CN104122067A - Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model - Google Patents
Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model Download PDFInfo
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- CN104122067A CN104122067A CN201310145140.3A CN201310145140A CN104122067A CN 104122067 A CN104122067 A CN 104122067A CN 201310145140 A CN201310145140 A CN 201310145140A CN 104122067 A CN104122067 A CN 104122067A
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- wind tunnel
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Abstract
The invention belongs to the technical field of flutter model design and wind tunnel tests in the technical field of aviation, and in particular, relates to a mechanism capable of independent variation in bending and torsional stiffness in a flutter model wind tunnel test. The mechanism comprises a decoupling mandrel (1), rotating spring pieces (2), a rotating shaft (3), a rigid support (4), spring piece supports (5), a groove binaural connector (6) and a bearing support (7). The rotating shaft (3) is installed on the rigid support (4) via the bearing support (7). The upper end of the rotating shaft (3) is equipped with the groove binaural connector (6). A fork groove for installing an airfoil test piece is disposed on the groove binaural connector (6). Fork ears at two ends of the lower surface of the groove binaural connector (6) are connected to a first end of the decoupling mandrel (1). The spring piece supports (5) are further disposed on the front and rear faces of the rigid support (4) respectively. The rotating spring pieces (2) are installed respectively on the spring piece supports (5). The top ends of the rotating spring pieces (2) are connected to a second end of the decoupling mandrel (1).
Description
Technical field
The invention belongs in aeronautical technology field flutter model design and wind-tunnel technique field, particularly relate to a kind of can be in flutter model wind tunnel test the mechanism of independent variation bending and torsion rigidity.
Background technology
The complete moving aerofoil buffet characteristic content that comprises two aspects of analyzing and researching: 1) utilize dynamic finite element model to carry out analytical calculation; 2) utilize model wind tunnel test research experiment.
Utilize mathematics of finite element analytical model can in model, change independently bending and torsion rigidity, the impact on complete moving aerofoil buffet characteristic when studying these two design parameters and changing separately.
And at model in wind tunnel design aspect, the domestic air mail institutes in the past bending and torsion of designed complete moving its root control system of aerofoil flutter model supports that rigidity all intercouples, can not as analysis model for finite element, can change independently bending and torsion rigidity, impact on complete moving aerofoil buffet characteristic when studying these two design parameters and changing separately, can not effectively tell the rule that buffet characteristic changes with single parameter, on clarifying each design parameter, the impact of buffet characteristic be brought to very large difficulty.
Supported in order to solve in the past the bending and torsion of moving its root control system of aerofoil flutter model entirely that rigidity intercoupled, impact on complete moving aerofoil buffet characteristic can not study these two design parameters change separately in wind tunnel test time, the technological difficulties of buffet characteristic with the rule of single parameter variation can not be effectively told, a kind of new simulation mechanism need to be proposed.
Summary of the invention
Object of the present invention:
The non-coupled simulation of the flutter wind tunnel test model bending-torsional rigidity mechanism of Patent design of the present invention, utilize decoupling zero push rod tension and compression rigidity to be far longer than the feature of its bending stiffness, the bending stiffness that the rotation that coupling design spring leaf provides and rotating shaft provide, the target that realizes bending on flutter model and rotational stiffness decoupling zero, has solved preferably and has studied in test the technical method of buffet characteristic with single parameter Changing Pattern.
Technical scheme of the present invention:
The non-coupled simulation of flutter wind tunnel test model bending-torsional rigidity mechanism, comprise decoupling zero push rod 1, rotating missile reed 2, rotating shaft 3, rigid mount 4, spring leaf bearing 5, grooved ears joint 6 and bearing spider 7 form, on rigid mount 4, by bearing spider 7, rotating shaft 3 is housed, grooved ears joint 6 is equipped with in the upper end of rotating shaft 3, the fork pockets that has installation aerofoil testpieces above of grooved ears joint 6, below grooved ears joint 6, the fork ear at two ends is connected with the first end of decoupling zero push rod 1, on rigid mount 4 front-backs, also respectively there is a spring leaf bearing 5, rotating missile reed 2 is respectively installed on spring leaf bearing 5, rotating missile reed 2 tops are connected with decoupling zero push rod 1 second end.
