CN107860550A - A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment - Google Patents
A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment Download PDFInfo
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- CN107860550A CN107860550A CN201710990378.4A CN201710990378A CN107860550A CN 107860550 A CN107860550 A CN 107860550A CN 201710990378 A CN201710990378 A CN 201710990378A CN 107860550 A CN107860550 A CN 107860550A
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- wind
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- support
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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
Abstract
The invention discloses a kind of method for supporting for being used for dummy vehicle in wind tunnel experiment, comprise the following steps：1) wind-tunnel and the dummy vehicle in the wind-tunnel are connected by space bar, and the wind-tunnel is not directly contacted with the dummy vehicle；2) requirement designed according to experiment measurement and support system, adjusts the diameter of support bar in the space bar, length, quantity, material and spatial distribution form, so as to realize the optimization of the rigidity of dummy vehicle support system.Using the method for supporting of the present invention, support system can be caused further to adapt to, meet the requirement of wind tunnel experiment content and measurement, reach the purpose for improving aerodynamic experiment data accuracy and confidence level, the problems such as efficiently solving the insufficient rigidity of support system in traditional support method, flow field interference big and system internal force complexity, there are the potentiality of obvious advantage and innovation and development in terms of wind tunnel experiment, especially in terms of for full size, large-sized model aerodynamic experiment.
Description
Technical field
The present invention relates to wind tunnel technique field, is used for more particularly to one kind a kind of for aircraft in wind tunnel experiment
The method for supporting of model.
Background technology
During practical flight, aircraft is frequently necessary to make pitching, driftage, rolling, heave, transverse translation and longitudinal direction
The action such as translation, therefore need to measure each side data of aircraft in the wind tunnel experiment of ground.On ground, wind-tunnel is real
In testing, typically fix or be relatively fixed using relative motion principle, i.e. dummy vehicle, wind-tunnel produces action of high-speed airflow and existed
Simulated flight situation on dummy vehicle.Therefore, wind tunnel experiment dummy vehicle must be supported and be consolidated using specific mode
Fixed, here it is commonly called model supporting system.
Currently used conventional support system can be divided into three classes：The first kind is tail support system, in dummy vehicle tail
Realize and support that such system design is easy, but cantilever design is often more clumsy, and the rigidity of structure is not by cantilever design in portion
Foot, experimental ability and scope have significant limitation, such as require that model dimension is small, weight is small；Second class is belly/back branch
Support system, realized and supported by cantilever design in the belly of aircraft or back, such system yardstick is huge, with aircraft mould
Type yardstick Bryant, often the flow field of heavy damage model surface, its interference region even can cover whole dummy vehicle,
It greatly affected the accuracy and confidence of experimental data；3rd class is bracing cable support system, using bracing cable (fine rule or steel wire
Deng) the multiple positions of model surface are connected to, bracing cable system is tightened by pretightning force, reaches the purpose of support, such system is set
Count and install it is complex, and in experimentation by bracing cable during airflow function pretightning force (internal force) there is complexity change
Change, it is difficult to be pre-designed and calculate, so as to limit bracing cable systematic difference scope, be generally used for aircraft and moved as low-speed maneuver
Support when making.
For produced problem in traditional wind tunnel experiment model support mode, the present invention proposes that one kind is used for wind tunnel experiment
The method for supporting of middle dummy vehicle.Multi-point support is realized to dummy vehicle using space bar, solves traditional support
The problems such as insufficient rigidity, flow field interference excessive, support system internal force complexity.The method for supporting has obvious in terms of wind tunnel experiment
Advantage and innovation and development potentiality, especially in terms of for full size, large-sized model aerodynamic experiment.
The content of the invention
It is an object of the invention to provide a kind of method for supporting for being used for dummy vehicle in wind tunnel experiment.Using the support
Method causes support system to have that specific stiffness is high, flow field interference is small, internal force is simple in wind-tunnel aerodynamic experiment and a flexible modulation etc.
Feature.Improve the accuracy and reliability of dummy vehicle aerodynamic experiment data.
