model aircraft is slotted again, and the upper end of support bar is connected with the sky flat elements in model aircraft, and then model aircraft, sky flat elements are fixed on support bar.Finally, line style support bar is connected bottom wind-tunnel tulwar through the lower end of test section lower wall panels and support bar, constitutes V-type and supports, makes support bar, model aircraft, sky flat elements be fixed in test section.
Compared with existing matrix bending supporting form, construction features of the present utility model is: this utility model arranges fluting in test section lower wall panels, for changing supporting way and structure with spatial；This utility model uses new connected mode, i.e. substitutes traditional matrix bending supporting mechanism with V-type mechanism；In this utility model, one end of line style support bar directly realizes being connected in the part staying indoor with wind-tunnel tulwar.
In existing matrix bending supporting mechanism, matrix supports stage casing, matrix supports back segment with model aircraft afterbody at a distance of relatively near, causes support interference more serious, and secondary interference cannot be deducted.And matrix is bent support and is improved to V-type mechanism supports by this utility model, increase the distance between model aircraft afterbody and V-type support means, reduce the impact on model aircraft afterbody flow field of the V-type support means, effectively reduce the support interference of result of the test.In other words, this utility model can effectively reduce the support interference of result of the test, improves the accuracy of test data.
In big aircraft dynamometer check, lift load is maximum.Traditional matrix bending supporting mechanism bears lift load in cantilever fashion, and tension and compression and bending, the poor stability of whole matrix bending supporting construction are born in multiple bending cross sections simultaneously.Matrix is bent support and is improved to V-type mechanism supports by this utility model, and its bearing mode is tension and compression carryings, increases support longitudinal load-bearing area and rigidity, intensity, reduces the model shake in process of the test, it is ensured that process of the test safety and data are reliable.V-type mechanism supports of the present utility model is in optimal force way, and Stability Analysis of Structures is safe and reliable.
Existing matrix bending supporting way, the distance that matrix supports between stage casing and test section lower wall panels is less, causes the change of the model aircraft angle of attack to be restricted.And in V-type mechanism supports mode of the present utility model, one end of line style support bar is connected bottom indoor wind-tunnel tulwar with staying, drives the motion of line style support bar by wind-tunnel bent blade mechanism, thus realize model aircraft angle of attack consecutive variations；It addition, this utility model is by arranging fluting in test section lower wall panels, increase model aircraft change in angle of attack scope.The solution of this problem, is effectively increased test capability and work efficiency.This utility model is capable of consecutive variations angle of attack, and scope is bigger.
This utility model processing is simple, easy-to-use, by the cooperation of fluting on line style support bar and test section lower wall panels, it is possible to for different wind-tunnel and model test, have good Social benefit and economic benefit.
In sum, compared with the bending support of existing matrix, this utility model eliminates strut support stage casing, supports back segment so that result of the test is more accurate；This utility model optimizes support bearing mode, one end of line style support bar is directly connected with the existing wind-tunnel bent blade mechanism staying indoor, owing to avoiding concave structure form, the rigidity of support means is made to be greatly improved, the jitter phenomenon being effectively reduced in process of the test；This utility model is matched with wind-tunnel tulwar by line style support bar so that this utility model can realize becoming angle of attack test continuously, and change in angle of attack scope increases, and test efficiency is greatly improved.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is that the matrix bending that existing big aircraft uses supports schematic diagram.
Fig. 2 is V-type support device structure schematic diagram of the present utility model.
Labelling in figure: 1 is model aircraft, 2 is sky flat elements, and 3 support leading portion for matrix, and 4 support stage casing for matrix, and 5 support back segment for matrix, and 6 is wind-tunnel tulwar, and 7 is test section wainscot, and 8 is test section lower wall panels, and 9 is line style support bar, and 10 is fluting.
Detailed description of the invention
Below in conjunction with the accompanying drawings, this utility model is described in detail.
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, this utility model is further elaborated.Should be appreciated that specific embodiment described herein, only in order to explain this utility model, is not used to limit this utility model.
Embodiment 1
The matrix bending that existing big aircraft uses supports schematic diagram as shown in Figure 1.In this structure, sky flat elements is used for power and the moment that survey aircraft model is subject to；Matrix supports leading portion, matrix supports stage casing, matrix supports back segment and constitutes matrix supporting mechanism, in order to support model aircraft and sky flat elements；Wherein, test section lower wall panels is not provided with slotting accordingly.Its principle is as follows, and matrix supports leading portion and entered by model aircraft abdominal part, and is connected with sky flat elements, to support model aircraft；Matrix supports back segment and is connected in the middle part of wind-tunnel tulwar, thus model aircraft, sky flat elements is fixed in test chamber.This supporting way has support interference compared with the technical deficiency such as big, structural stability is poor and change in angle of attack scope is limited.
And the support means of the present invention is as shown in Figure 2.As shown in Figure 2, the core component of the present invention is line style support bar.In the present embodiment, line style support bar is perpendicular to its axial section symmetrically aerofoil profile, as shown in Figure 2.Use this structure, it is possible to effectively reducing the tail interference of line style support bar, as preferably, the section of line style support bar preferably employs following current to symmetrical airfoil.
The upper end of line style support bar is connected with model aircraft, sky flat elements, and the lower end of line style support bar is connected with wind-tunnel tulwar.Line style support bar and model aircraft fuselage join domain, before should being positioned at model aircraft machine wing root chord leading edge point, thus ensure that line style support bar is in fuselage cross-section long-pending change flat zone, reduce the interference to big aircraft of the line style support bar.
