CN204314050U - A kind of flutter wind tunnel test model boxlike supportive device - Google Patents
A kind of flutter wind tunnel test model boxlike supportive device Download PDFInfo
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- CN204314050U CN204314050U CN201420815440.8U CN201420815440U CN204314050U CN 204314050 U CN204314050 U CN 204314050U CN 201420815440 U CN201420815440 U CN 201420815440U CN 204314050 U CN204314050 U CN 204314050U
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Abstract
The utility model relates to a kind of flutter wind tunnel test model boxlike supportive device, comprises the parts such as course reinforcing prop (11), head bearing cover plate (12), rotating shaft (13), head bearing (14), top chock (15), decoupling zero pin (16), normal direction reinforcing prop (17), lower bearing cover plate (18), lower bearing (19), spring leaf (20), base block (21) and pedestal (22); Course reinforcing prop (11), normal direction reinforcing prop (17), cushion block (21) and pedestal (22) form Integral box type metab.The utility model provides enough support rigidity and supports frequency; And utilize bearing that covering system is installed, achieve the quick-replaceable of model test process shaft, efficiently solve the technological difficulties in the past causing because of rotating shaft and bearing fit problem changing difficulty.
Description
Technical field
The utility model relates to a kind of flutter wind tunnel test model boxlike supportive device, for model provides enough fixtures to support frequency and the suitable device bending, reverse support rigidity in flutter model wind tunnel test, flutter model design and wind-tunnel technique field in technical field of aerospace can be belonged to.
Background technology
Complete dynamic aerofoil buffet characteristic depends on its factor such as geometric shape and natural vibration characteristic.Usually the mode adopting numerical analysis to combine with wind tunnel test in current aircraft type development is entirely moved aerofoil buffet characteristic and is analyzed and researched.And adopt the buffet characteristic of the mode research aircraft aerofoil of wind tunnel test, first need to carry out model wind tunnel test according to Dynamic similarity design subscale test model, and then obtain the buffet characteristic of plane airfoil.
In dynamically similar model design with ground experiment process, for the ease of coordinating bending decoupling mechanism, the bending of model and torsion are supported that rigidity effectively adjusts, identify exactly and obtain the natural vibration characteristic of model self aerofoil, its supporting structure mode is avoided to produce coupling effect to himself mode, the installation supportive device natural frequency of model need meet the requirement much larger than aerofoil self the highest pass frequency of heart, generally get and support that frequency reaches 3 times of aerofoil the highest pass frequency of heart, this just requires that model is installed supportive device and must be had enough rigidity.Therefore, just seem of crucial importance to the design of supportive device, it is related to the design of whole model system and test success or failure.
Existing flutter wind tunnel test model supportive device as shown in Figure 1, it is made up of metal support plate 1, top chock 2, head bearing 3, step 4, lower bearing 5, rotating shaft 6, spring leaf 7, decoupling zero pin 8, base 9, this device relies on metal support plate 1 to support and rotate to support for test model provides bending, because metal support plate 1 mainly holds curved in the process supported of supplying a model, and whole metal support plate 1 is only supported there is border with base 9 junction; Discontinuous with the link position place plate at bearing place, therefore the support rigidity that provides of metal support plate 1 pair of test model is less, support that frequency is lower, often be difficult to and even cannot reach completely the supportive device frequency requirement that test proposes, the characteristics of mode of model self may be caused to produce coupling with supportive device characteristics of mode, and then cause test accuracy to decline and even failure.In addition, top chock 2 all adopts interference fit with head bearing 3, step 4 with lower bearing 5, when rotating shaft 6, with head bearing 3 or lower bearing 5, clamping stagnation occurs, is difficult to change bearing or rotating shaft 6, causes testing performance difficulty.
Utility model content
Existing complete dynamic aerofoil flutter model supportive device rigidity is more weak, natural frequency is low, cannot meet test completely supports frequency requirement, its natural mode of vibration is easily coupled with model self natural mode of vibration, causes and effectively can not to identify in ground experiment process and to obtain the natural mode of vibration of test model; And this coupling will make bending decoupling device cannot effectively carry out bending, reversing support stiffness equivalent, thus make model inaccurate and even failed to plane airfoil simulation.