To reach above-mentioned purpose, the present invention uses following technical proposals：
A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment, comprises the following steps：
1) wind-tunnel and the dummy vehicle in the wind-tunnel are connected by space bar, and the wind-tunnel with it is described
Dummy vehicle is not directly contacted with；
2) according to experiment measurement and support system design requirement, adjust the diameter of support bar in the space bar,
Length, quantity, material and spatial distribution form, so as to realize the optimization of the rigidity of dummy vehicle support system.
Further, the diameter 0.5-10cm of the support bar, length are 50-200 times of the diameter.
Further, the support bar is in pre- tension state in the dummy vehicle installation process by the ball pivot,
And tension state is kept in whole experiment process.
Further, described support bar is metal or non-metal solid material.
Further, the dummy vehicle forms multi-point support by the space bar in the wind-tunnel.
Further, one end of support bar is connected with the wind-tunnel in the space bar, the other end and the aircraft mould
Type connects.
Further, the support bar is connected with the dummy vehicle by the ball pivot, and sufficient lubrication ball pivot, is reduced
Friction effects.
Further, the support bar is connected with the wind-tunnel facilities by the ball pivot, and sufficient lubrication ball pivot, reduction rub
Wiping power influences.
Preferably, the quantity of the support bar, distribution form are it is ensured that the dummy vehicle and the support system are
Static determinacy or statically indeterminate system.
Preferably, the dummy vehicle should be in effective Experimental Area of the wind-tunnel facilities.
Using the method for supporting of the present invention, space multi-point support will be carried out dummy vehicle, significantly improves support system
Rigidity and specific stiffness, the shortcomings that so as to overcome traditional tail support method insufficient rigidity；Support system can be greatly reduced
Size and weight, avoid traditional belly/severe jamming caused by back-supported stream field；Support bar can produce curved in itself
Square internal force, the load that the air-flow born on its surface is formed is resisted, the difficulty of support bar internal force analysis is reduced, overcomes traditional bracing cable
Method for supporting internal force resolves the problem of extremely complex.There is the method for supporting obvious advantage and innovation to send out in terms of wind tunnel experiment
The potentiality of exhibition, especially in terms of aerodynamic characteristics measurement is carried out for full size, large-sized model.
Beneficial effects of the present invention are as follows：
1st, multi-point support is carried out to dummy vehicle in wind tunnel experiment using the method for supporting of the present invention so that support system
Have the characteristics that specific stiffness is high, flow field interference is small, support system internal force is simple, regulation optimization simple in construction and easy.
2nd, using the present invention method for supporting, support system can be caused further to adapt to, meet wind tunnel experiment content and
The requirement of measurement, reach the purpose for improving aerodynamic experiment data accuracy and confidence level, efficiently solve in traditional support method
The problems such as big and system internal force complexity is disturbed in the insufficient rigidity of support system, flow field, have in terms of wind tunnel experiment obvious excellent
The potentiality of gesture and innovation and development, especially in terms of for full size, large-sized model aerodynamic experiment.
Brief description of the drawings
The embodiment of the present invention is described in further detail below in conjunction with the accompanying drawings.
Fig. 1 shows the front view of support system of the present invention.
Fig. 2 shows the left view of support system of the present invention.
Fig. 3 shows the structural representation of ball pivot in support system of the present invention.
Wherein, 1. wind-tunnel, 2. dummy vehicles, 3. support bars, 4, fixing end, 31. first ball pivots, 32. first ball pivot sets,
33. the first bolt, 34. second ball pivots, 35. second ball pivot sets, 36. second bolts.
Embodiment
In order to illustrate more clearly of the present invention, the present invention is done further with reference to preferred embodiments and drawings
It is bright.Similar part is indicated with identical reference in accompanying drawing.It will be appreciated by those skilled in the art that institute is specific below
The content of description is illustrative and be not restrictive, and should not be limited the scope of the invention with this.
In embodiments of the present invention, as depicted in figs. 1 and 2, the support system for dummy vehicle in wind tunnel experiment
System, including：Space bar and ball pivot；Space bar is distributed in wind-tunnel 1；Wind-tunnel 1 is connected with dummy vehicle 2 by space bar
Connect, and wind-tunnel 1 is not directly contacted with dummy vehicle 2；Space bar includes multiple support bars 3；Fixing end 4 is provided with wind-tunnel 1；
One end of support bar 3 and the fixing end 4 of wind-tunnel 1 are connected by ball pivot, and the other end is connected with dummy vehicle 2 by ball pivot
Connect.