Described decoupling zero push rod 1 diameter is
and be less than 1/10th of rotating shaft 3 diameters.
Technique effect of the present invention:
This invention realized flutter wind tunnel test model bending with torsional rigidity decoupling zero, solved that the bent/twisted rigidity existing in flutter model design in the past and wind tunnel test intercouples, buffet characteristic is with the unclear difficult point of sensitive parameter variation identification.By ground resonance test and wind tunnel test, verify that this design organization can realize the decoupling zero of bent/twisted rigidity well, reach directly and analyzed the object of responsive rigidity to airplane flutter properties influence by results of wind tunnel.
This designs invention advanced technology, the simple and direct practicality of test method, has not only reduced significantly the workload of modelling and correlation computations, has also reduced model and has produced and wind tunnel test cost, has saved research fund, has higher model practical value.
Brief description of the drawings
Fig. 1 bending-rotational stiffness decoupling mechanism axonometric drawing;
Fig. 2 bending-rotational stiffness decoupling mechanism side view;
Wherein, 1-decoupling zero push rod; 2-rotating missile reed; 3-rotating shaft; 4-rigid mount; 5-spring leaf bearing; 6-grooved ears joint; 7-bearing.
Embodiment
The non-coupled simulation of flutter wind tunnel test model bending-torsional rigidity mechanism, comprise decoupling zero push rod 1, rotating missile reed 2, rotating shaft 3, rigid mount 4, spring leaf bearing 5, grooved ears joint 6 and bearing spider 7 form, on rigid mount 4, by bearing spider 7, rotating shaft 3 is housed, grooved ears joint 6 is equipped with in the upper end of rotating shaft 3, the fork pockets that has installation aerofoil testpieces above of grooved ears joint 6, below grooved ears joint 6, the fork ear at two ends is connected with the first end of decoupling zero push rod 1, on rigid mount 4 front-backs, also respectively there is a spring leaf bearing 5, rotating missile reed 2 is respectively installed on spring leaf bearing 5, rotating missile reed 2 tops are connected with decoupling zero push rod 1 second end.
Described decoupling zero push rod 1 diameter is
and be less than 1/10th of rotating shaft 3 diameters.
Described decoupling zero push rod 1 is spring steel.
This mechanism principle is as follows: select two decoupling zero push rods that diameter is thinner, connect two rotating missile reeds and rotating shaft grooved ears joint.In decoupling zero push rod axis and shaft bearing, face is positioned in same plane.Decoupling zero push rod is designed to elongate rod, selects suitable decoupling zero push rod slenderness ratio by computational analysis, make its bending stiffness be far smaller than tension and compression rigidity and again can not unstability in the time of band movable model tension and compression rotating missile reed.In addition the bending stiffness of decoupling zero push rod is more than low more of the bending stiffness of rotating shaft, and in the time of shaft bending, the bending stiffness that decoupling zero push rod provides can be ignored completely like this, and model bending stiffness is only provided by rotating shaft.In the time that rotating shaft is rotated, model drives two spring leafs of two decoupling zero push rods difference tension and compression to produce rotational stiffness around the shaft, and rotating shaft does not provide rotational stiffness.So just realized the non-coupling of flutter wind tunnel test model bending-torsional rigidity, research single parameter changes separately the function on complete moving aerofoil buffet characteristic impact.
Claims (3)
1. the non-coupled simulation of flutter wind tunnel test model bending-torsional rigidity mechanism, it is characterized in that, this mechanism comprises decoupling zero push rod (1), rotating missile reed (2), rotating shaft (3), rigid mount (4), spring leaf bearing (5), grooved ears joint (6) and bearing spider (7) composition, rigid mount (4) is upper is equipped with rotating shaft (3) by bearing spider (7), grooved ears joint (6) is equipped with in the upper end of rotating shaft (3), the fork pockets that has installation aerofoil testpieces above of grooved ears joint (6), below grooved ears joint (6), the fork ear at two ends is connected with the first end of decoupling zero push rod (1), on rigid mount (4) front-back, also respectively there is a spring leaf bearing (5), rotating missile reed (2) is respectively installed on spring leaf bearing (5), rotating missile reed (2) top is connected with decoupling zero push rod (1) second end.