For the problem that above-mentioned existing test model supportive device brings, the utility model devises flutter wind tunnel test model boxlike supportive device.
The technical scheme that the utility model is taked is as follows: a kind of flutter wind tunnel test model boxlike supportive device, comprises the parts such as course reinforcing prop (11), head bearing cover plate (12), rotating shaft (13), head bearing (14), top chock (15), decoupling zero pin (16), normal direction reinforcing prop (17), lower bearing cover plate (18), lower bearing (19), spring leaf (20), base block (21) and pedestal (22); Course reinforcing prop (11), normal direction reinforcing prop (17), cushion block (21) and pedestal (22) form Integral box type metab;
Base block (21) is positioned at the bottommost of whole support base, and its upper surface contacts with pedestal (22), and the two is connected by the mode be spirally connected and weld; Pedestal (22) middle position perforate, as the bearing mounting base of lower bearing (19), bore edges opens screw hole, for lower bearing cover plate (18) is fixed on pedestal (22), to carry out the fixed constraint of vertical direction to lower bearing (19); Normal direction reinforcing prop (17) and course reinforcing prop (11) are arranged vertically, and provide by pedestal (22) and directly contact support, the two is symmetrically arranged in both sides relative to lower bearing (19) respectively; Normal direction reinforcing prop (17) and course reinforcing prop (11) upper ends top chock (15), adopt screw to be connected with normal direction reinforcing prop (17); Head bearing (14) is installed on top chock (15), it adopts head bearing cover plate (12) position constraint, ensure that outer race and top chock (15) fit tightly, and bearing inner ring freely can rotate; Rotating shaft (13) is fit into head bearing (14) and lower bearing (19) from top to bottom, and two bearings provide constraint support thus; Spring leaf (20) is bolted on course reinforcing prop (11), arranges one along course relative to each before and after lower bearing (19); Decoupling zero pin (16) is by self being threadedly connected to spring leaf (20) top.
Further, above-mentioned bearing (14,19) is self-aligning bearing.
Further, clearance fit is adopted between above-mentioned bearing (14,19) and bearing seat (15).
The utility model utilizes the feature that Integral box type metab structure height is large, provides enough support rigidity and support frequency to flutter wind tunnel test model; And utilize bearing that covering system is installed, achieve the quick-replaceable of model test process shaft, efficiently solve the technological difficulties in the past causing because of rotating shaft and bearing fit problem changing difficulty.This utilitarian design new technique is advanced, the simple and direct practicality of test method, not only improve modelling precision significantly, decrease the workload of modelling and correlation computations, also reduce model to produce and wind tunnel test cost, shorten the test period, save research fund, there is higher model practical value.
Accompanying drawing explanation
Fig. 1 existing flutter model supportive device structural representation;
The flutter wind tunnel test model boxlike supportive device structural representation that Fig. 2 the utility model relates to.
Embodiment
Below in conjunction with Figure of description, the present invention is described in further detail.A kind of flutter wind tunnel test model boxlike supportive device, comprises the parts such as course reinforcing prop 11, head bearing cover plate 12, rotating shaft 13, head bearing 14, top chock 15, decoupling zero pin 16, normal direction reinforcing prop 17, lower bearing cover plate 18, lower bearing 19, spring leaf 20, base block 21 and pedestal 22; Course reinforcing prop 11, normal direction reinforcing prop 17, cushion block 21 and pedestal 22 form Integral box type metab;
Base block 21 is positioned at the bottommost of whole support base, and its upper surface contacts with pedestal 22, and the two is connected by the mode be spirally connected and weld; The perforate of pedestal 22 middle position, as the bearing mounting base of lower bearing 19, bore edges opens screw hole, for being fixed on pedestal 22 by lower bearing cover plate 18, to carry out the fixed constraint of vertical direction to lower bearing 19; Normal direction reinforcing prop 17 and course reinforcing prop 11 are arranged vertically, and provide by pedestal 22 and directly contact support, the two is symmetrically arranged in both sides relative to lower bearing 19 respectively; Normal direction reinforcing prop 17 and course reinforcing prop 11 upper ends top chock 15, adopt screw to be connected with normal direction reinforcing prop 17; Head bearing 14 is installed on top chock 15, it adopts head bearing cover plate 12 position constraint, ensure that outer race and top chock 15 fit tightly, and bearing inner ring freely can rotate; Rotating shaft 13 is fit into head bearing 14 and lower bearing 19 from top to bottom, and two bearings provide constraint support thus; Spring leaf 20 is bolted on course reinforcing prop 11, arranges one along course relative to each before and after lower bearing 19; Decoupling zero pin 16 is by self being threadedly connected to spring leaf 20 top.