As shown in figure 3, the present invention provides a kind of specific ball pivot type of attachment, ball pivot includes the first ball pivot 31, the first ball
Hinge sleeve 32, the first bolt 33, the second ball pivot 34, the second ball pivot set 35 and the second bolt 36.Specifically, one end of support bar and the
One ball pivot 31 connects, and can use the forms such as welding, threaded connection, bolt connection；First ball pivot set 32 is set in the first ball pivot 31
Outer surface, sufficient lubrication between the two；First ball pivot set 32 is connected by the first bolt 33 with dummy vehicle 2；Support bar 3
The other end be connected with the second ball pivot 34, the form such as welding, threaded connection, bolt connection can be used；Second ball pivot set 35 is arranged
In the outer surface of the second ball pivot 34, sufficient lubrication between the two；Second ball pivot set 35 passes through consolidating by the second bolt 36 and wind-tunnel 1
Fixed end 4 connects.
A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment, comprises the following steps：
1) wind-tunnel 1 and the dummy vehicle 2 in wind-tunnel 1 are connected by space bar, and wind-tunnel 1 and aircraft mould
Type 2 is not directly contacted with；Dummy vehicle 2 forms multi-point support by space bar in wind-tunnel 1；
2) in the wind tunnel experiment preparatory stage, can according to different experiment content and measurement request, design space leverage
Length, diameter, quantity, material, the spatial distribution form of each support bar 3, so as to realize the optimization of the rigidity of support system；Tool
Body is as follows：700kg dummy vehicle is fixed on formation multiple spot branch in a diameter of 3.5m wind-tunnel by space bar
Support, i-th support bar (1≤i≤N, N represent support bar quantity) are for the overall stiffness contribution of support systemStiffness contribution amount of the support bar on the assigned direction of space in (such as x-axis) be,Therefore rigidity of the space bar on certain assigned direction (such as x-axis) isCan be by adjusting the length of support bar, diameter, quantity, material, space respectively
Distribution form and orientation carry out flexible modulation, and then design the requirement for meeting different experiments and measurement to Stiffness Distribution, and then
Obtain the optimised form of space bar.Wherein, Ei represents the modulus of elasticity (depending on material) of support bar, and di represents the straight of support bar
Footpath, li represent the length of support bar；αiThe angle of support bar and certain assigned direction (such as x-axis) is represented, can be by adjusting space
Distribution form is adjusted.
Obviously, the above embodiment of the present invention is only intended to clearly illustrate example of the present invention, and is not pair
The restriction of embodiments of the present invention, for those of ordinary skill in the field, may be used also on the basis of the above description
To make other changes in different forms, all embodiments can not be exhaustive here, it is every to belong to this hair
Row of the obvious changes or variations that bright technical scheme is extended out still in protection scope of the present invention.
Claims (8)
1. a kind of method for supporting for being used for dummy vehicle in wind tunnel experiment, it is characterised in that comprise the following steps：
1) wind-tunnel and the dummy vehicle in the wind-tunnel are connected by space bar, and the wind-tunnel and the flight
Device model is not directly contacted with；
2) according to experiment measurement and support system design requirement, adjust the diameter of support bar in the space bar, length,
Quantity, material and spatial distribution form, so as to realize the optimization of the rigidity of dummy vehicle support system.
2. method for supporting according to claim 1, it is characterised in that the diameter 0.5-10cm of the support bar, length are
50-200 times of the diameter.
3. method for supporting according to claim 1, it is characterised in that the support bar was installed in the dummy vehicle
Pre- tension state is in by the ball pivot in journey, and tension state is kept in whole experiment process.
4. method for supporting according to claim 1, it is characterised in that described support bar is metal or non-metal solid
Material.
5. method for supporting according to claim 1, it is characterised in that the dummy vehicle is existed by the space bar
Multi-point support is formed in the wind-tunnel.
6. method for supporting according to claim 1, it is characterised in that in the space bar one end of support bar with it is described
Wind-tunnel is connected, and the other end is connected with the dummy vehicle.
7. method for supporting according to claim 6, it is characterised in that the support bar is connected with the wind-tunnel by ball pivot
Connect.