Meanwhile, originally it is implemented in model aircraft fuselage corresponding join domain fluting, facilitates line style support bar to stretch into fuselage abdominal cavity, avoid fuselage to collide with line style support bar simultaneously.Line style post upper is connected by joint sky Intraabdominal with model aircraft flat elements, and the sky flat elements other end is connected with model aircraft fuselage by copper tapered sleeve, thus model aircraft and sky flat elements is fixed on line style support bar.Line style support bar is connected by screw bottom wind-tunnel tulwar, not only act as effect line style support bar, model aircraft and sky flat elements being fixed in test chamber, the motion of line style support bar can also be driven by wind-tunnel tulwar simultaneously, thus realize the change of model aircraft angle of attack attitude.In order to ensure that line style support bar passes test section lower wall panels, the present embodiment arranges fluting in test section lower wall panels relevant position.The width of fluting is determined by the thickness of line style support bar, and the length of fluting is determined by the change in angle of attack scope of model aircraft.
The operation principle of the support means of the present embodiment is as follows.Wind-tunnel tulwar, around its rotation heart motion, drives the line style support bar motion being fixed on bottom it, makes model aircraft come back in test section or bow, it is achieved the consecutive variations of angle of attack attitude.Owing to line style support bar is in optimal stress, structural stability is high, thus, in process of the test, model aircraft shake is little, and safe coefficient is high.In addition, tradition matrix support means in matrix support stage casing, matrix support back segment close together with model aircraft afterbody, and the line style support bar of the present invention increases and distance between model aircraft afterbody, support interference can be effectively reduced, improve test data precision.
To sum up, support means energy acquisition accurate, the safe and efficient big aircraft wind tunnel test data of the present invention, there is good Social benefit and economic benefit.
The foregoing is only preferred embodiment of the present utility model, not in order to limit this utility model, all any amendment, equivalent and improvement etc. made within spirit of the present utility model and principle, within should be included in protection domain of the present utility model.
Claims (6)
1. a transonic wind tunnel test support means, it is characterized in that, including test section wainscot, test section lower wall panels, model aircraft, the sky flat elements being arranged in model aircraft, wind-tunnel tulwar, described test section wainscot, test section lower wall panels constitute test section, described wind-tunnel tulwar is arranged on the side of test section, and described model aircraft is arranged in test section；
Also include line style support bar, it is provided with, in described test section lower wall panels, the fluting matched with line style support bar, the upper end of described line style support bar is connected with the sky flat elements in model aircraft, the lower end of described line style support bar is connected through fluting with wind-tunnel tulwar, and described line style support bar is connected with wind-tunnel tulwar V-shaped structure.
Transonic wind tunnel test support means the most according to claim 1, it is characterised in that the upper end of described line style support bar connects cone by balance and is connected with the sky flat elements in model aircraft.
Transonic wind tunnel test support means the most according to claim 1, it is characterised in that the lower end of described line style support bar is fixing with wind-tunnel tulwar to be connected.
Transonic wind tunnel test support means the most according to claim 3, it is characterised in that the lower end of described line style support bar is connected by screw or screw rod are fixing with wind-tunnel tulwar.
5. according to transonic wind tunnel test support means described in any one of claim 1 ~ 4, it is characterised in that described line style support bar is perpendicular to its axial section symmetrically aerofoil profile.
Transonic wind tunnel test support means the most according to claim 5, it is characterised in that it is that following current is to symmetrical airfoil that described line style support bar is perpendicular to its axial section.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620000643.0U CN205449433U (en) | 2016-01-04 | 2016-01-04 | Experimental strutting arrangement of transonic wind tunnel |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201620000643.0U CN205449433U (en) | 2016-01-04 | 2016-01-04 | Experimental strutting arrangement of transonic wind tunnel |
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| CN205449433U true CN205449433U (en) | 2016-08-10 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105527069A (en) * | 2016-01-04 | 2016-04-27 | 空气动力学国家重点实验室 | Transonic wind tunnel test supporting device, installation method and application thereof |
| CN106768800A (en) * | 2016-12-02 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model supporting device for multiple aircraft formation wind tunnel test |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN109946037A (en) * | 2019-04-25 | 2019-06-28 | 中国空气动力研究与发展中心高速空气动力研究所 | Simulate the sprue mobile device and application of the variation of support interferences amount |
| CN110987354A (en) * | 2019-12-05 | 2020-04-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method based on same |
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2016
- 2016-01-04 CN CN201620000643.0U patent/CN205449433U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105527069A (en) * | 2016-01-04 | 2016-04-27 | 空气动力学国家重点实验室 | Transonic wind tunnel test supporting device, installation method and application thereof |
| CN105527069B (en) * | 2016-01-04 | 2019-03-12 | 空气动力学国家重点实验室 | A kind of transonic wind tunnel test support device, its installation method and application |
| CN106768800A (en) * | 2016-12-02 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of model supporting device for multiple aircraft formation wind tunnel test |
| CN108106809A (en) * | 2017-12-14 | 2018-06-01 | 大连四达高技术发展有限公司 | Low blockage percentage support device |
| CN109946037A (en) * | 2019-04-25 | 2019-06-28 | 中国空气动力研究与发展中心高速空气动力研究所 | Simulate the sprue mobile device and application of the variation of support interferences amount |
| CN109946037B (en) * | 2019-04-25 | 2024-01-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Blocking moving device for simulating bracket interference quantity change and application |
| CN110987354A (en) * | 2019-12-05 | 2020-04-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method based on same |
| CN110987354B (en) * | 2019-12-05 | 2021-10-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method based on same |
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