Boxlike metab arranges top chock 15 and pedestal 22 is installed for head bearing 14 and lower bearing 19, clearance fit is adopted between bearing and bearing seat 15, utilize head bearing cover plate 12 and lower bearing cover plate 18 to carry out constraint to the outer shroud of head bearing 14 and lower bearing 19 respectively to fasten, but do not affect the rotation of bearing; During the more difficult directly dismounting of rotating shaft 13, indirectly realizing by dismantling corresponding bearing cover 18, solving rotating shaft 13 thus and coordinating tension with bearing 14 and the problem that cannot dismantle.Rotating shaft 13 is fit into base from top to bottom, provides freely-supported by metal (upper to it, and support rigidity for the test model be arranged on its ring flange provides bending, the large I of its rigidity is regulated by the different rotating shaft diameters of axle.Cause rotating shaft to install the problem of difficulty in order to avoid head bearing 14 and lower bearing 19 disalignment, bearing is chosen for self-aligning bearing, can carry out right alignment adjustment among a small circle.Utilize endless metal cushion block to be undertaken fastening by itself and lower bearing inner ring in rotating shaft 13 bottom, rotating shaft 13 upward-downward translation vertically when preventing model from bending, guarantee that the bending support rigidity that rotating shaft provides is not suffered a loss.
Spring leaf 20 is fixed on course reinforcing prop 11 by fastening bolt in conjunction with spring washer, is connected with test model by decoupling zero pin 16, supports rigidity for it provides to rotate; Its rigidity size regulates by the active section thickness of spring leaf 20, to meet model frequency requirement.
Rigidity reinforcement is carried out in the course that boxlike metab arranges the larger course reinforcing prop 11 pairs of metabs of width dimensions; The structure height of normal direction reinforcing prop 17 is high, and normal direction reinforcing prop 17 pairs of base normal direction that therefore design thickness is less carry out rigidity reinforcement; In addition, all components of base all adopt the metalwork that thickness, width dimensions are larger, and the closed cassette arrangement stiffness characteristics of formation is good, can provide enough back-up system frequencies.
To sum up, namely achieve the high Functional Design of model supports base model frequency by these rigidity Design measures, and the quick-replaceable of base device member designs parameter can be realized, guarantee to find parameter designing value fast in experimentation.This flutter wind tunnel test model boxlike supportive device has been succeeded application in Project R&D.
This utility model " flutter wind tunnel test model boxlike supportive device " achieves flutter test model root bending, reverses effective, the convenient simulation supporting rigidity, solve in the past that flutter model root back-up system model frequency is low, the technological difficulties that frequency requirement is supported in test cannot be met completely.By ground resonance test and wind tunnel test, demonstrating this design apparatus can provide complete dynamic aerofoil root bending to support rigidity with torsion well, and base clamp supports that frequency meets the requirement reaching model the highest pass frequency of heart 3 times, ensure that the success of test design.