8. wind tunnel experiment dummy vehicle method for supporting according to claim 6, it is characterised in that the support bar and institute
Dummy vehicle is stated to connect by ball pivot.
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| CN201710990378.4A CN107860550A (en) | 2017-10-23 | 2017-10-23 | A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment |
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| CN201710990378.4A CN107860550A (en) | 2017-10-23 | 2017-10-23 | A kind of method for supporting for being used for dummy vehicle in wind tunnel experiment |
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Cited By (5)
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| CN108645592A (en) * | 2018-06-27 | 2018-10-12 | 空气动力学国家重点实验室 | A kind of double balance twayblade support devices for transonic wind tunnel twin-fuselage configuration aircraft |
| CN109141803A (en) * | 2018-08-29 | 2019-01-04 | 杨雪锋 | A kind of transfer flight simulation wind-tunnel |
| CN109668710A (en) * | 2018-12-18 | 2019-04-23 | 大连理工大学 | Strut shoe formula dummy vehicle multi-dimensional vibration control method |
| CN111400878A (en) * | 2020-03-06 | 2020-07-10 | 中国航天空气动力技术研究院 | Design method of full-elastic model with air inlet channel |
| CN116399543A (en) * | 2023-04-10 | 2023-07-07 | 四川省机械研究设计院(集团)有限公司 | Six-degree-of-freedom wind tunnel model supporting system based on Hexaglide parallel mechanism and control method |
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| CN104931222A (en) * | 2015-05-04 | 2015-09-23 | 中国航天空气动力技术研究院 | Projectile separation trajectory captive test system |
| CN205102999U (en) * | 2015-10-28 | 2016-03-23 | 中国航空工业集团公司沈阳飞机设计研究所 | Mixed bearing structure of model aircraft |
| CN205157156U (en) * | 2015-10-28 | 2016-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Wind tunnel test strutting arrangement |
| CN205642790U (en) * | 2015-12-08 | 2016-10-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft strutting arrangement |
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| CN104132795A (en) * | 2014-08-11 | 2014-11-05 | 厦门大学 | Model rope supporting system capable of realizing wind tunnel virtual flight |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108645592A (en) * | 2018-06-27 | 2018-10-12 | 空气动力学国家重点实验室 | A kind of double balance twayblade support devices for transonic wind tunnel twin-fuselage configuration aircraft |
| CN108645592B (en) * | 2018-06-27 | 2024-02-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-balance double-blade supporting device for transonic wind tunnel double-fuselage layout aircraft |
| CN109141803A (en) * | 2018-08-29 | 2019-01-04 | 杨雪锋 | A kind of transfer flight simulation wind-tunnel |
| CN109141803B (en) * | 2018-08-29 | 2020-07-31 | 江苏普旭软件信息技术有限公司 | Move and carry flight simulation wind-tunnel |
| CN109668710A (en) * | 2018-12-18 | 2019-04-23 | 大连理工大学 | Strut shoe formula dummy vehicle multi-dimensional vibration control method |
| CN109668710B (en) * | 2018-12-18 | 2020-04-07 | 大连理工大学 | Multi-dimensional vibration control method for strut tail support type aircraft model |
| US10969298B2 (en) | 2018-12-18 | 2021-04-06 | Dalian University Of Technology | Multi-dimensional vibration control method for the model of strut tail-supported aircraft |
| CN111400878A (en) * | 2020-03-06 | 2020-07-10 | 中国航天空气动力技术研究院 | Design method of full-elastic model with air inlet channel |
| CN111400878B (en) * | 2020-03-06 | 2022-10-28 | 中国航天空气动力技术研究院 | Design method of full-elastic model with air inlet channel |
| CN116399543A (en) * | 2023-04-10 | 2023-07-07 | 四川省机械研究设计院(集团)有限公司 | Six-degree-of-freedom wind tunnel model supporting system based on Hexaglide parallel mechanism and control method |
| CN116399543B (en) * | 2023-04-10 | 2023-12-12 | 四川省机械研究设计院(集团)有限公司 | Six-degree-of-freedom wind tunnel model supporting system based on Hexaglide parallel mechanism and control method |
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Application publication date: 20180330 |