2. the non-coupled simulation of flutter wind tunnel test model bending-torsional rigidity as claimed in claim 1 mechanism, is characterized in that, described decoupling zero push rod (1) diameter is
and be less than 1/10th of rotating shaft (3) diameter.
3. the non-coupled simulation of flutter wind tunnel test model bending-torsional rigidity as claimed in claim 1 or 2 mechanism, is characterized in that, described decoupling zero push rod (1) is spring steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310145140.3A CN104122067A (en) | 2013-04-24 | 2013-04-24 | Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model |
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| CN201310145140.3A CN104122067A (en) | 2013-04-24 | 2013-04-24 | Bending-torsional stiffness uncoupled simulation mechanism for flutter wind tunnel test model |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104792490A (en) * | 2015-04-21 | 2015-07-22 | 中国航空工业集团公司沈阳飞机设计研究所 | External store side-sway frequency and yaw frequency decoupling device of wind tunnel flutter model |
| CN104897355A (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 | Folded wing non-linear flutter test 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 |
| CN109115455A (en) * | 2018-10-17 | 2019-01-01 | 江西洪都航空工业集团有限责任公司 | All movable rudder face flutter model bending stiffness and the independent of rotational stiffness become ginseng device |
| CN109297668A (en) * | 2018-10-30 | 2019-02-01 | 中国航天空气动力技术研究院 | A kind of rudder face gap wind-tunnel experiment simulator |
| CN109372886A (en) * | 2018-11-06 | 2019-02-22 | 中国航天空气动力技术研究院 | A kind of hinged fixed structure of rotary shaft model and rotating shaft support method |
| CN109506878A (en) * | 2018-10-29 | 2019-03-22 | 中国航天空气动力技术研究院 | A kind of multiple-degree-of-freedom mechanism |
| CN110631801A (en) * | 2019-09-18 | 2019-12-31 | 西安交通大学 | Bending-torsion rigidity decoupling flutter wind tunnel test device |
| CN114674547A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104792490A (en) * | 2015-04-21 | 2015-07-22 | 中国航空工业集团公司沈阳飞机设计研究所 | External store side-sway frequency and yaw frequency decoupling device of wind tunnel flutter model |
| CN104792490B (en) * | 2015-04-21 | 2018-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of wind-tunnel flutter model store Combinations side-sway frequency and yaw frequency decoupling device |
| CN104897355A (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 | Folded wing non-linear flutter test device |
| CN104897355B (en) * | 2015-06-23 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Folded wing non-linear flutter test 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 |
| CN109115455A (en) * | 2018-10-17 | 2019-01-01 | 江西洪都航空工业集团有限责任公司 | All movable rudder face flutter model bending stiffness and the independent of rotational stiffness become ginseng device |
| CN109506878A (en) * | 2018-10-29 | 2019-03-22 | 中国航天空气动力技术研究院 | A kind of multiple-degree-of-freedom mechanism |
| CN109506878B (en) * | 2018-10-29 | 2021-02-09 | 中国航天空气动力技术研究院 | Multi-degree-of-freedom mechanism |
| CN109297668A (en) * | 2018-10-30 | 2019-02-01 | 中国航天空气动力技术研究院 | A kind of rudder face gap wind-tunnel experiment simulator |
| CN109372886A (en) * | 2018-11-06 | 2019-02-22 | 中国航天空气动力技术研究院 | A kind of hinged fixed structure of rotary shaft model and rotating shaft support method |
| CN109372886B (en) * | 2018-11-06 | 2020-12-18 | 中国航天空气动力技术研究院 | Rotating shaft type model hinging and fixing structure and rotating shaft supporting method |
| CN110631801A (en) * | 2019-09-18 | 2019-12-31 | 西安交通大学 | Bending-torsion rigidity decoupling flutter wind tunnel test device |
| CN114674547A (en) * | 2022-05-30 | 2022-06-28 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
| CN114674547B (en) * | 2022-05-30 | 2022-08-05 | 中国飞机强度研究所 | Boundary rigidity simulation system in full-motion vertical fin buffeting test of airplane strength test |
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Application publication date: 20141029 |