Claims (3)
1. a flutter wind tunnel test model boxlike supportive device, is characterized in that: comprise the parts such as course reinforcing prop (11), head bearing cover plate (12), rotating shaft (13), head bearing (14), top chock (15), decoupling zero pin (16), normal direction reinforcing prop (17), lower bearing cover plate (18), lower bearing (19), spring leaf (20), base block (21) and pedestal (22); Course reinforcing prop (11), normal direction reinforcing prop (17), cushion block (21) and pedestal (22) form Integral box type metab;
Base block (21) is positioned at the bottommost of whole support base, and its upper surface contacts with pedestal (22), and the two is connected by the mode be spirally connected and weld; Pedestal (22) middle position perforate, as the bearing mounting base of lower bearing (19), bore edges opens screw hole, for lower bearing cover plate (18) is fixed on pedestal (22), to carry out the fixed constraint of vertical direction to lower bearing (19); Normal direction reinforcing prop (17) and course reinforcing prop (11) are arranged vertically, and provide by pedestal (22) and directly contact support, the two is symmetrically arranged in both sides relative to lower bearing (19) respectively; Normal direction reinforcing prop (17) and course reinforcing prop (11) upper ends top chock (15), adopt screw to be connected with normal direction reinforcing prop (17); Head bearing (14) is installed on top chock (15), it adopts head bearing cover plate (12) position constraint, ensure that outer race and top chock (15) fit tightly, and bearing inner ring freely can rotate; Rotating shaft (13) is fit into head bearing (14) and lower bearing (19) from top to bottom, and two bearings provide constraint support thus; Spring leaf (20) is bolted on course reinforcing prop (11), arranges one along course relative to each before and after lower bearing (19); Decoupling zero pin (16) is by self being threadedly connected to spring leaf (20) top.
2. flutter wind tunnel test model boxlike supportive device according to claim 1, is characterized in that: bearing (14,19) is self-aligning bearing.
3. flutter wind tunnel test model boxlike supportive device according to claim 1 and 2, is characterized in that: adopt clearance fit between bearing (14,19) and bearing seat (15).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201420815440.8U CN204314050U (en) | 2014-12-19 | 2014-12-19 | A kind of flutter wind tunnel test model boxlike supportive device |
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| CN201420815440.8U CN204314050U (en) | 2014-12-19 | 2014-12-19 | A kind of flutter wind tunnel test model boxlike supportive device |
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| CN204314050U true CN204314050U (en) | 2015-05-06 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890899A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Rotation flutter simulation device |
| CN107063624A (en) * | 2017-06-06 | 2017-08-18 | 大连理工大学 | A kind of device for simulating all movable rudder face flutter model bending support stiffness |
| CN107345847A (en) * | 2017-08-28 | 2017-11-14 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of entirely dynamic hinge elasticity support structure of aerofoil two of flutter wind tunnel model |
| CN110966330A (en) * | 2018-09-30 | 2020-04-07 | 上海微电子装备（集团）股份有限公司 | Combined reed, design method thereof and motion platform |
| CN112857719A (en) * | 2020-12-29 | 2021-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Fixed airfoil flutter ground test device and method |
| CN114235327A (en) * | 2021-12-24 | 2022-03-25 | 重庆大学 | Full triaxial aeroelastic test device of controllable degree of freedom |
-
2014
- 2014-12-19 CN CN201420815440.8U patent/CN204314050U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104890899A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Rotation flutter simulation device |
| CN107063624A (en) * | 2017-06-06 | 2017-08-18 | 大连理工大学 | A kind of device for simulating all movable rudder face flutter model bending support stiffness |
| CN107345847A (en) * | 2017-08-28 | 2017-11-14 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of entirely dynamic hinge elasticity support structure of aerofoil two of flutter wind tunnel model |
| CN110966330A (en) * | 2018-09-30 | 2020-04-07 | 上海微电子装备（集团）股份有限公司 | Combined reed, design method thereof and motion platform |
| CN112857719A (en) * | 2020-12-29 | 2021-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Fixed airfoil flutter ground test device and method |
| CN112857719B (en) * | 2020-12-29 | 2023-07-21 | 中国航空工业集团公司西安飞机设计研究所 | Fixed airfoil flutter ground test device and method |
| CN114235327A (en) * | 2021-12-24 | 2022-03-25 | 重庆大学 | Full triaxial aeroelastic test device of controllable degree of freedom |
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Address after: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee after: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute Address before: 610091 planning and Development Department of Chengdu aircraft design and Research Institute, 1610 Riyue Avenue, Qingyang District, Chengdu City, Sichuan Province Patentee before: AVIC CHENGDU AIRCRAFT DESIGN & Research Institute |